ConstantThrustManeuver

ElementMissed InstructionsCov.Missed BranchesCov.MissedCxtyMissedLinesMissedMethods
Total61 of 27778%7 of 1656%6181344210
accelerationDerivatives(SpacecraftState, String)334759%3350%2441101
setParameter(String, double)150%20%225511
getParameter(String)130%20%224411
ConstantThrustManeuver(AbsoluteDate, double, double, double, Vector3D)53100%2100%0201101
accelerationDerivatives(AbsoluteDate, Frame, FieldVector3D, FieldVector3D, FieldRotation, DerivativeStructure)44100%2100%020501
getEventsDetectors()31100%n/a010101
addContribution(SpacecraftState, TimeDerivativesEquations)26100%2100%020401
getISP()9100%n/a010101
getThrust()3100%n/a010101
getFlowRate()3100%n/a010101