| resetInitialState(FieldSpacecraftState) |  | 0% | | n/a | 1 | 1 | 7 | 7 | 1 | 1 |
| FieldGnssPropagator(FieldSpacecraftState, FieldGnssOrbitalElements, Frame, AttitudeProvider, CalculusFieldElement) | | 0% | | n/a | 1 | 1 | 3 | 3 | 1 | 1 |
| getTk(FieldAbsoluteDate) |  | 80% | | 75% | 1 | 3 | 1 | 6 | 0 | 1 |
| resetIntermediateState(FieldSpacecraftState, boolean) | | 0% | | n/a | 1 | 1 | 2 | 2 | 1 | 1 |
| getECI() | | 0% | | n/a | 1 | 1 | 1 | 1 | 1 | 1 |
| getECEF() | | 0% | | n/a | 1 | 1 | 1 | 1 | 1 | 1 |
| buildOrbitalElements(FieldSpacecraftState, FieldGnssOrbitalElements, NonKeplerianDriversFactory, Frame, AttitudeProvider, CalculusFieldElement) | | 100% | | 58% | 5 | 7 | 0 | 65 | 0 | 1 |
| propagateInEcef(FieldAbsoluteDate, CalculusFieldElement[]) | | 100% | | n/a | 0 | 1 | 0 | 38 | 0 | 1 |
| approximateInitialOrbit(FieldSpacecraftState, FieldGnssOrbitalElements, Frame) | | 100% | | 75% | 1 | 3 | 0 | 36 | 0 | 1 |
| toGradient(FieldGnssOrbitalElements, FieldKeplerianOrbit, NonKeplerianDriversFactory) | | 100% | | n/a | 0 | 1 | 0 | 14 | 0 | 1 |
| FieldGnssPropagator(FieldGnssOrbitalElements, Frame, Frame, AttitudeProvider, CalculusFieldElement) | | 100% | | n/a | 0 | 1 | 0 | 11 | 0 | 1 |
| propagateOrbit(FieldAbsoluteDate, CalculusFieldElement[]) | | 100% | | n/a | 0 | 1 | 0 | 3 | 0 | 1 |
| FieldGnssPropagator(Field, GNSSOrbitalElementsFactory) | | 100% | | n/a | 0 | 1 | 0 | 5 | 0 | 1 |
| getMU() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getParametersDrivers() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getMass(FieldAbsoluteDate) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| lambda$toGradient$0(CalculusFieldElement) | | 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 |