def __init__(self, aircraft): ''' initializes fuel object mostly used for documentation establishes link to the aircraft class ''' component.__init__(self) self.id = 'fuel' self.aircraft = aircraft self.level = 2 #Mass self.mFuelMAX = mFuelMAX() self.mFuelMAXcenterWT = mFuelMAXcenterWT() self.mFuelMAXinnerWT = mFuelMAXinnerWT() self.mFuelMAXouterWT = mFuelMAXouterWT() self.mFuelMAXTT = mFuelMAXTT() self.mFM = mFM( cpacsPath= '/cpacs/vehicles/aircraft/model/analyses/massBreakdown/fuel/massDescription/mass' ) self.mFuelCLIMB = mFuelCLIMB() self.mFuelDESCENT = mFuelDESCENT() self.mFuelCR = mFuelCR() self.mFuelTO = mFuelTO() self.mFuelRES = mFuelRES() self.TrimTank = TrimTank() # CoG self.posCoG = posCoG() self.posCoGcenterWT = posCoGcenterWT() self.posCoGinnerWT = posCoGinnerWT() self.posCoGouterWT = posCoGouterWT() self.posCoGTT = posCoGTT()
def __init__(self, aircraft): """ initializes fuel object mostly used for documentation establishes link to the aircraft class """ component.__init__(self) self.id = "fuel" self.aircraft = aircraft self.level = 2 # Mass self.mFuelMAX = mFuelMAX() self.mFuelMAXcenterWT = mFuelMAXcenterWT() self.mFuelMAXinnerWT = mFuelMAXinnerWT() self.mFuelMAXouterWT = mFuelMAXouterWT() self.mFuelMAXTT = mFuelMAXTT() self.mFM = mFM(cpacsPath="/cpacs/vehicles/aircraft/model/analyses/massBreakdown/fuel/massDescription/mass") self.mFuelCLIMB = mFuelCLIMB() self.mFuelDESCENT = mFuelDESCENT() self.mFuelCR = mFuelCR() self.mFuelTO = mFuelTO() self.mFuelRES = mFuelRES() self.TrimTank = TrimTank() # CoG self.posCoG = posCoG() self.posCoGcenterWT = posCoGcenterWT() self.posCoGinnerWT = posCoGinnerWT() self.posCoGouterWT = posCoGouterWT() self.posCoGTT = posCoGTT()
def __init__(self, aircraft): ''' initializes fuselage object mostly used for documentation establishes link to the aircraft class @Method: Component Constructor ''' component.__init__(self) self.id = 'fuselage' self.aircraft = aircraft self.level = 2 #Mass self.mFuselage = mFuselage() self.mFurn = mFurn( cpacsPath='/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mFurnishing/massDescription/mass') self.mStructure = mStructure( cpacsPath='/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mStructure/mFuselagesStructure/mFuselageStructure/massDescription/mass') #CoG self.posCoG = posCoG( cpacsPath='/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mStructure/mFuselagesStructure/mFuselageStructure/massDescription/location/x') #Geometry self.xRoot = xRoot()# the fuselages origin self.dfus = dfus() self.lfus = lfus()#cpacsPath='/cpacs/toolspecific/joeFuMo/lfuselage') self.lcabin = lcabin()#cpacsPath='/cpacs/toolspecific/joeFuMo/deck/length') self.lcockpit = lcockpit() self.lnose = lnose()#cpacsPath='/cpacs/toolspecific/joeFuMo/lnose') self.ltail = ltail()#cpacsPath='/cpacs/toolspecific/joeFuMo/ltail') self.loverlay = loverlay()#cpacsPath='/cpacs/toolspecific/joeFuMo/loverlay') self.wetArea = wetArea() self.LoD = LoD() #Cabin self.nRow = nRow() self.nPaxR = nPaxR() self.nAisle = nAisle() self.nClasses = nClasses() self.refLayout = refLayout()#cpacsPath='/cpacs/toolspecific/joeFuMo/deck/refLayout',) self.refAbreast = refAbreast()#cpacsPath='/cpacs/toolspecific/joeFuMo/deck/refAbreast',) self.cargoDeck = cargoDeck()#cpacsPath='/cpacs/toolspecific/joeFuMo/cargoDeck') self.paxDensity = paxDensity() self.dcabin = dcabin() self.hcabin = hcabin() self.vcabin = vcabin() self.yFloor = yFloor() self.zFloor = zFloor() #Aerodynamics self.formFactor = formFactor() self.reynoldsNr = reynoldsNr() self.cfLAM = cfLAM() self.cfTURB = cfTURB() self.cD0c = cD0c() self.dragArea = dragArea() self.nLam = nLam()
def __init__(self, wing): component.__init__(self) self.wing = wing self.id = 'slat' self.level = 3 #Geometry Data self.refArea = refArea() self.avgChord = avgChord()
def __init__(self, vtp): component.__init__(self) self.vtp = vtp self.id = 'rudder' self.level = 3 #Geometry Data self.refArea = refArea() self.span = span() self.cRoot = cRoot() self.cTip = cTip()
def __init__(self, aircraft): ''' @Method: Component Constructor ''' component.__init__(self) self.id = 'pylon' self.aircraft = aircraft self.level = 2 #Mass self.mPylon = mPylon()
def __init__(self, htp): component.__init__(self) self.htp = htp self.id = 'elevator' self.level = 3 #Geometry Data self.refArea = refArea() self.rootYLocation = rootYLocation() self.span = span() self.cRoot = cRoot() self.cTip = cTip()
def __init__(self, aircraft): ''' @Method: Component Constructor ''' component.__init__(self) self.id = 'pylon' self.aircraft = aircraft self.level = 2 #Mass self.mPylon = mPylon( cpacsPath='/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mStructure/mPylons/massDescription/mass')
def __init__(self, wing): component.__init__(self) self.wing = wing self.id = 'aileron' self.level = 3 #Geometry Data self.refArea = refArea() self.span = span() self.tipYLocation = tipYLocation() self.cRoot = cRoot() self.cTip = cTip() self.taperRatio = taperRatio()
def __init__(self, aircraft): ''' @Method: Component Constructor ''' component.__init__(self) self.id = 'systems' self.aircraft = aircraft self.level = 2 #Mass self.mSystems = mSystems( cpacsPath='/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mSystems/massDescription/mass') self.posCoG = posCoG( cpacsPath='/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mSystems/massDescription/location/x')
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 = 'tool' self.aircraft = aircraft self.level = 2 #=============================================================================== #Aircraft stuff #=============================================================================== self.aircraftName = parameter(cpacsPath='/cpacs/vehicles/aircraft/model/name', value='VAMPzero') self.aircraftDES = parameter(cpacsPath='/cpacs/vehicles/aircraft/model/description', value='VAMPzero') #commented out due to introduction of xMAC25 #self.refX = parameter(cpacsPath = '/cpacs/vehicles/aircraft/model/reference/point/x',value='0.0') self.refY = parameter(cpacsPath='/cpacs/vehicles/aircraft/model/reference/point/y', value='0.0') self.refZ = parameter(cpacsPath='/cpacs/vehicles/aircraft/model/reference/point/z', value='0.0') #======================================================================= # Lifting Line #======================================================================= self.liliname = parameter(cpacsPath='/cpacs/toolspecific/liftingLine/tool/name', value='LIFTING_LINE') self.liliversion = parameter(cpacsPath='/cpacs/toolspecific/liftingLine/tool/version', value='2.3.1') self.liliuID = parameter(cpacsPath='/cpacs/toolspecific/liftingLine/aircraftModelUID', value='A320modelID')#@todo: Model ID is not available at Time of Construction self.liliSpaneling = parameter( cpacsPath='/cpacs/toolspecific/liftingLine/toolParameters/wingPanelings/wingPaneling[1]/spanwise', value='5') self.liliCpaneling = parameter( cpacsPath='/cpacs/toolspecific/liftingLine/toolParameters/wingPanelings/wingPaneling[1]/chordwise', value='5') self.lilimode = parameter(cpacsPath='/cpacs/toolspecific/liftingLine/toolParameters/archiveMode', value='1') #self.lilipolars = parameter(cpacsPath = '/cpacs/toolspecific/liftingLine/performanceMaps',value='') #======================================================================= #Header Information #======================================================================= self.name = parameter(cpacsPath='/cpacs/header/name', value='Export from') self.creator = parameter(cpacsPath='/cpacs/header/creator', value='VAMPzero') self.timestamp = parameter(cpacsPath='/cpacs/header/timestamp', value='2010-12-31T12:00:00') self.version = parameter(cpacsPath='/cpacs/header/version', value='0.1') self.version = parameter(cpacsPath='/cpacs/header/cpacsVersion', value='2.0')
def __init__(self, aircraft): ''' @Method: Component Constructor ''' component.__init__(self) self.id = 'systems' self.aircraft = aircraft self.level = 2 #Mass self.mSystems = mSystems( cpacsPath= '/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mSystems/massDescription/mass' ) self.posCoG = posCoG( cpacsPath= '/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mSystems/massDescription/location/x' )
def __init__(self, wing): component.__init__(self) self.wing = wing self.id = 'flap' self.level = 3 #Geometry Data self.refArea = refArea() self.avgChordInnerFlap = avgChordInnerFlap() self.spanInnerFlap = spanInnerFlap() self.refAreaInnerFlap = refAreaInnerFlap() self.refAreaOuterFlap = refAreaOuterFlap() self.avgChordOuterFlap = avgChordOuterFlap() self.spanOuterFlap = spanOuterFlap() #Aerodynamic Data self.dCLmaxTO = dCLmaxTO() self.dCLmaxL = dCLmaxL() self.dCDTO = dCDTO() self.dCDL = dCDL()
def __init__(self, aircraft): ''' @Method: Component Constructor ''' component.__init__(self) self.id = 'landingGear' self.aircraft = aircraft self.level = 2 #Parameters self.mLandingGear = mLandingGear( cpacsPath='/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mStructure/mLandingGears/massDescription/mass') self.eta = eta() self.xsi = xsi() self.xLandingGear = xLandingGear() self.yLandingGear = yLandingGear() self.zLandingGear = zLandingGear() self.xNoseGear = xNoseGear() #Aerodynamic self.dCDextendedLG = dCDextendedLG()
def __init__(self, wing, position=''): component.__init__(self) self.wing = wing self.id = self.wing.id + position + 'airfoil' self.position = position self.level = 3 self.aType = aType() #Geometry Data self.tc = tc() self.ctm = ctm() #Aero Data self.reynoldsNr = reynoldsNr() self.clMAX = clMAX() ################################################################################################### #EOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFE# ###################################################################################################
def __init__(self, aircraft): ''' @Method: Component Constructor ''' component.__init__(self) self.id = 'landingGear' self.aircraft = aircraft self.level = 2 #Parameters self.mLandingGear = mLandingGear() self.mNoseGear = mNoseGear() self.eta = eta() self.xsi = xsi() self.xLandingGear = xLandingGear(cpacsPath='/cpacs/vehicles/aircraft/model/landingGear/mainGears/mainGear/fuselageAttachment/translation/x') self.yLandingGear = yLandingGear(cpacsPath='/cpacs/vehicles/aircraft/model/landingGear/mainGears/mainGear/fuselageAttachment/translation/y') self.zLandingGear = zLandingGear(cpacsPath='/cpacs/vehicles/aircraft/model/landingGear/mainGears/mainGear/fuselageAttachment/translation/z') self.xNoseGear = xNoseGear(cpacsPath='/cpacs/vehicles/aircraft/model/landingGear/noseGears/noseGear/fuselageAttachment/translation/x') self.yNoseGear = yNoseGear(cpacsPath='/cpacs/vehicles/aircraft/model/landingGear/noseGears/noseGear/fuselageAttachment/translation/y') self.zNoseGear = zNoseGear(cpacsPath='/cpacs/vehicles/aircraft/model/landingGear/noseGears/noseGear/fuselageAttachment/translation/z') #Aerodynamic self.dCDextendedLG = dCDextendedLG()
def __init__(self, aircraft): ''' @Method: Component Constructor ''' component.__init__(self) self.id = 'payload' self.aircraft = aircraft self.level = 2 #Mass self.mPayload = mPayload( cpacsPath='/cpacs/vehicles/aircraft/model/analyses/massBreakdown/payload/massDescription/mass') self.mCargo = mCargo( cpacsPath='/cpacs/vehicles/aircraft/model/analyses/massBreakdown/payload/mCargo/massDescription/mass') self.paxSeats = paxSeats(cpacsPath='/cpacs/vehicles/aircraft/model/global/paxSeats') self.mPax = mPax() self.mSinglePax = mSinglePax() #Cog self.posCoG = posCoG() ################################################################################################### #EOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFE# ###################################################################################################
def __init__(self, aircraft): ''' @Method: Component Constructor ''' component.__init__(self) self.id = 'payload' self.aircraft = aircraft self.level = 2 #Mass self.mPayload = mPayload( cpacsPath= '/cpacs/vehicles/aircraft/model/analyses/massBreakdown/payload/massDescription/mass' ) self.mCargo = mCargo( cpacsPath= '/cpacs/vehicles/aircraft/model/analyses/massBreakdown/payload/mCargo/massDescription/mass' ) self.paxSeats = paxSeats( cpacsPath='/cpacs/vehicles/aircraft/model/global/paxSeats') self.mPax = mPax() self.mSinglePax = mSinglePax() #Cog self.posCoG = posCoG()
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 = 'strut' self.aircraft = aircraft self.level = 2 # Mass self.mStrut = mStrut( cpacsPath= '/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mStructure/mWingsStructure/mWingStructure[4]/massDescription[' + self.id + '_mass]/mass') self.parentUID = parameter( value=self.id, cpacsPath= '/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mStructure/mWingsStructure/mWingStructure[4]/massDescription[' + self.id + '_mass]/parentUID') # Geometry self.refArea = refArea() self.expArea = expArea() self.wetArea = wetArea() self.aspectRatio = aspectRatio() self.span = span() self.depth = depth() self.active = active() 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.dihedral = dihedral() self.twist = twist() self.etaStrut = etaStrut() self.xRoot = xRoot() self.yRoot = yRoot() self.zRoot = zRoot() self.xTip = xTip() self.yTip = yTip() self.zTip = zTip() # Aerodynamics self.formFactor = formFactor() self.reynoldsNr = reynoldsNr() self.cfLAM = cfLAM() self.cfTURB = cfTURB() self.cD0c = cD0c() self.nLam = nLam() # Airfoil self.airfoilr = airfoil(self, position='root') self.airfoilt = airfoil(self, position='tip')
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 = "strut" self.aircraft = aircraft self.level = 2 # Mass self.mStrut = mStrut( cpacsPath="/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mStructure/mWingsStructure/mWingStructure[4]/massDescription[" + self.id + "_mass]/mass" ) self.parentUID = parameter( value=self.id, cpacsPath="/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mStructure/mWingsStructure/mWingStructure[4]/massDescription[" + self.id + "_mass]/parentUID", ) # Geometry self.refArea = refArea() self.expArea = expArea() self.wetArea = wetArea() self.aspectRatio = aspectRatio() self.span = span() self.depth = depth() self.active = active() 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.dihedral = dihedral() self.twist = twist() self.etaStrut = etaStrut() self.xRoot = xRoot() self.yRoot = yRoot() self.zRoot = zRoot() self.xTip = xTip() self.yTip = yTip() self.zTip = zTip() # Aerodynamics self.formFactor = formFactor() self.reynoldsNr = reynoldsNr() self.cfLAM = cfLAM() self.cfTURB = cfTURB() self.cD0c = cD0c() self.nLam = nLam() # Airfoil self.airfoilr = airfoil(self, position="root") self.airfoilt = airfoil(self, position="tip")
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 @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 @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): ''' 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 = '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()
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): ''' @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() ################################################################################################### #EOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFE# ###################################################################################################
def __init__(self, aircraft): ''' @Method: Component Constructor ''' component.__init__(self) self.id = 'atmosphere' self.aircraft = aircraft self.level = 2 #Airport Level self.hAP = hAP() self.aAP = aAP() self.pAP = pAP() self.rhoAP = rhoAP() self.sigmaAP = sigmaAP() self.TAP = TAP() self.deltaT = deltaT() #CruiseLevel self.aCR = aCR() self.EASCR = EASCR() self.hCR = hCR() self.MaCR = MaCR() self.myCR = myCR() self.nyCR = nyCR() self.qCR = qCR() self.rhoCR = rhoCR() self.sigmaCR = sigmaCR() self.TASCR = TASCR() self.TCR = TCR() #FL1500 self.aFL1500 = aFL1500() self.EASFL1500 = EASFL1500() self.hFL1500 = hFL1500() self.MaFL1500 = MaFL1500() self.myFL1500 = myFL1500() self.nyFL1500 = nyFL1500() self.qFL1500 = qFL1500() self.rhoFL1500 = rhoFL1500() self.sigmaFL1500 = sigmaFL1500() self.TASFL1500 = TASFL1500() self.TFL1500 = TFL1500() #FL100 self.aFL100 = aFL100() self.EASFL100 = EASFL100() self.hFL100 = hFL100() self.MaFL100 = MaFL100() self.myFL100 = myFL100() self.nyFL100 = nyFL100() self.qFL100 = qFL100() self.rhoFL100 = rhoFL100() self.sigmaFL100 = sigmaFL100() self.TASFL100 = TASFL100() self.TFL100 = TFL100() #Constants self.R_s = 287.05 # spezifische Gaskonstante der Luft self.kappa = 1.4 # Adiabatenkoeff. self.g = 9.81 # Erdbeschnleunigung self.beta = 1.458e-6 # Sutherland Konstante self.S_Sutherland = 110.4 # [K] Sutherland Temperatur self.HA = [0, 11000, 20000] self.gammaH = [-0.0065, 0, 0.001] self.TA = [288.15, 216.65, 216.65] self.pA = [101325, 22620, 5469] self.rhoA = [1.225, 0.3637, 0.0879]
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 = 'tool' self.aircraft = aircraft self.level = 2 #=============================================================================== #Aircraft stuff #=============================================================================== self.aircraftName = parameter( cpacsPath='/cpacs/vehicles/aircraft/model/name', value='VAMPzero') self.aircraftDES = parameter( cpacsPath='/cpacs/vehicles/aircraft/model/description', value='VAMPzero') #commented out due to introduction of xMAC25 #self.refX = parameter(cpacsPath = '/cpacs/vehicles/aircraft/model/reference/point/x',value='0.0') self.refY = parameter( cpacsPath='/cpacs/vehicles/aircraft/model/reference/point/y', value='0.0') self.refZ = parameter( cpacsPath='/cpacs/vehicles/aircraft/model/reference/point/z', value='0.0') #======================================================================= # Lifting Line #======================================================================= self.liliname = parameter( cpacsPath='/cpacs/toolspecific/liftingLine/tool/name', value='LIFTING_LINE') self.liliversion = parameter( cpacsPath='/cpacs/toolspecific/liftingLine/tool/version', value='2.3.1') self.liliuID = parameter( cpacsPath='/cpacs/toolspecific/liftingLine/aircraftModelUID', value='A320modelID' ) #@todo: Model ID is not available at Time of Construction self.liliSpaneling = parameter( cpacsPath= '/cpacs/toolspecific/liftingLine/toolParameters/wingPanelings/wingPaneling[1]/spanwise', value='5') self.liliCpaneling = parameter( cpacsPath= '/cpacs/toolspecific/liftingLine/toolParameters/wingPanelings/wingPaneling[1]/chordwise', value='5') self.lilimode = parameter( cpacsPath= '/cpacs/toolspecific/liftingLine/toolParameters/archiveMode', value='1') #self.lilipolars = parameter(cpacsPath = '/cpacs/toolspecific/liftingLine/performanceMaps',value='') #======================================================================= #Header Information #======================================================================= self.name = parameter(cpacsPath='/cpacs/header/name', value='Export from') self.creator = parameter(cpacsPath='/cpacs/header/creator', value='VAMPzero') self.timestamp = parameter(cpacsPath='/cpacs/header/timestamp', value='2010-12-31T12:00:00') self.version = parameter(cpacsPath='/cpacs/header/version', value='0.1') self.version = parameter(cpacsPath='/cpacs/header/cpacsVersion', value='2.0')