LPvsCF:
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Compare the delta-v and trajectory for two methods of relative orbit control.
- The "LP" method, which uses Simplex
- The "Closed-Form" method, which involves 3 in-plane burns at
half-orbit increments
Since version 7.
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Form:
[uLP,uCF,xLP,xCF] = LPvsCF( el0, g0, gF, nSPO, nOrbMvr, nOrbSim );
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Inputs
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el0 (1,6) Reference orbital elements
g0 (.) Initial state, expressed in geometric goal format
gF (.) Final state, expressed in geometric goal format
nSPO (1) Time step [sec]
nOrbMvr (1) Number of orbits to allow for maneuver
nOrbSim (1) Number of orbits to simulate (must be >= nOrbMvr)
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Outputs
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uLP (3,N) Acceleration vector from Linear Program method [m/s]
uCF (3,N) Acceleration vector from closed-form method [m/s]
xLP (6,N) State vector from Linear Program method [km; km/s]
xCF (6,N) State vector from closed-form method [km; km/s]
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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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Copyright 2004 Princeton Satellite Systems, Inc.
All rights reserved.
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Children:
FormationFlying: Control/InPlane
FormationFlying: Dynamics/DiscreteHills
FormationFlying: LP/LPCircular
FormationFlying: Transformation/Goals2DeltaElem
FormationFlying: Transformation/Goals2Hills
Math: Linear/Mag
SC: BasicOrbit/Period
