Examples
[acc]=CL_mod_expDensityDrag([350000,360000,350000,360000],[2.2,2.3,2.3,2.2]) |  |  |
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 [m] (default is %CL_eqRad)
(optional) Gravitational constant [m^3/s^2] (default value is %CL_mu)
Drag acceleration [m/s^2] (1xN)
CNES - DCT/SB
1) Mecanique spatiale, CNES - Cepadues 1995, Tome II, 13.4.1.3
[acc]=CL_mod_expDensityDrag([350000,360000,350000,360000],[2.2,2.3,2.3,2.2]) | | |