TrajectoryState

ElementMissed InstructionsCov.Missed BranchesCov.MissedCxtyMissedLinesMissedMethods
Total0 of 87100%0 of 6100%01002107
TrajectoryState(OrbitElementsType, AbsoluteDate, String[], int, List)38100%2100%020701
TrajectoryState(OrbitElementsType, AbsoluteDate, double[])14100%n/a010501
getAvailableDerivatives()14100%4100%030501
toCartesian(OneAxisEllipsoid, double)10100%n/a010101
getElements()5100%n/a010101
getDate()3100%n/a010101
getType()3100%n/a010101