IntegratedEphemeris

ElementMissed InstructionsCov.Missed BranchesCov.MissedCxtyMissedLinesMissedMethods
Total0 of 303100%0 of 14100%020055013
getInterpolatedState(AbsoluteDate)80100%4100%030701
updateAdditionalStates(SpacecraftState)75100%4100%0301401
IntegratedEphemeris(AbsoluteDate, AbsoluteDate, AbsoluteDate, StateMapper, PropagationType, DenseOutputModel, DoubleArrayDictionary, List, String[], int[])54100%2100%0201501
basicPropagate(AbsoluteDate)42100%2100%020701
setAttitudeProvider(AttitudeProvider)11100%2100%020401
resetInitialState(SpacecraftState)7100%n/a010101
resetIntermediateState(SpacecraftState, boolean)7100%n/a010101
getInitialState()7100%n/a010101
propagateOrbit(AbsoluteDate)5100%n/a010101
getMass(AbsoluteDate)5100%n/a010101
getFrame()4100%n/a010101
getMinDate()3100%n/a010101
getMaxDate()3100%n/a010101