| resetIntermediateState(SpacecraftState, boolean) |  | 0% | | n/a | 1 | 1 | 1 | 1 | 1 | 1 |
| propagateOrbit(AbsoluteDate) | | 0% | | n/a | 1 | 1 | 1 | 1 | 1 | 1 |
| getMass(AbsoluteDate) | | 0% | | n/a | 1 | 1 | 1 | 1 | 1 | 1 |
| getInterpolatedState(AbsoluteDate) |  | 100% | | 100% | 0 | 3 | 0 | 7 | 0 | 1 |
| IntegratedEphemeris(AbsoluteDate, AbsoluteDate, AbsoluteDate, StateMapper, PropagationType, DenseOutputModel, Map, List, String[]) | | 100% | | 100% | 0 | 3 | 0 | 14 | 0 | 1 |
| basicPropagate(AbsoluteDate) | | 100% | | 100% | 0 | 2 | 0 | 7 | 0 | 1 |
| setAttitudeProvider(AttitudeProvider) | | 100% | | 100% | 0 | 2 | 0 | 4 | 0 | 1 |
| resetInitialState(SpacecraftState) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getInitialState() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getPVCoordinates(AbsoluteDate, Frame) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getFrame() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getMinDate() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getMaxDate() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |