$LastChangedDate: 27-Juil-2011 $

# CL_mod_expDensityDrag

Atmospheric drag using exponential density model

## Calling Sequence

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

## Description

- 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

## 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) 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])