def __init__(self, aircraft):
'''
will initialize instance mainly used for documentation
links to the aircraft instance
initiates the airfoil class
@Method: Component Constructor
'''
component.__init__(self)
self.id = 'vtp'
self.aircraft = aircraft
self.level = 2
self.UID = uID(cpacsPath='/cpacs/toolspecific/vampZero/vtpUID')
# Mass
self.mVtp = mVtp(
cpacsPath='/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mStructure/mWingsStructure/mWingStructure[3]/massDescription['+self.id+'_mass]/mass')
self.parentUID = parameter(value=self.id,
cpacsPath='/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mStructure/mWingsStructure/mWingStructure[3]/massDescription['+self.id+'_mass]/parentUID')
# CoG
self.posCoG = posCoG(
cpacsPath='/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mStructure/mWingsStructure/mWingStructure[3]/massDescription['+self.id+'_mass]/location/x')
# Geometry
self.refArea = refArea()
self.refAreaTakeOff = refAreaTakeOff()
self.refAreaLanding = refAreaLanding()
self.expArea = expArea()
self.wetArea = wetArea()
self.aspectRatio = aspectRatio()
self.span = span()
self.taperRatio = taperRatio()
self.tcAVG = tcAVG()
self.cRoot = cRoot()
self.cTip = cTip()
self.cMAC = cMAC()
self.yMAC = yMAC()
self.xMAC = xMAC()
self.phiLE = phiLE()
self.phiTE = phiTE()
self.phi25 = phi25()
self.phi50 = phi50()
self.xRoot = xRoot()
self.zRoot = zRoot()
self.lVT = lVT()
self.cVT = cVT()
self.LoD = LoD()
# Aerodynamics
self.cLalpha = cLalpha()
self.cLMAX = cLMAX()
self.formFactor = formFactor()
self.reynoldsNr = reynoldsNr()
self.cfLAM = cfLAM()
self.cfTURB = cfTURB()
self.cD0c = cD0c()
self.nLam = nLam()
# Airfoil
self.airfoilr = airfoil(self) # Root Airfoil
self.airfoilt = airfoil(self) # Tip Airfoil
# Rudder
self.rudder = rudder(self)
def __init__(self, aircraft):
'''
@Method: Component Constructor
'''
component.__init__(self)
self.id = 'engine'
self.aircraft = aircraft
self.level = 2
self.UID = uID(cpacsPath='/cpacs/toolspecific/vampZero/engineUID')
#Mass
self.mEngine = mEngine(
cpacsPath='/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mPowerUnits/massDescription/mass')
#CoG
self.posCoG = posCoG()
#Inertia
self.massIX = massIX(
cpacsPath='/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mPowerUnits/massDescription/massInertia/Jxx')
self.massIY = massIY(
cpacsPath='/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mPowerUnits/massDescription/massInertia/Jyy')
self.massIZ = massIZ(
cpacsPath='/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mPowerUnits/massDescription/massInertia/Jzz')
#Geometry
self.lEngine = lEngine(cpacsPath='/cpacs/vehicles/engines/engine/geometry/length')
self.dEngine = dEngine(cpacsPath='/cpacs/vehicles/engines/engine/geometry/diameter')
self.yEngine = yEngine(cpacsPath='/cpacs/vehicles/aircraft/model/engines/engine/transformation/translation/y')
self.xEngine = xEngine(cpacsPath='/cpacs/vehicles/aircraft/model/engines/engine/transformation/translation/x')
self.zEngine = zEngine(cpacsPath='/cpacs/vehicles/aircraft/model/engines/engine/transformation/translation/z')
self.wetArea = wetArea()
self.location = location()
#Aerodynamics
self.formFactor = formFactor()
self.reynoldsNr = reynoldsNr()
self.cfLAM = cfLAM()
self.cfTURB = cfTURB()
self.cD0c = cD0c()
self.dCDOEI = dCDOEI()
self.nLam = nLam()
#Propulsion
self.mDotEngine = mDotEngine()
self.thrustTO = thrustTO(cpacsPath='/cpacs/vehicles/engines/engine/analysis/thrust00')
self.thrustTOISA = thrustTOISA()
self.thrustCR = thrustCR()
self.nEngine = nEngine()
self.sfcCR = sfcCR()
self.sfcLOI = sfcLOI()
self.bypassRatio = bypassRatio(cpacsPath='/cpacs/vehicles/engines/engine/analysis/bpr00')
self.thrustTWDat = thrustTWDat(cpacsPath='/cpacs/toolspecific/tWDat/thrust00Scaling')
self.etaCompr = etaCompr()
self.etaFan = etaFan()
self.etaProp = etaProp()
self.etaTherm = etaTherm()
self.etaTransm = etaTransm()
self.etaTurb = etaTurb()
self.TET = TET()
self.OPR = OPR()
def __init__(self):
'''
will initialize all values upon creation of the instance. Mainly used for documentation
'''
component.__init__(self)
self.id = 'aircraft'
self.level = 1
self.modelUID = uID(cpacsPath='/cpacs/toolspecific/vampZero/aircraftModelUID')
self.version = parameter(value=0.1, cpacsPath='/cpacs/header/version')
# Mass Data
self.mLM = mLM(cpacsPath='/cpacs/vehicles/aircraft/model/analyses/massBreakdown/designMasses/mMLM/mass')
self.mTOM = mTOM(cpacsPath='/cpacs/vehicles/aircraft/model/analyses/massBreakdown/designMasses/mTOM/mass')
self.mZFW = mZFW(cpacsPath='/cpacs/vehicles/aircraft/model/analyses/massBreakdown/designMasses/mZFM/mass')
self.oEM = oEM(cpacsPath='/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/massDescription/mass')
self.oIM = oIM(
cpacsPath='/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mOperatorItems/massDescription/mass')
# CoG
self.posCoG = posCoG(
cpacsPath='/cpacs/vehicles/aircraft/model/analyses/massBreakdown/designMasses/mTOM/location/x')
self.posNP = posNP()
self.posCoGOEM = posCoGOEM()
self.posCoGMIN = posCoGMIN()
self.posCoGMAX = posCoGMAX()
self.static_margin = static_margin()
# Inertia
self.massIXmTOM = massIXmTOM(
cpacsPath='/cpacs/vehicles/aircraft/model/analyses/massBreakdown/designMasses/mTOM/massInertia/Jxx')
self.massIYmTOM = massIYmTOM(
cpacsPath='/cpacs/vehicles/aircraft/model/analyses/massBreakdown/designMasses/mTOM/massInertia/Jyy')
self.massIZmTOM = massIZmTOM(
cpacsPath='/cpacs/vehicles/aircraft/model/analyses/massBreakdown/designMasses/mTOM/massInertia/Jzz')
self.massIXmZFW = massIXmZFW(
cpacsPath='/cpacs/vehicles/aircraft/model/analyses/massBreakdown/designMasses/mZFM/massInertia/Jxx')
self.massIYmZFW = massIYmZFW(
cpacsPath='/cpacs/vehicles/aircraft/model/analyses/massBreakdown/designMasses/mZFM/massInertia/Jyy')
self.massIZmZFW = massIZmZFW(
cpacsPath='/cpacs/vehicles/aircraft/model/analyses/massBreakdown/designMasses/mZFM/massInertia/Jzz')
self.massIXoEM = massIXoEM(
cpacsPath='/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/massDescription/massInertia/Jxx')
self.massIYoEM = massIYoEM(
cpacsPath='/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/massDescription/massInertia/Jyy')
self.massIZoEM = massIZoEM(
cpacsPath='/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/massDescription/massInertia/Jzz')
# Performance Data
self.desRange = desRange() #@todo: set correct xpath (cpacsPath='/cpacs/vehicles/aircraft/model/global/designRange')
self.machCR = machCR(cpacsPath='/cpacs/vehicles/aircraft/model/global/machCruise')
self.altCR = altCR()
self.sTOFL = sTOFL()
self.sTOFLISA = sTOFLISA()
self.sLFL = sLFL() #@todo: set correct xpath (cpacsPath='/cpacs/vehicles/aircraft/model/global/sFL')
self.rangeType = rangeType()
self.timeRES = timeRES()
self.timeDESCENT = timeDESCENT()
self.timeCLIMB = timeCLIMB()
self.timeCR = timeCR()
self.distRES = distRES()
self.distDESCENT = distDESCENT()
self.distCLIMB = distCLIMB()
self.distCR = distCR()
self.gammaCLIMB = gammaCLIMB()
self.gammaDESCENT = gammaDESCENT()
self.IASCLIMB = IASCLIMB()
self.IASDESCENT = IASDESCENT()
# Crew Data
self.nPilot = nPilot()
self.nCabinCrew = nCabinCrew()
# Sizing Data
self.wsTO = wsTO()
self.wsL = wsL()
self.wsMAX = wsMAX()
self.twTO = twTO()
self.twFAR20121a = twFAR25121a()
self.twFAR20121b = twFAR25121b()
self.twTOP25 = twTOP25()
# Aerodynamics Data
self.cLCR = cLCR()
self.cLMAX = cLMAX()
self.cLTO = cLTO()
self.cLL = cLL()
self.cDCR = cDCR()
self.cDTO = cDTO()
self.cDL = cDL()
self.cD0 = cD0()
self.loDCR = loDCR()
self.loDTO = loDTO()
self.loDLOI = loDLOI()
self.loDCLIMB = loDCLIMB()
self.oswald = oswald()
self.cLROLL = cLROLL()
# DOC
self.aFactor = aFactor()
self.inflation = inflation()
self.USDexchangeEURO = USDexchangeEURO()
self.tBlock = tBlock()
self.tFlight = tFlight()
self.utilization = utilization()
self.costDepreciation = costDepreciation()
self.costFuel = costFuel()
self.costMaintenance = costMaintenance()
self.costAircraftMaintenance = costAircraftMaintenance()
self.costEngineMaintenance = costEngineMaintenance()
self.costCrew = costCrew()
self.costCap = costCap()
self.costGround = costGround()
self.costNavigation = costNavigation()
self.costLanding = costLanding()
self.costInterest = costInterest()
self.costInsurance = costInsurance()
self.costEmissionTrade = costEmissionTrade()
self.flightCycles = flightCycles()
self.priceFuel = priceFuel()
self.priceAircraft = priceAircraft()
self.DOC = DOC()
self.COC = COC()
self.COO = COO()
self.C1 = C1()
self.C2 = C2()
self.aFactor = aFactor()
self.costCap = costCap()
self.flightCycles = flightCycles()
#Stability
#self.staticMargin = staticMargin()
#Controllability
#self.refAreaHtpMIN = refAreaHtpMIN()
# Component Objects
self.wing = wing(self)
self.strut = strut(self)
self.fuselage = fuselage(self)
self.vtp = vtp(self)
self.htp = htp(self)
self.engine = engine(self)
self.landingGear = landingGear(self)
self.systems = systems(self)
self.payload = payload(self)
self.pylon = pylon(self)
self.fuel = fuel(self)
self.atmosphere = atmosphere(self)
self.tool = tool(self)
def __init__(self, aircraft):
'''
will initialize instance mainly used for documentation
links to the aircraft instance
initiates the airfoil class
@Method: Component Constructor
'''
component.__init__(self)
self.id = 'vtp'
self.aircraft = aircraft
self.level = 2
self.UID = uID(cpacsPath='/cpacs/toolspecific/vampZero/vtpUID')
# Mass
self.mVtp = mVtp(
cpacsPath=
'/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mStructure/mWingsStructure/mWingStructure[3]/massDescription['
+ self.id + '_mass]/mass')
self.parentUID = parameter(
value=self.id,
cpacsPath=
'/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mStructure/mWingsStructure/mWingStructure[3]/massDescription['
+ self.id + '_mass]/parentUID')
# CoG
self.posCoG = posCoG(
cpacsPath=
'/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mStructure/mWingsStructure/mWingStructure[3]/massDescription['
+ self.id + '_mass]/location/x')
# Geometry
self.refArea = refArea()
self.refAreaTakeOff = refAreaTakeOff()
self.refAreaLanding = refAreaLanding()
self.expArea = expArea()
self.wetArea = wetArea()
self.aspectRatio = aspectRatio()
self.span = span()
self.taperRatio = taperRatio()
self.tcAVG = tcAVG()
self.cRoot = cRoot()
self.cTip = cTip()
self.cMAC = cMAC()
self.yMAC = yMAC()
self.xMAC = xMAC()
self.phiLE = phiLE()
self.phiTE = phiTE()
self.phi25 = phi25()
self.phi50 = phi50()
self.xRoot = xRoot()
self.zRoot = zRoot()
self.lVT = lVT()
self.cVT = cVT()
self.LoD = LoD()
# Aerodynamics
self.cLalpha = cLalpha()
self.cLMAX = cLMAX()
self.formFactor = formFactor()
self.reynoldsNr = reynoldsNr()
self.cfLAM = cfLAM()
self.cfTURB = cfTURB()
self.cD0c = cD0c()
self.nLam = nLam()
# Airfoil
self.airfoilr = airfoil(self) # Root Airfoil
self.airfoilt = airfoil(self) # Tip Airfoil
# Rudder
self.rudder = rudder(self)
def __init__(self, aircraft):
'''
will initialize instance mainly used for documentation
links to the aircraft instance
initiates the airfoil class
'''
component.__init__(self)
self.id = 'htp'
self.aircraft = aircraft
self.level = 2
self.UID = uID(cpacsPath='/cpacs/toolspecific/vampZero/htpUID')
# Mass
self.mHtp = mHtp(
cpacsPath='/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mStructure/mWingsStructure/mWingStructure[2]/massDescription['+self.id+'_mass]/mass')
self.parentUID = parameter(value=self.id,
cpacsPath='/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mStructure/mWingsStructure/mWingStructure[2]/massDescription['+self.id+'_mass]/parentUID')
# CoG
self.posCoG = posCoG(
cpacsPath='/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mStructure/mWingsStructure/mWingStructure[2]/massDescription['+self.id+'_mass]/location/x')
# Geometry
self.refArea = refArea()
self.refAreaTakeOff = refAreaTakeOff()
self.refAreaCruise = refAreaCruise()
self.refAreaLanding = refAreaLanding()
self.expArea = expArea()
self.wetArea = wetArea()
self.aspectRatio = aspectRatio()
self.span = span()
self.taperRatio = taperRatio()
self.tcAVG = tcAVG()
self.cRoot = cRoot()
self.cTip = cTip()
self.cMAC = cMAC()
self.yMAC = yMAC()
self.xMAC = xMAC()
self.xMAC25 = xMAC25()
self.phiLE = phiLE()
self.phiTE = phiTE()
self.phi25 = phi25()
self.phi50 = phi50()
self.xRoot = xRoot()
self.zRoot = zRoot()
self.lHT = lHT()
self.cHT = cHT()
self.dihedral = dihedral()
self.LoD = LoD()
self.location = location()
# Aerodynamic
self.cLalpha = cLalpha()
self.cLMAX = cLMAX()
#self.cLMIN = cLMIN()
self.cLMAXht = cLMAXht()
self.CLalphaHTP_TO = CLalphaHTP_TO()
self.CLalphaHTP_CR = CLalphaHTP_CR()
self.CLalphaHTP_L = CLalphaHTP_L()
self.formFactor = formFactor()
self.reynoldsNr = reynoldsNr()
self.cfLAM = cfLAM()
self.cfTURB = cfTURB()
self.cD0c = cD0c()
self.nLam = nLam()
self.detadalpha = detadalpha()
self.DPR = DPR()
# Airfoil
self.airfoilr = airfoil(self) # Root Airfoil
self.airfoilt = airfoil(self) # Tip Airfoil
# Elevator
self.elevator = elevator(self)
def __init__(self, aircraft):
'''
will initialize instance mainly used for documentation
links to the aircraft instance
initiates the airfoil class
'''
component.__init__(self)
self.id = 'htp'
self.aircraft = aircraft
self.level = 2
self.UID = uID(cpacsPath='/cpacs/toolspecific/vampZero/htpUID')
# Mass
self.mHtp = mHtp(
cpacsPath=
'/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mStructure/mWingsStructure/mWingStructure[2]/massDescription['
+ self.id + '_mass]/mass')
self.parentUID = parameter(
value=self.id,
cpacsPath=
'/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mStructure/mWingsStructure/mWingStructure[2]/massDescription['
+ self.id + '_mass]/parentUID')
# CoG
self.posCoG = posCoG(
cpacsPath=
'/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mStructure/mWingsStructure/mWingStructure[2]/massDescription['
+ self.id + '_mass]/location/x')
# Geometry
self.refArea = refArea()
self.refAreaTakeOff = refAreaTakeOff()
self.refAreaCruise = refAreaCruise()
self.refAreaLanding = refAreaLanding()
self.expArea = expArea()
self.wetArea = wetArea()
self.aspectRatio = aspectRatio()
self.span = span()
self.taperRatio = taperRatio()
self.tcAVG = tcAVG()
self.cRoot = cRoot()
self.cTip = cTip()
self.cMAC = cMAC()
self.yMAC = yMAC()
self.xMAC = xMAC()
self.xMAC25 = xMAC25()
self.phiLE = phiLE()
self.phiTE = phiTE()
self.phi25 = phi25()
self.phi50 = phi50()
self.xRoot = xRoot()
self.zRoot = zRoot()
self.lHT = lHT()
self.cHT = cHT()
self.dihedral = dihedral()
self.LoD = LoD()
self.location = location()
# Aerodynamic
self.cLalpha = cLalpha()
self.cLMAX = cLMAX()
#self.cLMIN = cLMIN()
self.cLMAXht = cLMAXht()
self.CLalphaHTP_TO = CLalphaHTP_TO()
self.CLalphaHTP_CR = CLalphaHTP_CR()
self.CLalphaHTP_L = CLalphaHTP_L()
self.formFactor = formFactor()
self.reynoldsNr = reynoldsNr()
self.cfLAM = cfLAM()
self.cfTURB = cfTURB()
self.cD0c = cD0c()
self.nLam = nLam()
self.detadalpha = detadalpha()
self.DPR = DPR()
# Airfoil
self.airfoilr = airfoil(self) # Root Airfoil
self.airfoilt = airfoil(self) # Tip Airfoil
# Elevator
self.elevator = elevator(self)
def __init__(self, aircraft):
'''
will initialize instance mainly used for documentation
links to the aircraft instance
initiates the airfoil class
@Method: Component Constructor
'''
component.__init__(self)
self.id = 'wing'
self.aircraft = aircraft
self.level = 2
self.UID = uID(cpacsPath='/cpacs/toolspecific/vampZero/wingUID')
# Mass
self.mWing = mWing(
cpacsPath='/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mStructure/mWingsStructure/mWingStructure[1]/massDescription['+self.id+'_mass]/mass')
self.parentUID = parameter(value=self.id,
cpacsPath='/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mStructure/mWingsStructure/mWingStructure[1]/massDescription['+self.id+'_mass]/parentUID')
# CoG
self.posCoG = posCoG(
cpacsPath='/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mStructure/mWingsStructure/mWingStructure[1]/massDescription['+self.id+'_mass]/location/x')
# Geometry
self.location = location()
self.refArea = refArea(cpacsPath='/cpacs/vehicles/aircraft/model/reference/area')
self.expArea = expArea()
self.wetArea = wetArea()
self.aspectRatio = aspectRatio()
self.span = span()
self.taperRatio = taperRatio()
self.tcAVG = tcAVG()
self.cRoot = cRoot()
self.cTip = cTip()
self.cMAC = cMAC(cpacsPath='/cpacs/vehicles/aircraft/model/reference/length')
self.yMAC = yMAC()
self.xMAC = xMAC()
self.xMAC25 = xMAC25(cpacsPath='/cpacs/vehicles/aircraft/model/reference/point/x')
self.phiLE = phiLE()
self.phiTE = phiTE()
self.phi25 = phi25()
self.phi50 = phi50()
self.dihedral = dihedral()
self.twist = twist()
self.xRoot = xRoot()
self.zRoot = zRoot()
self.LoD = LoD()
self.etaKink = etaKink()
self.etaEngine = etaEngine()
# Aerodynamics
self.cLalpha = cLalpha()
self.cLMAX = cLMAX()
self.formFactor = formFactor()
self.reynoldsNr = reynoldsNr() # cpacsPath='/cpacs/vehicles/aircraft/model/global/aeroPerformanceMap/reynoldsNumber')
self.cfLAM = cfLAM()
self.cfTURB = cfTURB()
self.cD0c = cD0c()
self.oswald = oswald()
self.cDMINoffset = cDMINoffset()
self.nLam = nLam()
self.cDw = cDw()
self.machDD = machDD()
self.machCrit = machCrit()
self.cM0CR = cM0CR()
self.cM0TO = cM0TO()
self.cM0L = cM0L()
# Airfoil
self.airfoilr = airfoil(self, position='root')
self.airfoilt = airfoil(self, position='tip')
# Aileron
self.aileron = aileron(self)
# Slat
self.slat = slat(self)
# Flap
self.flap = flap(self)
# Spoiler
self.spoiler = spoiler(self)
# CPACS Stuff for Export to higher Level
self.xFuselage = xFuselage()
self.yFuselage = yFuselage()
self.zFuselage = zFuselage()
self.cFuselage = cFuselage()
self.xKink = xKink()
self.yKink = yKink()
self.zKink = zKink()
self.cKink = cKink()
self.xTip = xTip()
self.zTip = zTip()
def __init__(self, aircraft):
'''
will initialize instance mainly used for documentation
links to the aircraft instance
initiates the airfoil class
@Method: Component Constructor
'''
component.__init__(self)
self.id = 'wing'
self.aircraft = aircraft
self.level = 2
self.UID = uID(cpacsPath='/cpacs/toolspecific/vampZero/wingUID')
# Mass
self.mWing = mWing(
cpacsPath=
'/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mStructure/mWingsStructure/mWingStructure[1]/massDescription['
+ self.id + '_mass]/mass')
self.parentUID = parameter(
value=self.id,
cpacsPath=
'/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mStructure/mWingsStructure/mWingStructure[1]/massDescription['
+ self.id + '_mass]/parentUID')
# CoG
self.posCoG = posCoG(
cpacsPath=
'/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mStructure/mWingsStructure/mWingStructure[1]/massDescription['
+ self.id + '_mass]/location/x')
# Geometry
self.location = location()
self.refArea = refArea(
cpacsPath='/cpacs/vehicles/aircraft/model/reference/area')
self.expArea = expArea()
self.wetArea = wetArea()
self.aspectRatio = aspectRatio()
self.span = span()
self.taperRatio = taperRatio()
self.tcAVG = tcAVG()
self.cRoot = cRoot()
self.cTip = cTip()
self.cMAC = cMAC(
cpacsPath='/cpacs/vehicles/aircraft/model/reference/length')
self.yMAC = yMAC()
self.xMAC = xMAC()
self.xMAC25 = xMAC25(
cpacsPath='/cpacs/vehicles/aircraft/model/reference/point/x')
self.phiLE = phiLE()
self.phiTE = phiTE()
self.phi25 = phi25()
self.phi50 = phi50()
self.dihedral = dihedral()
self.twist = twist()
self.xRoot = xRoot()
self.zRoot = zRoot()
self.LoD = LoD()
self.etaKink = etaKink()
self.etaEngine = etaEngine()
# Aerodynamics
self.cLalpha = cLalpha()
self.cLMAX = cLMAX()
self.formFactor = formFactor()
self.reynoldsNr = reynoldsNr(
) # cpacsPath='/cpacs/vehicles/aircraft/model/global/aeroPerformanceMap/reynoldsNumber')
self.cfLAM = cfLAM()
self.cfTURB = cfTURB()
self.cD0c = cD0c()
self.oswald = oswald()
self.cDMINoffset = cDMINoffset()
self.nLam = nLam()
self.cDw = cDw()
self.machDD = machDD()
self.machCrit = machCrit()
self.cM0CR = cM0CR()
self.cM0TO = cM0TO()
self.cM0L = cM0L()
# Airfoil
self.airfoilr = airfoil(self, position='root')
self.airfoilt = airfoil(self, position='tip')
# Aileron
self.aileron = aileron(self)
# Slat
self.slat = slat(self)
# Flap
self.flap = flap(self)
# Spoiler
self.spoiler = spoiler(self)
# CPACS Stuff for Export to higher Level
self.xFuselage = xFuselage()
self.yFuselage = yFuselage()
self.zFuselage = zFuselage()
self.cFuselage = cFuselage()
self.xKink = xKink()
self.yKink = yKink()
self.zKink = zKink()
self.cKink = cKink()
self.xTip = xTip()
self.zTip = zTip()
def __init__(self, aircraft):
'''
@Method: Component Constructor
'''
component.__init__(self)
self.id = 'engine'
self.aircraft = aircraft
self.level = 2
self.UID = uID(cpacsPath='/cpacs/toolspecific/vampZero/engineUID')
#Mass
self.mEngine = mEngine(
cpacsPath='/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mPowerUnits/massDescription/mass')
#CoG
self.posCoG = posCoG()
#Inertia
self.massIX = massIX(
cpacsPath='/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mPowerUnits/massDescription/massInertia/Jxx')
self.massIY = massIY(
cpacsPath='/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mPowerUnits/massDescription/massInertia/Jyy')
self.massIZ = massIZ(
cpacsPath='/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mPowerUnits/massDescription/massInertia/Jzz')
#Geometry
self.lEngine = lEngine(cpacsPath='/cpacs/vehicles/engines/engine/geometry/length')
self.dEngine = dEngine(cpacsPath='/cpacs/vehicles/engines/engine/geometry/diameter')
self.yEngine = yEngine(cpacsPath='/cpacs/vehicles/aircraft/model/engines/engine/transformation/translation/y')
self.xEngine = xEngine(cpacsPath='/cpacs/vehicles/aircraft/model/engines/engine/transformation/translation/x')
self.zEngine = zEngine(cpacsPath='/cpacs/vehicles/aircraft/model/engines/engine/transformation/translation/z')
self.wetArea = wetArea()
self.location = location()
#Aerodynamics
self.formFactor = formFactor()
self.reynoldsNr = reynoldsNr()
self.cfLAM = cfLAM()
self.cfTURB = cfTURB()
self.cD0c = cD0c()
self.dCDOEI = dCDOEI()
self.nLam = nLam()
#Propulsion
self.mDotEngine = mDotEngine()
self.thrustTO = thrustTO(cpacsPath='/cpacs/vehicles/engines/engine/analysis/thrust00')
self.thrustTOISA = thrustTOISA()
self.thrustCR = thrustCR()
self.nEngine = nEngine()
self.sfcCR = sfcCR()
self.sfcLOI = sfcLOI()
self.bypassRatio = bypassRatio(cpacsPath='/cpacs/vehicles/engines/engine/analysis/bpr00')
self.thrustTWDat = thrustTWDat(cpacsPath='/cpacs/toolspecific/tWDat/thrust00Scaling')
self.etaCompr = etaCompr()
self.etaFan = etaFan()
self.etaProp = etaProp()
self.etaTherm = etaTherm()
self.etaTransm = etaTransm()
self.etaTurb = etaTurb()
self.TET = TET()
self.OPR = OPR()
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