EarthOrbitDragDemo:

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.

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  See also:   AeroF, Constant, Date2JD, Period, RVFromKepler,
  SolarFluxPrediction, AtmJ70, EarthRte, Skew, ECIToEF, FOrbCart, Mag,
  TimeLabl,Plot2D, 
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%
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   Copyright (c) 2013 Princeton Satellite Systems, Inc.
   All rights reserved.
   Since version 11
   2025.1 Update to use AeroF for drag calculation
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Children:

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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