Path: Orbit/OrbitManeuver
% Computes the delta-V for a one-tangent transfer between coplanar orbits.
The maneuver starts at E = 0 for the transfer orbit.
Will perform a demo from LEO to GEO if given less than 4 inputs.
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Form:
[deltaV, tOF] = OrbMnvrOneTangent( rI, rF, nuT, type, mu )
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Inputs
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rI (1,1) Initial radius
rF (1,1) Final radius
nuT (1,1) True anomaly between initial and final burn
type (1,1) Either 'apoapsis' or 'periapsis'
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
.a (1,1) Delta-V at point a
.b (1,1) Delta-V at point b
tOF (1,1) Time of flight
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Reference: Vallado, D. A. (1997.) Fundamentals of Astrodynamics and
Applications. pp 287-292.
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