Hi all! I’m starting to work on some deployment models for a payload concept and wanted some clarification on how to implement a maneuver. If I use a numerical propagator with an initial keplerian orbit - I should be able to apply a maneuver at some time (t) via the 1st parameter. As per the API, I an using the LofOffset Attitude provider (with the TNW frame). So for a tangential burn, I would apply this thrust in the direction [1,0,0]. The questions I have is what is the specific relationship when the Isp, duration and thrust that Orekit is expecting?