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Path: Orbit/OrbitCoord
% Converts perigee and apogee to semi-major axis and eccentricity
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Form:
[a, e] = RPRA2AE( rP, rA )
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Inputs
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rP (1,1) Perigee
rA (1,1) Apogee
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Outputs
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a (1,1) Semi-major axis
e (1,1) Eccentricity
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References: Bate, R.R., et. al. Fundamentals of Astrodynamics,
pp. 70-71.
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