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SUPPORT SITE |
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Path: Orbit/Demos/OrbitSim
% Simple demo to compute drag over one orbit Assumes point mass s/c, two body propagation. The only perturbing acceleration considered is due to drag. Mass is assumed to be constant, fixed cross-sectional area and drag coefficient. Demo produces plots of spacecraft position and velocity (in ECI frame) and drag force (N) (in ECI frame). DV due to drag perturbation is displayed. Since version 11 ------------------------------------------------------------------------- See also: Constant, Date2JD, Period, RVFromKepler, SolarFluxPrediction, AtmJ70, EarthRte, Skew, ECIToEF, FOrbCart, Mag, TimeLabl,Plot2D, ------------------------------------------------------------------------- % ------------------------------------------------------------------------- Copyright (c) 2013 Princeton Satellite Systems, Inc. All rights reserved. -------------------------------------------------------------------------
AeroUtils: AtmosphericCalculations/AtmJ70 AeroUtils: Coord/ECIToEF Common: Database/Constant Common: Graphics/Plot2D Common: Graphics/TimeLabl Common: Time/Date2JD Common: Time/JD2T Math: Integration/RK4 Math: Linear/Mag Math: Linear/Skew OrbitMiniToolbox: Support/EarthRte SC: BasicOrbit/Period SC: BasicOrbit/RVFromKepler SC: Environs/SolarFluxPrediction
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