Path: FormationFlying/Analysis
% Test the LPEccentric function.
Provide the reference orbital elements, an initial relative state and initial
true anomaly, a desired/final relative state and final true anomaly, and the
number of samples to discretize over.
Two validation methods are used. In the first, we propagate the initial state
over nS samples, applying the control acceleration found by LPEccentric. In
the second, we integrate the two inertial states, applying the same control
acceleration, but in the ECI frame. We then transform back to the Hill's frame
for comparison.
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Form:
[xH_int,xH_lin,dVTot,eT,err] = TestLPCircular( el0, xH0, xHF, dur, nS, plotFlag )
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Inputs
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el0 (6,1) Initial orbital elements [a, i, W, w, e, M]
xH0 (6,1) Initial Hill's-frame state
xHF (6,1) Final/desired Hill's-frame state
dur (1) Maneuver duration [sec]
nS (1) Number of samples to discretize over
plotFlag (1) Create plots or not (0|1)
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Outputs
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xH_int (6,1) Hill's-frame state from integrating inertial states
xH_lin (6,1) Hill's-frame state from propagating linear system
dVTot (1) Total Delta-V for maneuver [m/s]
eT (1) Time elapsed during call to LPEccentric [sec]
err (6,1) State error at end of maneuver. Found by integrating
the inertial states from t=0 and applying control,
then comparing the final state with the target state.
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