def createShell(parent, parentUID, typeOfSeg, thickness=0.003, pitch=0.14):
'''
Used for generation of wing upper and lower shell within a componentSegment
@param parent: ComponentSegment object, upper and lower shell-object will be added here
@param thickness: thickness of the wing shell
@param pitch: pitch of the stringers
@param typeOfSeg: either advDoubleTrapezoid or trapezoid
'''
if typeOfSeg != 'strut':
myAlu2024 = materialDefinitionType(materialUID=stringUIDBaseType(isLink='True', valueOf_='aluminium2024'), thickness=doubleBaseType(valueOf_=str(thickness)))
myAlu7075 = materialDefinitionType(materialUID=stringUIDBaseType(isLink='True', valueOf_='aluminium7075'), thickness=doubleBaseType(valueOf_=str(thickness)))
mySkin2024 = wingSkinType(material=myAlu2024)
mySkin7075 = wingSkinType(material=myAlu7075)
myStringerUp = wingStringerType(stringerStructureUID=stringUIDBaseType(valueOf_='Stringer_WING_up'), angle=doubleBaseType(valueOf_='0.0'), pitch=doubleBaseType(valueOf_=str(pitch)))
myStringerLow = wingStringerType(stringerStructureUID=stringUIDBaseType(valueOf_='Stringer_WING_low'), angle=doubleBaseType(valueOf_='0.0'), pitch=doubleBaseType(valueOf_=str(pitch)))
myShell2024 = wingShellType(uID='', skin=mySkin2024, stringer=myStringerLow)
myShell7075 = wingShellType(uID='', skin=mySkin7075, stringer=myStringerUp)
parent.get_structure().set_upperShell(myShell7075)
parent.get_structure().set_lowerShell(myShell2024)
elif typeOfSeg == 'strut':
myComp_Long = materialDefinitionType(compositeUID = stringUIDBaseType(isLink='True',valueOf_='Comp_Long'), orthotropyDirection=doubleBaseType(valueOf_='0.'),\
thicknessScaling=doubleBaseType(valueOf_='0.001'))
mySkinComp = wingSkinType(material=myComp_Long)
myShellComp = wingShellType(uID='', skin=mySkinComp)
parent.get_structure().set_upperShell(myShellComp)
parent.get_structure().set_lowerShell(myShellComp)
def createHTP(CPACSObj, id, xRoot, zRoot, tcRoot, tcTip, cRoot, cTip, span, phiLE, dihedral, LoD=0, location=True):
if LoD == WING_LOD.NONE:
return
# just for now
cpacsPath = '/cpacs/vehicles/aircraft/model/wings/wing[' + id + ']'
# the next line is the one to use later on
# cpacsPath = '/cpacs/vehicles/aircraft/model[model]/wings/wing[' + self.id + ']'
# get the wing object from given cpacs path
myWing = getObjfromXpath(CPACSObj, cpacsPath)
myWing.set_name(stringBaseType(valueOf_='htp'))
strUID = createHeader(myWing, id)
myWing.set_symmetry('x-z-plane')
if location:
myWing.set_parentUID(stringUIDBaseType(isLink=True, valueOf_='fuselage'))
createTransformation(myWing, 'absGlobal', xRoot, 0., zRoot)
else:
myWing.set_parentUID(stringUIDBaseType(isLink=True, valueOf_='vtp'))
createTransformation(myWing, 'absGlobal', xRoot, 0., zRoot)
# call corresponding wing creation method
if LoD == WING_LOD.SINGLE:
createTrapezoidWing(myWing, id, tcTip, tcRoot, cTip, cRoot, span, phiLE, dihedral, 0., strUID)
if not location:
createWingWingAttachment(myWing.get_componentSegments().get_componentSegment()[0], strUID, targetUID='vtp_Cseg', typeOfSeg='ttail')
def cpacsExport(self, CPACSObj):
'''
Export routine for the engine
'''
cpacsPath = '/cpacs/vehicles/aircraft/model/engines/engine'
myEngine = getObjfromXpath(CPACSObj, cpacsPath)
myEngine.set_uID('engine')
myEngine.set_symmetry('x-z-plane')
myEngine.set_parentUID(stringUIDBaseType(valueOf_="enginePylon"))
x = doubleBaseType(valueOf_=str(self.xEngine.getValue()))
y = doubleBaseType(valueOf_=str(self.yEngine.getValue()))
z = doubleBaseType(valueOf_=str(self.zEngine.getValue()))
myTranslation = pointAbsRelType(refType="absGlobal", x=x, y=y, z=z)
myTransformation = transformationType(translation=myTranslation)
myEngine.set_transformation(myTransformation)
# Mass Export Engine Pylon
mass = doubleBaseType(valueOf_=str(self.mEngine.getValue()))
massIX = doubleBaseType(valueOf_=str(self.massIX.getValue()))
massIY = doubleBaseType(valueOf_=str(self.massIY.getValue()))
massIZ = doubleBaseType(valueOf_=str(self.massIZ.getValue()))
massInertia = massInertiaType(Jxx=massIX, Jyy=massIY, Jzz=massIZ)
cpacsPath = '/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mPowerUnits'
mEngines = getObjfromXpath(CPACSObj, cpacsPath)
massDescription = genericMassType(uID='engine_mass', mass=mass, parentUID=stringUIDBaseType(valueOf_="engine"),
massInertia=massInertia)
mEngines.set_massDescription(massDescription)
#call overall export method
super(engine, self).cpacsExport(CPACSObj)
def createSparSegment(parent,
parentUID,
targetUID='FS',
material='aluminium7075',
numOfPoints=3,
typeOfSeg='other'):
'''
Used for generation of sparSegment within sparSegments
@param parent: sparSegments, sparSegment will be added here
@param id: id of the spar either FS or RS
@param material: uID of the material to be used
@param numOfPoint: the number of SparPositions to position the spar
'''
myUID = parentUID + '' + targetUID
myName = stringBaseType(None, None, None, myUID)
myDescr = stringBaseType(None, None, None, myUID)
#===========================================================================
# Spar Position UIDS
#===========================================================================
mySparPositionUIDs = sparPositionUIDsType(None, None, None, None)
for i in range(numOfPoints):
sparPositionUID = stringUIDBaseType(None, None, None, None,
myUID + '_P' + str(i))
mySparPositionUIDs.add_sparPositionUID(sparPositionUID)
#===========================================================================
# Spar Cross Section
#===========================================================================
if typeOfSeg != 'strut':
myMaterialUID = stringUIDBaseType(isLink='True', valueOf_=material)
myThickness = doubleBaseType(valueOf_=str(0.003))
myMaterial = materialDefinitionType(materialUID=myMaterialUID,
thickness=myThickness)
elif typeOfSeg == 'strut':
myMaterial = materialDefinitionType(compositeUID = stringUIDBaseType(isLink='True',valueOf_='Comp_Shear'), orthotropyDirection=doubleBaseType(valueOf_='0.'),\
thicknessScaling=doubleBaseType(valueOf_='0.001'))
myArea = doubleBaseType(None, None, None, str(0.0003))
myCap = capType(None, None, None, myArea, myMaterial)
myRelPos = doubleBaseType(None, None, None, str(0.5))
myWeb = webType(None, None, None, myMaterial, myRelPos)
myRotation = doubleBaseType(None, None, None, str(90.0))
mySparCrossSection = sparCrossSectionType(None, None, None, myCap, myCap,
myWeb, None, None, myRotation)
#===========================================================================
mySpar = sparSegmentType(None, None, None, myUID, myName, myDescr,
mySparPositionUIDs, mySparCrossSection)
parent.add_sparSegment(mySpar)
def createShell(parent, parentUID, typeOfSeg, thickness=0.003, pitch=0.14):
'''
Used for generation of wing upper and lower shell within a componentSegment
@param parent: ComponentSegment object, upper and lower shell-object will be added here
@param thickness: thickness of the wing shell
@param pitch: pitch of the stringers
@param typeOfSeg: either advDoubleTrapezoid or trapezoid
'''
if typeOfSeg != 'strut':
myAlu2024 = materialDefinitionType(
materialUID=stringUIDBaseType(isLink='True',
valueOf_='aluminium2024'),
thickness=doubleBaseType(valueOf_=str(thickness)))
myAlu7075 = materialDefinitionType(
materialUID=stringUIDBaseType(isLink='True',
valueOf_='aluminium7075'),
thickness=doubleBaseType(valueOf_=str(thickness)))
mySkin2024 = wingSkinType(material=myAlu2024)
mySkin7075 = wingSkinType(material=myAlu7075)
myStringerUp = wingStringerType(
stringerStructureUID=stringUIDBaseType(
valueOf_='Stringer_WING_up'),
angle=doubleBaseType(valueOf_='0.0'),
pitch=doubleBaseType(valueOf_=str(pitch)))
myStringerLow = wingStringerType(
stringerStructureUID=stringUIDBaseType(
valueOf_='Stringer_WING_low'),
angle=doubleBaseType(valueOf_='0.0'),
pitch=doubleBaseType(valueOf_=str(pitch)))
myShell2024 = wingShellType(uID='',
skin=mySkin2024,
stringer=myStringerLow)
myShell7075 = wingShellType(uID='',
skin=mySkin7075,
stringer=myStringerUp)
parent.get_structure().set_upperShell(myShell7075)
parent.get_structure().set_lowerShell(myShell2024)
elif typeOfSeg == 'strut':
myComp_Long = materialDefinitionType(compositeUID = stringUIDBaseType(isLink='True',valueOf_='Comp_Long'), orthotropyDirection=doubleBaseType(valueOf_='0.'),\
thicknessScaling=doubleBaseType(valueOf_='0.001'))
mySkinComp = wingSkinType(material=myComp_Long)
myShellComp = wingShellType(uID='', skin=mySkinComp)
parent.get_structure().set_upperShell(myShellComp)
parent.get_structure().set_lowerShell(myShellComp)
def createWingFuselageAttachment(parent, parentUID, targetUID='fuselage', typeOfSeg='advDoubletrapezoid'):
if typeOfSeg == 'advDoubletrapezoid':
toFuselageUID = stringUIDBaseType(valueOf_=targetUID)
rib1 = ribIdentificationType(ribDefinitionUID=stringUIDBaseType(valueOf_='wing_ribs_inner'), ribNumber=integerBaseType(valueOf_=str(4)))
wingFuselageAttachment = wingFuselageAttachmentType(rib1=rib1)
if typeOfSeg =='strut':
toFuselageUID = stringUIDBaseType(valueOf_=targetUID)
rib1 = ribIdentificationType(ribDefinitionUID=stringUIDBaseType(valueOf_='strut_ribs'), ribNumber=integerBaseType(valueOf_=str(1)))
wingFuselageAttachment = wingFuselageAttachmentType(rib1=rib1)
wingFuselageAttachments = wingFuselageAttachmentsType(wingFuselageAttachment=[wingFuselageAttachment])
parent.set_wingFuselageAttachments(wingFuselageAttachments)
def createSpoiler(name, parentUID, innerEtaLE, innerEtaTE, innerXsiLE, innerXsiTE, outerEtaLE, outerEtaTE, outerXsiLE, outerXsiTE):
#===========================================================================
# Header
#===========================================================================
log.debug('VAMPzero SPOILER: Creating Spoiler: %s' % (str(name)))
log.debug('VAMPzero SPOILER: innerEtaLE: %s' % str(innerEtaLE))
log.debug('VAMPzero SPOILER: innerEtaTE: %s' % str(innerEtaTE))
log.debug('VAMPzero SPOILER: innerXsiLE: %s' % str(innerXsiLE))
log.debug('VAMPzero SPOILER: innerXsiTE: %s' % str(innerXsiTE))
log.debug('VAMPzero SPOILER: outerEtaLE: %s' % str(outerEtaLE))
log.debug('VAMPzero SPOILER: outerEtaTE: %s' % str(outerEtaTE))
log.debug('VAMPzero SPOILER: outerXsiLE: %s' % str(outerXsiLE))
log.debug('VAMPzero SPOILER: outerXsiTE: %s' % str(outerXsiTE))
myName = stringBaseType(None, None, None, name)
myDescription = stringBaseType(None, None, None, 'spoiler from VAMPzero')
myParentUID = stringUIDBaseType(None, None, 'True', None, parentUID)
myleadingEdgeShape = leadingEdgeShapeType(relHeightLE=doubleBaseType(valueOf_=str(0.75)))
innerBorder = controlSurfaceBorderSpoilerType(etaLE=doubleBaseType(valueOf_=str(innerEtaLE)), etaTE=doubleBaseType(valueOf_=str(innerEtaTE)), xsiLE=doubleBaseType(valueOf_=str(innerXsiLE)), xsiTE=doubleBaseType(valueOf_=str(innerXsiTE)), leadingEdgeShape=myleadingEdgeShape)
outerBorder = controlSurfaceBorderSpoilerType(etaLE=doubleBaseType(valueOf_=str(outerEtaLE)), etaTE=doubleBaseType(valueOf_=str(outerEtaTE)), xsiLE=doubleBaseType(valueOf_=str(outerXsiLE)), xsiTE=doubleBaseType(valueOf_=str(outerXsiTE)), leadingEdgeShape=myleadingEdgeShape)
myOuterShape = controlSurfaceOuterShapeSpoilerType(innerBorder=innerBorder, outerBorder=outerBorder)
myStructure = wingComponentSegmentStructureType()
mySpoiler = spoilerType(uID=name + 'UID', name=myName, description=myDescription, parentUID=myParentUID, outerShape=myOuterShape, structure=myStructure)
createSpoilerStructure(mySpoiler)
return mySpoiler
def createRudder(parentVtpCPACS, parentVtpVAMPzero, myRudder):
"""
This is the main export method for the wings aileron
"""
cpacsPath = "/cpacs/vehicles/aircraft/model/wings/wing[" + parentVtpVAMPzero.id + "]"
cpacsVtp = getObjfromXpath(parentVtpCPACS, cpacsPath)
cpacsComponentSegment = cpacsVtp.get_componentSegments().get_componentSegment()[0]
# ===========================================================================
# Header
# ===========================================================================
myName = stringBaseType(None, None, None, "rudder")
myDescription = stringBaseType(None, None, None, "rudder from VAMPzero")
myParentUID = stringUIDBaseType(None, None, "True", None, "vtp_Cseg")
# ===========================================================================
# Outer Shape
# With the rudder this is pretty simple as it is supposed to cover
# the same span as the VTP
# ===========================================================================
# the inner border eta is determined from the rooYLocation of the Rudder and the vtp span
vtpSpan = parentVtpVAMPzero.span.getValue() / 2.0
innerEtaLE = 0.0
outerEtaLE = 1.0
innerXsiLE = myRudder.cRoot.getValue() / parentVtpVAMPzero.cRoot.getValue()
outerXsiLE = myRudder.cTip.getValue() / parentVtpVAMPzero.cTip.getValue()
# start writing back
myleadingEdgeShape = leadingEdgeShapeType(
relHeightLE=doubleBaseType(valueOf_=str(0.5)),
xsiUpperSkin=doubleBaseType(valueOf_=str(0.85)),
xsiLowerSkin=doubleBaseType(valueOf_=str(0.85)),
)
innerBorder = controlSurfaceBorderTrailingEdgeType(
etaLE=doubleBaseType(valueOf_=str(innerEtaLE)),
xsiLE=doubleBaseType(valueOf_=str(innerXsiLE)),
leadingEdgeShape=myleadingEdgeShape,
)
outerBorder = controlSurfaceBorderTrailingEdgeType(
etaLE=doubleBaseType(valueOf_=str(outerEtaLE)),
xsiLE=doubleBaseType(valueOf_=str(outerXsiLE)),
leadingEdgeShape=myleadingEdgeShape,
)
myOuterShape = controlSurfaceOuterShapeTrailingEdgeType(innerBorder=innerBorder, outerBorder=outerBorder)
cpacsRudder = trailingEdgeDeviceType(
uID="rudderUID", name=myName, description=myDescription, parentUID=myParentUID, outerShape=myOuterShape
)
createPath(cpacsRudder, "rudder")
if type(cpacsComponentSegment.get_controlSurfaces()) == NoneType:
cpacsComponentSegment.set_controlSurfaces(controlSurfacesType())
if type(cpacsComponentSegment.get_controlSurfaces().get_trailingEdgeDevices()) == NoneType:
cpacsComponentSegment.get_controlSurfaces().set_trailingEdgeDevices(trailingEdgeDevicesType())
cpacsComponentSegment.get_controlSurfaces().get_trailingEdgeDevices().add_trailingEdgeDevice(cpacsRudder)
def createSparSegment(parent, parentUID, targetUID='FS', material='aluminium7075', numOfPoints=3, typeOfSeg='other'):
'''
Used for generation of sparSegment within sparSegments
@param parent: sparSegments, sparSegment will be added here
@param id: id of the spar either FS or RS
@param material: uID of the material to be used
@param numOfPoint: the number of SparPositions to position the spar
'''
myUID = parentUID + '' + targetUID
myName = stringBaseType(valueOf_=myUID)
myDescr = stringBaseType(valueOf_= myUID)
#===========================================================================
# Spar Position UIDS
#===========================================================================
mySparPositionUIDs = sparPositionUIDsType()
for i in range(numOfPoints):
sparPositionUID = stringUIDBaseType(valueOf_=myUID + '_P' + str(i))
mySparPositionUIDs.add_sparPositionUID(sparPositionUID)
#===========================================================================
# Spar Cross Section
#===========================================================================
if typeOfSeg != 'strut':
myMaterialUID = stringUIDBaseType(isLink='True', valueOf_=material)
myThickness = doubleBaseType(valueOf_=str(0.003))
myMaterial = materialDefinitionType(materialUID=myMaterialUID, thickness=myThickness)
elif typeOfSeg =='strut':
#myMaterial = materialDefinitionType(compositeUID = stringUIDBaseType(isLink='True',valueOf_='Comp_Shear'), orthotropyDirection=doubleBaseType(valueOf_='0.'),\
# thicknessScaling=doubleBaseType(valueOf_='0.001'))
myMaterial = materialDefinitionType(materialUID=stringUIDBaseType(isLink='True', valueOf_='aluminium7075'), thickness=doubleBaseType(valueOf_=str(0.03)))
myArea = doubleBaseType(valueOf_=str(0.0003))
myCap = capType(area=myArea, material=myMaterial)
myRelPos = doubleBaseType(valueOf_=str(0.5))
myWeb = webType(material=myMaterial, relPos=myRelPos)
myRotation = doubleBaseType(valueOf_= str(90.0))
mySparCrossSection = sparCrossSectionType(upperCap=myCap, lowerCap=myCap, web1=myWeb, rotation=myRotation)
#===========================================================================
mySpar = sparSegmentType(uID=myUID, name=myName, description=myDescr, sparPositionUIDs=mySparPositionUIDs, sparCrossSection=mySparCrossSection)
parent.add_sparSegment(mySpar)
def createHTP(CPACSObj,
id,
xRoot,
zRoot,
tcRoot,
tcTip,
cRoot,
cTip,
span,
phiLE,
dihedral,
LoD=0,
location=True):
if LoD == WING_LOD.NONE:
return
# just for now
cpacsPath = '/cpacs/vehicles/aircraft/model/wings/wing[' + id + ']'
# the next line is the one to use later on
# cpacsPath = '/cpacs/vehicles/aircraft/model[model]/wings/wing[' + self.id + ']'
# get the wing object from given cpacs path
myWing = getObjfromXpath(CPACSObj, cpacsPath)
myWing.set_name(stringBaseType(valueOf_='htp'))
strUID = createHeader(myWing, id)
myWing.set_symmetry('x-z-plane')
if location:
myWing.set_parentUID(
stringUIDBaseType(isLink=True, valueOf_='fuselage'))
createTransformation(myWing, 'absGlobal', xRoot, 0., zRoot)
else:
myWing.set_parentUID(stringUIDBaseType(isLink=True, valueOf_='vtp'))
createTransformation(myWing, 'absGlobal', xRoot, 0., zRoot)
# call corresponding wing creation method
if LoD == WING_LOD.SINGLE:
createTrapezoidWing(myWing, id, tcTip, tcRoot, cTip, cRoot, span,
phiLE, dihedral, 0., strUID)
if not location:
createWingWingAttachment(
myWing.get_componentSegments().get_componentSegment()[0],
strUID,
targetUID='vtp_Cseg',
typeOfSeg='ttail')
def createStabilizer(parentHtpCPACS, parentHtpVAMPzero, myElevator):
'''
This is the main export method for the stabilizer, i.e. the whole htp as control surface
'''
cpacsPath = '/cpacs/vehicles/aircraft/model/wings/wing[' + parentHtpVAMPzero.id + ']'
cpacsHtp = getObjfromXpath(parentHtpCPACS, cpacsPath)
cpacsComponentSegment = cpacsHtp.get_componentSegments(
).get_componentSegment()[0]
#===========================================================================
# Header
#===========================================================================
myName = stringBaseType(None, None, None, 'stabilizer')
myDescription = stringBaseType(None, None, None,
'stabilizer exported from VAMPzero')
myParentUID = stringUIDBaseType(None, None, 'True', None,
parentHtpVAMPzero.id)
#===========================================================================
# Outer Shape
#===========================================================================
innerEtaLE = 0.
innerXsiLE = 0.
outerEtaLE = 1.
outerXsiLE = 0.
# start writing back
#myleadingEdgeShape = leadingEdgeShapeType(relHeightLE=doubleBaseType(valueOf_=str(0.5)), xsiUpperSkin=doubleBaseType(valueOf_=str(0.85)), xsiLowerSkin=doubleBaseType(valueOf_=str(0.85)))
innerBorder = controlSurfaceBorderTrailingEdgeType(
etaLE=doubleBaseType(valueOf_=str(innerEtaLE)),
xsiLE=doubleBaseType(valueOf_=str(innerXsiLE)))
outerBorder = controlSurfaceBorderTrailingEdgeType(
etaLE=doubleBaseType(valueOf_=str(outerEtaLE)),
xsiLE=doubleBaseType(valueOf_=str(outerXsiLE)))
myOuterShape = controlSurfaceOuterShapeTrailingEdgeType(
innerBorder=innerBorder, outerBorder=outerBorder)
cpacsStabilizer = trailingEdgeDeviceType(uID='stabilizerUID',
name=myName,
description=myDescription,
parentUID=myParentUID,
outerShape=myOuterShape)
createPath(cpacsStabilizer, 'stabilizer')
if type(cpacsComponentSegment.get_controlSurfaces()) == NoneType:
cpacsComponentSegment.set_controlSurfaces(controlSurfacesType())
if type(cpacsComponentSegment.get_controlSurfaces().
get_trailingEdgeDevices()) == NoneType:
cpacsComponentSegment.get_controlSurfaces().set_trailingEdgeDevices(
trailingEdgeDevicesType())
cpacsComponentSegment.get_controlSurfaces().get_trailingEdgeDevices(
).add_trailingEdgeDevice(cpacsStabilizer)
def createFlap(name,
parentUID,
innerEtaLE,
innerXsiLE,
outerEtaLE,
outerXsiLE,
maxX,
appendInnerCruiseRoller=False,
type='flap',
innerX=0.,
outerX=0.):
log.debug('VAMPzero FLAP: Creating Flap: %s' % (str(name)))
log.debug('VAMPzero FLAP: innerEtaLE: %s' % str(innerEtaLE))
log.debug('VAMPzero FLAP: outerEtaLE: %s' % str(outerEtaLE))
log.debug('VAMPzero FLAP: innerXsiLE: %s' % str(innerXsiLE))
log.debug('VAMPzero FLAP: outerXsiLE: %s' % str(outerXsiLE))
myName = stringBaseType(None, None, None, name)
myDescription = stringBaseType(None, None, None, 'innerFlap from VAMPzero')
myParentUID = stringUIDBaseType(None, None, 'True', None, parentUID)
myleadingEdgeShape = leadingEdgeShapeType(
relHeightLE=doubleBaseType(valueOf_=str(0.2)),
xsiUpperSkin=doubleBaseType(valueOf_=str(0.5)),
xsiLowerSkin=doubleBaseType(valueOf_=str(0.95)))
innerBorder = controlSurfaceBorderTrailingEdgeType(
etaLE=doubleBaseType(valueOf_=str(innerEtaLE)),
etaTE=doubleBaseType(valueOf_=str(innerEtaLE)),
xsiLE=doubleBaseType(valueOf_=str(innerXsiLE)),
leadingEdgeShape=myleadingEdgeShape)
outerBorder = controlSurfaceBorderTrailingEdgeType(
etaLE=doubleBaseType(valueOf_=str(outerEtaLE)),
etaTE=doubleBaseType(valueOf_=str(outerEtaLE)),
xsiLE=doubleBaseType(valueOf_=str(outerXsiLE)),
leadingEdgeShape=myleadingEdgeShape)
myOuterShape = controlSurfaceOuterShapeTrailingEdgeType(
innerBorder=innerBorder, outerBorder=outerBorder)
myStructure = wingComponentSegmentStructureType()
myFlap = trailingEdgeDeviceType(uID=name + 'UID',
name=myName,
description=myDescription,
parentUID=myParentUID,
outerShape=myOuterShape,
structure=myStructure)
createFlapStructure(myFlap,
maxX,
innerXsiLE,
outerXsiLE,
appendInnerCruiseRoller,
type=type,
innerX=innerX,
outerX=outerX)
return myFlap
def createWingFuselageAttachment(parent,
parentUID,
targetUID='fuselage',
typeOfSeg='advDoubletrapezoid'):
if typeOfSeg == 'advDoubletrapezoid':
toFuselageUID = stringUIDBaseType(valueOf_=targetUID)
rib1 = ribIdentificationType(
ribDefinitionUID=stringUIDBaseType(valueOf_='wing_ribs_inner'),
ribNumber=integerBaseType(valueOf_=str(4)))
wingFuselageAttachment = wingFuselageAttachmentType(rib1=rib1)
if typeOfSeg == 'strut':
toFuselageUID = stringUIDBaseType(valueOf_=targetUID)
rib1 = ribIdentificationType(
ribDefinitionUID=stringUIDBaseType(valueOf_='strut_ribs'),
ribNumber=integerBaseType(valueOf_=str(1)))
wingFuselageAttachment = wingFuselageAttachmentType(rib1=rib1)
wingFuselageAttachments = wingFuselageAttachmentsType(
wingFuselageAttachment=[wingFuselageAttachment])
parent.set_wingFuselageAttachments(wingFuselageAttachments)
def cpacsExport(self, CPACSObj):
'''
Export routine for the pylon
'''
# pylon
cpacsPath = '/cpacs/vehicles/aircraft/model/enginePylons/enginePylon'
myPylon = getObjfromXpath(CPACSObj, cpacsPath)
myPylon.set_uID('enginePylon')
if self.aircraft.engine.location.getValue():
myPylon.set_parentUID(stringUIDBaseType(valueOf_="wing"))
else:
myPylon.set_parentUID(stringUIDBaseType(valueOf_="fuselage"))
# Mass Export Engine Pylon
mass = doubleBaseType(valueOf_=str(self.mPylon.getValue()))
cpacsPath = '/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mStructure/mPylons'
mPylons = getObjfromXpath(CPACSObj, cpacsPath)
massDescription = genericMassType(uID='pylon_mass', mass=mass, parentUID=stringUIDBaseType(valueOf_="enginePylon"))
mPylons.set_massDescription(massDescription)
#call overall export method
super(pylon, self).cpacsExport(CPACSObj)
def cpacsExport(self, CPACSObj):
'''
Export routine for the main and nose landing gear
'''
# Main Gear Export
cpacsPath = '/cpacs/vehicles/aircraft/model/landingGear/mainGears/mainGear'
myMainGear = getObjfromXpath(CPACSObj, cpacsPath)
myMainGear.set_parentUID(stringUIDBaseType(valueOf_="fuselage"))
myMainGear.set_uID('mainGear')
myMainGear.set_symmetry('x-z-plane')
# Mass Export Main Landing Gear
mass = doubleBaseType(valueOf_=str(self.mLandingGear.getValue()))
cpacsPath = '/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mStructure/mLandingGears'
myLandingGears = getObjfromXpath(CPACSObj, cpacsPath)
massDescription = genericMassType(uID='mainGear_Mass', mass=mass, parentUID=stringUIDBaseType(valueOf_="mainGear"))
myRightMainGear = mLandingGearType(massDescription=massDescription)
myLandingGears.add_mLandingGear(myRightMainGear)
# Nose Gear Export
cpacsPath = '/cpacs/vehicles/aircraft/model/landingGear/noseGears/noseGear'
myNoseGear = getObjfromXpath(CPACSObj, cpacsPath)
myNoseGear.set_parentUID(stringUIDBaseType(valueOf_="fuselage"))
myNoseGear.set_uID('noseGear')
# Mass Export Nose Landing Gear
mass = doubleBaseType(valueOf_=str(self.mNoseGear.getValue()))
cpacsPath = '/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mStructure/mLandingGears'
myLandingGears = getObjfromXpath(CPACSObj, cpacsPath)
massDescription = genericMassType(uID='noseGear_mass', mass=mass, parentUID=stringUIDBaseType(valueOf_="noseGear"))
myRightMainGear = mLandingGearType(massDescription=massDescription)
myLandingGears.add_mLandingGear(myRightMainGear)
#call overall export method
super(landingGear, self).cpacsExport(CPACSObj)
def createStabilizer(parentHtpCPACS, parentHtpVAMPzero, myElevator):
"""
This is the main export method for the stabilizer, i.e. the whole htp as control surface
"""
cpacsPath = "/cpacs/vehicles/aircraft/model/wings/wing[" + parentHtpVAMPzero.id + "]"
cpacsHtp = getObjfromXpath(parentHtpCPACS, cpacsPath)
cpacsComponentSegment = cpacsHtp.get_componentSegments().get_componentSegment()[0]
# ===========================================================================
# Header
# ===========================================================================
myName = stringBaseType(None, None, None, "stabilizer")
myDescription = stringBaseType(None, None, None, "stabilizer exported from VAMPzero")
myParentUID = stringUIDBaseType(None, None, "True", None, parentHtpVAMPzero.id)
# ===========================================================================
# Outer Shape
# ===========================================================================
innerEtaLE = 0.0
innerXsiLE = 0.0
outerEtaLE = 1.0
outerXsiLE = 0.0
# start writing back
# myleadingEdgeShape = leadingEdgeShapeType(relHeightLE=doubleBaseType(valueOf_=str(0.5)), xsiUpperSkin=doubleBaseType(valueOf_=str(0.85)), xsiLowerSkin=doubleBaseType(valueOf_=str(0.85)))
innerBorder = controlSurfaceBorderTrailingEdgeType(
etaLE=doubleBaseType(valueOf_=str(innerEtaLE)), xsiLE=doubleBaseType(valueOf_=str(innerXsiLE))
)
outerBorder = controlSurfaceBorderTrailingEdgeType(
etaLE=doubleBaseType(valueOf_=str(outerEtaLE)), xsiLE=doubleBaseType(valueOf_=str(outerXsiLE))
)
myOuterShape = controlSurfaceOuterShapeTrailingEdgeType(innerBorder=innerBorder, outerBorder=outerBorder)
cpacsStabilizer = trailingEdgeDeviceType(
uID="stabilizerUID", name=myName, description=myDescription, parentUID=myParentUID, outerShape=myOuterShape
)
createPath(cpacsStabilizer, "stabilizer")
if type(cpacsComponentSegment.get_controlSurfaces()) == NoneType:
cpacsComponentSegment.set_controlSurfaces(controlSurfacesType())
if type(cpacsComponentSegment.get_controlSurfaces().get_trailingEdgeDevices()) == NoneType:
cpacsComponentSegment.get_controlSurfaces().set_trailingEdgeDevices(trailingEdgeDevicesType())
cpacsComponentSegment.get_controlSurfaces().get_trailingEdgeDevices().add_trailingEdgeDevice(cpacsStabilizer)
def createSpoiler(name, parentUID, innerEtaLE, innerEtaTE, innerXsiLE,
innerXsiTE, outerEtaLE, outerEtaTE, outerXsiLE, outerXsiTE):
#===========================================================================
# Header
#===========================================================================
log.debug('VAMPzero SPOILER: Creating Spoiler: %s' % (str(name)))
log.debug('VAMPzero SPOILER: innerEtaLE: %s' % str(innerEtaLE))
log.debug('VAMPzero SPOILER: innerEtaTE: %s' % str(innerEtaTE))
log.debug('VAMPzero SPOILER: innerXsiLE: %s' % str(innerXsiLE))
log.debug('VAMPzero SPOILER: innerXsiTE: %s' % str(innerXsiTE))
log.debug('VAMPzero SPOILER: outerEtaLE: %s' % str(outerEtaLE))
log.debug('VAMPzero SPOILER: outerEtaTE: %s' % str(outerEtaTE))
log.debug('VAMPzero SPOILER: outerXsiLE: %s' % str(outerXsiLE))
log.debug('VAMPzero SPOILER: outerXsiTE: %s' % str(outerXsiTE))
myName = stringBaseType(None, None, None, name)
myDescription = stringBaseType(None, None, None, 'spoiler from VAMPzero')
myParentUID = stringUIDBaseType(None, None, 'True', None, parentUID)
myleadingEdgeShape = leadingEdgeShapeType(relHeightLE=doubleBaseType(
valueOf_=str(0.75)))
innerBorder = controlSurfaceBorderSpoilerType(
etaLE=doubleBaseType(valueOf_=str(innerEtaLE)),
etaTE=doubleBaseType(valueOf_=str(innerEtaTE)),
xsiLE=doubleBaseType(valueOf_=str(innerXsiLE)),
xsiTE=doubleBaseType(valueOf_=str(innerXsiTE)),
leadingEdgeShape=myleadingEdgeShape)
outerBorder = controlSurfaceBorderSpoilerType(
etaLE=doubleBaseType(valueOf_=str(outerEtaLE)),
etaTE=doubleBaseType(valueOf_=str(outerEtaTE)),
xsiLE=doubleBaseType(valueOf_=str(outerXsiLE)),
xsiTE=doubleBaseType(valueOf_=str(outerXsiTE)),
leadingEdgeShape=myleadingEdgeShape)
myOuterShape = controlSurfaceOuterShapeSpoilerType(innerBorder=innerBorder,
outerBorder=outerBorder)
myStructure = wingComponentSegmentStructureType()
mySpoiler = spoilerType(uID=name + 'UID',
name=myName,
description=myDescription,
parentUID=myParentUID,
outerShape=myOuterShape,
structure=myStructure)
createSpoilerStructure(mySpoiler)
return mySpoiler
def createVTP(CPACSObj,
id,
xRoot,
zRoot,
tcRoot,
tcTip,
cRoot,
cTip,
span,
phiLE,
LoD=0):
if LoD == WING_LOD.NONE:
return
# just for now
cpacsPath = '/cpacs/vehicles/aircraft/model/wings/wing[' + id + ']'
# the next line is the one to use later on
# cpacsPath = '/cpacs/vehicles/aircraft/model[model]/wings/wing[' + self.id + ']'
# get the wing object from given cpacs path
myWing = getObjfromXpath(CPACSObj, cpacsPath)
myWing.set_name(stringBaseType(valueOf_='vtp'))
myWing.set_parentUID(stringUIDBaseType(isLink=True, valueOf_='fuselage'))
strUID = createHeader(myWing, id)
# rotate vertical tail to correct orientation
createTransformation(myWing, 'absGlobal', xRoot, 0., zRoot, 1., 1., 1.,
90., 0., 0.)
# As the vtp is not symmetrical span values must be dubbled for conversion
span = span * 2
# call corresponding wing creation method
if LoD == WING_LOD.SINGLE:
createTrapezoidWing(myWing,
id,
tcRoot,
tcTip,
cTip,
cRoot,
span,
phiLE,
dihedral=0,
twist=0.,
strUID=strUID)
def createFlap(name, parentUID, innerEtaLE, innerXsiLE, outerEtaLE, outerXsiLE, maxX, appendInnerCruiseRoller=False, type='flap', innerX=0., outerX=0.):
log.debug('VAMPzero FLAP: Creating Flap: %s' % (str(name)))
log.debug('VAMPzero FLAP: innerEtaLE: %s' % str(innerEtaLE))
log.debug('VAMPzero FLAP: outerEtaLE: %s' % str(outerEtaLE))
log.debug('VAMPzero FLAP: innerXsiLE: %s' % str(innerXsiLE))
log.debug('VAMPzero FLAP: outerXsiLE: %s' % str(outerXsiLE))
myName = stringBaseType(None, None, None, name)
myDescription = stringBaseType(None, None, None, 'innerFlap from VAMPzero')
myParentUID = stringUIDBaseType(None, None, 'True', None, parentUID)
myleadingEdgeShape = leadingEdgeShapeType(relHeightLE=doubleBaseType(valueOf_=str(0.2)), xsiUpperSkin=doubleBaseType(valueOf_=str(0.5)), xsiLowerSkin=doubleBaseType(valueOf_=str(0.95)))
innerBorder = controlSurfaceBorderTrailingEdgeType(etaLE=doubleBaseType(valueOf_=str(innerEtaLE)), etaTE=doubleBaseType(valueOf_=str(innerEtaLE)), xsiLE=doubleBaseType(valueOf_=str(innerXsiLE)), leadingEdgeShape=myleadingEdgeShape)
outerBorder = controlSurfaceBorderTrailingEdgeType(etaLE=doubleBaseType(valueOf_=str(outerEtaLE)), etaTE=doubleBaseType(valueOf_=str(outerEtaLE)), xsiLE=doubleBaseType(valueOf_=str(outerXsiLE)), leadingEdgeShape=myleadingEdgeShape)
myOuterShape = controlSurfaceOuterShapeTrailingEdgeType(innerBorder=innerBorder, outerBorder=outerBorder)
myStructure = wingComponentSegmentStructureType()
myFlap = trailingEdgeDeviceType(uID=name + 'UID', name=myName, description=myDescription, parentUID=myParentUID, outerShape=myOuterShape, structure=myStructure)
createFlapStructure(myFlap, maxX, innerXsiLE, outerXsiLE, appendInnerCruiseRoller, type=type, innerX=innerX, outerX=outerX)
return myFlap
def setUIDs(self):
###################################################################################################
##Set UIDS
###################################################################################################
CPACSObj = cpacsLib.parse(self.cpacsOut)
#UID for aircraft model
cpacsPath = '/cpacs/vehicles/aircraft/model'
myCPACSAircraft = exportLib.getObjfromXpath(CPACSObj,cpacsPath)
myCPACSAircraft.set_uID(self.aircraft.modelUID.getValue())
#UID for engine
cpacsPath = '/cpacs/vehicles/aircraft/model/engines/engine'
myCPACSEngine = exportLib.getObjfromXpath(CPACSObj,cpacsPath)
myCPACSEngine.set_uID('model_engine')
myCPACSEngine.set_engineUID(cpacsLib.stringUIDBaseType(valueOf_='engine'))
myCPACSEngine.set_symmetry('x-z-plane')
#save and close
outfile = open(self.cpacsOut,'w')
CPACSObj.export(outfile,0)
outfile.close()
def createSlat(name, parentUID, innerEtaTE, innerXsiTE, outerEtaTE, outerXsiTE, innerX, outerX):
# Header
log.debug('VAMPzero SLAT: Creating Slat: %s' % (str(name)))
log.debug('VAMPzero SLAT: innerEtaTE: %s' % str(innerEtaTE))
log.debug('VAMPzero SLAT: outerEtaTE: %s' % str(outerEtaTE))
log.debug('VAMPzero SLAT: innerXsiTE: %s' % str(innerXsiTE))
log.debug('VAMPzero SLAT: outerXsiTE: %s' % str(outerXsiTE))
myName = stringBaseType(valueOf_=name)
myDescription = stringBaseType(valueOf_='slat from VAMPzero')
myParentUID = stringUIDBaseType(isLink='True', valueOf_=parentUID)
myleadingEdgeShape = leadingEdgeShapeType(relHeightLE=doubleBaseType(valueOf_=str(0.5)), xsiUpperSkin=doubleBaseType(valueOf_=str(0.85)), xsiLowerSkin=doubleBaseType(valueOf_=str(0.85)))
innerBorder = controlSurfaceBorderLeadingEdgeType(etaLE=doubleBaseType(valueOf_=str(innerEtaTE)), xsiTEUpper=doubleBaseType(valueOf_=str(innerXsiTE)), xsiTELower=doubleBaseType(valueOf_=str(0.02)), leadingEdgeShape=myleadingEdgeShape)
outerBorder = controlSurfaceBorderLeadingEdgeType(etaLE=doubleBaseType(valueOf_=str(outerEtaTE)), xsiTEUpper=doubleBaseType(valueOf_=str(outerXsiTE)), xsiTELower=doubleBaseType(valueOf_=str(0.02)), leadingEdgeShape=myleadingEdgeShape)
myOuterShape = controlSurfaceOuterShapeLeadingEdgeType(innerBorder=innerBorder, outerBorder=outerBorder)
mySlat = leadingEdgeDeviceType(uID=name + 'UID', name=myName, description=myDescription, parentUID=myParentUID, outerShape=myOuterShape)
createPath(mySlat, typeOfSeg = "slat", uID=name + 'UID', innerX=innerX, outerX=outerX, innerHingeXsi = 0.5, outerHingeXsi = 0.5)
return mySlat
def createActuator(uID='act', actuatorUID='Aileron_Act', etaControlSurface=0.3, parentXsi=0.7, parentHeight=0.1, controlSurfaceXsi=0.7, controlSurfaceHeight=0.1):
#===============================================================================
# Create the attachment
#===============================================================================
etaControlSurface = doubleBaseType(valueOf_=str(etaControlSurface))
material = materialDefinitionType(materialUID=stringBaseType(valueOf_='aluminium2024'), thickness=doubleBaseType(valueOf_='0.001'))
parentXsi = doubleBaseType(valueOf_=str(parentXsi))
parentHeight = doubleBaseType(valueOf_=str(parentHeight))
parentAttachment = actuatorParentAttachmentType(parentXsi=parentXsi, parentHeight=parentHeight, material=material)
parentXsi = doubleBaseType(valueOf_=str(controlSurfaceXsi))
parentHeight = doubleBaseType(valueOf_=str(controlSurfaceHeight))
controlSurfaceAttachment = actuatorControlSurfaceAttachmentType(parentXsi=parentXsi, parentHeight=parentHeight, material=material)
attachment = actuatorAttachmentType(etaControlSurface=etaControlSurface, parentAttachment=parentAttachment, controlSurfaceAttachment=controlSurfaceAttachment)
#===========================================================================
# Create the actuator
#===========================================================================
return controlSurfaceActuatorType(uID=uID, actuatorUID=stringUIDBaseType(isLink='True', valueOf_=actuatorUID), attachment=attachment)
def createTrackFlap(uID, eta, trackType, trackSubType=None, actuatorcounter=1):
eta = doubleBaseType(valueOf_=str(eta))
trackType = stringBaseType(valueOf_=trackType)
if trackSubType is not None:
trackSubType = stringBaseType(valueOf_=trackSubType)
global nFlapActuators
trackActuator = trackActuatorType(uID=uID + '_actuatorUID', actuatorUID=stringUIDBaseType(isLink='true', valueOf_='Act_FT'+str(nFlapActuators)), material=materialDefinitionType(materialUID=stringBaseType(valueOf_='aluminium2024'), thickness=doubleBaseType(valueOf_='0.001')))
nFlapActuators += 1
controlSurfaceAttachment = materialDefinitionType(materialUID=stringBaseType(valueOf_='aluminium2024'), thickness=doubleBaseType(valueOf_='0.001'))
#parentAttachment = materialDefinitionType(materialUID=stringBaseType(valueOf_='aluminium2024'), thickness=doubleBaseType(valueOf_='0.001'))
sidePanels = materialDefinitionType(materialUID=stringBaseType(valueOf_='aluminium2024'), thickness=doubleBaseType(valueOf_='0.001'))
upperPanel = materialDefinitionType(materialUID=stringBaseType(valueOf_='aluminium2024'), thickness=doubleBaseType(valueOf_='0.001'))
lowerPanel = materialDefinitionType(materialUID=stringBaseType(valueOf_='titan'), thickness=doubleBaseType(valueOf_='0.001'))
rollerTrack = materialDefinitionType(materialUID=stringBaseType(valueOf_='titan'), thickness=doubleBaseType(valueOf_='0.001'))
ribs = materialDefinitionType(materialUID=stringBaseType(valueOf_='aluminium2024'), thickness=doubleBaseType(valueOf_='0.001'))
car = materialDefinitionType(materialUID=stringBaseType(valueOf_='aluminium2024'), thickness=doubleBaseType(valueOf_='0.001'))
trackStructure = trackStructureType(controlSurfaceAttachment=controlSurfaceAttachment, sidePanels=sidePanels, upperPanel=upperPanel, lowerPanel=lowerPanel, rollerTrack=rollerTrack, ribs=ribs, car=car)
if trackSubType is None:
return controlSurfaceTrackTypeType(uID=uID, eta=eta, trackType=trackType, trackStructure=trackStructure, actuator=trackActuator)
else:
return controlSurfaceTrackTypeType(uID=uID, eta=eta, trackType=trackType, trackSubType=trackSubType, trackStructure=trackStructure, actuator=trackActuator)
def createSlat(name, parentUID, innerEtaTE, innerXsiTE, outerEtaTE, outerXsiTE, innerX, outerX):
#===========================================================================
# Header
#===========================================================================
log.debug('VAMPzero SLAT: Creating Slat: %s' % (str(name)))
log.debug('VAMPzero SLAT: innerEtaTE: %s' % str(innerEtaTE))
log.debug('VAMPzero SLAT: outerEtaTE: %s' % str(outerEtaTE))
log.debug('VAMPzero SLAT: innerXsiTE: %s' % str(innerXsiTE))
log.debug('VAMPzero SLAT: outerXsiTE: %s' % str(outerXsiTE))
myName = stringBaseType(None, None, None, name)
myDescription = stringBaseType(None, None, None, 'slat from VAMPzero')
myParentUID = stringUIDBaseType(None, None, 'True', None, parentUID)
myleadingEdgeShape = leadingEdgeShapeType(relHeightLE=doubleBaseType(valueOf_=str(0.5)), xsiUpperSkin=doubleBaseType(valueOf_=str(0.85)), xsiLowerSkin=doubleBaseType(valueOf_=str(0.85)))
innerBorder = controlSurfaceBorderLeadingEdgeType(etaLE=doubleBaseType(valueOf_=str(innerEtaTE)), xsiTEUpper=doubleBaseType(valueOf_=str(innerXsiTE)), xsiTELower=doubleBaseType(valueOf_=str(0.02)), leadingEdgeShape=myleadingEdgeShape)
outerBorder = controlSurfaceBorderLeadingEdgeType(etaLE=doubleBaseType(valueOf_=str(outerEtaTE)), xsiTEUpper=doubleBaseType(valueOf_=str(outerXsiTE)), xsiTELower=doubleBaseType(valueOf_=str(0.02)), leadingEdgeShape=myleadingEdgeShape)
myOuterShape = controlSurfaceOuterShapeLeadingEdgeType(innerBorder=innerBorder, outerBorder=outerBorder)
mySlat = leadingEdgeDeviceType(uID=name + 'UID', name=myName, description=myDescription, parentUID=myParentUID, outerShape=myOuterShape)
createPath(mySlat, typeOfSeg = "slat", uID=name + 'UID', innerX=innerX, outerX=outerX, innerHingeXsi = 0.5, outerHingeXsi = 0.5)
return mySlat
def createTanks(parent,
parentUID,
targetUID='tank1',
typeOfSeg='advDoubletrapezoid',
nRib='2'):
'''
Used for generation of a wing tank
@param parent: ComponentSegment object, wing fuel tank will be added here.
@param typeOfSeg: either advDoubleTrapezoid or trapezoid
@param iRib: index of Rib in wing_ribs ribDefinition
'''
tanks = []
#===========================================================================
# Tanks
#===========================================================================
if typeOfSeg == 'advDoubletrapezoid':
# Innermost
myUID = parentUID + '_tank_inner'
myName = stringBaseType(None, None, None, myUID)
front = wingFuelTankBorderType(
None, None, None,
stringUIDBaseType(None, None, 'True', None,
parentUID + '_Spar_FS'))
outer = wingFuelTankBorderType(
ribDefinitionUID=stringUIDBaseType(valueOf_='wing_ribs_inner'),
ribNumber=integerBaseType(valueOf_=str(4)))
rear = wingFuelTankBorderType(
None, None, None,
stringUIDBaseType(None, None, 'True', None,
parentUID + '_Spar_RS'))
myGeometry = wingFuelTankGeometryType(None, None, None,
[front, outer, rear])
tanks.append(
wingFuelTankType(None, None, None, myUID, myName, None, myGeometry,
None))
# root to tw
myUID = parentUID + '_tank_middle'
myName = stringBaseType(None, None, None, myUID)
inner = outer
front = wingFuelTankBorderType(
None, None, None,
stringUIDBaseType(None, None, 'True', None,
parentUID + '_Spar_FS'))
outer = wingFuelTankBorderType(
ribDefinitionUID=stringUIDBaseType(valueOf_='wing_ribs_engine2'),
ribNumber=integerBaseType(valueOf_=str(1)))
rear = wingFuelTankBorderType(
None, None, None,
stringUIDBaseType(None, None, 'True', None,
parentUID + '_Spar_RS'))
myGeometry = wingFuelTankGeometryType(None, None, None,
[inner, front, outer, rear])
tanks.append(
wingFuelTankType(None, None, None, myUID, myName, None, myGeometry,
None))
# tw to outer
myUID = parentUID + '_tank_outer'
myName = stringBaseType(None, None, None, myUID)
inner = outer
front = wingFuelTankBorderType(
None, None, None,
stringUIDBaseType(None, None, 'True', None,
parentUID + '_Spar_FS'))
outer = wingFuelTankBorderType(
ribDefinitionUID=stringUIDBaseType(valueOf_=parentUID +
'_ribs_outer'),
ribNumber=integerBaseType(valueOf_=str(nRib)))
rear = wingFuelTankBorderType(
None, None, None,
stringUIDBaseType(None, None, 'True', None,
parentUID + '_Spar_RS'))
myGeometry = wingFuelTankGeometryType(None, None, None,
[inner, front, outer, rear])
tanks.append(
wingFuelTankType(None, None, None, myUID, myName, None, myGeometry,
None))
if typeOfSeg == "strutBracedWing":
# Innermost
myUID = parentUID + '_tank_inner'
myName = stringBaseType(None, None, None, myUID)
front = wingFuelTankBorderType(
None, None, None,
stringUIDBaseType(None, None, 'True', None,
parentUID + '_Spar_FS'))
outer = wingFuelTankBorderType(
ribDefinitionUID=stringUIDBaseType(valueOf_='wing_ribs_inner'),
ribNumber=integerBaseType(valueOf_=str(4)))
rear = wingFuelTankBorderType(
None, None, None,
stringUIDBaseType(None, None, 'True', None,
parentUID + '_Spar_RS'))
myGeometry = wingFuelTankGeometryType(None, None, None,
[front, outer, rear])
tanks.append(
wingFuelTankType(None, None, None, myUID, myName, None, myGeometry,
None))
# root to strut
myUID = parentUID + '_tank_middle'
myName = stringBaseType(None, None, None, myUID)
inner = outer
front = wingFuelTankBorderType(
None, None, None,
stringUIDBaseType(None, None, 'True', None,
parentUID + '_Spar_FS'))
outer = wingFuelTankBorderType(
ribDefinitionUID=stringUIDBaseType(valueOf_='wing_ribs_outer'),
ribNumber=integerBaseType(valueOf_=str(1)))
rear = wingFuelTankBorderType(
None, None, None,
stringUIDBaseType(None, None, 'True', None,
parentUID + '_Spar_RS'))
myGeometry = wingFuelTankGeometryType(None, None, None,
[inner, front, outer, rear])
tanks.append(
wingFuelTankType(None, None, None, myUID, myName, None, myGeometry,
None))
# strut to outer
myUID = parentUID + '_tank_outer'
myName = stringBaseType(None, None, None, myUID)
inner = outer
front = wingFuelTankBorderType(
None, None, None,
stringUIDBaseType(None, None, 'True', None,
parentUID + '_Spar_FS'))
outer = wingFuelTankBorderType(
ribDefinitionUID=stringUIDBaseType(valueOf_=parentUID +
'_ribs_outer'),
ribNumber=integerBaseType(valueOf_=str(nRib)))
rear = wingFuelTankBorderType(
None, None, None,
stringUIDBaseType(None, None, 'True', None,
parentUID + '_Spar_RS'))
myGeometry = wingFuelTankGeometryType(None, None, None,
[inner, front, outer, rear])
tanks.append(
wingFuelTankType(None, None, None, myUID, myName, None, myGeometry,
None))
myTanks = wingFuelTanksType(None, None, None, tanks)
parent.set_wingFuelTanks(myTanks)
def createRudder(parentVtpCPACS, parentVtpVAMPzero, myRudder):
'''
This is the main export method for the wings aileron
'''
cpacsPath = '/cpacs/vehicles/aircraft/model/wings/wing[' + parentVtpVAMPzero.id + ']'
cpacsVtp = getObjfromXpath(parentVtpCPACS, cpacsPath)
cpacsComponentSegment = cpacsVtp.get_componentSegments(
).get_componentSegment()[0]
#===========================================================================
# Header
#===========================================================================
myName = stringBaseType(None, None, None, 'rudder')
myDescription = stringBaseType(None, None, None, 'rudder from VAMPzero')
myParentUID = stringUIDBaseType(None, None, 'True', None, 'vtp_Cseg')
#===========================================================================
# Outer Shape
# With the rudder this is pretty simple as it is supposed to cover
# the same span as the VTP
#===========================================================================
# the inner border eta is determined from the rooYLocation of the Rudder and the vtp span
vtpSpan = parentVtpVAMPzero.span.getValue() / 2.
innerEtaLE = 0.
outerEtaLE = 1.
innerXsiLE = myRudder.cRoot.getValue() / parentVtpVAMPzero.cRoot.getValue()
outerXsiLE = myRudder.cTip.getValue() / parentVtpVAMPzero.cTip.getValue()
# start writing back
myleadingEdgeShape = leadingEdgeShapeType(
relHeightLE=doubleBaseType(valueOf_=str(0.5)),
xsiUpperSkin=doubleBaseType(valueOf_=str(0.85)),
xsiLowerSkin=doubleBaseType(valueOf_=str(0.85)))
innerBorder = controlSurfaceBorderTrailingEdgeType(
etaLE=doubleBaseType(valueOf_=str(innerEtaLE)),
xsiLE=doubleBaseType(valueOf_=str(innerXsiLE)),
leadingEdgeShape=myleadingEdgeShape)
outerBorder = controlSurfaceBorderTrailingEdgeType(
etaLE=doubleBaseType(valueOf_=str(outerEtaLE)),
xsiLE=doubleBaseType(valueOf_=str(outerXsiLE)),
leadingEdgeShape=myleadingEdgeShape)
myOuterShape = controlSurfaceOuterShapeTrailingEdgeType(
innerBorder=innerBorder, outerBorder=outerBorder)
cpacsRudder = trailingEdgeDeviceType(uID='rudderUID',
name=myName,
description=myDescription,
parentUID=myParentUID,
outerShape=myOuterShape)
createPath(cpacsRudder, 'rudder')
if type(cpacsComponentSegment.get_controlSurfaces()) == NoneType:
cpacsComponentSegment.set_controlSurfaces(controlSurfacesType())
if type(cpacsComponentSegment.get_controlSurfaces().
get_trailingEdgeDevices()) == NoneType:
cpacsComponentSegment.get_controlSurfaces().set_trailingEdgeDevices(
trailingEdgeDevicesType())
cpacsComponentSegment.get_controlSurfaces().get_trailingEdgeDevices(
).add_trailingEdgeDevice(cpacsRudder)
def createAileron(parentWingCPACS, parentWingVAMPzero, myAileron):
'''
This is the main export method for the wings aileron
'''
cpacsPath = '/cpacs/vehicles/aircraft/model/wings/wing[' + parentWingVAMPzero.id + ']'
cpacsWing = getObjfromXpath(parentWingCPACS, cpacsPath)
cpacsComponentSegment = cpacsWing.get_componentSegments().get_componentSegment()[0]
# Header
myName = stringBaseType(None, None, None, 'aileron')
myDescription = stringBaseType(None, None, None, 'aileron from VAMPzero')
myParentUID = stringUIDBaseType(None, None, 'True', None, 'wing_Cseg')
# Initialization, i.e. fetching values throughout the code
xsis = []
etas = []
for i in range(3,7):
try:
xsis.append(eval(cpacsComponentSegment.get_structure().get_spars().get_sparPositions().get_sparPosition()[i].get_xsi().valueOf_))
etas.append(eval(cpacsComponentSegment.get_structure().get_spars().get_sparPositions().get_sparPosition()[i].get_eta().valueOf_))
except IndexError:
pass
xsiSpar_interp = scipy.interpolate.interp1d(etas, xsis)
sparOffset = 0.1
wingSpan = parentWingVAMPzero.span.getValue() / 2.
# Outer Shape
# The outer border eta station is set to 96 percent
outerEtaLE = 0.96
# The outer chord station is determined from the wing's chord at eta = 0.96
# and the rear spar location + the spar offset
outerXsiLE = xsiSpar_interp(0.96) + sparOffset
outerWingChord = calcChordLengthAtEta(outerEtaLE, parentWingVAMPzero, cpacsWing)
cTip = (1 - outerXsiLE) * outerWingChord
# now we need to determine the necessary span for the aileron by gently increasing the span
# this is an iterative process as the chord of the aileron is a function of the inbound span
aileronArea = parentWingVAMPzero.aileron.refArea.getValue()
delta = 0.01
calcArea = 0.
while abs(calcArea - aileronArea) > 0.1:
if delta > outerEtaLE:
parentWingVAMPzero.log.warning('VAMPzero EXPORT: Cannot determine the span of the aileron')
parentWingVAMPzero.log.warning('VAMPzero EXPORT: aileronArea= '+str(aileronArea))
parentWingVAMPzero.log.warning('VAMPzero EXPORT: Decreasing Spar Offset')
sparOffset = sparOffset - 0.02
delta = 0.01
innerEtaLE = outerEtaLE - delta
innerXsiLE = xsiSpar_interp(innerEtaLE) + sparOffset
innerWingChord = calcChordLengthAtEta(innerEtaLE, parentWingVAMPzero, cpacsWing)
cRoot = (1 - innerXsiLE) * innerWingChord
calcArea = (cTip + cRoot) / 2 * (outerEtaLE - innerEtaLE) * wingSpan
delta += 0.005
# start outer shape
myleadingEdgeShape = leadingEdgeShapeType(relHeightLE=doubleBaseType(valueOf_=str(0.5)), xsiUpperSkin=doubleBaseType(valueOf_=str(0.85)), xsiLowerSkin=doubleBaseType(valueOf_=str(0.85)))
innerBorder = controlSurfaceBorderTrailingEdgeType(etaLE=doubleBaseType(valueOf_=str(innerEtaLE)), etaTE=doubleBaseType(valueOf_=str(innerEtaLE)), xsiLE=doubleBaseType(valueOf_=str(innerXsiLE)), leadingEdgeShape=myleadingEdgeShape)
outerBorder = controlSurfaceBorderTrailingEdgeType(etaLE=doubleBaseType(valueOf_=str(outerEtaLE)), etaTE=doubleBaseType(valueOf_=str(outerEtaLE)), xsiLE=doubleBaseType(valueOf_=str(outerXsiLE)), leadingEdgeShape=myleadingEdgeShape)
myOuterShape = controlSurfaceOuterShapeTrailingEdgeType(innerBorder=innerBorder, outerBorder=outerBorder)
# structure
myStructure = wingComponentSegmentStructureType()
cpacsAileron = trailingEdgeDeviceType(uID='aileronUID', name=myName, description=myDescription, parentUID=myParentUID, outerShape=myOuterShape, structure=myStructure)
createAileronStructure(cpacsAileron)
# Forward information about innerEtaLE to the flap
parentWingVAMPzero.flap.maxEta = parameter(value=innerEtaLE, doc='This it the inner position of the aileron, the flap may not exceed it')
# moveables
deltaEta = outerEtaLE - innerEtaLE
innerParentXsi = xsiSpar_interp(innerEtaLE + 0.3 * deltaEta) + 0.02
outerParentXsi = xsiSpar_interp(innerEtaLE + 0.7 * deltaEta) + 0.02
createPath(cpacsAileron, 'aileron')
createTracks(cpacsAileron, 'aileron')
createActuators(cpacsAileron, 'aileron', [innerParentXsi, outerParentXsi])
if type(cpacsComponentSegment.get_controlSurfaces()) == NoneType:
cpacsComponentSegment.set_controlSurfaces(controlSurfacesType())
if type(cpacsComponentSegment.get_controlSurfaces().get_trailingEdgeDevices()) == NoneType:
cpacsComponentSegment.get_controlSurfaces().set_trailingEdgeDevices(trailingEdgeDevicesType())
cpacsComponentSegment.get_controlSurfaces().get_trailingEdgeDevices().add_trailingEdgeDevice(cpacsAileron)
def createWing(CPACSObj=None, zeroWing=None, id="1", LoD=0.):
"""
This function triggers the different export modes of the wing depending on the desired
level of detail.
Options include a single trapezoid, double trapezoid, advanced double trapezoid (that includes
a rectangular center fuselage section) and a strut-braced wing.
Please note, these are the internal guts of VAMPzero's CPACS export. A lot of the code
here is experimental and furthermore highly chaotic. In case of emergency contact Daniel or Jonas.
:param CPACSObj: The overall CPACS object of the export
:param zeroWing: The instance of the wing.
:param id: The id of the wing, mostly sth. like wing
:param LoD: The level of detail of the desired input.
:return: CPACSObj including a new wing
"""
if LoD == WING_LOD.NONE:
return
# just for now
cpacsPath = '/cpacs/vehicles/aircraft/model/wings/wing[' + id + ']'
# the next line is the one to use later on
# cpacsPath = '/cpacs/vehicles/aircraft/model[model]/wings/wing[' + self.id + ']'
# get the wing object from given cpacs path
cpacsWing = getObjfromXpath(CPACSObj, cpacsPath)
strUID = createHeader(cpacsWing, id)
cpacsWing.set_symmetry('x-z-plane')
cpacsWing.set_name(stringBaseType(valueOf_='wing'))
cpacsWing.set_parentUID(stringUIDBaseType(isLink=True,
valueOf_='fuselage'))
xRoot = zeroWing.xRoot.getValue()
zRoot = zeroWing.zRoot.getValue()
cRoot = zeroWing.cRoot.getValue()
cTip = zeroWing.cTip.getValue()
span = zeroWing.span.getValue()
dfus = zeroWing.aircraft.fuselage.dfus.getValue()
phiLE = zeroWing.phiLE.getValue()
dihedral = zeroWing.dihedral.getValue()
twist = zeroWing.twist.getValue()
Sref = zeroWing.refArea.getValue()
xMAC25 = zeroWing.xMAC25.getValue()
tcRoot = zeroWing.airfoilr.tc.getValue()
tcTip = zeroWing.airfoilt.tc.getValue()
try:
etakf = zeroWing.etaKink.getValue()
yFus = zeroWing.yFuselage.getValue()
etaEng = zeroWing.etaEngine.getValue()
etaFus = yFus / span * 2.
except AttributeError:
pass #As not all components that call this method have a kink
try:
yRoot = zeroWing.yRoot.getValue()
except AttributeError:
pass #As not all components that call this method have a kink
createTransformation(cpacsWing, 'absGlobal', xRoot, 0., zRoot)
# call corresponding wing creation method
if LoD == WING_LOD.SINGLE:
createTrapezoidWing(cpacsWing, id, tcRoot, tcTip, cTip, cRoot, span,
phiLE, dihedral, twist, strUID)
elif LoD == WING_LOD.DOUBLE:
createDoubleTrapezoidWing(cpacsWing, id, cTip, cRoot, span, Sref,
phiLE, dihedral, twist, xMAC25, etakf,
strUID)
elif LoD == WING_LOD.ADVDOUBLE:
createAdvDoubleTrapezoidWing(cpacsWing, id, cTip, cRoot, span, Sref,
dfus, phiLE, dihedral, twist, xMAC25,
etakf, strUID, yFus, xRoot, etaEng,
tcRoot, tcTip)
elif LoD == WING_LOD.UCAV:
createUCAVWing(cpacsWing, id, cTip, cRoot, span, Sref, phiLE, dihedral,
etakf, strUID)
elif LoD == WING_LOD.SBW:
print "dihedral", dihedral
etaStrut = zeroWing.aircraft.strut.etaStrut.getValue()
createStrutBracedWing(cpacsWing,
id=id,
cTip=cTip,
cRoot=cRoot,
span=span,
Sref=Sref,
phiLE=phiLE,
dihedral=dihedral,
twist=twist,
xMAC25=xMAC25,
etaFus=etaFus,
etaStrut=etaStrut,
tcRoot=tcRoot,
tcTip=tcTip,
xRoot=xRoot,
strUID=strUID)
elif LoD == WING_LOD.STRUT:
etaStrut = zeroWing.aircraft.strut.etaStrut.getValue()
createStrut(cpacsWing,
id=id,
cTip=cTip,
cRoot=cRoot,
span=span,
phiLE=phiLE,
dihedral=dihedral,
tcRoot=tcRoot,
tcTip=tcTip,
xRoot=xRoot,
yRoot=yRoot,
twist=twist,
etaStrut=etaStrut,
strUID=strUID)
def createWingWingAttachment(parent, parentUID, targetUID='wing_Cseg', typeOfSeg='strut'):
if typeOfSeg =='strut':
toComponentSegmentUID = stringUIDBaseType(valueOf_=targetUID)
fromElementUID = stringUIDBaseType(valueOf_='strut_Sec3_Elem1')
toElementUID = stringUIDBaseType(valueOf_='wing_Sec3_Elem1')
elements = wingWingAttachmentElementsType(fromElementUID=fromElementUID, toElementUID=toElementUID)
fromSparUID = stringUIDBaseType(valueOf_='strut_Spar_FS')
toSparUID = stringUIDBaseType(valueOf_='wing_Spar_FS')
sparAttachment = wingWingAttachmentSparsType(fromSparUID=fromSparUID, toSparUID=toSparUID)
sparAttachments = wingWingAttachmentsSparsType(sparAttachment=[sparAttachment])
upperShellAttachment= stringUIDBaseType(valueOf_='upperShell')
lowerShellAttachment= stringUIDBaseType(valueOf_='lowerShell')
wingWingAttachment = wingWingAttachmentType(toComponentSegmentUID=toComponentSegmentUID, elements=elements, sparAttachments=sparAttachments, upperShellAttachment=upperShellAttachment, lowerShellAttachment=lowerShellAttachment)
elif typeOfSeg == 'ttail':
toComponentSegmentUID = stringUIDBaseType(valueOf_=targetUID)
fromElementUID = stringUIDBaseType(valueOf_='htp_Sec1_Elem1')
toElementUID = stringUIDBaseType(valueOf_='vtp_Sec2_Elem1')
elements = wingWingAttachmentElementsType(fromElementUID=fromElementUID, toElementUID=toElementUID)
fromSparUID = stringUIDBaseType(valueOf_='htp_Spar_FS')
toSparUID = stringUIDBaseType(valueOf_='vtp_Spar_FS')
FS_sparAttachment = wingWingAttachmentSparsType(fromSparUID=fromSparUID, toSparUID=toSparUID)
fromSparUID = stringUIDBaseType(valueOf_='htp_Spar_RS')
toSparUID = stringUIDBaseType(valueOf_='vtp_Spar_RS')
RS_sparAttachment = wingWingAttachmentSparsType(fromSparUID=fromSparUID, toSparUID=toSparUID)
sparAttachments = wingWingAttachmentsSparsType(sparAttachment=[FS_sparAttachment, RS_sparAttachment])
upperShellAttachment= stringUIDBaseType(valueOf_='upperShell')
lowerShellAttachment= stringUIDBaseType(valueOf_='lowerShell')
wingWingAttachment = wingWingAttachmentType(toComponentSegmentUID=toComponentSegmentUID, elements=elements, sparAttachments=sparAttachments, upperShellAttachment=upperShellAttachment, lowerShellAttachment=lowerShellAttachment)
wingWingAttachments = wingWingAttachmentsType(wingWingAttachment=[wingWingAttachment])
parent.set_wingWingAttachments(wingWingAttachments)
def createRibs(parent, parentUID, typeOfSeg, thickness=0.03, pitch=.8, nRibs=None, etaFus=0.2, etaEng=.3, span=17., fanDiameter=1.9, etaStrut=0.0, phi25 = 0.0):
'''
Used for generation of a ribs definition in the wing
@param parent: ComponentSegment object, ribsDefinition will be added here
@param thickness: thickness of the ribs
@param pitch: pitch of the ribs
@param typeOfSeg: either advDoubleTrapezoid or trapezoid
'''
myUID = parentUID + '_ribs'
ribsList = []
#===============================================================================
# Advanced Double Trapezoid
#===============================================================================
if typeOfSeg.lower() == 'advdoubletrapezoid':
myName = stringBaseType(valueOf_='wing_ribs')
# Rib Cross Section
#=======================================================================
myMaterial = materialDefinitionType(materialUID=stringUIDBaseType(valueOf_='aluminium7075'), thickness=doubleBaseType(valueOf_=str(thickness)))
myCrossSection = wingRibCrossSectionType(material=myMaterial)
ribReference = stringBaseType(valueOf_=parentUID + '_Spar_FS')
ribStart = stringBaseType(valueOf_=parentUID + '_Spar_FS')
ribEnd = stringBaseType(valueOf_=parentUID + '_Spar_RS')
ribRotation = ribRotationType(ribRotationReference=stringBaseType(valueOf_='globalY'), z=doubleBaseType(valueOf_=str('90.')))
ribCrossing = ribCrossingBehaviourType(valueOf_='cross')
#=======================================================================
# First set of 4 ribs inside the fuselage
#=======================================================================
etaStart = doubleBaseType(valueOf_='0.0')
etaEnd = doubleBaseType(valueOf_=str(etaFus))
innerRibs = doubleBaseType(valueOf_= 4)
ribsPositioning = wingRibsPositioningType(ribReference=ribReference, etaStart=etaStart, etaEnd=etaEnd, ribStart=ribStart, ribEnd=ribEnd, \
numberOfRibs=innerRibs, ribCrossingBehaviour=ribCrossing, ribRotation=ribRotation)
myUID = parentUID + '_ribs_inner'
ribsList.append(wingRibsDefinitionType(uID=myUID, name=myName, ribsPositioning=ribsPositioning, ribCrossSection=myCrossSection))
#===============================================================
# Second set outside of the fuselage up to the engine
#===============================================================
etaPylon = 1. / 10. * fanDiameter / span
etaStart = doubleBaseType(valueOf_=str(etaFus + pitch / span))
etaEnd = doubleBaseType(valueOf_=str(etaEng - etaPylon))
middleRibs = int(ceil((etaEng - etaPylon - etaFus) * span / pitch)) - 1
if middleRibs < 1:
middleRibs = 1
middleRibs = doubleBaseType(valueOf_=middleRibs)
ribsPositioning = wingRibsPositioningType(ribReference=ribReference, etaStart=etaStart, etaEnd=etaEnd, ribStart=ribStart, ribEnd=ribEnd, \
numberOfRibs=middleRibs, ribCrossingBehaviour=ribCrossing, ribRotation=ribRotation)
myUID = parentUID + '_ribs_engine1'
ribsList.append(wingRibsDefinitionType(uID=myUID, name=myName, ribsPositioning=ribsPositioning, ribCrossSection=myCrossSection))
#===============================================================
# Third set one ribs outside of the pylon
#===============================================================
etaEnd = doubleBaseType(valueOf_= str(etaEng + etaPylon))
pylonRibs = doubleBaseType(valueOf_= str(1))
ribsPositioning = wingRibsPositioningType(ribReference=ribReference, etaStart=etaStart, etaEnd=etaEnd, ribStart=ribStart, ribEnd=ribEnd, \
numberOfRibs=pylonRibs, ribCrossingBehaviour=ribCrossing, ribRotation=ribRotation)
myUID = parentUID + '_ribs_engine2'
ribsList.append(wingRibsDefinitionType(uID=myUID, name=myName, ribsPositioning=ribsPositioning, ribCrossSection=myCrossSection))
#===============================================================
# Fourth set outside of the engine
#===============================================================
etaStart = doubleBaseType(valueOf_= str(etaEng + etaPylon + pitch / span))
etaEnd = doubleBaseType(valueOf_= '0.95')
ribCrossing = ribCrossingBehaviourType(valueOf_='end')
ribRotation = ribRotationType(ribRotationReference=stringBaseType(valueOf_='wing_Spar_FS'), \
z=doubleBaseType(valueOf_='90.'))
outerRibs = int(ceil((0.95 - etaEng + etaPylon) * span / pitch)) - 1
outerRibs = doubleBaseType(valueOf_= outerRibs)
ribsPositioning = wingRibsPositioningType(ribReference=ribReference, etaStart=etaStart, etaEnd=etaEnd, ribStart=ribStart, ribEnd=ribEnd, \
numberOfRibs=outerRibs, ribCrossingBehaviour=ribCrossing, ribRotation=ribRotation)
myUID = parentUID + '_ribs_outer'
ribsList.append(wingRibsDefinitionType(uID=myUID, name=myName, ribsPositioning=ribsPositioning, ribCrossSection=myCrossSection))
#===============================================================================
# Strut Braced Wing
#===============================================================================
if typeOfSeg.lower() == 'strutbracedwing':
myName = stringBaseType(valueOf_='wing_ribs')
# Rib Cross Section
#=======================================================================
myMaterial = materialDefinitionType(materialUID=stringUIDBaseType(valueOf_='aluminium7075'), thickness=doubleBaseType(valueOf_=str(thickness)))
myCrossSection = wingRibCrossSectionType(material=myMaterial)
ribReference = stringBaseType(valueOf_=parentUID + '_Spar_FS')
ribStart = stringBaseType(valueOf_=parentUID + '_Spar_FS')
ribEnd = stringBaseType(valueOf_=parentUID + '_Spar_RS')
ribRotation = ribRotationType(ribRotationReference=stringBaseType(valueOf_='globalY'), z=doubleBaseType(valueOf_=str('90.')))
ribCrossing = ribCrossingBehaviourType(valueOf_='cross')
#=======================================================================
# First set of 4 ribs inside the fuselage
#=======================================================================
etaStart = doubleBaseType(valueOf_='0.0')
etaEnd = doubleBaseType(valueOf_=str(etaFus))
innerRibs = doubleBaseType(valueOf_=4)
ribsPositioning = wingRibsPositioningType(ribReference=ribReference, etaStart=etaStart, etaEnd=etaEnd, ribStart=ribStart, ribEnd=ribEnd, \
numberOfRibs=innerRibs, ribCrossingBehaviour=ribCrossing, ribRotation=ribRotation)
myUID = parentUID + '_ribs_inner'
ribsList.append(wingRibsDefinitionType(uID=myUID, name=myName, ribsPositioning=ribsPositioning, ribCrossSection=myCrossSection))
#===============================================================
# Second set outside of the fuselage up to the strut
#===============================================================
etaStart = doubleBaseType(valueOf_=str(etaFus + pitch / span + phi25 * 0.0002))
etaEnd = doubleBaseType(valueOf_=str(etaStrut))
middleRibs = int(ceil((etaStrut - etaFus) * span / pitch)) - 1
middleRibs = doubleBaseType(valueOf_=middleRibs)
ribsPositioning = wingRibsPositioningType(ribReference=ribReference, etaStart=etaStart, etaEnd=etaEnd, ribStart=ribStart, ribEnd=ribEnd, \
numberOfRibs=middleRibs, ribCrossingBehaviour=ribCrossing, ribRotation=ribRotation)
myUID = parentUID + '_ribs_strut'
ribsList.append(wingRibsDefinitionType(uID=myUID, name=myName, ribsPositioning=ribsPositioning, ribCrossSection=myCrossSection))
#===============================================================
# Third set outside of the spar
#===============================================================
etaStart = doubleBaseType(valueOf_=str(etaStrut + pitch / span))
etaEnd = doubleBaseType(valueOf_='0.95')
ribCrossing = ribCrossingBehaviourType(valueOf_='end')
ribRotation = ribRotationType(ribRotationReference=stringBaseType(valueOf_='wing_Spar_FS'), z=doubleBaseType(valueOf_=str('90.')))
outerRibs = int(ceil((0.95 - etaStrut) * span / pitch)) - 1
outerRibs = doubleBaseType(valueOf_=outerRibs)
ribsPositioning = wingRibsPositioningType(ribReference=ribReference, etaStart=etaStart, etaEnd=etaEnd, ribStart=ribStart, ribEnd=ribEnd, \
numberOfRibs=outerRibs, ribCrossingBehaviour=ribCrossing, ribRotation=ribRotation)
myUID = parentUID + '_ribs_outer'
ribsList.append(wingRibsDefinitionType(uID=myUID, name=myName, ribsPositioning=ribsPositioning, ribCrossSection=myCrossSection))
#===============================================================================
# Strut (And only the strut not the wing that goes along with it)
#===============================================================================
if typeOfSeg.lower() == 'strut':
myName = stringBaseType(valueOf_='strut_ribs')
# Rib Cross Section
#=======================================================================
#myMaterial = materialDefinitionType(compositeUID=stringUIDBaseType(isLink='True',valueOf_='Comp_Shear'), orthotropyDirection=doubleBaseType(valueOf_='0.'),\
# thicknessScaling=doubleBaseType(valueOf_='0.001'))
myMaterial = materialDefinitionType(materialUID=stringUIDBaseType(valueOf_='aluminium7075'), thickness=doubleBaseType(valueOf_=str(thickness)))
myCrossSection = wingRibCrossSectionType(material=myMaterial)
ribReference = stringBaseType(valueOf_='leadingEdge')
ribStart = stringBaseType(valueOf_='leadingEdge')
ribEnd = stringBaseType(valueOf_='trailingEdge')
ribRotation = ribRotationType(ribRotationReference=stringBaseType(valueOf_='globalY'), z=doubleBaseType(valueOf_=str('90.')))
ribCrossing = ribCrossingBehaviourType(valueOf_='cross')
etaStart = doubleBaseType(valueOf_=str(0.))
etaEnd = doubleBaseType(valueOf_=str(1.))
middleRibs = doubleBaseType(valueOf_=5.)
ribsPositioning = wingRibsPositioningType(ribReference=ribReference, etaStart=etaStart, etaEnd=etaEnd, ribStart=ribStart, ribEnd=ribEnd, \
numberOfRibs=middleRibs, ribCrossingBehaviour=ribCrossing, ribRotation=ribRotation)
myUID = parentUID + '_ribs'
ribsList.append(wingRibsDefinitionType(uID=myUID, name=myName, ribsPositioning=ribsPositioning, ribCrossSection=myCrossSection))
#===============================================================================
# Aileron
#===============================================================================
if typeOfSeg.lower() == 'aileron':
myName = stringBaseType(valueOf_='aileron_ribs')
# Rib Cross Section
#=======================================================================
myMaterial = materialDefinitionType(materialUID=stringUIDBaseType(valueOf_='aluminium7075'), thickness=doubleBaseType(valueOf_=str(thickness)))
myCrossSection = wingRibCrossSectionType(material= myMaterial)
# Rib Positioning
#=======================================================================
etaStart = doubleBaseType(valueOf_='0.')
etaEnd = doubleBaseType(valueOf_='1.')
ribReference = stringBaseType(valueOf_=parentUID + '_Spar_FS')
ribStart = stringBaseType(valueOf_='leadingEdge')
ribEnd = stringBaseType(valueOf_='trailingEdge')
ribRotation = ribRotationType(ribRotationReference=stringBaseType(valueOf_='globalY'), z=doubleBaseType(valueOf_=str('90.')))
ribCrossing = ribCrossingBehaviourType(valueOf_='cross')
if nRibs is None:
ribSpacing = doubleBaseType(valueOf_=pitch)
ribsPositioning = wingRibsPositioningType(ribReference=ribReference, etaStart=etaStart, etaEnd=etaEnd, ribStart=ribStart, ribEnd=ribEnd, \
spacing=ribSpacing, ribCrossingBehaviour=ribCrossing, ribRotation=ribRotation)
else:
nRibs = doubleBaseType(valueOf_=nRibs)
ribsPositioning = wingRibsPositioningType(ribReference=ribReference, etaStart=etaStart, etaEnd=etaEnd, ribStart=ribStart, ribEnd=ribEnd, \
numberOfRibs=nRibs, ribCrossingBehaviour=ribCrossing, ribRotation=ribRotation)
ribsList.append(wingRibsDefinitionType(uID=myUID, name=myName, ribsPositioning=ribsPositioning, ribCrossSection=myCrossSection))
if typeOfSeg.lower() == 'trapezoid':
myName = stringBaseType(valueOf_='trapezoid_ribs')
# Rib Cross Section
#=======================================================================
myMaterial = materialDefinitionType(materialUID=stringUIDBaseType(valueOf_='aluminium7075'), thickness=doubleBaseType(valueOf_=str(thickness)))
myCrossSection = wingRibCrossSectionType(material= myMaterial)
# Rib Positioning
#=======================================================================
etaStart = doubleBaseType(valueOf_='0.')
etaEnd = doubleBaseType(valueOf_='1.')
ribReference = stringBaseType(valueOf_=parentUID + '_Spar_FS')
ribStart = stringBaseType(valueOf_='leadingEdge')
ribEnd = stringBaseType(valueOf_='trailingEdge')
ribRotation = ribRotationType(ribRotationReference=stringBaseType(valueOf_='globalY'), z=doubleBaseType(valueOf_=str('90.')))
ribCrossing = ribCrossingBehaviourType(valueOf_='cross')
middleRibs = doubleBaseType(valueOf_=5.)
ribsPositioning = wingRibsPositioningType(ribReference=ribReference, etaStart=etaStart, etaEnd=etaEnd, ribStart=ribStart, ribEnd=ribEnd, \
numberOfRibs=middleRibs, ribCrossingBehaviour=ribCrossing, ribRotation=ribRotation)
ribsList.append(wingRibsDefinitionType(uID=myUID, name=myName, ribsPositioning=ribsPositioning, ribCrossSection=myCrossSection))
#===============================================================================
# Flap
#===============================================================================
if typeOfSeg.lower() == 'flap' or typeOfSeg.lower() == 'innerflap':
myName = stringBaseType(valueOf_='flap_ribs')
# Rib Cross Section
#=======================================================================
myMaterial = materialDefinitionType(materialUID=stringUIDBaseType(valueOf_='aluminium7075'), thickness=doubleBaseType(valueOf_=str(thickness)))
myCrossSection = wingRibCrossSectionType(material= myMaterial)
# Rib Positioning
#=======================================================================
etaStart = doubleBaseType(valueOf_='0.')
etaEnd = doubleBaseType(valueOf_='1.')
ribReference = stringBaseType(valueOf_=parentUID + '_Spar_FS')
ribStart = stringBaseType(valueOf_='leadingEdge')
ribEnd = stringBaseType(valueOf_='trailingEdge')
ribRotation = ribRotationType(ribRotationReference=stringBaseType(valueOf_='globalY'), z=doubleBaseType(valueOf_=str('90.')))
ribCrossing = ribCrossingBehaviourType(valueOf_='cross')
if nRibs is None:
ribSpacing = doubleBaseType(valueOf_=pitch)
ribsPositioning = wingRibsPositioningType(ribReference=ribReference, etaStart=etaStart, etaEnd=etaEnd, ribStart=ribStart, ribEnd=ribEnd, \
spacing=ribSpacing, ribCrossingBehaviour=ribCrossing, ribRotation=ribRotation)
else:
nRibs = doubleBaseType(valueOf_=nRibs)
ribsPositioning = wingRibsPositioningType(ribReference=ribReference, etaStart=etaStart, etaEnd=etaEnd, ribStart=ribStart, ribEnd=ribEnd, \
numberOfRibs=nRibs, ribCrossingBehaviour=ribCrossing, ribRotation=ribRotation)
ribsList.append(wingRibsDefinitionType(uID=myUID, name=myName, ribsPositioning=ribsPositioning, ribCrossSection=myCrossSection))
#===============================================================================
# Spoiler
#===============================================================================
if typeOfSeg.lower() == 'spoiler':
myName = stringBaseType(valueOf_='spoiler_ribs')
# Rib Cross Section
#=======================================================================
myMaterial = materialDefinitionType(materialUID=stringUIDBaseType(valueOf_='aluminium7075'), thickness=doubleBaseType(valueOf_=str(thickness)))
myCrossSection = wingRibCrossSectionType(material= myMaterial)
# Rib Positioning
#=======================================================================
etaStart = doubleBaseType(valueOf_='0.')
etaEnd = doubleBaseType(valueOf_='1.')
ribReference = stringBaseType(valueOf_='leadingEdge')
ribStart = stringBaseType(valueOf_='leadingEdge')
ribEnd = stringBaseType(valueOf_='trailingEdge')
ribRotation = ribRotationType(ribRotationReference=stringBaseType(valueOf_='globalY'), z=doubleBaseType(valueOf_=str('90.')))
ribCrossing = ribCrossingBehaviourType(valueOf_='cross')
if nRibs is None:
ribSpacing = doubleBaseType(valueOf_=pitch)
ribsPositioning = wingRibsPositioningType(ribReference=ribReference, etaStart=etaStart, etaEnd=etaEnd, ribStart=ribStart, ribEnd=ribEnd, \
spacing=ribSpacing, ribCrossingBehaviour=ribCrossing, ribRotation=ribRotation)
else:
nRibs = doubleBaseType(valueOf_=nRibs)
ribsPositioning = wingRibsPositioningType(ribReference=ribReference, etaStart=etaStart, etaEnd=etaEnd, ribStart=ribStart, ribEnd=ribEnd, \
numberOfRibs=nRibs, ribCrossingBehaviour=ribCrossing, ribRotation=ribRotation)
ribsList.append(wingRibsDefinitionType(uID=myUID, name=myName, ribsPositioning=ribsPositioning, ribCrossSection=myCrossSection))
#=======================================================================
# RibsDefinition
#=======================================================================
myRibsDefinitions = wingRibsDefinitionsType(None, None, None, ribsList)
parent.get_structure().set_ribsDefinitions(myRibsDefinitions)
def createTanks(parent, parentUID, targetUID='tank1', typeOfSeg='advDoubletrapezoid', nRib='2'):
'''
Used for generation of a wing tank
@param parent: ComponentSegment object, wing fuel tank will be added here.
@param typeOfSeg: either advDoubleTrapezoid or trapezoid
@param iRib: index of Rib in wing_ribs ribDefinition
'''
tanks = []
#===========================================================================
# Tanks
#===========================================================================
if typeOfSeg == 'advDoubletrapezoid':
# Innermost
myUID = parentUID + '_tank_inner'
myName = stringBaseType(valueOf_=myUID)
front = wingFuelTankBorderType(sparUID=stringUIDBaseType(valueOf_=parentUID + '_Spar_FS'))
outer = wingFuelTankBorderType(ribDefinitionUID=stringUIDBaseType(valueOf_='wing_ribs_inner'), ribNumber=integerBaseType(valueOf_=str(4)))
rear = wingFuelTankBorderType(sparUID=stringUIDBaseType(valueOf_=parentUID + '_Spar_RS'))
myGeometry = wingFuelTankGeometryType(border=[front, outer, rear])
tanks.append(wingFuelTankType(uID=myUID, name=myName, geometry=myGeometry))
# root to tw
myUID = parentUID + '_tank_middle'
myName = stringBaseType(valueOf_=myUID)
inner = outer
front = wingFuelTankBorderType(sparUID=stringUIDBaseType(valueOf_=parentUID + '_Spar_FS'))
outer = wingFuelTankBorderType(ribDefinitionUID=stringUIDBaseType(valueOf_='wing_ribs_engine2'), ribNumber=integerBaseType(valueOf_=str(1)))
rear = wingFuelTankBorderType(sparUID=stringUIDBaseType(valueOf_=parentUID + '_Spar_RS'))
myGeometry = wingFuelTankGeometryType(border=[inner, front, outer, rear])
tanks.append(wingFuelTankType(uID=myUID, name=myName, geometry=myGeometry))
# tw to outer
myUID = parentUID + '_tank_outer'
myName = stringBaseType(valueOf_=myUID)
inner = outer
front = wingFuelTankBorderType(sparUID=stringUIDBaseType(valueOf_=parentUID + '_Spar_FS'))
outer = wingFuelTankBorderType(ribDefinitionUID=stringUIDBaseType(valueOf_=parentUID + '_ribs_outer'), ribNumber=integerBaseType(valueOf_=str(nRib)))
rear = wingFuelTankBorderType(sparUID=stringUIDBaseType(valueOf_=parentUID + '_Spar_RS'))
myGeometry = wingFuelTankGeometryType(border=[inner, front, outer, rear])
tanks.append(wingFuelTankType(uID=myUID, name=myName, geometry=myGeometry))
if typeOfSeg == "strutBracedWing":
# Innermost
myUID = parentUID + '_tank_inner'
myName = stringBaseType(valueOf_=myUID)
front = wingFuelTankBorderType(sparUID=stringUIDBaseType(valueOf_=parentUID + '_Spar_FS'))
outer = wingFuelTankBorderType(ribDefinitionUID=stringUIDBaseType(valueOf_='wing_ribs_inner'), ribNumber=integerBaseType(valueOf_=str(4)))
rear = wingFuelTankBorderType(sparUID=stringUIDBaseType(valueOf_=parentUID + '_Spar_RS'))
myGeometry = wingFuelTankGeometryType(border=[front, outer, rear])
tanks.append(wingFuelTankType(uID=myUID, name=myName, geometry=myGeometry))
# root to strut
myUID = parentUID + '_tank_middle'
myName = stringBaseType(valueOf_=myUID)
inner = outer
front = wingFuelTankBorderType(sparUID=stringUIDBaseType(valueOf_=parentUID + '_Spar_FS'))
outer = wingFuelTankBorderType(ribDefinitionUID=stringUIDBaseType(valueOf_='wing_ribs_outer'), ribNumber=integerBaseType(valueOf_=str(1)))
rear = wingFuelTankBorderType(sparUID=stringUIDBaseType(valueOf_=parentUID + '_Spar_RS'))
myGeometry = wingFuelTankGeometryType(border=[inner, front, outer, rear])
tanks.append(wingFuelTankType(uID=myUID, name=myName, geometry=myGeometry))
# strut to outer
myUID = parentUID + '_tank_outer'
myName = stringBaseType(valueOf_=myUID)
inner = outer
front = wingFuelTankBorderType(sparUID=stringUIDBaseType(valueOf_=parentUID + '_Spar_FS'))
outer = wingFuelTankBorderType(ribDefinitionUID=stringUIDBaseType(valueOf_=parentUID + '_ribs_outer'), ribNumber=integerBaseType(valueOf_=str(nRib)))
rear = wingFuelTankBorderType(sparUID=stringUIDBaseType(valueOf_=parentUID + '_Spar_RS'))
myGeometry = wingFuelTankGeometryType(border=[inner, front, outer, rear])
tanks.append(wingFuelTankType(uID=myUID, name=myName, geometry=myGeometry))
myTanks = wingFuelTanksType(wingFuelTank=tanks)
parent.set_wingFuelTanks(myTanks)
def createElevator(parentHtpCPACS, parentHtpVAMPzero, myElevator):
'''
This is the main export method for the htp elevator
'''
cpacsPath = '/cpacs/vehicles/aircraft/model/wings/wing[' + parentHtpVAMPzero.id + ']'
cpacsHtp = getObjfromXpath(parentHtpCPACS, cpacsPath)
cpacsComponentSegment = cpacsHtp.get_componentSegments().get_componentSegment()[0]
#===========================================================================
# Header
#===========================================================================
myName = stringBaseType(None, None, None, 'elevator')
myDescription = stringBaseType(None, None, None, 'elevator from VAMPzero')
myParentUID = stringUIDBaseType(None, None, 'True', None, parentHtpVAMPzero.id)
#===========================================================================
# Outer Shape
#===========================================================================
# the inner border eta is determined from the rooYLocation of the Elevator and the htp span
htpSpan = parentHtpVAMPzero.span.getValue() / 2.
innerEtaLE = myElevator.rootYLocation.getValue() / htpSpan
# the inner border xsi is determined from the Root Chord and the Chord of the Htp at the location
# the inner border xsi is determined from the Root Chord and the Chord of the Htp at the location
cTipHtp = parentHtpVAMPzero.cTip.getValue()
cRootHtp = parentHtpVAMPzero.cRoot.getValue()
cInnerWing = cRootHtp - (cRootHtp - cTipHtp)*innerEtaLE
innerXsiLE = 1 - (myElevator.cRoot.getValue() / cInnerWing)
if innerXsiLE < 0.2:
parentHtpVAMPzero.log.warning('VAMPzero EXPORT: The Elevator tap inner border is larger than the available chord')
parentHtpVAMPzero.log.warning('VAMPzero EXPORT: The Elevator tap inner border is now set to 0.1')
innerXsiLE = 0.2
# The outer border eta station is set to the inner eta plus the span of the elevator
outerEtaLE = innerEtaLE + myElevator.span.getValue() / htpSpan
# The outer border xsi is determined in the same way as the inner border xsi
cOuterWing = cRootHtp - (cRootHtp - cTipHtp)*outerEtaLE
outerXsiLE = 1 - (myElevator.cTip.getValue() / cOuterWing)
if outerXsiLE < 0.2:
parentHtpVAMPzero.log.warning('VAMPzero EXPORT: The Elevator tap outer border is larger than the available chord')
parentHtpVAMPzero.log.warning('VAMPzero EXPORT: The Elevator tap outer border is now set to 0.1')
outerXsiLE = 0.2
# start writing back
myleadingEdgeShape = leadingEdgeShapeType(relHeightLE=doubleBaseType(valueOf_=str(0.5)), xsiUpperSkin=doubleBaseType(valueOf_=str(0.85)), xsiLowerSkin=doubleBaseType(valueOf_=str(0.85)))
innerBorder = controlSurfaceBorderTrailingEdgeType(etaLE=doubleBaseType(valueOf_=str(innerEtaLE)), xsiLE=doubleBaseType(valueOf_=str(innerXsiLE)), leadingEdgeShape=myleadingEdgeShape)
outerBorder = controlSurfaceBorderTrailingEdgeType(etaLE=doubleBaseType(valueOf_=str(outerEtaLE)), xsiLE=doubleBaseType(valueOf_=str(outerXsiLE)), leadingEdgeShape=myleadingEdgeShape)
myOuterShape = controlSurfaceOuterShapeTrailingEdgeType(innerBorder=innerBorder, outerBorder=outerBorder)
cpacsElevator = trailingEdgeDeviceType(uID='elevatorUID', name=myName, description=myDescription, parentUID=myParentUID, outerShape=myOuterShape)
createPath(cpacsElevator, 'elevator')
if type(cpacsComponentSegment.get_controlSurfaces()) == NoneType:
cpacsComponentSegment.set_controlSurfaces(controlSurfacesType())
if type(cpacsComponentSegment.get_controlSurfaces().get_trailingEdgeDevices()) == NoneType:
cpacsComponentSegment.get_controlSurfaces().set_trailingEdgeDevices(trailingEdgeDevicesType())
cpacsComponentSegment.get_controlSurfaces().get_trailingEdgeDevices().add_trailingEdgeDevice(cpacsElevator)
def createElevator(parentHtpCPACS, parentHtpVAMPzero, myElevator):
"""
This is the main export method for the htp elevator
"""
cpacsPath = "/cpacs/vehicles/aircraft/model/wings/wing[" + parentHtpVAMPzero.id + "]"
cpacsHtp = getObjfromXpath(parentHtpCPACS, cpacsPath)
cpacsComponentSegment = cpacsHtp.get_componentSegments().get_componentSegment()[0]
# ===========================================================================
# Header
# ===========================================================================
myName = stringBaseType(None, None, None, "elevator")
myDescription = stringBaseType(None, None, None, "elevator from VAMPzero")
myParentUID = stringUIDBaseType(None, None, "True", None, parentHtpVAMPzero.id)
# ===========================================================================
# Outer Shape
# ===========================================================================
# the inner border eta is determined from the rooYLocation of the Elevator and the htp span
htpSpan = parentHtpVAMPzero.span.getValue() / 2.0
innerEtaLE = myElevator.rootYLocation.getValue() / htpSpan
# the inner border xsi is determined from the Root Chord and the Chord of the Htp at the location
phiLE = parentHtpVAMPzero.phiLE.getValue()
phiTE = parentHtpVAMPzero.phiTE.getValue()
x1 = tan(phiLE * rad) * htpSpan * innerEtaLE
x2 = tan(phiTE * rad) * htpSpan * innerEtaLE
cInnerWing = (x2 + parentHtpVAMPzero.cRoot.getValue()) - x1
innerXsiLE = 1 - (myElevator.cRoot.getValue() / cInnerWing)
# The outer border eta station is set to the inner eta plus the span of the elevator
outerEtaLE = innerEtaLE + myElevator.span.getValue() / htpSpan
# The outer border xsi is determined in the same way as the inner border xsi
x1 = tan(phiLE * rad) * htpSpan * outerEtaLE
x2 = tan(phiTE * rad) * htpSpan * outerEtaLE
cOuterWing = (x2 + parentHtpVAMPzero.cRoot.getValue()) - x1
outerXsiLE = 1 - (myElevator.cTip.getValue() / cOuterWing)
# start writing back
myleadingEdgeShape = leadingEdgeShapeType(
relHeightLE=doubleBaseType(valueOf_=str(0.5)),
xsiUpperSkin=doubleBaseType(valueOf_=str(0.85)),
xsiLowerSkin=doubleBaseType(valueOf_=str(0.85)),
)
innerBorder = controlSurfaceBorderTrailingEdgeType(
etaLE=doubleBaseType(valueOf_=str(innerEtaLE)),
xsiLE=doubleBaseType(valueOf_=str(innerXsiLE)),
leadingEdgeShape=myleadingEdgeShape,
)
outerBorder = controlSurfaceBorderTrailingEdgeType(
etaLE=doubleBaseType(valueOf_=str(outerEtaLE)),
xsiLE=doubleBaseType(valueOf_=str(outerXsiLE)),
leadingEdgeShape=myleadingEdgeShape,
)
myOuterShape = controlSurfaceOuterShapeTrailingEdgeType(innerBorder=innerBorder, outerBorder=outerBorder)
cpacsElevator = trailingEdgeDeviceType(
uID="elevatorUID", name=myName, description=myDescription, parentUID=myParentUID, outerShape=myOuterShape
)
createPath(cpacsElevator, "elevator")
if type(cpacsComponentSegment.get_controlSurfaces()) == NoneType:
cpacsComponentSegment.set_controlSurfaces(controlSurfacesType())
if type(cpacsComponentSegment.get_controlSurfaces().get_trailingEdgeDevices()) == NoneType:
cpacsComponentSegment.get_controlSurfaces().set_trailingEdgeDevices(trailingEdgeDevicesType())
cpacsComponentSegment.get_controlSurfaces().get_trailingEdgeDevices().add_trailingEdgeDevice(cpacsElevator)
def createAileron(parentWingCPACS, parentWingVAMPzero, myAileron):
'''
This is the main export method for the wings aileron
'''
cpacsPath = '/cpacs/vehicles/aircraft/model/wings/wing[' + parentWingVAMPzero.id + ']'
cpacsWing = getObjfromXpath(parentWingCPACS, cpacsPath)
cpacsComponentSegment = cpacsWing.get_componentSegments(
).get_componentSegment()[0]
#===========================================================================
# Header
#===========================================================================
myName = stringBaseType(None, None, None, 'aileron')
myDescription = stringBaseType(None, None, None, 'aileron from VAMPzero')
myParentUID = stringUIDBaseType(None, None, 'True', None, 'wing_Cseg')
#===========================================================================
# Initialization, i.e. fetching values throughout the code
#===========================================================================
xsiSparRoot = eval(cpacsComponentSegment.get_structure().get_spars(
).get_sparPositions().get_sparPosition()[3].get_xsi().valueOf_)
xsiSparFuselage = eval(cpacsComponentSegment.get_structure().get_spars(
).get_sparPositions().get_sparPosition()[4].get_xsi().valueOf_)
xsiSparKink = eval(cpacsComponentSegment.get_structure().get_spars(
).get_sparPositions().get_sparPosition()[5].get_xsi().valueOf_)
xsiSparTip = eval(cpacsComponentSegment.get_structure().get_spars(
).get_sparPositions().get_sparPosition()[6].get_xsi().valueOf_)
etaSparRoot = eval(cpacsComponentSegment.get_structure().get_spars(
).get_sparPositions().get_sparPosition()[3].get_eta().valueOf_)
etaSparFuselage = eval(cpacsComponentSegment.get_structure().get_spars(
).get_sparPositions().get_sparPosition()[4].get_eta().valueOf_)
etaSparKink = eval(cpacsComponentSegment.get_structure().get_spars(
).get_sparPositions().get_sparPosition()[5].get_eta().valueOf_)
etaSparTip = eval(cpacsComponentSegment.get_structure().get_spars(
).get_sparPositions().get_sparPosition()[6].get_eta().valueOf_)
xsiSpar_interp = scipy.interpolate.interp1d(
[etaSparRoot, etaSparFuselage, etaSparKink, etaSparTip],
[xsiSparRoot, xsiSparFuselage, xsiSparKink, xsiSparTip])
sparOffset = 0.1
wingSpan = parentWingVAMPzero.span.getValue() / 2.
#===========================================================================
# Outer Shape
#===========================================================================
# The outer border eta station is set to 96 percent
outerEtaLE = 0.96
# The outer chord station is determined from the wing's chord at eta = 0.96
# and the rear spar location + the spar offset
outerXsiLE = xsiSpar_interp(0.96) + sparOffset
outerWingChord = calcChordLengthAtEta(outerEtaLE, parentWingVAMPzero,
cpacsWing)
cTip = (1 - outerXsiLE) * outerWingChord
# now we need to determine the necessary span for the aileron by gently increasing the span
# this is an iterative process as the chord of the aileron is a function of the inbound span
aileronArea = parentWingVAMPzero.aileron.refArea.getValue()
delta = 0.01
calcArea = 0.
while abs(calcArea - aileronArea) > 0.1:
if delta > outerEtaLE:
parentWingVAMPzero.log.warning(
'VAMPzero EXPORT: Cannot determine the span of the aileron')
parentWingVAMPzero.log.warning('VAMPzero EXPORT: aileronArea= ' +
str(aileronArea))
parentWingVAMPzero.log.warning(
'VAMPzero EXPORT: Decreasing Spar Offset')
sparOffset = sparOffset - 0.02
delta = 0.01
innerEtaLE = outerEtaLE - delta
innerXsiLE = xsiSpar_interp(innerEtaLE) + sparOffset
innerWingChord = calcChordLengthAtEta(innerEtaLE, parentWingVAMPzero,
cpacsWing)
cRoot = (1 - innerXsiLE) * innerWingChord
calcArea = (cTip + cRoot) / 2 * (outerEtaLE - innerEtaLE) * wingSpan
delta += 0.005
# start outer shape
myleadingEdgeShape = leadingEdgeShapeType(
relHeightLE=doubleBaseType(valueOf_=str(0.5)),
xsiUpperSkin=doubleBaseType(valueOf_=str(0.85)),
xsiLowerSkin=doubleBaseType(valueOf_=str(0.85)))
innerBorder = controlSurfaceBorderTrailingEdgeType(
etaLE=doubleBaseType(valueOf_=str(innerEtaLE)),
etaTE=doubleBaseType(valueOf_=str(innerEtaLE)),
xsiLE=doubleBaseType(valueOf_=str(innerXsiLE)),
leadingEdgeShape=myleadingEdgeShape)
outerBorder = controlSurfaceBorderTrailingEdgeType(
etaLE=doubleBaseType(valueOf_=str(outerEtaLE)),
etaTE=doubleBaseType(valueOf_=str(outerEtaLE)),
xsiLE=doubleBaseType(valueOf_=str(outerXsiLE)),
leadingEdgeShape=myleadingEdgeShape)
myOuterShape = controlSurfaceOuterShapeTrailingEdgeType(
innerBorder=innerBorder, outerBorder=outerBorder)
# structure
myStructure = wingComponentSegmentStructureType()
cpacsAileron = trailingEdgeDeviceType(uID='aileronUID',
name=myName,
description=myDescription,
parentUID=myParentUID,
outerShape=myOuterShape,
structure=myStructure)
createAileronStructure(cpacsAileron)
# Forward information about innerEtaLE to the flap
parentWingVAMPzero.flap.maxEta = parameter(
value=innerEtaLE,
doc=
'This it the inner position of the aileron, the flap may not exceed it'
)
# moveables
deltaEta = outerEtaLE - innerEtaLE
innerParentXsi = xsiSpar_interp(innerEtaLE + 0.3 * deltaEta) + 0.02
outerParentXsi = xsiSpar_interp(innerEtaLE + 0.7 * deltaEta) + 0.02
createPath(cpacsAileron, 'aileron')
createTracks(cpacsAileron, 'aileron')
createActuators(cpacsAileron, 'aileron', [innerParentXsi, outerParentXsi])
if type(cpacsComponentSegment.get_controlSurfaces()) == NoneType:
cpacsComponentSegment.set_controlSurfaces(controlSurfacesType())
if type(cpacsComponentSegment.get_controlSurfaces().
get_trailingEdgeDevices()) == NoneType:
cpacsComponentSegment.get_controlSurfaces().set_trailingEdgeDevices(
trailingEdgeDevicesType())
cpacsComponentSegment.get_controlSurfaces().get_trailingEdgeDevices(
).add_trailingEdgeDevice(cpacsAileron)
def createWingWingAttachment(parent,
parentUID,
targetUID='wing_Cseg',
typeOfSeg='strut'):
if typeOfSeg == 'strut':
toComponentSegmentUID = stringUIDBaseType(valueOf_=targetUID)
fromElementUID = stringUIDBaseType(valueOf_='strut_Sec3_Elem1')
toElementUID = stringUIDBaseType(valueOf_='wing_Sec3_Elem1')
elements = wingWingAttachmentElementsType(
fromElementUID=fromElementUID, toElementUID=toElementUID)
fromSparUID = stringUIDBaseType(valueOf_='strut_Spar_FS')
toSparUID = stringUIDBaseType(valueOf_='wing_Spar_FS')
sparAttachment = wingWingAttachmentSparsType(fromSparUID=fromSparUID,
toSparUID=toSparUID)
sparAttachments = wingWingAttachmentsSparsType(
sparAttachment=[sparAttachment])
upperShellAttachment = stringUIDBaseType(valueOf_='upperShell')
lowerShellAttachment = stringUIDBaseType(valueOf_='lowerShell')
wingWingAttachment = wingWingAttachmentType(
toComponentSegmentUID=toComponentSegmentUID,
elements=elements,
sparAttachments=sparAttachments,
upperShellAttachment=upperShellAttachment,
lowerShellAttachment=lowerShellAttachment)
elif typeOfSeg == 'ttail':
toComponentSegmentUID = stringUIDBaseType(valueOf_=targetUID)
fromElementUID = stringUIDBaseType(valueOf_='htp_Sec1_Elem1')
toElementUID = stringUIDBaseType(valueOf_='vtp_Sec2_Elem1')
elements = wingWingAttachmentElementsType(
fromElementUID=fromElementUID, toElementUID=toElementUID)
fromSparUID = stringUIDBaseType(valueOf_='htp_Spar_FS')
toSparUID = stringUIDBaseType(valueOf_='vtp_Spar_FS')
FS_sparAttachment = wingWingAttachmentSparsType(
fromSparUID=fromSparUID, toSparUID=toSparUID)
fromSparUID = stringUIDBaseType(valueOf_='htp_Spar_RS')
toSparUID = stringUIDBaseType(valueOf_='vtp_Spar_RS')
RS_sparAttachment = wingWingAttachmentSparsType(
fromSparUID=fromSparUID, toSparUID=toSparUID)
sparAttachments = wingWingAttachmentsSparsType(
sparAttachment=[FS_sparAttachment, RS_sparAttachment])
upperShellAttachment = stringUIDBaseType(valueOf_='upperShell')
lowerShellAttachment = stringUIDBaseType(valueOf_='lowerShell')
wingWingAttachment = wingWingAttachmentType(
toComponentSegmentUID=toComponentSegmentUID,
elements=elements,
sparAttachments=sparAttachments,
upperShellAttachment=upperShellAttachment,
lowerShellAttachment=lowerShellAttachment)
wingWingAttachments = wingWingAttachmentsType(
wingWingAttachment=[wingWingAttachment])
parent.set_wingWingAttachments(wingWingAttachments)
def createElevator(parentHtpCPACS, parentHtpVAMPzero, myElevator):
'''
This is the main export method for the htp elevator
'''
cpacsPath = '/cpacs/vehicles/aircraft/model/wings/wing[' + parentHtpVAMPzero.id + ']'
cpacsHtp = getObjfromXpath(parentHtpCPACS, cpacsPath)
cpacsComponentSegment = cpacsHtp.get_componentSegments(
).get_componentSegment()[0]
#===========================================================================
# Header
#===========================================================================
myName = stringBaseType(None, None, None, 'elevator')
myDescription = stringBaseType(None, None, None, 'elevator from VAMPzero')
myParentUID = stringUIDBaseType(None, None, 'True', None,
parentHtpVAMPzero.id)
#===========================================================================
# Outer Shape
#===========================================================================
# the inner border eta is determined from the rooYLocation of the Elevator and the htp span
htpSpan = parentHtpVAMPzero.span.getValue() / 2.
innerEtaLE = myElevator.rootYLocation.getValue() / htpSpan
# the inner border xsi is determined from the Root Chord and the Chord of the Htp at the location
phiLE = parentHtpVAMPzero.phiLE.getValue()
phiTE = parentHtpVAMPzero.phiTE.getValue()
x1 = tan(phiLE * rad) * htpSpan * innerEtaLE
x2 = tan(phiTE * rad) * htpSpan * innerEtaLE
cInnerWing = (x2 + parentHtpVAMPzero.cRoot.getValue()) - x1
innerXsiLE = 1 - (myElevator.cRoot.getValue() / cInnerWing)
# The outer border eta station is set to the inner eta plus the span of the elevator
outerEtaLE = innerEtaLE + myElevator.span.getValue() / htpSpan
# The outer border xsi is determined in the same way as the inner border xsi
x1 = tan(phiLE * rad) * htpSpan * outerEtaLE
x2 = tan(phiTE * rad) * htpSpan * outerEtaLE
cOuterWing = (x2 + parentHtpVAMPzero.cRoot.getValue()) - x1
outerXsiLE = 1 - (myElevator.cTip.getValue() / cOuterWing)
# start writing back
myleadingEdgeShape = leadingEdgeShapeType(
relHeightLE=doubleBaseType(valueOf_=str(0.5)),
xsiUpperSkin=doubleBaseType(valueOf_=str(0.85)),
xsiLowerSkin=doubleBaseType(valueOf_=str(0.85)))
innerBorder = controlSurfaceBorderTrailingEdgeType(
etaLE=doubleBaseType(valueOf_=str(innerEtaLE)),
xsiLE=doubleBaseType(valueOf_=str(innerXsiLE)),
leadingEdgeShape=myleadingEdgeShape)
outerBorder = controlSurfaceBorderTrailingEdgeType(
etaLE=doubleBaseType(valueOf_=str(outerEtaLE)),
xsiLE=doubleBaseType(valueOf_=str(outerXsiLE)),
leadingEdgeShape=myleadingEdgeShape)
myOuterShape = controlSurfaceOuterShapeTrailingEdgeType(
innerBorder=innerBorder, outerBorder=outerBorder)
cpacsElevator = trailingEdgeDeviceType(uID='elevatorUID',
name=myName,
description=myDescription,
parentUID=myParentUID,
outerShape=myOuterShape)
createPath(cpacsElevator, 'elevator')
if type(cpacsComponentSegment.get_controlSurfaces()) == NoneType:
cpacsComponentSegment.set_controlSurfaces(controlSurfacesType())
if type(cpacsComponentSegment.get_controlSurfaces().
get_trailingEdgeDevices()) == NoneType:
cpacsComponentSegment.get_controlSurfaces().set_trailingEdgeDevices(
trailingEdgeDevicesType())
cpacsComponentSegment.get_controlSurfaces().get_trailingEdgeDevices(
).add_trailingEdgeDevice(cpacsElevator)
def createWing(CPACSObj = None, zeroWing = None, id="1", LoD = 0.):
"""
This function triggers the different export modes of the wing depending on the desired
level of detail.
Options include a single trapezoid, double trapezoid, advanced double trapezoid (that includes
a rectangular center fuselage section) and a strut-braced wing.
Please note, these are the internal guts of VAMPzero's CPACS export. A lot of the code
here is experimental and furthermore highly chaotic. In case of emergency contact Daniel or Jonas.
:param CPACSObj: The overall CPACS object of the export
:param zeroWing: The instance of the wing.
:param id: The id of the wing, mostly sth. like wing
:param LoD: The level of detail of the desired input.
:return: CPACSObj including a new wing
"""
if LoD == WING_LOD.NONE:
return
# just for now
cpacsPath = '/cpacs/vehicles/aircraft/model/wings/wing[' + id + ']'
# the next line is the one to use later on
# cpacsPath = '/cpacs/vehicles/aircraft/model[model]/wings/wing[' + self.id + ']'
# get the wing object from given cpacs path
cpacsWing = getObjfromXpath(CPACSObj, cpacsPath)
strUID = createHeader(cpacsWing, id)
cpacsWing.set_symmetry('x-z-plane')
cpacsWing.set_name(stringBaseType(valueOf_='wing'))
cpacsWing.set_parentUID(stringUIDBaseType(isLink=True, valueOf_='fuselage'))
xRoot = zeroWing.xRoot.getValue()
zRoot = zeroWing.zRoot.getValue()
cRoot = zeroWing.cRoot.getValue()
cTip = zeroWing.cTip.getValue()
span = zeroWing.span.getValue()
dfus = zeroWing.aircraft.fuselage.dfus.getValue()
phiLE = zeroWing.phiLE.getValue()
dihedral = zeroWing.dihedral.getValue()
twist = zeroWing.twist.getValue()
Sref = zeroWing.refArea.getValue()
xMAC25 = zeroWing.xMAC25.getValue()
tcRoot = zeroWing.airfoilr.tc.getValue()
tcTip = zeroWing.airfoilt.tc.getValue()
try:
etakf = zeroWing.etaKink.getValue()
yFus = zeroWing.yFuselage.getValue()
etaEng = zeroWing.etaEngine.getValue()
etaFus = yFus/span*2.
except AttributeError:
pass #As not all components that call this method have a kink
try:
yRoot = zeroWing.yRoot.getValue()
except AttributeError:
pass #As not all components that call this method have a kink
createTransformation(cpacsWing, 'absGlobal', xRoot, 0., zRoot)
# call corresponding wing creation method
if LoD == WING_LOD.SINGLE:
createTrapezoidWing(cpacsWing, id, tcRoot, tcTip, cTip, cRoot, span, phiLE, dihedral, twist, strUID)
elif LoD == WING_LOD.DOUBLE:
createDoubleTrapezoidWing(cpacsWing, id, cTip, cRoot, span, Sref, phiLE, dihedral, twist, xMAC25, etakf, strUID)
elif LoD == WING_LOD.ADVDOUBLE:
createAdvDoubleTrapezoidWing(cpacsWing, id, cTip, cRoot, span, Sref, dfus, phiLE, dihedral, twist, xMAC25, etakf, strUID, yFus, xRoot, etaEng, tcRoot, tcTip)
elif LoD == WING_LOD.UCAV:
createUCAVWing(cpacsWing, id, cTip, cRoot, span, Sref, phiLE, dihedral, etakf, strUID)
elif LoD == WING_LOD.SBW:
etaStrut = zeroWing.aircraft.strut.etaStrut.getValue()
createStrutBracedWing(cpacsWing, id=id, cTip=cTip, cRoot=cRoot, span=span, Sref=Sref, phiLE=phiLE, dihedral=dihedral, twist=twist, xMAC25=xMAC25, etaFus=etaFus, etaStrut=etaStrut, tcRoot=tcRoot, tcTip=tcTip, xRoot=xRoot, strUID=strUID)
elif LoD == WING_LOD.SBWStraight:
etaStrut = zeroWing.aircraft.strut.etaStrut.getValue()
createStraightStrutBracedWing(cpacsWing, id=id, cTip=cTip, cRoot=cRoot, span=span, Sref=Sref, phiLE=phiLE, dihedral=dihedral, twist=twist, xMAC25=xMAC25, etaFus=etaFus, etaStrut=etaStrut, tcRoot=tcRoot, tcTip=tcTip, xRoot=xRoot, strUID=strUID)
elif LoD == WING_LOD.STRUT:
etaStrut = zeroWing.aircraft.strut.etaStrut.getValue()
createStrut(cpacsWing, id=id, cTip=cTip, cRoot=cRoot, span=span, phiLE=phiLE, dihedral=dihedral, tcRoot=tcRoot, tcTip=tcTip, xRoot=xRoot, yRoot=yRoot, twist=twist, etaStrut=etaStrut, strUID=strUID)
def createRibs(parent,
parentUID,
typeOfSeg,
thickness=0.03,
pitch=.8,
nRibs=None,
etaFus=0.2,
etaEng=.3,
span=17.,
fanDiameter=1.9,
etaStrut=0.0,
phi25=0.0):
'''
Used for generation of a ribs definition in the wing
@param parent: ComponentSegment object, ribsDefinition will be added here
@param thickness: thickness of the ribs
@param pitch: pitch of the ribs
@param typeOfSeg: either advDoubleTrapezoid or trapezoid
'''
myUID = parentUID + '_ribs'
ribsList = []
#===============================================================================
# Advanced Double Trapezoid
#===============================================================================
if typeOfSeg.lower() == 'advdoubletrapezoid':
myName = stringBaseType(None, None, None, 'wing_ribs')
# Rib Cross Section
#=======================================================================
myMaterial = materialDefinitionType(None, None, None, None, None, None, stringUIDBaseType(None, None, 'True', None, 'aluminium7075'), \
doubleBaseType(None, None, None, str(thickness)))
myCrossSection = wingRibCrossSectionType(None, None, None, myMaterial,
None)
ribReference = stringBaseType(None, None, None, parentUID + '_Spar_FS')
ribStart = stringBaseType(None, None, None, parentUID + '_Spar_FS')
ribEnd = stringBaseType(None, None, None, parentUID + '_Spar_RS')
ribRotation = ribRotationType(None, None, None, stringBaseType(None, None, None, 'globalY'), \
doubleBaseType(None, None, None, '90.'))
ribCrossing = ribCrossingBehaviourType(None, None, None, 'cross')
#=======================================================================
# First set of 4 ribs inside the fuselage
#=======================================================================
etaStart = doubleBaseType(None, None, None, '0.0')
etaEnd = doubleBaseType(None, None, None, str(etaFus))
innerRibs = doubleBaseType(None, None, None, 4)
ribsPositioning = wingRibsPositioningType(None, None, None, ribReference, etaStart, etaEnd, ribStart, ribEnd, \
None, innerRibs, ribCrossing, ribRotation)
myUID = parentUID + '_ribs_inner'
ribsList.append(
wingRibsDefinitionType(None, None, None, myUID, myName, None,
ribsPositioning, myCrossSection))
#===============================================================
# Second set outside of the fuselage up to the engine
#===============================================================
etaPylon = 1. / 10. * fanDiameter / span
etaStart = doubleBaseType(None, None, None, str(etaFus + pitch / span))
etaEnd = doubleBaseType(None, None, None, str(etaEng - etaPylon))
middleRibs = int(ceil((etaEng - etaPylon - etaFus) * span / pitch)) - 1
if middleRibs < 1:
middleRibs = 1
middleRibs = doubleBaseType(None, None, None, middleRibs)
ribsPositioning = wingRibsPositioningType(None, None, None, ribReference, etaStart, etaEnd, ribStart, ribEnd, \
None, middleRibs, ribCrossing, ribRotation)
myUID = parentUID + '_ribs_engine1'
ribsList.append(
wingRibsDefinitionType(None, None, None, myUID, myName, None,
ribsPositioning, myCrossSection))
#===============================================================
# Third set one ribs outside of the pylon
#===============================================================
etaEnd = doubleBaseType(None, None, None, str(etaEng + etaPylon))
pylonRibs = doubleBaseType(None, None, None, str(1))
ribsPositioning = wingRibsPositioningType(None, None, None, ribReference, etaEnd, etaEnd, ribStart, ribEnd, \
None, pylonRibs, ribCrossing, ribRotation)
myUID = parentUID + '_ribs_engine2'
ribsList.append(
wingRibsDefinitionType(None, None, None, myUID, myName, None,
ribsPositioning, myCrossSection))
#===============================================================
# Fourth set outside of the engine
#===============================================================
etaStart = doubleBaseType(None, None, None,
str(etaEng + etaPylon + pitch / span))
etaEnd = doubleBaseType(None, None, None, '0.95')
ribCrossing = ribCrossingBehaviourType(None, None, None, 'end')
ribRotation = ribRotationType(None, None, None, stringBaseType(None, None, None, 'wing_Spar_FS'), \
doubleBaseType(None, None, None, '90.'))
outerRibs = int(ceil((0.95 - etaEng + etaPylon) * span / pitch)) - 1
outerRibs = doubleBaseType(None, None, None, outerRibs)
ribsPositioning = wingRibsPositioningType(None, None, None, ribReference, etaStart, etaEnd, ribStart, ribEnd, \
None, outerRibs, ribCrossing, ribRotation)
myUID = parentUID + '_ribs_outer'
ribsList.append(
wingRibsDefinitionType(None, None, None, myUID, myName, None,
ribsPositioning, myCrossSection))
#===============================================================================
# Strut Braced Wing
#===============================================================================
if typeOfSeg.lower() == 'strutbracedwing':
myName = stringBaseType(None, None, None, 'wing_ribs')
# Rib Cross Section
#=======================================================================
myMaterial = materialDefinitionType(None, None, None, None, None, None, stringUIDBaseType(None, None, 'True', None, 'aluminium7075'), \
doubleBaseType(None, None, None, str(thickness)))
myCrossSection = wingRibCrossSectionType(None, None, None, myMaterial,
None)
ribReference = stringBaseType(None, None, None, parentUID + '_Spar_FS')
ribStart = stringBaseType(None, None, None, parentUID + '_Spar_FS')
ribEnd = stringBaseType(None, None, None, parentUID + '_Spar_RS')
ribRotation = ribRotationType(None, None, None, stringBaseType(None, None, None, 'globalY'), \
doubleBaseType(None, None, None, '90.'))
ribCrossing = ribCrossingBehaviourType(None, None, None, 'cross')
#=======================================================================
# First set of 4 ribs inside the fuselage
#=======================================================================
etaStart = doubleBaseType(None, None, None, '0.0')
etaEnd = doubleBaseType(None, None, None, str(etaFus))
innerRibs = doubleBaseType(None, None, None, 4)
ribsPositioning = wingRibsPositioningType(None, None, None, ribReference, etaStart, etaEnd, ribStart, ribEnd, \
None, innerRibs, ribCrossing, ribRotation)
myUID = parentUID + '_ribs_inner'
ribsList.append(
wingRibsDefinitionType(None, None, None, myUID, myName, None,
ribsPositioning, myCrossSection))
#===============================================================
# Second set outside of the fuselage up to the strut
#===============================================================
etaStart = doubleBaseType(None, None, None,
str(etaFus + pitch / span + phi25 * 0.0002))
etaEnd = doubleBaseType(None, None, None, str(etaStrut))
middleRibs = int(ceil((etaStrut - etaFus) * span / pitch)) - 1
middleRibs = doubleBaseType(None, None, None, middleRibs)
ribsPositioning = wingRibsPositioningType(None, None, None, ribReference, etaStart, etaEnd, ribStart, ribEnd, \
None, middleRibs, ribCrossing, ribRotation)
myUID = parentUID + '_ribs_strut'
ribsList.append(
wingRibsDefinitionType(None, None, None, myUID, myName, None,
ribsPositioning, myCrossSection))
#===============================================================
# Third set outside of the spar
#===============================================================
etaStart = doubleBaseType(None, None, None,
str(etaStrut + pitch / span))
etaEnd = doubleBaseType(None, None, None, '0.95')
ribCrossing = ribCrossingBehaviourType(None, None, None, 'end')
ribRotation = ribRotationType(None, None, None, stringBaseType(None, None, None, 'wing_Spar_FS'), \
doubleBaseType(None, None, None, '90.'))
outerRibs = int(ceil((0.95 - etaStrut) * span / pitch)) - 1
outerRibs = doubleBaseType(None, None, None, outerRibs)
ribsPositioning = wingRibsPositioningType(None, None, None, ribReference, etaStart, etaEnd, ribStart, ribEnd, \
None, outerRibs, ribCrossing, ribRotation)
myUID = parentUID + '_ribs_outer'
ribsList.append(
wingRibsDefinitionType(None, None, None, myUID, myName, None,
ribsPositioning, myCrossSection))
#===============================================================================
# Strut (And only the strut not the wing that goes along with it)
#===============================================================================
if typeOfSeg.lower() == 'strut':
myName = stringBaseType(None, None, None, 'strut_ribs')
# Rib Cross Section
#=======================================================================
myMaterial = materialDefinitionType(compositeUID=stringUIDBaseType(isLink='True',valueOf_='Comp_Shear'), orthotropyDirection=doubleBaseType(valueOf_='0.'),\
thicknessScaling=doubleBaseType(valueOf_='0.001'))
myCrossSection = wingRibCrossSectionType(None, None, None, myMaterial,
None)
ribReference = stringBaseType(None, None, None, 'leadingEdge')
ribStart = stringBaseType(None, None, None, 'leadingEdge')
ribEnd = stringBaseType(None, None, None, 'trailingEdge')
ribRotation = ribRotationType(None, None, None, stringBaseType(None, None, None, 'globalY'), \
doubleBaseType(None, None, None, '90.'))
ribCrossing = ribCrossingBehaviourType(None, None, None, 'cross')
etaStart = doubleBaseType(None, None, None, str(0.001))
etaEnd = doubleBaseType(None, None, None, str(0.999))
#middleRibs = int(ceil(span / 0.70)) - 1
middleRibs = doubleBaseType(None, None, None, 5.)
ribsPositioning = wingRibsPositioningType(None, None, None, ribReference, etaStart, etaEnd, ribStart, ribEnd, \
None, middleRibs, ribCrossing, ribRotation)
myUID = parentUID + '_ribs'
ribsList.append(
wingRibsDefinitionType(None, None, None, myUID, myName, None,
ribsPositioning, myCrossSection))
#===============================================================================
# Aileron
#===============================================================================
if typeOfSeg.lower() == 'aileron':
myName = stringBaseType(None, None, None, 'aileron_ribs')
# Rib Cross Section
#=======================================================================
myMaterial = materialDefinitionType(None, None, None, None, None, None, stringUIDBaseType(None, None, 'True', None, 'aluminium2024'), \
doubleBaseType(None, None, None, str(thickness)))
myCrossSection = wingRibCrossSectionType(None, None, None, myMaterial,
None)
# Rib Positioning
#=======================================================================
etaStart = doubleBaseType(None, None, None, '0.')
etaEnd = doubleBaseType(None, None, None, '1.')
ribReference = stringBaseType(None, None, None, parentUID + '_Spar_FS')
ribStart = stringBaseType(None, None, None, 'leadingEdge')
ribEnd = stringBaseType(None, None, None, 'trailingEdge')
ribRotation = ribRotationType(None, None, None, stringBaseType(None, None, None, 'globalY'), \
doubleBaseType(None, None, None, '90.'))
ribCrossing = ribCrossingBehaviourType(None, None, None, 'cross')
if nRibs is None:
ribSpacing = doubleBaseType(None, None, None, pitch)
ribsPositioning = wingRibsPositioningType(None, None, None, ribReference, etaStart, etaEnd, ribStart, ribEnd, \
ribSpacing, None, ribCrossing, ribRotation)
else:
nRibs = doubleBaseType(None, None, None, nRibs)
ribsPositioning = wingRibsPositioningType(None, None, None, ribReference, etaStart, etaEnd, ribStart, ribEnd, \
None, nRibs, ribCrossing, ribRotation)
ribsList.append(
wingRibsDefinitionType(None, None, None, myUID, myName, None,
ribsPositioning, myCrossSection))
if typeOfSeg.lower() == 'trapezoid':
myName = stringBaseType(None, None, None, 'trapezoid_ribs')
# Rib Cross Section
#=======================================================================
myMaterial = materialDefinitionType(None, None, None, None, None, None, stringUIDBaseType(None, None, 'True', None, 'aluminium2024'), \
doubleBaseType(None, None, None, str(thickness)))
myCrossSection = wingRibCrossSectionType(None, None, None, myMaterial,
None)
# Rib Positioning
#=======================================================================
etaStart = doubleBaseType(None, None, None, '0.')
etaEnd = doubleBaseType(None, None, None, '1.')
ribReference = stringBaseType(None, None, None, parentUID + '_Spar_FS')
ribStart = stringBaseType(None, None, None, 'leadingEdge')
ribEnd = stringBaseType(None, None, None, 'trailingEdge')
ribRotation = ribRotationType(None, None, None, stringBaseType(None, None, None, 'globalY'), \
doubleBaseType(None, None, None, '90.'))
ribCrossing = ribCrossingBehaviourType(None, None, None, 'cross')
etaStart = doubleBaseType(None, None, None, str(0.0))
etaEnd = doubleBaseType(None, None, None, str(0.95))
middleRibs = doubleBaseType(None, None, None, 5.)
ribsPositioning = wingRibsPositioningType(None, None, None, ribReference, etaStart, etaEnd, ribStart, ribEnd, \
None, middleRibs, ribCrossing, ribRotation)
ribsList.append(
wingRibsDefinitionType(None, None, None, myUID, myName, None,
ribsPositioning, myCrossSection))
#===============================================================================
# Flap
#===============================================================================
if typeOfSeg.lower() == 'flap' or typeOfSeg.lower() == 'innerflap':
myName = stringBaseType(None, None, None, 'flap_ribs')
# Rib Cross Section
#=======================================================================
myMaterial = materialDefinitionType(None, None, None, None, None, None, stringUIDBaseType(None, None, 'True', None, 'aluminium2024'), \
doubleBaseType(None, None, None, str(thickness)))
myCrossSection = wingRibCrossSectionType(None, None, None, myMaterial,
None)
# Rib Positioning
#=======================================================================
etaStart = doubleBaseType(None, None, None, '0.')
etaEnd = doubleBaseType(None, None, None, '1.')
ribReference = stringBaseType(None, None, None, parentUID + '_Spar_FS')
ribStart = stringBaseType(None, None, None, 'leadingEdge')
ribEnd = stringBaseType(None, None, None, 'trailingEdge')
ribRotation = ribRotationType(None, None, None, stringBaseType(None, None, None, 'globalY'), \
doubleBaseType(None, None, None, '90.'))
ribCrossing = ribCrossingBehaviourType(None, None, None, 'cross')
if nRibs is None:
ribSpacing = doubleBaseType(None, None, None, pitch)
ribsPositioning = wingRibsPositioningType(None, None, None, ribReference, etaStart, etaEnd, ribStart, ribEnd, \
ribSpacing, None, ribCrossing, ribRotation)
else:
nRibs = doubleBaseType(None, None, None, nRibs)
ribsPositioning = wingRibsPositioningType(None, None, None, ribReference, etaStart, etaEnd, ribStart, ribEnd, \
None, nRibs, ribCrossing, ribRotation)
ribsList.append(
wingRibsDefinitionType(None, None, None, myUID, myName, None,
ribsPositioning, myCrossSection))
#===============================================================================
# Spoiler
#===============================================================================
if typeOfSeg.lower() == 'spoiler':
myName = stringBaseType(None, None, None, 'spoiler_ribs')
# Rib Cross Section
#=======================================================================
myMaterial = materialDefinitionType(None, None, None, None, None, None, stringUIDBaseType(None, None, 'True', None, 'aluminium2024'), \
doubleBaseType(None, None, None, str(thickness)))
myCrossSection = wingRibCrossSectionType(None, None, None, myMaterial,
None)
# Rib Positioning
#=======================================================================
etaStart = doubleBaseType(None, None, None, '0.')
etaEnd = doubleBaseType(None, None, None, '1.')
ribReference = stringBaseType(None, None, None, 'leadingEdge')
ribStart = stringBaseType(None, None, None, 'leadingEdge')
ribEnd = stringBaseType(None, None, None, 'trailingEdge')
ribRotation = ribRotationType(None, None, None, stringBaseType(None, None, None, 'leadingEdge'), \
doubleBaseType(None, None, None, '90.'))
ribCrossing = ribCrossingBehaviourType(None, None, None, 'cross')
if nRibs is None:
ribSpacing = doubleBaseType(None, None, None, pitch)
ribsPositioning = wingRibsPositioningType(None, None, None, ribReference, etaStart, etaEnd, ribStart, ribEnd, \
ribSpacing, None, ribCrossing, ribRotation)
else:
nRibs = doubleBaseType(None, None, None, nRibs)
ribsPositioning = wingRibsPositioningType(None, None, None, ribReference, etaStart, etaEnd, ribStart, ribEnd, \
None, nRibs, ribCrossing, ribRotation)
ribsList.append(
wingRibsDefinitionType(None, None, None, myUID, myName, None,
ribsPositioning, myCrossSection))
#=======================================================================
# RibsDefinition
#=======================================================================
myRibsDefinitions = wingRibsDefinitionsType(None, None, None, ribsList)
parent.get_structure().set_ribsDefinitions(myRibsDefinitions)
