| Element | Missed Instructions | Cov. | Missed Branches | Cov. | Missed | Cxty | Missed | Lines | Missed | Methods |
| Total | 0 of 203 | 100% | 0 of 0 | n/a | 0 | 12 | 0 | 34 | 0 | 12 |
| propagateInEcef(AbsoluteDate) | | 100% | n/a | 0 | 1 | 0 | 14 | 0 | 1 | |
| SBASPropagator(SBASOrbitalElements, Frame, Frame, AttitudeProvider, double, double) | | 100% | n/a | 0 | 1 | 0 | 8 | 0 | 1 | |
| propagateOrbit(AbsoluteDate) | | 100% | n/a | 0 | 1 | 0 | 3 | 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 | |
| getDT(AbsoluteDate) | | 100% | n/a | 0 | 1 | 0 | 1 | 0 | 1 | |
| getMU() | | 100% | n/a | 0 | 1 | 0 | 1 | 0 | 1 | |
| getECI() | | 100% | n/a | 0 | 1 | 0 | 1 | 0 | 1 | |
| getECEF() | | 100% | n/a | 0 | 1 | 0 | 1 | 0 | 1 | |
| getSBASOrbitalElements() | | 100% | n/a | 0 | 1 | 0 | 1 | 0 | 1 | |
| getFrame() | | 100% | n/a | 0 | 1 | 0 | 1 | 0 | 1 | |
| getMass(AbsoluteDate) | | 100% | n/a | 0 | 1 | 0 | 1 | 0 | 1 |