Path: Orbit/OrbitManeuver
% Find a coplanar orbit with a different altitude Compute the new eccentricity and semimajor axis after adding the delta altitude to both the apogee and perigee. -------------------------------------------------------------------------- Form: el2 = CoplanarOrbit( el1, deltaH ) -------------------------------------------------------------------------- ------ Inputs ------ el1 (1,6) Element set [a i W w e M] deltaH (1,1) Altitude change ------- Outputs ------- el2 (1,6) Element set [a i W w e M] --------------------------------------------------------------------------
Orbit: OrbitCoord/AE2RPRA Orbit: OrbitCoord/RPRA2AE Orbit: OrbitCoord/SLR Orbit: OrbitMechanics/RVOrbGen SC: BasicOrbit/CP2I SC: BasicOrbit/E2M SC: BasicOrbit/E2Nu SC: BasicOrbit/M2E SC: BasicOrbit/M2EApp SC: BasicOrbit/M2EEl SC: BasicOrbit/M2EHy SC: BasicOrbit/Nu2E SC: BasicOrbit/Nu2M Common: CommonData/SwooshWatermark Common: General/CellToMat Common: General/DeBlankLT Common: General/MatToCell Common: General/Watermark Common: Graphics/Axis3D Common: Graphics/Mesh2 Common: Graphics/NewFig Common: Graphics/Plot2D Common: Graphics/PltStyle Common: Graphics/TimeLabl Common: Graphics/XLabelS Common: Graphics/YLabelS Common: Graphics/ZLabelS Math: Linear/DupVect Math: Linear/Mag
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