| tolerances(double, AbsolutePVCoordinates) |  | 0% | | n/a | 1 | 1 | 13 | 13 | 1 | 1 |
| beforeIntegration(SpacecraftState, AbsoluteDate) |  | 14% | | 16% | 3 | 4 | 5 | 7 | 0 | 1 |
| removeForceModels() | | 46% | | 50% | 1 | 2 | 4 | 8 | 0 | 1 |
| addForceModel(ForceModel) | | 89% | | 100% | 0 | 4 | 2 | 12 | 0 | 1 |
| tolerances(double, Orbit, OrbitType) | | 100% | | 100% | 0 | 4 | 0 | 29 | 0 | 1 |
| NumericalPropagator(ODEIntegrator, AttitudeProvider) | | 100% | | n/a | 0 | 1 | 0 | 9 | 0 | 1 |
| hasNewtonianAttraction() | | 100% | | 100% | 0 | 3 | 0 | 2 | 0 | 1 |
| resetInitialState(SpacecraftState) | | 100% | | 100% | 0 | 2 | 0 | 5 | 0 | 1 |
| setMu(double) | | 100% | | 100% | 0 | 2 | 0 | 4 | 0 | 1 |
| createMapper(AbsoluteDate, double, OrbitType, PositionAngle, AttitudeProvider, Frame) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| NumericalPropagator(ODEIntegrator) | | 100% | | n/a | 0 | 1 | 0 | 3 | 0 | 1 |
| getPVCoordinates(AbsoluteDate, Frame) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getMainStateEquations(ODEIntegrator) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| setIgnoreCentralAttraction(boolean) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
| superSetMu(double) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
| getAllForceModels() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| setOrbitType(OrbitType) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
| setPositionAngleType(PositionAngle) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
| setInitialState(SpacecraftState) | | 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 |