Propagation with certain earth gravity field

Orekit Python Wrapper usage
21

No, the orbit in a SpacecraftState must be defined with respect to an inertial frame, not an Earth frame.

22

Ok, so if I convert position/velocity from ECEF to ECI_J2000, How can I define the SpacecraftState to give it as input for the NumericalPropagator?

23

You can build a SpecraftState directly from an Orbit, which can be a CartesianOrbit, i.e. build from position and velocity (plus frame, date and central attraction coefficient).

24

Hi @luc, After using osculating elements the propagation shows correct results.

Thank you very much for your help,

Bryan.