| fixState(FieldOrbit, FieldAttitude, CalculusFieldElement, CalculusFieldElement, FieldArrayDictionary, FieldArrayDictionary) |   | 84% | | 87% | 1 | 5 | 2 | 15 | 0 | 1 |
| resetInitialState(FieldSpacecraftState) | | 92% | | 50% | 1 | 2 | 0 | 10 | 0 | 1 |
| FieldKeplerianPropagator(FieldOrbit, AttitudeProvider, CalculusFieldElement, CalculusFieldElement) | | 100% | | n/a | 0 | 1 | 0 | 8 | 0 | 1 |
| propagateOrbit(FieldAbsoluteDate, CalculusFieldElement[]) | | 100% | | 100% | 0 | 2 | 0 | 4 | 0 | 1 |
| resetIntermediateState(FieldSpacecraftState, boolean) | | 100% | | 100% | 0 | 2 | 0 | 5 | 0 | 1 |
| FieldKeplerianPropagator(FieldOrbit) | | 100% | | n/a | 0 | 1 | 0 | 3 | 0 | 1 |
| FieldKeplerianPropagator(FieldOrbit, CalculusFieldElement) | | 100% | | n/a | 0 | 1 | 0 | 3 | 0 | 1 |
| FieldKeplerianPropagator(FieldOrbit, AttitudeProvider) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
| FieldKeplerianPropagator(FieldOrbit, AttitudeProvider, CalculusFieldElement) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
| getMass(FieldAbsoluteDate) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getParametersDrivers() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |