basicPropagate(FieldAbsoluteDate) | | 71% | | 50% | 1 | 2 | 2 | 7 | 0 | 1 |
getInterpolatedState(FieldAbsoluteDate) | | 100% | | 100% | 0 | 3 | 0 | 7 | 0 | 1 |
updateAdditionalStates(FieldSpacecraftState) | | 100% | | 100% | 0 | 3 | 0 | 14 | 0 | 1 |
FieldIntegratedEphemeris(FieldAbsoluteDate, FieldAbsoluteDate, FieldAbsoluteDate, FieldStateMapper, PropagationType, FieldDenseOutputModel, FieldArrayDictionary, List, String[], int[]) | | 100% | | 100% | 0 | 2 | 0 | 15 | 0 | 1 |
resetInitialState(FieldSpacecraftState) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
resetIntermediateState(FieldSpacecraftState, boolean) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
getInitialState() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
propagateOrbit(FieldAbsoluteDate, CalculusFieldElement[]) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
getMass(FieldAbsoluteDate) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
getFrame() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
getMinDate() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
getMaxDate() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
getParametersDrivers() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |