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SUPPORT SITE |
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SUPPORT SITE |
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Path: Orbit/OrbitMechanics
% Convert NORAD to Keplerian elements.
s 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')];
A file may contain multiple sets of elements.
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Form:
[el, name] = NORADToEl( jDStart, jDEnd, nPts, model, s )
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Inputs
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dStart (1,1) Days from Epoch of start
dEnd (1,1) Days from Epoch of end
nPts (1,1) Number of points
model (1,:) Model type 'SGP', 'SGP4', 'SDP4', 'SGP8', 'SGD8'
s (1,:) File name or string containing the two line elements
* includes demo
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Outputs
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el (:,6) Elements vector [a,i,W,w,e,M]
name {:} Satellite name
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Common: Graphics/Plot2D Orbit: OrbitMechanics/NORAD Orbit: OrbitMechanics/RVOrbGen SC: BasicOrbit/RV2El
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