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 |
getIntelsatElevenElements() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
getParametersDrivers() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |