Formation Flying and Rendezvous and Docking Simulator for ... · September 2004 Formation Flying...
Transcript of Formation Flying and Rendezvous and Docking Simulator for ... · September 2004 Formation Flying...
September 2004
www.gmv.com
Formation Flying and Rendezvous and Docking Simulator for Exploration Missions
(FAMOS-V2)
Galder Bengoa, F. Alonso, D. García, M. Graziano (GMV S.A.)Dr. Guillermo Ortega (ESA/ESTEC)
2nd ESA Workshop on Astrodynamics Tools and Techniques
ESTEC 13-15 September 2004
GMVSA 4115/04
FAMOSV2 CDR2
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Presentation Contents
m Introduction to FAMOS-V2
l FAMOS-V2 Description
l General architecture
l FAMOS-V2 Propagator
m Launcher ascent
m Rendezvous and Docking
l Change of plane
l Rendezvous and Docking manoeuvres
m Validation Scenarios Overview
m FAMOS-V2 Demonstration
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FAMOSV2 Description (1)
What’s FAMOS-V2?
m SW tool designed and developed by GMV S.A., Spain, under GSTP contract with ESA/ESTEC.
What FAMOS-V2 is meant for?
m Simulate Rendezvous and Docking sequences on Circular and Elliptical orbits for exploration mission-scenarios such us: Venus, Earth, Moon, Mars, Deimos, Triton and Europa.
m Cover launching phase of the second spacecraft involved in the RvD once it has left from Earth, Moon and Mars surfaces.
How FAMOS-V2 has been developed?m Two phases:
ü Simplified Versionü Full Version
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FAMOSV2 Description (2)
FAMOS-V2 Simplified Version (1/2):
m Open loop: no sensors or actuators
m Corrective manoeuvres
m Three degrees of freedom
m Environment: drag, solar radiation, third body, non-sphericity
m Launch ascent optimisation
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FAMOSV2 Description (3)
FAMOS-V2 Simplified Version (2/2):
m Available Orbital Manoeuvres for Rendezvous:
Circular:
Ø Hopping on V-bar
Ø Hohmann Re-phasing
Ø Hohmann Transfer
Ø Two Points Transfer
Ø Continuous Tangential Transfer
Ø Continuous Hopping on V-bar
Ø Applied Delta-V
Ø Station Keeping
Ø Forced Motion
Elliptical:
Ø Hopping on V-bar
Ø Re-phasing in Time
Ø Height Transfer
Ø Two Points Transfer
Ø Applied Delta-V
Ø Station Keeping
Ø Forced Motion
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FAMOSV2 Description (4)
FAMOS-V2 Full Version: Simplified Version plus:
m Close loop: feedback of sensors and actuators
m Six degrees of freedom (translation + attitude)
m Communications module
m Guidance, Navigation and Control (GNC)
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General Architecture (1)
m Definition of inputs
m Execution of simulation
m Visualization of results
Introduction to FAMOS-V2 Execution
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General Architecture (2)
The architecture of FAMOS-V2 has been design to achieve these three tasks.
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FAMOSV2 Propagator (1)
m Full Cowell numerical propagator, Domand-Prince (ode5)l Propagation around the following
central bodies:Ø Venus, Earth, Mars, Moon, Deimos,
Europa and Triton
l Four types of perturbation can be considered:Ø Aerodynamic drag perturbation
Ø Solar radiation pressure perturbation
Ø Non-sphericity perturbation
Ø Third body perturbation
l Simplified propagator for launcher ascent:Ø J2 and Aerodynamic drag perturbations
FAMOS-V2 Propagator
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Launch Optimisation Phases
m The Launch ascent phases:l First Phase: 1st stage ignition. Launch with a small
acceleration to allow passing through the dense atmospheric layers with a low dynamic pressure.
l Second Phase: Coast arc. At this time the rocket will not have any thrust.
l Third Phase: 2nd Stage. Bi-linear tangent law.
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Launch Optimisation Variables
m Matlab “fmincon” optimiser is used, which can impose equality and inequality constraints. The optimiser tries to maximize the payload mass to be delivered into orbit.
m Aerothermal flux simulated.
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Change of Plane
Change of plane manoeuvre:
l Previous to Rendezvous and Docking manoeuvres
l Corrects inclination and RAAN for flyer satellite
l Impulsive manoeuvre: optimum points for impulses minimizing total delta-V
l Free drift until desired along track distance achieved
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Rendezvous and Docking
m “Large scale” Approach Manoeuvres:
l Rough approach
m Final Approach Manoeuvres (typically 5000-0 m):
l Precise and slow approach
l Position keeping
m Collision Avoidance Manoeuvre
m Corrective Manoeuvres
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Circular Orbits
m Circular Manoeuvres for Rendezvous:
l Impulsive Hopping on V-bar
l Impulsive Hohmann Re-phasing
l Impulsive Hohmann Transfer
l Impulsive Two Points Transfer
l Continuous Tangential Transfer
l Continuous Hopping on V-bar
l Applied Delta-V
l Station Keeping
l Forced Motion
“Large scale”approach
Final approach
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Elliptical Orbits (1)
m The aim of the elliptical approach manoeuvre is to bring, in a high elliptical orbit, the chaser to a delayed position w.r.t the target.
m Parameters provided by the user:
l Virtual manoeuvre duration or time constant (T)
l Real manoeuvre duration (Td)
l Final position defined as:
Ø Time Delay (τ) of chaser respect to target (re-phasing in time)
Ø Relative position of chaser respect to target
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Elliptical Orbits (2): Formulation
m The delayed position (only for “re-phasing in time”
manoeuvre) is expressed as :
)t(tx)(tx ftargetfchaser −→
m The Elliptical Approach algorithm is based in the
Transition Matrix:00 ),( xttx ff δδ Φ=
Where
l τ is the delay time of chaser w.r.t the target
l tf is the time at the end of the manoeuvre
m The final position is expressed respect to target.
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Elliptical Orbits (3): Available Manoeuvres
m Elliptical Manoeuvres for Rendezvous:
Ø Hopping on V-bar
Ø Re-phasing in Time
Ø Height Transfer
Ø Two Points Transfer
Ø Applied Delta-V
Ø Station Keeping
Ø Forced Motion
“Large scale”approach
Final approach
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On-going Work
m FAMOS-V2 Full version introduces the following
capabilities (available from October 2004):
l Rendezvous Attitude Dynamics
l Rendezvous Sensors
l Rendezvous Actuators
l Rendezvous Navigation (Absolute and Relative)
l Communication Module
l Additional Visualization capabilities.
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Sensors
m RF
m CAMERA
m Lidar
m IMU:
• Gyroscope
• Accelerometer
m STR
m SAS (Developed by GMV)
CO1
XSAS (Boresight)
YSAS
ZSAS
CO2
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Additional Visualization capabilities: Attitude Guidance
Fix Relative
Target Pointing
Sun Pointing
Absolute Pointing
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Validation Scenarios
m Circular:
l Mars Sample Return (Launch ascent from Mars)
l Mars Sample Return (Change of Plane & Rendezvous)
l Deimos Sample Return (RvD with Deimos)
l Human Lunar Mission (Ascent)
l Human Lunar Mission (Rendezvous)
l ATV Mission (Rendezvous)
m Elliptic
l Launch Ascent to Elliptical Orbit
l ATV RvD with Corrective Manoeuvres
l Elliptical Approach
Courtesy of NASA
Courtesy of ESA