Path: Missions/Comsat
% Updates orbital elements based on an impulsive delta-V -------------------------------------------------------------------------- Form: el = OrbitDeltaV( el, dV, mu ) -------------------------------------------------------------------------- ------ Inputs ------ el (1,6) Keplerian Elements [a,i,W,w,e,M] (angles in rad) dV (3,1) Vector delta-V mu (1,1) Gravitational constant ------- Outputs ------- el (1,6) Keplerian Elements [a,i,W,w,e,M] (angles in rad) --------------------------------------------------------------------------
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/RV2El Common: CommonData/SwooshWatermark Common: General/CellToMat Common: General/DispWithTitle Common: General/MatToCell Common: General/Watermark Common: Graphics/NewFig Common: Graphics/Plot2D Common: Graphics/PltStyle Math: Linear/Cross Math: Linear/DupVect Math: Linear/Mag
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