Path: Orbit/OrbitManeuver
% Optimal inclination corrections for a Hohmann transfer with a plane change. The Hohman transfer is done from the perigee of the first orbit to the apogee of the second. -------------------------------------------------------------------------- Form: [dv, dv1, dv2, et, Di1] = OptDIH( e1, a1, e2, a2, Di, mu ) -------------------------------------------------------------------------- ------ Inputs ------ e1 Parking orbit eccentricity a1 Parking orbit semimajor axis e2 Final orbit eccentricity a2 Final orbit semimajor axis Di Change in inclination (rad) mu Gravitational parameter ------- Outputs ------- dv Total delta v dv1 Low orbit to transfer orbit delta v dv2 Transfer orbit to high orbit delta v et Transfer orbit eccentricity Di1 Inclination correction during first Dv -------------------------------------------------------------------------- References: Hornbeck, R., Numerical Methods, Quantum, 1975, pp. 66-67. --------------------------------------------------------------------------
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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