Path: FormationFlying/SafeGuidance
% Closed form solution of relative orbital motion using Hills equations.
Relative state expressed in Spacecraft-Local-Orbit (SLO) coordinate frame.
Since version 10.
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Form:
X = HillsEqnsSLO( Xo, w, t )
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Inputs
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Xo (6,nSC) Initial state in SLO frame, length unit [L], velocity unit [L/sec]
* each column is the state of a s/c, [x; y; z; xdot; ydot; zdot]
w (1) Orbital Rate (rad/s)
t (:) time vector (sec)
flag (1,1) If entered, the output is formatted as a (6,nSC) matrix.
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Outputs
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X (6*nSC,:) Position and velocity over time
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