IntegratedEphemeris

ElementMissed InstructionsCov.Missed BranchesCov.MissedCxtyMissedLinesMissedMethods
Total17 of 24092%0 of 12100%319341313
resetIntermediateState(SpacecraftState, boolean)70%n/a111111
propagateOrbit(AbsoluteDate)50%n/a111111
getMass(AbsoluteDate)50%n/a111111
getInterpolatedState(AbsoluteDate)80100%4100%030701
IntegratedEphemeris(AbsoluteDate, AbsoluteDate, AbsoluteDate, StateMapper, PropagationType, DenseOutputModel, Map, List, String[])58100%4100%0301401
basicPropagate(AbsoluteDate)44100%2100%020701
setAttitudeProvider(AttitudeProvider)11100%2100%020401
resetInitialState(SpacecraftState)7100%n/a010101
getInitialState()7100%n/a010101
getPVCoordinates(AbsoluteDate, Frame)6100%n/a010101
getFrame()4100%n/a010101
getMinDate()3100%n/a010101
getMaxDate()3100%n/a010101