Path: Orbit/OrbitMechanics
% Propagates the NORAD two line elements (TLE), 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.
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Forms:
rV = NORAD( dStart, dEnd, nPts, model, [], file )
rV = NORAD( tVec, [], [], model, [], file )
NORAD( tVec, [], [], model, pType, file ), creates desired plot type
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Inputs
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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
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Outputs
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rV (n) Structure for position and velocity vectors
rV.v (3,:)
rV.r (3,:)
rV.name (1,:)
x (n) Structure of NORAD element data
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Orbit: OrbitCoord/ConvertNORAD Orbit: OrbitMechanics/PropagateTLE Orbit: Visualization/OrbTrack Common: Graphics/TitleS Common: Time/Date2JD
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