Path: Orbit/OrbitManeuver
% Computes two impulses needed to transfer between two elliptical coplanar orbits.
Transfers from periapsis of 1 to apoapsis of 2.
Since version 1.
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Form:
[dv, dv1, dv2, et, at] = DVHohE( e1, a1, e2, a2, mu )
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Inputs
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e1 Eccentricity of first orbit
a1 Semi-major axis of first orbit
e2 Eccentricity of final orbit
a2 Semi-major axis of final orbit
mu Gravitational parameter
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Outputs
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dv Total delta v
dv1 Low orbit to transfer orbit delta v
dv2 Transfer orbit to high orbit delta v
et Transfer orbit eccentricity
at Transfer orbit semimajor axis
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References: Kaplan, M., Modern Spacecraft Dynamics and Control, John
Wiley, pp. 87-88.
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Orbit: OrbitCoord/A2Apogee Orbit: OrbitCoord/A2Perige Common: General/DeBlankLT 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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