GLONASSAnalyticalPropagator

ElementMissed InstructionsCov.Missed BranchesCov.MissedCxtyMissedLinesMissedMethods
Total54 of 1,57396%8 of 3275%93610258120
eMeSinE(UnivariateDerivative2, UnivariateDerivative2)213361%1150%1241001
getdTpr(AbsoluteDate)156180%1150%1211001
propagateInEcef(AbsoluteDate)1342197%3350%3436601
getEccentricAnomaly(UnivariateDerivative2, UnivariateDerivative2)22098%11191%1713001
getMU()0%n/a111111
getParameterDifferentials(UnivariateDerivative2, UnivariateDerivative2, UnivariateDerivative2, UnivariateDerivative2, UnivariateDerivative2)453100%n/a0107101
computeSma(UnivariateDerivative2, UnivariateDerivative2, UnivariateDerivative2)151100%2880%2603301
GLONASSAnalyticalPropagator(GLONASSOrbitalElements, Frame, Frame, AttitudeProvider, double, DataContext)44100%n/a0101101
computePA(UnivariateDerivative2, UnivariateDerivative2, UnivariateDerivative2, UnivariateDerivative2)30100%n/a010401
computeLambda(UnivariateDerivative2, UnivariateDerivative2, UnivariateDerivative2, UnivariateDerivative2)23100%n/a010301
propagateOrbit(AbsoluteDate)22100%n/a010301
getTrueAnomaly(UnivariateDerivative2, UnivariateDerivative2)21100%n/a010301
static {...}11100%n/a010601
resetInitialState(SpacecraftState)7100%n/a010101
resetIntermediateState(SpacecraftState, boolean)7100%n/a010101
getMass(AbsoluteDate)100%n/a010101
getGLONASSOrbitalElements()100%n/a010101
getECI()100%n/a010101
getECEF()100%n/a010101
getFrame()100%n/a010101