Atmospheric drag using exponential density model - DEPRECATED
acc = CL_mod_expDensityDrag(altitude, cbal [, er, mu])
This function is deprecated.
Computes the acceleration acc due to atmospheric drag using an exponential density model (expDensity with default values, see CL_mod_expDensity).
Inputs are the satellite's ballistic coefficient cbal and the satellite's altitude altitude
Satellite's altitude. [m] (1xN)
Satellite's ballistic coefficient : S*cx/m with S=equivalent drag surface, cx = drag coefficient, m = mass. [m^2/kg](1xN)
(optional) Equatorial radius. Default: %CL_eqRad. [m] (1x1)
(optional) Gravitational constant. Default: %CL_mu. [m^3/s^2] (1x1)
Drag acceleration. [m/s^2] (1xN)
CNES - DCT/SB
1) Mecanique spatiale, CNES - Cepadues 1995, Tome II, 13.4.1.3