Research Article Dynamics and Control of a Flexible Solar...
Transcript of Research Article Dynamics and Control of a Flexible Solar...
Research ArticleDynamics and Control of a Flexible Solar Sail
Jiafu Liu1 Siyuan Rong2 Fan Shen2 and Naigang Cui2
1 Department of Aerospace Engineering Shenyang Aerospace University Shenyang 110136 China2Department of Aerospace Engineering Harbin Institute of Technology Harbin 150001 China
Correspondence should be addressed to Jiafu Liu liujiafuericking163com
Received 15 July 2014 Accepted 20 October 2014 Published 30 November 2014
Academic Editor Sebastian Anita
Copyright copy 2014 Jiafu Liu et alThis is an open access article distributed under the Creative Commons Attribution License whichpermits unrestricted use distribution and reproduction in any medium provided the original work is properly cited
Solar sail can merely make use of solar radiation pressure (SRP) force as the thrust for space missions The attitude dynamics isobtained for the highly flexible solar sail with control vanes sliding masses and a gimbaled control boomThe vibration equationsare derived considering the geometric nonlinearity of the sail structure subjected to the forces generated by the control vanessolar radiation pressure (SRP) and sliding masses Then the dynamic models for attitudevibration controller design and dynamicsimulation are obtained respectively The linear quadratic regulator (LQR) based and optimal proportional-integral (PI) basedcontrollers are designed for the coupled attitudevibration models with constant disturbance torques caused by the center-of-mass(cm)center-of-pressure (cp) offset respectively It can be concluded from the theoretical analysis and simulation results that theoptimal PI based controller performs better than the LQR based controller from the view of eliminating the steady-state errorsTheresponses with and without the geometrical nonlinearity are performed and the differences are observed and analyzed And somesuggestions are also presented
1 Introduction
Solar sail is a novel spacecraft with the unique propulsionstyle and has a great application potential in the near futureThe continuous thrust can be obtained using the huge andhighly flexible membrane to reflect solar photons thus themuch longer mission duration is possible by solar sail [1]It is reported that lots of basic scientific questions involvingthe impact cosmic rays have on the long-term conditions ofthe earth environment and on earth itself can be answeredby in situ exploration of the heliopause and the heliosphericinterface by solar sailing [2] This mission can hardly beaccomplished by spacecraft with chemical fuels such as thetwo Voyager spacecraft launched in the 1970s The spacemissions such as deorbiting [3] pole sitter [4] heliostormwarning [5] and many novel orbits [6ndash8] can be accom-plished by solar sail much more suitable than the traditionalspacecraft The IKAROS [9] and NanoSail-D [10] solar sailspacecraft have been launched into space and several basictheories concerning solar sail have been demonstrated andseveral space missions have been accomplished
One of the critical problems with respect to success orfailure for an orbiting solar sail is the attitude dynamics
and control problem The attitude control system (ACS) isproposed by Wie and Murphy consisting of a propellantlessprimary ACS and a microthruster-based secondary ACS [11]The sliding masses and roll stabilizer bars are used for yawand pitch and roll control respectively in the former ACSThe lightweight pulsed plasma thruster (PPT) is used forattitude recovery from off-nominal conditions in the latterone In addition the robust attitude controller is developed byemploying the attitude control actuators abovementioned [1213]Themodal data can be obtained for solar sail with attitudecontrol actuators as in [14] by using the finite elementmethodwith high fidelity The attitude controller considering thevibration of solar sail structure can be designed based on themodal coordinate state-space system and the effectivenessof the controller is verified The passive attitude stabilizationmethod (to spin solar sail) is proposed in the presence ofa cmcp offset in [15 16] The attitude control methodsare proposed and the simulations are carried out using thecontrol boom control vanes and sail shifting and tilting[17 18] in the presence of cmcp offset
The attitude dynamics are derived by employing thesliding masses and roll stabilizer bars (RSB) for attitude
Hindawi Publishing CorporationMathematical Problems in EngineeringVolume 2014 Article ID 868419 25 pageshttpdxdoiorg1011552014868419
2 Mathematical Problems in Engineering
control actuators The validity of the ACS is demonstratedby numerical simulations [19] A high performance solar sailattitude controller is presented by employing sliding massesinside the supporting beams and its ability of performingtime efficient reorientation maneuvers is demonstrated [20]The proposed controller combines a feedforward and a feed-back controller the former is a fast response controller whilethe latter can be used to respond to unpredicted disturbances[21] The solar sail ACS presented in [22] includes themovement of the small control mass in the solar sail planeand the rotation of ballast with two masses at the extremitiesto realize the pitchyaw and roll control respectively
The robust attitude controllers are designed using 119867infinQFT and input shaping methods respectively to allow forthe uncertainties of inertia natural frequencies dampingand modal constants of solar sail The performances ofthe controllers are analyzed using the linear and nonlineardynamics respectively [23]The reduced dynamic model of aflexible solar sail with foreshortening deformation couplingwith its attitude and vibration is derived in [24ndash26] TheBang-Bang control scheme combining input shapingmethodis used to eliminate the vibration for a time optimal attitudemaneuver The attitude control system is proposed usingsmall reactionwheels andmagnetic torquers for a solar sail onlow earth orbit and the validity is demonstrated by numericalsimulation [27]
The dynamic model of the multibody solar sail withcontrol boom and reaction wheel is derived in [28 29] Thecontrollability and stability are analyzed and the proposedattitude control scheme is demonstrated The effectiveness ofthe solar sail attitude control system employing four controlvanes is demonstrated by simulating deep space explorationmissions [30]The dynamics is derived and the controllabilityand stability are analyzed for solar sail with control boomreaction wheel and control vanes The effectiveness of theproposed ACS is demonstrated for the solar sail with cmcpoffset [31]
The trajectory tracking control is accomplished by usingsolar sail with four control vanes to control the solar angleof the sail The resultant sailcraft thrust vector amplitudecan be controlled by the additional degree of freedom ofthe control vanes [32] A robust nonlinear attitude controlalgorithm is developed for solar sail with four control vaneswith single degree-of-freedom rejecting disturbances by cmand cp offset The control allocation is studied by usingnonlinear programming [33]
The novel and practical ACS for solar sail is continuouslyproposed A bus-basedACS is presented in [34] including thehighly reflective panel actuator for roll control located at thefree end of the bus-based boom and the tether control massactuator for yawpitch control running along the bus-basedboomThis scalableACS can decrease the risk and complexityinvolved in the design of the sail deployment subsystem TheACS designed for IKAROS is muchmore novel and practicalThe ACS utilizes the reflectivity control device (RCD) torealize the yawpitch control for the spinning solar power sailIt is a fuel-free and oscillation-free ACS [35] But this ACSwill fail to generate the required torques when it is edge tothe sun (the sun angle approaches 90∘) And recently a novel
attitude control method is proposed in [36] The requiredtorque can be generated by adjusting the position of a wingtip along the boomThismethod presents an effective attitudeapproach for large sailcraft But the exact shape of the films isdifficult to determine
The dynamic modeling and control for the flexible sail-craft are studied in [37 38] In [37] the vibration equationsfor the axial and transverse deformations are establishedby considering the geometrical nonlinearity of the sailcraftBut merely the vibration analysis is insufficient for theorbiting sailcraft experiencing attitude motion The coupledattitudevibration analysis is required In [38] the coupledattitudevibration dynamics is established and the solvingprocess is also presented The controller is designed by usingthe Bang-Bang based PD theory The effectiveness of thecontroller is verified by numerical simulation But the largedeformation of the structure is not considered
The coupled attitude-orbit dynamics of a solar sail isstudied in [39]The equilibrium point of the dynamics can beobtained by designing the inertia of the sail and the stabilityof the equilibrium point is analyzed through a linearization
The attitude dynamics and control are studied thoroughlyin above references The ACS for solar sail by using actu-ators such as control boom and control vanes or by usingmeans such as spinning and translatingtilting sail panels arestudied Little research concerns attitude dynamic modelingwith highly flexible structure and vibration modeling withgeometrical nonlinearity and the attitudevibration controlBut this is a problem worth studying
This paper establishes the attitude dynamics for the largeflexible solar sail with control vanes control boom and slid-ing masses And the vibration equations are also presentedThe LQR and optimal PI based controllers are designed forthe attitudevibration dynamics By theoretical analysis andsimulation the controller with better performance is selectedand some discussions are presented And the differencesbetween the dynamics models with and without the geomet-rical nonlinearity are also inserted and analyzed
2 Attitude Dynamics
In this section the configuration and structure of the sailcraftare presented The related reference frames and coordinatetransformations are given The kinetic and gravitationalpotential energies and the generalized loads are obtainedTheLagrange equation method is adopted to derive the attitudedynamics with control vanes control boom and slidingmasses The attitude dynamics is an important part of thecoupled attitudevibration dynamics
21 The Configuration and Structure The configuration andstructure of the infinite-point connected square solar sailadopted in this paper are shown in Figure 1The ACS consistsof the control boom sliding masses and control vanes Thefour supporting beams are the most rigid component Thestiffness of the four triangular membranes can be neglectedby comparing with the supporting beams thus the kinetic
Mathematical Problems in Engineering 3
Controlvanes
Payload
Slidingmasses
Controlboom
Figure 1 The configuration and structure of solar sail
energy caused by vibrations and elastic potential energy ofthe membrane structure can be neglected
The paper mainly focuses on the dynamics for highlyflexible solar sail The following assumptions are made tosimplify the problems
(1) The detailed vibration of the membrane is neglectedin this paper as most of the kinetic energy causedby vibrations is by the vibrations of the supportingbeams
(2) The masses of control vanes and control boom areneglected We regard the control vanes and controlboom as rigid bodies
(3) The deformation of the structure is not affected by thethermal loads and the wrinkle effect is also neglected
(4) The torque by the cmcp offset is the disturbancetorque And other disturbance torques (such as grav-ity gradient torque) are neglected
22 The Reference Frames and Coordinate Transformations
The Inertial Reference Frame (E119868X119868Y119868Z119868120587
119868) It is an inertial
reference frame for solar sail attitude and orbital motionE119868X119868is in the vernal equinox direction E
119868Z119868is in the Earthrsquos
rotation axis perpendicular to equatorial plane E119868Y119868is in the
equatorial plane and finishes the ldquotriadrdquo of unit vectors Theunit vector is e
119868= (i
119868 j119868 k
119868)119879
The body reference frames of solar sail (O119874x119887y119887z119887120587
119887)
and control vanes (C119894x119894y119894z119894120587
119894 119894 = 1 2 3 4) O
119874is the geo-
metric center of the film O119874x119887is perpendicular to the film
pointing to the payload sideO119874y119887andO
119874z119887are in the plane
of the sail C119894is the geometric center of the 119894th control vane
When there exist no relative motions between solar sail andcontrol vanes120587
119894is coincident with120587
119887The related frames can
be found in Figure 2The attitude motion is described in Euler angles using
the yaw-roll-pitch notation In this notation a three-elementvector Θ = [120595 120593 120579]
119879 is used to describe the attitude of solarsail with respect to the inertial frame The transformation
EI
ZI
YI
XI
yb
zb
1
2
C2
C1
x2
z2
z1
y1
x1
y2 OO
xb
12
3
3
44
C4
C3
x3
y3z3
z4
y4x4
Figure 2 120587119868
120587119887
and 120587119894
Sun line
EI
OO
rO
ZI
XI
YI
ZI z998400
120595
120595
XI
EI(O)
Z998400998400998400(zb)
Z998400998400120593
120593
120579
120579
x998400x998400998400 x998400998400998400(xb)
y998400998400 y998400998400998400(yb)y998400
YI
The orbit
Figure 3 The orbit and the attitude motion
from 120587119868to 120587
119887can be realized by a 3-1-2 rotation as shown
in Figure 3 (right) with the following rotation matrix
C119887119868
= R2(120579)R
1(120593)R
3(120595)
= [
[
119888120579119888120595 minus 119904120579119904120593119904120595 119888120579119904120595 + 119904120579119904120593119888120595 minus119904120579119888120593
minus119888120593119904120595 119888120593119888120595 119904120593
119904120579119888120595 + 119888120579119904120593119904120595 119904120579119904120595 minus 119888120579119904120593119888120595 119888120579119888120593
]
]
(1)
where
R3(120595) = [
[
cos120595 sin120595 0
minus sin120595 cos120595 0
0 0 1
]
]
R1(120593) = [
[
1 0 0
0 cos120593 sin120593
0 minus sin120593 cos120593]
]
R2(120579) = [
[
cos 120579 0 minus sin 120579
0 1 0
sin 120579 0 cos 120579]
]
(2)
120595 120593 and 120579 are yaw roll and pitch angles respectively 119888120579 and119904120579 are short for cos 120579 and sin 120579
And the transformation from 120587119894to 120587
119887can be obtained as
119862119887119894= [
[
119888120579119894119888120595
119894minus 119904120579
119894119904120593
119894119904120595
119894119888120579
119894119904120595
119894+ 119904120579
119894119904120593
119894119888120595
119894minus119904120579
119894119888120593
119894
minus119888120593119894119904120595
119894119888120593
119894119888120595
119894119904120593
119894
119904120579119894119888120595
119894+ 119888120579
119894119904120593
119894119904120595
119894119904120579
119894119904120595
119894minus 119888120579
119894119904120593
119894119888120595
119894119888120579
119894119888120593
119894
]
]
(3)
The attitude control can be performed by varying 120595119894 120593
119894 and
120579119894
4 Mathematical Problems in Engineering
OO
xb mp
14
1205821
zbyb
dm32
3
1205822
EI
p
ch1
h2
31205883
O m3
r
r r
rr
R R
Figure 4 The positions and orientations of the components
23 The Positions and Velocities of the Components Theabsolute position of an arbitrary point on the supportingbeams sliding masses and payload are given in Figure 4where r
119888119894(119894 = 1 2 3 4) is the position vector of the cp of
the 119894th control vane The cp of each control vane is assumed
to locate at the free end of the supporting beams r119901is the
position vector of the payload O119874is the origin of 120587
119887 The
positions and velocities of an arbitrary point on each supportbeam can be obtained as
R119898119894
= R119874+ r
119894+ 120588
119894 k
119898119894= R
119874+∘
120588119894
+ 120596 times (r119894+ 120588
119894) (4)
whereR119898119894(v
119898119894) is the position (velocity) vector of an arbitrary
point on the deformed supporting beam and r119894is the position
vector of an arbitrary point on the undeformed beam relativetoO
119874R
119874(R
119874= v
119874) is the orbital position and velocity of the
sailcraft 120588119894is the transverse deformation of an arbitrary point
on the supporting beam (sdot) is the first time derivatives withrespect to 120587
119868and (∘) is the first time derivatives with respect
to 120587119887 120596 is the angular velocity of solar sail expressed as
[
[
120596119909
120596119910
120596119911
]
]119887
= [
[
cos 120579 minus sin 120579 cos120593120579 + sin120593
sin 120579 + cos 120579 cos120593]
]
(5)
If the orbital motion and its influence on attitude motionare neglected we have
R1198983
= r3+120588
3= [120588
3119909 120588
3119910 119911
3]119879
R1198981
= r1+ 120588
1= [120588
1119909 120588
1119910 119911
1]119879
R1198982
= r2+ 120588
2= [120588
2119909 119910
2 120588
2119911]119879
R1198984
= r4+ 120588
4= [120588
4119909 119910
4 120588
4119911]119879
(6)
R1198983
=∘
1205883
+ 120596 times (r3+ 120588
3) =
[[
[
1205883119909
1205883119910
0
]]
]
+[[
[
cos 120579 minus sin 120579 cos120593120579 + sin120593
sin 120579 + cos 120579 cos120593
]]
]
times [
[
1205883119909
1205883119910
1199113
]
]
=
[[[
[
1205883119909
+ 1199113
120579 + 1199113 sin120593 minus 120588
3119910 sin 120579 minus 120588
3119910 cos 120579 cos120593
1205883119910
+ 1205883119909 sin 120579 + 120588
3119909 cos 120579 cos120593 minus 119911
3 cos 120579 + 119911
3 sin 120579 cos120593
1205883119910 cos 120579 minus 120588
3119910 sin 120579 cos120593 minus 120588
3119909
120579 minus 1205883119909 sin120593
]]]
]
(7)
R1198981
=∘
1205881
+ 120596 times (r1+ 120588
1) =
[[
[
1205881119909
1205881119910
0
]]
]
+[[
[
cos 120579 minus sin 120579 cos120593120579 + sin120593
sin 120579 + cos 120579 cos120593
]]
]
times [
[
1205881119909
1205881119910
1199111
]
]
=
[[[
[
1205881119909
+ 1199111
120579 + 1199111 sin120593 minus 120588
1119910 sin 120579 minus 120588
1119910 cos 120579 cos120593
1205881119910
+ 1205881119909 sin 120579 + 120588
1119909 cos 120579 cos120593 minus 119911
1 cos 120579 + 119911
1 sin 120579 cos120593
1205881119910 cos 120579 minus 120588
1119910 sin 120579 cos120593 minus 120588
1119909
120579 minus 1205881119909 sin120593
]]]
]
(8)
R1198982
=∘
1205882
+ 120596 times (r2+ 120588
2) =
[[
[
1205882119909
0
1205882119911
]]
]
+[[
[
cos 120579 minus sin 120579 cos120593120579 + sin120593
sin 120579 + cos 120579 cos120593
]]
]
times [
[
1205882119909
1199102
1205882119911
]
]
=[[
[
1205882119909
+ 1205882119911
120579 + 1205882119911 sin120593 minus 119910
2 sin 120579 minus 119910
2 cos 120579 cos120593
1205882119909 sin 120579 + 120588
2119909 cos 120579 cos120593 minus 120588
2119911 cos 120579 + 120588
2119911 sin 120579 cos120593
1205882119911
+ 1199102 cos 120579 minus 119910
2 sin 120579 cos120593 minus 120588
2119909
120579 minus 1205882119909 sin120593
]]
]
(9)
Mathematical Problems in Engineering 5
R1198984
=∘
1205884
+ 120596 times (r4+ 120588
4) = [
[
1205884119909
0
1205884119911
]
]
+[[
[
cos 120579 minus sin 120579 cos120593120579 + sin120593
sin 120579 + cos 120579 cos120593
]]
]
times [
[
1205884119909
1199104
1205884119911
]
]
=[[
[
1205884119909
+ 1205884119911
120579 + 1205884119911 sin120593 minus 119910
4 sin 120579 minus 119910
4 cos 120579 cos120593
1205884119909 sin 120579 + 120588
4119909 cos 120579 cos120593 minus 120588
4119911 cos 120579 + 120588
4119911 sin 120579 cos120593
1205884119911
+ 1199104 cos 120579 minus 119910
4 sin 120579 cos120593 minus 120588
4119909
120579 minus 1205884119909 sin120593
]]
]
(10)
The components of the position and velocity vectors of anarbitrary point on the supporting beam can be computed byusing the above five equations
In Figure 4 1205821and 120582
2are the boom tilt and azimuth
angles relative to the sailcraft body axes respectively Thecomponents of r
119901can be expressed as follows by using these
two angles
r119901=10038161003816100381610038161003816r119901
10038161003816100381610038161003816cos 120582
1i119887+10038161003816100381610038161003816r119901
10038161003816100381610038161003816sin 120582
1cos 120582
2j119887+10038161003816100381610038161003816r119901
10038161003816100381610038161003816sin 120582
1sin 120582
2k119887
(11)
The position and velocity vectors of the payload can beobtained as
R119874119901
= R119874+ r
119901 k
119874119901= k
119874+ r
119901 (12)
where r119901=∘r119901+ 120596 times r
119901 And ∘r
119901can be expressed as
∘r119901= minus
10038161003816100381610038161003816r119901
100381610038161003816100381610038161sin 120582
1i119887+10038161003816100381610038161003816r119901
10038161003816100381610038161003816
times (1cos 120582
1cos 120582
2minus
2sin 120582
1sin 120582
2) j
119887
+10038161003816100381610038161003816r119901
10038161003816100381610038161003816(
1cos 120582
1sin 120582
2+
2sin 120582
1cos 120582
2) k
119887
(13)
Thus r119901can be obtained as
r119901= [[minus119897
1199011sin 120582
1+ 119897
119901sin 120582
1sin 120582
2( 120579 + sin120593)
minus 119897119901sin 120582
1cos 120582
2( sin 120579 + cos 120579 cos120593)]
times [119897119901(
1cos 120582
1cos 120582
2minus
2sin 120582
1sin 120582
2)
+ 119897119901cos 120582
1( sin 120579 + cos 120579 cos120593)
minus 119897119901sin 120582
1sin 120582
2( cos 120579 minus sin 120579 cos120593)]
times 119897119901(
1cos 120582
1sin 120582
2+
2sin 120582
1cos 120582
2)
+ 119897119901sin 120582
1cos 120582
2( cos 120579 minus sin 120579 cos120593)
minus 119897119901cos 120582
1( 120579 + sin120593)]
(14)
The position vectors of the two sliding masses can beobtained as
Rℎ119895
= R119874+ r
ℎ119895+ 120588
ℎ119895
kℎ2
= k119874+∘rℎ119895
+∘
120588ℎ119895
+ 120596 times (rℎ119895
+ 120588ℎ119895)
(119895 = 1 2)
(15)
If the orbital motion and its influence on attitude motioncan be neglected then the position and velocity vectors canbe obtained as follows
Rℎ2
= rℎ2
+ 120588ℎ2
= [120588ℎ2119909
120588ℎ2119910
119911ℎ2]119879
Rℎ1
= rℎ1
+ 120588ℎ1
= [120588ℎ1119909
119910ℎ1 120588
ℎ1119911]119879
Rℎ2
=[[
[
120588ℎ2119909
+ 119911ℎ2
( 120579 + sin120593) minus 120588ℎ2119910
( sin 120579 + cos 120579 cos120593)120588ℎ2119910
+ 120588ℎ2119909
( sin 120579 + cos 120579 cos120593) minus 119911ℎ2
( cos 120579 minus sin 120579 cos120593)ℎ2
+ 120588ℎ2119910
( cos 120579 minus sin 120579 cos120593) minus 120588ℎ2119909
( 120579 + sin120593)
]]
]
Rℎ1
=[[
[
120588ℎ1119909
+ 120588ℎ1119911
( 120579 + sin120593) minus 119910ℎ1
( sin 120579 + cos 120579 cos120593)119910ℎ1
+ 120588ℎ1119909
( sin 120579 + cos 120579 cos120593) minus 120588ℎ1119911
( cos 120579 minus sin 120579 cos120593)120588ℎ1119911
+ 119910ℎ1
( cos 120579 minus sin 120579 cos120593) minus 120588ℎ1119909
( 120579 + sin120593)
]]
]
(16)
6 Mathematical Problems in Engineering
24 The Kinetic Energy The kinetic energy of the sail systemcan be obtained by neglecting the orbital motion and itsinfluence on attitude motion Consider
1198791198983
=1
2119898
119897int
119897
0
[∘
1205883
+ 120596 times (r3+ 120588
3)] sdot [
∘
1205883
+ 120596 times (r3+ 120588
3)] 119889119911
1198791198981
=1
2119898
119897int
0
minus119897
[∘
1205881
+ 120596 times (r1+ 120588
1)]
sdot [∘
1205881
+ 120596 times (r1+ 120588
1)] 119889119911
1198791198982
=1
2119898
119897int
119897
0
[∘
1205882
+ 120596 times (r2+ 120588
2)] sdot [
∘
1205882
+ 120596 times (r2+ 120588
2)] 119889119910
1198791198984
=1
2119898
119897int
0
minus119897
[∘
1205884
+ 120596 times (r4+ 120588
4)] sdot [
∘
1205884
+ 120596 times (r4+ 120588
4)] 119889119910
(17)
The above equations can be rewritten as
119879119898
=1
2120596 sdot J sdot 120596
+1
2119898
119897int
119897
0
2∘
1205883
sdot (120596 times r3) + (120596 times 120588
3) sdot (120596 times 120588
3)
+ 2 (120596 times r3) sdot (120596 times 120588
3) 119889119911
+1
2119898
119897int
0
minus119897
2∘
1205881
sdot (120596 times r1) + (120596 times 120588
1) sdot (120596 times 120588
1)
+ 2 (120596 times r1) sdot (120596 times 120588
1) 119889119911
+1
2119898
119897int
119897
0
2∘
1205882
sdot (120596 times r2) + (120596 times 120588
2) sdot (120596 times 120588
2)
+ 2 (120596 times r2) sdot (120596 times 120588
2) 119889119910
+1
2119898
119897int
0
minus119897
2∘
1205884
sdot (120596 times r4) + (120596 times 120588
4) sdot (120596 times 120588
4)
+ 2 (120596 times r4) sdot (120596 times 120588
4) + (120596 times r
4)
sdot (120596 times r4) 119889119910
(18)
where J = sum4
119895=1
J119898119895
is the moment of inertia of sail systemJ119898119895
(119895 = 1ndash4) is the moment of inertia of the 119895th sail sys-tem and the expression of J can be expressed as J = diag[119869
119909
119869119910 119869
119911] inO
119874x119887y119887z119887
The kinetic energy of the payload is
119879119901=
1
2119898
119901
10038161003816100381610038161003816r119901
10038161003816100381610038161003816
2
=1
2119898
119901[minus119897
1199011sin 120582
1+ 119897
119901sin 120582
1sin 120582
2( 120579 + sin120593)
minus 119897119901sin 120582
1cos 120582
2( sin 120579 + cos 120579 cos120593)]
2
+1
2119898
119901[119897119901(
1cos 120582
1cos 120582
2minus
2sin 120582
1sin 120582
2)
+ 119897119901cos 120582
1( sin 120579 + cos 120579 cos120593)
minus 119897119901sin 120582
1cos 120582
2( cos 120579 minus sin 120579 cos120593)]
2
+1
2119898
119901[119897119901(
1cos 120582
1sin 120582
2+
2sin 120582
1cos 120582
2)
+ 119897119901sin 120582
1cos 120582
2( cos 120579 minus sin 120579 cos120593)
minus 119897119901cos 120582
1( 120579 + sin120593)]
2
(19)
The kinetic energy of the sliding masses can be obtainedas follows by neglecting the orbital motion and its influenceon attitude control
119879ℎ1
=1
2119898
ℎ1[ ( 120588
ℎ1119909+ 120579120588
ℎ1119911+ 120588
ℎ1119911sin120593
minus 119910ℎ1sin 120579 minus 119910
ℎ1cos 120579 cos120593)
2
]
+1
2119898
ℎ1[( 119910
ℎ1+ 120588
ℎ1119909sin 120579 + 120588
ℎ1119909cos 120579 cos120593
minus 120588ℎ1119911
cos 120579 + 120588ℎ1119911
sin 120579 cos120593)2]
+1
2119898
ℎ1[( 120588
ℎ1119911+ 119910
ℎ1cos 120579 minus 119910
ℎ1sin 120579 cos120593
minus 120579120588ℎ1119909
+ 120588ℎ1119909
sin120593)2
]
119879ℎ2
=1
2119898
ℎ2[( 120588
ℎ2119909+ 120579119911
ℎ2+ 119911
ℎ2sin120593 minus 120588
ℎ2119910sin 120579
minus 120588ℎ2119910
cos 120579 cos120593)2
]
+1
2119898
ℎ2[( 120588
ℎ2119910+ 120588
ℎ2119909sin 120579 + 120588
ℎ2119909cos 120579 cos120593
minus 119911ℎ2cos 120579 + 119911
ℎ2sin 120579 cos120593)
2
]
+1
2119898
ℎ2[(
ℎ2+ 120588
ℎ2119910cos 120579 minus 120588
ℎ2119910sin 120579 cos120593
minus 120579120588ℎ2119909
minus 120588ℎ2119909
sin120593)2
]
(20)
25 The Gravitational Potential Energy The gravitationalpotential energies of the sail system 119880
119892119891 payload 119880
119892119901 and
sliding masses 119880119892ℎ1
119880119892ℎ2
can be obtained as
119880119892119891
= minus
120583119898119891
1003816100381610038161003816R119874
1003816100381610038161003816
119880119892119901
= minus
120583119898119901
10038161003816100381610038161003816R119874+ r
119901
10038161003816100381610038161003816
119880119892ℎ1
= minus120583119898
ℎ1
1003816100381610038161003816R119874+ r
ℎ1
1003816100381610038161003816
119880119892ℎ2
= minus120583119898
ℎ2
1003816100381610038161003816R119874+ r
ℎ2
1003816100381610038161003816
(21)
Mathematical Problems in Engineering 7
26 The Generalized Forces The components of the sunlightunit vector S can be obtained as follows by referring toFigure 3 (left) in 120587
119868
S = j119868= [1 0 0]
119879
119868
(22)
Based on the abovementioned equations the componentsof S in 120587
119887can be obtained as
S = C119887119868[1 0 0]
119879
119868
= [119878119909
119878119910
119878119911]119879
119887
(23)
The resultant SRP force can be simply modeled as followsfor a perfectly reflective control vane
F119894= 120578119875119860
119862119894(S sdot n
119862119894)2 n
119862119894= 119865
119862119894cos2120572
119862119894n119862119894 (24)
where 120578 is the overall sail-thrust coefficient (120578max = 2) 119875 =
4563 times 10minus6 Nm2 119860
119862119894is the area of the 119894th control vane
119865119862119894
= 120578119875119860119862119894is themaximumcontrol vane thrust andn
119862119894= i
119894
is the unit normal vector of the control vaneThe componentsof n
119862119894in 120587
119887can be written as
n119862119894
= C119887119894[1 0 0]
119879
119894
= [119878119909119894
119878119910119894
119878119911119894]119879
119887
(25)
The control torque by the 119894th control vane can beexpressed as
M119894= L
119894times F
119894 (26)
In fact L119894and F
119894are dependent on the deformations of
the supporting beams and control vanes In this paper it isassumed thatL
119894andF
119894are not influenced by the deformations
of the structure when computing the control torque by thecontrol vanes Thus L
119894and F
119894can be expressed as
L1= [0 0 minus119897]
119879
L2= [0 119897 0]
119879
L3= [0 0 119897]
119879
L4= [0 minus119897 0]
119879
F119894= 120578119875119860
119862119894([119878
119909119878119910
119878119911]119887
sdot [119878119909119894
119878119910119894
119878119911119894]119879
119887
)
2
[119878119909119894
119878119910119894
119878119911119894]119879
119887
(27)
The force of each control vane can be written as
F119894= (119865
119862119894cos2120572
119862119894)C
119887119894[1 0 0]
119879
119894
= (119865119862119894cos2120572
119862119894) [119878
119909119894119878119910119894
119878119911119894]119879
119887
(28)
where 120572119862119894
is the sun angle of the 119894th control vane that canbe measured by the sun sensor And the components of thecontrol torques can be obtained as
M1198881
= (1198651198621cos2120572
1198621)[
[
0
0
minus119897
]
]
times (C1198871
[
[
1
0
0
]
]
)
= (1198651198621cos2120572
1198621)
times [
[
minus119897 cos1205931sin120595
1
minus119897 (cos 1205791cos120595
1minus sin 120579
1sin120593
1sin120595
1)
0
]
]
M1198882
= (1198651198622cos2120572
1198622)
times [
[
119897 (sin 1205792cos120595
2+ cos 120579
2sin120593
2sin120595
2)
0
minus119897 (cos 1205792cos120595
2minus sin 120579
2sin120593
2sin120595
2)
]
]
M1198883
= (1198651198623cos2120572
1198623)
times [
[
119897 cos1205933sin120595
3
119897 (cos 1205793cos120595
3minus sin 120579
3sin120593
3sin120595
3)
0
]
]
M1198884
= (1198651198624cos2120572
1198624)
times [
[
minus119897 (sin 1205794cos120595
4+ cos 120579
4sin120593
4sin120595
4)
0
119897 (cos 1205794cos120595
4minus sin 120579
4sin120593
4sin120595
4)
]
]
(29)
27 Attitude Dynamics of Solar Sail The attitude dynamicscan be obtained by using the Lagrange equation method as
119889
119889119905(
120597119871
120597 119902119895
) minus120597119871
120597119902119895
= 119876119895 (30)
where 119871 is the Lagrange function 119902119895(119895 = 1ndash3) is the vector
of the generalized coordinates and 119876119895is the vector of the
generalized force 119871 can be computed as
119871 = 119879 minus 119880 =
4
sum
119894=1
119879119898119894
+ 119879119901+
2
sum
119895=1
119879ℎ119895
minus (119880119892119891
+ 119880119892119901
+
2
sum
119895=1
119880119892ℎ119895
)
(31)
where 119879119898119894 119879
119901 and 119879
ℎ119895are the kinetic energies of the
supporting beams payload and sliding masses respectively119880119892119891 119880
119892119901 and 119880
119892ℎ119895are the gravitational potential energies of
the sail system payload and sliding masses respectively
8 Mathematical Problems in Engineering
OOx
y
z
FCFCy
FCx
FCz
mh
q(x)
Figure 5 The vibration model
120590
120590e
120590120592
120590
Figure 6 The viscoelastic model
3 The Vibration of Solar Sail
The mechanical and material models of the sailcraft aregivenThe displacement filed stress and strain are presentedbased on the Euler beam assumptionThe Lagrange equationmethod is adopted to derive the vibration equations withlarge deformations based on the calculations of kineticenergies and works done by the external loads
31 The Mechanical Model The body frame O119874xyz is estab-
lished to describe the vibration (see Figure 5) F119862is the force
vector generated by the control vane used located at the tip ofthe supporting beam 119865
119862119909 119865
119862119910 and 119865
119862119911are the components
inO119874xyz 119902(119909) is the distributed load caused by SRP
32 The Material Model The carbon fibre enforced compos-ite material is used to construct the inflatable deploymentsupporting beam The model of the viscoelastic material canbe represented in Figure 6
The total stress is the summation of the elastic and viscousstresses It can be expressed as
120590 = 120590119890
+ 120590120592
= 119864120576 + 119888119887
120576 (32)
where 120590 120590119890 and 120590
120592 are the total elastic and viscous stressrespectively And 119864 is Youngrsquos modulus 120576 ( 120576) is the strain(strain rate) and 119888
119887is the coefficient of the internal damping
expressed as 119864120578119887 120578
119887is the proportionality constant of the
internal damping The dimensions of 119888119887and 120578
119887are N lowast sm2
and s respectively
OO x
y The support beam
Z
Figure 7 The schematic diagram of solar sail supporting beamdeformation
33 The Displacement Field Stress and Strain The deforma-tion of a spatial solar sail supporting beam is presented inFigure 7
The spatial displacement fields for supporting beam are as
119906 (119909 119910 119911 119905) = 1199060(119909 119905) minus 119910
120597V0
120597119909minus 119911
1205971199080
120597119909
V (119909 119910 119911 119905) = V0(119909 119905)
119908 (119909 119910 119911 119905) = 1199080(119909 119905)
(33)
119906(119909 119910 119911 119905) V(119909 119910 119911 119905) and 119908(119909 119910 119911 119905) are the displace-ments along 119909 119910 and 119911 directions respectively 119906
0(119909 119905)
V0(119909 119905) and 119908
0(119909 119905) are the axial and transverse displace-
ments of an arbitrary point on the neutral axisBy using Green strain definition von Karmanrsquos nonlinear
strain-displacement relationships based on assumptions oflarge deflections moderate rotations and small strains for a3D supporting beam are given as follows together with thestrain rate and normal stress
120576119909119909
=120597119906
0
120597119909+1
2(120597V
0
120597119909)
2
minus 1199101205972V
0
1205971199092
+1
2(120597119908
0
120597119909)
2
minus 1199111205972
1199080
1205971199092
120576119909119909
=120597
0
120597119909+(
120597V0
120597119909)(
120597V0
120597119909) minus 119910
1205972V
0
1205971199092
+(120597119908
0
120597119909)(
1205970
120597119909)
minus 1199111205972
0
1205971199092
120590119909119909
= 119864[120597119906
0
120597119909+1
2(120597V
0
120597119909)
2
minus 1199101205972V
0
1205971199092
+1
2(120597119908
0
120597119909)
2
minus 1199111205972
1199080
1205971199092
]
+ 119864120578119887(120597
0
120597119909+(
120597V0
120597119909)(
120597V0
120597119909) minus 119910
1205972V
0
1205971199092
+(120597119908
0
120597119909)(
1205970
120597119909) minus 119911
1205972
0
1205971199092
)
(34)
Mathematical Problems in Engineering 9
The single underlined terms in the preceding equationindicate the contribution by the geometrical nonlinearityThedynamics models and corresponding numerical simulationwithout considering the geometrical nonlinearity can beobtained and carried out by neglecting these terms
34 The Energies and Works Done by External Forces Thestrain energy can be derived as
119880119894=
1
2int
119897
0
119860119909119909
[120597119906
0
120597119909+
1
2(120597V
0
120597119909)
2
+1
2(120597119908
0
120597119909)
2
]
2
+ 119863119909119909
1205972V
0
1205971199092
+ 119863119909119909
1205972
1199080
1205971199092
119889119909
(35)
For an isotropic support beam the extensional stiffness119860
119909119909and bending stiffness119863
119909119909can be computed as
119860119909119909
= int119860
119864119889119860 119863119909119909
= int119860
1198641199112
119889119860 = int119860
1198641199102
119889119860 (36)
The dissipation function is as
Ψ119902=
1
2int
119897
0
[119860119909119909120578119887(120597
0
120597119909)
2
+ 119863119909119909120578119887(1205972V
0
1205971199092
)
2
+ 119863119909119909120578119887(1205972
0
1205971199092
)
2
]119889119909
(37)
The kinetic energy for the support beam is as
119879119890=
1
2int
119897
0
[119868119860(120597119906
0
120597119905)
2
+ 119868119860(120597119908
0
120597119905)
2
+ 119868119863(1205972
1199080
120597119909120597119905)
2
+ 119868119860(120597V
0
120597119905)
2
+ 119868119863(
1205972V
0
120597119909120597119905)
2
]119889119909
(38)
where 119868119860and 119868
119863are integration constant for the support
beam expressed as
119868119860= int
119860
120588119889119860 = 120588119860 119868119863= int
119860
1205881199112
119889119860 = int119860
1205881199102
119889119860 (39)
And the work done by the external force can be obtainedas119882 = 119865
119862119911sdot 119908 (119909
119888 119905) + 119865
119862119910sdot V (119909
119888 119905) + 119898
ℎ119886ℎ119910
(119909ℎ 119905) V (119909
ℎ 119905)
+ 119898ℎ119886ℎ119911
(119909ℎ 119905) 119908 (119909
ℎ 119905) + int
119897
0
119902 (119909) V (119909 119905) 119889119909
(40)where 119909
119888represents the position of the support beam
119908(119909119888 119905) V(119909
119888 119905) are the displacements along 119911 and 119910 direc-
tions respectively and the corresponding loads 119865119862119911 119865
119862119910are
known functions 119909ℎ 119897 and V
ℎare the position coordinate of
the sliding mass the length of the support beam and theconstant-velocity of the sliding mass The dynamic responseis studied only during the period [0 119897V
ℎ] 119898
ℎis the mass
and 119886ℎ119910(119909
ℎ 119905) and 119886
ℎ119911(119909
ℎ 119905) are the components of the
acceleration for a material point on the support beam theslidingmass just arrived at And the corresponding transversedeflections are 119908(119909
ℎ 119905) and V(119909
ℎ 119905) respectively
35 The Assumed Modes Method The axial displacement1199060(119909 119905) and the transverse deflections V
0(119909 119905) and119908
0(119909 119905) can
be represented as follows by considering the assumed modesmethod
1199060(119909 119905) =
infin
sum
119894=1
119880119894(119909)119880
119894(119905)
V0(119909 119905) =
infin
sum
119895=1
119881119895(119909) 119881
119895(119905)
1199080(119909 119905) =
infin
sum
119896=1
119882119896(119909)119882
119896(119905)
(41)
where 119880119894(119905) 119881
119895(119905) and 119882
119896(119905) are the time-dependent gen-
eralized coordinates and 119880119894(119909) 119881
119895(119909) and 119882
119896(119909) are the
assumedmodes For assumedmodemethod themode shapefunctions should satisfy the following requirements in thispaper
119880119894(119909)
1003816100381610038161003816119909=0= 0 119881
119895(119909)
10038161003816100381610038161003816119909=0= 0 119882
119896(119909)
1003816100381610038161003816119909=0= 0
1198811015840
119895
(119909)10038161003816100381610038161003816119909=0
= 0 1198821015840
119896
(119909)10038161003816100381610038161003816119909=0
= 0
(42)
The following first two assumed modes satisfying theassumed mode principle are used in this paper
1198801(119909) =
119909
119897 119880
2(119909) = (
119909
119897)
2
1198811(119909) = (
119909
119897)
2
1198812(119909) = (
119909
119897)
3
1198821(119909) = (
119909
119897)
2
1198822(119909) = (
119909
119897)
3
(43)
With the help of the assumedmodes the detailed expres-sions of 119880
119894 119879
119890119882
119911 and Ψ
119902can be obtained as
119880119894=
9
2
119860119909119909
1198973(119881
2
2
+ 1198822
2
)2
+27
4
119860119909119909
1198973(119881
11198812+ 119882
1119882
2)
times (1198812
2
+ 1198822
2
)
+18
7
119860119909119909
1198973[(119881
2
1
+ 1198822
1
) (1198812
2
+ 1198822
2
) + (11988111198812+ 119882
1119882
2)2
]
+119860
119909119909
1198973[3
2119897119880
2(119881
2
2
+ 1198822
2
) + (1198812
1
+ 1198822
1
)
times (11988111198812+ 119882
1119882
2)]
10 Mathematical Problems in Engineering
+1
10
119860119909119909
1198973[9119880
1119897 (119881
2
2
+ 1198822
2
) + 241198802119897 (119881
11198812+ 119882
1119882
2)
+ 4 (1198812
1
+ 1198822
1
)2
]
+119860
119909119909
1198972[3
21198801(119881
11198812+ 119882
1119882
2) + 119880
2(119881
2
1
+ 1198822
1
)]
+6119863
119909119909119881
2
2
1198973+ 119860
119909119909(2119880
1119881
2
1
31198972+
21198801119882
2
1
31198972+
21198802
2
3119897)
+6119863
119909119909119882
2
2
1198973+
611986311990911990911988111198812
1198973+
11986011990911990911988011198802
119897+
6119863119909119909119882
1119882
2
1198973
+119860
119909119909119880
2
1
2119897+
2119863119909119909119881
2
1
1198973+
2119863119909119909119882
2
1
1198973
119879119890=
1
14(119897119868
119860
2
2
+ 119897119868119860
2
2
) +1
6(119897119868
119860
1
2+ 119897119868
11986012)
+1
10(119897119868
119860
2
2
+ 119897119868119860
2
1
+9119868
119863
2
2
119897+ 119897119868
119860
2
1
+9119868
119863
2
2
119897)
+1
4(119897119868
11986012+
6119868119863
1
2
119897+
611986811986312
119897)
+1
6(119897119868
119860
2
1
+4119868
119863
2
1
119897+
4119868119863
2
1
119897)
119882119911= 119865
119862119911sdot [119882
1(119905) + 119882
2(119905)] + 119865
119862119910sdot [119881
1(119905) + 119881
2(119905)]
+ 119898ℎ[2V2
ℎ
1198972sdot 119881
1(119905) +
4V2ℎ
119905
1198972sdot
1(119905) + (
Vℎ119905
119897)
2
sdot 1(119905)
+6V3
ℎ
119905
1198973sdot 119881
2(119905) +
6V3ℎ
1199052
1198973
sdot 2(119905) + (
Vℎ119905
119897)
3
sdot 2(119905)]
times [(Vℎ119905
119897)
2
sdot 1198811(119905) + (
Vℎ119905
119897)
3
sdot 1198812(119905)]
+ 119898ℎ[2V2
ℎ
1198972sdot 119882
1(119905) +
4V2ℎ
119905
1198972sdot
1(119905) + (
Vℎ119905
119897)
2
sdot 1(119905)
+6V3
ℎ
119905
1198973sdot 119882
2(119905) +
6V3ℎ
1199052
1198973sdot
2(119905)
+ (Vℎ119905
119897)
3
sdot 2(119905)]
times [(Vℎ119905
119897)
2
sdot 1198821(119905) + (
Vℎ119905
119897)
3
sdot 1198822(119905)]
+ 1198811(119905) sdot int
119897
0
119902 (119909) (119909
119897)
2
119889119909 + 1198812(119905)
sdot int
119897
0
119902 (119909) (119909
119897)
3
119889119909
Ψ119902=
1
6(36119863
119909119909120578119887
2
2
1198976+
4119860119909119909120578119887
2
2
1198974+
36119863119909119909120578119887
2
2
1198976) 119897
3
+1
4(4119860
11990911990912057811988712
1198973+
2411986311990911990912057811988712
1198975
+24119863
119909119909120578119887
1
2
1198975) 119897
2
+1
2
119860119909119909120578119887
2
1
119897+
2119863119909119909120578119887
2
1
1198973+
2119863119909119909120578119887
2
1
1198973
(44)
36 The Vibration Equation The Lagrange equation methodis used to derive the vibration equations
120597119871
120597119902119899
minus119889
119889119905(
120597119871
120597 119902119899
) + 119876119889= 0 119899 = 1 2 6 (45)
where 119871 is the Lagrange function 119902119899
= (1198801 119880
2 119881
1 119881
2
1198821119882
2)119879 is the vector of the generalized coordinates and
119902119899is the corresponding generalized velocity vector 119876
119889is the
generalized damping force The expressions for 119871 and 119876119889are
as
119871 = 119879119890minus (119880
119894minus 119882
119911)
119876119889= minus
120597Ψ119902
120597 119902119899
(119899 = 1 sim 6)
(46)
The axial vibration equations can be obtained as followsfor 119880
1 119880
2
1
31198971198681198601+
1
41198971198681198602+
120578119887119860
1199091199091
119897+
120578119887119860
1199091199092
119897+
1198601199091199091198801
119897
+119860
1199091199091198802
119897+
2119860119909119909119881
2
1
31198972+
311986011990911990911988111198812
21198972+
9119860119909119909119881
2
2
101198972
+2119860
119909119909119882
2
1
31198972+
3119860119909119909119882
1119882
2
21198972+
9119860119909119909119882
2
2
101198972= 0
(47a)
1
41198971198681198601+
1
51198971198681198602+
120578119887119860
1199091199091
119897+
4120578119887119860
1199091199092
3119897
+119860
1199091199091198801
119897+4119860
1199091199091198802
3119897+119860
119909119909119881
2
1
1198972+12119860
11990911990911988111198812
51198972+3119860
119909119909119881
2
2
21198972
+119860
119909119909119882
2
1
1198972+
12119860119909119909119882
1119882
2
51198972+
3119860119909119909119882
2
2
21198972= 0
(47b)
The following can be seen from the above equations
(1) Since the assumed modes rather than the naturalmodes are used the coupling between axial and trans-verse vibrations is rather severe for axial vibrations
Mathematical Problems in Engineering 11
(2) The nonlinearity is apparent in above equations onlyexisting in the terms of 119881
1 119881
2119882
1119882
2 We take (47a)
as an exampleThe terms including1198802and its first and
second derivative 1198811 119881
2119882
1119882
2 can be regarded as
the applied loads for 1198801
(3) The coupling between the axial and transverse vibra-tionswill disappear as long as the linear displacement-strain relationship is adopted
(4) There are no external loads for axial vibrationsaccording to above equations
The transverse vibration equations for 1198811 119881
2and119882
1 119882
2
can be obtained as
4
3
1198681198631
119897+
1
51198971198681198601+
1
61198971198681198602minus
119898ℎV5ℎ
1199055
2
1198975+
31198681198632
2119897
+4119898
ℎV4ℎ
1199053
1
1198974+
4120578119887119863
1199091199091
1198973minus
2119898ℎV5ℎ
1199054
2
1198975+
6120578119887119863
1199091199092
1198973
+8119898
ℎV4ℎ
1199052
1198811
1198974+
41198631199091199091198811
1198973+
8119898ℎV5ℎ
1199053
1198812
1198975+
61198631199091199091198812
1198973
+27119860
1199091199091198812119882
2
2
81198973+
541198601199091199091198811119881
2
2
71198973+
181198601199091199091198811119882
2
2
71198973
+6119860
119909119909119881
2
1
1198812
1198973+
21198601199091199091198812119882
2
1
1198973+
1211986011990911990911988021198812
51198972
+8119860
1199091199091198811119882
2
1
51198973+
311986011990911990911988011198812
21198972+
211986011990911990911988021198811
1198972
+8119860
119909119909119881
3
1
51198973+
27119860119909119909119881
3
2
81198973+
361198601199091199091198812119882
1119882
2
71198973
+4119860
1199091199091198811119882
1119882
2
1198973+
411986011990911990911988011198811
31198972minus 119865
119888119910(119905) minus 05119865
025119865= 0
1
61198971198681198601+
3
2
1198681198631
119897minus
119898ℎV5ℎ
1199055
1
1198975+
1
71198971198681198602+
9
5
1198681198632
119897
+6120578
119887119863
1199091199091
1198973+
2119898ℎV5ℎ
1199054
1
1198975+
12120578119887119863
1199091199092
1198973+
6119898ℎV6ℎ
1199055
2
1198976
+6119863
1199091199091198811
1198973+
16119898ℎV5ℎ
1199053
1198811
1198975+
121198631199091199091198812
1198973+
18119898ℎV6ℎ
1199054
1198812
1198976
+9119860
1199091199091198812119882
2
2
21198973+
811198601199091199091198811119881
2
2
81198973+
311986011990911990911988011198811
21198972
+27119860
1199091199091198811119882
2
2
81198973+
541198601199091199091198812119881
2
1
71198973+
181198601199091199091198812119882
2
1
71198973
+3119860
11990911990911988021198812
1198972+
21198601199091199091198811119882
2
1
1198973+
911986011990911990911988011198812
51198972+
1211986011990911990911988021198811
51198972
+9119860
119909119909119881
3
2
21198973+
2119860119909119909119881
3
1
1198973+
271198601199091199091198812119882
1119882
2
41198973
+36119860
1199091199091198811119882
1119882
2
71198973minus 04119865
025119865minus 119865
119888119910(119905) = 0
4
3
119868119863
1
119897+
1
5119897119868119860
1+
3
2
119868119863
2
119897+
1
6119897119868119860
2minus
119898ℎV5ℎ
1199055
2
1198975
+4120578
119887119863
119909119909
1
1198973+
4119898ℎV4ℎ
1199053
1
1198974minus
2119898ℎV5ℎ
1199054
2
1198975+
6120578119887119863
119909119909
2
1198973
+4119863
119909119909119882
1
1198973+
8119898ℎV4ℎ
1199052
1198821
1198974+
8119898ℎV5ℎ
1199053
1198822
1198975+
6119863119909119909119882
2
1198973
+36119860
119909119909119882
211988111198812
71198973+
4119860119909119909119882
111988111198812
1198973+
27119860119909119909119882
2119881
2
2
81198973
+18119860
119909119909119882
1119881
2
2
71198973+
54119860119909119909119882
1119882
2
2
71198973+
6119860119909119909119882
2
1
1198822
1198973
+2119860
119909119909119882
2119881
2
1
1198973+
121198601199091199091198802119882
2
51198972+
8119860119909119909119882
1119881
2
1
51198973
+3119860
1199091199091198801119882
2
21198972+
21198601199091199091198802119882
1
1198972+
27119860119909119909119882
3
2
81198973
+8119860
119909119909119882
3
1
51198973+
41198601199091199091198801119882
1
31198972minus 119865
119888119911(119905) = 0
1
7119897119868119860
2+
9
5
119868119863
2
119897+
1
6119897119868119860
1minus
119898ℎV5ℎ
1199055
1
1198975+
3
2
119868119863
1
119897
+6120578
119887119863
119909119909
1
1198973+
2119898ℎV5ℎ
1199054
1
1198975+
6119898ℎV6ℎ
1199055
2
1198976
+12120578
119887119863
119909119909
2
1198973+
6119863119909119909119882
1
1198973+
16119898ℎV5ℎ
1199053
1198821
1198975
+12119863
119909119909119882
2
1198973+
18119898ℎV6ℎ
1199054
1198822
1198976+
31198601199091199091198801119882
1
21198972
+27119860
119909119909119882
211988111198812
41198973+
36119860119909119909119882
111988111198812
71198973+
9119860119909119909119882
2119881
2
2
21198973
+27119860
119909119909119882
1119881
2
2
81198973+
81119860119909119909119882
1119882
2
2
81198973+
18119860119909119909119882
2119881
2
1
71198973
+54119860
119909119909119882
2119882
2
1
71198973+
31198601199091199091198802119882
2
1198972+
2119860119909119909119882
1119881
2
1
1198973
+9119860
1199091199091198801119882
2
51198972+
121198601199091199091198802119882
1
51198972+
2119860119909119909119882
3
1
1198973
+9119860
119909119909119882
3
2
21198973minus 119865
119888119911(119905) = 0
(48)
The complexity high coupling and nonlinearity are obvi-ous in above equations
4 The Coupled Rigid-Flexible Dynamics
The dynamics for control and dynamic simulation shouldbe presented for solar sail based on the simplification ofequations derived in previous sections Some assumptions aremade before simplifying the equations as follows
12 Mathematical Problems in Engineering
(1) Only the attitude motion is affected by the slidingmass the vibration of solar sail structure is notaffected by the sliding mass
(2) Although the attitude control is accomplished byrotating control vanes and the gimbaled controlboom moving sliding masses the specific time his-tories of the actuators are not considered here
(3) The four supporting beams are regarded as an entirestructure thus the identical generalized coordinatesare adopted in the dynamic analysis
41 The Simplified Attitude Dynamics The kinetic energy ofsolar sail supporting beams can be obtained as
119879119898
=1
2120596 sdot J sdot 120596 + 119898
119897int
119897
0
2∘
1205883
sdot (120596 times r3) + (120596 times 120588
3) sdot (120596 times 120588
3)
+ 2 (120596 times r3) sdot (120596 times 120588
3) 119889119911
+ 119898119897int
119897
0
2∘
1205882
sdot (120596 times r2) + (120596 times 120588
2) sdot (120596 times 120588
2)
+ 2 (120596 times r2) sdot (120596 times 120588
2) 119889119910
(49)
The subscripts 2 and 3 represent the second and thirdsupporting beams The displacements can be expressed as
V0119909
(119911 119905) = (119911
119897)
2
sdot 1198811(119905) + (
119911
119897)
3
sdot 1198812(119905)
1199080119910
(119911 119905) = 120572V0119909
(119911 119905) = (119911
119897)
2
sdot 1205721198811(119905) + (
119911
119897)
3
sdot 1205721198812(119905)
for the 3rd beam
V0119909
(119910 119905) = 120573V0119909
(119911 119905) = (119910
119897)
2
sdot 1205731198811(119905) + (
119910
119897)
3
sdot 1205731198812(119905)
1199080119911
(119910 119905) = 120574V0119909
(119910 119905) = (119910
119897)
2
sdot 1205741198811(119905) + (
119910
119897)
3
sdot 1205741198812(119905)
for the 2nd beam
(50)
The subscripts 119909 119910 and 119911 of the left terms in (50)represent the displacements along119909119910 and 119911directions119881
1(119905)
and 1198812(119905) are the generalized coordinates The displacements
1199080119910(119911 119905) V
0119909(119910 119905) and 119908
0119911(119910 119905) can be obtained using the
assumed modes as
1205883= V
0119909(119911 119905) i
119887+ 119908
0119910(119911 119905) j
119887
=
[[[[[
[
(119911
119897)
2
sdot 1198811(119905) + (
119911
119897)
3
sdot 1198812(119905)
120572 [(119911
119897)
2
sdot 1198811(119905) + (
119911
119897)
3
sdot 1198812(119905)]
0
]]]]]
]
1205882= V
0119909(119910 119905) i
119887+ 119908
0119911(119910 119905) k
119887
=
[[[[[
[
120573[(119910
119897)
2
sdot 1198811(119905) + (
119910
119897)
3
sdot 1198812(119905)]
0
120574 [(119910
119897)
2
sdot 1198811(119905) + (
119910
119897)
3
sdot 1198812(119905)]
]]]]]
]
(51)
The vibration velocity can be obtained as
∘
1205883
= 1205883119909i119887+ 120588
3119910j119887=
[[[[[
[
(119911
119897)
2
sdot 1(119905) + (
119911
119897)
3
sdot 2(119905)
1205721[(
119911
119897)
2
sdot 1(119905) + (
119911
119897)
3
sdot 2(119905)]
0
]]]]]
]
∘
1205882
= 1205882119909i119887+ 120588
2119911k119887=
[[[[[
[
1205731[(
119910
119897)
2
sdot 1(119905) + (
119910
119897)
3
sdot 2(119905)]
0
1205741[(
119910
119897)
2
sdot 1(119905) + (
119910
119897)
3
sdot 2(119905)]
]]]]]
]
(52)
Without loss of generality 120572 = 120573 = 1205721= 120573
1= 1 and
120574 = 1205741= minus1 can be assumed in above expressions And the
kinetic energy of the slidingmasses can be obtained as followsby neglecting the vibration related terms
119879ℎ=
1
2119898
ℎ1(120596 times r
ℎ1) sdot (120596 times r
ℎ1) +
1
2119898
ℎ2(120596 times r
ℎ2)
sdot (120596 times rℎ2)
(53)
The kinetic energy of the payload can be obtained as
119879119901=
1
2119898
119901(120596 times r
119901) sdot (120596 times r
119901) (54)
The following simplified attitude dynamics can beobtained by neglecting the second and higher terms ofattitude angles and vibration modes in computing the kinetic
Mathematical Problems in Engineering 13
energies of the supporting beams payload and slidingmasses Consider
119869119909 minus 119898
1198971198972
1minus
4
5119898
1198971198972
2+ 119898
ℎ11199102
ℎ1
+ 119898ℎ21199112
ℎ2
minus 119898119901119903119901119909119903119901119911 + 119898
1199011199032
119901119911
+ 1198981199011199032
119901119910
minus 119898119901119903119901119909119903119901119910
120579 = 119876120593
119869119910
120579 +2
5119898
1198971198972
2+
1
2119898
1198971198972
1+ 119898
ℎ21199112
ℎ2
120579
+ 1198981199011199032
119901119911
120579 minus 119898119901119903119901119910119903119901119911 minus 119898
119901119903119901119909119903119901119910
+ 1198981199011199032
119901119909
120579 = 119876120579
119869119911 minus
2
51198972
1198981198972minus
1
21198972
1198981198971+ 119898
ℎ11199102
ℎ1
minus 119898119901119903119901119910119903119901119911
120579 + 1198981199011199032
119901119910
+ 1198981199011199032
119901119909
minus 119898119901119903119901119909119903119901119911 = 119876
120595
(55)
where 119876120593 119876
120579 and 119876
120595are the generalized nonpotential
attitude control torques generated by the control vanes Andthe attitude control torques generated by the gimbaled controlboom and sliding masses can be found on the left side ofthe above equation coupled with 120579 making the attitudecontroller design problem rather difficult
42 The Simplified Vibration Equations The couplingbetween the axial and transverse vibrations is neglectedand only the transverse vibration is considered The attitudedynamics for dynamic simulation can be obtained as followsbased on previous derivation by neglecting the action ofsolar-radiation pressure
4
3
1198681198631
119897+
1
51198971198681198601+
1
61198971198681198602+
31198681198632
2119897+
4120578119887119863
1199091199091
1198973
+6120578
119887119863
1199091199092
1198973+
41198631199091199091198811
1198973+
61198631199091199091198812
1198973+
271198601199091199091198812119882
2
2
81198973
+54119860
1199091199091198811119881
2
2
71198973+
181198601199091199091198811119882
2
2
71198973+
6119860119909119909119881
2
1
1198812
1198973
+2119860
1199091199091198812119882
2
1
1198973+
81198601199091199091198811119882
2
1
51198973+
8119860119909119909119881
3
1
51198973
+27119860
119909119909119881
3
2
81198973+
361198601199091199091198812119882
1119882
2
71198973+
41198601199091199091198811119882
1119882
2
1198973
minus 1198651198621
(119905) = 0
1
61198971198681198601+
3
2
1198681198631
119897+
1
71198971198681198602+
9
5
1198681198632
119897+
6120578119887119863
1199091199091
1198973
+12120578
119887119863
1199091199092
1198973+
61198631199091199091198811
1198973+
121198631199091199091198812
1198973+
91198601199091199091198812119882
2
2
21198973
+81119860
1199091199091198811119881
2
2
81198973+
271198601199091199091198811119882
2
2
81198973+
541198601199091199091198812119881
2
1
71198973
+18119860
1199091199091198812119882
2
1
71198973+
21198601199091199091198811119882
2
1
1198973+
9119860119909119909119881
3
2
21198973
+2119860
119909119909119881
3
1
1198973+
271198601199091199091198812119882
1119882
2
41198973+
361198601199091199091198811119882
1119882
2
71198973
minus 1198651198622
(119905) = 0
(56)
The following equations can be obtained by rearrangingthe above equations
4
3
1198681198631
119897+
1
51198971198681198601+
1
61198971198681198602+
31198681198632
2119897+
4120578119887119863
1199091199091
1198973
+6120578
119887119863
1199091199092
1198973+
41198631199091199091198811
1198973+
61198631199091199091198812
1198973+
16119860119909119909119881
3
1
51198973
+12119860
119909119909119881
2
1
1198812
1198973+
1081198601199091199091198811119881
2
2
71198973+
54119860119909119909119881
3
2
81198973
minus 1198651198621
(119905) = 0
1
61198971198681198601+
3
2
1198681198631
119897+
1
71198971198681198602+
9
5
1198681198632
119897+
6120578119887119863
1199091199091
1198973
+12120578
119887119863
1199091199092
1198973+
61198631199091199091198811
1198973+
121198631199091199091198812
1198973
+4119860
119909119909119881
3
1
1198973+
108119860119909119909119881
2
1
1198812
71198973+
811198601199091199091198811119881
2
2
41198973
+9119860
119909119909119881
3
2
1198973minus 119865
1198622(119905) = 0
(57)
1198651198621(119905) and 119865
1198622(119905) are used to represent all the generalized
external forces they can be used for vibration control Thesecomplicated equations abovementioned are the basis forobtaining the simplified equations used for controller design
The following equations can be obtained by neglecting thetwo and higher terms
4
3
1198681198631
119897+
1
51198971198681198601+
1
61198971198681198602+
31198681198632
2119897+
4120578119887119863
1199091199091
1198973
+6120578
119887119863
1199091199092
1198973+
41198631199091199091198811
1198973+
61198631199091199091198812
1198973= 119865
1198621
(119905)
14 Mathematical Problems in Engineering
1
61198971198681198601+
3
2
1198681198631
119897+
1
71198971198681198602+
9
5
1198681198632
119897+
6120578119887119863
1199091199091
1198973
+12120578
119887119863
1199091199092
1198973+
61198631199091199091198811
1198973+
121198631199091199091198812
1198973= 119865
1198622
(119905)
(58)
43 The Rigid-Flexible Coupled Dynamics The simplifiedattitude and vibration dynamics can be written as
119886120593 + 119886
120579
120579 + 119886120595 + 119886
1198811
1+ 119886
1198812
2= 119876
120593
119887120579
120579 + 119887120595 + 119887
120593 + 119887
1198811
1+ 119887
1198812
2= 119876
120579
119888120595 + 119888
120579
120579 + 119888120593 + 119888
1198811
1+ 119888
1198812
2= 119876
120595
119889
1198811
1+ 119889
1198812
2+ 119889
1198811
1+ 119889
1198812
2+ 119889
1198811
1198811
+ 1198891198812
1198812= 119876
1198811
119890
1198811
1+ 119890
1198812
2+ 119890
1198811
1+ 119890
1198812
2+ 119890
1198811
1198811
+ 1198901198812
1198812= 119876
1198812
(59)
The related coefficients in the preceding equation can befound in (A1) in the appendix The dynamics (see (59)) isnot suitable for attitude controller design because the controlinputs exist in some coefficients of the angular accelerationsThis will make the controller design rather difficult Thusthe following dynamic model is obtained by putting theterms including the control inputs right side of the dynamicequations
119869119909 minus 119898
1198971198972
1minus
4
5119898
1198971198972
2= 119876
120593+ 119906
119869119910
120579 +2
5119898
1198971198972
2+
1
2119898
1198971198972
1= 119876
120579+ 119906
120579
119869119911 minus
1
21198972
1198981198971minus
2
51198972
1198981198972= 119876
120595+ 119906
119889
1198811
1+ 119889
1198812
2+ 119889
1198811
1+ 119889
1198812
2
+ 1198891198811
1198811+ 119889
1198812
1198812= 119876
1198811
119890
1198811
1+ 119890
1198812
2+ 119890
1198811
1+ 119890
1198812
2
+ 1198901198811
1198811+ 119890
1198812
1198812= 119876
1198812
(60)
The expressions for 119906 119906
120579
and 119906are as
119906= minus119898
ℎ11199102
ℎ1
minus 119898ℎ21199112
ℎ2
+ 119898119901119903119901119909119903119901119911 minus 119898
1199011199032
119901119911
minus 1198981199011199032
119901119910
+ 119898119901119903119901119909119903119901119910
120579
119906
120579
= minus119898ℎ21199112
ℎ2
120579 minus 1198981199011199032
119901119911
120579 + 119898119901119903119901119910119903119901119911 + 119898
119901119903119901119909119903119901119910
minus 1198981199011199032
119901119909
120579
119906= minus119898
ℎ11199102
ℎ1
+ 119898119901119903119901119910119903119901119911
120579 minus 1198981199011199032
119901119910
minus 1198981199011199032
119901119909
+ 119898119901119903119901119909119903119901119911
(61)
119906 119906
120579
and 119906are the functions of the positions of sliding
masses and payload and the angular accelerations The statevariables in (60) are defined as
1199091= 120593 119909
2= 119909
3= 120579 119909
4= 120579
1199095= 120595 119909
6= 119909
7= 119881
1
1199098=
1 119909
9= 119881
2 119909
10=
2
(62)
Thedynamics (60) can bewritten as the state-spacemodelas following
1= 119909
2
2= 119886
11199097+ 119886
21199098+ 119886
31199099+ 119886
411990910
+ 119906120593
3= 119909
4
4= 119886
51199097+ 119886
61199098+ 119886
71199099+ 119886
811990910
+ 119906120579
5= 119909
6
6= 119886
91199097+ 119886
101199098+ 119886
111199099+ 119886
1211990910
+ 119906120595
7= 119909
8
8= 119886
131199097+ 119886
141199098+ 119886
151199099+ 119886
1611990910
+ 1199061198811
9= 119909
10
10
= 119886171199097+ 119886
181199098+ 119886
191199099+ 119886
2011990910
+ 1199061198812
(63)
where 119906120579 119906
120593 and 119906
120595are the generalized control inputs
for attitude control and 1199061198811
and 1199061198812
are the generalizedcontrol inputs for vibration control The controllability canbe satisfied by analyzing (63) The attitudevibration controlinputs and the coefficients will be presented later in thissection The form of a matrix differential equation can bewritten as follows for the above equation
x = Ax + Bu (64)
The expressions of the relatedmatrices and vectors can befound as
x = [1
2
3
4
5
6
7
8
9
10]119879 x (119905
0) = x
1199050
u = [119906120593 119906
120579 119906
120595 119906
1198811
1199061198812
]119879
u (1199050) is known
(65)
where A xB and u are the system matrix state variablesvector control matrix and control inputs vector respectively
Mathematical Problems in Engineering 15
The complexity of the state-space model can be seen bypresenting the detailed expressions of control inputs forattitudevibration and related parameters in (A2) in theappendix
5 AttitudeVibration Control and Simulation
The controller for the attitude and vibration is developedusing the LQR and optimal PI theory The dynamic simula-tion is performed based on the coupled dynamics derived inthe previous sections
51 LQR and Optimal PI Based Controllers Design Thedynamics for solar sail can bewritten as follows togetherwithits quadratic cost function also defined as
x = Ax + Bu x (1199050) = x
1199050
(known)
119869 =1
2int
infin
1199050
[x119879 (119905)Qx (119905) + u119879 (119905)Ru (119905)] 119889119905
(66)
whereQ = Q119879
⩾ 0 andR = R119879
gt 0 are constantThe control-lability of [AB] and the observability of [AD] can beensured when the equationDD119879
= Q holds for anymatrixDThe optimal control input ulowast(119905)within the scope of u(119905) isin R119903119905 isin [119905
0infin] can be computed as follows to make 119869minimum
ulowast (119905) = minusKxlowast (119905) K = Rminus1B119879P (67)
where P is the nonnegative definite symmetric solution of thefollowing Riccati algebraic equations
PA + A119879P minus PBRminus1B119879P +Q = 0 (68)
And the optimal performance index can be obtained asfollows for arbitrary initial states
119869lowast
[x (1199050) 119905
0] =
1
2x1198790
Px0 (69)
The closed-loop system
x = (A minus BRminus1B119879P) x (70)
is asymptotically stableFor an orbiting solar sail the primary disturbance torque
is by the cmcp offset and the impact of the tiny dust inthe deep space The state regulator can be used to controlthe dynamic system affected by pulse disturbance torquewith good steady-state errors but will never achieve accuratesteady-state errors if the dynamics is affected by constantdisturbance torque Thus the optimal state regulator withan integrator to eliminate the constant disturbance torqueshould be presented This optimal proportional-integral reg-ulator not only eliminates the constant disturbance torque butalso possesses the property of optimal regulator
Table 1 The related parameters
Parameters ValuesCMCP offsetm [0 017678 017678]119879
The side length of square sailm 100Nominal solar-radiation pressureconstant at 1 AU from the sunNm2 4563 times 10minus6
Solar-radiation pressure forceN 912 times 10minus2
Roll inertiakglowastm2 50383Pitch and yaw inertiakglowastm2 251915Outer radiusm 0229Thickness of the supporting beamm 75 times 10minus6
Youngrsquos modulus of the supportingbeamGPa 124
Moment of inertia of the cross-sectionof the supporting beamm4 2829412 times 10minus7
Bending stiffness of the supportingbeamNlowastm2 3508471336
Proportional damping coefficient ofsupporting beams 001
Line density of the supportingbeamkgm 0106879
Cross-sectional area of the supportingbeamm2 1079 times 10minus5
Roll disturbance torqueNlowastm 0Pitch (yaw) disturbance torqueNlowastm 0016122 (minus0016122)
For the following linear system with the correspondingperformance index
x = Ax + Bu x (1199050) = x
1199050
u (1199050) = u
1199050
119869 =1
2int
infin
1199050
(x119879Qx + u119879Ru + u119879Su) 119889119905(71)
where Q = Q119879
⩾ 0 R = R119879
gt 0 and S = S119879 gt 0 If [AB]is completely controllable and meanwhile [AD
11] is com-
pletely observable with the relationship D11D119879
11
= Q thesolution can be expressed as
ulowast = minusK1x minus K
2ulowast ulowast (119905
0) = u
1199050
(72)
If B119879B is full rank we can get
ulowast = minusK3x minus K
4x ulowast (119905
0) = u
1199050
(73)
K119894(119894 = 1 2 3 4) is the function of ABQR S
The closed-loop system
[xulowast] = [
A BminusK
1minusK
2
] [xulowast] [
[
x (1199050)
u (1199050)]
]
= [x1199050
u1199050
] (74)
is asymptotically stableThe compromise between the state variables (the angle
angular velocity the vibration displacement and velocity)and control inputs (the torque by all the actuators) can
16 Mathematical Problems in Engineering
0 2000 4000 6000
0 2000 4000 6000
0 2000 4000 6000minus5
0
5
minus5
0
5
minus5
0
5
minus4
minus2
0
2
4
times10minus4
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
00162
00164
00166
4800 4900 5000
4800 4900 5000
4800 4900 5000
minus00165
minus0016
Time (s) Time (s)
Time (s)
Time (s)
Time (s)
Time (s)
Roll
erro
r120593(∘
)
Roll
erro
r120593(∘
)
Pitc
h er
ror120579
(∘)
Pitc
h er
ror120579
(∘)
Yaw
erro
r120595(∘
)
Yaw
erro
r120595(∘
)
Figure 8 The roll pitch and yaw errors
be achieved by using both the LQR based and optimal PIbased controllers for the coupled attitudevibration dynamicsystem The fact is that the attitude control ability is limitedto the control torque by the control actuators The change ofthe attitude angles and rates should not be frequent to voidexciting vibrations
Thus the weighting matrix Q and the control weightingmatrix R are selected as follows for LQR based controller
Q (1 1) = 9 times 10minus6
Q (2 2) = 1 times 10minus6
Q (3 3) = 16 times 10minus6
Q (4 4) = Q (5 5) = Q (6 6) = Q (7 7) = Q (8 8)
= Q (9 9) = Q (10 10) = 1 times 10minus6
Q (119894 119895) = 0 (119894 = 119895 119894 119895 = 1 sim 10)
R (1 1) = R (2 2) = 900 R (3 3) = 100
R (4 4) = R (5 5) = 10000
R119894119895
= 0 (119894 = 119895 119894 119895 = 1 sim 5)
(75)
TheweightingmatrixQ and the control weightingmatrixR are selected as follows for the optimal PI based controller
Q (1 1) = Q (2 2) = 4 times 10minus8
Q (3 3) = Q (4 4) = Q (5 5) = Q (6 6) = Q (7 7)
= Q (8 8) = 16 times 10minus8
Mathematical Problems in Engineering 17
minus02
0
02
Roll
rate
(∘s)
Roll
rate
(∘s)
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Pitc
h ra
te(∘s)
Pitc
h ra
te(∘s)
0 1000 2000 3000 4000 5000
minus05
0
05
minus05
0
05
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
Time (s)
Yaw
rate
(∘
s)
Yaw
rate
(∘
s)
4800 4850 4900 4950 5000
Time (s)4800 4850 4900 4950 5000
Time (s)4800 4850 4900 4950 5000
minus2
0
2
minus2
0
2
minus2
0
2
times10minus4
times10minus4
times10minus4
Figure 9 The roll pitch and yaw rates
Q (9 9) = Q (10 10) = 1 times 10minus8
Q (119894 119895) = 0 (119894 = 119895 119894 119895 = 1 sim 10)
R (1 1) = R (2 2) = R (3 3) = 1 times 10minus8
R (4 4) = R (5 5) = 4 times 10minus8
R (119894 119895) = 0 (119894 = 119895 119894 119895 = 1 sim 5)
(76)
52 The Simulation Results The initial angle errors of rollpitch and yaw are adopted as 120593(119905
0) = 3
∘ 120579(1199050) = 3
∘ and120595(119905
0) = 3
∘ the initial angular velocity errors of roll pitchand yaw are adopted as (119905
0) = 0
∘
s 120579(1199050) = 0
∘
s and(119905
0) = 0
∘
s 1198811(1199050) = 01m 119881
2(1199050) = 01m
1(1199050) = 0ms
and 2(1199050) = 0ms are adopted in this paper for dynamic
simulationThe estimated cmcp offset is 025m for a 100 times 100m
square solar sail It is assumed that the components of cmcpoffset vector are [0 017678 017678]
119879 in the body frame
The relevant parameters for dynamic simulations are givenin Table 1
The dynamic simulation results are obtained as followsby using the LQR controller based on the abovementionedQ and R related parameters and initial conditions Thedynamics simulations with (denoted by ldquowith GFrdquo) andwithout (denoted by ldquowithout GFrdquo) considering the geo-metrical nonlinearity are presented And the correspondingdiscussions and analysis are also given according to thecalculated results
The roll pitch and yaw errors are presented based onthe dynamics models with and without considering thegeometrical nonlinearityThe control effect with zero steady-state error can be achieved for roll axis by referring tothe results But the steady-state errors exist for pitch andyaw axes from Figure 8 this is because there exist constantdisturbance torques for pitch and yaw axes caused by thecmcp offset Thus the LQR based controller cannot be usedfor attitude control with good steady-state performance Thesteady-state errors of pitch and yaw axes are about 0164
∘
and minus0164∘ respectively from the corresponding partial
enlarged drawing of the figures (see the corresponding left
18 Mathematical Problems in Engineering
minus20
0
20
Roll
torq
ue (N
lowastm
)
Roll
torq
ue (N
lowastm
)
minus50
0
50
minus50
0
50
Pitc
h to
rque
(Nlowast
m)
Pitc
h to
rque
(Nlowast
m)
0 1000 2000 3000 4000 5000
0 2000 4000 6000
0 2000 4000 6000
Yaw
torq
ue (N
lowastm
)
Yaw
torq
ue (N
lowastm
)
minus002
0
002
008
01
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
minus01
minus009
minus008
Time (s)Time (s)
Time (s)Time (s)
Time (s)Time (s)
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Figure 10 The roll pitch and yaw torques
figures) A simple and practical controller should be designedto eliminate the steady-state errorsThese errorswill affect theprecision of the super long duration space mission deeply
The differences between the dynamics with and withoutthe geometrical nonlinearity effect can be observed Theamplitudes and phases change a bit by comparing the corre-sponding results
It can be observed by the partial enlarged figures(the right figures of Figure 9) that there are no steady-stateerrors for roll pitch and yaw rates The relative satisfieddynamic performance is achieved In fact a result with muchmore satisfied dynamic performance can be obtained but itwill make the desired control torques much larger duringthe initial period This will not only excite the vibration ofthe structure but also increase the burden of the controlactuators
And the differences between the dynamics models withand without the geometrical nonlinearity can also be seenmerely in the phase of the angular velocities
The desired attitude control torques are presented inFigure 10 The roll torque will tend to be zero with thedecrement of the state variable errors The pitch and yawtorques tend to be constant from the middle and bottom
figures The pitch and yaw steady-state errors can never beeliminated although the pitch and yaw torques (009Nlowastmand minus009Nlowastm) are applied continuously by theoreticalanalysis and simulations This is just a great disadvantage ofthe LQR based controller in this paper The initial controltorques can be afforded by vibrating the gimbaled controlboom andmoving the slidingmasses that can afford a relativelarge torque The control vanes can be used to afford thecontrol torques when solar sail is in steady-state process Theexpression of the attitude control inputs 119906
120593 119906
120579 and 119906
120595can be
found in previous sectionMoreover the differences between dynamics responses
with and without geometrical nonlinearity can also beobserved by comparing the corresponding results Therequired torques for the attitude control are a little largerfor the dynamics with geometrical nonlinearity And thedifference in the phase is also clear
It can be seen that the vibration of the supporting beamis depressed effectively by the simulation results in Figure 11It can be seen that the steady-state errors and the dynamicperformance are relatively satisfied It can also be seen that thedynamics responses between the model with and without the
Mathematical Problems in Engineering 19
0 1000 2000 3000 4000 5000
0 1000 2000 3000 4000 5000
minus01
0
01
minus02
0
02
Time (s) Time (s)
Time (s) Time (s)
minus5
0
5
times10minus4
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
minus1
0
1
times10minus3
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
The d
ispla
cem
ent o
f the
tip
(m)
The d
ispla
cem
ent o
f the
tip
(m)
The v
eloci
ty o
f the
tip
(ms
)
The v
eloc
ity o
f the
tip
(ms
)
Figure 11 The displacement and velocity of the tip of the supporting beam
geometrical nonlinearity effect are different in the vibrationdisplacement and velocitymagnitudes and phases (Figure 15)
The simulation results can be obtained as follows by usingthe optimal PI based controller adopting the abovementionedparameters and initial conditions
The roll pitch and yaw errors are given by using theoptimal PI based controller These errors tend to disappearby observing the partially enlarged plotting of the figure (thecorresponding right figures) (shown in Figure 12) And therelative satisfied dynamic performance can also be obtainedFrom the view of eliminating the steady-state errors the opti-mal PI based controller performs better than the LQR basedcontroller by theoretical analysis and simulation results Theformer can achieve attitude control results without pitchand yaw steady-state errors From the view of dynamicperformance both the controllers perform well In additionit can be seen that the difference between the modelswith and without geometrical nonlinearity is merely inthe phase
The roll pitch and yaw rate errors are presented inFigure 13 The dynamic and steady-state performances aresatisfied by observing the simulation results And by observ-ing the difference between the dynamics responses with and
without the influence by the geometrical nonlinearity it canbe concluded that the merely difference is the phase
The desired control torques of the roll pitch and yaw areobtained in Figure 14 by using the optimal PI based controllerIt can be seen that the value of the desired roll control torquedecreases to zero as the values of the roll angle and ratedecrease to zero The desired pitch and yaw control torquestend to be the constant values 009Nlowastm and minus009Nlowastmrespectively The desired initial control torques are large byobserving Figure 14 It is suggested that the gimbaled controlboom combining the sliding masses is adopted to afford theinitial torque Then the control vanes can be used to controlthe solar sail after the initial phase The phase differencecan also be observed by inspecting the dynamics responsesduring the 4800sim5000 s period
The vibration can be controlled effectively based on theoptimal PI controller And the relative satisfied dynamicand steady-state performances can be achieved In additionthe tiny differences exist in the magnitudes of the requiredtorques And the phase differences also exist
It can be concluded as follows by analyzing and compar-ing the simulation results based on the LQR and optimal PItheories in detail
20 Mathematical Problems in Engineering
Roll
erro
r120593(∘
)
Roll
erro
r120593(∘
)
minus5
0
5
minus5
0
5
Pitc
h er
ror120579
(∘)
Pitc
h er
ror120579
(∘)
0 1000 2000 3000 4000 5000minus10
0
10
Time (s) Time (s)
Time (s)
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
Yaw
erro
r120595(∘
)
Yaw
erro
r120595(∘
)
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
minus1
0
1
times10minus3
minus1
0
1
times10minus3
minus1
0
1
times10minus3
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Figure 12 The roll pitch and yaw errors
(1) From the view of eliminating the steady-state errorsof the pitch and yaw errors the optimal PI based con-troller performs better than the LQR based controllerby theoretical analysis and simulation results Thedynamic performances of the two controllers are bothsatisfied and the desired control torques are relativelysmall
(2) The weighting of the state variables is reflected by theweighting matrix according to the LQR and optimalPI theories The constant weighting matrices selectedin this paper can effectively reflect the initial statevariable errors but maybe reflect the final state vari-able errors deficiently The time-varying weightingmatrices should be selected
(3) For the actual orbiting solar sail the control actuators(control vanes gimbaled control boom and slidingmasses) cannot afford excessive large control torquesThus the control torques should be as small as possibleon the premise of acquiring satisfied dynamic perfor-mance and steady-state errors It will not only reducethe burden of the control actuators but also avoid
exciting structural vibration In engineering practicethe weighting matrices and the control weightingmatrices should be selected based on the attitudecontrol requirement (eg dynamic performance andsteady-state errors etc)
(4) The dynamics responses influenced by the geometri-cal nonlinearity can be observed In a word the tinydifferences between the magnitudes of the physicalvariables exist for the models with and withoutthe geometrical nonlinearity And the relative cleardifferences exist in the phases for the attitude anglesrates required torques and so forth
6 Conclusions
The coupled attitude and structural dynamics is establishedfor the highly flexible sailcraft by using the von-Karman von-Karmanrsquos nonlinear strain-displacement relationships basedon assumptions of large deflections moderate rotationsand
Mathematical Problems in Engineering 21
Roll
rate
erro
r(∘ s
)
Roll
rate
erro
r(∘ s
)
minus01
0
01
minus01
0
01
Pitc
h ra
te er
ror (
∘ s)
Pitc
h ra
te er
ror (
∘ s)
0 1000 2000 3000 4000 5000minus02
0
02
Yaw
rate
erro
r (∘ s
)
Yaw
rate
erro
r (∘ s
)
4800 4850 4900 4950 5000
minus5
0
5times10minus4
minus5
0
5
times10minus4
minus5
0
5times10minus4
Time (s)
4800 4850 4900 4950 5000
Time (s)
4800 4850 4900 4950 5000
Time (s)
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Figure 13 The roll pitch and yaw rate errors
small strains The Lagrange equation method is utilizedto derive the dynamics for controller design and dynamicsimulation The LQR and optimal PI based controllers aredesigned for the dynamics with the constant disturbancetorque caused by the cmcp offset By theoretical analysisand simulation it can be seen that both controllers cancompromise between the state variables and control inputsBecause the control actuators can hardly afford large controltorque the dynamic performance should be relaxed toreduce the requirement for the attitude control actuatorsBesides the optimal PI based controller can also eliminatethe constant disturbance torque caused by the cmcp offsetthat always exists while the LQR based controller fails toachieve the results with satisfied steady-state performancealthough the attitude control torque is always applied to thecoupled dynamic systemThe dynamics simulations with andwithout the geometrical nonlinearity effect are also carriedout And the differences between the models in magnitudesand phases are identified and analyzed It can be concludedthat the optimal PI based controller performs better than the
LQRbased controller from the viewof eliminating the steady-state error caused by the disturbance torque by the cmcpoffset
Appendix
The related parameters in above equation are given as
119886120593= 119869
119909+ 119898
ℎ11199102
ℎ1
+ 119898ℎ21199112
ℎ2
+ 1198981199011199032
119901119911
+ 1198981199011199032
119901119910
119886120579= minus 119898
119901119903119901119909119903119901119910 119886
120595= minus119898
119901119903119901119909119903119901119911
1198861198811
= minus 1198981198971198972
1198861198812
= minus4
5119898
1198971198972
119887120579= 119869
119910+ 119898
ℎ21199112
ℎ2
+ 1198981199011199032
119901119911
+ 1198981199011199032
119901119909
119887120595= minus 119898
119901119903119901119910119903119901119911 119887
120593= minus119898
119901119903119901119909119903119901119910
22 Mathematical Problems in Engineering
Roll
torq
ue (N
lowastm
)
Roll
torq
ue (N
lowastm
)
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
0 2000 4000 6000
0 2000 4000 6000
0 2000 4000 6000
Time (s)
Time (s)
Time (s)
Time (s)
Time (s)
Time (s)4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
minus01
minus008
008
009
01
minus002
0
002
minus5
0
5
minus2
0
2
Pitc
h to
rque
(Nlowast
m)
Pitc
h to
rque
(Nlowast
m)
minus2
0
2
Yaw
torq
ue (N
lowastm
)
Yaw
torq
ue (N
lowastm
)
Figure 14 The roll pitch and yaw torques
1198871198811
=1
2119898
1198971198972
1198871198812
=2
5119898
1198971198972
119888120595= 119869
119911+ 119898
ℎ11199102
ℎ1
+ 1198981199011199032
119901119910
+ 1198981199011199032
119901119909
119888120579= minus 119898
119901119903119901119910119903119901119911 119888
120593= minus119898
119901119903119901119909119903119901119911
1198881198811
= minus1
21198972
119898119897 119888
1198812
= minus2
51198972
119898119897
119889
1198811
= (4
3
119868119863
119897+
1
5119897119868119860) 119889
1198812
= (1
6119897119868119860+
3119868119863
2119897)
119889
1198811
=4120578
119887119863
119909119909
1198973 119889
1198812
=6120578
119887119863
119909119909
1198973
1198891198811
=4119863
119909119909
1198973 119889
1198812
=6119863
119909119909
1198973
1198761198811
= 1198651198621
(119905)
119890
1198811
= (3
2
119868119863
119897+
1
6119897119868119860)
119890
1198812
= (1
7119897119868119860+
9
5
119868119863
119897) 119890
1198811
=6120578
119887119863
119909119909
1198973
119890
1198812
=12120578
119887119863
119909119909
1198973 119890
1198811
=6119863
119909119909
1198973
1198901198812
=12119863
119909119909
1198973 119876
1198812
= 1198651198622
(119905)
(A1)
The detailed expressions of control inputs for attitudevibration and related parameters in the state-space model ofthe dynamics (see (62) and (63)) are presented as follows
A =
[[[[[[[[[[[[[[
[
0 1 0 0 0 0 0 0 0 0
0 0 0 0 0 0 1198861
1198862
1198863
1198864
0 0 0 1 0 0 0 0 0 0
0 0 0 0 0 0 1198865
1198866
1198867
1198868
0 0 0 0 0 1 0 0 0 0
0 0 0 0 0 0 1198869
11988610
11988611
11988612
0 0 0 0 0 0 0 1 0 0
0 0 0 0 0 0 11988613
11988614
11988615
11988616
0 0 0 0 0 0 0 0 0 1
0 0 0 0 0 0 11988617
11988618
11988619
11988620
]]]]]]]]]]]]]]
]
Mathematical Problems in Engineering 23
0 1000 2000 3000 4000 5000
0 1000 2000 3000 4000 5000
minus01
0
01
minus02
0
02
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Time (s)
Time (s)Time (s)
Time (s)
minus1
0
1
minus1
0
1
times10minus3
times10minus3Th
e disp
lace
men
t of t
he ti
p (m
)
The d
ispla
cem
ent o
f the
tip
(m)
The v
eloci
ty o
f the
tip
(ms
)
The v
eloci
ty o
f the
tip
(ms
)
Figure 15 Vibration displacement and velocity of the tip
B =
[[[[[[[[[[[[[[
[
0 0 0 0 0
1 0 0 0 0
0 0 0 0 0
0 1 0 0 0
0 0 0 0 0
0 0 1 0 0
0 0 0 0 0
0 0 0 1 0
0 0 0 0 0
0 0 0 0 1
]]]]]]]]]]]]]]
]
1198861= minus
1198981198971198972
119869119909
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus4
5119869119909
1198981198971198972
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198862= minus
1198981198971198972
119869119909
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus4
5119869119909
1198981198971198972
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198863= minus
1198981198971198972
119869119909
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus4
5119869119909
1198981198971198972
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198864= minus
1198981198971198972
119869119909
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus4
5119869119909
1198981198971198972
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
119906120593=
119876120593
119869119909
+
119906
119869119909
+119898
1198971198972
119869119909
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+4
5119869119909
1198981198971198972
+
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198865=
1
2119869119910
1198981198971198972
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+2
5119869119910
1198981198971198972
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198866=
1
2119869119910
1198981198971198972
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+2
5119869119910
1198981198971198972
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198867=
1
2119869119910
1198981198971198972
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+2
5119869119910
1198981198971198972
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198868=
1
2119869119910
1198981198971198972
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
24 Mathematical Problems in Engineering
+2
5119869119910
1198981198971198972
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
119906120579=
119876120579
119869119910
+119906
120579
119869119910
minus1
2119869119910
1198981198971198972
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119910
1198981198971198972
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198869= minus
1
2119869119911
1198972
119898119897
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988610
= minus1
2119869119911
1198972
119898119897
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988611
= minus1
2119869119911
1198972
119898119897
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988612
= minus1
2119869119911
1198972
119898119897
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
119906120595=
119876120595
119869119911
+
119906
119869119911
+1
2119869119911
1198972
119898119897
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+2
5119869119911
1198972
119898119897
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988613
= minus
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988614
= minus
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988615
= minus
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988616
= minus
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
1199061198811
=
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988617
= minus
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988618
= minus
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988619
= minus
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988620
= minus
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1199061198812
=
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(A2)
Conflict of Interests
The authors declare that there is no conflict of interestsregarding the publication of this paper
Acknowledgments
The authors would like to thank the anonymous reviewers fortheir critical and constructive review of the paper This studywas cosupported by the National Natural Science Foundationof China (Project no 11302134 11272101)
References
[1] M Colin Solar Sailing Technology Dynamics and MissionApplications Springer-Praxis London UK 1st edition 1999
[2] V Lappas SWokesM Leipold A Lyngvi and P Falkner ldquoGui-dance and control for an Interstellar Heliopause Probe (IHP)solar sail mission to 200 AUrdquo in Proceedings of the AIAAGuidance Navigation and Control Conference and Exhibit pp2472ndash2492 San Francisco Calif USA August 2005
[3] L Charlotte C Camilla and C McInnes ldquoSolar radiation pres-sure augmented deorbiting fromhigh altitude sun-synchronousorbitsrdquo in Proceedings of the 4S Symposium 2012 Small SatellitesSystems and Services Portoroz Slovenia 2012
[4] M Ceriotti and C RMcInnes ldquoGeneration of optimal trajecto-ries for Earth hybrid pole sittersrdquo Journal of Guidance Controland Dynamics vol 34 no 3 pp 847ndash859 2011
[5] S Gong J Li andH Baoyin ldquoSolar sail transfer trajectory fromL1 point to sub-L1 pointrdquoAerospace Science and Technology vol15 no 7 pp 544ndash554 2011
[6] S Gong J Li and H Baoyin ldquoAnalysis of displaced solar sailorbits with passive controlrdquo Journal of Guidance Control andDynamics vol 31 no 3 pp 782ndash785 2008
[7] S Gong H Baoyin and J Li ldquoSolar sail three-body transfertrajectory designrdquo Journal of Guidance Control and Dynamicsvol 33 no 3 pp 873ndash886 2010
Mathematical Problems in Engineering 25
[8] S Gong J Li H Baoyin and J Simo ldquoA new solar sail orbitrdquoScience China Technological Sciences vol 55 no 3 pp 848ndash8552012
[9] Y Tsuda O Mori R Funase et al ldquoAchievement of IKAROS-Japanese deep space solar sail demonstration missionrdquo ActaAstronautica vol 82 no 2 pp 183ndash188 2013
[10] L Johnson MWhorton A Heaton R Pinson G Laue and CAdams ldquoNanoSail-D a solar sail demonstration missionrdquo ActaAstronautica vol 68 no 5-6 pp 571ndash575 2011
[11] B Wie and D Murphy ldquoSolar-sail attitude control design for asail flight validation missionrdquo Journal of Spacecraft and Rocketsvol 44 no 4 pp 809ndash821 2007
[12] B Wie D Murphy M Paluszek and S Thomas ldquoRobust atti-tude control systems design for solar sails part 1 propellantlessprimaryACSrdquo inProceedings of the AIAAGuidance Navigationand Control Conference and Exhibit Providence RI USAAugust 2004
[13] B Wie D Murphy M Paluszek and S Thomas ldquoRobust atti-tude control systems design for solar sails part 2 MicroPPT-based secondary ACSrdquo in Proceedings of the AIAA GuidanceNavigation and Control Conference and Exhibit pp 1325ndash1340Providence RI USA August 2004
[14] S Thomas M Paluszek B Wie and D Murphy ldquoAOCS per-formance and stability validation for large flexible solar sailspacecraftrdquo in Proceedings of the 41st AIAAASMESAEASEEJoint Propulsion Conference amp Exhibit Tucson Ariz USA 2005
[15] B Wie ldquoDynamic modeling and attitude control of solar sailspacecraft part Irdquo in Proceedings of the AIAAGuidance Naviga-tion and Control Conference and Exhibit Monterey Calif USAAugust 2002
[16] BWie ldquoSolar sail attitude control and dynamics part 1rdquo Journalof Guidance Control and Dynamics vol 27 no 4 pp 526ndash5352004
[17] B Wie ldquoDynamic modeling and attitude control of solar sailspacecraft part IIrdquo in Proceedings of the AIAA Guidance Nav-igation and Control Conference and Exhibit Monterey CalifUSA August 2002
[18] BWie ldquoSolar sail attitude control and dynamics part 2rdquo Journalof Guidance Control and Dynamics vol 27 no 4 pp 536ndash5442004
[19] C Luo and J-H Zheng ldquoSolar-sail attitude control based onmoving masses and roll stabilizer barsrdquo Journal of HarbinInstitute of Technology vol 43 no 3 pp 95ndash101 2011
[20] D Romagnoli and T Oehlschlagel ldquoHigh performance twodegrees of freedom attitude control for solar sailsrdquo Advances inSpace Research vol 48 no 11 pp 1869ndash1879 2011
[21] C Scholz D Romagnoli B Dachwald and S Theil ldquoPerfor-mance analysis of an attitude control system for solar sails usingsliding massesrdquo Advances in Space Research vol 48 no 11 pp1822ndash1835 2011
[22] A Bolle and C Circi ldquoSolar sail attitude control through in-plane moving massesrdquo Journal of Aerospace Engineering vol222 no 1 pp 81ndash94 2008
[23] M RotunnoM Basso A B Pome andM Sallusti ldquoA compari-son of robust attitude control techniques for a solar sail space-craftrdquo in Proceedings of the AIAA Guidance Navigation andControl Conference and Exhibit San Francisco Calif USA2005
[24] J Zhang K Zhai and T Wang ldquoControl of large angle maneu-vers for the flexible solar sailrdquo Science China Physics Mechanicsand Astronomy vol 54 no 4 pp 770ndash776 2011
[25] J Zhang andTWang ldquoCoupled attitude-orbit control of flexiblesolar sail for displaced solar orbitrdquo Journal of Spacecraft andRockets vol 50 no 3 pp 675ndash685 2013
[26] Q Li XMa and TWang ldquoReducedmodel for flexible solar saildynamicsrdquo Journal of Spacecraft and Rockets vol 48 no 3 pp446ndash453 2011
[27] M Polites J Kalmanson and D Mangus ldquoSolar sail attitudecontrol using small reaction wheels and magnetic torquersrdquoProceedings of the Institution of Mechanical Engineers G Journalof Aerospace Engineering vol 222 no 1 pp 53ndash62 2008
[28] H-T Cui J-H Luo J-H Feng and P-Y Cui ldquoAttitudecontrol of solar sail spacecraft with control boomrdquo Journal ofAstronautics vol 29 no 2 pp 560ndash566 2008
[29] E Mettler and S R Ploen ldquoSolar sail dynamics and controlusing a boom mounted bus articulated by a bi-state two-axisgimbal and reaction wheelsrdquo in Proceedings of the AIAAAASAstrodynamics Specialist Conference and Exhibit MontereyCalif USA August 2002
[30] J Luo X Li and J Feng ldquoPassive attitude control of solar sailspacecraftrdquo Flight Dynamics vol 26 no 5 pp 47ndash50 2008
[31] J Luo Study on attitude control of solar sail spaceraft [PhDthesis] School of Astronautics Harbin Institute of TechnologyHarbin China 2007
[32] D A Lawrence and S W Piggott ldquoIntegrated trajectory andattitude control for a four-vane solar sailrdquo in Proceedings ofthe AIAA Guidance Navigation and Control Conference andExhibit pp 2416ndash2431 San Francisco Calif USA August 2005
[33] E Mettler A B Acikmese and S R Ploen ldquoAttitude dynamicsand control of solar sails with articulated vanesrdquo in Proceedingsof the AIAA Guidance Navigation and Control Conference andExhibit pp 2396ndash2415 San Francisco Calif USA August 2005
[34] S N Adeli V J Lappas and B Wie ldquoA scalable bus-basedattitude control system for Solar Sailsrdquo Advances in SpaceResearch vol 48 no 11 pp 1836ndash1847 2011
[35] R Funase Y Shirasawa Y Mimasu et al ldquoOn-orbit verificationof fuel-free attitude control system for spinning solar sailutilizing solar radiation pressurerdquo Advances in Space Researchvol 48 no 11 pp 1740ndash1746 2011
[36] B Fu and F O Eke ldquoAttitude control methodology for largesolar sailsrdquo in AIAA Guidance Navigation and Control (GNC)Conference 2013
[37] J Liu N Cui F Shen and S Rong ldquoDynamics of highly-flexiblesolar sail subjected to various forcesrdquoActaAstronautica vol 103pp 55ndash72 2014
[38] J F Liu S Y Rong and J G Li ldquoAttitude dynamics modelingand control of large flexible solar sail spacecraftrdquo in Proceedingsof the 3rd International Symposium on Systems and Control inAeronautics and Astronautics (ISSCAA rsquo10) pp 243ndash247 IEEEPublications Piscataway NJ USA 2010
[39] S Gong H Baoyin and J Li ldquoCoupled attitude-orbit dynamicsand control for displaced solar orbitsrdquo Acta Astronautica vol65 no 5-6 pp 730ndash737 2009
Submit your manuscripts athttpwwwhindawicom
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
MathematicsJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Mathematical Problems in Engineering
Hindawi Publishing Corporationhttpwwwhindawicom
Differential EquationsInternational Journal of
Volume 2014
Applied MathematicsJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Probability and StatisticsHindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Journal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Mathematical PhysicsAdvances in
Complex AnalysisJournal of
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2 Mathematical Problems in Engineering
control actuators The validity of the ACS is demonstratedby numerical simulations [19] A high performance solar sailattitude controller is presented by employing sliding massesinside the supporting beams and its ability of performingtime efficient reorientation maneuvers is demonstrated [20]The proposed controller combines a feedforward and a feed-back controller the former is a fast response controller whilethe latter can be used to respond to unpredicted disturbances[21] The solar sail ACS presented in [22] includes themovement of the small control mass in the solar sail planeand the rotation of ballast with two masses at the extremitiesto realize the pitchyaw and roll control respectively
The robust attitude controllers are designed using 119867infinQFT and input shaping methods respectively to allow forthe uncertainties of inertia natural frequencies dampingand modal constants of solar sail The performances ofthe controllers are analyzed using the linear and nonlineardynamics respectively [23]The reduced dynamic model of aflexible solar sail with foreshortening deformation couplingwith its attitude and vibration is derived in [24ndash26] TheBang-Bang control scheme combining input shapingmethodis used to eliminate the vibration for a time optimal attitudemaneuver The attitude control system is proposed usingsmall reactionwheels andmagnetic torquers for a solar sail onlow earth orbit and the validity is demonstrated by numericalsimulation [27]
The dynamic model of the multibody solar sail withcontrol boom and reaction wheel is derived in [28 29] Thecontrollability and stability are analyzed and the proposedattitude control scheme is demonstrated The effectiveness ofthe solar sail attitude control system employing four controlvanes is demonstrated by simulating deep space explorationmissions [30]The dynamics is derived and the controllabilityand stability are analyzed for solar sail with control boomreaction wheel and control vanes The effectiveness of theproposed ACS is demonstrated for the solar sail with cmcpoffset [31]
The trajectory tracking control is accomplished by usingsolar sail with four control vanes to control the solar angleof the sail The resultant sailcraft thrust vector amplitudecan be controlled by the additional degree of freedom ofthe control vanes [32] A robust nonlinear attitude controlalgorithm is developed for solar sail with four control vaneswith single degree-of-freedom rejecting disturbances by cmand cp offset The control allocation is studied by usingnonlinear programming [33]
The novel and practical ACS for solar sail is continuouslyproposed A bus-basedACS is presented in [34] including thehighly reflective panel actuator for roll control located at thefree end of the bus-based boom and the tether control massactuator for yawpitch control running along the bus-basedboomThis scalableACS can decrease the risk and complexityinvolved in the design of the sail deployment subsystem TheACS designed for IKAROS is muchmore novel and practicalThe ACS utilizes the reflectivity control device (RCD) torealize the yawpitch control for the spinning solar power sailIt is a fuel-free and oscillation-free ACS [35] But this ACSwill fail to generate the required torques when it is edge tothe sun (the sun angle approaches 90∘) And recently a novel
attitude control method is proposed in [36] The requiredtorque can be generated by adjusting the position of a wingtip along the boomThismethod presents an effective attitudeapproach for large sailcraft But the exact shape of the films isdifficult to determine
The dynamic modeling and control for the flexible sail-craft are studied in [37 38] In [37] the vibration equationsfor the axial and transverse deformations are establishedby considering the geometrical nonlinearity of the sailcraftBut merely the vibration analysis is insufficient for theorbiting sailcraft experiencing attitude motion The coupledattitudevibration analysis is required In [38] the coupledattitudevibration dynamics is established and the solvingprocess is also presented The controller is designed by usingthe Bang-Bang based PD theory The effectiveness of thecontroller is verified by numerical simulation But the largedeformation of the structure is not considered
The coupled attitude-orbit dynamics of a solar sail isstudied in [39]The equilibrium point of the dynamics can beobtained by designing the inertia of the sail and the stabilityof the equilibrium point is analyzed through a linearization
The attitude dynamics and control are studied thoroughlyin above references The ACS for solar sail by using actu-ators such as control boom and control vanes or by usingmeans such as spinning and translatingtilting sail panels arestudied Little research concerns attitude dynamic modelingwith highly flexible structure and vibration modeling withgeometrical nonlinearity and the attitudevibration controlBut this is a problem worth studying
This paper establishes the attitude dynamics for the largeflexible solar sail with control vanes control boom and slid-ing masses And the vibration equations are also presentedThe LQR and optimal PI based controllers are designed forthe attitudevibration dynamics By theoretical analysis andsimulation the controller with better performance is selectedand some discussions are presented And the differencesbetween the dynamics models with and without the geomet-rical nonlinearity are also inserted and analyzed
2 Attitude Dynamics
In this section the configuration and structure of the sailcraftare presented The related reference frames and coordinatetransformations are given The kinetic and gravitationalpotential energies and the generalized loads are obtainedTheLagrange equation method is adopted to derive the attitudedynamics with control vanes control boom and slidingmasses The attitude dynamics is an important part of thecoupled attitudevibration dynamics
21 The Configuration and Structure The configuration andstructure of the infinite-point connected square solar sailadopted in this paper are shown in Figure 1The ACS consistsof the control boom sliding masses and control vanes Thefour supporting beams are the most rigid component Thestiffness of the four triangular membranes can be neglectedby comparing with the supporting beams thus the kinetic
Mathematical Problems in Engineering 3
Controlvanes
Payload
Slidingmasses
Controlboom
Figure 1 The configuration and structure of solar sail
energy caused by vibrations and elastic potential energy ofthe membrane structure can be neglected
The paper mainly focuses on the dynamics for highlyflexible solar sail The following assumptions are made tosimplify the problems
(1) The detailed vibration of the membrane is neglectedin this paper as most of the kinetic energy causedby vibrations is by the vibrations of the supportingbeams
(2) The masses of control vanes and control boom areneglected We regard the control vanes and controlboom as rigid bodies
(3) The deformation of the structure is not affected by thethermal loads and the wrinkle effect is also neglected
(4) The torque by the cmcp offset is the disturbancetorque And other disturbance torques (such as grav-ity gradient torque) are neglected
22 The Reference Frames and Coordinate Transformations
The Inertial Reference Frame (E119868X119868Y119868Z119868120587
119868) It is an inertial
reference frame for solar sail attitude and orbital motionE119868X119868is in the vernal equinox direction E
119868Z119868is in the Earthrsquos
rotation axis perpendicular to equatorial plane E119868Y119868is in the
equatorial plane and finishes the ldquotriadrdquo of unit vectors Theunit vector is e
119868= (i
119868 j119868 k
119868)119879
The body reference frames of solar sail (O119874x119887y119887z119887120587
119887)
and control vanes (C119894x119894y119894z119894120587
119894 119894 = 1 2 3 4) O
119874is the geo-
metric center of the film O119874x119887is perpendicular to the film
pointing to the payload sideO119874y119887andO
119874z119887are in the plane
of the sail C119894is the geometric center of the 119894th control vane
When there exist no relative motions between solar sail andcontrol vanes120587
119894is coincident with120587
119887The related frames can
be found in Figure 2The attitude motion is described in Euler angles using
the yaw-roll-pitch notation In this notation a three-elementvector Θ = [120595 120593 120579]
119879 is used to describe the attitude of solarsail with respect to the inertial frame The transformation
EI
ZI
YI
XI
yb
zb
1
2
C2
C1
x2
z2
z1
y1
x1
y2 OO
xb
12
3
3
44
C4
C3
x3
y3z3
z4
y4x4
Figure 2 120587119868
120587119887
and 120587119894
Sun line
EI
OO
rO
ZI
XI
YI
ZI z998400
120595
120595
XI
EI(O)
Z998400998400998400(zb)
Z998400998400120593
120593
120579
120579
x998400x998400998400 x998400998400998400(xb)
y998400998400 y998400998400998400(yb)y998400
YI
The orbit
Figure 3 The orbit and the attitude motion
from 120587119868to 120587
119887can be realized by a 3-1-2 rotation as shown
in Figure 3 (right) with the following rotation matrix
C119887119868
= R2(120579)R
1(120593)R
3(120595)
= [
[
119888120579119888120595 minus 119904120579119904120593119904120595 119888120579119904120595 + 119904120579119904120593119888120595 minus119904120579119888120593
minus119888120593119904120595 119888120593119888120595 119904120593
119904120579119888120595 + 119888120579119904120593119904120595 119904120579119904120595 minus 119888120579119904120593119888120595 119888120579119888120593
]
]
(1)
where
R3(120595) = [
[
cos120595 sin120595 0
minus sin120595 cos120595 0
0 0 1
]
]
R1(120593) = [
[
1 0 0
0 cos120593 sin120593
0 minus sin120593 cos120593]
]
R2(120579) = [
[
cos 120579 0 minus sin 120579
0 1 0
sin 120579 0 cos 120579]
]
(2)
120595 120593 and 120579 are yaw roll and pitch angles respectively 119888120579 and119904120579 are short for cos 120579 and sin 120579
And the transformation from 120587119894to 120587
119887can be obtained as
119862119887119894= [
[
119888120579119894119888120595
119894minus 119904120579
119894119904120593
119894119904120595
119894119888120579
119894119904120595
119894+ 119904120579
119894119904120593
119894119888120595
119894minus119904120579
119894119888120593
119894
minus119888120593119894119904120595
119894119888120593
119894119888120595
119894119904120593
119894
119904120579119894119888120595
119894+ 119888120579
119894119904120593
119894119904120595
119894119904120579
119894119904120595
119894minus 119888120579
119894119904120593
119894119888120595
119894119888120579
119894119888120593
119894
]
]
(3)
The attitude control can be performed by varying 120595119894 120593
119894 and
120579119894
4 Mathematical Problems in Engineering
OO
xb mp
14
1205821
zbyb
dm32
3
1205822
EI
p
ch1
h2
31205883
O m3
r
r r
rr
R R
Figure 4 The positions and orientations of the components
23 The Positions and Velocities of the Components Theabsolute position of an arbitrary point on the supportingbeams sliding masses and payload are given in Figure 4where r
119888119894(119894 = 1 2 3 4) is the position vector of the cp of
the 119894th control vane The cp of each control vane is assumed
to locate at the free end of the supporting beams r119901is the
position vector of the payload O119874is the origin of 120587
119887 The
positions and velocities of an arbitrary point on each supportbeam can be obtained as
R119898119894
= R119874+ r
119894+ 120588
119894 k
119898119894= R
119874+∘
120588119894
+ 120596 times (r119894+ 120588
119894) (4)
whereR119898119894(v
119898119894) is the position (velocity) vector of an arbitrary
point on the deformed supporting beam and r119894is the position
vector of an arbitrary point on the undeformed beam relativetoO
119874R
119874(R
119874= v
119874) is the orbital position and velocity of the
sailcraft 120588119894is the transverse deformation of an arbitrary point
on the supporting beam (sdot) is the first time derivatives withrespect to 120587
119868and (∘) is the first time derivatives with respect
to 120587119887 120596 is the angular velocity of solar sail expressed as
[
[
120596119909
120596119910
120596119911
]
]119887
= [
[
cos 120579 minus sin 120579 cos120593120579 + sin120593
sin 120579 + cos 120579 cos120593]
]
(5)
If the orbital motion and its influence on attitude motionare neglected we have
R1198983
= r3+120588
3= [120588
3119909 120588
3119910 119911
3]119879
R1198981
= r1+ 120588
1= [120588
1119909 120588
1119910 119911
1]119879
R1198982
= r2+ 120588
2= [120588
2119909 119910
2 120588
2119911]119879
R1198984
= r4+ 120588
4= [120588
4119909 119910
4 120588
4119911]119879
(6)
R1198983
=∘
1205883
+ 120596 times (r3+ 120588
3) =
[[
[
1205883119909
1205883119910
0
]]
]
+[[
[
cos 120579 minus sin 120579 cos120593120579 + sin120593
sin 120579 + cos 120579 cos120593
]]
]
times [
[
1205883119909
1205883119910
1199113
]
]
=
[[[
[
1205883119909
+ 1199113
120579 + 1199113 sin120593 minus 120588
3119910 sin 120579 minus 120588
3119910 cos 120579 cos120593
1205883119910
+ 1205883119909 sin 120579 + 120588
3119909 cos 120579 cos120593 minus 119911
3 cos 120579 + 119911
3 sin 120579 cos120593
1205883119910 cos 120579 minus 120588
3119910 sin 120579 cos120593 minus 120588
3119909
120579 minus 1205883119909 sin120593
]]]
]
(7)
R1198981
=∘
1205881
+ 120596 times (r1+ 120588
1) =
[[
[
1205881119909
1205881119910
0
]]
]
+[[
[
cos 120579 minus sin 120579 cos120593120579 + sin120593
sin 120579 + cos 120579 cos120593
]]
]
times [
[
1205881119909
1205881119910
1199111
]
]
=
[[[
[
1205881119909
+ 1199111
120579 + 1199111 sin120593 minus 120588
1119910 sin 120579 minus 120588
1119910 cos 120579 cos120593
1205881119910
+ 1205881119909 sin 120579 + 120588
1119909 cos 120579 cos120593 minus 119911
1 cos 120579 + 119911
1 sin 120579 cos120593
1205881119910 cos 120579 minus 120588
1119910 sin 120579 cos120593 minus 120588
1119909
120579 minus 1205881119909 sin120593
]]]
]
(8)
R1198982
=∘
1205882
+ 120596 times (r2+ 120588
2) =
[[
[
1205882119909
0
1205882119911
]]
]
+[[
[
cos 120579 minus sin 120579 cos120593120579 + sin120593
sin 120579 + cos 120579 cos120593
]]
]
times [
[
1205882119909
1199102
1205882119911
]
]
=[[
[
1205882119909
+ 1205882119911
120579 + 1205882119911 sin120593 minus 119910
2 sin 120579 minus 119910
2 cos 120579 cos120593
1205882119909 sin 120579 + 120588
2119909 cos 120579 cos120593 minus 120588
2119911 cos 120579 + 120588
2119911 sin 120579 cos120593
1205882119911
+ 1199102 cos 120579 minus 119910
2 sin 120579 cos120593 minus 120588
2119909
120579 minus 1205882119909 sin120593
]]
]
(9)
Mathematical Problems in Engineering 5
R1198984
=∘
1205884
+ 120596 times (r4+ 120588
4) = [
[
1205884119909
0
1205884119911
]
]
+[[
[
cos 120579 minus sin 120579 cos120593120579 + sin120593
sin 120579 + cos 120579 cos120593
]]
]
times [
[
1205884119909
1199104
1205884119911
]
]
=[[
[
1205884119909
+ 1205884119911
120579 + 1205884119911 sin120593 minus 119910
4 sin 120579 minus 119910
4 cos 120579 cos120593
1205884119909 sin 120579 + 120588
4119909 cos 120579 cos120593 minus 120588
4119911 cos 120579 + 120588
4119911 sin 120579 cos120593
1205884119911
+ 1199104 cos 120579 minus 119910
4 sin 120579 cos120593 minus 120588
4119909
120579 minus 1205884119909 sin120593
]]
]
(10)
The components of the position and velocity vectors of anarbitrary point on the supporting beam can be computed byusing the above five equations
In Figure 4 1205821and 120582
2are the boom tilt and azimuth
angles relative to the sailcraft body axes respectively Thecomponents of r
119901can be expressed as follows by using these
two angles
r119901=10038161003816100381610038161003816r119901
10038161003816100381610038161003816cos 120582
1i119887+10038161003816100381610038161003816r119901
10038161003816100381610038161003816sin 120582
1cos 120582
2j119887+10038161003816100381610038161003816r119901
10038161003816100381610038161003816sin 120582
1sin 120582
2k119887
(11)
The position and velocity vectors of the payload can beobtained as
R119874119901
= R119874+ r
119901 k
119874119901= k
119874+ r
119901 (12)
where r119901=∘r119901+ 120596 times r
119901 And ∘r
119901can be expressed as
∘r119901= minus
10038161003816100381610038161003816r119901
100381610038161003816100381610038161sin 120582
1i119887+10038161003816100381610038161003816r119901
10038161003816100381610038161003816
times (1cos 120582
1cos 120582
2minus
2sin 120582
1sin 120582
2) j
119887
+10038161003816100381610038161003816r119901
10038161003816100381610038161003816(
1cos 120582
1sin 120582
2+
2sin 120582
1cos 120582
2) k
119887
(13)
Thus r119901can be obtained as
r119901= [[minus119897
1199011sin 120582
1+ 119897
119901sin 120582
1sin 120582
2( 120579 + sin120593)
minus 119897119901sin 120582
1cos 120582
2( sin 120579 + cos 120579 cos120593)]
times [119897119901(
1cos 120582
1cos 120582
2minus
2sin 120582
1sin 120582
2)
+ 119897119901cos 120582
1( sin 120579 + cos 120579 cos120593)
minus 119897119901sin 120582
1sin 120582
2( cos 120579 minus sin 120579 cos120593)]
times 119897119901(
1cos 120582
1sin 120582
2+
2sin 120582
1cos 120582
2)
+ 119897119901sin 120582
1cos 120582
2( cos 120579 minus sin 120579 cos120593)
minus 119897119901cos 120582
1( 120579 + sin120593)]
(14)
The position vectors of the two sliding masses can beobtained as
Rℎ119895
= R119874+ r
ℎ119895+ 120588
ℎ119895
kℎ2
= k119874+∘rℎ119895
+∘
120588ℎ119895
+ 120596 times (rℎ119895
+ 120588ℎ119895)
(119895 = 1 2)
(15)
If the orbital motion and its influence on attitude motioncan be neglected then the position and velocity vectors canbe obtained as follows
Rℎ2
= rℎ2
+ 120588ℎ2
= [120588ℎ2119909
120588ℎ2119910
119911ℎ2]119879
Rℎ1
= rℎ1
+ 120588ℎ1
= [120588ℎ1119909
119910ℎ1 120588
ℎ1119911]119879
Rℎ2
=[[
[
120588ℎ2119909
+ 119911ℎ2
( 120579 + sin120593) minus 120588ℎ2119910
( sin 120579 + cos 120579 cos120593)120588ℎ2119910
+ 120588ℎ2119909
( sin 120579 + cos 120579 cos120593) minus 119911ℎ2
( cos 120579 minus sin 120579 cos120593)ℎ2
+ 120588ℎ2119910
( cos 120579 minus sin 120579 cos120593) minus 120588ℎ2119909
( 120579 + sin120593)
]]
]
Rℎ1
=[[
[
120588ℎ1119909
+ 120588ℎ1119911
( 120579 + sin120593) minus 119910ℎ1
( sin 120579 + cos 120579 cos120593)119910ℎ1
+ 120588ℎ1119909
( sin 120579 + cos 120579 cos120593) minus 120588ℎ1119911
( cos 120579 minus sin 120579 cos120593)120588ℎ1119911
+ 119910ℎ1
( cos 120579 minus sin 120579 cos120593) minus 120588ℎ1119909
( 120579 + sin120593)
]]
]
(16)
6 Mathematical Problems in Engineering
24 The Kinetic Energy The kinetic energy of the sail systemcan be obtained by neglecting the orbital motion and itsinfluence on attitude motion Consider
1198791198983
=1
2119898
119897int
119897
0
[∘
1205883
+ 120596 times (r3+ 120588
3)] sdot [
∘
1205883
+ 120596 times (r3+ 120588
3)] 119889119911
1198791198981
=1
2119898
119897int
0
minus119897
[∘
1205881
+ 120596 times (r1+ 120588
1)]
sdot [∘
1205881
+ 120596 times (r1+ 120588
1)] 119889119911
1198791198982
=1
2119898
119897int
119897
0
[∘
1205882
+ 120596 times (r2+ 120588
2)] sdot [
∘
1205882
+ 120596 times (r2+ 120588
2)] 119889119910
1198791198984
=1
2119898
119897int
0
minus119897
[∘
1205884
+ 120596 times (r4+ 120588
4)] sdot [
∘
1205884
+ 120596 times (r4+ 120588
4)] 119889119910
(17)
The above equations can be rewritten as
119879119898
=1
2120596 sdot J sdot 120596
+1
2119898
119897int
119897
0
2∘
1205883
sdot (120596 times r3) + (120596 times 120588
3) sdot (120596 times 120588
3)
+ 2 (120596 times r3) sdot (120596 times 120588
3) 119889119911
+1
2119898
119897int
0
minus119897
2∘
1205881
sdot (120596 times r1) + (120596 times 120588
1) sdot (120596 times 120588
1)
+ 2 (120596 times r1) sdot (120596 times 120588
1) 119889119911
+1
2119898
119897int
119897
0
2∘
1205882
sdot (120596 times r2) + (120596 times 120588
2) sdot (120596 times 120588
2)
+ 2 (120596 times r2) sdot (120596 times 120588
2) 119889119910
+1
2119898
119897int
0
minus119897
2∘
1205884
sdot (120596 times r4) + (120596 times 120588
4) sdot (120596 times 120588
4)
+ 2 (120596 times r4) sdot (120596 times 120588
4) + (120596 times r
4)
sdot (120596 times r4) 119889119910
(18)
where J = sum4
119895=1
J119898119895
is the moment of inertia of sail systemJ119898119895
(119895 = 1ndash4) is the moment of inertia of the 119895th sail sys-tem and the expression of J can be expressed as J = diag[119869
119909
119869119910 119869
119911] inO
119874x119887y119887z119887
The kinetic energy of the payload is
119879119901=
1
2119898
119901
10038161003816100381610038161003816r119901
10038161003816100381610038161003816
2
=1
2119898
119901[minus119897
1199011sin 120582
1+ 119897
119901sin 120582
1sin 120582
2( 120579 + sin120593)
minus 119897119901sin 120582
1cos 120582
2( sin 120579 + cos 120579 cos120593)]
2
+1
2119898
119901[119897119901(
1cos 120582
1cos 120582
2minus
2sin 120582
1sin 120582
2)
+ 119897119901cos 120582
1( sin 120579 + cos 120579 cos120593)
minus 119897119901sin 120582
1cos 120582
2( cos 120579 minus sin 120579 cos120593)]
2
+1
2119898
119901[119897119901(
1cos 120582
1sin 120582
2+
2sin 120582
1cos 120582
2)
+ 119897119901sin 120582
1cos 120582
2( cos 120579 minus sin 120579 cos120593)
minus 119897119901cos 120582
1( 120579 + sin120593)]
2
(19)
The kinetic energy of the sliding masses can be obtainedas follows by neglecting the orbital motion and its influenceon attitude control
119879ℎ1
=1
2119898
ℎ1[ ( 120588
ℎ1119909+ 120579120588
ℎ1119911+ 120588
ℎ1119911sin120593
minus 119910ℎ1sin 120579 minus 119910
ℎ1cos 120579 cos120593)
2
]
+1
2119898
ℎ1[( 119910
ℎ1+ 120588
ℎ1119909sin 120579 + 120588
ℎ1119909cos 120579 cos120593
minus 120588ℎ1119911
cos 120579 + 120588ℎ1119911
sin 120579 cos120593)2]
+1
2119898
ℎ1[( 120588
ℎ1119911+ 119910
ℎ1cos 120579 minus 119910
ℎ1sin 120579 cos120593
minus 120579120588ℎ1119909
+ 120588ℎ1119909
sin120593)2
]
119879ℎ2
=1
2119898
ℎ2[( 120588
ℎ2119909+ 120579119911
ℎ2+ 119911
ℎ2sin120593 minus 120588
ℎ2119910sin 120579
minus 120588ℎ2119910
cos 120579 cos120593)2
]
+1
2119898
ℎ2[( 120588
ℎ2119910+ 120588
ℎ2119909sin 120579 + 120588
ℎ2119909cos 120579 cos120593
minus 119911ℎ2cos 120579 + 119911
ℎ2sin 120579 cos120593)
2
]
+1
2119898
ℎ2[(
ℎ2+ 120588
ℎ2119910cos 120579 minus 120588
ℎ2119910sin 120579 cos120593
minus 120579120588ℎ2119909
minus 120588ℎ2119909
sin120593)2
]
(20)
25 The Gravitational Potential Energy The gravitationalpotential energies of the sail system 119880
119892119891 payload 119880
119892119901 and
sliding masses 119880119892ℎ1
119880119892ℎ2
can be obtained as
119880119892119891
= minus
120583119898119891
1003816100381610038161003816R119874
1003816100381610038161003816
119880119892119901
= minus
120583119898119901
10038161003816100381610038161003816R119874+ r
119901
10038161003816100381610038161003816
119880119892ℎ1
= minus120583119898
ℎ1
1003816100381610038161003816R119874+ r
ℎ1
1003816100381610038161003816
119880119892ℎ2
= minus120583119898
ℎ2
1003816100381610038161003816R119874+ r
ℎ2
1003816100381610038161003816
(21)
Mathematical Problems in Engineering 7
26 The Generalized Forces The components of the sunlightunit vector S can be obtained as follows by referring toFigure 3 (left) in 120587
119868
S = j119868= [1 0 0]
119879
119868
(22)
Based on the abovementioned equations the componentsof S in 120587
119887can be obtained as
S = C119887119868[1 0 0]
119879
119868
= [119878119909
119878119910
119878119911]119879
119887
(23)
The resultant SRP force can be simply modeled as followsfor a perfectly reflective control vane
F119894= 120578119875119860
119862119894(S sdot n
119862119894)2 n
119862119894= 119865
119862119894cos2120572
119862119894n119862119894 (24)
where 120578 is the overall sail-thrust coefficient (120578max = 2) 119875 =
4563 times 10minus6 Nm2 119860
119862119894is the area of the 119894th control vane
119865119862119894
= 120578119875119860119862119894is themaximumcontrol vane thrust andn
119862119894= i
119894
is the unit normal vector of the control vaneThe componentsof n
119862119894in 120587
119887can be written as
n119862119894
= C119887119894[1 0 0]
119879
119894
= [119878119909119894
119878119910119894
119878119911119894]119879
119887
(25)
The control torque by the 119894th control vane can beexpressed as
M119894= L
119894times F
119894 (26)
In fact L119894and F
119894are dependent on the deformations of
the supporting beams and control vanes In this paper it isassumed thatL
119894andF
119894are not influenced by the deformations
of the structure when computing the control torque by thecontrol vanes Thus L
119894and F
119894can be expressed as
L1= [0 0 minus119897]
119879
L2= [0 119897 0]
119879
L3= [0 0 119897]
119879
L4= [0 minus119897 0]
119879
F119894= 120578119875119860
119862119894([119878
119909119878119910
119878119911]119887
sdot [119878119909119894
119878119910119894
119878119911119894]119879
119887
)
2
[119878119909119894
119878119910119894
119878119911119894]119879
119887
(27)
The force of each control vane can be written as
F119894= (119865
119862119894cos2120572
119862119894)C
119887119894[1 0 0]
119879
119894
= (119865119862119894cos2120572
119862119894) [119878
119909119894119878119910119894
119878119911119894]119879
119887
(28)
where 120572119862119894
is the sun angle of the 119894th control vane that canbe measured by the sun sensor And the components of thecontrol torques can be obtained as
M1198881
= (1198651198621cos2120572
1198621)[
[
0
0
minus119897
]
]
times (C1198871
[
[
1
0
0
]
]
)
= (1198651198621cos2120572
1198621)
times [
[
minus119897 cos1205931sin120595
1
minus119897 (cos 1205791cos120595
1minus sin 120579
1sin120593
1sin120595
1)
0
]
]
M1198882
= (1198651198622cos2120572
1198622)
times [
[
119897 (sin 1205792cos120595
2+ cos 120579
2sin120593
2sin120595
2)
0
minus119897 (cos 1205792cos120595
2minus sin 120579
2sin120593
2sin120595
2)
]
]
M1198883
= (1198651198623cos2120572
1198623)
times [
[
119897 cos1205933sin120595
3
119897 (cos 1205793cos120595
3minus sin 120579
3sin120593
3sin120595
3)
0
]
]
M1198884
= (1198651198624cos2120572
1198624)
times [
[
minus119897 (sin 1205794cos120595
4+ cos 120579
4sin120593
4sin120595
4)
0
119897 (cos 1205794cos120595
4minus sin 120579
4sin120593
4sin120595
4)
]
]
(29)
27 Attitude Dynamics of Solar Sail The attitude dynamicscan be obtained by using the Lagrange equation method as
119889
119889119905(
120597119871
120597 119902119895
) minus120597119871
120597119902119895
= 119876119895 (30)
where 119871 is the Lagrange function 119902119895(119895 = 1ndash3) is the vector
of the generalized coordinates and 119876119895is the vector of the
generalized force 119871 can be computed as
119871 = 119879 minus 119880 =
4
sum
119894=1
119879119898119894
+ 119879119901+
2
sum
119895=1
119879ℎ119895
minus (119880119892119891
+ 119880119892119901
+
2
sum
119895=1
119880119892ℎ119895
)
(31)
where 119879119898119894 119879
119901 and 119879
ℎ119895are the kinetic energies of the
supporting beams payload and sliding masses respectively119880119892119891 119880
119892119901 and 119880
119892ℎ119895are the gravitational potential energies of
the sail system payload and sliding masses respectively
8 Mathematical Problems in Engineering
OOx
y
z
FCFCy
FCx
FCz
mh
q(x)
Figure 5 The vibration model
120590
120590e
120590120592
120590
Figure 6 The viscoelastic model
3 The Vibration of Solar Sail
The mechanical and material models of the sailcraft aregivenThe displacement filed stress and strain are presentedbased on the Euler beam assumptionThe Lagrange equationmethod is adopted to derive the vibration equations withlarge deformations based on the calculations of kineticenergies and works done by the external loads
31 The Mechanical Model The body frame O119874xyz is estab-
lished to describe the vibration (see Figure 5) F119862is the force
vector generated by the control vane used located at the tip ofthe supporting beam 119865
119862119909 119865
119862119910 and 119865
119862119911are the components
inO119874xyz 119902(119909) is the distributed load caused by SRP
32 The Material Model The carbon fibre enforced compos-ite material is used to construct the inflatable deploymentsupporting beam The model of the viscoelastic material canbe represented in Figure 6
The total stress is the summation of the elastic and viscousstresses It can be expressed as
120590 = 120590119890
+ 120590120592
= 119864120576 + 119888119887
120576 (32)
where 120590 120590119890 and 120590
120592 are the total elastic and viscous stressrespectively And 119864 is Youngrsquos modulus 120576 ( 120576) is the strain(strain rate) and 119888
119887is the coefficient of the internal damping
expressed as 119864120578119887 120578
119887is the proportionality constant of the
internal damping The dimensions of 119888119887and 120578
119887are N lowast sm2
and s respectively
OO x
y The support beam
Z
Figure 7 The schematic diagram of solar sail supporting beamdeformation
33 The Displacement Field Stress and Strain The deforma-tion of a spatial solar sail supporting beam is presented inFigure 7
The spatial displacement fields for supporting beam are as
119906 (119909 119910 119911 119905) = 1199060(119909 119905) minus 119910
120597V0
120597119909minus 119911
1205971199080
120597119909
V (119909 119910 119911 119905) = V0(119909 119905)
119908 (119909 119910 119911 119905) = 1199080(119909 119905)
(33)
119906(119909 119910 119911 119905) V(119909 119910 119911 119905) and 119908(119909 119910 119911 119905) are the displace-ments along 119909 119910 and 119911 directions respectively 119906
0(119909 119905)
V0(119909 119905) and 119908
0(119909 119905) are the axial and transverse displace-
ments of an arbitrary point on the neutral axisBy using Green strain definition von Karmanrsquos nonlinear
strain-displacement relationships based on assumptions oflarge deflections moderate rotations and small strains for a3D supporting beam are given as follows together with thestrain rate and normal stress
120576119909119909
=120597119906
0
120597119909+1
2(120597V
0
120597119909)
2
minus 1199101205972V
0
1205971199092
+1
2(120597119908
0
120597119909)
2
minus 1199111205972
1199080
1205971199092
120576119909119909
=120597
0
120597119909+(
120597V0
120597119909)(
120597V0
120597119909) minus 119910
1205972V
0
1205971199092
+(120597119908
0
120597119909)(
1205970
120597119909)
minus 1199111205972
0
1205971199092
120590119909119909
= 119864[120597119906
0
120597119909+1
2(120597V
0
120597119909)
2
minus 1199101205972V
0
1205971199092
+1
2(120597119908
0
120597119909)
2
minus 1199111205972
1199080
1205971199092
]
+ 119864120578119887(120597
0
120597119909+(
120597V0
120597119909)(
120597V0
120597119909) minus 119910
1205972V
0
1205971199092
+(120597119908
0
120597119909)(
1205970
120597119909) minus 119911
1205972
0
1205971199092
)
(34)
Mathematical Problems in Engineering 9
The single underlined terms in the preceding equationindicate the contribution by the geometrical nonlinearityThedynamics models and corresponding numerical simulationwithout considering the geometrical nonlinearity can beobtained and carried out by neglecting these terms
34 The Energies and Works Done by External Forces Thestrain energy can be derived as
119880119894=
1
2int
119897
0
119860119909119909
[120597119906
0
120597119909+
1
2(120597V
0
120597119909)
2
+1
2(120597119908
0
120597119909)
2
]
2
+ 119863119909119909
1205972V
0
1205971199092
+ 119863119909119909
1205972
1199080
1205971199092
119889119909
(35)
For an isotropic support beam the extensional stiffness119860
119909119909and bending stiffness119863
119909119909can be computed as
119860119909119909
= int119860
119864119889119860 119863119909119909
= int119860
1198641199112
119889119860 = int119860
1198641199102
119889119860 (36)
The dissipation function is as
Ψ119902=
1
2int
119897
0
[119860119909119909120578119887(120597
0
120597119909)
2
+ 119863119909119909120578119887(1205972V
0
1205971199092
)
2
+ 119863119909119909120578119887(1205972
0
1205971199092
)
2
]119889119909
(37)
The kinetic energy for the support beam is as
119879119890=
1
2int
119897
0
[119868119860(120597119906
0
120597119905)
2
+ 119868119860(120597119908
0
120597119905)
2
+ 119868119863(1205972
1199080
120597119909120597119905)
2
+ 119868119860(120597V
0
120597119905)
2
+ 119868119863(
1205972V
0
120597119909120597119905)
2
]119889119909
(38)
where 119868119860and 119868
119863are integration constant for the support
beam expressed as
119868119860= int
119860
120588119889119860 = 120588119860 119868119863= int
119860
1205881199112
119889119860 = int119860
1205881199102
119889119860 (39)
And the work done by the external force can be obtainedas119882 = 119865
119862119911sdot 119908 (119909
119888 119905) + 119865
119862119910sdot V (119909
119888 119905) + 119898
ℎ119886ℎ119910
(119909ℎ 119905) V (119909
ℎ 119905)
+ 119898ℎ119886ℎ119911
(119909ℎ 119905) 119908 (119909
ℎ 119905) + int
119897
0
119902 (119909) V (119909 119905) 119889119909
(40)where 119909
119888represents the position of the support beam
119908(119909119888 119905) V(119909
119888 119905) are the displacements along 119911 and 119910 direc-
tions respectively and the corresponding loads 119865119862119911 119865
119862119910are
known functions 119909ℎ 119897 and V
ℎare the position coordinate of
the sliding mass the length of the support beam and theconstant-velocity of the sliding mass The dynamic responseis studied only during the period [0 119897V
ℎ] 119898
ℎis the mass
and 119886ℎ119910(119909
ℎ 119905) and 119886
ℎ119911(119909
ℎ 119905) are the components of the
acceleration for a material point on the support beam theslidingmass just arrived at And the corresponding transversedeflections are 119908(119909
ℎ 119905) and V(119909
ℎ 119905) respectively
35 The Assumed Modes Method The axial displacement1199060(119909 119905) and the transverse deflections V
0(119909 119905) and119908
0(119909 119905) can
be represented as follows by considering the assumed modesmethod
1199060(119909 119905) =
infin
sum
119894=1
119880119894(119909)119880
119894(119905)
V0(119909 119905) =
infin
sum
119895=1
119881119895(119909) 119881
119895(119905)
1199080(119909 119905) =
infin
sum
119896=1
119882119896(119909)119882
119896(119905)
(41)
where 119880119894(119905) 119881
119895(119905) and 119882
119896(119905) are the time-dependent gen-
eralized coordinates and 119880119894(119909) 119881
119895(119909) and 119882
119896(119909) are the
assumedmodes For assumedmodemethod themode shapefunctions should satisfy the following requirements in thispaper
119880119894(119909)
1003816100381610038161003816119909=0= 0 119881
119895(119909)
10038161003816100381610038161003816119909=0= 0 119882
119896(119909)
1003816100381610038161003816119909=0= 0
1198811015840
119895
(119909)10038161003816100381610038161003816119909=0
= 0 1198821015840
119896
(119909)10038161003816100381610038161003816119909=0
= 0
(42)
The following first two assumed modes satisfying theassumed mode principle are used in this paper
1198801(119909) =
119909
119897 119880
2(119909) = (
119909
119897)
2
1198811(119909) = (
119909
119897)
2
1198812(119909) = (
119909
119897)
3
1198821(119909) = (
119909
119897)
2
1198822(119909) = (
119909
119897)
3
(43)
With the help of the assumedmodes the detailed expres-sions of 119880
119894 119879
119890119882
119911 and Ψ
119902can be obtained as
119880119894=
9
2
119860119909119909
1198973(119881
2
2
+ 1198822
2
)2
+27
4
119860119909119909
1198973(119881
11198812+ 119882
1119882
2)
times (1198812
2
+ 1198822
2
)
+18
7
119860119909119909
1198973[(119881
2
1
+ 1198822
1
) (1198812
2
+ 1198822
2
) + (11988111198812+ 119882
1119882
2)2
]
+119860
119909119909
1198973[3
2119897119880
2(119881
2
2
+ 1198822
2
) + (1198812
1
+ 1198822
1
)
times (11988111198812+ 119882
1119882
2)]
10 Mathematical Problems in Engineering
+1
10
119860119909119909
1198973[9119880
1119897 (119881
2
2
+ 1198822
2
) + 241198802119897 (119881
11198812+ 119882
1119882
2)
+ 4 (1198812
1
+ 1198822
1
)2
]
+119860
119909119909
1198972[3
21198801(119881
11198812+ 119882
1119882
2) + 119880
2(119881
2
1
+ 1198822
1
)]
+6119863
119909119909119881
2
2
1198973+ 119860
119909119909(2119880
1119881
2
1
31198972+
21198801119882
2
1
31198972+
21198802
2
3119897)
+6119863
119909119909119882
2
2
1198973+
611986311990911990911988111198812
1198973+
11986011990911990911988011198802
119897+
6119863119909119909119882
1119882
2
1198973
+119860
119909119909119880
2
1
2119897+
2119863119909119909119881
2
1
1198973+
2119863119909119909119882
2
1
1198973
119879119890=
1
14(119897119868
119860
2
2
+ 119897119868119860
2
2
) +1
6(119897119868
119860
1
2+ 119897119868
11986012)
+1
10(119897119868
119860
2
2
+ 119897119868119860
2
1
+9119868
119863
2
2
119897+ 119897119868
119860
2
1
+9119868
119863
2
2
119897)
+1
4(119897119868
11986012+
6119868119863
1
2
119897+
611986811986312
119897)
+1
6(119897119868
119860
2
1
+4119868
119863
2
1
119897+
4119868119863
2
1
119897)
119882119911= 119865
119862119911sdot [119882
1(119905) + 119882
2(119905)] + 119865
119862119910sdot [119881
1(119905) + 119881
2(119905)]
+ 119898ℎ[2V2
ℎ
1198972sdot 119881
1(119905) +
4V2ℎ
119905
1198972sdot
1(119905) + (
Vℎ119905
119897)
2
sdot 1(119905)
+6V3
ℎ
119905
1198973sdot 119881
2(119905) +
6V3ℎ
1199052
1198973
sdot 2(119905) + (
Vℎ119905
119897)
3
sdot 2(119905)]
times [(Vℎ119905
119897)
2
sdot 1198811(119905) + (
Vℎ119905
119897)
3
sdot 1198812(119905)]
+ 119898ℎ[2V2
ℎ
1198972sdot 119882
1(119905) +
4V2ℎ
119905
1198972sdot
1(119905) + (
Vℎ119905
119897)
2
sdot 1(119905)
+6V3
ℎ
119905
1198973sdot 119882
2(119905) +
6V3ℎ
1199052
1198973sdot
2(119905)
+ (Vℎ119905
119897)
3
sdot 2(119905)]
times [(Vℎ119905
119897)
2
sdot 1198821(119905) + (
Vℎ119905
119897)
3
sdot 1198822(119905)]
+ 1198811(119905) sdot int
119897
0
119902 (119909) (119909
119897)
2
119889119909 + 1198812(119905)
sdot int
119897
0
119902 (119909) (119909
119897)
3
119889119909
Ψ119902=
1
6(36119863
119909119909120578119887
2
2
1198976+
4119860119909119909120578119887
2
2
1198974+
36119863119909119909120578119887
2
2
1198976) 119897
3
+1
4(4119860
11990911990912057811988712
1198973+
2411986311990911990912057811988712
1198975
+24119863
119909119909120578119887
1
2
1198975) 119897
2
+1
2
119860119909119909120578119887
2
1
119897+
2119863119909119909120578119887
2
1
1198973+
2119863119909119909120578119887
2
1
1198973
(44)
36 The Vibration Equation The Lagrange equation methodis used to derive the vibration equations
120597119871
120597119902119899
minus119889
119889119905(
120597119871
120597 119902119899
) + 119876119889= 0 119899 = 1 2 6 (45)
where 119871 is the Lagrange function 119902119899
= (1198801 119880
2 119881
1 119881
2
1198821119882
2)119879 is the vector of the generalized coordinates and
119902119899is the corresponding generalized velocity vector 119876
119889is the
generalized damping force The expressions for 119871 and 119876119889are
as
119871 = 119879119890minus (119880
119894minus 119882
119911)
119876119889= minus
120597Ψ119902
120597 119902119899
(119899 = 1 sim 6)
(46)
The axial vibration equations can be obtained as followsfor 119880
1 119880
2
1
31198971198681198601+
1
41198971198681198602+
120578119887119860
1199091199091
119897+
120578119887119860
1199091199092
119897+
1198601199091199091198801
119897
+119860
1199091199091198802
119897+
2119860119909119909119881
2
1
31198972+
311986011990911990911988111198812
21198972+
9119860119909119909119881
2
2
101198972
+2119860
119909119909119882
2
1
31198972+
3119860119909119909119882
1119882
2
21198972+
9119860119909119909119882
2
2
101198972= 0
(47a)
1
41198971198681198601+
1
51198971198681198602+
120578119887119860
1199091199091
119897+
4120578119887119860
1199091199092
3119897
+119860
1199091199091198801
119897+4119860
1199091199091198802
3119897+119860
119909119909119881
2
1
1198972+12119860
11990911990911988111198812
51198972+3119860
119909119909119881
2
2
21198972
+119860
119909119909119882
2
1
1198972+
12119860119909119909119882
1119882
2
51198972+
3119860119909119909119882
2
2
21198972= 0
(47b)
The following can be seen from the above equations
(1) Since the assumed modes rather than the naturalmodes are used the coupling between axial and trans-verse vibrations is rather severe for axial vibrations
Mathematical Problems in Engineering 11
(2) The nonlinearity is apparent in above equations onlyexisting in the terms of 119881
1 119881
2119882
1119882
2 We take (47a)
as an exampleThe terms including1198802and its first and
second derivative 1198811 119881
2119882
1119882
2 can be regarded as
the applied loads for 1198801
(3) The coupling between the axial and transverse vibra-tionswill disappear as long as the linear displacement-strain relationship is adopted
(4) There are no external loads for axial vibrationsaccording to above equations
The transverse vibration equations for 1198811 119881
2and119882
1 119882
2
can be obtained as
4
3
1198681198631
119897+
1
51198971198681198601+
1
61198971198681198602minus
119898ℎV5ℎ
1199055
2
1198975+
31198681198632
2119897
+4119898
ℎV4ℎ
1199053
1
1198974+
4120578119887119863
1199091199091
1198973minus
2119898ℎV5ℎ
1199054
2
1198975+
6120578119887119863
1199091199092
1198973
+8119898
ℎV4ℎ
1199052
1198811
1198974+
41198631199091199091198811
1198973+
8119898ℎV5ℎ
1199053
1198812
1198975+
61198631199091199091198812
1198973
+27119860
1199091199091198812119882
2
2
81198973+
541198601199091199091198811119881
2
2
71198973+
181198601199091199091198811119882
2
2
71198973
+6119860
119909119909119881
2
1
1198812
1198973+
21198601199091199091198812119882
2
1
1198973+
1211986011990911990911988021198812
51198972
+8119860
1199091199091198811119882
2
1
51198973+
311986011990911990911988011198812
21198972+
211986011990911990911988021198811
1198972
+8119860
119909119909119881
3
1
51198973+
27119860119909119909119881
3
2
81198973+
361198601199091199091198812119882
1119882
2
71198973
+4119860
1199091199091198811119882
1119882
2
1198973+
411986011990911990911988011198811
31198972minus 119865
119888119910(119905) minus 05119865
025119865= 0
1
61198971198681198601+
3
2
1198681198631
119897minus
119898ℎV5ℎ
1199055
1
1198975+
1
71198971198681198602+
9
5
1198681198632
119897
+6120578
119887119863
1199091199091
1198973+
2119898ℎV5ℎ
1199054
1
1198975+
12120578119887119863
1199091199092
1198973+
6119898ℎV6ℎ
1199055
2
1198976
+6119863
1199091199091198811
1198973+
16119898ℎV5ℎ
1199053
1198811
1198975+
121198631199091199091198812
1198973+
18119898ℎV6ℎ
1199054
1198812
1198976
+9119860
1199091199091198812119882
2
2
21198973+
811198601199091199091198811119881
2
2
81198973+
311986011990911990911988011198811
21198972
+27119860
1199091199091198811119882
2
2
81198973+
541198601199091199091198812119881
2
1
71198973+
181198601199091199091198812119882
2
1
71198973
+3119860
11990911990911988021198812
1198972+
21198601199091199091198811119882
2
1
1198973+
911986011990911990911988011198812
51198972+
1211986011990911990911988021198811
51198972
+9119860
119909119909119881
3
2
21198973+
2119860119909119909119881
3
1
1198973+
271198601199091199091198812119882
1119882
2
41198973
+36119860
1199091199091198811119882
1119882
2
71198973minus 04119865
025119865minus 119865
119888119910(119905) = 0
4
3
119868119863
1
119897+
1
5119897119868119860
1+
3
2
119868119863
2
119897+
1
6119897119868119860
2minus
119898ℎV5ℎ
1199055
2
1198975
+4120578
119887119863
119909119909
1
1198973+
4119898ℎV4ℎ
1199053
1
1198974minus
2119898ℎV5ℎ
1199054
2
1198975+
6120578119887119863
119909119909
2
1198973
+4119863
119909119909119882
1
1198973+
8119898ℎV4ℎ
1199052
1198821
1198974+
8119898ℎV5ℎ
1199053
1198822
1198975+
6119863119909119909119882
2
1198973
+36119860
119909119909119882
211988111198812
71198973+
4119860119909119909119882
111988111198812
1198973+
27119860119909119909119882
2119881
2
2
81198973
+18119860
119909119909119882
1119881
2
2
71198973+
54119860119909119909119882
1119882
2
2
71198973+
6119860119909119909119882
2
1
1198822
1198973
+2119860
119909119909119882
2119881
2
1
1198973+
121198601199091199091198802119882
2
51198972+
8119860119909119909119882
1119881
2
1
51198973
+3119860
1199091199091198801119882
2
21198972+
21198601199091199091198802119882
1
1198972+
27119860119909119909119882
3
2
81198973
+8119860
119909119909119882
3
1
51198973+
41198601199091199091198801119882
1
31198972minus 119865
119888119911(119905) = 0
1
7119897119868119860
2+
9
5
119868119863
2
119897+
1
6119897119868119860
1minus
119898ℎV5ℎ
1199055
1
1198975+
3
2
119868119863
1
119897
+6120578
119887119863
119909119909
1
1198973+
2119898ℎV5ℎ
1199054
1
1198975+
6119898ℎV6ℎ
1199055
2
1198976
+12120578
119887119863
119909119909
2
1198973+
6119863119909119909119882
1
1198973+
16119898ℎV5ℎ
1199053
1198821
1198975
+12119863
119909119909119882
2
1198973+
18119898ℎV6ℎ
1199054
1198822
1198976+
31198601199091199091198801119882
1
21198972
+27119860
119909119909119882
211988111198812
41198973+
36119860119909119909119882
111988111198812
71198973+
9119860119909119909119882
2119881
2
2
21198973
+27119860
119909119909119882
1119881
2
2
81198973+
81119860119909119909119882
1119882
2
2
81198973+
18119860119909119909119882
2119881
2
1
71198973
+54119860
119909119909119882
2119882
2
1
71198973+
31198601199091199091198802119882
2
1198972+
2119860119909119909119882
1119881
2
1
1198973
+9119860
1199091199091198801119882
2
51198972+
121198601199091199091198802119882
1
51198972+
2119860119909119909119882
3
1
1198973
+9119860
119909119909119882
3
2
21198973minus 119865
119888119911(119905) = 0
(48)
The complexity high coupling and nonlinearity are obvi-ous in above equations
4 The Coupled Rigid-Flexible Dynamics
The dynamics for control and dynamic simulation shouldbe presented for solar sail based on the simplification ofequations derived in previous sections Some assumptions aremade before simplifying the equations as follows
12 Mathematical Problems in Engineering
(1) Only the attitude motion is affected by the slidingmass the vibration of solar sail structure is notaffected by the sliding mass
(2) Although the attitude control is accomplished byrotating control vanes and the gimbaled controlboom moving sliding masses the specific time his-tories of the actuators are not considered here
(3) The four supporting beams are regarded as an entirestructure thus the identical generalized coordinatesare adopted in the dynamic analysis
41 The Simplified Attitude Dynamics The kinetic energy ofsolar sail supporting beams can be obtained as
119879119898
=1
2120596 sdot J sdot 120596 + 119898
119897int
119897
0
2∘
1205883
sdot (120596 times r3) + (120596 times 120588
3) sdot (120596 times 120588
3)
+ 2 (120596 times r3) sdot (120596 times 120588
3) 119889119911
+ 119898119897int
119897
0
2∘
1205882
sdot (120596 times r2) + (120596 times 120588
2) sdot (120596 times 120588
2)
+ 2 (120596 times r2) sdot (120596 times 120588
2) 119889119910
(49)
The subscripts 2 and 3 represent the second and thirdsupporting beams The displacements can be expressed as
V0119909
(119911 119905) = (119911
119897)
2
sdot 1198811(119905) + (
119911
119897)
3
sdot 1198812(119905)
1199080119910
(119911 119905) = 120572V0119909
(119911 119905) = (119911
119897)
2
sdot 1205721198811(119905) + (
119911
119897)
3
sdot 1205721198812(119905)
for the 3rd beam
V0119909
(119910 119905) = 120573V0119909
(119911 119905) = (119910
119897)
2
sdot 1205731198811(119905) + (
119910
119897)
3
sdot 1205731198812(119905)
1199080119911
(119910 119905) = 120574V0119909
(119910 119905) = (119910
119897)
2
sdot 1205741198811(119905) + (
119910
119897)
3
sdot 1205741198812(119905)
for the 2nd beam
(50)
The subscripts 119909 119910 and 119911 of the left terms in (50)represent the displacements along119909119910 and 119911directions119881
1(119905)
and 1198812(119905) are the generalized coordinates The displacements
1199080119910(119911 119905) V
0119909(119910 119905) and 119908
0119911(119910 119905) can be obtained using the
assumed modes as
1205883= V
0119909(119911 119905) i
119887+ 119908
0119910(119911 119905) j
119887
=
[[[[[
[
(119911
119897)
2
sdot 1198811(119905) + (
119911
119897)
3
sdot 1198812(119905)
120572 [(119911
119897)
2
sdot 1198811(119905) + (
119911
119897)
3
sdot 1198812(119905)]
0
]]]]]
]
1205882= V
0119909(119910 119905) i
119887+ 119908
0119911(119910 119905) k
119887
=
[[[[[
[
120573[(119910
119897)
2
sdot 1198811(119905) + (
119910
119897)
3
sdot 1198812(119905)]
0
120574 [(119910
119897)
2
sdot 1198811(119905) + (
119910
119897)
3
sdot 1198812(119905)]
]]]]]
]
(51)
The vibration velocity can be obtained as
∘
1205883
= 1205883119909i119887+ 120588
3119910j119887=
[[[[[
[
(119911
119897)
2
sdot 1(119905) + (
119911
119897)
3
sdot 2(119905)
1205721[(
119911
119897)
2
sdot 1(119905) + (
119911
119897)
3
sdot 2(119905)]
0
]]]]]
]
∘
1205882
= 1205882119909i119887+ 120588
2119911k119887=
[[[[[
[
1205731[(
119910
119897)
2
sdot 1(119905) + (
119910
119897)
3
sdot 2(119905)]
0
1205741[(
119910
119897)
2
sdot 1(119905) + (
119910
119897)
3
sdot 2(119905)]
]]]]]
]
(52)
Without loss of generality 120572 = 120573 = 1205721= 120573
1= 1 and
120574 = 1205741= minus1 can be assumed in above expressions And the
kinetic energy of the slidingmasses can be obtained as followsby neglecting the vibration related terms
119879ℎ=
1
2119898
ℎ1(120596 times r
ℎ1) sdot (120596 times r
ℎ1) +
1
2119898
ℎ2(120596 times r
ℎ2)
sdot (120596 times rℎ2)
(53)
The kinetic energy of the payload can be obtained as
119879119901=
1
2119898
119901(120596 times r
119901) sdot (120596 times r
119901) (54)
The following simplified attitude dynamics can beobtained by neglecting the second and higher terms ofattitude angles and vibration modes in computing the kinetic
Mathematical Problems in Engineering 13
energies of the supporting beams payload and slidingmasses Consider
119869119909 minus 119898
1198971198972
1minus
4
5119898
1198971198972
2+ 119898
ℎ11199102
ℎ1
+ 119898ℎ21199112
ℎ2
minus 119898119901119903119901119909119903119901119911 + 119898
1199011199032
119901119911
+ 1198981199011199032
119901119910
minus 119898119901119903119901119909119903119901119910
120579 = 119876120593
119869119910
120579 +2
5119898
1198971198972
2+
1
2119898
1198971198972
1+ 119898
ℎ21199112
ℎ2
120579
+ 1198981199011199032
119901119911
120579 minus 119898119901119903119901119910119903119901119911 minus 119898
119901119903119901119909119903119901119910
+ 1198981199011199032
119901119909
120579 = 119876120579
119869119911 minus
2
51198972
1198981198972minus
1
21198972
1198981198971+ 119898
ℎ11199102
ℎ1
minus 119898119901119903119901119910119903119901119911
120579 + 1198981199011199032
119901119910
+ 1198981199011199032
119901119909
minus 119898119901119903119901119909119903119901119911 = 119876
120595
(55)
where 119876120593 119876
120579 and 119876
120595are the generalized nonpotential
attitude control torques generated by the control vanes Andthe attitude control torques generated by the gimbaled controlboom and sliding masses can be found on the left side ofthe above equation coupled with 120579 making the attitudecontroller design problem rather difficult
42 The Simplified Vibration Equations The couplingbetween the axial and transverse vibrations is neglectedand only the transverse vibration is considered The attitudedynamics for dynamic simulation can be obtained as followsbased on previous derivation by neglecting the action ofsolar-radiation pressure
4
3
1198681198631
119897+
1
51198971198681198601+
1
61198971198681198602+
31198681198632
2119897+
4120578119887119863
1199091199091
1198973
+6120578
119887119863
1199091199092
1198973+
41198631199091199091198811
1198973+
61198631199091199091198812
1198973+
271198601199091199091198812119882
2
2
81198973
+54119860
1199091199091198811119881
2
2
71198973+
181198601199091199091198811119882
2
2
71198973+
6119860119909119909119881
2
1
1198812
1198973
+2119860
1199091199091198812119882
2
1
1198973+
81198601199091199091198811119882
2
1
51198973+
8119860119909119909119881
3
1
51198973
+27119860
119909119909119881
3
2
81198973+
361198601199091199091198812119882
1119882
2
71198973+
41198601199091199091198811119882
1119882
2
1198973
minus 1198651198621
(119905) = 0
1
61198971198681198601+
3
2
1198681198631
119897+
1
71198971198681198602+
9
5
1198681198632
119897+
6120578119887119863
1199091199091
1198973
+12120578
119887119863
1199091199092
1198973+
61198631199091199091198811
1198973+
121198631199091199091198812
1198973+
91198601199091199091198812119882
2
2
21198973
+81119860
1199091199091198811119881
2
2
81198973+
271198601199091199091198811119882
2
2
81198973+
541198601199091199091198812119881
2
1
71198973
+18119860
1199091199091198812119882
2
1
71198973+
21198601199091199091198811119882
2
1
1198973+
9119860119909119909119881
3
2
21198973
+2119860
119909119909119881
3
1
1198973+
271198601199091199091198812119882
1119882
2
41198973+
361198601199091199091198811119882
1119882
2
71198973
minus 1198651198622
(119905) = 0
(56)
The following equations can be obtained by rearrangingthe above equations
4
3
1198681198631
119897+
1
51198971198681198601+
1
61198971198681198602+
31198681198632
2119897+
4120578119887119863
1199091199091
1198973
+6120578
119887119863
1199091199092
1198973+
41198631199091199091198811
1198973+
61198631199091199091198812
1198973+
16119860119909119909119881
3
1
51198973
+12119860
119909119909119881
2
1
1198812
1198973+
1081198601199091199091198811119881
2
2
71198973+
54119860119909119909119881
3
2
81198973
minus 1198651198621
(119905) = 0
1
61198971198681198601+
3
2
1198681198631
119897+
1
71198971198681198602+
9
5
1198681198632
119897+
6120578119887119863
1199091199091
1198973
+12120578
119887119863
1199091199092
1198973+
61198631199091199091198811
1198973+
121198631199091199091198812
1198973
+4119860
119909119909119881
3
1
1198973+
108119860119909119909119881
2
1
1198812
71198973+
811198601199091199091198811119881
2
2
41198973
+9119860
119909119909119881
3
2
1198973minus 119865
1198622(119905) = 0
(57)
1198651198621(119905) and 119865
1198622(119905) are used to represent all the generalized
external forces they can be used for vibration control Thesecomplicated equations abovementioned are the basis forobtaining the simplified equations used for controller design
The following equations can be obtained by neglecting thetwo and higher terms
4
3
1198681198631
119897+
1
51198971198681198601+
1
61198971198681198602+
31198681198632
2119897+
4120578119887119863
1199091199091
1198973
+6120578
119887119863
1199091199092
1198973+
41198631199091199091198811
1198973+
61198631199091199091198812
1198973= 119865
1198621
(119905)
14 Mathematical Problems in Engineering
1
61198971198681198601+
3
2
1198681198631
119897+
1
71198971198681198602+
9
5
1198681198632
119897+
6120578119887119863
1199091199091
1198973
+12120578
119887119863
1199091199092
1198973+
61198631199091199091198811
1198973+
121198631199091199091198812
1198973= 119865
1198622
(119905)
(58)
43 The Rigid-Flexible Coupled Dynamics The simplifiedattitude and vibration dynamics can be written as
119886120593 + 119886
120579
120579 + 119886120595 + 119886
1198811
1+ 119886
1198812
2= 119876
120593
119887120579
120579 + 119887120595 + 119887
120593 + 119887
1198811
1+ 119887
1198812
2= 119876
120579
119888120595 + 119888
120579
120579 + 119888120593 + 119888
1198811
1+ 119888
1198812
2= 119876
120595
119889
1198811
1+ 119889
1198812
2+ 119889
1198811
1+ 119889
1198812
2+ 119889
1198811
1198811
+ 1198891198812
1198812= 119876
1198811
119890
1198811
1+ 119890
1198812
2+ 119890
1198811
1+ 119890
1198812
2+ 119890
1198811
1198811
+ 1198901198812
1198812= 119876
1198812
(59)
The related coefficients in the preceding equation can befound in (A1) in the appendix The dynamics (see (59)) isnot suitable for attitude controller design because the controlinputs exist in some coefficients of the angular accelerationsThis will make the controller design rather difficult Thusthe following dynamic model is obtained by putting theterms including the control inputs right side of the dynamicequations
119869119909 minus 119898
1198971198972
1minus
4
5119898
1198971198972
2= 119876
120593+ 119906
119869119910
120579 +2
5119898
1198971198972
2+
1
2119898
1198971198972
1= 119876
120579+ 119906
120579
119869119911 minus
1
21198972
1198981198971minus
2
51198972
1198981198972= 119876
120595+ 119906
119889
1198811
1+ 119889
1198812
2+ 119889
1198811
1+ 119889
1198812
2
+ 1198891198811
1198811+ 119889
1198812
1198812= 119876
1198811
119890
1198811
1+ 119890
1198812
2+ 119890
1198811
1+ 119890
1198812
2
+ 1198901198811
1198811+ 119890
1198812
1198812= 119876
1198812
(60)
The expressions for 119906 119906
120579
and 119906are as
119906= minus119898
ℎ11199102
ℎ1
minus 119898ℎ21199112
ℎ2
+ 119898119901119903119901119909119903119901119911 minus 119898
1199011199032
119901119911
minus 1198981199011199032
119901119910
+ 119898119901119903119901119909119903119901119910
120579
119906
120579
= minus119898ℎ21199112
ℎ2
120579 minus 1198981199011199032
119901119911
120579 + 119898119901119903119901119910119903119901119911 + 119898
119901119903119901119909119903119901119910
minus 1198981199011199032
119901119909
120579
119906= minus119898
ℎ11199102
ℎ1
+ 119898119901119903119901119910119903119901119911
120579 minus 1198981199011199032
119901119910
minus 1198981199011199032
119901119909
+ 119898119901119903119901119909119903119901119911
(61)
119906 119906
120579
and 119906are the functions of the positions of sliding
masses and payload and the angular accelerations The statevariables in (60) are defined as
1199091= 120593 119909
2= 119909
3= 120579 119909
4= 120579
1199095= 120595 119909
6= 119909
7= 119881
1
1199098=
1 119909
9= 119881
2 119909
10=
2
(62)
Thedynamics (60) can bewritten as the state-spacemodelas following
1= 119909
2
2= 119886
11199097+ 119886
21199098+ 119886
31199099+ 119886
411990910
+ 119906120593
3= 119909
4
4= 119886
51199097+ 119886
61199098+ 119886
71199099+ 119886
811990910
+ 119906120579
5= 119909
6
6= 119886
91199097+ 119886
101199098+ 119886
111199099+ 119886
1211990910
+ 119906120595
7= 119909
8
8= 119886
131199097+ 119886
141199098+ 119886
151199099+ 119886
1611990910
+ 1199061198811
9= 119909
10
10
= 119886171199097+ 119886
181199098+ 119886
191199099+ 119886
2011990910
+ 1199061198812
(63)
where 119906120579 119906
120593 and 119906
120595are the generalized control inputs
for attitude control and 1199061198811
and 1199061198812
are the generalizedcontrol inputs for vibration control The controllability canbe satisfied by analyzing (63) The attitudevibration controlinputs and the coefficients will be presented later in thissection The form of a matrix differential equation can bewritten as follows for the above equation
x = Ax + Bu (64)
The expressions of the relatedmatrices and vectors can befound as
x = [1
2
3
4
5
6
7
8
9
10]119879 x (119905
0) = x
1199050
u = [119906120593 119906
120579 119906
120595 119906
1198811
1199061198812
]119879
u (1199050) is known
(65)
where A xB and u are the system matrix state variablesvector control matrix and control inputs vector respectively
Mathematical Problems in Engineering 15
The complexity of the state-space model can be seen bypresenting the detailed expressions of control inputs forattitudevibration and related parameters in (A2) in theappendix
5 AttitudeVibration Control and Simulation
The controller for the attitude and vibration is developedusing the LQR and optimal PI theory The dynamic simula-tion is performed based on the coupled dynamics derived inthe previous sections
51 LQR and Optimal PI Based Controllers Design Thedynamics for solar sail can bewritten as follows togetherwithits quadratic cost function also defined as
x = Ax + Bu x (1199050) = x
1199050
(known)
119869 =1
2int
infin
1199050
[x119879 (119905)Qx (119905) + u119879 (119905)Ru (119905)] 119889119905
(66)
whereQ = Q119879
⩾ 0 andR = R119879
gt 0 are constantThe control-lability of [AB] and the observability of [AD] can beensured when the equationDD119879
= Q holds for anymatrixDThe optimal control input ulowast(119905)within the scope of u(119905) isin R119903119905 isin [119905
0infin] can be computed as follows to make 119869minimum
ulowast (119905) = minusKxlowast (119905) K = Rminus1B119879P (67)
where P is the nonnegative definite symmetric solution of thefollowing Riccati algebraic equations
PA + A119879P minus PBRminus1B119879P +Q = 0 (68)
And the optimal performance index can be obtained asfollows for arbitrary initial states
119869lowast
[x (1199050) 119905
0] =
1
2x1198790
Px0 (69)
The closed-loop system
x = (A minus BRminus1B119879P) x (70)
is asymptotically stableFor an orbiting solar sail the primary disturbance torque
is by the cmcp offset and the impact of the tiny dust inthe deep space The state regulator can be used to controlthe dynamic system affected by pulse disturbance torquewith good steady-state errors but will never achieve accuratesteady-state errors if the dynamics is affected by constantdisturbance torque Thus the optimal state regulator withan integrator to eliminate the constant disturbance torqueshould be presented This optimal proportional-integral reg-ulator not only eliminates the constant disturbance torque butalso possesses the property of optimal regulator
Table 1 The related parameters
Parameters ValuesCMCP offsetm [0 017678 017678]119879
The side length of square sailm 100Nominal solar-radiation pressureconstant at 1 AU from the sunNm2 4563 times 10minus6
Solar-radiation pressure forceN 912 times 10minus2
Roll inertiakglowastm2 50383Pitch and yaw inertiakglowastm2 251915Outer radiusm 0229Thickness of the supporting beamm 75 times 10minus6
Youngrsquos modulus of the supportingbeamGPa 124
Moment of inertia of the cross-sectionof the supporting beamm4 2829412 times 10minus7
Bending stiffness of the supportingbeamNlowastm2 3508471336
Proportional damping coefficient ofsupporting beams 001
Line density of the supportingbeamkgm 0106879
Cross-sectional area of the supportingbeamm2 1079 times 10minus5
Roll disturbance torqueNlowastm 0Pitch (yaw) disturbance torqueNlowastm 0016122 (minus0016122)
For the following linear system with the correspondingperformance index
x = Ax + Bu x (1199050) = x
1199050
u (1199050) = u
1199050
119869 =1
2int
infin
1199050
(x119879Qx + u119879Ru + u119879Su) 119889119905(71)
where Q = Q119879
⩾ 0 R = R119879
gt 0 and S = S119879 gt 0 If [AB]is completely controllable and meanwhile [AD
11] is com-
pletely observable with the relationship D11D119879
11
= Q thesolution can be expressed as
ulowast = minusK1x minus K
2ulowast ulowast (119905
0) = u
1199050
(72)
If B119879B is full rank we can get
ulowast = minusK3x minus K
4x ulowast (119905
0) = u
1199050
(73)
K119894(119894 = 1 2 3 4) is the function of ABQR S
The closed-loop system
[xulowast] = [
A BminusK
1minusK
2
] [xulowast] [
[
x (1199050)
u (1199050)]
]
= [x1199050
u1199050
] (74)
is asymptotically stableThe compromise between the state variables (the angle
angular velocity the vibration displacement and velocity)and control inputs (the torque by all the actuators) can
16 Mathematical Problems in Engineering
0 2000 4000 6000
0 2000 4000 6000
0 2000 4000 6000minus5
0
5
minus5
0
5
minus5
0
5
minus4
minus2
0
2
4
times10minus4
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
00162
00164
00166
4800 4900 5000
4800 4900 5000
4800 4900 5000
minus00165
minus0016
Time (s) Time (s)
Time (s)
Time (s)
Time (s)
Time (s)
Roll
erro
r120593(∘
)
Roll
erro
r120593(∘
)
Pitc
h er
ror120579
(∘)
Pitc
h er
ror120579
(∘)
Yaw
erro
r120595(∘
)
Yaw
erro
r120595(∘
)
Figure 8 The roll pitch and yaw errors
be achieved by using both the LQR based and optimal PIbased controllers for the coupled attitudevibration dynamicsystem The fact is that the attitude control ability is limitedto the control torque by the control actuators The change ofthe attitude angles and rates should not be frequent to voidexciting vibrations
Thus the weighting matrix Q and the control weightingmatrix R are selected as follows for LQR based controller
Q (1 1) = 9 times 10minus6
Q (2 2) = 1 times 10minus6
Q (3 3) = 16 times 10minus6
Q (4 4) = Q (5 5) = Q (6 6) = Q (7 7) = Q (8 8)
= Q (9 9) = Q (10 10) = 1 times 10minus6
Q (119894 119895) = 0 (119894 = 119895 119894 119895 = 1 sim 10)
R (1 1) = R (2 2) = 900 R (3 3) = 100
R (4 4) = R (5 5) = 10000
R119894119895
= 0 (119894 = 119895 119894 119895 = 1 sim 5)
(75)
TheweightingmatrixQ and the control weightingmatrixR are selected as follows for the optimal PI based controller
Q (1 1) = Q (2 2) = 4 times 10minus8
Q (3 3) = Q (4 4) = Q (5 5) = Q (6 6) = Q (7 7)
= Q (8 8) = 16 times 10minus8
Mathematical Problems in Engineering 17
minus02
0
02
Roll
rate
(∘s)
Roll
rate
(∘s)
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Pitc
h ra
te(∘s)
Pitc
h ra
te(∘s)
0 1000 2000 3000 4000 5000
minus05
0
05
minus05
0
05
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
Time (s)
Yaw
rate
(∘
s)
Yaw
rate
(∘
s)
4800 4850 4900 4950 5000
Time (s)4800 4850 4900 4950 5000
Time (s)4800 4850 4900 4950 5000
minus2
0
2
minus2
0
2
minus2
0
2
times10minus4
times10minus4
times10minus4
Figure 9 The roll pitch and yaw rates
Q (9 9) = Q (10 10) = 1 times 10minus8
Q (119894 119895) = 0 (119894 = 119895 119894 119895 = 1 sim 10)
R (1 1) = R (2 2) = R (3 3) = 1 times 10minus8
R (4 4) = R (5 5) = 4 times 10minus8
R (119894 119895) = 0 (119894 = 119895 119894 119895 = 1 sim 5)
(76)
52 The Simulation Results The initial angle errors of rollpitch and yaw are adopted as 120593(119905
0) = 3
∘ 120579(1199050) = 3
∘ and120595(119905
0) = 3
∘ the initial angular velocity errors of roll pitchand yaw are adopted as (119905
0) = 0
∘
s 120579(1199050) = 0
∘
s and(119905
0) = 0
∘
s 1198811(1199050) = 01m 119881
2(1199050) = 01m
1(1199050) = 0ms
and 2(1199050) = 0ms are adopted in this paper for dynamic
simulationThe estimated cmcp offset is 025m for a 100 times 100m
square solar sail It is assumed that the components of cmcpoffset vector are [0 017678 017678]
119879 in the body frame
The relevant parameters for dynamic simulations are givenin Table 1
The dynamic simulation results are obtained as followsby using the LQR controller based on the abovementionedQ and R related parameters and initial conditions Thedynamics simulations with (denoted by ldquowith GFrdquo) andwithout (denoted by ldquowithout GFrdquo) considering the geo-metrical nonlinearity are presented And the correspondingdiscussions and analysis are also given according to thecalculated results
The roll pitch and yaw errors are presented based onthe dynamics models with and without considering thegeometrical nonlinearityThe control effect with zero steady-state error can be achieved for roll axis by referring tothe results But the steady-state errors exist for pitch andyaw axes from Figure 8 this is because there exist constantdisturbance torques for pitch and yaw axes caused by thecmcp offset Thus the LQR based controller cannot be usedfor attitude control with good steady-state performance Thesteady-state errors of pitch and yaw axes are about 0164
∘
and minus0164∘ respectively from the corresponding partial
enlarged drawing of the figures (see the corresponding left
18 Mathematical Problems in Engineering
minus20
0
20
Roll
torq
ue (N
lowastm
)
Roll
torq
ue (N
lowastm
)
minus50
0
50
minus50
0
50
Pitc
h to
rque
(Nlowast
m)
Pitc
h to
rque
(Nlowast
m)
0 1000 2000 3000 4000 5000
0 2000 4000 6000
0 2000 4000 6000
Yaw
torq
ue (N
lowastm
)
Yaw
torq
ue (N
lowastm
)
minus002
0
002
008
01
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
minus01
minus009
minus008
Time (s)Time (s)
Time (s)Time (s)
Time (s)Time (s)
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Figure 10 The roll pitch and yaw torques
figures) A simple and practical controller should be designedto eliminate the steady-state errorsThese errorswill affect theprecision of the super long duration space mission deeply
The differences between the dynamics with and withoutthe geometrical nonlinearity effect can be observed Theamplitudes and phases change a bit by comparing the corre-sponding results
It can be observed by the partial enlarged figures(the right figures of Figure 9) that there are no steady-stateerrors for roll pitch and yaw rates The relative satisfieddynamic performance is achieved In fact a result with muchmore satisfied dynamic performance can be obtained but itwill make the desired control torques much larger duringthe initial period This will not only excite the vibration ofthe structure but also increase the burden of the controlactuators
And the differences between the dynamics models withand without the geometrical nonlinearity can also be seenmerely in the phase of the angular velocities
The desired attitude control torques are presented inFigure 10 The roll torque will tend to be zero with thedecrement of the state variable errors The pitch and yawtorques tend to be constant from the middle and bottom
figures The pitch and yaw steady-state errors can never beeliminated although the pitch and yaw torques (009Nlowastmand minus009Nlowastm) are applied continuously by theoreticalanalysis and simulations This is just a great disadvantage ofthe LQR based controller in this paper The initial controltorques can be afforded by vibrating the gimbaled controlboom andmoving the slidingmasses that can afford a relativelarge torque The control vanes can be used to afford thecontrol torques when solar sail is in steady-state process Theexpression of the attitude control inputs 119906
120593 119906
120579 and 119906
120595can be
found in previous sectionMoreover the differences between dynamics responses
with and without geometrical nonlinearity can also beobserved by comparing the corresponding results Therequired torques for the attitude control are a little largerfor the dynamics with geometrical nonlinearity And thedifference in the phase is also clear
It can be seen that the vibration of the supporting beamis depressed effectively by the simulation results in Figure 11It can be seen that the steady-state errors and the dynamicperformance are relatively satisfied It can also be seen that thedynamics responses between the model with and without the
Mathematical Problems in Engineering 19
0 1000 2000 3000 4000 5000
0 1000 2000 3000 4000 5000
minus01
0
01
minus02
0
02
Time (s) Time (s)
Time (s) Time (s)
minus5
0
5
times10minus4
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
minus1
0
1
times10minus3
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
The d
ispla
cem
ent o
f the
tip
(m)
The d
ispla
cem
ent o
f the
tip
(m)
The v
eloci
ty o
f the
tip
(ms
)
The v
eloc
ity o
f the
tip
(ms
)
Figure 11 The displacement and velocity of the tip of the supporting beam
geometrical nonlinearity effect are different in the vibrationdisplacement and velocitymagnitudes and phases (Figure 15)
The simulation results can be obtained as follows by usingthe optimal PI based controller adopting the abovementionedparameters and initial conditions
The roll pitch and yaw errors are given by using theoptimal PI based controller These errors tend to disappearby observing the partially enlarged plotting of the figure (thecorresponding right figures) (shown in Figure 12) And therelative satisfied dynamic performance can also be obtainedFrom the view of eliminating the steady-state errors the opti-mal PI based controller performs better than the LQR basedcontroller by theoretical analysis and simulation results Theformer can achieve attitude control results without pitchand yaw steady-state errors From the view of dynamicperformance both the controllers perform well In additionit can be seen that the difference between the modelswith and without geometrical nonlinearity is merely inthe phase
The roll pitch and yaw rate errors are presented inFigure 13 The dynamic and steady-state performances aresatisfied by observing the simulation results And by observ-ing the difference between the dynamics responses with and
without the influence by the geometrical nonlinearity it canbe concluded that the merely difference is the phase
The desired control torques of the roll pitch and yaw areobtained in Figure 14 by using the optimal PI based controllerIt can be seen that the value of the desired roll control torquedecreases to zero as the values of the roll angle and ratedecrease to zero The desired pitch and yaw control torquestend to be the constant values 009Nlowastm and minus009Nlowastmrespectively The desired initial control torques are large byobserving Figure 14 It is suggested that the gimbaled controlboom combining the sliding masses is adopted to afford theinitial torque Then the control vanes can be used to controlthe solar sail after the initial phase The phase differencecan also be observed by inspecting the dynamics responsesduring the 4800sim5000 s period
The vibration can be controlled effectively based on theoptimal PI controller And the relative satisfied dynamicand steady-state performances can be achieved In additionthe tiny differences exist in the magnitudes of the requiredtorques And the phase differences also exist
It can be concluded as follows by analyzing and compar-ing the simulation results based on the LQR and optimal PItheories in detail
20 Mathematical Problems in Engineering
Roll
erro
r120593(∘
)
Roll
erro
r120593(∘
)
minus5
0
5
minus5
0
5
Pitc
h er
ror120579
(∘)
Pitc
h er
ror120579
(∘)
0 1000 2000 3000 4000 5000minus10
0
10
Time (s) Time (s)
Time (s)
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
Yaw
erro
r120595(∘
)
Yaw
erro
r120595(∘
)
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
minus1
0
1
times10minus3
minus1
0
1
times10minus3
minus1
0
1
times10minus3
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Figure 12 The roll pitch and yaw errors
(1) From the view of eliminating the steady-state errorsof the pitch and yaw errors the optimal PI based con-troller performs better than the LQR based controllerby theoretical analysis and simulation results Thedynamic performances of the two controllers are bothsatisfied and the desired control torques are relativelysmall
(2) The weighting of the state variables is reflected by theweighting matrix according to the LQR and optimalPI theories The constant weighting matrices selectedin this paper can effectively reflect the initial statevariable errors but maybe reflect the final state vari-able errors deficiently The time-varying weightingmatrices should be selected
(3) For the actual orbiting solar sail the control actuators(control vanes gimbaled control boom and slidingmasses) cannot afford excessive large control torquesThus the control torques should be as small as possibleon the premise of acquiring satisfied dynamic perfor-mance and steady-state errors It will not only reducethe burden of the control actuators but also avoid
exciting structural vibration In engineering practicethe weighting matrices and the control weightingmatrices should be selected based on the attitudecontrol requirement (eg dynamic performance andsteady-state errors etc)
(4) The dynamics responses influenced by the geometri-cal nonlinearity can be observed In a word the tinydifferences between the magnitudes of the physicalvariables exist for the models with and withoutthe geometrical nonlinearity And the relative cleardifferences exist in the phases for the attitude anglesrates required torques and so forth
6 Conclusions
The coupled attitude and structural dynamics is establishedfor the highly flexible sailcraft by using the von-Karman von-Karmanrsquos nonlinear strain-displacement relationships basedon assumptions of large deflections moderate rotationsand
Mathematical Problems in Engineering 21
Roll
rate
erro
r(∘ s
)
Roll
rate
erro
r(∘ s
)
minus01
0
01
minus01
0
01
Pitc
h ra
te er
ror (
∘ s)
Pitc
h ra
te er
ror (
∘ s)
0 1000 2000 3000 4000 5000minus02
0
02
Yaw
rate
erro
r (∘ s
)
Yaw
rate
erro
r (∘ s
)
4800 4850 4900 4950 5000
minus5
0
5times10minus4
minus5
0
5
times10minus4
minus5
0
5times10minus4
Time (s)
4800 4850 4900 4950 5000
Time (s)
4800 4850 4900 4950 5000
Time (s)
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Figure 13 The roll pitch and yaw rate errors
small strains The Lagrange equation method is utilizedto derive the dynamics for controller design and dynamicsimulation The LQR and optimal PI based controllers aredesigned for the dynamics with the constant disturbancetorque caused by the cmcp offset By theoretical analysisand simulation it can be seen that both controllers cancompromise between the state variables and control inputsBecause the control actuators can hardly afford large controltorque the dynamic performance should be relaxed toreduce the requirement for the attitude control actuatorsBesides the optimal PI based controller can also eliminatethe constant disturbance torque caused by the cmcp offsetthat always exists while the LQR based controller fails toachieve the results with satisfied steady-state performancealthough the attitude control torque is always applied to thecoupled dynamic systemThe dynamics simulations with andwithout the geometrical nonlinearity effect are also carriedout And the differences between the models in magnitudesand phases are identified and analyzed It can be concludedthat the optimal PI based controller performs better than the
LQRbased controller from the viewof eliminating the steady-state error caused by the disturbance torque by the cmcpoffset
Appendix
The related parameters in above equation are given as
119886120593= 119869
119909+ 119898
ℎ11199102
ℎ1
+ 119898ℎ21199112
ℎ2
+ 1198981199011199032
119901119911
+ 1198981199011199032
119901119910
119886120579= minus 119898
119901119903119901119909119903119901119910 119886
120595= minus119898
119901119903119901119909119903119901119911
1198861198811
= minus 1198981198971198972
1198861198812
= minus4
5119898
1198971198972
119887120579= 119869
119910+ 119898
ℎ21199112
ℎ2
+ 1198981199011199032
119901119911
+ 1198981199011199032
119901119909
119887120595= minus 119898
119901119903119901119910119903119901119911 119887
120593= minus119898
119901119903119901119909119903119901119910
22 Mathematical Problems in Engineering
Roll
torq
ue (N
lowastm
)
Roll
torq
ue (N
lowastm
)
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
0 2000 4000 6000
0 2000 4000 6000
0 2000 4000 6000
Time (s)
Time (s)
Time (s)
Time (s)
Time (s)
Time (s)4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
minus01
minus008
008
009
01
minus002
0
002
minus5
0
5
minus2
0
2
Pitc
h to
rque
(Nlowast
m)
Pitc
h to
rque
(Nlowast
m)
minus2
0
2
Yaw
torq
ue (N
lowastm
)
Yaw
torq
ue (N
lowastm
)
Figure 14 The roll pitch and yaw torques
1198871198811
=1
2119898
1198971198972
1198871198812
=2
5119898
1198971198972
119888120595= 119869
119911+ 119898
ℎ11199102
ℎ1
+ 1198981199011199032
119901119910
+ 1198981199011199032
119901119909
119888120579= minus 119898
119901119903119901119910119903119901119911 119888
120593= minus119898
119901119903119901119909119903119901119911
1198881198811
= minus1
21198972
119898119897 119888
1198812
= minus2
51198972
119898119897
119889
1198811
= (4
3
119868119863
119897+
1
5119897119868119860) 119889
1198812
= (1
6119897119868119860+
3119868119863
2119897)
119889
1198811
=4120578
119887119863
119909119909
1198973 119889
1198812
=6120578
119887119863
119909119909
1198973
1198891198811
=4119863
119909119909
1198973 119889
1198812
=6119863
119909119909
1198973
1198761198811
= 1198651198621
(119905)
119890
1198811
= (3
2
119868119863
119897+
1
6119897119868119860)
119890
1198812
= (1
7119897119868119860+
9
5
119868119863
119897) 119890
1198811
=6120578
119887119863
119909119909
1198973
119890
1198812
=12120578
119887119863
119909119909
1198973 119890
1198811
=6119863
119909119909
1198973
1198901198812
=12119863
119909119909
1198973 119876
1198812
= 1198651198622
(119905)
(A1)
The detailed expressions of control inputs for attitudevibration and related parameters in the state-space model ofthe dynamics (see (62) and (63)) are presented as follows
A =
[[[[[[[[[[[[[[
[
0 1 0 0 0 0 0 0 0 0
0 0 0 0 0 0 1198861
1198862
1198863
1198864
0 0 0 1 0 0 0 0 0 0
0 0 0 0 0 0 1198865
1198866
1198867
1198868
0 0 0 0 0 1 0 0 0 0
0 0 0 0 0 0 1198869
11988610
11988611
11988612
0 0 0 0 0 0 0 1 0 0
0 0 0 0 0 0 11988613
11988614
11988615
11988616
0 0 0 0 0 0 0 0 0 1
0 0 0 0 0 0 11988617
11988618
11988619
11988620
]]]]]]]]]]]]]]
]
Mathematical Problems in Engineering 23
0 1000 2000 3000 4000 5000
0 1000 2000 3000 4000 5000
minus01
0
01
minus02
0
02
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Time (s)
Time (s)Time (s)
Time (s)
minus1
0
1
minus1
0
1
times10minus3
times10minus3Th
e disp
lace
men
t of t
he ti
p (m
)
The d
ispla
cem
ent o
f the
tip
(m)
The v
eloci
ty o
f the
tip
(ms
)
The v
eloci
ty o
f the
tip
(ms
)
Figure 15 Vibration displacement and velocity of the tip
B =
[[[[[[[[[[[[[[
[
0 0 0 0 0
1 0 0 0 0
0 0 0 0 0
0 1 0 0 0
0 0 0 0 0
0 0 1 0 0
0 0 0 0 0
0 0 0 1 0
0 0 0 0 0
0 0 0 0 1
]]]]]]]]]]]]]]
]
1198861= minus
1198981198971198972
119869119909
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus4
5119869119909
1198981198971198972
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198862= minus
1198981198971198972
119869119909
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus4
5119869119909
1198981198971198972
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198863= minus
1198981198971198972
119869119909
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus4
5119869119909
1198981198971198972
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198864= minus
1198981198971198972
119869119909
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus4
5119869119909
1198981198971198972
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
119906120593=
119876120593
119869119909
+
119906
119869119909
+119898
1198971198972
119869119909
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+4
5119869119909
1198981198971198972
+
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198865=
1
2119869119910
1198981198971198972
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+2
5119869119910
1198981198971198972
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198866=
1
2119869119910
1198981198971198972
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+2
5119869119910
1198981198971198972
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198867=
1
2119869119910
1198981198971198972
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+2
5119869119910
1198981198971198972
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198868=
1
2119869119910
1198981198971198972
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
24 Mathematical Problems in Engineering
+2
5119869119910
1198981198971198972
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
119906120579=
119876120579
119869119910
+119906
120579
119869119910
minus1
2119869119910
1198981198971198972
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119910
1198981198971198972
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198869= minus
1
2119869119911
1198972
119898119897
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988610
= minus1
2119869119911
1198972
119898119897
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988611
= minus1
2119869119911
1198972
119898119897
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988612
= minus1
2119869119911
1198972
119898119897
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
119906120595=
119876120595
119869119911
+
119906
119869119911
+1
2119869119911
1198972
119898119897
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+2
5119869119911
1198972
119898119897
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988613
= minus
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988614
= minus
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988615
= minus
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988616
= minus
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
1199061198811
=
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988617
= minus
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988618
= minus
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988619
= minus
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988620
= minus
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1199061198812
=
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(A2)
Conflict of Interests
The authors declare that there is no conflict of interestsregarding the publication of this paper
Acknowledgments
The authors would like to thank the anonymous reviewers fortheir critical and constructive review of the paper This studywas cosupported by the National Natural Science Foundationof China (Project no 11302134 11272101)
References
[1] M Colin Solar Sailing Technology Dynamics and MissionApplications Springer-Praxis London UK 1st edition 1999
[2] V Lappas SWokesM Leipold A Lyngvi and P Falkner ldquoGui-dance and control for an Interstellar Heliopause Probe (IHP)solar sail mission to 200 AUrdquo in Proceedings of the AIAAGuidance Navigation and Control Conference and Exhibit pp2472ndash2492 San Francisco Calif USA August 2005
[3] L Charlotte C Camilla and C McInnes ldquoSolar radiation pres-sure augmented deorbiting fromhigh altitude sun-synchronousorbitsrdquo in Proceedings of the 4S Symposium 2012 Small SatellitesSystems and Services Portoroz Slovenia 2012
[4] M Ceriotti and C RMcInnes ldquoGeneration of optimal trajecto-ries for Earth hybrid pole sittersrdquo Journal of Guidance Controland Dynamics vol 34 no 3 pp 847ndash859 2011
[5] S Gong J Li andH Baoyin ldquoSolar sail transfer trajectory fromL1 point to sub-L1 pointrdquoAerospace Science and Technology vol15 no 7 pp 544ndash554 2011
[6] S Gong J Li and H Baoyin ldquoAnalysis of displaced solar sailorbits with passive controlrdquo Journal of Guidance Control andDynamics vol 31 no 3 pp 782ndash785 2008
[7] S Gong H Baoyin and J Li ldquoSolar sail three-body transfertrajectory designrdquo Journal of Guidance Control and Dynamicsvol 33 no 3 pp 873ndash886 2010
Mathematical Problems in Engineering 25
[8] S Gong J Li H Baoyin and J Simo ldquoA new solar sail orbitrdquoScience China Technological Sciences vol 55 no 3 pp 848ndash8552012
[9] Y Tsuda O Mori R Funase et al ldquoAchievement of IKAROS-Japanese deep space solar sail demonstration missionrdquo ActaAstronautica vol 82 no 2 pp 183ndash188 2013
[10] L Johnson MWhorton A Heaton R Pinson G Laue and CAdams ldquoNanoSail-D a solar sail demonstration missionrdquo ActaAstronautica vol 68 no 5-6 pp 571ndash575 2011
[11] B Wie and D Murphy ldquoSolar-sail attitude control design for asail flight validation missionrdquo Journal of Spacecraft and Rocketsvol 44 no 4 pp 809ndash821 2007
[12] B Wie D Murphy M Paluszek and S Thomas ldquoRobust atti-tude control systems design for solar sails part 1 propellantlessprimaryACSrdquo inProceedings of the AIAAGuidance Navigationand Control Conference and Exhibit Providence RI USAAugust 2004
[13] B Wie D Murphy M Paluszek and S Thomas ldquoRobust atti-tude control systems design for solar sails part 2 MicroPPT-based secondary ACSrdquo in Proceedings of the AIAA GuidanceNavigation and Control Conference and Exhibit pp 1325ndash1340Providence RI USA August 2004
[14] S Thomas M Paluszek B Wie and D Murphy ldquoAOCS per-formance and stability validation for large flexible solar sailspacecraftrdquo in Proceedings of the 41st AIAAASMESAEASEEJoint Propulsion Conference amp Exhibit Tucson Ariz USA 2005
[15] B Wie ldquoDynamic modeling and attitude control of solar sailspacecraft part Irdquo in Proceedings of the AIAAGuidance Naviga-tion and Control Conference and Exhibit Monterey Calif USAAugust 2002
[16] BWie ldquoSolar sail attitude control and dynamics part 1rdquo Journalof Guidance Control and Dynamics vol 27 no 4 pp 526ndash5352004
[17] B Wie ldquoDynamic modeling and attitude control of solar sailspacecraft part IIrdquo in Proceedings of the AIAA Guidance Nav-igation and Control Conference and Exhibit Monterey CalifUSA August 2002
[18] BWie ldquoSolar sail attitude control and dynamics part 2rdquo Journalof Guidance Control and Dynamics vol 27 no 4 pp 536ndash5442004
[19] C Luo and J-H Zheng ldquoSolar-sail attitude control based onmoving masses and roll stabilizer barsrdquo Journal of HarbinInstitute of Technology vol 43 no 3 pp 95ndash101 2011
[20] D Romagnoli and T Oehlschlagel ldquoHigh performance twodegrees of freedom attitude control for solar sailsrdquo Advances inSpace Research vol 48 no 11 pp 1869ndash1879 2011
[21] C Scholz D Romagnoli B Dachwald and S Theil ldquoPerfor-mance analysis of an attitude control system for solar sails usingsliding massesrdquo Advances in Space Research vol 48 no 11 pp1822ndash1835 2011
[22] A Bolle and C Circi ldquoSolar sail attitude control through in-plane moving massesrdquo Journal of Aerospace Engineering vol222 no 1 pp 81ndash94 2008
[23] M RotunnoM Basso A B Pome andM Sallusti ldquoA compari-son of robust attitude control techniques for a solar sail space-craftrdquo in Proceedings of the AIAA Guidance Navigation andControl Conference and Exhibit San Francisco Calif USA2005
[24] J Zhang K Zhai and T Wang ldquoControl of large angle maneu-vers for the flexible solar sailrdquo Science China Physics Mechanicsand Astronomy vol 54 no 4 pp 770ndash776 2011
[25] J Zhang andTWang ldquoCoupled attitude-orbit control of flexiblesolar sail for displaced solar orbitrdquo Journal of Spacecraft andRockets vol 50 no 3 pp 675ndash685 2013
[26] Q Li XMa and TWang ldquoReducedmodel for flexible solar saildynamicsrdquo Journal of Spacecraft and Rockets vol 48 no 3 pp446ndash453 2011
[27] M Polites J Kalmanson and D Mangus ldquoSolar sail attitudecontrol using small reaction wheels and magnetic torquersrdquoProceedings of the Institution of Mechanical Engineers G Journalof Aerospace Engineering vol 222 no 1 pp 53ndash62 2008
[28] H-T Cui J-H Luo J-H Feng and P-Y Cui ldquoAttitudecontrol of solar sail spacecraft with control boomrdquo Journal ofAstronautics vol 29 no 2 pp 560ndash566 2008
[29] E Mettler and S R Ploen ldquoSolar sail dynamics and controlusing a boom mounted bus articulated by a bi-state two-axisgimbal and reaction wheelsrdquo in Proceedings of the AIAAAASAstrodynamics Specialist Conference and Exhibit MontereyCalif USA August 2002
[30] J Luo X Li and J Feng ldquoPassive attitude control of solar sailspacecraftrdquo Flight Dynamics vol 26 no 5 pp 47ndash50 2008
[31] J Luo Study on attitude control of solar sail spaceraft [PhDthesis] School of Astronautics Harbin Institute of TechnologyHarbin China 2007
[32] D A Lawrence and S W Piggott ldquoIntegrated trajectory andattitude control for a four-vane solar sailrdquo in Proceedings ofthe AIAA Guidance Navigation and Control Conference andExhibit pp 2416ndash2431 San Francisco Calif USA August 2005
[33] E Mettler A B Acikmese and S R Ploen ldquoAttitude dynamicsand control of solar sails with articulated vanesrdquo in Proceedingsof the AIAA Guidance Navigation and Control Conference andExhibit pp 2396ndash2415 San Francisco Calif USA August 2005
[34] S N Adeli V J Lappas and B Wie ldquoA scalable bus-basedattitude control system for Solar Sailsrdquo Advances in SpaceResearch vol 48 no 11 pp 1836ndash1847 2011
[35] R Funase Y Shirasawa Y Mimasu et al ldquoOn-orbit verificationof fuel-free attitude control system for spinning solar sailutilizing solar radiation pressurerdquo Advances in Space Researchvol 48 no 11 pp 1740ndash1746 2011
[36] B Fu and F O Eke ldquoAttitude control methodology for largesolar sailsrdquo in AIAA Guidance Navigation and Control (GNC)Conference 2013
[37] J Liu N Cui F Shen and S Rong ldquoDynamics of highly-flexiblesolar sail subjected to various forcesrdquoActaAstronautica vol 103pp 55ndash72 2014
[38] J F Liu S Y Rong and J G Li ldquoAttitude dynamics modelingand control of large flexible solar sail spacecraftrdquo in Proceedingsof the 3rd International Symposium on Systems and Control inAeronautics and Astronautics (ISSCAA rsquo10) pp 243ndash247 IEEEPublications Piscataway NJ USA 2010
[39] S Gong H Baoyin and J Li ldquoCoupled attitude-orbit dynamicsand control for displaced solar orbitsrdquo Acta Astronautica vol65 no 5-6 pp 730ndash737 2009
Submit your manuscripts athttpwwwhindawicom
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
MathematicsJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Mathematical Problems in Engineering
Hindawi Publishing Corporationhttpwwwhindawicom
Differential EquationsInternational Journal of
Volume 2014
Applied MathematicsJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Probability and StatisticsHindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Journal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Mathematical PhysicsAdvances in
Complex AnalysisJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
OptimizationJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
CombinatoricsHindawi Publishing Corporationhttpwwwhindawicom Volume 2014
International Journal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Operations ResearchAdvances in
Journal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Function Spaces
Abstract and Applied AnalysisHindawi Publishing Corporationhttpwwwhindawicom Volume 2014
International Journal of Mathematics and Mathematical Sciences
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
The Scientific World JournalHindawi Publishing Corporation httpwwwhindawicom Volume 2014
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Algebra
Discrete Dynamics in Nature and Society
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Decision SciencesAdvances in
Discrete MathematicsJournal of
Hindawi Publishing Corporationhttpwwwhindawicom
Volume 2014 Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Stochastic AnalysisInternational Journal of
Mathematical Problems in Engineering 3
Controlvanes
Payload
Slidingmasses
Controlboom
Figure 1 The configuration and structure of solar sail
energy caused by vibrations and elastic potential energy ofthe membrane structure can be neglected
The paper mainly focuses on the dynamics for highlyflexible solar sail The following assumptions are made tosimplify the problems
(1) The detailed vibration of the membrane is neglectedin this paper as most of the kinetic energy causedby vibrations is by the vibrations of the supportingbeams
(2) The masses of control vanes and control boom areneglected We regard the control vanes and controlboom as rigid bodies
(3) The deformation of the structure is not affected by thethermal loads and the wrinkle effect is also neglected
(4) The torque by the cmcp offset is the disturbancetorque And other disturbance torques (such as grav-ity gradient torque) are neglected
22 The Reference Frames and Coordinate Transformations
The Inertial Reference Frame (E119868X119868Y119868Z119868120587
119868) It is an inertial
reference frame for solar sail attitude and orbital motionE119868X119868is in the vernal equinox direction E
119868Z119868is in the Earthrsquos
rotation axis perpendicular to equatorial plane E119868Y119868is in the
equatorial plane and finishes the ldquotriadrdquo of unit vectors Theunit vector is e
119868= (i
119868 j119868 k
119868)119879
The body reference frames of solar sail (O119874x119887y119887z119887120587
119887)
and control vanes (C119894x119894y119894z119894120587
119894 119894 = 1 2 3 4) O
119874is the geo-
metric center of the film O119874x119887is perpendicular to the film
pointing to the payload sideO119874y119887andO
119874z119887are in the plane
of the sail C119894is the geometric center of the 119894th control vane
When there exist no relative motions between solar sail andcontrol vanes120587
119894is coincident with120587
119887The related frames can
be found in Figure 2The attitude motion is described in Euler angles using
the yaw-roll-pitch notation In this notation a three-elementvector Θ = [120595 120593 120579]
119879 is used to describe the attitude of solarsail with respect to the inertial frame The transformation
EI
ZI
YI
XI
yb
zb
1
2
C2
C1
x2
z2
z1
y1
x1
y2 OO
xb
12
3
3
44
C4
C3
x3
y3z3
z4
y4x4
Figure 2 120587119868
120587119887
and 120587119894
Sun line
EI
OO
rO
ZI
XI
YI
ZI z998400
120595
120595
XI
EI(O)
Z998400998400998400(zb)
Z998400998400120593
120593
120579
120579
x998400x998400998400 x998400998400998400(xb)
y998400998400 y998400998400998400(yb)y998400
YI
The orbit
Figure 3 The orbit and the attitude motion
from 120587119868to 120587
119887can be realized by a 3-1-2 rotation as shown
in Figure 3 (right) with the following rotation matrix
C119887119868
= R2(120579)R
1(120593)R
3(120595)
= [
[
119888120579119888120595 minus 119904120579119904120593119904120595 119888120579119904120595 + 119904120579119904120593119888120595 minus119904120579119888120593
minus119888120593119904120595 119888120593119888120595 119904120593
119904120579119888120595 + 119888120579119904120593119904120595 119904120579119904120595 minus 119888120579119904120593119888120595 119888120579119888120593
]
]
(1)
where
R3(120595) = [
[
cos120595 sin120595 0
minus sin120595 cos120595 0
0 0 1
]
]
R1(120593) = [
[
1 0 0
0 cos120593 sin120593
0 minus sin120593 cos120593]
]
R2(120579) = [
[
cos 120579 0 minus sin 120579
0 1 0
sin 120579 0 cos 120579]
]
(2)
120595 120593 and 120579 are yaw roll and pitch angles respectively 119888120579 and119904120579 are short for cos 120579 and sin 120579
And the transformation from 120587119894to 120587
119887can be obtained as
119862119887119894= [
[
119888120579119894119888120595
119894minus 119904120579
119894119904120593
119894119904120595
119894119888120579
119894119904120595
119894+ 119904120579
119894119904120593
119894119888120595
119894minus119904120579
119894119888120593
119894
minus119888120593119894119904120595
119894119888120593
119894119888120595
119894119904120593
119894
119904120579119894119888120595
119894+ 119888120579
119894119904120593
119894119904120595
119894119904120579
119894119904120595
119894minus 119888120579
119894119904120593
119894119888120595
119894119888120579
119894119888120593
119894
]
]
(3)
The attitude control can be performed by varying 120595119894 120593
119894 and
120579119894
4 Mathematical Problems in Engineering
OO
xb mp
14
1205821
zbyb
dm32
3
1205822
EI
p
ch1
h2
31205883
O m3
r
r r
rr
R R
Figure 4 The positions and orientations of the components
23 The Positions and Velocities of the Components Theabsolute position of an arbitrary point on the supportingbeams sliding masses and payload are given in Figure 4where r
119888119894(119894 = 1 2 3 4) is the position vector of the cp of
the 119894th control vane The cp of each control vane is assumed
to locate at the free end of the supporting beams r119901is the
position vector of the payload O119874is the origin of 120587
119887 The
positions and velocities of an arbitrary point on each supportbeam can be obtained as
R119898119894
= R119874+ r
119894+ 120588
119894 k
119898119894= R
119874+∘
120588119894
+ 120596 times (r119894+ 120588
119894) (4)
whereR119898119894(v
119898119894) is the position (velocity) vector of an arbitrary
point on the deformed supporting beam and r119894is the position
vector of an arbitrary point on the undeformed beam relativetoO
119874R
119874(R
119874= v
119874) is the orbital position and velocity of the
sailcraft 120588119894is the transverse deformation of an arbitrary point
on the supporting beam (sdot) is the first time derivatives withrespect to 120587
119868and (∘) is the first time derivatives with respect
to 120587119887 120596 is the angular velocity of solar sail expressed as
[
[
120596119909
120596119910
120596119911
]
]119887
= [
[
cos 120579 minus sin 120579 cos120593120579 + sin120593
sin 120579 + cos 120579 cos120593]
]
(5)
If the orbital motion and its influence on attitude motionare neglected we have
R1198983
= r3+120588
3= [120588
3119909 120588
3119910 119911
3]119879
R1198981
= r1+ 120588
1= [120588
1119909 120588
1119910 119911
1]119879
R1198982
= r2+ 120588
2= [120588
2119909 119910
2 120588
2119911]119879
R1198984
= r4+ 120588
4= [120588
4119909 119910
4 120588
4119911]119879
(6)
R1198983
=∘
1205883
+ 120596 times (r3+ 120588
3) =
[[
[
1205883119909
1205883119910
0
]]
]
+[[
[
cos 120579 minus sin 120579 cos120593120579 + sin120593
sin 120579 + cos 120579 cos120593
]]
]
times [
[
1205883119909
1205883119910
1199113
]
]
=
[[[
[
1205883119909
+ 1199113
120579 + 1199113 sin120593 minus 120588
3119910 sin 120579 minus 120588
3119910 cos 120579 cos120593
1205883119910
+ 1205883119909 sin 120579 + 120588
3119909 cos 120579 cos120593 minus 119911
3 cos 120579 + 119911
3 sin 120579 cos120593
1205883119910 cos 120579 minus 120588
3119910 sin 120579 cos120593 minus 120588
3119909
120579 minus 1205883119909 sin120593
]]]
]
(7)
R1198981
=∘
1205881
+ 120596 times (r1+ 120588
1) =
[[
[
1205881119909
1205881119910
0
]]
]
+[[
[
cos 120579 minus sin 120579 cos120593120579 + sin120593
sin 120579 + cos 120579 cos120593
]]
]
times [
[
1205881119909
1205881119910
1199111
]
]
=
[[[
[
1205881119909
+ 1199111
120579 + 1199111 sin120593 minus 120588
1119910 sin 120579 minus 120588
1119910 cos 120579 cos120593
1205881119910
+ 1205881119909 sin 120579 + 120588
1119909 cos 120579 cos120593 minus 119911
1 cos 120579 + 119911
1 sin 120579 cos120593
1205881119910 cos 120579 minus 120588
1119910 sin 120579 cos120593 minus 120588
1119909
120579 minus 1205881119909 sin120593
]]]
]
(8)
R1198982
=∘
1205882
+ 120596 times (r2+ 120588
2) =
[[
[
1205882119909
0
1205882119911
]]
]
+[[
[
cos 120579 minus sin 120579 cos120593120579 + sin120593
sin 120579 + cos 120579 cos120593
]]
]
times [
[
1205882119909
1199102
1205882119911
]
]
=[[
[
1205882119909
+ 1205882119911
120579 + 1205882119911 sin120593 minus 119910
2 sin 120579 minus 119910
2 cos 120579 cos120593
1205882119909 sin 120579 + 120588
2119909 cos 120579 cos120593 minus 120588
2119911 cos 120579 + 120588
2119911 sin 120579 cos120593
1205882119911
+ 1199102 cos 120579 minus 119910
2 sin 120579 cos120593 minus 120588
2119909
120579 minus 1205882119909 sin120593
]]
]
(9)
Mathematical Problems in Engineering 5
R1198984
=∘
1205884
+ 120596 times (r4+ 120588
4) = [
[
1205884119909
0
1205884119911
]
]
+[[
[
cos 120579 minus sin 120579 cos120593120579 + sin120593
sin 120579 + cos 120579 cos120593
]]
]
times [
[
1205884119909
1199104
1205884119911
]
]
=[[
[
1205884119909
+ 1205884119911
120579 + 1205884119911 sin120593 minus 119910
4 sin 120579 minus 119910
4 cos 120579 cos120593
1205884119909 sin 120579 + 120588
4119909 cos 120579 cos120593 minus 120588
4119911 cos 120579 + 120588
4119911 sin 120579 cos120593
1205884119911
+ 1199104 cos 120579 minus 119910
4 sin 120579 cos120593 minus 120588
4119909
120579 minus 1205884119909 sin120593
]]
]
(10)
The components of the position and velocity vectors of anarbitrary point on the supporting beam can be computed byusing the above five equations
In Figure 4 1205821and 120582
2are the boom tilt and azimuth
angles relative to the sailcraft body axes respectively Thecomponents of r
119901can be expressed as follows by using these
two angles
r119901=10038161003816100381610038161003816r119901
10038161003816100381610038161003816cos 120582
1i119887+10038161003816100381610038161003816r119901
10038161003816100381610038161003816sin 120582
1cos 120582
2j119887+10038161003816100381610038161003816r119901
10038161003816100381610038161003816sin 120582
1sin 120582
2k119887
(11)
The position and velocity vectors of the payload can beobtained as
R119874119901
= R119874+ r
119901 k
119874119901= k
119874+ r
119901 (12)
where r119901=∘r119901+ 120596 times r
119901 And ∘r
119901can be expressed as
∘r119901= minus
10038161003816100381610038161003816r119901
100381610038161003816100381610038161sin 120582
1i119887+10038161003816100381610038161003816r119901
10038161003816100381610038161003816
times (1cos 120582
1cos 120582
2minus
2sin 120582
1sin 120582
2) j
119887
+10038161003816100381610038161003816r119901
10038161003816100381610038161003816(
1cos 120582
1sin 120582
2+
2sin 120582
1cos 120582
2) k
119887
(13)
Thus r119901can be obtained as
r119901= [[minus119897
1199011sin 120582
1+ 119897
119901sin 120582
1sin 120582
2( 120579 + sin120593)
minus 119897119901sin 120582
1cos 120582
2( sin 120579 + cos 120579 cos120593)]
times [119897119901(
1cos 120582
1cos 120582
2minus
2sin 120582
1sin 120582
2)
+ 119897119901cos 120582
1( sin 120579 + cos 120579 cos120593)
minus 119897119901sin 120582
1sin 120582
2( cos 120579 minus sin 120579 cos120593)]
times 119897119901(
1cos 120582
1sin 120582
2+
2sin 120582
1cos 120582
2)
+ 119897119901sin 120582
1cos 120582
2( cos 120579 minus sin 120579 cos120593)
minus 119897119901cos 120582
1( 120579 + sin120593)]
(14)
The position vectors of the two sliding masses can beobtained as
Rℎ119895
= R119874+ r
ℎ119895+ 120588
ℎ119895
kℎ2
= k119874+∘rℎ119895
+∘
120588ℎ119895
+ 120596 times (rℎ119895
+ 120588ℎ119895)
(119895 = 1 2)
(15)
If the orbital motion and its influence on attitude motioncan be neglected then the position and velocity vectors canbe obtained as follows
Rℎ2
= rℎ2
+ 120588ℎ2
= [120588ℎ2119909
120588ℎ2119910
119911ℎ2]119879
Rℎ1
= rℎ1
+ 120588ℎ1
= [120588ℎ1119909
119910ℎ1 120588
ℎ1119911]119879
Rℎ2
=[[
[
120588ℎ2119909
+ 119911ℎ2
( 120579 + sin120593) minus 120588ℎ2119910
( sin 120579 + cos 120579 cos120593)120588ℎ2119910
+ 120588ℎ2119909
( sin 120579 + cos 120579 cos120593) minus 119911ℎ2
( cos 120579 minus sin 120579 cos120593)ℎ2
+ 120588ℎ2119910
( cos 120579 minus sin 120579 cos120593) minus 120588ℎ2119909
( 120579 + sin120593)
]]
]
Rℎ1
=[[
[
120588ℎ1119909
+ 120588ℎ1119911
( 120579 + sin120593) minus 119910ℎ1
( sin 120579 + cos 120579 cos120593)119910ℎ1
+ 120588ℎ1119909
( sin 120579 + cos 120579 cos120593) minus 120588ℎ1119911
( cos 120579 minus sin 120579 cos120593)120588ℎ1119911
+ 119910ℎ1
( cos 120579 minus sin 120579 cos120593) minus 120588ℎ1119909
( 120579 + sin120593)
]]
]
(16)
6 Mathematical Problems in Engineering
24 The Kinetic Energy The kinetic energy of the sail systemcan be obtained by neglecting the orbital motion and itsinfluence on attitude motion Consider
1198791198983
=1
2119898
119897int
119897
0
[∘
1205883
+ 120596 times (r3+ 120588
3)] sdot [
∘
1205883
+ 120596 times (r3+ 120588
3)] 119889119911
1198791198981
=1
2119898
119897int
0
minus119897
[∘
1205881
+ 120596 times (r1+ 120588
1)]
sdot [∘
1205881
+ 120596 times (r1+ 120588
1)] 119889119911
1198791198982
=1
2119898
119897int
119897
0
[∘
1205882
+ 120596 times (r2+ 120588
2)] sdot [
∘
1205882
+ 120596 times (r2+ 120588
2)] 119889119910
1198791198984
=1
2119898
119897int
0
minus119897
[∘
1205884
+ 120596 times (r4+ 120588
4)] sdot [
∘
1205884
+ 120596 times (r4+ 120588
4)] 119889119910
(17)
The above equations can be rewritten as
119879119898
=1
2120596 sdot J sdot 120596
+1
2119898
119897int
119897
0
2∘
1205883
sdot (120596 times r3) + (120596 times 120588
3) sdot (120596 times 120588
3)
+ 2 (120596 times r3) sdot (120596 times 120588
3) 119889119911
+1
2119898
119897int
0
minus119897
2∘
1205881
sdot (120596 times r1) + (120596 times 120588
1) sdot (120596 times 120588
1)
+ 2 (120596 times r1) sdot (120596 times 120588
1) 119889119911
+1
2119898
119897int
119897
0
2∘
1205882
sdot (120596 times r2) + (120596 times 120588
2) sdot (120596 times 120588
2)
+ 2 (120596 times r2) sdot (120596 times 120588
2) 119889119910
+1
2119898
119897int
0
minus119897
2∘
1205884
sdot (120596 times r4) + (120596 times 120588
4) sdot (120596 times 120588
4)
+ 2 (120596 times r4) sdot (120596 times 120588
4) + (120596 times r
4)
sdot (120596 times r4) 119889119910
(18)
where J = sum4
119895=1
J119898119895
is the moment of inertia of sail systemJ119898119895
(119895 = 1ndash4) is the moment of inertia of the 119895th sail sys-tem and the expression of J can be expressed as J = diag[119869
119909
119869119910 119869
119911] inO
119874x119887y119887z119887
The kinetic energy of the payload is
119879119901=
1
2119898
119901
10038161003816100381610038161003816r119901
10038161003816100381610038161003816
2
=1
2119898
119901[minus119897
1199011sin 120582
1+ 119897
119901sin 120582
1sin 120582
2( 120579 + sin120593)
minus 119897119901sin 120582
1cos 120582
2( sin 120579 + cos 120579 cos120593)]
2
+1
2119898
119901[119897119901(
1cos 120582
1cos 120582
2minus
2sin 120582
1sin 120582
2)
+ 119897119901cos 120582
1( sin 120579 + cos 120579 cos120593)
minus 119897119901sin 120582
1cos 120582
2( cos 120579 minus sin 120579 cos120593)]
2
+1
2119898
119901[119897119901(
1cos 120582
1sin 120582
2+
2sin 120582
1cos 120582
2)
+ 119897119901sin 120582
1cos 120582
2( cos 120579 minus sin 120579 cos120593)
minus 119897119901cos 120582
1( 120579 + sin120593)]
2
(19)
The kinetic energy of the sliding masses can be obtainedas follows by neglecting the orbital motion and its influenceon attitude control
119879ℎ1
=1
2119898
ℎ1[ ( 120588
ℎ1119909+ 120579120588
ℎ1119911+ 120588
ℎ1119911sin120593
minus 119910ℎ1sin 120579 minus 119910
ℎ1cos 120579 cos120593)
2
]
+1
2119898
ℎ1[( 119910
ℎ1+ 120588
ℎ1119909sin 120579 + 120588
ℎ1119909cos 120579 cos120593
minus 120588ℎ1119911
cos 120579 + 120588ℎ1119911
sin 120579 cos120593)2]
+1
2119898
ℎ1[( 120588
ℎ1119911+ 119910
ℎ1cos 120579 minus 119910
ℎ1sin 120579 cos120593
minus 120579120588ℎ1119909
+ 120588ℎ1119909
sin120593)2
]
119879ℎ2
=1
2119898
ℎ2[( 120588
ℎ2119909+ 120579119911
ℎ2+ 119911
ℎ2sin120593 minus 120588
ℎ2119910sin 120579
minus 120588ℎ2119910
cos 120579 cos120593)2
]
+1
2119898
ℎ2[( 120588
ℎ2119910+ 120588
ℎ2119909sin 120579 + 120588
ℎ2119909cos 120579 cos120593
minus 119911ℎ2cos 120579 + 119911
ℎ2sin 120579 cos120593)
2
]
+1
2119898
ℎ2[(
ℎ2+ 120588
ℎ2119910cos 120579 minus 120588
ℎ2119910sin 120579 cos120593
minus 120579120588ℎ2119909
minus 120588ℎ2119909
sin120593)2
]
(20)
25 The Gravitational Potential Energy The gravitationalpotential energies of the sail system 119880
119892119891 payload 119880
119892119901 and
sliding masses 119880119892ℎ1
119880119892ℎ2
can be obtained as
119880119892119891
= minus
120583119898119891
1003816100381610038161003816R119874
1003816100381610038161003816
119880119892119901
= minus
120583119898119901
10038161003816100381610038161003816R119874+ r
119901
10038161003816100381610038161003816
119880119892ℎ1
= minus120583119898
ℎ1
1003816100381610038161003816R119874+ r
ℎ1
1003816100381610038161003816
119880119892ℎ2
= minus120583119898
ℎ2
1003816100381610038161003816R119874+ r
ℎ2
1003816100381610038161003816
(21)
Mathematical Problems in Engineering 7
26 The Generalized Forces The components of the sunlightunit vector S can be obtained as follows by referring toFigure 3 (left) in 120587
119868
S = j119868= [1 0 0]
119879
119868
(22)
Based on the abovementioned equations the componentsof S in 120587
119887can be obtained as
S = C119887119868[1 0 0]
119879
119868
= [119878119909
119878119910
119878119911]119879
119887
(23)
The resultant SRP force can be simply modeled as followsfor a perfectly reflective control vane
F119894= 120578119875119860
119862119894(S sdot n
119862119894)2 n
119862119894= 119865
119862119894cos2120572
119862119894n119862119894 (24)
where 120578 is the overall sail-thrust coefficient (120578max = 2) 119875 =
4563 times 10minus6 Nm2 119860
119862119894is the area of the 119894th control vane
119865119862119894
= 120578119875119860119862119894is themaximumcontrol vane thrust andn
119862119894= i
119894
is the unit normal vector of the control vaneThe componentsof n
119862119894in 120587
119887can be written as
n119862119894
= C119887119894[1 0 0]
119879
119894
= [119878119909119894
119878119910119894
119878119911119894]119879
119887
(25)
The control torque by the 119894th control vane can beexpressed as
M119894= L
119894times F
119894 (26)
In fact L119894and F
119894are dependent on the deformations of
the supporting beams and control vanes In this paper it isassumed thatL
119894andF
119894are not influenced by the deformations
of the structure when computing the control torque by thecontrol vanes Thus L
119894and F
119894can be expressed as
L1= [0 0 minus119897]
119879
L2= [0 119897 0]
119879
L3= [0 0 119897]
119879
L4= [0 minus119897 0]
119879
F119894= 120578119875119860
119862119894([119878
119909119878119910
119878119911]119887
sdot [119878119909119894
119878119910119894
119878119911119894]119879
119887
)
2
[119878119909119894
119878119910119894
119878119911119894]119879
119887
(27)
The force of each control vane can be written as
F119894= (119865
119862119894cos2120572
119862119894)C
119887119894[1 0 0]
119879
119894
= (119865119862119894cos2120572
119862119894) [119878
119909119894119878119910119894
119878119911119894]119879
119887
(28)
where 120572119862119894
is the sun angle of the 119894th control vane that canbe measured by the sun sensor And the components of thecontrol torques can be obtained as
M1198881
= (1198651198621cos2120572
1198621)[
[
0
0
minus119897
]
]
times (C1198871
[
[
1
0
0
]
]
)
= (1198651198621cos2120572
1198621)
times [
[
minus119897 cos1205931sin120595
1
minus119897 (cos 1205791cos120595
1minus sin 120579
1sin120593
1sin120595
1)
0
]
]
M1198882
= (1198651198622cos2120572
1198622)
times [
[
119897 (sin 1205792cos120595
2+ cos 120579
2sin120593
2sin120595
2)
0
minus119897 (cos 1205792cos120595
2minus sin 120579
2sin120593
2sin120595
2)
]
]
M1198883
= (1198651198623cos2120572
1198623)
times [
[
119897 cos1205933sin120595
3
119897 (cos 1205793cos120595
3minus sin 120579
3sin120593
3sin120595
3)
0
]
]
M1198884
= (1198651198624cos2120572
1198624)
times [
[
minus119897 (sin 1205794cos120595
4+ cos 120579
4sin120593
4sin120595
4)
0
119897 (cos 1205794cos120595
4minus sin 120579
4sin120593
4sin120595
4)
]
]
(29)
27 Attitude Dynamics of Solar Sail The attitude dynamicscan be obtained by using the Lagrange equation method as
119889
119889119905(
120597119871
120597 119902119895
) minus120597119871
120597119902119895
= 119876119895 (30)
where 119871 is the Lagrange function 119902119895(119895 = 1ndash3) is the vector
of the generalized coordinates and 119876119895is the vector of the
generalized force 119871 can be computed as
119871 = 119879 minus 119880 =
4
sum
119894=1
119879119898119894
+ 119879119901+
2
sum
119895=1
119879ℎ119895
minus (119880119892119891
+ 119880119892119901
+
2
sum
119895=1
119880119892ℎ119895
)
(31)
where 119879119898119894 119879
119901 and 119879
ℎ119895are the kinetic energies of the
supporting beams payload and sliding masses respectively119880119892119891 119880
119892119901 and 119880
119892ℎ119895are the gravitational potential energies of
the sail system payload and sliding masses respectively
8 Mathematical Problems in Engineering
OOx
y
z
FCFCy
FCx
FCz
mh
q(x)
Figure 5 The vibration model
120590
120590e
120590120592
120590
Figure 6 The viscoelastic model
3 The Vibration of Solar Sail
The mechanical and material models of the sailcraft aregivenThe displacement filed stress and strain are presentedbased on the Euler beam assumptionThe Lagrange equationmethod is adopted to derive the vibration equations withlarge deformations based on the calculations of kineticenergies and works done by the external loads
31 The Mechanical Model The body frame O119874xyz is estab-
lished to describe the vibration (see Figure 5) F119862is the force
vector generated by the control vane used located at the tip ofthe supporting beam 119865
119862119909 119865
119862119910 and 119865
119862119911are the components
inO119874xyz 119902(119909) is the distributed load caused by SRP
32 The Material Model The carbon fibre enforced compos-ite material is used to construct the inflatable deploymentsupporting beam The model of the viscoelastic material canbe represented in Figure 6
The total stress is the summation of the elastic and viscousstresses It can be expressed as
120590 = 120590119890
+ 120590120592
= 119864120576 + 119888119887
120576 (32)
where 120590 120590119890 and 120590
120592 are the total elastic and viscous stressrespectively And 119864 is Youngrsquos modulus 120576 ( 120576) is the strain(strain rate) and 119888
119887is the coefficient of the internal damping
expressed as 119864120578119887 120578
119887is the proportionality constant of the
internal damping The dimensions of 119888119887and 120578
119887are N lowast sm2
and s respectively
OO x
y The support beam
Z
Figure 7 The schematic diagram of solar sail supporting beamdeformation
33 The Displacement Field Stress and Strain The deforma-tion of a spatial solar sail supporting beam is presented inFigure 7
The spatial displacement fields for supporting beam are as
119906 (119909 119910 119911 119905) = 1199060(119909 119905) minus 119910
120597V0
120597119909minus 119911
1205971199080
120597119909
V (119909 119910 119911 119905) = V0(119909 119905)
119908 (119909 119910 119911 119905) = 1199080(119909 119905)
(33)
119906(119909 119910 119911 119905) V(119909 119910 119911 119905) and 119908(119909 119910 119911 119905) are the displace-ments along 119909 119910 and 119911 directions respectively 119906
0(119909 119905)
V0(119909 119905) and 119908
0(119909 119905) are the axial and transverse displace-
ments of an arbitrary point on the neutral axisBy using Green strain definition von Karmanrsquos nonlinear
strain-displacement relationships based on assumptions oflarge deflections moderate rotations and small strains for a3D supporting beam are given as follows together with thestrain rate and normal stress
120576119909119909
=120597119906
0
120597119909+1
2(120597V
0
120597119909)
2
minus 1199101205972V
0
1205971199092
+1
2(120597119908
0
120597119909)
2
minus 1199111205972
1199080
1205971199092
120576119909119909
=120597
0
120597119909+(
120597V0
120597119909)(
120597V0
120597119909) minus 119910
1205972V
0
1205971199092
+(120597119908
0
120597119909)(
1205970
120597119909)
minus 1199111205972
0
1205971199092
120590119909119909
= 119864[120597119906
0
120597119909+1
2(120597V
0
120597119909)
2
minus 1199101205972V
0
1205971199092
+1
2(120597119908
0
120597119909)
2
minus 1199111205972
1199080
1205971199092
]
+ 119864120578119887(120597
0
120597119909+(
120597V0
120597119909)(
120597V0
120597119909) minus 119910
1205972V
0
1205971199092
+(120597119908
0
120597119909)(
1205970
120597119909) minus 119911
1205972
0
1205971199092
)
(34)
Mathematical Problems in Engineering 9
The single underlined terms in the preceding equationindicate the contribution by the geometrical nonlinearityThedynamics models and corresponding numerical simulationwithout considering the geometrical nonlinearity can beobtained and carried out by neglecting these terms
34 The Energies and Works Done by External Forces Thestrain energy can be derived as
119880119894=
1
2int
119897
0
119860119909119909
[120597119906
0
120597119909+
1
2(120597V
0
120597119909)
2
+1
2(120597119908
0
120597119909)
2
]
2
+ 119863119909119909
1205972V
0
1205971199092
+ 119863119909119909
1205972
1199080
1205971199092
119889119909
(35)
For an isotropic support beam the extensional stiffness119860
119909119909and bending stiffness119863
119909119909can be computed as
119860119909119909
= int119860
119864119889119860 119863119909119909
= int119860
1198641199112
119889119860 = int119860
1198641199102
119889119860 (36)
The dissipation function is as
Ψ119902=
1
2int
119897
0
[119860119909119909120578119887(120597
0
120597119909)
2
+ 119863119909119909120578119887(1205972V
0
1205971199092
)
2
+ 119863119909119909120578119887(1205972
0
1205971199092
)
2
]119889119909
(37)
The kinetic energy for the support beam is as
119879119890=
1
2int
119897
0
[119868119860(120597119906
0
120597119905)
2
+ 119868119860(120597119908
0
120597119905)
2
+ 119868119863(1205972
1199080
120597119909120597119905)
2
+ 119868119860(120597V
0
120597119905)
2
+ 119868119863(
1205972V
0
120597119909120597119905)
2
]119889119909
(38)
where 119868119860and 119868
119863are integration constant for the support
beam expressed as
119868119860= int
119860
120588119889119860 = 120588119860 119868119863= int
119860
1205881199112
119889119860 = int119860
1205881199102
119889119860 (39)
And the work done by the external force can be obtainedas119882 = 119865
119862119911sdot 119908 (119909
119888 119905) + 119865
119862119910sdot V (119909
119888 119905) + 119898
ℎ119886ℎ119910
(119909ℎ 119905) V (119909
ℎ 119905)
+ 119898ℎ119886ℎ119911
(119909ℎ 119905) 119908 (119909
ℎ 119905) + int
119897
0
119902 (119909) V (119909 119905) 119889119909
(40)where 119909
119888represents the position of the support beam
119908(119909119888 119905) V(119909
119888 119905) are the displacements along 119911 and 119910 direc-
tions respectively and the corresponding loads 119865119862119911 119865
119862119910are
known functions 119909ℎ 119897 and V
ℎare the position coordinate of
the sliding mass the length of the support beam and theconstant-velocity of the sliding mass The dynamic responseis studied only during the period [0 119897V
ℎ] 119898
ℎis the mass
and 119886ℎ119910(119909
ℎ 119905) and 119886
ℎ119911(119909
ℎ 119905) are the components of the
acceleration for a material point on the support beam theslidingmass just arrived at And the corresponding transversedeflections are 119908(119909
ℎ 119905) and V(119909
ℎ 119905) respectively
35 The Assumed Modes Method The axial displacement1199060(119909 119905) and the transverse deflections V
0(119909 119905) and119908
0(119909 119905) can
be represented as follows by considering the assumed modesmethod
1199060(119909 119905) =
infin
sum
119894=1
119880119894(119909)119880
119894(119905)
V0(119909 119905) =
infin
sum
119895=1
119881119895(119909) 119881
119895(119905)
1199080(119909 119905) =
infin
sum
119896=1
119882119896(119909)119882
119896(119905)
(41)
where 119880119894(119905) 119881
119895(119905) and 119882
119896(119905) are the time-dependent gen-
eralized coordinates and 119880119894(119909) 119881
119895(119909) and 119882
119896(119909) are the
assumedmodes For assumedmodemethod themode shapefunctions should satisfy the following requirements in thispaper
119880119894(119909)
1003816100381610038161003816119909=0= 0 119881
119895(119909)
10038161003816100381610038161003816119909=0= 0 119882
119896(119909)
1003816100381610038161003816119909=0= 0
1198811015840
119895
(119909)10038161003816100381610038161003816119909=0
= 0 1198821015840
119896
(119909)10038161003816100381610038161003816119909=0
= 0
(42)
The following first two assumed modes satisfying theassumed mode principle are used in this paper
1198801(119909) =
119909
119897 119880
2(119909) = (
119909
119897)
2
1198811(119909) = (
119909
119897)
2
1198812(119909) = (
119909
119897)
3
1198821(119909) = (
119909
119897)
2
1198822(119909) = (
119909
119897)
3
(43)
With the help of the assumedmodes the detailed expres-sions of 119880
119894 119879
119890119882
119911 and Ψ
119902can be obtained as
119880119894=
9
2
119860119909119909
1198973(119881
2
2
+ 1198822
2
)2
+27
4
119860119909119909
1198973(119881
11198812+ 119882
1119882
2)
times (1198812
2
+ 1198822
2
)
+18
7
119860119909119909
1198973[(119881
2
1
+ 1198822
1
) (1198812
2
+ 1198822
2
) + (11988111198812+ 119882
1119882
2)2
]
+119860
119909119909
1198973[3
2119897119880
2(119881
2
2
+ 1198822
2
) + (1198812
1
+ 1198822
1
)
times (11988111198812+ 119882
1119882
2)]
10 Mathematical Problems in Engineering
+1
10
119860119909119909
1198973[9119880
1119897 (119881
2
2
+ 1198822
2
) + 241198802119897 (119881
11198812+ 119882
1119882
2)
+ 4 (1198812
1
+ 1198822
1
)2
]
+119860
119909119909
1198972[3
21198801(119881
11198812+ 119882
1119882
2) + 119880
2(119881
2
1
+ 1198822
1
)]
+6119863
119909119909119881
2
2
1198973+ 119860
119909119909(2119880
1119881
2
1
31198972+
21198801119882
2
1
31198972+
21198802
2
3119897)
+6119863
119909119909119882
2
2
1198973+
611986311990911990911988111198812
1198973+
11986011990911990911988011198802
119897+
6119863119909119909119882
1119882
2
1198973
+119860
119909119909119880
2
1
2119897+
2119863119909119909119881
2
1
1198973+
2119863119909119909119882
2
1
1198973
119879119890=
1
14(119897119868
119860
2
2
+ 119897119868119860
2
2
) +1
6(119897119868
119860
1
2+ 119897119868
11986012)
+1
10(119897119868
119860
2
2
+ 119897119868119860
2
1
+9119868
119863
2
2
119897+ 119897119868
119860
2
1
+9119868
119863
2
2
119897)
+1
4(119897119868
11986012+
6119868119863
1
2
119897+
611986811986312
119897)
+1
6(119897119868
119860
2
1
+4119868
119863
2
1
119897+
4119868119863
2
1
119897)
119882119911= 119865
119862119911sdot [119882
1(119905) + 119882
2(119905)] + 119865
119862119910sdot [119881
1(119905) + 119881
2(119905)]
+ 119898ℎ[2V2
ℎ
1198972sdot 119881
1(119905) +
4V2ℎ
119905
1198972sdot
1(119905) + (
Vℎ119905
119897)
2
sdot 1(119905)
+6V3
ℎ
119905
1198973sdot 119881
2(119905) +
6V3ℎ
1199052
1198973
sdot 2(119905) + (
Vℎ119905
119897)
3
sdot 2(119905)]
times [(Vℎ119905
119897)
2
sdot 1198811(119905) + (
Vℎ119905
119897)
3
sdot 1198812(119905)]
+ 119898ℎ[2V2
ℎ
1198972sdot 119882
1(119905) +
4V2ℎ
119905
1198972sdot
1(119905) + (
Vℎ119905
119897)
2
sdot 1(119905)
+6V3
ℎ
119905
1198973sdot 119882
2(119905) +
6V3ℎ
1199052
1198973sdot
2(119905)
+ (Vℎ119905
119897)
3
sdot 2(119905)]
times [(Vℎ119905
119897)
2
sdot 1198821(119905) + (
Vℎ119905
119897)
3
sdot 1198822(119905)]
+ 1198811(119905) sdot int
119897
0
119902 (119909) (119909
119897)
2
119889119909 + 1198812(119905)
sdot int
119897
0
119902 (119909) (119909
119897)
3
119889119909
Ψ119902=
1
6(36119863
119909119909120578119887
2
2
1198976+
4119860119909119909120578119887
2
2
1198974+
36119863119909119909120578119887
2
2
1198976) 119897
3
+1
4(4119860
11990911990912057811988712
1198973+
2411986311990911990912057811988712
1198975
+24119863
119909119909120578119887
1
2
1198975) 119897
2
+1
2
119860119909119909120578119887
2
1
119897+
2119863119909119909120578119887
2
1
1198973+
2119863119909119909120578119887
2
1
1198973
(44)
36 The Vibration Equation The Lagrange equation methodis used to derive the vibration equations
120597119871
120597119902119899
minus119889
119889119905(
120597119871
120597 119902119899
) + 119876119889= 0 119899 = 1 2 6 (45)
where 119871 is the Lagrange function 119902119899
= (1198801 119880
2 119881
1 119881
2
1198821119882
2)119879 is the vector of the generalized coordinates and
119902119899is the corresponding generalized velocity vector 119876
119889is the
generalized damping force The expressions for 119871 and 119876119889are
as
119871 = 119879119890minus (119880
119894minus 119882
119911)
119876119889= minus
120597Ψ119902
120597 119902119899
(119899 = 1 sim 6)
(46)
The axial vibration equations can be obtained as followsfor 119880
1 119880
2
1
31198971198681198601+
1
41198971198681198602+
120578119887119860
1199091199091
119897+
120578119887119860
1199091199092
119897+
1198601199091199091198801
119897
+119860
1199091199091198802
119897+
2119860119909119909119881
2
1
31198972+
311986011990911990911988111198812
21198972+
9119860119909119909119881
2
2
101198972
+2119860
119909119909119882
2
1
31198972+
3119860119909119909119882
1119882
2
21198972+
9119860119909119909119882
2
2
101198972= 0
(47a)
1
41198971198681198601+
1
51198971198681198602+
120578119887119860
1199091199091
119897+
4120578119887119860
1199091199092
3119897
+119860
1199091199091198801
119897+4119860
1199091199091198802
3119897+119860
119909119909119881
2
1
1198972+12119860
11990911990911988111198812
51198972+3119860
119909119909119881
2
2
21198972
+119860
119909119909119882
2
1
1198972+
12119860119909119909119882
1119882
2
51198972+
3119860119909119909119882
2
2
21198972= 0
(47b)
The following can be seen from the above equations
(1) Since the assumed modes rather than the naturalmodes are used the coupling between axial and trans-verse vibrations is rather severe for axial vibrations
Mathematical Problems in Engineering 11
(2) The nonlinearity is apparent in above equations onlyexisting in the terms of 119881
1 119881
2119882
1119882
2 We take (47a)
as an exampleThe terms including1198802and its first and
second derivative 1198811 119881
2119882
1119882
2 can be regarded as
the applied loads for 1198801
(3) The coupling between the axial and transverse vibra-tionswill disappear as long as the linear displacement-strain relationship is adopted
(4) There are no external loads for axial vibrationsaccording to above equations
The transverse vibration equations for 1198811 119881
2and119882
1 119882
2
can be obtained as
4
3
1198681198631
119897+
1
51198971198681198601+
1
61198971198681198602minus
119898ℎV5ℎ
1199055
2
1198975+
31198681198632
2119897
+4119898
ℎV4ℎ
1199053
1
1198974+
4120578119887119863
1199091199091
1198973minus
2119898ℎV5ℎ
1199054
2
1198975+
6120578119887119863
1199091199092
1198973
+8119898
ℎV4ℎ
1199052
1198811
1198974+
41198631199091199091198811
1198973+
8119898ℎV5ℎ
1199053
1198812
1198975+
61198631199091199091198812
1198973
+27119860
1199091199091198812119882
2
2
81198973+
541198601199091199091198811119881
2
2
71198973+
181198601199091199091198811119882
2
2
71198973
+6119860
119909119909119881
2
1
1198812
1198973+
21198601199091199091198812119882
2
1
1198973+
1211986011990911990911988021198812
51198972
+8119860
1199091199091198811119882
2
1
51198973+
311986011990911990911988011198812
21198972+
211986011990911990911988021198811
1198972
+8119860
119909119909119881
3
1
51198973+
27119860119909119909119881
3
2
81198973+
361198601199091199091198812119882
1119882
2
71198973
+4119860
1199091199091198811119882
1119882
2
1198973+
411986011990911990911988011198811
31198972minus 119865
119888119910(119905) minus 05119865
025119865= 0
1
61198971198681198601+
3
2
1198681198631
119897minus
119898ℎV5ℎ
1199055
1
1198975+
1
71198971198681198602+
9
5
1198681198632
119897
+6120578
119887119863
1199091199091
1198973+
2119898ℎV5ℎ
1199054
1
1198975+
12120578119887119863
1199091199092
1198973+
6119898ℎV6ℎ
1199055
2
1198976
+6119863
1199091199091198811
1198973+
16119898ℎV5ℎ
1199053
1198811
1198975+
121198631199091199091198812
1198973+
18119898ℎV6ℎ
1199054
1198812
1198976
+9119860
1199091199091198812119882
2
2
21198973+
811198601199091199091198811119881
2
2
81198973+
311986011990911990911988011198811
21198972
+27119860
1199091199091198811119882
2
2
81198973+
541198601199091199091198812119881
2
1
71198973+
181198601199091199091198812119882
2
1
71198973
+3119860
11990911990911988021198812
1198972+
21198601199091199091198811119882
2
1
1198973+
911986011990911990911988011198812
51198972+
1211986011990911990911988021198811
51198972
+9119860
119909119909119881
3
2
21198973+
2119860119909119909119881
3
1
1198973+
271198601199091199091198812119882
1119882
2
41198973
+36119860
1199091199091198811119882
1119882
2
71198973minus 04119865
025119865minus 119865
119888119910(119905) = 0
4
3
119868119863
1
119897+
1
5119897119868119860
1+
3
2
119868119863
2
119897+
1
6119897119868119860
2minus
119898ℎV5ℎ
1199055
2
1198975
+4120578
119887119863
119909119909
1
1198973+
4119898ℎV4ℎ
1199053
1
1198974minus
2119898ℎV5ℎ
1199054
2
1198975+
6120578119887119863
119909119909
2
1198973
+4119863
119909119909119882
1
1198973+
8119898ℎV4ℎ
1199052
1198821
1198974+
8119898ℎV5ℎ
1199053
1198822
1198975+
6119863119909119909119882
2
1198973
+36119860
119909119909119882
211988111198812
71198973+
4119860119909119909119882
111988111198812
1198973+
27119860119909119909119882
2119881
2
2
81198973
+18119860
119909119909119882
1119881
2
2
71198973+
54119860119909119909119882
1119882
2
2
71198973+
6119860119909119909119882
2
1
1198822
1198973
+2119860
119909119909119882
2119881
2
1
1198973+
121198601199091199091198802119882
2
51198972+
8119860119909119909119882
1119881
2
1
51198973
+3119860
1199091199091198801119882
2
21198972+
21198601199091199091198802119882
1
1198972+
27119860119909119909119882
3
2
81198973
+8119860
119909119909119882
3
1
51198973+
41198601199091199091198801119882
1
31198972minus 119865
119888119911(119905) = 0
1
7119897119868119860
2+
9
5
119868119863
2
119897+
1
6119897119868119860
1minus
119898ℎV5ℎ
1199055
1
1198975+
3
2
119868119863
1
119897
+6120578
119887119863
119909119909
1
1198973+
2119898ℎV5ℎ
1199054
1
1198975+
6119898ℎV6ℎ
1199055
2
1198976
+12120578
119887119863
119909119909
2
1198973+
6119863119909119909119882
1
1198973+
16119898ℎV5ℎ
1199053
1198821
1198975
+12119863
119909119909119882
2
1198973+
18119898ℎV6ℎ
1199054
1198822
1198976+
31198601199091199091198801119882
1
21198972
+27119860
119909119909119882
211988111198812
41198973+
36119860119909119909119882
111988111198812
71198973+
9119860119909119909119882
2119881
2
2
21198973
+27119860
119909119909119882
1119881
2
2
81198973+
81119860119909119909119882
1119882
2
2
81198973+
18119860119909119909119882
2119881
2
1
71198973
+54119860
119909119909119882
2119882
2
1
71198973+
31198601199091199091198802119882
2
1198972+
2119860119909119909119882
1119881
2
1
1198973
+9119860
1199091199091198801119882
2
51198972+
121198601199091199091198802119882
1
51198972+
2119860119909119909119882
3
1
1198973
+9119860
119909119909119882
3
2
21198973minus 119865
119888119911(119905) = 0
(48)
The complexity high coupling and nonlinearity are obvi-ous in above equations
4 The Coupled Rigid-Flexible Dynamics
The dynamics for control and dynamic simulation shouldbe presented for solar sail based on the simplification ofequations derived in previous sections Some assumptions aremade before simplifying the equations as follows
12 Mathematical Problems in Engineering
(1) Only the attitude motion is affected by the slidingmass the vibration of solar sail structure is notaffected by the sliding mass
(2) Although the attitude control is accomplished byrotating control vanes and the gimbaled controlboom moving sliding masses the specific time his-tories of the actuators are not considered here
(3) The four supporting beams are regarded as an entirestructure thus the identical generalized coordinatesare adopted in the dynamic analysis
41 The Simplified Attitude Dynamics The kinetic energy ofsolar sail supporting beams can be obtained as
119879119898
=1
2120596 sdot J sdot 120596 + 119898
119897int
119897
0
2∘
1205883
sdot (120596 times r3) + (120596 times 120588
3) sdot (120596 times 120588
3)
+ 2 (120596 times r3) sdot (120596 times 120588
3) 119889119911
+ 119898119897int
119897
0
2∘
1205882
sdot (120596 times r2) + (120596 times 120588
2) sdot (120596 times 120588
2)
+ 2 (120596 times r2) sdot (120596 times 120588
2) 119889119910
(49)
The subscripts 2 and 3 represent the second and thirdsupporting beams The displacements can be expressed as
V0119909
(119911 119905) = (119911
119897)
2
sdot 1198811(119905) + (
119911
119897)
3
sdot 1198812(119905)
1199080119910
(119911 119905) = 120572V0119909
(119911 119905) = (119911
119897)
2
sdot 1205721198811(119905) + (
119911
119897)
3
sdot 1205721198812(119905)
for the 3rd beam
V0119909
(119910 119905) = 120573V0119909
(119911 119905) = (119910
119897)
2
sdot 1205731198811(119905) + (
119910
119897)
3
sdot 1205731198812(119905)
1199080119911
(119910 119905) = 120574V0119909
(119910 119905) = (119910
119897)
2
sdot 1205741198811(119905) + (
119910
119897)
3
sdot 1205741198812(119905)
for the 2nd beam
(50)
The subscripts 119909 119910 and 119911 of the left terms in (50)represent the displacements along119909119910 and 119911directions119881
1(119905)
and 1198812(119905) are the generalized coordinates The displacements
1199080119910(119911 119905) V
0119909(119910 119905) and 119908
0119911(119910 119905) can be obtained using the
assumed modes as
1205883= V
0119909(119911 119905) i
119887+ 119908
0119910(119911 119905) j
119887
=
[[[[[
[
(119911
119897)
2
sdot 1198811(119905) + (
119911
119897)
3
sdot 1198812(119905)
120572 [(119911
119897)
2
sdot 1198811(119905) + (
119911
119897)
3
sdot 1198812(119905)]
0
]]]]]
]
1205882= V
0119909(119910 119905) i
119887+ 119908
0119911(119910 119905) k
119887
=
[[[[[
[
120573[(119910
119897)
2
sdot 1198811(119905) + (
119910
119897)
3
sdot 1198812(119905)]
0
120574 [(119910
119897)
2
sdot 1198811(119905) + (
119910
119897)
3
sdot 1198812(119905)]
]]]]]
]
(51)
The vibration velocity can be obtained as
∘
1205883
= 1205883119909i119887+ 120588
3119910j119887=
[[[[[
[
(119911
119897)
2
sdot 1(119905) + (
119911
119897)
3
sdot 2(119905)
1205721[(
119911
119897)
2
sdot 1(119905) + (
119911
119897)
3
sdot 2(119905)]
0
]]]]]
]
∘
1205882
= 1205882119909i119887+ 120588
2119911k119887=
[[[[[
[
1205731[(
119910
119897)
2
sdot 1(119905) + (
119910
119897)
3
sdot 2(119905)]
0
1205741[(
119910
119897)
2
sdot 1(119905) + (
119910
119897)
3
sdot 2(119905)]
]]]]]
]
(52)
Without loss of generality 120572 = 120573 = 1205721= 120573
1= 1 and
120574 = 1205741= minus1 can be assumed in above expressions And the
kinetic energy of the slidingmasses can be obtained as followsby neglecting the vibration related terms
119879ℎ=
1
2119898
ℎ1(120596 times r
ℎ1) sdot (120596 times r
ℎ1) +
1
2119898
ℎ2(120596 times r
ℎ2)
sdot (120596 times rℎ2)
(53)
The kinetic energy of the payload can be obtained as
119879119901=
1
2119898
119901(120596 times r
119901) sdot (120596 times r
119901) (54)
The following simplified attitude dynamics can beobtained by neglecting the second and higher terms ofattitude angles and vibration modes in computing the kinetic
Mathematical Problems in Engineering 13
energies of the supporting beams payload and slidingmasses Consider
119869119909 minus 119898
1198971198972
1minus
4
5119898
1198971198972
2+ 119898
ℎ11199102
ℎ1
+ 119898ℎ21199112
ℎ2
minus 119898119901119903119901119909119903119901119911 + 119898
1199011199032
119901119911
+ 1198981199011199032
119901119910
minus 119898119901119903119901119909119903119901119910
120579 = 119876120593
119869119910
120579 +2
5119898
1198971198972
2+
1
2119898
1198971198972
1+ 119898
ℎ21199112
ℎ2
120579
+ 1198981199011199032
119901119911
120579 minus 119898119901119903119901119910119903119901119911 minus 119898
119901119903119901119909119903119901119910
+ 1198981199011199032
119901119909
120579 = 119876120579
119869119911 minus
2
51198972
1198981198972minus
1
21198972
1198981198971+ 119898
ℎ11199102
ℎ1
minus 119898119901119903119901119910119903119901119911
120579 + 1198981199011199032
119901119910
+ 1198981199011199032
119901119909
minus 119898119901119903119901119909119903119901119911 = 119876
120595
(55)
where 119876120593 119876
120579 and 119876
120595are the generalized nonpotential
attitude control torques generated by the control vanes Andthe attitude control torques generated by the gimbaled controlboom and sliding masses can be found on the left side ofthe above equation coupled with 120579 making the attitudecontroller design problem rather difficult
42 The Simplified Vibration Equations The couplingbetween the axial and transverse vibrations is neglectedand only the transverse vibration is considered The attitudedynamics for dynamic simulation can be obtained as followsbased on previous derivation by neglecting the action ofsolar-radiation pressure
4
3
1198681198631
119897+
1
51198971198681198601+
1
61198971198681198602+
31198681198632
2119897+
4120578119887119863
1199091199091
1198973
+6120578
119887119863
1199091199092
1198973+
41198631199091199091198811
1198973+
61198631199091199091198812
1198973+
271198601199091199091198812119882
2
2
81198973
+54119860
1199091199091198811119881
2
2
71198973+
181198601199091199091198811119882
2
2
71198973+
6119860119909119909119881
2
1
1198812
1198973
+2119860
1199091199091198812119882
2
1
1198973+
81198601199091199091198811119882
2
1
51198973+
8119860119909119909119881
3
1
51198973
+27119860
119909119909119881
3
2
81198973+
361198601199091199091198812119882
1119882
2
71198973+
41198601199091199091198811119882
1119882
2
1198973
minus 1198651198621
(119905) = 0
1
61198971198681198601+
3
2
1198681198631
119897+
1
71198971198681198602+
9
5
1198681198632
119897+
6120578119887119863
1199091199091
1198973
+12120578
119887119863
1199091199092
1198973+
61198631199091199091198811
1198973+
121198631199091199091198812
1198973+
91198601199091199091198812119882
2
2
21198973
+81119860
1199091199091198811119881
2
2
81198973+
271198601199091199091198811119882
2
2
81198973+
541198601199091199091198812119881
2
1
71198973
+18119860
1199091199091198812119882
2
1
71198973+
21198601199091199091198811119882
2
1
1198973+
9119860119909119909119881
3
2
21198973
+2119860
119909119909119881
3
1
1198973+
271198601199091199091198812119882
1119882
2
41198973+
361198601199091199091198811119882
1119882
2
71198973
minus 1198651198622
(119905) = 0
(56)
The following equations can be obtained by rearrangingthe above equations
4
3
1198681198631
119897+
1
51198971198681198601+
1
61198971198681198602+
31198681198632
2119897+
4120578119887119863
1199091199091
1198973
+6120578
119887119863
1199091199092
1198973+
41198631199091199091198811
1198973+
61198631199091199091198812
1198973+
16119860119909119909119881
3
1
51198973
+12119860
119909119909119881
2
1
1198812
1198973+
1081198601199091199091198811119881
2
2
71198973+
54119860119909119909119881
3
2
81198973
minus 1198651198621
(119905) = 0
1
61198971198681198601+
3
2
1198681198631
119897+
1
71198971198681198602+
9
5
1198681198632
119897+
6120578119887119863
1199091199091
1198973
+12120578
119887119863
1199091199092
1198973+
61198631199091199091198811
1198973+
121198631199091199091198812
1198973
+4119860
119909119909119881
3
1
1198973+
108119860119909119909119881
2
1
1198812
71198973+
811198601199091199091198811119881
2
2
41198973
+9119860
119909119909119881
3
2
1198973minus 119865
1198622(119905) = 0
(57)
1198651198621(119905) and 119865
1198622(119905) are used to represent all the generalized
external forces they can be used for vibration control Thesecomplicated equations abovementioned are the basis forobtaining the simplified equations used for controller design
The following equations can be obtained by neglecting thetwo and higher terms
4
3
1198681198631
119897+
1
51198971198681198601+
1
61198971198681198602+
31198681198632
2119897+
4120578119887119863
1199091199091
1198973
+6120578
119887119863
1199091199092
1198973+
41198631199091199091198811
1198973+
61198631199091199091198812
1198973= 119865
1198621
(119905)
14 Mathematical Problems in Engineering
1
61198971198681198601+
3
2
1198681198631
119897+
1
71198971198681198602+
9
5
1198681198632
119897+
6120578119887119863
1199091199091
1198973
+12120578
119887119863
1199091199092
1198973+
61198631199091199091198811
1198973+
121198631199091199091198812
1198973= 119865
1198622
(119905)
(58)
43 The Rigid-Flexible Coupled Dynamics The simplifiedattitude and vibration dynamics can be written as
119886120593 + 119886
120579
120579 + 119886120595 + 119886
1198811
1+ 119886
1198812
2= 119876
120593
119887120579
120579 + 119887120595 + 119887
120593 + 119887
1198811
1+ 119887
1198812
2= 119876
120579
119888120595 + 119888
120579
120579 + 119888120593 + 119888
1198811
1+ 119888
1198812
2= 119876
120595
119889
1198811
1+ 119889
1198812
2+ 119889
1198811
1+ 119889
1198812
2+ 119889
1198811
1198811
+ 1198891198812
1198812= 119876
1198811
119890
1198811
1+ 119890
1198812
2+ 119890
1198811
1+ 119890
1198812
2+ 119890
1198811
1198811
+ 1198901198812
1198812= 119876
1198812
(59)
The related coefficients in the preceding equation can befound in (A1) in the appendix The dynamics (see (59)) isnot suitable for attitude controller design because the controlinputs exist in some coefficients of the angular accelerationsThis will make the controller design rather difficult Thusthe following dynamic model is obtained by putting theterms including the control inputs right side of the dynamicequations
119869119909 minus 119898
1198971198972
1minus
4
5119898
1198971198972
2= 119876
120593+ 119906
119869119910
120579 +2
5119898
1198971198972
2+
1
2119898
1198971198972
1= 119876
120579+ 119906
120579
119869119911 minus
1
21198972
1198981198971minus
2
51198972
1198981198972= 119876
120595+ 119906
119889
1198811
1+ 119889
1198812
2+ 119889
1198811
1+ 119889
1198812
2
+ 1198891198811
1198811+ 119889
1198812
1198812= 119876
1198811
119890
1198811
1+ 119890
1198812
2+ 119890
1198811
1+ 119890
1198812
2
+ 1198901198811
1198811+ 119890
1198812
1198812= 119876
1198812
(60)
The expressions for 119906 119906
120579
and 119906are as
119906= minus119898
ℎ11199102
ℎ1
minus 119898ℎ21199112
ℎ2
+ 119898119901119903119901119909119903119901119911 minus 119898
1199011199032
119901119911
minus 1198981199011199032
119901119910
+ 119898119901119903119901119909119903119901119910
120579
119906
120579
= minus119898ℎ21199112
ℎ2
120579 minus 1198981199011199032
119901119911
120579 + 119898119901119903119901119910119903119901119911 + 119898
119901119903119901119909119903119901119910
minus 1198981199011199032
119901119909
120579
119906= minus119898
ℎ11199102
ℎ1
+ 119898119901119903119901119910119903119901119911
120579 minus 1198981199011199032
119901119910
minus 1198981199011199032
119901119909
+ 119898119901119903119901119909119903119901119911
(61)
119906 119906
120579
and 119906are the functions of the positions of sliding
masses and payload and the angular accelerations The statevariables in (60) are defined as
1199091= 120593 119909
2= 119909
3= 120579 119909
4= 120579
1199095= 120595 119909
6= 119909
7= 119881
1
1199098=
1 119909
9= 119881
2 119909
10=
2
(62)
Thedynamics (60) can bewritten as the state-spacemodelas following
1= 119909
2
2= 119886
11199097+ 119886
21199098+ 119886
31199099+ 119886
411990910
+ 119906120593
3= 119909
4
4= 119886
51199097+ 119886
61199098+ 119886
71199099+ 119886
811990910
+ 119906120579
5= 119909
6
6= 119886
91199097+ 119886
101199098+ 119886
111199099+ 119886
1211990910
+ 119906120595
7= 119909
8
8= 119886
131199097+ 119886
141199098+ 119886
151199099+ 119886
1611990910
+ 1199061198811
9= 119909
10
10
= 119886171199097+ 119886
181199098+ 119886
191199099+ 119886
2011990910
+ 1199061198812
(63)
where 119906120579 119906
120593 and 119906
120595are the generalized control inputs
for attitude control and 1199061198811
and 1199061198812
are the generalizedcontrol inputs for vibration control The controllability canbe satisfied by analyzing (63) The attitudevibration controlinputs and the coefficients will be presented later in thissection The form of a matrix differential equation can bewritten as follows for the above equation
x = Ax + Bu (64)
The expressions of the relatedmatrices and vectors can befound as
x = [1
2
3
4
5
6
7
8
9
10]119879 x (119905
0) = x
1199050
u = [119906120593 119906
120579 119906
120595 119906
1198811
1199061198812
]119879
u (1199050) is known
(65)
where A xB and u are the system matrix state variablesvector control matrix and control inputs vector respectively
Mathematical Problems in Engineering 15
The complexity of the state-space model can be seen bypresenting the detailed expressions of control inputs forattitudevibration and related parameters in (A2) in theappendix
5 AttitudeVibration Control and Simulation
The controller for the attitude and vibration is developedusing the LQR and optimal PI theory The dynamic simula-tion is performed based on the coupled dynamics derived inthe previous sections
51 LQR and Optimal PI Based Controllers Design Thedynamics for solar sail can bewritten as follows togetherwithits quadratic cost function also defined as
x = Ax + Bu x (1199050) = x
1199050
(known)
119869 =1
2int
infin
1199050
[x119879 (119905)Qx (119905) + u119879 (119905)Ru (119905)] 119889119905
(66)
whereQ = Q119879
⩾ 0 andR = R119879
gt 0 are constantThe control-lability of [AB] and the observability of [AD] can beensured when the equationDD119879
= Q holds for anymatrixDThe optimal control input ulowast(119905)within the scope of u(119905) isin R119903119905 isin [119905
0infin] can be computed as follows to make 119869minimum
ulowast (119905) = minusKxlowast (119905) K = Rminus1B119879P (67)
where P is the nonnegative definite symmetric solution of thefollowing Riccati algebraic equations
PA + A119879P minus PBRminus1B119879P +Q = 0 (68)
And the optimal performance index can be obtained asfollows for arbitrary initial states
119869lowast
[x (1199050) 119905
0] =
1
2x1198790
Px0 (69)
The closed-loop system
x = (A minus BRminus1B119879P) x (70)
is asymptotically stableFor an orbiting solar sail the primary disturbance torque
is by the cmcp offset and the impact of the tiny dust inthe deep space The state regulator can be used to controlthe dynamic system affected by pulse disturbance torquewith good steady-state errors but will never achieve accuratesteady-state errors if the dynamics is affected by constantdisturbance torque Thus the optimal state regulator withan integrator to eliminate the constant disturbance torqueshould be presented This optimal proportional-integral reg-ulator not only eliminates the constant disturbance torque butalso possesses the property of optimal regulator
Table 1 The related parameters
Parameters ValuesCMCP offsetm [0 017678 017678]119879
The side length of square sailm 100Nominal solar-radiation pressureconstant at 1 AU from the sunNm2 4563 times 10minus6
Solar-radiation pressure forceN 912 times 10minus2
Roll inertiakglowastm2 50383Pitch and yaw inertiakglowastm2 251915Outer radiusm 0229Thickness of the supporting beamm 75 times 10minus6
Youngrsquos modulus of the supportingbeamGPa 124
Moment of inertia of the cross-sectionof the supporting beamm4 2829412 times 10minus7
Bending stiffness of the supportingbeamNlowastm2 3508471336
Proportional damping coefficient ofsupporting beams 001
Line density of the supportingbeamkgm 0106879
Cross-sectional area of the supportingbeamm2 1079 times 10minus5
Roll disturbance torqueNlowastm 0Pitch (yaw) disturbance torqueNlowastm 0016122 (minus0016122)
For the following linear system with the correspondingperformance index
x = Ax + Bu x (1199050) = x
1199050
u (1199050) = u
1199050
119869 =1
2int
infin
1199050
(x119879Qx + u119879Ru + u119879Su) 119889119905(71)
where Q = Q119879
⩾ 0 R = R119879
gt 0 and S = S119879 gt 0 If [AB]is completely controllable and meanwhile [AD
11] is com-
pletely observable with the relationship D11D119879
11
= Q thesolution can be expressed as
ulowast = minusK1x minus K
2ulowast ulowast (119905
0) = u
1199050
(72)
If B119879B is full rank we can get
ulowast = minusK3x minus K
4x ulowast (119905
0) = u
1199050
(73)
K119894(119894 = 1 2 3 4) is the function of ABQR S
The closed-loop system
[xulowast] = [
A BminusK
1minusK
2
] [xulowast] [
[
x (1199050)
u (1199050)]
]
= [x1199050
u1199050
] (74)
is asymptotically stableThe compromise between the state variables (the angle
angular velocity the vibration displacement and velocity)and control inputs (the torque by all the actuators) can
16 Mathematical Problems in Engineering
0 2000 4000 6000
0 2000 4000 6000
0 2000 4000 6000minus5
0
5
minus5
0
5
minus5
0
5
minus4
minus2
0
2
4
times10minus4
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
00162
00164
00166
4800 4900 5000
4800 4900 5000
4800 4900 5000
minus00165
minus0016
Time (s) Time (s)
Time (s)
Time (s)
Time (s)
Time (s)
Roll
erro
r120593(∘
)
Roll
erro
r120593(∘
)
Pitc
h er
ror120579
(∘)
Pitc
h er
ror120579
(∘)
Yaw
erro
r120595(∘
)
Yaw
erro
r120595(∘
)
Figure 8 The roll pitch and yaw errors
be achieved by using both the LQR based and optimal PIbased controllers for the coupled attitudevibration dynamicsystem The fact is that the attitude control ability is limitedto the control torque by the control actuators The change ofthe attitude angles and rates should not be frequent to voidexciting vibrations
Thus the weighting matrix Q and the control weightingmatrix R are selected as follows for LQR based controller
Q (1 1) = 9 times 10minus6
Q (2 2) = 1 times 10minus6
Q (3 3) = 16 times 10minus6
Q (4 4) = Q (5 5) = Q (6 6) = Q (7 7) = Q (8 8)
= Q (9 9) = Q (10 10) = 1 times 10minus6
Q (119894 119895) = 0 (119894 = 119895 119894 119895 = 1 sim 10)
R (1 1) = R (2 2) = 900 R (3 3) = 100
R (4 4) = R (5 5) = 10000
R119894119895
= 0 (119894 = 119895 119894 119895 = 1 sim 5)
(75)
TheweightingmatrixQ and the control weightingmatrixR are selected as follows for the optimal PI based controller
Q (1 1) = Q (2 2) = 4 times 10minus8
Q (3 3) = Q (4 4) = Q (5 5) = Q (6 6) = Q (7 7)
= Q (8 8) = 16 times 10minus8
Mathematical Problems in Engineering 17
minus02
0
02
Roll
rate
(∘s)
Roll
rate
(∘s)
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Pitc
h ra
te(∘s)
Pitc
h ra
te(∘s)
0 1000 2000 3000 4000 5000
minus05
0
05
minus05
0
05
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
Time (s)
Yaw
rate
(∘
s)
Yaw
rate
(∘
s)
4800 4850 4900 4950 5000
Time (s)4800 4850 4900 4950 5000
Time (s)4800 4850 4900 4950 5000
minus2
0
2
minus2
0
2
minus2
0
2
times10minus4
times10minus4
times10minus4
Figure 9 The roll pitch and yaw rates
Q (9 9) = Q (10 10) = 1 times 10minus8
Q (119894 119895) = 0 (119894 = 119895 119894 119895 = 1 sim 10)
R (1 1) = R (2 2) = R (3 3) = 1 times 10minus8
R (4 4) = R (5 5) = 4 times 10minus8
R (119894 119895) = 0 (119894 = 119895 119894 119895 = 1 sim 5)
(76)
52 The Simulation Results The initial angle errors of rollpitch and yaw are adopted as 120593(119905
0) = 3
∘ 120579(1199050) = 3
∘ and120595(119905
0) = 3
∘ the initial angular velocity errors of roll pitchand yaw are adopted as (119905
0) = 0
∘
s 120579(1199050) = 0
∘
s and(119905
0) = 0
∘
s 1198811(1199050) = 01m 119881
2(1199050) = 01m
1(1199050) = 0ms
and 2(1199050) = 0ms are adopted in this paper for dynamic
simulationThe estimated cmcp offset is 025m for a 100 times 100m
square solar sail It is assumed that the components of cmcpoffset vector are [0 017678 017678]
119879 in the body frame
The relevant parameters for dynamic simulations are givenin Table 1
The dynamic simulation results are obtained as followsby using the LQR controller based on the abovementionedQ and R related parameters and initial conditions Thedynamics simulations with (denoted by ldquowith GFrdquo) andwithout (denoted by ldquowithout GFrdquo) considering the geo-metrical nonlinearity are presented And the correspondingdiscussions and analysis are also given according to thecalculated results
The roll pitch and yaw errors are presented based onthe dynamics models with and without considering thegeometrical nonlinearityThe control effect with zero steady-state error can be achieved for roll axis by referring tothe results But the steady-state errors exist for pitch andyaw axes from Figure 8 this is because there exist constantdisturbance torques for pitch and yaw axes caused by thecmcp offset Thus the LQR based controller cannot be usedfor attitude control with good steady-state performance Thesteady-state errors of pitch and yaw axes are about 0164
∘
and minus0164∘ respectively from the corresponding partial
enlarged drawing of the figures (see the corresponding left
18 Mathematical Problems in Engineering
minus20
0
20
Roll
torq
ue (N
lowastm
)
Roll
torq
ue (N
lowastm
)
minus50
0
50
minus50
0
50
Pitc
h to
rque
(Nlowast
m)
Pitc
h to
rque
(Nlowast
m)
0 1000 2000 3000 4000 5000
0 2000 4000 6000
0 2000 4000 6000
Yaw
torq
ue (N
lowastm
)
Yaw
torq
ue (N
lowastm
)
minus002
0
002
008
01
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
minus01
minus009
minus008
Time (s)Time (s)
Time (s)Time (s)
Time (s)Time (s)
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Figure 10 The roll pitch and yaw torques
figures) A simple and practical controller should be designedto eliminate the steady-state errorsThese errorswill affect theprecision of the super long duration space mission deeply
The differences between the dynamics with and withoutthe geometrical nonlinearity effect can be observed Theamplitudes and phases change a bit by comparing the corre-sponding results
It can be observed by the partial enlarged figures(the right figures of Figure 9) that there are no steady-stateerrors for roll pitch and yaw rates The relative satisfieddynamic performance is achieved In fact a result with muchmore satisfied dynamic performance can be obtained but itwill make the desired control torques much larger duringthe initial period This will not only excite the vibration ofthe structure but also increase the burden of the controlactuators
And the differences between the dynamics models withand without the geometrical nonlinearity can also be seenmerely in the phase of the angular velocities
The desired attitude control torques are presented inFigure 10 The roll torque will tend to be zero with thedecrement of the state variable errors The pitch and yawtorques tend to be constant from the middle and bottom
figures The pitch and yaw steady-state errors can never beeliminated although the pitch and yaw torques (009Nlowastmand minus009Nlowastm) are applied continuously by theoreticalanalysis and simulations This is just a great disadvantage ofthe LQR based controller in this paper The initial controltorques can be afforded by vibrating the gimbaled controlboom andmoving the slidingmasses that can afford a relativelarge torque The control vanes can be used to afford thecontrol torques when solar sail is in steady-state process Theexpression of the attitude control inputs 119906
120593 119906
120579 and 119906
120595can be
found in previous sectionMoreover the differences between dynamics responses
with and without geometrical nonlinearity can also beobserved by comparing the corresponding results Therequired torques for the attitude control are a little largerfor the dynamics with geometrical nonlinearity And thedifference in the phase is also clear
It can be seen that the vibration of the supporting beamis depressed effectively by the simulation results in Figure 11It can be seen that the steady-state errors and the dynamicperformance are relatively satisfied It can also be seen that thedynamics responses between the model with and without the
Mathematical Problems in Engineering 19
0 1000 2000 3000 4000 5000
0 1000 2000 3000 4000 5000
minus01
0
01
minus02
0
02
Time (s) Time (s)
Time (s) Time (s)
minus5
0
5
times10minus4
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
minus1
0
1
times10minus3
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
The d
ispla
cem
ent o
f the
tip
(m)
The d
ispla
cem
ent o
f the
tip
(m)
The v
eloci
ty o
f the
tip
(ms
)
The v
eloc
ity o
f the
tip
(ms
)
Figure 11 The displacement and velocity of the tip of the supporting beam
geometrical nonlinearity effect are different in the vibrationdisplacement and velocitymagnitudes and phases (Figure 15)
The simulation results can be obtained as follows by usingthe optimal PI based controller adopting the abovementionedparameters and initial conditions
The roll pitch and yaw errors are given by using theoptimal PI based controller These errors tend to disappearby observing the partially enlarged plotting of the figure (thecorresponding right figures) (shown in Figure 12) And therelative satisfied dynamic performance can also be obtainedFrom the view of eliminating the steady-state errors the opti-mal PI based controller performs better than the LQR basedcontroller by theoretical analysis and simulation results Theformer can achieve attitude control results without pitchand yaw steady-state errors From the view of dynamicperformance both the controllers perform well In additionit can be seen that the difference between the modelswith and without geometrical nonlinearity is merely inthe phase
The roll pitch and yaw rate errors are presented inFigure 13 The dynamic and steady-state performances aresatisfied by observing the simulation results And by observ-ing the difference between the dynamics responses with and
without the influence by the geometrical nonlinearity it canbe concluded that the merely difference is the phase
The desired control torques of the roll pitch and yaw areobtained in Figure 14 by using the optimal PI based controllerIt can be seen that the value of the desired roll control torquedecreases to zero as the values of the roll angle and ratedecrease to zero The desired pitch and yaw control torquestend to be the constant values 009Nlowastm and minus009Nlowastmrespectively The desired initial control torques are large byobserving Figure 14 It is suggested that the gimbaled controlboom combining the sliding masses is adopted to afford theinitial torque Then the control vanes can be used to controlthe solar sail after the initial phase The phase differencecan also be observed by inspecting the dynamics responsesduring the 4800sim5000 s period
The vibration can be controlled effectively based on theoptimal PI controller And the relative satisfied dynamicand steady-state performances can be achieved In additionthe tiny differences exist in the magnitudes of the requiredtorques And the phase differences also exist
It can be concluded as follows by analyzing and compar-ing the simulation results based on the LQR and optimal PItheories in detail
20 Mathematical Problems in Engineering
Roll
erro
r120593(∘
)
Roll
erro
r120593(∘
)
minus5
0
5
minus5
0
5
Pitc
h er
ror120579
(∘)
Pitc
h er
ror120579
(∘)
0 1000 2000 3000 4000 5000minus10
0
10
Time (s) Time (s)
Time (s)
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
Yaw
erro
r120595(∘
)
Yaw
erro
r120595(∘
)
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
minus1
0
1
times10minus3
minus1
0
1
times10minus3
minus1
0
1
times10minus3
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Figure 12 The roll pitch and yaw errors
(1) From the view of eliminating the steady-state errorsof the pitch and yaw errors the optimal PI based con-troller performs better than the LQR based controllerby theoretical analysis and simulation results Thedynamic performances of the two controllers are bothsatisfied and the desired control torques are relativelysmall
(2) The weighting of the state variables is reflected by theweighting matrix according to the LQR and optimalPI theories The constant weighting matrices selectedin this paper can effectively reflect the initial statevariable errors but maybe reflect the final state vari-able errors deficiently The time-varying weightingmatrices should be selected
(3) For the actual orbiting solar sail the control actuators(control vanes gimbaled control boom and slidingmasses) cannot afford excessive large control torquesThus the control torques should be as small as possibleon the premise of acquiring satisfied dynamic perfor-mance and steady-state errors It will not only reducethe burden of the control actuators but also avoid
exciting structural vibration In engineering practicethe weighting matrices and the control weightingmatrices should be selected based on the attitudecontrol requirement (eg dynamic performance andsteady-state errors etc)
(4) The dynamics responses influenced by the geometri-cal nonlinearity can be observed In a word the tinydifferences between the magnitudes of the physicalvariables exist for the models with and withoutthe geometrical nonlinearity And the relative cleardifferences exist in the phases for the attitude anglesrates required torques and so forth
6 Conclusions
The coupled attitude and structural dynamics is establishedfor the highly flexible sailcraft by using the von-Karman von-Karmanrsquos nonlinear strain-displacement relationships basedon assumptions of large deflections moderate rotationsand
Mathematical Problems in Engineering 21
Roll
rate
erro
r(∘ s
)
Roll
rate
erro
r(∘ s
)
minus01
0
01
minus01
0
01
Pitc
h ra
te er
ror (
∘ s)
Pitc
h ra
te er
ror (
∘ s)
0 1000 2000 3000 4000 5000minus02
0
02
Yaw
rate
erro
r (∘ s
)
Yaw
rate
erro
r (∘ s
)
4800 4850 4900 4950 5000
minus5
0
5times10minus4
minus5
0
5
times10minus4
minus5
0
5times10minus4
Time (s)
4800 4850 4900 4950 5000
Time (s)
4800 4850 4900 4950 5000
Time (s)
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Figure 13 The roll pitch and yaw rate errors
small strains The Lagrange equation method is utilizedto derive the dynamics for controller design and dynamicsimulation The LQR and optimal PI based controllers aredesigned for the dynamics with the constant disturbancetorque caused by the cmcp offset By theoretical analysisand simulation it can be seen that both controllers cancompromise between the state variables and control inputsBecause the control actuators can hardly afford large controltorque the dynamic performance should be relaxed toreduce the requirement for the attitude control actuatorsBesides the optimal PI based controller can also eliminatethe constant disturbance torque caused by the cmcp offsetthat always exists while the LQR based controller fails toachieve the results with satisfied steady-state performancealthough the attitude control torque is always applied to thecoupled dynamic systemThe dynamics simulations with andwithout the geometrical nonlinearity effect are also carriedout And the differences between the models in magnitudesand phases are identified and analyzed It can be concludedthat the optimal PI based controller performs better than the
LQRbased controller from the viewof eliminating the steady-state error caused by the disturbance torque by the cmcpoffset
Appendix
The related parameters in above equation are given as
119886120593= 119869
119909+ 119898
ℎ11199102
ℎ1
+ 119898ℎ21199112
ℎ2
+ 1198981199011199032
119901119911
+ 1198981199011199032
119901119910
119886120579= minus 119898
119901119903119901119909119903119901119910 119886
120595= minus119898
119901119903119901119909119903119901119911
1198861198811
= minus 1198981198971198972
1198861198812
= minus4
5119898
1198971198972
119887120579= 119869
119910+ 119898
ℎ21199112
ℎ2
+ 1198981199011199032
119901119911
+ 1198981199011199032
119901119909
119887120595= minus 119898
119901119903119901119910119903119901119911 119887
120593= minus119898
119901119903119901119909119903119901119910
22 Mathematical Problems in Engineering
Roll
torq
ue (N
lowastm
)
Roll
torq
ue (N
lowastm
)
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
0 2000 4000 6000
0 2000 4000 6000
0 2000 4000 6000
Time (s)
Time (s)
Time (s)
Time (s)
Time (s)
Time (s)4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
minus01
minus008
008
009
01
minus002
0
002
minus5
0
5
minus2
0
2
Pitc
h to
rque
(Nlowast
m)
Pitc
h to
rque
(Nlowast
m)
minus2
0
2
Yaw
torq
ue (N
lowastm
)
Yaw
torq
ue (N
lowastm
)
Figure 14 The roll pitch and yaw torques
1198871198811
=1
2119898
1198971198972
1198871198812
=2
5119898
1198971198972
119888120595= 119869
119911+ 119898
ℎ11199102
ℎ1
+ 1198981199011199032
119901119910
+ 1198981199011199032
119901119909
119888120579= minus 119898
119901119903119901119910119903119901119911 119888
120593= minus119898
119901119903119901119909119903119901119911
1198881198811
= minus1
21198972
119898119897 119888
1198812
= minus2
51198972
119898119897
119889
1198811
= (4
3
119868119863
119897+
1
5119897119868119860) 119889
1198812
= (1
6119897119868119860+
3119868119863
2119897)
119889
1198811
=4120578
119887119863
119909119909
1198973 119889
1198812
=6120578
119887119863
119909119909
1198973
1198891198811
=4119863
119909119909
1198973 119889
1198812
=6119863
119909119909
1198973
1198761198811
= 1198651198621
(119905)
119890
1198811
= (3
2
119868119863
119897+
1
6119897119868119860)
119890
1198812
= (1
7119897119868119860+
9
5
119868119863
119897) 119890
1198811
=6120578
119887119863
119909119909
1198973
119890
1198812
=12120578
119887119863
119909119909
1198973 119890
1198811
=6119863
119909119909
1198973
1198901198812
=12119863
119909119909
1198973 119876
1198812
= 1198651198622
(119905)
(A1)
The detailed expressions of control inputs for attitudevibration and related parameters in the state-space model ofthe dynamics (see (62) and (63)) are presented as follows
A =
[[[[[[[[[[[[[[
[
0 1 0 0 0 0 0 0 0 0
0 0 0 0 0 0 1198861
1198862
1198863
1198864
0 0 0 1 0 0 0 0 0 0
0 0 0 0 0 0 1198865
1198866
1198867
1198868
0 0 0 0 0 1 0 0 0 0
0 0 0 0 0 0 1198869
11988610
11988611
11988612
0 0 0 0 0 0 0 1 0 0
0 0 0 0 0 0 11988613
11988614
11988615
11988616
0 0 0 0 0 0 0 0 0 1
0 0 0 0 0 0 11988617
11988618
11988619
11988620
]]]]]]]]]]]]]]
]
Mathematical Problems in Engineering 23
0 1000 2000 3000 4000 5000
0 1000 2000 3000 4000 5000
minus01
0
01
minus02
0
02
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Time (s)
Time (s)Time (s)
Time (s)
minus1
0
1
minus1
0
1
times10minus3
times10minus3Th
e disp
lace
men
t of t
he ti
p (m
)
The d
ispla
cem
ent o
f the
tip
(m)
The v
eloci
ty o
f the
tip
(ms
)
The v
eloci
ty o
f the
tip
(ms
)
Figure 15 Vibration displacement and velocity of the tip
B =
[[[[[[[[[[[[[[
[
0 0 0 0 0
1 0 0 0 0
0 0 0 0 0
0 1 0 0 0
0 0 0 0 0
0 0 1 0 0
0 0 0 0 0
0 0 0 1 0
0 0 0 0 0
0 0 0 0 1
]]]]]]]]]]]]]]
]
1198861= minus
1198981198971198972
119869119909
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus4
5119869119909
1198981198971198972
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198862= minus
1198981198971198972
119869119909
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus4
5119869119909
1198981198971198972
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198863= minus
1198981198971198972
119869119909
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus4
5119869119909
1198981198971198972
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198864= minus
1198981198971198972
119869119909
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus4
5119869119909
1198981198971198972
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
119906120593=
119876120593
119869119909
+
119906
119869119909
+119898
1198971198972
119869119909
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+4
5119869119909
1198981198971198972
+
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198865=
1
2119869119910
1198981198971198972
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+2
5119869119910
1198981198971198972
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198866=
1
2119869119910
1198981198971198972
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+2
5119869119910
1198981198971198972
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198867=
1
2119869119910
1198981198971198972
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+2
5119869119910
1198981198971198972
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198868=
1
2119869119910
1198981198971198972
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
24 Mathematical Problems in Engineering
+2
5119869119910
1198981198971198972
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
119906120579=
119876120579
119869119910
+119906
120579
119869119910
minus1
2119869119910
1198981198971198972
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119910
1198981198971198972
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198869= minus
1
2119869119911
1198972
119898119897
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988610
= minus1
2119869119911
1198972
119898119897
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988611
= minus1
2119869119911
1198972
119898119897
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988612
= minus1
2119869119911
1198972
119898119897
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
119906120595=
119876120595
119869119911
+
119906
119869119911
+1
2119869119911
1198972
119898119897
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+2
5119869119911
1198972
119898119897
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988613
= minus
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988614
= minus
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988615
= minus
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988616
= minus
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
1199061198811
=
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988617
= minus
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988618
= minus
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988619
= minus
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988620
= minus
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1199061198812
=
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(A2)
Conflict of Interests
The authors declare that there is no conflict of interestsregarding the publication of this paper
Acknowledgments
The authors would like to thank the anonymous reviewers fortheir critical and constructive review of the paper This studywas cosupported by the National Natural Science Foundationof China (Project no 11302134 11272101)
References
[1] M Colin Solar Sailing Technology Dynamics and MissionApplications Springer-Praxis London UK 1st edition 1999
[2] V Lappas SWokesM Leipold A Lyngvi and P Falkner ldquoGui-dance and control for an Interstellar Heliopause Probe (IHP)solar sail mission to 200 AUrdquo in Proceedings of the AIAAGuidance Navigation and Control Conference and Exhibit pp2472ndash2492 San Francisco Calif USA August 2005
[3] L Charlotte C Camilla and C McInnes ldquoSolar radiation pres-sure augmented deorbiting fromhigh altitude sun-synchronousorbitsrdquo in Proceedings of the 4S Symposium 2012 Small SatellitesSystems and Services Portoroz Slovenia 2012
[4] M Ceriotti and C RMcInnes ldquoGeneration of optimal trajecto-ries for Earth hybrid pole sittersrdquo Journal of Guidance Controland Dynamics vol 34 no 3 pp 847ndash859 2011
[5] S Gong J Li andH Baoyin ldquoSolar sail transfer trajectory fromL1 point to sub-L1 pointrdquoAerospace Science and Technology vol15 no 7 pp 544ndash554 2011
[6] S Gong J Li and H Baoyin ldquoAnalysis of displaced solar sailorbits with passive controlrdquo Journal of Guidance Control andDynamics vol 31 no 3 pp 782ndash785 2008
[7] S Gong H Baoyin and J Li ldquoSolar sail three-body transfertrajectory designrdquo Journal of Guidance Control and Dynamicsvol 33 no 3 pp 873ndash886 2010
Mathematical Problems in Engineering 25
[8] S Gong J Li H Baoyin and J Simo ldquoA new solar sail orbitrdquoScience China Technological Sciences vol 55 no 3 pp 848ndash8552012
[9] Y Tsuda O Mori R Funase et al ldquoAchievement of IKAROS-Japanese deep space solar sail demonstration missionrdquo ActaAstronautica vol 82 no 2 pp 183ndash188 2013
[10] L Johnson MWhorton A Heaton R Pinson G Laue and CAdams ldquoNanoSail-D a solar sail demonstration missionrdquo ActaAstronautica vol 68 no 5-6 pp 571ndash575 2011
[11] B Wie and D Murphy ldquoSolar-sail attitude control design for asail flight validation missionrdquo Journal of Spacecraft and Rocketsvol 44 no 4 pp 809ndash821 2007
[12] B Wie D Murphy M Paluszek and S Thomas ldquoRobust atti-tude control systems design for solar sails part 1 propellantlessprimaryACSrdquo inProceedings of the AIAAGuidance Navigationand Control Conference and Exhibit Providence RI USAAugust 2004
[13] B Wie D Murphy M Paluszek and S Thomas ldquoRobust atti-tude control systems design for solar sails part 2 MicroPPT-based secondary ACSrdquo in Proceedings of the AIAA GuidanceNavigation and Control Conference and Exhibit pp 1325ndash1340Providence RI USA August 2004
[14] S Thomas M Paluszek B Wie and D Murphy ldquoAOCS per-formance and stability validation for large flexible solar sailspacecraftrdquo in Proceedings of the 41st AIAAASMESAEASEEJoint Propulsion Conference amp Exhibit Tucson Ariz USA 2005
[15] B Wie ldquoDynamic modeling and attitude control of solar sailspacecraft part Irdquo in Proceedings of the AIAAGuidance Naviga-tion and Control Conference and Exhibit Monterey Calif USAAugust 2002
[16] BWie ldquoSolar sail attitude control and dynamics part 1rdquo Journalof Guidance Control and Dynamics vol 27 no 4 pp 526ndash5352004
[17] B Wie ldquoDynamic modeling and attitude control of solar sailspacecraft part IIrdquo in Proceedings of the AIAA Guidance Nav-igation and Control Conference and Exhibit Monterey CalifUSA August 2002
[18] BWie ldquoSolar sail attitude control and dynamics part 2rdquo Journalof Guidance Control and Dynamics vol 27 no 4 pp 536ndash5442004
[19] C Luo and J-H Zheng ldquoSolar-sail attitude control based onmoving masses and roll stabilizer barsrdquo Journal of HarbinInstitute of Technology vol 43 no 3 pp 95ndash101 2011
[20] D Romagnoli and T Oehlschlagel ldquoHigh performance twodegrees of freedom attitude control for solar sailsrdquo Advances inSpace Research vol 48 no 11 pp 1869ndash1879 2011
[21] C Scholz D Romagnoli B Dachwald and S Theil ldquoPerfor-mance analysis of an attitude control system for solar sails usingsliding massesrdquo Advances in Space Research vol 48 no 11 pp1822ndash1835 2011
[22] A Bolle and C Circi ldquoSolar sail attitude control through in-plane moving massesrdquo Journal of Aerospace Engineering vol222 no 1 pp 81ndash94 2008
[23] M RotunnoM Basso A B Pome andM Sallusti ldquoA compari-son of robust attitude control techniques for a solar sail space-craftrdquo in Proceedings of the AIAA Guidance Navigation andControl Conference and Exhibit San Francisco Calif USA2005
[24] J Zhang K Zhai and T Wang ldquoControl of large angle maneu-vers for the flexible solar sailrdquo Science China Physics Mechanicsand Astronomy vol 54 no 4 pp 770ndash776 2011
[25] J Zhang andTWang ldquoCoupled attitude-orbit control of flexiblesolar sail for displaced solar orbitrdquo Journal of Spacecraft andRockets vol 50 no 3 pp 675ndash685 2013
[26] Q Li XMa and TWang ldquoReducedmodel for flexible solar saildynamicsrdquo Journal of Spacecraft and Rockets vol 48 no 3 pp446ndash453 2011
[27] M Polites J Kalmanson and D Mangus ldquoSolar sail attitudecontrol using small reaction wheels and magnetic torquersrdquoProceedings of the Institution of Mechanical Engineers G Journalof Aerospace Engineering vol 222 no 1 pp 53ndash62 2008
[28] H-T Cui J-H Luo J-H Feng and P-Y Cui ldquoAttitudecontrol of solar sail spacecraft with control boomrdquo Journal ofAstronautics vol 29 no 2 pp 560ndash566 2008
[29] E Mettler and S R Ploen ldquoSolar sail dynamics and controlusing a boom mounted bus articulated by a bi-state two-axisgimbal and reaction wheelsrdquo in Proceedings of the AIAAAASAstrodynamics Specialist Conference and Exhibit MontereyCalif USA August 2002
[30] J Luo X Li and J Feng ldquoPassive attitude control of solar sailspacecraftrdquo Flight Dynamics vol 26 no 5 pp 47ndash50 2008
[31] J Luo Study on attitude control of solar sail spaceraft [PhDthesis] School of Astronautics Harbin Institute of TechnologyHarbin China 2007
[32] D A Lawrence and S W Piggott ldquoIntegrated trajectory andattitude control for a four-vane solar sailrdquo in Proceedings ofthe AIAA Guidance Navigation and Control Conference andExhibit pp 2416ndash2431 San Francisco Calif USA August 2005
[33] E Mettler A B Acikmese and S R Ploen ldquoAttitude dynamicsand control of solar sails with articulated vanesrdquo in Proceedingsof the AIAA Guidance Navigation and Control Conference andExhibit pp 2396ndash2415 San Francisco Calif USA August 2005
[34] S N Adeli V J Lappas and B Wie ldquoA scalable bus-basedattitude control system for Solar Sailsrdquo Advances in SpaceResearch vol 48 no 11 pp 1836ndash1847 2011
[35] R Funase Y Shirasawa Y Mimasu et al ldquoOn-orbit verificationof fuel-free attitude control system for spinning solar sailutilizing solar radiation pressurerdquo Advances in Space Researchvol 48 no 11 pp 1740ndash1746 2011
[36] B Fu and F O Eke ldquoAttitude control methodology for largesolar sailsrdquo in AIAA Guidance Navigation and Control (GNC)Conference 2013
[37] J Liu N Cui F Shen and S Rong ldquoDynamics of highly-flexiblesolar sail subjected to various forcesrdquoActaAstronautica vol 103pp 55ndash72 2014
[38] J F Liu S Y Rong and J G Li ldquoAttitude dynamics modelingand control of large flexible solar sail spacecraftrdquo in Proceedingsof the 3rd International Symposium on Systems and Control inAeronautics and Astronautics (ISSCAA rsquo10) pp 243ndash247 IEEEPublications Piscataway NJ USA 2010
[39] S Gong H Baoyin and J Li ldquoCoupled attitude-orbit dynamicsand control for displaced solar orbitsrdquo Acta Astronautica vol65 no 5-6 pp 730ndash737 2009
Submit your manuscripts athttpwwwhindawicom
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
MathematicsJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Mathematical Problems in Engineering
Hindawi Publishing Corporationhttpwwwhindawicom
Differential EquationsInternational Journal of
Volume 2014
Applied MathematicsJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Probability and StatisticsHindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Journal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Mathematical PhysicsAdvances in
Complex AnalysisJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
OptimizationJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
CombinatoricsHindawi Publishing Corporationhttpwwwhindawicom Volume 2014
International Journal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Operations ResearchAdvances in
Journal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Function Spaces
Abstract and Applied AnalysisHindawi Publishing Corporationhttpwwwhindawicom Volume 2014
International Journal of Mathematics and Mathematical Sciences
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
The Scientific World JournalHindawi Publishing Corporation httpwwwhindawicom Volume 2014
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Algebra
Discrete Dynamics in Nature and Society
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Decision SciencesAdvances in
Discrete MathematicsJournal of
Hindawi Publishing Corporationhttpwwwhindawicom
Volume 2014 Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Stochastic AnalysisInternational Journal of
4 Mathematical Problems in Engineering
OO
xb mp
14
1205821
zbyb
dm32
3
1205822
EI
p
ch1
h2
31205883
O m3
r
r r
rr
R R
Figure 4 The positions and orientations of the components
23 The Positions and Velocities of the Components Theabsolute position of an arbitrary point on the supportingbeams sliding masses and payload are given in Figure 4where r
119888119894(119894 = 1 2 3 4) is the position vector of the cp of
the 119894th control vane The cp of each control vane is assumed
to locate at the free end of the supporting beams r119901is the
position vector of the payload O119874is the origin of 120587
119887 The
positions and velocities of an arbitrary point on each supportbeam can be obtained as
R119898119894
= R119874+ r
119894+ 120588
119894 k
119898119894= R
119874+∘
120588119894
+ 120596 times (r119894+ 120588
119894) (4)
whereR119898119894(v
119898119894) is the position (velocity) vector of an arbitrary
point on the deformed supporting beam and r119894is the position
vector of an arbitrary point on the undeformed beam relativetoO
119874R
119874(R
119874= v
119874) is the orbital position and velocity of the
sailcraft 120588119894is the transverse deformation of an arbitrary point
on the supporting beam (sdot) is the first time derivatives withrespect to 120587
119868and (∘) is the first time derivatives with respect
to 120587119887 120596 is the angular velocity of solar sail expressed as
[
[
120596119909
120596119910
120596119911
]
]119887
= [
[
cos 120579 minus sin 120579 cos120593120579 + sin120593
sin 120579 + cos 120579 cos120593]
]
(5)
If the orbital motion and its influence on attitude motionare neglected we have
R1198983
= r3+120588
3= [120588
3119909 120588
3119910 119911
3]119879
R1198981
= r1+ 120588
1= [120588
1119909 120588
1119910 119911
1]119879
R1198982
= r2+ 120588
2= [120588
2119909 119910
2 120588
2119911]119879
R1198984
= r4+ 120588
4= [120588
4119909 119910
4 120588
4119911]119879
(6)
R1198983
=∘
1205883
+ 120596 times (r3+ 120588
3) =
[[
[
1205883119909
1205883119910
0
]]
]
+[[
[
cos 120579 minus sin 120579 cos120593120579 + sin120593
sin 120579 + cos 120579 cos120593
]]
]
times [
[
1205883119909
1205883119910
1199113
]
]
=
[[[
[
1205883119909
+ 1199113
120579 + 1199113 sin120593 minus 120588
3119910 sin 120579 minus 120588
3119910 cos 120579 cos120593
1205883119910
+ 1205883119909 sin 120579 + 120588
3119909 cos 120579 cos120593 minus 119911
3 cos 120579 + 119911
3 sin 120579 cos120593
1205883119910 cos 120579 minus 120588
3119910 sin 120579 cos120593 minus 120588
3119909
120579 minus 1205883119909 sin120593
]]]
]
(7)
R1198981
=∘
1205881
+ 120596 times (r1+ 120588
1) =
[[
[
1205881119909
1205881119910
0
]]
]
+[[
[
cos 120579 minus sin 120579 cos120593120579 + sin120593
sin 120579 + cos 120579 cos120593
]]
]
times [
[
1205881119909
1205881119910
1199111
]
]
=
[[[
[
1205881119909
+ 1199111
120579 + 1199111 sin120593 minus 120588
1119910 sin 120579 minus 120588
1119910 cos 120579 cos120593
1205881119910
+ 1205881119909 sin 120579 + 120588
1119909 cos 120579 cos120593 minus 119911
1 cos 120579 + 119911
1 sin 120579 cos120593
1205881119910 cos 120579 minus 120588
1119910 sin 120579 cos120593 minus 120588
1119909
120579 minus 1205881119909 sin120593
]]]
]
(8)
R1198982
=∘
1205882
+ 120596 times (r2+ 120588
2) =
[[
[
1205882119909
0
1205882119911
]]
]
+[[
[
cos 120579 minus sin 120579 cos120593120579 + sin120593
sin 120579 + cos 120579 cos120593
]]
]
times [
[
1205882119909
1199102
1205882119911
]
]
=[[
[
1205882119909
+ 1205882119911
120579 + 1205882119911 sin120593 minus 119910
2 sin 120579 minus 119910
2 cos 120579 cos120593
1205882119909 sin 120579 + 120588
2119909 cos 120579 cos120593 minus 120588
2119911 cos 120579 + 120588
2119911 sin 120579 cos120593
1205882119911
+ 1199102 cos 120579 minus 119910
2 sin 120579 cos120593 minus 120588
2119909
120579 minus 1205882119909 sin120593
]]
]
(9)
Mathematical Problems in Engineering 5
R1198984
=∘
1205884
+ 120596 times (r4+ 120588
4) = [
[
1205884119909
0
1205884119911
]
]
+[[
[
cos 120579 minus sin 120579 cos120593120579 + sin120593
sin 120579 + cos 120579 cos120593
]]
]
times [
[
1205884119909
1199104
1205884119911
]
]
=[[
[
1205884119909
+ 1205884119911
120579 + 1205884119911 sin120593 minus 119910
4 sin 120579 minus 119910
4 cos 120579 cos120593
1205884119909 sin 120579 + 120588
4119909 cos 120579 cos120593 minus 120588
4119911 cos 120579 + 120588
4119911 sin 120579 cos120593
1205884119911
+ 1199104 cos 120579 minus 119910
4 sin 120579 cos120593 minus 120588
4119909
120579 minus 1205884119909 sin120593
]]
]
(10)
The components of the position and velocity vectors of anarbitrary point on the supporting beam can be computed byusing the above five equations
In Figure 4 1205821and 120582
2are the boom tilt and azimuth
angles relative to the sailcraft body axes respectively Thecomponents of r
119901can be expressed as follows by using these
two angles
r119901=10038161003816100381610038161003816r119901
10038161003816100381610038161003816cos 120582
1i119887+10038161003816100381610038161003816r119901
10038161003816100381610038161003816sin 120582
1cos 120582
2j119887+10038161003816100381610038161003816r119901
10038161003816100381610038161003816sin 120582
1sin 120582
2k119887
(11)
The position and velocity vectors of the payload can beobtained as
R119874119901
= R119874+ r
119901 k
119874119901= k
119874+ r
119901 (12)
where r119901=∘r119901+ 120596 times r
119901 And ∘r
119901can be expressed as
∘r119901= minus
10038161003816100381610038161003816r119901
100381610038161003816100381610038161sin 120582
1i119887+10038161003816100381610038161003816r119901
10038161003816100381610038161003816
times (1cos 120582
1cos 120582
2minus
2sin 120582
1sin 120582
2) j
119887
+10038161003816100381610038161003816r119901
10038161003816100381610038161003816(
1cos 120582
1sin 120582
2+
2sin 120582
1cos 120582
2) k
119887
(13)
Thus r119901can be obtained as
r119901= [[minus119897
1199011sin 120582
1+ 119897
119901sin 120582
1sin 120582
2( 120579 + sin120593)
minus 119897119901sin 120582
1cos 120582
2( sin 120579 + cos 120579 cos120593)]
times [119897119901(
1cos 120582
1cos 120582
2minus
2sin 120582
1sin 120582
2)
+ 119897119901cos 120582
1( sin 120579 + cos 120579 cos120593)
minus 119897119901sin 120582
1sin 120582
2( cos 120579 minus sin 120579 cos120593)]
times 119897119901(
1cos 120582
1sin 120582
2+
2sin 120582
1cos 120582
2)
+ 119897119901sin 120582
1cos 120582
2( cos 120579 minus sin 120579 cos120593)
minus 119897119901cos 120582
1( 120579 + sin120593)]
(14)
The position vectors of the two sliding masses can beobtained as
Rℎ119895
= R119874+ r
ℎ119895+ 120588
ℎ119895
kℎ2
= k119874+∘rℎ119895
+∘
120588ℎ119895
+ 120596 times (rℎ119895
+ 120588ℎ119895)
(119895 = 1 2)
(15)
If the orbital motion and its influence on attitude motioncan be neglected then the position and velocity vectors canbe obtained as follows
Rℎ2
= rℎ2
+ 120588ℎ2
= [120588ℎ2119909
120588ℎ2119910
119911ℎ2]119879
Rℎ1
= rℎ1
+ 120588ℎ1
= [120588ℎ1119909
119910ℎ1 120588
ℎ1119911]119879
Rℎ2
=[[
[
120588ℎ2119909
+ 119911ℎ2
( 120579 + sin120593) minus 120588ℎ2119910
( sin 120579 + cos 120579 cos120593)120588ℎ2119910
+ 120588ℎ2119909
( sin 120579 + cos 120579 cos120593) minus 119911ℎ2
( cos 120579 minus sin 120579 cos120593)ℎ2
+ 120588ℎ2119910
( cos 120579 minus sin 120579 cos120593) minus 120588ℎ2119909
( 120579 + sin120593)
]]
]
Rℎ1
=[[
[
120588ℎ1119909
+ 120588ℎ1119911
( 120579 + sin120593) minus 119910ℎ1
( sin 120579 + cos 120579 cos120593)119910ℎ1
+ 120588ℎ1119909
( sin 120579 + cos 120579 cos120593) minus 120588ℎ1119911
( cos 120579 minus sin 120579 cos120593)120588ℎ1119911
+ 119910ℎ1
( cos 120579 minus sin 120579 cos120593) minus 120588ℎ1119909
( 120579 + sin120593)
]]
]
(16)
6 Mathematical Problems in Engineering
24 The Kinetic Energy The kinetic energy of the sail systemcan be obtained by neglecting the orbital motion and itsinfluence on attitude motion Consider
1198791198983
=1
2119898
119897int
119897
0
[∘
1205883
+ 120596 times (r3+ 120588
3)] sdot [
∘
1205883
+ 120596 times (r3+ 120588
3)] 119889119911
1198791198981
=1
2119898
119897int
0
minus119897
[∘
1205881
+ 120596 times (r1+ 120588
1)]
sdot [∘
1205881
+ 120596 times (r1+ 120588
1)] 119889119911
1198791198982
=1
2119898
119897int
119897
0
[∘
1205882
+ 120596 times (r2+ 120588
2)] sdot [
∘
1205882
+ 120596 times (r2+ 120588
2)] 119889119910
1198791198984
=1
2119898
119897int
0
minus119897
[∘
1205884
+ 120596 times (r4+ 120588
4)] sdot [
∘
1205884
+ 120596 times (r4+ 120588
4)] 119889119910
(17)
The above equations can be rewritten as
119879119898
=1
2120596 sdot J sdot 120596
+1
2119898
119897int
119897
0
2∘
1205883
sdot (120596 times r3) + (120596 times 120588
3) sdot (120596 times 120588
3)
+ 2 (120596 times r3) sdot (120596 times 120588
3) 119889119911
+1
2119898
119897int
0
minus119897
2∘
1205881
sdot (120596 times r1) + (120596 times 120588
1) sdot (120596 times 120588
1)
+ 2 (120596 times r1) sdot (120596 times 120588
1) 119889119911
+1
2119898
119897int
119897
0
2∘
1205882
sdot (120596 times r2) + (120596 times 120588
2) sdot (120596 times 120588
2)
+ 2 (120596 times r2) sdot (120596 times 120588
2) 119889119910
+1
2119898
119897int
0
minus119897
2∘
1205884
sdot (120596 times r4) + (120596 times 120588
4) sdot (120596 times 120588
4)
+ 2 (120596 times r4) sdot (120596 times 120588
4) + (120596 times r
4)
sdot (120596 times r4) 119889119910
(18)
where J = sum4
119895=1
J119898119895
is the moment of inertia of sail systemJ119898119895
(119895 = 1ndash4) is the moment of inertia of the 119895th sail sys-tem and the expression of J can be expressed as J = diag[119869
119909
119869119910 119869
119911] inO
119874x119887y119887z119887
The kinetic energy of the payload is
119879119901=
1
2119898
119901
10038161003816100381610038161003816r119901
10038161003816100381610038161003816
2
=1
2119898
119901[minus119897
1199011sin 120582
1+ 119897
119901sin 120582
1sin 120582
2( 120579 + sin120593)
minus 119897119901sin 120582
1cos 120582
2( sin 120579 + cos 120579 cos120593)]
2
+1
2119898
119901[119897119901(
1cos 120582
1cos 120582
2minus
2sin 120582
1sin 120582
2)
+ 119897119901cos 120582
1( sin 120579 + cos 120579 cos120593)
minus 119897119901sin 120582
1cos 120582
2( cos 120579 minus sin 120579 cos120593)]
2
+1
2119898
119901[119897119901(
1cos 120582
1sin 120582
2+
2sin 120582
1cos 120582
2)
+ 119897119901sin 120582
1cos 120582
2( cos 120579 minus sin 120579 cos120593)
minus 119897119901cos 120582
1( 120579 + sin120593)]
2
(19)
The kinetic energy of the sliding masses can be obtainedas follows by neglecting the orbital motion and its influenceon attitude control
119879ℎ1
=1
2119898
ℎ1[ ( 120588
ℎ1119909+ 120579120588
ℎ1119911+ 120588
ℎ1119911sin120593
minus 119910ℎ1sin 120579 minus 119910
ℎ1cos 120579 cos120593)
2
]
+1
2119898
ℎ1[( 119910
ℎ1+ 120588
ℎ1119909sin 120579 + 120588
ℎ1119909cos 120579 cos120593
minus 120588ℎ1119911
cos 120579 + 120588ℎ1119911
sin 120579 cos120593)2]
+1
2119898
ℎ1[( 120588
ℎ1119911+ 119910
ℎ1cos 120579 minus 119910
ℎ1sin 120579 cos120593
minus 120579120588ℎ1119909
+ 120588ℎ1119909
sin120593)2
]
119879ℎ2
=1
2119898
ℎ2[( 120588
ℎ2119909+ 120579119911
ℎ2+ 119911
ℎ2sin120593 minus 120588
ℎ2119910sin 120579
minus 120588ℎ2119910
cos 120579 cos120593)2
]
+1
2119898
ℎ2[( 120588
ℎ2119910+ 120588
ℎ2119909sin 120579 + 120588
ℎ2119909cos 120579 cos120593
minus 119911ℎ2cos 120579 + 119911
ℎ2sin 120579 cos120593)
2
]
+1
2119898
ℎ2[(
ℎ2+ 120588
ℎ2119910cos 120579 minus 120588
ℎ2119910sin 120579 cos120593
minus 120579120588ℎ2119909
minus 120588ℎ2119909
sin120593)2
]
(20)
25 The Gravitational Potential Energy The gravitationalpotential energies of the sail system 119880
119892119891 payload 119880
119892119901 and
sliding masses 119880119892ℎ1
119880119892ℎ2
can be obtained as
119880119892119891
= minus
120583119898119891
1003816100381610038161003816R119874
1003816100381610038161003816
119880119892119901
= minus
120583119898119901
10038161003816100381610038161003816R119874+ r
119901
10038161003816100381610038161003816
119880119892ℎ1
= minus120583119898
ℎ1
1003816100381610038161003816R119874+ r
ℎ1
1003816100381610038161003816
119880119892ℎ2
= minus120583119898
ℎ2
1003816100381610038161003816R119874+ r
ℎ2
1003816100381610038161003816
(21)
Mathematical Problems in Engineering 7
26 The Generalized Forces The components of the sunlightunit vector S can be obtained as follows by referring toFigure 3 (left) in 120587
119868
S = j119868= [1 0 0]
119879
119868
(22)
Based on the abovementioned equations the componentsof S in 120587
119887can be obtained as
S = C119887119868[1 0 0]
119879
119868
= [119878119909
119878119910
119878119911]119879
119887
(23)
The resultant SRP force can be simply modeled as followsfor a perfectly reflective control vane
F119894= 120578119875119860
119862119894(S sdot n
119862119894)2 n
119862119894= 119865
119862119894cos2120572
119862119894n119862119894 (24)
where 120578 is the overall sail-thrust coefficient (120578max = 2) 119875 =
4563 times 10minus6 Nm2 119860
119862119894is the area of the 119894th control vane
119865119862119894
= 120578119875119860119862119894is themaximumcontrol vane thrust andn
119862119894= i
119894
is the unit normal vector of the control vaneThe componentsof n
119862119894in 120587
119887can be written as
n119862119894
= C119887119894[1 0 0]
119879
119894
= [119878119909119894
119878119910119894
119878119911119894]119879
119887
(25)
The control torque by the 119894th control vane can beexpressed as
M119894= L
119894times F
119894 (26)
In fact L119894and F
119894are dependent on the deformations of
the supporting beams and control vanes In this paper it isassumed thatL
119894andF
119894are not influenced by the deformations
of the structure when computing the control torque by thecontrol vanes Thus L
119894and F
119894can be expressed as
L1= [0 0 minus119897]
119879
L2= [0 119897 0]
119879
L3= [0 0 119897]
119879
L4= [0 minus119897 0]
119879
F119894= 120578119875119860
119862119894([119878
119909119878119910
119878119911]119887
sdot [119878119909119894
119878119910119894
119878119911119894]119879
119887
)
2
[119878119909119894
119878119910119894
119878119911119894]119879
119887
(27)
The force of each control vane can be written as
F119894= (119865
119862119894cos2120572
119862119894)C
119887119894[1 0 0]
119879
119894
= (119865119862119894cos2120572
119862119894) [119878
119909119894119878119910119894
119878119911119894]119879
119887
(28)
where 120572119862119894
is the sun angle of the 119894th control vane that canbe measured by the sun sensor And the components of thecontrol torques can be obtained as
M1198881
= (1198651198621cos2120572
1198621)[
[
0
0
minus119897
]
]
times (C1198871
[
[
1
0
0
]
]
)
= (1198651198621cos2120572
1198621)
times [
[
minus119897 cos1205931sin120595
1
minus119897 (cos 1205791cos120595
1minus sin 120579
1sin120593
1sin120595
1)
0
]
]
M1198882
= (1198651198622cos2120572
1198622)
times [
[
119897 (sin 1205792cos120595
2+ cos 120579
2sin120593
2sin120595
2)
0
minus119897 (cos 1205792cos120595
2minus sin 120579
2sin120593
2sin120595
2)
]
]
M1198883
= (1198651198623cos2120572
1198623)
times [
[
119897 cos1205933sin120595
3
119897 (cos 1205793cos120595
3minus sin 120579
3sin120593
3sin120595
3)
0
]
]
M1198884
= (1198651198624cos2120572
1198624)
times [
[
minus119897 (sin 1205794cos120595
4+ cos 120579
4sin120593
4sin120595
4)
0
119897 (cos 1205794cos120595
4minus sin 120579
4sin120593
4sin120595
4)
]
]
(29)
27 Attitude Dynamics of Solar Sail The attitude dynamicscan be obtained by using the Lagrange equation method as
119889
119889119905(
120597119871
120597 119902119895
) minus120597119871
120597119902119895
= 119876119895 (30)
where 119871 is the Lagrange function 119902119895(119895 = 1ndash3) is the vector
of the generalized coordinates and 119876119895is the vector of the
generalized force 119871 can be computed as
119871 = 119879 minus 119880 =
4
sum
119894=1
119879119898119894
+ 119879119901+
2
sum
119895=1
119879ℎ119895
minus (119880119892119891
+ 119880119892119901
+
2
sum
119895=1
119880119892ℎ119895
)
(31)
where 119879119898119894 119879
119901 and 119879
ℎ119895are the kinetic energies of the
supporting beams payload and sliding masses respectively119880119892119891 119880
119892119901 and 119880
119892ℎ119895are the gravitational potential energies of
the sail system payload and sliding masses respectively
8 Mathematical Problems in Engineering
OOx
y
z
FCFCy
FCx
FCz
mh
q(x)
Figure 5 The vibration model
120590
120590e
120590120592
120590
Figure 6 The viscoelastic model
3 The Vibration of Solar Sail
The mechanical and material models of the sailcraft aregivenThe displacement filed stress and strain are presentedbased on the Euler beam assumptionThe Lagrange equationmethod is adopted to derive the vibration equations withlarge deformations based on the calculations of kineticenergies and works done by the external loads
31 The Mechanical Model The body frame O119874xyz is estab-
lished to describe the vibration (see Figure 5) F119862is the force
vector generated by the control vane used located at the tip ofthe supporting beam 119865
119862119909 119865
119862119910 and 119865
119862119911are the components
inO119874xyz 119902(119909) is the distributed load caused by SRP
32 The Material Model The carbon fibre enforced compos-ite material is used to construct the inflatable deploymentsupporting beam The model of the viscoelastic material canbe represented in Figure 6
The total stress is the summation of the elastic and viscousstresses It can be expressed as
120590 = 120590119890
+ 120590120592
= 119864120576 + 119888119887
120576 (32)
where 120590 120590119890 and 120590
120592 are the total elastic and viscous stressrespectively And 119864 is Youngrsquos modulus 120576 ( 120576) is the strain(strain rate) and 119888
119887is the coefficient of the internal damping
expressed as 119864120578119887 120578
119887is the proportionality constant of the
internal damping The dimensions of 119888119887and 120578
119887are N lowast sm2
and s respectively
OO x
y The support beam
Z
Figure 7 The schematic diagram of solar sail supporting beamdeformation
33 The Displacement Field Stress and Strain The deforma-tion of a spatial solar sail supporting beam is presented inFigure 7
The spatial displacement fields for supporting beam are as
119906 (119909 119910 119911 119905) = 1199060(119909 119905) minus 119910
120597V0
120597119909minus 119911
1205971199080
120597119909
V (119909 119910 119911 119905) = V0(119909 119905)
119908 (119909 119910 119911 119905) = 1199080(119909 119905)
(33)
119906(119909 119910 119911 119905) V(119909 119910 119911 119905) and 119908(119909 119910 119911 119905) are the displace-ments along 119909 119910 and 119911 directions respectively 119906
0(119909 119905)
V0(119909 119905) and 119908
0(119909 119905) are the axial and transverse displace-
ments of an arbitrary point on the neutral axisBy using Green strain definition von Karmanrsquos nonlinear
strain-displacement relationships based on assumptions oflarge deflections moderate rotations and small strains for a3D supporting beam are given as follows together with thestrain rate and normal stress
120576119909119909
=120597119906
0
120597119909+1
2(120597V
0
120597119909)
2
minus 1199101205972V
0
1205971199092
+1
2(120597119908
0
120597119909)
2
minus 1199111205972
1199080
1205971199092
120576119909119909
=120597
0
120597119909+(
120597V0
120597119909)(
120597V0
120597119909) minus 119910
1205972V
0
1205971199092
+(120597119908
0
120597119909)(
1205970
120597119909)
minus 1199111205972
0
1205971199092
120590119909119909
= 119864[120597119906
0
120597119909+1
2(120597V
0
120597119909)
2
minus 1199101205972V
0
1205971199092
+1
2(120597119908
0
120597119909)
2
minus 1199111205972
1199080
1205971199092
]
+ 119864120578119887(120597
0
120597119909+(
120597V0
120597119909)(
120597V0
120597119909) minus 119910
1205972V
0
1205971199092
+(120597119908
0
120597119909)(
1205970
120597119909) minus 119911
1205972
0
1205971199092
)
(34)
Mathematical Problems in Engineering 9
The single underlined terms in the preceding equationindicate the contribution by the geometrical nonlinearityThedynamics models and corresponding numerical simulationwithout considering the geometrical nonlinearity can beobtained and carried out by neglecting these terms
34 The Energies and Works Done by External Forces Thestrain energy can be derived as
119880119894=
1
2int
119897
0
119860119909119909
[120597119906
0
120597119909+
1
2(120597V
0
120597119909)
2
+1
2(120597119908
0
120597119909)
2
]
2
+ 119863119909119909
1205972V
0
1205971199092
+ 119863119909119909
1205972
1199080
1205971199092
119889119909
(35)
For an isotropic support beam the extensional stiffness119860
119909119909and bending stiffness119863
119909119909can be computed as
119860119909119909
= int119860
119864119889119860 119863119909119909
= int119860
1198641199112
119889119860 = int119860
1198641199102
119889119860 (36)
The dissipation function is as
Ψ119902=
1
2int
119897
0
[119860119909119909120578119887(120597
0
120597119909)
2
+ 119863119909119909120578119887(1205972V
0
1205971199092
)
2
+ 119863119909119909120578119887(1205972
0
1205971199092
)
2
]119889119909
(37)
The kinetic energy for the support beam is as
119879119890=
1
2int
119897
0
[119868119860(120597119906
0
120597119905)
2
+ 119868119860(120597119908
0
120597119905)
2
+ 119868119863(1205972
1199080
120597119909120597119905)
2
+ 119868119860(120597V
0
120597119905)
2
+ 119868119863(
1205972V
0
120597119909120597119905)
2
]119889119909
(38)
where 119868119860and 119868
119863are integration constant for the support
beam expressed as
119868119860= int
119860
120588119889119860 = 120588119860 119868119863= int
119860
1205881199112
119889119860 = int119860
1205881199102
119889119860 (39)
And the work done by the external force can be obtainedas119882 = 119865
119862119911sdot 119908 (119909
119888 119905) + 119865
119862119910sdot V (119909
119888 119905) + 119898
ℎ119886ℎ119910
(119909ℎ 119905) V (119909
ℎ 119905)
+ 119898ℎ119886ℎ119911
(119909ℎ 119905) 119908 (119909
ℎ 119905) + int
119897
0
119902 (119909) V (119909 119905) 119889119909
(40)where 119909
119888represents the position of the support beam
119908(119909119888 119905) V(119909
119888 119905) are the displacements along 119911 and 119910 direc-
tions respectively and the corresponding loads 119865119862119911 119865
119862119910are
known functions 119909ℎ 119897 and V
ℎare the position coordinate of
the sliding mass the length of the support beam and theconstant-velocity of the sliding mass The dynamic responseis studied only during the period [0 119897V
ℎ] 119898
ℎis the mass
and 119886ℎ119910(119909
ℎ 119905) and 119886
ℎ119911(119909
ℎ 119905) are the components of the
acceleration for a material point on the support beam theslidingmass just arrived at And the corresponding transversedeflections are 119908(119909
ℎ 119905) and V(119909
ℎ 119905) respectively
35 The Assumed Modes Method The axial displacement1199060(119909 119905) and the transverse deflections V
0(119909 119905) and119908
0(119909 119905) can
be represented as follows by considering the assumed modesmethod
1199060(119909 119905) =
infin
sum
119894=1
119880119894(119909)119880
119894(119905)
V0(119909 119905) =
infin
sum
119895=1
119881119895(119909) 119881
119895(119905)
1199080(119909 119905) =
infin
sum
119896=1
119882119896(119909)119882
119896(119905)
(41)
where 119880119894(119905) 119881
119895(119905) and 119882
119896(119905) are the time-dependent gen-
eralized coordinates and 119880119894(119909) 119881
119895(119909) and 119882
119896(119909) are the
assumedmodes For assumedmodemethod themode shapefunctions should satisfy the following requirements in thispaper
119880119894(119909)
1003816100381610038161003816119909=0= 0 119881
119895(119909)
10038161003816100381610038161003816119909=0= 0 119882
119896(119909)
1003816100381610038161003816119909=0= 0
1198811015840
119895
(119909)10038161003816100381610038161003816119909=0
= 0 1198821015840
119896
(119909)10038161003816100381610038161003816119909=0
= 0
(42)
The following first two assumed modes satisfying theassumed mode principle are used in this paper
1198801(119909) =
119909
119897 119880
2(119909) = (
119909
119897)
2
1198811(119909) = (
119909
119897)
2
1198812(119909) = (
119909
119897)
3
1198821(119909) = (
119909
119897)
2
1198822(119909) = (
119909
119897)
3
(43)
With the help of the assumedmodes the detailed expres-sions of 119880
119894 119879
119890119882
119911 and Ψ
119902can be obtained as
119880119894=
9
2
119860119909119909
1198973(119881
2
2
+ 1198822
2
)2
+27
4
119860119909119909
1198973(119881
11198812+ 119882
1119882
2)
times (1198812
2
+ 1198822
2
)
+18
7
119860119909119909
1198973[(119881
2
1
+ 1198822
1
) (1198812
2
+ 1198822
2
) + (11988111198812+ 119882
1119882
2)2
]
+119860
119909119909
1198973[3
2119897119880
2(119881
2
2
+ 1198822
2
) + (1198812
1
+ 1198822
1
)
times (11988111198812+ 119882
1119882
2)]
10 Mathematical Problems in Engineering
+1
10
119860119909119909
1198973[9119880
1119897 (119881
2
2
+ 1198822
2
) + 241198802119897 (119881
11198812+ 119882
1119882
2)
+ 4 (1198812
1
+ 1198822
1
)2
]
+119860
119909119909
1198972[3
21198801(119881
11198812+ 119882
1119882
2) + 119880
2(119881
2
1
+ 1198822
1
)]
+6119863
119909119909119881
2
2
1198973+ 119860
119909119909(2119880
1119881
2
1
31198972+
21198801119882
2
1
31198972+
21198802
2
3119897)
+6119863
119909119909119882
2
2
1198973+
611986311990911990911988111198812
1198973+
11986011990911990911988011198802
119897+
6119863119909119909119882
1119882
2
1198973
+119860
119909119909119880
2
1
2119897+
2119863119909119909119881
2
1
1198973+
2119863119909119909119882
2
1
1198973
119879119890=
1
14(119897119868
119860
2
2
+ 119897119868119860
2
2
) +1
6(119897119868
119860
1
2+ 119897119868
11986012)
+1
10(119897119868
119860
2
2
+ 119897119868119860
2
1
+9119868
119863
2
2
119897+ 119897119868
119860
2
1
+9119868
119863
2
2
119897)
+1
4(119897119868
11986012+
6119868119863
1
2
119897+
611986811986312
119897)
+1
6(119897119868
119860
2
1
+4119868
119863
2
1
119897+
4119868119863
2
1
119897)
119882119911= 119865
119862119911sdot [119882
1(119905) + 119882
2(119905)] + 119865
119862119910sdot [119881
1(119905) + 119881
2(119905)]
+ 119898ℎ[2V2
ℎ
1198972sdot 119881
1(119905) +
4V2ℎ
119905
1198972sdot
1(119905) + (
Vℎ119905
119897)
2
sdot 1(119905)
+6V3
ℎ
119905
1198973sdot 119881
2(119905) +
6V3ℎ
1199052
1198973
sdot 2(119905) + (
Vℎ119905
119897)
3
sdot 2(119905)]
times [(Vℎ119905
119897)
2
sdot 1198811(119905) + (
Vℎ119905
119897)
3
sdot 1198812(119905)]
+ 119898ℎ[2V2
ℎ
1198972sdot 119882
1(119905) +
4V2ℎ
119905
1198972sdot
1(119905) + (
Vℎ119905
119897)
2
sdot 1(119905)
+6V3
ℎ
119905
1198973sdot 119882
2(119905) +
6V3ℎ
1199052
1198973sdot
2(119905)
+ (Vℎ119905
119897)
3
sdot 2(119905)]
times [(Vℎ119905
119897)
2
sdot 1198821(119905) + (
Vℎ119905
119897)
3
sdot 1198822(119905)]
+ 1198811(119905) sdot int
119897
0
119902 (119909) (119909
119897)
2
119889119909 + 1198812(119905)
sdot int
119897
0
119902 (119909) (119909
119897)
3
119889119909
Ψ119902=
1
6(36119863
119909119909120578119887
2
2
1198976+
4119860119909119909120578119887
2
2
1198974+
36119863119909119909120578119887
2
2
1198976) 119897
3
+1
4(4119860
11990911990912057811988712
1198973+
2411986311990911990912057811988712
1198975
+24119863
119909119909120578119887
1
2
1198975) 119897
2
+1
2
119860119909119909120578119887
2
1
119897+
2119863119909119909120578119887
2
1
1198973+
2119863119909119909120578119887
2
1
1198973
(44)
36 The Vibration Equation The Lagrange equation methodis used to derive the vibration equations
120597119871
120597119902119899
minus119889
119889119905(
120597119871
120597 119902119899
) + 119876119889= 0 119899 = 1 2 6 (45)
where 119871 is the Lagrange function 119902119899
= (1198801 119880
2 119881
1 119881
2
1198821119882
2)119879 is the vector of the generalized coordinates and
119902119899is the corresponding generalized velocity vector 119876
119889is the
generalized damping force The expressions for 119871 and 119876119889are
as
119871 = 119879119890minus (119880
119894minus 119882
119911)
119876119889= minus
120597Ψ119902
120597 119902119899
(119899 = 1 sim 6)
(46)
The axial vibration equations can be obtained as followsfor 119880
1 119880
2
1
31198971198681198601+
1
41198971198681198602+
120578119887119860
1199091199091
119897+
120578119887119860
1199091199092
119897+
1198601199091199091198801
119897
+119860
1199091199091198802
119897+
2119860119909119909119881
2
1
31198972+
311986011990911990911988111198812
21198972+
9119860119909119909119881
2
2
101198972
+2119860
119909119909119882
2
1
31198972+
3119860119909119909119882
1119882
2
21198972+
9119860119909119909119882
2
2
101198972= 0
(47a)
1
41198971198681198601+
1
51198971198681198602+
120578119887119860
1199091199091
119897+
4120578119887119860
1199091199092
3119897
+119860
1199091199091198801
119897+4119860
1199091199091198802
3119897+119860
119909119909119881
2
1
1198972+12119860
11990911990911988111198812
51198972+3119860
119909119909119881
2
2
21198972
+119860
119909119909119882
2
1
1198972+
12119860119909119909119882
1119882
2
51198972+
3119860119909119909119882
2
2
21198972= 0
(47b)
The following can be seen from the above equations
(1) Since the assumed modes rather than the naturalmodes are used the coupling between axial and trans-verse vibrations is rather severe for axial vibrations
Mathematical Problems in Engineering 11
(2) The nonlinearity is apparent in above equations onlyexisting in the terms of 119881
1 119881
2119882
1119882
2 We take (47a)
as an exampleThe terms including1198802and its first and
second derivative 1198811 119881
2119882
1119882
2 can be regarded as
the applied loads for 1198801
(3) The coupling between the axial and transverse vibra-tionswill disappear as long as the linear displacement-strain relationship is adopted
(4) There are no external loads for axial vibrationsaccording to above equations
The transverse vibration equations for 1198811 119881
2and119882
1 119882
2
can be obtained as
4
3
1198681198631
119897+
1
51198971198681198601+
1
61198971198681198602minus
119898ℎV5ℎ
1199055
2
1198975+
31198681198632
2119897
+4119898
ℎV4ℎ
1199053
1
1198974+
4120578119887119863
1199091199091
1198973minus
2119898ℎV5ℎ
1199054
2
1198975+
6120578119887119863
1199091199092
1198973
+8119898
ℎV4ℎ
1199052
1198811
1198974+
41198631199091199091198811
1198973+
8119898ℎV5ℎ
1199053
1198812
1198975+
61198631199091199091198812
1198973
+27119860
1199091199091198812119882
2
2
81198973+
541198601199091199091198811119881
2
2
71198973+
181198601199091199091198811119882
2
2
71198973
+6119860
119909119909119881
2
1
1198812
1198973+
21198601199091199091198812119882
2
1
1198973+
1211986011990911990911988021198812
51198972
+8119860
1199091199091198811119882
2
1
51198973+
311986011990911990911988011198812
21198972+
211986011990911990911988021198811
1198972
+8119860
119909119909119881
3
1
51198973+
27119860119909119909119881
3
2
81198973+
361198601199091199091198812119882
1119882
2
71198973
+4119860
1199091199091198811119882
1119882
2
1198973+
411986011990911990911988011198811
31198972minus 119865
119888119910(119905) minus 05119865
025119865= 0
1
61198971198681198601+
3
2
1198681198631
119897minus
119898ℎV5ℎ
1199055
1
1198975+
1
71198971198681198602+
9
5
1198681198632
119897
+6120578
119887119863
1199091199091
1198973+
2119898ℎV5ℎ
1199054
1
1198975+
12120578119887119863
1199091199092
1198973+
6119898ℎV6ℎ
1199055
2
1198976
+6119863
1199091199091198811
1198973+
16119898ℎV5ℎ
1199053
1198811
1198975+
121198631199091199091198812
1198973+
18119898ℎV6ℎ
1199054
1198812
1198976
+9119860
1199091199091198812119882
2
2
21198973+
811198601199091199091198811119881
2
2
81198973+
311986011990911990911988011198811
21198972
+27119860
1199091199091198811119882
2
2
81198973+
541198601199091199091198812119881
2
1
71198973+
181198601199091199091198812119882
2
1
71198973
+3119860
11990911990911988021198812
1198972+
21198601199091199091198811119882
2
1
1198973+
911986011990911990911988011198812
51198972+
1211986011990911990911988021198811
51198972
+9119860
119909119909119881
3
2
21198973+
2119860119909119909119881
3
1
1198973+
271198601199091199091198812119882
1119882
2
41198973
+36119860
1199091199091198811119882
1119882
2
71198973minus 04119865
025119865minus 119865
119888119910(119905) = 0
4
3
119868119863
1
119897+
1
5119897119868119860
1+
3
2
119868119863
2
119897+
1
6119897119868119860
2minus
119898ℎV5ℎ
1199055
2
1198975
+4120578
119887119863
119909119909
1
1198973+
4119898ℎV4ℎ
1199053
1
1198974minus
2119898ℎV5ℎ
1199054
2
1198975+
6120578119887119863
119909119909
2
1198973
+4119863
119909119909119882
1
1198973+
8119898ℎV4ℎ
1199052
1198821
1198974+
8119898ℎV5ℎ
1199053
1198822
1198975+
6119863119909119909119882
2
1198973
+36119860
119909119909119882
211988111198812
71198973+
4119860119909119909119882
111988111198812
1198973+
27119860119909119909119882
2119881
2
2
81198973
+18119860
119909119909119882
1119881
2
2
71198973+
54119860119909119909119882
1119882
2
2
71198973+
6119860119909119909119882
2
1
1198822
1198973
+2119860
119909119909119882
2119881
2
1
1198973+
121198601199091199091198802119882
2
51198972+
8119860119909119909119882
1119881
2
1
51198973
+3119860
1199091199091198801119882
2
21198972+
21198601199091199091198802119882
1
1198972+
27119860119909119909119882
3
2
81198973
+8119860
119909119909119882
3
1
51198973+
41198601199091199091198801119882
1
31198972minus 119865
119888119911(119905) = 0
1
7119897119868119860
2+
9
5
119868119863
2
119897+
1
6119897119868119860
1minus
119898ℎV5ℎ
1199055
1
1198975+
3
2
119868119863
1
119897
+6120578
119887119863
119909119909
1
1198973+
2119898ℎV5ℎ
1199054
1
1198975+
6119898ℎV6ℎ
1199055
2
1198976
+12120578
119887119863
119909119909
2
1198973+
6119863119909119909119882
1
1198973+
16119898ℎV5ℎ
1199053
1198821
1198975
+12119863
119909119909119882
2
1198973+
18119898ℎV6ℎ
1199054
1198822
1198976+
31198601199091199091198801119882
1
21198972
+27119860
119909119909119882
211988111198812
41198973+
36119860119909119909119882
111988111198812
71198973+
9119860119909119909119882
2119881
2
2
21198973
+27119860
119909119909119882
1119881
2
2
81198973+
81119860119909119909119882
1119882
2
2
81198973+
18119860119909119909119882
2119881
2
1
71198973
+54119860
119909119909119882
2119882
2
1
71198973+
31198601199091199091198802119882
2
1198972+
2119860119909119909119882
1119881
2
1
1198973
+9119860
1199091199091198801119882
2
51198972+
121198601199091199091198802119882
1
51198972+
2119860119909119909119882
3
1
1198973
+9119860
119909119909119882
3
2
21198973minus 119865
119888119911(119905) = 0
(48)
The complexity high coupling and nonlinearity are obvi-ous in above equations
4 The Coupled Rigid-Flexible Dynamics
The dynamics for control and dynamic simulation shouldbe presented for solar sail based on the simplification ofequations derived in previous sections Some assumptions aremade before simplifying the equations as follows
12 Mathematical Problems in Engineering
(1) Only the attitude motion is affected by the slidingmass the vibration of solar sail structure is notaffected by the sliding mass
(2) Although the attitude control is accomplished byrotating control vanes and the gimbaled controlboom moving sliding masses the specific time his-tories of the actuators are not considered here
(3) The four supporting beams are regarded as an entirestructure thus the identical generalized coordinatesare adopted in the dynamic analysis
41 The Simplified Attitude Dynamics The kinetic energy ofsolar sail supporting beams can be obtained as
119879119898
=1
2120596 sdot J sdot 120596 + 119898
119897int
119897
0
2∘
1205883
sdot (120596 times r3) + (120596 times 120588
3) sdot (120596 times 120588
3)
+ 2 (120596 times r3) sdot (120596 times 120588
3) 119889119911
+ 119898119897int
119897
0
2∘
1205882
sdot (120596 times r2) + (120596 times 120588
2) sdot (120596 times 120588
2)
+ 2 (120596 times r2) sdot (120596 times 120588
2) 119889119910
(49)
The subscripts 2 and 3 represent the second and thirdsupporting beams The displacements can be expressed as
V0119909
(119911 119905) = (119911
119897)
2
sdot 1198811(119905) + (
119911
119897)
3
sdot 1198812(119905)
1199080119910
(119911 119905) = 120572V0119909
(119911 119905) = (119911
119897)
2
sdot 1205721198811(119905) + (
119911
119897)
3
sdot 1205721198812(119905)
for the 3rd beam
V0119909
(119910 119905) = 120573V0119909
(119911 119905) = (119910
119897)
2
sdot 1205731198811(119905) + (
119910
119897)
3
sdot 1205731198812(119905)
1199080119911
(119910 119905) = 120574V0119909
(119910 119905) = (119910
119897)
2
sdot 1205741198811(119905) + (
119910
119897)
3
sdot 1205741198812(119905)
for the 2nd beam
(50)
The subscripts 119909 119910 and 119911 of the left terms in (50)represent the displacements along119909119910 and 119911directions119881
1(119905)
and 1198812(119905) are the generalized coordinates The displacements
1199080119910(119911 119905) V
0119909(119910 119905) and 119908
0119911(119910 119905) can be obtained using the
assumed modes as
1205883= V
0119909(119911 119905) i
119887+ 119908
0119910(119911 119905) j
119887
=
[[[[[
[
(119911
119897)
2
sdot 1198811(119905) + (
119911
119897)
3
sdot 1198812(119905)
120572 [(119911
119897)
2
sdot 1198811(119905) + (
119911
119897)
3
sdot 1198812(119905)]
0
]]]]]
]
1205882= V
0119909(119910 119905) i
119887+ 119908
0119911(119910 119905) k
119887
=
[[[[[
[
120573[(119910
119897)
2
sdot 1198811(119905) + (
119910
119897)
3
sdot 1198812(119905)]
0
120574 [(119910
119897)
2
sdot 1198811(119905) + (
119910
119897)
3
sdot 1198812(119905)]
]]]]]
]
(51)
The vibration velocity can be obtained as
∘
1205883
= 1205883119909i119887+ 120588
3119910j119887=
[[[[[
[
(119911
119897)
2
sdot 1(119905) + (
119911
119897)
3
sdot 2(119905)
1205721[(
119911
119897)
2
sdot 1(119905) + (
119911
119897)
3
sdot 2(119905)]
0
]]]]]
]
∘
1205882
= 1205882119909i119887+ 120588
2119911k119887=
[[[[[
[
1205731[(
119910
119897)
2
sdot 1(119905) + (
119910
119897)
3
sdot 2(119905)]
0
1205741[(
119910
119897)
2
sdot 1(119905) + (
119910
119897)
3
sdot 2(119905)]
]]]]]
]
(52)
Without loss of generality 120572 = 120573 = 1205721= 120573
1= 1 and
120574 = 1205741= minus1 can be assumed in above expressions And the
kinetic energy of the slidingmasses can be obtained as followsby neglecting the vibration related terms
119879ℎ=
1
2119898
ℎ1(120596 times r
ℎ1) sdot (120596 times r
ℎ1) +
1
2119898
ℎ2(120596 times r
ℎ2)
sdot (120596 times rℎ2)
(53)
The kinetic energy of the payload can be obtained as
119879119901=
1
2119898
119901(120596 times r
119901) sdot (120596 times r
119901) (54)
The following simplified attitude dynamics can beobtained by neglecting the second and higher terms ofattitude angles and vibration modes in computing the kinetic
Mathematical Problems in Engineering 13
energies of the supporting beams payload and slidingmasses Consider
119869119909 minus 119898
1198971198972
1minus
4
5119898
1198971198972
2+ 119898
ℎ11199102
ℎ1
+ 119898ℎ21199112
ℎ2
minus 119898119901119903119901119909119903119901119911 + 119898
1199011199032
119901119911
+ 1198981199011199032
119901119910
minus 119898119901119903119901119909119903119901119910
120579 = 119876120593
119869119910
120579 +2
5119898
1198971198972
2+
1
2119898
1198971198972
1+ 119898
ℎ21199112
ℎ2
120579
+ 1198981199011199032
119901119911
120579 minus 119898119901119903119901119910119903119901119911 minus 119898
119901119903119901119909119903119901119910
+ 1198981199011199032
119901119909
120579 = 119876120579
119869119911 minus
2
51198972
1198981198972minus
1
21198972
1198981198971+ 119898
ℎ11199102
ℎ1
minus 119898119901119903119901119910119903119901119911
120579 + 1198981199011199032
119901119910
+ 1198981199011199032
119901119909
minus 119898119901119903119901119909119903119901119911 = 119876
120595
(55)
where 119876120593 119876
120579 and 119876
120595are the generalized nonpotential
attitude control torques generated by the control vanes Andthe attitude control torques generated by the gimbaled controlboom and sliding masses can be found on the left side ofthe above equation coupled with 120579 making the attitudecontroller design problem rather difficult
42 The Simplified Vibration Equations The couplingbetween the axial and transverse vibrations is neglectedand only the transverse vibration is considered The attitudedynamics for dynamic simulation can be obtained as followsbased on previous derivation by neglecting the action ofsolar-radiation pressure
4
3
1198681198631
119897+
1
51198971198681198601+
1
61198971198681198602+
31198681198632
2119897+
4120578119887119863
1199091199091
1198973
+6120578
119887119863
1199091199092
1198973+
41198631199091199091198811
1198973+
61198631199091199091198812
1198973+
271198601199091199091198812119882
2
2
81198973
+54119860
1199091199091198811119881
2
2
71198973+
181198601199091199091198811119882
2
2
71198973+
6119860119909119909119881
2
1
1198812
1198973
+2119860
1199091199091198812119882
2
1
1198973+
81198601199091199091198811119882
2
1
51198973+
8119860119909119909119881
3
1
51198973
+27119860
119909119909119881
3
2
81198973+
361198601199091199091198812119882
1119882
2
71198973+
41198601199091199091198811119882
1119882
2
1198973
minus 1198651198621
(119905) = 0
1
61198971198681198601+
3
2
1198681198631
119897+
1
71198971198681198602+
9
5
1198681198632
119897+
6120578119887119863
1199091199091
1198973
+12120578
119887119863
1199091199092
1198973+
61198631199091199091198811
1198973+
121198631199091199091198812
1198973+
91198601199091199091198812119882
2
2
21198973
+81119860
1199091199091198811119881
2
2
81198973+
271198601199091199091198811119882
2
2
81198973+
541198601199091199091198812119881
2
1
71198973
+18119860
1199091199091198812119882
2
1
71198973+
21198601199091199091198811119882
2
1
1198973+
9119860119909119909119881
3
2
21198973
+2119860
119909119909119881
3
1
1198973+
271198601199091199091198812119882
1119882
2
41198973+
361198601199091199091198811119882
1119882
2
71198973
minus 1198651198622
(119905) = 0
(56)
The following equations can be obtained by rearrangingthe above equations
4
3
1198681198631
119897+
1
51198971198681198601+
1
61198971198681198602+
31198681198632
2119897+
4120578119887119863
1199091199091
1198973
+6120578
119887119863
1199091199092
1198973+
41198631199091199091198811
1198973+
61198631199091199091198812
1198973+
16119860119909119909119881
3
1
51198973
+12119860
119909119909119881
2
1
1198812
1198973+
1081198601199091199091198811119881
2
2
71198973+
54119860119909119909119881
3
2
81198973
minus 1198651198621
(119905) = 0
1
61198971198681198601+
3
2
1198681198631
119897+
1
71198971198681198602+
9
5
1198681198632
119897+
6120578119887119863
1199091199091
1198973
+12120578
119887119863
1199091199092
1198973+
61198631199091199091198811
1198973+
121198631199091199091198812
1198973
+4119860
119909119909119881
3
1
1198973+
108119860119909119909119881
2
1
1198812
71198973+
811198601199091199091198811119881
2
2
41198973
+9119860
119909119909119881
3
2
1198973minus 119865
1198622(119905) = 0
(57)
1198651198621(119905) and 119865
1198622(119905) are used to represent all the generalized
external forces they can be used for vibration control Thesecomplicated equations abovementioned are the basis forobtaining the simplified equations used for controller design
The following equations can be obtained by neglecting thetwo and higher terms
4
3
1198681198631
119897+
1
51198971198681198601+
1
61198971198681198602+
31198681198632
2119897+
4120578119887119863
1199091199091
1198973
+6120578
119887119863
1199091199092
1198973+
41198631199091199091198811
1198973+
61198631199091199091198812
1198973= 119865
1198621
(119905)
14 Mathematical Problems in Engineering
1
61198971198681198601+
3
2
1198681198631
119897+
1
71198971198681198602+
9
5
1198681198632
119897+
6120578119887119863
1199091199091
1198973
+12120578
119887119863
1199091199092
1198973+
61198631199091199091198811
1198973+
121198631199091199091198812
1198973= 119865
1198622
(119905)
(58)
43 The Rigid-Flexible Coupled Dynamics The simplifiedattitude and vibration dynamics can be written as
119886120593 + 119886
120579
120579 + 119886120595 + 119886
1198811
1+ 119886
1198812
2= 119876
120593
119887120579
120579 + 119887120595 + 119887
120593 + 119887
1198811
1+ 119887
1198812
2= 119876
120579
119888120595 + 119888
120579
120579 + 119888120593 + 119888
1198811
1+ 119888
1198812
2= 119876
120595
119889
1198811
1+ 119889
1198812
2+ 119889
1198811
1+ 119889
1198812
2+ 119889
1198811
1198811
+ 1198891198812
1198812= 119876
1198811
119890
1198811
1+ 119890
1198812
2+ 119890
1198811
1+ 119890
1198812
2+ 119890
1198811
1198811
+ 1198901198812
1198812= 119876
1198812
(59)
The related coefficients in the preceding equation can befound in (A1) in the appendix The dynamics (see (59)) isnot suitable for attitude controller design because the controlinputs exist in some coefficients of the angular accelerationsThis will make the controller design rather difficult Thusthe following dynamic model is obtained by putting theterms including the control inputs right side of the dynamicequations
119869119909 minus 119898
1198971198972
1minus
4
5119898
1198971198972
2= 119876
120593+ 119906
119869119910
120579 +2
5119898
1198971198972
2+
1
2119898
1198971198972
1= 119876
120579+ 119906
120579
119869119911 minus
1
21198972
1198981198971minus
2
51198972
1198981198972= 119876
120595+ 119906
119889
1198811
1+ 119889
1198812
2+ 119889
1198811
1+ 119889
1198812
2
+ 1198891198811
1198811+ 119889
1198812
1198812= 119876
1198811
119890
1198811
1+ 119890
1198812
2+ 119890
1198811
1+ 119890
1198812
2
+ 1198901198811
1198811+ 119890
1198812
1198812= 119876
1198812
(60)
The expressions for 119906 119906
120579
and 119906are as
119906= minus119898
ℎ11199102
ℎ1
minus 119898ℎ21199112
ℎ2
+ 119898119901119903119901119909119903119901119911 minus 119898
1199011199032
119901119911
minus 1198981199011199032
119901119910
+ 119898119901119903119901119909119903119901119910
120579
119906
120579
= minus119898ℎ21199112
ℎ2
120579 minus 1198981199011199032
119901119911
120579 + 119898119901119903119901119910119903119901119911 + 119898
119901119903119901119909119903119901119910
minus 1198981199011199032
119901119909
120579
119906= minus119898
ℎ11199102
ℎ1
+ 119898119901119903119901119910119903119901119911
120579 minus 1198981199011199032
119901119910
minus 1198981199011199032
119901119909
+ 119898119901119903119901119909119903119901119911
(61)
119906 119906
120579
and 119906are the functions of the positions of sliding
masses and payload and the angular accelerations The statevariables in (60) are defined as
1199091= 120593 119909
2= 119909
3= 120579 119909
4= 120579
1199095= 120595 119909
6= 119909
7= 119881
1
1199098=
1 119909
9= 119881
2 119909
10=
2
(62)
Thedynamics (60) can bewritten as the state-spacemodelas following
1= 119909
2
2= 119886
11199097+ 119886
21199098+ 119886
31199099+ 119886
411990910
+ 119906120593
3= 119909
4
4= 119886
51199097+ 119886
61199098+ 119886
71199099+ 119886
811990910
+ 119906120579
5= 119909
6
6= 119886
91199097+ 119886
101199098+ 119886
111199099+ 119886
1211990910
+ 119906120595
7= 119909
8
8= 119886
131199097+ 119886
141199098+ 119886
151199099+ 119886
1611990910
+ 1199061198811
9= 119909
10
10
= 119886171199097+ 119886
181199098+ 119886
191199099+ 119886
2011990910
+ 1199061198812
(63)
where 119906120579 119906
120593 and 119906
120595are the generalized control inputs
for attitude control and 1199061198811
and 1199061198812
are the generalizedcontrol inputs for vibration control The controllability canbe satisfied by analyzing (63) The attitudevibration controlinputs and the coefficients will be presented later in thissection The form of a matrix differential equation can bewritten as follows for the above equation
x = Ax + Bu (64)
The expressions of the relatedmatrices and vectors can befound as
x = [1
2
3
4
5
6
7
8
9
10]119879 x (119905
0) = x
1199050
u = [119906120593 119906
120579 119906
120595 119906
1198811
1199061198812
]119879
u (1199050) is known
(65)
where A xB and u are the system matrix state variablesvector control matrix and control inputs vector respectively
Mathematical Problems in Engineering 15
The complexity of the state-space model can be seen bypresenting the detailed expressions of control inputs forattitudevibration and related parameters in (A2) in theappendix
5 AttitudeVibration Control and Simulation
The controller for the attitude and vibration is developedusing the LQR and optimal PI theory The dynamic simula-tion is performed based on the coupled dynamics derived inthe previous sections
51 LQR and Optimal PI Based Controllers Design Thedynamics for solar sail can bewritten as follows togetherwithits quadratic cost function also defined as
x = Ax + Bu x (1199050) = x
1199050
(known)
119869 =1
2int
infin
1199050
[x119879 (119905)Qx (119905) + u119879 (119905)Ru (119905)] 119889119905
(66)
whereQ = Q119879
⩾ 0 andR = R119879
gt 0 are constantThe control-lability of [AB] and the observability of [AD] can beensured when the equationDD119879
= Q holds for anymatrixDThe optimal control input ulowast(119905)within the scope of u(119905) isin R119903119905 isin [119905
0infin] can be computed as follows to make 119869minimum
ulowast (119905) = minusKxlowast (119905) K = Rminus1B119879P (67)
where P is the nonnegative definite symmetric solution of thefollowing Riccati algebraic equations
PA + A119879P minus PBRminus1B119879P +Q = 0 (68)
And the optimal performance index can be obtained asfollows for arbitrary initial states
119869lowast
[x (1199050) 119905
0] =
1
2x1198790
Px0 (69)
The closed-loop system
x = (A minus BRminus1B119879P) x (70)
is asymptotically stableFor an orbiting solar sail the primary disturbance torque
is by the cmcp offset and the impact of the tiny dust inthe deep space The state regulator can be used to controlthe dynamic system affected by pulse disturbance torquewith good steady-state errors but will never achieve accuratesteady-state errors if the dynamics is affected by constantdisturbance torque Thus the optimal state regulator withan integrator to eliminate the constant disturbance torqueshould be presented This optimal proportional-integral reg-ulator not only eliminates the constant disturbance torque butalso possesses the property of optimal regulator
Table 1 The related parameters
Parameters ValuesCMCP offsetm [0 017678 017678]119879
The side length of square sailm 100Nominal solar-radiation pressureconstant at 1 AU from the sunNm2 4563 times 10minus6
Solar-radiation pressure forceN 912 times 10minus2
Roll inertiakglowastm2 50383Pitch and yaw inertiakglowastm2 251915Outer radiusm 0229Thickness of the supporting beamm 75 times 10minus6
Youngrsquos modulus of the supportingbeamGPa 124
Moment of inertia of the cross-sectionof the supporting beamm4 2829412 times 10minus7
Bending stiffness of the supportingbeamNlowastm2 3508471336
Proportional damping coefficient ofsupporting beams 001
Line density of the supportingbeamkgm 0106879
Cross-sectional area of the supportingbeamm2 1079 times 10minus5
Roll disturbance torqueNlowastm 0Pitch (yaw) disturbance torqueNlowastm 0016122 (minus0016122)
For the following linear system with the correspondingperformance index
x = Ax + Bu x (1199050) = x
1199050
u (1199050) = u
1199050
119869 =1
2int
infin
1199050
(x119879Qx + u119879Ru + u119879Su) 119889119905(71)
where Q = Q119879
⩾ 0 R = R119879
gt 0 and S = S119879 gt 0 If [AB]is completely controllable and meanwhile [AD
11] is com-
pletely observable with the relationship D11D119879
11
= Q thesolution can be expressed as
ulowast = minusK1x minus K
2ulowast ulowast (119905
0) = u
1199050
(72)
If B119879B is full rank we can get
ulowast = minusK3x minus K
4x ulowast (119905
0) = u
1199050
(73)
K119894(119894 = 1 2 3 4) is the function of ABQR S
The closed-loop system
[xulowast] = [
A BminusK
1minusK
2
] [xulowast] [
[
x (1199050)
u (1199050)]
]
= [x1199050
u1199050
] (74)
is asymptotically stableThe compromise between the state variables (the angle
angular velocity the vibration displacement and velocity)and control inputs (the torque by all the actuators) can
16 Mathematical Problems in Engineering
0 2000 4000 6000
0 2000 4000 6000
0 2000 4000 6000minus5
0
5
minus5
0
5
minus5
0
5
minus4
minus2
0
2
4
times10minus4
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
00162
00164
00166
4800 4900 5000
4800 4900 5000
4800 4900 5000
minus00165
minus0016
Time (s) Time (s)
Time (s)
Time (s)
Time (s)
Time (s)
Roll
erro
r120593(∘
)
Roll
erro
r120593(∘
)
Pitc
h er
ror120579
(∘)
Pitc
h er
ror120579
(∘)
Yaw
erro
r120595(∘
)
Yaw
erro
r120595(∘
)
Figure 8 The roll pitch and yaw errors
be achieved by using both the LQR based and optimal PIbased controllers for the coupled attitudevibration dynamicsystem The fact is that the attitude control ability is limitedto the control torque by the control actuators The change ofthe attitude angles and rates should not be frequent to voidexciting vibrations
Thus the weighting matrix Q and the control weightingmatrix R are selected as follows for LQR based controller
Q (1 1) = 9 times 10minus6
Q (2 2) = 1 times 10minus6
Q (3 3) = 16 times 10minus6
Q (4 4) = Q (5 5) = Q (6 6) = Q (7 7) = Q (8 8)
= Q (9 9) = Q (10 10) = 1 times 10minus6
Q (119894 119895) = 0 (119894 = 119895 119894 119895 = 1 sim 10)
R (1 1) = R (2 2) = 900 R (3 3) = 100
R (4 4) = R (5 5) = 10000
R119894119895
= 0 (119894 = 119895 119894 119895 = 1 sim 5)
(75)
TheweightingmatrixQ and the control weightingmatrixR are selected as follows for the optimal PI based controller
Q (1 1) = Q (2 2) = 4 times 10minus8
Q (3 3) = Q (4 4) = Q (5 5) = Q (6 6) = Q (7 7)
= Q (8 8) = 16 times 10minus8
Mathematical Problems in Engineering 17
minus02
0
02
Roll
rate
(∘s)
Roll
rate
(∘s)
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Pitc
h ra
te(∘s)
Pitc
h ra
te(∘s)
0 1000 2000 3000 4000 5000
minus05
0
05
minus05
0
05
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
Time (s)
Yaw
rate
(∘
s)
Yaw
rate
(∘
s)
4800 4850 4900 4950 5000
Time (s)4800 4850 4900 4950 5000
Time (s)4800 4850 4900 4950 5000
minus2
0
2
minus2
0
2
minus2
0
2
times10minus4
times10minus4
times10minus4
Figure 9 The roll pitch and yaw rates
Q (9 9) = Q (10 10) = 1 times 10minus8
Q (119894 119895) = 0 (119894 = 119895 119894 119895 = 1 sim 10)
R (1 1) = R (2 2) = R (3 3) = 1 times 10minus8
R (4 4) = R (5 5) = 4 times 10minus8
R (119894 119895) = 0 (119894 = 119895 119894 119895 = 1 sim 5)
(76)
52 The Simulation Results The initial angle errors of rollpitch and yaw are adopted as 120593(119905
0) = 3
∘ 120579(1199050) = 3
∘ and120595(119905
0) = 3
∘ the initial angular velocity errors of roll pitchand yaw are adopted as (119905
0) = 0
∘
s 120579(1199050) = 0
∘
s and(119905
0) = 0
∘
s 1198811(1199050) = 01m 119881
2(1199050) = 01m
1(1199050) = 0ms
and 2(1199050) = 0ms are adopted in this paper for dynamic
simulationThe estimated cmcp offset is 025m for a 100 times 100m
square solar sail It is assumed that the components of cmcpoffset vector are [0 017678 017678]
119879 in the body frame
The relevant parameters for dynamic simulations are givenin Table 1
The dynamic simulation results are obtained as followsby using the LQR controller based on the abovementionedQ and R related parameters and initial conditions Thedynamics simulations with (denoted by ldquowith GFrdquo) andwithout (denoted by ldquowithout GFrdquo) considering the geo-metrical nonlinearity are presented And the correspondingdiscussions and analysis are also given according to thecalculated results
The roll pitch and yaw errors are presented based onthe dynamics models with and without considering thegeometrical nonlinearityThe control effect with zero steady-state error can be achieved for roll axis by referring tothe results But the steady-state errors exist for pitch andyaw axes from Figure 8 this is because there exist constantdisturbance torques for pitch and yaw axes caused by thecmcp offset Thus the LQR based controller cannot be usedfor attitude control with good steady-state performance Thesteady-state errors of pitch and yaw axes are about 0164
∘
and minus0164∘ respectively from the corresponding partial
enlarged drawing of the figures (see the corresponding left
18 Mathematical Problems in Engineering
minus20
0
20
Roll
torq
ue (N
lowastm
)
Roll
torq
ue (N
lowastm
)
minus50
0
50
minus50
0
50
Pitc
h to
rque
(Nlowast
m)
Pitc
h to
rque
(Nlowast
m)
0 1000 2000 3000 4000 5000
0 2000 4000 6000
0 2000 4000 6000
Yaw
torq
ue (N
lowastm
)
Yaw
torq
ue (N
lowastm
)
minus002
0
002
008
01
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
minus01
minus009
minus008
Time (s)Time (s)
Time (s)Time (s)
Time (s)Time (s)
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Figure 10 The roll pitch and yaw torques
figures) A simple and practical controller should be designedto eliminate the steady-state errorsThese errorswill affect theprecision of the super long duration space mission deeply
The differences between the dynamics with and withoutthe geometrical nonlinearity effect can be observed Theamplitudes and phases change a bit by comparing the corre-sponding results
It can be observed by the partial enlarged figures(the right figures of Figure 9) that there are no steady-stateerrors for roll pitch and yaw rates The relative satisfieddynamic performance is achieved In fact a result with muchmore satisfied dynamic performance can be obtained but itwill make the desired control torques much larger duringthe initial period This will not only excite the vibration ofthe structure but also increase the burden of the controlactuators
And the differences between the dynamics models withand without the geometrical nonlinearity can also be seenmerely in the phase of the angular velocities
The desired attitude control torques are presented inFigure 10 The roll torque will tend to be zero with thedecrement of the state variable errors The pitch and yawtorques tend to be constant from the middle and bottom
figures The pitch and yaw steady-state errors can never beeliminated although the pitch and yaw torques (009Nlowastmand minus009Nlowastm) are applied continuously by theoreticalanalysis and simulations This is just a great disadvantage ofthe LQR based controller in this paper The initial controltorques can be afforded by vibrating the gimbaled controlboom andmoving the slidingmasses that can afford a relativelarge torque The control vanes can be used to afford thecontrol torques when solar sail is in steady-state process Theexpression of the attitude control inputs 119906
120593 119906
120579 and 119906
120595can be
found in previous sectionMoreover the differences between dynamics responses
with and without geometrical nonlinearity can also beobserved by comparing the corresponding results Therequired torques for the attitude control are a little largerfor the dynamics with geometrical nonlinearity And thedifference in the phase is also clear
It can be seen that the vibration of the supporting beamis depressed effectively by the simulation results in Figure 11It can be seen that the steady-state errors and the dynamicperformance are relatively satisfied It can also be seen that thedynamics responses between the model with and without the
Mathematical Problems in Engineering 19
0 1000 2000 3000 4000 5000
0 1000 2000 3000 4000 5000
minus01
0
01
minus02
0
02
Time (s) Time (s)
Time (s) Time (s)
minus5
0
5
times10minus4
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
minus1
0
1
times10minus3
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
The d
ispla
cem
ent o
f the
tip
(m)
The d
ispla
cem
ent o
f the
tip
(m)
The v
eloci
ty o
f the
tip
(ms
)
The v
eloc
ity o
f the
tip
(ms
)
Figure 11 The displacement and velocity of the tip of the supporting beam
geometrical nonlinearity effect are different in the vibrationdisplacement and velocitymagnitudes and phases (Figure 15)
The simulation results can be obtained as follows by usingthe optimal PI based controller adopting the abovementionedparameters and initial conditions
The roll pitch and yaw errors are given by using theoptimal PI based controller These errors tend to disappearby observing the partially enlarged plotting of the figure (thecorresponding right figures) (shown in Figure 12) And therelative satisfied dynamic performance can also be obtainedFrom the view of eliminating the steady-state errors the opti-mal PI based controller performs better than the LQR basedcontroller by theoretical analysis and simulation results Theformer can achieve attitude control results without pitchand yaw steady-state errors From the view of dynamicperformance both the controllers perform well In additionit can be seen that the difference between the modelswith and without geometrical nonlinearity is merely inthe phase
The roll pitch and yaw rate errors are presented inFigure 13 The dynamic and steady-state performances aresatisfied by observing the simulation results And by observ-ing the difference between the dynamics responses with and
without the influence by the geometrical nonlinearity it canbe concluded that the merely difference is the phase
The desired control torques of the roll pitch and yaw areobtained in Figure 14 by using the optimal PI based controllerIt can be seen that the value of the desired roll control torquedecreases to zero as the values of the roll angle and ratedecrease to zero The desired pitch and yaw control torquestend to be the constant values 009Nlowastm and minus009Nlowastmrespectively The desired initial control torques are large byobserving Figure 14 It is suggested that the gimbaled controlboom combining the sliding masses is adopted to afford theinitial torque Then the control vanes can be used to controlthe solar sail after the initial phase The phase differencecan also be observed by inspecting the dynamics responsesduring the 4800sim5000 s period
The vibration can be controlled effectively based on theoptimal PI controller And the relative satisfied dynamicand steady-state performances can be achieved In additionthe tiny differences exist in the magnitudes of the requiredtorques And the phase differences also exist
It can be concluded as follows by analyzing and compar-ing the simulation results based on the LQR and optimal PItheories in detail
20 Mathematical Problems in Engineering
Roll
erro
r120593(∘
)
Roll
erro
r120593(∘
)
minus5
0
5
minus5
0
5
Pitc
h er
ror120579
(∘)
Pitc
h er
ror120579
(∘)
0 1000 2000 3000 4000 5000minus10
0
10
Time (s) Time (s)
Time (s)
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
Yaw
erro
r120595(∘
)
Yaw
erro
r120595(∘
)
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
minus1
0
1
times10minus3
minus1
0
1
times10minus3
minus1
0
1
times10minus3
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Figure 12 The roll pitch and yaw errors
(1) From the view of eliminating the steady-state errorsof the pitch and yaw errors the optimal PI based con-troller performs better than the LQR based controllerby theoretical analysis and simulation results Thedynamic performances of the two controllers are bothsatisfied and the desired control torques are relativelysmall
(2) The weighting of the state variables is reflected by theweighting matrix according to the LQR and optimalPI theories The constant weighting matrices selectedin this paper can effectively reflect the initial statevariable errors but maybe reflect the final state vari-able errors deficiently The time-varying weightingmatrices should be selected
(3) For the actual orbiting solar sail the control actuators(control vanes gimbaled control boom and slidingmasses) cannot afford excessive large control torquesThus the control torques should be as small as possibleon the premise of acquiring satisfied dynamic perfor-mance and steady-state errors It will not only reducethe burden of the control actuators but also avoid
exciting structural vibration In engineering practicethe weighting matrices and the control weightingmatrices should be selected based on the attitudecontrol requirement (eg dynamic performance andsteady-state errors etc)
(4) The dynamics responses influenced by the geometri-cal nonlinearity can be observed In a word the tinydifferences between the magnitudes of the physicalvariables exist for the models with and withoutthe geometrical nonlinearity And the relative cleardifferences exist in the phases for the attitude anglesrates required torques and so forth
6 Conclusions
The coupled attitude and structural dynamics is establishedfor the highly flexible sailcraft by using the von-Karman von-Karmanrsquos nonlinear strain-displacement relationships basedon assumptions of large deflections moderate rotationsand
Mathematical Problems in Engineering 21
Roll
rate
erro
r(∘ s
)
Roll
rate
erro
r(∘ s
)
minus01
0
01
minus01
0
01
Pitc
h ra
te er
ror (
∘ s)
Pitc
h ra
te er
ror (
∘ s)
0 1000 2000 3000 4000 5000minus02
0
02
Yaw
rate
erro
r (∘ s
)
Yaw
rate
erro
r (∘ s
)
4800 4850 4900 4950 5000
minus5
0
5times10minus4
minus5
0
5
times10minus4
minus5
0
5times10minus4
Time (s)
4800 4850 4900 4950 5000
Time (s)
4800 4850 4900 4950 5000
Time (s)
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Figure 13 The roll pitch and yaw rate errors
small strains The Lagrange equation method is utilizedto derive the dynamics for controller design and dynamicsimulation The LQR and optimal PI based controllers aredesigned for the dynamics with the constant disturbancetorque caused by the cmcp offset By theoretical analysisand simulation it can be seen that both controllers cancompromise between the state variables and control inputsBecause the control actuators can hardly afford large controltorque the dynamic performance should be relaxed toreduce the requirement for the attitude control actuatorsBesides the optimal PI based controller can also eliminatethe constant disturbance torque caused by the cmcp offsetthat always exists while the LQR based controller fails toachieve the results with satisfied steady-state performancealthough the attitude control torque is always applied to thecoupled dynamic systemThe dynamics simulations with andwithout the geometrical nonlinearity effect are also carriedout And the differences between the models in magnitudesand phases are identified and analyzed It can be concludedthat the optimal PI based controller performs better than the
LQRbased controller from the viewof eliminating the steady-state error caused by the disturbance torque by the cmcpoffset
Appendix
The related parameters in above equation are given as
119886120593= 119869
119909+ 119898
ℎ11199102
ℎ1
+ 119898ℎ21199112
ℎ2
+ 1198981199011199032
119901119911
+ 1198981199011199032
119901119910
119886120579= minus 119898
119901119903119901119909119903119901119910 119886
120595= minus119898
119901119903119901119909119903119901119911
1198861198811
= minus 1198981198971198972
1198861198812
= minus4
5119898
1198971198972
119887120579= 119869
119910+ 119898
ℎ21199112
ℎ2
+ 1198981199011199032
119901119911
+ 1198981199011199032
119901119909
119887120595= minus 119898
119901119903119901119910119903119901119911 119887
120593= minus119898
119901119903119901119909119903119901119910
22 Mathematical Problems in Engineering
Roll
torq
ue (N
lowastm
)
Roll
torq
ue (N
lowastm
)
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
0 2000 4000 6000
0 2000 4000 6000
0 2000 4000 6000
Time (s)
Time (s)
Time (s)
Time (s)
Time (s)
Time (s)4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
minus01
minus008
008
009
01
minus002
0
002
minus5
0
5
minus2
0
2
Pitc
h to
rque
(Nlowast
m)
Pitc
h to
rque
(Nlowast
m)
minus2
0
2
Yaw
torq
ue (N
lowastm
)
Yaw
torq
ue (N
lowastm
)
Figure 14 The roll pitch and yaw torques
1198871198811
=1
2119898
1198971198972
1198871198812
=2
5119898
1198971198972
119888120595= 119869
119911+ 119898
ℎ11199102
ℎ1
+ 1198981199011199032
119901119910
+ 1198981199011199032
119901119909
119888120579= minus 119898
119901119903119901119910119903119901119911 119888
120593= minus119898
119901119903119901119909119903119901119911
1198881198811
= minus1
21198972
119898119897 119888
1198812
= minus2
51198972
119898119897
119889
1198811
= (4
3
119868119863
119897+
1
5119897119868119860) 119889
1198812
= (1
6119897119868119860+
3119868119863
2119897)
119889
1198811
=4120578
119887119863
119909119909
1198973 119889
1198812
=6120578
119887119863
119909119909
1198973
1198891198811
=4119863
119909119909
1198973 119889
1198812
=6119863
119909119909
1198973
1198761198811
= 1198651198621
(119905)
119890
1198811
= (3
2
119868119863
119897+
1
6119897119868119860)
119890
1198812
= (1
7119897119868119860+
9
5
119868119863
119897) 119890
1198811
=6120578
119887119863
119909119909
1198973
119890
1198812
=12120578
119887119863
119909119909
1198973 119890
1198811
=6119863
119909119909
1198973
1198901198812
=12119863
119909119909
1198973 119876
1198812
= 1198651198622
(119905)
(A1)
The detailed expressions of control inputs for attitudevibration and related parameters in the state-space model ofthe dynamics (see (62) and (63)) are presented as follows
A =
[[[[[[[[[[[[[[
[
0 1 0 0 0 0 0 0 0 0
0 0 0 0 0 0 1198861
1198862
1198863
1198864
0 0 0 1 0 0 0 0 0 0
0 0 0 0 0 0 1198865
1198866
1198867
1198868
0 0 0 0 0 1 0 0 0 0
0 0 0 0 0 0 1198869
11988610
11988611
11988612
0 0 0 0 0 0 0 1 0 0
0 0 0 0 0 0 11988613
11988614
11988615
11988616
0 0 0 0 0 0 0 0 0 1
0 0 0 0 0 0 11988617
11988618
11988619
11988620
]]]]]]]]]]]]]]
]
Mathematical Problems in Engineering 23
0 1000 2000 3000 4000 5000
0 1000 2000 3000 4000 5000
minus01
0
01
minus02
0
02
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Time (s)
Time (s)Time (s)
Time (s)
minus1
0
1
minus1
0
1
times10minus3
times10minus3Th
e disp
lace
men
t of t
he ti
p (m
)
The d
ispla
cem
ent o
f the
tip
(m)
The v
eloci
ty o
f the
tip
(ms
)
The v
eloci
ty o
f the
tip
(ms
)
Figure 15 Vibration displacement and velocity of the tip
B =
[[[[[[[[[[[[[[
[
0 0 0 0 0
1 0 0 0 0
0 0 0 0 0
0 1 0 0 0
0 0 0 0 0
0 0 1 0 0
0 0 0 0 0
0 0 0 1 0
0 0 0 0 0
0 0 0 0 1
]]]]]]]]]]]]]]
]
1198861= minus
1198981198971198972
119869119909
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus4
5119869119909
1198981198971198972
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198862= minus
1198981198971198972
119869119909
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus4
5119869119909
1198981198971198972
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198863= minus
1198981198971198972
119869119909
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus4
5119869119909
1198981198971198972
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198864= minus
1198981198971198972
119869119909
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus4
5119869119909
1198981198971198972
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
119906120593=
119876120593
119869119909
+
119906
119869119909
+119898
1198971198972
119869119909
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+4
5119869119909
1198981198971198972
+
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198865=
1
2119869119910
1198981198971198972
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+2
5119869119910
1198981198971198972
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198866=
1
2119869119910
1198981198971198972
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+2
5119869119910
1198981198971198972
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198867=
1
2119869119910
1198981198971198972
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+2
5119869119910
1198981198971198972
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198868=
1
2119869119910
1198981198971198972
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
24 Mathematical Problems in Engineering
+2
5119869119910
1198981198971198972
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
119906120579=
119876120579
119869119910
+119906
120579
119869119910
minus1
2119869119910
1198981198971198972
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119910
1198981198971198972
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198869= minus
1
2119869119911
1198972
119898119897
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988610
= minus1
2119869119911
1198972
119898119897
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988611
= minus1
2119869119911
1198972
119898119897
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988612
= minus1
2119869119911
1198972
119898119897
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
119906120595=
119876120595
119869119911
+
119906
119869119911
+1
2119869119911
1198972
119898119897
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+2
5119869119911
1198972
119898119897
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988613
= minus
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988614
= minus
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988615
= minus
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988616
= minus
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
1199061198811
=
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988617
= minus
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988618
= minus
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988619
= minus
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988620
= minus
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1199061198812
=
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(A2)
Conflict of Interests
The authors declare that there is no conflict of interestsregarding the publication of this paper
Acknowledgments
The authors would like to thank the anonymous reviewers fortheir critical and constructive review of the paper This studywas cosupported by the National Natural Science Foundationof China (Project no 11302134 11272101)
References
[1] M Colin Solar Sailing Technology Dynamics and MissionApplications Springer-Praxis London UK 1st edition 1999
[2] V Lappas SWokesM Leipold A Lyngvi and P Falkner ldquoGui-dance and control for an Interstellar Heliopause Probe (IHP)solar sail mission to 200 AUrdquo in Proceedings of the AIAAGuidance Navigation and Control Conference and Exhibit pp2472ndash2492 San Francisco Calif USA August 2005
[3] L Charlotte C Camilla and C McInnes ldquoSolar radiation pres-sure augmented deorbiting fromhigh altitude sun-synchronousorbitsrdquo in Proceedings of the 4S Symposium 2012 Small SatellitesSystems and Services Portoroz Slovenia 2012
[4] M Ceriotti and C RMcInnes ldquoGeneration of optimal trajecto-ries for Earth hybrid pole sittersrdquo Journal of Guidance Controland Dynamics vol 34 no 3 pp 847ndash859 2011
[5] S Gong J Li andH Baoyin ldquoSolar sail transfer trajectory fromL1 point to sub-L1 pointrdquoAerospace Science and Technology vol15 no 7 pp 544ndash554 2011
[6] S Gong J Li and H Baoyin ldquoAnalysis of displaced solar sailorbits with passive controlrdquo Journal of Guidance Control andDynamics vol 31 no 3 pp 782ndash785 2008
[7] S Gong H Baoyin and J Li ldquoSolar sail three-body transfertrajectory designrdquo Journal of Guidance Control and Dynamicsvol 33 no 3 pp 873ndash886 2010
Mathematical Problems in Engineering 25
[8] S Gong J Li H Baoyin and J Simo ldquoA new solar sail orbitrdquoScience China Technological Sciences vol 55 no 3 pp 848ndash8552012
[9] Y Tsuda O Mori R Funase et al ldquoAchievement of IKAROS-Japanese deep space solar sail demonstration missionrdquo ActaAstronautica vol 82 no 2 pp 183ndash188 2013
[10] L Johnson MWhorton A Heaton R Pinson G Laue and CAdams ldquoNanoSail-D a solar sail demonstration missionrdquo ActaAstronautica vol 68 no 5-6 pp 571ndash575 2011
[11] B Wie and D Murphy ldquoSolar-sail attitude control design for asail flight validation missionrdquo Journal of Spacecraft and Rocketsvol 44 no 4 pp 809ndash821 2007
[12] B Wie D Murphy M Paluszek and S Thomas ldquoRobust atti-tude control systems design for solar sails part 1 propellantlessprimaryACSrdquo inProceedings of the AIAAGuidance Navigationand Control Conference and Exhibit Providence RI USAAugust 2004
[13] B Wie D Murphy M Paluszek and S Thomas ldquoRobust atti-tude control systems design for solar sails part 2 MicroPPT-based secondary ACSrdquo in Proceedings of the AIAA GuidanceNavigation and Control Conference and Exhibit pp 1325ndash1340Providence RI USA August 2004
[14] S Thomas M Paluszek B Wie and D Murphy ldquoAOCS per-formance and stability validation for large flexible solar sailspacecraftrdquo in Proceedings of the 41st AIAAASMESAEASEEJoint Propulsion Conference amp Exhibit Tucson Ariz USA 2005
[15] B Wie ldquoDynamic modeling and attitude control of solar sailspacecraft part Irdquo in Proceedings of the AIAAGuidance Naviga-tion and Control Conference and Exhibit Monterey Calif USAAugust 2002
[16] BWie ldquoSolar sail attitude control and dynamics part 1rdquo Journalof Guidance Control and Dynamics vol 27 no 4 pp 526ndash5352004
[17] B Wie ldquoDynamic modeling and attitude control of solar sailspacecraft part IIrdquo in Proceedings of the AIAA Guidance Nav-igation and Control Conference and Exhibit Monterey CalifUSA August 2002
[18] BWie ldquoSolar sail attitude control and dynamics part 2rdquo Journalof Guidance Control and Dynamics vol 27 no 4 pp 536ndash5442004
[19] C Luo and J-H Zheng ldquoSolar-sail attitude control based onmoving masses and roll stabilizer barsrdquo Journal of HarbinInstitute of Technology vol 43 no 3 pp 95ndash101 2011
[20] D Romagnoli and T Oehlschlagel ldquoHigh performance twodegrees of freedom attitude control for solar sailsrdquo Advances inSpace Research vol 48 no 11 pp 1869ndash1879 2011
[21] C Scholz D Romagnoli B Dachwald and S Theil ldquoPerfor-mance analysis of an attitude control system for solar sails usingsliding massesrdquo Advances in Space Research vol 48 no 11 pp1822ndash1835 2011
[22] A Bolle and C Circi ldquoSolar sail attitude control through in-plane moving massesrdquo Journal of Aerospace Engineering vol222 no 1 pp 81ndash94 2008
[23] M RotunnoM Basso A B Pome andM Sallusti ldquoA compari-son of robust attitude control techniques for a solar sail space-craftrdquo in Proceedings of the AIAA Guidance Navigation andControl Conference and Exhibit San Francisco Calif USA2005
[24] J Zhang K Zhai and T Wang ldquoControl of large angle maneu-vers for the flexible solar sailrdquo Science China Physics Mechanicsand Astronomy vol 54 no 4 pp 770ndash776 2011
[25] J Zhang andTWang ldquoCoupled attitude-orbit control of flexiblesolar sail for displaced solar orbitrdquo Journal of Spacecraft andRockets vol 50 no 3 pp 675ndash685 2013
[26] Q Li XMa and TWang ldquoReducedmodel for flexible solar saildynamicsrdquo Journal of Spacecraft and Rockets vol 48 no 3 pp446ndash453 2011
[27] M Polites J Kalmanson and D Mangus ldquoSolar sail attitudecontrol using small reaction wheels and magnetic torquersrdquoProceedings of the Institution of Mechanical Engineers G Journalof Aerospace Engineering vol 222 no 1 pp 53ndash62 2008
[28] H-T Cui J-H Luo J-H Feng and P-Y Cui ldquoAttitudecontrol of solar sail spacecraft with control boomrdquo Journal ofAstronautics vol 29 no 2 pp 560ndash566 2008
[29] E Mettler and S R Ploen ldquoSolar sail dynamics and controlusing a boom mounted bus articulated by a bi-state two-axisgimbal and reaction wheelsrdquo in Proceedings of the AIAAAASAstrodynamics Specialist Conference and Exhibit MontereyCalif USA August 2002
[30] J Luo X Li and J Feng ldquoPassive attitude control of solar sailspacecraftrdquo Flight Dynamics vol 26 no 5 pp 47ndash50 2008
[31] J Luo Study on attitude control of solar sail spaceraft [PhDthesis] School of Astronautics Harbin Institute of TechnologyHarbin China 2007
[32] D A Lawrence and S W Piggott ldquoIntegrated trajectory andattitude control for a four-vane solar sailrdquo in Proceedings ofthe AIAA Guidance Navigation and Control Conference andExhibit pp 2416ndash2431 San Francisco Calif USA August 2005
[33] E Mettler A B Acikmese and S R Ploen ldquoAttitude dynamicsand control of solar sails with articulated vanesrdquo in Proceedingsof the AIAA Guidance Navigation and Control Conference andExhibit pp 2396ndash2415 San Francisco Calif USA August 2005
[34] S N Adeli V J Lappas and B Wie ldquoA scalable bus-basedattitude control system for Solar Sailsrdquo Advances in SpaceResearch vol 48 no 11 pp 1836ndash1847 2011
[35] R Funase Y Shirasawa Y Mimasu et al ldquoOn-orbit verificationof fuel-free attitude control system for spinning solar sailutilizing solar radiation pressurerdquo Advances in Space Researchvol 48 no 11 pp 1740ndash1746 2011
[36] B Fu and F O Eke ldquoAttitude control methodology for largesolar sailsrdquo in AIAA Guidance Navigation and Control (GNC)Conference 2013
[37] J Liu N Cui F Shen and S Rong ldquoDynamics of highly-flexiblesolar sail subjected to various forcesrdquoActaAstronautica vol 103pp 55ndash72 2014
[38] J F Liu S Y Rong and J G Li ldquoAttitude dynamics modelingand control of large flexible solar sail spacecraftrdquo in Proceedingsof the 3rd International Symposium on Systems and Control inAeronautics and Astronautics (ISSCAA rsquo10) pp 243ndash247 IEEEPublications Piscataway NJ USA 2010
[39] S Gong H Baoyin and J Li ldquoCoupled attitude-orbit dynamicsand control for displaced solar orbitsrdquo Acta Astronautica vol65 no 5-6 pp 730ndash737 2009
Submit your manuscripts athttpwwwhindawicom
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
MathematicsJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Mathematical Problems in Engineering
Hindawi Publishing Corporationhttpwwwhindawicom
Differential EquationsInternational Journal of
Volume 2014
Applied MathematicsJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Probability and StatisticsHindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Journal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Mathematical PhysicsAdvances in
Complex AnalysisJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
OptimizationJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
CombinatoricsHindawi Publishing Corporationhttpwwwhindawicom Volume 2014
International Journal of
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Operations ResearchAdvances in
Journal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Function Spaces
Abstract and Applied AnalysisHindawi Publishing Corporationhttpwwwhindawicom Volume 2014
International Journal of Mathematics and Mathematical Sciences
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
The Scientific World JournalHindawi Publishing Corporation httpwwwhindawicom Volume 2014
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Algebra
Discrete Dynamics in Nature and Society
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
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Decision SciencesAdvances in
Discrete MathematicsJournal of
Hindawi Publishing Corporationhttpwwwhindawicom
Volume 2014 Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Stochastic AnalysisInternational Journal of
Mathematical Problems in Engineering 5
R1198984
=∘
1205884
+ 120596 times (r4+ 120588
4) = [
[
1205884119909
0
1205884119911
]
]
+[[
[
cos 120579 minus sin 120579 cos120593120579 + sin120593
sin 120579 + cos 120579 cos120593
]]
]
times [
[
1205884119909
1199104
1205884119911
]
]
=[[
[
1205884119909
+ 1205884119911
120579 + 1205884119911 sin120593 minus 119910
4 sin 120579 minus 119910
4 cos 120579 cos120593
1205884119909 sin 120579 + 120588
4119909 cos 120579 cos120593 minus 120588
4119911 cos 120579 + 120588
4119911 sin 120579 cos120593
1205884119911
+ 1199104 cos 120579 minus 119910
4 sin 120579 cos120593 minus 120588
4119909
120579 minus 1205884119909 sin120593
]]
]
(10)
The components of the position and velocity vectors of anarbitrary point on the supporting beam can be computed byusing the above five equations
In Figure 4 1205821and 120582
2are the boom tilt and azimuth
angles relative to the sailcraft body axes respectively Thecomponents of r
119901can be expressed as follows by using these
two angles
r119901=10038161003816100381610038161003816r119901
10038161003816100381610038161003816cos 120582
1i119887+10038161003816100381610038161003816r119901
10038161003816100381610038161003816sin 120582
1cos 120582
2j119887+10038161003816100381610038161003816r119901
10038161003816100381610038161003816sin 120582
1sin 120582
2k119887
(11)
The position and velocity vectors of the payload can beobtained as
R119874119901
= R119874+ r
119901 k
119874119901= k
119874+ r
119901 (12)
where r119901=∘r119901+ 120596 times r
119901 And ∘r
119901can be expressed as
∘r119901= minus
10038161003816100381610038161003816r119901
100381610038161003816100381610038161sin 120582
1i119887+10038161003816100381610038161003816r119901
10038161003816100381610038161003816
times (1cos 120582
1cos 120582
2minus
2sin 120582
1sin 120582
2) j
119887
+10038161003816100381610038161003816r119901
10038161003816100381610038161003816(
1cos 120582
1sin 120582
2+
2sin 120582
1cos 120582
2) k
119887
(13)
Thus r119901can be obtained as
r119901= [[minus119897
1199011sin 120582
1+ 119897
119901sin 120582
1sin 120582
2( 120579 + sin120593)
minus 119897119901sin 120582
1cos 120582
2( sin 120579 + cos 120579 cos120593)]
times [119897119901(
1cos 120582
1cos 120582
2minus
2sin 120582
1sin 120582
2)
+ 119897119901cos 120582
1( sin 120579 + cos 120579 cos120593)
minus 119897119901sin 120582
1sin 120582
2( cos 120579 minus sin 120579 cos120593)]
times 119897119901(
1cos 120582
1sin 120582
2+
2sin 120582
1cos 120582
2)
+ 119897119901sin 120582
1cos 120582
2( cos 120579 minus sin 120579 cos120593)
minus 119897119901cos 120582
1( 120579 + sin120593)]
(14)
The position vectors of the two sliding masses can beobtained as
Rℎ119895
= R119874+ r
ℎ119895+ 120588
ℎ119895
kℎ2
= k119874+∘rℎ119895
+∘
120588ℎ119895
+ 120596 times (rℎ119895
+ 120588ℎ119895)
(119895 = 1 2)
(15)
If the orbital motion and its influence on attitude motioncan be neglected then the position and velocity vectors canbe obtained as follows
Rℎ2
= rℎ2
+ 120588ℎ2
= [120588ℎ2119909
120588ℎ2119910
119911ℎ2]119879
Rℎ1
= rℎ1
+ 120588ℎ1
= [120588ℎ1119909
119910ℎ1 120588
ℎ1119911]119879
Rℎ2
=[[
[
120588ℎ2119909
+ 119911ℎ2
( 120579 + sin120593) minus 120588ℎ2119910
( sin 120579 + cos 120579 cos120593)120588ℎ2119910
+ 120588ℎ2119909
( sin 120579 + cos 120579 cos120593) minus 119911ℎ2
( cos 120579 minus sin 120579 cos120593)ℎ2
+ 120588ℎ2119910
( cos 120579 minus sin 120579 cos120593) minus 120588ℎ2119909
( 120579 + sin120593)
]]
]
Rℎ1
=[[
[
120588ℎ1119909
+ 120588ℎ1119911
( 120579 + sin120593) minus 119910ℎ1
( sin 120579 + cos 120579 cos120593)119910ℎ1
+ 120588ℎ1119909
( sin 120579 + cos 120579 cos120593) minus 120588ℎ1119911
( cos 120579 minus sin 120579 cos120593)120588ℎ1119911
+ 119910ℎ1
( cos 120579 minus sin 120579 cos120593) minus 120588ℎ1119909
( 120579 + sin120593)
]]
]
(16)
6 Mathematical Problems in Engineering
24 The Kinetic Energy The kinetic energy of the sail systemcan be obtained by neglecting the orbital motion and itsinfluence on attitude motion Consider
1198791198983
=1
2119898
119897int
119897
0
[∘
1205883
+ 120596 times (r3+ 120588
3)] sdot [
∘
1205883
+ 120596 times (r3+ 120588
3)] 119889119911
1198791198981
=1
2119898
119897int
0
minus119897
[∘
1205881
+ 120596 times (r1+ 120588
1)]
sdot [∘
1205881
+ 120596 times (r1+ 120588
1)] 119889119911
1198791198982
=1
2119898
119897int
119897
0
[∘
1205882
+ 120596 times (r2+ 120588
2)] sdot [
∘
1205882
+ 120596 times (r2+ 120588
2)] 119889119910
1198791198984
=1
2119898
119897int
0
minus119897
[∘
1205884
+ 120596 times (r4+ 120588
4)] sdot [
∘
1205884
+ 120596 times (r4+ 120588
4)] 119889119910
(17)
The above equations can be rewritten as
119879119898
=1
2120596 sdot J sdot 120596
+1
2119898
119897int
119897
0
2∘
1205883
sdot (120596 times r3) + (120596 times 120588
3) sdot (120596 times 120588
3)
+ 2 (120596 times r3) sdot (120596 times 120588
3) 119889119911
+1
2119898
119897int
0
minus119897
2∘
1205881
sdot (120596 times r1) + (120596 times 120588
1) sdot (120596 times 120588
1)
+ 2 (120596 times r1) sdot (120596 times 120588
1) 119889119911
+1
2119898
119897int
119897
0
2∘
1205882
sdot (120596 times r2) + (120596 times 120588
2) sdot (120596 times 120588
2)
+ 2 (120596 times r2) sdot (120596 times 120588
2) 119889119910
+1
2119898
119897int
0
minus119897
2∘
1205884
sdot (120596 times r4) + (120596 times 120588
4) sdot (120596 times 120588
4)
+ 2 (120596 times r4) sdot (120596 times 120588
4) + (120596 times r
4)
sdot (120596 times r4) 119889119910
(18)
where J = sum4
119895=1
J119898119895
is the moment of inertia of sail systemJ119898119895
(119895 = 1ndash4) is the moment of inertia of the 119895th sail sys-tem and the expression of J can be expressed as J = diag[119869
119909
119869119910 119869
119911] inO
119874x119887y119887z119887
The kinetic energy of the payload is
119879119901=
1
2119898
119901
10038161003816100381610038161003816r119901
10038161003816100381610038161003816
2
=1
2119898
119901[minus119897
1199011sin 120582
1+ 119897
119901sin 120582
1sin 120582
2( 120579 + sin120593)
minus 119897119901sin 120582
1cos 120582
2( sin 120579 + cos 120579 cos120593)]
2
+1
2119898
119901[119897119901(
1cos 120582
1cos 120582
2minus
2sin 120582
1sin 120582
2)
+ 119897119901cos 120582
1( sin 120579 + cos 120579 cos120593)
minus 119897119901sin 120582
1cos 120582
2( cos 120579 minus sin 120579 cos120593)]
2
+1
2119898
119901[119897119901(
1cos 120582
1sin 120582
2+
2sin 120582
1cos 120582
2)
+ 119897119901sin 120582
1cos 120582
2( cos 120579 minus sin 120579 cos120593)
minus 119897119901cos 120582
1( 120579 + sin120593)]
2
(19)
The kinetic energy of the sliding masses can be obtainedas follows by neglecting the orbital motion and its influenceon attitude control
119879ℎ1
=1
2119898
ℎ1[ ( 120588
ℎ1119909+ 120579120588
ℎ1119911+ 120588
ℎ1119911sin120593
minus 119910ℎ1sin 120579 minus 119910
ℎ1cos 120579 cos120593)
2
]
+1
2119898
ℎ1[( 119910
ℎ1+ 120588
ℎ1119909sin 120579 + 120588
ℎ1119909cos 120579 cos120593
minus 120588ℎ1119911
cos 120579 + 120588ℎ1119911
sin 120579 cos120593)2]
+1
2119898
ℎ1[( 120588
ℎ1119911+ 119910
ℎ1cos 120579 minus 119910
ℎ1sin 120579 cos120593
minus 120579120588ℎ1119909
+ 120588ℎ1119909
sin120593)2
]
119879ℎ2
=1
2119898
ℎ2[( 120588
ℎ2119909+ 120579119911
ℎ2+ 119911
ℎ2sin120593 minus 120588
ℎ2119910sin 120579
minus 120588ℎ2119910
cos 120579 cos120593)2
]
+1
2119898
ℎ2[( 120588
ℎ2119910+ 120588
ℎ2119909sin 120579 + 120588
ℎ2119909cos 120579 cos120593
minus 119911ℎ2cos 120579 + 119911
ℎ2sin 120579 cos120593)
2
]
+1
2119898
ℎ2[(
ℎ2+ 120588
ℎ2119910cos 120579 minus 120588
ℎ2119910sin 120579 cos120593
minus 120579120588ℎ2119909
minus 120588ℎ2119909
sin120593)2
]
(20)
25 The Gravitational Potential Energy The gravitationalpotential energies of the sail system 119880
119892119891 payload 119880
119892119901 and
sliding masses 119880119892ℎ1
119880119892ℎ2
can be obtained as
119880119892119891
= minus
120583119898119891
1003816100381610038161003816R119874
1003816100381610038161003816
119880119892119901
= minus
120583119898119901
10038161003816100381610038161003816R119874+ r
119901
10038161003816100381610038161003816
119880119892ℎ1
= minus120583119898
ℎ1
1003816100381610038161003816R119874+ r
ℎ1
1003816100381610038161003816
119880119892ℎ2
= minus120583119898
ℎ2
1003816100381610038161003816R119874+ r
ℎ2
1003816100381610038161003816
(21)
Mathematical Problems in Engineering 7
26 The Generalized Forces The components of the sunlightunit vector S can be obtained as follows by referring toFigure 3 (left) in 120587
119868
S = j119868= [1 0 0]
119879
119868
(22)
Based on the abovementioned equations the componentsof S in 120587
119887can be obtained as
S = C119887119868[1 0 0]
119879
119868
= [119878119909
119878119910
119878119911]119879
119887
(23)
The resultant SRP force can be simply modeled as followsfor a perfectly reflective control vane
F119894= 120578119875119860
119862119894(S sdot n
119862119894)2 n
119862119894= 119865
119862119894cos2120572
119862119894n119862119894 (24)
where 120578 is the overall sail-thrust coefficient (120578max = 2) 119875 =
4563 times 10minus6 Nm2 119860
119862119894is the area of the 119894th control vane
119865119862119894
= 120578119875119860119862119894is themaximumcontrol vane thrust andn
119862119894= i
119894
is the unit normal vector of the control vaneThe componentsof n
119862119894in 120587
119887can be written as
n119862119894
= C119887119894[1 0 0]
119879
119894
= [119878119909119894
119878119910119894
119878119911119894]119879
119887
(25)
The control torque by the 119894th control vane can beexpressed as
M119894= L
119894times F
119894 (26)
In fact L119894and F
119894are dependent on the deformations of
the supporting beams and control vanes In this paper it isassumed thatL
119894andF
119894are not influenced by the deformations
of the structure when computing the control torque by thecontrol vanes Thus L
119894and F
119894can be expressed as
L1= [0 0 minus119897]
119879
L2= [0 119897 0]
119879
L3= [0 0 119897]
119879
L4= [0 minus119897 0]
119879
F119894= 120578119875119860
119862119894([119878
119909119878119910
119878119911]119887
sdot [119878119909119894
119878119910119894
119878119911119894]119879
119887
)
2
[119878119909119894
119878119910119894
119878119911119894]119879
119887
(27)
The force of each control vane can be written as
F119894= (119865
119862119894cos2120572
119862119894)C
119887119894[1 0 0]
119879
119894
= (119865119862119894cos2120572
119862119894) [119878
119909119894119878119910119894
119878119911119894]119879
119887
(28)
where 120572119862119894
is the sun angle of the 119894th control vane that canbe measured by the sun sensor And the components of thecontrol torques can be obtained as
M1198881
= (1198651198621cos2120572
1198621)[
[
0
0
minus119897
]
]
times (C1198871
[
[
1
0
0
]
]
)
= (1198651198621cos2120572
1198621)
times [
[
minus119897 cos1205931sin120595
1
minus119897 (cos 1205791cos120595
1minus sin 120579
1sin120593
1sin120595
1)
0
]
]
M1198882
= (1198651198622cos2120572
1198622)
times [
[
119897 (sin 1205792cos120595
2+ cos 120579
2sin120593
2sin120595
2)
0
minus119897 (cos 1205792cos120595
2minus sin 120579
2sin120593
2sin120595
2)
]
]
M1198883
= (1198651198623cos2120572
1198623)
times [
[
119897 cos1205933sin120595
3
119897 (cos 1205793cos120595
3minus sin 120579
3sin120593
3sin120595
3)
0
]
]
M1198884
= (1198651198624cos2120572
1198624)
times [
[
minus119897 (sin 1205794cos120595
4+ cos 120579
4sin120593
4sin120595
4)
0
119897 (cos 1205794cos120595
4minus sin 120579
4sin120593
4sin120595
4)
]
]
(29)
27 Attitude Dynamics of Solar Sail The attitude dynamicscan be obtained by using the Lagrange equation method as
119889
119889119905(
120597119871
120597 119902119895
) minus120597119871
120597119902119895
= 119876119895 (30)
where 119871 is the Lagrange function 119902119895(119895 = 1ndash3) is the vector
of the generalized coordinates and 119876119895is the vector of the
generalized force 119871 can be computed as
119871 = 119879 minus 119880 =
4
sum
119894=1
119879119898119894
+ 119879119901+
2
sum
119895=1
119879ℎ119895
minus (119880119892119891
+ 119880119892119901
+
2
sum
119895=1
119880119892ℎ119895
)
(31)
where 119879119898119894 119879
119901 and 119879
ℎ119895are the kinetic energies of the
supporting beams payload and sliding masses respectively119880119892119891 119880
119892119901 and 119880
119892ℎ119895are the gravitational potential energies of
the sail system payload and sliding masses respectively
8 Mathematical Problems in Engineering
OOx
y
z
FCFCy
FCx
FCz
mh
q(x)
Figure 5 The vibration model
120590
120590e
120590120592
120590
Figure 6 The viscoelastic model
3 The Vibration of Solar Sail
The mechanical and material models of the sailcraft aregivenThe displacement filed stress and strain are presentedbased on the Euler beam assumptionThe Lagrange equationmethod is adopted to derive the vibration equations withlarge deformations based on the calculations of kineticenergies and works done by the external loads
31 The Mechanical Model The body frame O119874xyz is estab-
lished to describe the vibration (see Figure 5) F119862is the force
vector generated by the control vane used located at the tip ofthe supporting beam 119865
119862119909 119865
119862119910 and 119865
119862119911are the components
inO119874xyz 119902(119909) is the distributed load caused by SRP
32 The Material Model The carbon fibre enforced compos-ite material is used to construct the inflatable deploymentsupporting beam The model of the viscoelastic material canbe represented in Figure 6
The total stress is the summation of the elastic and viscousstresses It can be expressed as
120590 = 120590119890
+ 120590120592
= 119864120576 + 119888119887
120576 (32)
where 120590 120590119890 and 120590
120592 are the total elastic and viscous stressrespectively And 119864 is Youngrsquos modulus 120576 ( 120576) is the strain(strain rate) and 119888
119887is the coefficient of the internal damping
expressed as 119864120578119887 120578
119887is the proportionality constant of the
internal damping The dimensions of 119888119887and 120578
119887are N lowast sm2
and s respectively
OO x
y The support beam
Z
Figure 7 The schematic diagram of solar sail supporting beamdeformation
33 The Displacement Field Stress and Strain The deforma-tion of a spatial solar sail supporting beam is presented inFigure 7
The spatial displacement fields for supporting beam are as
119906 (119909 119910 119911 119905) = 1199060(119909 119905) minus 119910
120597V0
120597119909minus 119911
1205971199080
120597119909
V (119909 119910 119911 119905) = V0(119909 119905)
119908 (119909 119910 119911 119905) = 1199080(119909 119905)
(33)
119906(119909 119910 119911 119905) V(119909 119910 119911 119905) and 119908(119909 119910 119911 119905) are the displace-ments along 119909 119910 and 119911 directions respectively 119906
0(119909 119905)
V0(119909 119905) and 119908
0(119909 119905) are the axial and transverse displace-
ments of an arbitrary point on the neutral axisBy using Green strain definition von Karmanrsquos nonlinear
strain-displacement relationships based on assumptions oflarge deflections moderate rotations and small strains for a3D supporting beam are given as follows together with thestrain rate and normal stress
120576119909119909
=120597119906
0
120597119909+1
2(120597V
0
120597119909)
2
minus 1199101205972V
0
1205971199092
+1
2(120597119908
0
120597119909)
2
minus 1199111205972
1199080
1205971199092
120576119909119909
=120597
0
120597119909+(
120597V0
120597119909)(
120597V0
120597119909) minus 119910
1205972V
0
1205971199092
+(120597119908
0
120597119909)(
1205970
120597119909)
minus 1199111205972
0
1205971199092
120590119909119909
= 119864[120597119906
0
120597119909+1
2(120597V
0
120597119909)
2
minus 1199101205972V
0
1205971199092
+1
2(120597119908
0
120597119909)
2
minus 1199111205972
1199080
1205971199092
]
+ 119864120578119887(120597
0
120597119909+(
120597V0
120597119909)(
120597V0
120597119909) minus 119910
1205972V
0
1205971199092
+(120597119908
0
120597119909)(
1205970
120597119909) minus 119911
1205972
0
1205971199092
)
(34)
Mathematical Problems in Engineering 9
The single underlined terms in the preceding equationindicate the contribution by the geometrical nonlinearityThedynamics models and corresponding numerical simulationwithout considering the geometrical nonlinearity can beobtained and carried out by neglecting these terms
34 The Energies and Works Done by External Forces Thestrain energy can be derived as
119880119894=
1
2int
119897
0
119860119909119909
[120597119906
0
120597119909+
1
2(120597V
0
120597119909)
2
+1
2(120597119908
0
120597119909)
2
]
2
+ 119863119909119909
1205972V
0
1205971199092
+ 119863119909119909
1205972
1199080
1205971199092
119889119909
(35)
For an isotropic support beam the extensional stiffness119860
119909119909and bending stiffness119863
119909119909can be computed as
119860119909119909
= int119860
119864119889119860 119863119909119909
= int119860
1198641199112
119889119860 = int119860
1198641199102
119889119860 (36)
The dissipation function is as
Ψ119902=
1
2int
119897
0
[119860119909119909120578119887(120597
0
120597119909)
2
+ 119863119909119909120578119887(1205972V
0
1205971199092
)
2
+ 119863119909119909120578119887(1205972
0
1205971199092
)
2
]119889119909
(37)
The kinetic energy for the support beam is as
119879119890=
1
2int
119897
0
[119868119860(120597119906
0
120597119905)
2
+ 119868119860(120597119908
0
120597119905)
2
+ 119868119863(1205972
1199080
120597119909120597119905)
2
+ 119868119860(120597V
0
120597119905)
2
+ 119868119863(
1205972V
0
120597119909120597119905)
2
]119889119909
(38)
where 119868119860and 119868
119863are integration constant for the support
beam expressed as
119868119860= int
119860
120588119889119860 = 120588119860 119868119863= int
119860
1205881199112
119889119860 = int119860
1205881199102
119889119860 (39)
And the work done by the external force can be obtainedas119882 = 119865
119862119911sdot 119908 (119909
119888 119905) + 119865
119862119910sdot V (119909
119888 119905) + 119898
ℎ119886ℎ119910
(119909ℎ 119905) V (119909
ℎ 119905)
+ 119898ℎ119886ℎ119911
(119909ℎ 119905) 119908 (119909
ℎ 119905) + int
119897
0
119902 (119909) V (119909 119905) 119889119909
(40)where 119909
119888represents the position of the support beam
119908(119909119888 119905) V(119909
119888 119905) are the displacements along 119911 and 119910 direc-
tions respectively and the corresponding loads 119865119862119911 119865
119862119910are
known functions 119909ℎ 119897 and V
ℎare the position coordinate of
the sliding mass the length of the support beam and theconstant-velocity of the sliding mass The dynamic responseis studied only during the period [0 119897V
ℎ] 119898
ℎis the mass
and 119886ℎ119910(119909
ℎ 119905) and 119886
ℎ119911(119909
ℎ 119905) are the components of the
acceleration for a material point on the support beam theslidingmass just arrived at And the corresponding transversedeflections are 119908(119909
ℎ 119905) and V(119909
ℎ 119905) respectively
35 The Assumed Modes Method The axial displacement1199060(119909 119905) and the transverse deflections V
0(119909 119905) and119908
0(119909 119905) can
be represented as follows by considering the assumed modesmethod
1199060(119909 119905) =
infin
sum
119894=1
119880119894(119909)119880
119894(119905)
V0(119909 119905) =
infin
sum
119895=1
119881119895(119909) 119881
119895(119905)
1199080(119909 119905) =
infin
sum
119896=1
119882119896(119909)119882
119896(119905)
(41)
where 119880119894(119905) 119881
119895(119905) and 119882
119896(119905) are the time-dependent gen-
eralized coordinates and 119880119894(119909) 119881
119895(119909) and 119882
119896(119909) are the
assumedmodes For assumedmodemethod themode shapefunctions should satisfy the following requirements in thispaper
119880119894(119909)
1003816100381610038161003816119909=0= 0 119881
119895(119909)
10038161003816100381610038161003816119909=0= 0 119882
119896(119909)
1003816100381610038161003816119909=0= 0
1198811015840
119895
(119909)10038161003816100381610038161003816119909=0
= 0 1198821015840
119896
(119909)10038161003816100381610038161003816119909=0
= 0
(42)
The following first two assumed modes satisfying theassumed mode principle are used in this paper
1198801(119909) =
119909
119897 119880
2(119909) = (
119909
119897)
2
1198811(119909) = (
119909
119897)
2
1198812(119909) = (
119909
119897)
3
1198821(119909) = (
119909
119897)
2
1198822(119909) = (
119909
119897)
3
(43)
With the help of the assumedmodes the detailed expres-sions of 119880
119894 119879
119890119882
119911 and Ψ
119902can be obtained as
119880119894=
9
2
119860119909119909
1198973(119881
2
2
+ 1198822
2
)2
+27
4
119860119909119909
1198973(119881
11198812+ 119882
1119882
2)
times (1198812
2
+ 1198822
2
)
+18
7
119860119909119909
1198973[(119881
2
1
+ 1198822
1
) (1198812
2
+ 1198822
2
) + (11988111198812+ 119882
1119882
2)2
]
+119860
119909119909
1198973[3
2119897119880
2(119881
2
2
+ 1198822
2
) + (1198812
1
+ 1198822
1
)
times (11988111198812+ 119882
1119882
2)]
10 Mathematical Problems in Engineering
+1
10
119860119909119909
1198973[9119880
1119897 (119881
2
2
+ 1198822
2
) + 241198802119897 (119881
11198812+ 119882
1119882
2)
+ 4 (1198812
1
+ 1198822
1
)2
]
+119860
119909119909
1198972[3
21198801(119881
11198812+ 119882
1119882
2) + 119880
2(119881
2
1
+ 1198822
1
)]
+6119863
119909119909119881
2
2
1198973+ 119860
119909119909(2119880
1119881
2
1
31198972+
21198801119882
2
1
31198972+
21198802
2
3119897)
+6119863
119909119909119882
2
2
1198973+
611986311990911990911988111198812
1198973+
11986011990911990911988011198802
119897+
6119863119909119909119882
1119882
2
1198973
+119860
119909119909119880
2
1
2119897+
2119863119909119909119881
2
1
1198973+
2119863119909119909119882
2
1
1198973
119879119890=
1
14(119897119868
119860
2
2
+ 119897119868119860
2
2
) +1
6(119897119868
119860
1
2+ 119897119868
11986012)
+1
10(119897119868
119860
2
2
+ 119897119868119860
2
1
+9119868
119863
2
2
119897+ 119897119868
119860
2
1
+9119868
119863
2
2
119897)
+1
4(119897119868
11986012+
6119868119863
1
2
119897+
611986811986312
119897)
+1
6(119897119868
119860
2
1
+4119868
119863
2
1
119897+
4119868119863
2
1
119897)
119882119911= 119865
119862119911sdot [119882
1(119905) + 119882
2(119905)] + 119865
119862119910sdot [119881
1(119905) + 119881
2(119905)]
+ 119898ℎ[2V2
ℎ
1198972sdot 119881
1(119905) +
4V2ℎ
119905
1198972sdot
1(119905) + (
Vℎ119905
119897)
2
sdot 1(119905)
+6V3
ℎ
119905
1198973sdot 119881
2(119905) +
6V3ℎ
1199052
1198973
sdot 2(119905) + (
Vℎ119905
119897)
3
sdot 2(119905)]
times [(Vℎ119905
119897)
2
sdot 1198811(119905) + (
Vℎ119905
119897)
3
sdot 1198812(119905)]
+ 119898ℎ[2V2
ℎ
1198972sdot 119882
1(119905) +
4V2ℎ
119905
1198972sdot
1(119905) + (
Vℎ119905
119897)
2
sdot 1(119905)
+6V3
ℎ
119905
1198973sdot 119882
2(119905) +
6V3ℎ
1199052
1198973sdot
2(119905)
+ (Vℎ119905
119897)
3
sdot 2(119905)]
times [(Vℎ119905
119897)
2
sdot 1198821(119905) + (
Vℎ119905
119897)
3
sdot 1198822(119905)]
+ 1198811(119905) sdot int
119897
0
119902 (119909) (119909
119897)
2
119889119909 + 1198812(119905)
sdot int
119897
0
119902 (119909) (119909
119897)
3
119889119909
Ψ119902=
1
6(36119863
119909119909120578119887
2
2
1198976+
4119860119909119909120578119887
2
2
1198974+
36119863119909119909120578119887
2
2
1198976) 119897
3
+1
4(4119860
11990911990912057811988712
1198973+
2411986311990911990912057811988712
1198975
+24119863
119909119909120578119887
1
2
1198975) 119897
2
+1
2
119860119909119909120578119887
2
1
119897+
2119863119909119909120578119887
2
1
1198973+
2119863119909119909120578119887
2
1
1198973
(44)
36 The Vibration Equation The Lagrange equation methodis used to derive the vibration equations
120597119871
120597119902119899
minus119889
119889119905(
120597119871
120597 119902119899
) + 119876119889= 0 119899 = 1 2 6 (45)
where 119871 is the Lagrange function 119902119899
= (1198801 119880
2 119881
1 119881
2
1198821119882
2)119879 is the vector of the generalized coordinates and
119902119899is the corresponding generalized velocity vector 119876
119889is the
generalized damping force The expressions for 119871 and 119876119889are
as
119871 = 119879119890minus (119880
119894minus 119882
119911)
119876119889= minus
120597Ψ119902
120597 119902119899
(119899 = 1 sim 6)
(46)
The axial vibration equations can be obtained as followsfor 119880
1 119880
2
1
31198971198681198601+
1
41198971198681198602+
120578119887119860
1199091199091
119897+
120578119887119860
1199091199092
119897+
1198601199091199091198801
119897
+119860
1199091199091198802
119897+
2119860119909119909119881
2
1
31198972+
311986011990911990911988111198812
21198972+
9119860119909119909119881
2
2
101198972
+2119860
119909119909119882
2
1
31198972+
3119860119909119909119882
1119882
2
21198972+
9119860119909119909119882
2
2
101198972= 0
(47a)
1
41198971198681198601+
1
51198971198681198602+
120578119887119860
1199091199091
119897+
4120578119887119860
1199091199092
3119897
+119860
1199091199091198801
119897+4119860
1199091199091198802
3119897+119860
119909119909119881
2
1
1198972+12119860
11990911990911988111198812
51198972+3119860
119909119909119881
2
2
21198972
+119860
119909119909119882
2
1
1198972+
12119860119909119909119882
1119882
2
51198972+
3119860119909119909119882
2
2
21198972= 0
(47b)
The following can be seen from the above equations
(1) Since the assumed modes rather than the naturalmodes are used the coupling between axial and trans-verse vibrations is rather severe for axial vibrations
Mathematical Problems in Engineering 11
(2) The nonlinearity is apparent in above equations onlyexisting in the terms of 119881
1 119881
2119882
1119882
2 We take (47a)
as an exampleThe terms including1198802and its first and
second derivative 1198811 119881
2119882
1119882
2 can be regarded as
the applied loads for 1198801
(3) The coupling between the axial and transverse vibra-tionswill disappear as long as the linear displacement-strain relationship is adopted
(4) There are no external loads for axial vibrationsaccording to above equations
The transverse vibration equations for 1198811 119881
2and119882
1 119882
2
can be obtained as
4
3
1198681198631
119897+
1
51198971198681198601+
1
61198971198681198602minus
119898ℎV5ℎ
1199055
2
1198975+
31198681198632
2119897
+4119898
ℎV4ℎ
1199053
1
1198974+
4120578119887119863
1199091199091
1198973minus
2119898ℎV5ℎ
1199054
2
1198975+
6120578119887119863
1199091199092
1198973
+8119898
ℎV4ℎ
1199052
1198811
1198974+
41198631199091199091198811
1198973+
8119898ℎV5ℎ
1199053
1198812
1198975+
61198631199091199091198812
1198973
+27119860
1199091199091198812119882
2
2
81198973+
541198601199091199091198811119881
2
2
71198973+
181198601199091199091198811119882
2
2
71198973
+6119860
119909119909119881
2
1
1198812
1198973+
21198601199091199091198812119882
2
1
1198973+
1211986011990911990911988021198812
51198972
+8119860
1199091199091198811119882
2
1
51198973+
311986011990911990911988011198812
21198972+
211986011990911990911988021198811
1198972
+8119860
119909119909119881
3
1
51198973+
27119860119909119909119881
3
2
81198973+
361198601199091199091198812119882
1119882
2
71198973
+4119860
1199091199091198811119882
1119882
2
1198973+
411986011990911990911988011198811
31198972minus 119865
119888119910(119905) minus 05119865
025119865= 0
1
61198971198681198601+
3
2
1198681198631
119897minus
119898ℎV5ℎ
1199055
1
1198975+
1
71198971198681198602+
9
5
1198681198632
119897
+6120578
119887119863
1199091199091
1198973+
2119898ℎV5ℎ
1199054
1
1198975+
12120578119887119863
1199091199092
1198973+
6119898ℎV6ℎ
1199055
2
1198976
+6119863
1199091199091198811
1198973+
16119898ℎV5ℎ
1199053
1198811
1198975+
121198631199091199091198812
1198973+
18119898ℎV6ℎ
1199054
1198812
1198976
+9119860
1199091199091198812119882
2
2
21198973+
811198601199091199091198811119881
2
2
81198973+
311986011990911990911988011198811
21198972
+27119860
1199091199091198811119882
2
2
81198973+
541198601199091199091198812119881
2
1
71198973+
181198601199091199091198812119882
2
1
71198973
+3119860
11990911990911988021198812
1198972+
21198601199091199091198811119882
2
1
1198973+
911986011990911990911988011198812
51198972+
1211986011990911990911988021198811
51198972
+9119860
119909119909119881
3
2
21198973+
2119860119909119909119881
3
1
1198973+
271198601199091199091198812119882
1119882
2
41198973
+36119860
1199091199091198811119882
1119882
2
71198973minus 04119865
025119865minus 119865
119888119910(119905) = 0
4
3
119868119863
1
119897+
1
5119897119868119860
1+
3
2
119868119863
2
119897+
1
6119897119868119860
2minus
119898ℎV5ℎ
1199055
2
1198975
+4120578
119887119863
119909119909
1
1198973+
4119898ℎV4ℎ
1199053
1
1198974minus
2119898ℎV5ℎ
1199054
2
1198975+
6120578119887119863
119909119909
2
1198973
+4119863
119909119909119882
1
1198973+
8119898ℎV4ℎ
1199052
1198821
1198974+
8119898ℎV5ℎ
1199053
1198822
1198975+
6119863119909119909119882
2
1198973
+36119860
119909119909119882
211988111198812
71198973+
4119860119909119909119882
111988111198812
1198973+
27119860119909119909119882
2119881
2
2
81198973
+18119860
119909119909119882
1119881
2
2
71198973+
54119860119909119909119882
1119882
2
2
71198973+
6119860119909119909119882
2
1
1198822
1198973
+2119860
119909119909119882
2119881
2
1
1198973+
121198601199091199091198802119882
2
51198972+
8119860119909119909119882
1119881
2
1
51198973
+3119860
1199091199091198801119882
2
21198972+
21198601199091199091198802119882
1
1198972+
27119860119909119909119882
3
2
81198973
+8119860
119909119909119882
3
1
51198973+
41198601199091199091198801119882
1
31198972minus 119865
119888119911(119905) = 0
1
7119897119868119860
2+
9
5
119868119863
2
119897+
1
6119897119868119860
1minus
119898ℎV5ℎ
1199055
1
1198975+
3
2
119868119863
1
119897
+6120578
119887119863
119909119909
1
1198973+
2119898ℎV5ℎ
1199054
1
1198975+
6119898ℎV6ℎ
1199055
2
1198976
+12120578
119887119863
119909119909
2
1198973+
6119863119909119909119882
1
1198973+
16119898ℎV5ℎ
1199053
1198821
1198975
+12119863
119909119909119882
2
1198973+
18119898ℎV6ℎ
1199054
1198822
1198976+
31198601199091199091198801119882
1
21198972
+27119860
119909119909119882
211988111198812
41198973+
36119860119909119909119882
111988111198812
71198973+
9119860119909119909119882
2119881
2
2
21198973
+27119860
119909119909119882
1119881
2
2
81198973+
81119860119909119909119882
1119882
2
2
81198973+
18119860119909119909119882
2119881
2
1
71198973
+54119860
119909119909119882
2119882
2
1
71198973+
31198601199091199091198802119882
2
1198972+
2119860119909119909119882
1119881
2
1
1198973
+9119860
1199091199091198801119882
2
51198972+
121198601199091199091198802119882
1
51198972+
2119860119909119909119882
3
1
1198973
+9119860
119909119909119882
3
2
21198973minus 119865
119888119911(119905) = 0
(48)
The complexity high coupling and nonlinearity are obvi-ous in above equations
4 The Coupled Rigid-Flexible Dynamics
The dynamics for control and dynamic simulation shouldbe presented for solar sail based on the simplification ofequations derived in previous sections Some assumptions aremade before simplifying the equations as follows
12 Mathematical Problems in Engineering
(1) Only the attitude motion is affected by the slidingmass the vibration of solar sail structure is notaffected by the sliding mass
(2) Although the attitude control is accomplished byrotating control vanes and the gimbaled controlboom moving sliding masses the specific time his-tories of the actuators are not considered here
(3) The four supporting beams are regarded as an entirestructure thus the identical generalized coordinatesare adopted in the dynamic analysis
41 The Simplified Attitude Dynamics The kinetic energy ofsolar sail supporting beams can be obtained as
119879119898
=1
2120596 sdot J sdot 120596 + 119898
119897int
119897
0
2∘
1205883
sdot (120596 times r3) + (120596 times 120588
3) sdot (120596 times 120588
3)
+ 2 (120596 times r3) sdot (120596 times 120588
3) 119889119911
+ 119898119897int
119897
0
2∘
1205882
sdot (120596 times r2) + (120596 times 120588
2) sdot (120596 times 120588
2)
+ 2 (120596 times r2) sdot (120596 times 120588
2) 119889119910
(49)
The subscripts 2 and 3 represent the second and thirdsupporting beams The displacements can be expressed as
V0119909
(119911 119905) = (119911
119897)
2
sdot 1198811(119905) + (
119911
119897)
3
sdot 1198812(119905)
1199080119910
(119911 119905) = 120572V0119909
(119911 119905) = (119911
119897)
2
sdot 1205721198811(119905) + (
119911
119897)
3
sdot 1205721198812(119905)
for the 3rd beam
V0119909
(119910 119905) = 120573V0119909
(119911 119905) = (119910
119897)
2
sdot 1205731198811(119905) + (
119910
119897)
3
sdot 1205731198812(119905)
1199080119911
(119910 119905) = 120574V0119909
(119910 119905) = (119910
119897)
2
sdot 1205741198811(119905) + (
119910
119897)
3
sdot 1205741198812(119905)
for the 2nd beam
(50)
The subscripts 119909 119910 and 119911 of the left terms in (50)represent the displacements along119909119910 and 119911directions119881
1(119905)
and 1198812(119905) are the generalized coordinates The displacements
1199080119910(119911 119905) V
0119909(119910 119905) and 119908
0119911(119910 119905) can be obtained using the
assumed modes as
1205883= V
0119909(119911 119905) i
119887+ 119908
0119910(119911 119905) j
119887
=
[[[[[
[
(119911
119897)
2
sdot 1198811(119905) + (
119911
119897)
3
sdot 1198812(119905)
120572 [(119911
119897)
2
sdot 1198811(119905) + (
119911
119897)
3
sdot 1198812(119905)]
0
]]]]]
]
1205882= V
0119909(119910 119905) i
119887+ 119908
0119911(119910 119905) k
119887
=
[[[[[
[
120573[(119910
119897)
2
sdot 1198811(119905) + (
119910
119897)
3
sdot 1198812(119905)]
0
120574 [(119910
119897)
2
sdot 1198811(119905) + (
119910
119897)
3
sdot 1198812(119905)]
]]]]]
]
(51)
The vibration velocity can be obtained as
∘
1205883
= 1205883119909i119887+ 120588
3119910j119887=
[[[[[
[
(119911
119897)
2
sdot 1(119905) + (
119911
119897)
3
sdot 2(119905)
1205721[(
119911
119897)
2
sdot 1(119905) + (
119911
119897)
3
sdot 2(119905)]
0
]]]]]
]
∘
1205882
= 1205882119909i119887+ 120588
2119911k119887=
[[[[[
[
1205731[(
119910
119897)
2
sdot 1(119905) + (
119910
119897)
3
sdot 2(119905)]
0
1205741[(
119910
119897)
2
sdot 1(119905) + (
119910
119897)
3
sdot 2(119905)]
]]]]]
]
(52)
Without loss of generality 120572 = 120573 = 1205721= 120573
1= 1 and
120574 = 1205741= minus1 can be assumed in above expressions And the
kinetic energy of the slidingmasses can be obtained as followsby neglecting the vibration related terms
119879ℎ=
1
2119898
ℎ1(120596 times r
ℎ1) sdot (120596 times r
ℎ1) +
1
2119898
ℎ2(120596 times r
ℎ2)
sdot (120596 times rℎ2)
(53)
The kinetic energy of the payload can be obtained as
119879119901=
1
2119898
119901(120596 times r
119901) sdot (120596 times r
119901) (54)
The following simplified attitude dynamics can beobtained by neglecting the second and higher terms ofattitude angles and vibration modes in computing the kinetic
Mathematical Problems in Engineering 13
energies of the supporting beams payload and slidingmasses Consider
119869119909 minus 119898
1198971198972
1minus
4
5119898
1198971198972
2+ 119898
ℎ11199102
ℎ1
+ 119898ℎ21199112
ℎ2
minus 119898119901119903119901119909119903119901119911 + 119898
1199011199032
119901119911
+ 1198981199011199032
119901119910
minus 119898119901119903119901119909119903119901119910
120579 = 119876120593
119869119910
120579 +2
5119898
1198971198972
2+
1
2119898
1198971198972
1+ 119898
ℎ21199112
ℎ2
120579
+ 1198981199011199032
119901119911
120579 minus 119898119901119903119901119910119903119901119911 minus 119898
119901119903119901119909119903119901119910
+ 1198981199011199032
119901119909
120579 = 119876120579
119869119911 minus
2
51198972
1198981198972minus
1
21198972
1198981198971+ 119898
ℎ11199102
ℎ1
minus 119898119901119903119901119910119903119901119911
120579 + 1198981199011199032
119901119910
+ 1198981199011199032
119901119909
minus 119898119901119903119901119909119903119901119911 = 119876
120595
(55)
where 119876120593 119876
120579 and 119876
120595are the generalized nonpotential
attitude control torques generated by the control vanes Andthe attitude control torques generated by the gimbaled controlboom and sliding masses can be found on the left side ofthe above equation coupled with 120579 making the attitudecontroller design problem rather difficult
42 The Simplified Vibration Equations The couplingbetween the axial and transverse vibrations is neglectedand only the transverse vibration is considered The attitudedynamics for dynamic simulation can be obtained as followsbased on previous derivation by neglecting the action ofsolar-radiation pressure
4
3
1198681198631
119897+
1
51198971198681198601+
1
61198971198681198602+
31198681198632
2119897+
4120578119887119863
1199091199091
1198973
+6120578
119887119863
1199091199092
1198973+
41198631199091199091198811
1198973+
61198631199091199091198812
1198973+
271198601199091199091198812119882
2
2
81198973
+54119860
1199091199091198811119881
2
2
71198973+
181198601199091199091198811119882
2
2
71198973+
6119860119909119909119881
2
1
1198812
1198973
+2119860
1199091199091198812119882
2
1
1198973+
81198601199091199091198811119882
2
1
51198973+
8119860119909119909119881
3
1
51198973
+27119860
119909119909119881
3
2
81198973+
361198601199091199091198812119882
1119882
2
71198973+
41198601199091199091198811119882
1119882
2
1198973
minus 1198651198621
(119905) = 0
1
61198971198681198601+
3
2
1198681198631
119897+
1
71198971198681198602+
9
5
1198681198632
119897+
6120578119887119863
1199091199091
1198973
+12120578
119887119863
1199091199092
1198973+
61198631199091199091198811
1198973+
121198631199091199091198812
1198973+
91198601199091199091198812119882
2
2
21198973
+81119860
1199091199091198811119881
2
2
81198973+
271198601199091199091198811119882
2
2
81198973+
541198601199091199091198812119881
2
1
71198973
+18119860
1199091199091198812119882
2
1
71198973+
21198601199091199091198811119882
2
1
1198973+
9119860119909119909119881
3
2
21198973
+2119860
119909119909119881
3
1
1198973+
271198601199091199091198812119882
1119882
2
41198973+
361198601199091199091198811119882
1119882
2
71198973
minus 1198651198622
(119905) = 0
(56)
The following equations can be obtained by rearrangingthe above equations
4
3
1198681198631
119897+
1
51198971198681198601+
1
61198971198681198602+
31198681198632
2119897+
4120578119887119863
1199091199091
1198973
+6120578
119887119863
1199091199092
1198973+
41198631199091199091198811
1198973+
61198631199091199091198812
1198973+
16119860119909119909119881
3
1
51198973
+12119860
119909119909119881
2
1
1198812
1198973+
1081198601199091199091198811119881
2
2
71198973+
54119860119909119909119881
3
2
81198973
minus 1198651198621
(119905) = 0
1
61198971198681198601+
3
2
1198681198631
119897+
1
71198971198681198602+
9
5
1198681198632
119897+
6120578119887119863
1199091199091
1198973
+12120578
119887119863
1199091199092
1198973+
61198631199091199091198811
1198973+
121198631199091199091198812
1198973
+4119860
119909119909119881
3
1
1198973+
108119860119909119909119881
2
1
1198812
71198973+
811198601199091199091198811119881
2
2
41198973
+9119860
119909119909119881
3
2
1198973minus 119865
1198622(119905) = 0
(57)
1198651198621(119905) and 119865
1198622(119905) are used to represent all the generalized
external forces they can be used for vibration control Thesecomplicated equations abovementioned are the basis forobtaining the simplified equations used for controller design
The following equations can be obtained by neglecting thetwo and higher terms
4
3
1198681198631
119897+
1
51198971198681198601+
1
61198971198681198602+
31198681198632
2119897+
4120578119887119863
1199091199091
1198973
+6120578
119887119863
1199091199092
1198973+
41198631199091199091198811
1198973+
61198631199091199091198812
1198973= 119865
1198621
(119905)
14 Mathematical Problems in Engineering
1
61198971198681198601+
3
2
1198681198631
119897+
1
71198971198681198602+
9
5
1198681198632
119897+
6120578119887119863
1199091199091
1198973
+12120578
119887119863
1199091199092
1198973+
61198631199091199091198811
1198973+
121198631199091199091198812
1198973= 119865
1198622
(119905)
(58)
43 The Rigid-Flexible Coupled Dynamics The simplifiedattitude and vibration dynamics can be written as
119886120593 + 119886
120579
120579 + 119886120595 + 119886
1198811
1+ 119886
1198812
2= 119876
120593
119887120579
120579 + 119887120595 + 119887
120593 + 119887
1198811
1+ 119887
1198812
2= 119876
120579
119888120595 + 119888
120579
120579 + 119888120593 + 119888
1198811
1+ 119888
1198812
2= 119876
120595
119889
1198811
1+ 119889
1198812
2+ 119889
1198811
1+ 119889
1198812
2+ 119889
1198811
1198811
+ 1198891198812
1198812= 119876
1198811
119890
1198811
1+ 119890
1198812
2+ 119890
1198811
1+ 119890
1198812
2+ 119890
1198811
1198811
+ 1198901198812
1198812= 119876
1198812
(59)
The related coefficients in the preceding equation can befound in (A1) in the appendix The dynamics (see (59)) isnot suitable for attitude controller design because the controlinputs exist in some coefficients of the angular accelerationsThis will make the controller design rather difficult Thusthe following dynamic model is obtained by putting theterms including the control inputs right side of the dynamicequations
119869119909 minus 119898
1198971198972
1minus
4
5119898
1198971198972
2= 119876
120593+ 119906
119869119910
120579 +2
5119898
1198971198972
2+
1
2119898
1198971198972
1= 119876
120579+ 119906
120579
119869119911 minus
1
21198972
1198981198971minus
2
51198972
1198981198972= 119876
120595+ 119906
119889
1198811
1+ 119889
1198812
2+ 119889
1198811
1+ 119889
1198812
2
+ 1198891198811
1198811+ 119889
1198812
1198812= 119876
1198811
119890
1198811
1+ 119890
1198812
2+ 119890
1198811
1+ 119890
1198812
2
+ 1198901198811
1198811+ 119890
1198812
1198812= 119876
1198812
(60)
The expressions for 119906 119906
120579
and 119906are as
119906= minus119898
ℎ11199102
ℎ1
minus 119898ℎ21199112
ℎ2
+ 119898119901119903119901119909119903119901119911 minus 119898
1199011199032
119901119911
minus 1198981199011199032
119901119910
+ 119898119901119903119901119909119903119901119910
120579
119906
120579
= minus119898ℎ21199112
ℎ2
120579 minus 1198981199011199032
119901119911
120579 + 119898119901119903119901119910119903119901119911 + 119898
119901119903119901119909119903119901119910
minus 1198981199011199032
119901119909
120579
119906= minus119898
ℎ11199102
ℎ1
+ 119898119901119903119901119910119903119901119911
120579 minus 1198981199011199032
119901119910
minus 1198981199011199032
119901119909
+ 119898119901119903119901119909119903119901119911
(61)
119906 119906
120579
and 119906are the functions of the positions of sliding
masses and payload and the angular accelerations The statevariables in (60) are defined as
1199091= 120593 119909
2= 119909
3= 120579 119909
4= 120579
1199095= 120595 119909
6= 119909
7= 119881
1
1199098=
1 119909
9= 119881
2 119909
10=
2
(62)
Thedynamics (60) can bewritten as the state-spacemodelas following
1= 119909
2
2= 119886
11199097+ 119886
21199098+ 119886
31199099+ 119886
411990910
+ 119906120593
3= 119909
4
4= 119886
51199097+ 119886
61199098+ 119886
71199099+ 119886
811990910
+ 119906120579
5= 119909
6
6= 119886
91199097+ 119886
101199098+ 119886
111199099+ 119886
1211990910
+ 119906120595
7= 119909
8
8= 119886
131199097+ 119886
141199098+ 119886
151199099+ 119886
1611990910
+ 1199061198811
9= 119909
10
10
= 119886171199097+ 119886
181199098+ 119886
191199099+ 119886
2011990910
+ 1199061198812
(63)
where 119906120579 119906
120593 and 119906
120595are the generalized control inputs
for attitude control and 1199061198811
and 1199061198812
are the generalizedcontrol inputs for vibration control The controllability canbe satisfied by analyzing (63) The attitudevibration controlinputs and the coefficients will be presented later in thissection The form of a matrix differential equation can bewritten as follows for the above equation
x = Ax + Bu (64)
The expressions of the relatedmatrices and vectors can befound as
x = [1
2
3
4
5
6
7
8
9
10]119879 x (119905
0) = x
1199050
u = [119906120593 119906
120579 119906
120595 119906
1198811
1199061198812
]119879
u (1199050) is known
(65)
where A xB and u are the system matrix state variablesvector control matrix and control inputs vector respectively
Mathematical Problems in Engineering 15
The complexity of the state-space model can be seen bypresenting the detailed expressions of control inputs forattitudevibration and related parameters in (A2) in theappendix
5 AttitudeVibration Control and Simulation
The controller for the attitude and vibration is developedusing the LQR and optimal PI theory The dynamic simula-tion is performed based on the coupled dynamics derived inthe previous sections
51 LQR and Optimal PI Based Controllers Design Thedynamics for solar sail can bewritten as follows togetherwithits quadratic cost function also defined as
x = Ax + Bu x (1199050) = x
1199050
(known)
119869 =1
2int
infin
1199050
[x119879 (119905)Qx (119905) + u119879 (119905)Ru (119905)] 119889119905
(66)
whereQ = Q119879
⩾ 0 andR = R119879
gt 0 are constantThe control-lability of [AB] and the observability of [AD] can beensured when the equationDD119879
= Q holds for anymatrixDThe optimal control input ulowast(119905)within the scope of u(119905) isin R119903119905 isin [119905
0infin] can be computed as follows to make 119869minimum
ulowast (119905) = minusKxlowast (119905) K = Rminus1B119879P (67)
where P is the nonnegative definite symmetric solution of thefollowing Riccati algebraic equations
PA + A119879P minus PBRminus1B119879P +Q = 0 (68)
And the optimal performance index can be obtained asfollows for arbitrary initial states
119869lowast
[x (1199050) 119905
0] =
1
2x1198790
Px0 (69)
The closed-loop system
x = (A minus BRminus1B119879P) x (70)
is asymptotically stableFor an orbiting solar sail the primary disturbance torque
is by the cmcp offset and the impact of the tiny dust inthe deep space The state regulator can be used to controlthe dynamic system affected by pulse disturbance torquewith good steady-state errors but will never achieve accuratesteady-state errors if the dynamics is affected by constantdisturbance torque Thus the optimal state regulator withan integrator to eliminate the constant disturbance torqueshould be presented This optimal proportional-integral reg-ulator not only eliminates the constant disturbance torque butalso possesses the property of optimal regulator
Table 1 The related parameters
Parameters ValuesCMCP offsetm [0 017678 017678]119879
The side length of square sailm 100Nominal solar-radiation pressureconstant at 1 AU from the sunNm2 4563 times 10minus6
Solar-radiation pressure forceN 912 times 10minus2
Roll inertiakglowastm2 50383Pitch and yaw inertiakglowastm2 251915Outer radiusm 0229Thickness of the supporting beamm 75 times 10minus6
Youngrsquos modulus of the supportingbeamGPa 124
Moment of inertia of the cross-sectionof the supporting beamm4 2829412 times 10minus7
Bending stiffness of the supportingbeamNlowastm2 3508471336
Proportional damping coefficient ofsupporting beams 001
Line density of the supportingbeamkgm 0106879
Cross-sectional area of the supportingbeamm2 1079 times 10minus5
Roll disturbance torqueNlowastm 0Pitch (yaw) disturbance torqueNlowastm 0016122 (minus0016122)
For the following linear system with the correspondingperformance index
x = Ax + Bu x (1199050) = x
1199050
u (1199050) = u
1199050
119869 =1
2int
infin
1199050
(x119879Qx + u119879Ru + u119879Su) 119889119905(71)
where Q = Q119879
⩾ 0 R = R119879
gt 0 and S = S119879 gt 0 If [AB]is completely controllable and meanwhile [AD
11] is com-
pletely observable with the relationship D11D119879
11
= Q thesolution can be expressed as
ulowast = minusK1x minus K
2ulowast ulowast (119905
0) = u
1199050
(72)
If B119879B is full rank we can get
ulowast = minusK3x minus K
4x ulowast (119905
0) = u
1199050
(73)
K119894(119894 = 1 2 3 4) is the function of ABQR S
The closed-loop system
[xulowast] = [
A BminusK
1minusK
2
] [xulowast] [
[
x (1199050)
u (1199050)]
]
= [x1199050
u1199050
] (74)
is asymptotically stableThe compromise between the state variables (the angle
angular velocity the vibration displacement and velocity)and control inputs (the torque by all the actuators) can
16 Mathematical Problems in Engineering
0 2000 4000 6000
0 2000 4000 6000
0 2000 4000 6000minus5
0
5
minus5
0
5
minus5
0
5
minus4
minus2
0
2
4
times10minus4
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
00162
00164
00166
4800 4900 5000
4800 4900 5000
4800 4900 5000
minus00165
minus0016
Time (s) Time (s)
Time (s)
Time (s)
Time (s)
Time (s)
Roll
erro
r120593(∘
)
Roll
erro
r120593(∘
)
Pitc
h er
ror120579
(∘)
Pitc
h er
ror120579
(∘)
Yaw
erro
r120595(∘
)
Yaw
erro
r120595(∘
)
Figure 8 The roll pitch and yaw errors
be achieved by using both the LQR based and optimal PIbased controllers for the coupled attitudevibration dynamicsystem The fact is that the attitude control ability is limitedto the control torque by the control actuators The change ofthe attitude angles and rates should not be frequent to voidexciting vibrations
Thus the weighting matrix Q and the control weightingmatrix R are selected as follows for LQR based controller
Q (1 1) = 9 times 10minus6
Q (2 2) = 1 times 10minus6
Q (3 3) = 16 times 10minus6
Q (4 4) = Q (5 5) = Q (6 6) = Q (7 7) = Q (8 8)
= Q (9 9) = Q (10 10) = 1 times 10minus6
Q (119894 119895) = 0 (119894 = 119895 119894 119895 = 1 sim 10)
R (1 1) = R (2 2) = 900 R (3 3) = 100
R (4 4) = R (5 5) = 10000
R119894119895
= 0 (119894 = 119895 119894 119895 = 1 sim 5)
(75)
TheweightingmatrixQ and the control weightingmatrixR are selected as follows for the optimal PI based controller
Q (1 1) = Q (2 2) = 4 times 10minus8
Q (3 3) = Q (4 4) = Q (5 5) = Q (6 6) = Q (7 7)
= Q (8 8) = 16 times 10minus8
Mathematical Problems in Engineering 17
minus02
0
02
Roll
rate
(∘s)
Roll
rate
(∘s)
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Pitc
h ra
te(∘s)
Pitc
h ra
te(∘s)
0 1000 2000 3000 4000 5000
minus05
0
05
minus05
0
05
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
Time (s)
Yaw
rate
(∘
s)
Yaw
rate
(∘
s)
4800 4850 4900 4950 5000
Time (s)4800 4850 4900 4950 5000
Time (s)4800 4850 4900 4950 5000
minus2
0
2
minus2
0
2
minus2
0
2
times10minus4
times10minus4
times10minus4
Figure 9 The roll pitch and yaw rates
Q (9 9) = Q (10 10) = 1 times 10minus8
Q (119894 119895) = 0 (119894 = 119895 119894 119895 = 1 sim 10)
R (1 1) = R (2 2) = R (3 3) = 1 times 10minus8
R (4 4) = R (5 5) = 4 times 10minus8
R (119894 119895) = 0 (119894 = 119895 119894 119895 = 1 sim 5)
(76)
52 The Simulation Results The initial angle errors of rollpitch and yaw are adopted as 120593(119905
0) = 3
∘ 120579(1199050) = 3
∘ and120595(119905
0) = 3
∘ the initial angular velocity errors of roll pitchand yaw are adopted as (119905
0) = 0
∘
s 120579(1199050) = 0
∘
s and(119905
0) = 0
∘
s 1198811(1199050) = 01m 119881
2(1199050) = 01m
1(1199050) = 0ms
and 2(1199050) = 0ms are adopted in this paper for dynamic
simulationThe estimated cmcp offset is 025m for a 100 times 100m
square solar sail It is assumed that the components of cmcpoffset vector are [0 017678 017678]
119879 in the body frame
The relevant parameters for dynamic simulations are givenin Table 1
The dynamic simulation results are obtained as followsby using the LQR controller based on the abovementionedQ and R related parameters and initial conditions Thedynamics simulations with (denoted by ldquowith GFrdquo) andwithout (denoted by ldquowithout GFrdquo) considering the geo-metrical nonlinearity are presented And the correspondingdiscussions and analysis are also given according to thecalculated results
The roll pitch and yaw errors are presented based onthe dynamics models with and without considering thegeometrical nonlinearityThe control effect with zero steady-state error can be achieved for roll axis by referring tothe results But the steady-state errors exist for pitch andyaw axes from Figure 8 this is because there exist constantdisturbance torques for pitch and yaw axes caused by thecmcp offset Thus the LQR based controller cannot be usedfor attitude control with good steady-state performance Thesteady-state errors of pitch and yaw axes are about 0164
∘
and minus0164∘ respectively from the corresponding partial
enlarged drawing of the figures (see the corresponding left
18 Mathematical Problems in Engineering
minus20
0
20
Roll
torq
ue (N
lowastm
)
Roll
torq
ue (N
lowastm
)
minus50
0
50
minus50
0
50
Pitc
h to
rque
(Nlowast
m)
Pitc
h to
rque
(Nlowast
m)
0 1000 2000 3000 4000 5000
0 2000 4000 6000
0 2000 4000 6000
Yaw
torq
ue (N
lowastm
)
Yaw
torq
ue (N
lowastm
)
minus002
0
002
008
01
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
minus01
minus009
minus008
Time (s)Time (s)
Time (s)Time (s)
Time (s)Time (s)
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Figure 10 The roll pitch and yaw torques
figures) A simple and practical controller should be designedto eliminate the steady-state errorsThese errorswill affect theprecision of the super long duration space mission deeply
The differences between the dynamics with and withoutthe geometrical nonlinearity effect can be observed Theamplitudes and phases change a bit by comparing the corre-sponding results
It can be observed by the partial enlarged figures(the right figures of Figure 9) that there are no steady-stateerrors for roll pitch and yaw rates The relative satisfieddynamic performance is achieved In fact a result with muchmore satisfied dynamic performance can be obtained but itwill make the desired control torques much larger duringthe initial period This will not only excite the vibration ofthe structure but also increase the burden of the controlactuators
And the differences between the dynamics models withand without the geometrical nonlinearity can also be seenmerely in the phase of the angular velocities
The desired attitude control torques are presented inFigure 10 The roll torque will tend to be zero with thedecrement of the state variable errors The pitch and yawtorques tend to be constant from the middle and bottom
figures The pitch and yaw steady-state errors can never beeliminated although the pitch and yaw torques (009Nlowastmand minus009Nlowastm) are applied continuously by theoreticalanalysis and simulations This is just a great disadvantage ofthe LQR based controller in this paper The initial controltorques can be afforded by vibrating the gimbaled controlboom andmoving the slidingmasses that can afford a relativelarge torque The control vanes can be used to afford thecontrol torques when solar sail is in steady-state process Theexpression of the attitude control inputs 119906
120593 119906
120579 and 119906
120595can be
found in previous sectionMoreover the differences between dynamics responses
with and without geometrical nonlinearity can also beobserved by comparing the corresponding results Therequired torques for the attitude control are a little largerfor the dynamics with geometrical nonlinearity And thedifference in the phase is also clear
It can be seen that the vibration of the supporting beamis depressed effectively by the simulation results in Figure 11It can be seen that the steady-state errors and the dynamicperformance are relatively satisfied It can also be seen that thedynamics responses between the model with and without the
Mathematical Problems in Engineering 19
0 1000 2000 3000 4000 5000
0 1000 2000 3000 4000 5000
minus01
0
01
minus02
0
02
Time (s) Time (s)
Time (s) Time (s)
minus5
0
5
times10minus4
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
minus1
0
1
times10minus3
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
The d
ispla
cem
ent o
f the
tip
(m)
The d
ispla
cem
ent o
f the
tip
(m)
The v
eloci
ty o
f the
tip
(ms
)
The v
eloc
ity o
f the
tip
(ms
)
Figure 11 The displacement and velocity of the tip of the supporting beam
geometrical nonlinearity effect are different in the vibrationdisplacement and velocitymagnitudes and phases (Figure 15)
The simulation results can be obtained as follows by usingthe optimal PI based controller adopting the abovementionedparameters and initial conditions
The roll pitch and yaw errors are given by using theoptimal PI based controller These errors tend to disappearby observing the partially enlarged plotting of the figure (thecorresponding right figures) (shown in Figure 12) And therelative satisfied dynamic performance can also be obtainedFrom the view of eliminating the steady-state errors the opti-mal PI based controller performs better than the LQR basedcontroller by theoretical analysis and simulation results Theformer can achieve attitude control results without pitchand yaw steady-state errors From the view of dynamicperformance both the controllers perform well In additionit can be seen that the difference between the modelswith and without geometrical nonlinearity is merely inthe phase
The roll pitch and yaw rate errors are presented inFigure 13 The dynamic and steady-state performances aresatisfied by observing the simulation results And by observ-ing the difference between the dynamics responses with and
without the influence by the geometrical nonlinearity it canbe concluded that the merely difference is the phase
The desired control torques of the roll pitch and yaw areobtained in Figure 14 by using the optimal PI based controllerIt can be seen that the value of the desired roll control torquedecreases to zero as the values of the roll angle and ratedecrease to zero The desired pitch and yaw control torquestend to be the constant values 009Nlowastm and minus009Nlowastmrespectively The desired initial control torques are large byobserving Figure 14 It is suggested that the gimbaled controlboom combining the sliding masses is adopted to afford theinitial torque Then the control vanes can be used to controlthe solar sail after the initial phase The phase differencecan also be observed by inspecting the dynamics responsesduring the 4800sim5000 s period
The vibration can be controlled effectively based on theoptimal PI controller And the relative satisfied dynamicand steady-state performances can be achieved In additionthe tiny differences exist in the magnitudes of the requiredtorques And the phase differences also exist
It can be concluded as follows by analyzing and compar-ing the simulation results based on the LQR and optimal PItheories in detail
20 Mathematical Problems in Engineering
Roll
erro
r120593(∘
)
Roll
erro
r120593(∘
)
minus5
0
5
minus5
0
5
Pitc
h er
ror120579
(∘)
Pitc
h er
ror120579
(∘)
0 1000 2000 3000 4000 5000minus10
0
10
Time (s) Time (s)
Time (s)
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
Yaw
erro
r120595(∘
)
Yaw
erro
r120595(∘
)
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
minus1
0
1
times10minus3
minus1
0
1
times10minus3
minus1
0
1
times10minus3
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Figure 12 The roll pitch and yaw errors
(1) From the view of eliminating the steady-state errorsof the pitch and yaw errors the optimal PI based con-troller performs better than the LQR based controllerby theoretical analysis and simulation results Thedynamic performances of the two controllers are bothsatisfied and the desired control torques are relativelysmall
(2) The weighting of the state variables is reflected by theweighting matrix according to the LQR and optimalPI theories The constant weighting matrices selectedin this paper can effectively reflect the initial statevariable errors but maybe reflect the final state vari-able errors deficiently The time-varying weightingmatrices should be selected
(3) For the actual orbiting solar sail the control actuators(control vanes gimbaled control boom and slidingmasses) cannot afford excessive large control torquesThus the control torques should be as small as possibleon the premise of acquiring satisfied dynamic perfor-mance and steady-state errors It will not only reducethe burden of the control actuators but also avoid
exciting structural vibration In engineering practicethe weighting matrices and the control weightingmatrices should be selected based on the attitudecontrol requirement (eg dynamic performance andsteady-state errors etc)
(4) The dynamics responses influenced by the geometri-cal nonlinearity can be observed In a word the tinydifferences between the magnitudes of the physicalvariables exist for the models with and withoutthe geometrical nonlinearity And the relative cleardifferences exist in the phases for the attitude anglesrates required torques and so forth
6 Conclusions
The coupled attitude and structural dynamics is establishedfor the highly flexible sailcraft by using the von-Karman von-Karmanrsquos nonlinear strain-displacement relationships basedon assumptions of large deflections moderate rotationsand
Mathematical Problems in Engineering 21
Roll
rate
erro
r(∘ s
)
Roll
rate
erro
r(∘ s
)
minus01
0
01
minus01
0
01
Pitc
h ra
te er
ror (
∘ s)
Pitc
h ra
te er
ror (
∘ s)
0 1000 2000 3000 4000 5000minus02
0
02
Yaw
rate
erro
r (∘ s
)
Yaw
rate
erro
r (∘ s
)
4800 4850 4900 4950 5000
minus5
0
5times10minus4
minus5
0
5
times10minus4
minus5
0
5times10minus4
Time (s)
4800 4850 4900 4950 5000
Time (s)
4800 4850 4900 4950 5000
Time (s)
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Figure 13 The roll pitch and yaw rate errors
small strains The Lagrange equation method is utilizedto derive the dynamics for controller design and dynamicsimulation The LQR and optimal PI based controllers aredesigned for the dynamics with the constant disturbancetorque caused by the cmcp offset By theoretical analysisand simulation it can be seen that both controllers cancompromise between the state variables and control inputsBecause the control actuators can hardly afford large controltorque the dynamic performance should be relaxed toreduce the requirement for the attitude control actuatorsBesides the optimal PI based controller can also eliminatethe constant disturbance torque caused by the cmcp offsetthat always exists while the LQR based controller fails toachieve the results with satisfied steady-state performancealthough the attitude control torque is always applied to thecoupled dynamic systemThe dynamics simulations with andwithout the geometrical nonlinearity effect are also carriedout And the differences between the models in magnitudesand phases are identified and analyzed It can be concludedthat the optimal PI based controller performs better than the
LQRbased controller from the viewof eliminating the steady-state error caused by the disturbance torque by the cmcpoffset
Appendix
The related parameters in above equation are given as
119886120593= 119869
119909+ 119898
ℎ11199102
ℎ1
+ 119898ℎ21199112
ℎ2
+ 1198981199011199032
119901119911
+ 1198981199011199032
119901119910
119886120579= minus 119898
119901119903119901119909119903119901119910 119886
120595= minus119898
119901119903119901119909119903119901119911
1198861198811
= minus 1198981198971198972
1198861198812
= minus4
5119898
1198971198972
119887120579= 119869
119910+ 119898
ℎ21199112
ℎ2
+ 1198981199011199032
119901119911
+ 1198981199011199032
119901119909
119887120595= minus 119898
119901119903119901119910119903119901119911 119887
120593= minus119898
119901119903119901119909119903119901119910
22 Mathematical Problems in Engineering
Roll
torq
ue (N
lowastm
)
Roll
torq
ue (N
lowastm
)
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
0 2000 4000 6000
0 2000 4000 6000
0 2000 4000 6000
Time (s)
Time (s)
Time (s)
Time (s)
Time (s)
Time (s)4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
minus01
minus008
008
009
01
minus002
0
002
minus5
0
5
minus2
0
2
Pitc
h to
rque
(Nlowast
m)
Pitc
h to
rque
(Nlowast
m)
minus2
0
2
Yaw
torq
ue (N
lowastm
)
Yaw
torq
ue (N
lowastm
)
Figure 14 The roll pitch and yaw torques
1198871198811
=1
2119898
1198971198972
1198871198812
=2
5119898
1198971198972
119888120595= 119869
119911+ 119898
ℎ11199102
ℎ1
+ 1198981199011199032
119901119910
+ 1198981199011199032
119901119909
119888120579= minus 119898
119901119903119901119910119903119901119911 119888
120593= minus119898
119901119903119901119909119903119901119911
1198881198811
= minus1
21198972
119898119897 119888
1198812
= minus2
51198972
119898119897
119889
1198811
= (4
3
119868119863
119897+
1
5119897119868119860) 119889
1198812
= (1
6119897119868119860+
3119868119863
2119897)
119889
1198811
=4120578
119887119863
119909119909
1198973 119889
1198812
=6120578
119887119863
119909119909
1198973
1198891198811
=4119863
119909119909
1198973 119889
1198812
=6119863
119909119909
1198973
1198761198811
= 1198651198621
(119905)
119890
1198811
= (3
2
119868119863
119897+
1
6119897119868119860)
119890
1198812
= (1
7119897119868119860+
9
5
119868119863
119897) 119890
1198811
=6120578
119887119863
119909119909
1198973
119890
1198812
=12120578
119887119863
119909119909
1198973 119890
1198811
=6119863
119909119909
1198973
1198901198812
=12119863
119909119909
1198973 119876
1198812
= 1198651198622
(119905)
(A1)
The detailed expressions of control inputs for attitudevibration and related parameters in the state-space model ofthe dynamics (see (62) and (63)) are presented as follows
A =
[[[[[[[[[[[[[[
[
0 1 0 0 0 0 0 0 0 0
0 0 0 0 0 0 1198861
1198862
1198863
1198864
0 0 0 1 0 0 0 0 0 0
0 0 0 0 0 0 1198865
1198866
1198867
1198868
0 0 0 0 0 1 0 0 0 0
0 0 0 0 0 0 1198869
11988610
11988611
11988612
0 0 0 0 0 0 0 1 0 0
0 0 0 0 0 0 11988613
11988614
11988615
11988616
0 0 0 0 0 0 0 0 0 1
0 0 0 0 0 0 11988617
11988618
11988619
11988620
]]]]]]]]]]]]]]
]
Mathematical Problems in Engineering 23
0 1000 2000 3000 4000 5000
0 1000 2000 3000 4000 5000
minus01
0
01
minus02
0
02
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Time (s)
Time (s)Time (s)
Time (s)
minus1
0
1
minus1
0
1
times10minus3
times10minus3Th
e disp
lace
men
t of t
he ti
p (m
)
The d
ispla
cem
ent o
f the
tip
(m)
The v
eloci
ty o
f the
tip
(ms
)
The v
eloci
ty o
f the
tip
(ms
)
Figure 15 Vibration displacement and velocity of the tip
B =
[[[[[[[[[[[[[[
[
0 0 0 0 0
1 0 0 0 0
0 0 0 0 0
0 1 0 0 0
0 0 0 0 0
0 0 1 0 0
0 0 0 0 0
0 0 0 1 0
0 0 0 0 0
0 0 0 0 1
]]]]]]]]]]]]]]
]
1198861= minus
1198981198971198972
119869119909
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus4
5119869119909
1198981198971198972
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198862= minus
1198981198971198972
119869119909
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus4
5119869119909
1198981198971198972
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198863= minus
1198981198971198972
119869119909
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus4
5119869119909
1198981198971198972
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198864= minus
1198981198971198972
119869119909
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus4
5119869119909
1198981198971198972
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
119906120593=
119876120593
119869119909
+
119906
119869119909
+119898
1198971198972
119869119909
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+4
5119869119909
1198981198971198972
+
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198865=
1
2119869119910
1198981198971198972
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+2
5119869119910
1198981198971198972
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198866=
1
2119869119910
1198981198971198972
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+2
5119869119910
1198981198971198972
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198867=
1
2119869119910
1198981198971198972
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+2
5119869119910
1198981198971198972
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198868=
1
2119869119910
1198981198971198972
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
24 Mathematical Problems in Engineering
+2
5119869119910
1198981198971198972
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
119906120579=
119876120579
119869119910
+119906
120579
119869119910
minus1
2119869119910
1198981198971198972
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119910
1198981198971198972
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198869= minus
1
2119869119911
1198972
119898119897
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988610
= minus1
2119869119911
1198972
119898119897
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988611
= minus1
2119869119911
1198972
119898119897
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988612
= minus1
2119869119911
1198972
119898119897
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
119906120595=
119876120595
119869119911
+
119906
119869119911
+1
2119869119911
1198972
119898119897
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+2
5119869119911
1198972
119898119897
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988613
= minus
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988614
= minus
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988615
= minus
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988616
= minus
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
1199061198811
=
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988617
= minus
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988618
= minus
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988619
= minus
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988620
= minus
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1199061198812
=
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(A2)
Conflict of Interests
The authors declare that there is no conflict of interestsregarding the publication of this paper
Acknowledgments
The authors would like to thank the anonymous reviewers fortheir critical and constructive review of the paper This studywas cosupported by the National Natural Science Foundationof China (Project no 11302134 11272101)
References
[1] M Colin Solar Sailing Technology Dynamics and MissionApplications Springer-Praxis London UK 1st edition 1999
[2] V Lappas SWokesM Leipold A Lyngvi and P Falkner ldquoGui-dance and control for an Interstellar Heliopause Probe (IHP)solar sail mission to 200 AUrdquo in Proceedings of the AIAAGuidance Navigation and Control Conference and Exhibit pp2472ndash2492 San Francisco Calif USA August 2005
[3] L Charlotte C Camilla and C McInnes ldquoSolar radiation pres-sure augmented deorbiting fromhigh altitude sun-synchronousorbitsrdquo in Proceedings of the 4S Symposium 2012 Small SatellitesSystems and Services Portoroz Slovenia 2012
[4] M Ceriotti and C RMcInnes ldquoGeneration of optimal trajecto-ries for Earth hybrid pole sittersrdquo Journal of Guidance Controland Dynamics vol 34 no 3 pp 847ndash859 2011
[5] S Gong J Li andH Baoyin ldquoSolar sail transfer trajectory fromL1 point to sub-L1 pointrdquoAerospace Science and Technology vol15 no 7 pp 544ndash554 2011
[6] S Gong J Li and H Baoyin ldquoAnalysis of displaced solar sailorbits with passive controlrdquo Journal of Guidance Control andDynamics vol 31 no 3 pp 782ndash785 2008
[7] S Gong H Baoyin and J Li ldquoSolar sail three-body transfertrajectory designrdquo Journal of Guidance Control and Dynamicsvol 33 no 3 pp 873ndash886 2010
Mathematical Problems in Engineering 25
[8] S Gong J Li H Baoyin and J Simo ldquoA new solar sail orbitrdquoScience China Technological Sciences vol 55 no 3 pp 848ndash8552012
[9] Y Tsuda O Mori R Funase et al ldquoAchievement of IKAROS-Japanese deep space solar sail demonstration missionrdquo ActaAstronautica vol 82 no 2 pp 183ndash188 2013
[10] L Johnson MWhorton A Heaton R Pinson G Laue and CAdams ldquoNanoSail-D a solar sail demonstration missionrdquo ActaAstronautica vol 68 no 5-6 pp 571ndash575 2011
[11] B Wie and D Murphy ldquoSolar-sail attitude control design for asail flight validation missionrdquo Journal of Spacecraft and Rocketsvol 44 no 4 pp 809ndash821 2007
[12] B Wie D Murphy M Paluszek and S Thomas ldquoRobust atti-tude control systems design for solar sails part 1 propellantlessprimaryACSrdquo inProceedings of the AIAAGuidance Navigationand Control Conference and Exhibit Providence RI USAAugust 2004
[13] B Wie D Murphy M Paluszek and S Thomas ldquoRobust atti-tude control systems design for solar sails part 2 MicroPPT-based secondary ACSrdquo in Proceedings of the AIAA GuidanceNavigation and Control Conference and Exhibit pp 1325ndash1340Providence RI USA August 2004
[14] S Thomas M Paluszek B Wie and D Murphy ldquoAOCS per-formance and stability validation for large flexible solar sailspacecraftrdquo in Proceedings of the 41st AIAAASMESAEASEEJoint Propulsion Conference amp Exhibit Tucson Ariz USA 2005
[15] B Wie ldquoDynamic modeling and attitude control of solar sailspacecraft part Irdquo in Proceedings of the AIAAGuidance Naviga-tion and Control Conference and Exhibit Monterey Calif USAAugust 2002
[16] BWie ldquoSolar sail attitude control and dynamics part 1rdquo Journalof Guidance Control and Dynamics vol 27 no 4 pp 526ndash5352004
[17] B Wie ldquoDynamic modeling and attitude control of solar sailspacecraft part IIrdquo in Proceedings of the AIAA Guidance Nav-igation and Control Conference and Exhibit Monterey CalifUSA August 2002
[18] BWie ldquoSolar sail attitude control and dynamics part 2rdquo Journalof Guidance Control and Dynamics vol 27 no 4 pp 536ndash5442004
[19] C Luo and J-H Zheng ldquoSolar-sail attitude control based onmoving masses and roll stabilizer barsrdquo Journal of HarbinInstitute of Technology vol 43 no 3 pp 95ndash101 2011
[20] D Romagnoli and T Oehlschlagel ldquoHigh performance twodegrees of freedom attitude control for solar sailsrdquo Advances inSpace Research vol 48 no 11 pp 1869ndash1879 2011
[21] C Scholz D Romagnoli B Dachwald and S Theil ldquoPerfor-mance analysis of an attitude control system for solar sails usingsliding massesrdquo Advances in Space Research vol 48 no 11 pp1822ndash1835 2011
[22] A Bolle and C Circi ldquoSolar sail attitude control through in-plane moving massesrdquo Journal of Aerospace Engineering vol222 no 1 pp 81ndash94 2008
[23] M RotunnoM Basso A B Pome andM Sallusti ldquoA compari-son of robust attitude control techniques for a solar sail space-craftrdquo in Proceedings of the AIAA Guidance Navigation andControl Conference and Exhibit San Francisco Calif USA2005
[24] J Zhang K Zhai and T Wang ldquoControl of large angle maneu-vers for the flexible solar sailrdquo Science China Physics Mechanicsand Astronomy vol 54 no 4 pp 770ndash776 2011
[25] J Zhang andTWang ldquoCoupled attitude-orbit control of flexiblesolar sail for displaced solar orbitrdquo Journal of Spacecraft andRockets vol 50 no 3 pp 675ndash685 2013
[26] Q Li XMa and TWang ldquoReducedmodel for flexible solar saildynamicsrdquo Journal of Spacecraft and Rockets vol 48 no 3 pp446ndash453 2011
[27] M Polites J Kalmanson and D Mangus ldquoSolar sail attitudecontrol using small reaction wheels and magnetic torquersrdquoProceedings of the Institution of Mechanical Engineers G Journalof Aerospace Engineering vol 222 no 1 pp 53ndash62 2008
[28] H-T Cui J-H Luo J-H Feng and P-Y Cui ldquoAttitudecontrol of solar sail spacecraft with control boomrdquo Journal ofAstronautics vol 29 no 2 pp 560ndash566 2008
[29] E Mettler and S R Ploen ldquoSolar sail dynamics and controlusing a boom mounted bus articulated by a bi-state two-axisgimbal and reaction wheelsrdquo in Proceedings of the AIAAAASAstrodynamics Specialist Conference and Exhibit MontereyCalif USA August 2002
[30] J Luo X Li and J Feng ldquoPassive attitude control of solar sailspacecraftrdquo Flight Dynamics vol 26 no 5 pp 47ndash50 2008
[31] J Luo Study on attitude control of solar sail spaceraft [PhDthesis] School of Astronautics Harbin Institute of TechnologyHarbin China 2007
[32] D A Lawrence and S W Piggott ldquoIntegrated trajectory andattitude control for a four-vane solar sailrdquo in Proceedings ofthe AIAA Guidance Navigation and Control Conference andExhibit pp 2416ndash2431 San Francisco Calif USA August 2005
[33] E Mettler A B Acikmese and S R Ploen ldquoAttitude dynamicsand control of solar sails with articulated vanesrdquo in Proceedingsof the AIAA Guidance Navigation and Control Conference andExhibit pp 2396ndash2415 San Francisco Calif USA August 2005
[34] S N Adeli V J Lappas and B Wie ldquoA scalable bus-basedattitude control system for Solar Sailsrdquo Advances in SpaceResearch vol 48 no 11 pp 1836ndash1847 2011
[35] R Funase Y Shirasawa Y Mimasu et al ldquoOn-orbit verificationof fuel-free attitude control system for spinning solar sailutilizing solar radiation pressurerdquo Advances in Space Researchvol 48 no 11 pp 1740ndash1746 2011
[36] B Fu and F O Eke ldquoAttitude control methodology for largesolar sailsrdquo in AIAA Guidance Navigation and Control (GNC)Conference 2013
[37] J Liu N Cui F Shen and S Rong ldquoDynamics of highly-flexiblesolar sail subjected to various forcesrdquoActaAstronautica vol 103pp 55ndash72 2014
[38] J F Liu S Y Rong and J G Li ldquoAttitude dynamics modelingand control of large flexible solar sail spacecraftrdquo in Proceedingsof the 3rd International Symposium on Systems and Control inAeronautics and Astronautics (ISSCAA rsquo10) pp 243ndash247 IEEEPublications Piscataway NJ USA 2010
[39] S Gong H Baoyin and J Li ldquoCoupled attitude-orbit dynamicsand control for displaced solar orbitsrdquo Acta Astronautica vol65 no 5-6 pp 730ndash737 2009
Submit your manuscripts athttpwwwhindawicom
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
MathematicsJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Mathematical Problems in Engineering
Hindawi Publishing Corporationhttpwwwhindawicom
Differential EquationsInternational Journal of
Volume 2014
Applied MathematicsJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Probability and StatisticsHindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Journal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Mathematical PhysicsAdvances in
Complex AnalysisJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
OptimizationJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
CombinatoricsHindawi Publishing Corporationhttpwwwhindawicom Volume 2014
International Journal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Operations ResearchAdvances in
Journal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Function Spaces
Abstract and Applied AnalysisHindawi Publishing Corporationhttpwwwhindawicom Volume 2014
International Journal of Mathematics and Mathematical Sciences
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
The Scientific World JournalHindawi Publishing Corporation httpwwwhindawicom Volume 2014
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Algebra
Discrete Dynamics in Nature and Society
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Decision SciencesAdvances in
Discrete MathematicsJournal of
Hindawi Publishing Corporationhttpwwwhindawicom
Volume 2014 Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Stochastic AnalysisInternational Journal of
6 Mathematical Problems in Engineering
24 The Kinetic Energy The kinetic energy of the sail systemcan be obtained by neglecting the orbital motion and itsinfluence on attitude motion Consider
1198791198983
=1
2119898
119897int
119897
0
[∘
1205883
+ 120596 times (r3+ 120588
3)] sdot [
∘
1205883
+ 120596 times (r3+ 120588
3)] 119889119911
1198791198981
=1
2119898
119897int
0
minus119897
[∘
1205881
+ 120596 times (r1+ 120588
1)]
sdot [∘
1205881
+ 120596 times (r1+ 120588
1)] 119889119911
1198791198982
=1
2119898
119897int
119897
0
[∘
1205882
+ 120596 times (r2+ 120588
2)] sdot [
∘
1205882
+ 120596 times (r2+ 120588
2)] 119889119910
1198791198984
=1
2119898
119897int
0
minus119897
[∘
1205884
+ 120596 times (r4+ 120588
4)] sdot [
∘
1205884
+ 120596 times (r4+ 120588
4)] 119889119910
(17)
The above equations can be rewritten as
119879119898
=1
2120596 sdot J sdot 120596
+1
2119898
119897int
119897
0
2∘
1205883
sdot (120596 times r3) + (120596 times 120588
3) sdot (120596 times 120588
3)
+ 2 (120596 times r3) sdot (120596 times 120588
3) 119889119911
+1
2119898
119897int
0
minus119897
2∘
1205881
sdot (120596 times r1) + (120596 times 120588
1) sdot (120596 times 120588
1)
+ 2 (120596 times r1) sdot (120596 times 120588
1) 119889119911
+1
2119898
119897int
119897
0
2∘
1205882
sdot (120596 times r2) + (120596 times 120588
2) sdot (120596 times 120588
2)
+ 2 (120596 times r2) sdot (120596 times 120588
2) 119889119910
+1
2119898
119897int
0
minus119897
2∘
1205884
sdot (120596 times r4) + (120596 times 120588
4) sdot (120596 times 120588
4)
+ 2 (120596 times r4) sdot (120596 times 120588
4) + (120596 times r
4)
sdot (120596 times r4) 119889119910
(18)
where J = sum4
119895=1
J119898119895
is the moment of inertia of sail systemJ119898119895
(119895 = 1ndash4) is the moment of inertia of the 119895th sail sys-tem and the expression of J can be expressed as J = diag[119869
119909
119869119910 119869
119911] inO
119874x119887y119887z119887
The kinetic energy of the payload is
119879119901=
1
2119898
119901
10038161003816100381610038161003816r119901
10038161003816100381610038161003816
2
=1
2119898
119901[minus119897
1199011sin 120582
1+ 119897
119901sin 120582
1sin 120582
2( 120579 + sin120593)
minus 119897119901sin 120582
1cos 120582
2( sin 120579 + cos 120579 cos120593)]
2
+1
2119898
119901[119897119901(
1cos 120582
1cos 120582
2minus
2sin 120582
1sin 120582
2)
+ 119897119901cos 120582
1( sin 120579 + cos 120579 cos120593)
minus 119897119901sin 120582
1cos 120582
2( cos 120579 minus sin 120579 cos120593)]
2
+1
2119898
119901[119897119901(
1cos 120582
1sin 120582
2+
2sin 120582
1cos 120582
2)
+ 119897119901sin 120582
1cos 120582
2( cos 120579 minus sin 120579 cos120593)
minus 119897119901cos 120582
1( 120579 + sin120593)]
2
(19)
The kinetic energy of the sliding masses can be obtainedas follows by neglecting the orbital motion and its influenceon attitude control
119879ℎ1
=1
2119898
ℎ1[ ( 120588
ℎ1119909+ 120579120588
ℎ1119911+ 120588
ℎ1119911sin120593
minus 119910ℎ1sin 120579 minus 119910
ℎ1cos 120579 cos120593)
2
]
+1
2119898
ℎ1[( 119910
ℎ1+ 120588
ℎ1119909sin 120579 + 120588
ℎ1119909cos 120579 cos120593
minus 120588ℎ1119911
cos 120579 + 120588ℎ1119911
sin 120579 cos120593)2]
+1
2119898
ℎ1[( 120588
ℎ1119911+ 119910
ℎ1cos 120579 minus 119910
ℎ1sin 120579 cos120593
minus 120579120588ℎ1119909
+ 120588ℎ1119909
sin120593)2
]
119879ℎ2
=1
2119898
ℎ2[( 120588
ℎ2119909+ 120579119911
ℎ2+ 119911
ℎ2sin120593 minus 120588
ℎ2119910sin 120579
minus 120588ℎ2119910
cos 120579 cos120593)2
]
+1
2119898
ℎ2[( 120588
ℎ2119910+ 120588
ℎ2119909sin 120579 + 120588
ℎ2119909cos 120579 cos120593
minus 119911ℎ2cos 120579 + 119911
ℎ2sin 120579 cos120593)
2
]
+1
2119898
ℎ2[(
ℎ2+ 120588
ℎ2119910cos 120579 minus 120588
ℎ2119910sin 120579 cos120593
minus 120579120588ℎ2119909
minus 120588ℎ2119909
sin120593)2
]
(20)
25 The Gravitational Potential Energy The gravitationalpotential energies of the sail system 119880
119892119891 payload 119880
119892119901 and
sliding masses 119880119892ℎ1
119880119892ℎ2
can be obtained as
119880119892119891
= minus
120583119898119891
1003816100381610038161003816R119874
1003816100381610038161003816
119880119892119901
= minus
120583119898119901
10038161003816100381610038161003816R119874+ r
119901
10038161003816100381610038161003816
119880119892ℎ1
= minus120583119898
ℎ1
1003816100381610038161003816R119874+ r
ℎ1
1003816100381610038161003816
119880119892ℎ2
= minus120583119898
ℎ2
1003816100381610038161003816R119874+ r
ℎ2
1003816100381610038161003816
(21)
Mathematical Problems in Engineering 7
26 The Generalized Forces The components of the sunlightunit vector S can be obtained as follows by referring toFigure 3 (left) in 120587
119868
S = j119868= [1 0 0]
119879
119868
(22)
Based on the abovementioned equations the componentsof S in 120587
119887can be obtained as
S = C119887119868[1 0 0]
119879
119868
= [119878119909
119878119910
119878119911]119879
119887
(23)
The resultant SRP force can be simply modeled as followsfor a perfectly reflective control vane
F119894= 120578119875119860
119862119894(S sdot n
119862119894)2 n
119862119894= 119865
119862119894cos2120572
119862119894n119862119894 (24)
where 120578 is the overall sail-thrust coefficient (120578max = 2) 119875 =
4563 times 10minus6 Nm2 119860
119862119894is the area of the 119894th control vane
119865119862119894
= 120578119875119860119862119894is themaximumcontrol vane thrust andn
119862119894= i
119894
is the unit normal vector of the control vaneThe componentsof n
119862119894in 120587
119887can be written as
n119862119894
= C119887119894[1 0 0]
119879
119894
= [119878119909119894
119878119910119894
119878119911119894]119879
119887
(25)
The control torque by the 119894th control vane can beexpressed as
M119894= L
119894times F
119894 (26)
In fact L119894and F
119894are dependent on the deformations of
the supporting beams and control vanes In this paper it isassumed thatL
119894andF
119894are not influenced by the deformations
of the structure when computing the control torque by thecontrol vanes Thus L
119894and F
119894can be expressed as
L1= [0 0 minus119897]
119879
L2= [0 119897 0]
119879
L3= [0 0 119897]
119879
L4= [0 minus119897 0]
119879
F119894= 120578119875119860
119862119894([119878
119909119878119910
119878119911]119887
sdot [119878119909119894
119878119910119894
119878119911119894]119879
119887
)
2
[119878119909119894
119878119910119894
119878119911119894]119879
119887
(27)
The force of each control vane can be written as
F119894= (119865
119862119894cos2120572
119862119894)C
119887119894[1 0 0]
119879
119894
= (119865119862119894cos2120572
119862119894) [119878
119909119894119878119910119894
119878119911119894]119879
119887
(28)
where 120572119862119894
is the sun angle of the 119894th control vane that canbe measured by the sun sensor And the components of thecontrol torques can be obtained as
M1198881
= (1198651198621cos2120572
1198621)[
[
0
0
minus119897
]
]
times (C1198871
[
[
1
0
0
]
]
)
= (1198651198621cos2120572
1198621)
times [
[
minus119897 cos1205931sin120595
1
minus119897 (cos 1205791cos120595
1minus sin 120579
1sin120593
1sin120595
1)
0
]
]
M1198882
= (1198651198622cos2120572
1198622)
times [
[
119897 (sin 1205792cos120595
2+ cos 120579
2sin120593
2sin120595
2)
0
minus119897 (cos 1205792cos120595
2minus sin 120579
2sin120593
2sin120595
2)
]
]
M1198883
= (1198651198623cos2120572
1198623)
times [
[
119897 cos1205933sin120595
3
119897 (cos 1205793cos120595
3minus sin 120579
3sin120593
3sin120595
3)
0
]
]
M1198884
= (1198651198624cos2120572
1198624)
times [
[
minus119897 (sin 1205794cos120595
4+ cos 120579
4sin120593
4sin120595
4)
0
119897 (cos 1205794cos120595
4minus sin 120579
4sin120593
4sin120595
4)
]
]
(29)
27 Attitude Dynamics of Solar Sail The attitude dynamicscan be obtained by using the Lagrange equation method as
119889
119889119905(
120597119871
120597 119902119895
) minus120597119871
120597119902119895
= 119876119895 (30)
where 119871 is the Lagrange function 119902119895(119895 = 1ndash3) is the vector
of the generalized coordinates and 119876119895is the vector of the
generalized force 119871 can be computed as
119871 = 119879 minus 119880 =
4
sum
119894=1
119879119898119894
+ 119879119901+
2
sum
119895=1
119879ℎ119895
minus (119880119892119891
+ 119880119892119901
+
2
sum
119895=1
119880119892ℎ119895
)
(31)
where 119879119898119894 119879
119901 and 119879
ℎ119895are the kinetic energies of the
supporting beams payload and sliding masses respectively119880119892119891 119880
119892119901 and 119880
119892ℎ119895are the gravitational potential energies of
the sail system payload and sliding masses respectively
8 Mathematical Problems in Engineering
OOx
y
z
FCFCy
FCx
FCz
mh
q(x)
Figure 5 The vibration model
120590
120590e
120590120592
120590
Figure 6 The viscoelastic model
3 The Vibration of Solar Sail
The mechanical and material models of the sailcraft aregivenThe displacement filed stress and strain are presentedbased on the Euler beam assumptionThe Lagrange equationmethod is adopted to derive the vibration equations withlarge deformations based on the calculations of kineticenergies and works done by the external loads
31 The Mechanical Model The body frame O119874xyz is estab-
lished to describe the vibration (see Figure 5) F119862is the force
vector generated by the control vane used located at the tip ofthe supporting beam 119865
119862119909 119865
119862119910 and 119865
119862119911are the components
inO119874xyz 119902(119909) is the distributed load caused by SRP
32 The Material Model The carbon fibre enforced compos-ite material is used to construct the inflatable deploymentsupporting beam The model of the viscoelastic material canbe represented in Figure 6
The total stress is the summation of the elastic and viscousstresses It can be expressed as
120590 = 120590119890
+ 120590120592
= 119864120576 + 119888119887
120576 (32)
where 120590 120590119890 and 120590
120592 are the total elastic and viscous stressrespectively And 119864 is Youngrsquos modulus 120576 ( 120576) is the strain(strain rate) and 119888
119887is the coefficient of the internal damping
expressed as 119864120578119887 120578
119887is the proportionality constant of the
internal damping The dimensions of 119888119887and 120578
119887are N lowast sm2
and s respectively
OO x
y The support beam
Z
Figure 7 The schematic diagram of solar sail supporting beamdeformation
33 The Displacement Field Stress and Strain The deforma-tion of a spatial solar sail supporting beam is presented inFigure 7
The spatial displacement fields for supporting beam are as
119906 (119909 119910 119911 119905) = 1199060(119909 119905) minus 119910
120597V0
120597119909minus 119911
1205971199080
120597119909
V (119909 119910 119911 119905) = V0(119909 119905)
119908 (119909 119910 119911 119905) = 1199080(119909 119905)
(33)
119906(119909 119910 119911 119905) V(119909 119910 119911 119905) and 119908(119909 119910 119911 119905) are the displace-ments along 119909 119910 and 119911 directions respectively 119906
0(119909 119905)
V0(119909 119905) and 119908
0(119909 119905) are the axial and transverse displace-
ments of an arbitrary point on the neutral axisBy using Green strain definition von Karmanrsquos nonlinear
strain-displacement relationships based on assumptions oflarge deflections moderate rotations and small strains for a3D supporting beam are given as follows together with thestrain rate and normal stress
120576119909119909
=120597119906
0
120597119909+1
2(120597V
0
120597119909)
2
minus 1199101205972V
0
1205971199092
+1
2(120597119908
0
120597119909)
2
minus 1199111205972
1199080
1205971199092
120576119909119909
=120597
0
120597119909+(
120597V0
120597119909)(
120597V0
120597119909) minus 119910
1205972V
0
1205971199092
+(120597119908
0
120597119909)(
1205970
120597119909)
minus 1199111205972
0
1205971199092
120590119909119909
= 119864[120597119906
0
120597119909+1
2(120597V
0
120597119909)
2
minus 1199101205972V
0
1205971199092
+1
2(120597119908
0
120597119909)
2
minus 1199111205972
1199080
1205971199092
]
+ 119864120578119887(120597
0
120597119909+(
120597V0
120597119909)(
120597V0
120597119909) minus 119910
1205972V
0
1205971199092
+(120597119908
0
120597119909)(
1205970
120597119909) minus 119911
1205972
0
1205971199092
)
(34)
Mathematical Problems in Engineering 9
The single underlined terms in the preceding equationindicate the contribution by the geometrical nonlinearityThedynamics models and corresponding numerical simulationwithout considering the geometrical nonlinearity can beobtained and carried out by neglecting these terms
34 The Energies and Works Done by External Forces Thestrain energy can be derived as
119880119894=
1
2int
119897
0
119860119909119909
[120597119906
0
120597119909+
1
2(120597V
0
120597119909)
2
+1
2(120597119908
0
120597119909)
2
]
2
+ 119863119909119909
1205972V
0
1205971199092
+ 119863119909119909
1205972
1199080
1205971199092
119889119909
(35)
For an isotropic support beam the extensional stiffness119860
119909119909and bending stiffness119863
119909119909can be computed as
119860119909119909
= int119860
119864119889119860 119863119909119909
= int119860
1198641199112
119889119860 = int119860
1198641199102
119889119860 (36)
The dissipation function is as
Ψ119902=
1
2int
119897
0
[119860119909119909120578119887(120597
0
120597119909)
2
+ 119863119909119909120578119887(1205972V
0
1205971199092
)
2
+ 119863119909119909120578119887(1205972
0
1205971199092
)
2
]119889119909
(37)
The kinetic energy for the support beam is as
119879119890=
1
2int
119897
0
[119868119860(120597119906
0
120597119905)
2
+ 119868119860(120597119908
0
120597119905)
2
+ 119868119863(1205972
1199080
120597119909120597119905)
2
+ 119868119860(120597V
0
120597119905)
2
+ 119868119863(
1205972V
0
120597119909120597119905)
2
]119889119909
(38)
where 119868119860and 119868
119863are integration constant for the support
beam expressed as
119868119860= int
119860
120588119889119860 = 120588119860 119868119863= int
119860
1205881199112
119889119860 = int119860
1205881199102
119889119860 (39)
And the work done by the external force can be obtainedas119882 = 119865
119862119911sdot 119908 (119909
119888 119905) + 119865
119862119910sdot V (119909
119888 119905) + 119898
ℎ119886ℎ119910
(119909ℎ 119905) V (119909
ℎ 119905)
+ 119898ℎ119886ℎ119911
(119909ℎ 119905) 119908 (119909
ℎ 119905) + int
119897
0
119902 (119909) V (119909 119905) 119889119909
(40)where 119909
119888represents the position of the support beam
119908(119909119888 119905) V(119909
119888 119905) are the displacements along 119911 and 119910 direc-
tions respectively and the corresponding loads 119865119862119911 119865
119862119910are
known functions 119909ℎ 119897 and V
ℎare the position coordinate of
the sliding mass the length of the support beam and theconstant-velocity of the sliding mass The dynamic responseis studied only during the period [0 119897V
ℎ] 119898
ℎis the mass
and 119886ℎ119910(119909
ℎ 119905) and 119886
ℎ119911(119909
ℎ 119905) are the components of the
acceleration for a material point on the support beam theslidingmass just arrived at And the corresponding transversedeflections are 119908(119909
ℎ 119905) and V(119909
ℎ 119905) respectively
35 The Assumed Modes Method The axial displacement1199060(119909 119905) and the transverse deflections V
0(119909 119905) and119908
0(119909 119905) can
be represented as follows by considering the assumed modesmethod
1199060(119909 119905) =
infin
sum
119894=1
119880119894(119909)119880
119894(119905)
V0(119909 119905) =
infin
sum
119895=1
119881119895(119909) 119881
119895(119905)
1199080(119909 119905) =
infin
sum
119896=1
119882119896(119909)119882
119896(119905)
(41)
where 119880119894(119905) 119881
119895(119905) and 119882
119896(119905) are the time-dependent gen-
eralized coordinates and 119880119894(119909) 119881
119895(119909) and 119882
119896(119909) are the
assumedmodes For assumedmodemethod themode shapefunctions should satisfy the following requirements in thispaper
119880119894(119909)
1003816100381610038161003816119909=0= 0 119881
119895(119909)
10038161003816100381610038161003816119909=0= 0 119882
119896(119909)
1003816100381610038161003816119909=0= 0
1198811015840
119895
(119909)10038161003816100381610038161003816119909=0
= 0 1198821015840
119896
(119909)10038161003816100381610038161003816119909=0
= 0
(42)
The following first two assumed modes satisfying theassumed mode principle are used in this paper
1198801(119909) =
119909
119897 119880
2(119909) = (
119909
119897)
2
1198811(119909) = (
119909
119897)
2
1198812(119909) = (
119909
119897)
3
1198821(119909) = (
119909
119897)
2
1198822(119909) = (
119909
119897)
3
(43)
With the help of the assumedmodes the detailed expres-sions of 119880
119894 119879
119890119882
119911 and Ψ
119902can be obtained as
119880119894=
9
2
119860119909119909
1198973(119881
2
2
+ 1198822
2
)2
+27
4
119860119909119909
1198973(119881
11198812+ 119882
1119882
2)
times (1198812
2
+ 1198822
2
)
+18
7
119860119909119909
1198973[(119881
2
1
+ 1198822
1
) (1198812
2
+ 1198822
2
) + (11988111198812+ 119882
1119882
2)2
]
+119860
119909119909
1198973[3
2119897119880
2(119881
2
2
+ 1198822
2
) + (1198812
1
+ 1198822
1
)
times (11988111198812+ 119882
1119882
2)]
10 Mathematical Problems in Engineering
+1
10
119860119909119909
1198973[9119880
1119897 (119881
2
2
+ 1198822
2
) + 241198802119897 (119881
11198812+ 119882
1119882
2)
+ 4 (1198812
1
+ 1198822
1
)2
]
+119860
119909119909
1198972[3
21198801(119881
11198812+ 119882
1119882
2) + 119880
2(119881
2
1
+ 1198822
1
)]
+6119863
119909119909119881
2
2
1198973+ 119860
119909119909(2119880
1119881
2
1
31198972+
21198801119882
2
1
31198972+
21198802
2
3119897)
+6119863
119909119909119882
2
2
1198973+
611986311990911990911988111198812
1198973+
11986011990911990911988011198802
119897+
6119863119909119909119882
1119882
2
1198973
+119860
119909119909119880
2
1
2119897+
2119863119909119909119881
2
1
1198973+
2119863119909119909119882
2
1
1198973
119879119890=
1
14(119897119868
119860
2
2
+ 119897119868119860
2
2
) +1
6(119897119868
119860
1
2+ 119897119868
11986012)
+1
10(119897119868
119860
2
2
+ 119897119868119860
2
1
+9119868
119863
2
2
119897+ 119897119868
119860
2
1
+9119868
119863
2
2
119897)
+1
4(119897119868
11986012+
6119868119863
1
2
119897+
611986811986312
119897)
+1
6(119897119868
119860
2
1
+4119868
119863
2
1
119897+
4119868119863
2
1
119897)
119882119911= 119865
119862119911sdot [119882
1(119905) + 119882
2(119905)] + 119865
119862119910sdot [119881
1(119905) + 119881
2(119905)]
+ 119898ℎ[2V2
ℎ
1198972sdot 119881
1(119905) +
4V2ℎ
119905
1198972sdot
1(119905) + (
Vℎ119905
119897)
2
sdot 1(119905)
+6V3
ℎ
119905
1198973sdot 119881
2(119905) +
6V3ℎ
1199052
1198973
sdot 2(119905) + (
Vℎ119905
119897)
3
sdot 2(119905)]
times [(Vℎ119905
119897)
2
sdot 1198811(119905) + (
Vℎ119905
119897)
3
sdot 1198812(119905)]
+ 119898ℎ[2V2
ℎ
1198972sdot 119882
1(119905) +
4V2ℎ
119905
1198972sdot
1(119905) + (
Vℎ119905
119897)
2
sdot 1(119905)
+6V3
ℎ
119905
1198973sdot 119882
2(119905) +
6V3ℎ
1199052
1198973sdot
2(119905)
+ (Vℎ119905
119897)
3
sdot 2(119905)]
times [(Vℎ119905
119897)
2
sdot 1198821(119905) + (
Vℎ119905
119897)
3
sdot 1198822(119905)]
+ 1198811(119905) sdot int
119897
0
119902 (119909) (119909
119897)
2
119889119909 + 1198812(119905)
sdot int
119897
0
119902 (119909) (119909
119897)
3
119889119909
Ψ119902=
1
6(36119863
119909119909120578119887
2
2
1198976+
4119860119909119909120578119887
2
2
1198974+
36119863119909119909120578119887
2
2
1198976) 119897
3
+1
4(4119860
11990911990912057811988712
1198973+
2411986311990911990912057811988712
1198975
+24119863
119909119909120578119887
1
2
1198975) 119897
2
+1
2
119860119909119909120578119887
2
1
119897+
2119863119909119909120578119887
2
1
1198973+
2119863119909119909120578119887
2
1
1198973
(44)
36 The Vibration Equation The Lagrange equation methodis used to derive the vibration equations
120597119871
120597119902119899
minus119889
119889119905(
120597119871
120597 119902119899
) + 119876119889= 0 119899 = 1 2 6 (45)
where 119871 is the Lagrange function 119902119899
= (1198801 119880
2 119881
1 119881
2
1198821119882
2)119879 is the vector of the generalized coordinates and
119902119899is the corresponding generalized velocity vector 119876
119889is the
generalized damping force The expressions for 119871 and 119876119889are
as
119871 = 119879119890minus (119880
119894minus 119882
119911)
119876119889= minus
120597Ψ119902
120597 119902119899
(119899 = 1 sim 6)
(46)
The axial vibration equations can be obtained as followsfor 119880
1 119880
2
1
31198971198681198601+
1
41198971198681198602+
120578119887119860
1199091199091
119897+
120578119887119860
1199091199092
119897+
1198601199091199091198801
119897
+119860
1199091199091198802
119897+
2119860119909119909119881
2
1
31198972+
311986011990911990911988111198812
21198972+
9119860119909119909119881
2
2
101198972
+2119860
119909119909119882
2
1
31198972+
3119860119909119909119882
1119882
2
21198972+
9119860119909119909119882
2
2
101198972= 0
(47a)
1
41198971198681198601+
1
51198971198681198602+
120578119887119860
1199091199091
119897+
4120578119887119860
1199091199092
3119897
+119860
1199091199091198801
119897+4119860
1199091199091198802
3119897+119860
119909119909119881
2
1
1198972+12119860
11990911990911988111198812
51198972+3119860
119909119909119881
2
2
21198972
+119860
119909119909119882
2
1
1198972+
12119860119909119909119882
1119882
2
51198972+
3119860119909119909119882
2
2
21198972= 0
(47b)
The following can be seen from the above equations
(1) Since the assumed modes rather than the naturalmodes are used the coupling between axial and trans-verse vibrations is rather severe for axial vibrations
Mathematical Problems in Engineering 11
(2) The nonlinearity is apparent in above equations onlyexisting in the terms of 119881
1 119881
2119882
1119882
2 We take (47a)
as an exampleThe terms including1198802and its first and
second derivative 1198811 119881
2119882
1119882
2 can be regarded as
the applied loads for 1198801
(3) The coupling between the axial and transverse vibra-tionswill disappear as long as the linear displacement-strain relationship is adopted
(4) There are no external loads for axial vibrationsaccording to above equations
The transverse vibration equations for 1198811 119881
2and119882
1 119882
2
can be obtained as
4
3
1198681198631
119897+
1
51198971198681198601+
1
61198971198681198602minus
119898ℎV5ℎ
1199055
2
1198975+
31198681198632
2119897
+4119898
ℎV4ℎ
1199053
1
1198974+
4120578119887119863
1199091199091
1198973minus
2119898ℎV5ℎ
1199054
2
1198975+
6120578119887119863
1199091199092
1198973
+8119898
ℎV4ℎ
1199052
1198811
1198974+
41198631199091199091198811
1198973+
8119898ℎV5ℎ
1199053
1198812
1198975+
61198631199091199091198812
1198973
+27119860
1199091199091198812119882
2
2
81198973+
541198601199091199091198811119881
2
2
71198973+
181198601199091199091198811119882
2
2
71198973
+6119860
119909119909119881
2
1
1198812
1198973+
21198601199091199091198812119882
2
1
1198973+
1211986011990911990911988021198812
51198972
+8119860
1199091199091198811119882
2
1
51198973+
311986011990911990911988011198812
21198972+
211986011990911990911988021198811
1198972
+8119860
119909119909119881
3
1
51198973+
27119860119909119909119881
3
2
81198973+
361198601199091199091198812119882
1119882
2
71198973
+4119860
1199091199091198811119882
1119882
2
1198973+
411986011990911990911988011198811
31198972minus 119865
119888119910(119905) minus 05119865
025119865= 0
1
61198971198681198601+
3
2
1198681198631
119897minus
119898ℎV5ℎ
1199055
1
1198975+
1
71198971198681198602+
9
5
1198681198632
119897
+6120578
119887119863
1199091199091
1198973+
2119898ℎV5ℎ
1199054
1
1198975+
12120578119887119863
1199091199092
1198973+
6119898ℎV6ℎ
1199055
2
1198976
+6119863
1199091199091198811
1198973+
16119898ℎV5ℎ
1199053
1198811
1198975+
121198631199091199091198812
1198973+
18119898ℎV6ℎ
1199054
1198812
1198976
+9119860
1199091199091198812119882
2
2
21198973+
811198601199091199091198811119881
2
2
81198973+
311986011990911990911988011198811
21198972
+27119860
1199091199091198811119882
2
2
81198973+
541198601199091199091198812119881
2
1
71198973+
181198601199091199091198812119882
2
1
71198973
+3119860
11990911990911988021198812
1198972+
21198601199091199091198811119882
2
1
1198973+
911986011990911990911988011198812
51198972+
1211986011990911990911988021198811
51198972
+9119860
119909119909119881
3
2
21198973+
2119860119909119909119881
3
1
1198973+
271198601199091199091198812119882
1119882
2
41198973
+36119860
1199091199091198811119882
1119882
2
71198973minus 04119865
025119865minus 119865
119888119910(119905) = 0
4
3
119868119863
1
119897+
1
5119897119868119860
1+
3
2
119868119863
2
119897+
1
6119897119868119860
2minus
119898ℎV5ℎ
1199055
2
1198975
+4120578
119887119863
119909119909
1
1198973+
4119898ℎV4ℎ
1199053
1
1198974minus
2119898ℎV5ℎ
1199054
2
1198975+
6120578119887119863
119909119909
2
1198973
+4119863
119909119909119882
1
1198973+
8119898ℎV4ℎ
1199052
1198821
1198974+
8119898ℎV5ℎ
1199053
1198822
1198975+
6119863119909119909119882
2
1198973
+36119860
119909119909119882
211988111198812
71198973+
4119860119909119909119882
111988111198812
1198973+
27119860119909119909119882
2119881
2
2
81198973
+18119860
119909119909119882
1119881
2
2
71198973+
54119860119909119909119882
1119882
2
2
71198973+
6119860119909119909119882
2
1
1198822
1198973
+2119860
119909119909119882
2119881
2
1
1198973+
121198601199091199091198802119882
2
51198972+
8119860119909119909119882
1119881
2
1
51198973
+3119860
1199091199091198801119882
2
21198972+
21198601199091199091198802119882
1
1198972+
27119860119909119909119882
3
2
81198973
+8119860
119909119909119882
3
1
51198973+
41198601199091199091198801119882
1
31198972minus 119865
119888119911(119905) = 0
1
7119897119868119860
2+
9
5
119868119863
2
119897+
1
6119897119868119860
1minus
119898ℎV5ℎ
1199055
1
1198975+
3
2
119868119863
1
119897
+6120578
119887119863
119909119909
1
1198973+
2119898ℎV5ℎ
1199054
1
1198975+
6119898ℎV6ℎ
1199055
2
1198976
+12120578
119887119863
119909119909
2
1198973+
6119863119909119909119882
1
1198973+
16119898ℎV5ℎ
1199053
1198821
1198975
+12119863
119909119909119882
2
1198973+
18119898ℎV6ℎ
1199054
1198822
1198976+
31198601199091199091198801119882
1
21198972
+27119860
119909119909119882
211988111198812
41198973+
36119860119909119909119882
111988111198812
71198973+
9119860119909119909119882
2119881
2
2
21198973
+27119860
119909119909119882
1119881
2
2
81198973+
81119860119909119909119882
1119882
2
2
81198973+
18119860119909119909119882
2119881
2
1
71198973
+54119860
119909119909119882
2119882
2
1
71198973+
31198601199091199091198802119882
2
1198972+
2119860119909119909119882
1119881
2
1
1198973
+9119860
1199091199091198801119882
2
51198972+
121198601199091199091198802119882
1
51198972+
2119860119909119909119882
3
1
1198973
+9119860
119909119909119882
3
2
21198973minus 119865
119888119911(119905) = 0
(48)
The complexity high coupling and nonlinearity are obvi-ous in above equations
4 The Coupled Rigid-Flexible Dynamics
The dynamics for control and dynamic simulation shouldbe presented for solar sail based on the simplification ofequations derived in previous sections Some assumptions aremade before simplifying the equations as follows
12 Mathematical Problems in Engineering
(1) Only the attitude motion is affected by the slidingmass the vibration of solar sail structure is notaffected by the sliding mass
(2) Although the attitude control is accomplished byrotating control vanes and the gimbaled controlboom moving sliding masses the specific time his-tories of the actuators are not considered here
(3) The four supporting beams are regarded as an entirestructure thus the identical generalized coordinatesare adopted in the dynamic analysis
41 The Simplified Attitude Dynamics The kinetic energy ofsolar sail supporting beams can be obtained as
119879119898
=1
2120596 sdot J sdot 120596 + 119898
119897int
119897
0
2∘
1205883
sdot (120596 times r3) + (120596 times 120588
3) sdot (120596 times 120588
3)
+ 2 (120596 times r3) sdot (120596 times 120588
3) 119889119911
+ 119898119897int
119897
0
2∘
1205882
sdot (120596 times r2) + (120596 times 120588
2) sdot (120596 times 120588
2)
+ 2 (120596 times r2) sdot (120596 times 120588
2) 119889119910
(49)
The subscripts 2 and 3 represent the second and thirdsupporting beams The displacements can be expressed as
V0119909
(119911 119905) = (119911
119897)
2
sdot 1198811(119905) + (
119911
119897)
3
sdot 1198812(119905)
1199080119910
(119911 119905) = 120572V0119909
(119911 119905) = (119911
119897)
2
sdot 1205721198811(119905) + (
119911
119897)
3
sdot 1205721198812(119905)
for the 3rd beam
V0119909
(119910 119905) = 120573V0119909
(119911 119905) = (119910
119897)
2
sdot 1205731198811(119905) + (
119910
119897)
3
sdot 1205731198812(119905)
1199080119911
(119910 119905) = 120574V0119909
(119910 119905) = (119910
119897)
2
sdot 1205741198811(119905) + (
119910
119897)
3
sdot 1205741198812(119905)
for the 2nd beam
(50)
The subscripts 119909 119910 and 119911 of the left terms in (50)represent the displacements along119909119910 and 119911directions119881
1(119905)
and 1198812(119905) are the generalized coordinates The displacements
1199080119910(119911 119905) V
0119909(119910 119905) and 119908
0119911(119910 119905) can be obtained using the
assumed modes as
1205883= V
0119909(119911 119905) i
119887+ 119908
0119910(119911 119905) j
119887
=
[[[[[
[
(119911
119897)
2
sdot 1198811(119905) + (
119911
119897)
3
sdot 1198812(119905)
120572 [(119911
119897)
2
sdot 1198811(119905) + (
119911
119897)
3
sdot 1198812(119905)]
0
]]]]]
]
1205882= V
0119909(119910 119905) i
119887+ 119908
0119911(119910 119905) k
119887
=
[[[[[
[
120573[(119910
119897)
2
sdot 1198811(119905) + (
119910
119897)
3
sdot 1198812(119905)]
0
120574 [(119910
119897)
2
sdot 1198811(119905) + (
119910
119897)
3
sdot 1198812(119905)]
]]]]]
]
(51)
The vibration velocity can be obtained as
∘
1205883
= 1205883119909i119887+ 120588
3119910j119887=
[[[[[
[
(119911
119897)
2
sdot 1(119905) + (
119911
119897)
3
sdot 2(119905)
1205721[(
119911
119897)
2
sdot 1(119905) + (
119911
119897)
3
sdot 2(119905)]
0
]]]]]
]
∘
1205882
= 1205882119909i119887+ 120588
2119911k119887=
[[[[[
[
1205731[(
119910
119897)
2
sdot 1(119905) + (
119910
119897)
3
sdot 2(119905)]
0
1205741[(
119910
119897)
2
sdot 1(119905) + (
119910
119897)
3
sdot 2(119905)]
]]]]]
]
(52)
Without loss of generality 120572 = 120573 = 1205721= 120573
1= 1 and
120574 = 1205741= minus1 can be assumed in above expressions And the
kinetic energy of the slidingmasses can be obtained as followsby neglecting the vibration related terms
119879ℎ=
1
2119898
ℎ1(120596 times r
ℎ1) sdot (120596 times r
ℎ1) +
1
2119898
ℎ2(120596 times r
ℎ2)
sdot (120596 times rℎ2)
(53)
The kinetic energy of the payload can be obtained as
119879119901=
1
2119898
119901(120596 times r
119901) sdot (120596 times r
119901) (54)
The following simplified attitude dynamics can beobtained by neglecting the second and higher terms ofattitude angles and vibration modes in computing the kinetic
Mathematical Problems in Engineering 13
energies of the supporting beams payload and slidingmasses Consider
119869119909 minus 119898
1198971198972
1minus
4
5119898
1198971198972
2+ 119898
ℎ11199102
ℎ1
+ 119898ℎ21199112
ℎ2
minus 119898119901119903119901119909119903119901119911 + 119898
1199011199032
119901119911
+ 1198981199011199032
119901119910
minus 119898119901119903119901119909119903119901119910
120579 = 119876120593
119869119910
120579 +2
5119898
1198971198972
2+
1
2119898
1198971198972
1+ 119898
ℎ21199112
ℎ2
120579
+ 1198981199011199032
119901119911
120579 minus 119898119901119903119901119910119903119901119911 minus 119898
119901119903119901119909119903119901119910
+ 1198981199011199032
119901119909
120579 = 119876120579
119869119911 minus
2
51198972
1198981198972minus
1
21198972
1198981198971+ 119898
ℎ11199102
ℎ1
minus 119898119901119903119901119910119903119901119911
120579 + 1198981199011199032
119901119910
+ 1198981199011199032
119901119909
minus 119898119901119903119901119909119903119901119911 = 119876
120595
(55)
where 119876120593 119876
120579 and 119876
120595are the generalized nonpotential
attitude control torques generated by the control vanes Andthe attitude control torques generated by the gimbaled controlboom and sliding masses can be found on the left side ofthe above equation coupled with 120579 making the attitudecontroller design problem rather difficult
42 The Simplified Vibration Equations The couplingbetween the axial and transverse vibrations is neglectedand only the transverse vibration is considered The attitudedynamics for dynamic simulation can be obtained as followsbased on previous derivation by neglecting the action ofsolar-radiation pressure
4
3
1198681198631
119897+
1
51198971198681198601+
1
61198971198681198602+
31198681198632
2119897+
4120578119887119863
1199091199091
1198973
+6120578
119887119863
1199091199092
1198973+
41198631199091199091198811
1198973+
61198631199091199091198812
1198973+
271198601199091199091198812119882
2
2
81198973
+54119860
1199091199091198811119881
2
2
71198973+
181198601199091199091198811119882
2
2
71198973+
6119860119909119909119881
2
1
1198812
1198973
+2119860
1199091199091198812119882
2
1
1198973+
81198601199091199091198811119882
2
1
51198973+
8119860119909119909119881
3
1
51198973
+27119860
119909119909119881
3
2
81198973+
361198601199091199091198812119882
1119882
2
71198973+
41198601199091199091198811119882
1119882
2
1198973
minus 1198651198621
(119905) = 0
1
61198971198681198601+
3
2
1198681198631
119897+
1
71198971198681198602+
9
5
1198681198632
119897+
6120578119887119863
1199091199091
1198973
+12120578
119887119863
1199091199092
1198973+
61198631199091199091198811
1198973+
121198631199091199091198812
1198973+
91198601199091199091198812119882
2
2
21198973
+81119860
1199091199091198811119881
2
2
81198973+
271198601199091199091198811119882
2
2
81198973+
541198601199091199091198812119881
2
1
71198973
+18119860
1199091199091198812119882
2
1
71198973+
21198601199091199091198811119882
2
1
1198973+
9119860119909119909119881
3
2
21198973
+2119860
119909119909119881
3
1
1198973+
271198601199091199091198812119882
1119882
2
41198973+
361198601199091199091198811119882
1119882
2
71198973
minus 1198651198622
(119905) = 0
(56)
The following equations can be obtained by rearrangingthe above equations
4
3
1198681198631
119897+
1
51198971198681198601+
1
61198971198681198602+
31198681198632
2119897+
4120578119887119863
1199091199091
1198973
+6120578
119887119863
1199091199092
1198973+
41198631199091199091198811
1198973+
61198631199091199091198812
1198973+
16119860119909119909119881
3
1
51198973
+12119860
119909119909119881
2
1
1198812
1198973+
1081198601199091199091198811119881
2
2
71198973+
54119860119909119909119881
3
2
81198973
minus 1198651198621
(119905) = 0
1
61198971198681198601+
3
2
1198681198631
119897+
1
71198971198681198602+
9
5
1198681198632
119897+
6120578119887119863
1199091199091
1198973
+12120578
119887119863
1199091199092
1198973+
61198631199091199091198811
1198973+
121198631199091199091198812
1198973
+4119860
119909119909119881
3
1
1198973+
108119860119909119909119881
2
1
1198812
71198973+
811198601199091199091198811119881
2
2
41198973
+9119860
119909119909119881
3
2
1198973minus 119865
1198622(119905) = 0
(57)
1198651198621(119905) and 119865
1198622(119905) are used to represent all the generalized
external forces they can be used for vibration control Thesecomplicated equations abovementioned are the basis forobtaining the simplified equations used for controller design
The following equations can be obtained by neglecting thetwo and higher terms
4
3
1198681198631
119897+
1
51198971198681198601+
1
61198971198681198602+
31198681198632
2119897+
4120578119887119863
1199091199091
1198973
+6120578
119887119863
1199091199092
1198973+
41198631199091199091198811
1198973+
61198631199091199091198812
1198973= 119865
1198621
(119905)
14 Mathematical Problems in Engineering
1
61198971198681198601+
3
2
1198681198631
119897+
1
71198971198681198602+
9
5
1198681198632
119897+
6120578119887119863
1199091199091
1198973
+12120578
119887119863
1199091199092
1198973+
61198631199091199091198811
1198973+
121198631199091199091198812
1198973= 119865
1198622
(119905)
(58)
43 The Rigid-Flexible Coupled Dynamics The simplifiedattitude and vibration dynamics can be written as
119886120593 + 119886
120579
120579 + 119886120595 + 119886
1198811
1+ 119886
1198812
2= 119876
120593
119887120579
120579 + 119887120595 + 119887
120593 + 119887
1198811
1+ 119887
1198812
2= 119876
120579
119888120595 + 119888
120579
120579 + 119888120593 + 119888
1198811
1+ 119888
1198812
2= 119876
120595
119889
1198811
1+ 119889
1198812
2+ 119889
1198811
1+ 119889
1198812
2+ 119889
1198811
1198811
+ 1198891198812
1198812= 119876
1198811
119890
1198811
1+ 119890
1198812
2+ 119890
1198811
1+ 119890
1198812
2+ 119890
1198811
1198811
+ 1198901198812
1198812= 119876
1198812
(59)
The related coefficients in the preceding equation can befound in (A1) in the appendix The dynamics (see (59)) isnot suitable for attitude controller design because the controlinputs exist in some coefficients of the angular accelerationsThis will make the controller design rather difficult Thusthe following dynamic model is obtained by putting theterms including the control inputs right side of the dynamicequations
119869119909 minus 119898
1198971198972
1minus
4
5119898
1198971198972
2= 119876
120593+ 119906
119869119910
120579 +2
5119898
1198971198972
2+
1
2119898
1198971198972
1= 119876
120579+ 119906
120579
119869119911 minus
1
21198972
1198981198971minus
2
51198972
1198981198972= 119876
120595+ 119906
119889
1198811
1+ 119889
1198812
2+ 119889
1198811
1+ 119889
1198812
2
+ 1198891198811
1198811+ 119889
1198812
1198812= 119876
1198811
119890
1198811
1+ 119890
1198812
2+ 119890
1198811
1+ 119890
1198812
2
+ 1198901198811
1198811+ 119890
1198812
1198812= 119876
1198812
(60)
The expressions for 119906 119906
120579
and 119906are as
119906= minus119898
ℎ11199102
ℎ1
minus 119898ℎ21199112
ℎ2
+ 119898119901119903119901119909119903119901119911 minus 119898
1199011199032
119901119911
minus 1198981199011199032
119901119910
+ 119898119901119903119901119909119903119901119910
120579
119906
120579
= minus119898ℎ21199112
ℎ2
120579 minus 1198981199011199032
119901119911
120579 + 119898119901119903119901119910119903119901119911 + 119898
119901119903119901119909119903119901119910
minus 1198981199011199032
119901119909
120579
119906= minus119898
ℎ11199102
ℎ1
+ 119898119901119903119901119910119903119901119911
120579 minus 1198981199011199032
119901119910
minus 1198981199011199032
119901119909
+ 119898119901119903119901119909119903119901119911
(61)
119906 119906
120579
and 119906are the functions of the positions of sliding
masses and payload and the angular accelerations The statevariables in (60) are defined as
1199091= 120593 119909
2= 119909
3= 120579 119909
4= 120579
1199095= 120595 119909
6= 119909
7= 119881
1
1199098=
1 119909
9= 119881
2 119909
10=
2
(62)
Thedynamics (60) can bewritten as the state-spacemodelas following
1= 119909
2
2= 119886
11199097+ 119886
21199098+ 119886
31199099+ 119886
411990910
+ 119906120593
3= 119909
4
4= 119886
51199097+ 119886
61199098+ 119886
71199099+ 119886
811990910
+ 119906120579
5= 119909
6
6= 119886
91199097+ 119886
101199098+ 119886
111199099+ 119886
1211990910
+ 119906120595
7= 119909
8
8= 119886
131199097+ 119886
141199098+ 119886
151199099+ 119886
1611990910
+ 1199061198811
9= 119909
10
10
= 119886171199097+ 119886
181199098+ 119886
191199099+ 119886
2011990910
+ 1199061198812
(63)
where 119906120579 119906
120593 and 119906
120595are the generalized control inputs
for attitude control and 1199061198811
and 1199061198812
are the generalizedcontrol inputs for vibration control The controllability canbe satisfied by analyzing (63) The attitudevibration controlinputs and the coefficients will be presented later in thissection The form of a matrix differential equation can bewritten as follows for the above equation
x = Ax + Bu (64)
The expressions of the relatedmatrices and vectors can befound as
x = [1
2
3
4
5
6
7
8
9
10]119879 x (119905
0) = x
1199050
u = [119906120593 119906
120579 119906
120595 119906
1198811
1199061198812
]119879
u (1199050) is known
(65)
where A xB and u are the system matrix state variablesvector control matrix and control inputs vector respectively
Mathematical Problems in Engineering 15
The complexity of the state-space model can be seen bypresenting the detailed expressions of control inputs forattitudevibration and related parameters in (A2) in theappendix
5 AttitudeVibration Control and Simulation
The controller for the attitude and vibration is developedusing the LQR and optimal PI theory The dynamic simula-tion is performed based on the coupled dynamics derived inthe previous sections
51 LQR and Optimal PI Based Controllers Design Thedynamics for solar sail can bewritten as follows togetherwithits quadratic cost function also defined as
x = Ax + Bu x (1199050) = x
1199050
(known)
119869 =1
2int
infin
1199050
[x119879 (119905)Qx (119905) + u119879 (119905)Ru (119905)] 119889119905
(66)
whereQ = Q119879
⩾ 0 andR = R119879
gt 0 are constantThe control-lability of [AB] and the observability of [AD] can beensured when the equationDD119879
= Q holds for anymatrixDThe optimal control input ulowast(119905)within the scope of u(119905) isin R119903119905 isin [119905
0infin] can be computed as follows to make 119869minimum
ulowast (119905) = minusKxlowast (119905) K = Rminus1B119879P (67)
where P is the nonnegative definite symmetric solution of thefollowing Riccati algebraic equations
PA + A119879P minus PBRminus1B119879P +Q = 0 (68)
And the optimal performance index can be obtained asfollows for arbitrary initial states
119869lowast
[x (1199050) 119905
0] =
1
2x1198790
Px0 (69)
The closed-loop system
x = (A minus BRminus1B119879P) x (70)
is asymptotically stableFor an orbiting solar sail the primary disturbance torque
is by the cmcp offset and the impact of the tiny dust inthe deep space The state regulator can be used to controlthe dynamic system affected by pulse disturbance torquewith good steady-state errors but will never achieve accuratesteady-state errors if the dynamics is affected by constantdisturbance torque Thus the optimal state regulator withan integrator to eliminate the constant disturbance torqueshould be presented This optimal proportional-integral reg-ulator not only eliminates the constant disturbance torque butalso possesses the property of optimal regulator
Table 1 The related parameters
Parameters ValuesCMCP offsetm [0 017678 017678]119879
The side length of square sailm 100Nominal solar-radiation pressureconstant at 1 AU from the sunNm2 4563 times 10minus6
Solar-radiation pressure forceN 912 times 10minus2
Roll inertiakglowastm2 50383Pitch and yaw inertiakglowastm2 251915Outer radiusm 0229Thickness of the supporting beamm 75 times 10minus6
Youngrsquos modulus of the supportingbeamGPa 124
Moment of inertia of the cross-sectionof the supporting beamm4 2829412 times 10minus7
Bending stiffness of the supportingbeamNlowastm2 3508471336
Proportional damping coefficient ofsupporting beams 001
Line density of the supportingbeamkgm 0106879
Cross-sectional area of the supportingbeamm2 1079 times 10minus5
Roll disturbance torqueNlowastm 0Pitch (yaw) disturbance torqueNlowastm 0016122 (minus0016122)
For the following linear system with the correspondingperformance index
x = Ax + Bu x (1199050) = x
1199050
u (1199050) = u
1199050
119869 =1
2int
infin
1199050
(x119879Qx + u119879Ru + u119879Su) 119889119905(71)
where Q = Q119879
⩾ 0 R = R119879
gt 0 and S = S119879 gt 0 If [AB]is completely controllable and meanwhile [AD
11] is com-
pletely observable with the relationship D11D119879
11
= Q thesolution can be expressed as
ulowast = minusK1x minus K
2ulowast ulowast (119905
0) = u
1199050
(72)
If B119879B is full rank we can get
ulowast = minusK3x minus K
4x ulowast (119905
0) = u
1199050
(73)
K119894(119894 = 1 2 3 4) is the function of ABQR S
The closed-loop system
[xulowast] = [
A BminusK
1minusK
2
] [xulowast] [
[
x (1199050)
u (1199050)]
]
= [x1199050
u1199050
] (74)
is asymptotically stableThe compromise between the state variables (the angle
angular velocity the vibration displacement and velocity)and control inputs (the torque by all the actuators) can
16 Mathematical Problems in Engineering
0 2000 4000 6000
0 2000 4000 6000
0 2000 4000 6000minus5
0
5
minus5
0
5
minus5
0
5
minus4
minus2
0
2
4
times10minus4
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
00162
00164
00166
4800 4900 5000
4800 4900 5000
4800 4900 5000
minus00165
minus0016
Time (s) Time (s)
Time (s)
Time (s)
Time (s)
Time (s)
Roll
erro
r120593(∘
)
Roll
erro
r120593(∘
)
Pitc
h er
ror120579
(∘)
Pitc
h er
ror120579
(∘)
Yaw
erro
r120595(∘
)
Yaw
erro
r120595(∘
)
Figure 8 The roll pitch and yaw errors
be achieved by using both the LQR based and optimal PIbased controllers for the coupled attitudevibration dynamicsystem The fact is that the attitude control ability is limitedto the control torque by the control actuators The change ofthe attitude angles and rates should not be frequent to voidexciting vibrations
Thus the weighting matrix Q and the control weightingmatrix R are selected as follows for LQR based controller
Q (1 1) = 9 times 10minus6
Q (2 2) = 1 times 10minus6
Q (3 3) = 16 times 10minus6
Q (4 4) = Q (5 5) = Q (6 6) = Q (7 7) = Q (8 8)
= Q (9 9) = Q (10 10) = 1 times 10minus6
Q (119894 119895) = 0 (119894 = 119895 119894 119895 = 1 sim 10)
R (1 1) = R (2 2) = 900 R (3 3) = 100
R (4 4) = R (5 5) = 10000
R119894119895
= 0 (119894 = 119895 119894 119895 = 1 sim 5)
(75)
TheweightingmatrixQ and the control weightingmatrixR are selected as follows for the optimal PI based controller
Q (1 1) = Q (2 2) = 4 times 10minus8
Q (3 3) = Q (4 4) = Q (5 5) = Q (6 6) = Q (7 7)
= Q (8 8) = 16 times 10minus8
Mathematical Problems in Engineering 17
minus02
0
02
Roll
rate
(∘s)
Roll
rate
(∘s)
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Pitc
h ra
te(∘s)
Pitc
h ra
te(∘s)
0 1000 2000 3000 4000 5000
minus05
0
05
minus05
0
05
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
Time (s)
Yaw
rate
(∘
s)
Yaw
rate
(∘
s)
4800 4850 4900 4950 5000
Time (s)4800 4850 4900 4950 5000
Time (s)4800 4850 4900 4950 5000
minus2
0
2
minus2
0
2
minus2
0
2
times10minus4
times10minus4
times10minus4
Figure 9 The roll pitch and yaw rates
Q (9 9) = Q (10 10) = 1 times 10minus8
Q (119894 119895) = 0 (119894 = 119895 119894 119895 = 1 sim 10)
R (1 1) = R (2 2) = R (3 3) = 1 times 10minus8
R (4 4) = R (5 5) = 4 times 10minus8
R (119894 119895) = 0 (119894 = 119895 119894 119895 = 1 sim 5)
(76)
52 The Simulation Results The initial angle errors of rollpitch and yaw are adopted as 120593(119905
0) = 3
∘ 120579(1199050) = 3
∘ and120595(119905
0) = 3
∘ the initial angular velocity errors of roll pitchand yaw are adopted as (119905
0) = 0
∘
s 120579(1199050) = 0
∘
s and(119905
0) = 0
∘
s 1198811(1199050) = 01m 119881
2(1199050) = 01m
1(1199050) = 0ms
and 2(1199050) = 0ms are adopted in this paper for dynamic
simulationThe estimated cmcp offset is 025m for a 100 times 100m
square solar sail It is assumed that the components of cmcpoffset vector are [0 017678 017678]
119879 in the body frame
The relevant parameters for dynamic simulations are givenin Table 1
The dynamic simulation results are obtained as followsby using the LQR controller based on the abovementionedQ and R related parameters and initial conditions Thedynamics simulations with (denoted by ldquowith GFrdquo) andwithout (denoted by ldquowithout GFrdquo) considering the geo-metrical nonlinearity are presented And the correspondingdiscussions and analysis are also given according to thecalculated results
The roll pitch and yaw errors are presented based onthe dynamics models with and without considering thegeometrical nonlinearityThe control effect with zero steady-state error can be achieved for roll axis by referring tothe results But the steady-state errors exist for pitch andyaw axes from Figure 8 this is because there exist constantdisturbance torques for pitch and yaw axes caused by thecmcp offset Thus the LQR based controller cannot be usedfor attitude control with good steady-state performance Thesteady-state errors of pitch and yaw axes are about 0164
∘
and minus0164∘ respectively from the corresponding partial
enlarged drawing of the figures (see the corresponding left
18 Mathematical Problems in Engineering
minus20
0
20
Roll
torq
ue (N
lowastm
)
Roll
torq
ue (N
lowastm
)
minus50
0
50
minus50
0
50
Pitc
h to
rque
(Nlowast
m)
Pitc
h to
rque
(Nlowast
m)
0 1000 2000 3000 4000 5000
0 2000 4000 6000
0 2000 4000 6000
Yaw
torq
ue (N
lowastm
)
Yaw
torq
ue (N
lowastm
)
minus002
0
002
008
01
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
minus01
minus009
minus008
Time (s)Time (s)
Time (s)Time (s)
Time (s)Time (s)
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Figure 10 The roll pitch and yaw torques
figures) A simple and practical controller should be designedto eliminate the steady-state errorsThese errorswill affect theprecision of the super long duration space mission deeply
The differences between the dynamics with and withoutthe geometrical nonlinearity effect can be observed Theamplitudes and phases change a bit by comparing the corre-sponding results
It can be observed by the partial enlarged figures(the right figures of Figure 9) that there are no steady-stateerrors for roll pitch and yaw rates The relative satisfieddynamic performance is achieved In fact a result with muchmore satisfied dynamic performance can be obtained but itwill make the desired control torques much larger duringthe initial period This will not only excite the vibration ofthe structure but also increase the burden of the controlactuators
And the differences between the dynamics models withand without the geometrical nonlinearity can also be seenmerely in the phase of the angular velocities
The desired attitude control torques are presented inFigure 10 The roll torque will tend to be zero with thedecrement of the state variable errors The pitch and yawtorques tend to be constant from the middle and bottom
figures The pitch and yaw steady-state errors can never beeliminated although the pitch and yaw torques (009Nlowastmand minus009Nlowastm) are applied continuously by theoreticalanalysis and simulations This is just a great disadvantage ofthe LQR based controller in this paper The initial controltorques can be afforded by vibrating the gimbaled controlboom andmoving the slidingmasses that can afford a relativelarge torque The control vanes can be used to afford thecontrol torques when solar sail is in steady-state process Theexpression of the attitude control inputs 119906
120593 119906
120579 and 119906
120595can be
found in previous sectionMoreover the differences between dynamics responses
with and without geometrical nonlinearity can also beobserved by comparing the corresponding results Therequired torques for the attitude control are a little largerfor the dynamics with geometrical nonlinearity And thedifference in the phase is also clear
It can be seen that the vibration of the supporting beamis depressed effectively by the simulation results in Figure 11It can be seen that the steady-state errors and the dynamicperformance are relatively satisfied It can also be seen that thedynamics responses between the model with and without the
Mathematical Problems in Engineering 19
0 1000 2000 3000 4000 5000
0 1000 2000 3000 4000 5000
minus01
0
01
minus02
0
02
Time (s) Time (s)
Time (s) Time (s)
minus5
0
5
times10minus4
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
minus1
0
1
times10minus3
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
The d
ispla
cem
ent o
f the
tip
(m)
The d
ispla
cem
ent o
f the
tip
(m)
The v
eloci
ty o
f the
tip
(ms
)
The v
eloc
ity o
f the
tip
(ms
)
Figure 11 The displacement and velocity of the tip of the supporting beam
geometrical nonlinearity effect are different in the vibrationdisplacement and velocitymagnitudes and phases (Figure 15)
The simulation results can be obtained as follows by usingthe optimal PI based controller adopting the abovementionedparameters and initial conditions
The roll pitch and yaw errors are given by using theoptimal PI based controller These errors tend to disappearby observing the partially enlarged plotting of the figure (thecorresponding right figures) (shown in Figure 12) And therelative satisfied dynamic performance can also be obtainedFrom the view of eliminating the steady-state errors the opti-mal PI based controller performs better than the LQR basedcontroller by theoretical analysis and simulation results Theformer can achieve attitude control results without pitchand yaw steady-state errors From the view of dynamicperformance both the controllers perform well In additionit can be seen that the difference between the modelswith and without geometrical nonlinearity is merely inthe phase
The roll pitch and yaw rate errors are presented inFigure 13 The dynamic and steady-state performances aresatisfied by observing the simulation results And by observ-ing the difference between the dynamics responses with and
without the influence by the geometrical nonlinearity it canbe concluded that the merely difference is the phase
The desired control torques of the roll pitch and yaw areobtained in Figure 14 by using the optimal PI based controllerIt can be seen that the value of the desired roll control torquedecreases to zero as the values of the roll angle and ratedecrease to zero The desired pitch and yaw control torquestend to be the constant values 009Nlowastm and minus009Nlowastmrespectively The desired initial control torques are large byobserving Figure 14 It is suggested that the gimbaled controlboom combining the sliding masses is adopted to afford theinitial torque Then the control vanes can be used to controlthe solar sail after the initial phase The phase differencecan also be observed by inspecting the dynamics responsesduring the 4800sim5000 s period
The vibration can be controlled effectively based on theoptimal PI controller And the relative satisfied dynamicand steady-state performances can be achieved In additionthe tiny differences exist in the magnitudes of the requiredtorques And the phase differences also exist
It can be concluded as follows by analyzing and compar-ing the simulation results based on the LQR and optimal PItheories in detail
20 Mathematical Problems in Engineering
Roll
erro
r120593(∘
)
Roll
erro
r120593(∘
)
minus5
0
5
minus5
0
5
Pitc
h er
ror120579
(∘)
Pitc
h er
ror120579
(∘)
0 1000 2000 3000 4000 5000minus10
0
10
Time (s) Time (s)
Time (s)
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
Yaw
erro
r120595(∘
)
Yaw
erro
r120595(∘
)
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
minus1
0
1
times10minus3
minus1
0
1
times10minus3
minus1
0
1
times10minus3
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Figure 12 The roll pitch and yaw errors
(1) From the view of eliminating the steady-state errorsof the pitch and yaw errors the optimal PI based con-troller performs better than the LQR based controllerby theoretical analysis and simulation results Thedynamic performances of the two controllers are bothsatisfied and the desired control torques are relativelysmall
(2) The weighting of the state variables is reflected by theweighting matrix according to the LQR and optimalPI theories The constant weighting matrices selectedin this paper can effectively reflect the initial statevariable errors but maybe reflect the final state vari-able errors deficiently The time-varying weightingmatrices should be selected
(3) For the actual orbiting solar sail the control actuators(control vanes gimbaled control boom and slidingmasses) cannot afford excessive large control torquesThus the control torques should be as small as possibleon the premise of acquiring satisfied dynamic perfor-mance and steady-state errors It will not only reducethe burden of the control actuators but also avoid
exciting structural vibration In engineering practicethe weighting matrices and the control weightingmatrices should be selected based on the attitudecontrol requirement (eg dynamic performance andsteady-state errors etc)
(4) The dynamics responses influenced by the geometri-cal nonlinearity can be observed In a word the tinydifferences between the magnitudes of the physicalvariables exist for the models with and withoutthe geometrical nonlinearity And the relative cleardifferences exist in the phases for the attitude anglesrates required torques and so forth
6 Conclusions
The coupled attitude and structural dynamics is establishedfor the highly flexible sailcraft by using the von-Karman von-Karmanrsquos nonlinear strain-displacement relationships basedon assumptions of large deflections moderate rotationsand
Mathematical Problems in Engineering 21
Roll
rate
erro
r(∘ s
)
Roll
rate
erro
r(∘ s
)
minus01
0
01
minus01
0
01
Pitc
h ra
te er
ror (
∘ s)
Pitc
h ra
te er
ror (
∘ s)
0 1000 2000 3000 4000 5000minus02
0
02
Yaw
rate
erro
r (∘ s
)
Yaw
rate
erro
r (∘ s
)
4800 4850 4900 4950 5000
minus5
0
5times10minus4
minus5
0
5
times10minus4
minus5
0
5times10minus4
Time (s)
4800 4850 4900 4950 5000
Time (s)
4800 4850 4900 4950 5000
Time (s)
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Figure 13 The roll pitch and yaw rate errors
small strains The Lagrange equation method is utilizedto derive the dynamics for controller design and dynamicsimulation The LQR and optimal PI based controllers aredesigned for the dynamics with the constant disturbancetorque caused by the cmcp offset By theoretical analysisand simulation it can be seen that both controllers cancompromise between the state variables and control inputsBecause the control actuators can hardly afford large controltorque the dynamic performance should be relaxed toreduce the requirement for the attitude control actuatorsBesides the optimal PI based controller can also eliminatethe constant disturbance torque caused by the cmcp offsetthat always exists while the LQR based controller fails toachieve the results with satisfied steady-state performancealthough the attitude control torque is always applied to thecoupled dynamic systemThe dynamics simulations with andwithout the geometrical nonlinearity effect are also carriedout And the differences between the models in magnitudesand phases are identified and analyzed It can be concludedthat the optimal PI based controller performs better than the
LQRbased controller from the viewof eliminating the steady-state error caused by the disturbance torque by the cmcpoffset
Appendix
The related parameters in above equation are given as
119886120593= 119869
119909+ 119898
ℎ11199102
ℎ1
+ 119898ℎ21199112
ℎ2
+ 1198981199011199032
119901119911
+ 1198981199011199032
119901119910
119886120579= minus 119898
119901119903119901119909119903119901119910 119886
120595= minus119898
119901119903119901119909119903119901119911
1198861198811
= minus 1198981198971198972
1198861198812
= minus4
5119898
1198971198972
119887120579= 119869
119910+ 119898
ℎ21199112
ℎ2
+ 1198981199011199032
119901119911
+ 1198981199011199032
119901119909
119887120595= minus 119898
119901119903119901119910119903119901119911 119887
120593= minus119898
119901119903119901119909119903119901119910
22 Mathematical Problems in Engineering
Roll
torq
ue (N
lowastm
)
Roll
torq
ue (N
lowastm
)
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
0 2000 4000 6000
0 2000 4000 6000
0 2000 4000 6000
Time (s)
Time (s)
Time (s)
Time (s)
Time (s)
Time (s)4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
minus01
minus008
008
009
01
minus002
0
002
minus5
0
5
minus2
0
2
Pitc
h to
rque
(Nlowast
m)
Pitc
h to
rque
(Nlowast
m)
minus2
0
2
Yaw
torq
ue (N
lowastm
)
Yaw
torq
ue (N
lowastm
)
Figure 14 The roll pitch and yaw torques
1198871198811
=1
2119898
1198971198972
1198871198812
=2
5119898
1198971198972
119888120595= 119869
119911+ 119898
ℎ11199102
ℎ1
+ 1198981199011199032
119901119910
+ 1198981199011199032
119901119909
119888120579= minus 119898
119901119903119901119910119903119901119911 119888
120593= minus119898
119901119903119901119909119903119901119911
1198881198811
= minus1
21198972
119898119897 119888
1198812
= minus2
51198972
119898119897
119889
1198811
= (4
3
119868119863
119897+
1
5119897119868119860) 119889
1198812
= (1
6119897119868119860+
3119868119863
2119897)
119889
1198811
=4120578
119887119863
119909119909
1198973 119889
1198812
=6120578
119887119863
119909119909
1198973
1198891198811
=4119863
119909119909
1198973 119889
1198812
=6119863
119909119909
1198973
1198761198811
= 1198651198621
(119905)
119890
1198811
= (3
2
119868119863
119897+
1
6119897119868119860)
119890
1198812
= (1
7119897119868119860+
9
5
119868119863
119897) 119890
1198811
=6120578
119887119863
119909119909
1198973
119890
1198812
=12120578
119887119863
119909119909
1198973 119890
1198811
=6119863
119909119909
1198973
1198901198812
=12119863
119909119909
1198973 119876
1198812
= 1198651198622
(119905)
(A1)
The detailed expressions of control inputs for attitudevibration and related parameters in the state-space model ofthe dynamics (see (62) and (63)) are presented as follows
A =
[[[[[[[[[[[[[[
[
0 1 0 0 0 0 0 0 0 0
0 0 0 0 0 0 1198861
1198862
1198863
1198864
0 0 0 1 0 0 0 0 0 0
0 0 0 0 0 0 1198865
1198866
1198867
1198868
0 0 0 0 0 1 0 0 0 0
0 0 0 0 0 0 1198869
11988610
11988611
11988612
0 0 0 0 0 0 0 1 0 0
0 0 0 0 0 0 11988613
11988614
11988615
11988616
0 0 0 0 0 0 0 0 0 1
0 0 0 0 0 0 11988617
11988618
11988619
11988620
]]]]]]]]]]]]]]
]
Mathematical Problems in Engineering 23
0 1000 2000 3000 4000 5000
0 1000 2000 3000 4000 5000
minus01
0
01
minus02
0
02
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Time (s)
Time (s)Time (s)
Time (s)
minus1
0
1
minus1
0
1
times10minus3
times10minus3Th
e disp
lace
men
t of t
he ti
p (m
)
The d
ispla
cem
ent o
f the
tip
(m)
The v
eloci
ty o
f the
tip
(ms
)
The v
eloci
ty o
f the
tip
(ms
)
Figure 15 Vibration displacement and velocity of the tip
B =
[[[[[[[[[[[[[[
[
0 0 0 0 0
1 0 0 0 0
0 0 0 0 0
0 1 0 0 0
0 0 0 0 0
0 0 1 0 0
0 0 0 0 0
0 0 0 1 0
0 0 0 0 0
0 0 0 0 1
]]]]]]]]]]]]]]
]
1198861= minus
1198981198971198972
119869119909
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus4
5119869119909
1198981198971198972
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198862= minus
1198981198971198972
119869119909
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus4
5119869119909
1198981198971198972
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198863= minus
1198981198971198972
119869119909
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus4
5119869119909
1198981198971198972
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198864= minus
1198981198971198972
119869119909
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus4
5119869119909
1198981198971198972
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
119906120593=
119876120593
119869119909
+
119906
119869119909
+119898
1198971198972
119869119909
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+4
5119869119909
1198981198971198972
+
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198865=
1
2119869119910
1198981198971198972
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+2
5119869119910
1198981198971198972
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198866=
1
2119869119910
1198981198971198972
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+2
5119869119910
1198981198971198972
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198867=
1
2119869119910
1198981198971198972
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+2
5119869119910
1198981198971198972
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198868=
1
2119869119910
1198981198971198972
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
24 Mathematical Problems in Engineering
+2
5119869119910
1198981198971198972
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
119906120579=
119876120579
119869119910
+119906
120579
119869119910
minus1
2119869119910
1198981198971198972
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119910
1198981198971198972
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198869= minus
1
2119869119911
1198972
119898119897
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988610
= minus1
2119869119911
1198972
119898119897
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988611
= minus1
2119869119911
1198972
119898119897
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988612
= minus1
2119869119911
1198972
119898119897
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
119906120595=
119876120595
119869119911
+
119906
119869119911
+1
2119869119911
1198972
119898119897
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+2
5119869119911
1198972
119898119897
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988613
= minus
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988614
= minus
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988615
= minus
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988616
= minus
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
1199061198811
=
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988617
= minus
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988618
= minus
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988619
= minus
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988620
= minus
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1199061198812
=
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(A2)
Conflict of Interests
The authors declare that there is no conflict of interestsregarding the publication of this paper
Acknowledgments
The authors would like to thank the anonymous reviewers fortheir critical and constructive review of the paper This studywas cosupported by the National Natural Science Foundationof China (Project no 11302134 11272101)
References
[1] M Colin Solar Sailing Technology Dynamics and MissionApplications Springer-Praxis London UK 1st edition 1999
[2] V Lappas SWokesM Leipold A Lyngvi and P Falkner ldquoGui-dance and control for an Interstellar Heliopause Probe (IHP)solar sail mission to 200 AUrdquo in Proceedings of the AIAAGuidance Navigation and Control Conference and Exhibit pp2472ndash2492 San Francisco Calif USA August 2005
[3] L Charlotte C Camilla and C McInnes ldquoSolar radiation pres-sure augmented deorbiting fromhigh altitude sun-synchronousorbitsrdquo in Proceedings of the 4S Symposium 2012 Small SatellitesSystems and Services Portoroz Slovenia 2012
[4] M Ceriotti and C RMcInnes ldquoGeneration of optimal trajecto-ries for Earth hybrid pole sittersrdquo Journal of Guidance Controland Dynamics vol 34 no 3 pp 847ndash859 2011
[5] S Gong J Li andH Baoyin ldquoSolar sail transfer trajectory fromL1 point to sub-L1 pointrdquoAerospace Science and Technology vol15 no 7 pp 544ndash554 2011
[6] S Gong J Li and H Baoyin ldquoAnalysis of displaced solar sailorbits with passive controlrdquo Journal of Guidance Control andDynamics vol 31 no 3 pp 782ndash785 2008
[7] S Gong H Baoyin and J Li ldquoSolar sail three-body transfertrajectory designrdquo Journal of Guidance Control and Dynamicsvol 33 no 3 pp 873ndash886 2010
Mathematical Problems in Engineering 25
[8] S Gong J Li H Baoyin and J Simo ldquoA new solar sail orbitrdquoScience China Technological Sciences vol 55 no 3 pp 848ndash8552012
[9] Y Tsuda O Mori R Funase et al ldquoAchievement of IKAROS-Japanese deep space solar sail demonstration missionrdquo ActaAstronautica vol 82 no 2 pp 183ndash188 2013
[10] L Johnson MWhorton A Heaton R Pinson G Laue and CAdams ldquoNanoSail-D a solar sail demonstration missionrdquo ActaAstronautica vol 68 no 5-6 pp 571ndash575 2011
[11] B Wie and D Murphy ldquoSolar-sail attitude control design for asail flight validation missionrdquo Journal of Spacecraft and Rocketsvol 44 no 4 pp 809ndash821 2007
[12] B Wie D Murphy M Paluszek and S Thomas ldquoRobust atti-tude control systems design for solar sails part 1 propellantlessprimaryACSrdquo inProceedings of the AIAAGuidance Navigationand Control Conference and Exhibit Providence RI USAAugust 2004
[13] B Wie D Murphy M Paluszek and S Thomas ldquoRobust atti-tude control systems design for solar sails part 2 MicroPPT-based secondary ACSrdquo in Proceedings of the AIAA GuidanceNavigation and Control Conference and Exhibit pp 1325ndash1340Providence RI USA August 2004
[14] S Thomas M Paluszek B Wie and D Murphy ldquoAOCS per-formance and stability validation for large flexible solar sailspacecraftrdquo in Proceedings of the 41st AIAAASMESAEASEEJoint Propulsion Conference amp Exhibit Tucson Ariz USA 2005
[15] B Wie ldquoDynamic modeling and attitude control of solar sailspacecraft part Irdquo in Proceedings of the AIAAGuidance Naviga-tion and Control Conference and Exhibit Monterey Calif USAAugust 2002
[16] BWie ldquoSolar sail attitude control and dynamics part 1rdquo Journalof Guidance Control and Dynamics vol 27 no 4 pp 526ndash5352004
[17] B Wie ldquoDynamic modeling and attitude control of solar sailspacecraft part IIrdquo in Proceedings of the AIAA Guidance Nav-igation and Control Conference and Exhibit Monterey CalifUSA August 2002
[18] BWie ldquoSolar sail attitude control and dynamics part 2rdquo Journalof Guidance Control and Dynamics vol 27 no 4 pp 536ndash5442004
[19] C Luo and J-H Zheng ldquoSolar-sail attitude control based onmoving masses and roll stabilizer barsrdquo Journal of HarbinInstitute of Technology vol 43 no 3 pp 95ndash101 2011
[20] D Romagnoli and T Oehlschlagel ldquoHigh performance twodegrees of freedom attitude control for solar sailsrdquo Advances inSpace Research vol 48 no 11 pp 1869ndash1879 2011
[21] C Scholz D Romagnoli B Dachwald and S Theil ldquoPerfor-mance analysis of an attitude control system for solar sails usingsliding massesrdquo Advances in Space Research vol 48 no 11 pp1822ndash1835 2011
[22] A Bolle and C Circi ldquoSolar sail attitude control through in-plane moving massesrdquo Journal of Aerospace Engineering vol222 no 1 pp 81ndash94 2008
[23] M RotunnoM Basso A B Pome andM Sallusti ldquoA compari-son of robust attitude control techniques for a solar sail space-craftrdquo in Proceedings of the AIAA Guidance Navigation andControl Conference and Exhibit San Francisco Calif USA2005
[24] J Zhang K Zhai and T Wang ldquoControl of large angle maneu-vers for the flexible solar sailrdquo Science China Physics Mechanicsand Astronomy vol 54 no 4 pp 770ndash776 2011
[25] J Zhang andTWang ldquoCoupled attitude-orbit control of flexiblesolar sail for displaced solar orbitrdquo Journal of Spacecraft andRockets vol 50 no 3 pp 675ndash685 2013
[26] Q Li XMa and TWang ldquoReducedmodel for flexible solar saildynamicsrdquo Journal of Spacecraft and Rockets vol 48 no 3 pp446ndash453 2011
[27] M Polites J Kalmanson and D Mangus ldquoSolar sail attitudecontrol using small reaction wheels and magnetic torquersrdquoProceedings of the Institution of Mechanical Engineers G Journalof Aerospace Engineering vol 222 no 1 pp 53ndash62 2008
[28] H-T Cui J-H Luo J-H Feng and P-Y Cui ldquoAttitudecontrol of solar sail spacecraft with control boomrdquo Journal ofAstronautics vol 29 no 2 pp 560ndash566 2008
[29] E Mettler and S R Ploen ldquoSolar sail dynamics and controlusing a boom mounted bus articulated by a bi-state two-axisgimbal and reaction wheelsrdquo in Proceedings of the AIAAAASAstrodynamics Specialist Conference and Exhibit MontereyCalif USA August 2002
[30] J Luo X Li and J Feng ldquoPassive attitude control of solar sailspacecraftrdquo Flight Dynamics vol 26 no 5 pp 47ndash50 2008
[31] J Luo Study on attitude control of solar sail spaceraft [PhDthesis] School of Astronautics Harbin Institute of TechnologyHarbin China 2007
[32] D A Lawrence and S W Piggott ldquoIntegrated trajectory andattitude control for a four-vane solar sailrdquo in Proceedings ofthe AIAA Guidance Navigation and Control Conference andExhibit pp 2416ndash2431 San Francisco Calif USA August 2005
[33] E Mettler A B Acikmese and S R Ploen ldquoAttitude dynamicsand control of solar sails with articulated vanesrdquo in Proceedingsof the AIAA Guidance Navigation and Control Conference andExhibit pp 2396ndash2415 San Francisco Calif USA August 2005
[34] S N Adeli V J Lappas and B Wie ldquoA scalable bus-basedattitude control system for Solar Sailsrdquo Advances in SpaceResearch vol 48 no 11 pp 1836ndash1847 2011
[35] R Funase Y Shirasawa Y Mimasu et al ldquoOn-orbit verificationof fuel-free attitude control system for spinning solar sailutilizing solar radiation pressurerdquo Advances in Space Researchvol 48 no 11 pp 1740ndash1746 2011
[36] B Fu and F O Eke ldquoAttitude control methodology for largesolar sailsrdquo in AIAA Guidance Navigation and Control (GNC)Conference 2013
[37] J Liu N Cui F Shen and S Rong ldquoDynamics of highly-flexiblesolar sail subjected to various forcesrdquoActaAstronautica vol 103pp 55ndash72 2014
[38] J F Liu S Y Rong and J G Li ldquoAttitude dynamics modelingand control of large flexible solar sail spacecraftrdquo in Proceedingsof the 3rd International Symposium on Systems and Control inAeronautics and Astronautics (ISSCAA rsquo10) pp 243ndash247 IEEEPublications Piscataway NJ USA 2010
[39] S Gong H Baoyin and J Li ldquoCoupled attitude-orbit dynamicsand control for displaced solar orbitsrdquo Acta Astronautica vol65 no 5-6 pp 730ndash737 2009
Submit your manuscripts athttpwwwhindawicom
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
MathematicsJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Mathematical Problems in Engineering
Hindawi Publishing Corporationhttpwwwhindawicom
Differential EquationsInternational Journal of
Volume 2014
Applied MathematicsJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Probability and StatisticsHindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Journal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Mathematical PhysicsAdvances in
Complex AnalysisJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
OptimizationJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
CombinatoricsHindawi Publishing Corporationhttpwwwhindawicom Volume 2014
International Journal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Operations ResearchAdvances in
Journal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Function Spaces
Abstract and Applied AnalysisHindawi Publishing Corporationhttpwwwhindawicom Volume 2014
International Journal of Mathematics and Mathematical Sciences
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
The Scientific World JournalHindawi Publishing Corporation httpwwwhindawicom Volume 2014
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Algebra
Discrete Dynamics in Nature and Society
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Decision SciencesAdvances in
Discrete MathematicsJournal of
Hindawi Publishing Corporationhttpwwwhindawicom
Volume 2014 Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Stochastic AnalysisInternational Journal of
Mathematical Problems in Engineering 7
26 The Generalized Forces The components of the sunlightunit vector S can be obtained as follows by referring toFigure 3 (left) in 120587
119868
S = j119868= [1 0 0]
119879
119868
(22)
Based on the abovementioned equations the componentsof S in 120587
119887can be obtained as
S = C119887119868[1 0 0]
119879
119868
= [119878119909
119878119910
119878119911]119879
119887
(23)
The resultant SRP force can be simply modeled as followsfor a perfectly reflective control vane
F119894= 120578119875119860
119862119894(S sdot n
119862119894)2 n
119862119894= 119865
119862119894cos2120572
119862119894n119862119894 (24)
where 120578 is the overall sail-thrust coefficient (120578max = 2) 119875 =
4563 times 10minus6 Nm2 119860
119862119894is the area of the 119894th control vane
119865119862119894
= 120578119875119860119862119894is themaximumcontrol vane thrust andn
119862119894= i
119894
is the unit normal vector of the control vaneThe componentsof n
119862119894in 120587
119887can be written as
n119862119894
= C119887119894[1 0 0]
119879
119894
= [119878119909119894
119878119910119894
119878119911119894]119879
119887
(25)
The control torque by the 119894th control vane can beexpressed as
M119894= L
119894times F
119894 (26)
In fact L119894and F
119894are dependent on the deformations of
the supporting beams and control vanes In this paper it isassumed thatL
119894andF
119894are not influenced by the deformations
of the structure when computing the control torque by thecontrol vanes Thus L
119894and F
119894can be expressed as
L1= [0 0 minus119897]
119879
L2= [0 119897 0]
119879
L3= [0 0 119897]
119879
L4= [0 minus119897 0]
119879
F119894= 120578119875119860
119862119894([119878
119909119878119910
119878119911]119887
sdot [119878119909119894
119878119910119894
119878119911119894]119879
119887
)
2
[119878119909119894
119878119910119894
119878119911119894]119879
119887
(27)
The force of each control vane can be written as
F119894= (119865
119862119894cos2120572
119862119894)C
119887119894[1 0 0]
119879
119894
= (119865119862119894cos2120572
119862119894) [119878
119909119894119878119910119894
119878119911119894]119879
119887
(28)
where 120572119862119894
is the sun angle of the 119894th control vane that canbe measured by the sun sensor And the components of thecontrol torques can be obtained as
M1198881
= (1198651198621cos2120572
1198621)[
[
0
0
minus119897
]
]
times (C1198871
[
[
1
0
0
]
]
)
= (1198651198621cos2120572
1198621)
times [
[
minus119897 cos1205931sin120595
1
minus119897 (cos 1205791cos120595
1minus sin 120579
1sin120593
1sin120595
1)
0
]
]
M1198882
= (1198651198622cos2120572
1198622)
times [
[
119897 (sin 1205792cos120595
2+ cos 120579
2sin120593
2sin120595
2)
0
minus119897 (cos 1205792cos120595
2minus sin 120579
2sin120593
2sin120595
2)
]
]
M1198883
= (1198651198623cos2120572
1198623)
times [
[
119897 cos1205933sin120595
3
119897 (cos 1205793cos120595
3minus sin 120579
3sin120593
3sin120595
3)
0
]
]
M1198884
= (1198651198624cos2120572
1198624)
times [
[
minus119897 (sin 1205794cos120595
4+ cos 120579
4sin120593
4sin120595
4)
0
119897 (cos 1205794cos120595
4minus sin 120579
4sin120593
4sin120595
4)
]
]
(29)
27 Attitude Dynamics of Solar Sail The attitude dynamicscan be obtained by using the Lagrange equation method as
119889
119889119905(
120597119871
120597 119902119895
) minus120597119871
120597119902119895
= 119876119895 (30)
where 119871 is the Lagrange function 119902119895(119895 = 1ndash3) is the vector
of the generalized coordinates and 119876119895is the vector of the
generalized force 119871 can be computed as
119871 = 119879 minus 119880 =
4
sum
119894=1
119879119898119894
+ 119879119901+
2
sum
119895=1
119879ℎ119895
minus (119880119892119891
+ 119880119892119901
+
2
sum
119895=1
119880119892ℎ119895
)
(31)
where 119879119898119894 119879
119901 and 119879
ℎ119895are the kinetic energies of the
supporting beams payload and sliding masses respectively119880119892119891 119880
119892119901 and 119880
119892ℎ119895are the gravitational potential energies of
the sail system payload and sliding masses respectively
8 Mathematical Problems in Engineering
OOx
y
z
FCFCy
FCx
FCz
mh
q(x)
Figure 5 The vibration model
120590
120590e
120590120592
120590
Figure 6 The viscoelastic model
3 The Vibration of Solar Sail
The mechanical and material models of the sailcraft aregivenThe displacement filed stress and strain are presentedbased on the Euler beam assumptionThe Lagrange equationmethod is adopted to derive the vibration equations withlarge deformations based on the calculations of kineticenergies and works done by the external loads
31 The Mechanical Model The body frame O119874xyz is estab-
lished to describe the vibration (see Figure 5) F119862is the force
vector generated by the control vane used located at the tip ofthe supporting beam 119865
119862119909 119865
119862119910 and 119865
119862119911are the components
inO119874xyz 119902(119909) is the distributed load caused by SRP
32 The Material Model The carbon fibre enforced compos-ite material is used to construct the inflatable deploymentsupporting beam The model of the viscoelastic material canbe represented in Figure 6
The total stress is the summation of the elastic and viscousstresses It can be expressed as
120590 = 120590119890
+ 120590120592
= 119864120576 + 119888119887
120576 (32)
where 120590 120590119890 and 120590
120592 are the total elastic and viscous stressrespectively And 119864 is Youngrsquos modulus 120576 ( 120576) is the strain(strain rate) and 119888
119887is the coefficient of the internal damping
expressed as 119864120578119887 120578
119887is the proportionality constant of the
internal damping The dimensions of 119888119887and 120578
119887are N lowast sm2
and s respectively
OO x
y The support beam
Z
Figure 7 The schematic diagram of solar sail supporting beamdeformation
33 The Displacement Field Stress and Strain The deforma-tion of a spatial solar sail supporting beam is presented inFigure 7
The spatial displacement fields for supporting beam are as
119906 (119909 119910 119911 119905) = 1199060(119909 119905) minus 119910
120597V0
120597119909minus 119911
1205971199080
120597119909
V (119909 119910 119911 119905) = V0(119909 119905)
119908 (119909 119910 119911 119905) = 1199080(119909 119905)
(33)
119906(119909 119910 119911 119905) V(119909 119910 119911 119905) and 119908(119909 119910 119911 119905) are the displace-ments along 119909 119910 and 119911 directions respectively 119906
0(119909 119905)
V0(119909 119905) and 119908
0(119909 119905) are the axial and transverse displace-
ments of an arbitrary point on the neutral axisBy using Green strain definition von Karmanrsquos nonlinear
strain-displacement relationships based on assumptions oflarge deflections moderate rotations and small strains for a3D supporting beam are given as follows together with thestrain rate and normal stress
120576119909119909
=120597119906
0
120597119909+1
2(120597V
0
120597119909)
2
minus 1199101205972V
0
1205971199092
+1
2(120597119908
0
120597119909)
2
minus 1199111205972
1199080
1205971199092
120576119909119909
=120597
0
120597119909+(
120597V0
120597119909)(
120597V0
120597119909) minus 119910
1205972V
0
1205971199092
+(120597119908
0
120597119909)(
1205970
120597119909)
minus 1199111205972
0
1205971199092
120590119909119909
= 119864[120597119906
0
120597119909+1
2(120597V
0
120597119909)
2
minus 1199101205972V
0
1205971199092
+1
2(120597119908
0
120597119909)
2
minus 1199111205972
1199080
1205971199092
]
+ 119864120578119887(120597
0
120597119909+(
120597V0
120597119909)(
120597V0
120597119909) minus 119910
1205972V
0
1205971199092
+(120597119908
0
120597119909)(
1205970
120597119909) minus 119911
1205972
0
1205971199092
)
(34)
Mathematical Problems in Engineering 9
The single underlined terms in the preceding equationindicate the contribution by the geometrical nonlinearityThedynamics models and corresponding numerical simulationwithout considering the geometrical nonlinearity can beobtained and carried out by neglecting these terms
34 The Energies and Works Done by External Forces Thestrain energy can be derived as
119880119894=
1
2int
119897
0
119860119909119909
[120597119906
0
120597119909+
1
2(120597V
0
120597119909)
2
+1
2(120597119908
0
120597119909)
2
]
2
+ 119863119909119909
1205972V
0
1205971199092
+ 119863119909119909
1205972
1199080
1205971199092
119889119909
(35)
For an isotropic support beam the extensional stiffness119860
119909119909and bending stiffness119863
119909119909can be computed as
119860119909119909
= int119860
119864119889119860 119863119909119909
= int119860
1198641199112
119889119860 = int119860
1198641199102
119889119860 (36)
The dissipation function is as
Ψ119902=
1
2int
119897
0
[119860119909119909120578119887(120597
0
120597119909)
2
+ 119863119909119909120578119887(1205972V
0
1205971199092
)
2
+ 119863119909119909120578119887(1205972
0
1205971199092
)
2
]119889119909
(37)
The kinetic energy for the support beam is as
119879119890=
1
2int
119897
0
[119868119860(120597119906
0
120597119905)
2
+ 119868119860(120597119908
0
120597119905)
2
+ 119868119863(1205972
1199080
120597119909120597119905)
2
+ 119868119860(120597V
0
120597119905)
2
+ 119868119863(
1205972V
0
120597119909120597119905)
2
]119889119909
(38)
where 119868119860and 119868
119863are integration constant for the support
beam expressed as
119868119860= int
119860
120588119889119860 = 120588119860 119868119863= int
119860
1205881199112
119889119860 = int119860
1205881199102
119889119860 (39)
And the work done by the external force can be obtainedas119882 = 119865
119862119911sdot 119908 (119909
119888 119905) + 119865
119862119910sdot V (119909
119888 119905) + 119898
ℎ119886ℎ119910
(119909ℎ 119905) V (119909
ℎ 119905)
+ 119898ℎ119886ℎ119911
(119909ℎ 119905) 119908 (119909
ℎ 119905) + int
119897
0
119902 (119909) V (119909 119905) 119889119909
(40)where 119909
119888represents the position of the support beam
119908(119909119888 119905) V(119909
119888 119905) are the displacements along 119911 and 119910 direc-
tions respectively and the corresponding loads 119865119862119911 119865
119862119910are
known functions 119909ℎ 119897 and V
ℎare the position coordinate of
the sliding mass the length of the support beam and theconstant-velocity of the sliding mass The dynamic responseis studied only during the period [0 119897V
ℎ] 119898
ℎis the mass
and 119886ℎ119910(119909
ℎ 119905) and 119886
ℎ119911(119909
ℎ 119905) are the components of the
acceleration for a material point on the support beam theslidingmass just arrived at And the corresponding transversedeflections are 119908(119909
ℎ 119905) and V(119909
ℎ 119905) respectively
35 The Assumed Modes Method The axial displacement1199060(119909 119905) and the transverse deflections V
0(119909 119905) and119908
0(119909 119905) can
be represented as follows by considering the assumed modesmethod
1199060(119909 119905) =
infin
sum
119894=1
119880119894(119909)119880
119894(119905)
V0(119909 119905) =
infin
sum
119895=1
119881119895(119909) 119881
119895(119905)
1199080(119909 119905) =
infin
sum
119896=1
119882119896(119909)119882
119896(119905)
(41)
where 119880119894(119905) 119881
119895(119905) and 119882
119896(119905) are the time-dependent gen-
eralized coordinates and 119880119894(119909) 119881
119895(119909) and 119882
119896(119909) are the
assumedmodes For assumedmodemethod themode shapefunctions should satisfy the following requirements in thispaper
119880119894(119909)
1003816100381610038161003816119909=0= 0 119881
119895(119909)
10038161003816100381610038161003816119909=0= 0 119882
119896(119909)
1003816100381610038161003816119909=0= 0
1198811015840
119895
(119909)10038161003816100381610038161003816119909=0
= 0 1198821015840
119896
(119909)10038161003816100381610038161003816119909=0
= 0
(42)
The following first two assumed modes satisfying theassumed mode principle are used in this paper
1198801(119909) =
119909
119897 119880
2(119909) = (
119909
119897)
2
1198811(119909) = (
119909
119897)
2
1198812(119909) = (
119909
119897)
3
1198821(119909) = (
119909
119897)
2
1198822(119909) = (
119909
119897)
3
(43)
With the help of the assumedmodes the detailed expres-sions of 119880
119894 119879
119890119882
119911 and Ψ
119902can be obtained as
119880119894=
9
2
119860119909119909
1198973(119881
2
2
+ 1198822
2
)2
+27
4
119860119909119909
1198973(119881
11198812+ 119882
1119882
2)
times (1198812
2
+ 1198822
2
)
+18
7
119860119909119909
1198973[(119881
2
1
+ 1198822
1
) (1198812
2
+ 1198822
2
) + (11988111198812+ 119882
1119882
2)2
]
+119860
119909119909
1198973[3
2119897119880
2(119881
2
2
+ 1198822
2
) + (1198812
1
+ 1198822
1
)
times (11988111198812+ 119882
1119882
2)]
10 Mathematical Problems in Engineering
+1
10
119860119909119909
1198973[9119880
1119897 (119881
2
2
+ 1198822
2
) + 241198802119897 (119881
11198812+ 119882
1119882
2)
+ 4 (1198812
1
+ 1198822
1
)2
]
+119860
119909119909
1198972[3
21198801(119881
11198812+ 119882
1119882
2) + 119880
2(119881
2
1
+ 1198822
1
)]
+6119863
119909119909119881
2
2
1198973+ 119860
119909119909(2119880
1119881
2
1
31198972+
21198801119882
2
1
31198972+
21198802
2
3119897)
+6119863
119909119909119882
2
2
1198973+
611986311990911990911988111198812
1198973+
11986011990911990911988011198802
119897+
6119863119909119909119882
1119882
2
1198973
+119860
119909119909119880
2
1
2119897+
2119863119909119909119881
2
1
1198973+
2119863119909119909119882
2
1
1198973
119879119890=
1
14(119897119868
119860
2
2
+ 119897119868119860
2
2
) +1
6(119897119868
119860
1
2+ 119897119868
11986012)
+1
10(119897119868
119860
2
2
+ 119897119868119860
2
1
+9119868
119863
2
2
119897+ 119897119868
119860
2
1
+9119868
119863
2
2
119897)
+1
4(119897119868
11986012+
6119868119863
1
2
119897+
611986811986312
119897)
+1
6(119897119868
119860
2
1
+4119868
119863
2
1
119897+
4119868119863
2
1
119897)
119882119911= 119865
119862119911sdot [119882
1(119905) + 119882
2(119905)] + 119865
119862119910sdot [119881
1(119905) + 119881
2(119905)]
+ 119898ℎ[2V2
ℎ
1198972sdot 119881
1(119905) +
4V2ℎ
119905
1198972sdot
1(119905) + (
Vℎ119905
119897)
2
sdot 1(119905)
+6V3
ℎ
119905
1198973sdot 119881
2(119905) +
6V3ℎ
1199052
1198973
sdot 2(119905) + (
Vℎ119905
119897)
3
sdot 2(119905)]
times [(Vℎ119905
119897)
2
sdot 1198811(119905) + (
Vℎ119905
119897)
3
sdot 1198812(119905)]
+ 119898ℎ[2V2
ℎ
1198972sdot 119882
1(119905) +
4V2ℎ
119905
1198972sdot
1(119905) + (
Vℎ119905
119897)
2
sdot 1(119905)
+6V3
ℎ
119905
1198973sdot 119882
2(119905) +
6V3ℎ
1199052
1198973sdot
2(119905)
+ (Vℎ119905
119897)
3
sdot 2(119905)]
times [(Vℎ119905
119897)
2
sdot 1198821(119905) + (
Vℎ119905
119897)
3
sdot 1198822(119905)]
+ 1198811(119905) sdot int
119897
0
119902 (119909) (119909
119897)
2
119889119909 + 1198812(119905)
sdot int
119897
0
119902 (119909) (119909
119897)
3
119889119909
Ψ119902=
1
6(36119863
119909119909120578119887
2
2
1198976+
4119860119909119909120578119887
2
2
1198974+
36119863119909119909120578119887
2
2
1198976) 119897
3
+1
4(4119860
11990911990912057811988712
1198973+
2411986311990911990912057811988712
1198975
+24119863
119909119909120578119887
1
2
1198975) 119897
2
+1
2
119860119909119909120578119887
2
1
119897+
2119863119909119909120578119887
2
1
1198973+
2119863119909119909120578119887
2
1
1198973
(44)
36 The Vibration Equation The Lagrange equation methodis used to derive the vibration equations
120597119871
120597119902119899
minus119889
119889119905(
120597119871
120597 119902119899
) + 119876119889= 0 119899 = 1 2 6 (45)
where 119871 is the Lagrange function 119902119899
= (1198801 119880
2 119881
1 119881
2
1198821119882
2)119879 is the vector of the generalized coordinates and
119902119899is the corresponding generalized velocity vector 119876
119889is the
generalized damping force The expressions for 119871 and 119876119889are
as
119871 = 119879119890minus (119880
119894minus 119882
119911)
119876119889= minus
120597Ψ119902
120597 119902119899
(119899 = 1 sim 6)
(46)
The axial vibration equations can be obtained as followsfor 119880
1 119880
2
1
31198971198681198601+
1
41198971198681198602+
120578119887119860
1199091199091
119897+
120578119887119860
1199091199092
119897+
1198601199091199091198801
119897
+119860
1199091199091198802
119897+
2119860119909119909119881
2
1
31198972+
311986011990911990911988111198812
21198972+
9119860119909119909119881
2
2
101198972
+2119860
119909119909119882
2
1
31198972+
3119860119909119909119882
1119882
2
21198972+
9119860119909119909119882
2
2
101198972= 0
(47a)
1
41198971198681198601+
1
51198971198681198602+
120578119887119860
1199091199091
119897+
4120578119887119860
1199091199092
3119897
+119860
1199091199091198801
119897+4119860
1199091199091198802
3119897+119860
119909119909119881
2
1
1198972+12119860
11990911990911988111198812
51198972+3119860
119909119909119881
2
2
21198972
+119860
119909119909119882
2
1
1198972+
12119860119909119909119882
1119882
2
51198972+
3119860119909119909119882
2
2
21198972= 0
(47b)
The following can be seen from the above equations
(1) Since the assumed modes rather than the naturalmodes are used the coupling between axial and trans-verse vibrations is rather severe for axial vibrations
Mathematical Problems in Engineering 11
(2) The nonlinearity is apparent in above equations onlyexisting in the terms of 119881
1 119881
2119882
1119882
2 We take (47a)
as an exampleThe terms including1198802and its first and
second derivative 1198811 119881
2119882
1119882
2 can be regarded as
the applied loads for 1198801
(3) The coupling between the axial and transverse vibra-tionswill disappear as long as the linear displacement-strain relationship is adopted
(4) There are no external loads for axial vibrationsaccording to above equations
The transverse vibration equations for 1198811 119881
2and119882
1 119882
2
can be obtained as
4
3
1198681198631
119897+
1
51198971198681198601+
1
61198971198681198602minus
119898ℎV5ℎ
1199055
2
1198975+
31198681198632
2119897
+4119898
ℎV4ℎ
1199053
1
1198974+
4120578119887119863
1199091199091
1198973minus
2119898ℎV5ℎ
1199054
2
1198975+
6120578119887119863
1199091199092
1198973
+8119898
ℎV4ℎ
1199052
1198811
1198974+
41198631199091199091198811
1198973+
8119898ℎV5ℎ
1199053
1198812
1198975+
61198631199091199091198812
1198973
+27119860
1199091199091198812119882
2
2
81198973+
541198601199091199091198811119881
2
2
71198973+
181198601199091199091198811119882
2
2
71198973
+6119860
119909119909119881
2
1
1198812
1198973+
21198601199091199091198812119882
2
1
1198973+
1211986011990911990911988021198812
51198972
+8119860
1199091199091198811119882
2
1
51198973+
311986011990911990911988011198812
21198972+
211986011990911990911988021198811
1198972
+8119860
119909119909119881
3
1
51198973+
27119860119909119909119881
3
2
81198973+
361198601199091199091198812119882
1119882
2
71198973
+4119860
1199091199091198811119882
1119882
2
1198973+
411986011990911990911988011198811
31198972minus 119865
119888119910(119905) minus 05119865
025119865= 0
1
61198971198681198601+
3
2
1198681198631
119897minus
119898ℎV5ℎ
1199055
1
1198975+
1
71198971198681198602+
9
5
1198681198632
119897
+6120578
119887119863
1199091199091
1198973+
2119898ℎV5ℎ
1199054
1
1198975+
12120578119887119863
1199091199092
1198973+
6119898ℎV6ℎ
1199055
2
1198976
+6119863
1199091199091198811
1198973+
16119898ℎV5ℎ
1199053
1198811
1198975+
121198631199091199091198812
1198973+
18119898ℎV6ℎ
1199054
1198812
1198976
+9119860
1199091199091198812119882
2
2
21198973+
811198601199091199091198811119881
2
2
81198973+
311986011990911990911988011198811
21198972
+27119860
1199091199091198811119882
2
2
81198973+
541198601199091199091198812119881
2
1
71198973+
181198601199091199091198812119882
2
1
71198973
+3119860
11990911990911988021198812
1198972+
21198601199091199091198811119882
2
1
1198973+
911986011990911990911988011198812
51198972+
1211986011990911990911988021198811
51198972
+9119860
119909119909119881
3
2
21198973+
2119860119909119909119881
3
1
1198973+
271198601199091199091198812119882
1119882
2
41198973
+36119860
1199091199091198811119882
1119882
2
71198973minus 04119865
025119865minus 119865
119888119910(119905) = 0
4
3
119868119863
1
119897+
1
5119897119868119860
1+
3
2
119868119863
2
119897+
1
6119897119868119860
2minus
119898ℎV5ℎ
1199055
2
1198975
+4120578
119887119863
119909119909
1
1198973+
4119898ℎV4ℎ
1199053
1
1198974minus
2119898ℎV5ℎ
1199054
2
1198975+
6120578119887119863
119909119909
2
1198973
+4119863
119909119909119882
1
1198973+
8119898ℎV4ℎ
1199052
1198821
1198974+
8119898ℎV5ℎ
1199053
1198822
1198975+
6119863119909119909119882
2
1198973
+36119860
119909119909119882
211988111198812
71198973+
4119860119909119909119882
111988111198812
1198973+
27119860119909119909119882
2119881
2
2
81198973
+18119860
119909119909119882
1119881
2
2
71198973+
54119860119909119909119882
1119882
2
2
71198973+
6119860119909119909119882
2
1
1198822
1198973
+2119860
119909119909119882
2119881
2
1
1198973+
121198601199091199091198802119882
2
51198972+
8119860119909119909119882
1119881
2
1
51198973
+3119860
1199091199091198801119882
2
21198972+
21198601199091199091198802119882
1
1198972+
27119860119909119909119882
3
2
81198973
+8119860
119909119909119882
3
1
51198973+
41198601199091199091198801119882
1
31198972minus 119865
119888119911(119905) = 0
1
7119897119868119860
2+
9
5
119868119863
2
119897+
1
6119897119868119860
1minus
119898ℎV5ℎ
1199055
1
1198975+
3
2
119868119863
1
119897
+6120578
119887119863
119909119909
1
1198973+
2119898ℎV5ℎ
1199054
1
1198975+
6119898ℎV6ℎ
1199055
2
1198976
+12120578
119887119863
119909119909
2
1198973+
6119863119909119909119882
1
1198973+
16119898ℎV5ℎ
1199053
1198821
1198975
+12119863
119909119909119882
2
1198973+
18119898ℎV6ℎ
1199054
1198822
1198976+
31198601199091199091198801119882
1
21198972
+27119860
119909119909119882
211988111198812
41198973+
36119860119909119909119882
111988111198812
71198973+
9119860119909119909119882
2119881
2
2
21198973
+27119860
119909119909119882
1119881
2
2
81198973+
81119860119909119909119882
1119882
2
2
81198973+
18119860119909119909119882
2119881
2
1
71198973
+54119860
119909119909119882
2119882
2
1
71198973+
31198601199091199091198802119882
2
1198972+
2119860119909119909119882
1119881
2
1
1198973
+9119860
1199091199091198801119882
2
51198972+
121198601199091199091198802119882
1
51198972+
2119860119909119909119882
3
1
1198973
+9119860
119909119909119882
3
2
21198973minus 119865
119888119911(119905) = 0
(48)
The complexity high coupling and nonlinearity are obvi-ous in above equations
4 The Coupled Rigid-Flexible Dynamics
The dynamics for control and dynamic simulation shouldbe presented for solar sail based on the simplification ofequations derived in previous sections Some assumptions aremade before simplifying the equations as follows
12 Mathematical Problems in Engineering
(1) Only the attitude motion is affected by the slidingmass the vibration of solar sail structure is notaffected by the sliding mass
(2) Although the attitude control is accomplished byrotating control vanes and the gimbaled controlboom moving sliding masses the specific time his-tories of the actuators are not considered here
(3) The four supporting beams are regarded as an entirestructure thus the identical generalized coordinatesare adopted in the dynamic analysis
41 The Simplified Attitude Dynamics The kinetic energy ofsolar sail supporting beams can be obtained as
119879119898
=1
2120596 sdot J sdot 120596 + 119898
119897int
119897
0
2∘
1205883
sdot (120596 times r3) + (120596 times 120588
3) sdot (120596 times 120588
3)
+ 2 (120596 times r3) sdot (120596 times 120588
3) 119889119911
+ 119898119897int
119897
0
2∘
1205882
sdot (120596 times r2) + (120596 times 120588
2) sdot (120596 times 120588
2)
+ 2 (120596 times r2) sdot (120596 times 120588
2) 119889119910
(49)
The subscripts 2 and 3 represent the second and thirdsupporting beams The displacements can be expressed as
V0119909
(119911 119905) = (119911
119897)
2
sdot 1198811(119905) + (
119911
119897)
3
sdot 1198812(119905)
1199080119910
(119911 119905) = 120572V0119909
(119911 119905) = (119911
119897)
2
sdot 1205721198811(119905) + (
119911
119897)
3
sdot 1205721198812(119905)
for the 3rd beam
V0119909
(119910 119905) = 120573V0119909
(119911 119905) = (119910
119897)
2
sdot 1205731198811(119905) + (
119910
119897)
3
sdot 1205731198812(119905)
1199080119911
(119910 119905) = 120574V0119909
(119910 119905) = (119910
119897)
2
sdot 1205741198811(119905) + (
119910
119897)
3
sdot 1205741198812(119905)
for the 2nd beam
(50)
The subscripts 119909 119910 and 119911 of the left terms in (50)represent the displacements along119909119910 and 119911directions119881
1(119905)
and 1198812(119905) are the generalized coordinates The displacements
1199080119910(119911 119905) V
0119909(119910 119905) and 119908
0119911(119910 119905) can be obtained using the
assumed modes as
1205883= V
0119909(119911 119905) i
119887+ 119908
0119910(119911 119905) j
119887
=
[[[[[
[
(119911
119897)
2
sdot 1198811(119905) + (
119911
119897)
3
sdot 1198812(119905)
120572 [(119911
119897)
2
sdot 1198811(119905) + (
119911
119897)
3
sdot 1198812(119905)]
0
]]]]]
]
1205882= V
0119909(119910 119905) i
119887+ 119908
0119911(119910 119905) k
119887
=
[[[[[
[
120573[(119910
119897)
2
sdot 1198811(119905) + (
119910
119897)
3
sdot 1198812(119905)]
0
120574 [(119910
119897)
2
sdot 1198811(119905) + (
119910
119897)
3
sdot 1198812(119905)]
]]]]]
]
(51)
The vibration velocity can be obtained as
∘
1205883
= 1205883119909i119887+ 120588
3119910j119887=
[[[[[
[
(119911
119897)
2
sdot 1(119905) + (
119911
119897)
3
sdot 2(119905)
1205721[(
119911
119897)
2
sdot 1(119905) + (
119911
119897)
3
sdot 2(119905)]
0
]]]]]
]
∘
1205882
= 1205882119909i119887+ 120588
2119911k119887=
[[[[[
[
1205731[(
119910
119897)
2
sdot 1(119905) + (
119910
119897)
3
sdot 2(119905)]
0
1205741[(
119910
119897)
2
sdot 1(119905) + (
119910
119897)
3
sdot 2(119905)]
]]]]]
]
(52)
Without loss of generality 120572 = 120573 = 1205721= 120573
1= 1 and
120574 = 1205741= minus1 can be assumed in above expressions And the
kinetic energy of the slidingmasses can be obtained as followsby neglecting the vibration related terms
119879ℎ=
1
2119898
ℎ1(120596 times r
ℎ1) sdot (120596 times r
ℎ1) +
1
2119898
ℎ2(120596 times r
ℎ2)
sdot (120596 times rℎ2)
(53)
The kinetic energy of the payload can be obtained as
119879119901=
1
2119898
119901(120596 times r
119901) sdot (120596 times r
119901) (54)
The following simplified attitude dynamics can beobtained by neglecting the second and higher terms ofattitude angles and vibration modes in computing the kinetic
Mathematical Problems in Engineering 13
energies of the supporting beams payload and slidingmasses Consider
119869119909 minus 119898
1198971198972
1minus
4
5119898
1198971198972
2+ 119898
ℎ11199102
ℎ1
+ 119898ℎ21199112
ℎ2
minus 119898119901119903119901119909119903119901119911 + 119898
1199011199032
119901119911
+ 1198981199011199032
119901119910
minus 119898119901119903119901119909119903119901119910
120579 = 119876120593
119869119910
120579 +2
5119898
1198971198972
2+
1
2119898
1198971198972
1+ 119898
ℎ21199112
ℎ2
120579
+ 1198981199011199032
119901119911
120579 minus 119898119901119903119901119910119903119901119911 minus 119898
119901119903119901119909119903119901119910
+ 1198981199011199032
119901119909
120579 = 119876120579
119869119911 minus
2
51198972
1198981198972minus
1
21198972
1198981198971+ 119898
ℎ11199102
ℎ1
minus 119898119901119903119901119910119903119901119911
120579 + 1198981199011199032
119901119910
+ 1198981199011199032
119901119909
minus 119898119901119903119901119909119903119901119911 = 119876
120595
(55)
where 119876120593 119876
120579 and 119876
120595are the generalized nonpotential
attitude control torques generated by the control vanes Andthe attitude control torques generated by the gimbaled controlboom and sliding masses can be found on the left side ofthe above equation coupled with 120579 making the attitudecontroller design problem rather difficult
42 The Simplified Vibration Equations The couplingbetween the axial and transverse vibrations is neglectedand only the transverse vibration is considered The attitudedynamics for dynamic simulation can be obtained as followsbased on previous derivation by neglecting the action ofsolar-radiation pressure
4
3
1198681198631
119897+
1
51198971198681198601+
1
61198971198681198602+
31198681198632
2119897+
4120578119887119863
1199091199091
1198973
+6120578
119887119863
1199091199092
1198973+
41198631199091199091198811
1198973+
61198631199091199091198812
1198973+
271198601199091199091198812119882
2
2
81198973
+54119860
1199091199091198811119881
2
2
71198973+
181198601199091199091198811119882
2
2
71198973+
6119860119909119909119881
2
1
1198812
1198973
+2119860
1199091199091198812119882
2
1
1198973+
81198601199091199091198811119882
2
1
51198973+
8119860119909119909119881
3
1
51198973
+27119860
119909119909119881
3
2
81198973+
361198601199091199091198812119882
1119882
2
71198973+
41198601199091199091198811119882
1119882
2
1198973
minus 1198651198621
(119905) = 0
1
61198971198681198601+
3
2
1198681198631
119897+
1
71198971198681198602+
9
5
1198681198632
119897+
6120578119887119863
1199091199091
1198973
+12120578
119887119863
1199091199092
1198973+
61198631199091199091198811
1198973+
121198631199091199091198812
1198973+
91198601199091199091198812119882
2
2
21198973
+81119860
1199091199091198811119881
2
2
81198973+
271198601199091199091198811119882
2
2
81198973+
541198601199091199091198812119881
2
1
71198973
+18119860
1199091199091198812119882
2
1
71198973+
21198601199091199091198811119882
2
1
1198973+
9119860119909119909119881
3
2
21198973
+2119860
119909119909119881
3
1
1198973+
271198601199091199091198812119882
1119882
2
41198973+
361198601199091199091198811119882
1119882
2
71198973
minus 1198651198622
(119905) = 0
(56)
The following equations can be obtained by rearrangingthe above equations
4
3
1198681198631
119897+
1
51198971198681198601+
1
61198971198681198602+
31198681198632
2119897+
4120578119887119863
1199091199091
1198973
+6120578
119887119863
1199091199092
1198973+
41198631199091199091198811
1198973+
61198631199091199091198812
1198973+
16119860119909119909119881
3
1
51198973
+12119860
119909119909119881
2
1
1198812
1198973+
1081198601199091199091198811119881
2
2
71198973+
54119860119909119909119881
3
2
81198973
minus 1198651198621
(119905) = 0
1
61198971198681198601+
3
2
1198681198631
119897+
1
71198971198681198602+
9
5
1198681198632
119897+
6120578119887119863
1199091199091
1198973
+12120578
119887119863
1199091199092
1198973+
61198631199091199091198811
1198973+
121198631199091199091198812
1198973
+4119860
119909119909119881
3
1
1198973+
108119860119909119909119881
2
1
1198812
71198973+
811198601199091199091198811119881
2
2
41198973
+9119860
119909119909119881
3
2
1198973minus 119865
1198622(119905) = 0
(57)
1198651198621(119905) and 119865
1198622(119905) are used to represent all the generalized
external forces they can be used for vibration control Thesecomplicated equations abovementioned are the basis forobtaining the simplified equations used for controller design
The following equations can be obtained by neglecting thetwo and higher terms
4
3
1198681198631
119897+
1
51198971198681198601+
1
61198971198681198602+
31198681198632
2119897+
4120578119887119863
1199091199091
1198973
+6120578
119887119863
1199091199092
1198973+
41198631199091199091198811
1198973+
61198631199091199091198812
1198973= 119865
1198621
(119905)
14 Mathematical Problems in Engineering
1
61198971198681198601+
3
2
1198681198631
119897+
1
71198971198681198602+
9
5
1198681198632
119897+
6120578119887119863
1199091199091
1198973
+12120578
119887119863
1199091199092
1198973+
61198631199091199091198811
1198973+
121198631199091199091198812
1198973= 119865
1198622
(119905)
(58)
43 The Rigid-Flexible Coupled Dynamics The simplifiedattitude and vibration dynamics can be written as
119886120593 + 119886
120579
120579 + 119886120595 + 119886
1198811
1+ 119886
1198812
2= 119876
120593
119887120579
120579 + 119887120595 + 119887
120593 + 119887
1198811
1+ 119887
1198812
2= 119876
120579
119888120595 + 119888
120579
120579 + 119888120593 + 119888
1198811
1+ 119888
1198812
2= 119876
120595
119889
1198811
1+ 119889
1198812
2+ 119889
1198811
1+ 119889
1198812
2+ 119889
1198811
1198811
+ 1198891198812
1198812= 119876
1198811
119890
1198811
1+ 119890
1198812
2+ 119890
1198811
1+ 119890
1198812
2+ 119890
1198811
1198811
+ 1198901198812
1198812= 119876
1198812
(59)
The related coefficients in the preceding equation can befound in (A1) in the appendix The dynamics (see (59)) isnot suitable for attitude controller design because the controlinputs exist in some coefficients of the angular accelerationsThis will make the controller design rather difficult Thusthe following dynamic model is obtained by putting theterms including the control inputs right side of the dynamicequations
119869119909 minus 119898
1198971198972
1minus
4
5119898
1198971198972
2= 119876
120593+ 119906
119869119910
120579 +2
5119898
1198971198972
2+
1
2119898
1198971198972
1= 119876
120579+ 119906
120579
119869119911 minus
1
21198972
1198981198971minus
2
51198972
1198981198972= 119876
120595+ 119906
119889
1198811
1+ 119889
1198812
2+ 119889
1198811
1+ 119889
1198812
2
+ 1198891198811
1198811+ 119889
1198812
1198812= 119876
1198811
119890
1198811
1+ 119890
1198812
2+ 119890
1198811
1+ 119890
1198812
2
+ 1198901198811
1198811+ 119890
1198812
1198812= 119876
1198812
(60)
The expressions for 119906 119906
120579
and 119906are as
119906= minus119898
ℎ11199102
ℎ1
minus 119898ℎ21199112
ℎ2
+ 119898119901119903119901119909119903119901119911 minus 119898
1199011199032
119901119911
minus 1198981199011199032
119901119910
+ 119898119901119903119901119909119903119901119910
120579
119906
120579
= minus119898ℎ21199112
ℎ2
120579 minus 1198981199011199032
119901119911
120579 + 119898119901119903119901119910119903119901119911 + 119898
119901119903119901119909119903119901119910
minus 1198981199011199032
119901119909
120579
119906= minus119898
ℎ11199102
ℎ1
+ 119898119901119903119901119910119903119901119911
120579 minus 1198981199011199032
119901119910
minus 1198981199011199032
119901119909
+ 119898119901119903119901119909119903119901119911
(61)
119906 119906
120579
and 119906are the functions of the positions of sliding
masses and payload and the angular accelerations The statevariables in (60) are defined as
1199091= 120593 119909
2= 119909
3= 120579 119909
4= 120579
1199095= 120595 119909
6= 119909
7= 119881
1
1199098=
1 119909
9= 119881
2 119909
10=
2
(62)
Thedynamics (60) can bewritten as the state-spacemodelas following
1= 119909
2
2= 119886
11199097+ 119886
21199098+ 119886
31199099+ 119886
411990910
+ 119906120593
3= 119909
4
4= 119886
51199097+ 119886
61199098+ 119886
71199099+ 119886
811990910
+ 119906120579
5= 119909
6
6= 119886
91199097+ 119886
101199098+ 119886
111199099+ 119886
1211990910
+ 119906120595
7= 119909
8
8= 119886
131199097+ 119886
141199098+ 119886
151199099+ 119886
1611990910
+ 1199061198811
9= 119909
10
10
= 119886171199097+ 119886
181199098+ 119886
191199099+ 119886
2011990910
+ 1199061198812
(63)
where 119906120579 119906
120593 and 119906
120595are the generalized control inputs
for attitude control and 1199061198811
and 1199061198812
are the generalizedcontrol inputs for vibration control The controllability canbe satisfied by analyzing (63) The attitudevibration controlinputs and the coefficients will be presented later in thissection The form of a matrix differential equation can bewritten as follows for the above equation
x = Ax + Bu (64)
The expressions of the relatedmatrices and vectors can befound as
x = [1
2
3
4
5
6
7
8
9
10]119879 x (119905
0) = x
1199050
u = [119906120593 119906
120579 119906
120595 119906
1198811
1199061198812
]119879
u (1199050) is known
(65)
where A xB and u are the system matrix state variablesvector control matrix and control inputs vector respectively
Mathematical Problems in Engineering 15
The complexity of the state-space model can be seen bypresenting the detailed expressions of control inputs forattitudevibration and related parameters in (A2) in theappendix
5 AttitudeVibration Control and Simulation
The controller for the attitude and vibration is developedusing the LQR and optimal PI theory The dynamic simula-tion is performed based on the coupled dynamics derived inthe previous sections
51 LQR and Optimal PI Based Controllers Design Thedynamics for solar sail can bewritten as follows togetherwithits quadratic cost function also defined as
x = Ax + Bu x (1199050) = x
1199050
(known)
119869 =1
2int
infin
1199050
[x119879 (119905)Qx (119905) + u119879 (119905)Ru (119905)] 119889119905
(66)
whereQ = Q119879
⩾ 0 andR = R119879
gt 0 are constantThe control-lability of [AB] and the observability of [AD] can beensured when the equationDD119879
= Q holds for anymatrixDThe optimal control input ulowast(119905)within the scope of u(119905) isin R119903119905 isin [119905
0infin] can be computed as follows to make 119869minimum
ulowast (119905) = minusKxlowast (119905) K = Rminus1B119879P (67)
where P is the nonnegative definite symmetric solution of thefollowing Riccati algebraic equations
PA + A119879P minus PBRminus1B119879P +Q = 0 (68)
And the optimal performance index can be obtained asfollows for arbitrary initial states
119869lowast
[x (1199050) 119905
0] =
1
2x1198790
Px0 (69)
The closed-loop system
x = (A minus BRminus1B119879P) x (70)
is asymptotically stableFor an orbiting solar sail the primary disturbance torque
is by the cmcp offset and the impact of the tiny dust inthe deep space The state regulator can be used to controlthe dynamic system affected by pulse disturbance torquewith good steady-state errors but will never achieve accuratesteady-state errors if the dynamics is affected by constantdisturbance torque Thus the optimal state regulator withan integrator to eliminate the constant disturbance torqueshould be presented This optimal proportional-integral reg-ulator not only eliminates the constant disturbance torque butalso possesses the property of optimal regulator
Table 1 The related parameters
Parameters ValuesCMCP offsetm [0 017678 017678]119879
The side length of square sailm 100Nominal solar-radiation pressureconstant at 1 AU from the sunNm2 4563 times 10minus6
Solar-radiation pressure forceN 912 times 10minus2
Roll inertiakglowastm2 50383Pitch and yaw inertiakglowastm2 251915Outer radiusm 0229Thickness of the supporting beamm 75 times 10minus6
Youngrsquos modulus of the supportingbeamGPa 124
Moment of inertia of the cross-sectionof the supporting beamm4 2829412 times 10minus7
Bending stiffness of the supportingbeamNlowastm2 3508471336
Proportional damping coefficient ofsupporting beams 001
Line density of the supportingbeamkgm 0106879
Cross-sectional area of the supportingbeamm2 1079 times 10minus5
Roll disturbance torqueNlowastm 0Pitch (yaw) disturbance torqueNlowastm 0016122 (minus0016122)
For the following linear system with the correspondingperformance index
x = Ax + Bu x (1199050) = x
1199050
u (1199050) = u
1199050
119869 =1
2int
infin
1199050
(x119879Qx + u119879Ru + u119879Su) 119889119905(71)
where Q = Q119879
⩾ 0 R = R119879
gt 0 and S = S119879 gt 0 If [AB]is completely controllable and meanwhile [AD
11] is com-
pletely observable with the relationship D11D119879
11
= Q thesolution can be expressed as
ulowast = minusK1x minus K
2ulowast ulowast (119905
0) = u
1199050
(72)
If B119879B is full rank we can get
ulowast = minusK3x minus K
4x ulowast (119905
0) = u
1199050
(73)
K119894(119894 = 1 2 3 4) is the function of ABQR S
The closed-loop system
[xulowast] = [
A BminusK
1minusK
2
] [xulowast] [
[
x (1199050)
u (1199050)]
]
= [x1199050
u1199050
] (74)
is asymptotically stableThe compromise between the state variables (the angle
angular velocity the vibration displacement and velocity)and control inputs (the torque by all the actuators) can
16 Mathematical Problems in Engineering
0 2000 4000 6000
0 2000 4000 6000
0 2000 4000 6000minus5
0
5
minus5
0
5
minus5
0
5
minus4
minus2
0
2
4
times10minus4
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
00162
00164
00166
4800 4900 5000
4800 4900 5000
4800 4900 5000
minus00165
minus0016
Time (s) Time (s)
Time (s)
Time (s)
Time (s)
Time (s)
Roll
erro
r120593(∘
)
Roll
erro
r120593(∘
)
Pitc
h er
ror120579
(∘)
Pitc
h er
ror120579
(∘)
Yaw
erro
r120595(∘
)
Yaw
erro
r120595(∘
)
Figure 8 The roll pitch and yaw errors
be achieved by using both the LQR based and optimal PIbased controllers for the coupled attitudevibration dynamicsystem The fact is that the attitude control ability is limitedto the control torque by the control actuators The change ofthe attitude angles and rates should not be frequent to voidexciting vibrations
Thus the weighting matrix Q and the control weightingmatrix R are selected as follows for LQR based controller
Q (1 1) = 9 times 10minus6
Q (2 2) = 1 times 10minus6
Q (3 3) = 16 times 10minus6
Q (4 4) = Q (5 5) = Q (6 6) = Q (7 7) = Q (8 8)
= Q (9 9) = Q (10 10) = 1 times 10minus6
Q (119894 119895) = 0 (119894 = 119895 119894 119895 = 1 sim 10)
R (1 1) = R (2 2) = 900 R (3 3) = 100
R (4 4) = R (5 5) = 10000
R119894119895
= 0 (119894 = 119895 119894 119895 = 1 sim 5)
(75)
TheweightingmatrixQ and the control weightingmatrixR are selected as follows for the optimal PI based controller
Q (1 1) = Q (2 2) = 4 times 10minus8
Q (3 3) = Q (4 4) = Q (5 5) = Q (6 6) = Q (7 7)
= Q (8 8) = 16 times 10minus8
Mathematical Problems in Engineering 17
minus02
0
02
Roll
rate
(∘s)
Roll
rate
(∘s)
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Pitc
h ra
te(∘s)
Pitc
h ra
te(∘s)
0 1000 2000 3000 4000 5000
minus05
0
05
minus05
0
05
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
Time (s)
Yaw
rate
(∘
s)
Yaw
rate
(∘
s)
4800 4850 4900 4950 5000
Time (s)4800 4850 4900 4950 5000
Time (s)4800 4850 4900 4950 5000
minus2
0
2
minus2
0
2
minus2
0
2
times10minus4
times10minus4
times10minus4
Figure 9 The roll pitch and yaw rates
Q (9 9) = Q (10 10) = 1 times 10minus8
Q (119894 119895) = 0 (119894 = 119895 119894 119895 = 1 sim 10)
R (1 1) = R (2 2) = R (3 3) = 1 times 10minus8
R (4 4) = R (5 5) = 4 times 10minus8
R (119894 119895) = 0 (119894 = 119895 119894 119895 = 1 sim 5)
(76)
52 The Simulation Results The initial angle errors of rollpitch and yaw are adopted as 120593(119905
0) = 3
∘ 120579(1199050) = 3
∘ and120595(119905
0) = 3
∘ the initial angular velocity errors of roll pitchand yaw are adopted as (119905
0) = 0
∘
s 120579(1199050) = 0
∘
s and(119905
0) = 0
∘
s 1198811(1199050) = 01m 119881
2(1199050) = 01m
1(1199050) = 0ms
and 2(1199050) = 0ms are adopted in this paper for dynamic
simulationThe estimated cmcp offset is 025m for a 100 times 100m
square solar sail It is assumed that the components of cmcpoffset vector are [0 017678 017678]
119879 in the body frame
The relevant parameters for dynamic simulations are givenin Table 1
The dynamic simulation results are obtained as followsby using the LQR controller based on the abovementionedQ and R related parameters and initial conditions Thedynamics simulations with (denoted by ldquowith GFrdquo) andwithout (denoted by ldquowithout GFrdquo) considering the geo-metrical nonlinearity are presented And the correspondingdiscussions and analysis are also given according to thecalculated results
The roll pitch and yaw errors are presented based onthe dynamics models with and without considering thegeometrical nonlinearityThe control effect with zero steady-state error can be achieved for roll axis by referring tothe results But the steady-state errors exist for pitch andyaw axes from Figure 8 this is because there exist constantdisturbance torques for pitch and yaw axes caused by thecmcp offset Thus the LQR based controller cannot be usedfor attitude control with good steady-state performance Thesteady-state errors of pitch and yaw axes are about 0164
∘
and minus0164∘ respectively from the corresponding partial
enlarged drawing of the figures (see the corresponding left
18 Mathematical Problems in Engineering
minus20
0
20
Roll
torq
ue (N
lowastm
)
Roll
torq
ue (N
lowastm
)
minus50
0
50
minus50
0
50
Pitc
h to
rque
(Nlowast
m)
Pitc
h to
rque
(Nlowast
m)
0 1000 2000 3000 4000 5000
0 2000 4000 6000
0 2000 4000 6000
Yaw
torq
ue (N
lowastm
)
Yaw
torq
ue (N
lowastm
)
minus002
0
002
008
01
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
minus01
minus009
minus008
Time (s)Time (s)
Time (s)Time (s)
Time (s)Time (s)
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Figure 10 The roll pitch and yaw torques
figures) A simple and practical controller should be designedto eliminate the steady-state errorsThese errorswill affect theprecision of the super long duration space mission deeply
The differences between the dynamics with and withoutthe geometrical nonlinearity effect can be observed Theamplitudes and phases change a bit by comparing the corre-sponding results
It can be observed by the partial enlarged figures(the right figures of Figure 9) that there are no steady-stateerrors for roll pitch and yaw rates The relative satisfieddynamic performance is achieved In fact a result with muchmore satisfied dynamic performance can be obtained but itwill make the desired control torques much larger duringthe initial period This will not only excite the vibration ofthe structure but also increase the burden of the controlactuators
And the differences between the dynamics models withand without the geometrical nonlinearity can also be seenmerely in the phase of the angular velocities
The desired attitude control torques are presented inFigure 10 The roll torque will tend to be zero with thedecrement of the state variable errors The pitch and yawtorques tend to be constant from the middle and bottom
figures The pitch and yaw steady-state errors can never beeliminated although the pitch and yaw torques (009Nlowastmand minus009Nlowastm) are applied continuously by theoreticalanalysis and simulations This is just a great disadvantage ofthe LQR based controller in this paper The initial controltorques can be afforded by vibrating the gimbaled controlboom andmoving the slidingmasses that can afford a relativelarge torque The control vanes can be used to afford thecontrol torques when solar sail is in steady-state process Theexpression of the attitude control inputs 119906
120593 119906
120579 and 119906
120595can be
found in previous sectionMoreover the differences between dynamics responses
with and without geometrical nonlinearity can also beobserved by comparing the corresponding results Therequired torques for the attitude control are a little largerfor the dynamics with geometrical nonlinearity And thedifference in the phase is also clear
It can be seen that the vibration of the supporting beamis depressed effectively by the simulation results in Figure 11It can be seen that the steady-state errors and the dynamicperformance are relatively satisfied It can also be seen that thedynamics responses between the model with and without the
Mathematical Problems in Engineering 19
0 1000 2000 3000 4000 5000
0 1000 2000 3000 4000 5000
minus01
0
01
minus02
0
02
Time (s) Time (s)
Time (s) Time (s)
minus5
0
5
times10minus4
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
minus1
0
1
times10minus3
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
The d
ispla
cem
ent o
f the
tip
(m)
The d
ispla
cem
ent o
f the
tip
(m)
The v
eloci
ty o
f the
tip
(ms
)
The v
eloc
ity o
f the
tip
(ms
)
Figure 11 The displacement and velocity of the tip of the supporting beam
geometrical nonlinearity effect are different in the vibrationdisplacement and velocitymagnitudes and phases (Figure 15)
The simulation results can be obtained as follows by usingthe optimal PI based controller adopting the abovementionedparameters and initial conditions
The roll pitch and yaw errors are given by using theoptimal PI based controller These errors tend to disappearby observing the partially enlarged plotting of the figure (thecorresponding right figures) (shown in Figure 12) And therelative satisfied dynamic performance can also be obtainedFrom the view of eliminating the steady-state errors the opti-mal PI based controller performs better than the LQR basedcontroller by theoretical analysis and simulation results Theformer can achieve attitude control results without pitchand yaw steady-state errors From the view of dynamicperformance both the controllers perform well In additionit can be seen that the difference between the modelswith and without geometrical nonlinearity is merely inthe phase
The roll pitch and yaw rate errors are presented inFigure 13 The dynamic and steady-state performances aresatisfied by observing the simulation results And by observ-ing the difference between the dynamics responses with and
without the influence by the geometrical nonlinearity it canbe concluded that the merely difference is the phase
The desired control torques of the roll pitch and yaw areobtained in Figure 14 by using the optimal PI based controllerIt can be seen that the value of the desired roll control torquedecreases to zero as the values of the roll angle and ratedecrease to zero The desired pitch and yaw control torquestend to be the constant values 009Nlowastm and minus009Nlowastmrespectively The desired initial control torques are large byobserving Figure 14 It is suggested that the gimbaled controlboom combining the sliding masses is adopted to afford theinitial torque Then the control vanes can be used to controlthe solar sail after the initial phase The phase differencecan also be observed by inspecting the dynamics responsesduring the 4800sim5000 s period
The vibration can be controlled effectively based on theoptimal PI controller And the relative satisfied dynamicand steady-state performances can be achieved In additionthe tiny differences exist in the magnitudes of the requiredtorques And the phase differences also exist
It can be concluded as follows by analyzing and compar-ing the simulation results based on the LQR and optimal PItheories in detail
20 Mathematical Problems in Engineering
Roll
erro
r120593(∘
)
Roll
erro
r120593(∘
)
minus5
0
5
minus5
0
5
Pitc
h er
ror120579
(∘)
Pitc
h er
ror120579
(∘)
0 1000 2000 3000 4000 5000minus10
0
10
Time (s) Time (s)
Time (s)
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
Yaw
erro
r120595(∘
)
Yaw
erro
r120595(∘
)
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
minus1
0
1
times10minus3
minus1
0
1
times10minus3
minus1
0
1
times10minus3
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Figure 12 The roll pitch and yaw errors
(1) From the view of eliminating the steady-state errorsof the pitch and yaw errors the optimal PI based con-troller performs better than the LQR based controllerby theoretical analysis and simulation results Thedynamic performances of the two controllers are bothsatisfied and the desired control torques are relativelysmall
(2) The weighting of the state variables is reflected by theweighting matrix according to the LQR and optimalPI theories The constant weighting matrices selectedin this paper can effectively reflect the initial statevariable errors but maybe reflect the final state vari-able errors deficiently The time-varying weightingmatrices should be selected
(3) For the actual orbiting solar sail the control actuators(control vanes gimbaled control boom and slidingmasses) cannot afford excessive large control torquesThus the control torques should be as small as possibleon the premise of acquiring satisfied dynamic perfor-mance and steady-state errors It will not only reducethe burden of the control actuators but also avoid
exciting structural vibration In engineering practicethe weighting matrices and the control weightingmatrices should be selected based on the attitudecontrol requirement (eg dynamic performance andsteady-state errors etc)
(4) The dynamics responses influenced by the geometri-cal nonlinearity can be observed In a word the tinydifferences between the magnitudes of the physicalvariables exist for the models with and withoutthe geometrical nonlinearity And the relative cleardifferences exist in the phases for the attitude anglesrates required torques and so forth
6 Conclusions
The coupled attitude and structural dynamics is establishedfor the highly flexible sailcraft by using the von-Karman von-Karmanrsquos nonlinear strain-displacement relationships basedon assumptions of large deflections moderate rotationsand
Mathematical Problems in Engineering 21
Roll
rate
erro
r(∘ s
)
Roll
rate
erro
r(∘ s
)
minus01
0
01
minus01
0
01
Pitc
h ra
te er
ror (
∘ s)
Pitc
h ra
te er
ror (
∘ s)
0 1000 2000 3000 4000 5000minus02
0
02
Yaw
rate
erro
r (∘ s
)
Yaw
rate
erro
r (∘ s
)
4800 4850 4900 4950 5000
minus5
0
5times10minus4
minus5
0
5
times10minus4
minus5
0
5times10minus4
Time (s)
4800 4850 4900 4950 5000
Time (s)
4800 4850 4900 4950 5000
Time (s)
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Figure 13 The roll pitch and yaw rate errors
small strains The Lagrange equation method is utilizedto derive the dynamics for controller design and dynamicsimulation The LQR and optimal PI based controllers aredesigned for the dynamics with the constant disturbancetorque caused by the cmcp offset By theoretical analysisand simulation it can be seen that both controllers cancompromise between the state variables and control inputsBecause the control actuators can hardly afford large controltorque the dynamic performance should be relaxed toreduce the requirement for the attitude control actuatorsBesides the optimal PI based controller can also eliminatethe constant disturbance torque caused by the cmcp offsetthat always exists while the LQR based controller fails toachieve the results with satisfied steady-state performancealthough the attitude control torque is always applied to thecoupled dynamic systemThe dynamics simulations with andwithout the geometrical nonlinearity effect are also carriedout And the differences between the models in magnitudesand phases are identified and analyzed It can be concludedthat the optimal PI based controller performs better than the
LQRbased controller from the viewof eliminating the steady-state error caused by the disturbance torque by the cmcpoffset
Appendix
The related parameters in above equation are given as
119886120593= 119869
119909+ 119898
ℎ11199102
ℎ1
+ 119898ℎ21199112
ℎ2
+ 1198981199011199032
119901119911
+ 1198981199011199032
119901119910
119886120579= minus 119898
119901119903119901119909119903119901119910 119886
120595= minus119898
119901119903119901119909119903119901119911
1198861198811
= minus 1198981198971198972
1198861198812
= minus4
5119898
1198971198972
119887120579= 119869
119910+ 119898
ℎ21199112
ℎ2
+ 1198981199011199032
119901119911
+ 1198981199011199032
119901119909
119887120595= minus 119898
119901119903119901119910119903119901119911 119887
120593= minus119898
119901119903119901119909119903119901119910
22 Mathematical Problems in Engineering
Roll
torq
ue (N
lowastm
)
Roll
torq
ue (N
lowastm
)
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
0 2000 4000 6000
0 2000 4000 6000
0 2000 4000 6000
Time (s)
Time (s)
Time (s)
Time (s)
Time (s)
Time (s)4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
minus01
minus008
008
009
01
minus002
0
002
minus5
0
5
minus2
0
2
Pitc
h to
rque
(Nlowast
m)
Pitc
h to
rque
(Nlowast
m)
minus2
0
2
Yaw
torq
ue (N
lowastm
)
Yaw
torq
ue (N
lowastm
)
Figure 14 The roll pitch and yaw torques
1198871198811
=1
2119898
1198971198972
1198871198812
=2
5119898
1198971198972
119888120595= 119869
119911+ 119898
ℎ11199102
ℎ1
+ 1198981199011199032
119901119910
+ 1198981199011199032
119901119909
119888120579= minus 119898
119901119903119901119910119903119901119911 119888
120593= minus119898
119901119903119901119909119903119901119911
1198881198811
= minus1
21198972
119898119897 119888
1198812
= minus2
51198972
119898119897
119889
1198811
= (4
3
119868119863
119897+
1
5119897119868119860) 119889
1198812
= (1
6119897119868119860+
3119868119863
2119897)
119889
1198811
=4120578
119887119863
119909119909
1198973 119889
1198812
=6120578
119887119863
119909119909
1198973
1198891198811
=4119863
119909119909
1198973 119889
1198812
=6119863
119909119909
1198973
1198761198811
= 1198651198621
(119905)
119890
1198811
= (3
2
119868119863
119897+
1
6119897119868119860)
119890
1198812
= (1
7119897119868119860+
9
5
119868119863
119897) 119890
1198811
=6120578
119887119863
119909119909
1198973
119890
1198812
=12120578
119887119863
119909119909
1198973 119890
1198811
=6119863
119909119909
1198973
1198901198812
=12119863
119909119909
1198973 119876
1198812
= 1198651198622
(119905)
(A1)
The detailed expressions of control inputs for attitudevibration and related parameters in the state-space model ofthe dynamics (see (62) and (63)) are presented as follows
A =
[[[[[[[[[[[[[[
[
0 1 0 0 0 0 0 0 0 0
0 0 0 0 0 0 1198861
1198862
1198863
1198864
0 0 0 1 0 0 0 0 0 0
0 0 0 0 0 0 1198865
1198866
1198867
1198868
0 0 0 0 0 1 0 0 0 0
0 0 0 0 0 0 1198869
11988610
11988611
11988612
0 0 0 0 0 0 0 1 0 0
0 0 0 0 0 0 11988613
11988614
11988615
11988616
0 0 0 0 0 0 0 0 0 1
0 0 0 0 0 0 11988617
11988618
11988619
11988620
]]]]]]]]]]]]]]
]
Mathematical Problems in Engineering 23
0 1000 2000 3000 4000 5000
0 1000 2000 3000 4000 5000
minus01
0
01
minus02
0
02
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Time (s)
Time (s)Time (s)
Time (s)
minus1
0
1
minus1
0
1
times10minus3
times10minus3Th
e disp
lace
men
t of t
he ti
p (m
)
The d
ispla
cem
ent o
f the
tip
(m)
The v
eloci
ty o
f the
tip
(ms
)
The v
eloci
ty o
f the
tip
(ms
)
Figure 15 Vibration displacement and velocity of the tip
B =
[[[[[[[[[[[[[[
[
0 0 0 0 0
1 0 0 0 0
0 0 0 0 0
0 1 0 0 0
0 0 0 0 0
0 0 1 0 0
0 0 0 0 0
0 0 0 1 0
0 0 0 0 0
0 0 0 0 1
]]]]]]]]]]]]]]
]
1198861= minus
1198981198971198972
119869119909
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus4
5119869119909
1198981198971198972
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198862= minus
1198981198971198972
119869119909
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus4
5119869119909
1198981198971198972
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198863= minus
1198981198971198972
119869119909
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus4
5119869119909
1198981198971198972
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198864= minus
1198981198971198972
119869119909
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus4
5119869119909
1198981198971198972
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
119906120593=
119876120593
119869119909
+
119906
119869119909
+119898
1198971198972
119869119909
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+4
5119869119909
1198981198971198972
+
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198865=
1
2119869119910
1198981198971198972
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+2
5119869119910
1198981198971198972
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198866=
1
2119869119910
1198981198971198972
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+2
5119869119910
1198981198971198972
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198867=
1
2119869119910
1198981198971198972
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+2
5119869119910
1198981198971198972
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198868=
1
2119869119910
1198981198971198972
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
24 Mathematical Problems in Engineering
+2
5119869119910
1198981198971198972
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
119906120579=
119876120579
119869119910
+119906
120579
119869119910
minus1
2119869119910
1198981198971198972
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119910
1198981198971198972
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198869= minus
1
2119869119911
1198972
119898119897
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988610
= minus1
2119869119911
1198972
119898119897
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988611
= minus1
2119869119911
1198972
119898119897
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988612
= minus1
2119869119911
1198972
119898119897
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
119906120595=
119876120595
119869119911
+
119906
119869119911
+1
2119869119911
1198972
119898119897
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+2
5119869119911
1198972
119898119897
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988613
= minus
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988614
= minus
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988615
= minus
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988616
= minus
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
1199061198811
=
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988617
= minus
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988618
= minus
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988619
= minus
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988620
= minus
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1199061198812
=
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(A2)
Conflict of Interests
The authors declare that there is no conflict of interestsregarding the publication of this paper
Acknowledgments
The authors would like to thank the anonymous reviewers fortheir critical and constructive review of the paper This studywas cosupported by the National Natural Science Foundationof China (Project no 11302134 11272101)
References
[1] M Colin Solar Sailing Technology Dynamics and MissionApplications Springer-Praxis London UK 1st edition 1999
[2] V Lappas SWokesM Leipold A Lyngvi and P Falkner ldquoGui-dance and control for an Interstellar Heliopause Probe (IHP)solar sail mission to 200 AUrdquo in Proceedings of the AIAAGuidance Navigation and Control Conference and Exhibit pp2472ndash2492 San Francisco Calif USA August 2005
[3] L Charlotte C Camilla and C McInnes ldquoSolar radiation pres-sure augmented deorbiting fromhigh altitude sun-synchronousorbitsrdquo in Proceedings of the 4S Symposium 2012 Small SatellitesSystems and Services Portoroz Slovenia 2012
[4] M Ceriotti and C RMcInnes ldquoGeneration of optimal trajecto-ries for Earth hybrid pole sittersrdquo Journal of Guidance Controland Dynamics vol 34 no 3 pp 847ndash859 2011
[5] S Gong J Li andH Baoyin ldquoSolar sail transfer trajectory fromL1 point to sub-L1 pointrdquoAerospace Science and Technology vol15 no 7 pp 544ndash554 2011
[6] S Gong J Li and H Baoyin ldquoAnalysis of displaced solar sailorbits with passive controlrdquo Journal of Guidance Control andDynamics vol 31 no 3 pp 782ndash785 2008
[7] S Gong H Baoyin and J Li ldquoSolar sail three-body transfertrajectory designrdquo Journal of Guidance Control and Dynamicsvol 33 no 3 pp 873ndash886 2010
Mathematical Problems in Engineering 25
[8] S Gong J Li H Baoyin and J Simo ldquoA new solar sail orbitrdquoScience China Technological Sciences vol 55 no 3 pp 848ndash8552012
[9] Y Tsuda O Mori R Funase et al ldquoAchievement of IKAROS-Japanese deep space solar sail demonstration missionrdquo ActaAstronautica vol 82 no 2 pp 183ndash188 2013
[10] L Johnson MWhorton A Heaton R Pinson G Laue and CAdams ldquoNanoSail-D a solar sail demonstration missionrdquo ActaAstronautica vol 68 no 5-6 pp 571ndash575 2011
[11] B Wie and D Murphy ldquoSolar-sail attitude control design for asail flight validation missionrdquo Journal of Spacecraft and Rocketsvol 44 no 4 pp 809ndash821 2007
[12] B Wie D Murphy M Paluszek and S Thomas ldquoRobust atti-tude control systems design for solar sails part 1 propellantlessprimaryACSrdquo inProceedings of the AIAAGuidance Navigationand Control Conference and Exhibit Providence RI USAAugust 2004
[13] B Wie D Murphy M Paluszek and S Thomas ldquoRobust atti-tude control systems design for solar sails part 2 MicroPPT-based secondary ACSrdquo in Proceedings of the AIAA GuidanceNavigation and Control Conference and Exhibit pp 1325ndash1340Providence RI USA August 2004
[14] S Thomas M Paluszek B Wie and D Murphy ldquoAOCS per-formance and stability validation for large flexible solar sailspacecraftrdquo in Proceedings of the 41st AIAAASMESAEASEEJoint Propulsion Conference amp Exhibit Tucson Ariz USA 2005
[15] B Wie ldquoDynamic modeling and attitude control of solar sailspacecraft part Irdquo in Proceedings of the AIAAGuidance Naviga-tion and Control Conference and Exhibit Monterey Calif USAAugust 2002
[16] BWie ldquoSolar sail attitude control and dynamics part 1rdquo Journalof Guidance Control and Dynamics vol 27 no 4 pp 526ndash5352004
[17] B Wie ldquoDynamic modeling and attitude control of solar sailspacecraft part IIrdquo in Proceedings of the AIAA Guidance Nav-igation and Control Conference and Exhibit Monterey CalifUSA August 2002
[18] BWie ldquoSolar sail attitude control and dynamics part 2rdquo Journalof Guidance Control and Dynamics vol 27 no 4 pp 536ndash5442004
[19] C Luo and J-H Zheng ldquoSolar-sail attitude control based onmoving masses and roll stabilizer barsrdquo Journal of HarbinInstitute of Technology vol 43 no 3 pp 95ndash101 2011
[20] D Romagnoli and T Oehlschlagel ldquoHigh performance twodegrees of freedom attitude control for solar sailsrdquo Advances inSpace Research vol 48 no 11 pp 1869ndash1879 2011
[21] C Scholz D Romagnoli B Dachwald and S Theil ldquoPerfor-mance analysis of an attitude control system for solar sails usingsliding massesrdquo Advances in Space Research vol 48 no 11 pp1822ndash1835 2011
[22] A Bolle and C Circi ldquoSolar sail attitude control through in-plane moving massesrdquo Journal of Aerospace Engineering vol222 no 1 pp 81ndash94 2008
[23] M RotunnoM Basso A B Pome andM Sallusti ldquoA compari-son of robust attitude control techniques for a solar sail space-craftrdquo in Proceedings of the AIAA Guidance Navigation andControl Conference and Exhibit San Francisco Calif USA2005
[24] J Zhang K Zhai and T Wang ldquoControl of large angle maneu-vers for the flexible solar sailrdquo Science China Physics Mechanicsand Astronomy vol 54 no 4 pp 770ndash776 2011
[25] J Zhang andTWang ldquoCoupled attitude-orbit control of flexiblesolar sail for displaced solar orbitrdquo Journal of Spacecraft andRockets vol 50 no 3 pp 675ndash685 2013
[26] Q Li XMa and TWang ldquoReducedmodel for flexible solar saildynamicsrdquo Journal of Spacecraft and Rockets vol 48 no 3 pp446ndash453 2011
[27] M Polites J Kalmanson and D Mangus ldquoSolar sail attitudecontrol using small reaction wheels and magnetic torquersrdquoProceedings of the Institution of Mechanical Engineers G Journalof Aerospace Engineering vol 222 no 1 pp 53ndash62 2008
[28] H-T Cui J-H Luo J-H Feng and P-Y Cui ldquoAttitudecontrol of solar sail spacecraft with control boomrdquo Journal ofAstronautics vol 29 no 2 pp 560ndash566 2008
[29] E Mettler and S R Ploen ldquoSolar sail dynamics and controlusing a boom mounted bus articulated by a bi-state two-axisgimbal and reaction wheelsrdquo in Proceedings of the AIAAAASAstrodynamics Specialist Conference and Exhibit MontereyCalif USA August 2002
[30] J Luo X Li and J Feng ldquoPassive attitude control of solar sailspacecraftrdquo Flight Dynamics vol 26 no 5 pp 47ndash50 2008
[31] J Luo Study on attitude control of solar sail spaceraft [PhDthesis] School of Astronautics Harbin Institute of TechnologyHarbin China 2007
[32] D A Lawrence and S W Piggott ldquoIntegrated trajectory andattitude control for a four-vane solar sailrdquo in Proceedings ofthe AIAA Guidance Navigation and Control Conference andExhibit pp 2416ndash2431 San Francisco Calif USA August 2005
[33] E Mettler A B Acikmese and S R Ploen ldquoAttitude dynamicsand control of solar sails with articulated vanesrdquo in Proceedingsof the AIAA Guidance Navigation and Control Conference andExhibit pp 2396ndash2415 San Francisco Calif USA August 2005
[34] S N Adeli V J Lappas and B Wie ldquoA scalable bus-basedattitude control system for Solar Sailsrdquo Advances in SpaceResearch vol 48 no 11 pp 1836ndash1847 2011
[35] R Funase Y Shirasawa Y Mimasu et al ldquoOn-orbit verificationof fuel-free attitude control system for spinning solar sailutilizing solar radiation pressurerdquo Advances in Space Researchvol 48 no 11 pp 1740ndash1746 2011
[36] B Fu and F O Eke ldquoAttitude control methodology for largesolar sailsrdquo in AIAA Guidance Navigation and Control (GNC)Conference 2013
[37] J Liu N Cui F Shen and S Rong ldquoDynamics of highly-flexiblesolar sail subjected to various forcesrdquoActaAstronautica vol 103pp 55ndash72 2014
[38] J F Liu S Y Rong and J G Li ldquoAttitude dynamics modelingand control of large flexible solar sail spacecraftrdquo in Proceedingsof the 3rd International Symposium on Systems and Control inAeronautics and Astronautics (ISSCAA rsquo10) pp 243ndash247 IEEEPublications Piscataway NJ USA 2010
[39] S Gong H Baoyin and J Li ldquoCoupled attitude-orbit dynamicsand control for displaced solar orbitsrdquo Acta Astronautica vol65 no 5-6 pp 730ndash737 2009
Submit your manuscripts athttpwwwhindawicom
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
MathematicsJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Mathematical Problems in Engineering
Hindawi Publishing Corporationhttpwwwhindawicom
Differential EquationsInternational Journal of
Volume 2014
Applied MathematicsJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Probability and StatisticsHindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Journal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Mathematical PhysicsAdvances in
Complex AnalysisJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
OptimizationJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
CombinatoricsHindawi Publishing Corporationhttpwwwhindawicom Volume 2014
International Journal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Operations ResearchAdvances in
Journal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Function Spaces
Abstract and Applied AnalysisHindawi Publishing Corporationhttpwwwhindawicom Volume 2014
International Journal of Mathematics and Mathematical Sciences
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
The Scientific World JournalHindawi Publishing Corporation httpwwwhindawicom Volume 2014
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Algebra
Discrete Dynamics in Nature and Society
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Decision SciencesAdvances in
Discrete MathematicsJournal of
Hindawi Publishing Corporationhttpwwwhindawicom
Volume 2014 Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Stochastic AnalysisInternational Journal of
8 Mathematical Problems in Engineering
OOx
y
z
FCFCy
FCx
FCz
mh
q(x)
Figure 5 The vibration model
120590
120590e
120590120592
120590
Figure 6 The viscoelastic model
3 The Vibration of Solar Sail
The mechanical and material models of the sailcraft aregivenThe displacement filed stress and strain are presentedbased on the Euler beam assumptionThe Lagrange equationmethod is adopted to derive the vibration equations withlarge deformations based on the calculations of kineticenergies and works done by the external loads
31 The Mechanical Model The body frame O119874xyz is estab-
lished to describe the vibration (see Figure 5) F119862is the force
vector generated by the control vane used located at the tip ofthe supporting beam 119865
119862119909 119865
119862119910 and 119865
119862119911are the components
inO119874xyz 119902(119909) is the distributed load caused by SRP
32 The Material Model The carbon fibre enforced compos-ite material is used to construct the inflatable deploymentsupporting beam The model of the viscoelastic material canbe represented in Figure 6
The total stress is the summation of the elastic and viscousstresses It can be expressed as
120590 = 120590119890
+ 120590120592
= 119864120576 + 119888119887
120576 (32)
where 120590 120590119890 and 120590
120592 are the total elastic and viscous stressrespectively And 119864 is Youngrsquos modulus 120576 ( 120576) is the strain(strain rate) and 119888
119887is the coefficient of the internal damping
expressed as 119864120578119887 120578
119887is the proportionality constant of the
internal damping The dimensions of 119888119887and 120578
119887are N lowast sm2
and s respectively
OO x
y The support beam
Z
Figure 7 The schematic diagram of solar sail supporting beamdeformation
33 The Displacement Field Stress and Strain The deforma-tion of a spatial solar sail supporting beam is presented inFigure 7
The spatial displacement fields for supporting beam are as
119906 (119909 119910 119911 119905) = 1199060(119909 119905) minus 119910
120597V0
120597119909minus 119911
1205971199080
120597119909
V (119909 119910 119911 119905) = V0(119909 119905)
119908 (119909 119910 119911 119905) = 1199080(119909 119905)
(33)
119906(119909 119910 119911 119905) V(119909 119910 119911 119905) and 119908(119909 119910 119911 119905) are the displace-ments along 119909 119910 and 119911 directions respectively 119906
0(119909 119905)
V0(119909 119905) and 119908
0(119909 119905) are the axial and transverse displace-
ments of an arbitrary point on the neutral axisBy using Green strain definition von Karmanrsquos nonlinear
strain-displacement relationships based on assumptions oflarge deflections moderate rotations and small strains for a3D supporting beam are given as follows together with thestrain rate and normal stress
120576119909119909
=120597119906
0
120597119909+1
2(120597V
0
120597119909)
2
minus 1199101205972V
0
1205971199092
+1
2(120597119908
0
120597119909)
2
minus 1199111205972
1199080
1205971199092
120576119909119909
=120597
0
120597119909+(
120597V0
120597119909)(
120597V0
120597119909) minus 119910
1205972V
0
1205971199092
+(120597119908
0
120597119909)(
1205970
120597119909)
minus 1199111205972
0
1205971199092
120590119909119909
= 119864[120597119906
0
120597119909+1
2(120597V
0
120597119909)
2
minus 1199101205972V
0
1205971199092
+1
2(120597119908
0
120597119909)
2
minus 1199111205972
1199080
1205971199092
]
+ 119864120578119887(120597
0
120597119909+(
120597V0
120597119909)(
120597V0
120597119909) minus 119910
1205972V
0
1205971199092
+(120597119908
0
120597119909)(
1205970
120597119909) minus 119911
1205972
0
1205971199092
)
(34)
Mathematical Problems in Engineering 9
The single underlined terms in the preceding equationindicate the contribution by the geometrical nonlinearityThedynamics models and corresponding numerical simulationwithout considering the geometrical nonlinearity can beobtained and carried out by neglecting these terms
34 The Energies and Works Done by External Forces Thestrain energy can be derived as
119880119894=
1
2int
119897
0
119860119909119909
[120597119906
0
120597119909+
1
2(120597V
0
120597119909)
2
+1
2(120597119908
0
120597119909)
2
]
2
+ 119863119909119909
1205972V
0
1205971199092
+ 119863119909119909
1205972
1199080
1205971199092
119889119909
(35)
For an isotropic support beam the extensional stiffness119860
119909119909and bending stiffness119863
119909119909can be computed as
119860119909119909
= int119860
119864119889119860 119863119909119909
= int119860
1198641199112
119889119860 = int119860
1198641199102
119889119860 (36)
The dissipation function is as
Ψ119902=
1
2int
119897
0
[119860119909119909120578119887(120597
0
120597119909)
2
+ 119863119909119909120578119887(1205972V
0
1205971199092
)
2
+ 119863119909119909120578119887(1205972
0
1205971199092
)
2
]119889119909
(37)
The kinetic energy for the support beam is as
119879119890=
1
2int
119897
0
[119868119860(120597119906
0
120597119905)
2
+ 119868119860(120597119908
0
120597119905)
2
+ 119868119863(1205972
1199080
120597119909120597119905)
2
+ 119868119860(120597V
0
120597119905)
2
+ 119868119863(
1205972V
0
120597119909120597119905)
2
]119889119909
(38)
where 119868119860and 119868
119863are integration constant for the support
beam expressed as
119868119860= int
119860
120588119889119860 = 120588119860 119868119863= int
119860
1205881199112
119889119860 = int119860
1205881199102
119889119860 (39)
And the work done by the external force can be obtainedas119882 = 119865
119862119911sdot 119908 (119909
119888 119905) + 119865
119862119910sdot V (119909
119888 119905) + 119898
ℎ119886ℎ119910
(119909ℎ 119905) V (119909
ℎ 119905)
+ 119898ℎ119886ℎ119911
(119909ℎ 119905) 119908 (119909
ℎ 119905) + int
119897
0
119902 (119909) V (119909 119905) 119889119909
(40)where 119909
119888represents the position of the support beam
119908(119909119888 119905) V(119909
119888 119905) are the displacements along 119911 and 119910 direc-
tions respectively and the corresponding loads 119865119862119911 119865
119862119910are
known functions 119909ℎ 119897 and V
ℎare the position coordinate of
the sliding mass the length of the support beam and theconstant-velocity of the sliding mass The dynamic responseis studied only during the period [0 119897V
ℎ] 119898
ℎis the mass
and 119886ℎ119910(119909
ℎ 119905) and 119886
ℎ119911(119909
ℎ 119905) are the components of the
acceleration for a material point on the support beam theslidingmass just arrived at And the corresponding transversedeflections are 119908(119909
ℎ 119905) and V(119909
ℎ 119905) respectively
35 The Assumed Modes Method The axial displacement1199060(119909 119905) and the transverse deflections V
0(119909 119905) and119908
0(119909 119905) can
be represented as follows by considering the assumed modesmethod
1199060(119909 119905) =
infin
sum
119894=1
119880119894(119909)119880
119894(119905)
V0(119909 119905) =
infin
sum
119895=1
119881119895(119909) 119881
119895(119905)
1199080(119909 119905) =
infin
sum
119896=1
119882119896(119909)119882
119896(119905)
(41)
where 119880119894(119905) 119881
119895(119905) and 119882
119896(119905) are the time-dependent gen-
eralized coordinates and 119880119894(119909) 119881
119895(119909) and 119882
119896(119909) are the
assumedmodes For assumedmodemethod themode shapefunctions should satisfy the following requirements in thispaper
119880119894(119909)
1003816100381610038161003816119909=0= 0 119881
119895(119909)
10038161003816100381610038161003816119909=0= 0 119882
119896(119909)
1003816100381610038161003816119909=0= 0
1198811015840
119895
(119909)10038161003816100381610038161003816119909=0
= 0 1198821015840
119896
(119909)10038161003816100381610038161003816119909=0
= 0
(42)
The following first two assumed modes satisfying theassumed mode principle are used in this paper
1198801(119909) =
119909
119897 119880
2(119909) = (
119909
119897)
2
1198811(119909) = (
119909
119897)
2
1198812(119909) = (
119909
119897)
3
1198821(119909) = (
119909
119897)
2
1198822(119909) = (
119909
119897)
3
(43)
With the help of the assumedmodes the detailed expres-sions of 119880
119894 119879
119890119882
119911 and Ψ
119902can be obtained as
119880119894=
9
2
119860119909119909
1198973(119881
2
2
+ 1198822
2
)2
+27
4
119860119909119909
1198973(119881
11198812+ 119882
1119882
2)
times (1198812
2
+ 1198822
2
)
+18
7
119860119909119909
1198973[(119881
2
1
+ 1198822
1
) (1198812
2
+ 1198822
2
) + (11988111198812+ 119882
1119882
2)2
]
+119860
119909119909
1198973[3
2119897119880
2(119881
2
2
+ 1198822
2
) + (1198812
1
+ 1198822
1
)
times (11988111198812+ 119882
1119882
2)]
10 Mathematical Problems in Engineering
+1
10
119860119909119909
1198973[9119880
1119897 (119881
2
2
+ 1198822
2
) + 241198802119897 (119881
11198812+ 119882
1119882
2)
+ 4 (1198812
1
+ 1198822
1
)2
]
+119860
119909119909
1198972[3
21198801(119881
11198812+ 119882
1119882
2) + 119880
2(119881
2
1
+ 1198822
1
)]
+6119863
119909119909119881
2
2
1198973+ 119860
119909119909(2119880
1119881
2
1
31198972+
21198801119882
2
1
31198972+
21198802
2
3119897)
+6119863
119909119909119882
2
2
1198973+
611986311990911990911988111198812
1198973+
11986011990911990911988011198802
119897+
6119863119909119909119882
1119882
2
1198973
+119860
119909119909119880
2
1
2119897+
2119863119909119909119881
2
1
1198973+
2119863119909119909119882
2
1
1198973
119879119890=
1
14(119897119868
119860
2
2
+ 119897119868119860
2
2
) +1
6(119897119868
119860
1
2+ 119897119868
11986012)
+1
10(119897119868
119860
2
2
+ 119897119868119860
2
1
+9119868
119863
2
2
119897+ 119897119868
119860
2
1
+9119868
119863
2
2
119897)
+1
4(119897119868
11986012+
6119868119863
1
2
119897+
611986811986312
119897)
+1
6(119897119868
119860
2
1
+4119868
119863
2
1
119897+
4119868119863
2
1
119897)
119882119911= 119865
119862119911sdot [119882
1(119905) + 119882
2(119905)] + 119865
119862119910sdot [119881
1(119905) + 119881
2(119905)]
+ 119898ℎ[2V2
ℎ
1198972sdot 119881
1(119905) +
4V2ℎ
119905
1198972sdot
1(119905) + (
Vℎ119905
119897)
2
sdot 1(119905)
+6V3
ℎ
119905
1198973sdot 119881
2(119905) +
6V3ℎ
1199052
1198973
sdot 2(119905) + (
Vℎ119905
119897)
3
sdot 2(119905)]
times [(Vℎ119905
119897)
2
sdot 1198811(119905) + (
Vℎ119905
119897)
3
sdot 1198812(119905)]
+ 119898ℎ[2V2
ℎ
1198972sdot 119882
1(119905) +
4V2ℎ
119905
1198972sdot
1(119905) + (
Vℎ119905
119897)
2
sdot 1(119905)
+6V3
ℎ
119905
1198973sdot 119882
2(119905) +
6V3ℎ
1199052
1198973sdot
2(119905)
+ (Vℎ119905
119897)
3
sdot 2(119905)]
times [(Vℎ119905
119897)
2
sdot 1198821(119905) + (
Vℎ119905
119897)
3
sdot 1198822(119905)]
+ 1198811(119905) sdot int
119897
0
119902 (119909) (119909
119897)
2
119889119909 + 1198812(119905)
sdot int
119897
0
119902 (119909) (119909
119897)
3
119889119909
Ψ119902=
1
6(36119863
119909119909120578119887
2
2
1198976+
4119860119909119909120578119887
2
2
1198974+
36119863119909119909120578119887
2
2
1198976) 119897
3
+1
4(4119860
11990911990912057811988712
1198973+
2411986311990911990912057811988712
1198975
+24119863
119909119909120578119887
1
2
1198975) 119897
2
+1
2
119860119909119909120578119887
2
1
119897+
2119863119909119909120578119887
2
1
1198973+
2119863119909119909120578119887
2
1
1198973
(44)
36 The Vibration Equation The Lagrange equation methodis used to derive the vibration equations
120597119871
120597119902119899
minus119889
119889119905(
120597119871
120597 119902119899
) + 119876119889= 0 119899 = 1 2 6 (45)
where 119871 is the Lagrange function 119902119899
= (1198801 119880
2 119881
1 119881
2
1198821119882
2)119879 is the vector of the generalized coordinates and
119902119899is the corresponding generalized velocity vector 119876
119889is the
generalized damping force The expressions for 119871 and 119876119889are
as
119871 = 119879119890minus (119880
119894minus 119882
119911)
119876119889= minus
120597Ψ119902
120597 119902119899
(119899 = 1 sim 6)
(46)
The axial vibration equations can be obtained as followsfor 119880
1 119880
2
1
31198971198681198601+
1
41198971198681198602+
120578119887119860
1199091199091
119897+
120578119887119860
1199091199092
119897+
1198601199091199091198801
119897
+119860
1199091199091198802
119897+
2119860119909119909119881
2
1
31198972+
311986011990911990911988111198812
21198972+
9119860119909119909119881
2
2
101198972
+2119860
119909119909119882
2
1
31198972+
3119860119909119909119882
1119882
2
21198972+
9119860119909119909119882
2
2
101198972= 0
(47a)
1
41198971198681198601+
1
51198971198681198602+
120578119887119860
1199091199091
119897+
4120578119887119860
1199091199092
3119897
+119860
1199091199091198801
119897+4119860
1199091199091198802
3119897+119860
119909119909119881
2
1
1198972+12119860
11990911990911988111198812
51198972+3119860
119909119909119881
2
2
21198972
+119860
119909119909119882
2
1
1198972+
12119860119909119909119882
1119882
2
51198972+
3119860119909119909119882
2
2
21198972= 0
(47b)
The following can be seen from the above equations
(1) Since the assumed modes rather than the naturalmodes are used the coupling between axial and trans-verse vibrations is rather severe for axial vibrations
Mathematical Problems in Engineering 11
(2) The nonlinearity is apparent in above equations onlyexisting in the terms of 119881
1 119881
2119882
1119882
2 We take (47a)
as an exampleThe terms including1198802and its first and
second derivative 1198811 119881
2119882
1119882
2 can be regarded as
the applied loads for 1198801
(3) The coupling between the axial and transverse vibra-tionswill disappear as long as the linear displacement-strain relationship is adopted
(4) There are no external loads for axial vibrationsaccording to above equations
The transverse vibration equations for 1198811 119881
2and119882
1 119882
2
can be obtained as
4
3
1198681198631
119897+
1
51198971198681198601+
1
61198971198681198602minus
119898ℎV5ℎ
1199055
2
1198975+
31198681198632
2119897
+4119898
ℎV4ℎ
1199053
1
1198974+
4120578119887119863
1199091199091
1198973minus
2119898ℎV5ℎ
1199054
2
1198975+
6120578119887119863
1199091199092
1198973
+8119898
ℎV4ℎ
1199052
1198811
1198974+
41198631199091199091198811
1198973+
8119898ℎV5ℎ
1199053
1198812
1198975+
61198631199091199091198812
1198973
+27119860
1199091199091198812119882
2
2
81198973+
541198601199091199091198811119881
2
2
71198973+
181198601199091199091198811119882
2
2
71198973
+6119860
119909119909119881
2
1
1198812
1198973+
21198601199091199091198812119882
2
1
1198973+
1211986011990911990911988021198812
51198972
+8119860
1199091199091198811119882
2
1
51198973+
311986011990911990911988011198812
21198972+
211986011990911990911988021198811
1198972
+8119860
119909119909119881
3
1
51198973+
27119860119909119909119881
3
2
81198973+
361198601199091199091198812119882
1119882
2
71198973
+4119860
1199091199091198811119882
1119882
2
1198973+
411986011990911990911988011198811
31198972minus 119865
119888119910(119905) minus 05119865
025119865= 0
1
61198971198681198601+
3
2
1198681198631
119897minus
119898ℎV5ℎ
1199055
1
1198975+
1
71198971198681198602+
9
5
1198681198632
119897
+6120578
119887119863
1199091199091
1198973+
2119898ℎV5ℎ
1199054
1
1198975+
12120578119887119863
1199091199092
1198973+
6119898ℎV6ℎ
1199055
2
1198976
+6119863
1199091199091198811
1198973+
16119898ℎV5ℎ
1199053
1198811
1198975+
121198631199091199091198812
1198973+
18119898ℎV6ℎ
1199054
1198812
1198976
+9119860
1199091199091198812119882
2
2
21198973+
811198601199091199091198811119881
2
2
81198973+
311986011990911990911988011198811
21198972
+27119860
1199091199091198811119882
2
2
81198973+
541198601199091199091198812119881
2
1
71198973+
181198601199091199091198812119882
2
1
71198973
+3119860
11990911990911988021198812
1198972+
21198601199091199091198811119882
2
1
1198973+
911986011990911990911988011198812
51198972+
1211986011990911990911988021198811
51198972
+9119860
119909119909119881
3
2
21198973+
2119860119909119909119881
3
1
1198973+
271198601199091199091198812119882
1119882
2
41198973
+36119860
1199091199091198811119882
1119882
2
71198973minus 04119865
025119865minus 119865
119888119910(119905) = 0
4
3
119868119863
1
119897+
1
5119897119868119860
1+
3
2
119868119863
2
119897+
1
6119897119868119860
2minus
119898ℎV5ℎ
1199055
2
1198975
+4120578
119887119863
119909119909
1
1198973+
4119898ℎV4ℎ
1199053
1
1198974minus
2119898ℎV5ℎ
1199054
2
1198975+
6120578119887119863
119909119909
2
1198973
+4119863
119909119909119882
1
1198973+
8119898ℎV4ℎ
1199052
1198821
1198974+
8119898ℎV5ℎ
1199053
1198822
1198975+
6119863119909119909119882
2
1198973
+36119860
119909119909119882
211988111198812
71198973+
4119860119909119909119882
111988111198812
1198973+
27119860119909119909119882
2119881
2
2
81198973
+18119860
119909119909119882
1119881
2
2
71198973+
54119860119909119909119882
1119882
2
2
71198973+
6119860119909119909119882
2
1
1198822
1198973
+2119860
119909119909119882
2119881
2
1
1198973+
121198601199091199091198802119882
2
51198972+
8119860119909119909119882
1119881
2
1
51198973
+3119860
1199091199091198801119882
2
21198972+
21198601199091199091198802119882
1
1198972+
27119860119909119909119882
3
2
81198973
+8119860
119909119909119882
3
1
51198973+
41198601199091199091198801119882
1
31198972minus 119865
119888119911(119905) = 0
1
7119897119868119860
2+
9
5
119868119863
2
119897+
1
6119897119868119860
1minus
119898ℎV5ℎ
1199055
1
1198975+
3
2
119868119863
1
119897
+6120578
119887119863
119909119909
1
1198973+
2119898ℎV5ℎ
1199054
1
1198975+
6119898ℎV6ℎ
1199055
2
1198976
+12120578
119887119863
119909119909
2
1198973+
6119863119909119909119882
1
1198973+
16119898ℎV5ℎ
1199053
1198821
1198975
+12119863
119909119909119882
2
1198973+
18119898ℎV6ℎ
1199054
1198822
1198976+
31198601199091199091198801119882
1
21198972
+27119860
119909119909119882
211988111198812
41198973+
36119860119909119909119882
111988111198812
71198973+
9119860119909119909119882
2119881
2
2
21198973
+27119860
119909119909119882
1119881
2
2
81198973+
81119860119909119909119882
1119882
2
2
81198973+
18119860119909119909119882
2119881
2
1
71198973
+54119860
119909119909119882
2119882
2
1
71198973+
31198601199091199091198802119882
2
1198972+
2119860119909119909119882
1119881
2
1
1198973
+9119860
1199091199091198801119882
2
51198972+
121198601199091199091198802119882
1
51198972+
2119860119909119909119882
3
1
1198973
+9119860
119909119909119882
3
2
21198973minus 119865
119888119911(119905) = 0
(48)
The complexity high coupling and nonlinearity are obvi-ous in above equations
4 The Coupled Rigid-Flexible Dynamics
The dynamics for control and dynamic simulation shouldbe presented for solar sail based on the simplification ofequations derived in previous sections Some assumptions aremade before simplifying the equations as follows
12 Mathematical Problems in Engineering
(1) Only the attitude motion is affected by the slidingmass the vibration of solar sail structure is notaffected by the sliding mass
(2) Although the attitude control is accomplished byrotating control vanes and the gimbaled controlboom moving sliding masses the specific time his-tories of the actuators are not considered here
(3) The four supporting beams are regarded as an entirestructure thus the identical generalized coordinatesare adopted in the dynamic analysis
41 The Simplified Attitude Dynamics The kinetic energy ofsolar sail supporting beams can be obtained as
119879119898
=1
2120596 sdot J sdot 120596 + 119898
119897int
119897
0
2∘
1205883
sdot (120596 times r3) + (120596 times 120588
3) sdot (120596 times 120588
3)
+ 2 (120596 times r3) sdot (120596 times 120588
3) 119889119911
+ 119898119897int
119897
0
2∘
1205882
sdot (120596 times r2) + (120596 times 120588
2) sdot (120596 times 120588
2)
+ 2 (120596 times r2) sdot (120596 times 120588
2) 119889119910
(49)
The subscripts 2 and 3 represent the second and thirdsupporting beams The displacements can be expressed as
V0119909
(119911 119905) = (119911
119897)
2
sdot 1198811(119905) + (
119911
119897)
3
sdot 1198812(119905)
1199080119910
(119911 119905) = 120572V0119909
(119911 119905) = (119911
119897)
2
sdot 1205721198811(119905) + (
119911
119897)
3
sdot 1205721198812(119905)
for the 3rd beam
V0119909
(119910 119905) = 120573V0119909
(119911 119905) = (119910
119897)
2
sdot 1205731198811(119905) + (
119910
119897)
3
sdot 1205731198812(119905)
1199080119911
(119910 119905) = 120574V0119909
(119910 119905) = (119910
119897)
2
sdot 1205741198811(119905) + (
119910
119897)
3
sdot 1205741198812(119905)
for the 2nd beam
(50)
The subscripts 119909 119910 and 119911 of the left terms in (50)represent the displacements along119909119910 and 119911directions119881
1(119905)
and 1198812(119905) are the generalized coordinates The displacements
1199080119910(119911 119905) V
0119909(119910 119905) and 119908
0119911(119910 119905) can be obtained using the
assumed modes as
1205883= V
0119909(119911 119905) i
119887+ 119908
0119910(119911 119905) j
119887
=
[[[[[
[
(119911
119897)
2
sdot 1198811(119905) + (
119911
119897)
3
sdot 1198812(119905)
120572 [(119911
119897)
2
sdot 1198811(119905) + (
119911
119897)
3
sdot 1198812(119905)]
0
]]]]]
]
1205882= V
0119909(119910 119905) i
119887+ 119908
0119911(119910 119905) k
119887
=
[[[[[
[
120573[(119910
119897)
2
sdot 1198811(119905) + (
119910
119897)
3
sdot 1198812(119905)]
0
120574 [(119910
119897)
2
sdot 1198811(119905) + (
119910
119897)
3
sdot 1198812(119905)]
]]]]]
]
(51)
The vibration velocity can be obtained as
∘
1205883
= 1205883119909i119887+ 120588
3119910j119887=
[[[[[
[
(119911
119897)
2
sdot 1(119905) + (
119911
119897)
3
sdot 2(119905)
1205721[(
119911
119897)
2
sdot 1(119905) + (
119911
119897)
3
sdot 2(119905)]
0
]]]]]
]
∘
1205882
= 1205882119909i119887+ 120588
2119911k119887=
[[[[[
[
1205731[(
119910
119897)
2
sdot 1(119905) + (
119910
119897)
3
sdot 2(119905)]
0
1205741[(
119910
119897)
2
sdot 1(119905) + (
119910
119897)
3
sdot 2(119905)]
]]]]]
]
(52)
Without loss of generality 120572 = 120573 = 1205721= 120573
1= 1 and
120574 = 1205741= minus1 can be assumed in above expressions And the
kinetic energy of the slidingmasses can be obtained as followsby neglecting the vibration related terms
119879ℎ=
1
2119898
ℎ1(120596 times r
ℎ1) sdot (120596 times r
ℎ1) +
1
2119898
ℎ2(120596 times r
ℎ2)
sdot (120596 times rℎ2)
(53)
The kinetic energy of the payload can be obtained as
119879119901=
1
2119898
119901(120596 times r
119901) sdot (120596 times r
119901) (54)
The following simplified attitude dynamics can beobtained by neglecting the second and higher terms ofattitude angles and vibration modes in computing the kinetic
Mathematical Problems in Engineering 13
energies of the supporting beams payload and slidingmasses Consider
119869119909 minus 119898
1198971198972
1minus
4
5119898
1198971198972
2+ 119898
ℎ11199102
ℎ1
+ 119898ℎ21199112
ℎ2
minus 119898119901119903119901119909119903119901119911 + 119898
1199011199032
119901119911
+ 1198981199011199032
119901119910
minus 119898119901119903119901119909119903119901119910
120579 = 119876120593
119869119910
120579 +2
5119898
1198971198972
2+
1
2119898
1198971198972
1+ 119898
ℎ21199112
ℎ2
120579
+ 1198981199011199032
119901119911
120579 minus 119898119901119903119901119910119903119901119911 minus 119898
119901119903119901119909119903119901119910
+ 1198981199011199032
119901119909
120579 = 119876120579
119869119911 minus
2
51198972
1198981198972minus
1
21198972
1198981198971+ 119898
ℎ11199102
ℎ1
minus 119898119901119903119901119910119903119901119911
120579 + 1198981199011199032
119901119910
+ 1198981199011199032
119901119909
minus 119898119901119903119901119909119903119901119911 = 119876
120595
(55)
where 119876120593 119876
120579 and 119876
120595are the generalized nonpotential
attitude control torques generated by the control vanes Andthe attitude control torques generated by the gimbaled controlboom and sliding masses can be found on the left side ofthe above equation coupled with 120579 making the attitudecontroller design problem rather difficult
42 The Simplified Vibration Equations The couplingbetween the axial and transverse vibrations is neglectedand only the transverse vibration is considered The attitudedynamics for dynamic simulation can be obtained as followsbased on previous derivation by neglecting the action ofsolar-radiation pressure
4
3
1198681198631
119897+
1
51198971198681198601+
1
61198971198681198602+
31198681198632
2119897+
4120578119887119863
1199091199091
1198973
+6120578
119887119863
1199091199092
1198973+
41198631199091199091198811
1198973+
61198631199091199091198812
1198973+
271198601199091199091198812119882
2
2
81198973
+54119860
1199091199091198811119881
2
2
71198973+
181198601199091199091198811119882
2
2
71198973+
6119860119909119909119881
2
1
1198812
1198973
+2119860
1199091199091198812119882
2
1
1198973+
81198601199091199091198811119882
2
1
51198973+
8119860119909119909119881
3
1
51198973
+27119860
119909119909119881
3
2
81198973+
361198601199091199091198812119882
1119882
2
71198973+
41198601199091199091198811119882
1119882
2
1198973
minus 1198651198621
(119905) = 0
1
61198971198681198601+
3
2
1198681198631
119897+
1
71198971198681198602+
9
5
1198681198632
119897+
6120578119887119863
1199091199091
1198973
+12120578
119887119863
1199091199092
1198973+
61198631199091199091198811
1198973+
121198631199091199091198812
1198973+
91198601199091199091198812119882
2
2
21198973
+81119860
1199091199091198811119881
2
2
81198973+
271198601199091199091198811119882
2
2
81198973+
541198601199091199091198812119881
2
1
71198973
+18119860
1199091199091198812119882
2
1
71198973+
21198601199091199091198811119882
2
1
1198973+
9119860119909119909119881
3
2
21198973
+2119860
119909119909119881
3
1
1198973+
271198601199091199091198812119882
1119882
2
41198973+
361198601199091199091198811119882
1119882
2
71198973
minus 1198651198622
(119905) = 0
(56)
The following equations can be obtained by rearrangingthe above equations
4
3
1198681198631
119897+
1
51198971198681198601+
1
61198971198681198602+
31198681198632
2119897+
4120578119887119863
1199091199091
1198973
+6120578
119887119863
1199091199092
1198973+
41198631199091199091198811
1198973+
61198631199091199091198812
1198973+
16119860119909119909119881
3
1
51198973
+12119860
119909119909119881
2
1
1198812
1198973+
1081198601199091199091198811119881
2
2
71198973+
54119860119909119909119881
3
2
81198973
minus 1198651198621
(119905) = 0
1
61198971198681198601+
3
2
1198681198631
119897+
1
71198971198681198602+
9
5
1198681198632
119897+
6120578119887119863
1199091199091
1198973
+12120578
119887119863
1199091199092
1198973+
61198631199091199091198811
1198973+
121198631199091199091198812
1198973
+4119860
119909119909119881
3
1
1198973+
108119860119909119909119881
2
1
1198812
71198973+
811198601199091199091198811119881
2
2
41198973
+9119860
119909119909119881
3
2
1198973minus 119865
1198622(119905) = 0
(57)
1198651198621(119905) and 119865
1198622(119905) are used to represent all the generalized
external forces they can be used for vibration control Thesecomplicated equations abovementioned are the basis forobtaining the simplified equations used for controller design
The following equations can be obtained by neglecting thetwo and higher terms
4
3
1198681198631
119897+
1
51198971198681198601+
1
61198971198681198602+
31198681198632
2119897+
4120578119887119863
1199091199091
1198973
+6120578
119887119863
1199091199092
1198973+
41198631199091199091198811
1198973+
61198631199091199091198812
1198973= 119865
1198621
(119905)
14 Mathematical Problems in Engineering
1
61198971198681198601+
3
2
1198681198631
119897+
1
71198971198681198602+
9
5
1198681198632
119897+
6120578119887119863
1199091199091
1198973
+12120578
119887119863
1199091199092
1198973+
61198631199091199091198811
1198973+
121198631199091199091198812
1198973= 119865
1198622
(119905)
(58)
43 The Rigid-Flexible Coupled Dynamics The simplifiedattitude and vibration dynamics can be written as
119886120593 + 119886
120579
120579 + 119886120595 + 119886
1198811
1+ 119886
1198812
2= 119876
120593
119887120579
120579 + 119887120595 + 119887
120593 + 119887
1198811
1+ 119887
1198812
2= 119876
120579
119888120595 + 119888
120579
120579 + 119888120593 + 119888
1198811
1+ 119888
1198812
2= 119876
120595
119889
1198811
1+ 119889
1198812
2+ 119889
1198811
1+ 119889
1198812
2+ 119889
1198811
1198811
+ 1198891198812
1198812= 119876
1198811
119890
1198811
1+ 119890
1198812
2+ 119890
1198811
1+ 119890
1198812
2+ 119890
1198811
1198811
+ 1198901198812
1198812= 119876
1198812
(59)
The related coefficients in the preceding equation can befound in (A1) in the appendix The dynamics (see (59)) isnot suitable for attitude controller design because the controlinputs exist in some coefficients of the angular accelerationsThis will make the controller design rather difficult Thusthe following dynamic model is obtained by putting theterms including the control inputs right side of the dynamicequations
119869119909 minus 119898
1198971198972
1minus
4
5119898
1198971198972
2= 119876
120593+ 119906
119869119910
120579 +2
5119898
1198971198972
2+
1
2119898
1198971198972
1= 119876
120579+ 119906
120579
119869119911 minus
1
21198972
1198981198971minus
2
51198972
1198981198972= 119876
120595+ 119906
119889
1198811
1+ 119889
1198812
2+ 119889
1198811
1+ 119889
1198812
2
+ 1198891198811
1198811+ 119889
1198812
1198812= 119876
1198811
119890
1198811
1+ 119890
1198812
2+ 119890
1198811
1+ 119890
1198812
2
+ 1198901198811
1198811+ 119890
1198812
1198812= 119876
1198812
(60)
The expressions for 119906 119906
120579
and 119906are as
119906= minus119898
ℎ11199102
ℎ1
minus 119898ℎ21199112
ℎ2
+ 119898119901119903119901119909119903119901119911 minus 119898
1199011199032
119901119911
minus 1198981199011199032
119901119910
+ 119898119901119903119901119909119903119901119910
120579
119906
120579
= minus119898ℎ21199112
ℎ2
120579 minus 1198981199011199032
119901119911
120579 + 119898119901119903119901119910119903119901119911 + 119898
119901119903119901119909119903119901119910
minus 1198981199011199032
119901119909
120579
119906= minus119898
ℎ11199102
ℎ1
+ 119898119901119903119901119910119903119901119911
120579 minus 1198981199011199032
119901119910
minus 1198981199011199032
119901119909
+ 119898119901119903119901119909119903119901119911
(61)
119906 119906
120579
and 119906are the functions of the positions of sliding
masses and payload and the angular accelerations The statevariables in (60) are defined as
1199091= 120593 119909
2= 119909
3= 120579 119909
4= 120579
1199095= 120595 119909
6= 119909
7= 119881
1
1199098=
1 119909
9= 119881
2 119909
10=
2
(62)
Thedynamics (60) can bewritten as the state-spacemodelas following
1= 119909
2
2= 119886
11199097+ 119886
21199098+ 119886
31199099+ 119886
411990910
+ 119906120593
3= 119909
4
4= 119886
51199097+ 119886
61199098+ 119886
71199099+ 119886
811990910
+ 119906120579
5= 119909
6
6= 119886
91199097+ 119886
101199098+ 119886
111199099+ 119886
1211990910
+ 119906120595
7= 119909
8
8= 119886
131199097+ 119886
141199098+ 119886
151199099+ 119886
1611990910
+ 1199061198811
9= 119909
10
10
= 119886171199097+ 119886
181199098+ 119886
191199099+ 119886
2011990910
+ 1199061198812
(63)
where 119906120579 119906
120593 and 119906
120595are the generalized control inputs
for attitude control and 1199061198811
and 1199061198812
are the generalizedcontrol inputs for vibration control The controllability canbe satisfied by analyzing (63) The attitudevibration controlinputs and the coefficients will be presented later in thissection The form of a matrix differential equation can bewritten as follows for the above equation
x = Ax + Bu (64)
The expressions of the relatedmatrices and vectors can befound as
x = [1
2
3
4
5
6
7
8
9
10]119879 x (119905
0) = x
1199050
u = [119906120593 119906
120579 119906
120595 119906
1198811
1199061198812
]119879
u (1199050) is known
(65)
where A xB and u are the system matrix state variablesvector control matrix and control inputs vector respectively
Mathematical Problems in Engineering 15
The complexity of the state-space model can be seen bypresenting the detailed expressions of control inputs forattitudevibration and related parameters in (A2) in theappendix
5 AttitudeVibration Control and Simulation
The controller for the attitude and vibration is developedusing the LQR and optimal PI theory The dynamic simula-tion is performed based on the coupled dynamics derived inthe previous sections
51 LQR and Optimal PI Based Controllers Design Thedynamics for solar sail can bewritten as follows togetherwithits quadratic cost function also defined as
x = Ax + Bu x (1199050) = x
1199050
(known)
119869 =1
2int
infin
1199050
[x119879 (119905)Qx (119905) + u119879 (119905)Ru (119905)] 119889119905
(66)
whereQ = Q119879
⩾ 0 andR = R119879
gt 0 are constantThe control-lability of [AB] and the observability of [AD] can beensured when the equationDD119879
= Q holds for anymatrixDThe optimal control input ulowast(119905)within the scope of u(119905) isin R119903119905 isin [119905
0infin] can be computed as follows to make 119869minimum
ulowast (119905) = minusKxlowast (119905) K = Rminus1B119879P (67)
where P is the nonnegative definite symmetric solution of thefollowing Riccati algebraic equations
PA + A119879P minus PBRminus1B119879P +Q = 0 (68)
And the optimal performance index can be obtained asfollows for arbitrary initial states
119869lowast
[x (1199050) 119905
0] =
1
2x1198790
Px0 (69)
The closed-loop system
x = (A minus BRminus1B119879P) x (70)
is asymptotically stableFor an orbiting solar sail the primary disturbance torque
is by the cmcp offset and the impact of the tiny dust inthe deep space The state regulator can be used to controlthe dynamic system affected by pulse disturbance torquewith good steady-state errors but will never achieve accuratesteady-state errors if the dynamics is affected by constantdisturbance torque Thus the optimal state regulator withan integrator to eliminate the constant disturbance torqueshould be presented This optimal proportional-integral reg-ulator not only eliminates the constant disturbance torque butalso possesses the property of optimal regulator
Table 1 The related parameters
Parameters ValuesCMCP offsetm [0 017678 017678]119879
The side length of square sailm 100Nominal solar-radiation pressureconstant at 1 AU from the sunNm2 4563 times 10minus6
Solar-radiation pressure forceN 912 times 10minus2
Roll inertiakglowastm2 50383Pitch and yaw inertiakglowastm2 251915Outer radiusm 0229Thickness of the supporting beamm 75 times 10minus6
Youngrsquos modulus of the supportingbeamGPa 124
Moment of inertia of the cross-sectionof the supporting beamm4 2829412 times 10minus7
Bending stiffness of the supportingbeamNlowastm2 3508471336
Proportional damping coefficient ofsupporting beams 001
Line density of the supportingbeamkgm 0106879
Cross-sectional area of the supportingbeamm2 1079 times 10minus5
Roll disturbance torqueNlowastm 0Pitch (yaw) disturbance torqueNlowastm 0016122 (minus0016122)
For the following linear system with the correspondingperformance index
x = Ax + Bu x (1199050) = x
1199050
u (1199050) = u
1199050
119869 =1
2int
infin
1199050
(x119879Qx + u119879Ru + u119879Su) 119889119905(71)
where Q = Q119879
⩾ 0 R = R119879
gt 0 and S = S119879 gt 0 If [AB]is completely controllable and meanwhile [AD
11] is com-
pletely observable with the relationship D11D119879
11
= Q thesolution can be expressed as
ulowast = minusK1x minus K
2ulowast ulowast (119905
0) = u
1199050
(72)
If B119879B is full rank we can get
ulowast = minusK3x minus K
4x ulowast (119905
0) = u
1199050
(73)
K119894(119894 = 1 2 3 4) is the function of ABQR S
The closed-loop system
[xulowast] = [
A BminusK
1minusK
2
] [xulowast] [
[
x (1199050)
u (1199050)]
]
= [x1199050
u1199050
] (74)
is asymptotically stableThe compromise between the state variables (the angle
angular velocity the vibration displacement and velocity)and control inputs (the torque by all the actuators) can
16 Mathematical Problems in Engineering
0 2000 4000 6000
0 2000 4000 6000
0 2000 4000 6000minus5
0
5
minus5
0
5
minus5
0
5
minus4
minus2
0
2
4
times10minus4
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
00162
00164
00166
4800 4900 5000
4800 4900 5000
4800 4900 5000
minus00165
minus0016
Time (s) Time (s)
Time (s)
Time (s)
Time (s)
Time (s)
Roll
erro
r120593(∘
)
Roll
erro
r120593(∘
)
Pitc
h er
ror120579
(∘)
Pitc
h er
ror120579
(∘)
Yaw
erro
r120595(∘
)
Yaw
erro
r120595(∘
)
Figure 8 The roll pitch and yaw errors
be achieved by using both the LQR based and optimal PIbased controllers for the coupled attitudevibration dynamicsystem The fact is that the attitude control ability is limitedto the control torque by the control actuators The change ofthe attitude angles and rates should not be frequent to voidexciting vibrations
Thus the weighting matrix Q and the control weightingmatrix R are selected as follows for LQR based controller
Q (1 1) = 9 times 10minus6
Q (2 2) = 1 times 10minus6
Q (3 3) = 16 times 10minus6
Q (4 4) = Q (5 5) = Q (6 6) = Q (7 7) = Q (8 8)
= Q (9 9) = Q (10 10) = 1 times 10minus6
Q (119894 119895) = 0 (119894 = 119895 119894 119895 = 1 sim 10)
R (1 1) = R (2 2) = 900 R (3 3) = 100
R (4 4) = R (5 5) = 10000
R119894119895
= 0 (119894 = 119895 119894 119895 = 1 sim 5)
(75)
TheweightingmatrixQ and the control weightingmatrixR are selected as follows for the optimal PI based controller
Q (1 1) = Q (2 2) = 4 times 10minus8
Q (3 3) = Q (4 4) = Q (5 5) = Q (6 6) = Q (7 7)
= Q (8 8) = 16 times 10minus8
Mathematical Problems in Engineering 17
minus02
0
02
Roll
rate
(∘s)
Roll
rate
(∘s)
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Pitc
h ra
te(∘s)
Pitc
h ra
te(∘s)
0 1000 2000 3000 4000 5000
minus05
0
05
minus05
0
05
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
Time (s)
Yaw
rate
(∘
s)
Yaw
rate
(∘
s)
4800 4850 4900 4950 5000
Time (s)4800 4850 4900 4950 5000
Time (s)4800 4850 4900 4950 5000
minus2
0
2
minus2
0
2
minus2
0
2
times10minus4
times10minus4
times10minus4
Figure 9 The roll pitch and yaw rates
Q (9 9) = Q (10 10) = 1 times 10minus8
Q (119894 119895) = 0 (119894 = 119895 119894 119895 = 1 sim 10)
R (1 1) = R (2 2) = R (3 3) = 1 times 10minus8
R (4 4) = R (5 5) = 4 times 10minus8
R (119894 119895) = 0 (119894 = 119895 119894 119895 = 1 sim 5)
(76)
52 The Simulation Results The initial angle errors of rollpitch and yaw are adopted as 120593(119905
0) = 3
∘ 120579(1199050) = 3
∘ and120595(119905
0) = 3
∘ the initial angular velocity errors of roll pitchand yaw are adopted as (119905
0) = 0
∘
s 120579(1199050) = 0
∘
s and(119905
0) = 0
∘
s 1198811(1199050) = 01m 119881
2(1199050) = 01m
1(1199050) = 0ms
and 2(1199050) = 0ms are adopted in this paper for dynamic
simulationThe estimated cmcp offset is 025m for a 100 times 100m
square solar sail It is assumed that the components of cmcpoffset vector are [0 017678 017678]
119879 in the body frame
The relevant parameters for dynamic simulations are givenin Table 1
The dynamic simulation results are obtained as followsby using the LQR controller based on the abovementionedQ and R related parameters and initial conditions Thedynamics simulations with (denoted by ldquowith GFrdquo) andwithout (denoted by ldquowithout GFrdquo) considering the geo-metrical nonlinearity are presented And the correspondingdiscussions and analysis are also given according to thecalculated results
The roll pitch and yaw errors are presented based onthe dynamics models with and without considering thegeometrical nonlinearityThe control effect with zero steady-state error can be achieved for roll axis by referring tothe results But the steady-state errors exist for pitch andyaw axes from Figure 8 this is because there exist constantdisturbance torques for pitch and yaw axes caused by thecmcp offset Thus the LQR based controller cannot be usedfor attitude control with good steady-state performance Thesteady-state errors of pitch and yaw axes are about 0164
∘
and minus0164∘ respectively from the corresponding partial
enlarged drawing of the figures (see the corresponding left
18 Mathematical Problems in Engineering
minus20
0
20
Roll
torq
ue (N
lowastm
)
Roll
torq
ue (N
lowastm
)
minus50
0
50
minus50
0
50
Pitc
h to
rque
(Nlowast
m)
Pitc
h to
rque
(Nlowast
m)
0 1000 2000 3000 4000 5000
0 2000 4000 6000
0 2000 4000 6000
Yaw
torq
ue (N
lowastm
)
Yaw
torq
ue (N
lowastm
)
minus002
0
002
008
01
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
minus01
minus009
minus008
Time (s)Time (s)
Time (s)Time (s)
Time (s)Time (s)
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Figure 10 The roll pitch and yaw torques
figures) A simple and practical controller should be designedto eliminate the steady-state errorsThese errorswill affect theprecision of the super long duration space mission deeply
The differences between the dynamics with and withoutthe geometrical nonlinearity effect can be observed Theamplitudes and phases change a bit by comparing the corre-sponding results
It can be observed by the partial enlarged figures(the right figures of Figure 9) that there are no steady-stateerrors for roll pitch and yaw rates The relative satisfieddynamic performance is achieved In fact a result with muchmore satisfied dynamic performance can be obtained but itwill make the desired control torques much larger duringthe initial period This will not only excite the vibration ofthe structure but also increase the burden of the controlactuators
And the differences between the dynamics models withand without the geometrical nonlinearity can also be seenmerely in the phase of the angular velocities
The desired attitude control torques are presented inFigure 10 The roll torque will tend to be zero with thedecrement of the state variable errors The pitch and yawtorques tend to be constant from the middle and bottom
figures The pitch and yaw steady-state errors can never beeliminated although the pitch and yaw torques (009Nlowastmand minus009Nlowastm) are applied continuously by theoreticalanalysis and simulations This is just a great disadvantage ofthe LQR based controller in this paper The initial controltorques can be afforded by vibrating the gimbaled controlboom andmoving the slidingmasses that can afford a relativelarge torque The control vanes can be used to afford thecontrol torques when solar sail is in steady-state process Theexpression of the attitude control inputs 119906
120593 119906
120579 and 119906
120595can be
found in previous sectionMoreover the differences between dynamics responses
with and without geometrical nonlinearity can also beobserved by comparing the corresponding results Therequired torques for the attitude control are a little largerfor the dynamics with geometrical nonlinearity And thedifference in the phase is also clear
It can be seen that the vibration of the supporting beamis depressed effectively by the simulation results in Figure 11It can be seen that the steady-state errors and the dynamicperformance are relatively satisfied It can also be seen that thedynamics responses between the model with and without the
Mathematical Problems in Engineering 19
0 1000 2000 3000 4000 5000
0 1000 2000 3000 4000 5000
minus01
0
01
minus02
0
02
Time (s) Time (s)
Time (s) Time (s)
minus5
0
5
times10minus4
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
minus1
0
1
times10minus3
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
The d
ispla
cem
ent o
f the
tip
(m)
The d
ispla
cem
ent o
f the
tip
(m)
The v
eloci
ty o
f the
tip
(ms
)
The v
eloc
ity o
f the
tip
(ms
)
Figure 11 The displacement and velocity of the tip of the supporting beam
geometrical nonlinearity effect are different in the vibrationdisplacement and velocitymagnitudes and phases (Figure 15)
The simulation results can be obtained as follows by usingthe optimal PI based controller adopting the abovementionedparameters and initial conditions
The roll pitch and yaw errors are given by using theoptimal PI based controller These errors tend to disappearby observing the partially enlarged plotting of the figure (thecorresponding right figures) (shown in Figure 12) And therelative satisfied dynamic performance can also be obtainedFrom the view of eliminating the steady-state errors the opti-mal PI based controller performs better than the LQR basedcontroller by theoretical analysis and simulation results Theformer can achieve attitude control results without pitchand yaw steady-state errors From the view of dynamicperformance both the controllers perform well In additionit can be seen that the difference between the modelswith and without geometrical nonlinearity is merely inthe phase
The roll pitch and yaw rate errors are presented inFigure 13 The dynamic and steady-state performances aresatisfied by observing the simulation results And by observ-ing the difference between the dynamics responses with and
without the influence by the geometrical nonlinearity it canbe concluded that the merely difference is the phase
The desired control torques of the roll pitch and yaw areobtained in Figure 14 by using the optimal PI based controllerIt can be seen that the value of the desired roll control torquedecreases to zero as the values of the roll angle and ratedecrease to zero The desired pitch and yaw control torquestend to be the constant values 009Nlowastm and minus009Nlowastmrespectively The desired initial control torques are large byobserving Figure 14 It is suggested that the gimbaled controlboom combining the sliding masses is adopted to afford theinitial torque Then the control vanes can be used to controlthe solar sail after the initial phase The phase differencecan also be observed by inspecting the dynamics responsesduring the 4800sim5000 s period
The vibration can be controlled effectively based on theoptimal PI controller And the relative satisfied dynamicand steady-state performances can be achieved In additionthe tiny differences exist in the magnitudes of the requiredtorques And the phase differences also exist
It can be concluded as follows by analyzing and compar-ing the simulation results based on the LQR and optimal PItheories in detail
20 Mathematical Problems in Engineering
Roll
erro
r120593(∘
)
Roll
erro
r120593(∘
)
minus5
0
5
minus5
0
5
Pitc
h er
ror120579
(∘)
Pitc
h er
ror120579
(∘)
0 1000 2000 3000 4000 5000minus10
0
10
Time (s) Time (s)
Time (s)
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
Yaw
erro
r120595(∘
)
Yaw
erro
r120595(∘
)
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
minus1
0
1
times10minus3
minus1
0
1
times10minus3
minus1
0
1
times10minus3
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Figure 12 The roll pitch and yaw errors
(1) From the view of eliminating the steady-state errorsof the pitch and yaw errors the optimal PI based con-troller performs better than the LQR based controllerby theoretical analysis and simulation results Thedynamic performances of the two controllers are bothsatisfied and the desired control torques are relativelysmall
(2) The weighting of the state variables is reflected by theweighting matrix according to the LQR and optimalPI theories The constant weighting matrices selectedin this paper can effectively reflect the initial statevariable errors but maybe reflect the final state vari-able errors deficiently The time-varying weightingmatrices should be selected
(3) For the actual orbiting solar sail the control actuators(control vanes gimbaled control boom and slidingmasses) cannot afford excessive large control torquesThus the control torques should be as small as possibleon the premise of acquiring satisfied dynamic perfor-mance and steady-state errors It will not only reducethe burden of the control actuators but also avoid
exciting structural vibration In engineering practicethe weighting matrices and the control weightingmatrices should be selected based on the attitudecontrol requirement (eg dynamic performance andsteady-state errors etc)
(4) The dynamics responses influenced by the geometri-cal nonlinearity can be observed In a word the tinydifferences between the magnitudes of the physicalvariables exist for the models with and withoutthe geometrical nonlinearity And the relative cleardifferences exist in the phases for the attitude anglesrates required torques and so forth
6 Conclusions
The coupled attitude and structural dynamics is establishedfor the highly flexible sailcraft by using the von-Karman von-Karmanrsquos nonlinear strain-displacement relationships basedon assumptions of large deflections moderate rotationsand
Mathematical Problems in Engineering 21
Roll
rate
erro
r(∘ s
)
Roll
rate
erro
r(∘ s
)
minus01
0
01
minus01
0
01
Pitc
h ra
te er
ror (
∘ s)
Pitc
h ra
te er
ror (
∘ s)
0 1000 2000 3000 4000 5000minus02
0
02
Yaw
rate
erro
r (∘ s
)
Yaw
rate
erro
r (∘ s
)
4800 4850 4900 4950 5000
minus5
0
5times10minus4
minus5
0
5
times10minus4
minus5
0
5times10minus4
Time (s)
4800 4850 4900 4950 5000
Time (s)
4800 4850 4900 4950 5000
Time (s)
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Figure 13 The roll pitch and yaw rate errors
small strains The Lagrange equation method is utilizedto derive the dynamics for controller design and dynamicsimulation The LQR and optimal PI based controllers aredesigned for the dynamics with the constant disturbancetorque caused by the cmcp offset By theoretical analysisand simulation it can be seen that both controllers cancompromise between the state variables and control inputsBecause the control actuators can hardly afford large controltorque the dynamic performance should be relaxed toreduce the requirement for the attitude control actuatorsBesides the optimal PI based controller can also eliminatethe constant disturbance torque caused by the cmcp offsetthat always exists while the LQR based controller fails toachieve the results with satisfied steady-state performancealthough the attitude control torque is always applied to thecoupled dynamic systemThe dynamics simulations with andwithout the geometrical nonlinearity effect are also carriedout And the differences between the models in magnitudesand phases are identified and analyzed It can be concludedthat the optimal PI based controller performs better than the
LQRbased controller from the viewof eliminating the steady-state error caused by the disturbance torque by the cmcpoffset
Appendix
The related parameters in above equation are given as
119886120593= 119869
119909+ 119898
ℎ11199102
ℎ1
+ 119898ℎ21199112
ℎ2
+ 1198981199011199032
119901119911
+ 1198981199011199032
119901119910
119886120579= minus 119898
119901119903119901119909119903119901119910 119886
120595= minus119898
119901119903119901119909119903119901119911
1198861198811
= minus 1198981198971198972
1198861198812
= minus4
5119898
1198971198972
119887120579= 119869
119910+ 119898
ℎ21199112
ℎ2
+ 1198981199011199032
119901119911
+ 1198981199011199032
119901119909
119887120595= minus 119898
119901119903119901119910119903119901119911 119887
120593= minus119898
119901119903119901119909119903119901119910
22 Mathematical Problems in Engineering
Roll
torq
ue (N
lowastm
)
Roll
torq
ue (N
lowastm
)
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
0 2000 4000 6000
0 2000 4000 6000
0 2000 4000 6000
Time (s)
Time (s)
Time (s)
Time (s)
Time (s)
Time (s)4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
minus01
minus008
008
009
01
minus002
0
002
minus5
0
5
minus2
0
2
Pitc
h to
rque
(Nlowast
m)
Pitc
h to
rque
(Nlowast
m)
minus2
0
2
Yaw
torq
ue (N
lowastm
)
Yaw
torq
ue (N
lowastm
)
Figure 14 The roll pitch and yaw torques
1198871198811
=1
2119898
1198971198972
1198871198812
=2
5119898
1198971198972
119888120595= 119869
119911+ 119898
ℎ11199102
ℎ1
+ 1198981199011199032
119901119910
+ 1198981199011199032
119901119909
119888120579= minus 119898
119901119903119901119910119903119901119911 119888
120593= minus119898
119901119903119901119909119903119901119911
1198881198811
= minus1
21198972
119898119897 119888
1198812
= minus2
51198972
119898119897
119889
1198811
= (4
3
119868119863
119897+
1
5119897119868119860) 119889
1198812
= (1
6119897119868119860+
3119868119863
2119897)
119889
1198811
=4120578
119887119863
119909119909
1198973 119889
1198812
=6120578
119887119863
119909119909
1198973
1198891198811
=4119863
119909119909
1198973 119889
1198812
=6119863
119909119909
1198973
1198761198811
= 1198651198621
(119905)
119890
1198811
= (3
2
119868119863
119897+
1
6119897119868119860)
119890
1198812
= (1
7119897119868119860+
9
5
119868119863
119897) 119890
1198811
=6120578
119887119863
119909119909
1198973
119890
1198812
=12120578
119887119863
119909119909
1198973 119890
1198811
=6119863
119909119909
1198973
1198901198812
=12119863
119909119909
1198973 119876
1198812
= 1198651198622
(119905)
(A1)
The detailed expressions of control inputs for attitudevibration and related parameters in the state-space model ofthe dynamics (see (62) and (63)) are presented as follows
A =
[[[[[[[[[[[[[[
[
0 1 0 0 0 0 0 0 0 0
0 0 0 0 0 0 1198861
1198862
1198863
1198864
0 0 0 1 0 0 0 0 0 0
0 0 0 0 0 0 1198865
1198866
1198867
1198868
0 0 0 0 0 1 0 0 0 0
0 0 0 0 0 0 1198869
11988610
11988611
11988612
0 0 0 0 0 0 0 1 0 0
0 0 0 0 0 0 11988613
11988614
11988615
11988616
0 0 0 0 0 0 0 0 0 1
0 0 0 0 0 0 11988617
11988618
11988619
11988620
]]]]]]]]]]]]]]
]
Mathematical Problems in Engineering 23
0 1000 2000 3000 4000 5000
0 1000 2000 3000 4000 5000
minus01
0
01
minus02
0
02
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Time (s)
Time (s)Time (s)
Time (s)
minus1
0
1
minus1
0
1
times10minus3
times10minus3Th
e disp
lace
men
t of t
he ti
p (m
)
The d
ispla
cem
ent o
f the
tip
(m)
The v
eloci
ty o
f the
tip
(ms
)
The v
eloci
ty o
f the
tip
(ms
)
Figure 15 Vibration displacement and velocity of the tip
B =
[[[[[[[[[[[[[[
[
0 0 0 0 0
1 0 0 0 0
0 0 0 0 0
0 1 0 0 0
0 0 0 0 0
0 0 1 0 0
0 0 0 0 0
0 0 0 1 0
0 0 0 0 0
0 0 0 0 1
]]]]]]]]]]]]]]
]
1198861= minus
1198981198971198972
119869119909
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus4
5119869119909
1198981198971198972
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198862= minus
1198981198971198972
119869119909
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus4
5119869119909
1198981198971198972
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198863= minus
1198981198971198972
119869119909
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus4
5119869119909
1198981198971198972
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198864= minus
1198981198971198972
119869119909
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus4
5119869119909
1198981198971198972
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
119906120593=
119876120593
119869119909
+
119906
119869119909
+119898
1198971198972
119869119909
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+4
5119869119909
1198981198971198972
+
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198865=
1
2119869119910
1198981198971198972
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+2
5119869119910
1198981198971198972
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198866=
1
2119869119910
1198981198971198972
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+2
5119869119910
1198981198971198972
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198867=
1
2119869119910
1198981198971198972
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+2
5119869119910
1198981198971198972
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198868=
1
2119869119910
1198981198971198972
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
24 Mathematical Problems in Engineering
+2
5119869119910
1198981198971198972
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
119906120579=
119876120579
119869119910
+119906
120579
119869119910
minus1
2119869119910
1198981198971198972
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119910
1198981198971198972
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198869= minus
1
2119869119911
1198972
119898119897
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988610
= minus1
2119869119911
1198972
119898119897
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988611
= minus1
2119869119911
1198972
119898119897
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988612
= minus1
2119869119911
1198972
119898119897
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
119906120595=
119876120595
119869119911
+
119906
119869119911
+1
2119869119911
1198972
119898119897
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+2
5119869119911
1198972
119898119897
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988613
= minus
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988614
= minus
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988615
= minus
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988616
= minus
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
1199061198811
=
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988617
= minus
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988618
= minus
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988619
= minus
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988620
= minus
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1199061198812
=
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(A2)
Conflict of Interests
The authors declare that there is no conflict of interestsregarding the publication of this paper
Acknowledgments
The authors would like to thank the anonymous reviewers fortheir critical and constructive review of the paper This studywas cosupported by the National Natural Science Foundationof China (Project no 11302134 11272101)
References
[1] M Colin Solar Sailing Technology Dynamics and MissionApplications Springer-Praxis London UK 1st edition 1999
[2] V Lappas SWokesM Leipold A Lyngvi and P Falkner ldquoGui-dance and control for an Interstellar Heliopause Probe (IHP)solar sail mission to 200 AUrdquo in Proceedings of the AIAAGuidance Navigation and Control Conference and Exhibit pp2472ndash2492 San Francisco Calif USA August 2005
[3] L Charlotte C Camilla and C McInnes ldquoSolar radiation pres-sure augmented deorbiting fromhigh altitude sun-synchronousorbitsrdquo in Proceedings of the 4S Symposium 2012 Small SatellitesSystems and Services Portoroz Slovenia 2012
[4] M Ceriotti and C RMcInnes ldquoGeneration of optimal trajecto-ries for Earth hybrid pole sittersrdquo Journal of Guidance Controland Dynamics vol 34 no 3 pp 847ndash859 2011
[5] S Gong J Li andH Baoyin ldquoSolar sail transfer trajectory fromL1 point to sub-L1 pointrdquoAerospace Science and Technology vol15 no 7 pp 544ndash554 2011
[6] S Gong J Li and H Baoyin ldquoAnalysis of displaced solar sailorbits with passive controlrdquo Journal of Guidance Control andDynamics vol 31 no 3 pp 782ndash785 2008
[7] S Gong H Baoyin and J Li ldquoSolar sail three-body transfertrajectory designrdquo Journal of Guidance Control and Dynamicsvol 33 no 3 pp 873ndash886 2010
Mathematical Problems in Engineering 25
[8] S Gong J Li H Baoyin and J Simo ldquoA new solar sail orbitrdquoScience China Technological Sciences vol 55 no 3 pp 848ndash8552012
[9] Y Tsuda O Mori R Funase et al ldquoAchievement of IKAROS-Japanese deep space solar sail demonstration missionrdquo ActaAstronautica vol 82 no 2 pp 183ndash188 2013
[10] L Johnson MWhorton A Heaton R Pinson G Laue and CAdams ldquoNanoSail-D a solar sail demonstration missionrdquo ActaAstronautica vol 68 no 5-6 pp 571ndash575 2011
[11] B Wie and D Murphy ldquoSolar-sail attitude control design for asail flight validation missionrdquo Journal of Spacecraft and Rocketsvol 44 no 4 pp 809ndash821 2007
[12] B Wie D Murphy M Paluszek and S Thomas ldquoRobust atti-tude control systems design for solar sails part 1 propellantlessprimaryACSrdquo inProceedings of the AIAAGuidance Navigationand Control Conference and Exhibit Providence RI USAAugust 2004
[13] B Wie D Murphy M Paluszek and S Thomas ldquoRobust atti-tude control systems design for solar sails part 2 MicroPPT-based secondary ACSrdquo in Proceedings of the AIAA GuidanceNavigation and Control Conference and Exhibit pp 1325ndash1340Providence RI USA August 2004
[14] S Thomas M Paluszek B Wie and D Murphy ldquoAOCS per-formance and stability validation for large flexible solar sailspacecraftrdquo in Proceedings of the 41st AIAAASMESAEASEEJoint Propulsion Conference amp Exhibit Tucson Ariz USA 2005
[15] B Wie ldquoDynamic modeling and attitude control of solar sailspacecraft part Irdquo in Proceedings of the AIAAGuidance Naviga-tion and Control Conference and Exhibit Monterey Calif USAAugust 2002
[16] BWie ldquoSolar sail attitude control and dynamics part 1rdquo Journalof Guidance Control and Dynamics vol 27 no 4 pp 526ndash5352004
[17] B Wie ldquoDynamic modeling and attitude control of solar sailspacecraft part IIrdquo in Proceedings of the AIAA Guidance Nav-igation and Control Conference and Exhibit Monterey CalifUSA August 2002
[18] BWie ldquoSolar sail attitude control and dynamics part 2rdquo Journalof Guidance Control and Dynamics vol 27 no 4 pp 536ndash5442004
[19] C Luo and J-H Zheng ldquoSolar-sail attitude control based onmoving masses and roll stabilizer barsrdquo Journal of HarbinInstitute of Technology vol 43 no 3 pp 95ndash101 2011
[20] D Romagnoli and T Oehlschlagel ldquoHigh performance twodegrees of freedom attitude control for solar sailsrdquo Advances inSpace Research vol 48 no 11 pp 1869ndash1879 2011
[21] C Scholz D Romagnoli B Dachwald and S Theil ldquoPerfor-mance analysis of an attitude control system for solar sails usingsliding massesrdquo Advances in Space Research vol 48 no 11 pp1822ndash1835 2011
[22] A Bolle and C Circi ldquoSolar sail attitude control through in-plane moving massesrdquo Journal of Aerospace Engineering vol222 no 1 pp 81ndash94 2008
[23] M RotunnoM Basso A B Pome andM Sallusti ldquoA compari-son of robust attitude control techniques for a solar sail space-craftrdquo in Proceedings of the AIAA Guidance Navigation andControl Conference and Exhibit San Francisco Calif USA2005
[24] J Zhang K Zhai and T Wang ldquoControl of large angle maneu-vers for the flexible solar sailrdquo Science China Physics Mechanicsand Astronomy vol 54 no 4 pp 770ndash776 2011
[25] J Zhang andTWang ldquoCoupled attitude-orbit control of flexiblesolar sail for displaced solar orbitrdquo Journal of Spacecraft andRockets vol 50 no 3 pp 675ndash685 2013
[26] Q Li XMa and TWang ldquoReducedmodel for flexible solar saildynamicsrdquo Journal of Spacecraft and Rockets vol 48 no 3 pp446ndash453 2011
[27] M Polites J Kalmanson and D Mangus ldquoSolar sail attitudecontrol using small reaction wheels and magnetic torquersrdquoProceedings of the Institution of Mechanical Engineers G Journalof Aerospace Engineering vol 222 no 1 pp 53ndash62 2008
[28] H-T Cui J-H Luo J-H Feng and P-Y Cui ldquoAttitudecontrol of solar sail spacecraft with control boomrdquo Journal ofAstronautics vol 29 no 2 pp 560ndash566 2008
[29] E Mettler and S R Ploen ldquoSolar sail dynamics and controlusing a boom mounted bus articulated by a bi-state two-axisgimbal and reaction wheelsrdquo in Proceedings of the AIAAAASAstrodynamics Specialist Conference and Exhibit MontereyCalif USA August 2002
[30] J Luo X Li and J Feng ldquoPassive attitude control of solar sailspacecraftrdquo Flight Dynamics vol 26 no 5 pp 47ndash50 2008
[31] J Luo Study on attitude control of solar sail spaceraft [PhDthesis] School of Astronautics Harbin Institute of TechnologyHarbin China 2007
[32] D A Lawrence and S W Piggott ldquoIntegrated trajectory andattitude control for a four-vane solar sailrdquo in Proceedings ofthe AIAA Guidance Navigation and Control Conference andExhibit pp 2416ndash2431 San Francisco Calif USA August 2005
[33] E Mettler A B Acikmese and S R Ploen ldquoAttitude dynamicsand control of solar sails with articulated vanesrdquo in Proceedingsof the AIAA Guidance Navigation and Control Conference andExhibit pp 2396ndash2415 San Francisco Calif USA August 2005
[34] S N Adeli V J Lappas and B Wie ldquoA scalable bus-basedattitude control system for Solar Sailsrdquo Advances in SpaceResearch vol 48 no 11 pp 1836ndash1847 2011
[35] R Funase Y Shirasawa Y Mimasu et al ldquoOn-orbit verificationof fuel-free attitude control system for spinning solar sailutilizing solar radiation pressurerdquo Advances in Space Researchvol 48 no 11 pp 1740ndash1746 2011
[36] B Fu and F O Eke ldquoAttitude control methodology for largesolar sailsrdquo in AIAA Guidance Navigation and Control (GNC)Conference 2013
[37] J Liu N Cui F Shen and S Rong ldquoDynamics of highly-flexiblesolar sail subjected to various forcesrdquoActaAstronautica vol 103pp 55ndash72 2014
[38] J F Liu S Y Rong and J G Li ldquoAttitude dynamics modelingand control of large flexible solar sail spacecraftrdquo in Proceedingsof the 3rd International Symposium on Systems and Control inAeronautics and Astronautics (ISSCAA rsquo10) pp 243ndash247 IEEEPublications Piscataway NJ USA 2010
[39] S Gong H Baoyin and J Li ldquoCoupled attitude-orbit dynamicsand control for displaced solar orbitsrdquo Acta Astronautica vol65 no 5-6 pp 730ndash737 2009
Submit your manuscripts athttpwwwhindawicom
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
MathematicsJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Mathematical Problems in Engineering
Hindawi Publishing Corporationhttpwwwhindawicom
Differential EquationsInternational Journal of
Volume 2014
Applied MathematicsJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Probability and StatisticsHindawi Publishing Corporationhttpwwwhindawicom Volume 2014
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Mathematical PhysicsAdvances in
Complex AnalysisJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
OptimizationJournal of
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International Journal of
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Operations ResearchAdvances in
Journal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Function Spaces
Abstract and Applied AnalysisHindawi Publishing Corporationhttpwwwhindawicom Volume 2014
International Journal of Mathematics and Mathematical Sciences
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
The Scientific World JournalHindawi Publishing Corporation httpwwwhindawicom Volume 2014
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Algebra
Discrete Dynamics in Nature and Society
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
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Decision SciencesAdvances in
Discrete MathematicsJournal of
Hindawi Publishing Corporationhttpwwwhindawicom
Volume 2014 Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Stochastic AnalysisInternational Journal of
Mathematical Problems in Engineering 9
The single underlined terms in the preceding equationindicate the contribution by the geometrical nonlinearityThedynamics models and corresponding numerical simulationwithout considering the geometrical nonlinearity can beobtained and carried out by neglecting these terms
34 The Energies and Works Done by External Forces Thestrain energy can be derived as
119880119894=
1
2int
119897
0
119860119909119909
[120597119906
0
120597119909+
1
2(120597V
0
120597119909)
2
+1
2(120597119908
0
120597119909)
2
]
2
+ 119863119909119909
1205972V
0
1205971199092
+ 119863119909119909
1205972
1199080
1205971199092
119889119909
(35)
For an isotropic support beam the extensional stiffness119860
119909119909and bending stiffness119863
119909119909can be computed as
119860119909119909
= int119860
119864119889119860 119863119909119909
= int119860
1198641199112
119889119860 = int119860
1198641199102
119889119860 (36)
The dissipation function is as
Ψ119902=
1
2int
119897
0
[119860119909119909120578119887(120597
0
120597119909)
2
+ 119863119909119909120578119887(1205972V
0
1205971199092
)
2
+ 119863119909119909120578119887(1205972
0
1205971199092
)
2
]119889119909
(37)
The kinetic energy for the support beam is as
119879119890=
1
2int
119897
0
[119868119860(120597119906
0
120597119905)
2
+ 119868119860(120597119908
0
120597119905)
2
+ 119868119863(1205972
1199080
120597119909120597119905)
2
+ 119868119860(120597V
0
120597119905)
2
+ 119868119863(
1205972V
0
120597119909120597119905)
2
]119889119909
(38)
where 119868119860and 119868
119863are integration constant for the support
beam expressed as
119868119860= int
119860
120588119889119860 = 120588119860 119868119863= int
119860
1205881199112
119889119860 = int119860
1205881199102
119889119860 (39)
And the work done by the external force can be obtainedas119882 = 119865
119862119911sdot 119908 (119909
119888 119905) + 119865
119862119910sdot V (119909
119888 119905) + 119898
ℎ119886ℎ119910
(119909ℎ 119905) V (119909
ℎ 119905)
+ 119898ℎ119886ℎ119911
(119909ℎ 119905) 119908 (119909
ℎ 119905) + int
119897
0
119902 (119909) V (119909 119905) 119889119909
(40)where 119909
119888represents the position of the support beam
119908(119909119888 119905) V(119909
119888 119905) are the displacements along 119911 and 119910 direc-
tions respectively and the corresponding loads 119865119862119911 119865
119862119910are
known functions 119909ℎ 119897 and V
ℎare the position coordinate of
the sliding mass the length of the support beam and theconstant-velocity of the sliding mass The dynamic responseis studied only during the period [0 119897V
ℎ] 119898
ℎis the mass
and 119886ℎ119910(119909
ℎ 119905) and 119886
ℎ119911(119909
ℎ 119905) are the components of the
acceleration for a material point on the support beam theslidingmass just arrived at And the corresponding transversedeflections are 119908(119909
ℎ 119905) and V(119909
ℎ 119905) respectively
35 The Assumed Modes Method The axial displacement1199060(119909 119905) and the transverse deflections V
0(119909 119905) and119908
0(119909 119905) can
be represented as follows by considering the assumed modesmethod
1199060(119909 119905) =
infin
sum
119894=1
119880119894(119909)119880
119894(119905)
V0(119909 119905) =
infin
sum
119895=1
119881119895(119909) 119881
119895(119905)
1199080(119909 119905) =
infin
sum
119896=1
119882119896(119909)119882
119896(119905)
(41)
where 119880119894(119905) 119881
119895(119905) and 119882
119896(119905) are the time-dependent gen-
eralized coordinates and 119880119894(119909) 119881
119895(119909) and 119882
119896(119909) are the
assumedmodes For assumedmodemethod themode shapefunctions should satisfy the following requirements in thispaper
119880119894(119909)
1003816100381610038161003816119909=0= 0 119881
119895(119909)
10038161003816100381610038161003816119909=0= 0 119882
119896(119909)
1003816100381610038161003816119909=0= 0
1198811015840
119895
(119909)10038161003816100381610038161003816119909=0
= 0 1198821015840
119896
(119909)10038161003816100381610038161003816119909=0
= 0
(42)
The following first two assumed modes satisfying theassumed mode principle are used in this paper
1198801(119909) =
119909
119897 119880
2(119909) = (
119909
119897)
2
1198811(119909) = (
119909
119897)
2
1198812(119909) = (
119909
119897)
3
1198821(119909) = (
119909
119897)
2
1198822(119909) = (
119909
119897)
3
(43)
With the help of the assumedmodes the detailed expres-sions of 119880
119894 119879
119890119882
119911 and Ψ
119902can be obtained as
119880119894=
9
2
119860119909119909
1198973(119881
2
2
+ 1198822
2
)2
+27
4
119860119909119909
1198973(119881
11198812+ 119882
1119882
2)
times (1198812
2
+ 1198822
2
)
+18
7
119860119909119909
1198973[(119881
2
1
+ 1198822
1
) (1198812
2
+ 1198822
2
) + (11988111198812+ 119882
1119882
2)2
]
+119860
119909119909
1198973[3
2119897119880
2(119881
2
2
+ 1198822
2
) + (1198812
1
+ 1198822
1
)
times (11988111198812+ 119882
1119882
2)]
10 Mathematical Problems in Engineering
+1
10
119860119909119909
1198973[9119880
1119897 (119881
2
2
+ 1198822
2
) + 241198802119897 (119881
11198812+ 119882
1119882
2)
+ 4 (1198812
1
+ 1198822
1
)2
]
+119860
119909119909
1198972[3
21198801(119881
11198812+ 119882
1119882
2) + 119880
2(119881
2
1
+ 1198822
1
)]
+6119863
119909119909119881
2
2
1198973+ 119860
119909119909(2119880
1119881
2
1
31198972+
21198801119882
2
1
31198972+
21198802
2
3119897)
+6119863
119909119909119882
2
2
1198973+
611986311990911990911988111198812
1198973+
11986011990911990911988011198802
119897+
6119863119909119909119882
1119882
2
1198973
+119860
119909119909119880
2
1
2119897+
2119863119909119909119881
2
1
1198973+
2119863119909119909119882
2
1
1198973
119879119890=
1
14(119897119868
119860
2
2
+ 119897119868119860
2
2
) +1
6(119897119868
119860
1
2+ 119897119868
11986012)
+1
10(119897119868
119860
2
2
+ 119897119868119860
2
1
+9119868
119863
2
2
119897+ 119897119868
119860
2
1
+9119868
119863
2
2
119897)
+1
4(119897119868
11986012+
6119868119863
1
2
119897+
611986811986312
119897)
+1
6(119897119868
119860
2
1
+4119868
119863
2
1
119897+
4119868119863
2
1
119897)
119882119911= 119865
119862119911sdot [119882
1(119905) + 119882
2(119905)] + 119865
119862119910sdot [119881
1(119905) + 119881
2(119905)]
+ 119898ℎ[2V2
ℎ
1198972sdot 119881
1(119905) +
4V2ℎ
119905
1198972sdot
1(119905) + (
Vℎ119905
119897)
2
sdot 1(119905)
+6V3
ℎ
119905
1198973sdot 119881
2(119905) +
6V3ℎ
1199052
1198973
sdot 2(119905) + (
Vℎ119905
119897)
3
sdot 2(119905)]
times [(Vℎ119905
119897)
2
sdot 1198811(119905) + (
Vℎ119905
119897)
3
sdot 1198812(119905)]
+ 119898ℎ[2V2
ℎ
1198972sdot 119882
1(119905) +
4V2ℎ
119905
1198972sdot
1(119905) + (
Vℎ119905
119897)
2
sdot 1(119905)
+6V3
ℎ
119905
1198973sdot 119882
2(119905) +
6V3ℎ
1199052
1198973sdot
2(119905)
+ (Vℎ119905
119897)
3
sdot 2(119905)]
times [(Vℎ119905
119897)
2
sdot 1198821(119905) + (
Vℎ119905
119897)
3
sdot 1198822(119905)]
+ 1198811(119905) sdot int
119897
0
119902 (119909) (119909
119897)
2
119889119909 + 1198812(119905)
sdot int
119897
0
119902 (119909) (119909
119897)
3
119889119909
Ψ119902=
1
6(36119863
119909119909120578119887
2
2
1198976+
4119860119909119909120578119887
2
2
1198974+
36119863119909119909120578119887
2
2
1198976) 119897
3
+1
4(4119860
11990911990912057811988712
1198973+
2411986311990911990912057811988712
1198975
+24119863
119909119909120578119887
1
2
1198975) 119897
2
+1
2
119860119909119909120578119887
2
1
119897+
2119863119909119909120578119887
2
1
1198973+
2119863119909119909120578119887
2
1
1198973
(44)
36 The Vibration Equation The Lagrange equation methodis used to derive the vibration equations
120597119871
120597119902119899
minus119889
119889119905(
120597119871
120597 119902119899
) + 119876119889= 0 119899 = 1 2 6 (45)
where 119871 is the Lagrange function 119902119899
= (1198801 119880
2 119881
1 119881
2
1198821119882
2)119879 is the vector of the generalized coordinates and
119902119899is the corresponding generalized velocity vector 119876
119889is the
generalized damping force The expressions for 119871 and 119876119889are
as
119871 = 119879119890minus (119880
119894minus 119882
119911)
119876119889= minus
120597Ψ119902
120597 119902119899
(119899 = 1 sim 6)
(46)
The axial vibration equations can be obtained as followsfor 119880
1 119880
2
1
31198971198681198601+
1
41198971198681198602+
120578119887119860
1199091199091
119897+
120578119887119860
1199091199092
119897+
1198601199091199091198801
119897
+119860
1199091199091198802
119897+
2119860119909119909119881
2
1
31198972+
311986011990911990911988111198812
21198972+
9119860119909119909119881
2
2
101198972
+2119860
119909119909119882
2
1
31198972+
3119860119909119909119882
1119882
2
21198972+
9119860119909119909119882
2
2
101198972= 0
(47a)
1
41198971198681198601+
1
51198971198681198602+
120578119887119860
1199091199091
119897+
4120578119887119860
1199091199092
3119897
+119860
1199091199091198801
119897+4119860
1199091199091198802
3119897+119860
119909119909119881
2
1
1198972+12119860
11990911990911988111198812
51198972+3119860
119909119909119881
2
2
21198972
+119860
119909119909119882
2
1
1198972+
12119860119909119909119882
1119882
2
51198972+
3119860119909119909119882
2
2
21198972= 0
(47b)
The following can be seen from the above equations
(1) Since the assumed modes rather than the naturalmodes are used the coupling between axial and trans-verse vibrations is rather severe for axial vibrations
Mathematical Problems in Engineering 11
(2) The nonlinearity is apparent in above equations onlyexisting in the terms of 119881
1 119881
2119882
1119882
2 We take (47a)
as an exampleThe terms including1198802and its first and
second derivative 1198811 119881
2119882
1119882
2 can be regarded as
the applied loads for 1198801
(3) The coupling between the axial and transverse vibra-tionswill disappear as long as the linear displacement-strain relationship is adopted
(4) There are no external loads for axial vibrationsaccording to above equations
The transverse vibration equations for 1198811 119881
2and119882
1 119882
2
can be obtained as
4
3
1198681198631
119897+
1
51198971198681198601+
1
61198971198681198602minus
119898ℎV5ℎ
1199055
2
1198975+
31198681198632
2119897
+4119898
ℎV4ℎ
1199053
1
1198974+
4120578119887119863
1199091199091
1198973minus
2119898ℎV5ℎ
1199054
2
1198975+
6120578119887119863
1199091199092
1198973
+8119898
ℎV4ℎ
1199052
1198811
1198974+
41198631199091199091198811
1198973+
8119898ℎV5ℎ
1199053
1198812
1198975+
61198631199091199091198812
1198973
+27119860
1199091199091198812119882
2
2
81198973+
541198601199091199091198811119881
2
2
71198973+
181198601199091199091198811119882
2
2
71198973
+6119860
119909119909119881
2
1
1198812
1198973+
21198601199091199091198812119882
2
1
1198973+
1211986011990911990911988021198812
51198972
+8119860
1199091199091198811119882
2
1
51198973+
311986011990911990911988011198812
21198972+
211986011990911990911988021198811
1198972
+8119860
119909119909119881
3
1
51198973+
27119860119909119909119881
3
2
81198973+
361198601199091199091198812119882
1119882
2
71198973
+4119860
1199091199091198811119882
1119882
2
1198973+
411986011990911990911988011198811
31198972minus 119865
119888119910(119905) minus 05119865
025119865= 0
1
61198971198681198601+
3
2
1198681198631
119897minus
119898ℎV5ℎ
1199055
1
1198975+
1
71198971198681198602+
9
5
1198681198632
119897
+6120578
119887119863
1199091199091
1198973+
2119898ℎV5ℎ
1199054
1
1198975+
12120578119887119863
1199091199092
1198973+
6119898ℎV6ℎ
1199055
2
1198976
+6119863
1199091199091198811
1198973+
16119898ℎV5ℎ
1199053
1198811
1198975+
121198631199091199091198812
1198973+
18119898ℎV6ℎ
1199054
1198812
1198976
+9119860
1199091199091198812119882
2
2
21198973+
811198601199091199091198811119881
2
2
81198973+
311986011990911990911988011198811
21198972
+27119860
1199091199091198811119882
2
2
81198973+
541198601199091199091198812119881
2
1
71198973+
181198601199091199091198812119882
2
1
71198973
+3119860
11990911990911988021198812
1198972+
21198601199091199091198811119882
2
1
1198973+
911986011990911990911988011198812
51198972+
1211986011990911990911988021198811
51198972
+9119860
119909119909119881
3
2
21198973+
2119860119909119909119881
3
1
1198973+
271198601199091199091198812119882
1119882
2
41198973
+36119860
1199091199091198811119882
1119882
2
71198973minus 04119865
025119865minus 119865
119888119910(119905) = 0
4
3
119868119863
1
119897+
1
5119897119868119860
1+
3
2
119868119863
2
119897+
1
6119897119868119860
2minus
119898ℎV5ℎ
1199055
2
1198975
+4120578
119887119863
119909119909
1
1198973+
4119898ℎV4ℎ
1199053
1
1198974minus
2119898ℎV5ℎ
1199054
2
1198975+
6120578119887119863
119909119909
2
1198973
+4119863
119909119909119882
1
1198973+
8119898ℎV4ℎ
1199052
1198821
1198974+
8119898ℎV5ℎ
1199053
1198822
1198975+
6119863119909119909119882
2
1198973
+36119860
119909119909119882
211988111198812
71198973+
4119860119909119909119882
111988111198812
1198973+
27119860119909119909119882
2119881
2
2
81198973
+18119860
119909119909119882
1119881
2
2
71198973+
54119860119909119909119882
1119882
2
2
71198973+
6119860119909119909119882
2
1
1198822
1198973
+2119860
119909119909119882
2119881
2
1
1198973+
121198601199091199091198802119882
2
51198972+
8119860119909119909119882
1119881
2
1
51198973
+3119860
1199091199091198801119882
2
21198972+
21198601199091199091198802119882
1
1198972+
27119860119909119909119882
3
2
81198973
+8119860
119909119909119882
3
1
51198973+
41198601199091199091198801119882
1
31198972minus 119865
119888119911(119905) = 0
1
7119897119868119860
2+
9
5
119868119863
2
119897+
1
6119897119868119860
1minus
119898ℎV5ℎ
1199055
1
1198975+
3
2
119868119863
1
119897
+6120578
119887119863
119909119909
1
1198973+
2119898ℎV5ℎ
1199054
1
1198975+
6119898ℎV6ℎ
1199055
2
1198976
+12120578
119887119863
119909119909
2
1198973+
6119863119909119909119882
1
1198973+
16119898ℎV5ℎ
1199053
1198821
1198975
+12119863
119909119909119882
2
1198973+
18119898ℎV6ℎ
1199054
1198822
1198976+
31198601199091199091198801119882
1
21198972
+27119860
119909119909119882
211988111198812
41198973+
36119860119909119909119882
111988111198812
71198973+
9119860119909119909119882
2119881
2
2
21198973
+27119860
119909119909119882
1119881
2
2
81198973+
81119860119909119909119882
1119882
2
2
81198973+
18119860119909119909119882
2119881
2
1
71198973
+54119860
119909119909119882
2119882
2
1
71198973+
31198601199091199091198802119882
2
1198972+
2119860119909119909119882
1119881
2
1
1198973
+9119860
1199091199091198801119882
2
51198972+
121198601199091199091198802119882
1
51198972+
2119860119909119909119882
3
1
1198973
+9119860
119909119909119882
3
2
21198973minus 119865
119888119911(119905) = 0
(48)
The complexity high coupling and nonlinearity are obvi-ous in above equations
4 The Coupled Rigid-Flexible Dynamics
The dynamics for control and dynamic simulation shouldbe presented for solar sail based on the simplification ofequations derived in previous sections Some assumptions aremade before simplifying the equations as follows
12 Mathematical Problems in Engineering
(1) Only the attitude motion is affected by the slidingmass the vibration of solar sail structure is notaffected by the sliding mass
(2) Although the attitude control is accomplished byrotating control vanes and the gimbaled controlboom moving sliding masses the specific time his-tories of the actuators are not considered here
(3) The four supporting beams are regarded as an entirestructure thus the identical generalized coordinatesare adopted in the dynamic analysis
41 The Simplified Attitude Dynamics The kinetic energy ofsolar sail supporting beams can be obtained as
119879119898
=1
2120596 sdot J sdot 120596 + 119898
119897int
119897
0
2∘
1205883
sdot (120596 times r3) + (120596 times 120588
3) sdot (120596 times 120588
3)
+ 2 (120596 times r3) sdot (120596 times 120588
3) 119889119911
+ 119898119897int
119897
0
2∘
1205882
sdot (120596 times r2) + (120596 times 120588
2) sdot (120596 times 120588
2)
+ 2 (120596 times r2) sdot (120596 times 120588
2) 119889119910
(49)
The subscripts 2 and 3 represent the second and thirdsupporting beams The displacements can be expressed as
V0119909
(119911 119905) = (119911
119897)
2
sdot 1198811(119905) + (
119911
119897)
3
sdot 1198812(119905)
1199080119910
(119911 119905) = 120572V0119909
(119911 119905) = (119911
119897)
2
sdot 1205721198811(119905) + (
119911
119897)
3
sdot 1205721198812(119905)
for the 3rd beam
V0119909
(119910 119905) = 120573V0119909
(119911 119905) = (119910
119897)
2
sdot 1205731198811(119905) + (
119910
119897)
3
sdot 1205731198812(119905)
1199080119911
(119910 119905) = 120574V0119909
(119910 119905) = (119910
119897)
2
sdot 1205741198811(119905) + (
119910
119897)
3
sdot 1205741198812(119905)
for the 2nd beam
(50)
The subscripts 119909 119910 and 119911 of the left terms in (50)represent the displacements along119909119910 and 119911directions119881
1(119905)
and 1198812(119905) are the generalized coordinates The displacements
1199080119910(119911 119905) V
0119909(119910 119905) and 119908
0119911(119910 119905) can be obtained using the
assumed modes as
1205883= V
0119909(119911 119905) i
119887+ 119908
0119910(119911 119905) j
119887
=
[[[[[
[
(119911
119897)
2
sdot 1198811(119905) + (
119911
119897)
3
sdot 1198812(119905)
120572 [(119911
119897)
2
sdot 1198811(119905) + (
119911
119897)
3
sdot 1198812(119905)]
0
]]]]]
]
1205882= V
0119909(119910 119905) i
119887+ 119908
0119911(119910 119905) k
119887
=
[[[[[
[
120573[(119910
119897)
2
sdot 1198811(119905) + (
119910
119897)
3
sdot 1198812(119905)]
0
120574 [(119910
119897)
2
sdot 1198811(119905) + (
119910
119897)
3
sdot 1198812(119905)]
]]]]]
]
(51)
The vibration velocity can be obtained as
∘
1205883
= 1205883119909i119887+ 120588
3119910j119887=
[[[[[
[
(119911
119897)
2
sdot 1(119905) + (
119911
119897)
3
sdot 2(119905)
1205721[(
119911
119897)
2
sdot 1(119905) + (
119911
119897)
3
sdot 2(119905)]
0
]]]]]
]
∘
1205882
= 1205882119909i119887+ 120588
2119911k119887=
[[[[[
[
1205731[(
119910
119897)
2
sdot 1(119905) + (
119910
119897)
3
sdot 2(119905)]
0
1205741[(
119910
119897)
2
sdot 1(119905) + (
119910
119897)
3
sdot 2(119905)]
]]]]]
]
(52)
Without loss of generality 120572 = 120573 = 1205721= 120573
1= 1 and
120574 = 1205741= minus1 can be assumed in above expressions And the
kinetic energy of the slidingmasses can be obtained as followsby neglecting the vibration related terms
119879ℎ=
1
2119898
ℎ1(120596 times r
ℎ1) sdot (120596 times r
ℎ1) +
1
2119898
ℎ2(120596 times r
ℎ2)
sdot (120596 times rℎ2)
(53)
The kinetic energy of the payload can be obtained as
119879119901=
1
2119898
119901(120596 times r
119901) sdot (120596 times r
119901) (54)
The following simplified attitude dynamics can beobtained by neglecting the second and higher terms ofattitude angles and vibration modes in computing the kinetic
Mathematical Problems in Engineering 13
energies of the supporting beams payload and slidingmasses Consider
119869119909 minus 119898
1198971198972
1minus
4
5119898
1198971198972
2+ 119898
ℎ11199102
ℎ1
+ 119898ℎ21199112
ℎ2
minus 119898119901119903119901119909119903119901119911 + 119898
1199011199032
119901119911
+ 1198981199011199032
119901119910
minus 119898119901119903119901119909119903119901119910
120579 = 119876120593
119869119910
120579 +2
5119898
1198971198972
2+
1
2119898
1198971198972
1+ 119898
ℎ21199112
ℎ2
120579
+ 1198981199011199032
119901119911
120579 minus 119898119901119903119901119910119903119901119911 minus 119898
119901119903119901119909119903119901119910
+ 1198981199011199032
119901119909
120579 = 119876120579
119869119911 minus
2
51198972
1198981198972minus
1
21198972
1198981198971+ 119898
ℎ11199102
ℎ1
minus 119898119901119903119901119910119903119901119911
120579 + 1198981199011199032
119901119910
+ 1198981199011199032
119901119909
minus 119898119901119903119901119909119903119901119911 = 119876
120595
(55)
where 119876120593 119876
120579 and 119876
120595are the generalized nonpotential
attitude control torques generated by the control vanes Andthe attitude control torques generated by the gimbaled controlboom and sliding masses can be found on the left side ofthe above equation coupled with 120579 making the attitudecontroller design problem rather difficult
42 The Simplified Vibration Equations The couplingbetween the axial and transverse vibrations is neglectedand only the transverse vibration is considered The attitudedynamics for dynamic simulation can be obtained as followsbased on previous derivation by neglecting the action ofsolar-radiation pressure
4
3
1198681198631
119897+
1
51198971198681198601+
1
61198971198681198602+
31198681198632
2119897+
4120578119887119863
1199091199091
1198973
+6120578
119887119863
1199091199092
1198973+
41198631199091199091198811
1198973+
61198631199091199091198812
1198973+
271198601199091199091198812119882
2
2
81198973
+54119860
1199091199091198811119881
2
2
71198973+
181198601199091199091198811119882
2
2
71198973+
6119860119909119909119881
2
1
1198812
1198973
+2119860
1199091199091198812119882
2
1
1198973+
81198601199091199091198811119882
2
1
51198973+
8119860119909119909119881
3
1
51198973
+27119860
119909119909119881
3
2
81198973+
361198601199091199091198812119882
1119882
2
71198973+
41198601199091199091198811119882
1119882
2
1198973
minus 1198651198621
(119905) = 0
1
61198971198681198601+
3
2
1198681198631
119897+
1
71198971198681198602+
9
5
1198681198632
119897+
6120578119887119863
1199091199091
1198973
+12120578
119887119863
1199091199092
1198973+
61198631199091199091198811
1198973+
121198631199091199091198812
1198973+
91198601199091199091198812119882
2
2
21198973
+81119860
1199091199091198811119881
2
2
81198973+
271198601199091199091198811119882
2
2
81198973+
541198601199091199091198812119881
2
1
71198973
+18119860
1199091199091198812119882
2
1
71198973+
21198601199091199091198811119882
2
1
1198973+
9119860119909119909119881
3
2
21198973
+2119860
119909119909119881
3
1
1198973+
271198601199091199091198812119882
1119882
2
41198973+
361198601199091199091198811119882
1119882
2
71198973
minus 1198651198622
(119905) = 0
(56)
The following equations can be obtained by rearrangingthe above equations
4
3
1198681198631
119897+
1
51198971198681198601+
1
61198971198681198602+
31198681198632
2119897+
4120578119887119863
1199091199091
1198973
+6120578
119887119863
1199091199092
1198973+
41198631199091199091198811
1198973+
61198631199091199091198812
1198973+
16119860119909119909119881
3
1
51198973
+12119860
119909119909119881
2
1
1198812
1198973+
1081198601199091199091198811119881
2
2
71198973+
54119860119909119909119881
3
2
81198973
minus 1198651198621
(119905) = 0
1
61198971198681198601+
3
2
1198681198631
119897+
1
71198971198681198602+
9
5
1198681198632
119897+
6120578119887119863
1199091199091
1198973
+12120578
119887119863
1199091199092
1198973+
61198631199091199091198811
1198973+
121198631199091199091198812
1198973
+4119860
119909119909119881
3
1
1198973+
108119860119909119909119881
2
1
1198812
71198973+
811198601199091199091198811119881
2
2
41198973
+9119860
119909119909119881
3
2
1198973minus 119865
1198622(119905) = 0
(57)
1198651198621(119905) and 119865
1198622(119905) are used to represent all the generalized
external forces they can be used for vibration control Thesecomplicated equations abovementioned are the basis forobtaining the simplified equations used for controller design
The following equations can be obtained by neglecting thetwo and higher terms
4
3
1198681198631
119897+
1
51198971198681198601+
1
61198971198681198602+
31198681198632
2119897+
4120578119887119863
1199091199091
1198973
+6120578
119887119863
1199091199092
1198973+
41198631199091199091198811
1198973+
61198631199091199091198812
1198973= 119865
1198621
(119905)
14 Mathematical Problems in Engineering
1
61198971198681198601+
3
2
1198681198631
119897+
1
71198971198681198602+
9
5
1198681198632
119897+
6120578119887119863
1199091199091
1198973
+12120578
119887119863
1199091199092
1198973+
61198631199091199091198811
1198973+
121198631199091199091198812
1198973= 119865
1198622
(119905)
(58)
43 The Rigid-Flexible Coupled Dynamics The simplifiedattitude and vibration dynamics can be written as
119886120593 + 119886
120579
120579 + 119886120595 + 119886
1198811
1+ 119886
1198812
2= 119876
120593
119887120579
120579 + 119887120595 + 119887
120593 + 119887
1198811
1+ 119887
1198812
2= 119876
120579
119888120595 + 119888
120579
120579 + 119888120593 + 119888
1198811
1+ 119888
1198812
2= 119876
120595
119889
1198811
1+ 119889
1198812
2+ 119889
1198811
1+ 119889
1198812
2+ 119889
1198811
1198811
+ 1198891198812
1198812= 119876
1198811
119890
1198811
1+ 119890
1198812
2+ 119890
1198811
1+ 119890
1198812
2+ 119890
1198811
1198811
+ 1198901198812
1198812= 119876
1198812
(59)
The related coefficients in the preceding equation can befound in (A1) in the appendix The dynamics (see (59)) isnot suitable for attitude controller design because the controlinputs exist in some coefficients of the angular accelerationsThis will make the controller design rather difficult Thusthe following dynamic model is obtained by putting theterms including the control inputs right side of the dynamicequations
119869119909 minus 119898
1198971198972
1minus
4
5119898
1198971198972
2= 119876
120593+ 119906
119869119910
120579 +2
5119898
1198971198972
2+
1
2119898
1198971198972
1= 119876
120579+ 119906
120579
119869119911 minus
1
21198972
1198981198971minus
2
51198972
1198981198972= 119876
120595+ 119906
119889
1198811
1+ 119889
1198812
2+ 119889
1198811
1+ 119889
1198812
2
+ 1198891198811
1198811+ 119889
1198812
1198812= 119876
1198811
119890
1198811
1+ 119890
1198812
2+ 119890
1198811
1+ 119890
1198812
2
+ 1198901198811
1198811+ 119890
1198812
1198812= 119876
1198812
(60)
The expressions for 119906 119906
120579
and 119906are as
119906= minus119898
ℎ11199102
ℎ1
minus 119898ℎ21199112
ℎ2
+ 119898119901119903119901119909119903119901119911 minus 119898
1199011199032
119901119911
minus 1198981199011199032
119901119910
+ 119898119901119903119901119909119903119901119910
120579
119906
120579
= minus119898ℎ21199112
ℎ2
120579 minus 1198981199011199032
119901119911
120579 + 119898119901119903119901119910119903119901119911 + 119898
119901119903119901119909119903119901119910
minus 1198981199011199032
119901119909
120579
119906= minus119898
ℎ11199102
ℎ1
+ 119898119901119903119901119910119903119901119911
120579 minus 1198981199011199032
119901119910
minus 1198981199011199032
119901119909
+ 119898119901119903119901119909119903119901119911
(61)
119906 119906
120579
and 119906are the functions of the positions of sliding
masses and payload and the angular accelerations The statevariables in (60) are defined as
1199091= 120593 119909
2= 119909
3= 120579 119909
4= 120579
1199095= 120595 119909
6= 119909
7= 119881
1
1199098=
1 119909
9= 119881
2 119909
10=
2
(62)
Thedynamics (60) can bewritten as the state-spacemodelas following
1= 119909
2
2= 119886
11199097+ 119886
21199098+ 119886
31199099+ 119886
411990910
+ 119906120593
3= 119909
4
4= 119886
51199097+ 119886
61199098+ 119886
71199099+ 119886
811990910
+ 119906120579
5= 119909
6
6= 119886
91199097+ 119886
101199098+ 119886
111199099+ 119886
1211990910
+ 119906120595
7= 119909
8
8= 119886
131199097+ 119886
141199098+ 119886
151199099+ 119886
1611990910
+ 1199061198811
9= 119909
10
10
= 119886171199097+ 119886
181199098+ 119886
191199099+ 119886
2011990910
+ 1199061198812
(63)
where 119906120579 119906
120593 and 119906
120595are the generalized control inputs
for attitude control and 1199061198811
and 1199061198812
are the generalizedcontrol inputs for vibration control The controllability canbe satisfied by analyzing (63) The attitudevibration controlinputs and the coefficients will be presented later in thissection The form of a matrix differential equation can bewritten as follows for the above equation
x = Ax + Bu (64)
The expressions of the relatedmatrices and vectors can befound as
x = [1
2
3
4
5
6
7
8
9
10]119879 x (119905
0) = x
1199050
u = [119906120593 119906
120579 119906
120595 119906
1198811
1199061198812
]119879
u (1199050) is known
(65)
where A xB and u are the system matrix state variablesvector control matrix and control inputs vector respectively
Mathematical Problems in Engineering 15
The complexity of the state-space model can be seen bypresenting the detailed expressions of control inputs forattitudevibration and related parameters in (A2) in theappendix
5 AttitudeVibration Control and Simulation
The controller for the attitude and vibration is developedusing the LQR and optimal PI theory The dynamic simula-tion is performed based on the coupled dynamics derived inthe previous sections
51 LQR and Optimal PI Based Controllers Design Thedynamics for solar sail can bewritten as follows togetherwithits quadratic cost function also defined as
x = Ax + Bu x (1199050) = x
1199050
(known)
119869 =1
2int
infin
1199050
[x119879 (119905)Qx (119905) + u119879 (119905)Ru (119905)] 119889119905
(66)
whereQ = Q119879
⩾ 0 andR = R119879
gt 0 are constantThe control-lability of [AB] and the observability of [AD] can beensured when the equationDD119879
= Q holds for anymatrixDThe optimal control input ulowast(119905)within the scope of u(119905) isin R119903119905 isin [119905
0infin] can be computed as follows to make 119869minimum
ulowast (119905) = minusKxlowast (119905) K = Rminus1B119879P (67)
where P is the nonnegative definite symmetric solution of thefollowing Riccati algebraic equations
PA + A119879P minus PBRminus1B119879P +Q = 0 (68)
And the optimal performance index can be obtained asfollows for arbitrary initial states
119869lowast
[x (1199050) 119905
0] =
1
2x1198790
Px0 (69)
The closed-loop system
x = (A minus BRminus1B119879P) x (70)
is asymptotically stableFor an orbiting solar sail the primary disturbance torque
is by the cmcp offset and the impact of the tiny dust inthe deep space The state regulator can be used to controlthe dynamic system affected by pulse disturbance torquewith good steady-state errors but will never achieve accuratesteady-state errors if the dynamics is affected by constantdisturbance torque Thus the optimal state regulator withan integrator to eliminate the constant disturbance torqueshould be presented This optimal proportional-integral reg-ulator not only eliminates the constant disturbance torque butalso possesses the property of optimal regulator
Table 1 The related parameters
Parameters ValuesCMCP offsetm [0 017678 017678]119879
The side length of square sailm 100Nominal solar-radiation pressureconstant at 1 AU from the sunNm2 4563 times 10minus6
Solar-radiation pressure forceN 912 times 10minus2
Roll inertiakglowastm2 50383Pitch and yaw inertiakglowastm2 251915Outer radiusm 0229Thickness of the supporting beamm 75 times 10minus6
Youngrsquos modulus of the supportingbeamGPa 124
Moment of inertia of the cross-sectionof the supporting beamm4 2829412 times 10minus7
Bending stiffness of the supportingbeamNlowastm2 3508471336
Proportional damping coefficient ofsupporting beams 001
Line density of the supportingbeamkgm 0106879
Cross-sectional area of the supportingbeamm2 1079 times 10minus5
Roll disturbance torqueNlowastm 0Pitch (yaw) disturbance torqueNlowastm 0016122 (minus0016122)
For the following linear system with the correspondingperformance index
x = Ax + Bu x (1199050) = x
1199050
u (1199050) = u
1199050
119869 =1
2int
infin
1199050
(x119879Qx + u119879Ru + u119879Su) 119889119905(71)
where Q = Q119879
⩾ 0 R = R119879
gt 0 and S = S119879 gt 0 If [AB]is completely controllable and meanwhile [AD
11] is com-
pletely observable with the relationship D11D119879
11
= Q thesolution can be expressed as
ulowast = minusK1x minus K
2ulowast ulowast (119905
0) = u
1199050
(72)
If B119879B is full rank we can get
ulowast = minusK3x minus K
4x ulowast (119905
0) = u
1199050
(73)
K119894(119894 = 1 2 3 4) is the function of ABQR S
The closed-loop system
[xulowast] = [
A BminusK
1minusK
2
] [xulowast] [
[
x (1199050)
u (1199050)]
]
= [x1199050
u1199050
] (74)
is asymptotically stableThe compromise between the state variables (the angle
angular velocity the vibration displacement and velocity)and control inputs (the torque by all the actuators) can
16 Mathematical Problems in Engineering
0 2000 4000 6000
0 2000 4000 6000
0 2000 4000 6000minus5
0
5
minus5
0
5
minus5
0
5
minus4
minus2
0
2
4
times10minus4
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
00162
00164
00166
4800 4900 5000
4800 4900 5000
4800 4900 5000
minus00165
minus0016
Time (s) Time (s)
Time (s)
Time (s)
Time (s)
Time (s)
Roll
erro
r120593(∘
)
Roll
erro
r120593(∘
)
Pitc
h er
ror120579
(∘)
Pitc
h er
ror120579
(∘)
Yaw
erro
r120595(∘
)
Yaw
erro
r120595(∘
)
Figure 8 The roll pitch and yaw errors
be achieved by using both the LQR based and optimal PIbased controllers for the coupled attitudevibration dynamicsystem The fact is that the attitude control ability is limitedto the control torque by the control actuators The change ofthe attitude angles and rates should not be frequent to voidexciting vibrations
Thus the weighting matrix Q and the control weightingmatrix R are selected as follows for LQR based controller
Q (1 1) = 9 times 10minus6
Q (2 2) = 1 times 10minus6
Q (3 3) = 16 times 10minus6
Q (4 4) = Q (5 5) = Q (6 6) = Q (7 7) = Q (8 8)
= Q (9 9) = Q (10 10) = 1 times 10minus6
Q (119894 119895) = 0 (119894 = 119895 119894 119895 = 1 sim 10)
R (1 1) = R (2 2) = 900 R (3 3) = 100
R (4 4) = R (5 5) = 10000
R119894119895
= 0 (119894 = 119895 119894 119895 = 1 sim 5)
(75)
TheweightingmatrixQ and the control weightingmatrixR are selected as follows for the optimal PI based controller
Q (1 1) = Q (2 2) = 4 times 10minus8
Q (3 3) = Q (4 4) = Q (5 5) = Q (6 6) = Q (7 7)
= Q (8 8) = 16 times 10minus8
Mathematical Problems in Engineering 17
minus02
0
02
Roll
rate
(∘s)
Roll
rate
(∘s)
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Pitc
h ra
te(∘s)
Pitc
h ra
te(∘s)
0 1000 2000 3000 4000 5000
minus05
0
05
minus05
0
05
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
Time (s)
Yaw
rate
(∘
s)
Yaw
rate
(∘
s)
4800 4850 4900 4950 5000
Time (s)4800 4850 4900 4950 5000
Time (s)4800 4850 4900 4950 5000
minus2
0
2
minus2
0
2
minus2
0
2
times10minus4
times10minus4
times10minus4
Figure 9 The roll pitch and yaw rates
Q (9 9) = Q (10 10) = 1 times 10minus8
Q (119894 119895) = 0 (119894 = 119895 119894 119895 = 1 sim 10)
R (1 1) = R (2 2) = R (3 3) = 1 times 10minus8
R (4 4) = R (5 5) = 4 times 10minus8
R (119894 119895) = 0 (119894 = 119895 119894 119895 = 1 sim 5)
(76)
52 The Simulation Results The initial angle errors of rollpitch and yaw are adopted as 120593(119905
0) = 3
∘ 120579(1199050) = 3
∘ and120595(119905
0) = 3
∘ the initial angular velocity errors of roll pitchand yaw are adopted as (119905
0) = 0
∘
s 120579(1199050) = 0
∘
s and(119905
0) = 0
∘
s 1198811(1199050) = 01m 119881
2(1199050) = 01m
1(1199050) = 0ms
and 2(1199050) = 0ms are adopted in this paper for dynamic
simulationThe estimated cmcp offset is 025m for a 100 times 100m
square solar sail It is assumed that the components of cmcpoffset vector are [0 017678 017678]
119879 in the body frame
The relevant parameters for dynamic simulations are givenin Table 1
The dynamic simulation results are obtained as followsby using the LQR controller based on the abovementionedQ and R related parameters and initial conditions Thedynamics simulations with (denoted by ldquowith GFrdquo) andwithout (denoted by ldquowithout GFrdquo) considering the geo-metrical nonlinearity are presented And the correspondingdiscussions and analysis are also given according to thecalculated results
The roll pitch and yaw errors are presented based onthe dynamics models with and without considering thegeometrical nonlinearityThe control effect with zero steady-state error can be achieved for roll axis by referring tothe results But the steady-state errors exist for pitch andyaw axes from Figure 8 this is because there exist constantdisturbance torques for pitch and yaw axes caused by thecmcp offset Thus the LQR based controller cannot be usedfor attitude control with good steady-state performance Thesteady-state errors of pitch and yaw axes are about 0164
∘
and minus0164∘ respectively from the corresponding partial
enlarged drawing of the figures (see the corresponding left
18 Mathematical Problems in Engineering
minus20
0
20
Roll
torq
ue (N
lowastm
)
Roll
torq
ue (N
lowastm
)
minus50
0
50
minus50
0
50
Pitc
h to
rque
(Nlowast
m)
Pitc
h to
rque
(Nlowast
m)
0 1000 2000 3000 4000 5000
0 2000 4000 6000
0 2000 4000 6000
Yaw
torq
ue (N
lowastm
)
Yaw
torq
ue (N
lowastm
)
minus002
0
002
008
01
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
minus01
minus009
minus008
Time (s)Time (s)
Time (s)Time (s)
Time (s)Time (s)
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Figure 10 The roll pitch and yaw torques
figures) A simple and practical controller should be designedto eliminate the steady-state errorsThese errorswill affect theprecision of the super long duration space mission deeply
The differences between the dynamics with and withoutthe geometrical nonlinearity effect can be observed Theamplitudes and phases change a bit by comparing the corre-sponding results
It can be observed by the partial enlarged figures(the right figures of Figure 9) that there are no steady-stateerrors for roll pitch and yaw rates The relative satisfieddynamic performance is achieved In fact a result with muchmore satisfied dynamic performance can be obtained but itwill make the desired control torques much larger duringthe initial period This will not only excite the vibration ofthe structure but also increase the burden of the controlactuators
And the differences between the dynamics models withand without the geometrical nonlinearity can also be seenmerely in the phase of the angular velocities
The desired attitude control torques are presented inFigure 10 The roll torque will tend to be zero with thedecrement of the state variable errors The pitch and yawtorques tend to be constant from the middle and bottom
figures The pitch and yaw steady-state errors can never beeliminated although the pitch and yaw torques (009Nlowastmand minus009Nlowastm) are applied continuously by theoreticalanalysis and simulations This is just a great disadvantage ofthe LQR based controller in this paper The initial controltorques can be afforded by vibrating the gimbaled controlboom andmoving the slidingmasses that can afford a relativelarge torque The control vanes can be used to afford thecontrol torques when solar sail is in steady-state process Theexpression of the attitude control inputs 119906
120593 119906
120579 and 119906
120595can be
found in previous sectionMoreover the differences between dynamics responses
with and without geometrical nonlinearity can also beobserved by comparing the corresponding results Therequired torques for the attitude control are a little largerfor the dynamics with geometrical nonlinearity And thedifference in the phase is also clear
It can be seen that the vibration of the supporting beamis depressed effectively by the simulation results in Figure 11It can be seen that the steady-state errors and the dynamicperformance are relatively satisfied It can also be seen that thedynamics responses between the model with and without the
Mathematical Problems in Engineering 19
0 1000 2000 3000 4000 5000
0 1000 2000 3000 4000 5000
minus01
0
01
minus02
0
02
Time (s) Time (s)
Time (s) Time (s)
minus5
0
5
times10minus4
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
minus1
0
1
times10minus3
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
The d
ispla
cem
ent o
f the
tip
(m)
The d
ispla
cem
ent o
f the
tip
(m)
The v
eloci
ty o
f the
tip
(ms
)
The v
eloc
ity o
f the
tip
(ms
)
Figure 11 The displacement and velocity of the tip of the supporting beam
geometrical nonlinearity effect are different in the vibrationdisplacement and velocitymagnitudes and phases (Figure 15)
The simulation results can be obtained as follows by usingthe optimal PI based controller adopting the abovementionedparameters and initial conditions
The roll pitch and yaw errors are given by using theoptimal PI based controller These errors tend to disappearby observing the partially enlarged plotting of the figure (thecorresponding right figures) (shown in Figure 12) And therelative satisfied dynamic performance can also be obtainedFrom the view of eliminating the steady-state errors the opti-mal PI based controller performs better than the LQR basedcontroller by theoretical analysis and simulation results Theformer can achieve attitude control results without pitchand yaw steady-state errors From the view of dynamicperformance both the controllers perform well In additionit can be seen that the difference between the modelswith and without geometrical nonlinearity is merely inthe phase
The roll pitch and yaw rate errors are presented inFigure 13 The dynamic and steady-state performances aresatisfied by observing the simulation results And by observ-ing the difference between the dynamics responses with and
without the influence by the geometrical nonlinearity it canbe concluded that the merely difference is the phase
The desired control torques of the roll pitch and yaw areobtained in Figure 14 by using the optimal PI based controllerIt can be seen that the value of the desired roll control torquedecreases to zero as the values of the roll angle and ratedecrease to zero The desired pitch and yaw control torquestend to be the constant values 009Nlowastm and minus009Nlowastmrespectively The desired initial control torques are large byobserving Figure 14 It is suggested that the gimbaled controlboom combining the sliding masses is adopted to afford theinitial torque Then the control vanes can be used to controlthe solar sail after the initial phase The phase differencecan also be observed by inspecting the dynamics responsesduring the 4800sim5000 s period
The vibration can be controlled effectively based on theoptimal PI controller And the relative satisfied dynamicand steady-state performances can be achieved In additionthe tiny differences exist in the magnitudes of the requiredtorques And the phase differences also exist
It can be concluded as follows by analyzing and compar-ing the simulation results based on the LQR and optimal PItheories in detail
20 Mathematical Problems in Engineering
Roll
erro
r120593(∘
)
Roll
erro
r120593(∘
)
minus5
0
5
minus5
0
5
Pitc
h er
ror120579
(∘)
Pitc
h er
ror120579
(∘)
0 1000 2000 3000 4000 5000minus10
0
10
Time (s) Time (s)
Time (s)
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
Yaw
erro
r120595(∘
)
Yaw
erro
r120595(∘
)
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
minus1
0
1
times10minus3
minus1
0
1
times10minus3
minus1
0
1
times10minus3
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Figure 12 The roll pitch and yaw errors
(1) From the view of eliminating the steady-state errorsof the pitch and yaw errors the optimal PI based con-troller performs better than the LQR based controllerby theoretical analysis and simulation results Thedynamic performances of the two controllers are bothsatisfied and the desired control torques are relativelysmall
(2) The weighting of the state variables is reflected by theweighting matrix according to the LQR and optimalPI theories The constant weighting matrices selectedin this paper can effectively reflect the initial statevariable errors but maybe reflect the final state vari-able errors deficiently The time-varying weightingmatrices should be selected
(3) For the actual orbiting solar sail the control actuators(control vanes gimbaled control boom and slidingmasses) cannot afford excessive large control torquesThus the control torques should be as small as possibleon the premise of acquiring satisfied dynamic perfor-mance and steady-state errors It will not only reducethe burden of the control actuators but also avoid
exciting structural vibration In engineering practicethe weighting matrices and the control weightingmatrices should be selected based on the attitudecontrol requirement (eg dynamic performance andsteady-state errors etc)
(4) The dynamics responses influenced by the geometri-cal nonlinearity can be observed In a word the tinydifferences between the magnitudes of the physicalvariables exist for the models with and withoutthe geometrical nonlinearity And the relative cleardifferences exist in the phases for the attitude anglesrates required torques and so forth
6 Conclusions
The coupled attitude and structural dynamics is establishedfor the highly flexible sailcraft by using the von-Karman von-Karmanrsquos nonlinear strain-displacement relationships basedon assumptions of large deflections moderate rotationsand
Mathematical Problems in Engineering 21
Roll
rate
erro
r(∘ s
)
Roll
rate
erro
r(∘ s
)
minus01
0
01
minus01
0
01
Pitc
h ra
te er
ror (
∘ s)
Pitc
h ra
te er
ror (
∘ s)
0 1000 2000 3000 4000 5000minus02
0
02
Yaw
rate
erro
r (∘ s
)
Yaw
rate
erro
r (∘ s
)
4800 4850 4900 4950 5000
minus5
0
5times10minus4
minus5
0
5
times10minus4
minus5
0
5times10minus4
Time (s)
4800 4850 4900 4950 5000
Time (s)
4800 4850 4900 4950 5000
Time (s)
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Figure 13 The roll pitch and yaw rate errors
small strains The Lagrange equation method is utilizedto derive the dynamics for controller design and dynamicsimulation The LQR and optimal PI based controllers aredesigned for the dynamics with the constant disturbancetorque caused by the cmcp offset By theoretical analysisand simulation it can be seen that both controllers cancompromise between the state variables and control inputsBecause the control actuators can hardly afford large controltorque the dynamic performance should be relaxed toreduce the requirement for the attitude control actuatorsBesides the optimal PI based controller can also eliminatethe constant disturbance torque caused by the cmcp offsetthat always exists while the LQR based controller fails toachieve the results with satisfied steady-state performancealthough the attitude control torque is always applied to thecoupled dynamic systemThe dynamics simulations with andwithout the geometrical nonlinearity effect are also carriedout And the differences between the models in magnitudesand phases are identified and analyzed It can be concludedthat the optimal PI based controller performs better than the
LQRbased controller from the viewof eliminating the steady-state error caused by the disturbance torque by the cmcpoffset
Appendix
The related parameters in above equation are given as
119886120593= 119869
119909+ 119898
ℎ11199102
ℎ1
+ 119898ℎ21199112
ℎ2
+ 1198981199011199032
119901119911
+ 1198981199011199032
119901119910
119886120579= minus 119898
119901119903119901119909119903119901119910 119886
120595= minus119898
119901119903119901119909119903119901119911
1198861198811
= minus 1198981198971198972
1198861198812
= minus4
5119898
1198971198972
119887120579= 119869
119910+ 119898
ℎ21199112
ℎ2
+ 1198981199011199032
119901119911
+ 1198981199011199032
119901119909
119887120595= minus 119898
119901119903119901119910119903119901119911 119887
120593= minus119898
119901119903119901119909119903119901119910
22 Mathematical Problems in Engineering
Roll
torq
ue (N
lowastm
)
Roll
torq
ue (N
lowastm
)
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
0 2000 4000 6000
0 2000 4000 6000
0 2000 4000 6000
Time (s)
Time (s)
Time (s)
Time (s)
Time (s)
Time (s)4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
minus01
minus008
008
009
01
minus002
0
002
minus5
0
5
minus2
0
2
Pitc
h to
rque
(Nlowast
m)
Pitc
h to
rque
(Nlowast
m)
minus2
0
2
Yaw
torq
ue (N
lowastm
)
Yaw
torq
ue (N
lowastm
)
Figure 14 The roll pitch and yaw torques
1198871198811
=1
2119898
1198971198972
1198871198812
=2
5119898
1198971198972
119888120595= 119869
119911+ 119898
ℎ11199102
ℎ1
+ 1198981199011199032
119901119910
+ 1198981199011199032
119901119909
119888120579= minus 119898
119901119903119901119910119903119901119911 119888
120593= minus119898
119901119903119901119909119903119901119911
1198881198811
= minus1
21198972
119898119897 119888
1198812
= minus2
51198972
119898119897
119889
1198811
= (4
3
119868119863
119897+
1
5119897119868119860) 119889
1198812
= (1
6119897119868119860+
3119868119863
2119897)
119889
1198811
=4120578
119887119863
119909119909
1198973 119889
1198812
=6120578
119887119863
119909119909
1198973
1198891198811
=4119863
119909119909
1198973 119889
1198812
=6119863
119909119909
1198973
1198761198811
= 1198651198621
(119905)
119890
1198811
= (3
2
119868119863
119897+
1
6119897119868119860)
119890
1198812
= (1
7119897119868119860+
9
5
119868119863
119897) 119890
1198811
=6120578
119887119863
119909119909
1198973
119890
1198812
=12120578
119887119863
119909119909
1198973 119890
1198811
=6119863
119909119909
1198973
1198901198812
=12119863
119909119909
1198973 119876
1198812
= 1198651198622
(119905)
(A1)
The detailed expressions of control inputs for attitudevibration and related parameters in the state-space model ofthe dynamics (see (62) and (63)) are presented as follows
A =
[[[[[[[[[[[[[[
[
0 1 0 0 0 0 0 0 0 0
0 0 0 0 0 0 1198861
1198862
1198863
1198864
0 0 0 1 0 0 0 0 0 0
0 0 0 0 0 0 1198865
1198866
1198867
1198868
0 0 0 0 0 1 0 0 0 0
0 0 0 0 0 0 1198869
11988610
11988611
11988612
0 0 0 0 0 0 0 1 0 0
0 0 0 0 0 0 11988613
11988614
11988615
11988616
0 0 0 0 0 0 0 0 0 1
0 0 0 0 0 0 11988617
11988618
11988619
11988620
]]]]]]]]]]]]]]
]
Mathematical Problems in Engineering 23
0 1000 2000 3000 4000 5000
0 1000 2000 3000 4000 5000
minus01
0
01
minus02
0
02
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Time (s)
Time (s)Time (s)
Time (s)
minus1
0
1
minus1
0
1
times10minus3
times10minus3Th
e disp
lace
men
t of t
he ti
p (m
)
The d
ispla
cem
ent o
f the
tip
(m)
The v
eloci
ty o
f the
tip
(ms
)
The v
eloci
ty o
f the
tip
(ms
)
Figure 15 Vibration displacement and velocity of the tip
B =
[[[[[[[[[[[[[[
[
0 0 0 0 0
1 0 0 0 0
0 0 0 0 0
0 1 0 0 0
0 0 0 0 0
0 0 1 0 0
0 0 0 0 0
0 0 0 1 0
0 0 0 0 0
0 0 0 0 1
]]]]]]]]]]]]]]
]
1198861= minus
1198981198971198972
119869119909
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus4
5119869119909
1198981198971198972
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198862= minus
1198981198971198972
119869119909
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus4
5119869119909
1198981198971198972
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198863= minus
1198981198971198972
119869119909
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus4
5119869119909
1198981198971198972
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198864= minus
1198981198971198972
119869119909
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus4
5119869119909
1198981198971198972
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
119906120593=
119876120593
119869119909
+
119906
119869119909
+119898
1198971198972
119869119909
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+4
5119869119909
1198981198971198972
+
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198865=
1
2119869119910
1198981198971198972
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+2
5119869119910
1198981198971198972
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198866=
1
2119869119910
1198981198971198972
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+2
5119869119910
1198981198971198972
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198867=
1
2119869119910
1198981198971198972
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+2
5119869119910
1198981198971198972
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198868=
1
2119869119910
1198981198971198972
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
24 Mathematical Problems in Engineering
+2
5119869119910
1198981198971198972
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
119906120579=
119876120579
119869119910
+119906
120579
119869119910
minus1
2119869119910
1198981198971198972
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119910
1198981198971198972
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198869= minus
1
2119869119911
1198972
119898119897
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988610
= minus1
2119869119911
1198972
119898119897
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988611
= minus1
2119869119911
1198972
119898119897
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988612
= minus1
2119869119911
1198972
119898119897
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
119906120595=
119876120595
119869119911
+
119906
119869119911
+1
2119869119911
1198972
119898119897
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+2
5119869119911
1198972
119898119897
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988613
= minus
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988614
= minus
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988615
= minus
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988616
= minus
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
1199061198811
=
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988617
= minus
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988618
= minus
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988619
= minus
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988620
= minus
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1199061198812
=
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(A2)
Conflict of Interests
The authors declare that there is no conflict of interestsregarding the publication of this paper
Acknowledgments
The authors would like to thank the anonymous reviewers fortheir critical and constructive review of the paper This studywas cosupported by the National Natural Science Foundationof China (Project no 11302134 11272101)
References
[1] M Colin Solar Sailing Technology Dynamics and MissionApplications Springer-Praxis London UK 1st edition 1999
[2] V Lappas SWokesM Leipold A Lyngvi and P Falkner ldquoGui-dance and control for an Interstellar Heliopause Probe (IHP)solar sail mission to 200 AUrdquo in Proceedings of the AIAAGuidance Navigation and Control Conference and Exhibit pp2472ndash2492 San Francisco Calif USA August 2005
[3] L Charlotte C Camilla and C McInnes ldquoSolar radiation pres-sure augmented deorbiting fromhigh altitude sun-synchronousorbitsrdquo in Proceedings of the 4S Symposium 2012 Small SatellitesSystems and Services Portoroz Slovenia 2012
[4] M Ceriotti and C RMcInnes ldquoGeneration of optimal trajecto-ries for Earth hybrid pole sittersrdquo Journal of Guidance Controland Dynamics vol 34 no 3 pp 847ndash859 2011
[5] S Gong J Li andH Baoyin ldquoSolar sail transfer trajectory fromL1 point to sub-L1 pointrdquoAerospace Science and Technology vol15 no 7 pp 544ndash554 2011
[6] S Gong J Li and H Baoyin ldquoAnalysis of displaced solar sailorbits with passive controlrdquo Journal of Guidance Control andDynamics vol 31 no 3 pp 782ndash785 2008
[7] S Gong H Baoyin and J Li ldquoSolar sail three-body transfertrajectory designrdquo Journal of Guidance Control and Dynamicsvol 33 no 3 pp 873ndash886 2010
Mathematical Problems in Engineering 25
[8] S Gong J Li H Baoyin and J Simo ldquoA new solar sail orbitrdquoScience China Technological Sciences vol 55 no 3 pp 848ndash8552012
[9] Y Tsuda O Mori R Funase et al ldquoAchievement of IKAROS-Japanese deep space solar sail demonstration missionrdquo ActaAstronautica vol 82 no 2 pp 183ndash188 2013
[10] L Johnson MWhorton A Heaton R Pinson G Laue and CAdams ldquoNanoSail-D a solar sail demonstration missionrdquo ActaAstronautica vol 68 no 5-6 pp 571ndash575 2011
[11] B Wie and D Murphy ldquoSolar-sail attitude control design for asail flight validation missionrdquo Journal of Spacecraft and Rocketsvol 44 no 4 pp 809ndash821 2007
[12] B Wie D Murphy M Paluszek and S Thomas ldquoRobust atti-tude control systems design for solar sails part 1 propellantlessprimaryACSrdquo inProceedings of the AIAAGuidance Navigationand Control Conference and Exhibit Providence RI USAAugust 2004
[13] B Wie D Murphy M Paluszek and S Thomas ldquoRobust atti-tude control systems design for solar sails part 2 MicroPPT-based secondary ACSrdquo in Proceedings of the AIAA GuidanceNavigation and Control Conference and Exhibit pp 1325ndash1340Providence RI USA August 2004
[14] S Thomas M Paluszek B Wie and D Murphy ldquoAOCS per-formance and stability validation for large flexible solar sailspacecraftrdquo in Proceedings of the 41st AIAAASMESAEASEEJoint Propulsion Conference amp Exhibit Tucson Ariz USA 2005
[15] B Wie ldquoDynamic modeling and attitude control of solar sailspacecraft part Irdquo in Proceedings of the AIAAGuidance Naviga-tion and Control Conference and Exhibit Monterey Calif USAAugust 2002
[16] BWie ldquoSolar sail attitude control and dynamics part 1rdquo Journalof Guidance Control and Dynamics vol 27 no 4 pp 526ndash5352004
[17] B Wie ldquoDynamic modeling and attitude control of solar sailspacecraft part IIrdquo in Proceedings of the AIAA Guidance Nav-igation and Control Conference and Exhibit Monterey CalifUSA August 2002
[18] BWie ldquoSolar sail attitude control and dynamics part 2rdquo Journalof Guidance Control and Dynamics vol 27 no 4 pp 536ndash5442004
[19] C Luo and J-H Zheng ldquoSolar-sail attitude control based onmoving masses and roll stabilizer barsrdquo Journal of HarbinInstitute of Technology vol 43 no 3 pp 95ndash101 2011
[20] D Romagnoli and T Oehlschlagel ldquoHigh performance twodegrees of freedom attitude control for solar sailsrdquo Advances inSpace Research vol 48 no 11 pp 1869ndash1879 2011
[21] C Scholz D Romagnoli B Dachwald and S Theil ldquoPerfor-mance analysis of an attitude control system for solar sails usingsliding massesrdquo Advances in Space Research vol 48 no 11 pp1822ndash1835 2011
[22] A Bolle and C Circi ldquoSolar sail attitude control through in-plane moving massesrdquo Journal of Aerospace Engineering vol222 no 1 pp 81ndash94 2008
[23] M RotunnoM Basso A B Pome andM Sallusti ldquoA compari-son of robust attitude control techniques for a solar sail space-craftrdquo in Proceedings of the AIAA Guidance Navigation andControl Conference and Exhibit San Francisco Calif USA2005
[24] J Zhang K Zhai and T Wang ldquoControl of large angle maneu-vers for the flexible solar sailrdquo Science China Physics Mechanicsand Astronomy vol 54 no 4 pp 770ndash776 2011
[25] J Zhang andTWang ldquoCoupled attitude-orbit control of flexiblesolar sail for displaced solar orbitrdquo Journal of Spacecraft andRockets vol 50 no 3 pp 675ndash685 2013
[26] Q Li XMa and TWang ldquoReducedmodel for flexible solar saildynamicsrdquo Journal of Spacecraft and Rockets vol 48 no 3 pp446ndash453 2011
[27] M Polites J Kalmanson and D Mangus ldquoSolar sail attitudecontrol using small reaction wheels and magnetic torquersrdquoProceedings of the Institution of Mechanical Engineers G Journalof Aerospace Engineering vol 222 no 1 pp 53ndash62 2008
[28] H-T Cui J-H Luo J-H Feng and P-Y Cui ldquoAttitudecontrol of solar sail spacecraft with control boomrdquo Journal ofAstronautics vol 29 no 2 pp 560ndash566 2008
[29] E Mettler and S R Ploen ldquoSolar sail dynamics and controlusing a boom mounted bus articulated by a bi-state two-axisgimbal and reaction wheelsrdquo in Proceedings of the AIAAAASAstrodynamics Specialist Conference and Exhibit MontereyCalif USA August 2002
[30] J Luo X Li and J Feng ldquoPassive attitude control of solar sailspacecraftrdquo Flight Dynamics vol 26 no 5 pp 47ndash50 2008
[31] J Luo Study on attitude control of solar sail spaceraft [PhDthesis] School of Astronautics Harbin Institute of TechnologyHarbin China 2007
[32] D A Lawrence and S W Piggott ldquoIntegrated trajectory andattitude control for a four-vane solar sailrdquo in Proceedings ofthe AIAA Guidance Navigation and Control Conference andExhibit pp 2416ndash2431 San Francisco Calif USA August 2005
[33] E Mettler A B Acikmese and S R Ploen ldquoAttitude dynamicsand control of solar sails with articulated vanesrdquo in Proceedingsof the AIAA Guidance Navigation and Control Conference andExhibit pp 2396ndash2415 San Francisco Calif USA August 2005
[34] S N Adeli V J Lappas and B Wie ldquoA scalable bus-basedattitude control system for Solar Sailsrdquo Advances in SpaceResearch vol 48 no 11 pp 1836ndash1847 2011
[35] R Funase Y Shirasawa Y Mimasu et al ldquoOn-orbit verificationof fuel-free attitude control system for spinning solar sailutilizing solar radiation pressurerdquo Advances in Space Researchvol 48 no 11 pp 1740ndash1746 2011
[36] B Fu and F O Eke ldquoAttitude control methodology for largesolar sailsrdquo in AIAA Guidance Navigation and Control (GNC)Conference 2013
[37] J Liu N Cui F Shen and S Rong ldquoDynamics of highly-flexiblesolar sail subjected to various forcesrdquoActaAstronautica vol 103pp 55ndash72 2014
[38] J F Liu S Y Rong and J G Li ldquoAttitude dynamics modelingand control of large flexible solar sail spacecraftrdquo in Proceedingsof the 3rd International Symposium on Systems and Control inAeronautics and Astronautics (ISSCAA rsquo10) pp 243ndash247 IEEEPublications Piscataway NJ USA 2010
[39] S Gong H Baoyin and J Li ldquoCoupled attitude-orbit dynamicsand control for displaced solar orbitsrdquo Acta Astronautica vol65 no 5-6 pp 730ndash737 2009
Submit your manuscripts athttpwwwhindawicom
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
MathematicsJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Mathematical Problems in Engineering
Hindawi Publishing Corporationhttpwwwhindawicom
Differential EquationsInternational Journal of
Volume 2014
Applied MathematicsJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Probability and StatisticsHindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Journal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Mathematical PhysicsAdvances in
Complex AnalysisJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
OptimizationJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
CombinatoricsHindawi Publishing Corporationhttpwwwhindawicom Volume 2014
International Journal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Operations ResearchAdvances in
Journal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Function Spaces
Abstract and Applied AnalysisHindawi Publishing Corporationhttpwwwhindawicom Volume 2014
International Journal of Mathematics and Mathematical Sciences
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
The Scientific World JournalHindawi Publishing Corporation httpwwwhindawicom Volume 2014
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Algebra
Discrete Dynamics in Nature and Society
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Decision SciencesAdvances in
Discrete MathematicsJournal of
Hindawi Publishing Corporationhttpwwwhindawicom
Volume 2014 Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Stochastic AnalysisInternational Journal of
10 Mathematical Problems in Engineering
+1
10
119860119909119909
1198973[9119880
1119897 (119881
2
2
+ 1198822
2
) + 241198802119897 (119881
11198812+ 119882
1119882
2)
+ 4 (1198812
1
+ 1198822
1
)2
]
+119860
119909119909
1198972[3
21198801(119881
11198812+ 119882
1119882
2) + 119880
2(119881
2
1
+ 1198822
1
)]
+6119863
119909119909119881
2
2
1198973+ 119860
119909119909(2119880
1119881
2
1
31198972+
21198801119882
2
1
31198972+
21198802
2
3119897)
+6119863
119909119909119882
2
2
1198973+
611986311990911990911988111198812
1198973+
11986011990911990911988011198802
119897+
6119863119909119909119882
1119882
2
1198973
+119860
119909119909119880
2
1
2119897+
2119863119909119909119881
2
1
1198973+
2119863119909119909119882
2
1
1198973
119879119890=
1
14(119897119868
119860
2
2
+ 119897119868119860
2
2
) +1
6(119897119868
119860
1
2+ 119897119868
11986012)
+1
10(119897119868
119860
2
2
+ 119897119868119860
2
1
+9119868
119863
2
2
119897+ 119897119868
119860
2
1
+9119868
119863
2
2
119897)
+1
4(119897119868
11986012+
6119868119863
1
2
119897+
611986811986312
119897)
+1
6(119897119868
119860
2
1
+4119868
119863
2
1
119897+
4119868119863
2
1
119897)
119882119911= 119865
119862119911sdot [119882
1(119905) + 119882
2(119905)] + 119865
119862119910sdot [119881
1(119905) + 119881
2(119905)]
+ 119898ℎ[2V2
ℎ
1198972sdot 119881
1(119905) +
4V2ℎ
119905
1198972sdot
1(119905) + (
Vℎ119905
119897)
2
sdot 1(119905)
+6V3
ℎ
119905
1198973sdot 119881
2(119905) +
6V3ℎ
1199052
1198973
sdot 2(119905) + (
Vℎ119905
119897)
3
sdot 2(119905)]
times [(Vℎ119905
119897)
2
sdot 1198811(119905) + (
Vℎ119905
119897)
3
sdot 1198812(119905)]
+ 119898ℎ[2V2
ℎ
1198972sdot 119882
1(119905) +
4V2ℎ
119905
1198972sdot
1(119905) + (
Vℎ119905
119897)
2
sdot 1(119905)
+6V3
ℎ
119905
1198973sdot 119882
2(119905) +
6V3ℎ
1199052
1198973sdot
2(119905)
+ (Vℎ119905
119897)
3
sdot 2(119905)]
times [(Vℎ119905
119897)
2
sdot 1198821(119905) + (
Vℎ119905
119897)
3
sdot 1198822(119905)]
+ 1198811(119905) sdot int
119897
0
119902 (119909) (119909
119897)
2
119889119909 + 1198812(119905)
sdot int
119897
0
119902 (119909) (119909
119897)
3
119889119909
Ψ119902=
1
6(36119863
119909119909120578119887
2
2
1198976+
4119860119909119909120578119887
2
2
1198974+
36119863119909119909120578119887
2
2
1198976) 119897
3
+1
4(4119860
11990911990912057811988712
1198973+
2411986311990911990912057811988712
1198975
+24119863
119909119909120578119887
1
2
1198975) 119897
2
+1
2
119860119909119909120578119887
2
1
119897+
2119863119909119909120578119887
2
1
1198973+
2119863119909119909120578119887
2
1
1198973
(44)
36 The Vibration Equation The Lagrange equation methodis used to derive the vibration equations
120597119871
120597119902119899
minus119889
119889119905(
120597119871
120597 119902119899
) + 119876119889= 0 119899 = 1 2 6 (45)
where 119871 is the Lagrange function 119902119899
= (1198801 119880
2 119881
1 119881
2
1198821119882
2)119879 is the vector of the generalized coordinates and
119902119899is the corresponding generalized velocity vector 119876
119889is the
generalized damping force The expressions for 119871 and 119876119889are
as
119871 = 119879119890minus (119880
119894minus 119882
119911)
119876119889= minus
120597Ψ119902
120597 119902119899
(119899 = 1 sim 6)
(46)
The axial vibration equations can be obtained as followsfor 119880
1 119880
2
1
31198971198681198601+
1
41198971198681198602+
120578119887119860
1199091199091
119897+
120578119887119860
1199091199092
119897+
1198601199091199091198801
119897
+119860
1199091199091198802
119897+
2119860119909119909119881
2
1
31198972+
311986011990911990911988111198812
21198972+
9119860119909119909119881
2
2
101198972
+2119860
119909119909119882
2
1
31198972+
3119860119909119909119882
1119882
2
21198972+
9119860119909119909119882
2
2
101198972= 0
(47a)
1
41198971198681198601+
1
51198971198681198602+
120578119887119860
1199091199091
119897+
4120578119887119860
1199091199092
3119897
+119860
1199091199091198801
119897+4119860
1199091199091198802
3119897+119860
119909119909119881
2
1
1198972+12119860
11990911990911988111198812
51198972+3119860
119909119909119881
2
2
21198972
+119860
119909119909119882
2
1
1198972+
12119860119909119909119882
1119882
2
51198972+
3119860119909119909119882
2
2
21198972= 0
(47b)
The following can be seen from the above equations
(1) Since the assumed modes rather than the naturalmodes are used the coupling between axial and trans-verse vibrations is rather severe for axial vibrations
Mathematical Problems in Engineering 11
(2) The nonlinearity is apparent in above equations onlyexisting in the terms of 119881
1 119881
2119882
1119882
2 We take (47a)
as an exampleThe terms including1198802and its first and
second derivative 1198811 119881
2119882
1119882
2 can be regarded as
the applied loads for 1198801
(3) The coupling between the axial and transverse vibra-tionswill disappear as long as the linear displacement-strain relationship is adopted
(4) There are no external loads for axial vibrationsaccording to above equations
The transverse vibration equations for 1198811 119881
2and119882
1 119882
2
can be obtained as
4
3
1198681198631
119897+
1
51198971198681198601+
1
61198971198681198602minus
119898ℎV5ℎ
1199055
2
1198975+
31198681198632
2119897
+4119898
ℎV4ℎ
1199053
1
1198974+
4120578119887119863
1199091199091
1198973minus
2119898ℎV5ℎ
1199054
2
1198975+
6120578119887119863
1199091199092
1198973
+8119898
ℎV4ℎ
1199052
1198811
1198974+
41198631199091199091198811
1198973+
8119898ℎV5ℎ
1199053
1198812
1198975+
61198631199091199091198812
1198973
+27119860
1199091199091198812119882
2
2
81198973+
541198601199091199091198811119881
2
2
71198973+
181198601199091199091198811119882
2
2
71198973
+6119860
119909119909119881
2
1
1198812
1198973+
21198601199091199091198812119882
2
1
1198973+
1211986011990911990911988021198812
51198972
+8119860
1199091199091198811119882
2
1
51198973+
311986011990911990911988011198812
21198972+
211986011990911990911988021198811
1198972
+8119860
119909119909119881
3
1
51198973+
27119860119909119909119881
3
2
81198973+
361198601199091199091198812119882
1119882
2
71198973
+4119860
1199091199091198811119882
1119882
2
1198973+
411986011990911990911988011198811
31198972minus 119865
119888119910(119905) minus 05119865
025119865= 0
1
61198971198681198601+
3
2
1198681198631
119897minus
119898ℎV5ℎ
1199055
1
1198975+
1
71198971198681198602+
9
5
1198681198632
119897
+6120578
119887119863
1199091199091
1198973+
2119898ℎV5ℎ
1199054
1
1198975+
12120578119887119863
1199091199092
1198973+
6119898ℎV6ℎ
1199055
2
1198976
+6119863
1199091199091198811
1198973+
16119898ℎV5ℎ
1199053
1198811
1198975+
121198631199091199091198812
1198973+
18119898ℎV6ℎ
1199054
1198812
1198976
+9119860
1199091199091198812119882
2
2
21198973+
811198601199091199091198811119881
2
2
81198973+
311986011990911990911988011198811
21198972
+27119860
1199091199091198811119882
2
2
81198973+
541198601199091199091198812119881
2
1
71198973+
181198601199091199091198812119882
2
1
71198973
+3119860
11990911990911988021198812
1198972+
21198601199091199091198811119882
2
1
1198973+
911986011990911990911988011198812
51198972+
1211986011990911990911988021198811
51198972
+9119860
119909119909119881
3
2
21198973+
2119860119909119909119881
3
1
1198973+
271198601199091199091198812119882
1119882
2
41198973
+36119860
1199091199091198811119882
1119882
2
71198973minus 04119865
025119865minus 119865
119888119910(119905) = 0
4
3
119868119863
1
119897+
1
5119897119868119860
1+
3
2
119868119863
2
119897+
1
6119897119868119860
2minus
119898ℎV5ℎ
1199055
2
1198975
+4120578
119887119863
119909119909
1
1198973+
4119898ℎV4ℎ
1199053
1
1198974minus
2119898ℎV5ℎ
1199054
2
1198975+
6120578119887119863
119909119909
2
1198973
+4119863
119909119909119882
1
1198973+
8119898ℎV4ℎ
1199052
1198821
1198974+
8119898ℎV5ℎ
1199053
1198822
1198975+
6119863119909119909119882
2
1198973
+36119860
119909119909119882
211988111198812
71198973+
4119860119909119909119882
111988111198812
1198973+
27119860119909119909119882
2119881
2
2
81198973
+18119860
119909119909119882
1119881
2
2
71198973+
54119860119909119909119882
1119882
2
2
71198973+
6119860119909119909119882
2
1
1198822
1198973
+2119860
119909119909119882
2119881
2
1
1198973+
121198601199091199091198802119882
2
51198972+
8119860119909119909119882
1119881
2
1
51198973
+3119860
1199091199091198801119882
2
21198972+
21198601199091199091198802119882
1
1198972+
27119860119909119909119882
3
2
81198973
+8119860
119909119909119882
3
1
51198973+
41198601199091199091198801119882
1
31198972minus 119865
119888119911(119905) = 0
1
7119897119868119860
2+
9
5
119868119863
2
119897+
1
6119897119868119860
1minus
119898ℎV5ℎ
1199055
1
1198975+
3
2
119868119863
1
119897
+6120578
119887119863
119909119909
1
1198973+
2119898ℎV5ℎ
1199054
1
1198975+
6119898ℎV6ℎ
1199055
2
1198976
+12120578
119887119863
119909119909
2
1198973+
6119863119909119909119882
1
1198973+
16119898ℎV5ℎ
1199053
1198821
1198975
+12119863
119909119909119882
2
1198973+
18119898ℎV6ℎ
1199054
1198822
1198976+
31198601199091199091198801119882
1
21198972
+27119860
119909119909119882
211988111198812
41198973+
36119860119909119909119882
111988111198812
71198973+
9119860119909119909119882
2119881
2
2
21198973
+27119860
119909119909119882
1119881
2
2
81198973+
81119860119909119909119882
1119882
2
2
81198973+
18119860119909119909119882
2119881
2
1
71198973
+54119860
119909119909119882
2119882
2
1
71198973+
31198601199091199091198802119882
2
1198972+
2119860119909119909119882
1119881
2
1
1198973
+9119860
1199091199091198801119882
2
51198972+
121198601199091199091198802119882
1
51198972+
2119860119909119909119882
3
1
1198973
+9119860
119909119909119882
3
2
21198973minus 119865
119888119911(119905) = 0
(48)
The complexity high coupling and nonlinearity are obvi-ous in above equations
4 The Coupled Rigid-Flexible Dynamics
The dynamics for control and dynamic simulation shouldbe presented for solar sail based on the simplification ofequations derived in previous sections Some assumptions aremade before simplifying the equations as follows
12 Mathematical Problems in Engineering
(1) Only the attitude motion is affected by the slidingmass the vibration of solar sail structure is notaffected by the sliding mass
(2) Although the attitude control is accomplished byrotating control vanes and the gimbaled controlboom moving sliding masses the specific time his-tories of the actuators are not considered here
(3) The four supporting beams are regarded as an entirestructure thus the identical generalized coordinatesare adopted in the dynamic analysis
41 The Simplified Attitude Dynamics The kinetic energy ofsolar sail supporting beams can be obtained as
119879119898
=1
2120596 sdot J sdot 120596 + 119898
119897int
119897
0
2∘
1205883
sdot (120596 times r3) + (120596 times 120588
3) sdot (120596 times 120588
3)
+ 2 (120596 times r3) sdot (120596 times 120588
3) 119889119911
+ 119898119897int
119897
0
2∘
1205882
sdot (120596 times r2) + (120596 times 120588
2) sdot (120596 times 120588
2)
+ 2 (120596 times r2) sdot (120596 times 120588
2) 119889119910
(49)
The subscripts 2 and 3 represent the second and thirdsupporting beams The displacements can be expressed as
V0119909
(119911 119905) = (119911
119897)
2
sdot 1198811(119905) + (
119911
119897)
3
sdot 1198812(119905)
1199080119910
(119911 119905) = 120572V0119909
(119911 119905) = (119911
119897)
2
sdot 1205721198811(119905) + (
119911
119897)
3
sdot 1205721198812(119905)
for the 3rd beam
V0119909
(119910 119905) = 120573V0119909
(119911 119905) = (119910
119897)
2
sdot 1205731198811(119905) + (
119910
119897)
3
sdot 1205731198812(119905)
1199080119911
(119910 119905) = 120574V0119909
(119910 119905) = (119910
119897)
2
sdot 1205741198811(119905) + (
119910
119897)
3
sdot 1205741198812(119905)
for the 2nd beam
(50)
The subscripts 119909 119910 and 119911 of the left terms in (50)represent the displacements along119909119910 and 119911directions119881
1(119905)
and 1198812(119905) are the generalized coordinates The displacements
1199080119910(119911 119905) V
0119909(119910 119905) and 119908
0119911(119910 119905) can be obtained using the
assumed modes as
1205883= V
0119909(119911 119905) i
119887+ 119908
0119910(119911 119905) j
119887
=
[[[[[
[
(119911
119897)
2
sdot 1198811(119905) + (
119911
119897)
3
sdot 1198812(119905)
120572 [(119911
119897)
2
sdot 1198811(119905) + (
119911
119897)
3
sdot 1198812(119905)]
0
]]]]]
]
1205882= V
0119909(119910 119905) i
119887+ 119908
0119911(119910 119905) k
119887
=
[[[[[
[
120573[(119910
119897)
2
sdot 1198811(119905) + (
119910
119897)
3
sdot 1198812(119905)]
0
120574 [(119910
119897)
2
sdot 1198811(119905) + (
119910
119897)
3
sdot 1198812(119905)]
]]]]]
]
(51)
The vibration velocity can be obtained as
∘
1205883
= 1205883119909i119887+ 120588
3119910j119887=
[[[[[
[
(119911
119897)
2
sdot 1(119905) + (
119911
119897)
3
sdot 2(119905)
1205721[(
119911
119897)
2
sdot 1(119905) + (
119911
119897)
3
sdot 2(119905)]
0
]]]]]
]
∘
1205882
= 1205882119909i119887+ 120588
2119911k119887=
[[[[[
[
1205731[(
119910
119897)
2
sdot 1(119905) + (
119910
119897)
3
sdot 2(119905)]
0
1205741[(
119910
119897)
2
sdot 1(119905) + (
119910
119897)
3
sdot 2(119905)]
]]]]]
]
(52)
Without loss of generality 120572 = 120573 = 1205721= 120573
1= 1 and
120574 = 1205741= minus1 can be assumed in above expressions And the
kinetic energy of the slidingmasses can be obtained as followsby neglecting the vibration related terms
119879ℎ=
1
2119898
ℎ1(120596 times r
ℎ1) sdot (120596 times r
ℎ1) +
1
2119898
ℎ2(120596 times r
ℎ2)
sdot (120596 times rℎ2)
(53)
The kinetic energy of the payload can be obtained as
119879119901=
1
2119898
119901(120596 times r
119901) sdot (120596 times r
119901) (54)
The following simplified attitude dynamics can beobtained by neglecting the second and higher terms ofattitude angles and vibration modes in computing the kinetic
Mathematical Problems in Engineering 13
energies of the supporting beams payload and slidingmasses Consider
119869119909 minus 119898
1198971198972
1minus
4
5119898
1198971198972
2+ 119898
ℎ11199102
ℎ1
+ 119898ℎ21199112
ℎ2
minus 119898119901119903119901119909119903119901119911 + 119898
1199011199032
119901119911
+ 1198981199011199032
119901119910
minus 119898119901119903119901119909119903119901119910
120579 = 119876120593
119869119910
120579 +2
5119898
1198971198972
2+
1
2119898
1198971198972
1+ 119898
ℎ21199112
ℎ2
120579
+ 1198981199011199032
119901119911
120579 minus 119898119901119903119901119910119903119901119911 minus 119898
119901119903119901119909119903119901119910
+ 1198981199011199032
119901119909
120579 = 119876120579
119869119911 minus
2
51198972
1198981198972minus
1
21198972
1198981198971+ 119898
ℎ11199102
ℎ1
minus 119898119901119903119901119910119903119901119911
120579 + 1198981199011199032
119901119910
+ 1198981199011199032
119901119909
minus 119898119901119903119901119909119903119901119911 = 119876
120595
(55)
where 119876120593 119876
120579 and 119876
120595are the generalized nonpotential
attitude control torques generated by the control vanes Andthe attitude control torques generated by the gimbaled controlboom and sliding masses can be found on the left side ofthe above equation coupled with 120579 making the attitudecontroller design problem rather difficult
42 The Simplified Vibration Equations The couplingbetween the axial and transverse vibrations is neglectedand only the transverse vibration is considered The attitudedynamics for dynamic simulation can be obtained as followsbased on previous derivation by neglecting the action ofsolar-radiation pressure
4
3
1198681198631
119897+
1
51198971198681198601+
1
61198971198681198602+
31198681198632
2119897+
4120578119887119863
1199091199091
1198973
+6120578
119887119863
1199091199092
1198973+
41198631199091199091198811
1198973+
61198631199091199091198812
1198973+
271198601199091199091198812119882
2
2
81198973
+54119860
1199091199091198811119881
2
2
71198973+
181198601199091199091198811119882
2
2
71198973+
6119860119909119909119881
2
1
1198812
1198973
+2119860
1199091199091198812119882
2
1
1198973+
81198601199091199091198811119882
2
1
51198973+
8119860119909119909119881
3
1
51198973
+27119860
119909119909119881
3
2
81198973+
361198601199091199091198812119882
1119882
2
71198973+
41198601199091199091198811119882
1119882
2
1198973
minus 1198651198621
(119905) = 0
1
61198971198681198601+
3
2
1198681198631
119897+
1
71198971198681198602+
9
5
1198681198632
119897+
6120578119887119863
1199091199091
1198973
+12120578
119887119863
1199091199092
1198973+
61198631199091199091198811
1198973+
121198631199091199091198812
1198973+
91198601199091199091198812119882
2
2
21198973
+81119860
1199091199091198811119881
2
2
81198973+
271198601199091199091198811119882
2
2
81198973+
541198601199091199091198812119881
2
1
71198973
+18119860
1199091199091198812119882
2
1
71198973+
21198601199091199091198811119882
2
1
1198973+
9119860119909119909119881
3
2
21198973
+2119860
119909119909119881
3
1
1198973+
271198601199091199091198812119882
1119882
2
41198973+
361198601199091199091198811119882
1119882
2
71198973
minus 1198651198622
(119905) = 0
(56)
The following equations can be obtained by rearrangingthe above equations
4
3
1198681198631
119897+
1
51198971198681198601+
1
61198971198681198602+
31198681198632
2119897+
4120578119887119863
1199091199091
1198973
+6120578
119887119863
1199091199092
1198973+
41198631199091199091198811
1198973+
61198631199091199091198812
1198973+
16119860119909119909119881
3
1
51198973
+12119860
119909119909119881
2
1
1198812
1198973+
1081198601199091199091198811119881
2
2
71198973+
54119860119909119909119881
3
2
81198973
minus 1198651198621
(119905) = 0
1
61198971198681198601+
3
2
1198681198631
119897+
1
71198971198681198602+
9
5
1198681198632
119897+
6120578119887119863
1199091199091
1198973
+12120578
119887119863
1199091199092
1198973+
61198631199091199091198811
1198973+
121198631199091199091198812
1198973
+4119860
119909119909119881
3
1
1198973+
108119860119909119909119881
2
1
1198812
71198973+
811198601199091199091198811119881
2
2
41198973
+9119860
119909119909119881
3
2
1198973minus 119865
1198622(119905) = 0
(57)
1198651198621(119905) and 119865
1198622(119905) are used to represent all the generalized
external forces they can be used for vibration control Thesecomplicated equations abovementioned are the basis forobtaining the simplified equations used for controller design
The following equations can be obtained by neglecting thetwo and higher terms
4
3
1198681198631
119897+
1
51198971198681198601+
1
61198971198681198602+
31198681198632
2119897+
4120578119887119863
1199091199091
1198973
+6120578
119887119863
1199091199092
1198973+
41198631199091199091198811
1198973+
61198631199091199091198812
1198973= 119865
1198621
(119905)
14 Mathematical Problems in Engineering
1
61198971198681198601+
3
2
1198681198631
119897+
1
71198971198681198602+
9
5
1198681198632
119897+
6120578119887119863
1199091199091
1198973
+12120578
119887119863
1199091199092
1198973+
61198631199091199091198811
1198973+
121198631199091199091198812
1198973= 119865
1198622
(119905)
(58)
43 The Rigid-Flexible Coupled Dynamics The simplifiedattitude and vibration dynamics can be written as
119886120593 + 119886
120579
120579 + 119886120595 + 119886
1198811
1+ 119886
1198812
2= 119876
120593
119887120579
120579 + 119887120595 + 119887
120593 + 119887
1198811
1+ 119887
1198812
2= 119876
120579
119888120595 + 119888
120579
120579 + 119888120593 + 119888
1198811
1+ 119888
1198812
2= 119876
120595
119889
1198811
1+ 119889
1198812
2+ 119889
1198811
1+ 119889
1198812
2+ 119889
1198811
1198811
+ 1198891198812
1198812= 119876
1198811
119890
1198811
1+ 119890
1198812
2+ 119890
1198811
1+ 119890
1198812
2+ 119890
1198811
1198811
+ 1198901198812
1198812= 119876
1198812
(59)
The related coefficients in the preceding equation can befound in (A1) in the appendix The dynamics (see (59)) isnot suitable for attitude controller design because the controlinputs exist in some coefficients of the angular accelerationsThis will make the controller design rather difficult Thusthe following dynamic model is obtained by putting theterms including the control inputs right side of the dynamicequations
119869119909 minus 119898
1198971198972
1minus
4
5119898
1198971198972
2= 119876
120593+ 119906
119869119910
120579 +2
5119898
1198971198972
2+
1
2119898
1198971198972
1= 119876
120579+ 119906
120579
119869119911 minus
1
21198972
1198981198971minus
2
51198972
1198981198972= 119876
120595+ 119906
119889
1198811
1+ 119889
1198812
2+ 119889
1198811
1+ 119889
1198812
2
+ 1198891198811
1198811+ 119889
1198812
1198812= 119876
1198811
119890
1198811
1+ 119890
1198812
2+ 119890
1198811
1+ 119890
1198812
2
+ 1198901198811
1198811+ 119890
1198812
1198812= 119876
1198812
(60)
The expressions for 119906 119906
120579
and 119906are as
119906= minus119898
ℎ11199102
ℎ1
minus 119898ℎ21199112
ℎ2
+ 119898119901119903119901119909119903119901119911 minus 119898
1199011199032
119901119911
minus 1198981199011199032
119901119910
+ 119898119901119903119901119909119903119901119910
120579
119906
120579
= minus119898ℎ21199112
ℎ2
120579 minus 1198981199011199032
119901119911
120579 + 119898119901119903119901119910119903119901119911 + 119898
119901119903119901119909119903119901119910
minus 1198981199011199032
119901119909
120579
119906= minus119898
ℎ11199102
ℎ1
+ 119898119901119903119901119910119903119901119911
120579 minus 1198981199011199032
119901119910
minus 1198981199011199032
119901119909
+ 119898119901119903119901119909119903119901119911
(61)
119906 119906
120579
and 119906are the functions of the positions of sliding
masses and payload and the angular accelerations The statevariables in (60) are defined as
1199091= 120593 119909
2= 119909
3= 120579 119909
4= 120579
1199095= 120595 119909
6= 119909
7= 119881
1
1199098=
1 119909
9= 119881
2 119909
10=
2
(62)
Thedynamics (60) can bewritten as the state-spacemodelas following
1= 119909
2
2= 119886
11199097+ 119886
21199098+ 119886
31199099+ 119886
411990910
+ 119906120593
3= 119909
4
4= 119886
51199097+ 119886
61199098+ 119886
71199099+ 119886
811990910
+ 119906120579
5= 119909
6
6= 119886
91199097+ 119886
101199098+ 119886
111199099+ 119886
1211990910
+ 119906120595
7= 119909
8
8= 119886
131199097+ 119886
141199098+ 119886
151199099+ 119886
1611990910
+ 1199061198811
9= 119909
10
10
= 119886171199097+ 119886
181199098+ 119886
191199099+ 119886
2011990910
+ 1199061198812
(63)
where 119906120579 119906
120593 and 119906
120595are the generalized control inputs
for attitude control and 1199061198811
and 1199061198812
are the generalizedcontrol inputs for vibration control The controllability canbe satisfied by analyzing (63) The attitudevibration controlinputs and the coefficients will be presented later in thissection The form of a matrix differential equation can bewritten as follows for the above equation
x = Ax + Bu (64)
The expressions of the relatedmatrices and vectors can befound as
x = [1
2
3
4
5
6
7
8
9
10]119879 x (119905
0) = x
1199050
u = [119906120593 119906
120579 119906
120595 119906
1198811
1199061198812
]119879
u (1199050) is known
(65)
where A xB and u are the system matrix state variablesvector control matrix and control inputs vector respectively
Mathematical Problems in Engineering 15
The complexity of the state-space model can be seen bypresenting the detailed expressions of control inputs forattitudevibration and related parameters in (A2) in theappendix
5 AttitudeVibration Control and Simulation
The controller for the attitude and vibration is developedusing the LQR and optimal PI theory The dynamic simula-tion is performed based on the coupled dynamics derived inthe previous sections
51 LQR and Optimal PI Based Controllers Design Thedynamics for solar sail can bewritten as follows togetherwithits quadratic cost function also defined as
x = Ax + Bu x (1199050) = x
1199050
(known)
119869 =1
2int
infin
1199050
[x119879 (119905)Qx (119905) + u119879 (119905)Ru (119905)] 119889119905
(66)
whereQ = Q119879
⩾ 0 andR = R119879
gt 0 are constantThe control-lability of [AB] and the observability of [AD] can beensured when the equationDD119879
= Q holds for anymatrixDThe optimal control input ulowast(119905)within the scope of u(119905) isin R119903119905 isin [119905
0infin] can be computed as follows to make 119869minimum
ulowast (119905) = minusKxlowast (119905) K = Rminus1B119879P (67)
where P is the nonnegative definite symmetric solution of thefollowing Riccati algebraic equations
PA + A119879P minus PBRminus1B119879P +Q = 0 (68)
And the optimal performance index can be obtained asfollows for arbitrary initial states
119869lowast
[x (1199050) 119905
0] =
1
2x1198790
Px0 (69)
The closed-loop system
x = (A minus BRminus1B119879P) x (70)
is asymptotically stableFor an orbiting solar sail the primary disturbance torque
is by the cmcp offset and the impact of the tiny dust inthe deep space The state regulator can be used to controlthe dynamic system affected by pulse disturbance torquewith good steady-state errors but will never achieve accuratesteady-state errors if the dynamics is affected by constantdisturbance torque Thus the optimal state regulator withan integrator to eliminate the constant disturbance torqueshould be presented This optimal proportional-integral reg-ulator not only eliminates the constant disturbance torque butalso possesses the property of optimal regulator
Table 1 The related parameters
Parameters ValuesCMCP offsetm [0 017678 017678]119879
The side length of square sailm 100Nominal solar-radiation pressureconstant at 1 AU from the sunNm2 4563 times 10minus6
Solar-radiation pressure forceN 912 times 10minus2
Roll inertiakglowastm2 50383Pitch and yaw inertiakglowastm2 251915Outer radiusm 0229Thickness of the supporting beamm 75 times 10minus6
Youngrsquos modulus of the supportingbeamGPa 124
Moment of inertia of the cross-sectionof the supporting beamm4 2829412 times 10minus7
Bending stiffness of the supportingbeamNlowastm2 3508471336
Proportional damping coefficient ofsupporting beams 001
Line density of the supportingbeamkgm 0106879
Cross-sectional area of the supportingbeamm2 1079 times 10minus5
Roll disturbance torqueNlowastm 0Pitch (yaw) disturbance torqueNlowastm 0016122 (minus0016122)
For the following linear system with the correspondingperformance index
x = Ax + Bu x (1199050) = x
1199050
u (1199050) = u
1199050
119869 =1
2int
infin
1199050
(x119879Qx + u119879Ru + u119879Su) 119889119905(71)
where Q = Q119879
⩾ 0 R = R119879
gt 0 and S = S119879 gt 0 If [AB]is completely controllable and meanwhile [AD
11] is com-
pletely observable with the relationship D11D119879
11
= Q thesolution can be expressed as
ulowast = minusK1x minus K
2ulowast ulowast (119905
0) = u
1199050
(72)
If B119879B is full rank we can get
ulowast = minusK3x minus K
4x ulowast (119905
0) = u
1199050
(73)
K119894(119894 = 1 2 3 4) is the function of ABQR S
The closed-loop system
[xulowast] = [
A BminusK
1minusK
2
] [xulowast] [
[
x (1199050)
u (1199050)]
]
= [x1199050
u1199050
] (74)
is asymptotically stableThe compromise between the state variables (the angle
angular velocity the vibration displacement and velocity)and control inputs (the torque by all the actuators) can
16 Mathematical Problems in Engineering
0 2000 4000 6000
0 2000 4000 6000
0 2000 4000 6000minus5
0
5
minus5
0
5
minus5
0
5
minus4
minus2
0
2
4
times10minus4
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
00162
00164
00166
4800 4900 5000
4800 4900 5000
4800 4900 5000
minus00165
minus0016
Time (s) Time (s)
Time (s)
Time (s)
Time (s)
Time (s)
Roll
erro
r120593(∘
)
Roll
erro
r120593(∘
)
Pitc
h er
ror120579
(∘)
Pitc
h er
ror120579
(∘)
Yaw
erro
r120595(∘
)
Yaw
erro
r120595(∘
)
Figure 8 The roll pitch and yaw errors
be achieved by using both the LQR based and optimal PIbased controllers for the coupled attitudevibration dynamicsystem The fact is that the attitude control ability is limitedto the control torque by the control actuators The change ofthe attitude angles and rates should not be frequent to voidexciting vibrations
Thus the weighting matrix Q and the control weightingmatrix R are selected as follows for LQR based controller
Q (1 1) = 9 times 10minus6
Q (2 2) = 1 times 10minus6
Q (3 3) = 16 times 10minus6
Q (4 4) = Q (5 5) = Q (6 6) = Q (7 7) = Q (8 8)
= Q (9 9) = Q (10 10) = 1 times 10minus6
Q (119894 119895) = 0 (119894 = 119895 119894 119895 = 1 sim 10)
R (1 1) = R (2 2) = 900 R (3 3) = 100
R (4 4) = R (5 5) = 10000
R119894119895
= 0 (119894 = 119895 119894 119895 = 1 sim 5)
(75)
TheweightingmatrixQ and the control weightingmatrixR are selected as follows for the optimal PI based controller
Q (1 1) = Q (2 2) = 4 times 10minus8
Q (3 3) = Q (4 4) = Q (5 5) = Q (6 6) = Q (7 7)
= Q (8 8) = 16 times 10minus8
Mathematical Problems in Engineering 17
minus02
0
02
Roll
rate
(∘s)
Roll
rate
(∘s)
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Pitc
h ra
te(∘s)
Pitc
h ra
te(∘s)
0 1000 2000 3000 4000 5000
minus05
0
05
minus05
0
05
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
Time (s)
Yaw
rate
(∘
s)
Yaw
rate
(∘
s)
4800 4850 4900 4950 5000
Time (s)4800 4850 4900 4950 5000
Time (s)4800 4850 4900 4950 5000
minus2
0
2
minus2
0
2
minus2
0
2
times10minus4
times10minus4
times10minus4
Figure 9 The roll pitch and yaw rates
Q (9 9) = Q (10 10) = 1 times 10minus8
Q (119894 119895) = 0 (119894 = 119895 119894 119895 = 1 sim 10)
R (1 1) = R (2 2) = R (3 3) = 1 times 10minus8
R (4 4) = R (5 5) = 4 times 10minus8
R (119894 119895) = 0 (119894 = 119895 119894 119895 = 1 sim 5)
(76)
52 The Simulation Results The initial angle errors of rollpitch and yaw are adopted as 120593(119905
0) = 3
∘ 120579(1199050) = 3
∘ and120595(119905
0) = 3
∘ the initial angular velocity errors of roll pitchand yaw are adopted as (119905
0) = 0
∘
s 120579(1199050) = 0
∘
s and(119905
0) = 0
∘
s 1198811(1199050) = 01m 119881
2(1199050) = 01m
1(1199050) = 0ms
and 2(1199050) = 0ms are adopted in this paper for dynamic
simulationThe estimated cmcp offset is 025m for a 100 times 100m
square solar sail It is assumed that the components of cmcpoffset vector are [0 017678 017678]
119879 in the body frame
The relevant parameters for dynamic simulations are givenin Table 1
The dynamic simulation results are obtained as followsby using the LQR controller based on the abovementionedQ and R related parameters and initial conditions Thedynamics simulations with (denoted by ldquowith GFrdquo) andwithout (denoted by ldquowithout GFrdquo) considering the geo-metrical nonlinearity are presented And the correspondingdiscussions and analysis are also given according to thecalculated results
The roll pitch and yaw errors are presented based onthe dynamics models with and without considering thegeometrical nonlinearityThe control effect with zero steady-state error can be achieved for roll axis by referring tothe results But the steady-state errors exist for pitch andyaw axes from Figure 8 this is because there exist constantdisturbance torques for pitch and yaw axes caused by thecmcp offset Thus the LQR based controller cannot be usedfor attitude control with good steady-state performance Thesteady-state errors of pitch and yaw axes are about 0164
∘
and minus0164∘ respectively from the corresponding partial
enlarged drawing of the figures (see the corresponding left
18 Mathematical Problems in Engineering
minus20
0
20
Roll
torq
ue (N
lowastm
)
Roll
torq
ue (N
lowastm
)
minus50
0
50
minus50
0
50
Pitc
h to
rque
(Nlowast
m)
Pitc
h to
rque
(Nlowast
m)
0 1000 2000 3000 4000 5000
0 2000 4000 6000
0 2000 4000 6000
Yaw
torq
ue (N
lowastm
)
Yaw
torq
ue (N
lowastm
)
minus002
0
002
008
01
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
minus01
minus009
minus008
Time (s)Time (s)
Time (s)Time (s)
Time (s)Time (s)
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Figure 10 The roll pitch and yaw torques
figures) A simple and practical controller should be designedto eliminate the steady-state errorsThese errorswill affect theprecision of the super long duration space mission deeply
The differences between the dynamics with and withoutthe geometrical nonlinearity effect can be observed Theamplitudes and phases change a bit by comparing the corre-sponding results
It can be observed by the partial enlarged figures(the right figures of Figure 9) that there are no steady-stateerrors for roll pitch and yaw rates The relative satisfieddynamic performance is achieved In fact a result with muchmore satisfied dynamic performance can be obtained but itwill make the desired control torques much larger duringthe initial period This will not only excite the vibration ofthe structure but also increase the burden of the controlactuators
And the differences between the dynamics models withand without the geometrical nonlinearity can also be seenmerely in the phase of the angular velocities
The desired attitude control torques are presented inFigure 10 The roll torque will tend to be zero with thedecrement of the state variable errors The pitch and yawtorques tend to be constant from the middle and bottom
figures The pitch and yaw steady-state errors can never beeliminated although the pitch and yaw torques (009Nlowastmand minus009Nlowastm) are applied continuously by theoreticalanalysis and simulations This is just a great disadvantage ofthe LQR based controller in this paper The initial controltorques can be afforded by vibrating the gimbaled controlboom andmoving the slidingmasses that can afford a relativelarge torque The control vanes can be used to afford thecontrol torques when solar sail is in steady-state process Theexpression of the attitude control inputs 119906
120593 119906
120579 and 119906
120595can be
found in previous sectionMoreover the differences between dynamics responses
with and without geometrical nonlinearity can also beobserved by comparing the corresponding results Therequired torques for the attitude control are a little largerfor the dynamics with geometrical nonlinearity And thedifference in the phase is also clear
It can be seen that the vibration of the supporting beamis depressed effectively by the simulation results in Figure 11It can be seen that the steady-state errors and the dynamicperformance are relatively satisfied It can also be seen that thedynamics responses between the model with and without the
Mathematical Problems in Engineering 19
0 1000 2000 3000 4000 5000
0 1000 2000 3000 4000 5000
minus01
0
01
minus02
0
02
Time (s) Time (s)
Time (s) Time (s)
minus5
0
5
times10minus4
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
minus1
0
1
times10minus3
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
The d
ispla
cem
ent o
f the
tip
(m)
The d
ispla
cem
ent o
f the
tip
(m)
The v
eloci
ty o
f the
tip
(ms
)
The v
eloc
ity o
f the
tip
(ms
)
Figure 11 The displacement and velocity of the tip of the supporting beam
geometrical nonlinearity effect are different in the vibrationdisplacement and velocitymagnitudes and phases (Figure 15)
The simulation results can be obtained as follows by usingthe optimal PI based controller adopting the abovementionedparameters and initial conditions
The roll pitch and yaw errors are given by using theoptimal PI based controller These errors tend to disappearby observing the partially enlarged plotting of the figure (thecorresponding right figures) (shown in Figure 12) And therelative satisfied dynamic performance can also be obtainedFrom the view of eliminating the steady-state errors the opti-mal PI based controller performs better than the LQR basedcontroller by theoretical analysis and simulation results Theformer can achieve attitude control results without pitchand yaw steady-state errors From the view of dynamicperformance both the controllers perform well In additionit can be seen that the difference between the modelswith and without geometrical nonlinearity is merely inthe phase
The roll pitch and yaw rate errors are presented inFigure 13 The dynamic and steady-state performances aresatisfied by observing the simulation results And by observ-ing the difference between the dynamics responses with and
without the influence by the geometrical nonlinearity it canbe concluded that the merely difference is the phase
The desired control torques of the roll pitch and yaw areobtained in Figure 14 by using the optimal PI based controllerIt can be seen that the value of the desired roll control torquedecreases to zero as the values of the roll angle and ratedecrease to zero The desired pitch and yaw control torquestend to be the constant values 009Nlowastm and minus009Nlowastmrespectively The desired initial control torques are large byobserving Figure 14 It is suggested that the gimbaled controlboom combining the sliding masses is adopted to afford theinitial torque Then the control vanes can be used to controlthe solar sail after the initial phase The phase differencecan also be observed by inspecting the dynamics responsesduring the 4800sim5000 s period
The vibration can be controlled effectively based on theoptimal PI controller And the relative satisfied dynamicand steady-state performances can be achieved In additionthe tiny differences exist in the magnitudes of the requiredtorques And the phase differences also exist
It can be concluded as follows by analyzing and compar-ing the simulation results based on the LQR and optimal PItheories in detail
20 Mathematical Problems in Engineering
Roll
erro
r120593(∘
)
Roll
erro
r120593(∘
)
minus5
0
5
minus5
0
5
Pitc
h er
ror120579
(∘)
Pitc
h er
ror120579
(∘)
0 1000 2000 3000 4000 5000minus10
0
10
Time (s) Time (s)
Time (s)
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
Yaw
erro
r120595(∘
)
Yaw
erro
r120595(∘
)
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
minus1
0
1
times10minus3
minus1
0
1
times10minus3
minus1
0
1
times10minus3
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Figure 12 The roll pitch and yaw errors
(1) From the view of eliminating the steady-state errorsof the pitch and yaw errors the optimal PI based con-troller performs better than the LQR based controllerby theoretical analysis and simulation results Thedynamic performances of the two controllers are bothsatisfied and the desired control torques are relativelysmall
(2) The weighting of the state variables is reflected by theweighting matrix according to the LQR and optimalPI theories The constant weighting matrices selectedin this paper can effectively reflect the initial statevariable errors but maybe reflect the final state vari-able errors deficiently The time-varying weightingmatrices should be selected
(3) For the actual orbiting solar sail the control actuators(control vanes gimbaled control boom and slidingmasses) cannot afford excessive large control torquesThus the control torques should be as small as possibleon the premise of acquiring satisfied dynamic perfor-mance and steady-state errors It will not only reducethe burden of the control actuators but also avoid
exciting structural vibration In engineering practicethe weighting matrices and the control weightingmatrices should be selected based on the attitudecontrol requirement (eg dynamic performance andsteady-state errors etc)
(4) The dynamics responses influenced by the geometri-cal nonlinearity can be observed In a word the tinydifferences between the magnitudes of the physicalvariables exist for the models with and withoutthe geometrical nonlinearity And the relative cleardifferences exist in the phases for the attitude anglesrates required torques and so forth
6 Conclusions
The coupled attitude and structural dynamics is establishedfor the highly flexible sailcraft by using the von-Karman von-Karmanrsquos nonlinear strain-displacement relationships basedon assumptions of large deflections moderate rotationsand
Mathematical Problems in Engineering 21
Roll
rate
erro
r(∘ s
)
Roll
rate
erro
r(∘ s
)
minus01
0
01
minus01
0
01
Pitc
h ra
te er
ror (
∘ s)
Pitc
h ra
te er
ror (
∘ s)
0 1000 2000 3000 4000 5000minus02
0
02
Yaw
rate
erro
r (∘ s
)
Yaw
rate
erro
r (∘ s
)
4800 4850 4900 4950 5000
minus5
0
5times10minus4
minus5
0
5
times10minus4
minus5
0
5times10minus4
Time (s)
4800 4850 4900 4950 5000
Time (s)
4800 4850 4900 4950 5000
Time (s)
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Figure 13 The roll pitch and yaw rate errors
small strains The Lagrange equation method is utilizedto derive the dynamics for controller design and dynamicsimulation The LQR and optimal PI based controllers aredesigned for the dynamics with the constant disturbancetorque caused by the cmcp offset By theoretical analysisand simulation it can be seen that both controllers cancompromise between the state variables and control inputsBecause the control actuators can hardly afford large controltorque the dynamic performance should be relaxed toreduce the requirement for the attitude control actuatorsBesides the optimal PI based controller can also eliminatethe constant disturbance torque caused by the cmcp offsetthat always exists while the LQR based controller fails toachieve the results with satisfied steady-state performancealthough the attitude control torque is always applied to thecoupled dynamic systemThe dynamics simulations with andwithout the geometrical nonlinearity effect are also carriedout And the differences between the models in magnitudesand phases are identified and analyzed It can be concludedthat the optimal PI based controller performs better than the
LQRbased controller from the viewof eliminating the steady-state error caused by the disturbance torque by the cmcpoffset
Appendix
The related parameters in above equation are given as
119886120593= 119869
119909+ 119898
ℎ11199102
ℎ1
+ 119898ℎ21199112
ℎ2
+ 1198981199011199032
119901119911
+ 1198981199011199032
119901119910
119886120579= minus 119898
119901119903119901119909119903119901119910 119886
120595= minus119898
119901119903119901119909119903119901119911
1198861198811
= minus 1198981198971198972
1198861198812
= minus4
5119898
1198971198972
119887120579= 119869
119910+ 119898
ℎ21199112
ℎ2
+ 1198981199011199032
119901119911
+ 1198981199011199032
119901119909
119887120595= minus 119898
119901119903119901119910119903119901119911 119887
120593= minus119898
119901119903119901119909119903119901119910
22 Mathematical Problems in Engineering
Roll
torq
ue (N
lowastm
)
Roll
torq
ue (N
lowastm
)
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
0 2000 4000 6000
0 2000 4000 6000
0 2000 4000 6000
Time (s)
Time (s)
Time (s)
Time (s)
Time (s)
Time (s)4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
minus01
minus008
008
009
01
minus002
0
002
minus5
0
5
minus2
0
2
Pitc
h to
rque
(Nlowast
m)
Pitc
h to
rque
(Nlowast
m)
minus2
0
2
Yaw
torq
ue (N
lowastm
)
Yaw
torq
ue (N
lowastm
)
Figure 14 The roll pitch and yaw torques
1198871198811
=1
2119898
1198971198972
1198871198812
=2
5119898
1198971198972
119888120595= 119869
119911+ 119898
ℎ11199102
ℎ1
+ 1198981199011199032
119901119910
+ 1198981199011199032
119901119909
119888120579= minus 119898
119901119903119901119910119903119901119911 119888
120593= minus119898
119901119903119901119909119903119901119911
1198881198811
= minus1
21198972
119898119897 119888
1198812
= minus2
51198972
119898119897
119889
1198811
= (4
3
119868119863
119897+
1
5119897119868119860) 119889
1198812
= (1
6119897119868119860+
3119868119863
2119897)
119889
1198811
=4120578
119887119863
119909119909
1198973 119889
1198812
=6120578
119887119863
119909119909
1198973
1198891198811
=4119863
119909119909
1198973 119889
1198812
=6119863
119909119909
1198973
1198761198811
= 1198651198621
(119905)
119890
1198811
= (3
2
119868119863
119897+
1
6119897119868119860)
119890
1198812
= (1
7119897119868119860+
9
5
119868119863
119897) 119890
1198811
=6120578
119887119863
119909119909
1198973
119890
1198812
=12120578
119887119863
119909119909
1198973 119890
1198811
=6119863
119909119909
1198973
1198901198812
=12119863
119909119909
1198973 119876
1198812
= 1198651198622
(119905)
(A1)
The detailed expressions of control inputs for attitudevibration and related parameters in the state-space model ofthe dynamics (see (62) and (63)) are presented as follows
A =
[[[[[[[[[[[[[[
[
0 1 0 0 0 0 0 0 0 0
0 0 0 0 0 0 1198861
1198862
1198863
1198864
0 0 0 1 0 0 0 0 0 0
0 0 0 0 0 0 1198865
1198866
1198867
1198868
0 0 0 0 0 1 0 0 0 0
0 0 0 0 0 0 1198869
11988610
11988611
11988612
0 0 0 0 0 0 0 1 0 0
0 0 0 0 0 0 11988613
11988614
11988615
11988616
0 0 0 0 0 0 0 0 0 1
0 0 0 0 0 0 11988617
11988618
11988619
11988620
]]]]]]]]]]]]]]
]
Mathematical Problems in Engineering 23
0 1000 2000 3000 4000 5000
0 1000 2000 3000 4000 5000
minus01
0
01
minus02
0
02
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Time (s)
Time (s)Time (s)
Time (s)
minus1
0
1
minus1
0
1
times10minus3
times10minus3Th
e disp
lace
men
t of t
he ti
p (m
)
The d
ispla
cem
ent o
f the
tip
(m)
The v
eloci
ty o
f the
tip
(ms
)
The v
eloci
ty o
f the
tip
(ms
)
Figure 15 Vibration displacement and velocity of the tip
B =
[[[[[[[[[[[[[[
[
0 0 0 0 0
1 0 0 0 0
0 0 0 0 0
0 1 0 0 0
0 0 0 0 0
0 0 1 0 0
0 0 0 0 0
0 0 0 1 0
0 0 0 0 0
0 0 0 0 1
]]]]]]]]]]]]]]
]
1198861= minus
1198981198971198972
119869119909
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus4
5119869119909
1198981198971198972
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198862= minus
1198981198971198972
119869119909
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus4
5119869119909
1198981198971198972
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198863= minus
1198981198971198972
119869119909
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus4
5119869119909
1198981198971198972
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198864= minus
1198981198971198972
119869119909
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus4
5119869119909
1198981198971198972
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
119906120593=
119876120593
119869119909
+
119906
119869119909
+119898
1198971198972
119869119909
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+4
5119869119909
1198981198971198972
+
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198865=
1
2119869119910
1198981198971198972
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+2
5119869119910
1198981198971198972
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198866=
1
2119869119910
1198981198971198972
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+2
5119869119910
1198981198971198972
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198867=
1
2119869119910
1198981198971198972
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+2
5119869119910
1198981198971198972
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198868=
1
2119869119910
1198981198971198972
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
24 Mathematical Problems in Engineering
+2
5119869119910
1198981198971198972
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
119906120579=
119876120579
119869119910
+119906
120579
119869119910
minus1
2119869119910
1198981198971198972
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119910
1198981198971198972
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198869= minus
1
2119869119911
1198972
119898119897
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988610
= minus1
2119869119911
1198972
119898119897
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988611
= minus1
2119869119911
1198972
119898119897
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988612
= minus1
2119869119911
1198972
119898119897
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
119906120595=
119876120595
119869119911
+
119906
119869119911
+1
2119869119911
1198972
119898119897
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+2
5119869119911
1198972
119898119897
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988613
= minus
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988614
= minus
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988615
= minus
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988616
= minus
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
1199061198811
=
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988617
= minus
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988618
= minus
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988619
= minus
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988620
= minus
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1199061198812
=
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(A2)
Conflict of Interests
The authors declare that there is no conflict of interestsregarding the publication of this paper
Acknowledgments
The authors would like to thank the anonymous reviewers fortheir critical and constructive review of the paper This studywas cosupported by the National Natural Science Foundationof China (Project no 11302134 11272101)
References
[1] M Colin Solar Sailing Technology Dynamics and MissionApplications Springer-Praxis London UK 1st edition 1999
[2] V Lappas SWokesM Leipold A Lyngvi and P Falkner ldquoGui-dance and control for an Interstellar Heliopause Probe (IHP)solar sail mission to 200 AUrdquo in Proceedings of the AIAAGuidance Navigation and Control Conference and Exhibit pp2472ndash2492 San Francisco Calif USA August 2005
[3] L Charlotte C Camilla and C McInnes ldquoSolar radiation pres-sure augmented deorbiting fromhigh altitude sun-synchronousorbitsrdquo in Proceedings of the 4S Symposium 2012 Small SatellitesSystems and Services Portoroz Slovenia 2012
[4] M Ceriotti and C RMcInnes ldquoGeneration of optimal trajecto-ries for Earth hybrid pole sittersrdquo Journal of Guidance Controland Dynamics vol 34 no 3 pp 847ndash859 2011
[5] S Gong J Li andH Baoyin ldquoSolar sail transfer trajectory fromL1 point to sub-L1 pointrdquoAerospace Science and Technology vol15 no 7 pp 544ndash554 2011
[6] S Gong J Li and H Baoyin ldquoAnalysis of displaced solar sailorbits with passive controlrdquo Journal of Guidance Control andDynamics vol 31 no 3 pp 782ndash785 2008
[7] S Gong H Baoyin and J Li ldquoSolar sail three-body transfertrajectory designrdquo Journal of Guidance Control and Dynamicsvol 33 no 3 pp 873ndash886 2010
Mathematical Problems in Engineering 25
[8] S Gong J Li H Baoyin and J Simo ldquoA new solar sail orbitrdquoScience China Technological Sciences vol 55 no 3 pp 848ndash8552012
[9] Y Tsuda O Mori R Funase et al ldquoAchievement of IKAROS-Japanese deep space solar sail demonstration missionrdquo ActaAstronautica vol 82 no 2 pp 183ndash188 2013
[10] L Johnson MWhorton A Heaton R Pinson G Laue and CAdams ldquoNanoSail-D a solar sail demonstration missionrdquo ActaAstronautica vol 68 no 5-6 pp 571ndash575 2011
[11] B Wie and D Murphy ldquoSolar-sail attitude control design for asail flight validation missionrdquo Journal of Spacecraft and Rocketsvol 44 no 4 pp 809ndash821 2007
[12] B Wie D Murphy M Paluszek and S Thomas ldquoRobust atti-tude control systems design for solar sails part 1 propellantlessprimaryACSrdquo inProceedings of the AIAAGuidance Navigationand Control Conference and Exhibit Providence RI USAAugust 2004
[13] B Wie D Murphy M Paluszek and S Thomas ldquoRobust atti-tude control systems design for solar sails part 2 MicroPPT-based secondary ACSrdquo in Proceedings of the AIAA GuidanceNavigation and Control Conference and Exhibit pp 1325ndash1340Providence RI USA August 2004
[14] S Thomas M Paluszek B Wie and D Murphy ldquoAOCS per-formance and stability validation for large flexible solar sailspacecraftrdquo in Proceedings of the 41st AIAAASMESAEASEEJoint Propulsion Conference amp Exhibit Tucson Ariz USA 2005
[15] B Wie ldquoDynamic modeling and attitude control of solar sailspacecraft part Irdquo in Proceedings of the AIAAGuidance Naviga-tion and Control Conference and Exhibit Monterey Calif USAAugust 2002
[16] BWie ldquoSolar sail attitude control and dynamics part 1rdquo Journalof Guidance Control and Dynamics vol 27 no 4 pp 526ndash5352004
[17] B Wie ldquoDynamic modeling and attitude control of solar sailspacecraft part IIrdquo in Proceedings of the AIAA Guidance Nav-igation and Control Conference and Exhibit Monterey CalifUSA August 2002
[18] BWie ldquoSolar sail attitude control and dynamics part 2rdquo Journalof Guidance Control and Dynamics vol 27 no 4 pp 536ndash5442004
[19] C Luo and J-H Zheng ldquoSolar-sail attitude control based onmoving masses and roll stabilizer barsrdquo Journal of HarbinInstitute of Technology vol 43 no 3 pp 95ndash101 2011
[20] D Romagnoli and T Oehlschlagel ldquoHigh performance twodegrees of freedom attitude control for solar sailsrdquo Advances inSpace Research vol 48 no 11 pp 1869ndash1879 2011
[21] C Scholz D Romagnoli B Dachwald and S Theil ldquoPerfor-mance analysis of an attitude control system for solar sails usingsliding massesrdquo Advances in Space Research vol 48 no 11 pp1822ndash1835 2011
[22] A Bolle and C Circi ldquoSolar sail attitude control through in-plane moving massesrdquo Journal of Aerospace Engineering vol222 no 1 pp 81ndash94 2008
[23] M RotunnoM Basso A B Pome andM Sallusti ldquoA compari-son of robust attitude control techniques for a solar sail space-craftrdquo in Proceedings of the AIAA Guidance Navigation andControl Conference and Exhibit San Francisco Calif USA2005
[24] J Zhang K Zhai and T Wang ldquoControl of large angle maneu-vers for the flexible solar sailrdquo Science China Physics Mechanicsand Astronomy vol 54 no 4 pp 770ndash776 2011
[25] J Zhang andTWang ldquoCoupled attitude-orbit control of flexiblesolar sail for displaced solar orbitrdquo Journal of Spacecraft andRockets vol 50 no 3 pp 675ndash685 2013
[26] Q Li XMa and TWang ldquoReducedmodel for flexible solar saildynamicsrdquo Journal of Spacecraft and Rockets vol 48 no 3 pp446ndash453 2011
[27] M Polites J Kalmanson and D Mangus ldquoSolar sail attitudecontrol using small reaction wheels and magnetic torquersrdquoProceedings of the Institution of Mechanical Engineers G Journalof Aerospace Engineering vol 222 no 1 pp 53ndash62 2008
[28] H-T Cui J-H Luo J-H Feng and P-Y Cui ldquoAttitudecontrol of solar sail spacecraft with control boomrdquo Journal ofAstronautics vol 29 no 2 pp 560ndash566 2008
[29] E Mettler and S R Ploen ldquoSolar sail dynamics and controlusing a boom mounted bus articulated by a bi-state two-axisgimbal and reaction wheelsrdquo in Proceedings of the AIAAAASAstrodynamics Specialist Conference and Exhibit MontereyCalif USA August 2002
[30] J Luo X Li and J Feng ldquoPassive attitude control of solar sailspacecraftrdquo Flight Dynamics vol 26 no 5 pp 47ndash50 2008
[31] J Luo Study on attitude control of solar sail spaceraft [PhDthesis] School of Astronautics Harbin Institute of TechnologyHarbin China 2007
[32] D A Lawrence and S W Piggott ldquoIntegrated trajectory andattitude control for a four-vane solar sailrdquo in Proceedings ofthe AIAA Guidance Navigation and Control Conference andExhibit pp 2416ndash2431 San Francisco Calif USA August 2005
[33] E Mettler A B Acikmese and S R Ploen ldquoAttitude dynamicsand control of solar sails with articulated vanesrdquo in Proceedingsof the AIAA Guidance Navigation and Control Conference andExhibit pp 2396ndash2415 San Francisco Calif USA August 2005
[34] S N Adeli V J Lappas and B Wie ldquoA scalable bus-basedattitude control system for Solar Sailsrdquo Advances in SpaceResearch vol 48 no 11 pp 1836ndash1847 2011
[35] R Funase Y Shirasawa Y Mimasu et al ldquoOn-orbit verificationof fuel-free attitude control system for spinning solar sailutilizing solar radiation pressurerdquo Advances in Space Researchvol 48 no 11 pp 1740ndash1746 2011
[36] B Fu and F O Eke ldquoAttitude control methodology for largesolar sailsrdquo in AIAA Guidance Navigation and Control (GNC)Conference 2013
[37] J Liu N Cui F Shen and S Rong ldquoDynamics of highly-flexiblesolar sail subjected to various forcesrdquoActaAstronautica vol 103pp 55ndash72 2014
[38] J F Liu S Y Rong and J G Li ldquoAttitude dynamics modelingand control of large flexible solar sail spacecraftrdquo in Proceedingsof the 3rd International Symposium on Systems and Control inAeronautics and Astronautics (ISSCAA rsquo10) pp 243ndash247 IEEEPublications Piscataway NJ USA 2010
[39] S Gong H Baoyin and J Li ldquoCoupled attitude-orbit dynamicsand control for displaced solar orbitsrdquo Acta Astronautica vol65 no 5-6 pp 730ndash737 2009
Submit your manuscripts athttpwwwhindawicom
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
MathematicsJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Mathematical Problems in Engineering
Hindawi Publishing Corporationhttpwwwhindawicom
Differential EquationsInternational Journal of
Volume 2014
Applied MathematicsJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Probability and StatisticsHindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Journal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Mathematical PhysicsAdvances in
Complex AnalysisJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
OptimizationJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
CombinatoricsHindawi Publishing Corporationhttpwwwhindawicom Volume 2014
International Journal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Operations ResearchAdvances in
Journal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Function Spaces
Abstract and Applied AnalysisHindawi Publishing Corporationhttpwwwhindawicom Volume 2014
International Journal of Mathematics and Mathematical Sciences
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
The Scientific World JournalHindawi Publishing Corporation httpwwwhindawicom Volume 2014
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Algebra
Discrete Dynamics in Nature and Society
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Decision SciencesAdvances in
Discrete MathematicsJournal of
Hindawi Publishing Corporationhttpwwwhindawicom
Volume 2014 Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Stochastic AnalysisInternational Journal of
Mathematical Problems in Engineering 11
(2) The nonlinearity is apparent in above equations onlyexisting in the terms of 119881
1 119881
2119882
1119882
2 We take (47a)
as an exampleThe terms including1198802and its first and
second derivative 1198811 119881
2119882
1119882
2 can be regarded as
the applied loads for 1198801
(3) The coupling between the axial and transverse vibra-tionswill disappear as long as the linear displacement-strain relationship is adopted
(4) There are no external loads for axial vibrationsaccording to above equations
The transverse vibration equations for 1198811 119881
2and119882
1 119882
2
can be obtained as
4
3
1198681198631
119897+
1
51198971198681198601+
1
61198971198681198602minus
119898ℎV5ℎ
1199055
2
1198975+
31198681198632
2119897
+4119898
ℎV4ℎ
1199053
1
1198974+
4120578119887119863
1199091199091
1198973minus
2119898ℎV5ℎ
1199054
2
1198975+
6120578119887119863
1199091199092
1198973
+8119898
ℎV4ℎ
1199052
1198811
1198974+
41198631199091199091198811
1198973+
8119898ℎV5ℎ
1199053
1198812
1198975+
61198631199091199091198812
1198973
+27119860
1199091199091198812119882
2
2
81198973+
541198601199091199091198811119881
2
2
71198973+
181198601199091199091198811119882
2
2
71198973
+6119860
119909119909119881
2
1
1198812
1198973+
21198601199091199091198812119882
2
1
1198973+
1211986011990911990911988021198812
51198972
+8119860
1199091199091198811119882
2
1
51198973+
311986011990911990911988011198812
21198972+
211986011990911990911988021198811
1198972
+8119860
119909119909119881
3
1
51198973+
27119860119909119909119881
3
2
81198973+
361198601199091199091198812119882
1119882
2
71198973
+4119860
1199091199091198811119882
1119882
2
1198973+
411986011990911990911988011198811
31198972minus 119865
119888119910(119905) minus 05119865
025119865= 0
1
61198971198681198601+
3
2
1198681198631
119897minus
119898ℎV5ℎ
1199055
1
1198975+
1
71198971198681198602+
9
5
1198681198632
119897
+6120578
119887119863
1199091199091
1198973+
2119898ℎV5ℎ
1199054
1
1198975+
12120578119887119863
1199091199092
1198973+
6119898ℎV6ℎ
1199055
2
1198976
+6119863
1199091199091198811
1198973+
16119898ℎV5ℎ
1199053
1198811
1198975+
121198631199091199091198812
1198973+
18119898ℎV6ℎ
1199054
1198812
1198976
+9119860
1199091199091198812119882
2
2
21198973+
811198601199091199091198811119881
2
2
81198973+
311986011990911990911988011198811
21198972
+27119860
1199091199091198811119882
2
2
81198973+
541198601199091199091198812119881
2
1
71198973+
181198601199091199091198812119882
2
1
71198973
+3119860
11990911990911988021198812
1198972+
21198601199091199091198811119882
2
1
1198973+
911986011990911990911988011198812
51198972+
1211986011990911990911988021198811
51198972
+9119860
119909119909119881
3
2
21198973+
2119860119909119909119881
3
1
1198973+
271198601199091199091198812119882
1119882
2
41198973
+36119860
1199091199091198811119882
1119882
2
71198973minus 04119865
025119865minus 119865
119888119910(119905) = 0
4
3
119868119863
1
119897+
1
5119897119868119860
1+
3
2
119868119863
2
119897+
1
6119897119868119860
2minus
119898ℎV5ℎ
1199055
2
1198975
+4120578
119887119863
119909119909
1
1198973+
4119898ℎV4ℎ
1199053
1
1198974minus
2119898ℎV5ℎ
1199054
2
1198975+
6120578119887119863
119909119909
2
1198973
+4119863
119909119909119882
1
1198973+
8119898ℎV4ℎ
1199052
1198821
1198974+
8119898ℎV5ℎ
1199053
1198822
1198975+
6119863119909119909119882
2
1198973
+36119860
119909119909119882
211988111198812
71198973+
4119860119909119909119882
111988111198812
1198973+
27119860119909119909119882
2119881
2
2
81198973
+18119860
119909119909119882
1119881
2
2
71198973+
54119860119909119909119882
1119882
2
2
71198973+
6119860119909119909119882
2
1
1198822
1198973
+2119860
119909119909119882
2119881
2
1
1198973+
121198601199091199091198802119882
2
51198972+
8119860119909119909119882
1119881
2
1
51198973
+3119860
1199091199091198801119882
2
21198972+
21198601199091199091198802119882
1
1198972+
27119860119909119909119882
3
2
81198973
+8119860
119909119909119882
3
1
51198973+
41198601199091199091198801119882
1
31198972minus 119865
119888119911(119905) = 0
1
7119897119868119860
2+
9
5
119868119863
2
119897+
1
6119897119868119860
1minus
119898ℎV5ℎ
1199055
1
1198975+
3
2
119868119863
1
119897
+6120578
119887119863
119909119909
1
1198973+
2119898ℎV5ℎ
1199054
1
1198975+
6119898ℎV6ℎ
1199055
2
1198976
+12120578
119887119863
119909119909
2
1198973+
6119863119909119909119882
1
1198973+
16119898ℎV5ℎ
1199053
1198821
1198975
+12119863
119909119909119882
2
1198973+
18119898ℎV6ℎ
1199054
1198822
1198976+
31198601199091199091198801119882
1
21198972
+27119860
119909119909119882
211988111198812
41198973+
36119860119909119909119882
111988111198812
71198973+
9119860119909119909119882
2119881
2
2
21198973
+27119860
119909119909119882
1119881
2
2
81198973+
81119860119909119909119882
1119882
2
2
81198973+
18119860119909119909119882
2119881
2
1
71198973
+54119860
119909119909119882
2119882
2
1
71198973+
31198601199091199091198802119882
2
1198972+
2119860119909119909119882
1119881
2
1
1198973
+9119860
1199091199091198801119882
2
51198972+
121198601199091199091198802119882
1
51198972+
2119860119909119909119882
3
1
1198973
+9119860
119909119909119882
3
2
21198973minus 119865
119888119911(119905) = 0
(48)
The complexity high coupling and nonlinearity are obvi-ous in above equations
4 The Coupled Rigid-Flexible Dynamics
The dynamics for control and dynamic simulation shouldbe presented for solar sail based on the simplification ofequations derived in previous sections Some assumptions aremade before simplifying the equations as follows
12 Mathematical Problems in Engineering
(1) Only the attitude motion is affected by the slidingmass the vibration of solar sail structure is notaffected by the sliding mass
(2) Although the attitude control is accomplished byrotating control vanes and the gimbaled controlboom moving sliding masses the specific time his-tories of the actuators are not considered here
(3) The four supporting beams are regarded as an entirestructure thus the identical generalized coordinatesare adopted in the dynamic analysis
41 The Simplified Attitude Dynamics The kinetic energy ofsolar sail supporting beams can be obtained as
119879119898
=1
2120596 sdot J sdot 120596 + 119898
119897int
119897
0
2∘
1205883
sdot (120596 times r3) + (120596 times 120588
3) sdot (120596 times 120588
3)
+ 2 (120596 times r3) sdot (120596 times 120588
3) 119889119911
+ 119898119897int
119897
0
2∘
1205882
sdot (120596 times r2) + (120596 times 120588
2) sdot (120596 times 120588
2)
+ 2 (120596 times r2) sdot (120596 times 120588
2) 119889119910
(49)
The subscripts 2 and 3 represent the second and thirdsupporting beams The displacements can be expressed as
V0119909
(119911 119905) = (119911
119897)
2
sdot 1198811(119905) + (
119911
119897)
3
sdot 1198812(119905)
1199080119910
(119911 119905) = 120572V0119909
(119911 119905) = (119911
119897)
2
sdot 1205721198811(119905) + (
119911
119897)
3
sdot 1205721198812(119905)
for the 3rd beam
V0119909
(119910 119905) = 120573V0119909
(119911 119905) = (119910
119897)
2
sdot 1205731198811(119905) + (
119910
119897)
3
sdot 1205731198812(119905)
1199080119911
(119910 119905) = 120574V0119909
(119910 119905) = (119910
119897)
2
sdot 1205741198811(119905) + (
119910
119897)
3
sdot 1205741198812(119905)
for the 2nd beam
(50)
The subscripts 119909 119910 and 119911 of the left terms in (50)represent the displacements along119909119910 and 119911directions119881
1(119905)
and 1198812(119905) are the generalized coordinates The displacements
1199080119910(119911 119905) V
0119909(119910 119905) and 119908
0119911(119910 119905) can be obtained using the
assumed modes as
1205883= V
0119909(119911 119905) i
119887+ 119908
0119910(119911 119905) j
119887
=
[[[[[
[
(119911
119897)
2
sdot 1198811(119905) + (
119911
119897)
3
sdot 1198812(119905)
120572 [(119911
119897)
2
sdot 1198811(119905) + (
119911
119897)
3
sdot 1198812(119905)]
0
]]]]]
]
1205882= V
0119909(119910 119905) i
119887+ 119908
0119911(119910 119905) k
119887
=
[[[[[
[
120573[(119910
119897)
2
sdot 1198811(119905) + (
119910
119897)
3
sdot 1198812(119905)]
0
120574 [(119910
119897)
2
sdot 1198811(119905) + (
119910
119897)
3
sdot 1198812(119905)]
]]]]]
]
(51)
The vibration velocity can be obtained as
∘
1205883
= 1205883119909i119887+ 120588
3119910j119887=
[[[[[
[
(119911
119897)
2
sdot 1(119905) + (
119911
119897)
3
sdot 2(119905)
1205721[(
119911
119897)
2
sdot 1(119905) + (
119911
119897)
3
sdot 2(119905)]
0
]]]]]
]
∘
1205882
= 1205882119909i119887+ 120588
2119911k119887=
[[[[[
[
1205731[(
119910
119897)
2
sdot 1(119905) + (
119910
119897)
3
sdot 2(119905)]
0
1205741[(
119910
119897)
2
sdot 1(119905) + (
119910
119897)
3
sdot 2(119905)]
]]]]]
]
(52)
Without loss of generality 120572 = 120573 = 1205721= 120573
1= 1 and
120574 = 1205741= minus1 can be assumed in above expressions And the
kinetic energy of the slidingmasses can be obtained as followsby neglecting the vibration related terms
119879ℎ=
1
2119898
ℎ1(120596 times r
ℎ1) sdot (120596 times r
ℎ1) +
1
2119898
ℎ2(120596 times r
ℎ2)
sdot (120596 times rℎ2)
(53)
The kinetic energy of the payload can be obtained as
119879119901=
1
2119898
119901(120596 times r
119901) sdot (120596 times r
119901) (54)
The following simplified attitude dynamics can beobtained by neglecting the second and higher terms ofattitude angles and vibration modes in computing the kinetic
Mathematical Problems in Engineering 13
energies of the supporting beams payload and slidingmasses Consider
119869119909 minus 119898
1198971198972
1minus
4
5119898
1198971198972
2+ 119898
ℎ11199102
ℎ1
+ 119898ℎ21199112
ℎ2
minus 119898119901119903119901119909119903119901119911 + 119898
1199011199032
119901119911
+ 1198981199011199032
119901119910
minus 119898119901119903119901119909119903119901119910
120579 = 119876120593
119869119910
120579 +2
5119898
1198971198972
2+
1
2119898
1198971198972
1+ 119898
ℎ21199112
ℎ2
120579
+ 1198981199011199032
119901119911
120579 minus 119898119901119903119901119910119903119901119911 minus 119898
119901119903119901119909119903119901119910
+ 1198981199011199032
119901119909
120579 = 119876120579
119869119911 minus
2
51198972
1198981198972minus
1
21198972
1198981198971+ 119898
ℎ11199102
ℎ1
minus 119898119901119903119901119910119903119901119911
120579 + 1198981199011199032
119901119910
+ 1198981199011199032
119901119909
minus 119898119901119903119901119909119903119901119911 = 119876
120595
(55)
where 119876120593 119876
120579 and 119876
120595are the generalized nonpotential
attitude control torques generated by the control vanes Andthe attitude control torques generated by the gimbaled controlboom and sliding masses can be found on the left side ofthe above equation coupled with 120579 making the attitudecontroller design problem rather difficult
42 The Simplified Vibration Equations The couplingbetween the axial and transverse vibrations is neglectedand only the transverse vibration is considered The attitudedynamics for dynamic simulation can be obtained as followsbased on previous derivation by neglecting the action ofsolar-radiation pressure
4
3
1198681198631
119897+
1
51198971198681198601+
1
61198971198681198602+
31198681198632
2119897+
4120578119887119863
1199091199091
1198973
+6120578
119887119863
1199091199092
1198973+
41198631199091199091198811
1198973+
61198631199091199091198812
1198973+
271198601199091199091198812119882
2
2
81198973
+54119860
1199091199091198811119881
2
2
71198973+
181198601199091199091198811119882
2
2
71198973+
6119860119909119909119881
2
1
1198812
1198973
+2119860
1199091199091198812119882
2
1
1198973+
81198601199091199091198811119882
2
1
51198973+
8119860119909119909119881
3
1
51198973
+27119860
119909119909119881
3
2
81198973+
361198601199091199091198812119882
1119882
2
71198973+
41198601199091199091198811119882
1119882
2
1198973
minus 1198651198621
(119905) = 0
1
61198971198681198601+
3
2
1198681198631
119897+
1
71198971198681198602+
9
5
1198681198632
119897+
6120578119887119863
1199091199091
1198973
+12120578
119887119863
1199091199092
1198973+
61198631199091199091198811
1198973+
121198631199091199091198812
1198973+
91198601199091199091198812119882
2
2
21198973
+81119860
1199091199091198811119881
2
2
81198973+
271198601199091199091198811119882
2
2
81198973+
541198601199091199091198812119881
2
1
71198973
+18119860
1199091199091198812119882
2
1
71198973+
21198601199091199091198811119882
2
1
1198973+
9119860119909119909119881
3
2
21198973
+2119860
119909119909119881
3
1
1198973+
271198601199091199091198812119882
1119882
2
41198973+
361198601199091199091198811119882
1119882
2
71198973
minus 1198651198622
(119905) = 0
(56)
The following equations can be obtained by rearrangingthe above equations
4
3
1198681198631
119897+
1
51198971198681198601+
1
61198971198681198602+
31198681198632
2119897+
4120578119887119863
1199091199091
1198973
+6120578
119887119863
1199091199092
1198973+
41198631199091199091198811
1198973+
61198631199091199091198812
1198973+
16119860119909119909119881
3
1
51198973
+12119860
119909119909119881
2
1
1198812
1198973+
1081198601199091199091198811119881
2
2
71198973+
54119860119909119909119881
3
2
81198973
minus 1198651198621
(119905) = 0
1
61198971198681198601+
3
2
1198681198631
119897+
1
71198971198681198602+
9
5
1198681198632
119897+
6120578119887119863
1199091199091
1198973
+12120578
119887119863
1199091199092
1198973+
61198631199091199091198811
1198973+
121198631199091199091198812
1198973
+4119860
119909119909119881
3
1
1198973+
108119860119909119909119881
2
1
1198812
71198973+
811198601199091199091198811119881
2
2
41198973
+9119860
119909119909119881
3
2
1198973minus 119865
1198622(119905) = 0
(57)
1198651198621(119905) and 119865
1198622(119905) are used to represent all the generalized
external forces they can be used for vibration control Thesecomplicated equations abovementioned are the basis forobtaining the simplified equations used for controller design
The following equations can be obtained by neglecting thetwo and higher terms
4
3
1198681198631
119897+
1
51198971198681198601+
1
61198971198681198602+
31198681198632
2119897+
4120578119887119863
1199091199091
1198973
+6120578
119887119863
1199091199092
1198973+
41198631199091199091198811
1198973+
61198631199091199091198812
1198973= 119865
1198621
(119905)
14 Mathematical Problems in Engineering
1
61198971198681198601+
3
2
1198681198631
119897+
1
71198971198681198602+
9
5
1198681198632
119897+
6120578119887119863
1199091199091
1198973
+12120578
119887119863
1199091199092
1198973+
61198631199091199091198811
1198973+
121198631199091199091198812
1198973= 119865
1198622
(119905)
(58)
43 The Rigid-Flexible Coupled Dynamics The simplifiedattitude and vibration dynamics can be written as
119886120593 + 119886
120579
120579 + 119886120595 + 119886
1198811
1+ 119886
1198812
2= 119876
120593
119887120579
120579 + 119887120595 + 119887
120593 + 119887
1198811
1+ 119887
1198812
2= 119876
120579
119888120595 + 119888
120579
120579 + 119888120593 + 119888
1198811
1+ 119888
1198812
2= 119876
120595
119889
1198811
1+ 119889
1198812
2+ 119889
1198811
1+ 119889
1198812
2+ 119889
1198811
1198811
+ 1198891198812
1198812= 119876
1198811
119890
1198811
1+ 119890
1198812
2+ 119890
1198811
1+ 119890
1198812
2+ 119890
1198811
1198811
+ 1198901198812
1198812= 119876
1198812
(59)
The related coefficients in the preceding equation can befound in (A1) in the appendix The dynamics (see (59)) isnot suitable for attitude controller design because the controlinputs exist in some coefficients of the angular accelerationsThis will make the controller design rather difficult Thusthe following dynamic model is obtained by putting theterms including the control inputs right side of the dynamicequations
119869119909 minus 119898
1198971198972
1minus
4
5119898
1198971198972
2= 119876
120593+ 119906
119869119910
120579 +2
5119898
1198971198972
2+
1
2119898
1198971198972
1= 119876
120579+ 119906
120579
119869119911 minus
1
21198972
1198981198971minus
2
51198972
1198981198972= 119876
120595+ 119906
119889
1198811
1+ 119889
1198812
2+ 119889
1198811
1+ 119889
1198812
2
+ 1198891198811
1198811+ 119889
1198812
1198812= 119876
1198811
119890
1198811
1+ 119890
1198812
2+ 119890
1198811
1+ 119890
1198812
2
+ 1198901198811
1198811+ 119890
1198812
1198812= 119876
1198812
(60)
The expressions for 119906 119906
120579
and 119906are as
119906= minus119898
ℎ11199102
ℎ1
minus 119898ℎ21199112
ℎ2
+ 119898119901119903119901119909119903119901119911 minus 119898
1199011199032
119901119911
minus 1198981199011199032
119901119910
+ 119898119901119903119901119909119903119901119910
120579
119906
120579
= minus119898ℎ21199112
ℎ2
120579 minus 1198981199011199032
119901119911
120579 + 119898119901119903119901119910119903119901119911 + 119898
119901119903119901119909119903119901119910
minus 1198981199011199032
119901119909
120579
119906= minus119898
ℎ11199102
ℎ1
+ 119898119901119903119901119910119903119901119911
120579 minus 1198981199011199032
119901119910
minus 1198981199011199032
119901119909
+ 119898119901119903119901119909119903119901119911
(61)
119906 119906
120579
and 119906are the functions of the positions of sliding
masses and payload and the angular accelerations The statevariables in (60) are defined as
1199091= 120593 119909
2= 119909
3= 120579 119909
4= 120579
1199095= 120595 119909
6= 119909
7= 119881
1
1199098=
1 119909
9= 119881
2 119909
10=
2
(62)
Thedynamics (60) can bewritten as the state-spacemodelas following
1= 119909
2
2= 119886
11199097+ 119886
21199098+ 119886
31199099+ 119886
411990910
+ 119906120593
3= 119909
4
4= 119886
51199097+ 119886
61199098+ 119886
71199099+ 119886
811990910
+ 119906120579
5= 119909
6
6= 119886
91199097+ 119886
101199098+ 119886
111199099+ 119886
1211990910
+ 119906120595
7= 119909
8
8= 119886
131199097+ 119886
141199098+ 119886
151199099+ 119886
1611990910
+ 1199061198811
9= 119909
10
10
= 119886171199097+ 119886
181199098+ 119886
191199099+ 119886
2011990910
+ 1199061198812
(63)
where 119906120579 119906
120593 and 119906
120595are the generalized control inputs
for attitude control and 1199061198811
and 1199061198812
are the generalizedcontrol inputs for vibration control The controllability canbe satisfied by analyzing (63) The attitudevibration controlinputs and the coefficients will be presented later in thissection The form of a matrix differential equation can bewritten as follows for the above equation
x = Ax + Bu (64)
The expressions of the relatedmatrices and vectors can befound as
x = [1
2
3
4
5
6
7
8
9
10]119879 x (119905
0) = x
1199050
u = [119906120593 119906
120579 119906
120595 119906
1198811
1199061198812
]119879
u (1199050) is known
(65)
where A xB and u are the system matrix state variablesvector control matrix and control inputs vector respectively
Mathematical Problems in Engineering 15
The complexity of the state-space model can be seen bypresenting the detailed expressions of control inputs forattitudevibration and related parameters in (A2) in theappendix
5 AttitudeVibration Control and Simulation
The controller for the attitude and vibration is developedusing the LQR and optimal PI theory The dynamic simula-tion is performed based on the coupled dynamics derived inthe previous sections
51 LQR and Optimal PI Based Controllers Design Thedynamics for solar sail can bewritten as follows togetherwithits quadratic cost function also defined as
x = Ax + Bu x (1199050) = x
1199050
(known)
119869 =1
2int
infin
1199050
[x119879 (119905)Qx (119905) + u119879 (119905)Ru (119905)] 119889119905
(66)
whereQ = Q119879
⩾ 0 andR = R119879
gt 0 are constantThe control-lability of [AB] and the observability of [AD] can beensured when the equationDD119879
= Q holds for anymatrixDThe optimal control input ulowast(119905)within the scope of u(119905) isin R119903119905 isin [119905
0infin] can be computed as follows to make 119869minimum
ulowast (119905) = minusKxlowast (119905) K = Rminus1B119879P (67)
where P is the nonnegative definite symmetric solution of thefollowing Riccati algebraic equations
PA + A119879P minus PBRminus1B119879P +Q = 0 (68)
And the optimal performance index can be obtained asfollows for arbitrary initial states
119869lowast
[x (1199050) 119905
0] =
1
2x1198790
Px0 (69)
The closed-loop system
x = (A minus BRminus1B119879P) x (70)
is asymptotically stableFor an orbiting solar sail the primary disturbance torque
is by the cmcp offset and the impact of the tiny dust inthe deep space The state regulator can be used to controlthe dynamic system affected by pulse disturbance torquewith good steady-state errors but will never achieve accuratesteady-state errors if the dynamics is affected by constantdisturbance torque Thus the optimal state regulator withan integrator to eliminate the constant disturbance torqueshould be presented This optimal proportional-integral reg-ulator not only eliminates the constant disturbance torque butalso possesses the property of optimal regulator
Table 1 The related parameters
Parameters ValuesCMCP offsetm [0 017678 017678]119879
The side length of square sailm 100Nominal solar-radiation pressureconstant at 1 AU from the sunNm2 4563 times 10minus6
Solar-radiation pressure forceN 912 times 10minus2
Roll inertiakglowastm2 50383Pitch and yaw inertiakglowastm2 251915Outer radiusm 0229Thickness of the supporting beamm 75 times 10minus6
Youngrsquos modulus of the supportingbeamGPa 124
Moment of inertia of the cross-sectionof the supporting beamm4 2829412 times 10minus7
Bending stiffness of the supportingbeamNlowastm2 3508471336
Proportional damping coefficient ofsupporting beams 001
Line density of the supportingbeamkgm 0106879
Cross-sectional area of the supportingbeamm2 1079 times 10minus5
Roll disturbance torqueNlowastm 0Pitch (yaw) disturbance torqueNlowastm 0016122 (minus0016122)
For the following linear system with the correspondingperformance index
x = Ax + Bu x (1199050) = x
1199050
u (1199050) = u
1199050
119869 =1
2int
infin
1199050
(x119879Qx + u119879Ru + u119879Su) 119889119905(71)
where Q = Q119879
⩾ 0 R = R119879
gt 0 and S = S119879 gt 0 If [AB]is completely controllable and meanwhile [AD
11] is com-
pletely observable with the relationship D11D119879
11
= Q thesolution can be expressed as
ulowast = minusK1x minus K
2ulowast ulowast (119905
0) = u
1199050
(72)
If B119879B is full rank we can get
ulowast = minusK3x minus K
4x ulowast (119905
0) = u
1199050
(73)
K119894(119894 = 1 2 3 4) is the function of ABQR S
The closed-loop system
[xulowast] = [
A BminusK
1minusK
2
] [xulowast] [
[
x (1199050)
u (1199050)]
]
= [x1199050
u1199050
] (74)
is asymptotically stableThe compromise between the state variables (the angle
angular velocity the vibration displacement and velocity)and control inputs (the torque by all the actuators) can
16 Mathematical Problems in Engineering
0 2000 4000 6000
0 2000 4000 6000
0 2000 4000 6000minus5
0
5
minus5
0
5
minus5
0
5
minus4
minus2
0
2
4
times10minus4
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
00162
00164
00166
4800 4900 5000
4800 4900 5000
4800 4900 5000
minus00165
minus0016
Time (s) Time (s)
Time (s)
Time (s)
Time (s)
Time (s)
Roll
erro
r120593(∘
)
Roll
erro
r120593(∘
)
Pitc
h er
ror120579
(∘)
Pitc
h er
ror120579
(∘)
Yaw
erro
r120595(∘
)
Yaw
erro
r120595(∘
)
Figure 8 The roll pitch and yaw errors
be achieved by using both the LQR based and optimal PIbased controllers for the coupled attitudevibration dynamicsystem The fact is that the attitude control ability is limitedto the control torque by the control actuators The change ofthe attitude angles and rates should not be frequent to voidexciting vibrations
Thus the weighting matrix Q and the control weightingmatrix R are selected as follows for LQR based controller
Q (1 1) = 9 times 10minus6
Q (2 2) = 1 times 10minus6
Q (3 3) = 16 times 10minus6
Q (4 4) = Q (5 5) = Q (6 6) = Q (7 7) = Q (8 8)
= Q (9 9) = Q (10 10) = 1 times 10minus6
Q (119894 119895) = 0 (119894 = 119895 119894 119895 = 1 sim 10)
R (1 1) = R (2 2) = 900 R (3 3) = 100
R (4 4) = R (5 5) = 10000
R119894119895
= 0 (119894 = 119895 119894 119895 = 1 sim 5)
(75)
TheweightingmatrixQ and the control weightingmatrixR are selected as follows for the optimal PI based controller
Q (1 1) = Q (2 2) = 4 times 10minus8
Q (3 3) = Q (4 4) = Q (5 5) = Q (6 6) = Q (7 7)
= Q (8 8) = 16 times 10minus8
Mathematical Problems in Engineering 17
minus02
0
02
Roll
rate
(∘s)
Roll
rate
(∘s)
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Pitc
h ra
te(∘s)
Pitc
h ra
te(∘s)
0 1000 2000 3000 4000 5000
minus05
0
05
minus05
0
05
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
Time (s)
Yaw
rate
(∘
s)
Yaw
rate
(∘
s)
4800 4850 4900 4950 5000
Time (s)4800 4850 4900 4950 5000
Time (s)4800 4850 4900 4950 5000
minus2
0
2
minus2
0
2
minus2
0
2
times10minus4
times10minus4
times10minus4
Figure 9 The roll pitch and yaw rates
Q (9 9) = Q (10 10) = 1 times 10minus8
Q (119894 119895) = 0 (119894 = 119895 119894 119895 = 1 sim 10)
R (1 1) = R (2 2) = R (3 3) = 1 times 10minus8
R (4 4) = R (5 5) = 4 times 10minus8
R (119894 119895) = 0 (119894 = 119895 119894 119895 = 1 sim 5)
(76)
52 The Simulation Results The initial angle errors of rollpitch and yaw are adopted as 120593(119905
0) = 3
∘ 120579(1199050) = 3
∘ and120595(119905
0) = 3
∘ the initial angular velocity errors of roll pitchand yaw are adopted as (119905
0) = 0
∘
s 120579(1199050) = 0
∘
s and(119905
0) = 0
∘
s 1198811(1199050) = 01m 119881
2(1199050) = 01m
1(1199050) = 0ms
and 2(1199050) = 0ms are adopted in this paper for dynamic
simulationThe estimated cmcp offset is 025m for a 100 times 100m
square solar sail It is assumed that the components of cmcpoffset vector are [0 017678 017678]
119879 in the body frame
The relevant parameters for dynamic simulations are givenin Table 1
The dynamic simulation results are obtained as followsby using the LQR controller based on the abovementionedQ and R related parameters and initial conditions Thedynamics simulations with (denoted by ldquowith GFrdquo) andwithout (denoted by ldquowithout GFrdquo) considering the geo-metrical nonlinearity are presented And the correspondingdiscussions and analysis are also given according to thecalculated results
The roll pitch and yaw errors are presented based onthe dynamics models with and without considering thegeometrical nonlinearityThe control effect with zero steady-state error can be achieved for roll axis by referring tothe results But the steady-state errors exist for pitch andyaw axes from Figure 8 this is because there exist constantdisturbance torques for pitch and yaw axes caused by thecmcp offset Thus the LQR based controller cannot be usedfor attitude control with good steady-state performance Thesteady-state errors of pitch and yaw axes are about 0164
∘
and minus0164∘ respectively from the corresponding partial
enlarged drawing of the figures (see the corresponding left
18 Mathematical Problems in Engineering
minus20
0
20
Roll
torq
ue (N
lowastm
)
Roll
torq
ue (N
lowastm
)
minus50
0
50
minus50
0
50
Pitc
h to
rque
(Nlowast
m)
Pitc
h to
rque
(Nlowast
m)
0 1000 2000 3000 4000 5000
0 2000 4000 6000
0 2000 4000 6000
Yaw
torq
ue (N
lowastm
)
Yaw
torq
ue (N
lowastm
)
minus002
0
002
008
01
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
minus01
minus009
minus008
Time (s)Time (s)
Time (s)Time (s)
Time (s)Time (s)
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Figure 10 The roll pitch and yaw torques
figures) A simple and practical controller should be designedto eliminate the steady-state errorsThese errorswill affect theprecision of the super long duration space mission deeply
The differences between the dynamics with and withoutthe geometrical nonlinearity effect can be observed Theamplitudes and phases change a bit by comparing the corre-sponding results
It can be observed by the partial enlarged figures(the right figures of Figure 9) that there are no steady-stateerrors for roll pitch and yaw rates The relative satisfieddynamic performance is achieved In fact a result with muchmore satisfied dynamic performance can be obtained but itwill make the desired control torques much larger duringthe initial period This will not only excite the vibration ofthe structure but also increase the burden of the controlactuators
And the differences between the dynamics models withand without the geometrical nonlinearity can also be seenmerely in the phase of the angular velocities
The desired attitude control torques are presented inFigure 10 The roll torque will tend to be zero with thedecrement of the state variable errors The pitch and yawtorques tend to be constant from the middle and bottom
figures The pitch and yaw steady-state errors can never beeliminated although the pitch and yaw torques (009Nlowastmand minus009Nlowastm) are applied continuously by theoreticalanalysis and simulations This is just a great disadvantage ofthe LQR based controller in this paper The initial controltorques can be afforded by vibrating the gimbaled controlboom andmoving the slidingmasses that can afford a relativelarge torque The control vanes can be used to afford thecontrol torques when solar sail is in steady-state process Theexpression of the attitude control inputs 119906
120593 119906
120579 and 119906
120595can be
found in previous sectionMoreover the differences between dynamics responses
with and without geometrical nonlinearity can also beobserved by comparing the corresponding results Therequired torques for the attitude control are a little largerfor the dynamics with geometrical nonlinearity And thedifference in the phase is also clear
It can be seen that the vibration of the supporting beamis depressed effectively by the simulation results in Figure 11It can be seen that the steady-state errors and the dynamicperformance are relatively satisfied It can also be seen that thedynamics responses between the model with and without the
Mathematical Problems in Engineering 19
0 1000 2000 3000 4000 5000
0 1000 2000 3000 4000 5000
minus01
0
01
minus02
0
02
Time (s) Time (s)
Time (s) Time (s)
minus5
0
5
times10minus4
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
minus1
0
1
times10minus3
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
The d
ispla
cem
ent o
f the
tip
(m)
The d
ispla
cem
ent o
f the
tip
(m)
The v
eloci
ty o
f the
tip
(ms
)
The v
eloc
ity o
f the
tip
(ms
)
Figure 11 The displacement and velocity of the tip of the supporting beam
geometrical nonlinearity effect are different in the vibrationdisplacement and velocitymagnitudes and phases (Figure 15)
The simulation results can be obtained as follows by usingthe optimal PI based controller adopting the abovementionedparameters and initial conditions
The roll pitch and yaw errors are given by using theoptimal PI based controller These errors tend to disappearby observing the partially enlarged plotting of the figure (thecorresponding right figures) (shown in Figure 12) And therelative satisfied dynamic performance can also be obtainedFrom the view of eliminating the steady-state errors the opti-mal PI based controller performs better than the LQR basedcontroller by theoretical analysis and simulation results Theformer can achieve attitude control results without pitchand yaw steady-state errors From the view of dynamicperformance both the controllers perform well In additionit can be seen that the difference between the modelswith and without geometrical nonlinearity is merely inthe phase
The roll pitch and yaw rate errors are presented inFigure 13 The dynamic and steady-state performances aresatisfied by observing the simulation results And by observ-ing the difference between the dynamics responses with and
without the influence by the geometrical nonlinearity it canbe concluded that the merely difference is the phase
The desired control torques of the roll pitch and yaw areobtained in Figure 14 by using the optimal PI based controllerIt can be seen that the value of the desired roll control torquedecreases to zero as the values of the roll angle and ratedecrease to zero The desired pitch and yaw control torquestend to be the constant values 009Nlowastm and minus009Nlowastmrespectively The desired initial control torques are large byobserving Figure 14 It is suggested that the gimbaled controlboom combining the sliding masses is adopted to afford theinitial torque Then the control vanes can be used to controlthe solar sail after the initial phase The phase differencecan also be observed by inspecting the dynamics responsesduring the 4800sim5000 s period
The vibration can be controlled effectively based on theoptimal PI controller And the relative satisfied dynamicand steady-state performances can be achieved In additionthe tiny differences exist in the magnitudes of the requiredtorques And the phase differences also exist
It can be concluded as follows by analyzing and compar-ing the simulation results based on the LQR and optimal PItheories in detail
20 Mathematical Problems in Engineering
Roll
erro
r120593(∘
)
Roll
erro
r120593(∘
)
minus5
0
5
minus5
0
5
Pitc
h er
ror120579
(∘)
Pitc
h er
ror120579
(∘)
0 1000 2000 3000 4000 5000minus10
0
10
Time (s) Time (s)
Time (s)
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
Yaw
erro
r120595(∘
)
Yaw
erro
r120595(∘
)
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
minus1
0
1
times10minus3
minus1
0
1
times10minus3
minus1
0
1
times10minus3
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Figure 12 The roll pitch and yaw errors
(1) From the view of eliminating the steady-state errorsof the pitch and yaw errors the optimal PI based con-troller performs better than the LQR based controllerby theoretical analysis and simulation results Thedynamic performances of the two controllers are bothsatisfied and the desired control torques are relativelysmall
(2) The weighting of the state variables is reflected by theweighting matrix according to the LQR and optimalPI theories The constant weighting matrices selectedin this paper can effectively reflect the initial statevariable errors but maybe reflect the final state vari-able errors deficiently The time-varying weightingmatrices should be selected
(3) For the actual orbiting solar sail the control actuators(control vanes gimbaled control boom and slidingmasses) cannot afford excessive large control torquesThus the control torques should be as small as possibleon the premise of acquiring satisfied dynamic perfor-mance and steady-state errors It will not only reducethe burden of the control actuators but also avoid
exciting structural vibration In engineering practicethe weighting matrices and the control weightingmatrices should be selected based on the attitudecontrol requirement (eg dynamic performance andsteady-state errors etc)
(4) The dynamics responses influenced by the geometri-cal nonlinearity can be observed In a word the tinydifferences between the magnitudes of the physicalvariables exist for the models with and withoutthe geometrical nonlinearity And the relative cleardifferences exist in the phases for the attitude anglesrates required torques and so forth
6 Conclusions
The coupled attitude and structural dynamics is establishedfor the highly flexible sailcraft by using the von-Karman von-Karmanrsquos nonlinear strain-displacement relationships basedon assumptions of large deflections moderate rotationsand
Mathematical Problems in Engineering 21
Roll
rate
erro
r(∘ s
)
Roll
rate
erro
r(∘ s
)
minus01
0
01
minus01
0
01
Pitc
h ra
te er
ror (
∘ s)
Pitc
h ra
te er
ror (
∘ s)
0 1000 2000 3000 4000 5000minus02
0
02
Yaw
rate
erro
r (∘ s
)
Yaw
rate
erro
r (∘ s
)
4800 4850 4900 4950 5000
minus5
0
5times10minus4
minus5
0
5
times10minus4
minus5
0
5times10minus4
Time (s)
4800 4850 4900 4950 5000
Time (s)
4800 4850 4900 4950 5000
Time (s)
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Figure 13 The roll pitch and yaw rate errors
small strains The Lagrange equation method is utilizedto derive the dynamics for controller design and dynamicsimulation The LQR and optimal PI based controllers aredesigned for the dynamics with the constant disturbancetorque caused by the cmcp offset By theoretical analysisand simulation it can be seen that both controllers cancompromise between the state variables and control inputsBecause the control actuators can hardly afford large controltorque the dynamic performance should be relaxed toreduce the requirement for the attitude control actuatorsBesides the optimal PI based controller can also eliminatethe constant disturbance torque caused by the cmcp offsetthat always exists while the LQR based controller fails toachieve the results with satisfied steady-state performancealthough the attitude control torque is always applied to thecoupled dynamic systemThe dynamics simulations with andwithout the geometrical nonlinearity effect are also carriedout And the differences between the models in magnitudesand phases are identified and analyzed It can be concludedthat the optimal PI based controller performs better than the
LQRbased controller from the viewof eliminating the steady-state error caused by the disturbance torque by the cmcpoffset
Appendix
The related parameters in above equation are given as
119886120593= 119869
119909+ 119898
ℎ11199102
ℎ1
+ 119898ℎ21199112
ℎ2
+ 1198981199011199032
119901119911
+ 1198981199011199032
119901119910
119886120579= minus 119898
119901119903119901119909119903119901119910 119886
120595= minus119898
119901119903119901119909119903119901119911
1198861198811
= minus 1198981198971198972
1198861198812
= minus4
5119898
1198971198972
119887120579= 119869
119910+ 119898
ℎ21199112
ℎ2
+ 1198981199011199032
119901119911
+ 1198981199011199032
119901119909
119887120595= minus 119898
119901119903119901119910119903119901119911 119887
120593= minus119898
119901119903119901119909119903119901119910
22 Mathematical Problems in Engineering
Roll
torq
ue (N
lowastm
)
Roll
torq
ue (N
lowastm
)
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
0 2000 4000 6000
0 2000 4000 6000
0 2000 4000 6000
Time (s)
Time (s)
Time (s)
Time (s)
Time (s)
Time (s)4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
minus01
minus008
008
009
01
minus002
0
002
minus5
0
5
minus2
0
2
Pitc
h to
rque
(Nlowast
m)
Pitc
h to
rque
(Nlowast
m)
minus2
0
2
Yaw
torq
ue (N
lowastm
)
Yaw
torq
ue (N
lowastm
)
Figure 14 The roll pitch and yaw torques
1198871198811
=1
2119898
1198971198972
1198871198812
=2
5119898
1198971198972
119888120595= 119869
119911+ 119898
ℎ11199102
ℎ1
+ 1198981199011199032
119901119910
+ 1198981199011199032
119901119909
119888120579= minus 119898
119901119903119901119910119903119901119911 119888
120593= minus119898
119901119903119901119909119903119901119911
1198881198811
= minus1
21198972
119898119897 119888
1198812
= minus2
51198972
119898119897
119889
1198811
= (4
3
119868119863
119897+
1
5119897119868119860) 119889
1198812
= (1
6119897119868119860+
3119868119863
2119897)
119889
1198811
=4120578
119887119863
119909119909
1198973 119889
1198812
=6120578
119887119863
119909119909
1198973
1198891198811
=4119863
119909119909
1198973 119889
1198812
=6119863
119909119909
1198973
1198761198811
= 1198651198621
(119905)
119890
1198811
= (3
2
119868119863
119897+
1
6119897119868119860)
119890
1198812
= (1
7119897119868119860+
9
5
119868119863
119897) 119890
1198811
=6120578
119887119863
119909119909
1198973
119890
1198812
=12120578
119887119863
119909119909
1198973 119890
1198811
=6119863
119909119909
1198973
1198901198812
=12119863
119909119909
1198973 119876
1198812
= 1198651198622
(119905)
(A1)
The detailed expressions of control inputs for attitudevibration and related parameters in the state-space model ofthe dynamics (see (62) and (63)) are presented as follows
A =
[[[[[[[[[[[[[[
[
0 1 0 0 0 0 0 0 0 0
0 0 0 0 0 0 1198861
1198862
1198863
1198864
0 0 0 1 0 0 0 0 0 0
0 0 0 0 0 0 1198865
1198866
1198867
1198868
0 0 0 0 0 1 0 0 0 0
0 0 0 0 0 0 1198869
11988610
11988611
11988612
0 0 0 0 0 0 0 1 0 0
0 0 0 0 0 0 11988613
11988614
11988615
11988616
0 0 0 0 0 0 0 0 0 1
0 0 0 0 0 0 11988617
11988618
11988619
11988620
]]]]]]]]]]]]]]
]
Mathematical Problems in Engineering 23
0 1000 2000 3000 4000 5000
0 1000 2000 3000 4000 5000
minus01
0
01
minus02
0
02
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Time (s)
Time (s)Time (s)
Time (s)
minus1
0
1
minus1
0
1
times10minus3
times10minus3Th
e disp
lace
men
t of t
he ti
p (m
)
The d
ispla
cem
ent o
f the
tip
(m)
The v
eloci
ty o
f the
tip
(ms
)
The v
eloci
ty o
f the
tip
(ms
)
Figure 15 Vibration displacement and velocity of the tip
B =
[[[[[[[[[[[[[[
[
0 0 0 0 0
1 0 0 0 0
0 0 0 0 0
0 1 0 0 0
0 0 0 0 0
0 0 1 0 0
0 0 0 0 0
0 0 0 1 0
0 0 0 0 0
0 0 0 0 1
]]]]]]]]]]]]]]
]
1198861= minus
1198981198971198972
119869119909
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus4
5119869119909
1198981198971198972
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198862= minus
1198981198971198972
119869119909
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus4
5119869119909
1198981198971198972
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198863= minus
1198981198971198972
119869119909
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus4
5119869119909
1198981198971198972
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198864= minus
1198981198971198972
119869119909
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus4
5119869119909
1198981198971198972
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
119906120593=
119876120593
119869119909
+
119906
119869119909
+119898
1198971198972
119869119909
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+4
5119869119909
1198981198971198972
+
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198865=
1
2119869119910
1198981198971198972
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+2
5119869119910
1198981198971198972
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198866=
1
2119869119910
1198981198971198972
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+2
5119869119910
1198981198971198972
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198867=
1
2119869119910
1198981198971198972
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+2
5119869119910
1198981198971198972
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198868=
1
2119869119910
1198981198971198972
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
24 Mathematical Problems in Engineering
+2
5119869119910
1198981198971198972
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
119906120579=
119876120579
119869119910
+119906
120579
119869119910
minus1
2119869119910
1198981198971198972
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119910
1198981198971198972
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198869= minus
1
2119869119911
1198972
119898119897
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988610
= minus1
2119869119911
1198972
119898119897
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988611
= minus1
2119869119911
1198972
119898119897
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988612
= minus1
2119869119911
1198972
119898119897
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
119906120595=
119876120595
119869119911
+
119906
119869119911
+1
2119869119911
1198972
119898119897
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+2
5119869119911
1198972
119898119897
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988613
= minus
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988614
= minus
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988615
= minus
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988616
= minus
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
1199061198811
=
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988617
= minus
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988618
= minus
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988619
= minus
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988620
= minus
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1199061198812
=
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(A2)
Conflict of Interests
The authors declare that there is no conflict of interestsregarding the publication of this paper
Acknowledgments
The authors would like to thank the anonymous reviewers fortheir critical and constructive review of the paper This studywas cosupported by the National Natural Science Foundationof China (Project no 11302134 11272101)
References
[1] M Colin Solar Sailing Technology Dynamics and MissionApplications Springer-Praxis London UK 1st edition 1999
[2] V Lappas SWokesM Leipold A Lyngvi and P Falkner ldquoGui-dance and control for an Interstellar Heliopause Probe (IHP)solar sail mission to 200 AUrdquo in Proceedings of the AIAAGuidance Navigation and Control Conference and Exhibit pp2472ndash2492 San Francisco Calif USA August 2005
[3] L Charlotte C Camilla and C McInnes ldquoSolar radiation pres-sure augmented deorbiting fromhigh altitude sun-synchronousorbitsrdquo in Proceedings of the 4S Symposium 2012 Small SatellitesSystems and Services Portoroz Slovenia 2012
[4] M Ceriotti and C RMcInnes ldquoGeneration of optimal trajecto-ries for Earth hybrid pole sittersrdquo Journal of Guidance Controland Dynamics vol 34 no 3 pp 847ndash859 2011
[5] S Gong J Li andH Baoyin ldquoSolar sail transfer trajectory fromL1 point to sub-L1 pointrdquoAerospace Science and Technology vol15 no 7 pp 544ndash554 2011
[6] S Gong J Li and H Baoyin ldquoAnalysis of displaced solar sailorbits with passive controlrdquo Journal of Guidance Control andDynamics vol 31 no 3 pp 782ndash785 2008
[7] S Gong H Baoyin and J Li ldquoSolar sail three-body transfertrajectory designrdquo Journal of Guidance Control and Dynamicsvol 33 no 3 pp 873ndash886 2010
Mathematical Problems in Engineering 25
[8] S Gong J Li H Baoyin and J Simo ldquoA new solar sail orbitrdquoScience China Technological Sciences vol 55 no 3 pp 848ndash8552012
[9] Y Tsuda O Mori R Funase et al ldquoAchievement of IKAROS-Japanese deep space solar sail demonstration missionrdquo ActaAstronautica vol 82 no 2 pp 183ndash188 2013
[10] L Johnson MWhorton A Heaton R Pinson G Laue and CAdams ldquoNanoSail-D a solar sail demonstration missionrdquo ActaAstronautica vol 68 no 5-6 pp 571ndash575 2011
[11] B Wie and D Murphy ldquoSolar-sail attitude control design for asail flight validation missionrdquo Journal of Spacecraft and Rocketsvol 44 no 4 pp 809ndash821 2007
[12] B Wie D Murphy M Paluszek and S Thomas ldquoRobust atti-tude control systems design for solar sails part 1 propellantlessprimaryACSrdquo inProceedings of the AIAAGuidance Navigationand Control Conference and Exhibit Providence RI USAAugust 2004
[13] B Wie D Murphy M Paluszek and S Thomas ldquoRobust atti-tude control systems design for solar sails part 2 MicroPPT-based secondary ACSrdquo in Proceedings of the AIAA GuidanceNavigation and Control Conference and Exhibit pp 1325ndash1340Providence RI USA August 2004
[14] S Thomas M Paluszek B Wie and D Murphy ldquoAOCS per-formance and stability validation for large flexible solar sailspacecraftrdquo in Proceedings of the 41st AIAAASMESAEASEEJoint Propulsion Conference amp Exhibit Tucson Ariz USA 2005
[15] B Wie ldquoDynamic modeling and attitude control of solar sailspacecraft part Irdquo in Proceedings of the AIAAGuidance Naviga-tion and Control Conference and Exhibit Monterey Calif USAAugust 2002
[16] BWie ldquoSolar sail attitude control and dynamics part 1rdquo Journalof Guidance Control and Dynamics vol 27 no 4 pp 526ndash5352004
[17] B Wie ldquoDynamic modeling and attitude control of solar sailspacecraft part IIrdquo in Proceedings of the AIAA Guidance Nav-igation and Control Conference and Exhibit Monterey CalifUSA August 2002
[18] BWie ldquoSolar sail attitude control and dynamics part 2rdquo Journalof Guidance Control and Dynamics vol 27 no 4 pp 536ndash5442004
[19] C Luo and J-H Zheng ldquoSolar-sail attitude control based onmoving masses and roll stabilizer barsrdquo Journal of HarbinInstitute of Technology vol 43 no 3 pp 95ndash101 2011
[20] D Romagnoli and T Oehlschlagel ldquoHigh performance twodegrees of freedom attitude control for solar sailsrdquo Advances inSpace Research vol 48 no 11 pp 1869ndash1879 2011
[21] C Scholz D Romagnoli B Dachwald and S Theil ldquoPerfor-mance analysis of an attitude control system for solar sails usingsliding massesrdquo Advances in Space Research vol 48 no 11 pp1822ndash1835 2011
[22] A Bolle and C Circi ldquoSolar sail attitude control through in-plane moving massesrdquo Journal of Aerospace Engineering vol222 no 1 pp 81ndash94 2008
[23] M RotunnoM Basso A B Pome andM Sallusti ldquoA compari-son of robust attitude control techniques for a solar sail space-craftrdquo in Proceedings of the AIAA Guidance Navigation andControl Conference and Exhibit San Francisco Calif USA2005
[24] J Zhang K Zhai and T Wang ldquoControl of large angle maneu-vers for the flexible solar sailrdquo Science China Physics Mechanicsand Astronomy vol 54 no 4 pp 770ndash776 2011
[25] J Zhang andTWang ldquoCoupled attitude-orbit control of flexiblesolar sail for displaced solar orbitrdquo Journal of Spacecraft andRockets vol 50 no 3 pp 675ndash685 2013
[26] Q Li XMa and TWang ldquoReducedmodel for flexible solar saildynamicsrdquo Journal of Spacecraft and Rockets vol 48 no 3 pp446ndash453 2011
[27] M Polites J Kalmanson and D Mangus ldquoSolar sail attitudecontrol using small reaction wheels and magnetic torquersrdquoProceedings of the Institution of Mechanical Engineers G Journalof Aerospace Engineering vol 222 no 1 pp 53ndash62 2008
[28] H-T Cui J-H Luo J-H Feng and P-Y Cui ldquoAttitudecontrol of solar sail spacecraft with control boomrdquo Journal ofAstronautics vol 29 no 2 pp 560ndash566 2008
[29] E Mettler and S R Ploen ldquoSolar sail dynamics and controlusing a boom mounted bus articulated by a bi-state two-axisgimbal and reaction wheelsrdquo in Proceedings of the AIAAAASAstrodynamics Specialist Conference and Exhibit MontereyCalif USA August 2002
[30] J Luo X Li and J Feng ldquoPassive attitude control of solar sailspacecraftrdquo Flight Dynamics vol 26 no 5 pp 47ndash50 2008
[31] J Luo Study on attitude control of solar sail spaceraft [PhDthesis] School of Astronautics Harbin Institute of TechnologyHarbin China 2007
[32] D A Lawrence and S W Piggott ldquoIntegrated trajectory andattitude control for a four-vane solar sailrdquo in Proceedings ofthe AIAA Guidance Navigation and Control Conference andExhibit pp 2416ndash2431 San Francisco Calif USA August 2005
[33] E Mettler A B Acikmese and S R Ploen ldquoAttitude dynamicsand control of solar sails with articulated vanesrdquo in Proceedingsof the AIAA Guidance Navigation and Control Conference andExhibit pp 2396ndash2415 San Francisco Calif USA August 2005
[34] S N Adeli V J Lappas and B Wie ldquoA scalable bus-basedattitude control system for Solar Sailsrdquo Advances in SpaceResearch vol 48 no 11 pp 1836ndash1847 2011
[35] R Funase Y Shirasawa Y Mimasu et al ldquoOn-orbit verificationof fuel-free attitude control system for spinning solar sailutilizing solar radiation pressurerdquo Advances in Space Researchvol 48 no 11 pp 1740ndash1746 2011
[36] B Fu and F O Eke ldquoAttitude control methodology for largesolar sailsrdquo in AIAA Guidance Navigation and Control (GNC)Conference 2013
[37] J Liu N Cui F Shen and S Rong ldquoDynamics of highly-flexiblesolar sail subjected to various forcesrdquoActaAstronautica vol 103pp 55ndash72 2014
[38] J F Liu S Y Rong and J G Li ldquoAttitude dynamics modelingand control of large flexible solar sail spacecraftrdquo in Proceedingsof the 3rd International Symposium on Systems and Control inAeronautics and Astronautics (ISSCAA rsquo10) pp 243ndash247 IEEEPublications Piscataway NJ USA 2010
[39] S Gong H Baoyin and J Li ldquoCoupled attitude-orbit dynamicsand control for displaced solar orbitsrdquo Acta Astronautica vol65 no 5-6 pp 730ndash737 2009
Submit your manuscripts athttpwwwhindawicom
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
MathematicsJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Mathematical Problems in Engineering
Hindawi Publishing Corporationhttpwwwhindawicom
Differential EquationsInternational Journal of
Volume 2014
Applied MathematicsJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Probability and StatisticsHindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Journal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Mathematical PhysicsAdvances in
Complex AnalysisJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
OptimizationJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
CombinatoricsHindawi Publishing Corporationhttpwwwhindawicom Volume 2014
International Journal of
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Operations ResearchAdvances in
Journal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Function Spaces
Abstract and Applied AnalysisHindawi Publishing Corporationhttpwwwhindawicom Volume 2014
International Journal of Mathematics and Mathematical Sciences
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
The Scientific World JournalHindawi Publishing Corporation httpwwwhindawicom Volume 2014
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Algebra
Discrete Dynamics in Nature and Society
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Decision SciencesAdvances in
Discrete MathematicsJournal of
Hindawi Publishing Corporationhttpwwwhindawicom
Volume 2014 Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Stochastic AnalysisInternational Journal of
12 Mathematical Problems in Engineering
(1) Only the attitude motion is affected by the slidingmass the vibration of solar sail structure is notaffected by the sliding mass
(2) Although the attitude control is accomplished byrotating control vanes and the gimbaled controlboom moving sliding masses the specific time his-tories of the actuators are not considered here
(3) The four supporting beams are regarded as an entirestructure thus the identical generalized coordinatesare adopted in the dynamic analysis
41 The Simplified Attitude Dynamics The kinetic energy ofsolar sail supporting beams can be obtained as
119879119898
=1
2120596 sdot J sdot 120596 + 119898
119897int
119897
0
2∘
1205883
sdot (120596 times r3) + (120596 times 120588
3) sdot (120596 times 120588
3)
+ 2 (120596 times r3) sdot (120596 times 120588
3) 119889119911
+ 119898119897int
119897
0
2∘
1205882
sdot (120596 times r2) + (120596 times 120588
2) sdot (120596 times 120588
2)
+ 2 (120596 times r2) sdot (120596 times 120588
2) 119889119910
(49)
The subscripts 2 and 3 represent the second and thirdsupporting beams The displacements can be expressed as
V0119909
(119911 119905) = (119911
119897)
2
sdot 1198811(119905) + (
119911
119897)
3
sdot 1198812(119905)
1199080119910
(119911 119905) = 120572V0119909
(119911 119905) = (119911
119897)
2
sdot 1205721198811(119905) + (
119911
119897)
3
sdot 1205721198812(119905)
for the 3rd beam
V0119909
(119910 119905) = 120573V0119909
(119911 119905) = (119910
119897)
2
sdot 1205731198811(119905) + (
119910
119897)
3
sdot 1205731198812(119905)
1199080119911
(119910 119905) = 120574V0119909
(119910 119905) = (119910
119897)
2
sdot 1205741198811(119905) + (
119910
119897)
3
sdot 1205741198812(119905)
for the 2nd beam
(50)
The subscripts 119909 119910 and 119911 of the left terms in (50)represent the displacements along119909119910 and 119911directions119881
1(119905)
and 1198812(119905) are the generalized coordinates The displacements
1199080119910(119911 119905) V
0119909(119910 119905) and 119908
0119911(119910 119905) can be obtained using the
assumed modes as
1205883= V
0119909(119911 119905) i
119887+ 119908
0119910(119911 119905) j
119887
=
[[[[[
[
(119911
119897)
2
sdot 1198811(119905) + (
119911
119897)
3
sdot 1198812(119905)
120572 [(119911
119897)
2
sdot 1198811(119905) + (
119911
119897)
3
sdot 1198812(119905)]
0
]]]]]
]
1205882= V
0119909(119910 119905) i
119887+ 119908
0119911(119910 119905) k
119887
=
[[[[[
[
120573[(119910
119897)
2
sdot 1198811(119905) + (
119910
119897)
3
sdot 1198812(119905)]
0
120574 [(119910
119897)
2
sdot 1198811(119905) + (
119910
119897)
3
sdot 1198812(119905)]
]]]]]
]
(51)
The vibration velocity can be obtained as
∘
1205883
= 1205883119909i119887+ 120588
3119910j119887=
[[[[[
[
(119911
119897)
2
sdot 1(119905) + (
119911
119897)
3
sdot 2(119905)
1205721[(
119911
119897)
2
sdot 1(119905) + (
119911
119897)
3
sdot 2(119905)]
0
]]]]]
]
∘
1205882
= 1205882119909i119887+ 120588
2119911k119887=
[[[[[
[
1205731[(
119910
119897)
2
sdot 1(119905) + (
119910
119897)
3
sdot 2(119905)]
0
1205741[(
119910
119897)
2
sdot 1(119905) + (
119910
119897)
3
sdot 2(119905)]
]]]]]
]
(52)
Without loss of generality 120572 = 120573 = 1205721= 120573
1= 1 and
120574 = 1205741= minus1 can be assumed in above expressions And the
kinetic energy of the slidingmasses can be obtained as followsby neglecting the vibration related terms
119879ℎ=
1
2119898
ℎ1(120596 times r
ℎ1) sdot (120596 times r
ℎ1) +
1
2119898
ℎ2(120596 times r
ℎ2)
sdot (120596 times rℎ2)
(53)
The kinetic energy of the payload can be obtained as
119879119901=
1
2119898
119901(120596 times r
119901) sdot (120596 times r
119901) (54)
The following simplified attitude dynamics can beobtained by neglecting the second and higher terms ofattitude angles and vibration modes in computing the kinetic
Mathematical Problems in Engineering 13
energies of the supporting beams payload and slidingmasses Consider
119869119909 minus 119898
1198971198972
1minus
4
5119898
1198971198972
2+ 119898
ℎ11199102
ℎ1
+ 119898ℎ21199112
ℎ2
minus 119898119901119903119901119909119903119901119911 + 119898
1199011199032
119901119911
+ 1198981199011199032
119901119910
minus 119898119901119903119901119909119903119901119910
120579 = 119876120593
119869119910
120579 +2
5119898
1198971198972
2+
1
2119898
1198971198972
1+ 119898
ℎ21199112
ℎ2
120579
+ 1198981199011199032
119901119911
120579 minus 119898119901119903119901119910119903119901119911 minus 119898
119901119903119901119909119903119901119910
+ 1198981199011199032
119901119909
120579 = 119876120579
119869119911 minus
2
51198972
1198981198972minus
1
21198972
1198981198971+ 119898
ℎ11199102
ℎ1
minus 119898119901119903119901119910119903119901119911
120579 + 1198981199011199032
119901119910
+ 1198981199011199032
119901119909
minus 119898119901119903119901119909119903119901119911 = 119876
120595
(55)
where 119876120593 119876
120579 and 119876
120595are the generalized nonpotential
attitude control torques generated by the control vanes Andthe attitude control torques generated by the gimbaled controlboom and sliding masses can be found on the left side ofthe above equation coupled with 120579 making the attitudecontroller design problem rather difficult
42 The Simplified Vibration Equations The couplingbetween the axial and transverse vibrations is neglectedand only the transverse vibration is considered The attitudedynamics for dynamic simulation can be obtained as followsbased on previous derivation by neglecting the action ofsolar-radiation pressure
4
3
1198681198631
119897+
1
51198971198681198601+
1
61198971198681198602+
31198681198632
2119897+
4120578119887119863
1199091199091
1198973
+6120578
119887119863
1199091199092
1198973+
41198631199091199091198811
1198973+
61198631199091199091198812
1198973+
271198601199091199091198812119882
2
2
81198973
+54119860
1199091199091198811119881
2
2
71198973+
181198601199091199091198811119882
2
2
71198973+
6119860119909119909119881
2
1
1198812
1198973
+2119860
1199091199091198812119882
2
1
1198973+
81198601199091199091198811119882
2
1
51198973+
8119860119909119909119881
3
1
51198973
+27119860
119909119909119881
3
2
81198973+
361198601199091199091198812119882
1119882
2
71198973+
41198601199091199091198811119882
1119882
2
1198973
minus 1198651198621
(119905) = 0
1
61198971198681198601+
3
2
1198681198631
119897+
1
71198971198681198602+
9
5
1198681198632
119897+
6120578119887119863
1199091199091
1198973
+12120578
119887119863
1199091199092
1198973+
61198631199091199091198811
1198973+
121198631199091199091198812
1198973+
91198601199091199091198812119882
2
2
21198973
+81119860
1199091199091198811119881
2
2
81198973+
271198601199091199091198811119882
2
2
81198973+
541198601199091199091198812119881
2
1
71198973
+18119860
1199091199091198812119882
2
1
71198973+
21198601199091199091198811119882
2
1
1198973+
9119860119909119909119881
3
2
21198973
+2119860
119909119909119881
3
1
1198973+
271198601199091199091198812119882
1119882
2
41198973+
361198601199091199091198811119882
1119882
2
71198973
minus 1198651198622
(119905) = 0
(56)
The following equations can be obtained by rearrangingthe above equations
4
3
1198681198631
119897+
1
51198971198681198601+
1
61198971198681198602+
31198681198632
2119897+
4120578119887119863
1199091199091
1198973
+6120578
119887119863
1199091199092
1198973+
41198631199091199091198811
1198973+
61198631199091199091198812
1198973+
16119860119909119909119881
3
1
51198973
+12119860
119909119909119881
2
1
1198812
1198973+
1081198601199091199091198811119881
2
2
71198973+
54119860119909119909119881
3
2
81198973
minus 1198651198621
(119905) = 0
1
61198971198681198601+
3
2
1198681198631
119897+
1
71198971198681198602+
9
5
1198681198632
119897+
6120578119887119863
1199091199091
1198973
+12120578
119887119863
1199091199092
1198973+
61198631199091199091198811
1198973+
121198631199091199091198812
1198973
+4119860
119909119909119881
3
1
1198973+
108119860119909119909119881
2
1
1198812
71198973+
811198601199091199091198811119881
2
2
41198973
+9119860
119909119909119881
3
2
1198973minus 119865
1198622(119905) = 0
(57)
1198651198621(119905) and 119865
1198622(119905) are used to represent all the generalized
external forces they can be used for vibration control Thesecomplicated equations abovementioned are the basis forobtaining the simplified equations used for controller design
The following equations can be obtained by neglecting thetwo and higher terms
4
3
1198681198631
119897+
1
51198971198681198601+
1
61198971198681198602+
31198681198632
2119897+
4120578119887119863
1199091199091
1198973
+6120578
119887119863
1199091199092
1198973+
41198631199091199091198811
1198973+
61198631199091199091198812
1198973= 119865
1198621
(119905)
14 Mathematical Problems in Engineering
1
61198971198681198601+
3
2
1198681198631
119897+
1
71198971198681198602+
9
5
1198681198632
119897+
6120578119887119863
1199091199091
1198973
+12120578
119887119863
1199091199092
1198973+
61198631199091199091198811
1198973+
121198631199091199091198812
1198973= 119865
1198622
(119905)
(58)
43 The Rigid-Flexible Coupled Dynamics The simplifiedattitude and vibration dynamics can be written as
119886120593 + 119886
120579
120579 + 119886120595 + 119886
1198811
1+ 119886
1198812
2= 119876
120593
119887120579
120579 + 119887120595 + 119887
120593 + 119887
1198811
1+ 119887
1198812
2= 119876
120579
119888120595 + 119888
120579
120579 + 119888120593 + 119888
1198811
1+ 119888
1198812
2= 119876
120595
119889
1198811
1+ 119889
1198812
2+ 119889
1198811
1+ 119889
1198812
2+ 119889
1198811
1198811
+ 1198891198812
1198812= 119876
1198811
119890
1198811
1+ 119890
1198812
2+ 119890
1198811
1+ 119890
1198812
2+ 119890
1198811
1198811
+ 1198901198812
1198812= 119876
1198812
(59)
The related coefficients in the preceding equation can befound in (A1) in the appendix The dynamics (see (59)) isnot suitable for attitude controller design because the controlinputs exist in some coefficients of the angular accelerationsThis will make the controller design rather difficult Thusthe following dynamic model is obtained by putting theterms including the control inputs right side of the dynamicequations
119869119909 minus 119898
1198971198972
1minus
4
5119898
1198971198972
2= 119876
120593+ 119906
119869119910
120579 +2
5119898
1198971198972
2+
1
2119898
1198971198972
1= 119876
120579+ 119906
120579
119869119911 minus
1
21198972
1198981198971minus
2
51198972
1198981198972= 119876
120595+ 119906
119889
1198811
1+ 119889
1198812
2+ 119889
1198811
1+ 119889
1198812
2
+ 1198891198811
1198811+ 119889
1198812
1198812= 119876
1198811
119890
1198811
1+ 119890
1198812
2+ 119890
1198811
1+ 119890
1198812
2
+ 1198901198811
1198811+ 119890
1198812
1198812= 119876
1198812
(60)
The expressions for 119906 119906
120579
and 119906are as
119906= minus119898
ℎ11199102
ℎ1
minus 119898ℎ21199112
ℎ2
+ 119898119901119903119901119909119903119901119911 minus 119898
1199011199032
119901119911
minus 1198981199011199032
119901119910
+ 119898119901119903119901119909119903119901119910
120579
119906
120579
= minus119898ℎ21199112
ℎ2
120579 minus 1198981199011199032
119901119911
120579 + 119898119901119903119901119910119903119901119911 + 119898
119901119903119901119909119903119901119910
minus 1198981199011199032
119901119909
120579
119906= minus119898
ℎ11199102
ℎ1
+ 119898119901119903119901119910119903119901119911
120579 minus 1198981199011199032
119901119910
minus 1198981199011199032
119901119909
+ 119898119901119903119901119909119903119901119911
(61)
119906 119906
120579
and 119906are the functions of the positions of sliding
masses and payload and the angular accelerations The statevariables in (60) are defined as
1199091= 120593 119909
2= 119909
3= 120579 119909
4= 120579
1199095= 120595 119909
6= 119909
7= 119881
1
1199098=
1 119909
9= 119881
2 119909
10=
2
(62)
Thedynamics (60) can bewritten as the state-spacemodelas following
1= 119909
2
2= 119886
11199097+ 119886
21199098+ 119886
31199099+ 119886
411990910
+ 119906120593
3= 119909
4
4= 119886
51199097+ 119886
61199098+ 119886
71199099+ 119886
811990910
+ 119906120579
5= 119909
6
6= 119886
91199097+ 119886
101199098+ 119886
111199099+ 119886
1211990910
+ 119906120595
7= 119909
8
8= 119886
131199097+ 119886
141199098+ 119886
151199099+ 119886
1611990910
+ 1199061198811
9= 119909
10
10
= 119886171199097+ 119886
181199098+ 119886
191199099+ 119886
2011990910
+ 1199061198812
(63)
where 119906120579 119906
120593 and 119906
120595are the generalized control inputs
for attitude control and 1199061198811
and 1199061198812
are the generalizedcontrol inputs for vibration control The controllability canbe satisfied by analyzing (63) The attitudevibration controlinputs and the coefficients will be presented later in thissection The form of a matrix differential equation can bewritten as follows for the above equation
x = Ax + Bu (64)
The expressions of the relatedmatrices and vectors can befound as
x = [1
2
3
4
5
6
7
8
9
10]119879 x (119905
0) = x
1199050
u = [119906120593 119906
120579 119906
120595 119906
1198811
1199061198812
]119879
u (1199050) is known
(65)
where A xB and u are the system matrix state variablesvector control matrix and control inputs vector respectively
Mathematical Problems in Engineering 15
The complexity of the state-space model can be seen bypresenting the detailed expressions of control inputs forattitudevibration and related parameters in (A2) in theappendix
5 AttitudeVibration Control and Simulation
The controller for the attitude and vibration is developedusing the LQR and optimal PI theory The dynamic simula-tion is performed based on the coupled dynamics derived inthe previous sections
51 LQR and Optimal PI Based Controllers Design Thedynamics for solar sail can bewritten as follows togetherwithits quadratic cost function also defined as
x = Ax + Bu x (1199050) = x
1199050
(known)
119869 =1
2int
infin
1199050
[x119879 (119905)Qx (119905) + u119879 (119905)Ru (119905)] 119889119905
(66)
whereQ = Q119879
⩾ 0 andR = R119879
gt 0 are constantThe control-lability of [AB] and the observability of [AD] can beensured when the equationDD119879
= Q holds for anymatrixDThe optimal control input ulowast(119905)within the scope of u(119905) isin R119903119905 isin [119905
0infin] can be computed as follows to make 119869minimum
ulowast (119905) = minusKxlowast (119905) K = Rminus1B119879P (67)
where P is the nonnegative definite symmetric solution of thefollowing Riccati algebraic equations
PA + A119879P minus PBRminus1B119879P +Q = 0 (68)
And the optimal performance index can be obtained asfollows for arbitrary initial states
119869lowast
[x (1199050) 119905
0] =
1
2x1198790
Px0 (69)
The closed-loop system
x = (A minus BRminus1B119879P) x (70)
is asymptotically stableFor an orbiting solar sail the primary disturbance torque
is by the cmcp offset and the impact of the tiny dust inthe deep space The state regulator can be used to controlthe dynamic system affected by pulse disturbance torquewith good steady-state errors but will never achieve accuratesteady-state errors if the dynamics is affected by constantdisturbance torque Thus the optimal state regulator withan integrator to eliminate the constant disturbance torqueshould be presented This optimal proportional-integral reg-ulator not only eliminates the constant disturbance torque butalso possesses the property of optimal regulator
Table 1 The related parameters
Parameters ValuesCMCP offsetm [0 017678 017678]119879
The side length of square sailm 100Nominal solar-radiation pressureconstant at 1 AU from the sunNm2 4563 times 10minus6
Solar-radiation pressure forceN 912 times 10minus2
Roll inertiakglowastm2 50383Pitch and yaw inertiakglowastm2 251915Outer radiusm 0229Thickness of the supporting beamm 75 times 10minus6
Youngrsquos modulus of the supportingbeamGPa 124
Moment of inertia of the cross-sectionof the supporting beamm4 2829412 times 10minus7
Bending stiffness of the supportingbeamNlowastm2 3508471336
Proportional damping coefficient ofsupporting beams 001
Line density of the supportingbeamkgm 0106879
Cross-sectional area of the supportingbeamm2 1079 times 10minus5
Roll disturbance torqueNlowastm 0Pitch (yaw) disturbance torqueNlowastm 0016122 (minus0016122)
For the following linear system with the correspondingperformance index
x = Ax + Bu x (1199050) = x
1199050
u (1199050) = u
1199050
119869 =1
2int
infin
1199050
(x119879Qx + u119879Ru + u119879Su) 119889119905(71)
where Q = Q119879
⩾ 0 R = R119879
gt 0 and S = S119879 gt 0 If [AB]is completely controllable and meanwhile [AD
11] is com-
pletely observable with the relationship D11D119879
11
= Q thesolution can be expressed as
ulowast = minusK1x minus K
2ulowast ulowast (119905
0) = u
1199050
(72)
If B119879B is full rank we can get
ulowast = minusK3x minus K
4x ulowast (119905
0) = u
1199050
(73)
K119894(119894 = 1 2 3 4) is the function of ABQR S
The closed-loop system
[xulowast] = [
A BminusK
1minusK
2
] [xulowast] [
[
x (1199050)
u (1199050)]
]
= [x1199050
u1199050
] (74)
is asymptotically stableThe compromise between the state variables (the angle
angular velocity the vibration displacement and velocity)and control inputs (the torque by all the actuators) can
16 Mathematical Problems in Engineering
0 2000 4000 6000
0 2000 4000 6000
0 2000 4000 6000minus5
0
5
minus5
0
5
minus5
0
5
minus4
minus2
0
2
4
times10minus4
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
00162
00164
00166
4800 4900 5000
4800 4900 5000
4800 4900 5000
minus00165
minus0016
Time (s) Time (s)
Time (s)
Time (s)
Time (s)
Time (s)
Roll
erro
r120593(∘
)
Roll
erro
r120593(∘
)
Pitc
h er
ror120579
(∘)
Pitc
h er
ror120579
(∘)
Yaw
erro
r120595(∘
)
Yaw
erro
r120595(∘
)
Figure 8 The roll pitch and yaw errors
be achieved by using both the LQR based and optimal PIbased controllers for the coupled attitudevibration dynamicsystem The fact is that the attitude control ability is limitedto the control torque by the control actuators The change ofthe attitude angles and rates should not be frequent to voidexciting vibrations
Thus the weighting matrix Q and the control weightingmatrix R are selected as follows for LQR based controller
Q (1 1) = 9 times 10minus6
Q (2 2) = 1 times 10minus6
Q (3 3) = 16 times 10minus6
Q (4 4) = Q (5 5) = Q (6 6) = Q (7 7) = Q (8 8)
= Q (9 9) = Q (10 10) = 1 times 10minus6
Q (119894 119895) = 0 (119894 = 119895 119894 119895 = 1 sim 10)
R (1 1) = R (2 2) = 900 R (3 3) = 100
R (4 4) = R (5 5) = 10000
R119894119895
= 0 (119894 = 119895 119894 119895 = 1 sim 5)
(75)
TheweightingmatrixQ and the control weightingmatrixR are selected as follows for the optimal PI based controller
Q (1 1) = Q (2 2) = 4 times 10minus8
Q (3 3) = Q (4 4) = Q (5 5) = Q (6 6) = Q (7 7)
= Q (8 8) = 16 times 10minus8
Mathematical Problems in Engineering 17
minus02
0
02
Roll
rate
(∘s)
Roll
rate
(∘s)
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Pitc
h ra
te(∘s)
Pitc
h ra
te(∘s)
0 1000 2000 3000 4000 5000
minus05
0
05
minus05
0
05
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
Time (s)
Yaw
rate
(∘
s)
Yaw
rate
(∘
s)
4800 4850 4900 4950 5000
Time (s)4800 4850 4900 4950 5000
Time (s)4800 4850 4900 4950 5000
minus2
0
2
minus2
0
2
minus2
0
2
times10minus4
times10minus4
times10minus4
Figure 9 The roll pitch and yaw rates
Q (9 9) = Q (10 10) = 1 times 10minus8
Q (119894 119895) = 0 (119894 = 119895 119894 119895 = 1 sim 10)
R (1 1) = R (2 2) = R (3 3) = 1 times 10minus8
R (4 4) = R (5 5) = 4 times 10minus8
R (119894 119895) = 0 (119894 = 119895 119894 119895 = 1 sim 5)
(76)
52 The Simulation Results The initial angle errors of rollpitch and yaw are adopted as 120593(119905
0) = 3
∘ 120579(1199050) = 3
∘ and120595(119905
0) = 3
∘ the initial angular velocity errors of roll pitchand yaw are adopted as (119905
0) = 0
∘
s 120579(1199050) = 0
∘
s and(119905
0) = 0
∘
s 1198811(1199050) = 01m 119881
2(1199050) = 01m
1(1199050) = 0ms
and 2(1199050) = 0ms are adopted in this paper for dynamic
simulationThe estimated cmcp offset is 025m for a 100 times 100m
square solar sail It is assumed that the components of cmcpoffset vector are [0 017678 017678]
119879 in the body frame
The relevant parameters for dynamic simulations are givenin Table 1
The dynamic simulation results are obtained as followsby using the LQR controller based on the abovementionedQ and R related parameters and initial conditions Thedynamics simulations with (denoted by ldquowith GFrdquo) andwithout (denoted by ldquowithout GFrdquo) considering the geo-metrical nonlinearity are presented And the correspondingdiscussions and analysis are also given according to thecalculated results
The roll pitch and yaw errors are presented based onthe dynamics models with and without considering thegeometrical nonlinearityThe control effect with zero steady-state error can be achieved for roll axis by referring tothe results But the steady-state errors exist for pitch andyaw axes from Figure 8 this is because there exist constantdisturbance torques for pitch and yaw axes caused by thecmcp offset Thus the LQR based controller cannot be usedfor attitude control with good steady-state performance Thesteady-state errors of pitch and yaw axes are about 0164
∘
and minus0164∘ respectively from the corresponding partial
enlarged drawing of the figures (see the corresponding left
18 Mathematical Problems in Engineering
minus20
0
20
Roll
torq
ue (N
lowastm
)
Roll
torq
ue (N
lowastm
)
minus50
0
50
minus50
0
50
Pitc
h to
rque
(Nlowast
m)
Pitc
h to
rque
(Nlowast
m)
0 1000 2000 3000 4000 5000
0 2000 4000 6000
0 2000 4000 6000
Yaw
torq
ue (N
lowastm
)
Yaw
torq
ue (N
lowastm
)
minus002
0
002
008
01
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
minus01
minus009
minus008
Time (s)Time (s)
Time (s)Time (s)
Time (s)Time (s)
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Figure 10 The roll pitch and yaw torques
figures) A simple and practical controller should be designedto eliminate the steady-state errorsThese errorswill affect theprecision of the super long duration space mission deeply
The differences between the dynamics with and withoutthe geometrical nonlinearity effect can be observed Theamplitudes and phases change a bit by comparing the corre-sponding results
It can be observed by the partial enlarged figures(the right figures of Figure 9) that there are no steady-stateerrors for roll pitch and yaw rates The relative satisfieddynamic performance is achieved In fact a result with muchmore satisfied dynamic performance can be obtained but itwill make the desired control torques much larger duringthe initial period This will not only excite the vibration ofthe structure but also increase the burden of the controlactuators
And the differences between the dynamics models withand without the geometrical nonlinearity can also be seenmerely in the phase of the angular velocities
The desired attitude control torques are presented inFigure 10 The roll torque will tend to be zero with thedecrement of the state variable errors The pitch and yawtorques tend to be constant from the middle and bottom
figures The pitch and yaw steady-state errors can never beeliminated although the pitch and yaw torques (009Nlowastmand minus009Nlowastm) are applied continuously by theoreticalanalysis and simulations This is just a great disadvantage ofthe LQR based controller in this paper The initial controltorques can be afforded by vibrating the gimbaled controlboom andmoving the slidingmasses that can afford a relativelarge torque The control vanes can be used to afford thecontrol torques when solar sail is in steady-state process Theexpression of the attitude control inputs 119906
120593 119906
120579 and 119906
120595can be
found in previous sectionMoreover the differences between dynamics responses
with and without geometrical nonlinearity can also beobserved by comparing the corresponding results Therequired torques for the attitude control are a little largerfor the dynamics with geometrical nonlinearity And thedifference in the phase is also clear
It can be seen that the vibration of the supporting beamis depressed effectively by the simulation results in Figure 11It can be seen that the steady-state errors and the dynamicperformance are relatively satisfied It can also be seen that thedynamics responses between the model with and without the
Mathematical Problems in Engineering 19
0 1000 2000 3000 4000 5000
0 1000 2000 3000 4000 5000
minus01
0
01
minus02
0
02
Time (s) Time (s)
Time (s) Time (s)
minus5
0
5
times10minus4
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
minus1
0
1
times10minus3
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
The d
ispla
cem
ent o
f the
tip
(m)
The d
ispla
cem
ent o
f the
tip
(m)
The v
eloci
ty o
f the
tip
(ms
)
The v
eloc
ity o
f the
tip
(ms
)
Figure 11 The displacement and velocity of the tip of the supporting beam
geometrical nonlinearity effect are different in the vibrationdisplacement and velocitymagnitudes and phases (Figure 15)
The simulation results can be obtained as follows by usingthe optimal PI based controller adopting the abovementionedparameters and initial conditions
The roll pitch and yaw errors are given by using theoptimal PI based controller These errors tend to disappearby observing the partially enlarged plotting of the figure (thecorresponding right figures) (shown in Figure 12) And therelative satisfied dynamic performance can also be obtainedFrom the view of eliminating the steady-state errors the opti-mal PI based controller performs better than the LQR basedcontroller by theoretical analysis and simulation results Theformer can achieve attitude control results without pitchand yaw steady-state errors From the view of dynamicperformance both the controllers perform well In additionit can be seen that the difference between the modelswith and without geometrical nonlinearity is merely inthe phase
The roll pitch and yaw rate errors are presented inFigure 13 The dynamic and steady-state performances aresatisfied by observing the simulation results And by observ-ing the difference between the dynamics responses with and
without the influence by the geometrical nonlinearity it canbe concluded that the merely difference is the phase
The desired control torques of the roll pitch and yaw areobtained in Figure 14 by using the optimal PI based controllerIt can be seen that the value of the desired roll control torquedecreases to zero as the values of the roll angle and ratedecrease to zero The desired pitch and yaw control torquestend to be the constant values 009Nlowastm and minus009Nlowastmrespectively The desired initial control torques are large byobserving Figure 14 It is suggested that the gimbaled controlboom combining the sliding masses is adopted to afford theinitial torque Then the control vanes can be used to controlthe solar sail after the initial phase The phase differencecan also be observed by inspecting the dynamics responsesduring the 4800sim5000 s period
The vibration can be controlled effectively based on theoptimal PI controller And the relative satisfied dynamicand steady-state performances can be achieved In additionthe tiny differences exist in the magnitudes of the requiredtorques And the phase differences also exist
It can be concluded as follows by analyzing and compar-ing the simulation results based on the LQR and optimal PItheories in detail
20 Mathematical Problems in Engineering
Roll
erro
r120593(∘
)
Roll
erro
r120593(∘
)
minus5
0
5
minus5
0
5
Pitc
h er
ror120579
(∘)
Pitc
h er
ror120579
(∘)
0 1000 2000 3000 4000 5000minus10
0
10
Time (s) Time (s)
Time (s)
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
Yaw
erro
r120595(∘
)
Yaw
erro
r120595(∘
)
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
minus1
0
1
times10minus3
minus1
0
1
times10minus3
minus1
0
1
times10minus3
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Figure 12 The roll pitch and yaw errors
(1) From the view of eliminating the steady-state errorsof the pitch and yaw errors the optimal PI based con-troller performs better than the LQR based controllerby theoretical analysis and simulation results Thedynamic performances of the two controllers are bothsatisfied and the desired control torques are relativelysmall
(2) The weighting of the state variables is reflected by theweighting matrix according to the LQR and optimalPI theories The constant weighting matrices selectedin this paper can effectively reflect the initial statevariable errors but maybe reflect the final state vari-able errors deficiently The time-varying weightingmatrices should be selected
(3) For the actual orbiting solar sail the control actuators(control vanes gimbaled control boom and slidingmasses) cannot afford excessive large control torquesThus the control torques should be as small as possibleon the premise of acquiring satisfied dynamic perfor-mance and steady-state errors It will not only reducethe burden of the control actuators but also avoid
exciting structural vibration In engineering practicethe weighting matrices and the control weightingmatrices should be selected based on the attitudecontrol requirement (eg dynamic performance andsteady-state errors etc)
(4) The dynamics responses influenced by the geometri-cal nonlinearity can be observed In a word the tinydifferences between the magnitudes of the physicalvariables exist for the models with and withoutthe geometrical nonlinearity And the relative cleardifferences exist in the phases for the attitude anglesrates required torques and so forth
6 Conclusions
The coupled attitude and structural dynamics is establishedfor the highly flexible sailcraft by using the von-Karman von-Karmanrsquos nonlinear strain-displacement relationships basedon assumptions of large deflections moderate rotationsand
Mathematical Problems in Engineering 21
Roll
rate
erro
r(∘ s
)
Roll
rate
erro
r(∘ s
)
minus01
0
01
minus01
0
01
Pitc
h ra
te er
ror (
∘ s)
Pitc
h ra
te er
ror (
∘ s)
0 1000 2000 3000 4000 5000minus02
0
02
Yaw
rate
erro
r (∘ s
)
Yaw
rate
erro
r (∘ s
)
4800 4850 4900 4950 5000
minus5
0
5times10minus4
minus5
0
5
times10minus4
minus5
0
5times10minus4
Time (s)
4800 4850 4900 4950 5000
Time (s)
4800 4850 4900 4950 5000
Time (s)
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Figure 13 The roll pitch and yaw rate errors
small strains The Lagrange equation method is utilizedto derive the dynamics for controller design and dynamicsimulation The LQR and optimal PI based controllers aredesigned for the dynamics with the constant disturbancetorque caused by the cmcp offset By theoretical analysisand simulation it can be seen that both controllers cancompromise between the state variables and control inputsBecause the control actuators can hardly afford large controltorque the dynamic performance should be relaxed toreduce the requirement for the attitude control actuatorsBesides the optimal PI based controller can also eliminatethe constant disturbance torque caused by the cmcp offsetthat always exists while the LQR based controller fails toachieve the results with satisfied steady-state performancealthough the attitude control torque is always applied to thecoupled dynamic systemThe dynamics simulations with andwithout the geometrical nonlinearity effect are also carriedout And the differences between the models in magnitudesand phases are identified and analyzed It can be concludedthat the optimal PI based controller performs better than the
LQRbased controller from the viewof eliminating the steady-state error caused by the disturbance torque by the cmcpoffset
Appendix
The related parameters in above equation are given as
119886120593= 119869
119909+ 119898
ℎ11199102
ℎ1
+ 119898ℎ21199112
ℎ2
+ 1198981199011199032
119901119911
+ 1198981199011199032
119901119910
119886120579= minus 119898
119901119903119901119909119903119901119910 119886
120595= minus119898
119901119903119901119909119903119901119911
1198861198811
= minus 1198981198971198972
1198861198812
= minus4
5119898
1198971198972
119887120579= 119869
119910+ 119898
ℎ21199112
ℎ2
+ 1198981199011199032
119901119911
+ 1198981199011199032
119901119909
119887120595= minus 119898
119901119903119901119910119903119901119911 119887
120593= minus119898
119901119903119901119909119903119901119910
22 Mathematical Problems in Engineering
Roll
torq
ue (N
lowastm
)
Roll
torq
ue (N
lowastm
)
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
0 2000 4000 6000
0 2000 4000 6000
0 2000 4000 6000
Time (s)
Time (s)
Time (s)
Time (s)
Time (s)
Time (s)4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
minus01
minus008
008
009
01
minus002
0
002
minus5
0
5
minus2
0
2
Pitc
h to
rque
(Nlowast
m)
Pitc
h to
rque
(Nlowast
m)
minus2
0
2
Yaw
torq
ue (N
lowastm
)
Yaw
torq
ue (N
lowastm
)
Figure 14 The roll pitch and yaw torques
1198871198811
=1
2119898
1198971198972
1198871198812
=2
5119898
1198971198972
119888120595= 119869
119911+ 119898
ℎ11199102
ℎ1
+ 1198981199011199032
119901119910
+ 1198981199011199032
119901119909
119888120579= minus 119898
119901119903119901119910119903119901119911 119888
120593= minus119898
119901119903119901119909119903119901119911
1198881198811
= minus1
21198972
119898119897 119888
1198812
= minus2
51198972
119898119897
119889
1198811
= (4
3
119868119863
119897+
1
5119897119868119860) 119889
1198812
= (1
6119897119868119860+
3119868119863
2119897)
119889
1198811
=4120578
119887119863
119909119909
1198973 119889
1198812
=6120578
119887119863
119909119909
1198973
1198891198811
=4119863
119909119909
1198973 119889
1198812
=6119863
119909119909
1198973
1198761198811
= 1198651198621
(119905)
119890
1198811
= (3
2
119868119863
119897+
1
6119897119868119860)
119890
1198812
= (1
7119897119868119860+
9
5
119868119863
119897) 119890
1198811
=6120578
119887119863
119909119909
1198973
119890
1198812
=12120578
119887119863
119909119909
1198973 119890
1198811
=6119863
119909119909
1198973
1198901198812
=12119863
119909119909
1198973 119876
1198812
= 1198651198622
(119905)
(A1)
The detailed expressions of control inputs for attitudevibration and related parameters in the state-space model ofthe dynamics (see (62) and (63)) are presented as follows
A =
[[[[[[[[[[[[[[
[
0 1 0 0 0 0 0 0 0 0
0 0 0 0 0 0 1198861
1198862
1198863
1198864
0 0 0 1 0 0 0 0 0 0
0 0 0 0 0 0 1198865
1198866
1198867
1198868
0 0 0 0 0 1 0 0 0 0
0 0 0 0 0 0 1198869
11988610
11988611
11988612
0 0 0 0 0 0 0 1 0 0
0 0 0 0 0 0 11988613
11988614
11988615
11988616
0 0 0 0 0 0 0 0 0 1
0 0 0 0 0 0 11988617
11988618
11988619
11988620
]]]]]]]]]]]]]]
]
Mathematical Problems in Engineering 23
0 1000 2000 3000 4000 5000
0 1000 2000 3000 4000 5000
minus01
0
01
minus02
0
02
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Time (s)
Time (s)Time (s)
Time (s)
minus1
0
1
minus1
0
1
times10minus3
times10minus3Th
e disp
lace
men
t of t
he ti
p (m
)
The d
ispla
cem
ent o
f the
tip
(m)
The v
eloci
ty o
f the
tip
(ms
)
The v
eloci
ty o
f the
tip
(ms
)
Figure 15 Vibration displacement and velocity of the tip
B =
[[[[[[[[[[[[[[
[
0 0 0 0 0
1 0 0 0 0
0 0 0 0 0
0 1 0 0 0
0 0 0 0 0
0 0 1 0 0
0 0 0 0 0
0 0 0 1 0
0 0 0 0 0
0 0 0 0 1
]]]]]]]]]]]]]]
]
1198861= minus
1198981198971198972
119869119909
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus4
5119869119909
1198981198971198972
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198862= minus
1198981198971198972
119869119909
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus4
5119869119909
1198981198971198972
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198863= minus
1198981198971198972
119869119909
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus4
5119869119909
1198981198971198972
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198864= minus
1198981198971198972
119869119909
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus4
5119869119909
1198981198971198972
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
119906120593=
119876120593
119869119909
+
119906
119869119909
+119898
1198971198972
119869119909
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+4
5119869119909
1198981198971198972
+
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198865=
1
2119869119910
1198981198971198972
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+2
5119869119910
1198981198971198972
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198866=
1
2119869119910
1198981198971198972
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+2
5119869119910
1198981198971198972
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198867=
1
2119869119910
1198981198971198972
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+2
5119869119910
1198981198971198972
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198868=
1
2119869119910
1198981198971198972
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
24 Mathematical Problems in Engineering
+2
5119869119910
1198981198971198972
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
119906120579=
119876120579
119869119910
+119906
120579
119869119910
minus1
2119869119910
1198981198971198972
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119910
1198981198971198972
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198869= minus
1
2119869119911
1198972
119898119897
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988610
= minus1
2119869119911
1198972
119898119897
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988611
= minus1
2119869119911
1198972
119898119897
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988612
= minus1
2119869119911
1198972
119898119897
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
119906120595=
119876120595
119869119911
+
119906
119869119911
+1
2119869119911
1198972
119898119897
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+2
5119869119911
1198972
119898119897
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988613
= minus
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988614
= minus
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988615
= minus
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988616
= minus
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
1199061198811
=
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988617
= minus
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988618
= minus
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988619
= minus
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988620
= minus
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1199061198812
=
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(A2)
Conflict of Interests
The authors declare that there is no conflict of interestsregarding the publication of this paper
Acknowledgments
The authors would like to thank the anonymous reviewers fortheir critical and constructive review of the paper This studywas cosupported by the National Natural Science Foundationof China (Project no 11302134 11272101)
References
[1] M Colin Solar Sailing Technology Dynamics and MissionApplications Springer-Praxis London UK 1st edition 1999
[2] V Lappas SWokesM Leipold A Lyngvi and P Falkner ldquoGui-dance and control for an Interstellar Heliopause Probe (IHP)solar sail mission to 200 AUrdquo in Proceedings of the AIAAGuidance Navigation and Control Conference and Exhibit pp2472ndash2492 San Francisco Calif USA August 2005
[3] L Charlotte C Camilla and C McInnes ldquoSolar radiation pres-sure augmented deorbiting fromhigh altitude sun-synchronousorbitsrdquo in Proceedings of the 4S Symposium 2012 Small SatellitesSystems and Services Portoroz Slovenia 2012
[4] M Ceriotti and C RMcInnes ldquoGeneration of optimal trajecto-ries for Earth hybrid pole sittersrdquo Journal of Guidance Controland Dynamics vol 34 no 3 pp 847ndash859 2011
[5] S Gong J Li andH Baoyin ldquoSolar sail transfer trajectory fromL1 point to sub-L1 pointrdquoAerospace Science and Technology vol15 no 7 pp 544ndash554 2011
[6] S Gong J Li and H Baoyin ldquoAnalysis of displaced solar sailorbits with passive controlrdquo Journal of Guidance Control andDynamics vol 31 no 3 pp 782ndash785 2008
[7] S Gong H Baoyin and J Li ldquoSolar sail three-body transfertrajectory designrdquo Journal of Guidance Control and Dynamicsvol 33 no 3 pp 873ndash886 2010
Mathematical Problems in Engineering 25
[8] S Gong J Li H Baoyin and J Simo ldquoA new solar sail orbitrdquoScience China Technological Sciences vol 55 no 3 pp 848ndash8552012
[9] Y Tsuda O Mori R Funase et al ldquoAchievement of IKAROS-Japanese deep space solar sail demonstration missionrdquo ActaAstronautica vol 82 no 2 pp 183ndash188 2013
[10] L Johnson MWhorton A Heaton R Pinson G Laue and CAdams ldquoNanoSail-D a solar sail demonstration missionrdquo ActaAstronautica vol 68 no 5-6 pp 571ndash575 2011
[11] B Wie and D Murphy ldquoSolar-sail attitude control design for asail flight validation missionrdquo Journal of Spacecraft and Rocketsvol 44 no 4 pp 809ndash821 2007
[12] B Wie D Murphy M Paluszek and S Thomas ldquoRobust atti-tude control systems design for solar sails part 1 propellantlessprimaryACSrdquo inProceedings of the AIAAGuidance Navigationand Control Conference and Exhibit Providence RI USAAugust 2004
[13] B Wie D Murphy M Paluszek and S Thomas ldquoRobust atti-tude control systems design for solar sails part 2 MicroPPT-based secondary ACSrdquo in Proceedings of the AIAA GuidanceNavigation and Control Conference and Exhibit pp 1325ndash1340Providence RI USA August 2004
[14] S Thomas M Paluszek B Wie and D Murphy ldquoAOCS per-formance and stability validation for large flexible solar sailspacecraftrdquo in Proceedings of the 41st AIAAASMESAEASEEJoint Propulsion Conference amp Exhibit Tucson Ariz USA 2005
[15] B Wie ldquoDynamic modeling and attitude control of solar sailspacecraft part Irdquo in Proceedings of the AIAAGuidance Naviga-tion and Control Conference and Exhibit Monterey Calif USAAugust 2002
[16] BWie ldquoSolar sail attitude control and dynamics part 1rdquo Journalof Guidance Control and Dynamics vol 27 no 4 pp 526ndash5352004
[17] B Wie ldquoDynamic modeling and attitude control of solar sailspacecraft part IIrdquo in Proceedings of the AIAA Guidance Nav-igation and Control Conference and Exhibit Monterey CalifUSA August 2002
[18] BWie ldquoSolar sail attitude control and dynamics part 2rdquo Journalof Guidance Control and Dynamics vol 27 no 4 pp 536ndash5442004
[19] C Luo and J-H Zheng ldquoSolar-sail attitude control based onmoving masses and roll stabilizer barsrdquo Journal of HarbinInstitute of Technology vol 43 no 3 pp 95ndash101 2011
[20] D Romagnoli and T Oehlschlagel ldquoHigh performance twodegrees of freedom attitude control for solar sailsrdquo Advances inSpace Research vol 48 no 11 pp 1869ndash1879 2011
[21] C Scholz D Romagnoli B Dachwald and S Theil ldquoPerfor-mance analysis of an attitude control system for solar sails usingsliding massesrdquo Advances in Space Research vol 48 no 11 pp1822ndash1835 2011
[22] A Bolle and C Circi ldquoSolar sail attitude control through in-plane moving massesrdquo Journal of Aerospace Engineering vol222 no 1 pp 81ndash94 2008
[23] M RotunnoM Basso A B Pome andM Sallusti ldquoA compari-son of robust attitude control techniques for a solar sail space-craftrdquo in Proceedings of the AIAA Guidance Navigation andControl Conference and Exhibit San Francisco Calif USA2005
[24] J Zhang K Zhai and T Wang ldquoControl of large angle maneu-vers for the flexible solar sailrdquo Science China Physics Mechanicsand Astronomy vol 54 no 4 pp 770ndash776 2011
[25] J Zhang andTWang ldquoCoupled attitude-orbit control of flexiblesolar sail for displaced solar orbitrdquo Journal of Spacecraft andRockets vol 50 no 3 pp 675ndash685 2013
[26] Q Li XMa and TWang ldquoReducedmodel for flexible solar saildynamicsrdquo Journal of Spacecraft and Rockets vol 48 no 3 pp446ndash453 2011
[27] M Polites J Kalmanson and D Mangus ldquoSolar sail attitudecontrol using small reaction wheels and magnetic torquersrdquoProceedings of the Institution of Mechanical Engineers G Journalof Aerospace Engineering vol 222 no 1 pp 53ndash62 2008
[28] H-T Cui J-H Luo J-H Feng and P-Y Cui ldquoAttitudecontrol of solar sail spacecraft with control boomrdquo Journal ofAstronautics vol 29 no 2 pp 560ndash566 2008
[29] E Mettler and S R Ploen ldquoSolar sail dynamics and controlusing a boom mounted bus articulated by a bi-state two-axisgimbal and reaction wheelsrdquo in Proceedings of the AIAAAASAstrodynamics Specialist Conference and Exhibit MontereyCalif USA August 2002
[30] J Luo X Li and J Feng ldquoPassive attitude control of solar sailspacecraftrdquo Flight Dynamics vol 26 no 5 pp 47ndash50 2008
[31] J Luo Study on attitude control of solar sail spaceraft [PhDthesis] School of Astronautics Harbin Institute of TechnologyHarbin China 2007
[32] D A Lawrence and S W Piggott ldquoIntegrated trajectory andattitude control for a four-vane solar sailrdquo in Proceedings ofthe AIAA Guidance Navigation and Control Conference andExhibit pp 2416ndash2431 San Francisco Calif USA August 2005
[33] E Mettler A B Acikmese and S R Ploen ldquoAttitude dynamicsand control of solar sails with articulated vanesrdquo in Proceedingsof the AIAA Guidance Navigation and Control Conference andExhibit pp 2396ndash2415 San Francisco Calif USA August 2005
[34] S N Adeli V J Lappas and B Wie ldquoA scalable bus-basedattitude control system for Solar Sailsrdquo Advances in SpaceResearch vol 48 no 11 pp 1836ndash1847 2011
[35] R Funase Y Shirasawa Y Mimasu et al ldquoOn-orbit verificationof fuel-free attitude control system for spinning solar sailutilizing solar radiation pressurerdquo Advances in Space Researchvol 48 no 11 pp 1740ndash1746 2011
[36] B Fu and F O Eke ldquoAttitude control methodology for largesolar sailsrdquo in AIAA Guidance Navigation and Control (GNC)Conference 2013
[37] J Liu N Cui F Shen and S Rong ldquoDynamics of highly-flexiblesolar sail subjected to various forcesrdquoActaAstronautica vol 103pp 55ndash72 2014
[38] J F Liu S Y Rong and J G Li ldquoAttitude dynamics modelingand control of large flexible solar sail spacecraftrdquo in Proceedingsof the 3rd International Symposium on Systems and Control inAeronautics and Astronautics (ISSCAA rsquo10) pp 243ndash247 IEEEPublications Piscataway NJ USA 2010
[39] S Gong H Baoyin and J Li ldquoCoupled attitude-orbit dynamicsand control for displaced solar orbitsrdquo Acta Astronautica vol65 no 5-6 pp 730ndash737 2009
Submit your manuscripts athttpwwwhindawicom
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
MathematicsJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Mathematical Problems in Engineering
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Differential EquationsInternational Journal of
Volume 2014
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Abstract and Applied AnalysisHindawi Publishing Corporationhttpwwwhindawicom Volume 2014
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Volume 2014 Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Stochastic AnalysisInternational Journal of
Mathematical Problems in Engineering 13
energies of the supporting beams payload and slidingmasses Consider
119869119909 minus 119898
1198971198972
1minus
4
5119898
1198971198972
2+ 119898
ℎ11199102
ℎ1
+ 119898ℎ21199112
ℎ2
minus 119898119901119903119901119909119903119901119911 + 119898
1199011199032
119901119911
+ 1198981199011199032
119901119910
minus 119898119901119903119901119909119903119901119910
120579 = 119876120593
119869119910
120579 +2
5119898
1198971198972
2+
1
2119898
1198971198972
1+ 119898
ℎ21199112
ℎ2
120579
+ 1198981199011199032
119901119911
120579 minus 119898119901119903119901119910119903119901119911 minus 119898
119901119903119901119909119903119901119910
+ 1198981199011199032
119901119909
120579 = 119876120579
119869119911 minus
2
51198972
1198981198972minus
1
21198972
1198981198971+ 119898
ℎ11199102
ℎ1
minus 119898119901119903119901119910119903119901119911
120579 + 1198981199011199032
119901119910
+ 1198981199011199032
119901119909
minus 119898119901119903119901119909119903119901119911 = 119876
120595
(55)
where 119876120593 119876
120579 and 119876
120595are the generalized nonpotential
attitude control torques generated by the control vanes Andthe attitude control torques generated by the gimbaled controlboom and sliding masses can be found on the left side ofthe above equation coupled with 120579 making the attitudecontroller design problem rather difficult
42 The Simplified Vibration Equations The couplingbetween the axial and transverse vibrations is neglectedand only the transverse vibration is considered The attitudedynamics for dynamic simulation can be obtained as followsbased on previous derivation by neglecting the action ofsolar-radiation pressure
4
3
1198681198631
119897+
1
51198971198681198601+
1
61198971198681198602+
31198681198632
2119897+
4120578119887119863
1199091199091
1198973
+6120578
119887119863
1199091199092
1198973+
41198631199091199091198811
1198973+
61198631199091199091198812
1198973+
271198601199091199091198812119882
2
2
81198973
+54119860
1199091199091198811119881
2
2
71198973+
181198601199091199091198811119882
2
2
71198973+
6119860119909119909119881
2
1
1198812
1198973
+2119860
1199091199091198812119882
2
1
1198973+
81198601199091199091198811119882
2
1
51198973+
8119860119909119909119881
3
1
51198973
+27119860
119909119909119881
3
2
81198973+
361198601199091199091198812119882
1119882
2
71198973+
41198601199091199091198811119882
1119882
2
1198973
minus 1198651198621
(119905) = 0
1
61198971198681198601+
3
2
1198681198631
119897+
1
71198971198681198602+
9
5
1198681198632
119897+
6120578119887119863
1199091199091
1198973
+12120578
119887119863
1199091199092
1198973+
61198631199091199091198811
1198973+
121198631199091199091198812
1198973+
91198601199091199091198812119882
2
2
21198973
+81119860
1199091199091198811119881
2
2
81198973+
271198601199091199091198811119882
2
2
81198973+
541198601199091199091198812119881
2
1
71198973
+18119860
1199091199091198812119882
2
1
71198973+
21198601199091199091198811119882
2
1
1198973+
9119860119909119909119881
3
2
21198973
+2119860
119909119909119881
3
1
1198973+
271198601199091199091198812119882
1119882
2
41198973+
361198601199091199091198811119882
1119882
2
71198973
minus 1198651198622
(119905) = 0
(56)
The following equations can be obtained by rearrangingthe above equations
4
3
1198681198631
119897+
1
51198971198681198601+
1
61198971198681198602+
31198681198632
2119897+
4120578119887119863
1199091199091
1198973
+6120578
119887119863
1199091199092
1198973+
41198631199091199091198811
1198973+
61198631199091199091198812
1198973+
16119860119909119909119881
3
1
51198973
+12119860
119909119909119881
2
1
1198812
1198973+
1081198601199091199091198811119881
2
2
71198973+
54119860119909119909119881
3
2
81198973
minus 1198651198621
(119905) = 0
1
61198971198681198601+
3
2
1198681198631
119897+
1
71198971198681198602+
9
5
1198681198632
119897+
6120578119887119863
1199091199091
1198973
+12120578
119887119863
1199091199092
1198973+
61198631199091199091198811
1198973+
121198631199091199091198812
1198973
+4119860
119909119909119881
3
1
1198973+
108119860119909119909119881
2
1
1198812
71198973+
811198601199091199091198811119881
2
2
41198973
+9119860
119909119909119881
3
2
1198973minus 119865
1198622(119905) = 0
(57)
1198651198621(119905) and 119865
1198622(119905) are used to represent all the generalized
external forces they can be used for vibration control Thesecomplicated equations abovementioned are the basis forobtaining the simplified equations used for controller design
The following equations can be obtained by neglecting thetwo and higher terms
4
3
1198681198631
119897+
1
51198971198681198601+
1
61198971198681198602+
31198681198632
2119897+
4120578119887119863
1199091199091
1198973
+6120578
119887119863
1199091199092
1198973+
41198631199091199091198811
1198973+
61198631199091199091198812
1198973= 119865
1198621
(119905)
14 Mathematical Problems in Engineering
1
61198971198681198601+
3
2
1198681198631
119897+
1
71198971198681198602+
9
5
1198681198632
119897+
6120578119887119863
1199091199091
1198973
+12120578
119887119863
1199091199092
1198973+
61198631199091199091198811
1198973+
121198631199091199091198812
1198973= 119865
1198622
(119905)
(58)
43 The Rigid-Flexible Coupled Dynamics The simplifiedattitude and vibration dynamics can be written as
119886120593 + 119886
120579
120579 + 119886120595 + 119886
1198811
1+ 119886
1198812
2= 119876
120593
119887120579
120579 + 119887120595 + 119887
120593 + 119887
1198811
1+ 119887
1198812
2= 119876
120579
119888120595 + 119888
120579
120579 + 119888120593 + 119888
1198811
1+ 119888
1198812
2= 119876
120595
119889
1198811
1+ 119889
1198812
2+ 119889
1198811
1+ 119889
1198812
2+ 119889
1198811
1198811
+ 1198891198812
1198812= 119876
1198811
119890
1198811
1+ 119890
1198812
2+ 119890
1198811
1+ 119890
1198812
2+ 119890
1198811
1198811
+ 1198901198812
1198812= 119876
1198812
(59)
The related coefficients in the preceding equation can befound in (A1) in the appendix The dynamics (see (59)) isnot suitable for attitude controller design because the controlinputs exist in some coefficients of the angular accelerationsThis will make the controller design rather difficult Thusthe following dynamic model is obtained by putting theterms including the control inputs right side of the dynamicequations
119869119909 minus 119898
1198971198972
1minus
4
5119898
1198971198972
2= 119876
120593+ 119906
119869119910
120579 +2
5119898
1198971198972
2+
1
2119898
1198971198972
1= 119876
120579+ 119906
120579
119869119911 minus
1
21198972
1198981198971minus
2
51198972
1198981198972= 119876
120595+ 119906
119889
1198811
1+ 119889
1198812
2+ 119889
1198811
1+ 119889
1198812
2
+ 1198891198811
1198811+ 119889
1198812
1198812= 119876
1198811
119890
1198811
1+ 119890
1198812
2+ 119890
1198811
1+ 119890
1198812
2
+ 1198901198811
1198811+ 119890
1198812
1198812= 119876
1198812
(60)
The expressions for 119906 119906
120579
and 119906are as
119906= minus119898
ℎ11199102
ℎ1
minus 119898ℎ21199112
ℎ2
+ 119898119901119903119901119909119903119901119911 minus 119898
1199011199032
119901119911
minus 1198981199011199032
119901119910
+ 119898119901119903119901119909119903119901119910
120579
119906
120579
= minus119898ℎ21199112
ℎ2
120579 minus 1198981199011199032
119901119911
120579 + 119898119901119903119901119910119903119901119911 + 119898
119901119903119901119909119903119901119910
minus 1198981199011199032
119901119909
120579
119906= minus119898
ℎ11199102
ℎ1
+ 119898119901119903119901119910119903119901119911
120579 minus 1198981199011199032
119901119910
minus 1198981199011199032
119901119909
+ 119898119901119903119901119909119903119901119911
(61)
119906 119906
120579
and 119906are the functions of the positions of sliding
masses and payload and the angular accelerations The statevariables in (60) are defined as
1199091= 120593 119909
2= 119909
3= 120579 119909
4= 120579
1199095= 120595 119909
6= 119909
7= 119881
1
1199098=
1 119909
9= 119881
2 119909
10=
2
(62)
Thedynamics (60) can bewritten as the state-spacemodelas following
1= 119909
2
2= 119886
11199097+ 119886
21199098+ 119886
31199099+ 119886
411990910
+ 119906120593
3= 119909
4
4= 119886
51199097+ 119886
61199098+ 119886
71199099+ 119886
811990910
+ 119906120579
5= 119909
6
6= 119886
91199097+ 119886
101199098+ 119886
111199099+ 119886
1211990910
+ 119906120595
7= 119909
8
8= 119886
131199097+ 119886
141199098+ 119886
151199099+ 119886
1611990910
+ 1199061198811
9= 119909
10
10
= 119886171199097+ 119886
181199098+ 119886
191199099+ 119886
2011990910
+ 1199061198812
(63)
where 119906120579 119906
120593 and 119906
120595are the generalized control inputs
for attitude control and 1199061198811
and 1199061198812
are the generalizedcontrol inputs for vibration control The controllability canbe satisfied by analyzing (63) The attitudevibration controlinputs and the coefficients will be presented later in thissection The form of a matrix differential equation can bewritten as follows for the above equation
x = Ax + Bu (64)
The expressions of the relatedmatrices and vectors can befound as
x = [1
2
3
4
5
6
7
8
9
10]119879 x (119905
0) = x
1199050
u = [119906120593 119906
120579 119906
120595 119906
1198811
1199061198812
]119879
u (1199050) is known
(65)
where A xB and u are the system matrix state variablesvector control matrix and control inputs vector respectively
Mathematical Problems in Engineering 15
The complexity of the state-space model can be seen bypresenting the detailed expressions of control inputs forattitudevibration and related parameters in (A2) in theappendix
5 AttitudeVibration Control and Simulation
The controller for the attitude and vibration is developedusing the LQR and optimal PI theory The dynamic simula-tion is performed based on the coupled dynamics derived inthe previous sections
51 LQR and Optimal PI Based Controllers Design Thedynamics for solar sail can bewritten as follows togetherwithits quadratic cost function also defined as
x = Ax + Bu x (1199050) = x
1199050
(known)
119869 =1
2int
infin
1199050
[x119879 (119905)Qx (119905) + u119879 (119905)Ru (119905)] 119889119905
(66)
whereQ = Q119879
⩾ 0 andR = R119879
gt 0 are constantThe control-lability of [AB] and the observability of [AD] can beensured when the equationDD119879
= Q holds for anymatrixDThe optimal control input ulowast(119905)within the scope of u(119905) isin R119903119905 isin [119905
0infin] can be computed as follows to make 119869minimum
ulowast (119905) = minusKxlowast (119905) K = Rminus1B119879P (67)
where P is the nonnegative definite symmetric solution of thefollowing Riccati algebraic equations
PA + A119879P minus PBRminus1B119879P +Q = 0 (68)
And the optimal performance index can be obtained asfollows for arbitrary initial states
119869lowast
[x (1199050) 119905
0] =
1
2x1198790
Px0 (69)
The closed-loop system
x = (A minus BRminus1B119879P) x (70)
is asymptotically stableFor an orbiting solar sail the primary disturbance torque
is by the cmcp offset and the impact of the tiny dust inthe deep space The state regulator can be used to controlthe dynamic system affected by pulse disturbance torquewith good steady-state errors but will never achieve accuratesteady-state errors if the dynamics is affected by constantdisturbance torque Thus the optimal state regulator withan integrator to eliminate the constant disturbance torqueshould be presented This optimal proportional-integral reg-ulator not only eliminates the constant disturbance torque butalso possesses the property of optimal regulator
Table 1 The related parameters
Parameters ValuesCMCP offsetm [0 017678 017678]119879
The side length of square sailm 100Nominal solar-radiation pressureconstant at 1 AU from the sunNm2 4563 times 10minus6
Solar-radiation pressure forceN 912 times 10minus2
Roll inertiakglowastm2 50383Pitch and yaw inertiakglowastm2 251915Outer radiusm 0229Thickness of the supporting beamm 75 times 10minus6
Youngrsquos modulus of the supportingbeamGPa 124
Moment of inertia of the cross-sectionof the supporting beamm4 2829412 times 10minus7
Bending stiffness of the supportingbeamNlowastm2 3508471336
Proportional damping coefficient ofsupporting beams 001
Line density of the supportingbeamkgm 0106879
Cross-sectional area of the supportingbeamm2 1079 times 10minus5
Roll disturbance torqueNlowastm 0Pitch (yaw) disturbance torqueNlowastm 0016122 (minus0016122)
For the following linear system with the correspondingperformance index
x = Ax + Bu x (1199050) = x
1199050
u (1199050) = u
1199050
119869 =1
2int
infin
1199050
(x119879Qx + u119879Ru + u119879Su) 119889119905(71)
where Q = Q119879
⩾ 0 R = R119879
gt 0 and S = S119879 gt 0 If [AB]is completely controllable and meanwhile [AD
11] is com-
pletely observable with the relationship D11D119879
11
= Q thesolution can be expressed as
ulowast = minusK1x minus K
2ulowast ulowast (119905
0) = u
1199050
(72)
If B119879B is full rank we can get
ulowast = minusK3x minus K
4x ulowast (119905
0) = u
1199050
(73)
K119894(119894 = 1 2 3 4) is the function of ABQR S
The closed-loop system
[xulowast] = [
A BminusK
1minusK
2
] [xulowast] [
[
x (1199050)
u (1199050)]
]
= [x1199050
u1199050
] (74)
is asymptotically stableThe compromise between the state variables (the angle
angular velocity the vibration displacement and velocity)and control inputs (the torque by all the actuators) can
16 Mathematical Problems in Engineering
0 2000 4000 6000
0 2000 4000 6000
0 2000 4000 6000minus5
0
5
minus5
0
5
minus5
0
5
minus4
minus2
0
2
4
times10minus4
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
00162
00164
00166
4800 4900 5000
4800 4900 5000
4800 4900 5000
minus00165
minus0016
Time (s) Time (s)
Time (s)
Time (s)
Time (s)
Time (s)
Roll
erro
r120593(∘
)
Roll
erro
r120593(∘
)
Pitc
h er
ror120579
(∘)
Pitc
h er
ror120579
(∘)
Yaw
erro
r120595(∘
)
Yaw
erro
r120595(∘
)
Figure 8 The roll pitch and yaw errors
be achieved by using both the LQR based and optimal PIbased controllers for the coupled attitudevibration dynamicsystem The fact is that the attitude control ability is limitedto the control torque by the control actuators The change ofthe attitude angles and rates should not be frequent to voidexciting vibrations
Thus the weighting matrix Q and the control weightingmatrix R are selected as follows for LQR based controller
Q (1 1) = 9 times 10minus6
Q (2 2) = 1 times 10minus6
Q (3 3) = 16 times 10minus6
Q (4 4) = Q (5 5) = Q (6 6) = Q (7 7) = Q (8 8)
= Q (9 9) = Q (10 10) = 1 times 10minus6
Q (119894 119895) = 0 (119894 = 119895 119894 119895 = 1 sim 10)
R (1 1) = R (2 2) = 900 R (3 3) = 100
R (4 4) = R (5 5) = 10000
R119894119895
= 0 (119894 = 119895 119894 119895 = 1 sim 5)
(75)
TheweightingmatrixQ and the control weightingmatrixR are selected as follows for the optimal PI based controller
Q (1 1) = Q (2 2) = 4 times 10minus8
Q (3 3) = Q (4 4) = Q (5 5) = Q (6 6) = Q (7 7)
= Q (8 8) = 16 times 10minus8
Mathematical Problems in Engineering 17
minus02
0
02
Roll
rate
(∘s)
Roll
rate
(∘s)
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Pitc
h ra
te(∘s)
Pitc
h ra
te(∘s)
0 1000 2000 3000 4000 5000
minus05
0
05
minus05
0
05
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
Time (s)
Yaw
rate
(∘
s)
Yaw
rate
(∘
s)
4800 4850 4900 4950 5000
Time (s)4800 4850 4900 4950 5000
Time (s)4800 4850 4900 4950 5000
minus2
0
2
minus2
0
2
minus2
0
2
times10minus4
times10minus4
times10minus4
Figure 9 The roll pitch and yaw rates
Q (9 9) = Q (10 10) = 1 times 10minus8
Q (119894 119895) = 0 (119894 = 119895 119894 119895 = 1 sim 10)
R (1 1) = R (2 2) = R (3 3) = 1 times 10minus8
R (4 4) = R (5 5) = 4 times 10minus8
R (119894 119895) = 0 (119894 = 119895 119894 119895 = 1 sim 5)
(76)
52 The Simulation Results The initial angle errors of rollpitch and yaw are adopted as 120593(119905
0) = 3
∘ 120579(1199050) = 3
∘ and120595(119905
0) = 3
∘ the initial angular velocity errors of roll pitchand yaw are adopted as (119905
0) = 0
∘
s 120579(1199050) = 0
∘
s and(119905
0) = 0
∘
s 1198811(1199050) = 01m 119881
2(1199050) = 01m
1(1199050) = 0ms
and 2(1199050) = 0ms are adopted in this paper for dynamic
simulationThe estimated cmcp offset is 025m for a 100 times 100m
square solar sail It is assumed that the components of cmcpoffset vector are [0 017678 017678]
119879 in the body frame
The relevant parameters for dynamic simulations are givenin Table 1
The dynamic simulation results are obtained as followsby using the LQR controller based on the abovementionedQ and R related parameters and initial conditions Thedynamics simulations with (denoted by ldquowith GFrdquo) andwithout (denoted by ldquowithout GFrdquo) considering the geo-metrical nonlinearity are presented And the correspondingdiscussions and analysis are also given according to thecalculated results
The roll pitch and yaw errors are presented based onthe dynamics models with and without considering thegeometrical nonlinearityThe control effect with zero steady-state error can be achieved for roll axis by referring tothe results But the steady-state errors exist for pitch andyaw axes from Figure 8 this is because there exist constantdisturbance torques for pitch and yaw axes caused by thecmcp offset Thus the LQR based controller cannot be usedfor attitude control with good steady-state performance Thesteady-state errors of pitch and yaw axes are about 0164
∘
and minus0164∘ respectively from the corresponding partial
enlarged drawing of the figures (see the corresponding left
18 Mathematical Problems in Engineering
minus20
0
20
Roll
torq
ue (N
lowastm
)
Roll
torq
ue (N
lowastm
)
minus50
0
50
minus50
0
50
Pitc
h to
rque
(Nlowast
m)
Pitc
h to
rque
(Nlowast
m)
0 1000 2000 3000 4000 5000
0 2000 4000 6000
0 2000 4000 6000
Yaw
torq
ue (N
lowastm
)
Yaw
torq
ue (N
lowastm
)
minus002
0
002
008
01
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
minus01
minus009
minus008
Time (s)Time (s)
Time (s)Time (s)
Time (s)Time (s)
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Figure 10 The roll pitch and yaw torques
figures) A simple and practical controller should be designedto eliminate the steady-state errorsThese errorswill affect theprecision of the super long duration space mission deeply
The differences between the dynamics with and withoutthe geometrical nonlinearity effect can be observed Theamplitudes and phases change a bit by comparing the corre-sponding results
It can be observed by the partial enlarged figures(the right figures of Figure 9) that there are no steady-stateerrors for roll pitch and yaw rates The relative satisfieddynamic performance is achieved In fact a result with muchmore satisfied dynamic performance can be obtained but itwill make the desired control torques much larger duringthe initial period This will not only excite the vibration ofthe structure but also increase the burden of the controlactuators
And the differences between the dynamics models withand without the geometrical nonlinearity can also be seenmerely in the phase of the angular velocities
The desired attitude control torques are presented inFigure 10 The roll torque will tend to be zero with thedecrement of the state variable errors The pitch and yawtorques tend to be constant from the middle and bottom
figures The pitch and yaw steady-state errors can never beeliminated although the pitch and yaw torques (009Nlowastmand minus009Nlowastm) are applied continuously by theoreticalanalysis and simulations This is just a great disadvantage ofthe LQR based controller in this paper The initial controltorques can be afforded by vibrating the gimbaled controlboom andmoving the slidingmasses that can afford a relativelarge torque The control vanes can be used to afford thecontrol torques when solar sail is in steady-state process Theexpression of the attitude control inputs 119906
120593 119906
120579 and 119906
120595can be
found in previous sectionMoreover the differences between dynamics responses
with and without geometrical nonlinearity can also beobserved by comparing the corresponding results Therequired torques for the attitude control are a little largerfor the dynamics with geometrical nonlinearity And thedifference in the phase is also clear
It can be seen that the vibration of the supporting beamis depressed effectively by the simulation results in Figure 11It can be seen that the steady-state errors and the dynamicperformance are relatively satisfied It can also be seen that thedynamics responses between the model with and without the
Mathematical Problems in Engineering 19
0 1000 2000 3000 4000 5000
0 1000 2000 3000 4000 5000
minus01
0
01
minus02
0
02
Time (s) Time (s)
Time (s) Time (s)
minus5
0
5
times10minus4
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
minus1
0
1
times10minus3
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
The d
ispla
cem
ent o
f the
tip
(m)
The d
ispla
cem
ent o
f the
tip
(m)
The v
eloci
ty o
f the
tip
(ms
)
The v
eloc
ity o
f the
tip
(ms
)
Figure 11 The displacement and velocity of the tip of the supporting beam
geometrical nonlinearity effect are different in the vibrationdisplacement and velocitymagnitudes and phases (Figure 15)
The simulation results can be obtained as follows by usingthe optimal PI based controller adopting the abovementionedparameters and initial conditions
The roll pitch and yaw errors are given by using theoptimal PI based controller These errors tend to disappearby observing the partially enlarged plotting of the figure (thecorresponding right figures) (shown in Figure 12) And therelative satisfied dynamic performance can also be obtainedFrom the view of eliminating the steady-state errors the opti-mal PI based controller performs better than the LQR basedcontroller by theoretical analysis and simulation results Theformer can achieve attitude control results without pitchand yaw steady-state errors From the view of dynamicperformance both the controllers perform well In additionit can be seen that the difference between the modelswith and without geometrical nonlinearity is merely inthe phase
The roll pitch and yaw rate errors are presented inFigure 13 The dynamic and steady-state performances aresatisfied by observing the simulation results And by observ-ing the difference between the dynamics responses with and
without the influence by the geometrical nonlinearity it canbe concluded that the merely difference is the phase
The desired control torques of the roll pitch and yaw areobtained in Figure 14 by using the optimal PI based controllerIt can be seen that the value of the desired roll control torquedecreases to zero as the values of the roll angle and ratedecrease to zero The desired pitch and yaw control torquestend to be the constant values 009Nlowastm and minus009Nlowastmrespectively The desired initial control torques are large byobserving Figure 14 It is suggested that the gimbaled controlboom combining the sliding masses is adopted to afford theinitial torque Then the control vanes can be used to controlthe solar sail after the initial phase The phase differencecan also be observed by inspecting the dynamics responsesduring the 4800sim5000 s period
The vibration can be controlled effectively based on theoptimal PI controller And the relative satisfied dynamicand steady-state performances can be achieved In additionthe tiny differences exist in the magnitudes of the requiredtorques And the phase differences also exist
It can be concluded as follows by analyzing and compar-ing the simulation results based on the LQR and optimal PItheories in detail
20 Mathematical Problems in Engineering
Roll
erro
r120593(∘
)
Roll
erro
r120593(∘
)
minus5
0
5
minus5
0
5
Pitc
h er
ror120579
(∘)
Pitc
h er
ror120579
(∘)
0 1000 2000 3000 4000 5000minus10
0
10
Time (s) Time (s)
Time (s)
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
Yaw
erro
r120595(∘
)
Yaw
erro
r120595(∘
)
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
minus1
0
1
times10minus3
minus1
0
1
times10minus3
minus1
0
1
times10minus3
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Figure 12 The roll pitch and yaw errors
(1) From the view of eliminating the steady-state errorsof the pitch and yaw errors the optimal PI based con-troller performs better than the LQR based controllerby theoretical analysis and simulation results Thedynamic performances of the two controllers are bothsatisfied and the desired control torques are relativelysmall
(2) The weighting of the state variables is reflected by theweighting matrix according to the LQR and optimalPI theories The constant weighting matrices selectedin this paper can effectively reflect the initial statevariable errors but maybe reflect the final state vari-able errors deficiently The time-varying weightingmatrices should be selected
(3) For the actual orbiting solar sail the control actuators(control vanes gimbaled control boom and slidingmasses) cannot afford excessive large control torquesThus the control torques should be as small as possibleon the premise of acquiring satisfied dynamic perfor-mance and steady-state errors It will not only reducethe burden of the control actuators but also avoid
exciting structural vibration In engineering practicethe weighting matrices and the control weightingmatrices should be selected based on the attitudecontrol requirement (eg dynamic performance andsteady-state errors etc)
(4) The dynamics responses influenced by the geometri-cal nonlinearity can be observed In a word the tinydifferences between the magnitudes of the physicalvariables exist for the models with and withoutthe geometrical nonlinearity And the relative cleardifferences exist in the phases for the attitude anglesrates required torques and so forth
6 Conclusions
The coupled attitude and structural dynamics is establishedfor the highly flexible sailcraft by using the von-Karman von-Karmanrsquos nonlinear strain-displacement relationships basedon assumptions of large deflections moderate rotationsand
Mathematical Problems in Engineering 21
Roll
rate
erro
r(∘ s
)
Roll
rate
erro
r(∘ s
)
minus01
0
01
minus01
0
01
Pitc
h ra
te er
ror (
∘ s)
Pitc
h ra
te er
ror (
∘ s)
0 1000 2000 3000 4000 5000minus02
0
02
Yaw
rate
erro
r (∘ s
)
Yaw
rate
erro
r (∘ s
)
4800 4850 4900 4950 5000
minus5
0
5times10minus4
minus5
0
5
times10minus4
minus5
0
5times10minus4
Time (s)
4800 4850 4900 4950 5000
Time (s)
4800 4850 4900 4950 5000
Time (s)
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Figure 13 The roll pitch and yaw rate errors
small strains The Lagrange equation method is utilizedto derive the dynamics for controller design and dynamicsimulation The LQR and optimal PI based controllers aredesigned for the dynamics with the constant disturbancetorque caused by the cmcp offset By theoretical analysisand simulation it can be seen that both controllers cancompromise between the state variables and control inputsBecause the control actuators can hardly afford large controltorque the dynamic performance should be relaxed toreduce the requirement for the attitude control actuatorsBesides the optimal PI based controller can also eliminatethe constant disturbance torque caused by the cmcp offsetthat always exists while the LQR based controller fails toachieve the results with satisfied steady-state performancealthough the attitude control torque is always applied to thecoupled dynamic systemThe dynamics simulations with andwithout the geometrical nonlinearity effect are also carriedout And the differences between the models in magnitudesand phases are identified and analyzed It can be concludedthat the optimal PI based controller performs better than the
LQRbased controller from the viewof eliminating the steady-state error caused by the disturbance torque by the cmcpoffset
Appendix
The related parameters in above equation are given as
119886120593= 119869
119909+ 119898
ℎ11199102
ℎ1
+ 119898ℎ21199112
ℎ2
+ 1198981199011199032
119901119911
+ 1198981199011199032
119901119910
119886120579= minus 119898
119901119903119901119909119903119901119910 119886
120595= minus119898
119901119903119901119909119903119901119911
1198861198811
= minus 1198981198971198972
1198861198812
= minus4
5119898
1198971198972
119887120579= 119869
119910+ 119898
ℎ21199112
ℎ2
+ 1198981199011199032
119901119911
+ 1198981199011199032
119901119909
119887120595= minus 119898
119901119903119901119910119903119901119911 119887
120593= minus119898
119901119903119901119909119903119901119910
22 Mathematical Problems in Engineering
Roll
torq
ue (N
lowastm
)
Roll
torq
ue (N
lowastm
)
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
0 2000 4000 6000
0 2000 4000 6000
0 2000 4000 6000
Time (s)
Time (s)
Time (s)
Time (s)
Time (s)
Time (s)4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
minus01
minus008
008
009
01
minus002
0
002
minus5
0
5
minus2
0
2
Pitc
h to
rque
(Nlowast
m)
Pitc
h to
rque
(Nlowast
m)
minus2
0
2
Yaw
torq
ue (N
lowastm
)
Yaw
torq
ue (N
lowastm
)
Figure 14 The roll pitch and yaw torques
1198871198811
=1
2119898
1198971198972
1198871198812
=2
5119898
1198971198972
119888120595= 119869
119911+ 119898
ℎ11199102
ℎ1
+ 1198981199011199032
119901119910
+ 1198981199011199032
119901119909
119888120579= minus 119898
119901119903119901119910119903119901119911 119888
120593= minus119898
119901119903119901119909119903119901119911
1198881198811
= minus1
21198972
119898119897 119888
1198812
= minus2
51198972
119898119897
119889
1198811
= (4
3
119868119863
119897+
1
5119897119868119860) 119889
1198812
= (1
6119897119868119860+
3119868119863
2119897)
119889
1198811
=4120578
119887119863
119909119909
1198973 119889
1198812
=6120578
119887119863
119909119909
1198973
1198891198811
=4119863
119909119909
1198973 119889
1198812
=6119863
119909119909
1198973
1198761198811
= 1198651198621
(119905)
119890
1198811
= (3
2
119868119863
119897+
1
6119897119868119860)
119890
1198812
= (1
7119897119868119860+
9
5
119868119863
119897) 119890
1198811
=6120578
119887119863
119909119909
1198973
119890
1198812
=12120578
119887119863
119909119909
1198973 119890
1198811
=6119863
119909119909
1198973
1198901198812
=12119863
119909119909
1198973 119876
1198812
= 1198651198622
(119905)
(A1)
The detailed expressions of control inputs for attitudevibration and related parameters in the state-space model ofthe dynamics (see (62) and (63)) are presented as follows
A =
[[[[[[[[[[[[[[
[
0 1 0 0 0 0 0 0 0 0
0 0 0 0 0 0 1198861
1198862
1198863
1198864
0 0 0 1 0 0 0 0 0 0
0 0 0 0 0 0 1198865
1198866
1198867
1198868
0 0 0 0 0 1 0 0 0 0
0 0 0 0 0 0 1198869
11988610
11988611
11988612
0 0 0 0 0 0 0 1 0 0
0 0 0 0 0 0 11988613
11988614
11988615
11988616
0 0 0 0 0 0 0 0 0 1
0 0 0 0 0 0 11988617
11988618
11988619
11988620
]]]]]]]]]]]]]]
]
Mathematical Problems in Engineering 23
0 1000 2000 3000 4000 5000
0 1000 2000 3000 4000 5000
minus01
0
01
minus02
0
02
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Time (s)
Time (s)Time (s)
Time (s)
minus1
0
1
minus1
0
1
times10minus3
times10minus3Th
e disp
lace
men
t of t
he ti
p (m
)
The d
ispla
cem
ent o
f the
tip
(m)
The v
eloci
ty o
f the
tip
(ms
)
The v
eloci
ty o
f the
tip
(ms
)
Figure 15 Vibration displacement and velocity of the tip
B =
[[[[[[[[[[[[[[
[
0 0 0 0 0
1 0 0 0 0
0 0 0 0 0
0 1 0 0 0
0 0 0 0 0
0 0 1 0 0
0 0 0 0 0
0 0 0 1 0
0 0 0 0 0
0 0 0 0 1
]]]]]]]]]]]]]]
]
1198861= minus
1198981198971198972
119869119909
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus4
5119869119909
1198981198971198972
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198862= minus
1198981198971198972
119869119909
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus4
5119869119909
1198981198971198972
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198863= minus
1198981198971198972
119869119909
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus4
5119869119909
1198981198971198972
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198864= minus
1198981198971198972
119869119909
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus4
5119869119909
1198981198971198972
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
119906120593=
119876120593
119869119909
+
119906
119869119909
+119898
1198971198972
119869119909
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+4
5119869119909
1198981198971198972
+
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198865=
1
2119869119910
1198981198971198972
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+2
5119869119910
1198981198971198972
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198866=
1
2119869119910
1198981198971198972
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+2
5119869119910
1198981198971198972
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198867=
1
2119869119910
1198981198971198972
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+2
5119869119910
1198981198971198972
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198868=
1
2119869119910
1198981198971198972
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
24 Mathematical Problems in Engineering
+2
5119869119910
1198981198971198972
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
119906120579=
119876120579
119869119910
+119906
120579
119869119910
minus1
2119869119910
1198981198971198972
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119910
1198981198971198972
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198869= minus
1
2119869119911
1198972
119898119897
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988610
= minus1
2119869119911
1198972
119898119897
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988611
= minus1
2119869119911
1198972
119898119897
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988612
= minus1
2119869119911
1198972
119898119897
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
119906120595=
119876120595
119869119911
+
119906
119869119911
+1
2119869119911
1198972
119898119897
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+2
5119869119911
1198972
119898119897
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988613
= minus
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988614
= minus
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988615
= minus
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988616
= minus
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
1199061198811
=
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988617
= minus
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988618
= minus
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988619
= minus
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988620
= minus
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1199061198812
=
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(A2)
Conflict of Interests
The authors declare that there is no conflict of interestsregarding the publication of this paper
Acknowledgments
The authors would like to thank the anonymous reviewers fortheir critical and constructive review of the paper This studywas cosupported by the National Natural Science Foundationof China (Project no 11302134 11272101)
References
[1] M Colin Solar Sailing Technology Dynamics and MissionApplications Springer-Praxis London UK 1st edition 1999
[2] V Lappas SWokesM Leipold A Lyngvi and P Falkner ldquoGui-dance and control for an Interstellar Heliopause Probe (IHP)solar sail mission to 200 AUrdquo in Proceedings of the AIAAGuidance Navigation and Control Conference and Exhibit pp2472ndash2492 San Francisco Calif USA August 2005
[3] L Charlotte C Camilla and C McInnes ldquoSolar radiation pres-sure augmented deorbiting fromhigh altitude sun-synchronousorbitsrdquo in Proceedings of the 4S Symposium 2012 Small SatellitesSystems and Services Portoroz Slovenia 2012
[4] M Ceriotti and C RMcInnes ldquoGeneration of optimal trajecto-ries for Earth hybrid pole sittersrdquo Journal of Guidance Controland Dynamics vol 34 no 3 pp 847ndash859 2011
[5] S Gong J Li andH Baoyin ldquoSolar sail transfer trajectory fromL1 point to sub-L1 pointrdquoAerospace Science and Technology vol15 no 7 pp 544ndash554 2011
[6] S Gong J Li and H Baoyin ldquoAnalysis of displaced solar sailorbits with passive controlrdquo Journal of Guidance Control andDynamics vol 31 no 3 pp 782ndash785 2008
[7] S Gong H Baoyin and J Li ldquoSolar sail three-body transfertrajectory designrdquo Journal of Guidance Control and Dynamicsvol 33 no 3 pp 873ndash886 2010
Mathematical Problems in Engineering 25
[8] S Gong J Li H Baoyin and J Simo ldquoA new solar sail orbitrdquoScience China Technological Sciences vol 55 no 3 pp 848ndash8552012
[9] Y Tsuda O Mori R Funase et al ldquoAchievement of IKAROS-Japanese deep space solar sail demonstration missionrdquo ActaAstronautica vol 82 no 2 pp 183ndash188 2013
[10] L Johnson MWhorton A Heaton R Pinson G Laue and CAdams ldquoNanoSail-D a solar sail demonstration missionrdquo ActaAstronautica vol 68 no 5-6 pp 571ndash575 2011
[11] B Wie and D Murphy ldquoSolar-sail attitude control design for asail flight validation missionrdquo Journal of Spacecraft and Rocketsvol 44 no 4 pp 809ndash821 2007
[12] B Wie D Murphy M Paluszek and S Thomas ldquoRobust atti-tude control systems design for solar sails part 1 propellantlessprimaryACSrdquo inProceedings of the AIAAGuidance Navigationand Control Conference and Exhibit Providence RI USAAugust 2004
[13] B Wie D Murphy M Paluszek and S Thomas ldquoRobust atti-tude control systems design for solar sails part 2 MicroPPT-based secondary ACSrdquo in Proceedings of the AIAA GuidanceNavigation and Control Conference and Exhibit pp 1325ndash1340Providence RI USA August 2004
[14] S Thomas M Paluszek B Wie and D Murphy ldquoAOCS per-formance and stability validation for large flexible solar sailspacecraftrdquo in Proceedings of the 41st AIAAASMESAEASEEJoint Propulsion Conference amp Exhibit Tucson Ariz USA 2005
[15] B Wie ldquoDynamic modeling and attitude control of solar sailspacecraft part Irdquo in Proceedings of the AIAAGuidance Naviga-tion and Control Conference and Exhibit Monterey Calif USAAugust 2002
[16] BWie ldquoSolar sail attitude control and dynamics part 1rdquo Journalof Guidance Control and Dynamics vol 27 no 4 pp 526ndash5352004
[17] B Wie ldquoDynamic modeling and attitude control of solar sailspacecraft part IIrdquo in Proceedings of the AIAA Guidance Nav-igation and Control Conference and Exhibit Monterey CalifUSA August 2002
[18] BWie ldquoSolar sail attitude control and dynamics part 2rdquo Journalof Guidance Control and Dynamics vol 27 no 4 pp 536ndash5442004
[19] C Luo and J-H Zheng ldquoSolar-sail attitude control based onmoving masses and roll stabilizer barsrdquo Journal of HarbinInstitute of Technology vol 43 no 3 pp 95ndash101 2011
[20] D Romagnoli and T Oehlschlagel ldquoHigh performance twodegrees of freedom attitude control for solar sailsrdquo Advances inSpace Research vol 48 no 11 pp 1869ndash1879 2011
[21] C Scholz D Romagnoli B Dachwald and S Theil ldquoPerfor-mance analysis of an attitude control system for solar sails usingsliding massesrdquo Advances in Space Research vol 48 no 11 pp1822ndash1835 2011
[22] A Bolle and C Circi ldquoSolar sail attitude control through in-plane moving massesrdquo Journal of Aerospace Engineering vol222 no 1 pp 81ndash94 2008
[23] M RotunnoM Basso A B Pome andM Sallusti ldquoA compari-son of robust attitude control techniques for a solar sail space-craftrdquo in Proceedings of the AIAA Guidance Navigation andControl Conference and Exhibit San Francisco Calif USA2005
[24] J Zhang K Zhai and T Wang ldquoControl of large angle maneu-vers for the flexible solar sailrdquo Science China Physics Mechanicsand Astronomy vol 54 no 4 pp 770ndash776 2011
[25] J Zhang andTWang ldquoCoupled attitude-orbit control of flexiblesolar sail for displaced solar orbitrdquo Journal of Spacecraft andRockets vol 50 no 3 pp 675ndash685 2013
[26] Q Li XMa and TWang ldquoReducedmodel for flexible solar saildynamicsrdquo Journal of Spacecraft and Rockets vol 48 no 3 pp446ndash453 2011
[27] M Polites J Kalmanson and D Mangus ldquoSolar sail attitudecontrol using small reaction wheels and magnetic torquersrdquoProceedings of the Institution of Mechanical Engineers G Journalof Aerospace Engineering vol 222 no 1 pp 53ndash62 2008
[28] H-T Cui J-H Luo J-H Feng and P-Y Cui ldquoAttitudecontrol of solar sail spacecraft with control boomrdquo Journal ofAstronautics vol 29 no 2 pp 560ndash566 2008
[29] E Mettler and S R Ploen ldquoSolar sail dynamics and controlusing a boom mounted bus articulated by a bi-state two-axisgimbal and reaction wheelsrdquo in Proceedings of the AIAAAASAstrodynamics Specialist Conference and Exhibit MontereyCalif USA August 2002
[30] J Luo X Li and J Feng ldquoPassive attitude control of solar sailspacecraftrdquo Flight Dynamics vol 26 no 5 pp 47ndash50 2008
[31] J Luo Study on attitude control of solar sail spaceraft [PhDthesis] School of Astronautics Harbin Institute of TechnologyHarbin China 2007
[32] D A Lawrence and S W Piggott ldquoIntegrated trajectory andattitude control for a four-vane solar sailrdquo in Proceedings ofthe AIAA Guidance Navigation and Control Conference andExhibit pp 2416ndash2431 San Francisco Calif USA August 2005
[33] E Mettler A B Acikmese and S R Ploen ldquoAttitude dynamicsand control of solar sails with articulated vanesrdquo in Proceedingsof the AIAA Guidance Navigation and Control Conference andExhibit pp 2396ndash2415 San Francisco Calif USA August 2005
[34] S N Adeli V J Lappas and B Wie ldquoA scalable bus-basedattitude control system for Solar Sailsrdquo Advances in SpaceResearch vol 48 no 11 pp 1836ndash1847 2011
[35] R Funase Y Shirasawa Y Mimasu et al ldquoOn-orbit verificationof fuel-free attitude control system for spinning solar sailutilizing solar radiation pressurerdquo Advances in Space Researchvol 48 no 11 pp 1740ndash1746 2011
[36] B Fu and F O Eke ldquoAttitude control methodology for largesolar sailsrdquo in AIAA Guidance Navigation and Control (GNC)Conference 2013
[37] J Liu N Cui F Shen and S Rong ldquoDynamics of highly-flexiblesolar sail subjected to various forcesrdquoActaAstronautica vol 103pp 55ndash72 2014
[38] J F Liu S Y Rong and J G Li ldquoAttitude dynamics modelingand control of large flexible solar sail spacecraftrdquo in Proceedingsof the 3rd International Symposium on Systems and Control inAeronautics and Astronautics (ISSCAA rsquo10) pp 243ndash247 IEEEPublications Piscataway NJ USA 2010
[39] S Gong H Baoyin and J Li ldquoCoupled attitude-orbit dynamicsand control for displaced solar orbitsrdquo Acta Astronautica vol65 no 5-6 pp 730ndash737 2009
Submit your manuscripts athttpwwwhindawicom
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
MathematicsJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Mathematical Problems in Engineering
Hindawi Publishing Corporationhttpwwwhindawicom
Differential EquationsInternational Journal of
Volume 2014
Applied MathematicsJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Probability and StatisticsHindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Journal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Mathematical PhysicsAdvances in
Complex AnalysisJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
OptimizationJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
CombinatoricsHindawi Publishing Corporationhttpwwwhindawicom Volume 2014
International Journal of
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Operations ResearchAdvances in
Journal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Function Spaces
Abstract and Applied AnalysisHindawi Publishing Corporationhttpwwwhindawicom Volume 2014
International Journal of Mathematics and Mathematical Sciences
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
The Scientific World JournalHindawi Publishing Corporation httpwwwhindawicom Volume 2014
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Algebra
Discrete Dynamics in Nature and Society
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Decision SciencesAdvances in
Discrete MathematicsJournal of
Hindawi Publishing Corporationhttpwwwhindawicom
Volume 2014 Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Stochastic AnalysisInternational Journal of
14 Mathematical Problems in Engineering
1
61198971198681198601+
3
2
1198681198631
119897+
1
71198971198681198602+
9
5
1198681198632
119897+
6120578119887119863
1199091199091
1198973
+12120578
119887119863
1199091199092
1198973+
61198631199091199091198811
1198973+
121198631199091199091198812
1198973= 119865
1198622
(119905)
(58)
43 The Rigid-Flexible Coupled Dynamics The simplifiedattitude and vibration dynamics can be written as
119886120593 + 119886
120579
120579 + 119886120595 + 119886
1198811
1+ 119886
1198812
2= 119876
120593
119887120579
120579 + 119887120595 + 119887
120593 + 119887
1198811
1+ 119887
1198812
2= 119876
120579
119888120595 + 119888
120579
120579 + 119888120593 + 119888
1198811
1+ 119888
1198812
2= 119876
120595
119889
1198811
1+ 119889
1198812
2+ 119889
1198811
1+ 119889
1198812
2+ 119889
1198811
1198811
+ 1198891198812
1198812= 119876
1198811
119890
1198811
1+ 119890
1198812
2+ 119890
1198811
1+ 119890
1198812
2+ 119890
1198811
1198811
+ 1198901198812
1198812= 119876
1198812
(59)
The related coefficients in the preceding equation can befound in (A1) in the appendix The dynamics (see (59)) isnot suitable for attitude controller design because the controlinputs exist in some coefficients of the angular accelerationsThis will make the controller design rather difficult Thusthe following dynamic model is obtained by putting theterms including the control inputs right side of the dynamicequations
119869119909 minus 119898
1198971198972
1minus
4
5119898
1198971198972
2= 119876
120593+ 119906
119869119910
120579 +2
5119898
1198971198972
2+
1
2119898
1198971198972
1= 119876
120579+ 119906
120579
119869119911 minus
1
21198972
1198981198971minus
2
51198972
1198981198972= 119876
120595+ 119906
119889
1198811
1+ 119889
1198812
2+ 119889
1198811
1+ 119889
1198812
2
+ 1198891198811
1198811+ 119889
1198812
1198812= 119876
1198811
119890
1198811
1+ 119890
1198812
2+ 119890
1198811
1+ 119890
1198812
2
+ 1198901198811
1198811+ 119890
1198812
1198812= 119876
1198812
(60)
The expressions for 119906 119906
120579
and 119906are as
119906= minus119898
ℎ11199102
ℎ1
minus 119898ℎ21199112
ℎ2
+ 119898119901119903119901119909119903119901119911 minus 119898
1199011199032
119901119911
minus 1198981199011199032
119901119910
+ 119898119901119903119901119909119903119901119910
120579
119906
120579
= minus119898ℎ21199112
ℎ2
120579 minus 1198981199011199032
119901119911
120579 + 119898119901119903119901119910119903119901119911 + 119898
119901119903119901119909119903119901119910
minus 1198981199011199032
119901119909
120579
119906= minus119898
ℎ11199102
ℎ1
+ 119898119901119903119901119910119903119901119911
120579 minus 1198981199011199032
119901119910
minus 1198981199011199032
119901119909
+ 119898119901119903119901119909119903119901119911
(61)
119906 119906
120579
and 119906are the functions of the positions of sliding
masses and payload and the angular accelerations The statevariables in (60) are defined as
1199091= 120593 119909
2= 119909
3= 120579 119909
4= 120579
1199095= 120595 119909
6= 119909
7= 119881
1
1199098=
1 119909
9= 119881
2 119909
10=
2
(62)
Thedynamics (60) can bewritten as the state-spacemodelas following
1= 119909
2
2= 119886
11199097+ 119886
21199098+ 119886
31199099+ 119886
411990910
+ 119906120593
3= 119909
4
4= 119886
51199097+ 119886
61199098+ 119886
71199099+ 119886
811990910
+ 119906120579
5= 119909
6
6= 119886
91199097+ 119886
101199098+ 119886
111199099+ 119886
1211990910
+ 119906120595
7= 119909
8
8= 119886
131199097+ 119886
141199098+ 119886
151199099+ 119886
1611990910
+ 1199061198811
9= 119909
10
10
= 119886171199097+ 119886
181199098+ 119886
191199099+ 119886
2011990910
+ 1199061198812
(63)
where 119906120579 119906
120593 and 119906
120595are the generalized control inputs
for attitude control and 1199061198811
and 1199061198812
are the generalizedcontrol inputs for vibration control The controllability canbe satisfied by analyzing (63) The attitudevibration controlinputs and the coefficients will be presented later in thissection The form of a matrix differential equation can bewritten as follows for the above equation
x = Ax + Bu (64)
The expressions of the relatedmatrices and vectors can befound as
x = [1
2
3
4
5
6
7
8
9
10]119879 x (119905
0) = x
1199050
u = [119906120593 119906
120579 119906
120595 119906
1198811
1199061198812
]119879
u (1199050) is known
(65)
where A xB and u are the system matrix state variablesvector control matrix and control inputs vector respectively
Mathematical Problems in Engineering 15
The complexity of the state-space model can be seen bypresenting the detailed expressions of control inputs forattitudevibration and related parameters in (A2) in theappendix
5 AttitudeVibration Control and Simulation
The controller for the attitude and vibration is developedusing the LQR and optimal PI theory The dynamic simula-tion is performed based on the coupled dynamics derived inthe previous sections
51 LQR and Optimal PI Based Controllers Design Thedynamics for solar sail can bewritten as follows togetherwithits quadratic cost function also defined as
x = Ax + Bu x (1199050) = x
1199050
(known)
119869 =1
2int
infin
1199050
[x119879 (119905)Qx (119905) + u119879 (119905)Ru (119905)] 119889119905
(66)
whereQ = Q119879
⩾ 0 andR = R119879
gt 0 are constantThe control-lability of [AB] and the observability of [AD] can beensured when the equationDD119879
= Q holds for anymatrixDThe optimal control input ulowast(119905)within the scope of u(119905) isin R119903119905 isin [119905
0infin] can be computed as follows to make 119869minimum
ulowast (119905) = minusKxlowast (119905) K = Rminus1B119879P (67)
where P is the nonnegative definite symmetric solution of thefollowing Riccati algebraic equations
PA + A119879P minus PBRminus1B119879P +Q = 0 (68)
And the optimal performance index can be obtained asfollows for arbitrary initial states
119869lowast
[x (1199050) 119905
0] =
1
2x1198790
Px0 (69)
The closed-loop system
x = (A minus BRminus1B119879P) x (70)
is asymptotically stableFor an orbiting solar sail the primary disturbance torque
is by the cmcp offset and the impact of the tiny dust inthe deep space The state regulator can be used to controlthe dynamic system affected by pulse disturbance torquewith good steady-state errors but will never achieve accuratesteady-state errors if the dynamics is affected by constantdisturbance torque Thus the optimal state regulator withan integrator to eliminate the constant disturbance torqueshould be presented This optimal proportional-integral reg-ulator not only eliminates the constant disturbance torque butalso possesses the property of optimal regulator
Table 1 The related parameters
Parameters ValuesCMCP offsetm [0 017678 017678]119879
The side length of square sailm 100Nominal solar-radiation pressureconstant at 1 AU from the sunNm2 4563 times 10minus6
Solar-radiation pressure forceN 912 times 10minus2
Roll inertiakglowastm2 50383Pitch and yaw inertiakglowastm2 251915Outer radiusm 0229Thickness of the supporting beamm 75 times 10minus6
Youngrsquos modulus of the supportingbeamGPa 124
Moment of inertia of the cross-sectionof the supporting beamm4 2829412 times 10minus7
Bending stiffness of the supportingbeamNlowastm2 3508471336
Proportional damping coefficient ofsupporting beams 001
Line density of the supportingbeamkgm 0106879
Cross-sectional area of the supportingbeamm2 1079 times 10minus5
Roll disturbance torqueNlowastm 0Pitch (yaw) disturbance torqueNlowastm 0016122 (minus0016122)
For the following linear system with the correspondingperformance index
x = Ax + Bu x (1199050) = x
1199050
u (1199050) = u
1199050
119869 =1
2int
infin
1199050
(x119879Qx + u119879Ru + u119879Su) 119889119905(71)
where Q = Q119879
⩾ 0 R = R119879
gt 0 and S = S119879 gt 0 If [AB]is completely controllable and meanwhile [AD
11] is com-
pletely observable with the relationship D11D119879
11
= Q thesolution can be expressed as
ulowast = minusK1x minus K
2ulowast ulowast (119905
0) = u
1199050
(72)
If B119879B is full rank we can get
ulowast = minusK3x minus K
4x ulowast (119905
0) = u
1199050
(73)
K119894(119894 = 1 2 3 4) is the function of ABQR S
The closed-loop system
[xulowast] = [
A BminusK
1minusK
2
] [xulowast] [
[
x (1199050)
u (1199050)]
]
= [x1199050
u1199050
] (74)
is asymptotically stableThe compromise between the state variables (the angle
angular velocity the vibration displacement and velocity)and control inputs (the torque by all the actuators) can
16 Mathematical Problems in Engineering
0 2000 4000 6000
0 2000 4000 6000
0 2000 4000 6000minus5
0
5
minus5
0
5
minus5
0
5
minus4
minus2
0
2
4
times10minus4
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
00162
00164
00166
4800 4900 5000
4800 4900 5000
4800 4900 5000
minus00165
minus0016
Time (s) Time (s)
Time (s)
Time (s)
Time (s)
Time (s)
Roll
erro
r120593(∘
)
Roll
erro
r120593(∘
)
Pitc
h er
ror120579
(∘)
Pitc
h er
ror120579
(∘)
Yaw
erro
r120595(∘
)
Yaw
erro
r120595(∘
)
Figure 8 The roll pitch and yaw errors
be achieved by using both the LQR based and optimal PIbased controllers for the coupled attitudevibration dynamicsystem The fact is that the attitude control ability is limitedto the control torque by the control actuators The change ofthe attitude angles and rates should not be frequent to voidexciting vibrations
Thus the weighting matrix Q and the control weightingmatrix R are selected as follows for LQR based controller
Q (1 1) = 9 times 10minus6
Q (2 2) = 1 times 10minus6
Q (3 3) = 16 times 10minus6
Q (4 4) = Q (5 5) = Q (6 6) = Q (7 7) = Q (8 8)
= Q (9 9) = Q (10 10) = 1 times 10minus6
Q (119894 119895) = 0 (119894 = 119895 119894 119895 = 1 sim 10)
R (1 1) = R (2 2) = 900 R (3 3) = 100
R (4 4) = R (5 5) = 10000
R119894119895
= 0 (119894 = 119895 119894 119895 = 1 sim 5)
(75)
TheweightingmatrixQ and the control weightingmatrixR are selected as follows for the optimal PI based controller
Q (1 1) = Q (2 2) = 4 times 10minus8
Q (3 3) = Q (4 4) = Q (5 5) = Q (6 6) = Q (7 7)
= Q (8 8) = 16 times 10minus8
Mathematical Problems in Engineering 17
minus02
0
02
Roll
rate
(∘s)
Roll
rate
(∘s)
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Pitc
h ra
te(∘s)
Pitc
h ra
te(∘s)
0 1000 2000 3000 4000 5000
minus05
0
05
minus05
0
05
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
Time (s)
Yaw
rate
(∘
s)
Yaw
rate
(∘
s)
4800 4850 4900 4950 5000
Time (s)4800 4850 4900 4950 5000
Time (s)4800 4850 4900 4950 5000
minus2
0
2
minus2
0
2
minus2
0
2
times10minus4
times10minus4
times10minus4
Figure 9 The roll pitch and yaw rates
Q (9 9) = Q (10 10) = 1 times 10minus8
Q (119894 119895) = 0 (119894 = 119895 119894 119895 = 1 sim 10)
R (1 1) = R (2 2) = R (3 3) = 1 times 10minus8
R (4 4) = R (5 5) = 4 times 10minus8
R (119894 119895) = 0 (119894 = 119895 119894 119895 = 1 sim 5)
(76)
52 The Simulation Results The initial angle errors of rollpitch and yaw are adopted as 120593(119905
0) = 3
∘ 120579(1199050) = 3
∘ and120595(119905
0) = 3
∘ the initial angular velocity errors of roll pitchand yaw are adopted as (119905
0) = 0
∘
s 120579(1199050) = 0
∘
s and(119905
0) = 0
∘
s 1198811(1199050) = 01m 119881
2(1199050) = 01m
1(1199050) = 0ms
and 2(1199050) = 0ms are adopted in this paper for dynamic
simulationThe estimated cmcp offset is 025m for a 100 times 100m
square solar sail It is assumed that the components of cmcpoffset vector are [0 017678 017678]
119879 in the body frame
The relevant parameters for dynamic simulations are givenin Table 1
The dynamic simulation results are obtained as followsby using the LQR controller based on the abovementionedQ and R related parameters and initial conditions Thedynamics simulations with (denoted by ldquowith GFrdquo) andwithout (denoted by ldquowithout GFrdquo) considering the geo-metrical nonlinearity are presented And the correspondingdiscussions and analysis are also given according to thecalculated results
The roll pitch and yaw errors are presented based onthe dynamics models with and without considering thegeometrical nonlinearityThe control effect with zero steady-state error can be achieved for roll axis by referring tothe results But the steady-state errors exist for pitch andyaw axes from Figure 8 this is because there exist constantdisturbance torques for pitch and yaw axes caused by thecmcp offset Thus the LQR based controller cannot be usedfor attitude control with good steady-state performance Thesteady-state errors of pitch and yaw axes are about 0164
∘
and minus0164∘ respectively from the corresponding partial
enlarged drawing of the figures (see the corresponding left
18 Mathematical Problems in Engineering
minus20
0
20
Roll
torq
ue (N
lowastm
)
Roll
torq
ue (N
lowastm
)
minus50
0
50
minus50
0
50
Pitc
h to
rque
(Nlowast
m)
Pitc
h to
rque
(Nlowast
m)
0 1000 2000 3000 4000 5000
0 2000 4000 6000
0 2000 4000 6000
Yaw
torq
ue (N
lowastm
)
Yaw
torq
ue (N
lowastm
)
minus002
0
002
008
01
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
minus01
minus009
minus008
Time (s)Time (s)
Time (s)Time (s)
Time (s)Time (s)
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Figure 10 The roll pitch and yaw torques
figures) A simple and practical controller should be designedto eliminate the steady-state errorsThese errorswill affect theprecision of the super long duration space mission deeply
The differences between the dynamics with and withoutthe geometrical nonlinearity effect can be observed Theamplitudes and phases change a bit by comparing the corre-sponding results
It can be observed by the partial enlarged figures(the right figures of Figure 9) that there are no steady-stateerrors for roll pitch and yaw rates The relative satisfieddynamic performance is achieved In fact a result with muchmore satisfied dynamic performance can be obtained but itwill make the desired control torques much larger duringthe initial period This will not only excite the vibration ofthe structure but also increase the burden of the controlactuators
And the differences between the dynamics models withand without the geometrical nonlinearity can also be seenmerely in the phase of the angular velocities
The desired attitude control torques are presented inFigure 10 The roll torque will tend to be zero with thedecrement of the state variable errors The pitch and yawtorques tend to be constant from the middle and bottom
figures The pitch and yaw steady-state errors can never beeliminated although the pitch and yaw torques (009Nlowastmand minus009Nlowastm) are applied continuously by theoreticalanalysis and simulations This is just a great disadvantage ofthe LQR based controller in this paper The initial controltorques can be afforded by vibrating the gimbaled controlboom andmoving the slidingmasses that can afford a relativelarge torque The control vanes can be used to afford thecontrol torques when solar sail is in steady-state process Theexpression of the attitude control inputs 119906
120593 119906
120579 and 119906
120595can be
found in previous sectionMoreover the differences between dynamics responses
with and without geometrical nonlinearity can also beobserved by comparing the corresponding results Therequired torques for the attitude control are a little largerfor the dynamics with geometrical nonlinearity And thedifference in the phase is also clear
It can be seen that the vibration of the supporting beamis depressed effectively by the simulation results in Figure 11It can be seen that the steady-state errors and the dynamicperformance are relatively satisfied It can also be seen that thedynamics responses between the model with and without the
Mathematical Problems in Engineering 19
0 1000 2000 3000 4000 5000
0 1000 2000 3000 4000 5000
minus01
0
01
minus02
0
02
Time (s) Time (s)
Time (s) Time (s)
minus5
0
5
times10minus4
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
minus1
0
1
times10minus3
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
The d
ispla
cem
ent o
f the
tip
(m)
The d
ispla
cem
ent o
f the
tip
(m)
The v
eloci
ty o
f the
tip
(ms
)
The v
eloc
ity o
f the
tip
(ms
)
Figure 11 The displacement and velocity of the tip of the supporting beam
geometrical nonlinearity effect are different in the vibrationdisplacement and velocitymagnitudes and phases (Figure 15)
The simulation results can be obtained as follows by usingthe optimal PI based controller adopting the abovementionedparameters and initial conditions
The roll pitch and yaw errors are given by using theoptimal PI based controller These errors tend to disappearby observing the partially enlarged plotting of the figure (thecorresponding right figures) (shown in Figure 12) And therelative satisfied dynamic performance can also be obtainedFrom the view of eliminating the steady-state errors the opti-mal PI based controller performs better than the LQR basedcontroller by theoretical analysis and simulation results Theformer can achieve attitude control results without pitchand yaw steady-state errors From the view of dynamicperformance both the controllers perform well In additionit can be seen that the difference between the modelswith and without geometrical nonlinearity is merely inthe phase
The roll pitch and yaw rate errors are presented inFigure 13 The dynamic and steady-state performances aresatisfied by observing the simulation results And by observ-ing the difference between the dynamics responses with and
without the influence by the geometrical nonlinearity it canbe concluded that the merely difference is the phase
The desired control torques of the roll pitch and yaw areobtained in Figure 14 by using the optimal PI based controllerIt can be seen that the value of the desired roll control torquedecreases to zero as the values of the roll angle and ratedecrease to zero The desired pitch and yaw control torquestend to be the constant values 009Nlowastm and minus009Nlowastmrespectively The desired initial control torques are large byobserving Figure 14 It is suggested that the gimbaled controlboom combining the sliding masses is adopted to afford theinitial torque Then the control vanes can be used to controlthe solar sail after the initial phase The phase differencecan also be observed by inspecting the dynamics responsesduring the 4800sim5000 s period
The vibration can be controlled effectively based on theoptimal PI controller And the relative satisfied dynamicand steady-state performances can be achieved In additionthe tiny differences exist in the magnitudes of the requiredtorques And the phase differences also exist
It can be concluded as follows by analyzing and compar-ing the simulation results based on the LQR and optimal PItheories in detail
20 Mathematical Problems in Engineering
Roll
erro
r120593(∘
)
Roll
erro
r120593(∘
)
minus5
0
5
minus5
0
5
Pitc
h er
ror120579
(∘)
Pitc
h er
ror120579
(∘)
0 1000 2000 3000 4000 5000minus10
0
10
Time (s) Time (s)
Time (s)
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
Yaw
erro
r120595(∘
)
Yaw
erro
r120595(∘
)
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
minus1
0
1
times10minus3
minus1
0
1
times10minus3
minus1
0
1
times10minus3
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Figure 12 The roll pitch and yaw errors
(1) From the view of eliminating the steady-state errorsof the pitch and yaw errors the optimal PI based con-troller performs better than the LQR based controllerby theoretical analysis and simulation results Thedynamic performances of the two controllers are bothsatisfied and the desired control torques are relativelysmall
(2) The weighting of the state variables is reflected by theweighting matrix according to the LQR and optimalPI theories The constant weighting matrices selectedin this paper can effectively reflect the initial statevariable errors but maybe reflect the final state vari-able errors deficiently The time-varying weightingmatrices should be selected
(3) For the actual orbiting solar sail the control actuators(control vanes gimbaled control boom and slidingmasses) cannot afford excessive large control torquesThus the control torques should be as small as possibleon the premise of acquiring satisfied dynamic perfor-mance and steady-state errors It will not only reducethe burden of the control actuators but also avoid
exciting structural vibration In engineering practicethe weighting matrices and the control weightingmatrices should be selected based on the attitudecontrol requirement (eg dynamic performance andsteady-state errors etc)
(4) The dynamics responses influenced by the geometri-cal nonlinearity can be observed In a word the tinydifferences between the magnitudes of the physicalvariables exist for the models with and withoutthe geometrical nonlinearity And the relative cleardifferences exist in the phases for the attitude anglesrates required torques and so forth
6 Conclusions
The coupled attitude and structural dynamics is establishedfor the highly flexible sailcraft by using the von-Karman von-Karmanrsquos nonlinear strain-displacement relationships basedon assumptions of large deflections moderate rotationsand
Mathematical Problems in Engineering 21
Roll
rate
erro
r(∘ s
)
Roll
rate
erro
r(∘ s
)
minus01
0
01
minus01
0
01
Pitc
h ra
te er
ror (
∘ s)
Pitc
h ra
te er
ror (
∘ s)
0 1000 2000 3000 4000 5000minus02
0
02
Yaw
rate
erro
r (∘ s
)
Yaw
rate
erro
r (∘ s
)
4800 4850 4900 4950 5000
minus5
0
5times10minus4
minus5
0
5
times10minus4
minus5
0
5times10minus4
Time (s)
4800 4850 4900 4950 5000
Time (s)
4800 4850 4900 4950 5000
Time (s)
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Figure 13 The roll pitch and yaw rate errors
small strains The Lagrange equation method is utilizedto derive the dynamics for controller design and dynamicsimulation The LQR and optimal PI based controllers aredesigned for the dynamics with the constant disturbancetorque caused by the cmcp offset By theoretical analysisand simulation it can be seen that both controllers cancompromise between the state variables and control inputsBecause the control actuators can hardly afford large controltorque the dynamic performance should be relaxed toreduce the requirement for the attitude control actuatorsBesides the optimal PI based controller can also eliminatethe constant disturbance torque caused by the cmcp offsetthat always exists while the LQR based controller fails toachieve the results with satisfied steady-state performancealthough the attitude control torque is always applied to thecoupled dynamic systemThe dynamics simulations with andwithout the geometrical nonlinearity effect are also carriedout And the differences between the models in magnitudesand phases are identified and analyzed It can be concludedthat the optimal PI based controller performs better than the
LQRbased controller from the viewof eliminating the steady-state error caused by the disturbance torque by the cmcpoffset
Appendix
The related parameters in above equation are given as
119886120593= 119869
119909+ 119898
ℎ11199102
ℎ1
+ 119898ℎ21199112
ℎ2
+ 1198981199011199032
119901119911
+ 1198981199011199032
119901119910
119886120579= minus 119898
119901119903119901119909119903119901119910 119886
120595= minus119898
119901119903119901119909119903119901119911
1198861198811
= minus 1198981198971198972
1198861198812
= minus4
5119898
1198971198972
119887120579= 119869
119910+ 119898
ℎ21199112
ℎ2
+ 1198981199011199032
119901119911
+ 1198981199011199032
119901119909
119887120595= minus 119898
119901119903119901119910119903119901119911 119887
120593= minus119898
119901119903119901119909119903119901119910
22 Mathematical Problems in Engineering
Roll
torq
ue (N
lowastm
)
Roll
torq
ue (N
lowastm
)
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
0 2000 4000 6000
0 2000 4000 6000
0 2000 4000 6000
Time (s)
Time (s)
Time (s)
Time (s)
Time (s)
Time (s)4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
minus01
minus008
008
009
01
minus002
0
002
minus5
0
5
minus2
0
2
Pitc
h to
rque
(Nlowast
m)
Pitc
h to
rque
(Nlowast
m)
minus2
0
2
Yaw
torq
ue (N
lowastm
)
Yaw
torq
ue (N
lowastm
)
Figure 14 The roll pitch and yaw torques
1198871198811
=1
2119898
1198971198972
1198871198812
=2
5119898
1198971198972
119888120595= 119869
119911+ 119898
ℎ11199102
ℎ1
+ 1198981199011199032
119901119910
+ 1198981199011199032
119901119909
119888120579= minus 119898
119901119903119901119910119903119901119911 119888
120593= minus119898
119901119903119901119909119903119901119911
1198881198811
= minus1
21198972
119898119897 119888
1198812
= minus2
51198972
119898119897
119889
1198811
= (4
3
119868119863
119897+
1
5119897119868119860) 119889
1198812
= (1
6119897119868119860+
3119868119863
2119897)
119889
1198811
=4120578
119887119863
119909119909
1198973 119889
1198812
=6120578
119887119863
119909119909
1198973
1198891198811
=4119863
119909119909
1198973 119889
1198812
=6119863
119909119909
1198973
1198761198811
= 1198651198621
(119905)
119890
1198811
= (3
2
119868119863
119897+
1
6119897119868119860)
119890
1198812
= (1
7119897119868119860+
9
5
119868119863
119897) 119890
1198811
=6120578
119887119863
119909119909
1198973
119890
1198812
=12120578
119887119863
119909119909
1198973 119890
1198811
=6119863
119909119909
1198973
1198901198812
=12119863
119909119909
1198973 119876
1198812
= 1198651198622
(119905)
(A1)
The detailed expressions of control inputs for attitudevibration and related parameters in the state-space model ofthe dynamics (see (62) and (63)) are presented as follows
A =
[[[[[[[[[[[[[[
[
0 1 0 0 0 0 0 0 0 0
0 0 0 0 0 0 1198861
1198862
1198863
1198864
0 0 0 1 0 0 0 0 0 0
0 0 0 0 0 0 1198865
1198866
1198867
1198868
0 0 0 0 0 1 0 0 0 0
0 0 0 0 0 0 1198869
11988610
11988611
11988612
0 0 0 0 0 0 0 1 0 0
0 0 0 0 0 0 11988613
11988614
11988615
11988616
0 0 0 0 0 0 0 0 0 1
0 0 0 0 0 0 11988617
11988618
11988619
11988620
]]]]]]]]]]]]]]
]
Mathematical Problems in Engineering 23
0 1000 2000 3000 4000 5000
0 1000 2000 3000 4000 5000
minus01
0
01
minus02
0
02
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Time (s)
Time (s)Time (s)
Time (s)
minus1
0
1
minus1
0
1
times10minus3
times10minus3Th
e disp
lace
men
t of t
he ti
p (m
)
The d
ispla
cem
ent o
f the
tip
(m)
The v
eloci
ty o
f the
tip
(ms
)
The v
eloci
ty o
f the
tip
(ms
)
Figure 15 Vibration displacement and velocity of the tip
B =
[[[[[[[[[[[[[[
[
0 0 0 0 0
1 0 0 0 0
0 0 0 0 0
0 1 0 0 0
0 0 0 0 0
0 0 1 0 0
0 0 0 0 0
0 0 0 1 0
0 0 0 0 0
0 0 0 0 1
]]]]]]]]]]]]]]
]
1198861= minus
1198981198971198972
119869119909
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus4
5119869119909
1198981198971198972
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198862= minus
1198981198971198972
119869119909
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus4
5119869119909
1198981198971198972
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198863= minus
1198981198971198972
119869119909
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus4
5119869119909
1198981198971198972
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198864= minus
1198981198971198972
119869119909
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus4
5119869119909
1198981198971198972
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
119906120593=
119876120593
119869119909
+
119906
119869119909
+119898
1198971198972
119869119909
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+4
5119869119909
1198981198971198972
+
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198865=
1
2119869119910
1198981198971198972
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+2
5119869119910
1198981198971198972
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198866=
1
2119869119910
1198981198971198972
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+2
5119869119910
1198981198971198972
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198867=
1
2119869119910
1198981198971198972
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+2
5119869119910
1198981198971198972
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198868=
1
2119869119910
1198981198971198972
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
24 Mathematical Problems in Engineering
+2
5119869119910
1198981198971198972
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
119906120579=
119876120579
119869119910
+119906
120579
119869119910
minus1
2119869119910
1198981198971198972
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119910
1198981198971198972
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198869= minus
1
2119869119911
1198972
119898119897
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988610
= minus1
2119869119911
1198972
119898119897
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988611
= minus1
2119869119911
1198972
119898119897
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988612
= minus1
2119869119911
1198972
119898119897
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
119906120595=
119876120595
119869119911
+
119906
119869119911
+1
2119869119911
1198972
119898119897
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+2
5119869119911
1198972
119898119897
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988613
= minus
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988614
= minus
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988615
= minus
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988616
= minus
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
1199061198811
=
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988617
= minus
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988618
= minus
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988619
= minus
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988620
= minus
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1199061198812
=
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(A2)
Conflict of Interests
The authors declare that there is no conflict of interestsregarding the publication of this paper
Acknowledgments
The authors would like to thank the anonymous reviewers fortheir critical and constructive review of the paper This studywas cosupported by the National Natural Science Foundationof China (Project no 11302134 11272101)
References
[1] M Colin Solar Sailing Technology Dynamics and MissionApplications Springer-Praxis London UK 1st edition 1999
[2] V Lappas SWokesM Leipold A Lyngvi and P Falkner ldquoGui-dance and control for an Interstellar Heliopause Probe (IHP)solar sail mission to 200 AUrdquo in Proceedings of the AIAAGuidance Navigation and Control Conference and Exhibit pp2472ndash2492 San Francisco Calif USA August 2005
[3] L Charlotte C Camilla and C McInnes ldquoSolar radiation pres-sure augmented deorbiting fromhigh altitude sun-synchronousorbitsrdquo in Proceedings of the 4S Symposium 2012 Small SatellitesSystems and Services Portoroz Slovenia 2012
[4] M Ceriotti and C RMcInnes ldquoGeneration of optimal trajecto-ries for Earth hybrid pole sittersrdquo Journal of Guidance Controland Dynamics vol 34 no 3 pp 847ndash859 2011
[5] S Gong J Li andH Baoyin ldquoSolar sail transfer trajectory fromL1 point to sub-L1 pointrdquoAerospace Science and Technology vol15 no 7 pp 544ndash554 2011
[6] S Gong J Li and H Baoyin ldquoAnalysis of displaced solar sailorbits with passive controlrdquo Journal of Guidance Control andDynamics vol 31 no 3 pp 782ndash785 2008
[7] S Gong H Baoyin and J Li ldquoSolar sail three-body transfertrajectory designrdquo Journal of Guidance Control and Dynamicsvol 33 no 3 pp 873ndash886 2010
Mathematical Problems in Engineering 25
[8] S Gong J Li H Baoyin and J Simo ldquoA new solar sail orbitrdquoScience China Technological Sciences vol 55 no 3 pp 848ndash8552012
[9] Y Tsuda O Mori R Funase et al ldquoAchievement of IKAROS-Japanese deep space solar sail demonstration missionrdquo ActaAstronautica vol 82 no 2 pp 183ndash188 2013
[10] L Johnson MWhorton A Heaton R Pinson G Laue and CAdams ldquoNanoSail-D a solar sail demonstration missionrdquo ActaAstronautica vol 68 no 5-6 pp 571ndash575 2011
[11] B Wie and D Murphy ldquoSolar-sail attitude control design for asail flight validation missionrdquo Journal of Spacecraft and Rocketsvol 44 no 4 pp 809ndash821 2007
[12] B Wie D Murphy M Paluszek and S Thomas ldquoRobust atti-tude control systems design for solar sails part 1 propellantlessprimaryACSrdquo inProceedings of the AIAAGuidance Navigationand Control Conference and Exhibit Providence RI USAAugust 2004
[13] B Wie D Murphy M Paluszek and S Thomas ldquoRobust atti-tude control systems design for solar sails part 2 MicroPPT-based secondary ACSrdquo in Proceedings of the AIAA GuidanceNavigation and Control Conference and Exhibit pp 1325ndash1340Providence RI USA August 2004
[14] S Thomas M Paluszek B Wie and D Murphy ldquoAOCS per-formance and stability validation for large flexible solar sailspacecraftrdquo in Proceedings of the 41st AIAAASMESAEASEEJoint Propulsion Conference amp Exhibit Tucson Ariz USA 2005
[15] B Wie ldquoDynamic modeling and attitude control of solar sailspacecraft part Irdquo in Proceedings of the AIAAGuidance Naviga-tion and Control Conference and Exhibit Monterey Calif USAAugust 2002
[16] BWie ldquoSolar sail attitude control and dynamics part 1rdquo Journalof Guidance Control and Dynamics vol 27 no 4 pp 526ndash5352004
[17] B Wie ldquoDynamic modeling and attitude control of solar sailspacecraft part IIrdquo in Proceedings of the AIAA Guidance Nav-igation and Control Conference and Exhibit Monterey CalifUSA August 2002
[18] BWie ldquoSolar sail attitude control and dynamics part 2rdquo Journalof Guidance Control and Dynamics vol 27 no 4 pp 536ndash5442004
[19] C Luo and J-H Zheng ldquoSolar-sail attitude control based onmoving masses and roll stabilizer barsrdquo Journal of HarbinInstitute of Technology vol 43 no 3 pp 95ndash101 2011
[20] D Romagnoli and T Oehlschlagel ldquoHigh performance twodegrees of freedom attitude control for solar sailsrdquo Advances inSpace Research vol 48 no 11 pp 1869ndash1879 2011
[21] C Scholz D Romagnoli B Dachwald and S Theil ldquoPerfor-mance analysis of an attitude control system for solar sails usingsliding massesrdquo Advances in Space Research vol 48 no 11 pp1822ndash1835 2011
[22] A Bolle and C Circi ldquoSolar sail attitude control through in-plane moving massesrdquo Journal of Aerospace Engineering vol222 no 1 pp 81ndash94 2008
[23] M RotunnoM Basso A B Pome andM Sallusti ldquoA compari-son of robust attitude control techniques for a solar sail space-craftrdquo in Proceedings of the AIAA Guidance Navigation andControl Conference and Exhibit San Francisco Calif USA2005
[24] J Zhang K Zhai and T Wang ldquoControl of large angle maneu-vers for the flexible solar sailrdquo Science China Physics Mechanicsand Astronomy vol 54 no 4 pp 770ndash776 2011
[25] J Zhang andTWang ldquoCoupled attitude-orbit control of flexiblesolar sail for displaced solar orbitrdquo Journal of Spacecraft andRockets vol 50 no 3 pp 675ndash685 2013
[26] Q Li XMa and TWang ldquoReducedmodel for flexible solar saildynamicsrdquo Journal of Spacecraft and Rockets vol 48 no 3 pp446ndash453 2011
[27] M Polites J Kalmanson and D Mangus ldquoSolar sail attitudecontrol using small reaction wheels and magnetic torquersrdquoProceedings of the Institution of Mechanical Engineers G Journalof Aerospace Engineering vol 222 no 1 pp 53ndash62 2008
[28] H-T Cui J-H Luo J-H Feng and P-Y Cui ldquoAttitudecontrol of solar sail spacecraft with control boomrdquo Journal ofAstronautics vol 29 no 2 pp 560ndash566 2008
[29] E Mettler and S R Ploen ldquoSolar sail dynamics and controlusing a boom mounted bus articulated by a bi-state two-axisgimbal and reaction wheelsrdquo in Proceedings of the AIAAAASAstrodynamics Specialist Conference and Exhibit MontereyCalif USA August 2002
[30] J Luo X Li and J Feng ldquoPassive attitude control of solar sailspacecraftrdquo Flight Dynamics vol 26 no 5 pp 47ndash50 2008
[31] J Luo Study on attitude control of solar sail spaceraft [PhDthesis] School of Astronautics Harbin Institute of TechnologyHarbin China 2007
[32] D A Lawrence and S W Piggott ldquoIntegrated trajectory andattitude control for a four-vane solar sailrdquo in Proceedings ofthe AIAA Guidance Navigation and Control Conference andExhibit pp 2416ndash2431 San Francisco Calif USA August 2005
[33] E Mettler A B Acikmese and S R Ploen ldquoAttitude dynamicsand control of solar sails with articulated vanesrdquo in Proceedingsof the AIAA Guidance Navigation and Control Conference andExhibit pp 2396ndash2415 San Francisco Calif USA August 2005
[34] S N Adeli V J Lappas and B Wie ldquoA scalable bus-basedattitude control system for Solar Sailsrdquo Advances in SpaceResearch vol 48 no 11 pp 1836ndash1847 2011
[35] R Funase Y Shirasawa Y Mimasu et al ldquoOn-orbit verificationof fuel-free attitude control system for spinning solar sailutilizing solar radiation pressurerdquo Advances in Space Researchvol 48 no 11 pp 1740ndash1746 2011
[36] B Fu and F O Eke ldquoAttitude control methodology for largesolar sailsrdquo in AIAA Guidance Navigation and Control (GNC)Conference 2013
[37] J Liu N Cui F Shen and S Rong ldquoDynamics of highly-flexiblesolar sail subjected to various forcesrdquoActaAstronautica vol 103pp 55ndash72 2014
[38] J F Liu S Y Rong and J G Li ldquoAttitude dynamics modelingand control of large flexible solar sail spacecraftrdquo in Proceedingsof the 3rd International Symposium on Systems and Control inAeronautics and Astronautics (ISSCAA rsquo10) pp 243ndash247 IEEEPublications Piscataway NJ USA 2010
[39] S Gong H Baoyin and J Li ldquoCoupled attitude-orbit dynamicsand control for displaced solar orbitsrdquo Acta Astronautica vol65 no 5-6 pp 730ndash737 2009
Submit your manuscripts athttpwwwhindawicom
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
MathematicsJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Mathematical Problems in Engineering
Hindawi Publishing Corporationhttpwwwhindawicom
Differential EquationsInternational Journal of
Volume 2014
Applied MathematicsJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Probability and StatisticsHindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Journal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Mathematical PhysicsAdvances in
Complex AnalysisJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
OptimizationJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
CombinatoricsHindawi Publishing Corporationhttpwwwhindawicom Volume 2014
International Journal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Operations ResearchAdvances in
Journal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Function Spaces
Abstract and Applied AnalysisHindawi Publishing Corporationhttpwwwhindawicom Volume 2014
International Journal of Mathematics and Mathematical Sciences
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
The Scientific World JournalHindawi Publishing Corporation httpwwwhindawicom Volume 2014
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Algebra
Discrete Dynamics in Nature and Society
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Decision SciencesAdvances in
Discrete MathematicsJournal of
Hindawi Publishing Corporationhttpwwwhindawicom
Volume 2014 Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Stochastic AnalysisInternational Journal of
Mathematical Problems in Engineering 15
The complexity of the state-space model can be seen bypresenting the detailed expressions of control inputs forattitudevibration and related parameters in (A2) in theappendix
5 AttitudeVibration Control and Simulation
The controller for the attitude and vibration is developedusing the LQR and optimal PI theory The dynamic simula-tion is performed based on the coupled dynamics derived inthe previous sections
51 LQR and Optimal PI Based Controllers Design Thedynamics for solar sail can bewritten as follows togetherwithits quadratic cost function also defined as
x = Ax + Bu x (1199050) = x
1199050
(known)
119869 =1
2int
infin
1199050
[x119879 (119905)Qx (119905) + u119879 (119905)Ru (119905)] 119889119905
(66)
whereQ = Q119879
⩾ 0 andR = R119879
gt 0 are constantThe control-lability of [AB] and the observability of [AD] can beensured when the equationDD119879
= Q holds for anymatrixDThe optimal control input ulowast(119905)within the scope of u(119905) isin R119903119905 isin [119905
0infin] can be computed as follows to make 119869minimum
ulowast (119905) = minusKxlowast (119905) K = Rminus1B119879P (67)
where P is the nonnegative definite symmetric solution of thefollowing Riccati algebraic equations
PA + A119879P minus PBRminus1B119879P +Q = 0 (68)
And the optimal performance index can be obtained asfollows for arbitrary initial states
119869lowast
[x (1199050) 119905
0] =
1
2x1198790
Px0 (69)
The closed-loop system
x = (A minus BRminus1B119879P) x (70)
is asymptotically stableFor an orbiting solar sail the primary disturbance torque
is by the cmcp offset and the impact of the tiny dust inthe deep space The state regulator can be used to controlthe dynamic system affected by pulse disturbance torquewith good steady-state errors but will never achieve accuratesteady-state errors if the dynamics is affected by constantdisturbance torque Thus the optimal state regulator withan integrator to eliminate the constant disturbance torqueshould be presented This optimal proportional-integral reg-ulator not only eliminates the constant disturbance torque butalso possesses the property of optimal regulator
Table 1 The related parameters
Parameters ValuesCMCP offsetm [0 017678 017678]119879
The side length of square sailm 100Nominal solar-radiation pressureconstant at 1 AU from the sunNm2 4563 times 10minus6
Solar-radiation pressure forceN 912 times 10minus2
Roll inertiakglowastm2 50383Pitch and yaw inertiakglowastm2 251915Outer radiusm 0229Thickness of the supporting beamm 75 times 10minus6
Youngrsquos modulus of the supportingbeamGPa 124
Moment of inertia of the cross-sectionof the supporting beamm4 2829412 times 10minus7
Bending stiffness of the supportingbeamNlowastm2 3508471336
Proportional damping coefficient ofsupporting beams 001
Line density of the supportingbeamkgm 0106879
Cross-sectional area of the supportingbeamm2 1079 times 10minus5
Roll disturbance torqueNlowastm 0Pitch (yaw) disturbance torqueNlowastm 0016122 (minus0016122)
For the following linear system with the correspondingperformance index
x = Ax + Bu x (1199050) = x
1199050
u (1199050) = u
1199050
119869 =1
2int
infin
1199050
(x119879Qx + u119879Ru + u119879Su) 119889119905(71)
where Q = Q119879
⩾ 0 R = R119879
gt 0 and S = S119879 gt 0 If [AB]is completely controllable and meanwhile [AD
11] is com-
pletely observable with the relationship D11D119879
11
= Q thesolution can be expressed as
ulowast = minusK1x minus K
2ulowast ulowast (119905
0) = u
1199050
(72)
If B119879B is full rank we can get
ulowast = minusK3x minus K
4x ulowast (119905
0) = u
1199050
(73)
K119894(119894 = 1 2 3 4) is the function of ABQR S
The closed-loop system
[xulowast] = [
A BminusK
1minusK
2
] [xulowast] [
[
x (1199050)
u (1199050)]
]
= [x1199050
u1199050
] (74)
is asymptotically stableThe compromise between the state variables (the angle
angular velocity the vibration displacement and velocity)and control inputs (the torque by all the actuators) can
16 Mathematical Problems in Engineering
0 2000 4000 6000
0 2000 4000 6000
0 2000 4000 6000minus5
0
5
minus5
0
5
minus5
0
5
minus4
minus2
0
2
4
times10minus4
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
00162
00164
00166
4800 4900 5000
4800 4900 5000
4800 4900 5000
minus00165
minus0016
Time (s) Time (s)
Time (s)
Time (s)
Time (s)
Time (s)
Roll
erro
r120593(∘
)
Roll
erro
r120593(∘
)
Pitc
h er
ror120579
(∘)
Pitc
h er
ror120579
(∘)
Yaw
erro
r120595(∘
)
Yaw
erro
r120595(∘
)
Figure 8 The roll pitch and yaw errors
be achieved by using both the LQR based and optimal PIbased controllers for the coupled attitudevibration dynamicsystem The fact is that the attitude control ability is limitedto the control torque by the control actuators The change ofthe attitude angles and rates should not be frequent to voidexciting vibrations
Thus the weighting matrix Q and the control weightingmatrix R are selected as follows for LQR based controller
Q (1 1) = 9 times 10minus6
Q (2 2) = 1 times 10minus6
Q (3 3) = 16 times 10minus6
Q (4 4) = Q (5 5) = Q (6 6) = Q (7 7) = Q (8 8)
= Q (9 9) = Q (10 10) = 1 times 10minus6
Q (119894 119895) = 0 (119894 = 119895 119894 119895 = 1 sim 10)
R (1 1) = R (2 2) = 900 R (3 3) = 100
R (4 4) = R (5 5) = 10000
R119894119895
= 0 (119894 = 119895 119894 119895 = 1 sim 5)
(75)
TheweightingmatrixQ and the control weightingmatrixR are selected as follows for the optimal PI based controller
Q (1 1) = Q (2 2) = 4 times 10minus8
Q (3 3) = Q (4 4) = Q (5 5) = Q (6 6) = Q (7 7)
= Q (8 8) = 16 times 10minus8
Mathematical Problems in Engineering 17
minus02
0
02
Roll
rate
(∘s)
Roll
rate
(∘s)
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Pitc
h ra
te(∘s)
Pitc
h ra
te(∘s)
0 1000 2000 3000 4000 5000
minus05
0
05
minus05
0
05
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
Time (s)
Yaw
rate
(∘
s)
Yaw
rate
(∘
s)
4800 4850 4900 4950 5000
Time (s)4800 4850 4900 4950 5000
Time (s)4800 4850 4900 4950 5000
minus2
0
2
minus2
0
2
minus2
0
2
times10minus4
times10minus4
times10minus4
Figure 9 The roll pitch and yaw rates
Q (9 9) = Q (10 10) = 1 times 10minus8
Q (119894 119895) = 0 (119894 = 119895 119894 119895 = 1 sim 10)
R (1 1) = R (2 2) = R (3 3) = 1 times 10minus8
R (4 4) = R (5 5) = 4 times 10minus8
R (119894 119895) = 0 (119894 = 119895 119894 119895 = 1 sim 5)
(76)
52 The Simulation Results The initial angle errors of rollpitch and yaw are adopted as 120593(119905
0) = 3
∘ 120579(1199050) = 3
∘ and120595(119905
0) = 3
∘ the initial angular velocity errors of roll pitchand yaw are adopted as (119905
0) = 0
∘
s 120579(1199050) = 0
∘
s and(119905
0) = 0
∘
s 1198811(1199050) = 01m 119881
2(1199050) = 01m
1(1199050) = 0ms
and 2(1199050) = 0ms are adopted in this paper for dynamic
simulationThe estimated cmcp offset is 025m for a 100 times 100m
square solar sail It is assumed that the components of cmcpoffset vector are [0 017678 017678]
119879 in the body frame
The relevant parameters for dynamic simulations are givenin Table 1
The dynamic simulation results are obtained as followsby using the LQR controller based on the abovementionedQ and R related parameters and initial conditions Thedynamics simulations with (denoted by ldquowith GFrdquo) andwithout (denoted by ldquowithout GFrdquo) considering the geo-metrical nonlinearity are presented And the correspondingdiscussions and analysis are also given according to thecalculated results
The roll pitch and yaw errors are presented based onthe dynamics models with and without considering thegeometrical nonlinearityThe control effect with zero steady-state error can be achieved for roll axis by referring tothe results But the steady-state errors exist for pitch andyaw axes from Figure 8 this is because there exist constantdisturbance torques for pitch and yaw axes caused by thecmcp offset Thus the LQR based controller cannot be usedfor attitude control with good steady-state performance Thesteady-state errors of pitch and yaw axes are about 0164
∘
and minus0164∘ respectively from the corresponding partial
enlarged drawing of the figures (see the corresponding left
18 Mathematical Problems in Engineering
minus20
0
20
Roll
torq
ue (N
lowastm
)
Roll
torq
ue (N
lowastm
)
minus50
0
50
minus50
0
50
Pitc
h to
rque
(Nlowast
m)
Pitc
h to
rque
(Nlowast
m)
0 1000 2000 3000 4000 5000
0 2000 4000 6000
0 2000 4000 6000
Yaw
torq
ue (N
lowastm
)
Yaw
torq
ue (N
lowastm
)
minus002
0
002
008
01
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
minus01
minus009
minus008
Time (s)Time (s)
Time (s)Time (s)
Time (s)Time (s)
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Figure 10 The roll pitch and yaw torques
figures) A simple and practical controller should be designedto eliminate the steady-state errorsThese errorswill affect theprecision of the super long duration space mission deeply
The differences between the dynamics with and withoutthe geometrical nonlinearity effect can be observed Theamplitudes and phases change a bit by comparing the corre-sponding results
It can be observed by the partial enlarged figures(the right figures of Figure 9) that there are no steady-stateerrors for roll pitch and yaw rates The relative satisfieddynamic performance is achieved In fact a result with muchmore satisfied dynamic performance can be obtained but itwill make the desired control torques much larger duringthe initial period This will not only excite the vibration ofthe structure but also increase the burden of the controlactuators
And the differences between the dynamics models withand without the geometrical nonlinearity can also be seenmerely in the phase of the angular velocities
The desired attitude control torques are presented inFigure 10 The roll torque will tend to be zero with thedecrement of the state variable errors The pitch and yawtorques tend to be constant from the middle and bottom
figures The pitch and yaw steady-state errors can never beeliminated although the pitch and yaw torques (009Nlowastmand minus009Nlowastm) are applied continuously by theoreticalanalysis and simulations This is just a great disadvantage ofthe LQR based controller in this paper The initial controltorques can be afforded by vibrating the gimbaled controlboom andmoving the slidingmasses that can afford a relativelarge torque The control vanes can be used to afford thecontrol torques when solar sail is in steady-state process Theexpression of the attitude control inputs 119906
120593 119906
120579 and 119906
120595can be
found in previous sectionMoreover the differences between dynamics responses
with and without geometrical nonlinearity can also beobserved by comparing the corresponding results Therequired torques for the attitude control are a little largerfor the dynamics with geometrical nonlinearity And thedifference in the phase is also clear
It can be seen that the vibration of the supporting beamis depressed effectively by the simulation results in Figure 11It can be seen that the steady-state errors and the dynamicperformance are relatively satisfied It can also be seen that thedynamics responses between the model with and without the
Mathematical Problems in Engineering 19
0 1000 2000 3000 4000 5000
0 1000 2000 3000 4000 5000
minus01
0
01
minus02
0
02
Time (s) Time (s)
Time (s) Time (s)
minus5
0
5
times10minus4
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
minus1
0
1
times10minus3
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
The d
ispla
cem
ent o
f the
tip
(m)
The d
ispla
cem
ent o
f the
tip
(m)
The v
eloci
ty o
f the
tip
(ms
)
The v
eloc
ity o
f the
tip
(ms
)
Figure 11 The displacement and velocity of the tip of the supporting beam
geometrical nonlinearity effect are different in the vibrationdisplacement and velocitymagnitudes and phases (Figure 15)
The simulation results can be obtained as follows by usingthe optimal PI based controller adopting the abovementionedparameters and initial conditions
The roll pitch and yaw errors are given by using theoptimal PI based controller These errors tend to disappearby observing the partially enlarged plotting of the figure (thecorresponding right figures) (shown in Figure 12) And therelative satisfied dynamic performance can also be obtainedFrom the view of eliminating the steady-state errors the opti-mal PI based controller performs better than the LQR basedcontroller by theoretical analysis and simulation results Theformer can achieve attitude control results without pitchand yaw steady-state errors From the view of dynamicperformance both the controllers perform well In additionit can be seen that the difference between the modelswith and without geometrical nonlinearity is merely inthe phase
The roll pitch and yaw rate errors are presented inFigure 13 The dynamic and steady-state performances aresatisfied by observing the simulation results And by observ-ing the difference between the dynamics responses with and
without the influence by the geometrical nonlinearity it canbe concluded that the merely difference is the phase
The desired control torques of the roll pitch and yaw areobtained in Figure 14 by using the optimal PI based controllerIt can be seen that the value of the desired roll control torquedecreases to zero as the values of the roll angle and ratedecrease to zero The desired pitch and yaw control torquestend to be the constant values 009Nlowastm and minus009Nlowastmrespectively The desired initial control torques are large byobserving Figure 14 It is suggested that the gimbaled controlboom combining the sliding masses is adopted to afford theinitial torque Then the control vanes can be used to controlthe solar sail after the initial phase The phase differencecan also be observed by inspecting the dynamics responsesduring the 4800sim5000 s period
The vibration can be controlled effectively based on theoptimal PI controller And the relative satisfied dynamicand steady-state performances can be achieved In additionthe tiny differences exist in the magnitudes of the requiredtorques And the phase differences also exist
It can be concluded as follows by analyzing and compar-ing the simulation results based on the LQR and optimal PItheories in detail
20 Mathematical Problems in Engineering
Roll
erro
r120593(∘
)
Roll
erro
r120593(∘
)
minus5
0
5
minus5
0
5
Pitc
h er
ror120579
(∘)
Pitc
h er
ror120579
(∘)
0 1000 2000 3000 4000 5000minus10
0
10
Time (s) Time (s)
Time (s)
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
Yaw
erro
r120595(∘
)
Yaw
erro
r120595(∘
)
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
minus1
0
1
times10minus3
minus1
0
1
times10minus3
minus1
0
1
times10minus3
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Figure 12 The roll pitch and yaw errors
(1) From the view of eliminating the steady-state errorsof the pitch and yaw errors the optimal PI based con-troller performs better than the LQR based controllerby theoretical analysis and simulation results Thedynamic performances of the two controllers are bothsatisfied and the desired control torques are relativelysmall
(2) The weighting of the state variables is reflected by theweighting matrix according to the LQR and optimalPI theories The constant weighting matrices selectedin this paper can effectively reflect the initial statevariable errors but maybe reflect the final state vari-able errors deficiently The time-varying weightingmatrices should be selected
(3) For the actual orbiting solar sail the control actuators(control vanes gimbaled control boom and slidingmasses) cannot afford excessive large control torquesThus the control torques should be as small as possibleon the premise of acquiring satisfied dynamic perfor-mance and steady-state errors It will not only reducethe burden of the control actuators but also avoid
exciting structural vibration In engineering practicethe weighting matrices and the control weightingmatrices should be selected based on the attitudecontrol requirement (eg dynamic performance andsteady-state errors etc)
(4) The dynamics responses influenced by the geometri-cal nonlinearity can be observed In a word the tinydifferences between the magnitudes of the physicalvariables exist for the models with and withoutthe geometrical nonlinearity And the relative cleardifferences exist in the phases for the attitude anglesrates required torques and so forth
6 Conclusions
The coupled attitude and structural dynamics is establishedfor the highly flexible sailcraft by using the von-Karman von-Karmanrsquos nonlinear strain-displacement relationships basedon assumptions of large deflections moderate rotationsand
Mathematical Problems in Engineering 21
Roll
rate
erro
r(∘ s
)
Roll
rate
erro
r(∘ s
)
minus01
0
01
minus01
0
01
Pitc
h ra
te er
ror (
∘ s)
Pitc
h ra
te er
ror (
∘ s)
0 1000 2000 3000 4000 5000minus02
0
02
Yaw
rate
erro
r (∘ s
)
Yaw
rate
erro
r (∘ s
)
4800 4850 4900 4950 5000
minus5
0
5times10minus4
minus5
0
5
times10minus4
minus5
0
5times10minus4
Time (s)
4800 4850 4900 4950 5000
Time (s)
4800 4850 4900 4950 5000
Time (s)
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Figure 13 The roll pitch and yaw rate errors
small strains The Lagrange equation method is utilizedto derive the dynamics for controller design and dynamicsimulation The LQR and optimal PI based controllers aredesigned for the dynamics with the constant disturbancetorque caused by the cmcp offset By theoretical analysisand simulation it can be seen that both controllers cancompromise between the state variables and control inputsBecause the control actuators can hardly afford large controltorque the dynamic performance should be relaxed toreduce the requirement for the attitude control actuatorsBesides the optimal PI based controller can also eliminatethe constant disturbance torque caused by the cmcp offsetthat always exists while the LQR based controller fails toachieve the results with satisfied steady-state performancealthough the attitude control torque is always applied to thecoupled dynamic systemThe dynamics simulations with andwithout the geometrical nonlinearity effect are also carriedout And the differences between the models in magnitudesand phases are identified and analyzed It can be concludedthat the optimal PI based controller performs better than the
LQRbased controller from the viewof eliminating the steady-state error caused by the disturbance torque by the cmcpoffset
Appendix
The related parameters in above equation are given as
119886120593= 119869
119909+ 119898
ℎ11199102
ℎ1
+ 119898ℎ21199112
ℎ2
+ 1198981199011199032
119901119911
+ 1198981199011199032
119901119910
119886120579= minus 119898
119901119903119901119909119903119901119910 119886
120595= minus119898
119901119903119901119909119903119901119911
1198861198811
= minus 1198981198971198972
1198861198812
= minus4
5119898
1198971198972
119887120579= 119869
119910+ 119898
ℎ21199112
ℎ2
+ 1198981199011199032
119901119911
+ 1198981199011199032
119901119909
119887120595= minus 119898
119901119903119901119910119903119901119911 119887
120593= minus119898
119901119903119901119909119903119901119910
22 Mathematical Problems in Engineering
Roll
torq
ue (N
lowastm
)
Roll
torq
ue (N
lowastm
)
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
0 2000 4000 6000
0 2000 4000 6000
0 2000 4000 6000
Time (s)
Time (s)
Time (s)
Time (s)
Time (s)
Time (s)4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
minus01
minus008
008
009
01
minus002
0
002
minus5
0
5
minus2
0
2
Pitc
h to
rque
(Nlowast
m)
Pitc
h to
rque
(Nlowast
m)
minus2
0
2
Yaw
torq
ue (N
lowastm
)
Yaw
torq
ue (N
lowastm
)
Figure 14 The roll pitch and yaw torques
1198871198811
=1
2119898
1198971198972
1198871198812
=2
5119898
1198971198972
119888120595= 119869
119911+ 119898
ℎ11199102
ℎ1
+ 1198981199011199032
119901119910
+ 1198981199011199032
119901119909
119888120579= minus 119898
119901119903119901119910119903119901119911 119888
120593= minus119898
119901119903119901119909119903119901119911
1198881198811
= minus1
21198972
119898119897 119888
1198812
= minus2
51198972
119898119897
119889
1198811
= (4
3
119868119863
119897+
1
5119897119868119860) 119889
1198812
= (1
6119897119868119860+
3119868119863
2119897)
119889
1198811
=4120578
119887119863
119909119909
1198973 119889
1198812
=6120578
119887119863
119909119909
1198973
1198891198811
=4119863
119909119909
1198973 119889
1198812
=6119863
119909119909
1198973
1198761198811
= 1198651198621
(119905)
119890
1198811
= (3
2
119868119863
119897+
1
6119897119868119860)
119890
1198812
= (1
7119897119868119860+
9
5
119868119863
119897) 119890
1198811
=6120578
119887119863
119909119909
1198973
119890
1198812
=12120578
119887119863
119909119909
1198973 119890
1198811
=6119863
119909119909
1198973
1198901198812
=12119863
119909119909
1198973 119876
1198812
= 1198651198622
(119905)
(A1)
The detailed expressions of control inputs for attitudevibration and related parameters in the state-space model ofthe dynamics (see (62) and (63)) are presented as follows
A =
[[[[[[[[[[[[[[
[
0 1 0 0 0 0 0 0 0 0
0 0 0 0 0 0 1198861
1198862
1198863
1198864
0 0 0 1 0 0 0 0 0 0
0 0 0 0 0 0 1198865
1198866
1198867
1198868
0 0 0 0 0 1 0 0 0 0
0 0 0 0 0 0 1198869
11988610
11988611
11988612
0 0 0 0 0 0 0 1 0 0
0 0 0 0 0 0 11988613
11988614
11988615
11988616
0 0 0 0 0 0 0 0 0 1
0 0 0 0 0 0 11988617
11988618
11988619
11988620
]]]]]]]]]]]]]]
]
Mathematical Problems in Engineering 23
0 1000 2000 3000 4000 5000
0 1000 2000 3000 4000 5000
minus01
0
01
minus02
0
02
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Time (s)
Time (s)Time (s)
Time (s)
minus1
0
1
minus1
0
1
times10minus3
times10minus3Th
e disp
lace
men
t of t
he ti
p (m
)
The d
ispla
cem
ent o
f the
tip
(m)
The v
eloci
ty o
f the
tip
(ms
)
The v
eloci
ty o
f the
tip
(ms
)
Figure 15 Vibration displacement and velocity of the tip
B =
[[[[[[[[[[[[[[
[
0 0 0 0 0
1 0 0 0 0
0 0 0 0 0
0 1 0 0 0
0 0 0 0 0
0 0 1 0 0
0 0 0 0 0
0 0 0 1 0
0 0 0 0 0
0 0 0 0 1
]]]]]]]]]]]]]]
]
1198861= minus
1198981198971198972
119869119909
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus4
5119869119909
1198981198971198972
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198862= minus
1198981198971198972
119869119909
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus4
5119869119909
1198981198971198972
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198863= minus
1198981198971198972
119869119909
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus4
5119869119909
1198981198971198972
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198864= minus
1198981198971198972
119869119909
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus4
5119869119909
1198981198971198972
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
119906120593=
119876120593
119869119909
+
119906
119869119909
+119898
1198971198972
119869119909
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+4
5119869119909
1198981198971198972
+
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198865=
1
2119869119910
1198981198971198972
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+2
5119869119910
1198981198971198972
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198866=
1
2119869119910
1198981198971198972
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+2
5119869119910
1198981198971198972
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198867=
1
2119869119910
1198981198971198972
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+2
5119869119910
1198981198971198972
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198868=
1
2119869119910
1198981198971198972
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
24 Mathematical Problems in Engineering
+2
5119869119910
1198981198971198972
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
119906120579=
119876120579
119869119910
+119906
120579
119869119910
minus1
2119869119910
1198981198971198972
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119910
1198981198971198972
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198869= minus
1
2119869119911
1198972
119898119897
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988610
= minus1
2119869119911
1198972
119898119897
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988611
= minus1
2119869119911
1198972
119898119897
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988612
= minus1
2119869119911
1198972
119898119897
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
119906120595=
119876120595
119869119911
+
119906
119869119911
+1
2119869119911
1198972
119898119897
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+2
5119869119911
1198972
119898119897
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988613
= minus
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988614
= minus
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988615
= minus
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988616
= minus
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
1199061198811
=
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988617
= minus
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988618
= minus
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988619
= minus
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988620
= minus
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1199061198812
=
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(A2)
Conflict of Interests
The authors declare that there is no conflict of interestsregarding the publication of this paper
Acknowledgments
The authors would like to thank the anonymous reviewers fortheir critical and constructive review of the paper This studywas cosupported by the National Natural Science Foundationof China (Project no 11302134 11272101)
References
[1] M Colin Solar Sailing Technology Dynamics and MissionApplications Springer-Praxis London UK 1st edition 1999
[2] V Lappas SWokesM Leipold A Lyngvi and P Falkner ldquoGui-dance and control for an Interstellar Heliopause Probe (IHP)solar sail mission to 200 AUrdquo in Proceedings of the AIAAGuidance Navigation and Control Conference and Exhibit pp2472ndash2492 San Francisco Calif USA August 2005
[3] L Charlotte C Camilla and C McInnes ldquoSolar radiation pres-sure augmented deorbiting fromhigh altitude sun-synchronousorbitsrdquo in Proceedings of the 4S Symposium 2012 Small SatellitesSystems and Services Portoroz Slovenia 2012
[4] M Ceriotti and C RMcInnes ldquoGeneration of optimal trajecto-ries for Earth hybrid pole sittersrdquo Journal of Guidance Controland Dynamics vol 34 no 3 pp 847ndash859 2011
[5] S Gong J Li andH Baoyin ldquoSolar sail transfer trajectory fromL1 point to sub-L1 pointrdquoAerospace Science and Technology vol15 no 7 pp 544ndash554 2011
[6] S Gong J Li and H Baoyin ldquoAnalysis of displaced solar sailorbits with passive controlrdquo Journal of Guidance Control andDynamics vol 31 no 3 pp 782ndash785 2008
[7] S Gong H Baoyin and J Li ldquoSolar sail three-body transfertrajectory designrdquo Journal of Guidance Control and Dynamicsvol 33 no 3 pp 873ndash886 2010
Mathematical Problems in Engineering 25
[8] S Gong J Li H Baoyin and J Simo ldquoA new solar sail orbitrdquoScience China Technological Sciences vol 55 no 3 pp 848ndash8552012
[9] Y Tsuda O Mori R Funase et al ldquoAchievement of IKAROS-Japanese deep space solar sail demonstration missionrdquo ActaAstronautica vol 82 no 2 pp 183ndash188 2013
[10] L Johnson MWhorton A Heaton R Pinson G Laue and CAdams ldquoNanoSail-D a solar sail demonstration missionrdquo ActaAstronautica vol 68 no 5-6 pp 571ndash575 2011
[11] B Wie and D Murphy ldquoSolar-sail attitude control design for asail flight validation missionrdquo Journal of Spacecraft and Rocketsvol 44 no 4 pp 809ndash821 2007
[12] B Wie D Murphy M Paluszek and S Thomas ldquoRobust atti-tude control systems design for solar sails part 1 propellantlessprimaryACSrdquo inProceedings of the AIAAGuidance Navigationand Control Conference and Exhibit Providence RI USAAugust 2004
[13] B Wie D Murphy M Paluszek and S Thomas ldquoRobust atti-tude control systems design for solar sails part 2 MicroPPT-based secondary ACSrdquo in Proceedings of the AIAA GuidanceNavigation and Control Conference and Exhibit pp 1325ndash1340Providence RI USA August 2004
[14] S Thomas M Paluszek B Wie and D Murphy ldquoAOCS per-formance and stability validation for large flexible solar sailspacecraftrdquo in Proceedings of the 41st AIAAASMESAEASEEJoint Propulsion Conference amp Exhibit Tucson Ariz USA 2005
[15] B Wie ldquoDynamic modeling and attitude control of solar sailspacecraft part Irdquo in Proceedings of the AIAAGuidance Naviga-tion and Control Conference and Exhibit Monterey Calif USAAugust 2002
[16] BWie ldquoSolar sail attitude control and dynamics part 1rdquo Journalof Guidance Control and Dynamics vol 27 no 4 pp 526ndash5352004
[17] B Wie ldquoDynamic modeling and attitude control of solar sailspacecraft part IIrdquo in Proceedings of the AIAA Guidance Nav-igation and Control Conference and Exhibit Monterey CalifUSA August 2002
[18] BWie ldquoSolar sail attitude control and dynamics part 2rdquo Journalof Guidance Control and Dynamics vol 27 no 4 pp 536ndash5442004
[19] C Luo and J-H Zheng ldquoSolar-sail attitude control based onmoving masses and roll stabilizer barsrdquo Journal of HarbinInstitute of Technology vol 43 no 3 pp 95ndash101 2011
[20] D Romagnoli and T Oehlschlagel ldquoHigh performance twodegrees of freedom attitude control for solar sailsrdquo Advances inSpace Research vol 48 no 11 pp 1869ndash1879 2011
[21] C Scholz D Romagnoli B Dachwald and S Theil ldquoPerfor-mance analysis of an attitude control system for solar sails usingsliding massesrdquo Advances in Space Research vol 48 no 11 pp1822ndash1835 2011
[22] A Bolle and C Circi ldquoSolar sail attitude control through in-plane moving massesrdquo Journal of Aerospace Engineering vol222 no 1 pp 81ndash94 2008
[23] M RotunnoM Basso A B Pome andM Sallusti ldquoA compari-son of robust attitude control techniques for a solar sail space-craftrdquo in Proceedings of the AIAA Guidance Navigation andControl Conference and Exhibit San Francisco Calif USA2005
[24] J Zhang K Zhai and T Wang ldquoControl of large angle maneu-vers for the flexible solar sailrdquo Science China Physics Mechanicsand Astronomy vol 54 no 4 pp 770ndash776 2011
[25] J Zhang andTWang ldquoCoupled attitude-orbit control of flexiblesolar sail for displaced solar orbitrdquo Journal of Spacecraft andRockets vol 50 no 3 pp 675ndash685 2013
[26] Q Li XMa and TWang ldquoReducedmodel for flexible solar saildynamicsrdquo Journal of Spacecraft and Rockets vol 48 no 3 pp446ndash453 2011
[27] M Polites J Kalmanson and D Mangus ldquoSolar sail attitudecontrol using small reaction wheels and magnetic torquersrdquoProceedings of the Institution of Mechanical Engineers G Journalof Aerospace Engineering vol 222 no 1 pp 53ndash62 2008
[28] H-T Cui J-H Luo J-H Feng and P-Y Cui ldquoAttitudecontrol of solar sail spacecraft with control boomrdquo Journal ofAstronautics vol 29 no 2 pp 560ndash566 2008
[29] E Mettler and S R Ploen ldquoSolar sail dynamics and controlusing a boom mounted bus articulated by a bi-state two-axisgimbal and reaction wheelsrdquo in Proceedings of the AIAAAASAstrodynamics Specialist Conference and Exhibit MontereyCalif USA August 2002
[30] J Luo X Li and J Feng ldquoPassive attitude control of solar sailspacecraftrdquo Flight Dynamics vol 26 no 5 pp 47ndash50 2008
[31] J Luo Study on attitude control of solar sail spaceraft [PhDthesis] School of Astronautics Harbin Institute of TechnologyHarbin China 2007
[32] D A Lawrence and S W Piggott ldquoIntegrated trajectory andattitude control for a four-vane solar sailrdquo in Proceedings ofthe AIAA Guidance Navigation and Control Conference andExhibit pp 2416ndash2431 San Francisco Calif USA August 2005
[33] E Mettler A B Acikmese and S R Ploen ldquoAttitude dynamicsand control of solar sails with articulated vanesrdquo in Proceedingsof the AIAA Guidance Navigation and Control Conference andExhibit pp 2396ndash2415 San Francisco Calif USA August 2005
[34] S N Adeli V J Lappas and B Wie ldquoA scalable bus-basedattitude control system for Solar Sailsrdquo Advances in SpaceResearch vol 48 no 11 pp 1836ndash1847 2011
[35] R Funase Y Shirasawa Y Mimasu et al ldquoOn-orbit verificationof fuel-free attitude control system for spinning solar sailutilizing solar radiation pressurerdquo Advances in Space Researchvol 48 no 11 pp 1740ndash1746 2011
[36] B Fu and F O Eke ldquoAttitude control methodology for largesolar sailsrdquo in AIAA Guidance Navigation and Control (GNC)Conference 2013
[37] J Liu N Cui F Shen and S Rong ldquoDynamics of highly-flexiblesolar sail subjected to various forcesrdquoActaAstronautica vol 103pp 55ndash72 2014
[38] J F Liu S Y Rong and J G Li ldquoAttitude dynamics modelingand control of large flexible solar sail spacecraftrdquo in Proceedingsof the 3rd International Symposium on Systems and Control inAeronautics and Astronautics (ISSCAA rsquo10) pp 243ndash247 IEEEPublications Piscataway NJ USA 2010
[39] S Gong H Baoyin and J Li ldquoCoupled attitude-orbit dynamicsand control for displaced solar orbitsrdquo Acta Astronautica vol65 no 5-6 pp 730ndash737 2009
Submit your manuscripts athttpwwwhindawicom
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
MathematicsJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Mathematical Problems in Engineering
Hindawi Publishing Corporationhttpwwwhindawicom
Differential EquationsInternational Journal of
Volume 2014
Applied MathematicsJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Probability and StatisticsHindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Journal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Mathematical PhysicsAdvances in
Complex AnalysisJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
OptimizationJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
CombinatoricsHindawi Publishing Corporationhttpwwwhindawicom Volume 2014
International Journal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Operations ResearchAdvances in
Journal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Function Spaces
Abstract and Applied AnalysisHindawi Publishing Corporationhttpwwwhindawicom Volume 2014
International Journal of Mathematics and Mathematical Sciences
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
The Scientific World JournalHindawi Publishing Corporation httpwwwhindawicom Volume 2014
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Algebra
Discrete Dynamics in Nature and Society
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Decision SciencesAdvances in
Discrete MathematicsJournal of
Hindawi Publishing Corporationhttpwwwhindawicom
Volume 2014 Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Stochastic AnalysisInternational Journal of
16 Mathematical Problems in Engineering
0 2000 4000 6000
0 2000 4000 6000
0 2000 4000 6000minus5
0
5
minus5
0
5
minus5
0
5
minus4
minus2
0
2
4
times10minus4
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
00162
00164
00166
4800 4900 5000
4800 4900 5000
4800 4900 5000
minus00165
minus0016
Time (s) Time (s)
Time (s)
Time (s)
Time (s)
Time (s)
Roll
erro
r120593(∘
)
Roll
erro
r120593(∘
)
Pitc
h er
ror120579
(∘)
Pitc
h er
ror120579
(∘)
Yaw
erro
r120595(∘
)
Yaw
erro
r120595(∘
)
Figure 8 The roll pitch and yaw errors
be achieved by using both the LQR based and optimal PIbased controllers for the coupled attitudevibration dynamicsystem The fact is that the attitude control ability is limitedto the control torque by the control actuators The change ofthe attitude angles and rates should not be frequent to voidexciting vibrations
Thus the weighting matrix Q and the control weightingmatrix R are selected as follows for LQR based controller
Q (1 1) = 9 times 10minus6
Q (2 2) = 1 times 10minus6
Q (3 3) = 16 times 10minus6
Q (4 4) = Q (5 5) = Q (6 6) = Q (7 7) = Q (8 8)
= Q (9 9) = Q (10 10) = 1 times 10minus6
Q (119894 119895) = 0 (119894 = 119895 119894 119895 = 1 sim 10)
R (1 1) = R (2 2) = 900 R (3 3) = 100
R (4 4) = R (5 5) = 10000
R119894119895
= 0 (119894 = 119895 119894 119895 = 1 sim 5)
(75)
TheweightingmatrixQ and the control weightingmatrixR are selected as follows for the optimal PI based controller
Q (1 1) = Q (2 2) = 4 times 10minus8
Q (3 3) = Q (4 4) = Q (5 5) = Q (6 6) = Q (7 7)
= Q (8 8) = 16 times 10minus8
Mathematical Problems in Engineering 17
minus02
0
02
Roll
rate
(∘s)
Roll
rate
(∘s)
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Pitc
h ra
te(∘s)
Pitc
h ra
te(∘s)
0 1000 2000 3000 4000 5000
minus05
0
05
minus05
0
05
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
Time (s)
Yaw
rate
(∘
s)
Yaw
rate
(∘
s)
4800 4850 4900 4950 5000
Time (s)4800 4850 4900 4950 5000
Time (s)4800 4850 4900 4950 5000
minus2
0
2
minus2
0
2
minus2
0
2
times10minus4
times10minus4
times10minus4
Figure 9 The roll pitch and yaw rates
Q (9 9) = Q (10 10) = 1 times 10minus8
Q (119894 119895) = 0 (119894 = 119895 119894 119895 = 1 sim 10)
R (1 1) = R (2 2) = R (3 3) = 1 times 10minus8
R (4 4) = R (5 5) = 4 times 10minus8
R (119894 119895) = 0 (119894 = 119895 119894 119895 = 1 sim 5)
(76)
52 The Simulation Results The initial angle errors of rollpitch and yaw are adopted as 120593(119905
0) = 3
∘ 120579(1199050) = 3
∘ and120595(119905
0) = 3
∘ the initial angular velocity errors of roll pitchand yaw are adopted as (119905
0) = 0
∘
s 120579(1199050) = 0
∘
s and(119905
0) = 0
∘
s 1198811(1199050) = 01m 119881
2(1199050) = 01m
1(1199050) = 0ms
and 2(1199050) = 0ms are adopted in this paper for dynamic
simulationThe estimated cmcp offset is 025m for a 100 times 100m
square solar sail It is assumed that the components of cmcpoffset vector are [0 017678 017678]
119879 in the body frame
The relevant parameters for dynamic simulations are givenin Table 1
The dynamic simulation results are obtained as followsby using the LQR controller based on the abovementionedQ and R related parameters and initial conditions Thedynamics simulations with (denoted by ldquowith GFrdquo) andwithout (denoted by ldquowithout GFrdquo) considering the geo-metrical nonlinearity are presented And the correspondingdiscussions and analysis are also given according to thecalculated results
The roll pitch and yaw errors are presented based onthe dynamics models with and without considering thegeometrical nonlinearityThe control effect with zero steady-state error can be achieved for roll axis by referring tothe results But the steady-state errors exist for pitch andyaw axes from Figure 8 this is because there exist constantdisturbance torques for pitch and yaw axes caused by thecmcp offset Thus the LQR based controller cannot be usedfor attitude control with good steady-state performance Thesteady-state errors of pitch and yaw axes are about 0164
∘
and minus0164∘ respectively from the corresponding partial
enlarged drawing of the figures (see the corresponding left
18 Mathematical Problems in Engineering
minus20
0
20
Roll
torq
ue (N
lowastm
)
Roll
torq
ue (N
lowastm
)
minus50
0
50
minus50
0
50
Pitc
h to
rque
(Nlowast
m)
Pitc
h to
rque
(Nlowast
m)
0 1000 2000 3000 4000 5000
0 2000 4000 6000
0 2000 4000 6000
Yaw
torq
ue (N
lowastm
)
Yaw
torq
ue (N
lowastm
)
minus002
0
002
008
01
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
minus01
minus009
minus008
Time (s)Time (s)
Time (s)Time (s)
Time (s)Time (s)
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Figure 10 The roll pitch and yaw torques
figures) A simple and practical controller should be designedto eliminate the steady-state errorsThese errorswill affect theprecision of the super long duration space mission deeply
The differences between the dynamics with and withoutthe geometrical nonlinearity effect can be observed Theamplitudes and phases change a bit by comparing the corre-sponding results
It can be observed by the partial enlarged figures(the right figures of Figure 9) that there are no steady-stateerrors for roll pitch and yaw rates The relative satisfieddynamic performance is achieved In fact a result with muchmore satisfied dynamic performance can be obtained but itwill make the desired control torques much larger duringthe initial period This will not only excite the vibration ofthe structure but also increase the burden of the controlactuators
And the differences between the dynamics models withand without the geometrical nonlinearity can also be seenmerely in the phase of the angular velocities
The desired attitude control torques are presented inFigure 10 The roll torque will tend to be zero with thedecrement of the state variable errors The pitch and yawtorques tend to be constant from the middle and bottom
figures The pitch and yaw steady-state errors can never beeliminated although the pitch and yaw torques (009Nlowastmand minus009Nlowastm) are applied continuously by theoreticalanalysis and simulations This is just a great disadvantage ofthe LQR based controller in this paper The initial controltorques can be afforded by vibrating the gimbaled controlboom andmoving the slidingmasses that can afford a relativelarge torque The control vanes can be used to afford thecontrol torques when solar sail is in steady-state process Theexpression of the attitude control inputs 119906
120593 119906
120579 and 119906
120595can be
found in previous sectionMoreover the differences between dynamics responses
with and without geometrical nonlinearity can also beobserved by comparing the corresponding results Therequired torques for the attitude control are a little largerfor the dynamics with geometrical nonlinearity And thedifference in the phase is also clear
It can be seen that the vibration of the supporting beamis depressed effectively by the simulation results in Figure 11It can be seen that the steady-state errors and the dynamicperformance are relatively satisfied It can also be seen that thedynamics responses between the model with and without the
Mathematical Problems in Engineering 19
0 1000 2000 3000 4000 5000
0 1000 2000 3000 4000 5000
minus01
0
01
minus02
0
02
Time (s) Time (s)
Time (s) Time (s)
minus5
0
5
times10minus4
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
minus1
0
1
times10minus3
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
The d
ispla
cem
ent o
f the
tip
(m)
The d
ispla
cem
ent o
f the
tip
(m)
The v
eloci
ty o
f the
tip
(ms
)
The v
eloc
ity o
f the
tip
(ms
)
Figure 11 The displacement and velocity of the tip of the supporting beam
geometrical nonlinearity effect are different in the vibrationdisplacement and velocitymagnitudes and phases (Figure 15)
The simulation results can be obtained as follows by usingthe optimal PI based controller adopting the abovementionedparameters and initial conditions
The roll pitch and yaw errors are given by using theoptimal PI based controller These errors tend to disappearby observing the partially enlarged plotting of the figure (thecorresponding right figures) (shown in Figure 12) And therelative satisfied dynamic performance can also be obtainedFrom the view of eliminating the steady-state errors the opti-mal PI based controller performs better than the LQR basedcontroller by theoretical analysis and simulation results Theformer can achieve attitude control results without pitchand yaw steady-state errors From the view of dynamicperformance both the controllers perform well In additionit can be seen that the difference between the modelswith and without geometrical nonlinearity is merely inthe phase
The roll pitch and yaw rate errors are presented inFigure 13 The dynamic and steady-state performances aresatisfied by observing the simulation results And by observ-ing the difference between the dynamics responses with and
without the influence by the geometrical nonlinearity it canbe concluded that the merely difference is the phase
The desired control torques of the roll pitch and yaw areobtained in Figure 14 by using the optimal PI based controllerIt can be seen that the value of the desired roll control torquedecreases to zero as the values of the roll angle and ratedecrease to zero The desired pitch and yaw control torquestend to be the constant values 009Nlowastm and minus009Nlowastmrespectively The desired initial control torques are large byobserving Figure 14 It is suggested that the gimbaled controlboom combining the sliding masses is adopted to afford theinitial torque Then the control vanes can be used to controlthe solar sail after the initial phase The phase differencecan also be observed by inspecting the dynamics responsesduring the 4800sim5000 s period
The vibration can be controlled effectively based on theoptimal PI controller And the relative satisfied dynamicand steady-state performances can be achieved In additionthe tiny differences exist in the magnitudes of the requiredtorques And the phase differences also exist
It can be concluded as follows by analyzing and compar-ing the simulation results based on the LQR and optimal PItheories in detail
20 Mathematical Problems in Engineering
Roll
erro
r120593(∘
)
Roll
erro
r120593(∘
)
minus5
0
5
minus5
0
5
Pitc
h er
ror120579
(∘)
Pitc
h er
ror120579
(∘)
0 1000 2000 3000 4000 5000minus10
0
10
Time (s) Time (s)
Time (s)
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
Yaw
erro
r120595(∘
)
Yaw
erro
r120595(∘
)
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
minus1
0
1
times10minus3
minus1
0
1
times10minus3
minus1
0
1
times10minus3
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Figure 12 The roll pitch and yaw errors
(1) From the view of eliminating the steady-state errorsof the pitch and yaw errors the optimal PI based con-troller performs better than the LQR based controllerby theoretical analysis and simulation results Thedynamic performances of the two controllers are bothsatisfied and the desired control torques are relativelysmall
(2) The weighting of the state variables is reflected by theweighting matrix according to the LQR and optimalPI theories The constant weighting matrices selectedin this paper can effectively reflect the initial statevariable errors but maybe reflect the final state vari-able errors deficiently The time-varying weightingmatrices should be selected
(3) For the actual orbiting solar sail the control actuators(control vanes gimbaled control boom and slidingmasses) cannot afford excessive large control torquesThus the control torques should be as small as possibleon the premise of acquiring satisfied dynamic perfor-mance and steady-state errors It will not only reducethe burden of the control actuators but also avoid
exciting structural vibration In engineering practicethe weighting matrices and the control weightingmatrices should be selected based on the attitudecontrol requirement (eg dynamic performance andsteady-state errors etc)
(4) The dynamics responses influenced by the geometri-cal nonlinearity can be observed In a word the tinydifferences between the magnitudes of the physicalvariables exist for the models with and withoutthe geometrical nonlinearity And the relative cleardifferences exist in the phases for the attitude anglesrates required torques and so forth
6 Conclusions
The coupled attitude and structural dynamics is establishedfor the highly flexible sailcraft by using the von-Karman von-Karmanrsquos nonlinear strain-displacement relationships basedon assumptions of large deflections moderate rotationsand
Mathematical Problems in Engineering 21
Roll
rate
erro
r(∘ s
)
Roll
rate
erro
r(∘ s
)
minus01
0
01
minus01
0
01
Pitc
h ra
te er
ror (
∘ s)
Pitc
h ra
te er
ror (
∘ s)
0 1000 2000 3000 4000 5000minus02
0
02
Yaw
rate
erro
r (∘ s
)
Yaw
rate
erro
r (∘ s
)
4800 4850 4900 4950 5000
minus5
0
5times10minus4
minus5
0
5
times10minus4
minus5
0
5times10minus4
Time (s)
4800 4850 4900 4950 5000
Time (s)
4800 4850 4900 4950 5000
Time (s)
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Figure 13 The roll pitch and yaw rate errors
small strains The Lagrange equation method is utilizedto derive the dynamics for controller design and dynamicsimulation The LQR and optimal PI based controllers aredesigned for the dynamics with the constant disturbancetorque caused by the cmcp offset By theoretical analysisand simulation it can be seen that both controllers cancompromise between the state variables and control inputsBecause the control actuators can hardly afford large controltorque the dynamic performance should be relaxed toreduce the requirement for the attitude control actuatorsBesides the optimal PI based controller can also eliminatethe constant disturbance torque caused by the cmcp offsetthat always exists while the LQR based controller fails toachieve the results with satisfied steady-state performancealthough the attitude control torque is always applied to thecoupled dynamic systemThe dynamics simulations with andwithout the geometrical nonlinearity effect are also carriedout And the differences between the models in magnitudesand phases are identified and analyzed It can be concludedthat the optimal PI based controller performs better than the
LQRbased controller from the viewof eliminating the steady-state error caused by the disturbance torque by the cmcpoffset
Appendix
The related parameters in above equation are given as
119886120593= 119869
119909+ 119898
ℎ11199102
ℎ1
+ 119898ℎ21199112
ℎ2
+ 1198981199011199032
119901119911
+ 1198981199011199032
119901119910
119886120579= minus 119898
119901119903119901119909119903119901119910 119886
120595= minus119898
119901119903119901119909119903119901119911
1198861198811
= minus 1198981198971198972
1198861198812
= minus4
5119898
1198971198972
119887120579= 119869
119910+ 119898
ℎ21199112
ℎ2
+ 1198981199011199032
119901119911
+ 1198981199011199032
119901119909
119887120595= minus 119898
119901119903119901119910119903119901119911 119887
120593= minus119898
119901119903119901119909119903119901119910
22 Mathematical Problems in Engineering
Roll
torq
ue (N
lowastm
)
Roll
torq
ue (N
lowastm
)
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
0 2000 4000 6000
0 2000 4000 6000
0 2000 4000 6000
Time (s)
Time (s)
Time (s)
Time (s)
Time (s)
Time (s)4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
minus01
minus008
008
009
01
minus002
0
002
minus5
0
5
minus2
0
2
Pitc
h to
rque
(Nlowast
m)
Pitc
h to
rque
(Nlowast
m)
minus2
0
2
Yaw
torq
ue (N
lowastm
)
Yaw
torq
ue (N
lowastm
)
Figure 14 The roll pitch and yaw torques
1198871198811
=1
2119898
1198971198972
1198871198812
=2
5119898
1198971198972
119888120595= 119869
119911+ 119898
ℎ11199102
ℎ1
+ 1198981199011199032
119901119910
+ 1198981199011199032
119901119909
119888120579= minus 119898
119901119903119901119910119903119901119911 119888
120593= minus119898
119901119903119901119909119903119901119911
1198881198811
= minus1
21198972
119898119897 119888
1198812
= minus2
51198972
119898119897
119889
1198811
= (4
3
119868119863
119897+
1
5119897119868119860) 119889
1198812
= (1
6119897119868119860+
3119868119863
2119897)
119889
1198811
=4120578
119887119863
119909119909
1198973 119889
1198812
=6120578
119887119863
119909119909
1198973
1198891198811
=4119863
119909119909
1198973 119889
1198812
=6119863
119909119909
1198973
1198761198811
= 1198651198621
(119905)
119890
1198811
= (3
2
119868119863
119897+
1
6119897119868119860)
119890
1198812
= (1
7119897119868119860+
9
5
119868119863
119897) 119890
1198811
=6120578
119887119863
119909119909
1198973
119890
1198812
=12120578
119887119863
119909119909
1198973 119890
1198811
=6119863
119909119909
1198973
1198901198812
=12119863
119909119909
1198973 119876
1198812
= 1198651198622
(119905)
(A1)
The detailed expressions of control inputs for attitudevibration and related parameters in the state-space model ofthe dynamics (see (62) and (63)) are presented as follows
A =
[[[[[[[[[[[[[[
[
0 1 0 0 0 0 0 0 0 0
0 0 0 0 0 0 1198861
1198862
1198863
1198864
0 0 0 1 0 0 0 0 0 0
0 0 0 0 0 0 1198865
1198866
1198867
1198868
0 0 0 0 0 1 0 0 0 0
0 0 0 0 0 0 1198869
11988610
11988611
11988612
0 0 0 0 0 0 0 1 0 0
0 0 0 0 0 0 11988613
11988614
11988615
11988616
0 0 0 0 0 0 0 0 0 1
0 0 0 0 0 0 11988617
11988618
11988619
11988620
]]]]]]]]]]]]]]
]
Mathematical Problems in Engineering 23
0 1000 2000 3000 4000 5000
0 1000 2000 3000 4000 5000
minus01
0
01
minus02
0
02
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Time (s)
Time (s)Time (s)
Time (s)
minus1
0
1
minus1
0
1
times10minus3
times10minus3Th
e disp
lace
men
t of t
he ti
p (m
)
The d
ispla
cem
ent o
f the
tip
(m)
The v
eloci
ty o
f the
tip
(ms
)
The v
eloci
ty o
f the
tip
(ms
)
Figure 15 Vibration displacement and velocity of the tip
B =
[[[[[[[[[[[[[[
[
0 0 0 0 0
1 0 0 0 0
0 0 0 0 0
0 1 0 0 0
0 0 0 0 0
0 0 1 0 0
0 0 0 0 0
0 0 0 1 0
0 0 0 0 0
0 0 0 0 1
]]]]]]]]]]]]]]
]
1198861= minus
1198981198971198972
119869119909
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus4
5119869119909
1198981198971198972
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198862= minus
1198981198971198972
119869119909
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus4
5119869119909
1198981198971198972
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198863= minus
1198981198971198972
119869119909
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus4
5119869119909
1198981198971198972
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198864= minus
1198981198971198972
119869119909
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus4
5119869119909
1198981198971198972
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
119906120593=
119876120593
119869119909
+
119906
119869119909
+119898
1198971198972
119869119909
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+4
5119869119909
1198981198971198972
+
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198865=
1
2119869119910
1198981198971198972
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+2
5119869119910
1198981198971198972
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198866=
1
2119869119910
1198981198971198972
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+2
5119869119910
1198981198971198972
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198867=
1
2119869119910
1198981198971198972
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+2
5119869119910
1198981198971198972
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198868=
1
2119869119910
1198981198971198972
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
24 Mathematical Problems in Engineering
+2
5119869119910
1198981198971198972
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
119906120579=
119876120579
119869119910
+119906
120579
119869119910
minus1
2119869119910
1198981198971198972
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119910
1198981198971198972
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198869= minus
1
2119869119911
1198972
119898119897
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988610
= minus1
2119869119911
1198972
119898119897
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988611
= minus1
2119869119911
1198972
119898119897
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988612
= minus1
2119869119911
1198972
119898119897
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
119906120595=
119876120595
119869119911
+
119906
119869119911
+1
2119869119911
1198972
119898119897
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+2
5119869119911
1198972
119898119897
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988613
= minus
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988614
= minus
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988615
= minus
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988616
= minus
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
1199061198811
=
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988617
= minus
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988618
= minus
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988619
= minus
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988620
= minus
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1199061198812
=
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(A2)
Conflict of Interests
The authors declare that there is no conflict of interestsregarding the publication of this paper
Acknowledgments
The authors would like to thank the anonymous reviewers fortheir critical and constructive review of the paper This studywas cosupported by the National Natural Science Foundationof China (Project no 11302134 11272101)
References
[1] M Colin Solar Sailing Technology Dynamics and MissionApplications Springer-Praxis London UK 1st edition 1999
[2] V Lappas SWokesM Leipold A Lyngvi and P Falkner ldquoGui-dance and control for an Interstellar Heliopause Probe (IHP)solar sail mission to 200 AUrdquo in Proceedings of the AIAAGuidance Navigation and Control Conference and Exhibit pp2472ndash2492 San Francisco Calif USA August 2005
[3] L Charlotte C Camilla and C McInnes ldquoSolar radiation pres-sure augmented deorbiting fromhigh altitude sun-synchronousorbitsrdquo in Proceedings of the 4S Symposium 2012 Small SatellitesSystems and Services Portoroz Slovenia 2012
[4] M Ceriotti and C RMcInnes ldquoGeneration of optimal trajecto-ries for Earth hybrid pole sittersrdquo Journal of Guidance Controland Dynamics vol 34 no 3 pp 847ndash859 2011
[5] S Gong J Li andH Baoyin ldquoSolar sail transfer trajectory fromL1 point to sub-L1 pointrdquoAerospace Science and Technology vol15 no 7 pp 544ndash554 2011
[6] S Gong J Li and H Baoyin ldquoAnalysis of displaced solar sailorbits with passive controlrdquo Journal of Guidance Control andDynamics vol 31 no 3 pp 782ndash785 2008
[7] S Gong H Baoyin and J Li ldquoSolar sail three-body transfertrajectory designrdquo Journal of Guidance Control and Dynamicsvol 33 no 3 pp 873ndash886 2010
Mathematical Problems in Engineering 25
[8] S Gong J Li H Baoyin and J Simo ldquoA new solar sail orbitrdquoScience China Technological Sciences vol 55 no 3 pp 848ndash8552012
[9] Y Tsuda O Mori R Funase et al ldquoAchievement of IKAROS-Japanese deep space solar sail demonstration missionrdquo ActaAstronautica vol 82 no 2 pp 183ndash188 2013
[10] L Johnson MWhorton A Heaton R Pinson G Laue and CAdams ldquoNanoSail-D a solar sail demonstration missionrdquo ActaAstronautica vol 68 no 5-6 pp 571ndash575 2011
[11] B Wie and D Murphy ldquoSolar-sail attitude control design for asail flight validation missionrdquo Journal of Spacecraft and Rocketsvol 44 no 4 pp 809ndash821 2007
[12] B Wie D Murphy M Paluszek and S Thomas ldquoRobust atti-tude control systems design for solar sails part 1 propellantlessprimaryACSrdquo inProceedings of the AIAAGuidance Navigationand Control Conference and Exhibit Providence RI USAAugust 2004
[13] B Wie D Murphy M Paluszek and S Thomas ldquoRobust atti-tude control systems design for solar sails part 2 MicroPPT-based secondary ACSrdquo in Proceedings of the AIAA GuidanceNavigation and Control Conference and Exhibit pp 1325ndash1340Providence RI USA August 2004
[14] S Thomas M Paluszek B Wie and D Murphy ldquoAOCS per-formance and stability validation for large flexible solar sailspacecraftrdquo in Proceedings of the 41st AIAAASMESAEASEEJoint Propulsion Conference amp Exhibit Tucson Ariz USA 2005
[15] B Wie ldquoDynamic modeling and attitude control of solar sailspacecraft part Irdquo in Proceedings of the AIAAGuidance Naviga-tion and Control Conference and Exhibit Monterey Calif USAAugust 2002
[16] BWie ldquoSolar sail attitude control and dynamics part 1rdquo Journalof Guidance Control and Dynamics vol 27 no 4 pp 526ndash5352004
[17] B Wie ldquoDynamic modeling and attitude control of solar sailspacecraft part IIrdquo in Proceedings of the AIAA Guidance Nav-igation and Control Conference and Exhibit Monterey CalifUSA August 2002
[18] BWie ldquoSolar sail attitude control and dynamics part 2rdquo Journalof Guidance Control and Dynamics vol 27 no 4 pp 536ndash5442004
[19] C Luo and J-H Zheng ldquoSolar-sail attitude control based onmoving masses and roll stabilizer barsrdquo Journal of HarbinInstitute of Technology vol 43 no 3 pp 95ndash101 2011
[20] D Romagnoli and T Oehlschlagel ldquoHigh performance twodegrees of freedom attitude control for solar sailsrdquo Advances inSpace Research vol 48 no 11 pp 1869ndash1879 2011
[21] C Scholz D Romagnoli B Dachwald and S Theil ldquoPerfor-mance analysis of an attitude control system for solar sails usingsliding massesrdquo Advances in Space Research vol 48 no 11 pp1822ndash1835 2011
[22] A Bolle and C Circi ldquoSolar sail attitude control through in-plane moving massesrdquo Journal of Aerospace Engineering vol222 no 1 pp 81ndash94 2008
[23] M RotunnoM Basso A B Pome andM Sallusti ldquoA compari-son of robust attitude control techniques for a solar sail space-craftrdquo in Proceedings of the AIAA Guidance Navigation andControl Conference and Exhibit San Francisco Calif USA2005
[24] J Zhang K Zhai and T Wang ldquoControl of large angle maneu-vers for the flexible solar sailrdquo Science China Physics Mechanicsand Astronomy vol 54 no 4 pp 770ndash776 2011
[25] J Zhang andTWang ldquoCoupled attitude-orbit control of flexiblesolar sail for displaced solar orbitrdquo Journal of Spacecraft andRockets vol 50 no 3 pp 675ndash685 2013
[26] Q Li XMa and TWang ldquoReducedmodel for flexible solar saildynamicsrdquo Journal of Spacecraft and Rockets vol 48 no 3 pp446ndash453 2011
[27] M Polites J Kalmanson and D Mangus ldquoSolar sail attitudecontrol using small reaction wheels and magnetic torquersrdquoProceedings of the Institution of Mechanical Engineers G Journalof Aerospace Engineering vol 222 no 1 pp 53ndash62 2008
[28] H-T Cui J-H Luo J-H Feng and P-Y Cui ldquoAttitudecontrol of solar sail spacecraft with control boomrdquo Journal ofAstronautics vol 29 no 2 pp 560ndash566 2008
[29] E Mettler and S R Ploen ldquoSolar sail dynamics and controlusing a boom mounted bus articulated by a bi-state two-axisgimbal and reaction wheelsrdquo in Proceedings of the AIAAAASAstrodynamics Specialist Conference and Exhibit MontereyCalif USA August 2002
[30] J Luo X Li and J Feng ldquoPassive attitude control of solar sailspacecraftrdquo Flight Dynamics vol 26 no 5 pp 47ndash50 2008
[31] J Luo Study on attitude control of solar sail spaceraft [PhDthesis] School of Astronautics Harbin Institute of TechnologyHarbin China 2007
[32] D A Lawrence and S W Piggott ldquoIntegrated trajectory andattitude control for a four-vane solar sailrdquo in Proceedings ofthe AIAA Guidance Navigation and Control Conference andExhibit pp 2416ndash2431 San Francisco Calif USA August 2005
[33] E Mettler A B Acikmese and S R Ploen ldquoAttitude dynamicsand control of solar sails with articulated vanesrdquo in Proceedingsof the AIAA Guidance Navigation and Control Conference andExhibit pp 2396ndash2415 San Francisco Calif USA August 2005
[34] S N Adeli V J Lappas and B Wie ldquoA scalable bus-basedattitude control system for Solar Sailsrdquo Advances in SpaceResearch vol 48 no 11 pp 1836ndash1847 2011
[35] R Funase Y Shirasawa Y Mimasu et al ldquoOn-orbit verificationof fuel-free attitude control system for spinning solar sailutilizing solar radiation pressurerdquo Advances in Space Researchvol 48 no 11 pp 1740ndash1746 2011
[36] B Fu and F O Eke ldquoAttitude control methodology for largesolar sailsrdquo in AIAA Guidance Navigation and Control (GNC)Conference 2013
[37] J Liu N Cui F Shen and S Rong ldquoDynamics of highly-flexiblesolar sail subjected to various forcesrdquoActaAstronautica vol 103pp 55ndash72 2014
[38] J F Liu S Y Rong and J G Li ldquoAttitude dynamics modelingand control of large flexible solar sail spacecraftrdquo in Proceedingsof the 3rd International Symposium on Systems and Control inAeronautics and Astronautics (ISSCAA rsquo10) pp 243ndash247 IEEEPublications Piscataway NJ USA 2010
[39] S Gong H Baoyin and J Li ldquoCoupled attitude-orbit dynamicsand control for displaced solar orbitsrdquo Acta Astronautica vol65 no 5-6 pp 730ndash737 2009
Submit your manuscripts athttpwwwhindawicom
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
MathematicsJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Mathematical Problems in Engineering
Hindawi Publishing Corporationhttpwwwhindawicom
Differential EquationsInternational Journal of
Volume 2014
Applied MathematicsJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Probability and StatisticsHindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Journal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Mathematical PhysicsAdvances in
Complex AnalysisJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
OptimizationJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
CombinatoricsHindawi Publishing Corporationhttpwwwhindawicom Volume 2014
International Journal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Operations ResearchAdvances in
Journal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Function Spaces
Abstract and Applied AnalysisHindawi Publishing Corporationhttpwwwhindawicom Volume 2014
International Journal of Mathematics and Mathematical Sciences
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
The Scientific World JournalHindawi Publishing Corporation httpwwwhindawicom Volume 2014
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Algebra
Discrete Dynamics in Nature and Society
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Decision SciencesAdvances in
Discrete MathematicsJournal of
Hindawi Publishing Corporationhttpwwwhindawicom
Volume 2014 Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Stochastic AnalysisInternational Journal of
Mathematical Problems in Engineering 17
minus02
0
02
Roll
rate
(∘s)
Roll
rate
(∘s)
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Pitc
h ra
te(∘s)
Pitc
h ra
te(∘s)
0 1000 2000 3000 4000 5000
minus05
0
05
minus05
0
05
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
Time (s)
Yaw
rate
(∘
s)
Yaw
rate
(∘
s)
4800 4850 4900 4950 5000
Time (s)4800 4850 4900 4950 5000
Time (s)4800 4850 4900 4950 5000
minus2
0
2
minus2
0
2
minus2
0
2
times10minus4
times10minus4
times10minus4
Figure 9 The roll pitch and yaw rates
Q (9 9) = Q (10 10) = 1 times 10minus8
Q (119894 119895) = 0 (119894 = 119895 119894 119895 = 1 sim 10)
R (1 1) = R (2 2) = R (3 3) = 1 times 10minus8
R (4 4) = R (5 5) = 4 times 10minus8
R (119894 119895) = 0 (119894 = 119895 119894 119895 = 1 sim 5)
(76)
52 The Simulation Results The initial angle errors of rollpitch and yaw are adopted as 120593(119905
0) = 3
∘ 120579(1199050) = 3
∘ and120595(119905
0) = 3
∘ the initial angular velocity errors of roll pitchand yaw are adopted as (119905
0) = 0
∘
s 120579(1199050) = 0
∘
s and(119905
0) = 0
∘
s 1198811(1199050) = 01m 119881
2(1199050) = 01m
1(1199050) = 0ms
and 2(1199050) = 0ms are adopted in this paper for dynamic
simulationThe estimated cmcp offset is 025m for a 100 times 100m
square solar sail It is assumed that the components of cmcpoffset vector are [0 017678 017678]
119879 in the body frame
The relevant parameters for dynamic simulations are givenin Table 1
The dynamic simulation results are obtained as followsby using the LQR controller based on the abovementionedQ and R related parameters and initial conditions Thedynamics simulations with (denoted by ldquowith GFrdquo) andwithout (denoted by ldquowithout GFrdquo) considering the geo-metrical nonlinearity are presented And the correspondingdiscussions and analysis are also given according to thecalculated results
The roll pitch and yaw errors are presented based onthe dynamics models with and without considering thegeometrical nonlinearityThe control effect with zero steady-state error can be achieved for roll axis by referring tothe results But the steady-state errors exist for pitch andyaw axes from Figure 8 this is because there exist constantdisturbance torques for pitch and yaw axes caused by thecmcp offset Thus the LQR based controller cannot be usedfor attitude control with good steady-state performance Thesteady-state errors of pitch and yaw axes are about 0164
∘
and minus0164∘ respectively from the corresponding partial
enlarged drawing of the figures (see the corresponding left
18 Mathematical Problems in Engineering
minus20
0
20
Roll
torq
ue (N
lowastm
)
Roll
torq
ue (N
lowastm
)
minus50
0
50
minus50
0
50
Pitc
h to
rque
(Nlowast
m)
Pitc
h to
rque
(Nlowast
m)
0 1000 2000 3000 4000 5000
0 2000 4000 6000
0 2000 4000 6000
Yaw
torq
ue (N
lowastm
)
Yaw
torq
ue (N
lowastm
)
minus002
0
002
008
01
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
minus01
minus009
minus008
Time (s)Time (s)
Time (s)Time (s)
Time (s)Time (s)
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Figure 10 The roll pitch and yaw torques
figures) A simple and practical controller should be designedto eliminate the steady-state errorsThese errorswill affect theprecision of the super long duration space mission deeply
The differences between the dynamics with and withoutthe geometrical nonlinearity effect can be observed Theamplitudes and phases change a bit by comparing the corre-sponding results
It can be observed by the partial enlarged figures(the right figures of Figure 9) that there are no steady-stateerrors for roll pitch and yaw rates The relative satisfieddynamic performance is achieved In fact a result with muchmore satisfied dynamic performance can be obtained but itwill make the desired control torques much larger duringthe initial period This will not only excite the vibration ofthe structure but also increase the burden of the controlactuators
And the differences between the dynamics models withand without the geometrical nonlinearity can also be seenmerely in the phase of the angular velocities
The desired attitude control torques are presented inFigure 10 The roll torque will tend to be zero with thedecrement of the state variable errors The pitch and yawtorques tend to be constant from the middle and bottom
figures The pitch and yaw steady-state errors can never beeliminated although the pitch and yaw torques (009Nlowastmand minus009Nlowastm) are applied continuously by theoreticalanalysis and simulations This is just a great disadvantage ofthe LQR based controller in this paper The initial controltorques can be afforded by vibrating the gimbaled controlboom andmoving the slidingmasses that can afford a relativelarge torque The control vanes can be used to afford thecontrol torques when solar sail is in steady-state process Theexpression of the attitude control inputs 119906
120593 119906
120579 and 119906
120595can be
found in previous sectionMoreover the differences between dynamics responses
with and without geometrical nonlinearity can also beobserved by comparing the corresponding results Therequired torques for the attitude control are a little largerfor the dynamics with geometrical nonlinearity And thedifference in the phase is also clear
It can be seen that the vibration of the supporting beamis depressed effectively by the simulation results in Figure 11It can be seen that the steady-state errors and the dynamicperformance are relatively satisfied It can also be seen that thedynamics responses between the model with and without the
Mathematical Problems in Engineering 19
0 1000 2000 3000 4000 5000
0 1000 2000 3000 4000 5000
minus01
0
01
minus02
0
02
Time (s) Time (s)
Time (s) Time (s)
minus5
0
5
times10minus4
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
minus1
0
1
times10minus3
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
The d
ispla
cem
ent o
f the
tip
(m)
The d
ispla
cem
ent o
f the
tip
(m)
The v
eloci
ty o
f the
tip
(ms
)
The v
eloc
ity o
f the
tip
(ms
)
Figure 11 The displacement and velocity of the tip of the supporting beam
geometrical nonlinearity effect are different in the vibrationdisplacement and velocitymagnitudes and phases (Figure 15)
The simulation results can be obtained as follows by usingthe optimal PI based controller adopting the abovementionedparameters and initial conditions
The roll pitch and yaw errors are given by using theoptimal PI based controller These errors tend to disappearby observing the partially enlarged plotting of the figure (thecorresponding right figures) (shown in Figure 12) And therelative satisfied dynamic performance can also be obtainedFrom the view of eliminating the steady-state errors the opti-mal PI based controller performs better than the LQR basedcontroller by theoretical analysis and simulation results Theformer can achieve attitude control results without pitchand yaw steady-state errors From the view of dynamicperformance both the controllers perform well In additionit can be seen that the difference between the modelswith and without geometrical nonlinearity is merely inthe phase
The roll pitch and yaw rate errors are presented inFigure 13 The dynamic and steady-state performances aresatisfied by observing the simulation results And by observ-ing the difference between the dynamics responses with and
without the influence by the geometrical nonlinearity it canbe concluded that the merely difference is the phase
The desired control torques of the roll pitch and yaw areobtained in Figure 14 by using the optimal PI based controllerIt can be seen that the value of the desired roll control torquedecreases to zero as the values of the roll angle and ratedecrease to zero The desired pitch and yaw control torquestend to be the constant values 009Nlowastm and minus009Nlowastmrespectively The desired initial control torques are large byobserving Figure 14 It is suggested that the gimbaled controlboom combining the sliding masses is adopted to afford theinitial torque Then the control vanes can be used to controlthe solar sail after the initial phase The phase differencecan also be observed by inspecting the dynamics responsesduring the 4800sim5000 s period
The vibration can be controlled effectively based on theoptimal PI controller And the relative satisfied dynamicand steady-state performances can be achieved In additionthe tiny differences exist in the magnitudes of the requiredtorques And the phase differences also exist
It can be concluded as follows by analyzing and compar-ing the simulation results based on the LQR and optimal PItheories in detail
20 Mathematical Problems in Engineering
Roll
erro
r120593(∘
)
Roll
erro
r120593(∘
)
minus5
0
5
minus5
0
5
Pitc
h er
ror120579
(∘)
Pitc
h er
ror120579
(∘)
0 1000 2000 3000 4000 5000minus10
0
10
Time (s) Time (s)
Time (s)
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
Yaw
erro
r120595(∘
)
Yaw
erro
r120595(∘
)
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
minus1
0
1
times10minus3
minus1
0
1
times10minus3
minus1
0
1
times10minus3
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Figure 12 The roll pitch and yaw errors
(1) From the view of eliminating the steady-state errorsof the pitch and yaw errors the optimal PI based con-troller performs better than the LQR based controllerby theoretical analysis and simulation results Thedynamic performances of the two controllers are bothsatisfied and the desired control torques are relativelysmall
(2) The weighting of the state variables is reflected by theweighting matrix according to the LQR and optimalPI theories The constant weighting matrices selectedin this paper can effectively reflect the initial statevariable errors but maybe reflect the final state vari-able errors deficiently The time-varying weightingmatrices should be selected
(3) For the actual orbiting solar sail the control actuators(control vanes gimbaled control boom and slidingmasses) cannot afford excessive large control torquesThus the control torques should be as small as possibleon the premise of acquiring satisfied dynamic perfor-mance and steady-state errors It will not only reducethe burden of the control actuators but also avoid
exciting structural vibration In engineering practicethe weighting matrices and the control weightingmatrices should be selected based on the attitudecontrol requirement (eg dynamic performance andsteady-state errors etc)
(4) The dynamics responses influenced by the geometri-cal nonlinearity can be observed In a word the tinydifferences between the magnitudes of the physicalvariables exist for the models with and withoutthe geometrical nonlinearity And the relative cleardifferences exist in the phases for the attitude anglesrates required torques and so forth
6 Conclusions
The coupled attitude and structural dynamics is establishedfor the highly flexible sailcraft by using the von-Karman von-Karmanrsquos nonlinear strain-displacement relationships basedon assumptions of large deflections moderate rotationsand
Mathematical Problems in Engineering 21
Roll
rate
erro
r(∘ s
)
Roll
rate
erro
r(∘ s
)
minus01
0
01
minus01
0
01
Pitc
h ra
te er
ror (
∘ s)
Pitc
h ra
te er
ror (
∘ s)
0 1000 2000 3000 4000 5000minus02
0
02
Yaw
rate
erro
r (∘ s
)
Yaw
rate
erro
r (∘ s
)
4800 4850 4900 4950 5000
minus5
0
5times10minus4
minus5
0
5
times10minus4
minus5
0
5times10minus4
Time (s)
4800 4850 4900 4950 5000
Time (s)
4800 4850 4900 4950 5000
Time (s)
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Figure 13 The roll pitch and yaw rate errors
small strains The Lagrange equation method is utilizedto derive the dynamics for controller design and dynamicsimulation The LQR and optimal PI based controllers aredesigned for the dynamics with the constant disturbancetorque caused by the cmcp offset By theoretical analysisand simulation it can be seen that both controllers cancompromise between the state variables and control inputsBecause the control actuators can hardly afford large controltorque the dynamic performance should be relaxed toreduce the requirement for the attitude control actuatorsBesides the optimal PI based controller can also eliminatethe constant disturbance torque caused by the cmcp offsetthat always exists while the LQR based controller fails toachieve the results with satisfied steady-state performancealthough the attitude control torque is always applied to thecoupled dynamic systemThe dynamics simulations with andwithout the geometrical nonlinearity effect are also carriedout And the differences between the models in magnitudesand phases are identified and analyzed It can be concludedthat the optimal PI based controller performs better than the
LQRbased controller from the viewof eliminating the steady-state error caused by the disturbance torque by the cmcpoffset
Appendix
The related parameters in above equation are given as
119886120593= 119869
119909+ 119898
ℎ11199102
ℎ1
+ 119898ℎ21199112
ℎ2
+ 1198981199011199032
119901119911
+ 1198981199011199032
119901119910
119886120579= minus 119898
119901119903119901119909119903119901119910 119886
120595= minus119898
119901119903119901119909119903119901119911
1198861198811
= minus 1198981198971198972
1198861198812
= minus4
5119898
1198971198972
119887120579= 119869
119910+ 119898
ℎ21199112
ℎ2
+ 1198981199011199032
119901119911
+ 1198981199011199032
119901119909
119887120595= minus 119898
119901119903119901119910119903119901119911 119887
120593= minus119898
119901119903119901119909119903119901119910
22 Mathematical Problems in Engineering
Roll
torq
ue (N
lowastm
)
Roll
torq
ue (N
lowastm
)
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
0 2000 4000 6000
0 2000 4000 6000
0 2000 4000 6000
Time (s)
Time (s)
Time (s)
Time (s)
Time (s)
Time (s)4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
minus01
minus008
008
009
01
minus002
0
002
minus5
0
5
minus2
0
2
Pitc
h to
rque
(Nlowast
m)
Pitc
h to
rque
(Nlowast
m)
minus2
0
2
Yaw
torq
ue (N
lowastm
)
Yaw
torq
ue (N
lowastm
)
Figure 14 The roll pitch and yaw torques
1198871198811
=1
2119898
1198971198972
1198871198812
=2
5119898
1198971198972
119888120595= 119869
119911+ 119898
ℎ11199102
ℎ1
+ 1198981199011199032
119901119910
+ 1198981199011199032
119901119909
119888120579= minus 119898
119901119903119901119910119903119901119911 119888
120593= minus119898
119901119903119901119909119903119901119911
1198881198811
= minus1
21198972
119898119897 119888
1198812
= minus2
51198972
119898119897
119889
1198811
= (4
3
119868119863
119897+
1
5119897119868119860) 119889
1198812
= (1
6119897119868119860+
3119868119863
2119897)
119889
1198811
=4120578
119887119863
119909119909
1198973 119889
1198812
=6120578
119887119863
119909119909
1198973
1198891198811
=4119863
119909119909
1198973 119889
1198812
=6119863
119909119909
1198973
1198761198811
= 1198651198621
(119905)
119890
1198811
= (3
2
119868119863
119897+
1
6119897119868119860)
119890
1198812
= (1
7119897119868119860+
9
5
119868119863
119897) 119890
1198811
=6120578
119887119863
119909119909
1198973
119890
1198812
=12120578
119887119863
119909119909
1198973 119890
1198811
=6119863
119909119909
1198973
1198901198812
=12119863
119909119909
1198973 119876
1198812
= 1198651198622
(119905)
(A1)
The detailed expressions of control inputs for attitudevibration and related parameters in the state-space model ofthe dynamics (see (62) and (63)) are presented as follows
A =
[[[[[[[[[[[[[[
[
0 1 0 0 0 0 0 0 0 0
0 0 0 0 0 0 1198861
1198862
1198863
1198864
0 0 0 1 0 0 0 0 0 0
0 0 0 0 0 0 1198865
1198866
1198867
1198868
0 0 0 0 0 1 0 0 0 0
0 0 0 0 0 0 1198869
11988610
11988611
11988612
0 0 0 0 0 0 0 1 0 0
0 0 0 0 0 0 11988613
11988614
11988615
11988616
0 0 0 0 0 0 0 0 0 1
0 0 0 0 0 0 11988617
11988618
11988619
11988620
]]]]]]]]]]]]]]
]
Mathematical Problems in Engineering 23
0 1000 2000 3000 4000 5000
0 1000 2000 3000 4000 5000
minus01
0
01
minus02
0
02
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Time (s)
Time (s)Time (s)
Time (s)
minus1
0
1
minus1
0
1
times10minus3
times10minus3Th
e disp
lace
men
t of t
he ti
p (m
)
The d
ispla
cem
ent o
f the
tip
(m)
The v
eloci
ty o
f the
tip
(ms
)
The v
eloci
ty o
f the
tip
(ms
)
Figure 15 Vibration displacement and velocity of the tip
B =
[[[[[[[[[[[[[[
[
0 0 0 0 0
1 0 0 0 0
0 0 0 0 0
0 1 0 0 0
0 0 0 0 0
0 0 1 0 0
0 0 0 0 0
0 0 0 1 0
0 0 0 0 0
0 0 0 0 1
]]]]]]]]]]]]]]
]
1198861= minus
1198981198971198972
119869119909
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus4
5119869119909
1198981198971198972
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198862= minus
1198981198971198972
119869119909
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus4
5119869119909
1198981198971198972
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198863= minus
1198981198971198972
119869119909
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus4
5119869119909
1198981198971198972
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198864= minus
1198981198971198972
119869119909
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus4
5119869119909
1198981198971198972
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
119906120593=
119876120593
119869119909
+
119906
119869119909
+119898
1198971198972
119869119909
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+4
5119869119909
1198981198971198972
+
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198865=
1
2119869119910
1198981198971198972
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+2
5119869119910
1198981198971198972
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198866=
1
2119869119910
1198981198971198972
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+2
5119869119910
1198981198971198972
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198867=
1
2119869119910
1198981198971198972
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+2
5119869119910
1198981198971198972
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198868=
1
2119869119910
1198981198971198972
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
24 Mathematical Problems in Engineering
+2
5119869119910
1198981198971198972
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
119906120579=
119876120579
119869119910
+119906
120579
119869119910
minus1
2119869119910
1198981198971198972
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119910
1198981198971198972
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198869= minus
1
2119869119911
1198972
119898119897
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988610
= minus1
2119869119911
1198972
119898119897
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988611
= minus1
2119869119911
1198972
119898119897
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988612
= minus1
2119869119911
1198972
119898119897
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
119906120595=
119876120595
119869119911
+
119906
119869119911
+1
2119869119911
1198972
119898119897
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+2
5119869119911
1198972
119898119897
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988613
= minus
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988614
= minus
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988615
= minus
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988616
= minus
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
1199061198811
=
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988617
= minus
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988618
= minus
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988619
= minus
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988620
= minus
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1199061198812
=
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(A2)
Conflict of Interests
The authors declare that there is no conflict of interestsregarding the publication of this paper
Acknowledgments
The authors would like to thank the anonymous reviewers fortheir critical and constructive review of the paper This studywas cosupported by the National Natural Science Foundationof China (Project no 11302134 11272101)
References
[1] M Colin Solar Sailing Technology Dynamics and MissionApplications Springer-Praxis London UK 1st edition 1999
[2] V Lappas SWokesM Leipold A Lyngvi and P Falkner ldquoGui-dance and control for an Interstellar Heliopause Probe (IHP)solar sail mission to 200 AUrdquo in Proceedings of the AIAAGuidance Navigation and Control Conference and Exhibit pp2472ndash2492 San Francisco Calif USA August 2005
[3] L Charlotte C Camilla and C McInnes ldquoSolar radiation pres-sure augmented deorbiting fromhigh altitude sun-synchronousorbitsrdquo in Proceedings of the 4S Symposium 2012 Small SatellitesSystems and Services Portoroz Slovenia 2012
[4] M Ceriotti and C RMcInnes ldquoGeneration of optimal trajecto-ries for Earth hybrid pole sittersrdquo Journal of Guidance Controland Dynamics vol 34 no 3 pp 847ndash859 2011
[5] S Gong J Li andH Baoyin ldquoSolar sail transfer trajectory fromL1 point to sub-L1 pointrdquoAerospace Science and Technology vol15 no 7 pp 544ndash554 2011
[6] S Gong J Li and H Baoyin ldquoAnalysis of displaced solar sailorbits with passive controlrdquo Journal of Guidance Control andDynamics vol 31 no 3 pp 782ndash785 2008
[7] S Gong H Baoyin and J Li ldquoSolar sail three-body transfertrajectory designrdquo Journal of Guidance Control and Dynamicsvol 33 no 3 pp 873ndash886 2010
Mathematical Problems in Engineering 25
[8] S Gong J Li H Baoyin and J Simo ldquoA new solar sail orbitrdquoScience China Technological Sciences vol 55 no 3 pp 848ndash8552012
[9] Y Tsuda O Mori R Funase et al ldquoAchievement of IKAROS-Japanese deep space solar sail demonstration missionrdquo ActaAstronautica vol 82 no 2 pp 183ndash188 2013
[10] L Johnson MWhorton A Heaton R Pinson G Laue and CAdams ldquoNanoSail-D a solar sail demonstration missionrdquo ActaAstronautica vol 68 no 5-6 pp 571ndash575 2011
[11] B Wie and D Murphy ldquoSolar-sail attitude control design for asail flight validation missionrdquo Journal of Spacecraft and Rocketsvol 44 no 4 pp 809ndash821 2007
[12] B Wie D Murphy M Paluszek and S Thomas ldquoRobust atti-tude control systems design for solar sails part 1 propellantlessprimaryACSrdquo inProceedings of the AIAAGuidance Navigationand Control Conference and Exhibit Providence RI USAAugust 2004
[13] B Wie D Murphy M Paluszek and S Thomas ldquoRobust atti-tude control systems design for solar sails part 2 MicroPPT-based secondary ACSrdquo in Proceedings of the AIAA GuidanceNavigation and Control Conference and Exhibit pp 1325ndash1340Providence RI USA August 2004
[14] S Thomas M Paluszek B Wie and D Murphy ldquoAOCS per-formance and stability validation for large flexible solar sailspacecraftrdquo in Proceedings of the 41st AIAAASMESAEASEEJoint Propulsion Conference amp Exhibit Tucson Ariz USA 2005
[15] B Wie ldquoDynamic modeling and attitude control of solar sailspacecraft part Irdquo in Proceedings of the AIAAGuidance Naviga-tion and Control Conference and Exhibit Monterey Calif USAAugust 2002
[16] BWie ldquoSolar sail attitude control and dynamics part 1rdquo Journalof Guidance Control and Dynamics vol 27 no 4 pp 526ndash5352004
[17] B Wie ldquoDynamic modeling and attitude control of solar sailspacecraft part IIrdquo in Proceedings of the AIAA Guidance Nav-igation and Control Conference and Exhibit Monterey CalifUSA August 2002
[18] BWie ldquoSolar sail attitude control and dynamics part 2rdquo Journalof Guidance Control and Dynamics vol 27 no 4 pp 536ndash5442004
[19] C Luo and J-H Zheng ldquoSolar-sail attitude control based onmoving masses and roll stabilizer barsrdquo Journal of HarbinInstitute of Technology vol 43 no 3 pp 95ndash101 2011
[20] D Romagnoli and T Oehlschlagel ldquoHigh performance twodegrees of freedom attitude control for solar sailsrdquo Advances inSpace Research vol 48 no 11 pp 1869ndash1879 2011
[21] C Scholz D Romagnoli B Dachwald and S Theil ldquoPerfor-mance analysis of an attitude control system for solar sails usingsliding massesrdquo Advances in Space Research vol 48 no 11 pp1822ndash1835 2011
[22] A Bolle and C Circi ldquoSolar sail attitude control through in-plane moving massesrdquo Journal of Aerospace Engineering vol222 no 1 pp 81ndash94 2008
[23] M RotunnoM Basso A B Pome andM Sallusti ldquoA compari-son of robust attitude control techniques for a solar sail space-craftrdquo in Proceedings of the AIAA Guidance Navigation andControl Conference and Exhibit San Francisco Calif USA2005
[24] J Zhang K Zhai and T Wang ldquoControl of large angle maneu-vers for the flexible solar sailrdquo Science China Physics Mechanicsand Astronomy vol 54 no 4 pp 770ndash776 2011
[25] J Zhang andTWang ldquoCoupled attitude-orbit control of flexiblesolar sail for displaced solar orbitrdquo Journal of Spacecraft andRockets vol 50 no 3 pp 675ndash685 2013
[26] Q Li XMa and TWang ldquoReducedmodel for flexible solar saildynamicsrdquo Journal of Spacecraft and Rockets vol 48 no 3 pp446ndash453 2011
[27] M Polites J Kalmanson and D Mangus ldquoSolar sail attitudecontrol using small reaction wheels and magnetic torquersrdquoProceedings of the Institution of Mechanical Engineers G Journalof Aerospace Engineering vol 222 no 1 pp 53ndash62 2008
[28] H-T Cui J-H Luo J-H Feng and P-Y Cui ldquoAttitudecontrol of solar sail spacecraft with control boomrdquo Journal ofAstronautics vol 29 no 2 pp 560ndash566 2008
[29] E Mettler and S R Ploen ldquoSolar sail dynamics and controlusing a boom mounted bus articulated by a bi-state two-axisgimbal and reaction wheelsrdquo in Proceedings of the AIAAAASAstrodynamics Specialist Conference and Exhibit MontereyCalif USA August 2002
[30] J Luo X Li and J Feng ldquoPassive attitude control of solar sailspacecraftrdquo Flight Dynamics vol 26 no 5 pp 47ndash50 2008
[31] J Luo Study on attitude control of solar sail spaceraft [PhDthesis] School of Astronautics Harbin Institute of TechnologyHarbin China 2007
[32] D A Lawrence and S W Piggott ldquoIntegrated trajectory andattitude control for a four-vane solar sailrdquo in Proceedings ofthe AIAA Guidance Navigation and Control Conference andExhibit pp 2416ndash2431 San Francisco Calif USA August 2005
[33] E Mettler A B Acikmese and S R Ploen ldquoAttitude dynamicsand control of solar sails with articulated vanesrdquo in Proceedingsof the AIAA Guidance Navigation and Control Conference andExhibit pp 2396ndash2415 San Francisco Calif USA August 2005
[34] S N Adeli V J Lappas and B Wie ldquoA scalable bus-basedattitude control system for Solar Sailsrdquo Advances in SpaceResearch vol 48 no 11 pp 1836ndash1847 2011
[35] R Funase Y Shirasawa Y Mimasu et al ldquoOn-orbit verificationof fuel-free attitude control system for spinning solar sailutilizing solar radiation pressurerdquo Advances in Space Researchvol 48 no 11 pp 1740ndash1746 2011
[36] B Fu and F O Eke ldquoAttitude control methodology for largesolar sailsrdquo in AIAA Guidance Navigation and Control (GNC)Conference 2013
[37] J Liu N Cui F Shen and S Rong ldquoDynamics of highly-flexiblesolar sail subjected to various forcesrdquoActaAstronautica vol 103pp 55ndash72 2014
[38] J F Liu S Y Rong and J G Li ldquoAttitude dynamics modelingand control of large flexible solar sail spacecraftrdquo in Proceedingsof the 3rd International Symposium on Systems and Control inAeronautics and Astronautics (ISSCAA rsquo10) pp 243ndash247 IEEEPublications Piscataway NJ USA 2010
[39] S Gong H Baoyin and J Li ldquoCoupled attitude-orbit dynamicsand control for displaced solar orbitsrdquo Acta Astronautica vol65 no 5-6 pp 730ndash737 2009
Submit your manuscripts athttpwwwhindawicom
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
MathematicsJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Mathematical Problems in Engineering
Hindawi Publishing Corporationhttpwwwhindawicom
Differential EquationsInternational Journal of
Volume 2014
Applied MathematicsJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Probability and StatisticsHindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Journal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Mathematical PhysicsAdvances in
Complex AnalysisJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
OptimizationJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
CombinatoricsHindawi Publishing Corporationhttpwwwhindawicom Volume 2014
International Journal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Operations ResearchAdvances in
Journal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Function Spaces
Abstract and Applied AnalysisHindawi Publishing Corporationhttpwwwhindawicom Volume 2014
International Journal of Mathematics and Mathematical Sciences
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
The Scientific World JournalHindawi Publishing Corporation httpwwwhindawicom Volume 2014
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Algebra
Discrete Dynamics in Nature and Society
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Decision SciencesAdvances in
Discrete MathematicsJournal of
Hindawi Publishing Corporationhttpwwwhindawicom
Volume 2014 Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Stochastic AnalysisInternational Journal of
18 Mathematical Problems in Engineering
minus20
0
20
Roll
torq
ue (N
lowastm
)
Roll
torq
ue (N
lowastm
)
minus50
0
50
minus50
0
50
Pitc
h to
rque
(Nlowast
m)
Pitc
h to
rque
(Nlowast
m)
0 1000 2000 3000 4000 5000
0 2000 4000 6000
0 2000 4000 6000
Yaw
torq
ue (N
lowastm
)
Yaw
torq
ue (N
lowastm
)
minus002
0
002
008
01
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
minus01
minus009
minus008
Time (s)Time (s)
Time (s)Time (s)
Time (s)Time (s)
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Figure 10 The roll pitch and yaw torques
figures) A simple and practical controller should be designedto eliminate the steady-state errorsThese errorswill affect theprecision of the super long duration space mission deeply
The differences between the dynamics with and withoutthe geometrical nonlinearity effect can be observed Theamplitudes and phases change a bit by comparing the corre-sponding results
It can be observed by the partial enlarged figures(the right figures of Figure 9) that there are no steady-stateerrors for roll pitch and yaw rates The relative satisfieddynamic performance is achieved In fact a result with muchmore satisfied dynamic performance can be obtained but itwill make the desired control torques much larger duringthe initial period This will not only excite the vibration ofthe structure but also increase the burden of the controlactuators
And the differences between the dynamics models withand without the geometrical nonlinearity can also be seenmerely in the phase of the angular velocities
The desired attitude control torques are presented inFigure 10 The roll torque will tend to be zero with thedecrement of the state variable errors The pitch and yawtorques tend to be constant from the middle and bottom
figures The pitch and yaw steady-state errors can never beeliminated although the pitch and yaw torques (009Nlowastmand minus009Nlowastm) are applied continuously by theoreticalanalysis and simulations This is just a great disadvantage ofthe LQR based controller in this paper The initial controltorques can be afforded by vibrating the gimbaled controlboom andmoving the slidingmasses that can afford a relativelarge torque The control vanes can be used to afford thecontrol torques when solar sail is in steady-state process Theexpression of the attitude control inputs 119906
120593 119906
120579 and 119906
120595can be
found in previous sectionMoreover the differences between dynamics responses
with and without geometrical nonlinearity can also beobserved by comparing the corresponding results Therequired torques for the attitude control are a little largerfor the dynamics with geometrical nonlinearity And thedifference in the phase is also clear
It can be seen that the vibration of the supporting beamis depressed effectively by the simulation results in Figure 11It can be seen that the steady-state errors and the dynamicperformance are relatively satisfied It can also be seen that thedynamics responses between the model with and without the
Mathematical Problems in Engineering 19
0 1000 2000 3000 4000 5000
0 1000 2000 3000 4000 5000
minus01
0
01
minus02
0
02
Time (s) Time (s)
Time (s) Time (s)
minus5
0
5
times10minus4
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
minus1
0
1
times10minus3
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
The d
ispla
cem
ent o
f the
tip
(m)
The d
ispla
cem
ent o
f the
tip
(m)
The v
eloci
ty o
f the
tip
(ms
)
The v
eloc
ity o
f the
tip
(ms
)
Figure 11 The displacement and velocity of the tip of the supporting beam
geometrical nonlinearity effect are different in the vibrationdisplacement and velocitymagnitudes and phases (Figure 15)
The simulation results can be obtained as follows by usingthe optimal PI based controller adopting the abovementionedparameters and initial conditions
The roll pitch and yaw errors are given by using theoptimal PI based controller These errors tend to disappearby observing the partially enlarged plotting of the figure (thecorresponding right figures) (shown in Figure 12) And therelative satisfied dynamic performance can also be obtainedFrom the view of eliminating the steady-state errors the opti-mal PI based controller performs better than the LQR basedcontroller by theoretical analysis and simulation results Theformer can achieve attitude control results without pitchand yaw steady-state errors From the view of dynamicperformance both the controllers perform well In additionit can be seen that the difference between the modelswith and without geometrical nonlinearity is merely inthe phase
The roll pitch and yaw rate errors are presented inFigure 13 The dynamic and steady-state performances aresatisfied by observing the simulation results And by observ-ing the difference between the dynamics responses with and
without the influence by the geometrical nonlinearity it canbe concluded that the merely difference is the phase
The desired control torques of the roll pitch and yaw areobtained in Figure 14 by using the optimal PI based controllerIt can be seen that the value of the desired roll control torquedecreases to zero as the values of the roll angle and ratedecrease to zero The desired pitch and yaw control torquestend to be the constant values 009Nlowastm and minus009Nlowastmrespectively The desired initial control torques are large byobserving Figure 14 It is suggested that the gimbaled controlboom combining the sliding masses is adopted to afford theinitial torque Then the control vanes can be used to controlthe solar sail after the initial phase The phase differencecan also be observed by inspecting the dynamics responsesduring the 4800sim5000 s period
The vibration can be controlled effectively based on theoptimal PI controller And the relative satisfied dynamicand steady-state performances can be achieved In additionthe tiny differences exist in the magnitudes of the requiredtorques And the phase differences also exist
It can be concluded as follows by analyzing and compar-ing the simulation results based on the LQR and optimal PItheories in detail
20 Mathematical Problems in Engineering
Roll
erro
r120593(∘
)
Roll
erro
r120593(∘
)
minus5
0
5
minus5
0
5
Pitc
h er
ror120579
(∘)
Pitc
h er
ror120579
(∘)
0 1000 2000 3000 4000 5000minus10
0
10
Time (s) Time (s)
Time (s)
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
Yaw
erro
r120595(∘
)
Yaw
erro
r120595(∘
)
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
minus1
0
1
times10minus3
minus1
0
1
times10minus3
minus1
0
1
times10minus3
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Figure 12 The roll pitch and yaw errors
(1) From the view of eliminating the steady-state errorsof the pitch and yaw errors the optimal PI based con-troller performs better than the LQR based controllerby theoretical analysis and simulation results Thedynamic performances of the two controllers are bothsatisfied and the desired control torques are relativelysmall
(2) The weighting of the state variables is reflected by theweighting matrix according to the LQR and optimalPI theories The constant weighting matrices selectedin this paper can effectively reflect the initial statevariable errors but maybe reflect the final state vari-able errors deficiently The time-varying weightingmatrices should be selected
(3) For the actual orbiting solar sail the control actuators(control vanes gimbaled control boom and slidingmasses) cannot afford excessive large control torquesThus the control torques should be as small as possibleon the premise of acquiring satisfied dynamic perfor-mance and steady-state errors It will not only reducethe burden of the control actuators but also avoid
exciting structural vibration In engineering practicethe weighting matrices and the control weightingmatrices should be selected based on the attitudecontrol requirement (eg dynamic performance andsteady-state errors etc)
(4) The dynamics responses influenced by the geometri-cal nonlinearity can be observed In a word the tinydifferences between the magnitudes of the physicalvariables exist for the models with and withoutthe geometrical nonlinearity And the relative cleardifferences exist in the phases for the attitude anglesrates required torques and so forth
6 Conclusions
The coupled attitude and structural dynamics is establishedfor the highly flexible sailcraft by using the von-Karman von-Karmanrsquos nonlinear strain-displacement relationships basedon assumptions of large deflections moderate rotationsand
Mathematical Problems in Engineering 21
Roll
rate
erro
r(∘ s
)
Roll
rate
erro
r(∘ s
)
minus01
0
01
minus01
0
01
Pitc
h ra
te er
ror (
∘ s)
Pitc
h ra
te er
ror (
∘ s)
0 1000 2000 3000 4000 5000minus02
0
02
Yaw
rate
erro
r (∘ s
)
Yaw
rate
erro
r (∘ s
)
4800 4850 4900 4950 5000
minus5
0
5times10minus4
minus5
0
5
times10minus4
minus5
0
5times10minus4
Time (s)
4800 4850 4900 4950 5000
Time (s)
4800 4850 4900 4950 5000
Time (s)
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Figure 13 The roll pitch and yaw rate errors
small strains The Lagrange equation method is utilizedto derive the dynamics for controller design and dynamicsimulation The LQR and optimal PI based controllers aredesigned for the dynamics with the constant disturbancetorque caused by the cmcp offset By theoretical analysisand simulation it can be seen that both controllers cancompromise between the state variables and control inputsBecause the control actuators can hardly afford large controltorque the dynamic performance should be relaxed toreduce the requirement for the attitude control actuatorsBesides the optimal PI based controller can also eliminatethe constant disturbance torque caused by the cmcp offsetthat always exists while the LQR based controller fails toachieve the results with satisfied steady-state performancealthough the attitude control torque is always applied to thecoupled dynamic systemThe dynamics simulations with andwithout the geometrical nonlinearity effect are also carriedout And the differences between the models in magnitudesand phases are identified and analyzed It can be concludedthat the optimal PI based controller performs better than the
LQRbased controller from the viewof eliminating the steady-state error caused by the disturbance torque by the cmcpoffset
Appendix
The related parameters in above equation are given as
119886120593= 119869
119909+ 119898
ℎ11199102
ℎ1
+ 119898ℎ21199112
ℎ2
+ 1198981199011199032
119901119911
+ 1198981199011199032
119901119910
119886120579= minus 119898
119901119903119901119909119903119901119910 119886
120595= minus119898
119901119903119901119909119903119901119911
1198861198811
= minus 1198981198971198972
1198861198812
= minus4
5119898
1198971198972
119887120579= 119869
119910+ 119898
ℎ21199112
ℎ2
+ 1198981199011199032
119901119911
+ 1198981199011199032
119901119909
119887120595= minus 119898
119901119903119901119910119903119901119911 119887
120593= minus119898
119901119903119901119909119903119901119910
22 Mathematical Problems in Engineering
Roll
torq
ue (N
lowastm
)
Roll
torq
ue (N
lowastm
)
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
0 2000 4000 6000
0 2000 4000 6000
0 2000 4000 6000
Time (s)
Time (s)
Time (s)
Time (s)
Time (s)
Time (s)4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
minus01
minus008
008
009
01
minus002
0
002
minus5
0
5
minus2
0
2
Pitc
h to
rque
(Nlowast
m)
Pitc
h to
rque
(Nlowast
m)
minus2
0
2
Yaw
torq
ue (N
lowastm
)
Yaw
torq
ue (N
lowastm
)
Figure 14 The roll pitch and yaw torques
1198871198811
=1
2119898
1198971198972
1198871198812
=2
5119898
1198971198972
119888120595= 119869
119911+ 119898
ℎ11199102
ℎ1
+ 1198981199011199032
119901119910
+ 1198981199011199032
119901119909
119888120579= minus 119898
119901119903119901119910119903119901119911 119888
120593= minus119898
119901119903119901119909119903119901119911
1198881198811
= minus1
21198972
119898119897 119888
1198812
= minus2
51198972
119898119897
119889
1198811
= (4
3
119868119863
119897+
1
5119897119868119860) 119889
1198812
= (1
6119897119868119860+
3119868119863
2119897)
119889
1198811
=4120578
119887119863
119909119909
1198973 119889
1198812
=6120578
119887119863
119909119909
1198973
1198891198811
=4119863
119909119909
1198973 119889
1198812
=6119863
119909119909
1198973
1198761198811
= 1198651198621
(119905)
119890
1198811
= (3
2
119868119863
119897+
1
6119897119868119860)
119890
1198812
= (1
7119897119868119860+
9
5
119868119863
119897) 119890
1198811
=6120578
119887119863
119909119909
1198973
119890
1198812
=12120578
119887119863
119909119909
1198973 119890
1198811
=6119863
119909119909
1198973
1198901198812
=12119863
119909119909
1198973 119876
1198812
= 1198651198622
(119905)
(A1)
The detailed expressions of control inputs for attitudevibration and related parameters in the state-space model ofthe dynamics (see (62) and (63)) are presented as follows
A =
[[[[[[[[[[[[[[
[
0 1 0 0 0 0 0 0 0 0
0 0 0 0 0 0 1198861
1198862
1198863
1198864
0 0 0 1 0 0 0 0 0 0
0 0 0 0 0 0 1198865
1198866
1198867
1198868
0 0 0 0 0 1 0 0 0 0
0 0 0 0 0 0 1198869
11988610
11988611
11988612
0 0 0 0 0 0 0 1 0 0
0 0 0 0 0 0 11988613
11988614
11988615
11988616
0 0 0 0 0 0 0 0 0 1
0 0 0 0 0 0 11988617
11988618
11988619
11988620
]]]]]]]]]]]]]]
]
Mathematical Problems in Engineering 23
0 1000 2000 3000 4000 5000
0 1000 2000 3000 4000 5000
minus01
0
01
minus02
0
02
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Time (s)
Time (s)Time (s)
Time (s)
minus1
0
1
minus1
0
1
times10minus3
times10minus3Th
e disp
lace
men
t of t
he ti
p (m
)
The d
ispla
cem
ent o
f the
tip
(m)
The v
eloci
ty o
f the
tip
(ms
)
The v
eloci
ty o
f the
tip
(ms
)
Figure 15 Vibration displacement and velocity of the tip
B =
[[[[[[[[[[[[[[
[
0 0 0 0 0
1 0 0 0 0
0 0 0 0 0
0 1 0 0 0
0 0 0 0 0
0 0 1 0 0
0 0 0 0 0
0 0 0 1 0
0 0 0 0 0
0 0 0 0 1
]]]]]]]]]]]]]]
]
1198861= minus
1198981198971198972
119869119909
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus4
5119869119909
1198981198971198972
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198862= minus
1198981198971198972
119869119909
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus4
5119869119909
1198981198971198972
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198863= minus
1198981198971198972
119869119909
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus4
5119869119909
1198981198971198972
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198864= minus
1198981198971198972
119869119909
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus4
5119869119909
1198981198971198972
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
119906120593=
119876120593
119869119909
+
119906
119869119909
+119898
1198971198972
119869119909
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+4
5119869119909
1198981198971198972
+
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198865=
1
2119869119910
1198981198971198972
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+2
5119869119910
1198981198971198972
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198866=
1
2119869119910
1198981198971198972
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+2
5119869119910
1198981198971198972
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198867=
1
2119869119910
1198981198971198972
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+2
5119869119910
1198981198971198972
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198868=
1
2119869119910
1198981198971198972
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
24 Mathematical Problems in Engineering
+2
5119869119910
1198981198971198972
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
119906120579=
119876120579
119869119910
+119906
120579
119869119910
minus1
2119869119910
1198981198971198972
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119910
1198981198971198972
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198869= minus
1
2119869119911
1198972
119898119897
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988610
= minus1
2119869119911
1198972
119898119897
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988611
= minus1
2119869119911
1198972
119898119897
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988612
= minus1
2119869119911
1198972
119898119897
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
119906120595=
119876120595
119869119911
+
119906
119869119911
+1
2119869119911
1198972
119898119897
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+2
5119869119911
1198972
119898119897
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988613
= minus
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988614
= minus
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988615
= minus
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988616
= minus
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
1199061198811
=
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988617
= minus
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988618
= minus
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988619
= minus
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988620
= minus
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1199061198812
=
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(A2)
Conflict of Interests
The authors declare that there is no conflict of interestsregarding the publication of this paper
Acknowledgments
The authors would like to thank the anonymous reviewers fortheir critical and constructive review of the paper This studywas cosupported by the National Natural Science Foundationof China (Project no 11302134 11272101)
References
[1] M Colin Solar Sailing Technology Dynamics and MissionApplications Springer-Praxis London UK 1st edition 1999
[2] V Lappas SWokesM Leipold A Lyngvi and P Falkner ldquoGui-dance and control for an Interstellar Heliopause Probe (IHP)solar sail mission to 200 AUrdquo in Proceedings of the AIAAGuidance Navigation and Control Conference and Exhibit pp2472ndash2492 San Francisco Calif USA August 2005
[3] L Charlotte C Camilla and C McInnes ldquoSolar radiation pres-sure augmented deorbiting fromhigh altitude sun-synchronousorbitsrdquo in Proceedings of the 4S Symposium 2012 Small SatellitesSystems and Services Portoroz Slovenia 2012
[4] M Ceriotti and C RMcInnes ldquoGeneration of optimal trajecto-ries for Earth hybrid pole sittersrdquo Journal of Guidance Controland Dynamics vol 34 no 3 pp 847ndash859 2011
[5] S Gong J Li andH Baoyin ldquoSolar sail transfer trajectory fromL1 point to sub-L1 pointrdquoAerospace Science and Technology vol15 no 7 pp 544ndash554 2011
[6] S Gong J Li and H Baoyin ldquoAnalysis of displaced solar sailorbits with passive controlrdquo Journal of Guidance Control andDynamics vol 31 no 3 pp 782ndash785 2008
[7] S Gong H Baoyin and J Li ldquoSolar sail three-body transfertrajectory designrdquo Journal of Guidance Control and Dynamicsvol 33 no 3 pp 873ndash886 2010
Mathematical Problems in Engineering 25
[8] S Gong J Li H Baoyin and J Simo ldquoA new solar sail orbitrdquoScience China Technological Sciences vol 55 no 3 pp 848ndash8552012
[9] Y Tsuda O Mori R Funase et al ldquoAchievement of IKAROS-Japanese deep space solar sail demonstration missionrdquo ActaAstronautica vol 82 no 2 pp 183ndash188 2013
[10] L Johnson MWhorton A Heaton R Pinson G Laue and CAdams ldquoNanoSail-D a solar sail demonstration missionrdquo ActaAstronautica vol 68 no 5-6 pp 571ndash575 2011
[11] B Wie and D Murphy ldquoSolar-sail attitude control design for asail flight validation missionrdquo Journal of Spacecraft and Rocketsvol 44 no 4 pp 809ndash821 2007
[12] B Wie D Murphy M Paluszek and S Thomas ldquoRobust atti-tude control systems design for solar sails part 1 propellantlessprimaryACSrdquo inProceedings of the AIAAGuidance Navigationand Control Conference and Exhibit Providence RI USAAugust 2004
[13] B Wie D Murphy M Paluszek and S Thomas ldquoRobust atti-tude control systems design for solar sails part 2 MicroPPT-based secondary ACSrdquo in Proceedings of the AIAA GuidanceNavigation and Control Conference and Exhibit pp 1325ndash1340Providence RI USA August 2004
[14] S Thomas M Paluszek B Wie and D Murphy ldquoAOCS per-formance and stability validation for large flexible solar sailspacecraftrdquo in Proceedings of the 41st AIAAASMESAEASEEJoint Propulsion Conference amp Exhibit Tucson Ariz USA 2005
[15] B Wie ldquoDynamic modeling and attitude control of solar sailspacecraft part Irdquo in Proceedings of the AIAAGuidance Naviga-tion and Control Conference and Exhibit Monterey Calif USAAugust 2002
[16] BWie ldquoSolar sail attitude control and dynamics part 1rdquo Journalof Guidance Control and Dynamics vol 27 no 4 pp 526ndash5352004
[17] B Wie ldquoDynamic modeling and attitude control of solar sailspacecraft part IIrdquo in Proceedings of the AIAA Guidance Nav-igation and Control Conference and Exhibit Monterey CalifUSA August 2002
[18] BWie ldquoSolar sail attitude control and dynamics part 2rdquo Journalof Guidance Control and Dynamics vol 27 no 4 pp 536ndash5442004
[19] C Luo and J-H Zheng ldquoSolar-sail attitude control based onmoving masses and roll stabilizer barsrdquo Journal of HarbinInstitute of Technology vol 43 no 3 pp 95ndash101 2011
[20] D Romagnoli and T Oehlschlagel ldquoHigh performance twodegrees of freedom attitude control for solar sailsrdquo Advances inSpace Research vol 48 no 11 pp 1869ndash1879 2011
[21] C Scholz D Romagnoli B Dachwald and S Theil ldquoPerfor-mance analysis of an attitude control system for solar sails usingsliding massesrdquo Advances in Space Research vol 48 no 11 pp1822ndash1835 2011
[22] A Bolle and C Circi ldquoSolar sail attitude control through in-plane moving massesrdquo Journal of Aerospace Engineering vol222 no 1 pp 81ndash94 2008
[23] M RotunnoM Basso A B Pome andM Sallusti ldquoA compari-son of robust attitude control techniques for a solar sail space-craftrdquo in Proceedings of the AIAA Guidance Navigation andControl Conference and Exhibit San Francisco Calif USA2005
[24] J Zhang K Zhai and T Wang ldquoControl of large angle maneu-vers for the flexible solar sailrdquo Science China Physics Mechanicsand Astronomy vol 54 no 4 pp 770ndash776 2011
[25] J Zhang andTWang ldquoCoupled attitude-orbit control of flexiblesolar sail for displaced solar orbitrdquo Journal of Spacecraft andRockets vol 50 no 3 pp 675ndash685 2013
[26] Q Li XMa and TWang ldquoReducedmodel for flexible solar saildynamicsrdquo Journal of Spacecraft and Rockets vol 48 no 3 pp446ndash453 2011
[27] M Polites J Kalmanson and D Mangus ldquoSolar sail attitudecontrol using small reaction wheels and magnetic torquersrdquoProceedings of the Institution of Mechanical Engineers G Journalof Aerospace Engineering vol 222 no 1 pp 53ndash62 2008
[28] H-T Cui J-H Luo J-H Feng and P-Y Cui ldquoAttitudecontrol of solar sail spacecraft with control boomrdquo Journal ofAstronautics vol 29 no 2 pp 560ndash566 2008
[29] E Mettler and S R Ploen ldquoSolar sail dynamics and controlusing a boom mounted bus articulated by a bi-state two-axisgimbal and reaction wheelsrdquo in Proceedings of the AIAAAASAstrodynamics Specialist Conference and Exhibit MontereyCalif USA August 2002
[30] J Luo X Li and J Feng ldquoPassive attitude control of solar sailspacecraftrdquo Flight Dynamics vol 26 no 5 pp 47ndash50 2008
[31] J Luo Study on attitude control of solar sail spaceraft [PhDthesis] School of Astronautics Harbin Institute of TechnologyHarbin China 2007
[32] D A Lawrence and S W Piggott ldquoIntegrated trajectory andattitude control for a four-vane solar sailrdquo in Proceedings ofthe AIAA Guidance Navigation and Control Conference andExhibit pp 2416ndash2431 San Francisco Calif USA August 2005
[33] E Mettler A B Acikmese and S R Ploen ldquoAttitude dynamicsand control of solar sails with articulated vanesrdquo in Proceedingsof the AIAA Guidance Navigation and Control Conference andExhibit pp 2396ndash2415 San Francisco Calif USA August 2005
[34] S N Adeli V J Lappas and B Wie ldquoA scalable bus-basedattitude control system for Solar Sailsrdquo Advances in SpaceResearch vol 48 no 11 pp 1836ndash1847 2011
[35] R Funase Y Shirasawa Y Mimasu et al ldquoOn-orbit verificationof fuel-free attitude control system for spinning solar sailutilizing solar radiation pressurerdquo Advances in Space Researchvol 48 no 11 pp 1740ndash1746 2011
[36] B Fu and F O Eke ldquoAttitude control methodology for largesolar sailsrdquo in AIAA Guidance Navigation and Control (GNC)Conference 2013
[37] J Liu N Cui F Shen and S Rong ldquoDynamics of highly-flexiblesolar sail subjected to various forcesrdquoActaAstronautica vol 103pp 55ndash72 2014
[38] J F Liu S Y Rong and J G Li ldquoAttitude dynamics modelingand control of large flexible solar sail spacecraftrdquo in Proceedingsof the 3rd International Symposium on Systems and Control inAeronautics and Astronautics (ISSCAA rsquo10) pp 243ndash247 IEEEPublications Piscataway NJ USA 2010
[39] S Gong H Baoyin and J Li ldquoCoupled attitude-orbit dynamicsand control for displaced solar orbitsrdquo Acta Astronautica vol65 no 5-6 pp 730ndash737 2009
Submit your manuscripts athttpwwwhindawicom
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
MathematicsJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Mathematical Problems in Engineering
Hindawi Publishing Corporationhttpwwwhindawicom
Differential EquationsInternational Journal of
Volume 2014
Applied MathematicsJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Probability and StatisticsHindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Journal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Mathematical PhysicsAdvances in
Complex AnalysisJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
OptimizationJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
CombinatoricsHindawi Publishing Corporationhttpwwwhindawicom Volume 2014
International Journal of
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Operations ResearchAdvances in
Journal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Function Spaces
Abstract and Applied AnalysisHindawi Publishing Corporationhttpwwwhindawicom Volume 2014
International Journal of Mathematics and Mathematical Sciences
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
The Scientific World JournalHindawi Publishing Corporation httpwwwhindawicom Volume 2014
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Algebra
Discrete Dynamics in Nature and Society
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Decision SciencesAdvances in
Discrete MathematicsJournal of
Hindawi Publishing Corporationhttpwwwhindawicom
Volume 2014 Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Stochastic AnalysisInternational Journal of
Mathematical Problems in Engineering 19
0 1000 2000 3000 4000 5000
0 1000 2000 3000 4000 5000
minus01
0
01
minus02
0
02
Time (s) Time (s)
Time (s) Time (s)
minus5
0
5
times10minus4
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
minus1
0
1
times10minus3
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
The d
ispla
cem
ent o
f the
tip
(m)
The d
ispla
cem
ent o
f the
tip
(m)
The v
eloci
ty o
f the
tip
(ms
)
The v
eloc
ity o
f the
tip
(ms
)
Figure 11 The displacement and velocity of the tip of the supporting beam
geometrical nonlinearity effect are different in the vibrationdisplacement and velocitymagnitudes and phases (Figure 15)
The simulation results can be obtained as follows by usingthe optimal PI based controller adopting the abovementionedparameters and initial conditions
The roll pitch and yaw errors are given by using theoptimal PI based controller These errors tend to disappearby observing the partially enlarged plotting of the figure (thecorresponding right figures) (shown in Figure 12) And therelative satisfied dynamic performance can also be obtainedFrom the view of eliminating the steady-state errors the opti-mal PI based controller performs better than the LQR basedcontroller by theoretical analysis and simulation results Theformer can achieve attitude control results without pitchand yaw steady-state errors From the view of dynamicperformance both the controllers perform well In additionit can be seen that the difference between the modelswith and without geometrical nonlinearity is merely inthe phase
The roll pitch and yaw rate errors are presented inFigure 13 The dynamic and steady-state performances aresatisfied by observing the simulation results And by observ-ing the difference between the dynamics responses with and
without the influence by the geometrical nonlinearity it canbe concluded that the merely difference is the phase
The desired control torques of the roll pitch and yaw areobtained in Figure 14 by using the optimal PI based controllerIt can be seen that the value of the desired roll control torquedecreases to zero as the values of the roll angle and ratedecrease to zero The desired pitch and yaw control torquestend to be the constant values 009Nlowastm and minus009Nlowastmrespectively The desired initial control torques are large byobserving Figure 14 It is suggested that the gimbaled controlboom combining the sliding masses is adopted to afford theinitial torque Then the control vanes can be used to controlthe solar sail after the initial phase The phase differencecan also be observed by inspecting the dynamics responsesduring the 4800sim5000 s period
The vibration can be controlled effectively based on theoptimal PI controller And the relative satisfied dynamicand steady-state performances can be achieved In additionthe tiny differences exist in the magnitudes of the requiredtorques And the phase differences also exist
It can be concluded as follows by analyzing and compar-ing the simulation results based on the LQR and optimal PItheories in detail
20 Mathematical Problems in Engineering
Roll
erro
r120593(∘
)
Roll
erro
r120593(∘
)
minus5
0
5
minus5
0
5
Pitc
h er
ror120579
(∘)
Pitc
h er
ror120579
(∘)
0 1000 2000 3000 4000 5000minus10
0
10
Time (s) Time (s)
Time (s)
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
Yaw
erro
r120595(∘
)
Yaw
erro
r120595(∘
)
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
minus1
0
1
times10minus3
minus1
0
1
times10minus3
minus1
0
1
times10minus3
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Figure 12 The roll pitch and yaw errors
(1) From the view of eliminating the steady-state errorsof the pitch and yaw errors the optimal PI based con-troller performs better than the LQR based controllerby theoretical analysis and simulation results Thedynamic performances of the two controllers are bothsatisfied and the desired control torques are relativelysmall
(2) The weighting of the state variables is reflected by theweighting matrix according to the LQR and optimalPI theories The constant weighting matrices selectedin this paper can effectively reflect the initial statevariable errors but maybe reflect the final state vari-able errors deficiently The time-varying weightingmatrices should be selected
(3) For the actual orbiting solar sail the control actuators(control vanes gimbaled control boom and slidingmasses) cannot afford excessive large control torquesThus the control torques should be as small as possibleon the premise of acquiring satisfied dynamic perfor-mance and steady-state errors It will not only reducethe burden of the control actuators but also avoid
exciting structural vibration In engineering practicethe weighting matrices and the control weightingmatrices should be selected based on the attitudecontrol requirement (eg dynamic performance andsteady-state errors etc)
(4) The dynamics responses influenced by the geometri-cal nonlinearity can be observed In a word the tinydifferences between the magnitudes of the physicalvariables exist for the models with and withoutthe geometrical nonlinearity And the relative cleardifferences exist in the phases for the attitude anglesrates required torques and so forth
6 Conclusions
The coupled attitude and structural dynamics is establishedfor the highly flexible sailcraft by using the von-Karman von-Karmanrsquos nonlinear strain-displacement relationships basedon assumptions of large deflections moderate rotationsand
Mathematical Problems in Engineering 21
Roll
rate
erro
r(∘ s
)
Roll
rate
erro
r(∘ s
)
minus01
0
01
minus01
0
01
Pitc
h ra
te er
ror (
∘ s)
Pitc
h ra
te er
ror (
∘ s)
0 1000 2000 3000 4000 5000minus02
0
02
Yaw
rate
erro
r (∘ s
)
Yaw
rate
erro
r (∘ s
)
4800 4850 4900 4950 5000
minus5
0
5times10minus4
minus5
0
5
times10minus4
minus5
0
5times10minus4
Time (s)
4800 4850 4900 4950 5000
Time (s)
4800 4850 4900 4950 5000
Time (s)
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Figure 13 The roll pitch and yaw rate errors
small strains The Lagrange equation method is utilizedto derive the dynamics for controller design and dynamicsimulation The LQR and optimal PI based controllers aredesigned for the dynamics with the constant disturbancetorque caused by the cmcp offset By theoretical analysisand simulation it can be seen that both controllers cancompromise between the state variables and control inputsBecause the control actuators can hardly afford large controltorque the dynamic performance should be relaxed toreduce the requirement for the attitude control actuatorsBesides the optimal PI based controller can also eliminatethe constant disturbance torque caused by the cmcp offsetthat always exists while the LQR based controller fails toachieve the results with satisfied steady-state performancealthough the attitude control torque is always applied to thecoupled dynamic systemThe dynamics simulations with andwithout the geometrical nonlinearity effect are also carriedout And the differences between the models in magnitudesand phases are identified and analyzed It can be concludedthat the optimal PI based controller performs better than the
LQRbased controller from the viewof eliminating the steady-state error caused by the disturbance torque by the cmcpoffset
Appendix
The related parameters in above equation are given as
119886120593= 119869
119909+ 119898
ℎ11199102
ℎ1
+ 119898ℎ21199112
ℎ2
+ 1198981199011199032
119901119911
+ 1198981199011199032
119901119910
119886120579= minus 119898
119901119903119901119909119903119901119910 119886
120595= minus119898
119901119903119901119909119903119901119911
1198861198811
= minus 1198981198971198972
1198861198812
= minus4
5119898
1198971198972
119887120579= 119869
119910+ 119898
ℎ21199112
ℎ2
+ 1198981199011199032
119901119911
+ 1198981199011199032
119901119909
119887120595= minus 119898
119901119903119901119910119903119901119911 119887
120593= minus119898
119901119903119901119909119903119901119910
22 Mathematical Problems in Engineering
Roll
torq
ue (N
lowastm
)
Roll
torq
ue (N
lowastm
)
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
0 2000 4000 6000
0 2000 4000 6000
0 2000 4000 6000
Time (s)
Time (s)
Time (s)
Time (s)
Time (s)
Time (s)4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
minus01
minus008
008
009
01
minus002
0
002
minus5
0
5
minus2
0
2
Pitc
h to
rque
(Nlowast
m)
Pitc
h to
rque
(Nlowast
m)
minus2
0
2
Yaw
torq
ue (N
lowastm
)
Yaw
torq
ue (N
lowastm
)
Figure 14 The roll pitch and yaw torques
1198871198811
=1
2119898
1198971198972
1198871198812
=2
5119898
1198971198972
119888120595= 119869
119911+ 119898
ℎ11199102
ℎ1
+ 1198981199011199032
119901119910
+ 1198981199011199032
119901119909
119888120579= minus 119898
119901119903119901119910119903119901119911 119888
120593= minus119898
119901119903119901119909119903119901119911
1198881198811
= minus1
21198972
119898119897 119888
1198812
= minus2
51198972
119898119897
119889
1198811
= (4
3
119868119863
119897+
1
5119897119868119860) 119889
1198812
= (1
6119897119868119860+
3119868119863
2119897)
119889
1198811
=4120578
119887119863
119909119909
1198973 119889
1198812
=6120578
119887119863
119909119909
1198973
1198891198811
=4119863
119909119909
1198973 119889
1198812
=6119863
119909119909
1198973
1198761198811
= 1198651198621
(119905)
119890
1198811
= (3
2
119868119863
119897+
1
6119897119868119860)
119890
1198812
= (1
7119897119868119860+
9
5
119868119863
119897) 119890
1198811
=6120578
119887119863
119909119909
1198973
119890
1198812
=12120578
119887119863
119909119909
1198973 119890
1198811
=6119863
119909119909
1198973
1198901198812
=12119863
119909119909
1198973 119876
1198812
= 1198651198622
(119905)
(A1)
The detailed expressions of control inputs for attitudevibration and related parameters in the state-space model ofthe dynamics (see (62) and (63)) are presented as follows
A =
[[[[[[[[[[[[[[
[
0 1 0 0 0 0 0 0 0 0
0 0 0 0 0 0 1198861
1198862
1198863
1198864
0 0 0 1 0 0 0 0 0 0
0 0 0 0 0 0 1198865
1198866
1198867
1198868
0 0 0 0 0 1 0 0 0 0
0 0 0 0 0 0 1198869
11988610
11988611
11988612
0 0 0 0 0 0 0 1 0 0
0 0 0 0 0 0 11988613
11988614
11988615
11988616
0 0 0 0 0 0 0 0 0 1
0 0 0 0 0 0 11988617
11988618
11988619
11988620
]]]]]]]]]]]]]]
]
Mathematical Problems in Engineering 23
0 1000 2000 3000 4000 5000
0 1000 2000 3000 4000 5000
minus01
0
01
minus02
0
02
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Time (s)
Time (s)Time (s)
Time (s)
minus1
0
1
minus1
0
1
times10minus3
times10minus3Th
e disp
lace
men
t of t
he ti
p (m
)
The d
ispla
cem
ent o
f the
tip
(m)
The v
eloci
ty o
f the
tip
(ms
)
The v
eloci
ty o
f the
tip
(ms
)
Figure 15 Vibration displacement and velocity of the tip
B =
[[[[[[[[[[[[[[
[
0 0 0 0 0
1 0 0 0 0
0 0 0 0 0
0 1 0 0 0
0 0 0 0 0
0 0 1 0 0
0 0 0 0 0
0 0 0 1 0
0 0 0 0 0
0 0 0 0 1
]]]]]]]]]]]]]]
]
1198861= minus
1198981198971198972
119869119909
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus4
5119869119909
1198981198971198972
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198862= minus
1198981198971198972
119869119909
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus4
5119869119909
1198981198971198972
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198863= minus
1198981198971198972
119869119909
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus4
5119869119909
1198981198971198972
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198864= minus
1198981198971198972
119869119909
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus4
5119869119909
1198981198971198972
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
119906120593=
119876120593
119869119909
+
119906
119869119909
+119898
1198971198972
119869119909
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+4
5119869119909
1198981198971198972
+
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198865=
1
2119869119910
1198981198971198972
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+2
5119869119910
1198981198971198972
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198866=
1
2119869119910
1198981198971198972
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+2
5119869119910
1198981198971198972
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198867=
1
2119869119910
1198981198971198972
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+2
5119869119910
1198981198971198972
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198868=
1
2119869119910
1198981198971198972
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
24 Mathematical Problems in Engineering
+2
5119869119910
1198981198971198972
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
119906120579=
119876120579
119869119910
+119906
120579
119869119910
minus1
2119869119910
1198981198971198972
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119910
1198981198971198972
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198869= minus
1
2119869119911
1198972
119898119897
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988610
= minus1
2119869119911
1198972
119898119897
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988611
= minus1
2119869119911
1198972
119898119897
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988612
= minus1
2119869119911
1198972
119898119897
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
119906120595=
119876120595
119869119911
+
119906
119869119911
+1
2119869119911
1198972
119898119897
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+2
5119869119911
1198972
119898119897
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988613
= minus
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988614
= minus
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988615
= minus
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988616
= minus
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
1199061198811
=
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988617
= minus
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988618
= minus
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988619
= minus
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988620
= minus
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1199061198812
=
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(A2)
Conflict of Interests
The authors declare that there is no conflict of interestsregarding the publication of this paper
Acknowledgments
The authors would like to thank the anonymous reviewers fortheir critical and constructive review of the paper This studywas cosupported by the National Natural Science Foundationof China (Project no 11302134 11272101)
References
[1] M Colin Solar Sailing Technology Dynamics and MissionApplications Springer-Praxis London UK 1st edition 1999
[2] V Lappas SWokesM Leipold A Lyngvi and P Falkner ldquoGui-dance and control for an Interstellar Heliopause Probe (IHP)solar sail mission to 200 AUrdquo in Proceedings of the AIAAGuidance Navigation and Control Conference and Exhibit pp2472ndash2492 San Francisco Calif USA August 2005
[3] L Charlotte C Camilla and C McInnes ldquoSolar radiation pres-sure augmented deorbiting fromhigh altitude sun-synchronousorbitsrdquo in Proceedings of the 4S Symposium 2012 Small SatellitesSystems and Services Portoroz Slovenia 2012
[4] M Ceriotti and C RMcInnes ldquoGeneration of optimal trajecto-ries for Earth hybrid pole sittersrdquo Journal of Guidance Controland Dynamics vol 34 no 3 pp 847ndash859 2011
[5] S Gong J Li andH Baoyin ldquoSolar sail transfer trajectory fromL1 point to sub-L1 pointrdquoAerospace Science and Technology vol15 no 7 pp 544ndash554 2011
[6] S Gong J Li and H Baoyin ldquoAnalysis of displaced solar sailorbits with passive controlrdquo Journal of Guidance Control andDynamics vol 31 no 3 pp 782ndash785 2008
[7] S Gong H Baoyin and J Li ldquoSolar sail three-body transfertrajectory designrdquo Journal of Guidance Control and Dynamicsvol 33 no 3 pp 873ndash886 2010
Mathematical Problems in Engineering 25
[8] S Gong J Li H Baoyin and J Simo ldquoA new solar sail orbitrdquoScience China Technological Sciences vol 55 no 3 pp 848ndash8552012
[9] Y Tsuda O Mori R Funase et al ldquoAchievement of IKAROS-Japanese deep space solar sail demonstration missionrdquo ActaAstronautica vol 82 no 2 pp 183ndash188 2013
[10] L Johnson MWhorton A Heaton R Pinson G Laue and CAdams ldquoNanoSail-D a solar sail demonstration missionrdquo ActaAstronautica vol 68 no 5-6 pp 571ndash575 2011
[11] B Wie and D Murphy ldquoSolar-sail attitude control design for asail flight validation missionrdquo Journal of Spacecraft and Rocketsvol 44 no 4 pp 809ndash821 2007
[12] B Wie D Murphy M Paluszek and S Thomas ldquoRobust atti-tude control systems design for solar sails part 1 propellantlessprimaryACSrdquo inProceedings of the AIAAGuidance Navigationand Control Conference and Exhibit Providence RI USAAugust 2004
[13] B Wie D Murphy M Paluszek and S Thomas ldquoRobust atti-tude control systems design for solar sails part 2 MicroPPT-based secondary ACSrdquo in Proceedings of the AIAA GuidanceNavigation and Control Conference and Exhibit pp 1325ndash1340Providence RI USA August 2004
[14] S Thomas M Paluszek B Wie and D Murphy ldquoAOCS per-formance and stability validation for large flexible solar sailspacecraftrdquo in Proceedings of the 41st AIAAASMESAEASEEJoint Propulsion Conference amp Exhibit Tucson Ariz USA 2005
[15] B Wie ldquoDynamic modeling and attitude control of solar sailspacecraft part Irdquo in Proceedings of the AIAAGuidance Naviga-tion and Control Conference and Exhibit Monterey Calif USAAugust 2002
[16] BWie ldquoSolar sail attitude control and dynamics part 1rdquo Journalof Guidance Control and Dynamics vol 27 no 4 pp 526ndash5352004
[17] B Wie ldquoDynamic modeling and attitude control of solar sailspacecraft part IIrdquo in Proceedings of the AIAA Guidance Nav-igation and Control Conference and Exhibit Monterey CalifUSA August 2002
[18] BWie ldquoSolar sail attitude control and dynamics part 2rdquo Journalof Guidance Control and Dynamics vol 27 no 4 pp 536ndash5442004
[19] C Luo and J-H Zheng ldquoSolar-sail attitude control based onmoving masses and roll stabilizer barsrdquo Journal of HarbinInstitute of Technology vol 43 no 3 pp 95ndash101 2011
[20] D Romagnoli and T Oehlschlagel ldquoHigh performance twodegrees of freedom attitude control for solar sailsrdquo Advances inSpace Research vol 48 no 11 pp 1869ndash1879 2011
[21] C Scholz D Romagnoli B Dachwald and S Theil ldquoPerfor-mance analysis of an attitude control system for solar sails usingsliding massesrdquo Advances in Space Research vol 48 no 11 pp1822ndash1835 2011
[22] A Bolle and C Circi ldquoSolar sail attitude control through in-plane moving massesrdquo Journal of Aerospace Engineering vol222 no 1 pp 81ndash94 2008
[23] M RotunnoM Basso A B Pome andM Sallusti ldquoA compari-son of robust attitude control techniques for a solar sail space-craftrdquo in Proceedings of the AIAA Guidance Navigation andControl Conference and Exhibit San Francisco Calif USA2005
[24] J Zhang K Zhai and T Wang ldquoControl of large angle maneu-vers for the flexible solar sailrdquo Science China Physics Mechanicsand Astronomy vol 54 no 4 pp 770ndash776 2011
[25] J Zhang andTWang ldquoCoupled attitude-orbit control of flexiblesolar sail for displaced solar orbitrdquo Journal of Spacecraft andRockets vol 50 no 3 pp 675ndash685 2013
[26] Q Li XMa and TWang ldquoReducedmodel for flexible solar saildynamicsrdquo Journal of Spacecraft and Rockets vol 48 no 3 pp446ndash453 2011
[27] M Polites J Kalmanson and D Mangus ldquoSolar sail attitudecontrol using small reaction wheels and magnetic torquersrdquoProceedings of the Institution of Mechanical Engineers G Journalof Aerospace Engineering vol 222 no 1 pp 53ndash62 2008
[28] H-T Cui J-H Luo J-H Feng and P-Y Cui ldquoAttitudecontrol of solar sail spacecraft with control boomrdquo Journal ofAstronautics vol 29 no 2 pp 560ndash566 2008
[29] E Mettler and S R Ploen ldquoSolar sail dynamics and controlusing a boom mounted bus articulated by a bi-state two-axisgimbal and reaction wheelsrdquo in Proceedings of the AIAAAASAstrodynamics Specialist Conference and Exhibit MontereyCalif USA August 2002
[30] J Luo X Li and J Feng ldquoPassive attitude control of solar sailspacecraftrdquo Flight Dynamics vol 26 no 5 pp 47ndash50 2008
[31] J Luo Study on attitude control of solar sail spaceraft [PhDthesis] School of Astronautics Harbin Institute of TechnologyHarbin China 2007
[32] D A Lawrence and S W Piggott ldquoIntegrated trajectory andattitude control for a four-vane solar sailrdquo in Proceedings ofthe AIAA Guidance Navigation and Control Conference andExhibit pp 2416ndash2431 San Francisco Calif USA August 2005
[33] E Mettler A B Acikmese and S R Ploen ldquoAttitude dynamicsand control of solar sails with articulated vanesrdquo in Proceedingsof the AIAA Guidance Navigation and Control Conference andExhibit pp 2396ndash2415 San Francisco Calif USA August 2005
[34] S N Adeli V J Lappas and B Wie ldquoA scalable bus-basedattitude control system for Solar Sailsrdquo Advances in SpaceResearch vol 48 no 11 pp 1836ndash1847 2011
[35] R Funase Y Shirasawa Y Mimasu et al ldquoOn-orbit verificationof fuel-free attitude control system for spinning solar sailutilizing solar radiation pressurerdquo Advances in Space Researchvol 48 no 11 pp 1740ndash1746 2011
[36] B Fu and F O Eke ldquoAttitude control methodology for largesolar sailsrdquo in AIAA Guidance Navigation and Control (GNC)Conference 2013
[37] J Liu N Cui F Shen and S Rong ldquoDynamics of highly-flexiblesolar sail subjected to various forcesrdquoActaAstronautica vol 103pp 55ndash72 2014
[38] J F Liu S Y Rong and J G Li ldquoAttitude dynamics modelingand control of large flexible solar sail spacecraftrdquo in Proceedingsof the 3rd International Symposium on Systems and Control inAeronautics and Astronautics (ISSCAA rsquo10) pp 243ndash247 IEEEPublications Piscataway NJ USA 2010
[39] S Gong H Baoyin and J Li ldquoCoupled attitude-orbit dynamicsand control for displaced solar orbitsrdquo Acta Astronautica vol65 no 5-6 pp 730ndash737 2009
Submit your manuscripts athttpwwwhindawicom
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
MathematicsJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Mathematical Problems in Engineering
Hindawi Publishing Corporationhttpwwwhindawicom
Differential EquationsInternational Journal of
Volume 2014
Applied MathematicsJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Probability and StatisticsHindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Journal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Mathematical PhysicsAdvances in
Complex AnalysisJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
OptimizationJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
CombinatoricsHindawi Publishing Corporationhttpwwwhindawicom Volume 2014
International Journal of
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Operations ResearchAdvances in
Journal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Function Spaces
Abstract and Applied AnalysisHindawi Publishing Corporationhttpwwwhindawicom Volume 2014
International Journal of Mathematics and Mathematical Sciences
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
The Scientific World JournalHindawi Publishing Corporation httpwwwhindawicom Volume 2014
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Algebra
Discrete Dynamics in Nature and Society
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
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Decision SciencesAdvances in
Discrete MathematicsJournal of
Hindawi Publishing Corporationhttpwwwhindawicom
Volume 2014 Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Stochastic AnalysisInternational Journal of
20 Mathematical Problems in Engineering
Roll
erro
r120593(∘
)
Roll
erro
r120593(∘
)
minus5
0
5
minus5
0
5
Pitc
h er
ror120579
(∘)
Pitc
h er
ror120579
(∘)
0 1000 2000 3000 4000 5000minus10
0
10
Time (s) Time (s)
Time (s)
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
Yaw
erro
r120595(∘
)
Yaw
erro
r120595(∘
)
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
minus1
0
1
times10minus3
minus1
0
1
times10minus3
minus1
0
1
times10minus3
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Figure 12 The roll pitch and yaw errors
(1) From the view of eliminating the steady-state errorsof the pitch and yaw errors the optimal PI based con-troller performs better than the LQR based controllerby theoretical analysis and simulation results Thedynamic performances of the two controllers are bothsatisfied and the desired control torques are relativelysmall
(2) The weighting of the state variables is reflected by theweighting matrix according to the LQR and optimalPI theories The constant weighting matrices selectedin this paper can effectively reflect the initial statevariable errors but maybe reflect the final state vari-able errors deficiently The time-varying weightingmatrices should be selected
(3) For the actual orbiting solar sail the control actuators(control vanes gimbaled control boom and slidingmasses) cannot afford excessive large control torquesThus the control torques should be as small as possibleon the premise of acquiring satisfied dynamic perfor-mance and steady-state errors It will not only reducethe burden of the control actuators but also avoid
exciting structural vibration In engineering practicethe weighting matrices and the control weightingmatrices should be selected based on the attitudecontrol requirement (eg dynamic performance andsteady-state errors etc)
(4) The dynamics responses influenced by the geometri-cal nonlinearity can be observed In a word the tinydifferences between the magnitudes of the physicalvariables exist for the models with and withoutthe geometrical nonlinearity And the relative cleardifferences exist in the phases for the attitude anglesrates required torques and so forth
6 Conclusions
The coupled attitude and structural dynamics is establishedfor the highly flexible sailcraft by using the von-Karman von-Karmanrsquos nonlinear strain-displacement relationships basedon assumptions of large deflections moderate rotationsand
Mathematical Problems in Engineering 21
Roll
rate
erro
r(∘ s
)
Roll
rate
erro
r(∘ s
)
minus01
0
01
minus01
0
01
Pitc
h ra
te er
ror (
∘ s)
Pitc
h ra
te er
ror (
∘ s)
0 1000 2000 3000 4000 5000minus02
0
02
Yaw
rate
erro
r (∘ s
)
Yaw
rate
erro
r (∘ s
)
4800 4850 4900 4950 5000
minus5
0
5times10minus4
minus5
0
5
times10minus4
minus5
0
5times10minus4
Time (s)
4800 4850 4900 4950 5000
Time (s)
4800 4850 4900 4950 5000
Time (s)
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Figure 13 The roll pitch and yaw rate errors
small strains The Lagrange equation method is utilizedto derive the dynamics for controller design and dynamicsimulation The LQR and optimal PI based controllers aredesigned for the dynamics with the constant disturbancetorque caused by the cmcp offset By theoretical analysisand simulation it can be seen that both controllers cancompromise between the state variables and control inputsBecause the control actuators can hardly afford large controltorque the dynamic performance should be relaxed toreduce the requirement for the attitude control actuatorsBesides the optimal PI based controller can also eliminatethe constant disturbance torque caused by the cmcp offsetthat always exists while the LQR based controller fails toachieve the results with satisfied steady-state performancealthough the attitude control torque is always applied to thecoupled dynamic systemThe dynamics simulations with andwithout the geometrical nonlinearity effect are also carriedout And the differences between the models in magnitudesand phases are identified and analyzed It can be concludedthat the optimal PI based controller performs better than the
LQRbased controller from the viewof eliminating the steady-state error caused by the disturbance torque by the cmcpoffset
Appendix
The related parameters in above equation are given as
119886120593= 119869
119909+ 119898
ℎ11199102
ℎ1
+ 119898ℎ21199112
ℎ2
+ 1198981199011199032
119901119911
+ 1198981199011199032
119901119910
119886120579= minus 119898
119901119903119901119909119903119901119910 119886
120595= minus119898
119901119903119901119909119903119901119911
1198861198811
= minus 1198981198971198972
1198861198812
= minus4
5119898
1198971198972
119887120579= 119869
119910+ 119898
ℎ21199112
ℎ2
+ 1198981199011199032
119901119911
+ 1198981199011199032
119901119909
119887120595= minus 119898
119901119903119901119910119903119901119911 119887
120593= minus119898
119901119903119901119909119903119901119910
22 Mathematical Problems in Engineering
Roll
torq
ue (N
lowastm
)
Roll
torq
ue (N
lowastm
)
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
0 2000 4000 6000
0 2000 4000 6000
0 2000 4000 6000
Time (s)
Time (s)
Time (s)
Time (s)
Time (s)
Time (s)4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
minus01
minus008
008
009
01
minus002
0
002
minus5
0
5
minus2
0
2
Pitc
h to
rque
(Nlowast
m)
Pitc
h to
rque
(Nlowast
m)
minus2
0
2
Yaw
torq
ue (N
lowastm
)
Yaw
torq
ue (N
lowastm
)
Figure 14 The roll pitch and yaw torques
1198871198811
=1
2119898
1198971198972
1198871198812
=2
5119898
1198971198972
119888120595= 119869
119911+ 119898
ℎ11199102
ℎ1
+ 1198981199011199032
119901119910
+ 1198981199011199032
119901119909
119888120579= minus 119898
119901119903119901119910119903119901119911 119888
120593= minus119898
119901119903119901119909119903119901119911
1198881198811
= minus1
21198972
119898119897 119888
1198812
= minus2
51198972
119898119897
119889
1198811
= (4
3
119868119863
119897+
1
5119897119868119860) 119889
1198812
= (1
6119897119868119860+
3119868119863
2119897)
119889
1198811
=4120578
119887119863
119909119909
1198973 119889
1198812
=6120578
119887119863
119909119909
1198973
1198891198811
=4119863
119909119909
1198973 119889
1198812
=6119863
119909119909
1198973
1198761198811
= 1198651198621
(119905)
119890
1198811
= (3
2
119868119863
119897+
1
6119897119868119860)
119890
1198812
= (1
7119897119868119860+
9
5
119868119863
119897) 119890
1198811
=6120578
119887119863
119909119909
1198973
119890
1198812
=12120578
119887119863
119909119909
1198973 119890
1198811
=6119863
119909119909
1198973
1198901198812
=12119863
119909119909
1198973 119876
1198812
= 1198651198622
(119905)
(A1)
The detailed expressions of control inputs for attitudevibration and related parameters in the state-space model ofthe dynamics (see (62) and (63)) are presented as follows
A =
[[[[[[[[[[[[[[
[
0 1 0 0 0 0 0 0 0 0
0 0 0 0 0 0 1198861
1198862
1198863
1198864
0 0 0 1 0 0 0 0 0 0
0 0 0 0 0 0 1198865
1198866
1198867
1198868
0 0 0 0 0 1 0 0 0 0
0 0 0 0 0 0 1198869
11988610
11988611
11988612
0 0 0 0 0 0 0 1 0 0
0 0 0 0 0 0 11988613
11988614
11988615
11988616
0 0 0 0 0 0 0 0 0 1
0 0 0 0 0 0 11988617
11988618
11988619
11988620
]]]]]]]]]]]]]]
]
Mathematical Problems in Engineering 23
0 1000 2000 3000 4000 5000
0 1000 2000 3000 4000 5000
minus01
0
01
minus02
0
02
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Time (s)
Time (s)Time (s)
Time (s)
minus1
0
1
minus1
0
1
times10minus3
times10minus3Th
e disp
lace
men
t of t
he ti
p (m
)
The d
ispla
cem
ent o
f the
tip
(m)
The v
eloci
ty o
f the
tip
(ms
)
The v
eloci
ty o
f the
tip
(ms
)
Figure 15 Vibration displacement and velocity of the tip
B =
[[[[[[[[[[[[[[
[
0 0 0 0 0
1 0 0 0 0
0 0 0 0 0
0 1 0 0 0
0 0 0 0 0
0 0 1 0 0
0 0 0 0 0
0 0 0 1 0
0 0 0 0 0
0 0 0 0 1
]]]]]]]]]]]]]]
]
1198861= minus
1198981198971198972
119869119909
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus4
5119869119909
1198981198971198972
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198862= minus
1198981198971198972
119869119909
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus4
5119869119909
1198981198971198972
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198863= minus
1198981198971198972
119869119909
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus4
5119869119909
1198981198971198972
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198864= minus
1198981198971198972
119869119909
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus4
5119869119909
1198981198971198972
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
119906120593=
119876120593
119869119909
+
119906
119869119909
+119898
1198971198972
119869119909
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+4
5119869119909
1198981198971198972
+
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198865=
1
2119869119910
1198981198971198972
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+2
5119869119910
1198981198971198972
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198866=
1
2119869119910
1198981198971198972
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+2
5119869119910
1198981198971198972
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198867=
1
2119869119910
1198981198971198972
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+2
5119869119910
1198981198971198972
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198868=
1
2119869119910
1198981198971198972
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
24 Mathematical Problems in Engineering
+2
5119869119910
1198981198971198972
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
119906120579=
119876120579
119869119910
+119906
120579
119869119910
minus1
2119869119910
1198981198971198972
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119910
1198981198971198972
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198869= minus
1
2119869119911
1198972
119898119897
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988610
= minus1
2119869119911
1198972
119898119897
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988611
= minus1
2119869119911
1198972
119898119897
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988612
= minus1
2119869119911
1198972
119898119897
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
119906120595=
119876120595
119869119911
+
119906
119869119911
+1
2119869119911
1198972
119898119897
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+2
5119869119911
1198972
119898119897
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988613
= minus
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988614
= minus
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988615
= minus
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988616
= minus
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
1199061198811
=
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988617
= minus
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988618
= minus
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988619
= minus
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988620
= minus
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1199061198812
=
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(A2)
Conflict of Interests
The authors declare that there is no conflict of interestsregarding the publication of this paper
Acknowledgments
The authors would like to thank the anonymous reviewers fortheir critical and constructive review of the paper This studywas cosupported by the National Natural Science Foundationof China (Project no 11302134 11272101)
References
[1] M Colin Solar Sailing Technology Dynamics and MissionApplications Springer-Praxis London UK 1st edition 1999
[2] V Lappas SWokesM Leipold A Lyngvi and P Falkner ldquoGui-dance and control for an Interstellar Heliopause Probe (IHP)solar sail mission to 200 AUrdquo in Proceedings of the AIAAGuidance Navigation and Control Conference and Exhibit pp2472ndash2492 San Francisco Calif USA August 2005
[3] L Charlotte C Camilla and C McInnes ldquoSolar radiation pres-sure augmented deorbiting fromhigh altitude sun-synchronousorbitsrdquo in Proceedings of the 4S Symposium 2012 Small SatellitesSystems and Services Portoroz Slovenia 2012
[4] M Ceriotti and C RMcInnes ldquoGeneration of optimal trajecto-ries for Earth hybrid pole sittersrdquo Journal of Guidance Controland Dynamics vol 34 no 3 pp 847ndash859 2011
[5] S Gong J Li andH Baoyin ldquoSolar sail transfer trajectory fromL1 point to sub-L1 pointrdquoAerospace Science and Technology vol15 no 7 pp 544ndash554 2011
[6] S Gong J Li and H Baoyin ldquoAnalysis of displaced solar sailorbits with passive controlrdquo Journal of Guidance Control andDynamics vol 31 no 3 pp 782ndash785 2008
[7] S Gong H Baoyin and J Li ldquoSolar sail three-body transfertrajectory designrdquo Journal of Guidance Control and Dynamicsvol 33 no 3 pp 873ndash886 2010
Mathematical Problems in Engineering 25
[8] S Gong J Li H Baoyin and J Simo ldquoA new solar sail orbitrdquoScience China Technological Sciences vol 55 no 3 pp 848ndash8552012
[9] Y Tsuda O Mori R Funase et al ldquoAchievement of IKAROS-Japanese deep space solar sail demonstration missionrdquo ActaAstronautica vol 82 no 2 pp 183ndash188 2013
[10] L Johnson MWhorton A Heaton R Pinson G Laue and CAdams ldquoNanoSail-D a solar sail demonstration missionrdquo ActaAstronautica vol 68 no 5-6 pp 571ndash575 2011
[11] B Wie and D Murphy ldquoSolar-sail attitude control design for asail flight validation missionrdquo Journal of Spacecraft and Rocketsvol 44 no 4 pp 809ndash821 2007
[12] B Wie D Murphy M Paluszek and S Thomas ldquoRobust atti-tude control systems design for solar sails part 1 propellantlessprimaryACSrdquo inProceedings of the AIAAGuidance Navigationand Control Conference and Exhibit Providence RI USAAugust 2004
[13] B Wie D Murphy M Paluszek and S Thomas ldquoRobust atti-tude control systems design for solar sails part 2 MicroPPT-based secondary ACSrdquo in Proceedings of the AIAA GuidanceNavigation and Control Conference and Exhibit pp 1325ndash1340Providence RI USA August 2004
[14] S Thomas M Paluszek B Wie and D Murphy ldquoAOCS per-formance and stability validation for large flexible solar sailspacecraftrdquo in Proceedings of the 41st AIAAASMESAEASEEJoint Propulsion Conference amp Exhibit Tucson Ariz USA 2005
[15] B Wie ldquoDynamic modeling and attitude control of solar sailspacecraft part Irdquo in Proceedings of the AIAAGuidance Naviga-tion and Control Conference and Exhibit Monterey Calif USAAugust 2002
[16] BWie ldquoSolar sail attitude control and dynamics part 1rdquo Journalof Guidance Control and Dynamics vol 27 no 4 pp 526ndash5352004
[17] B Wie ldquoDynamic modeling and attitude control of solar sailspacecraft part IIrdquo in Proceedings of the AIAA Guidance Nav-igation and Control Conference and Exhibit Monterey CalifUSA August 2002
[18] BWie ldquoSolar sail attitude control and dynamics part 2rdquo Journalof Guidance Control and Dynamics vol 27 no 4 pp 536ndash5442004
[19] C Luo and J-H Zheng ldquoSolar-sail attitude control based onmoving masses and roll stabilizer barsrdquo Journal of HarbinInstitute of Technology vol 43 no 3 pp 95ndash101 2011
[20] D Romagnoli and T Oehlschlagel ldquoHigh performance twodegrees of freedom attitude control for solar sailsrdquo Advances inSpace Research vol 48 no 11 pp 1869ndash1879 2011
[21] C Scholz D Romagnoli B Dachwald and S Theil ldquoPerfor-mance analysis of an attitude control system for solar sails usingsliding massesrdquo Advances in Space Research vol 48 no 11 pp1822ndash1835 2011
[22] A Bolle and C Circi ldquoSolar sail attitude control through in-plane moving massesrdquo Journal of Aerospace Engineering vol222 no 1 pp 81ndash94 2008
[23] M RotunnoM Basso A B Pome andM Sallusti ldquoA compari-son of robust attitude control techniques for a solar sail space-craftrdquo in Proceedings of the AIAA Guidance Navigation andControl Conference and Exhibit San Francisco Calif USA2005
[24] J Zhang K Zhai and T Wang ldquoControl of large angle maneu-vers for the flexible solar sailrdquo Science China Physics Mechanicsand Astronomy vol 54 no 4 pp 770ndash776 2011
[25] J Zhang andTWang ldquoCoupled attitude-orbit control of flexiblesolar sail for displaced solar orbitrdquo Journal of Spacecraft andRockets vol 50 no 3 pp 675ndash685 2013
[26] Q Li XMa and TWang ldquoReducedmodel for flexible solar saildynamicsrdquo Journal of Spacecraft and Rockets vol 48 no 3 pp446ndash453 2011
[27] M Polites J Kalmanson and D Mangus ldquoSolar sail attitudecontrol using small reaction wheels and magnetic torquersrdquoProceedings of the Institution of Mechanical Engineers G Journalof Aerospace Engineering vol 222 no 1 pp 53ndash62 2008
[28] H-T Cui J-H Luo J-H Feng and P-Y Cui ldquoAttitudecontrol of solar sail spacecraft with control boomrdquo Journal ofAstronautics vol 29 no 2 pp 560ndash566 2008
[29] E Mettler and S R Ploen ldquoSolar sail dynamics and controlusing a boom mounted bus articulated by a bi-state two-axisgimbal and reaction wheelsrdquo in Proceedings of the AIAAAASAstrodynamics Specialist Conference and Exhibit MontereyCalif USA August 2002
[30] J Luo X Li and J Feng ldquoPassive attitude control of solar sailspacecraftrdquo Flight Dynamics vol 26 no 5 pp 47ndash50 2008
[31] J Luo Study on attitude control of solar sail spaceraft [PhDthesis] School of Astronautics Harbin Institute of TechnologyHarbin China 2007
[32] D A Lawrence and S W Piggott ldquoIntegrated trajectory andattitude control for a four-vane solar sailrdquo in Proceedings ofthe AIAA Guidance Navigation and Control Conference andExhibit pp 2416ndash2431 San Francisco Calif USA August 2005
[33] E Mettler A B Acikmese and S R Ploen ldquoAttitude dynamicsand control of solar sails with articulated vanesrdquo in Proceedingsof the AIAA Guidance Navigation and Control Conference andExhibit pp 2396ndash2415 San Francisco Calif USA August 2005
[34] S N Adeli V J Lappas and B Wie ldquoA scalable bus-basedattitude control system for Solar Sailsrdquo Advances in SpaceResearch vol 48 no 11 pp 1836ndash1847 2011
[35] R Funase Y Shirasawa Y Mimasu et al ldquoOn-orbit verificationof fuel-free attitude control system for spinning solar sailutilizing solar radiation pressurerdquo Advances in Space Researchvol 48 no 11 pp 1740ndash1746 2011
[36] B Fu and F O Eke ldquoAttitude control methodology for largesolar sailsrdquo in AIAA Guidance Navigation and Control (GNC)Conference 2013
[37] J Liu N Cui F Shen and S Rong ldquoDynamics of highly-flexiblesolar sail subjected to various forcesrdquoActaAstronautica vol 103pp 55ndash72 2014
[38] J F Liu S Y Rong and J G Li ldquoAttitude dynamics modelingand control of large flexible solar sail spacecraftrdquo in Proceedingsof the 3rd International Symposium on Systems and Control inAeronautics and Astronautics (ISSCAA rsquo10) pp 243ndash247 IEEEPublications Piscataway NJ USA 2010
[39] S Gong H Baoyin and J Li ldquoCoupled attitude-orbit dynamicsand control for displaced solar orbitsrdquo Acta Astronautica vol65 no 5-6 pp 730ndash737 2009
Submit your manuscripts athttpwwwhindawicom
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
MathematicsJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Mathematical Problems in Engineering
Hindawi Publishing Corporationhttpwwwhindawicom
Differential EquationsInternational Journal of
Volume 2014
Applied MathematicsJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Probability and StatisticsHindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Journal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Mathematical PhysicsAdvances in
Complex AnalysisJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
OptimizationJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
CombinatoricsHindawi Publishing Corporationhttpwwwhindawicom Volume 2014
International Journal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Operations ResearchAdvances in
Journal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Function Spaces
Abstract and Applied AnalysisHindawi Publishing Corporationhttpwwwhindawicom Volume 2014
International Journal of Mathematics and Mathematical Sciences
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
The Scientific World JournalHindawi Publishing Corporation httpwwwhindawicom Volume 2014
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Algebra
Discrete Dynamics in Nature and Society
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Decision SciencesAdvances in
Discrete MathematicsJournal of
Hindawi Publishing Corporationhttpwwwhindawicom
Volume 2014 Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Stochastic AnalysisInternational Journal of
Mathematical Problems in Engineering 21
Roll
rate
erro
r(∘ s
)
Roll
rate
erro
r(∘ s
)
minus01
0
01
minus01
0
01
Pitc
h ra
te er
ror (
∘ s)
Pitc
h ra
te er
ror (
∘ s)
0 1000 2000 3000 4000 5000minus02
0
02
Yaw
rate
erro
r (∘ s
)
Yaw
rate
erro
r (∘ s
)
4800 4850 4900 4950 5000
minus5
0
5times10minus4
minus5
0
5
times10minus4
minus5
0
5times10minus4
Time (s)
4800 4850 4900 4950 5000
Time (s)
4800 4850 4900 4950 5000
Time (s)
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
0 1000 2000 3000 4000 5000
Time (s)
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Figure 13 The roll pitch and yaw rate errors
small strains The Lagrange equation method is utilizedto derive the dynamics for controller design and dynamicsimulation The LQR and optimal PI based controllers aredesigned for the dynamics with the constant disturbancetorque caused by the cmcp offset By theoretical analysisand simulation it can be seen that both controllers cancompromise between the state variables and control inputsBecause the control actuators can hardly afford large controltorque the dynamic performance should be relaxed toreduce the requirement for the attitude control actuatorsBesides the optimal PI based controller can also eliminatethe constant disturbance torque caused by the cmcp offsetthat always exists while the LQR based controller fails toachieve the results with satisfied steady-state performancealthough the attitude control torque is always applied to thecoupled dynamic systemThe dynamics simulations with andwithout the geometrical nonlinearity effect are also carriedout And the differences between the models in magnitudesand phases are identified and analyzed It can be concludedthat the optimal PI based controller performs better than the
LQRbased controller from the viewof eliminating the steady-state error caused by the disturbance torque by the cmcpoffset
Appendix
The related parameters in above equation are given as
119886120593= 119869
119909+ 119898
ℎ11199102
ℎ1
+ 119898ℎ21199112
ℎ2
+ 1198981199011199032
119901119911
+ 1198981199011199032
119901119910
119886120579= minus 119898
119901119903119901119909119903119901119910 119886
120595= minus119898
119901119903119901119909119903119901119911
1198861198811
= minus 1198981198971198972
1198861198812
= minus4
5119898
1198971198972
119887120579= 119869
119910+ 119898
ℎ21199112
ℎ2
+ 1198981199011199032
119901119911
+ 1198981199011199032
119901119909
119887120595= minus 119898
119901119903119901119910119903119901119911 119887
120593= minus119898
119901119903119901119909119903119901119910
22 Mathematical Problems in Engineering
Roll
torq
ue (N
lowastm
)
Roll
torq
ue (N
lowastm
)
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
0 2000 4000 6000
0 2000 4000 6000
0 2000 4000 6000
Time (s)
Time (s)
Time (s)
Time (s)
Time (s)
Time (s)4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
minus01
minus008
008
009
01
minus002
0
002
minus5
0
5
minus2
0
2
Pitc
h to
rque
(Nlowast
m)
Pitc
h to
rque
(Nlowast
m)
minus2
0
2
Yaw
torq
ue (N
lowastm
)
Yaw
torq
ue (N
lowastm
)
Figure 14 The roll pitch and yaw torques
1198871198811
=1
2119898
1198971198972
1198871198812
=2
5119898
1198971198972
119888120595= 119869
119911+ 119898
ℎ11199102
ℎ1
+ 1198981199011199032
119901119910
+ 1198981199011199032
119901119909
119888120579= minus 119898
119901119903119901119910119903119901119911 119888
120593= minus119898
119901119903119901119909119903119901119911
1198881198811
= minus1
21198972
119898119897 119888
1198812
= minus2
51198972
119898119897
119889
1198811
= (4
3
119868119863
119897+
1
5119897119868119860) 119889
1198812
= (1
6119897119868119860+
3119868119863
2119897)
119889
1198811
=4120578
119887119863
119909119909
1198973 119889
1198812
=6120578
119887119863
119909119909
1198973
1198891198811
=4119863
119909119909
1198973 119889
1198812
=6119863
119909119909
1198973
1198761198811
= 1198651198621
(119905)
119890
1198811
= (3
2
119868119863
119897+
1
6119897119868119860)
119890
1198812
= (1
7119897119868119860+
9
5
119868119863
119897) 119890
1198811
=6120578
119887119863
119909119909
1198973
119890
1198812
=12120578
119887119863
119909119909
1198973 119890
1198811
=6119863
119909119909
1198973
1198901198812
=12119863
119909119909
1198973 119876
1198812
= 1198651198622
(119905)
(A1)
The detailed expressions of control inputs for attitudevibration and related parameters in the state-space model ofthe dynamics (see (62) and (63)) are presented as follows
A =
[[[[[[[[[[[[[[
[
0 1 0 0 0 0 0 0 0 0
0 0 0 0 0 0 1198861
1198862
1198863
1198864
0 0 0 1 0 0 0 0 0 0
0 0 0 0 0 0 1198865
1198866
1198867
1198868
0 0 0 0 0 1 0 0 0 0
0 0 0 0 0 0 1198869
11988610
11988611
11988612
0 0 0 0 0 0 0 1 0 0
0 0 0 0 0 0 11988613
11988614
11988615
11988616
0 0 0 0 0 0 0 0 0 1
0 0 0 0 0 0 11988617
11988618
11988619
11988620
]]]]]]]]]]]]]]
]
Mathematical Problems in Engineering 23
0 1000 2000 3000 4000 5000
0 1000 2000 3000 4000 5000
minus01
0
01
minus02
0
02
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Time (s)
Time (s)Time (s)
Time (s)
minus1
0
1
minus1
0
1
times10minus3
times10minus3Th
e disp
lace
men
t of t
he ti
p (m
)
The d
ispla
cem
ent o
f the
tip
(m)
The v
eloci
ty o
f the
tip
(ms
)
The v
eloci
ty o
f the
tip
(ms
)
Figure 15 Vibration displacement and velocity of the tip
B =
[[[[[[[[[[[[[[
[
0 0 0 0 0
1 0 0 0 0
0 0 0 0 0
0 1 0 0 0
0 0 0 0 0
0 0 1 0 0
0 0 0 0 0
0 0 0 1 0
0 0 0 0 0
0 0 0 0 1
]]]]]]]]]]]]]]
]
1198861= minus
1198981198971198972
119869119909
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus4
5119869119909
1198981198971198972
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198862= minus
1198981198971198972
119869119909
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus4
5119869119909
1198981198971198972
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198863= minus
1198981198971198972
119869119909
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus4
5119869119909
1198981198971198972
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198864= minus
1198981198971198972
119869119909
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus4
5119869119909
1198981198971198972
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
119906120593=
119876120593
119869119909
+
119906
119869119909
+119898
1198971198972
119869119909
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+4
5119869119909
1198981198971198972
+
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198865=
1
2119869119910
1198981198971198972
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+2
5119869119910
1198981198971198972
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198866=
1
2119869119910
1198981198971198972
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+2
5119869119910
1198981198971198972
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198867=
1
2119869119910
1198981198971198972
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+2
5119869119910
1198981198971198972
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198868=
1
2119869119910
1198981198971198972
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
24 Mathematical Problems in Engineering
+2
5119869119910
1198981198971198972
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
119906120579=
119876120579
119869119910
+119906
120579
119869119910
minus1
2119869119910
1198981198971198972
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119910
1198981198971198972
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198869= minus
1
2119869119911
1198972
119898119897
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988610
= minus1
2119869119911
1198972
119898119897
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988611
= minus1
2119869119911
1198972
119898119897
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988612
= minus1
2119869119911
1198972
119898119897
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
119906120595=
119876120595
119869119911
+
119906
119869119911
+1
2119869119911
1198972
119898119897
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+2
5119869119911
1198972
119898119897
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988613
= minus
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988614
= minus
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988615
= minus
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988616
= minus
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
1199061198811
=
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988617
= minus
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988618
= minus
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988619
= minus
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988620
= minus
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1199061198812
=
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(A2)
Conflict of Interests
The authors declare that there is no conflict of interestsregarding the publication of this paper
Acknowledgments
The authors would like to thank the anonymous reviewers fortheir critical and constructive review of the paper This studywas cosupported by the National Natural Science Foundationof China (Project no 11302134 11272101)
References
[1] M Colin Solar Sailing Technology Dynamics and MissionApplications Springer-Praxis London UK 1st edition 1999
[2] V Lappas SWokesM Leipold A Lyngvi and P Falkner ldquoGui-dance and control for an Interstellar Heliopause Probe (IHP)solar sail mission to 200 AUrdquo in Proceedings of the AIAAGuidance Navigation and Control Conference and Exhibit pp2472ndash2492 San Francisco Calif USA August 2005
[3] L Charlotte C Camilla and C McInnes ldquoSolar radiation pres-sure augmented deorbiting fromhigh altitude sun-synchronousorbitsrdquo in Proceedings of the 4S Symposium 2012 Small SatellitesSystems and Services Portoroz Slovenia 2012
[4] M Ceriotti and C RMcInnes ldquoGeneration of optimal trajecto-ries for Earth hybrid pole sittersrdquo Journal of Guidance Controland Dynamics vol 34 no 3 pp 847ndash859 2011
[5] S Gong J Li andH Baoyin ldquoSolar sail transfer trajectory fromL1 point to sub-L1 pointrdquoAerospace Science and Technology vol15 no 7 pp 544ndash554 2011
[6] S Gong J Li and H Baoyin ldquoAnalysis of displaced solar sailorbits with passive controlrdquo Journal of Guidance Control andDynamics vol 31 no 3 pp 782ndash785 2008
[7] S Gong H Baoyin and J Li ldquoSolar sail three-body transfertrajectory designrdquo Journal of Guidance Control and Dynamicsvol 33 no 3 pp 873ndash886 2010
Mathematical Problems in Engineering 25
[8] S Gong J Li H Baoyin and J Simo ldquoA new solar sail orbitrdquoScience China Technological Sciences vol 55 no 3 pp 848ndash8552012
[9] Y Tsuda O Mori R Funase et al ldquoAchievement of IKAROS-Japanese deep space solar sail demonstration missionrdquo ActaAstronautica vol 82 no 2 pp 183ndash188 2013
[10] L Johnson MWhorton A Heaton R Pinson G Laue and CAdams ldquoNanoSail-D a solar sail demonstration missionrdquo ActaAstronautica vol 68 no 5-6 pp 571ndash575 2011
[11] B Wie and D Murphy ldquoSolar-sail attitude control design for asail flight validation missionrdquo Journal of Spacecraft and Rocketsvol 44 no 4 pp 809ndash821 2007
[12] B Wie D Murphy M Paluszek and S Thomas ldquoRobust atti-tude control systems design for solar sails part 1 propellantlessprimaryACSrdquo inProceedings of the AIAAGuidance Navigationand Control Conference and Exhibit Providence RI USAAugust 2004
[13] B Wie D Murphy M Paluszek and S Thomas ldquoRobust atti-tude control systems design for solar sails part 2 MicroPPT-based secondary ACSrdquo in Proceedings of the AIAA GuidanceNavigation and Control Conference and Exhibit pp 1325ndash1340Providence RI USA August 2004
[14] S Thomas M Paluszek B Wie and D Murphy ldquoAOCS per-formance and stability validation for large flexible solar sailspacecraftrdquo in Proceedings of the 41st AIAAASMESAEASEEJoint Propulsion Conference amp Exhibit Tucson Ariz USA 2005
[15] B Wie ldquoDynamic modeling and attitude control of solar sailspacecraft part Irdquo in Proceedings of the AIAAGuidance Naviga-tion and Control Conference and Exhibit Monterey Calif USAAugust 2002
[16] BWie ldquoSolar sail attitude control and dynamics part 1rdquo Journalof Guidance Control and Dynamics vol 27 no 4 pp 526ndash5352004
[17] B Wie ldquoDynamic modeling and attitude control of solar sailspacecraft part IIrdquo in Proceedings of the AIAA Guidance Nav-igation and Control Conference and Exhibit Monterey CalifUSA August 2002
[18] BWie ldquoSolar sail attitude control and dynamics part 2rdquo Journalof Guidance Control and Dynamics vol 27 no 4 pp 536ndash5442004
[19] C Luo and J-H Zheng ldquoSolar-sail attitude control based onmoving masses and roll stabilizer barsrdquo Journal of HarbinInstitute of Technology vol 43 no 3 pp 95ndash101 2011
[20] D Romagnoli and T Oehlschlagel ldquoHigh performance twodegrees of freedom attitude control for solar sailsrdquo Advances inSpace Research vol 48 no 11 pp 1869ndash1879 2011
[21] C Scholz D Romagnoli B Dachwald and S Theil ldquoPerfor-mance analysis of an attitude control system for solar sails usingsliding massesrdquo Advances in Space Research vol 48 no 11 pp1822ndash1835 2011
[22] A Bolle and C Circi ldquoSolar sail attitude control through in-plane moving massesrdquo Journal of Aerospace Engineering vol222 no 1 pp 81ndash94 2008
[23] M RotunnoM Basso A B Pome andM Sallusti ldquoA compari-son of robust attitude control techniques for a solar sail space-craftrdquo in Proceedings of the AIAA Guidance Navigation andControl Conference and Exhibit San Francisco Calif USA2005
[24] J Zhang K Zhai and T Wang ldquoControl of large angle maneu-vers for the flexible solar sailrdquo Science China Physics Mechanicsand Astronomy vol 54 no 4 pp 770ndash776 2011
[25] J Zhang andTWang ldquoCoupled attitude-orbit control of flexiblesolar sail for displaced solar orbitrdquo Journal of Spacecraft andRockets vol 50 no 3 pp 675ndash685 2013
[26] Q Li XMa and TWang ldquoReducedmodel for flexible solar saildynamicsrdquo Journal of Spacecraft and Rockets vol 48 no 3 pp446ndash453 2011
[27] M Polites J Kalmanson and D Mangus ldquoSolar sail attitudecontrol using small reaction wheels and magnetic torquersrdquoProceedings of the Institution of Mechanical Engineers G Journalof Aerospace Engineering vol 222 no 1 pp 53ndash62 2008
[28] H-T Cui J-H Luo J-H Feng and P-Y Cui ldquoAttitudecontrol of solar sail spacecraft with control boomrdquo Journal ofAstronautics vol 29 no 2 pp 560ndash566 2008
[29] E Mettler and S R Ploen ldquoSolar sail dynamics and controlusing a boom mounted bus articulated by a bi-state two-axisgimbal and reaction wheelsrdquo in Proceedings of the AIAAAASAstrodynamics Specialist Conference and Exhibit MontereyCalif USA August 2002
[30] J Luo X Li and J Feng ldquoPassive attitude control of solar sailspacecraftrdquo Flight Dynamics vol 26 no 5 pp 47ndash50 2008
[31] J Luo Study on attitude control of solar sail spaceraft [PhDthesis] School of Astronautics Harbin Institute of TechnologyHarbin China 2007
[32] D A Lawrence and S W Piggott ldquoIntegrated trajectory andattitude control for a four-vane solar sailrdquo in Proceedings ofthe AIAA Guidance Navigation and Control Conference andExhibit pp 2416ndash2431 San Francisco Calif USA August 2005
[33] E Mettler A B Acikmese and S R Ploen ldquoAttitude dynamicsand control of solar sails with articulated vanesrdquo in Proceedingsof the AIAA Guidance Navigation and Control Conference andExhibit pp 2396ndash2415 San Francisco Calif USA August 2005
[34] S N Adeli V J Lappas and B Wie ldquoA scalable bus-basedattitude control system for Solar Sailsrdquo Advances in SpaceResearch vol 48 no 11 pp 1836ndash1847 2011
[35] R Funase Y Shirasawa Y Mimasu et al ldquoOn-orbit verificationof fuel-free attitude control system for spinning solar sailutilizing solar radiation pressurerdquo Advances in Space Researchvol 48 no 11 pp 1740ndash1746 2011
[36] B Fu and F O Eke ldquoAttitude control methodology for largesolar sailsrdquo in AIAA Guidance Navigation and Control (GNC)Conference 2013
[37] J Liu N Cui F Shen and S Rong ldquoDynamics of highly-flexiblesolar sail subjected to various forcesrdquoActaAstronautica vol 103pp 55ndash72 2014
[38] J F Liu S Y Rong and J G Li ldquoAttitude dynamics modelingand control of large flexible solar sail spacecraftrdquo in Proceedingsof the 3rd International Symposium on Systems and Control inAeronautics and Astronautics (ISSCAA rsquo10) pp 243ndash247 IEEEPublications Piscataway NJ USA 2010
[39] S Gong H Baoyin and J Li ldquoCoupled attitude-orbit dynamicsand control for displaced solar orbitsrdquo Acta Astronautica vol65 no 5-6 pp 730ndash737 2009
Submit your manuscripts athttpwwwhindawicom
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
MathematicsJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Mathematical Problems in Engineering
Hindawi Publishing Corporationhttpwwwhindawicom
Differential EquationsInternational Journal of
Volume 2014
Applied MathematicsJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Probability and StatisticsHindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Journal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Mathematical PhysicsAdvances in
Complex AnalysisJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
OptimizationJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
CombinatoricsHindawi Publishing Corporationhttpwwwhindawicom Volume 2014
International Journal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Operations ResearchAdvances in
Journal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Function Spaces
Abstract and Applied AnalysisHindawi Publishing Corporationhttpwwwhindawicom Volume 2014
International Journal of Mathematics and Mathematical Sciences
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
The Scientific World JournalHindawi Publishing Corporation httpwwwhindawicom Volume 2014
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Algebra
Discrete Dynamics in Nature and Society
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Decision SciencesAdvances in
Discrete MathematicsJournal of
Hindawi Publishing Corporationhttpwwwhindawicom
Volume 2014 Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Stochastic AnalysisInternational Journal of
22 Mathematical Problems in Engineering
Roll
torq
ue (N
lowastm
)
Roll
torq
ue (N
lowastm
)
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
0 2000 4000 6000
0 2000 4000 6000
0 2000 4000 6000
Time (s)
Time (s)
Time (s)
Time (s)
Time (s)
Time (s)4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
minus01
minus008
008
009
01
minus002
0
002
minus5
0
5
minus2
0
2
Pitc
h to
rque
(Nlowast
m)
Pitc
h to
rque
(Nlowast
m)
minus2
0
2
Yaw
torq
ue (N
lowastm
)
Yaw
torq
ue (N
lowastm
)
Figure 14 The roll pitch and yaw torques
1198871198811
=1
2119898
1198971198972
1198871198812
=2
5119898
1198971198972
119888120595= 119869
119911+ 119898
ℎ11199102
ℎ1
+ 1198981199011199032
119901119910
+ 1198981199011199032
119901119909
119888120579= minus 119898
119901119903119901119910119903119901119911 119888
120593= minus119898
119901119903119901119909119903119901119911
1198881198811
= minus1
21198972
119898119897 119888
1198812
= minus2
51198972
119898119897
119889
1198811
= (4
3
119868119863
119897+
1
5119897119868119860) 119889
1198812
= (1
6119897119868119860+
3119868119863
2119897)
119889
1198811
=4120578
119887119863
119909119909
1198973 119889
1198812
=6120578
119887119863
119909119909
1198973
1198891198811
=4119863
119909119909
1198973 119889
1198812
=6119863
119909119909
1198973
1198761198811
= 1198651198621
(119905)
119890
1198811
= (3
2
119868119863
119897+
1
6119897119868119860)
119890
1198812
= (1
7119897119868119860+
9
5
119868119863
119897) 119890
1198811
=6120578
119887119863
119909119909
1198973
119890
1198812
=12120578
119887119863
119909119909
1198973 119890
1198811
=6119863
119909119909
1198973
1198901198812
=12119863
119909119909
1198973 119876
1198812
= 1198651198622
(119905)
(A1)
The detailed expressions of control inputs for attitudevibration and related parameters in the state-space model ofthe dynamics (see (62) and (63)) are presented as follows
A =
[[[[[[[[[[[[[[
[
0 1 0 0 0 0 0 0 0 0
0 0 0 0 0 0 1198861
1198862
1198863
1198864
0 0 0 1 0 0 0 0 0 0
0 0 0 0 0 0 1198865
1198866
1198867
1198868
0 0 0 0 0 1 0 0 0 0
0 0 0 0 0 0 1198869
11988610
11988611
11988612
0 0 0 0 0 0 0 1 0 0
0 0 0 0 0 0 11988613
11988614
11988615
11988616
0 0 0 0 0 0 0 0 0 1
0 0 0 0 0 0 11988617
11988618
11988619
11988620
]]]]]]]]]]]]]]
]
Mathematical Problems in Engineering 23
0 1000 2000 3000 4000 5000
0 1000 2000 3000 4000 5000
minus01
0
01
minus02
0
02
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Time (s)
Time (s)Time (s)
Time (s)
minus1
0
1
minus1
0
1
times10minus3
times10minus3Th
e disp
lace
men
t of t
he ti
p (m
)
The d
ispla
cem
ent o
f the
tip
(m)
The v
eloci
ty o
f the
tip
(ms
)
The v
eloci
ty o
f the
tip
(ms
)
Figure 15 Vibration displacement and velocity of the tip
B =
[[[[[[[[[[[[[[
[
0 0 0 0 0
1 0 0 0 0
0 0 0 0 0
0 1 0 0 0
0 0 0 0 0
0 0 1 0 0
0 0 0 0 0
0 0 0 1 0
0 0 0 0 0
0 0 0 0 1
]]]]]]]]]]]]]]
]
1198861= minus
1198981198971198972
119869119909
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus4
5119869119909
1198981198971198972
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198862= minus
1198981198971198972
119869119909
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus4
5119869119909
1198981198971198972
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198863= minus
1198981198971198972
119869119909
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus4
5119869119909
1198981198971198972
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198864= minus
1198981198971198972
119869119909
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus4
5119869119909
1198981198971198972
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
119906120593=
119876120593
119869119909
+
119906
119869119909
+119898
1198971198972
119869119909
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+4
5119869119909
1198981198971198972
+
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198865=
1
2119869119910
1198981198971198972
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+2
5119869119910
1198981198971198972
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198866=
1
2119869119910
1198981198971198972
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+2
5119869119910
1198981198971198972
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198867=
1
2119869119910
1198981198971198972
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+2
5119869119910
1198981198971198972
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198868=
1
2119869119910
1198981198971198972
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
24 Mathematical Problems in Engineering
+2
5119869119910
1198981198971198972
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
119906120579=
119876120579
119869119910
+119906
120579
119869119910
minus1
2119869119910
1198981198971198972
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119910
1198981198971198972
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198869= minus
1
2119869119911
1198972
119898119897
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988610
= minus1
2119869119911
1198972
119898119897
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988611
= minus1
2119869119911
1198972
119898119897
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988612
= minus1
2119869119911
1198972
119898119897
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
119906120595=
119876120595
119869119911
+
119906
119869119911
+1
2119869119911
1198972
119898119897
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+2
5119869119911
1198972
119898119897
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988613
= minus
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988614
= minus
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988615
= minus
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988616
= minus
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
1199061198811
=
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988617
= minus
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988618
= minus
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988619
= minus
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988620
= minus
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1199061198812
=
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(A2)
Conflict of Interests
The authors declare that there is no conflict of interestsregarding the publication of this paper
Acknowledgments
The authors would like to thank the anonymous reviewers fortheir critical and constructive review of the paper This studywas cosupported by the National Natural Science Foundationof China (Project no 11302134 11272101)
References
[1] M Colin Solar Sailing Technology Dynamics and MissionApplications Springer-Praxis London UK 1st edition 1999
[2] V Lappas SWokesM Leipold A Lyngvi and P Falkner ldquoGui-dance and control for an Interstellar Heliopause Probe (IHP)solar sail mission to 200 AUrdquo in Proceedings of the AIAAGuidance Navigation and Control Conference and Exhibit pp2472ndash2492 San Francisco Calif USA August 2005
[3] L Charlotte C Camilla and C McInnes ldquoSolar radiation pres-sure augmented deorbiting fromhigh altitude sun-synchronousorbitsrdquo in Proceedings of the 4S Symposium 2012 Small SatellitesSystems and Services Portoroz Slovenia 2012
[4] M Ceriotti and C RMcInnes ldquoGeneration of optimal trajecto-ries for Earth hybrid pole sittersrdquo Journal of Guidance Controland Dynamics vol 34 no 3 pp 847ndash859 2011
[5] S Gong J Li andH Baoyin ldquoSolar sail transfer trajectory fromL1 point to sub-L1 pointrdquoAerospace Science and Technology vol15 no 7 pp 544ndash554 2011
[6] S Gong J Li and H Baoyin ldquoAnalysis of displaced solar sailorbits with passive controlrdquo Journal of Guidance Control andDynamics vol 31 no 3 pp 782ndash785 2008
[7] S Gong H Baoyin and J Li ldquoSolar sail three-body transfertrajectory designrdquo Journal of Guidance Control and Dynamicsvol 33 no 3 pp 873ndash886 2010
Mathematical Problems in Engineering 25
[8] S Gong J Li H Baoyin and J Simo ldquoA new solar sail orbitrdquoScience China Technological Sciences vol 55 no 3 pp 848ndash8552012
[9] Y Tsuda O Mori R Funase et al ldquoAchievement of IKAROS-Japanese deep space solar sail demonstration missionrdquo ActaAstronautica vol 82 no 2 pp 183ndash188 2013
[10] L Johnson MWhorton A Heaton R Pinson G Laue and CAdams ldquoNanoSail-D a solar sail demonstration missionrdquo ActaAstronautica vol 68 no 5-6 pp 571ndash575 2011
[11] B Wie and D Murphy ldquoSolar-sail attitude control design for asail flight validation missionrdquo Journal of Spacecraft and Rocketsvol 44 no 4 pp 809ndash821 2007
[12] B Wie D Murphy M Paluszek and S Thomas ldquoRobust atti-tude control systems design for solar sails part 1 propellantlessprimaryACSrdquo inProceedings of the AIAAGuidance Navigationand Control Conference and Exhibit Providence RI USAAugust 2004
[13] B Wie D Murphy M Paluszek and S Thomas ldquoRobust atti-tude control systems design for solar sails part 2 MicroPPT-based secondary ACSrdquo in Proceedings of the AIAA GuidanceNavigation and Control Conference and Exhibit pp 1325ndash1340Providence RI USA August 2004
[14] S Thomas M Paluszek B Wie and D Murphy ldquoAOCS per-formance and stability validation for large flexible solar sailspacecraftrdquo in Proceedings of the 41st AIAAASMESAEASEEJoint Propulsion Conference amp Exhibit Tucson Ariz USA 2005
[15] B Wie ldquoDynamic modeling and attitude control of solar sailspacecraft part Irdquo in Proceedings of the AIAAGuidance Naviga-tion and Control Conference and Exhibit Monterey Calif USAAugust 2002
[16] BWie ldquoSolar sail attitude control and dynamics part 1rdquo Journalof Guidance Control and Dynamics vol 27 no 4 pp 526ndash5352004
[17] B Wie ldquoDynamic modeling and attitude control of solar sailspacecraft part IIrdquo in Proceedings of the AIAA Guidance Nav-igation and Control Conference and Exhibit Monterey CalifUSA August 2002
[18] BWie ldquoSolar sail attitude control and dynamics part 2rdquo Journalof Guidance Control and Dynamics vol 27 no 4 pp 536ndash5442004
[19] C Luo and J-H Zheng ldquoSolar-sail attitude control based onmoving masses and roll stabilizer barsrdquo Journal of HarbinInstitute of Technology vol 43 no 3 pp 95ndash101 2011
[20] D Romagnoli and T Oehlschlagel ldquoHigh performance twodegrees of freedom attitude control for solar sailsrdquo Advances inSpace Research vol 48 no 11 pp 1869ndash1879 2011
[21] C Scholz D Romagnoli B Dachwald and S Theil ldquoPerfor-mance analysis of an attitude control system for solar sails usingsliding massesrdquo Advances in Space Research vol 48 no 11 pp1822ndash1835 2011
[22] A Bolle and C Circi ldquoSolar sail attitude control through in-plane moving massesrdquo Journal of Aerospace Engineering vol222 no 1 pp 81ndash94 2008
[23] M RotunnoM Basso A B Pome andM Sallusti ldquoA compari-son of robust attitude control techniques for a solar sail space-craftrdquo in Proceedings of the AIAA Guidance Navigation andControl Conference and Exhibit San Francisco Calif USA2005
[24] J Zhang K Zhai and T Wang ldquoControl of large angle maneu-vers for the flexible solar sailrdquo Science China Physics Mechanicsand Astronomy vol 54 no 4 pp 770ndash776 2011
[25] J Zhang andTWang ldquoCoupled attitude-orbit control of flexiblesolar sail for displaced solar orbitrdquo Journal of Spacecraft andRockets vol 50 no 3 pp 675ndash685 2013
[26] Q Li XMa and TWang ldquoReducedmodel for flexible solar saildynamicsrdquo Journal of Spacecraft and Rockets vol 48 no 3 pp446ndash453 2011
[27] M Polites J Kalmanson and D Mangus ldquoSolar sail attitudecontrol using small reaction wheels and magnetic torquersrdquoProceedings of the Institution of Mechanical Engineers G Journalof Aerospace Engineering vol 222 no 1 pp 53ndash62 2008
[28] H-T Cui J-H Luo J-H Feng and P-Y Cui ldquoAttitudecontrol of solar sail spacecraft with control boomrdquo Journal ofAstronautics vol 29 no 2 pp 560ndash566 2008
[29] E Mettler and S R Ploen ldquoSolar sail dynamics and controlusing a boom mounted bus articulated by a bi-state two-axisgimbal and reaction wheelsrdquo in Proceedings of the AIAAAASAstrodynamics Specialist Conference and Exhibit MontereyCalif USA August 2002
[30] J Luo X Li and J Feng ldquoPassive attitude control of solar sailspacecraftrdquo Flight Dynamics vol 26 no 5 pp 47ndash50 2008
[31] J Luo Study on attitude control of solar sail spaceraft [PhDthesis] School of Astronautics Harbin Institute of TechnologyHarbin China 2007
[32] D A Lawrence and S W Piggott ldquoIntegrated trajectory andattitude control for a four-vane solar sailrdquo in Proceedings ofthe AIAA Guidance Navigation and Control Conference andExhibit pp 2416ndash2431 San Francisco Calif USA August 2005
[33] E Mettler A B Acikmese and S R Ploen ldquoAttitude dynamicsand control of solar sails with articulated vanesrdquo in Proceedingsof the AIAA Guidance Navigation and Control Conference andExhibit pp 2396ndash2415 San Francisco Calif USA August 2005
[34] S N Adeli V J Lappas and B Wie ldquoA scalable bus-basedattitude control system for Solar Sailsrdquo Advances in SpaceResearch vol 48 no 11 pp 1836ndash1847 2011
[35] R Funase Y Shirasawa Y Mimasu et al ldquoOn-orbit verificationof fuel-free attitude control system for spinning solar sailutilizing solar radiation pressurerdquo Advances in Space Researchvol 48 no 11 pp 1740ndash1746 2011
[36] B Fu and F O Eke ldquoAttitude control methodology for largesolar sailsrdquo in AIAA Guidance Navigation and Control (GNC)Conference 2013
[37] J Liu N Cui F Shen and S Rong ldquoDynamics of highly-flexiblesolar sail subjected to various forcesrdquoActaAstronautica vol 103pp 55ndash72 2014
[38] J F Liu S Y Rong and J G Li ldquoAttitude dynamics modelingand control of large flexible solar sail spacecraftrdquo in Proceedingsof the 3rd International Symposium on Systems and Control inAeronautics and Astronautics (ISSCAA rsquo10) pp 243ndash247 IEEEPublications Piscataway NJ USA 2010
[39] S Gong H Baoyin and J Li ldquoCoupled attitude-orbit dynamicsand control for displaced solar orbitsrdquo Acta Astronautica vol65 no 5-6 pp 730ndash737 2009
Submit your manuscripts athttpwwwhindawicom
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
MathematicsJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Mathematical Problems in Engineering
Hindawi Publishing Corporationhttpwwwhindawicom
Differential EquationsInternational Journal of
Volume 2014
Applied MathematicsJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Probability and StatisticsHindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Journal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Mathematical PhysicsAdvances in
Complex AnalysisJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
OptimizationJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
CombinatoricsHindawi Publishing Corporationhttpwwwhindawicom Volume 2014
International Journal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Operations ResearchAdvances in
Journal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Function Spaces
Abstract and Applied AnalysisHindawi Publishing Corporationhttpwwwhindawicom Volume 2014
International Journal of Mathematics and Mathematical Sciences
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
The Scientific World JournalHindawi Publishing Corporation httpwwwhindawicom Volume 2014
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Algebra
Discrete Dynamics in Nature and Society
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Decision SciencesAdvances in
Discrete MathematicsJournal of
Hindawi Publishing Corporationhttpwwwhindawicom
Volume 2014 Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Stochastic AnalysisInternational Journal of
Mathematical Problems in Engineering 23
0 1000 2000 3000 4000 5000
0 1000 2000 3000 4000 5000
minus01
0
01
minus02
0
02
4800 4850 4900 4950 5000
4800 4850 4900 4950 5000
With GFWithout GF
With GFWithout GF
With GFWithout GF
With GFWithout GF
Time (s)
Time (s)Time (s)
Time (s)
minus1
0
1
minus1
0
1
times10minus3
times10minus3Th
e disp
lace
men
t of t
he ti
p (m
)
The d
ispla
cem
ent o
f the
tip
(m)
The v
eloci
ty o
f the
tip
(ms
)
The v
eloci
ty o
f the
tip
(ms
)
Figure 15 Vibration displacement and velocity of the tip
B =
[[[[[[[[[[[[[[
[
0 0 0 0 0
1 0 0 0 0
0 0 0 0 0
0 1 0 0 0
0 0 0 0 0
0 0 1 0 0
0 0 0 0 0
0 0 0 1 0
0 0 0 0 0
0 0 0 0 1
]]]]]]]]]]]]]]
]
1198861= minus
1198981198971198972
119869119909
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus4
5119869119909
1198981198971198972
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198862= minus
1198981198971198972
119869119909
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus4
5119869119909
1198981198971198972
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198863= minus
1198981198971198972
119869119909
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus4
5119869119909
1198981198971198972
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198864= minus
1198981198971198972
119869119909
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus4
5119869119909
1198981198971198972
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
119906120593=
119876120593
119869119909
+
119906
119869119909
+119898
1198971198972
119869119909
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+4
5119869119909
1198981198971198972
+
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198865=
1
2119869119910
1198981198971198972
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+2
5119869119910
1198981198971198972
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198866=
1
2119869119910
1198981198971198972
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+2
5119869119910
1198981198971198972
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198867=
1
2119869119910
1198981198971198972
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+2
5119869119910
1198981198971198972
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198868=
1
2119869119910
1198981198971198972
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
24 Mathematical Problems in Engineering
+2
5119869119910
1198981198971198972
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
119906120579=
119876120579
119869119910
+119906
120579
119869119910
minus1
2119869119910
1198981198971198972
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119910
1198981198971198972
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198869= minus
1
2119869119911
1198972
119898119897
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988610
= minus1
2119869119911
1198972
119898119897
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988611
= minus1
2119869119911
1198972
119898119897
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988612
= minus1
2119869119911
1198972
119898119897
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
119906120595=
119876120595
119869119911
+
119906
119869119911
+1
2119869119911
1198972
119898119897
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+2
5119869119911
1198972
119898119897
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988613
= minus
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988614
= minus
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988615
= minus
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988616
= minus
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
1199061198811
=
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988617
= minus
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988618
= minus
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988619
= minus
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988620
= minus
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1199061198812
=
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(A2)
Conflict of Interests
The authors declare that there is no conflict of interestsregarding the publication of this paper
Acknowledgments
The authors would like to thank the anonymous reviewers fortheir critical and constructive review of the paper This studywas cosupported by the National Natural Science Foundationof China (Project no 11302134 11272101)
References
[1] M Colin Solar Sailing Technology Dynamics and MissionApplications Springer-Praxis London UK 1st edition 1999
[2] V Lappas SWokesM Leipold A Lyngvi and P Falkner ldquoGui-dance and control for an Interstellar Heliopause Probe (IHP)solar sail mission to 200 AUrdquo in Proceedings of the AIAAGuidance Navigation and Control Conference and Exhibit pp2472ndash2492 San Francisco Calif USA August 2005
[3] L Charlotte C Camilla and C McInnes ldquoSolar radiation pres-sure augmented deorbiting fromhigh altitude sun-synchronousorbitsrdquo in Proceedings of the 4S Symposium 2012 Small SatellitesSystems and Services Portoroz Slovenia 2012
[4] M Ceriotti and C RMcInnes ldquoGeneration of optimal trajecto-ries for Earth hybrid pole sittersrdquo Journal of Guidance Controland Dynamics vol 34 no 3 pp 847ndash859 2011
[5] S Gong J Li andH Baoyin ldquoSolar sail transfer trajectory fromL1 point to sub-L1 pointrdquoAerospace Science and Technology vol15 no 7 pp 544ndash554 2011
[6] S Gong J Li and H Baoyin ldquoAnalysis of displaced solar sailorbits with passive controlrdquo Journal of Guidance Control andDynamics vol 31 no 3 pp 782ndash785 2008
[7] S Gong H Baoyin and J Li ldquoSolar sail three-body transfertrajectory designrdquo Journal of Guidance Control and Dynamicsvol 33 no 3 pp 873ndash886 2010
Mathematical Problems in Engineering 25
[8] S Gong J Li H Baoyin and J Simo ldquoA new solar sail orbitrdquoScience China Technological Sciences vol 55 no 3 pp 848ndash8552012
[9] Y Tsuda O Mori R Funase et al ldquoAchievement of IKAROS-Japanese deep space solar sail demonstration missionrdquo ActaAstronautica vol 82 no 2 pp 183ndash188 2013
[10] L Johnson MWhorton A Heaton R Pinson G Laue and CAdams ldquoNanoSail-D a solar sail demonstration missionrdquo ActaAstronautica vol 68 no 5-6 pp 571ndash575 2011
[11] B Wie and D Murphy ldquoSolar-sail attitude control design for asail flight validation missionrdquo Journal of Spacecraft and Rocketsvol 44 no 4 pp 809ndash821 2007
[12] B Wie D Murphy M Paluszek and S Thomas ldquoRobust atti-tude control systems design for solar sails part 1 propellantlessprimaryACSrdquo inProceedings of the AIAAGuidance Navigationand Control Conference and Exhibit Providence RI USAAugust 2004
[13] B Wie D Murphy M Paluszek and S Thomas ldquoRobust atti-tude control systems design for solar sails part 2 MicroPPT-based secondary ACSrdquo in Proceedings of the AIAA GuidanceNavigation and Control Conference and Exhibit pp 1325ndash1340Providence RI USA August 2004
[14] S Thomas M Paluszek B Wie and D Murphy ldquoAOCS per-formance and stability validation for large flexible solar sailspacecraftrdquo in Proceedings of the 41st AIAAASMESAEASEEJoint Propulsion Conference amp Exhibit Tucson Ariz USA 2005
[15] B Wie ldquoDynamic modeling and attitude control of solar sailspacecraft part Irdquo in Proceedings of the AIAAGuidance Naviga-tion and Control Conference and Exhibit Monterey Calif USAAugust 2002
[16] BWie ldquoSolar sail attitude control and dynamics part 1rdquo Journalof Guidance Control and Dynamics vol 27 no 4 pp 526ndash5352004
[17] B Wie ldquoDynamic modeling and attitude control of solar sailspacecraft part IIrdquo in Proceedings of the AIAA Guidance Nav-igation and Control Conference and Exhibit Monterey CalifUSA August 2002
[18] BWie ldquoSolar sail attitude control and dynamics part 2rdquo Journalof Guidance Control and Dynamics vol 27 no 4 pp 536ndash5442004
[19] C Luo and J-H Zheng ldquoSolar-sail attitude control based onmoving masses and roll stabilizer barsrdquo Journal of HarbinInstitute of Technology vol 43 no 3 pp 95ndash101 2011
[20] D Romagnoli and T Oehlschlagel ldquoHigh performance twodegrees of freedom attitude control for solar sailsrdquo Advances inSpace Research vol 48 no 11 pp 1869ndash1879 2011
[21] C Scholz D Romagnoli B Dachwald and S Theil ldquoPerfor-mance analysis of an attitude control system for solar sails usingsliding massesrdquo Advances in Space Research vol 48 no 11 pp1822ndash1835 2011
[22] A Bolle and C Circi ldquoSolar sail attitude control through in-plane moving massesrdquo Journal of Aerospace Engineering vol222 no 1 pp 81ndash94 2008
[23] M RotunnoM Basso A B Pome andM Sallusti ldquoA compari-son of robust attitude control techniques for a solar sail space-craftrdquo in Proceedings of the AIAA Guidance Navigation andControl Conference and Exhibit San Francisco Calif USA2005
[24] J Zhang K Zhai and T Wang ldquoControl of large angle maneu-vers for the flexible solar sailrdquo Science China Physics Mechanicsand Astronomy vol 54 no 4 pp 770ndash776 2011
[25] J Zhang andTWang ldquoCoupled attitude-orbit control of flexiblesolar sail for displaced solar orbitrdquo Journal of Spacecraft andRockets vol 50 no 3 pp 675ndash685 2013
[26] Q Li XMa and TWang ldquoReducedmodel for flexible solar saildynamicsrdquo Journal of Spacecraft and Rockets vol 48 no 3 pp446ndash453 2011
[27] M Polites J Kalmanson and D Mangus ldquoSolar sail attitudecontrol using small reaction wheels and magnetic torquersrdquoProceedings of the Institution of Mechanical Engineers G Journalof Aerospace Engineering vol 222 no 1 pp 53ndash62 2008
[28] H-T Cui J-H Luo J-H Feng and P-Y Cui ldquoAttitudecontrol of solar sail spacecraft with control boomrdquo Journal ofAstronautics vol 29 no 2 pp 560ndash566 2008
[29] E Mettler and S R Ploen ldquoSolar sail dynamics and controlusing a boom mounted bus articulated by a bi-state two-axisgimbal and reaction wheelsrdquo in Proceedings of the AIAAAASAstrodynamics Specialist Conference and Exhibit MontereyCalif USA August 2002
[30] J Luo X Li and J Feng ldquoPassive attitude control of solar sailspacecraftrdquo Flight Dynamics vol 26 no 5 pp 47ndash50 2008
[31] J Luo Study on attitude control of solar sail spaceraft [PhDthesis] School of Astronautics Harbin Institute of TechnologyHarbin China 2007
[32] D A Lawrence and S W Piggott ldquoIntegrated trajectory andattitude control for a four-vane solar sailrdquo in Proceedings ofthe AIAA Guidance Navigation and Control Conference andExhibit pp 2416ndash2431 San Francisco Calif USA August 2005
[33] E Mettler A B Acikmese and S R Ploen ldquoAttitude dynamicsand control of solar sails with articulated vanesrdquo in Proceedingsof the AIAA Guidance Navigation and Control Conference andExhibit pp 2396ndash2415 San Francisco Calif USA August 2005
[34] S N Adeli V J Lappas and B Wie ldquoA scalable bus-basedattitude control system for Solar Sailsrdquo Advances in SpaceResearch vol 48 no 11 pp 1836ndash1847 2011
[35] R Funase Y Shirasawa Y Mimasu et al ldquoOn-orbit verificationof fuel-free attitude control system for spinning solar sailutilizing solar radiation pressurerdquo Advances in Space Researchvol 48 no 11 pp 1740ndash1746 2011
[36] B Fu and F O Eke ldquoAttitude control methodology for largesolar sailsrdquo in AIAA Guidance Navigation and Control (GNC)Conference 2013
[37] J Liu N Cui F Shen and S Rong ldquoDynamics of highly-flexiblesolar sail subjected to various forcesrdquoActaAstronautica vol 103pp 55ndash72 2014
[38] J F Liu S Y Rong and J G Li ldquoAttitude dynamics modelingand control of large flexible solar sail spacecraftrdquo in Proceedingsof the 3rd International Symposium on Systems and Control inAeronautics and Astronautics (ISSCAA rsquo10) pp 243ndash247 IEEEPublications Piscataway NJ USA 2010
[39] S Gong H Baoyin and J Li ldquoCoupled attitude-orbit dynamicsand control for displaced solar orbitsrdquo Acta Astronautica vol65 no 5-6 pp 730ndash737 2009
Submit your manuscripts athttpwwwhindawicom
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
MathematicsJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Mathematical Problems in Engineering
Hindawi Publishing Corporationhttpwwwhindawicom
Differential EquationsInternational Journal of
Volume 2014
Applied MathematicsJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Probability and StatisticsHindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Journal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Mathematical PhysicsAdvances in
Complex AnalysisJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
OptimizationJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
CombinatoricsHindawi Publishing Corporationhttpwwwhindawicom Volume 2014
International Journal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Operations ResearchAdvances in
Journal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Function Spaces
Abstract and Applied AnalysisHindawi Publishing Corporationhttpwwwhindawicom Volume 2014
International Journal of Mathematics and Mathematical Sciences
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
The Scientific World JournalHindawi Publishing Corporation httpwwwhindawicom Volume 2014
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Algebra
Discrete Dynamics in Nature and Society
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Decision SciencesAdvances in
Discrete MathematicsJournal of
Hindawi Publishing Corporationhttpwwwhindawicom
Volume 2014 Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Stochastic AnalysisInternational Journal of
24 Mathematical Problems in Engineering
+2
5119869119910
1198981198971198972
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
119906120579=
119876120579
119869119910
+119906
120579
119869119910
minus1
2119869119910
1198981198971198972
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119910
1198981198971198972
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1198869= minus
1
2119869119911
1198972
119898119897
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988610
= minus1
2119869119911
1198972
119898119897
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988611
= minus1
2119869119911
1198972
119898119897
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988612
= minus1
2119869119911
1198972
119898119897
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
minus2
5119869119911
1198972
119898119897
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
119906120595=
119876120595
119869119911
+
119906
119869119911
+1
2119869119911
1198972
119898119897
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
+2
5119869119911
1198972
119898119897
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988613
= minus
(119890
1198812
1198891198811
minus 1198901198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988614
= minus
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988615
= minus
(119890
1198812
1198891198812
minus 1198901198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988616
= minus
(119890
1198812
119889
1198812
minus 119890
1198812
119889
1198812
)
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
1199061198811
=
119890
1198812
1198761198811
minus 119889
1198812
1198761198812
(119890
1198812
119889
1198811
minus 119890
1198811
119889
1198812
)
11988617
= minus
(119890
1198811
1198891198811
minus 1198901198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988618
= minus
(119890
1198811
119889
1198811
minus 119890
1198811
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988619
= minus
(119890
1198811
1198891198812
minus 1198901198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
11988620
= minus
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
1199061198812
=
119890
1198811
1198761198811
minus 119889
1198811
1198761198812
(119890
1198811
119889
1198812
minus 119890
1198812
119889
1198811
)
(A2)
Conflict of Interests
The authors declare that there is no conflict of interestsregarding the publication of this paper
Acknowledgments
The authors would like to thank the anonymous reviewers fortheir critical and constructive review of the paper This studywas cosupported by the National Natural Science Foundationof China (Project no 11302134 11272101)
References
[1] M Colin Solar Sailing Technology Dynamics and MissionApplications Springer-Praxis London UK 1st edition 1999
[2] V Lappas SWokesM Leipold A Lyngvi and P Falkner ldquoGui-dance and control for an Interstellar Heliopause Probe (IHP)solar sail mission to 200 AUrdquo in Proceedings of the AIAAGuidance Navigation and Control Conference and Exhibit pp2472ndash2492 San Francisco Calif USA August 2005
[3] L Charlotte C Camilla and C McInnes ldquoSolar radiation pres-sure augmented deorbiting fromhigh altitude sun-synchronousorbitsrdquo in Proceedings of the 4S Symposium 2012 Small SatellitesSystems and Services Portoroz Slovenia 2012
[4] M Ceriotti and C RMcInnes ldquoGeneration of optimal trajecto-ries for Earth hybrid pole sittersrdquo Journal of Guidance Controland Dynamics vol 34 no 3 pp 847ndash859 2011
[5] S Gong J Li andH Baoyin ldquoSolar sail transfer trajectory fromL1 point to sub-L1 pointrdquoAerospace Science and Technology vol15 no 7 pp 544ndash554 2011
[6] S Gong J Li and H Baoyin ldquoAnalysis of displaced solar sailorbits with passive controlrdquo Journal of Guidance Control andDynamics vol 31 no 3 pp 782ndash785 2008
[7] S Gong H Baoyin and J Li ldquoSolar sail three-body transfertrajectory designrdquo Journal of Guidance Control and Dynamicsvol 33 no 3 pp 873ndash886 2010
Mathematical Problems in Engineering 25
[8] S Gong J Li H Baoyin and J Simo ldquoA new solar sail orbitrdquoScience China Technological Sciences vol 55 no 3 pp 848ndash8552012
[9] Y Tsuda O Mori R Funase et al ldquoAchievement of IKAROS-Japanese deep space solar sail demonstration missionrdquo ActaAstronautica vol 82 no 2 pp 183ndash188 2013
[10] L Johnson MWhorton A Heaton R Pinson G Laue and CAdams ldquoNanoSail-D a solar sail demonstration missionrdquo ActaAstronautica vol 68 no 5-6 pp 571ndash575 2011
[11] B Wie and D Murphy ldquoSolar-sail attitude control design for asail flight validation missionrdquo Journal of Spacecraft and Rocketsvol 44 no 4 pp 809ndash821 2007
[12] B Wie D Murphy M Paluszek and S Thomas ldquoRobust atti-tude control systems design for solar sails part 1 propellantlessprimaryACSrdquo inProceedings of the AIAAGuidance Navigationand Control Conference and Exhibit Providence RI USAAugust 2004
[13] B Wie D Murphy M Paluszek and S Thomas ldquoRobust atti-tude control systems design for solar sails part 2 MicroPPT-based secondary ACSrdquo in Proceedings of the AIAA GuidanceNavigation and Control Conference and Exhibit pp 1325ndash1340Providence RI USA August 2004
[14] S Thomas M Paluszek B Wie and D Murphy ldquoAOCS per-formance and stability validation for large flexible solar sailspacecraftrdquo in Proceedings of the 41st AIAAASMESAEASEEJoint Propulsion Conference amp Exhibit Tucson Ariz USA 2005
[15] B Wie ldquoDynamic modeling and attitude control of solar sailspacecraft part Irdquo in Proceedings of the AIAAGuidance Naviga-tion and Control Conference and Exhibit Monterey Calif USAAugust 2002
[16] BWie ldquoSolar sail attitude control and dynamics part 1rdquo Journalof Guidance Control and Dynamics vol 27 no 4 pp 526ndash5352004
[17] B Wie ldquoDynamic modeling and attitude control of solar sailspacecraft part IIrdquo in Proceedings of the AIAA Guidance Nav-igation and Control Conference and Exhibit Monterey CalifUSA August 2002
[18] BWie ldquoSolar sail attitude control and dynamics part 2rdquo Journalof Guidance Control and Dynamics vol 27 no 4 pp 536ndash5442004
[19] C Luo and J-H Zheng ldquoSolar-sail attitude control based onmoving masses and roll stabilizer barsrdquo Journal of HarbinInstitute of Technology vol 43 no 3 pp 95ndash101 2011
[20] D Romagnoli and T Oehlschlagel ldquoHigh performance twodegrees of freedom attitude control for solar sailsrdquo Advances inSpace Research vol 48 no 11 pp 1869ndash1879 2011
[21] C Scholz D Romagnoli B Dachwald and S Theil ldquoPerfor-mance analysis of an attitude control system for solar sails usingsliding massesrdquo Advances in Space Research vol 48 no 11 pp1822ndash1835 2011
[22] A Bolle and C Circi ldquoSolar sail attitude control through in-plane moving massesrdquo Journal of Aerospace Engineering vol222 no 1 pp 81ndash94 2008
[23] M RotunnoM Basso A B Pome andM Sallusti ldquoA compari-son of robust attitude control techniques for a solar sail space-craftrdquo in Proceedings of the AIAA Guidance Navigation andControl Conference and Exhibit San Francisco Calif USA2005
[24] J Zhang K Zhai and T Wang ldquoControl of large angle maneu-vers for the flexible solar sailrdquo Science China Physics Mechanicsand Astronomy vol 54 no 4 pp 770ndash776 2011
[25] J Zhang andTWang ldquoCoupled attitude-orbit control of flexiblesolar sail for displaced solar orbitrdquo Journal of Spacecraft andRockets vol 50 no 3 pp 675ndash685 2013
[26] Q Li XMa and TWang ldquoReducedmodel for flexible solar saildynamicsrdquo Journal of Spacecraft and Rockets vol 48 no 3 pp446ndash453 2011
[27] M Polites J Kalmanson and D Mangus ldquoSolar sail attitudecontrol using small reaction wheels and magnetic torquersrdquoProceedings of the Institution of Mechanical Engineers G Journalof Aerospace Engineering vol 222 no 1 pp 53ndash62 2008
[28] H-T Cui J-H Luo J-H Feng and P-Y Cui ldquoAttitudecontrol of solar sail spacecraft with control boomrdquo Journal ofAstronautics vol 29 no 2 pp 560ndash566 2008
[29] E Mettler and S R Ploen ldquoSolar sail dynamics and controlusing a boom mounted bus articulated by a bi-state two-axisgimbal and reaction wheelsrdquo in Proceedings of the AIAAAASAstrodynamics Specialist Conference and Exhibit MontereyCalif USA August 2002
[30] J Luo X Li and J Feng ldquoPassive attitude control of solar sailspacecraftrdquo Flight Dynamics vol 26 no 5 pp 47ndash50 2008
[31] J Luo Study on attitude control of solar sail spaceraft [PhDthesis] School of Astronautics Harbin Institute of TechnologyHarbin China 2007
[32] D A Lawrence and S W Piggott ldquoIntegrated trajectory andattitude control for a four-vane solar sailrdquo in Proceedings ofthe AIAA Guidance Navigation and Control Conference andExhibit pp 2416ndash2431 San Francisco Calif USA August 2005
[33] E Mettler A B Acikmese and S R Ploen ldquoAttitude dynamicsand control of solar sails with articulated vanesrdquo in Proceedingsof the AIAA Guidance Navigation and Control Conference andExhibit pp 2396ndash2415 San Francisco Calif USA August 2005
[34] S N Adeli V J Lappas and B Wie ldquoA scalable bus-basedattitude control system for Solar Sailsrdquo Advances in SpaceResearch vol 48 no 11 pp 1836ndash1847 2011
[35] R Funase Y Shirasawa Y Mimasu et al ldquoOn-orbit verificationof fuel-free attitude control system for spinning solar sailutilizing solar radiation pressurerdquo Advances in Space Researchvol 48 no 11 pp 1740ndash1746 2011
[36] B Fu and F O Eke ldquoAttitude control methodology for largesolar sailsrdquo in AIAA Guidance Navigation and Control (GNC)Conference 2013
[37] J Liu N Cui F Shen and S Rong ldquoDynamics of highly-flexiblesolar sail subjected to various forcesrdquoActaAstronautica vol 103pp 55ndash72 2014
[38] J F Liu S Y Rong and J G Li ldquoAttitude dynamics modelingand control of large flexible solar sail spacecraftrdquo in Proceedingsof the 3rd International Symposium on Systems and Control inAeronautics and Astronautics (ISSCAA rsquo10) pp 243ndash247 IEEEPublications Piscataway NJ USA 2010
[39] S Gong H Baoyin and J Li ldquoCoupled attitude-orbit dynamicsand control for displaced solar orbitsrdquo Acta Astronautica vol65 no 5-6 pp 730ndash737 2009
Submit your manuscripts athttpwwwhindawicom
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
MathematicsJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Mathematical Problems in Engineering
Hindawi Publishing Corporationhttpwwwhindawicom
Differential EquationsInternational Journal of
Volume 2014
Applied MathematicsJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Probability and StatisticsHindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Journal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Mathematical PhysicsAdvances in
Complex AnalysisJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
OptimizationJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
CombinatoricsHindawi Publishing Corporationhttpwwwhindawicom Volume 2014
International Journal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Operations ResearchAdvances in
Journal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Function Spaces
Abstract and Applied AnalysisHindawi Publishing Corporationhttpwwwhindawicom Volume 2014
International Journal of Mathematics and Mathematical Sciences
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
The Scientific World JournalHindawi Publishing Corporation httpwwwhindawicom Volume 2014
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Algebra
Discrete Dynamics in Nature and Society
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Decision SciencesAdvances in
Discrete MathematicsJournal of
Hindawi Publishing Corporationhttpwwwhindawicom
Volume 2014 Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Stochastic AnalysisInternational Journal of
Mathematical Problems in Engineering 25
[8] S Gong J Li H Baoyin and J Simo ldquoA new solar sail orbitrdquoScience China Technological Sciences vol 55 no 3 pp 848ndash8552012
[9] Y Tsuda O Mori R Funase et al ldquoAchievement of IKAROS-Japanese deep space solar sail demonstration missionrdquo ActaAstronautica vol 82 no 2 pp 183ndash188 2013
[10] L Johnson MWhorton A Heaton R Pinson G Laue and CAdams ldquoNanoSail-D a solar sail demonstration missionrdquo ActaAstronautica vol 68 no 5-6 pp 571ndash575 2011
[11] B Wie and D Murphy ldquoSolar-sail attitude control design for asail flight validation missionrdquo Journal of Spacecraft and Rocketsvol 44 no 4 pp 809ndash821 2007
[12] B Wie D Murphy M Paluszek and S Thomas ldquoRobust atti-tude control systems design for solar sails part 1 propellantlessprimaryACSrdquo inProceedings of the AIAAGuidance Navigationand Control Conference and Exhibit Providence RI USAAugust 2004
[13] B Wie D Murphy M Paluszek and S Thomas ldquoRobust atti-tude control systems design for solar sails part 2 MicroPPT-based secondary ACSrdquo in Proceedings of the AIAA GuidanceNavigation and Control Conference and Exhibit pp 1325ndash1340Providence RI USA August 2004
[14] S Thomas M Paluszek B Wie and D Murphy ldquoAOCS per-formance and stability validation for large flexible solar sailspacecraftrdquo in Proceedings of the 41st AIAAASMESAEASEEJoint Propulsion Conference amp Exhibit Tucson Ariz USA 2005
[15] B Wie ldquoDynamic modeling and attitude control of solar sailspacecraft part Irdquo in Proceedings of the AIAAGuidance Naviga-tion and Control Conference and Exhibit Monterey Calif USAAugust 2002
[16] BWie ldquoSolar sail attitude control and dynamics part 1rdquo Journalof Guidance Control and Dynamics vol 27 no 4 pp 526ndash5352004
[17] B Wie ldquoDynamic modeling and attitude control of solar sailspacecraft part IIrdquo in Proceedings of the AIAA Guidance Nav-igation and Control Conference and Exhibit Monterey CalifUSA August 2002
[18] BWie ldquoSolar sail attitude control and dynamics part 2rdquo Journalof Guidance Control and Dynamics vol 27 no 4 pp 536ndash5442004
[19] C Luo and J-H Zheng ldquoSolar-sail attitude control based onmoving masses and roll stabilizer barsrdquo Journal of HarbinInstitute of Technology vol 43 no 3 pp 95ndash101 2011
[20] D Romagnoli and T Oehlschlagel ldquoHigh performance twodegrees of freedom attitude control for solar sailsrdquo Advances inSpace Research vol 48 no 11 pp 1869ndash1879 2011
[21] C Scholz D Romagnoli B Dachwald and S Theil ldquoPerfor-mance analysis of an attitude control system for solar sails usingsliding massesrdquo Advances in Space Research vol 48 no 11 pp1822ndash1835 2011
[22] A Bolle and C Circi ldquoSolar sail attitude control through in-plane moving massesrdquo Journal of Aerospace Engineering vol222 no 1 pp 81ndash94 2008
[23] M RotunnoM Basso A B Pome andM Sallusti ldquoA compari-son of robust attitude control techniques for a solar sail space-craftrdquo in Proceedings of the AIAA Guidance Navigation andControl Conference and Exhibit San Francisco Calif USA2005
[24] J Zhang K Zhai and T Wang ldquoControl of large angle maneu-vers for the flexible solar sailrdquo Science China Physics Mechanicsand Astronomy vol 54 no 4 pp 770ndash776 2011
[25] J Zhang andTWang ldquoCoupled attitude-orbit control of flexiblesolar sail for displaced solar orbitrdquo Journal of Spacecraft andRockets vol 50 no 3 pp 675ndash685 2013
[26] Q Li XMa and TWang ldquoReducedmodel for flexible solar saildynamicsrdquo Journal of Spacecraft and Rockets vol 48 no 3 pp446ndash453 2011
[27] M Polites J Kalmanson and D Mangus ldquoSolar sail attitudecontrol using small reaction wheels and magnetic torquersrdquoProceedings of the Institution of Mechanical Engineers G Journalof Aerospace Engineering vol 222 no 1 pp 53ndash62 2008
[28] H-T Cui J-H Luo J-H Feng and P-Y Cui ldquoAttitudecontrol of solar sail spacecraft with control boomrdquo Journal ofAstronautics vol 29 no 2 pp 560ndash566 2008
[29] E Mettler and S R Ploen ldquoSolar sail dynamics and controlusing a boom mounted bus articulated by a bi-state two-axisgimbal and reaction wheelsrdquo in Proceedings of the AIAAAASAstrodynamics Specialist Conference and Exhibit MontereyCalif USA August 2002
[30] J Luo X Li and J Feng ldquoPassive attitude control of solar sailspacecraftrdquo Flight Dynamics vol 26 no 5 pp 47ndash50 2008
[31] J Luo Study on attitude control of solar sail spaceraft [PhDthesis] School of Astronautics Harbin Institute of TechnologyHarbin China 2007
[32] D A Lawrence and S W Piggott ldquoIntegrated trajectory andattitude control for a four-vane solar sailrdquo in Proceedings ofthe AIAA Guidance Navigation and Control Conference andExhibit pp 2416ndash2431 San Francisco Calif USA August 2005
[33] E Mettler A B Acikmese and S R Ploen ldquoAttitude dynamicsand control of solar sails with articulated vanesrdquo in Proceedingsof the AIAA Guidance Navigation and Control Conference andExhibit pp 2396ndash2415 San Francisco Calif USA August 2005
[34] S N Adeli V J Lappas and B Wie ldquoA scalable bus-basedattitude control system for Solar Sailsrdquo Advances in SpaceResearch vol 48 no 11 pp 1836ndash1847 2011
[35] R Funase Y Shirasawa Y Mimasu et al ldquoOn-orbit verificationof fuel-free attitude control system for spinning solar sailutilizing solar radiation pressurerdquo Advances in Space Researchvol 48 no 11 pp 1740ndash1746 2011
[36] B Fu and F O Eke ldquoAttitude control methodology for largesolar sailsrdquo in AIAA Guidance Navigation and Control (GNC)Conference 2013
[37] J Liu N Cui F Shen and S Rong ldquoDynamics of highly-flexiblesolar sail subjected to various forcesrdquoActaAstronautica vol 103pp 55ndash72 2014
[38] J F Liu S Y Rong and J G Li ldquoAttitude dynamics modelingand control of large flexible solar sail spacecraftrdquo in Proceedingsof the 3rd International Symposium on Systems and Control inAeronautics and Astronautics (ISSCAA rsquo10) pp 243ndash247 IEEEPublications Piscataway NJ USA 2010
[39] S Gong H Baoyin and J Li ldquoCoupled attitude-orbit dynamicsand control for displaced solar orbitsrdquo Acta Astronautica vol65 no 5-6 pp 730ndash737 2009
Submit your manuscripts athttpwwwhindawicom
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
MathematicsJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Mathematical Problems in Engineering
Hindawi Publishing Corporationhttpwwwhindawicom
Differential EquationsInternational Journal of
Volume 2014
Applied MathematicsJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Probability and StatisticsHindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Journal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Mathematical PhysicsAdvances in
Complex AnalysisJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
OptimizationJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
CombinatoricsHindawi Publishing Corporationhttpwwwhindawicom Volume 2014
International Journal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Operations ResearchAdvances in
Journal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Function Spaces
Abstract and Applied AnalysisHindawi Publishing Corporationhttpwwwhindawicom Volume 2014
International Journal of Mathematics and Mathematical Sciences
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
The Scientific World JournalHindawi Publishing Corporation httpwwwhindawicom Volume 2014
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Algebra
Discrete Dynamics in Nature and Society
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Decision SciencesAdvances in
Discrete MathematicsJournal of
Hindawi Publishing Corporationhttpwwwhindawicom
Volume 2014 Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Stochastic AnalysisInternational Journal of
Submit your manuscripts athttpwwwhindawicom
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
MathematicsJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Mathematical Problems in Engineering
Hindawi Publishing Corporationhttpwwwhindawicom
Differential EquationsInternational Journal of
Volume 2014
Applied MathematicsJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Probability and StatisticsHindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Journal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Mathematical PhysicsAdvances in
Complex AnalysisJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
OptimizationJournal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
CombinatoricsHindawi Publishing Corporationhttpwwwhindawicom Volume 2014
International Journal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Operations ResearchAdvances in
Journal of
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Function Spaces
Abstract and Applied AnalysisHindawi Publishing Corporationhttpwwwhindawicom Volume 2014
International Journal of Mathematics and Mathematical Sciences
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
The Scientific World JournalHindawi Publishing Corporation httpwwwhindawicom Volume 2014
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Algebra
Discrete Dynamics in Nature and Society
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Decision SciencesAdvances in
Discrete MathematicsJournal of
Hindawi Publishing Corporationhttpwwwhindawicom
Volume 2014 Hindawi Publishing Corporationhttpwwwhindawicom Volume 2014
Stochastic AnalysisInternational Journal of