Name

CL_mod_expDensityDrag — Atmospheric drag using exponential density model

Calling Sequence

   [acc]=CL_mod_expDensityDrag(altitude,cbal[,er,mu])
   
   

Description

  • This function computes the acceleration acc due to atmospheric drag using exponential density model (CL_mod_expDensity).

    Inputs are satellite's ballistic coefficient cbal and satellite's altitude altitude

  • Last update : 12/09/2007

Parameters

altitude:

satellite's altitude [m] (1xN)

cbal:

satellite's ballistic coefficient : S*cx/m with S=equivalent drag surface, cx = drag coefficient, m = mass [m^2/kg](1xN)

er:

(optional) equatorial radius [m] (default is %CL_eqRad)

mu:

(optional) geocentric gravitational constant [m^3/s^2] (default value is %CL_mu)

acc:

drag acceleration [m/s^2] (1xN)

Authors

CNES - DCT/SB

See also

CL_cw_diffDrag, CL_mod_expDensity

Bibliography

1 Mecanique spatiale, CNES - Cepadues 1995, Tome II, 13.4.1.3

Examples

[acc]=CL_mod_expDensityDrag([350000,360000,350000,360000],[2.2,2.3,2.3,2.2])