| convert(FieldSpacecraftState) |  | 0% | | 0% | 2 | 2 | 8 | 8 | 1 | 1 |
| convert(FieldODEStateAndDerivative) |  | 51% | | 50% | 1 | 2 | 4 | 11 | 0 | 1 |
| integrateDynamics(FieldAbsoluteDate) | | 89% | | 90% | 1 | 6 | 4 | 37 | 0 | 1 |
| propagate(FieldAbsoluteDate) | | 79% | | 75% | 1 | 3 | 1 | 5 | 0 | 1 |
| createInitialState(FieldSpacecraftState) | | 100% | | 100% | 0 | 3 | 0 | 10 | 0 | 1 |
| propagate(FieldAbsoluteDate, FieldAbsoluteDate) | | 100% | | 100% | 0 | 5 | 0 | 14 | 0 | 1 |
| createODE(FieldODEIntegrator, FieldODEState) | | 100% | | 100% | 0 | 2 | 0 | 8 | 0 | 1 |
| getCompleteState(CalculusFieldElement, CalculusFieldElement[], CalculusFieldElement[]) | | 100% | | 100% | 0 | 3 | 0 | 7 | 0 | 1 |
| getManagedAdditionalStates() | | 100% | | 100% | 0 | 2 | 0 | 6 | 0 | 1 |
| FieldAbstractIntegratedPropagator(Field, FieldODEIntegrator, PropagationType) | | 100% | | n/a | 0 | 1 | 0 | 8 | 0 | 1 |
| isAdditionalStateManaged(String) | | 100% | | 100% | 0 | 4 | 0 | 7 | 0 | 1 |
| setAttitudeProvider(AttitudeProvider) | | 100% | | n/a | 0 | 1 | 0 | 5 | 0 | 1 |
| addAdditionalEquations(FieldAdditionalEquations) | | 100% | | 100% | 0 | 2 | 0 | 5 | 0 | 1 |
| setOrbitType(OrbitType) | | 100% | | n/a | 0 | 1 | 0 | 4 | 0 | 1 |
| setPositionAngleType(PositionAngle) | | 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 |
| setUpEventDetector(FieldODEIntegrator, FieldEventDetector) | | 100% | | n/a | 0 | 1 | 0 | 5 | 0 | 1 |
| getEphemerisGenerator() | | 100% | | n/a | 0 | 1 | 0 | 3 | 0 | 1 |
| addEventDetector(FieldEventDetector) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
| setResetAtEnd(boolean) | | 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 |
| isMeanOrbit() | | 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 |