The above question may sound naive. I am trying to understand how satellite ground track can be computed when satellite position and velocity vectors are available from on-board GPS receiver of a low earth orbiting satellite.

  • $\begingroup$ Here is half of the answer - the other half is converting from ECEF to ECI. $\endgroup$ – Chris Sep 7 '16 at 15:22
  • $\begingroup$ @ Chris I got the conversion from ECI state vectors to keplerian elements. But how to convert state vector ECEF frame to ECI frame. $\endgroup$ – Soumajit Sep 12 '16 at 15:17

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