FieldEcksteinHechlerPropagator

ElementMissed InstructionsCov.Missed BranchesCov.MissedCxtyMissedLinesMissedMethods
Total45 of 1,05595%7 of 2470%10408179328
FieldEcksteinHechlerPropagator(FieldOrbit, CalculusFieldElement, double, CalculusFieldElement, double, double, double, double, double)150%n/a112211
computeMeanParameters(FieldCircularOrbit, CalculusFieldElement, double, int)1224895%51168%5913701
resetInitialState(FieldSpacecraftState, PropagationType)70%n/a112211
resetIntermediateState(FieldSpacecraftState, boolean, double, int)62580%1150%121701
resetInitialState(FieldSpacecraftState)50%n/a112211
toCartesian(FieldAbsoluteDate, FieldUnivariateDerivative2[])208100%n/a0103301
meanToEccentric(FieldUnivariateDerivative2, FieldUnivariateDerivative2, FieldUnivariateDerivative2)85100%1375%1301701
FieldEcksteinHechlerPropagator(FieldOrbit, AttitudeProvider, CalculusFieldElement, double, CalculusFieldElement, double, double, double, double, double, PropagationType, double, int)68100%n/a0101201
resetInitialState(FieldSpacecraftState, PropagationType, double, int)45100%2100%020701
FieldEcksteinHechlerPropagator(FieldOrbit, AttitudeProvider, CalculusFieldElement, UnnormalizedSphericalHarmonicsProvider, UnnormalizedSphericalHarmonicsProvider.UnnormalizedSphericalHarmonics, PropagationType)35100%n/a010701
FieldEcksteinHechlerPropagator(FieldOrbit, AttitudeProvider, CalculusFieldElement, UnnormalizedSphericalHarmonicsProvider, UnnormalizedSphericalHarmonicsProvider.UnnormalizedSphericalHarmonics)34100%n/a010701
computeMeanOrbit(FieldOrbit, double, double, double, double, double, double, double, double, int)31100%n/a010501
computeMeanOrbit(FieldOrbit, UnnormalizedSphericalHarmonicsProvider, UnnormalizedSphericalHarmonicsProvider.UnnormalizedSphericalHarmonics, double, int)29100%n/a010701
propagateOrbit(FieldAbsoluteDate, CalculusFieldElement[])21100%n/a010301
FieldEcksteinHechlerPropagator(FieldOrbit, double, CalculusFieldElement, double, double, double, double, double)19100%n/a010301
FieldEcksteinHechlerPropagator(FieldOrbit, UnnormalizedSphericalHarmonicsProvider, PropagationType)19100%n/a010401
FieldEcksteinHechlerPropagator(FieldOrbit, UnnormalizedSphericalHarmonicsProvider)18100%n/a010401
FieldEcksteinHechlerPropagator(FieldOrbit, AttitudeProvider, double, CalculusFieldElement, double, double, double, double, double)17100%n/a010201
FieldEcksteinHechlerPropagator(FieldOrbit, AttitudeProvider, UnnormalizedSphericalHarmonicsProvider)16100%n/a010201
FieldEcksteinHechlerPropagator(FieldOrbit, AttitudeProvider, CalculusFieldElement, double, CalculusFieldElement, double, double, double, double, double, PropagationType)16100%n/a010201
FieldEcksteinHechlerPropagator(FieldOrbit, CalculusFieldElement, UnnormalizedSphericalHarmonicsProvider)14100%n/a010301
FieldEcksteinHechlerPropagator(FieldOrbit, AttitudeProvider, CalculusFieldElement, double, CalculusFieldElement, double, double, double, double, double)14100%n/a010201
FieldEcksteinHechlerPropagator(FieldOrbit, AttitudeProvider, CalculusFieldElement, UnnormalizedSphericalHarmonicsProvider, PropagationType)13100%n/a010201
FieldEcksteinHechlerPropagator(FieldOrbit, AttitudeProvider, CalculusFieldElement, UnnormalizedSphericalHarmonicsProvider)12100%n/a010201
computeMeanOrbit(FieldOrbit, UnnormalizedSphericalHarmonicsProvider, UnnormalizedSphericalHarmonicsProvider.UnnormalizedSphericalHarmonics)7100%n/a010101
resetIntermediateState(FieldSpacecraftState, boolean)7100%n/a010201
getMass(FieldAbsoluteDate)7100%n/a010101
getParametersDrivers()100%n/a010101