I'm a MSC student in computer science. For my thesis I'm using SGP4 tool to propagate a LEO satellite.
If I have understood rightly, the SPG4 returns the two state vectors r and v in TEME format. (celestrak).
Here my problem: I need to obtain the Keplerian orbital parameter from those two vectors but I have some conversion trouble. I can't figure the difference between TEME and ECI. Are they the same? Can I convert from TEME with this method?