| basicPropagate(FieldAbsoluteDate) |   | 71% | | 50% | 1 | 2 | 2 | 7 | 0 | 1 |
| getInterpolatedState(FieldAbsoluteDate) | | 100% | | 100% | 0 | 3 | 0 | 7 | 0 | 1 |
| updateAdditionalStates(FieldSpacecraftState) | | 100% | | 100% | 0 | 3 | 0 | 14 | 0 | 1 |
| FieldIntegratedEphemeris(FieldAbsoluteDate, FieldAbsoluteDate, FieldAbsoluteDate, FieldStateMapper, AttitudeProvider, PropagationType, FieldDenseOutputModel, FieldArrayDictionary, List, String[], int[]) | | 100% | | 100% | 0 | 2 | 0 | 16 | 0 | 1 |
| resetInitialState(FieldSpacecraftState) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| resetIntermediateState(FieldSpacecraftState, boolean) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getInitialState() | | 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 |
| getFrame() | | 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 |
| getParametersDrivers() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |