OptimalInPlaneDeltaV:
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Computes the delta-v's and half-orbit delays for an in-plane maneuver.
Since version 7.
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Usage:
[dV1,dV2,dV3,M,N] = OptimalInPlaneDeltaV( nOrbMin, nOrbMax, a, th0, th1, ...
delta_a, delta_th0, delta_q1, delta_q2 );
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Inputs
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nOrbMin (1) Minimum number of orbits the maneuver may last
nOrbMax (1) Maximum number of orbits the maneuver may last
a (1) Mean semi-major axis of reference [km]
th0 (1) Latitude of reference at measurement [rad]
th1 (1) Latitude at first burn [rad]
delta_a (1) Error in semi-major axis difference [km]
delta_th0 (1) Error in latitude difference [rad]
delta_q1 (1) Error in q1 difference
delta_q2 (1) Error in q2 difference
analyze (1) Flag indicating whether to analyze the
performance of this optimization (optional)
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Outputs
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dV1 (1) First delta-v [km/s]
dV2 (1) Second delta-v [km/s]
dV3 (1) Third delta-v [km/s]
M (1) Number of half-orbits between burn 1 and burn 2
N (1) Number of half-orbits between burn 1 and burn 3
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