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 |