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 createRoller(uID='cruiseRoller1UID', eta=0.02, xsi=0.05, relHeight=0.3, positiv="False", negativ="True"):
position = cruiseRollerPositionType(eta=doubleBaseType(valueOf_=str(eta)), xsi=doubleBaseType(valueOf_=str(xsi)), relHeight=doubleBaseType(valueOf_=str(relHeight)))
parentAttachment = materialDefinitionType(materialUID=stringBaseType(valueOf_='aluminium2024'), thickness=doubleBaseType(valueOf_='0.001'))
controlSurfaceAttachment = materialDefinitionType(materialUID=stringBaseType(valueOf_='aluminium2024'), thickness=doubleBaseType(valueOf_='0.001'))
blockedDOF = blockedDOFType(positive=booleanBaseType(valueOf_=positiv), negative=booleanBaseType(valueOf_=negativ))
return cruiseRollerType(uID=uID, position=position, parentAttachment=parentAttachment, controlSurfaceAttachment=controlSurfaceAttachment, blockedDOF=blockedDOF)
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 createTrackAileron(uid, eta, trackType):
eta = doubleBaseType(valueOf_=str(eta))
trackType = stringBaseType(valueOf_=trackType)
controlSurfaceAttachment = materialDefinitionType(materialUID=stringBaseType(valueOf_='aluminium2024'), thickness=doubleBaseType(valueOf_='0.001'))
#parentAttachment = materialDefinitionType(materialUID=stringBaseType(valueOf_='aluminium2024'), thickness=doubleBaseType(valueOf_='0.001'))
trackStructure = trackStructureType(controlSurfaceAttachment=controlSurfaceAttachment)
return controlSurfaceTrackTypeType(uID=uid, eta=eta, trackType=trackType, trackStructure=trackStructure)
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 createRoller(uID='cruiseRoller1UID',
eta=0.02,
xsi=0.05,
relHeight=0.3,
positiv="False",
negativ="True"):
position = cruiseRollerPositionType(
eta=doubleBaseType(valueOf_=str(eta)),
xsi=doubleBaseType(valueOf_=str(xsi)),
relHeight=doubleBaseType(valueOf_=str(relHeight)))
parentAttachment = materialDefinitionType(
materialUID=stringBaseType(valueOf_='aluminium2024'),
thickness=doubleBaseType(valueOf_='0.001'))
controlSurfaceAttachment = materialDefinitionType(
materialUID=stringBaseType(valueOf_='aluminium2024'),
thickness=doubleBaseType(valueOf_='0.001'))
blockedDOF = blockedDOFType(positive=booleanBaseType(valueOf_=positiv),
negative=booleanBaseType(valueOf_=negativ))
return cruiseRollerType(uID=uID,
position=position,
parentAttachment=parentAttachment,
controlSurfaceAttachment=controlSurfaceAttachment,
blockedDOF=blockedDOF)
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 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 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)