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 tOM (1,1) Time of maneuver --------------------------------------------------------------------------
Orbit: OrbitCoord/RPRA2AE Orbit: OrbitCoord/SLR Orbit: OrbitMechanics/RVOrbGen SC: BasicOrbit/CP2I SC: BasicOrbit/E2M SC: BasicOrbit/E2Nu SC: BasicOrbit/El2RV SC: BasicOrbit/M2E SC: BasicOrbit/M2EApp SC: BasicOrbit/M2EEl SC: BasicOrbit/M2EHy SC: BasicOrbit/M2Nu SC: BasicOrbit/M2NuPb SC: BasicOrbit/Nu2E SC: BasicOrbit/Nu2M SC: BasicOrbit/Period SC: BasicOrbit/RVFromKepler SC: BasicOrbit/VOrbit Common: CommonData/SwooshWatermark Common: General/CellToMat Common: General/DeBlankLT Common: General/DispWithTitle Common: General/MatToCell Common: General/Watermark Common: Graphics/Axis3D Common: Graphics/Mesh2 Common: Graphics/NewFig Common: Graphics/Plot2D Common: Graphics/Plot3D Common: Graphics/PltStyle Common: Graphics/TimeLabl Common: Graphics/XLabelS Common: Graphics/YLabelS Common: Graphics/ZLabelS Math: Linear/DupVect
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