GNSSPropagator

ElementMissed InstructionsCov.Missed BranchesCov.MissedCxtyMissedLinesMissedMethods
Total24 of 66296%2 of 1888%2255108016
eMeSinE(UnivariateDerivative2)213461%1150%1241001
getEccentricAnomaly(UnivariateDerivative2)323198%11191%1713001
propagateInEcef(AbsoluteDate)227100%n/a0103401
getTk(AbsoluteDate)34100%4100%030701
getTrueAnomaly(UnivariateDerivative2)25100%n/a010301
propagateOrbit(AbsoluteDate)23100%n/a010301
GNSSPropagator(GNSSOrbitalElements, Frame, Frame, AttitudeProvider, double)20100%n/a010701
static {...}11100%n/a010601
resetInitialState(SpacecraftState)7100%n/a010101
resetIntermediateState(SpacecraftState, boolean)7100%n/a010101
getMU()4100%n/a010101
getECI()3100%n/a010101
getECEF()3100%n/a010101
getOrbitalElements()3100%n/a010101
getFrame()3100%n/a010101
getMass(AbsoluteDate)3100%n/a010101