FieldDSSTPropagator

ElementMissed InstructionsCov.Missed BranchesCov.MissedCxtyMissedLinesMissedMethods
Total111 of 95088%13 of 6379%196726199835
removeForceModels()280%20%228811
addForceModel(DSSTForceModel)174673%1583%1431301
computeMeanOrbit(FieldSpacecraftState, AttitudeProvider, Collection, double, int)1225595%51372%51014401
getSelectedCoefficients()110%20%222211
afterIntegration()82071%1375%132801
setAttitudeProvider(AttitudeProvider)81157%1150%122501
setInitialState(FieldSpacecraftState, PropagationType)51777%1266%131801
setSatelliteRevolution(int)50%n/a112211
getAllForceModels()40%n/a111111
getSatelliteRevolution()40%n/a111111
initialIsOsculating()30%n/a111111
getOrbitType()30%n/a111111
getPositionAngleType()30%n/a111111
beforeIntegration(FieldSpacecraftState, FieldAbsoluteDate)110100%8100%0502201
computeOsculatingOrbit(FieldSpacecraftState, List)73100%4100%0301201
computeOsculatingState(FieldSpacecraftState, AttitudeProvider, Collection)63100%2100%0201101
createMapper(FieldAbsoluteDate, CalculusFieldElement, OrbitType, PositionAngle, AttitudeProvider, Frame)33100%2100%020701
FieldDSSTPropagator(Field, FieldODEIntegrator, PropagationType, AttitudeProvider)29100%n/a010901
FieldDSSTPropagator(Field, FieldODEIntegrator, AttitudeProvider)29100%n/a010901
hasNewtonianAttraction()18100%4100%030201
computeMeanState(FieldSpacecraftState, AttitudeProvider, Collection, double, int)18100%n/a010201
resetInitialState(FieldSpacecraftState)15100%2100%020501
getInitialIntegrationState()14100%2100%020301
setSelectedCoefficients(Set)12100%2100%020201
FieldDSSTPropagator(Field, FieldODEIntegrator, PropagationType)9100%n/a010301
setInterpolationGridToFixedNumberOfPoints(int)9100%n/a010201
setInterpolationGridToMaxTimeGap(CalculusFieldElement)9100%n/a010201
FieldDSSTPropagator(Field, FieldODEIntegrator)8100%n/a010301
setMu(CalculusFieldElement)8100%n/a010201
computeMeanState(FieldSpacecraftState, AttitudeProvider, Collection)7100%n/a010101
getMainStateEquations(FieldODEIntegrator)6100%n/a010101
tolerances(CalculusFieldElement, CalculusFieldElement, FieldOrbit)6100%n/a010101
setInitialState(FieldSpacecraftState)5100%n/a010201
tolerances(CalculusFieldElement, FieldOrbit)5100%n/a010101
superSetMu(CalculusFieldElement)4100%n/a010201