NumericalPropagator

ElementMissed InstructionsCov.Missed BranchesCov.MissedCxtyMissedLinesMissedMethods
Total4 of 26498%1 of 888%120158016
resetInitialState(SpacecraftState)41071%1150%121501
tolerances(double, Orbit, OrbitType)158100%6100%0402401
NumericalPropagator(AbstractIntegrator)26100%n/a010901
setMu(double)10100%n/a010301
createMapper(AbsoluteDate, double, OrbitType, PositionAngle, AttitudeProvider, Frame)10100%n/a010101
addForceModel(ForceModel)6100%n/a010201
getPVCoordinates(AbsoluteDate, Frame)6100%n/a010101
getMainStateEquations(AbstractIntegrator)6100%n/a010101
removeForceModels()4100%n/a010201
setOrbitType(OrbitType)4100%n/a010201
setPositionAngleType(PositionAngle)4100%n/a010201
setInitialState(SpacecraftState)4100%n/a010201
getForceModels()3100%n/a010101
getNewtonianAttractionForceModel()3100%n/a010101
getOrbitType()3100%n/a010101
getPositionAngleType()3100%n/a010101