OrbitDrag:

Path: Orbit/OrbitMechanics

% Approximate the acceleration due to drag over an orbit arc, h0 to hF.
   Uses AtmDens2.

   Since version 2014.1
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   Form:
   [a,t,rho] = OrbitDrag( v0, gamma0, h, BC );
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   ------
   Inputs
   ------
   v0              (1,:)     Initial velocity at h0 (km/s)
   gamma0          (1,:)     Initial flight path angle at h0 (rad)
   h               (1,:)     Altitude (km)
   bC              (1,1)     Ballistic coefficient (kg/m^2)

   -------
   Outputs
   -------
   a               (1,:)     Acceleration over arc (km/s/s)
   t               (1,:)     Time (monotonic from 0) over arc (s)
   rho             (1,:)     Atmospheric density over arc (kg/m^3)

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Children:

AerospaceUtils: AtmosphericCalculations/AtmDens2
Orbit: OrbitMechanics/OrbitVel2D

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