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 |