| acceleration(FieldSpacecraftState, CalculusFieldElement[]) |  | 100% | | 100% | 0 | 3 | 0 | 8 | 0 | 1 |
| acceleration(SpacecraftState, double[]) | | 100% | | 100% | 0 | 3 | 0 | 7 | 0 | 1 |
| addContribution(FieldSpacecraftState, FieldTimeDerivativesEquations) | | 100% | | 100% | 0 | 2 | 0 | 5 | 0 | 1 |
| addContribution(SpacecraftState, TimeDerivativesEquations) | | 100% | | 100% | 0 | 2 | 0 | 5 | 0 | 1 |
| getParametersDrivers() | | 100% | | 100% | 0 | 2 | 0 | 6 | 0 | 1 |
| getAttitudeModelParameters(CalculusFieldElement[]) | | 100% | | 100% | 0 | 2 | 0 | 2 | 0 | 1 |
| getAttitudeModelParameters(double[]) | | 100% | | 100% | 0 | 2 | 0 | 2 | 0 | 1 |
| getManeuverTriggersParameters(CalculusFieldElement[]) | | 100% | | n/a | 0 | 1 | 0 | 3 | 0 | 1 |
| getManeuverTriggersParameters(double[]) | | 100% | | n/a | 0 | 1 | 0 | 3 | 0 | 1 |
| getName() | | 100% | | 100% | 0 | 2 | 0 | 4 | 0 | 1 |
| Maneuver(AttitudeRotationModel, ManeuverTriggers, PropulsionModel) | | 100% | | n/a | 0 | 1 | 0 | 5 | 0 | 1 |
| init(SpacecraftState, AbsoluteDate) | | 100% | | n/a | 0 | 1 | 0 | 3 | 0 | 1 |
| init(FieldSpacecraftState, FieldAbsoluteDate) | | 100% | | n/a | 0 | 1 | 0 | 3 | 0 | 1 |
| getFieldEventDetectors(Field) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
| getPropulsionModelParameters(CalculusFieldElement[]) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getEventDetectors() | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
| getPropulsionModelParameters(double[]) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getControl3DVectorCostType() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getAttitudeOverride() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getPropulsionModel() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getManeuverTriggers() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| dependsOnPositionOnly() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |