| getMass(FieldAbsoluteDate) |  | 0% | | n/a | 1 | 1 | 1 | 1 | 1 | 1 |
| getFrame() | | 0% | | n/a | 1 | 1 | 1 | 1 | 1 | 1 |
| propagateInEcef(FieldAbsoluteDate) |  | 100% | | n/a | 0 | 1 | 0 | 26 | 0 | 1 |
| computeSatelliteEastLongitudeDegrees(FieldUnivariateDerivative2, FieldSinCos, FieldSinCos) | | 100% | | n/a | 0 | 1 | 0 | 13 | 0 | 1 |
| computeSatelliteRadiusKilometers(CalculusFieldElement, FieldSinCos) | | 100% | | n/a | 0 | 1 | 0 | 11 | 0 | 1 |
| FieldIntelsatElevenElementsPropagator(FieldIntelsatElevenElements, Frame, Frame, AttitudeProvider, CalculusFieldElement) | | 100% | | n/a | 0 | 1 | 0 | 10 | 0 | 1 |
| computeSatelliteGeocentricLatitudeDegrees(FieldUnivariateDerivative2, FieldSinCos) | | 100% | | n/a | 0 | 1 | 0 | 3 | 0 | 1 |
| propagateOrbit(FieldAbsoluteDate, CalculusFieldElement[]) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
| FieldIntelsatElevenElementsPropagator(FieldIntelsatElevenElements, Frame, Frame) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
| FieldIntelsatElevenElementsPropagator(FieldIntelsatElevenElements) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
| resetInitialState(FieldSpacecraftState) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| resetIntermediateState(FieldSpacecraftState, boolean) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getEastLongitudeDegrees() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getGeocentricLatitudeDegrees() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getOrbitRadius() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getParametersDrivers() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |