Idea is to transform specific cartesian state vector to a TLE such that if SGP4 is initialized with those parameters, it would produce the state vector if propagated to that epoch.
the method is
transform the cartesian state vector to purely keplerian orbit parameters
Use these as a starting point for an optimization method:
We vary all 6 orbital parameters in the TLE. The objective function runs SGP4 and figures out the sum of squares error in the position and velocity vectors.
Idea is to transform specific cartesian state vector to a TLE such that if SGP4 is initialized with those parameters, it would produce the state vector if propagated to that epoch.
the method is
We vary all 6 orbital parameters in the TLE. The objective function runs SGP4 and figures out the sum of squares error in the position and velocity vectors.