Path: Orbit/OrbitManeuver
% Computes the delta-V for an inclination correction.
Type OrbMnvrInclination for a demo.
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Form:
deltaV = OrbMnvrInclination( v, e, nu, deltaI, mu )
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Inputs
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v (1,1) Velocity (km/s)
e (1,1) Orbit eccentricity
nu (1,1) True anomaly (rad)
deltaI (1,1) Change in inclination (rad)
mu (1,1) Gravitational parameter (km^3/s^2)
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Outputs
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deltaV (1,1) Delta-V data structure.
.total (1,1) Total required delta-V (km/s)
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Reference: Vallado, D. A. (1997.) Fundamentals of Astrodynamics and
Applications. p. 300.
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