Path: FormationFlying/Analysis
% Test the LPEccentricGVE 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] = TestLPEccentricGVE( el0, xH0, nu0, xHF, nuF, 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
nu0 (1) Initial true anomaly
xHF (6,1) Final/desired Hill's-frame state
nuF (1) Final true anomaly
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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