Path: Orbit/OrbitManeuver
% Delta-V to change apogee.
Computes the delta-v needed to go from a transfer orbit
to a final orbit with a plane change. Assumes that the
node line coincides with the line of apsides.
The default mu is km^3/sec^2.
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Form:
[dV, theta] = ApogeeDV( eT, iT, a2, e2, i2, mu )
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Inputs
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eT eccentricity of the transfer orbit
iT inclination of the transfer orbit (rad)
a2 semi-major axis of the final orbit
e2 eccentricity of the final orbit
i2 inclination of the final orbit (rad)
mu gravitational parameter
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Outputs
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dV total delta v
theta angle of burn with respect to the
final velocity vector
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References: Kaplan, M., Modern Spacecraft Dynamics and Control, John
Wiley & Sons, p. 91.
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Orbit: OrbitCoord/A2Apogee Common: General/DeBlankLT Common: Graphics/AxesCart Common: Graphics/Axis3D Common: Graphics/Mesh2 Common: Graphics/NewFig Common: Graphics/PltStyle Common: Graphics/XLabelS Common: Graphics/YLabelS Common: Graphics/ZLabelS Math: Linear/DupVect
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