Post on 08-Oct-2019
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ESA Guidance, Navigation, and Control Section
ESA Guidance, Navigation, and Control Systems
Guillermo.Ortega@esa.int
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ESA Guidance, Navigation, and Control Section
“...Guidance, navigation and control (abbreviated GNC) is a branch of engineering dealing with the design of
systems to control the movement of space vehicles...”
KeyNote: Dresdner Automatisierungstechnischen Kolloquien. Monday 27th January 2014 - ESA Guidance, Navigation, and Control Systems
Acknowledgements and Agenda
About this talk, Definition, Terms, History, Acronyms
Guidance and Optimal Trajectories (G)
Navigation and Estimation (N)
Spacecraft Control (C)
Failure Detection, Isolation, and Recovery (FDIR)
Mission Vehicle Management (MVM)
Examples of GNC Systems:
Earth Orbiting Spacecraft
Entry, Descent, and Landing
Rendezvous and Formation Flying
Interplanetary Space Vehicles
Launchers
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Dresdner Automatisierungstechnischen
Kolloquien
Gez. Prof. Dr. techn.
Klaus Janschek
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ESA Guidance, Navigation, and Control Section
About this talk, Definition, Terms, History, Acronyms,...
KeyNote: Dresdner Automatisierungstechnischen Kolloquien. Monday 27th January 2014 - ESA Guidance, Navigation, and Control Systems
About the speaker
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Dr. Guillermo Ortega is the Head of the Guidance, Navigation and Control Section of ESA
Space engineering activities in the GNC area in ESA
Design and implement GNC systems for space vehicles including: interplanetary cruise, aero assistance, precision landing, ascent, rendezvous and docking, re-entry, formation flying and drag- free systems
Implementation of the ESA policy and requirements in the GNC area including standardisation, and overall technology planning and development
KeyNote: Dresdner Automatisierungstechnischen Kolloquien. Monday 27th January 2014 - ESA Guidance, Navigation, and Control Systems
Definitions
GUIDANCE: establishment of the desired path to follow (current, i.e. in real-time and future)NAVIGATION: establishment of the current and future stateCONTROL: actions to match the current state (navigation) with the foreseen path (guidance)
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http://www.ecss.nl
KeyNote: Dresdner Automatisierungstechnischen Kolloquien. Monday 27th January 2014 - ESA Guidance, Navigation, and Control Systems
Problem description: Position
Want to “move” a space vehicle from point “A” to point “B”
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Pt Touch-down
Pd De-orbiting
Landing
Entry and Descent
Depart from ISS
KeyNote: Dresdner Automatisierungstechnischen Kolloquien. Monday 27th January 2014 - ESA Guidance, Navigation, and Control Systems
Problem description: Attitude
Want to “slew” the axis of a space vehicle from axis “A” to axis “B”
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satellite
yaw
roll
pitch
X
Y
Z
orbit
object ofinterest
line
of s
ight
time
follow-onmaneuver
change ofobjectivemaneuver
KeyNote: Dresdner Automatisierungstechnischen Kolloquien. Monday 27th January 2014 - ESA Guidance, Navigation, and Control Systems
Simplified GNC block diagram
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S/CKINEMATICS
ATTITUDECONTROL
NAVIGATION
MissionData (guidance)
StabilizationData (guidance)
SENSORS
POSITIONCONTROL
Noise
Noise
Positions,Velocities,
Accelerations
Roll φ,Yaw ψ,Pitch ϕ
Fck
Tca
SENSORS
S/CDYNAMICS
KeyNote: Dresdner Automatisierungstechnischen Kolloquien. Monday 27th January 2014 - ESA Guidance, Navigation, and Control Systems
GNC elements
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Star tracker
Gyro
Sun sensor
Infra-red sensor
Solar panel flaps
ThrustersWheels
Guidance, Navigation, and Control
Spacecraft Dynamics and Kinematics
KeyNote: Dresdner Automatisierungstechnischen Kolloquien. Monday 27th January 2014 - ESA Guidance, Navigation, and Control Systems
MVM functional diagram
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Mission Vehicle Management (MVM)
Guidance, Navigation, and Control (GNC)
Failure, Detection, Isolation, and Recovery (FDIR)
Heath Monitoring (HM)
Guidance (G) Navigation (N) Control (C)
KeyNote: Dresdner Automatisierungstechnischen Kolloquien. Monday 27th January 2014 - ESA Guidance, Navigation, and Control Systems
Definitions
“...GUIDANCE is the determination of the desired path of travel (trajectory) from the vehicle's current location to a designated target, as well as desired changes in velocity, rotation and acceleration for following that path..”“...Astrodynamics is the application of celestial mechanics to the practical problems concerning the motion of planetary bodies and spacecraft...”“...Celestial mechanics is the branch of astronomy that deals with the motions of celestial objects...”“...TRAJECTORY is the path of a vehicle in space...”
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KeyNote: Dresdner Automatisierungstechnischen Kolloquien. Monday 27th January 2014 - ESA Guidance, Navigation, and Control Systems
Guidance Engineer Work Profile
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AscentEntry
Interplanetary
Rendezvous
Loitering
Mission ArcsDisciplines
Technologies
Propulsion
Aerodynamics
Structures
Systems Optimization
MathematicalmodelingSoftware design and
development
Informatics skills
KeyNote: Dresdner Automatisierungstechnischen Kolloquien. Monday 27th January 2014 - ESA Guidance, Navigation, and Control Systems
Johannes Kepler “3 laws” -> Year 1609
“...The orbit of every planet is an ellipse with the sun at a focus...”“...A line joining a planet and the Sun sweeps out equal areas during equal intervals of time...”“...The square of the orbital period of a planet is directly proportional to the cube of the semi-major axis of its orbit...”
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KeyNote: Dresdner Automatisierungstechnischen Kolloquien. Monday 27th January 2014 - ESA Guidance, Navigation, and Control Systems
Isaac Newton “3 laws” -> Year 1687
“...An object at rest tends to stay at rest and that an object in uniform motion tends to stay in uniform motion unless acted upon by a net external force...”“...An applied force on an object equals the rate of change of its momentum with time...”“...For every action there is an equal and opposite reaction...”
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KeyNote: Dresdner Automatisierungstechnischen Kolloquien. Monday 27th January 2014 - ESA Guidance, Navigation, and Control Systems
Albert Einstein “3 principles” -> Year 1905
“...The speed of light in the vacuum is always the same...”“...Energy is equivalent to matter...”“...The continuos space-time is curved by matter and energy...”
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KeyNote: Dresdner Automatisierungstechnischen Kolloquien. Monday 27th January 2014 - ESA Guidance, Navigation, and Control Systems
Orbital Geometry and Classic Elements
Semimajor axis (a): distance between the geometric center of the orbital ellipse with the periapsis (point of closest approach to the central body), passing through the focal
Eccentricity (e): shape of the ellipse, describing how flattened it is
Inclination (i): tilt of the ellipse with respect to the reference plane, measured at the ascending node
Longitude of the ascending node (Ω): horizontally orients the ascending node of the ellipse with respect to the reference frame
Argument of periapsis (ω): defines the orientation of the ellipse in the orbital plane, as an angle measured from the ascending node to the semimajor axis
True anomaly at epoch (ν): defines the position of the orbiting body along the ellipse at a specific time
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KeyNote: Dresdner Automatisierungstechnischen Kolloquien. Monday 27th January 2014 - ESA Guidance, Navigation, and Control Systems
Orbital Elements
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νω
Ωi
Ascending node
Vernal Equinox
ApoaxisOrbital plane
Equatorial plane
KeyNote: Dresdner Automatisierungstechnischen Kolloquien. Monday 27th January 2014 - ESA Guidance, Navigation, and Control Systems
Foundations of Trajectory Optimization
Is the process of designing a trajectory that minimizes or maximizes some measure of performance within prescribed constraint boundaries
Boundary conditions: initial conditions (launch pad), target orbit, return of rocket stages, staging conditions, visibility of ground stations, ....
Path constraints: max. dynamic pressure, max. heat load, bending moment, max. acceleration, constraints on flight path...
Performance Indices/Cost Functions: maximize payload, minimize fuel consumption, minimize cost ...
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KeyNote: Dresdner Automatisierungstechnischen Kolloquien. Monday 27th January 2014 - ESA Guidance, Navigation, and Control Systems
Definition
NAVIGATION is the process to find the present and future position and orbit of a spacecraft using a series of measurements
Step 1: MEASURING
Obtaining state vectors (x, y, z, Vx, Vy, Vz,...) at timely intervals
Step 2: DETERMINING
Reconstructing the orbit based on a set of state vectors
Step 3: PREDICTING
Forecasting the imminent future state vector
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Measurements taken
Now
Measures interval
Orbit set computation
Now
Measures interval
Orbit set prediction
Now
Measures interval
Prediction
KeyNote: Dresdner Automatisierungstechnischen Kolloquien. Monday 27th January 2014 - ESA Guidance, Navigation, and Control Systems
Sensors: Optical
Star tracker
Provides precise 3-axis inertial attitude 10” from Lost in Space (star pattern recognition)
Orbital position required for Earth pointing
New generation: APS (CMOS) instead of CCD
Earth sensor
Provides 2-axis attitude w.r.t. Earth
Third axis = sun sensor or gyroscoping stiffness
0.03 deg GEO (radiance sensitivity)
Scanning or static
Sun sensor
Provides 2-axis attitude w.r.t. Sun
Either coarse analogue (acquisition) or fine digital
Navigation camera
Celestial body imaging and navigation algorithms
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Scanning infra-red Earth sensor
2-axis Digital Sun sensor
Autonomous CCD-Star Tracker
KeyNote: Dresdner Automatisierungstechnischen Kolloquien. Monday 27th January 2014 - ESA Guidance, Navigation, and Control Systems
Sensors: Inertial, Magnetic
Magnetometer
Provides (coarse) magnetic field measurement
Light and cheap sensor for acquisition in LEO
Integrating gyros
Provides integrated angular rate
High bandwidth and accuracy (but drift error)
Possible hybrid with optical sensor (Kalman filter)
Accelerometer
Stand-alone or within IMU
No space qualified European sensor
Coarse rate sensors
Provides angular rate <10 deg/h accuracy
Light and cheap sensor for de-tumble, acquisition, short term attitude propagation
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3-axis MEMS rate sensor
4-axis Fiber Optic Gyroscope
3-axis magnetometer AMR
KeyNote: Dresdner Automatisierungstechnischen Kolloquien. Monday 27th January 2014 - ESA Guidance, Navigation, and Control Systems
Estimation Techniques
Deterministic
Kalman-like estimation: Extended Kalman (EKF), Unscented Kalman (UKF), Ensemble Kalman (EnKF)
Wiener estimator (WE)
Particle filter estimators (PF)
Method of moments (MoM)
Minimum-variance unbiased estimator (MVUE)
Stochastic
Maximum likelihood estimators (ML)
Bayes estimator (BE)
Minimum mean squared error estimator (MMSE)
Maximum a posteriori estimation (MPE)
Markov chain Monte Carlo (MCMC)
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KeyNote: Dresdner Automatisierungstechnischen Kolloquien. Monday 27th January 2014 - ESA Guidance, Navigation, and Control Systems
Objectives of advanced control techniques at ESA
Ob1) Minimize the spacecraft propellant mass or overall mass, hence reducing mission costOb2) Increase the accuracy of the control when tracking or regulating the plantOb3) Increase the agility of the spacecraft maneuversOb4) Facilitate the overall design process of the GNC subsystem, hence reducing mission cost
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KeyNote: Dresdner Automatisierungstechnischen Kolloquien. Monday 27th January 2014 - ESA Guidance, Navigation, and Control Systems 28
Attitude control
Z
X
Y
yaw: ψ
roll: φ
Pitch: θ
α +α −LOS
α +
α −LOS
Thruster 1
Thruster 2
KeyNote: Dresdner Automatisierungstechnischen Kolloquien. Monday 27th January 2014 - ESA Guidance, Navigation, and Control Systems 29
Spacecraft Pointing Control
Tdist
θrealθref.
Controllaw
Satelliteplant
Sensor
Noise
+
-
e
+Y
+Z
+X
θ
ψ
φ
Pitch
Yaw
Roll
KeyNote: Dresdner Automatisierungstechnischen Kolloquien. Monday 27th January 2014 - ESA Guidance, Navigation, and Control Systems 30
Broad Control System Categories
ControlSystems
Regulators
TrackingSystems
Inputs
DisturbancesPlant
variations
Noise
Outputs
Preliminary Design Criterion: Desired RAISING TIME
Preliminary Design Criterion: Desired TRANSIENT RESPONSE
Disturbances
Plantvariations
Inputs
Outputs(Constant)
Noise
Moving Plant Poles to the
desired location
KeyNote: Dresdner Automatisierungstechnischen Kolloquien. Monday 27th January 2014 - ESA Guidance, Navigation, and Control Systems
Actuators:
Reaction Wheels
Momentum capacity 10-40 Nms, Torque up to 0.1Nm (momentum exchange)
Off-loading needs, microvibration issues
Control Momentum Gyroscopes
Gyroscopic Torque: 5 to 45 Nm, provide satellite agility
Propulsion
High to low external torque capacity, used for orbit control and initial acquisition
Efficiency Isp(s): Δm.g Isp = F.Δt = Msat.ΔV
Types:
Cold gas, hydrazine, bi-liquid
Electric propulsion (high Isp, low thrust)
Magnetic torquer
Interaction with Earth magnetic field T= M x B
LEO: acquisition/safe mode and RW off-loading w/o orbit perturbation (no force)
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12 Nms Reaction wheel
400N main engine
Magnetic torquer
CMG
KeyNote: Dresdner Automatisierungstechnischen Kolloquien. Monday 27th January 2014 - ESA Guidance, Navigation, and Control Systems
Disturbances
Disturbing torques strongly impact AOCS design
Minimized by Platform design trade-offs
Orbit and Platform configuration dependent:
Aerodynamic torque/force: LEO k.exp(-altitude), (typically mNm at 600km (Solar Array) or align with velocity)
Gravity gradient torque: LEO (GEO) 1/R3 (typically mNm at 600 km or get principal axis towards Earth)
Magnetic torque: LEO (GEO) 1/R3 (typically 10 μNm with small residual magnetic momentum)
Solar pressure torque/force: GEO (LEO) constant (typ. 10 μNm in GEO with 2 symmetrical Solar Arrays then 50 Nms wheel can provide gyroscopic stiffness)
Generated by the Satellite:
Micro-vibrations
Propellant sloshing
Orbit control thrusters: typically 1Nm
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KeyNote: Dresdner Automatisierungstechnischen Kolloquien. Monday 27th January 2014 - ESA Guidance, Navigation, and Control Systems
Advanced Control Techniques classified
Multivariable Linear-Time-Invariant systemsH-infinity, Structured Singular Value (SSV), Quantitative Feedback Theory (QFT), Model-Based Predictive Control (MPC), Linear Parameter Varying (LPV)
Multivariable Non-Linear systemsNon-Linear Dynamics Inversion (NDI), Feedback Linearization (FL), Sliding Mode Control (SMC), Numerical Optimization (NO), Fuzzy Logic Control and Neural Networks Control
Control of Distributed Parameters SystemsHuman Control Systems
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KeyNote: Dresdner Automatisierungstechnischen Kolloquien. Monday 27th January 2014 - ESA Guidance, Navigation, and Control Systems
FDIR
Different levels of complexity:
Compromise between mission continuation and spacecraft safety
Ensure smooth automatic reconfiguration in case of H/W anomaly
Ultimately go to Sun pointing Safe Mode (mission outage but S/C safety)
Implement or not independent sensors to monitor critical operations, in addition to the sensors and actuators in the loop
Redundancy
Branch A and branch B or single string
Cross strapping between units to combine A and B units
At unit level, or only electronics
example: 4 Reaction Wheels in a skewed configuration
3 out of 4: 3 RW’s being sufficient for 3-axis torque generation
False alarm risks
tuning of the monitoring threshold and time constant to avoid false alarm
Reliability
Compute probability of success over the required lifetime, based on H/W units MTBF (Mean Time Between Failure)
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KeyNote: Dresdner Automatisierungstechnischen Kolloquien. Monday 27th January 2014 - ESA Guidance, Navigation, and Control Systems
Caution and Warning
Performance factors to taken into account: controllability, stability, algorithm speed, computational loads, etc
Predefined yellow (caution) and red tubes (warning) around the nominal path have been established to mean the controllability of the system around the pre-established optimal trajectory.
In general, the FDIR system strategies shall be robust to the flight conditions at specific Mach numbers and dynamic pressures chosen by the control engineer along the complete flight path
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Caution tube
Warning tubeNominal trajectory
Real trajectory
KeyNote: Dresdner Automatisierungstechnischen Kolloquien. Monday 27th January 2014 - ESA Guidance, Navigation, and Control Systems
Role of GNC analyst in a space project
Identify relevant requirements, needs, and constraintsTrade-off alternative mission scenarios to fulfill requirementsAnalyze system budgetsDefine a mission conceptSketch a mission time-lineShare results and produce report
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KeyNote: Dresdner Automatisierungstechnischen Kolloquien. Monday 27th January 2014 - ESA Guidance, Navigation, and Control Systems
Space Project Phases
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Production-ground qualification testing
Detailed definition
Utilization
Disposal
ECSS-E-10 http://www.ecss.nl
B C E FD0 A
Mission needs identification
Feasibility
Preliminary definition
KeyNote: Dresdner Automatisierungstechnischen Kolloquien. Monday 27th January 2014 - ESA Guidance, Navigation, and Control Systems 40
Spacecraft MVM Life Cycle (zoomed)
Mission requirementsand performances
Orbit design,Equipment design,
Modes design
Analysis: Time & Frequency
domains and stability
Interactive simulations & animations forperformance verification
Control laws generationModes transitionFailure recovery
Computer code generation
Testing on
ground
Real processing on flight
MV
MD
esig
n
KeyNote: Dresdner Automatisierungstechnischen Kolloquien. Monday 27th January 2014 - ESA Guidance, Navigation, and Control Systems
Telecommunications
~0.12° for absolute pointing (half cone, at antenna level)
minimization of mission outage (back up modes before safe mode)
Large solar arrays (flexible modes 0.01 Hz), transfer GTO to GEO
Long lifetime (typ. 15 years) and harsh environment (radiations)
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Mission Orbit type
Artemis Geostationary
SMART-OLEV Geostationary
EDRS Geostationary
KeyNote: Dresdner Automatisierungstechnischen Kolloquien. Monday 27th January 2014 - ESA Guidance, Navigation, and Control Systems
Scientific satellites
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AOCS
Fine Sun sensor 16 Thrusters
2 Sun acquisition sensors
3-axis rate gyros 4 Control wheels
Star tracker
Quadrant star sensor
Earth limb sensor
1.000 Km
70.000 Km
Mission Orbit type
XMM Highly elliptical
INTEGRAL Highly elliptical
from 0.1° to <1 milliarcsec for absolute pointingCutting edge missions with very specific requirementsinstrument as AOCS sensorVariety of orbits: LEO, GEO, Lagrange point L2
KeyNote: Dresdner Automatisierungstechnischen Kolloquien. Monday 27th January 2014 - ESA Guidance, Navigation, and Control Systems
Observing the Earth
from 0.1° to 0.01° for absolute pointing
Angular rate stability for image acquisition: typical 0.001 °/s, agility
on-ground post-processing (image rectification and localization)
LEO: eclipse and intermittent link with Control Centre
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Mission Orbit type
Cryosat Highly elliptical
Aeolus Circular, Sun Synchornous
Goce Circular
Sentinel Circular
KeyNote: Dresdner Automatisierungstechnischen Kolloquien. Monday 27th January 2014 - ESA Guidance, Navigation, and Control Systems
Navigation
~0.2° for absolute pointing Yaw steering due to non sun synchronous orbitMEO: high level of radiations
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Mission Orbit type
Galileo Constellation, circular
EGNOS Geostationary
EDRS Geostationary
KeyNote: Dresdner Automatisierungstechnischen Kolloquien. Monday 27th January 2014 - ESA Guidance, Navigation, and Control Systems
EDL Missions and GNC
Type of entry:Ballistic:
Normally spin stabilized to keep desired attitudeNo active control (no thrusters)
ControlledUsing thrusters and/or aero-dynamics surfaces
GNC design based on mission features, constraints, and requirements
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ARD (ESA)
Huygens (ESA)
IXV (ESA)
X-38 (ESA and NASA)
KeyNote: Dresdner Automatisierungstechnischen Kolloquien. Monday 27th January 2014 - ESA Guidance, Navigation, and Control Systems
EDL Mission Sequence and Problem Description
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Entry
Descent
Landing
Entry gate
Landing point
TAEM
De-orbitInitial boundary constraints
Final boundary constraints
Path constraints
Path constraints
Marsenvironment conditions
Vehicle features
KeyNote: Dresdner Automatisierungstechnischen Kolloquien. Monday 27th January 2014 - ESA Guidance, Navigation, and Control Systems
Definitions
Trajectory optimization of entry trajectories
Ballistic or controlled
Foot prints and landing ellipses
Equilibrium glide
Path constraints and boundary constraints
maximum dynamic pressure
maximum heat-flux
maximum acceleration
angle of attack (Mach-dependent)
control reserve (equilibrium glide)
Performance indices:
minimum heat-load
maximum safety
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KeyNote: Dresdner Automatisierungstechnischen Kolloquien. Monday 27th January 2014 - ESA Guidance, Navigation, and Control Systems 50
Crew Rescue Vehicle
Development of the control laws for automatic re-entry vehicle type CRV
trajectory control
attitude control
Control target
Easy control in all possible regions of the flight
Cut-down cost for GNC adjustment to new lading sites
GNC
GPS SPS or PPS Thruster activation
Parachute controls
3-axis accelerometer
3-axis rate gyro
Flaps, rudder deflections
FADS
Alt.
Time
120 Km
10 Km
90 Km
30 Km
Parachute deployment3 Km
Roll maneuver
400 s 1600 s800 s
End of RCS; start rudder
KeyNote: Dresdner Automatisierungstechnischen Kolloquien. Monday 27th January 2014 - ESA Guidance, Navigation, and Control Systems
Rendezvous Missions and GNC
Designed to approach two spacecraft and mate them
Circular or elliptical rendezvous
Circular rendezvous governed by the Clohessy-Wiltshire equations. Elliptical much difficult
Uses a special coordinate system: Local Vertical Local Horizontal
Need a high accurate sensing suite
Need spacial propulsion systems to accurate position and slew the vehicle
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HTV (JAXA)
Progress (Rosscosmos)
ATV (ESA)
KeyNote: Dresdner Automatisierungstechnischen Kolloquien. Monday 27th January 2014 - ESA Guidance, Navigation, and Control Systems 53
Automatic Transfer Vehicle
Development of the control laws for automatic rendezvous and docking of servicing vehicles:
trajectory controlattitude control
Control targetSoft docking and structural latching operationsMore performance in the follow-up of the target docking port of the station
Flight Direction
S0S1
7000 m
2000 m
V-bar
R-bar
ISS docking port target
Local Vertical Local Horizontal coordinate
system
KeyNote: Dresdner Automatisierungstechnischen Kolloquien. Monday 27th January 2014 - ESA Guidance, Navigation, and Control Systems
Comparisons: ATV, Progress, Apollo
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KeyNote: Dresdner Automatisierungstechnischen Kolloquien. Monday 27th January 2014 - ESA Guidance, Navigation, and Control Systems
ATV rendezvous with ISS
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Flight Direction
S0S1
S2S3S4
ATV
6000 m
2000 m
V-bar
R-bar
ISS docking port target
Local Vertical Local
Horizontal coordinate
system
S52500 m500 m
[-20000 m, 0 m, 10000 m]
KeyNote: Dresdner Automatisierungstechnischen Kolloquien. Monday 27th January 2014 - ESA Guidance, Navigation, and Control Systems
Interplanetary Vehicles and GNC
Fly-by between planets
Mid-course correction maneuvers
Optimal pointing of antennae to ground stations
Station keeping in Lagrangian points
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Venus Express
Mars Express
Rosetta
KeyNote: Dresdner Automatisierungstechnischen Kolloquien. Monday 27th January 2014 - ESA Guidance, Navigation, and Control Systems
Missions Examples
High pointing accuracy on attitude stabilization
Agility on attitude slew
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Mission Orbit type
ExoMars Ascent, loitering, interplanetary, entry
Mars Sample Return
Ascent, loitering, interplanetary, entry,
rendezvous
Moon Lander
Ascent, loitering, interplanetary, entry,
rendezvous
Human Mission to Mars
Ascent, loitering, interplanetary, entry,
rendezvous
KeyNote: Dresdner Automatisierungstechnischen Kolloquien. Monday 27th January 2014 - ESA Guidance, Navigation, and Control Systems
Missions Examples
Very high accuracy in terms of attitude stabilization and control (case of LISA)
Hard survival environment for vehicles very closed to the Sun (case of SOLO)
Very long periods of trip and quick and frequent maneuvers coupling attitude and trajectory
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KeyNote: Dresdner Automatisierungstechnischen Kolloquien. Monday 27th January 2014 - ESA Guidance, Navigation, and Control Systems
GNC for launchers
Trajectory optimization of nominal ascent trajectories
Performance maps of rockets
Optimization of non-nominal trajectories: missionization
Nominal Splash down of stages
Stages fragmentation analysis and splash down locations
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Mission
Ariane-5
Soyuz
Vega
Heavy Lift Launcher
Impact Z9
Impact Z23Impact P80
KeyNote: Dresdner Automatisierungstechnischen Kolloquien. Monday 27th January 2014 - ESA Guidance, Navigation, and Control Systems
ESA rocket family
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KeyNote: Dresdner Automatisierungstechnischen Kolloquien. Monday 27th January 2014 - ESA Guidance, Navigation, and Control Systems
GNC of a Small Rocket
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