OrbDecay:

Path: Orbit/OrbitMechanics

% Approximate time for an orbit to decay based on an exponential atmosphere.
 Default units are km.

   Type OrbDecay for a demo in earth orbit

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   Form:
   t = OrbDecay( h, cD, A, m, mu, R, rho0, hScale )
--------------------------------------------------------------------------

   ------
   Inputs
   ------
   h                  Altitudes                                  [km]
   cD                 Drag coefficient (2 to 4)
   A                  Effective satellite area                   [m2]
   m                  Satellite mass                             [kg]
   mu                 Gravitational parameter              [km3/sec2]
   R                  Planet radius                              [km]
   rho0               Base density (at zero altitude)         [kg/m3]
   hScale             Atmospheric scale height (default is 6 km) [km]

   -------
   Outputs
   -------
   t                  Decay time

--------------------------------------------------------------------------
    References: Wiesel, W. E., Spaceflight Dynamics, McGraw-Hill, 1988,
                pp. 83-86.
                Hughes, P. C., Spacecraft Attitude Dynamics, John Wiley
                1986, p. 259.
--------------------------------------------------------------------------

Children:

Common: CommonData/SwooshWatermark
Common: General/CellToMat
Common: General/MatToCell
Common: General/Watermark
Common: Graphics/NewFig
Common: Graphics/Plot2D
Common: Graphics/PltStyle

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