getInterpolatedState(AbsoluteDate) | | 100% | | 100% | 0 | 3 | 0 | 7 | 0 | 1 |
updateAdditionalStates(SpacecraftState) | | 100% | | 100% | 0 | 3 | 0 | 14 | 0 | 1 |
IntegratedEphemeris(AbsoluteDate, AbsoluteDate, AbsoluteDate, StateMapper, PropagationType, DenseOutputModel, DoubleArrayDictionary, List, String[], int[]) | | 100% | | 100% | 0 | 2 | 0 | 15 | 0 | 1 |
basicPropagate(AbsoluteDate) | | 100% | | 100% | 0 | 2 | 0 | 7 | 0 | 1 |
setAttitudeProvider(AttitudeProvider) | | 100% | | 100% | 0 | 2 | 0 | 4 | 0 | 1 |
resetInitialState(SpacecraftState) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
resetIntermediateState(SpacecraftState, boolean) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
getInitialState() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
propagateOrbit(AbsoluteDate) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
getMass(AbsoluteDate) | | 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 |