I am simulating the trajectory of my vehicle as “Earth-Orbiting Spacecraft”, e.g. with Kepler parameters. However, I have some problems replicating the Kepler orbit from the ECEF coordinates and velocities defined in the receiver_antenna.csv.
Transformation from ECEF to ECI and computing the kepler elements yield oscullating elements in my case. Does Skydel model more than a two-body orbit when “Earth-Orbiting Spacecraft” is selcted? If no, what conventions do you follow to transform ECEF to ECI coordaintes and what is the source of the default Earth Orientation Parameters?