AbstractConstantThrustPropulsionModel(double, double, Vector3D, String) |  | 100% | | n/a | 0 | 1 | 0 | 5 | 0 | 1 |
getIsp() |  | 100% | | n/a | 0 | 1 | 0 | 3 | 0 | 1 |
getDirection() |  | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
getThrust() |  | 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 |
getThrustVector(SpacecraftState) |  | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
getFlowRate(SpacecraftState) |  | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |