| EphemerisSegmentPropagator(EphemerisFile.EphemerisSegment, AttitudeProvider) |  | 100% | | n/a | 0 | 1 | 0 | 20 | 0 | 1 |
| propagateOrbit(AbsoluteDate) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
| interpolate(AbsoluteDate) | | 100% | | n/a | 0 | 1 | 0 | 4 | 0 | 1 |
| getVelocity(AbsoluteDate, Frame) | | 100% | | n/a | 0 | 1 | 0 | 3 | 0 | 1 |
| getPosition(AbsoluteDate, Frame) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
| getPVCoordinates(AbsoluteDate, Frame) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
| resetIntermediateState(SpacecraftState, boolean) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| resetInitialState(SpacecraftState) | | 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 |
| getMass(AbsoluteDate) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| lambda$interpolate$0(TimeStampedPVCoordinates) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |