Path: FormationFlying/Analysis
% Compare two methods of computing the relative motion in an eccentric orbit.
The first case uses the homogenous LTV solution to Lawden's equations.
The second case computes the absolute trajectories of both orbits in
the ECI frame, then transforms into the relative Hill's frame.
Note: The reference elements are provided, defining one orbit. The initial
relative state is also provided, which is added to the initial
reference state to define the second orbit.
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Form:
[xH1,xH2] = FFEccFrameCompare( elRef0, xH0, nOrbits, nS, method );
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Inputs
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elRef0 (1,6) Initial elements of reference orbit
xH0 (6,1) Initial state in Hills frame
nOrbits (1) Number of orbits to simulate
nS (1) Number of samples to use
method (1) Indicate which method to use for initialization
0 - do not enforce periodic motion, use supplied xH0 exactly
1 - enforce periodic, symmetric motion about origin
2 - enforce periodic motion via fuel optimization
3 - enforce periodic motion using the velocity constraint
(only change y-velocity)
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Outputs
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xH1 (6,nS) Relative state trajectory from first case
xH2 (6,nS) Relative state trajectory from second case
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References: Inalhan, Tillerson, How, "Relative Dynamics and Control of
Spacecraft Formations in Eccentric Orbits", Journal of Guidance,
Control & Dynamics, Vol.25, No.1, Jan-Feb 2002.
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FormationFlying: Coord/GetHillsMats FormationFlying: EccDynamics/FFEccDH FormationFlying: EccDynamics/FFEccDMatPeriodic FormationFlying: EccDynamics/FFEccIntConst FormationFlying: EccDynamics/FFEccLawdensEqns FormationFlying: EccDynamics/FFEccRMat FormationFlying: Transformation/ECI2Hills FormationFlying: Transformation/Hills2ECI FormationFlying: Utility/Nu2TimeDomain FormationFlying: Utility/NuDot FormationFlying: Utility/Time2NuDomain Orbit: OrbitCoord/SLR Orbit: OrbitMechanics/RVOrbGen SC: BasicOrbit/CP2I SC: BasicOrbit/E2M SC: BasicOrbit/E2Nu SC: BasicOrbit/El2RV SC: BasicOrbit/M2E SC: BasicOrbit/M2EApp SC: BasicOrbit/M2EEl SC: BasicOrbit/M2EHy SC: BasicOrbit/M2Nu SC: BasicOrbit/M2NuPb SC: BasicOrbit/Nu2E SC: BasicOrbit/Nu2M SC: BasicOrbit/OrbRate SC: BasicOrbit/Period SC: BasicOrbit/RV2El Common: CommonData/SwooshWatermark Common: General/CellToMat Common: General/DeBlankLT Common: General/DispWithTitle Common: General/MatToCell Common: General/Watermark Common: Graphics/Axis3D Common: Graphics/Mesh2 Common: Graphics/NewFig Common: Graphics/Plot2D Common: Graphics/PltStyle Common: Graphics/TimeLabl Common: Graphics/XLabelS Common: Graphics/YLabelS Common: Graphics/ZLabelS Math: Linear/Cross Math: Linear/Dot Math: Linear/DupVect Math: Linear/Mag
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