resetIntermediateState(SpacecraftState, boolean) | | 0% | | n/a | 1 | 1 | 1 | 1 | 1 | 1 |
Ephemeris(List, int, double) | | 100% | | 100% | 0 | 3 | 0 | 18 | 0 | 1 |
basicPropagate(AbsoluteDate) | | 100% | | 100% | 0 | 6 | 0 | 14 | 0 | 1 |
isAdditionalStateManaged(String) | | 100% | | 100% | 0 | 4 | 0 | 6 | 0 | 1 |
getManagedAdditionalStates() | | 100% | | n/a | 0 | 1 | 0 | 5 | 0 | 1 |
writeReplace() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
resetInitialState(SpacecraftState) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
Ephemeris(List, int) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
getPVCoordinates(AbsoluteDate, Frame) | | 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 |
getInitialState() | | 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 |
getExtrapolationThreshold() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
getFrame() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |