| writeReplace() |   | 62% | | 25% | 4 | 5 | 9 | 17 | 0 | 1 |
| basicPropagate(AbsoluteDate) | | 70% | | 50% | 2 | 4 | 5 | 14 | 0 | 1 |
| propagateOrbit(AbsoluteDate) | | 0% | | n/a | 1 | 1 | 1 | 1 | 1 | 1 |
| getMass(AbsoluteDate) | | 0% | | n/a | 1 | 1 | 1 | 1 | 1 | 1 |
| IntegratedEphemeris(AbsoluteDate, AbsoluteDate, AbsoluteDate, StateMapper, boolean, ContinuousOutputModel, Map, List, String[]) | | 100% | | 100% | 0 | 3 | 0 | 14 | 0 | 1 |
| setInterpolationDate(AbsoluteDate) | | 100% | | 100% | 0 | 4 | 0 | 6 | 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 |