def __init__(self, aircraft):
'''
will initialize instance mainly used for documentation
links to the aircraft instance
initiates the airfoil class
'''
component.__init__(self)
self.id = 'htp'
self.aircraft = aircraft
self.level = 2
self.UID = uID(cpacsPath='/cpacs/toolspecific/vampZero/htpUID')
# Mass
self.mHtp = mHtp(
cpacsPath='/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mStructure/mWingsStructure/mWingStructure[2]/massDescription['+self.id+'_mass]/mass')
self.parentUID = parameter(value=self.id,
cpacsPath='/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mStructure/mWingsStructure/mWingStructure[2]/massDescription['+self.id+'_mass]/parentUID')
# CoG
self.posCoG = posCoG(
cpacsPath='/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mStructure/mWingsStructure/mWingStructure[2]/massDescription['+self.id+'_mass]/location/x')
# Geometry
self.refArea = refArea()
self.refAreaTakeOff = refAreaTakeOff()
self.refAreaCruise = refAreaCruise()
self.refAreaLanding = refAreaLanding()
self.expArea = expArea()
self.wetArea = wetArea()
self.aspectRatio = aspectRatio()
self.span = span()
self.taperRatio = taperRatio()
self.tcAVG = tcAVG()
self.cRoot = cRoot()
self.cTip = cTip()
self.cMAC = cMAC()
self.yMAC = yMAC()
self.xMAC = xMAC()
self.xMAC25 = xMAC25()
self.phiLE = phiLE()
self.phiTE = phiTE()
self.phi25 = phi25()
self.phi50 = phi50()
self.xRoot = xRoot()
self.zRoot = zRoot()
self.lHT = lHT()
self.cHT = cHT()
self.dihedral = dihedral()
self.LoD = LoD()
self.location = location()
# Aerodynamic
self.cLalpha = cLalpha()
self.cLMAX = cLMAX()
#self.cLMIN = cLMIN()
self.cLMAXht = cLMAXht()
self.CLalphaHTP_TO = CLalphaHTP_TO()
self.CLalphaHTP_CR = CLalphaHTP_CR()
self.CLalphaHTP_L = CLalphaHTP_L()
self.formFactor = formFactor()
self.reynoldsNr = reynoldsNr()
self.cfLAM = cfLAM()
self.cfTURB = cfTURB()
self.cD0c = cD0c()
self.nLam = nLam()
self.detadalpha = detadalpha()
self.DPR = DPR()
# Airfoil
self.airfoilr = airfoil(self) # Root Airfoil
self.airfoilt = airfoil(self) # Tip Airfoil
# Elevator
self.elevator = elevator(self)
def __init__(self, aircraft):
'''
will initialize instance mainly used for documentation
links to the aircraft instance
initiates the airfoil class
'''
component.__init__(self)
self.id = 'htp'
self.aircraft = aircraft
self.level = 2
self.UID = uID(cpacsPath='/cpacs/toolspecific/vampZero/htpUID')
# Mass
self.mHtp = mHtp(
cpacsPath=
'/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mStructure/mWingsStructure/mWingStructure[2]/massDescription['
+ self.id + '_mass]/mass')
self.parentUID = parameter(
value=self.id,
cpacsPath=
'/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mStructure/mWingsStructure/mWingStructure[2]/massDescription['
+ self.id + '_mass]/parentUID')
# CoG
self.posCoG = posCoG(
cpacsPath=
'/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mStructure/mWingsStructure/mWingStructure[2]/massDescription['
+ self.id + '_mass]/location/x')
# Geometry
self.refArea = refArea()
self.refAreaTakeOff = refAreaTakeOff()
self.refAreaCruise = refAreaCruise()
self.refAreaLanding = refAreaLanding()
self.expArea = expArea()
self.wetArea = wetArea()
self.aspectRatio = aspectRatio()
self.span = span()
self.taperRatio = taperRatio()
self.tcAVG = tcAVG()
self.cRoot = cRoot()
self.cTip = cTip()
self.cMAC = cMAC()
self.yMAC = yMAC()
self.xMAC = xMAC()
self.xMAC25 = xMAC25()
self.phiLE = phiLE()
self.phiTE = phiTE()
self.phi25 = phi25()
self.phi50 = phi50()
self.xRoot = xRoot()
self.zRoot = zRoot()
self.lHT = lHT()
self.cHT = cHT()
self.dihedral = dihedral()
self.LoD = LoD()
self.location = location()
# Aerodynamic
self.cLalpha = cLalpha()
self.cLMAX = cLMAX()
#self.cLMIN = cLMIN()
self.cLMAXht = cLMAXht()
self.CLalphaHTP_TO = CLalphaHTP_TO()
self.CLalphaHTP_CR = CLalphaHTP_CR()
self.CLalphaHTP_L = CLalphaHTP_L()
self.formFactor = formFactor()
self.reynoldsNr = reynoldsNr()
self.cfLAM = cfLAM()
self.cfTURB = cfTURB()
self.cD0c = cD0c()
self.nLam = nLam()
self.detadalpha = detadalpha()
self.DPR = DPR()
# Airfoil
self.airfoilr = airfoil(self) # Root Airfoil
self.airfoilt = airfoil(self) # Tip Airfoil
# Elevator
self.elevator = elevator(self)
class htp(wing):
'''
The horizontal tailplane it inherits the wing class
Several parameters are inherited from the wing as well!!!
'''
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 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
'''
xRoot = self.xRoot.getValue()
zRoot = self.zRoot.getValue()
createHTP(CPACSObj, self.id, xRoot, zRoot, self.airfoilr.tc.getValue(), self.airfoilt.tc.getValue(), self.cRoot.getValue(),
self.cTip.getValue(), self.span.getValue(), self.phiLE.getValue(), self.dihedral.getValue(),
self.LoD.getValue(), self.location.getValue())
super(wing, self).cpacsExport(CPACSObj)
class htp(wing):
'''
The horizontal tailplane it inherits the wing class
Several parameters are inherited from the wing as well!!!
'''
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 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]
if self.location.getValue():
xRoot = self.xRoot.getValue()
zRoot = self.zRoot.getValue()
else:
vtp_span = self.aircraft.vtp.span.getValue()
vtp_phiLE = (self.aircraft.vtp.phiLE.getValue()) * pi / 180.
xRoot = tan(vtp_phiLE) * vtp_span
try:
xRoot = xRoot.real
except:
pass
zRoot = vtp_span
createHTP(CPACSObj, self.id, xRoot, zRoot, self.airfoilr.tc.getValue(),
self.airfoilt.tc.getValue(), self.cRoot.getValue(),
self.cTip.getValue(), self.span.getValue(),
self.phiLE.getValue(), self.dihedral.getValue(),
self.LoD.getValue(), self.location.getValue())
super(wing, self).cpacsExport(CPACSObj)
