| getMass(AbsoluteDate) |  | 0% | | n/a | 1 | 1 | 1 | 1 | 1 | 1 |
| getFrame() | | 0% | | n/a | 1 | 1 | 1 | 1 | 1 | 1 |
| propagateInEcef(AbsoluteDate) |  | 100% | | n/a | 0 | 1 | 0 | 25 | 0 | 1 |
| computeSatelliteEastLongitudeDegrees(UnivariateDerivative2, FieldSinCos, FieldSinCos) | | 100% | | n/a | 0 | 1 | 0 | 9 | 0 | 1 |
| computeSatelliteRadiusKilometers(double, FieldSinCos) | | 100% | | n/a | 0 | 1 | 0 | 6 | 0 | 1 |
| IntelsatElevenElementsPropagator(IntelsatElevenElements, Frame, Frame, AttitudeProvider, double) | | 100% | | n/a | 0 | 1 | 0 | 10 | 0 | 1 |
| computeSatelliteGeocentricLatitudeDegrees(UnivariateDerivative2, FieldSinCos) | | 100% | | n/a | 0 | 1 | 0 | 3 | 0 | 1 |
| propagateOrbit(AbsoluteDate) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| IntelsatElevenElementsPropagator(IntelsatElevenElements) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
| IntelsatElevenElementsPropagator(IntelsatElevenElements, Frame, Frame) | | 100% | | n/a | 0 | 1 | 0 | 2 | 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 |
| 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 |
| getIntelsatElevenElements() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |