| integrateDynamics(FieldAbsoluteDate) |   | 90% | | 87% | 1 | 5 | 2 | 31 | 0 | 1 |
| propagate(FieldAbsoluteDate) | | 79% | | 75% | 1 | 3 | 1 | 5 | 0 | 1 |
| secondary(FieldSpacecraftState) | | 96% | | 75% | 1 | 3 | 1 | 10 | 0 | 1 |
| secondaryDerivative(FieldSpacecraftState) | | 96% | | 75% | 1 | 3 | 1 | 10 | 0 | 1 |
| propagate(FieldAbsoluteDate, FieldAbsoluteDate) | | 100% | | 100% | 0 | 5 | 0 | 16 | 0 | 1 |
| convert(FieldODEStateAndDerivative) | | 100% | | 100% | 0 | 3 | 0 | 16 | 0 | 1 |
| createInitialState(FieldSpacecraftState) | | 100% | | 100% | 0 | 3 | 0 | 10 | 0 | 1 |
| updateAdditionalStatesAndDerivatives(FieldSpacecraftState, FieldODEStateAndDerivative) | | 100% | | 100% | 0 | 3 | 0 | 12 | 0 | 1 |
| getManagedAdditionalStates() | | 100% | | 100% | 0 | 2 | 0 | 6 | 0 | 1 |
| convert(FieldSpacecraftState) | | 100% | | n/a | 0 | 1 | 0 | 6 | 0 | 1 |
| FieldAbstractIntegratedPropagator(Field, FieldODEIntegrator, PropagationType) | | 100% | | n/a | 0 | 1 | 0 | 9 | 0 | 1 |
| isAdditionalStateManaged(String) | | 100% | | 100% | 0 | 4 | 0 | 7 | 0 | 1 |
| addAdditionalDerivativesProvider(FieldAdditionalDerivativesProvider) | | 100% | | 100% | 0 | 2 | 0 | 6 | 0 | 1 |
| setAttitudeProvider(AttitudeProvider) | | 100% | | n/a | 0 | 1 | 0 | 5 | 0 | 1 |
| createODE(FieldODEIntegrator) | | 100% | | 100% | 0 | 2 | 0 | 5 | 0 | 1 |
| setOrbitType(OrbitType) | | 100% | | n/a | 0 | 1 | 0 | 4 | 0 | 1 |
| setPositionAngleType(PositionAngleType) | | 100% | | n/a | 0 | 1 | 0 | 4 | 0 | 1 |
| setMu(CalculusFieldElement) | | 100% | | n/a | 0 | 1 | 0 | 4 | 0 | 1 |
| initMapper(Field) | | 100% | | n/a | 0 | 1 | 0 | 3 | 0 | 1 |
| setUpUserEventDetectors() | | 100% | | 100% | 0 | 2 | 0 | 4 | 0 | 1 |
| getEphemerisGenerator() | | 100% | | n/a | 0 | 1 | 0 | 3 | 0 | 1 |
| setUpEventDetector(FieldODEIntegrator, FieldEventDetector) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
| addEventDetector(FieldEventDetector) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
| setResetAtEnd(boolean) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
| getIntegratorName() | | 100% | | n/a | 0 | 1 | 0 | 1 | 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 |
| getAdditionalDerivativesProviders() | | 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 |
| getResetAtEnd() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| initializeAttitudeProviderForDerivatives() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| isMeanOrbit() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getPropagationType() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getCalls() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getInitialIntegrationState() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getIntegrator() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getBasicDimension() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| beforeIntegration(FieldSpacecraftState, FieldAbsoluteDate) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| afterIntegration() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |