Name

CL_cw_diffDrag — Differential acceleration drag

Calling Sequence

   [acc_diff]=CL_cw_diffDrag(altitude,cbal1,cbal2[,er,mu])
   
   

Parameters

altitude:

spacecraft (target) altitude [m] (1xN)

ballistic_coef_target:

target ballistic coefficient S*cx/m S=equivalent drag surface, cx = drag coefficient, m = mass [m^2/kg] (1xN)

ballistic_coef_chaser:

chaser ballistic coefficient S*cx/m 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_diff:

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

Description

  • Computes the differential acceleration due to drag (using exponential density model), between chaser and target (i.e : acc_drag(target) - acc_drag(chaser))
  • Last update : 08/08/2007

Authors

CNES - DCT/SB

See also

CL_mod_expDensityDrag

Bibliography

Mecanique spatiale, CNES - Cepadues 1995, Tome II, 16.3.2.4.7

Examples

[acc_diff]=CL_cw_diffDrag(350000,2.25,2.15)