NORAD:

Path: Orbit/OrbitMechanics

% Propagates the NORAD two line elements, ex. SGP, SGP4, SGP8. 
 
   [] can be entered for any input. To input a time vector, pass it in for
   dStart and pass an empty matrix ([]) for dEnd and nPts.
   file can be a file name or a string input. The string must have the
   same format as the file for example:

   s = [sprintf('SGPTest \n'),...
   sprintf('1 88888U          80275.98708465  .00073094  13844-3  66816-4 0     8\n'),...
   sprintf('2 88888  72.8435 115.9689 0086731  52.6988  110.5714 16.05824518  105')];

   See also LoadNORAD, ConvertNORAD, TNORAD, and PropagateTLE.

   Since version 2.
--------------------------------------------------------------------------
   Forms:
   rV = NORAD( dStart, dEnd, nPts, model, [], file )
   rV = NORAD( tVec, [], [], model, [], file )
   NORAD( tVec, [], [], model, pType, file ), creates desired plot type
--------------------------------------------------------------------------

   ------
   Inputs
   ------
   dStart    (1,1) or (1,:)   Days from Epoch of start or time vector (sec)
   dEnd          (1,1)        Days from Epoch of end
   nPts          (1,1)        Number of points
   model         (1,:)        Model type 'SGP', 'SGP4', 'SDP4', 'SGP8', 'SGD8'
   pType         (1,:)        Either '2d' or '3d' plot, 3d is default
   file          (1,:)        File name

   -------
   Outputs
   -------
   rV            (n)     Structure for position and velocity vectors
                         rV.v    (3,:)
                         rV.r    (3,:)
                         rV.name (1,:)
   x             (n)     Structure of NORAD element data

--------------------------------------------------------------------------

Children:

Common: Graphics/TitleS
Common: Time/Date2JD
Orbit: OrbitCoord/ConvertNORAD
Orbit: OrbitMechanics/PropagateTLE
Orbit: Visualization/OrbTrack

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