| addContribution(SpacecraftState, TimeDerivativesEquations) |  | 100% | | n/a | 0 | 1 | 0 | 4 | 0 | 1 |
| addContribution(FieldSpacecraftState, FieldTimeDerivativesEquations) | | 100% | | n/a | 0 | 1 | 0 | 4 | 0 | 1 |
| init(FieldSpacecraftState, FieldAbsoluteDate) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
| getFieldEventDetectors(Field) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getMassDerivative(FieldSpacecraftState, CalculusFieldElement[]) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getEventDetectors() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getMassDerivative(SpacecraftState, double[]) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| dependsOnAttitudeRate() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| init(SpacecraftState, AbsoluteDate) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |