Path: Orbit/OrbitManeuver
% Computes the delta-V for a longitude only maneuver for a circular orbit.
The delta-V will have the same units as the velocity entered, using the
formula:
$$ DV = 2 v \sin(a/2) $$
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Form:
[deltaV, u] = OrbMnvrLongitude( v, i, deltaLon, mu )
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Inputs
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v (1,1) Velocity
i (1,1) Orbit inclination (rad)
deltaLon (1,:) Change in longitude (rad)
mu (1,1) Gravitational parameter (optional)
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Outputs
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deltaV (.) Delta-V data structure.
.total (1,1) Total required delta-V
.angle (1,1) Angle (rad)
u (.) 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. 304.
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