I am trying to convert a state vector given from PVCoordinates into a set of coordinates in lat, lon, alt and am having trouble finding any information on the feasibility or methods of doing so

I am reasonably new to Orekit and orbital mechanics. I have so far tried to explore converting PVCoordinates to an Orbit object and exploring the methods in that class/ subclasses. I have also done some googling and have not seen anything immediately relevant re: converting state vectors or keplarian elements to a geodetic point.

Maybe its possible to convert a CartesianOrbit to a geodetic point through the use of some formulas that I found within this thread? I note that I should be aware of what frames I am working in. I believe my state vectors are in ECEF.

Thank you in advance for any help.