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 |