Dear all, Most people here use TLE and SGP4 combination for orbit analysis, and the output is in the ill-defined quasi-inertial TEME frame. I guess many users here would like to convert this into the Earth Fixed frame ITRF to be able to use them properly in Azimuth-Elevation based local frame setups. I wrote a Python script that defines TEME and the intermediate TIRS frames in the Astropy library and converts the TEME propagation results into the Earth Fixed ITRF and inertial GCRF (very close to J2000) frames. I explained the details in the Jupyter notebook here: https://github.com/egemenimre/satstuff/blob/master/notebooks/astropy/sgp4_teme_astropy.ipynb I tried to explain everything in a way that it can be hopefully easily applied to your programming language of preference, as long as you use the SOFA or ERFA routines under the hood for precise coordinate transformations. The SGP4 is the one from Brandon Rhodes, which in turn uses one of the standard implementations from Vallado's "Revisiting Spacetrack Report #3" paper. https://celestrak.com/publications/AIAA/2006-6753/ Any comments or questions welcome. Regards, Egemen _______________________________________________ Seesat-l mailing list http://mailman.satobs.org/mailman/listinfo/seesat-lReceived on Sun Apr 26 2020 - 09:33:27 UTC
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