PropagateTLE:

Path: Orbit/OrbitMechanics

--------------------------------------------------------------------------
   Propagates the NORAD two line elements, ex. SGP, SGP4, SGP8. 
   SGP4 output is in the TEME frame - true equator, mean equinox.
   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 NORAD, LoadNORAD, ConvertNORAD.
--------------------------------------------------------------------------
   Form:
   [r,v,x] = PropagateTLE( tVec, file, model )
   [r,v,x] = PropagateTLE( tVec, x, model )
--------------------------------------------------------------------------

   ------
   Inputs
   ------
   tVec          (1,:)   Time vector (sec)
   file          (1,:)   File name OR converted data structure
   model         (1,:)   Model type 'SGP', 'SGP4', 'SDP4', 'SGP8', 'SGD8'
                           The default model is SGP4.

   -------
   Outputs
   -------
   r      (3,:) or {:}   Position vectors
   v      (3,:) or {:}   Velocity vectors
   x             (:)     Structure of NORAD element data

--------------------------------------------------------------------------
	References:	Hoots, F. R. and R. L. Roehrich, "Spacetrack Report No. 3:
               Models for Propagation of NORAD Element Sets", Dec. 1980.
--------------------------------------------------------------------------

Children:

Orbit: OrbitCoord/ConvertNORAD
OrbitMiniToolbox: Support/GMSTime

Back to the Orbit Module page