| getIsp(AbsoluteDate) |  | 0% | | n/a | 1 | 1 | 2 | 2 | 1 | 1 |
| getDirection(AbsoluteDate) | | 0% | | n/a | 1 | 1 | 1 | 1 | 1 | 1 |
| getThrustMagnitude(AbsoluteDate) | | 0% | | n/a | 1 | 1 | 1 | 1 | 1 | 1 |
| getControl3DVectorCostType() | | 0% | | n/a | 1 | 1 | 1 | 1 | 1 | 1 |
| AbstractConstantThrustPropulsionModel(double, double, Vector3D, Control3DVectorCostType, String) |  | 100% | | n/a | 0 | 1 | 0 | 6 | 0 | 1 |
| getIsp() | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
| AbstractConstantThrustPropulsionModel(double, double, Vector3D, String) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
| getDirection() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getThrustVector(SpacecraftState) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getFlowRate(SpacecraftState) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getThrustMagnitude() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getThrustVector(SpacecraftState, double[]) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getFlowRate(SpacecraftState, double[]) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getThrustVector(FieldSpacecraftState, CalculusFieldElement[]) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getFlowRate(FieldSpacecraftState, CalculusFieldElement[]) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getInitialThrustVector() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getInitialFlowRate() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getName() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| static {...} | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |