Path: Orbit/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. ------------------------------------------------------------------------- See also: AeroF, Constant, Date2JD, Period, RVFromKepler, SolarFluxPrediction, AtmJ70, EarthRte, Skew, ECIToEF, FOrbCart, Mag, TimeLabl,Plot2D, ------------------------------------------------------------------------- % ------------------------------------------------------------------------- Copyright (c) 2013 Princeton Satellite Systems, Inc. All rights reserved. Since version 11 2025.1 Update to use AeroF for drag calculation -------------------------------------------------------------------------
AerospaceUtils: AtmosphericCalculations/AtmJ70 AerospaceUtils: Coord/ECIToEF Orbit: OrbitMechanics/Period Orbit: OrbitSim/RVFromKepler Orbit: RHSOrbit/FOrbCart SC: Disturbances/AeroF SC: Environs/SolarFluxPrediction SC: Ephem/EarthRte Common: Database/Constant Common: Graphics/Plot2D Common: Graphics/TimeLabl Common: Time/Date2JD Common: Time/JD2T Math: Integration/RK4 Math: Linear/Mag Math: Linear/Skew Math: Linear/Unit
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