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, 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, 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, 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')
