| addForceModel(ForceModel) |   | 81% | | 83% | 1 | 4 | 3 | 12 | 0 | 1 |
| tolerances(CalculusFieldElement, FieldOrbit, OrbitType) | | 0% | | n/a | 1 | 1 | 1 | 1 | 1 | 1 |
| resetInitialState(FieldSpacecraftState) | | 73% | | 50% | 1 | 2 | 1 | 5 | 0 | 1 |
| removeForceModels() | | 0% | | n/a | 1 | 1 | 2 | 2 | 1 | 1 |
| initializeAttitudeProviderForDerivatives() | | 81% | | 50% | 1 | 2 | 0 | 3 | 0 | 1 |
| FieldNumericalPropagator(Field, FieldODEIntegrator, AttitudeProvider) | | 100% | | n/a | 0 | 1 | 0 | 12 | 0 | 1 |
| hasNewtonianAttraction() | | 100% | | 75% | 1 | 3 | 0 | 2 | 0 | 1 |
| setMu(CalculusFieldElement) | | 100% | | 100% | 0 | 2 | 0 | 4 | 0 | 1 |
| tolerances(CalculusFieldElement, CalculusFieldElement, FieldOrbit, OrbitType) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
| createMapper(FieldAbsoluteDate, CalculusFieldElement, OrbitType, PositionAngleType, AttitudeProvider, Frame) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| FieldNumericalPropagator(Field, FieldODEIntegrator) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
| getMainStateEquations(FieldODEIntegrator) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| setIgnoreCentralAttraction(boolean) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
| superSetMu(CalculusFieldElement) | | 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(PositionAngleType) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
| setInitialState(FieldSpacecraftState) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
| getOrbitType() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| superGetOrbitType() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getPositionAngleType() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |