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()
class wing(component):
'''
class for the description of the wing
inherits component for throwing errors
Component Class
'''
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 cpacsExport(self, CPACSObj):
'''
this methods exports all parameters nested in the component. Nested Components will be called as well.
cpacsPath must be filled
@author: Jonas Jepsen
@param CPACSObj: the CPACS object holding the data for export
'''
if self.aircraft.strut.active.getValue():
self.LoD.setValueCalc(WING_LOD.SBW)
try:
etaKink = self.etaKink.getValue()
etaEngine = self.aircraft.engine.yEngine.getValue() / self.span.getValue() * 2.
createWingAirfoil(CPACSObj)
createWing(CPACSObj, id=self.id, zeroWing=self, LoD=self.LoD.getValue())
except ZeroDivisionError, e:
self.log.warning('VAMPzero EXPORT: WING could not be created due to "%s"!', e)
super(wing, self).cpacsExport(CPACSObj)
class wing(component):
'''
class for the description of the wing
inherits component for throwing errors
Component Class
'''
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()
###################################################################################################
# #Export to CPACS
###################################################################################################
def cpacsExport(self, CPACSObj):
'''
this methods exports all parameters nested in the component. Nested Components will be called as well.
cpacsPath must be filled
@author: Jonas Jepsen
@param CPACSObj: the CPACS object holding the data for export
'''
if self.aircraft.strut.active.getValue():
self.LoD.setValueFix(WING_LOD.SBW)
try:
etaKink = self.etaKink.getValue()
etaEngine = self.aircraft.engine.yEngine.getValue(
) / self.span.getValue() * 2.
createWingAirfoil(CPACSObj)
createWing(CPACSObj,
id=self.id,
zeroWing=self,
LoD=self.LoD.getValue())
except ZeroDivisionError, e:
self.log.warning(
'VAMPzero EXPORT: WING could not be created due to "%s"!', e)
super(wing, self).cpacsExport(CPACSObj)
