writeReplace() | | 62% | | 25% | 4 | 5 | 9 | 17 | 0 | 1 |
basicPropagate(AbsoluteDate) | | 71% | | 50% | 2 | 4 | 5 | 14 | 0 | 1 |
resetIntermediateState(SpacecraftState, boolean) | | 0% | | n/a | 1 | 1 | 1 | 1 | 1 | 1 |
propagateOrbit(AbsoluteDate) | | 0% | | n/a | 1 | 1 | 1 | 1 | 1 | 1 |
getMass(AbsoluteDate) | | 0% | | n/a | 1 | 1 | 1 | 1 | 1 | 1 |
IntegratedEphemeris(AbsoluteDate, AbsoluteDate, AbsoluteDate, StateMapper, boolean, ContinuousOutputModel, Map, List, String[]) | | 100% | | 100% | 0 | 3 | 0 | 14 | 0 | 1 |
setInterpolationDate(AbsoluteDate) | | 100% | | 100% | 0 | 4 | 0 | 6 | 0 | 1 |
resetInitialState(SpacecraftState) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
getInitialState() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
getPVCoordinates(AbsoluteDate, Frame) | | 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 |