I have zero background in Astro Physics. Using Orekit 10.3 and a friends help I was able to piece together a method that accepts a Vehicle’s State Vector along with an Epoch then performs a propagation that returns a TLE. This method seemed to work just fine, until I encountered a Highly Circular Polar Orbit, upon which my method quickly chokes yeilding “org.orekit.errors.OrekitException: invalid parameter eccentricity: -0 not in range [0, ?]”. Now this seems odd since I am certain I provided an positive eccentricity to my initial TLE, so what to do? I’d like to be able to accept an arbitrary State Vector for an Earth Orbiting body and to be able to create a TLE. Perhaps the issue is that I am using KeplerianOrbit exclusively but I’ve tried CircularOrbit and EquinoctialOrbit orbits and they were no different. However I assume my attempts were unknowingly incorrect.
I created a test project that demonstrates my problem exactly, it can be found here:
Any help would appreciated.