Tle2Orbit

This program computes the outputfileOrbit from two-line elements (TLE/3LE) as can be found at e.g. http://celestrak.org/NORAD/elements/. The first satellite in the input file that matches the wildcard of satelliteName is used. If more records with exactly the same name are found, the one with the closest reference epoch is used for each point in the timeSeries.

The program uses the Simplified General Perturbation (SGP) model. More information can be found in the Revisiting Spacetrack Report 3 by Vallado et al. 2006.

Name	Type	Annotation
outputfileOrbit	filename
inputfileTLE	filename	two line elements (TLE/3LE)
satelliteName	string	first name of wildcard match is used
timeSeries	timeSeries	output orbit at these times
earthRotation	earthRotation	rotation to CRF