SBASPropagator

ElementMissed InstructionsCov.Missed BranchesCov.MissedCxtyMissedLinesMissedMethods
Total0 of 203100%0 of 0n/a012034012
propagateInEcef(AbsoluteDate)119100%n/a0101401
SBASPropagator(SBASOrbitalElements, Frame, Frame, AttitudeProvider, double, double)23100%n/a010801
propagateOrbit(AbsoluteDate)23100%n/a010301
resetInitialState(SpacecraftState)7100%n/a010101
resetIntermediateState(SpacecraftState, boolean)7100%n/a010101
getDT(AbsoluteDate)6100%n/a010101
getMU()3100%n/a010101
getECI()3100%n/a010101
getECEF()3100%n/a010101
getSBASOrbitalElements()3100%n/a010101
getFrame()3100%n/a010101
getMass(AbsoluteDate)3100%n/a010101