| accelerationDerivatives(SpacecraftState, String) |   | 59% | | 50% | 2 | 4 | 4 | 12 | 0 | 1 |
| ConstantThrustManeuver(AbsoluteDate, double, double, double, Vector3D) | | 94% | | 100% | 0 | 2 | 2 | 19 | 0 | 1 |
| init(SpacecraftState, AbsoluteDate) | | 100% | | 100% | 0 | 11 | 0 | 8 | 0 | 1 |
| accelerationDerivatives(AbsoluteDate, Frame, FieldVector3D, FieldVector3D, FieldRotation, DerivativeStructure) | | 100% | | 100% | 0 | 2 | 0 | 7 | 0 | 1 |
| getEventsDetectors() | | 100% | | n/a | 0 | 1 | 0 | 3 | 0 | 1 |
| addContribution(SpacecraftState, TimeDerivativesEquations) | | 100% | | 100% | 0 | 2 | 0 | 6 | 0 | 1 |
| getISP() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| static {...} | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
| getParametersDrivers() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getThrust() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getFlowRate() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |