Path: FormationFlying/SafeGuidance
% Relative dynamic simulation for two LEO satellites with safe guidance.
Includes differential disturbance forces for J2, drag and solar.
Explicitly calls SafeGuidance maneuver planning algorithm.
Assumptions:
- satellites have different masses
- satellites have differential area for solar pressure
- satellites have differential area for drag
- disturbances do not measurably affect reference orbit over simulation
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Form:
simData = FFRelSim( simOptions )
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Sim options fields:
elRef [a,i,W,w,e,M]
nOrbits
nPts Discretization points per orbit
distOpt Flags for [solar drag J2]
harmonicOrder
control
params
noise
flags
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