Orbital Mechanics - Webmae-nas.eng.usu.edu › MAE_5540_Web › propulsion_systems › section2 ›...
Transcript of Orbital Mechanics - Webmae-nas.eng.usu.edu › MAE_5540_Web › propulsion_systems › section2 ›...
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MAE 5540 - Propulsion Systems
Orbital Mechanics:
Conservation of Angular Momentumand the In-plane Velocity vector
Kepler's Second & Third Laws
Sutton and Biblarz: Chapter 4
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MAE 5540 - Propulsion Systems
Kepler's Second Law
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MAE 5540 - Propulsion Systems
Incremental Area Swept Out by Radius vector
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MAE 5540 - Propulsion Systems
Area Swept out by an Elliptical Arc
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MAE 5540 - Propulsion Systems
Area Swept out by an Elliptical Arc (cont’d)
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MAE 5540 - Propulsion Systems
Area Swept out by an Elliptical Arc (concluded)
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MAE 5540 - Propulsion Systems
Total Area of an Elliptical Orbit
• But … theTotal area integralIs a “Pretty Nice”form
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MAE 5540 - Propulsion Systems
Mathematical Representation of Kepler's Second Law
T -->Orbital period
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MAE 5540 - Propulsion Systems
Area Swept from Perapsis
T = “orbit period”
t2
t1
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MAE 5540 - Propulsion Systems
Time-Of-Flight Graphs0
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MAE 5540 - Propulsion Systems
t2
t1
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MAE 5540 - Propulsion Systems
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MAE 5540 - Propulsion Systems
Time of FlightFinal position
Time of flight
t2
t1
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MAE 5540 - Propulsion Systems
Orbit Propagation … Kepler’s Equation
Solving this numerical integral for time of flight … given initial And final positions is “doable”
… but the inverse problem is numerically unstable …. and while TOF charts are good for illustrative purposes … they are impractical for orbit propagation calculations …
Fortunately …. 17th century mathematicians developed a better way
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MAE 5540 - Propulsion Systems
True and Eccentric Anomaly
• Define the angle obtained by drawing an auxiliary circle of around the ellipse, and drawing a line perpendicular to the semi-major axis and intersecting it at Point A
• The angle defined by the center radius “a” is called the “eccentric anomaly” E
A
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MAE 5540 - Propulsion Systems
True and Eccentric Anomaly
• Calculating the projectionsAlong the semi major axis
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MAE 5540 - Propulsion Systems
True and Eccentric Anomaly (cont'd)
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MAE 5540 - Propulsion Systems
True and Eccentric Anomaly (cont'd)
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MAE 5540 - Propulsion Systems
True and Eccentric Anomaly (cont'd)
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MAE 5540 - Propulsion Systems
True and Eccentric Anomaly (concluded)
After some REALLYMessy algebra …
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MAE 5540 - Propulsion Systems
FINALLY ... (WHEW!) “KEPLER'S EQUATION”
And after some even Messier algebra the “area integral” reduces to
“M” – Mean Anomaly à NormalizedOrbit Period Fraction
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MAE 5540 - Propulsion Systems
Using Mean Anomaly toPropagate the Orbital Position
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MAE 5540 - Propulsion Systems
Using Mean Anomaly toPropagate the Orbital Position
(cont'd)
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MAE 5540 - Propulsion Systems
Using Mean Anomaly toPropagate the Orbital Position
(cont'd)
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MAE 5540 - Propulsion Systems
Using Mean Anomaly toPropagate the Orbital Position
(concluded)
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MAE 5540 - Propulsion Systems
The Propagation Algorithm
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MAE 5540 - Propulsion Systems
Propagation Algorithm(continued)
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MAE 5540 - Propulsion Systems
Propagation Algorithm(continued)
Kepler’s third lawWe still need to derive this!
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MAE 5540 - Propulsion Systems
Propagation Algorithm(continued)
……… Use your Newton Solver! …………….
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MAE 5540 - Propulsion Systems
Propagation Algorithm(concluded)
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MAE 5540 - Propulsion Systems
Kepler's Second Law (Alternate form)What is the physical Interpretation?
Reconsider the “Swept Area” Integral
Let’s look at this integral in differential form …
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MAE 5540 - Propulsion Systems
Kepler's Second Law (Alternate form)What is the physical Interpretation?
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MAE 5540 - Propulsion Systems
Mathematical Representation of Kepler's Second Law (continued)
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MAE 5540 - Propulsion Systems
Torque Acting on Orbiting Space Craft
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MAE 5540 - Propulsion Systems
Angular Momentum ofAn Orbiting Spacecraft
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MAE 5540 - Propulsion Systems
Angular Momentum ofAn Orbiting Spacecraft (cont'd)
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MAE 5540 - Propulsion Systems
Angular Momentum ofAn Orbiting Spacecraft (cont’d)
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MAE 5540 - Propulsion Systems
Alternate Statement of of Kepler’sSecond law:
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MAE 5540 - Propulsion Systems
VELOCITY VECTOR
• for a while we haveOnly worried about
position… now revisit
velocity
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MAE 5540 - Propulsion Systems
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MAE 5540 - Propulsion Systems
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MAE 5540 - Propulsion Systems
Velocity Vector, Elliptical orbit
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MAE 5540 - Propulsion Systems
Velocity Vector, re-examined
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MAE 5540 - Propulsion Systems
Velocity Vector, re-examined(concluded)
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MAE 5540 - Propulsion Systems
Angular Velocity of Spacecraft
Later we’ll showThis is the same
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MAE 5540 - Propulsion Systems
Kepler's third law
Later we’ll showThis is the same
Let
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MAE 5540 - Propulsion Systems
Angular Velocity of Spacecraft (cont’d)
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MAE 5540 - Propulsion Systems
Angular Velocity of Spacecraft (cont’d)
Constant!
Not ! Constant
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MAE 5540 - Propulsion Systems
Elliptical Orbit, Normalized Angular Velocity
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MAE 5540 - Propulsion Systems
Orbital Speed -- Magnitude of the Velocity Vector (cont'd)
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MAE 5540 - Propulsion Systems
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MAE 5540 - Propulsion Systems
Orbital Speed -- Magnitude of the Velocity Vector (cont'd)
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MAE 5540 - Propulsion Systems
Orbital Speed -- Magnitude of the Velocity Vector (cont'd)
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MAE 5540 - Propulsion Systems
Orbital Speed -- Magnitude of the Velocity Vector (concluded)
Later we’ll showThis is the same
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MAE 5540 - Propulsion Systems
Kepler’s Second and Third Law Summary•
à Derives from constant angular momentum
• Swept Area Rule :
dA(t)dt=a2π 1−e2
T=
12r 2 dνdt=ω ⋅r 2
2
• Angular Momentum :
!l =!Lm= ω ⋅r 2 ⋅
!iκ
• Gravitational Torque :
τgrav =!r×!Fgrav = 0→
!Lm= const
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MAE 5540 - Propulsion Systems
Kepler’s Second and Third Law Summary (2)
• Kepler 's Third Law :
l,a,e→ const{ }→ define constant µ≡ l2
a ⋅ 1−e2( )
→ a2π 1−e2
T= l
2→T = 2 ⋅a2π 1−e2
l=
2 ⋅a2π 1−e2
µ ⋅a ⋅ 1−e2( )=
2 ⋅π
µ
⎛
⎝
⎜⎜⎜⎜⎜
⎞
⎠
⎟⎟⎟⎟⎟⋅a3/2
à Corollary to Second law
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MAE 5540 - Propulsion Systems
Kepler’s Second and Third Law Summary (3)• Angular Velocity :
ω= 1r 2
2a2π 1−e2
T• Velocity Vector :
!
V =r ⋅ω ⋅ e ⋅sinν
1+ e ⋅cosν⋅!ir
r ⋅ω ⋅!iν
⎡
⎣
⎢⎢⎢⎢⎢
⎤
⎦
⎥⎥⎥⎥⎥
→ r= a ⋅ 1−e2
1−e ⋅cosν
ω= 1r 2
2a2π 1−e2
T
⎡
⎣
⎢⎢⎢⎢⎢⎢
⎤
⎦
⎥⎥⎥⎥⎥⎥
• Normalized Angular Velocity :
ω ⋅T = 2a2π 1−e2
r 2 =2a2π 1−e2
a ⋅ 1−e2
1−ecosν
⎛
⎝⎜⎜⎜⎜
⎞
⎠⎟⎟⎟⎟
2 = 2 ⋅π ⋅1+ e ⋅cosν( )2
1−e2( )3/2
![Page 58: Orbital Mechanics - Webmae-nas.eng.usu.edu › MAE_5540_Web › propulsion_systems › section2 › sectio… · Orbital Mechanics: Conservation of Angular Momentum and the In-plane](https://reader030.fdocuments.us/reader030/viewer/2022040309/5f26543a2ff761448e4fa6da/html5/thumbnails/58.jpg)
MAE 5540 - Propulsion Systems
Kepler’s Second and Third Law Summary (4)
• Normalized Angular Velocity :
ω ⋅T = 2a2π 1−e2
r 2 =2a2π 1−e2
a ⋅ 1−e2
1−ecosν
⎛
⎝⎜⎜⎜⎜
⎞
⎠⎟⎟⎟⎟
2 = 2 ⋅π ⋅1+ e ⋅cosν( )2
1−e2( )3/2
![Page 59: Orbital Mechanics - Webmae-nas.eng.usu.edu › MAE_5540_Web › propulsion_systems › section2 › sectio… · Orbital Mechanics: Conservation of Angular Momentum and the In-plane](https://reader030.fdocuments.us/reader030/viewer/2022040309/5f26543a2ff761448e4fa6da/html5/thumbnails/59.jpg)
MAE 5540 - Propulsion Systems
• Kepler’s Second and Third Law Summary (5)
•Orbital Speed
!V
2= r 2 ⋅ω2 ⋅
e ⋅sinν1+ e ⋅cosν
⎛
⎝⎜⎜⎜
⎞
⎠⎟⎟⎟⎟
2
+1⎛
⎝
⎜⎜⎜⎜⎜
⎞
⎠
⎟⎟⎟⎟⎟⎟=
l2
a ⋅ 1−e2( )⋅
2r−
1a
⎛
⎝⎜⎜⎜
⎞
⎠⎟⎟⎟⎟≡µ ⋅
2r−
1a
⎛
⎝⎜⎜⎜
⎞
⎠⎟⎟⎟⎟
!V = 2 ⋅µ
r−µa
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MAE 5540 - Propulsion Systems
Linear Velocity of Spacecraft
• Just an alternate Form of the Energy Equation
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MAE 5540 - Propulsion Systems
Orbital Energy
• Next Isaac Newton and His Apple!
![Page 62: Orbital Mechanics - Webmae-nas.eng.usu.edu › MAE_5540_Web › propulsion_systems › section2 › sectio… · Orbital Mechanics: Conservation of Angular Momentum and the In-plane](https://reader030.fdocuments.us/reader030/viewer/2022040309/5f26543a2ff761448e4fa6da/html5/thumbnails/62.jpg)
MAE 5540 - Propulsion Systems
Linear Velocity of Spacecraft
We’ll prove this next!
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MAE 5540 - Propulsion Systems