Path: Orbit/OrbitMechanics
% Compute orbit insertion velocity and flight path angle.
Since version 8.
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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
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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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Common: Graphics/Plot2D Math: Linear/Dot Math: Linear/Mag
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