| computePVCoordinates() |   | 98% | | 86% | 2 | 8 | 1 | 85 | 0 | 1 |
| resetInitialState(SpacecraftState) | | 0% | | n/a | 1 | 1 | 1 | 1 | 1 | 1 |
| resetIntermediateState(SpacecraftState, boolean) | | 0% | | n/a | 1 | 1 | 1 | 1 | 1 | 1 |
| propagateOrbit(AbsoluteDate) | | 65% | | n/a | 0 | 1 | 2 | 3 | 0 | 1 |
| initializeCommons() | | 100% | | 100% | 0 | 3 | 0 | 51 | 0 | 1 |
| selectExtrapolator(TLE, AttitudeProvider, double) | | 100% | | 100% | 0 | 2 | 0 | 10 | 0 | 1 |
| TLEPropagator(TLE, AttitudeProvider, double) | | 100% | | n/a | 0 | 1 | 0 | 11 | 0 | 1 |
| getPVCoordinates(AbsoluteDate) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
| selectExtrapolator(TLE) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getMass(AbsoluteDate) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getTLE() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getFrame() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getMU() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |