| writeReplace() |   | 95% | | 91% | 1 | 7 | 2 | 24 | 0 | 1 |
| resetInitialState(SpacecraftState) | | 91% | | 50% | 1 | 2 | 0 | 8 | 0 | 1 |
| KeplerianPropagator(Orbit, AttitudeProvider, double, double) | | 100% | | n/a | 0 | 1 | 0 | 8 | 0 | 1 |
| fixState(Orbit, Attitude, double, double) | | 100% | | n/a | 0 | 1 | 0 | 6 | 0 | 1 |
| propagateOrbit(AbsoluteDate) | | 100% | | 100% | 0 | 2 | 0 | 4 | 0 | 1 |
| resetIntermediateState(SpacecraftState, boolean) | | 100% | | 100% | 0 | 2 | 0 | 4 | 0 | 1 |
| KeplerianPropagator(Orbit) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
| KeplerianPropagator(Orbit, AttitudeProvider) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
| KeplerianPropagator(Orbit, double) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
| KeplerianPropagator(Orbit, AttitudeProvider, double) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
| getMass(AbsoluteDate) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |