Path: Orbit/OrbitMechanics
% Propagates the ephemeris one step. Since version 1. -------------------------------------------------------------------------- Form: [el, jd, uSun, uMoon, uNadir, radiusEarth] = PropEph( elStart, jd, dT, mu ) -------------------------------------------------------------------------- ------ Inputs ------ elStart (1,6) Initial Keplerian orbital elements [a,i,W,w,e,M] (angles in rad) jd Julian date (days) dT (:) Time step (sec) mu Gravitational parameter for the earth ------- Outputs ------- el (6,:) Keplerian orbital elements jd Julian date (days) uSun (3,:) Sun unit vector uMoon (3,:) Moon unit vector uNadir (3,:) Earth unit vector radiusEarth (:) Earth angular radius (rad) --------------------------------------------------------------------------
SC: BasicOrbit/CP2I 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: Ephem/MoonV2 SC: Ephem/SunV1 Common: CommonData/SwooshWatermark Common: General/CellToMat Common: General/DispWithTitle Common: General/MatToCell Common: General/Watermark Common: Graphics/NewFig Common: Graphics/Plot2D Common: Graphics/PltStyle Common: Time/DTSToDTA Common: Time/Date2JD Math: Linear/DupVect Math: Linear/Mag Math: Linear/Unit Math: Trigonometry/CosD Math: Trigonometry/SinD
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