AeroF:

Path: SC/Disturbances

%   Compute the aerodynamic forces on a set of elemental areas.
   The velocity vector and normal vectors must be in the same frame.

   Since version 10.
--------------------------------------------------------------------------
   Form:
   [f,fT] = AeroF( rho, cD, v, normal, area )
--------------------------------------------------------------------------
 
   ------
   Inputs
   ------
   rho           (1,1) Atmospheric density (kg/m3)
   cD            (1,1) Coefficient of drag
   v             (3,1) Velocity relative to the atmosphere (km/s)
   normal        (3,n) Surface normal vectors
   area          (n)   Elemental area (m2)
 
   -------
   Outputs
   -------
   f             (3,n) Aero force on elements (N)
   fT            (3,1) Total force on body
 
--------------------------------------------------------------------------
	  Reference: Hughes, P. C., "Spacecraft Attitude Dynamics"
                John Wiley and Sons, 1986, pp. 251.
--------------------------------------------------------------------------

Children:

Math: Linear/Mag

Back to the SC Module page