OrbitInsertion

OrbitInsertion:

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   Compute orbit insertion velocity and flight path angle.
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   Form:
   [v, gamma, a, e] = OrbitInsertion( rA, phiM, rM, mu )
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   Inputs
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   rA              (1,1) Apogee radius
   phiM            (1,1) Insertion true anomaly (rad)
   rM              (1,1) Insertion altitude
   mu              (1,1) Gravitational constant

   -------
   Outputs
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   v               (2,1) Insertion velocity
   gamma           (1,1) Insertion flight path angle (rad)
   a               (1,1) Semi-major axis transfer orbit
   e               (1,1) Eccentricity transfer orbit

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   Reference: Bond, V. R. and M. C. Allman, "Modern Astrodynamics,"
              Princeton, 1996, pp. 100-107.
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Children:

Common: Graphics/Plot2D
Common: Math/Dot
Common: Math/Mag