CL_mod_expDensityDrag — Atmospheric drag using exponential density model
[acc]=CL_mod_expDensityDrag(altitude,cbal[,er,mu])
Inputs are satellite's ballistic coefficient cbal and 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 [m] (default is %CL_eqRad)
(optional) geocentric gravitational constant [m^3/s^2] (default value is %CL_mu)
drag acceleration [m/s^2] (1xN)