Path: Orbit/OrbitMechanics
% Compute orbit insertion velocity and flight path angle.
Since version 8.
--------------------------------------------------------------------------
Form:
[v, gamma, a, e] = OrbitInsertion( rA, phiM, rM, mu )
--------------------------------------------------------------------------
------
Inputs
------
rA (1,1) Apogee radius
phiM (1,1) Insertion true anomaly (rad)
rM (1,1) Insertion altitude
mu (1,1) Gravitational constant
-------
Outputs
-------
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
--------------------------------------------------------------------------
Reference: Bond, V. R. and M. C. Allman, "Modern Astrodynamics,"
Princeton, 1996, pp. 100-107.
--------------------------------------------------------------------------
Common: CommonData/SwooshWatermark Common: General/CellToMat Common: General/MatToCell Common: General/Watermark Common: Graphics/NewFig Common: Graphics/Plot2D Common: Graphics/PltStyle Math: Linear/Dot Math: Linear/Mag
Back to the Orbit Module page