| resetInitialState(FieldSpacecraftState) |  | 0% | | n/a | 1 | 1 | 5 | 5 | 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 |
| getFrame() | | 0% | | n/a | 1 | 1 | 1 | 1 | 1 | 1 |
| buildOrbitalElements(FieldSpacecraftState, FieldGnssOrbitalElements, Frame, AttitudeProvider, CalculusFieldElement) | | 100% | | 66% | 2 | 4 | 0 | 43 | 0 | 1 |
| propagateInEcef(FieldAbsoluteDate, CalculusFieldElement[]) | | 100% | | n/a | 0 | 1 | 0 | 36 | 0 | 1 |
| approximateInitialOrbit(FieldSpacecraftState, FieldGnssOrbitalElements, Frame) | | 100% | | 75% | 1 | 3 | 0 | 35 | 0 | 1 |
| defaultParameters() | | 100% | | n/a | 0 | 1 | 0 | 11 | 0 | 1 |
| convert(FieldGnssOrbitalElements, FieldKeplerianOrbit) | | 100% | | n/a | 0 | 1 | 0 | 9 | 0 | 1 |
| FieldGnssPropagator(FieldGnssOrbitalElements, Frame, Frame, AttitudeProvider, CalculusFieldElement) | | 100% | | n/a | 0 | 1 | 0 | 8 | 0 | 1 |
| propagateOrbit(FieldAbsoluteDate, CalculusFieldElement[]) | | 100% | | n/a | 0 | 1 | 0 | 3 | 0 | 1 |
| FieldGnssPropagator(FieldSpacecraftState, FieldGnssOrbitalElements, Frame, AttitudeProvider, CalculusFieldElement) | | 100% | | n/a | 0 | 1 | 0 | 3 | 0 | 1 |
| getParametersDrivers() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getMU() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getMass(FieldAbsoluteDate) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| lambda$convert$0(CalculusFieldElement) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |