Path: Orbit/OrbitManeuver
% Delta-V for an longitude and inclination change maneuver for a circular orbit.
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Form:
[deltaV, u] = OrbMnvrLongAndIncl( v, iI, iF, deltaLon, mu )
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Inputs
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v (1,1) Velocity
iI (1,1) Initial orbit inclination (rad)
iF (1,1) Final orbit inclination (rad)
deltaLon (1,1) Change in longitude
mu (1,1) Gravitational parameter
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Outputs
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deltaV (1,1) Delta-V data structure.
.total (1,1) Total required delta-V
u (1,1) Argument of latitude for the common points
.final (1,1) Final latitude (rad)
.initial (1,1) Initial latitude (rad)
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Reference: Vallado, D. A. (1997.) Fundamentals of Astrodynamics and
Applications. p. 306.
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