PropagateTLECommonTime:

Path: Orbit/OrbitMechanics

% Propagates a set of NORAD two line elements with a common time frame.
   
   For each each TLE set, Propagate TLE is called with the appropriate
   "tVec" input so that the starting epoch of all trajectories is "jD0".

   If "jD0" is empty, the latest Julian date of the given TLEs is used.

   See also NORAD, LoadNORAD, ConvertNORAD, PropagateTLE

   Since version 8.
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   Form:
   [r,v,x] = PropagateTLECommonTime( jD, tVec, file, model )
   [r,v,x] = PropagateTLECommonTime( jD, tVec, x, model )
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   ------
   Inputs
   ------
   jD0           (1,1)   Epoch Julian date for all TLEs
   tVec          (1,:)   Time vector (sec). Referenced to jD0.
   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

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	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
Orbit: OrbitMechanics/PropagateTLE

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