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SUPPORT SITE |
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SUPPORT SITE |
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Path: Orbit/OrbitManeuver
% Computes the delta-V to lower apogee. Generates the time to the maneuver which is done at perigee. It is assumed that the maneuver is an impulse. Type OrbMnvrLowerApogee for a circularization demo. -------------------------------------------------------------------------- Form: [deltaV, tToM] = OrbMnvrLowerApogee( el0, rAF, mu ) -------------------------------------------------------------------------- ------ Inputs ------ elI (1,6) Initial elements [a i W w e M] rAF (1,1) Final apogee mu (1,1) Gravitational parameter (Earth is the default) ------- Outputs ------- deltaV (1,1) Delta-V tOF (1,1) Time to maneuver --------------------------------------------------------------------------
Common: Graphics/Plot3D Orbit: OrbitCoord/RPRA2AE Orbit: OrbitMechanics/RVOrbGen OrbitMiniToolbox: Support/El2RV SC: BasicOrbit/Period SC: BasicOrbit/VOrbit
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