| resetInitialState(FieldSpacecraftState) |  | 0% | | n/a | 1 | 1 | 2 | 2 | 1 | 1 |
| isAdditionalDataManaged(String) |  | 93% | | 83% | 1 | 4 | 1 | 6 | 0 | 1 |
| FieldEphemeris(List, FieldTimeInterpolator, AttitudeProvider) | | 100% | | 100% | 0 | 2 | 0 | 14 | 0 | 1 |
| basicPropagate(FieldAbsoluteDate) | | 100% | | 100% | 0 | 2 | 0 | 15 | 0 | 1 |
| checkStatesDefinitionsConsistency(List) | | 100% | | 100% | 0 | 3 | 0 | 8 | 0 | 1 |
| getManagedAdditionalData() | | 100% | | n/a | 0 | 1 | 0 | 5 | 0 | 1 |
| FieldEphemeris(Field, Ephemeris) | | 100% | | n/a | 0 | 1 | 0 | 4 | 0 | 1 |
| FieldEphemeris(List, int) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
| FieldEphemeris(List, FieldTimeInterpolator) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
| checkInputConsistency(List, FieldTimeInterpolator) | | 100% | | n/a | 0 | 1 | 0 | 3 | 0 | 1 |
| resetIntermediateState(FieldSpacecraftState, boolean) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| lambda$new$0(Field, SpacecraftState) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| propagateOrbit(FieldAbsoluteDate, CalculusFieldElement[]) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getMass(FieldAbsoluteDate) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getInitialState() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getStates() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getParametersDrivers() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getMinDate() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getMaxDate() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getFrame() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getStateInterpolator() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |