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)
class vtp(wing):
'''
Class for the vertical tailplane it inherits the wing 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 = '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 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
'''
# self.LoD.setValue(1) # level of detail [0,1]
createVTP(CPACSObj, self.id, self.xRoot.getValue(), self.zRoot.getValue(), self.airfoilr.tc.getValue(), self.airfoilt.tc.getValue(), self.cRoot.getValue(),
self.cTip.getValue(), self.span.getValue(), self.phiLE.getValue(), self.LoD.getValue())
super(wing, self).cpacsExport(CPACSObj)
class vtp(wing):
'''
Class for the vertical tailplane it inherits the wing 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 = '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 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
'''
# self.LoD.setValue(1) # level of detail [0,1]
createVTP(CPACSObj, self.id, self.xRoot.getValue(),
self.zRoot.getValue(), self.airfoilr.tc.getValue(),
self.airfoilt.tc.getValue(), self.cRoot.getValue(),
self.cTip.getValue(), self.span.getValue(),
self.phiLE.getValue(), self.LoD.getValue())
super(wing, self).cpacsExport(CPACSObj)
