| buildOrbitalElements(SpacecraftState, GNSSOrbitalElements, Frame, AttitudeProvider, double) |  | 100% |  | 66% | 2 | 4 | 0 | 39 | 0 | 1 |
| propagateInEcef(AbsoluteDate) | | 100% | | n/a | 0 | 1 | 0 | 29 | 0 | 1 |
| approximateInitialOrbit(SpacecraftState, GNSSOrbitalElements, Frame) | | 100% | | 75% | 1 | 3 | 0 | 35 | 0 | 1 |
| convert(GNSSOrbitalElements, KeplerianOrbit) | | 100% | | n/a | 0 | 1 | 0 | 9 | 0 | 1 |
| getJacobiansColumnsNames() | | 100% | | 87% | 1 | 5 | 0 | 8 | 0 | 1 |
| resetInitialState(SpacecraftState) | | 100% | | n/a | 0 | 1 | 0 | 5 | 0 | 1 |
| GNSSPropagator(GNSSOrbitalElements, Frame, Frame, AttitudeProvider, double) | | 100% | | n/a | 0 | 1 | 0 | 8 | 0 | 1 |
| getTk(AbsoluteDate) | | 100% | | 100% | 0 | 3 | 0 | 7 | 0 | 1 |
| propagateOrbit(AbsoluteDate) | | 100% | | n/a | 0 | 1 | 0 | 3 | 0 | 1 |
| GNSSPropagator(SpacecraftState, GNSSOrbitalElements, Frame, AttitudeProvider, double) | | 100% | | n/a | 0 | 1 | 0 | 3 | 0 | 1 |
| createHarvester(String, RealMatrix, DoubleArrayDictionary) | | 100% | | n/a | 0 | 1 | 0 | 3 | 0 | 1 |
| getMU() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getMass(AbsoluteDate) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| resetIntermediateState(SpacecraftState, boolean) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
| getECI() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getECEF() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getOrbitalElements() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getFrame() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |