| propagate(AbsoluteDate, boolean) |   | 90% | | 90% | 1 | 6 | 3 | 36 | 0 | 1 |
| propagate(AbsoluteDate, AbsoluteDate) | | 80% | | 75% | 2 | 5 | 1 | 10 | 0 | 1 |
| propagate(AbsoluteDate) | | 80% | | 75% | 2 | 5 | 1 | 10 | 0 | 1 |
| getCompleteState(double, double[]) | | 100% | | 100% | 0 | 6 | 0 | 22 | 0 | 1 |
| createODE(AbstractIntegrator) | | 100% | | 100% | 0 | 2 | 0 | 12 | 0 | 1 |
| getManagedAdditionalStates() | | 100% | | 100% | 0 | 2 | 0 | 6 | 0 | 1 |
| isAdditionalStateManaged(String) | | 100% | | 100% | 0 | 4 | 0 | 6 | 0 | 1 |
| setAttitudeProvider(AttitudeProvider) | | 100% | | n/a | 0 | 1 | 0 | 3 | 0 | 1 |
| addAdditionalEquations(AdditionalEquations) | | 100% | | 100% | 0 | 2 | 0 | 4 | 0 | 1 |
| setOrbitType(OrbitType) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
| setPositionAngleType(PositionAngle) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
| setMu(double) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
| setMasterMode(OrekitStepHandler) | | 100% | | n/a | 0 | 1 | 0 | 6 | 0 | 1 |
| setUpUserEventDetectors() | | 100% | | 100% | 0 | 2 | 0 | 3 | 0 | 1 |
| setEphemerisMode() | | 100% | | n/a | 0 | 1 | 0 | 6 | 0 | 1 |
| AbstractIntegratedPropagator(AbstractIntegrator) | | 100% | | n/a | 0 | 1 | 0 | 5 | 0 | 1 |
| setUpEventDetector(AbstractIntegrator, EventDetector) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
| getGeneratedEphemeris() | | 100% | | 100% | 0 | 2 | 0 | 3 | 0 | 1 |
| setSlaveMode() | | 100% | | 50% | 1 | 2 | 0 | 5 | 0 | 1 |
| initMapper() | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
| addEventDetector(EventDetector) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
| getOrbitType() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getPositionAngleType() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getMu() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getEventsDetectors() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| clearEventsDetectors() | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
| getCalls() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getBasicDimension() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| beforeIntegration(SpacecraftState, AbsoluteDate) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| afterIntegration() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |