FieldSpacecraftState

ElementMissed InstructionsCov.Missed BranchesCov.MissedCxtyMissedLinesMissedMethods
Total79 of 2,24296%10 of 16493%111525349170
toString()320%n/a111111
getEquinoctialEx()9847%1150%120101
getEquinoctialEy()9847%1150%120101
getE()9847%1150%120101
getAbsPVA()7646%1150%121301
getOrbit()7646%1150%121301
getPVCoordinates(Frame)4969%1150%120101
ensureCompatibleAdditionalStates(FieldSpacecraftState)19398%42083%41323101
FieldSpacecraftState(Field, SpacecraftState)324100%18100%01004901
interpolate(FieldAbsoluteDate, Stream)232100%18100%01004201
toSpacecraftState()143100%14100%0802301
lambda$interpolate$0(FieldAbsoluteDate, List, List, List, FieldHermiteInterpolator, Map, Map, FieldSpacecraftState)99100%6100%0401501
FieldSpacecraftState(FieldOrbit, FieldAttitude, CalculusFieldElement, FieldArrayDictionary, FieldArrayDictionary)53100%4100%0301301
checkConsistency(FieldOrbit, FieldAttitude)53100%4100%030801
FieldSpacecraftState(FieldAbsolutePVCoordinates, FieldAttitude, CalculusFieldElement, FieldArrayDictionary, FieldArrayDictionary)52100%4100%0301301
checkConsistency(FieldAbsolutePVCoordinates, FieldAttitude)52100%4100%030801
shiftedBy(double)42100%2100%020501
addAdditionalState(String, CalculusFieldElement[])41100%2100%020501
addAdditionalStateDerivative(String, CalculusFieldElement[])41100%2100%020501
shiftedBy(CalculusFieldElement)41100%2100%020501
shiftAdditional(double)39100%6100%040901
shiftAdditional(CalculusFieldElement)39100%6100%040901
FieldSpacecraftState(FieldOrbit)26100%n/a010401
FieldSpacecraftState(FieldAbsolutePVCoordinates)26100%n/a010501
FieldSpacecraftState(FieldOrbit, FieldArrayDictionary)25100%n/a010401
FieldSpacecraftState(FieldAbsolutePVCoordinates, FieldArrayDictionary)25100%n/a010501
toTransform()24100%n/a010401
getAdditionalState(String)21100%2100%020401
getAdditionalStateDerivative(String)21100%2100%020401
FieldSpacecraftState(FieldOrbit, CalculusFieldElement)19100%n/a010401
FieldSpacecraftState(FieldAbsolutePVCoordinates, CalculusFieldElement)19100%n/a010401
FieldSpacecraftState(FieldOrbit, CalculusFieldElement, FieldArrayDictionary)18100%n/a010301
FieldSpacecraftState(FieldAbsolutePVCoordinates, CalculusFieldElement, FieldArrayDictionary)18100%n/a010401
getMu()17100%2100%020101
getKeplerianPeriod()17100%2100%020101
getKeplerianMeanMotion()17100%2100%020101
getA()17100%2100%020101
getHx()17100%2100%020101
getHy()17100%2100%020101
getLv()17100%2100%020101
getLE()17100%2100%020101
getLM()17100%2100%020101
getI()17100%2100%020101
FieldSpacecraftState(FieldOrbit, FieldAttitude)15100%n/a010201
FieldSpacecraftState(FieldAbsolutePVCoordinates, FieldAttitude)15100%n/a010201
FieldSpacecraftState(FieldOrbit, FieldAttitude, FieldArrayDictionary)14100%n/a010201
FieldSpacecraftState(FieldAbsolutePVCoordinates, FieldAttitude, FieldArrayDictionary)14100%n/a010201
FieldSpacecraftState(FieldOrbit, FieldAttitude, CalculusFieldElement, Map)13100%n/a010201
FieldSpacecraftState(FieldAbsolutePVCoordinates, FieldAttitude, CalculusFieldElement, Map)13100%n/a010201
FieldSpacecraftState(FieldOrbit, FieldAttitude, Map)12100%n/a010201
FieldSpacecraftState(FieldOrbit, CalculusFieldElement, Map)12100%n/a010201
FieldSpacecraftState(FieldAbsolutePVCoordinates, FieldAttitude, Map)12100%n/a010201
FieldSpacecraftState(FieldAbsolutePVCoordinates, CalculusFieldElement, Map)12100%n/a010201
FieldSpacecraftState(FieldOrbit, Map)11100%n/a010201
FieldSpacecraftState(FieldAbsolutePVCoordinates, Map)11100%n/a010201
getDate()11100%2100%020101
getFrame()11100%2100%020101
getPVCoordinates()11100%2100%020101
hasAdditionalState(String)9100%2100%020101
hasAdditionalStateDerivative(String)9100%2100%020101
FieldSpacecraftState(FieldOrbit, FieldAttitude, CalculusFieldElement)8100%n/a010201
FieldSpacecraftState(FieldOrbit, FieldAttitude, CalculusFieldElement, FieldArrayDictionary)8100%n/a010201
FieldSpacecraftState(FieldAbsolutePVCoordinates, FieldAttitude, CalculusFieldElement)8100%n/a010201
FieldSpacecraftState(FieldAbsolutePVCoordinates, FieldAttitude, CalculusFieldElement, FieldArrayDictionary)8100%n/a010201
isOrbitDefined()7100%2100%020101
getAdditionalStates()4100%n/a010101
getAdditionalStatesValues()4100%n/a010101
getAdditionalStatesDerivatives()4100%n/a010101
getAttitude()3100%n/a010101
getMass()3100%n/a010101