CircularOrbit

ElementMissed InstructionsCov.Missed BranchesCov.MissedCxtyMissedLinesMissedMethods
Total72 of 2,41997%5 of 3485%6525303132
toString()440%n/a111111
CircularOrbit(PVCoordinates, Frame, AbsoluteDate, double)1121895%1150%1213401
CircularOrbit(double, double, double, double, double, double, int, Frame, AbsoluteDate, double)117187%1583%1511801
addKeplerContribution(PositionAngle, double, double[])11297%1375%1411401
CircularOrbit(double, double, double, double, double, double, PositionAngle, Frame, AbsoluteDate, double)6596%1583%1511701
computeJacobianMeanWrtCartesian()877100%n/a0107801
initPVCoordinates()236100%n/a0103101
computeJacobianTrueWrtCartesian()156100%2100%0202301
interpolate(AbsoluteDate, Collection)137100%4100%0302001
meanToEccentric(double)81100%1375%1301701
computeJacobianEccentricWrtCartesian()67100%2100%0201101
CircularOrbit(Orbit)63100%n/a0101201
getAlphaE()53100%n/a010401
eccentricToTrue(double)50100%n/a010401
shiftedBy(double)30100%n/a010101
getAlphaM()17100%n/a010201
getAlpha(PositionAngle)15100%4100%030101
getEquinoctialEx()14100%n/a010101
getEquinoctialEy()14100%n/a010101
getE()13100%n/a010101
getHx()10100%n/a010101
getHy()10100%n/a010101
getLv()100%n/a010101
getLE()100%n/a010101
getLM()100%n/a010101
getA()100%n/a010101
getCircularEx()100%n/a010101
getCircularEy()100%n/a010101
getAlphaV()100%n/a010101
getI()100%n/a010101
getRightAscensionOfAscendingNode()100%n/a010101
getType()100%n/a010101