Path: Orbit/OrbitManeuver
% Computes the delta-V for a change in semi-major axis.
Will perform a demo for a low earth orbit.
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Form:
deltaV = OrbMnvrSemimajor( v, a, deltaA, mu )
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Inputs
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v (1,1) Velocity
a (1,1) Semimajor axis
deltaA (1,1) Change in semimajor axis
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
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Reference: Vallado, D. A. (1997.) Fundamentals of Astrodynamics and
Applications. p. 300.
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