SpacecraftToObservedBody

ElementMissed InstructionsCov.Missed BranchesCov.MissedCxtyMissedLinesMissedMethods
Total24 of 50095%4 of 2684%426482013
SpacecraftToObservedBody(Frame, Frame, AbsoluteDate, AbsoluteDate, double, double, List, int, CartesianDerivativesFilter, List, int, AngularDerivativesFilter)2429792%41477%41045001
interpolate(AbsoluteDate, List)72100%2100%020701
SpacecraftToObservedBody(Frame, Frame, AbsoluteDate, AbsoluteDate, double, double, List, List)51100%2100%0201401
isInRange(AbsoluteDate)20100%4100%030201
getScToInertial(AbsoluteDate)6100%n/a010101
getInertialToBody(AbsoluteDate)6100%n/a010101
getBodyToInertial(AbsoluteDate)6100%n/a010101
getInertialFrame()3100%n/a010101
getBodyFrame()3100%n/a010101
getMinDate()3100%n/a010101
getMaxDate()3100%n/a010101
getTStep()3100%n/a010101
getOvershootTolerance()3100%n/a010101