| basicPropagate(AbsoluteDate) |   | 69% | | 50% | 1 | 2 | 3 | 10 | 0 | 1 |
| getMass(AbsoluteDate) | | 0% | | n/a | 1 | 1 | 1 | 1 | 1 | 1 |
| resetIntermediateState(SpacecraftState, boolean) | | 0% | | n/a | 1 | 1 | 1 | 1 | 1 | 1 |
| AggregateBoundedPropagator(Collection) | | 100% | | n/a | 0 | 1 | 0 | 8 | 0 | 1 |
| AggregateBoundedPropagator(NavigableMap, AbsoluteDate, AbsoluteDate) | | 100% | | n/a | 0 | 1 | 0 | 8 | 0 | 1 |
| getPropagator(AbsoluteDate) | | 100% | | 100% | 0 | 2 | 0 | 4 | 0 | 1 |
| lambda$new$1(AbsoluteDate, BoundedPropagator) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| lambda$new$0(BoundedPropagator) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getPosition(AbsoluteDate, Frame) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getPVCoordinates(AbsoluteDate, Frame) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| propagateOrbit(AbsoluteDate) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getInitialState() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| resetInitialState(SpacecraftState) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getPropagatorsMap() | | 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 |