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 createPositioning(parent, uID, fromID, toID, length, sweep, dihedral,
name):
'''
Create a positioning for Fuselage Elements
parent Element should be of PositioningsType
from ID must not be given, if None then element is placed relative to origin
uID will be saved as "positioning"+uID
@author: Jonas Jepsen
'''
#Convert Types
mytoID = stringBaseType(None, None, None, toID)
myName = stringBaseType(None, None, None, name)
myLength = doubleBaseType(None, None, None, str(length))
mySweep = doubleBaseType(None, None, None, str(sweep))
myDihedral = doubleBaseType(None, None, None, str(dihedral))
#Check if fromID is given
#if it is given convert Type and create Positioning
if fromID is not None:
myfromID = stringBaseType(None, None, None, fromID)
myPositioning = positioningType(None, None, None, uID, myName, None,
myLength, mySweep, myDihedral,
myfromID, mytoID)
#if no from ID is given create Positioning with None
else:
myPositioning = positioningType(None, None, None, uID, myName, None,
myLength, mySweep, myDihedral, None,
mytoID)
#Add to parent
parent.add_positioning(myPositioning)
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 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 createTransformation(
parent, refType="absGlobal", tx=0.0, ty=0.0, tz=0.0, sx=1.0, sy=1.0, sz=1.0, rx=0.0, ry=0.0, rz=0.0
): # allgemein
"""
This Method is used for creation in Transformation Element build up from pointTypes for Translation, Scaling and Rotation
Note that in CPACS 1.0 Translation should be of Type pointAbsRelType Due to TIGL issues this feature is still unabled inside the cpacslib.py
@author: Jonas Jepsen
@param parent: should be any Type holding a TransformationType
@param tx, ty, tz, sx, sy, sz, rx, ry, rz:Translation, Scaling and Rotation
"""
# Convert to CPACS Types
myTranslation = pointAbsRelType(
refType=refType,
x=doubleBaseType(valueOf_=str(tx)),
y=doubleBaseType(valueOf_=str(ty)),
z=doubleBaseType(valueOf_=str(tz)),
)
myScaling = pointType(
x=doubleBaseType(valueOf_=str(sx)), y=doubleBaseType(valueOf_=str(sy)), z=doubleBaseType(valueOf_=str(sz))
)
myRotation = pointType(
x=doubleBaseType(valueOf_=str(rx)), y=doubleBaseType(valueOf_=str(ry)), z=doubleBaseType(valueOf_=str(rz))
)
# Create Element
myTransformation = transformationType(scaling=myScaling, rotation=myRotation, translation=myTranslation)
# Append to Parent
parent.set_transformation(myTransformation)
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 createPointList(pointList):
#new Point List object
myPointList = pointListType(None, None, None, None)
for [xvalue, yvalue] in pointList:
#Convert Types and Create Point
x = doubleBaseType(None, None, None, str(xvalue))
y = doubleBaseType(None, None, None, str(yvalue))
z = doubleBaseType(None, None, None, str(0.0))
myPoint = pointType(None, None, None, None, x, y, z)
#Add Point to PointList
myPointList.add_point(myPoint)
return myPointList
def createPointList(pointList):
# new Point List object
myPointList = pointListType()
for [xvalue, yvalue] in pointList:
# Convert Types and Create Point
x = doubleBaseType(valueOf_=str(xvalue))
y = doubleBaseType(valueOf_=str(yvalue))
z = doubleBaseType(valueOf_=str(0.0))
myPoint = pointType(x=x, y=y, z=z)
# Add Point to PointList
myPointList.add_point(myPoint)
return myPointList
def createPointList(nparray):
'''
create a point list for each cog location
This method is currently without use, as long as there is no update to CPACS 2.2.1
'''
myPointList = pointListType()
zero = doubleBaseType(valueOf_='0.')
for item in nparray.tolist():
newPoint = pointType(x=doubleBaseType(valueOf_=str(item)),y=zero, z=zero)
myPointList.add_point(newPoint)
return myPointList
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 createVectorPointList(nparray):
'''
create a point list for each cog location
'''
myPointList = pointListType()
x = '; '.join(str(x) for x in nparray.tolist())
zeros = np.zeros(nparray.shape)
y = '; '.join(str(y) for y in zeros.tolist())
newPoint = pointType(x=doubleBaseType(valueOf_=str(x)),y=doubleBaseType(valueOf_=y), z=doubleBaseType(valueOf_=y))
myPointList.add_point(newPoint)
return myPointList
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 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 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 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 createPoint(parent, x, y, z=None):
'''
Methods builds a Point from PointType and adds it to parent
@author: Jonas Jepsen
@param parent: parent element (i.e. pointListType)
@param x: X-Coordinate
@param y: Y-Coordinate
@param z: Z-Coordinate, default is NONE
'''
xP = doubleBaseType(None, None, None, str(x))
yP = doubleBaseType(None, None, None, str(0.0))
zP = doubleBaseType(None, None, None, str(y))
if z is None:
myPoint = pointType(None, None, None, None, xP, yP, None)
else:
zP = doubleBaseType(None, None, None, str(z))
myPoint = pointType(None, None, None, None, xP, yP, zP)
parent.add_point(myPoint)
def createPoint(parent, x, y, z=None):
"""
Methods builds a Point from PointType and adds it to parent
@author: Jonas Jepsen
@param parent: parent element (i.e. pointListType)
@param x: X-Coordinate
@param y: Y-Coordinate
@param z: Z-Coordinate, default is NONE
"""
xP = doubleBaseType(valueOf_=str(x))
yP = doubleBaseType(valueOf_=str(0.0))
zP = doubleBaseType(valueOf_=str(y))
if z is None:
myPoint = pointType(x=xP, y=yP)
else:
zP = doubleBaseType(valueOf_=str(z))
myPoint = pointType(x=xP, y=yP, z=zP)
parent.add_point(myPoint)
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 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 createDoubleTrapezoidWing(myWing, id, cTip, cRoot, span, Sref, phiLE, dihedral, twist, xMAC25, etakf, strUID):
'''
This method creates a double trapezoid wing geometry in the 'myWing' parameter.
@author: Jonas Jepsen
@param myWing: wings CPACS object
@param id: the VAMPzero-id of the wing
@param cTip: length of chord at wing tip [m]
@param cRoot: length of chord at wing root [m]
@param span: span of the wing [m]
@param Sref: reference area [m^2]
@param phiLE: sweep angle at the leading edge [deg]
@param dihedral: dihedralangle of the wing [deg]
@param twist: twist of the outer wing section [deg]
@param etakf: dimensionless span coordinate [-]
@param strUID: the CPACS-uID of the wing
'''
# sections and positionings will be created, all existing sections and positionings will be deleted
mySections = wingSectionsType()
myPositionings = positioningsType()
# calc Lvl 1 parameters
taperRatio = (cTip/cRoot)
cRoot, cKink, cTip = calcWing(span, Sref, taperRatio, phiLE, etakf)
createWingSection(mySections, 0.,0.,0., cRoot,1.,cRoot, 0.,0.,0., 'NACA653218', 1, strUID + '_Sec1', strUID + '_Sec1', strUID + '_Sec1')
createWingSection(mySections, 0.,0.,0., cKink,1.,cKink, 0.,0.,0., 'NACA653218', 1, strUID + '_Sec2', strUID + '_Sec2', strUID + '_Sec2')
createWingSection(mySections, 0.,0.,0., cTip,1.,cTip, 0.,twist,0., 'NACA653218', 1, strUID + '_Sec3', strUID + '_Sec3', strUID + '_Sec3')
# calc length from span, sweep and dihedral
sweep_rad = phiLE/180. * pi
dihedral_rad = dihedral/180. * pi
length1 = (etakf*span/2.)/cos(sweep_rad)/cos(dihedral_rad)
length2 = span/2.*(1-etakf)/cos(sweep_rad)/cos(dihedral_rad)
createPositioning(myPositionings,str(id) + '_Pos1',None, str(id) + '_Sec1',0.,0.,0.,id)
createPositioning(myPositionings,str(id) + '_Pos2',str(id) + '_Sec1',str(id) + '_Sec2',length1,phiLE,dihedral,id)
createPositioning(myPositionings,str(id) + '_Pos3',str(id) + '_Sec2',str(id) + '_Sec3',length2,phiLE,dihedral,id)
myWing.set_sections(mySections)
myWing.set_positionings(myPositionings)
createWingSegments(myWing, strUID, 2)
createComponentSegment(myWing, strUID)
# calc wing position
tauk = cTip/cKink
myLambda = span**2/Sref
sweep_rad = 35./180.*pi
tanPhi25a = calcPhi25a(sweep_rad, taperRatio, tauk, etakf, span, cRoot)
tanPhi25i = calcPhi25i(sweep_rad, taperRatio, tauk, etakf, span, cRoot)
Xef = calcXef(cRoot, myLambda, tanPhi25i, tanPhi25a, etakf, taperRatio, tauk)
xRoot = calcXRoot(xMAC25, Xef, cRoot)
# set wing x - position
myWing.get_transformation().get_translation().set_x(doubleBaseType(None, None, None,str(xRoot)))
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 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 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 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 createStep(deflection, x1, y1, z1, x2, z2, rotation):
relDeflection = doubleBaseType(valueOf_=str(deflection))
innerHingeTranslation = pointType(x=doubleBaseType(valueOf_=str(x1)),
y=doubleBaseType(valueOf_=str(y1)),
z=doubleBaseType(valueOf_=str(z1)))
outerHingeTranslation = pointXZType(x=doubleBaseType(valueOf_=str(x2)),
z=doubleBaseType(valueOf_=str(z2)))
hingeLineRotation = doubleBaseType(valueOf_=str(rotation))
return controlSurfaceStepType(relDeflection=relDeflection,
innerHingeTranslation=innerHingeTranslation,
outerHingeTranslation=outerHingeTranslation,
hingeLineRotation=hingeLineRotation)
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 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 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 createPositioning(parent, uID, fromID, toID, length, sweep, dihedral, name):
"""
Create a positioning for Fuselage Elements
parent Element should be of PositioningsType
from ID must not be given, if None then element is placed relative to origin
uID will be saved as "positioning"+uID
@author: Jonas Jepsen
"""
# Convert Types
mytoID = stringBaseType(valueOf_=toID)
myName = stringBaseType(valueOf_=name)
myLength = doubleBaseType(valueOf_=str(length))
mySweep = doubleBaseType(valueOf_=str(sweep))
myDihedral = doubleBaseType(valueOf_=str(dihedral))
# Check if fromID is given
# if it is given convert Type and create Positioning
if fromID is not None:
myfromID = stringBaseType(valueOf_=fromID)
myPositioning = positioningType(
uID=uID,
name=myName,
length=myLength,
sweepAngle=mySweep,
dihedralAngle=myDihedral,
fromSectionUID=myfromID,
toSectionUID=mytoID,
)
# if no from ID is given create Positioning with None
else:
myPositioning = positioningType(
uID=uID, name=myName, length=myLength, sweepAngle=mySweep, dihedralAngle=myDihedral, toSectionUID=mytoID
)
# Add to parent
parent.add_positioning(myPositioning)
def createStep(deflection, x1, y1, z1, x2, z2, rotation):
relDeflection = doubleBaseType(valueOf_=str(deflection))
innerHingeTranslation = pointType(
x=doubleBaseType(valueOf_=str(x1)), y=doubleBaseType(valueOf_=str(y1)), z=doubleBaseType(valueOf_=str(z1))
)
outerHingeTranslation = pointXZType(x=doubleBaseType(valueOf_=str(x2)), z=doubleBaseType(valueOf_=str(z2)))
hingeLineRotation = doubleBaseType(valueOf_=str(rotation))
return controlSurfaceStepType(
relDeflection=relDeflection,
innerHingeTranslation=innerHingeTranslation,
outerHingeTranslation=outerHingeTranslation,
hingeLineRotation=hingeLineRotation,
)
def createTransformation(parent,
refType='absGlobal',
tx=0.,
ty=0.,
tz=0.,
sx=1.,
sy=1.,
sz=1.,
rx=0.,
ry=0.,
rz=0.): # allgemein
'''
This Method is used for creation in Transformation Element build up from pointTypes for Translation, Scaling and Rotation
Note that in CPACS 1.0 Translation should be of Type pointAbsRelType Due to TIGL issues this feature is still unabled inside the cpacslib.py
@author: Jonas Jepsen
@param parent: should be any Type holding a TransformationType
@param tx, ty, tz, sx, sy, sz, rx, ry, rz:Translation, Scaling and Rotation
'''
# Convert to CPACS Types
myTranslation = pointAbsRelType(refType=refType,
x=doubleBaseType(valueOf_=str(tx)),
y=doubleBaseType(valueOf_=str(ty)),
z=doubleBaseType(valueOf_=str(tz)))
myScaling = pointType(x=doubleBaseType(valueOf_=str(sx)),
y=doubleBaseType(valueOf_=str(sy)),
z=doubleBaseType(valueOf_=str(sz)))
myRotation = pointType(x=doubleBaseType(valueOf_=str(rx)),
y=doubleBaseType(valueOf_=str(ry)),
z=doubleBaseType(valueOf_=str(rz)))
#Create Element
myTransformation = transformationType(scaling=myScaling,
rotation=myRotation,
translation=myTranslation)
#Append to Parent
parent.set_transformation(myTransformation)
def createStrut(myWing, id, tcRoot, tcTip, cTip, cRoot, span, phiLE, dihedral, twist, xRoot, yRoot, etaStrut, strUID):
'''
This method creates a trapezoid wing geometry in the 'myWing' parameter.
@author: Jonas Jepsen
@param myWing: wings CPACS object
@param id: the VAMPzero-id of the wing
@param cTip: length of chord at wing tip [m]
@param cRoot: length of chord at wing root [m]
@param span: span of the wing [m]
@param phiLE: sweep angle at the leading edge [deg]
@param dihedral: dihedralangle of the wing [deg]
@param twist: twist of the outer wing section [deg]
@param strUID: the CPACS-uID of the wing
'''
# sections and positionings will be created, all existing sections and positionings will be deleted
mySections = wingSectionsType()
myPositionings = positioningsType()
incidence_angle = 2.
createWingSection(mySections, tcRoot / 0.09, 0., 0., 0., cRoot, 1., cRoot, 0., incidence_angle, 0., 'NACA0009', 1, strUID + '_Sec1', strUID + '_Sec1', strUID + '_Sec1')
createWingSection(mySections, tcRoot / 0.09, 0., 0., 0., cRoot, 1., cRoot, dihedral, incidence_angle, 0., 'NACA0009', 1, strUID + '_Sec2', strUID + '_Sec2', strUID + '_Sec2')
createWingSection(mySections, tcTip / 0.09, 0., 0., 0., cTip, 1., cTip, dihedral, incidence_angle, 0., 'NACA0009', 1, strUID + '_Sec3', strUID + '_Sec3', strUID + '_Sec3')
createPositioning(myPositionings, str(id) + '_Pos1', None, str(id) + '_Sec1', 0., 0., 0., id)
createPositioning(myPositionings, str(id) + '_Pos2', str(id) + '_Sec1', str(id) + '_Sec2', yRoot, 0., 0., id)
createPositioning(myPositionings, str(id) + '_Pos3', str(id) + '_Sec2', str(id) + '_Sec3', span, phiLE, dihedral, id)
myWing.set_sections(mySections)
myWing.set_positionings(myPositionings)
createWingSegments(myWing, strUID, 2)
createComponentSegment(myWing, strUID, fromElement='_Sec2_Elem1')
createRibs(myWing.get_componentSegments().get_componentSegment()[0], strUID, 'strut', etaStrut=etaStrut)
createSpars(myWing.get_componentSegments().get_componentSegment()[0], strUID, 'strut')
createShell(myWing.get_componentSegments().get_componentSegment()[0], strUID, 'strut')
createWingFuselageAttachment(myWing.get_componentSegments().get_componentSegment()[0], strUID, typeOfSeg='strut')
createWingWingAttachment(myWing.get_componentSegments().get_componentSegment()[0], strUID, typeOfSeg='strut')
# set wing x - position and twist
myWing.get_transformation().get_translation().set_x(doubleBaseType(None, None, None, str(xRoot)))
#myWing.get_transformation().get_translation().set_y(doubleBaseType(None, None, None, str(yRoot)))
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 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 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 createStrutBracedWing(myWing, id, cTip, cRoot, span, Sref, phiLE, dihedral, twist, xMAC25, etaFus, etaStrut, tcRoot, tcTip, xRoot, strUID):
'''
This method creates a double trapezoid wing geometry in the 'myWing' parameter.
@author: Jonas Jepsen
@param myWing: wings CPACS object
@param id: the VAMPzero-id of the wing
@param cTip: length of chord at wing tip [m]
@param cRoot: length of chord at wing root [m]
@param span: span of the wing [m]
@param Sref: reference area [m^2]
@param phiLE: sweep angle at the leading edge [deg]
@param dihedral: dihedralangle of the wing [deg]
@param twist: twist of the outer wing section [deg]
@param etakf: dimensionless span coordinate [-]
@param strUID: the CPACS-uID of the wing
'''
mySections = wingSectionsType()
myPositionings = positioningsType()
# calc Lvl 1 parameters
taperRatio = (cTip/cRoot)
#cRoot, cFuselage, cTip = calcWing(span, Sref, taperRatio, phiLE, etaFus)
cStrut = cRoot+(cTip-cRoot)*(etaStrut-etaFus)/(1-etaFus)
# calc length from span, sweep and dihedral
sweep_rad = phiLE/180. * pi
dihedral_rad = dihedral/180. * pi
length1 = (etaFus*span/2.)
length2 = (etaStrut-etaFus)*span/2/cos(sweep_rad)/cos(dihedral_rad)
length3 = span/2.*(1-etaStrut)/cos(sweep_rad)/cos(dihedral_rad)
# Increase (or reduce the twist by 4deg as that is the overall angle of incidence of the wing)
incidenceAngle = 4.
twist = twist + incidenceAngle
twistgrad = twist / (span / 2.)
twist2 = twistgrad * length2
twist3 = twist
createWingSection(mySections, tcRoot/0.09, 0.,0.,0., cRoot,1.,cRoot, 0.,incidenceAngle,0., 'NACA0009', 1, strUID + '_Sec1', strUID + '_Sec1', strUID + '_Sec1')
createWingSection(mySections, tcRoot / 0.18, 0.,0.,0., cRoot,1.,cRoot, 0.,incidenceAngle,0., 'NACA653218', 1, strUID + '_Sec2', strUID + '_Sec2', strUID + '_Sec2')
createWingSection(mySections, tcRoot / 0.18, 0.,0.,0., cStrut,1.,cStrut, 0.,twist2,0., 'NACA653218', 1, strUID + '_Sec3', strUID + '_Sec3', strUID + '_Sec3')
createWingSection(mySections, tcTip / 0.18, 0.,0.,0., cTip,1.,cTip, 0.,twist3,0., 'NACA653218', 1, strUID + '_Sec4', strUID + '_Sec4', strUID + '_Sec4')
createPositioning(myPositionings,str(id) + '_Pos1',None, str(id) + '_Sec1',0.,0.,0.,id)
createPositioning(myPositionings,str(id) + '_Pos2',str(id) + '_Sec1',str(id) + '_Sec2',length1,0.,0.,id)
createPositioning(myPositionings,str(id) + '_Pos3',str(id) + '_Sec2',str(id) + '_Sec3',length2,phiLE,dihedral,id)
createPositioning(myPositionings,str(id) + '_Pos4',str(id) + '_Sec3',str(id) + '_Sec4',length3,phiLE,dihedral,id)
myWing.set_sections(mySections)
myWing.set_positionings(myPositionings)
createWingSegments(myWing, strUID, 3)
createComponentSegment(myWing, strUID)
# Ribs outboard of the Fuselage section are placed at 0.8 m distance
nouterRibs = int(ceil((0.95 - etaFus - 0.05) * span / 2. / 0.8))
createRibs(myWing.get_componentSegments().get_componentSegment()[0], strUID, 'strutBracedWing', etaFus=etaFus, nRibs=nouterRibs, etaStrut=etaStrut, span=span / 2., phi25 = phiLE)
createSpars(myWing.get_componentSegments().get_componentSegment()[0], strUID, 'strutBracedWing', etaFus=etaFus, cTip=cTip, cRoot=cRoot)
createShell(myWing.get_componentSegments().get_componentSegment()[0], strUID, 'strutBracedWing')
iRib = int(span * (0.9 - etaStrut) / (2 * 0.8)) - 1
if iRib == 1:
iRib = 2
createTanks(myWing.get_componentSegments().get_componentSegment()[0], strUID, typeOfSeg='strutBracedWing', nRib=iRib)
createWingFuselageAttachment(myWing.get_componentSegments().get_componentSegment()[0], strUID, 'advDoubletrapezoid')
# set wing x - position and twist
myWing.get_transformation().get_translation().set_x(doubleBaseType(None, None, None, str(xRoot)))
def createStrut(myWing, id, tcRoot, tcTip, cTip, cRoot, span, phiLE, dihedral,
twist, xRoot, yRoot, etaStrut, strUID):
'''
This method creates a trapezoid wing geometry in the 'myWing' parameter.
@author: Jonas Jepsen
@param myWing: wings CPACS object
@param id: the VAMPzero-id of the wing
@param cTip: length of chord at wing tip [m]
@param cRoot: length of chord at wing root [m]
@param span: span of the wing [m]
@param phiLE: sweep angle at the leading edge [deg]
@param dihedral: dihedralangle of the wing [deg]
@param twist: twist of the outer wing section [deg]
@param strUID: the CPACS-uID of the wing
'''
# sections and positionings will be created, all existing sections and positionings will be deleted
mySections = wingSectionsType()
myPositionings = positioningsType()
incidence_angle = 2.
createWingSection(mySections, tcRoot / 0.09, 0., 0., 0., cRoot, 1., cRoot,
0., incidence_angle, 0., 'NACA0009', 1, strUID + '_Sec1',
strUID + '_Sec1', strUID + '_Sec1')
createWingSection(mySections, tcRoot / 0.09, 0., 0., 0., cRoot, 1., cRoot,
dihedral, incidence_angle, 0., 'NACA0009', 1,
strUID + '_Sec2', strUID + '_Sec2', strUID + '_Sec2')
createWingSection(mySections, tcTip / 0.09, 0., 0., 0., cTip, 1., cTip,
dihedral, incidence_angle, 0., 'NACA0009', 1,
strUID + '_Sec3', strUID + '_Sec3', strUID + '_Sec3')
createPositioning(myPositionings,
str(id) + '_Pos1', None,
str(id) + '_Sec1', 0., 0., 0., id)
createPositioning(myPositionings,
str(id) + '_Pos2',
str(id) + '_Sec1',
str(id) + '_Sec2', yRoot, 0., 0., id)
createPositioning(myPositionings,
str(id) + '_Pos3',
str(id) + '_Sec2',
str(id) + '_Sec3', span, phiLE, dihedral, id)
myWing.set_sections(mySections)
myWing.set_positionings(myPositionings)
createWingSegments(myWing, strUID, 2)
createComponentSegment(myWing, strUID, fromElement='_Sec2_Elem1')
createRibs(myWing.get_componentSegments().get_componentSegment()[0],
strUID,
'strut',
etaStrut=etaStrut)
createSpars(myWing.get_componentSegments().get_componentSegment()[0],
strUID, 'strut')
createShell(myWing.get_componentSegments().get_componentSegment()[0],
strUID, 'strut')
createWingFuselageAttachment(
myWing.get_componentSegments().get_componentSegment()[0],
strUID,
typeOfSeg='strut')
createWingWingAttachment(
myWing.get_componentSegments().get_componentSegment()[0],
strUID,
typeOfSeg='strut')
# set wing x - position and twist
myWing.get_transformation().get_translation().set_x(
doubleBaseType(None, None, None, str(xRoot)))
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 createPath(
parent,
typeOfSeg="aileron",
uID="controlSurface",
innerX="0.",
outerX="0.",
innerHingeXsi="0.8",
outerHingeXsi="0.8",
):
if typeOfSeg == "aileron":
innerHingeXsi = 0.75
innerRelHeight = 0.2
outerHingeXsi = 0.75
outerRelHeight = 0.2
steps = createStepsAileron()
if typeOfSeg == "elevator":
innerHingeXsi = 0.75
innerRelHeight = 0.2
outerHingeXsi = 0.75
outerRelHeight = 0.2
steps = createStepsAileron()
if typeOfSeg == "stabilizer":
innerHingeXsi = 0.25
innerRelHeight = 0.5
outerHingeXsi = 0.25
outerRelHeight = 0.5
steps = createStepsAileron()
if typeOfSeg == "rudder":
innerHingeXsi = 0.75
innerRelHeight = 0.2
outerHingeXsi = 0.75
outerRelHeight = 0.2
steps = createStepsAileron()
if typeOfSeg == "flap" or typeOfSeg == "innerFlap":
innerHingeXsi = innerHingeXsi
innerRelHeight = 0.5
outerHingeXsi = outerHingeXsi
outerRelHeight = 0.5
steps = createStepsFlaps(innerX, outerX)
if typeOfSeg == "slat":
innerHingeXsi = innerHingeXsi
innerRelHeight = 0.5
outerHingeXsi = outerHingeXsi
outerRelHeight = 0.5
steps = createStepsSlats(innerX, outerX)
innerHinge = controlSurfaceHingePointType(
hingeXsi=doubleBaseType(valueOf_=str(innerHingeXsi)),
hingeRelHeight=doubleBaseType(valueOf_=str(innerRelHeight)),
)
outerHinge = controlSurfaceHingePointType(
hingeXsi=doubleBaseType(valueOf_=str(outerHingeXsi)),
hingeRelHeight=doubleBaseType(valueOf_=str(outerRelHeight)),
)
myPath = controlSurfacePathType(innerHingePoint=innerHinge, outerHingePoint=outerHinge, steps=steps)
parent.set_path(myPath)
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 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 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 createSpars(parent,
parentUID,
typeOfSeg,
etaFus=0.1,
etaKink=0.3,
cTip=1.0,
cRoot=6.0):
'''
Used for generation of spars within a componentSegment
@param parent: ComponentSegment object, spars-object will be added here
@param etaFus: eta Position at the Fuselage intersection
@param etaKink: eta Position at the Kink
@param typeOfSeg: either advDoubleTrapezoid or trapezoid or aileron
.. todo:
Maybe it would be a good idea to catch errors for high values of sweep
and high kink ratios. For this case the spar maybe out of bounds of the inner wing!
'''
mySparPositions = sparPositionsType(None, None, None, None)
myUID = parentUID + '_Spar'
#===========================================================================
# Spar Postions
#===========================================================================
if typeOfSeg == 'advDoubletrapezoid':
# The front spar should have a constant distance to the leading edge
distance = cRoot * .1
xsiRoot = distance / cRoot
xsiTip_front = distance / cTip
xsiTip_rear = 0.59
if xsiTip_front >= xsiTip_rear:
xsiTip_rear = xsiTip_front + 0.1
if xsiTip_rear > 1.0:
print "VAMPzero Warning: Rear spar location at the tip is larger than 1. Increase Taper Ratio!!!"
frontSparLocactions = [[0.0, xsiRoot], [etaFus, xsiRoot],
[1.0, xsiTip_front]]
rearSparLocactions = [[0.0, 0.56], [etaFus, 0.56], [etaKink, 0.6],
[1.0, xsiTip_rear]]
if typeOfSeg == 'strutBracedWing':
# The calculation of the strut braced wing is similar to that of the
# double trapezoid wing. nevertheless, we exclude the kink spar position
#
# The front spar should have a constant distance to the leading edge
distance = cRoot * .1
xsiRoot = distance / cRoot
xsiTip_front = distance / cTip
xsiTip_rear = 0.59
if xsiTip_front >= xsiTip_rear:
xsiTip_rear = xsiTip_front + 0.1
if xsiTip_rear > 1.0:
print "VAMPzero Warning: Rear spar location at the tip is larger than 1. Increase Taper Ratio!!!"
frontSparLocactions = [[0.0, xsiRoot], [etaFus, xsiRoot],
[1.0, xsiTip_front]]
rearSparLocactions = [[0.0, 0.56], [0.05, 0.56], [etaFus, 0.56],
[1.0, xsiTip_rear]]
if typeOfSeg == 'trapezoid':
frontSparLocactions = [[0.0, 0.22], [1.0, 0.22]]
rearSparLocactions = [[0.0, 0.55], [1.0, 0.55]]
if typeOfSeg == 'strut':
frontSparLocactions = [[0.0, 0.3], [1.0, 0.3]]
rearSparLocactions = []
if typeOfSeg == 'aileron':
frontSparLocactions = [[0.0, 0.2], [1.0, 0.2]]
rearSparLocactions = [[0.0, 0.7], [1.0, 0.7]]
if typeOfSeg == 'flap' or typeOfSeg == 'innerFlap':
frontSparLocactions = [[0.0, 0.2], [1.0, 0.2]]
rearSparLocactions = [[0.0, 0.7], [1.0, 0.7]]
if typeOfSeg == 'spoiler':
frontSparLocactions = [[0.0, 0.2], [1.0, 0.2]]
rearSparLocactions = []
#===========================================================================
# Assign Spar Locations
#===========================================================================
for item in frontSparLocactions:
x = doubleBaseType(valueOf_=str(item[0]))
y = doubleBaseType(valueOf_=str(item[1]))
mySparPostion = sparPositionType(None,
None,
None,
myUID + '_FS_P' +
str(frontSparLocactions.index(item)),
eta=x,
xsi=y)
mySparPositions.add_sparPosition(mySparPostion)
if len(rearSparLocactions) != 0:
for item in rearSparLocactions:
x = doubleBaseType(valueOf_=str(item[0]))
y = doubleBaseType(valueOf_=str(item[1]))
mySparPostion = sparPositionType(
None,
None,
None,
myUID + '_RS_P' + str(rearSparLocactions.index(item)),
eta=x,
xsi=y)
mySparPositions.add_sparPosition(mySparPostion)
#===========================================================================
# Create Segments
#===========================================================================
mySparSegments = sparSegmentsType(None, None, None, None)
createSparSegment(mySparSegments,
myUID,
'_FS',
numOfPoints=len(frontSparLocactions),
typeOfSeg=typeOfSeg)
if len(rearSparLocactions) != 0:
createSparSegment(mySparSegments,
myUID,
'_RS',
numOfPoints=len(rearSparLocactions))
#===========================================================================
# Back to CPACS
#===========================================================================
mySpars = wingSparType(None, None, None, mySparPositions, mySparSegments)
parent.get_structure().set_spars(mySpars)
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)
def createSpars(parent, parentUID, typeOfSeg, etaFus=0.1, etaKink=0.3, cTip=1.0, cRoot=6.0):
'''
Used for generation of spars within a componentSegment
@param parent: ComponentSegment object, spars-object will be added here
@param etaFus: eta Position at the Fuselage intersection
@param etaKink: eta Position at the Kink
@param typeOfSeg: either advDoubleTrapezoid or trapezoid or aileron
.. todo:
Maybe it would be a good idea to catch errors for high values of sweep
and high kink ratios. For this case the spar maybe out of bounds of the inner wing!
'''
mySparPositions = sparPositionsType(None, None, None, None)
myUID = parentUID + '_Spar'
#===========================================================================
# Spar Postions
#===========================================================================
if typeOfSeg == 'advDoubletrapezoid':
# The front spar should have a constant distance to the leading edge
distance = cRoot * .1
xsiRoot = distance / cRoot
xsiTip_front = distance / cTip
xsiTip_rear = 0.59
if xsiTip_front >= xsiTip_rear:
xsiTip_rear = xsiTip_front + 0.1
if xsiTip_rear > 1.0:
print "VAMPzero Warning: Rear spar location at the tip is larger than 1. Increase Taper Ratio!!!"
frontSparLocactions = [[0.0, xsiRoot], [etaFus, xsiRoot], [1.0, xsiTip_front]]
rearSparLocactions = [[0.0, 0.56], [etaFus, 0.56], [etaKink, 0.6], [1.0, xsiTip_rear]]
if typeOfSeg == 'strutBracedWing':
# The calculation of the strut braced wing is similar to that of the
# double trapezoid wing. nevertheless, we exclude the kink spar position
#
# The front spar should have a constant distance to the leading edge
distance = cRoot * .1
xsiRoot = distance / cRoot
xsiTip_front = distance / cTip
xsiTip_rear = 0.59
if xsiTip_front >= xsiTip_rear:
xsiTip_rear = xsiTip_front + 0.1
if xsiTip_rear > 1.0:
print "VAMPzero Warning: Rear spar location at the tip is larger than 1. Increase Taper Ratio!!!"
frontSparLocactions = [[0.0, xsiRoot], [etaFus, xsiRoot], [1.0, xsiTip_front]]
rearSparLocactions = [[0.0, 0.56], [etaFus, 0.56], [1.0, xsiTip_rear]]
if typeOfSeg == 'trapezoid':
frontSparLocactions = [[0.0, 0.22], [1.0, 0.22]]
rearSparLocactions = [[0.0, 0.55], [1.0, 0.55]]
if typeOfSeg == 'strut':
frontSparLocactions = [[0.0, 0.3], [1.0, 0.3]]
rearSparLocactions = []
if typeOfSeg == 'aileron':
frontSparLocactions = [[0.0, 0.2], [1.0, 0.2]]
rearSparLocactions = [[0.0, 0.7], [1.0, 0.7]]
if typeOfSeg == 'flap' or typeOfSeg == 'innerFlap':
frontSparLocactions = [[0.0, 0.2], [1.0, 0.2]]
rearSparLocactions = [[0.0, 0.7], [1.0, 0.7]]
if typeOfSeg == 'spoiler':
frontSparLocactions = [[0.0, 0.2], [1.0, 0.2]]
rearSparLocactions = []
#===========================================================================
# Assign Spar Locations
#===========================================================================
for item in frontSparLocactions:
x = doubleBaseType(valueOf_=str(item[0]))
y = doubleBaseType(valueOf_=str(item[1]))
mySparPostion = sparPositionType(uID= myUID + '_FS_P' + str(frontSparLocactions.index(item)), eta=x, xsi=y)
mySparPositions.add_sparPosition(mySparPostion)
if len(rearSparLocactions) != 0:
for item in rearSparLocactions:
x = doubleBaseType(valueOf_=str(item[0]))
y = doubleBaseType(valueOf_=str(item[1]))
mySparPostion = sparPositionType(uID=myUID + '_RS_P' + str(rearSparLocactions.index(item)), eta=x, xsi=y)
mySparPositions.add_sparPosition(mySparPostion)
#===========================================================================
# Create Segments
#===========================================================================
mySparSegments = sparSegmentsType()
createSparSegment(mySparSegments, myUID, '_FS', numOfPoints=len(frontSparLocactions), typeOfSeg=typeOfSeg)
if len(rearSparLocactions) != 0:
createSparSegment(mySparSegments, myUID, '_RS', numOfPoints=len(rearSparLocactions))
#===========================================================================
# Back to CPACS
#===========================================================================
mySpars = wingSparType(None, None, None, mySparPositions, mySparSegments)
parent.get_structure().set_spars(mySpars)
def createAdvDoubleTrapezoidWing(myWing, id, cTip, cRoot, span, Sref, dfus,
phiLE, dihedral, twist, xMAC25, etakf, strUID,
yfus, xRoot, etaEng, tcRoot, tcTip):
'''
This method creates a double trapezoid wing geometry in the 'myWing' parameter.
** Introduced a linear twist distribution from *0* at root to *twist* at tip
@author: Jonas Jepsen
@param myWing: wings CPACS object
@param id: the VAMPzero-id of the wing
@param cTip: length of chord at wing tip [m]
@param cRoot: length of chord at wing root [m]
@param span: span of the wing [m]
@param Sref: reference area [m^2]
@param dfus: fuselage diameter [m]
@param phiLE: sweep angle at the leading edge [deg]
@param dihedral: dihedralangle of the wing [deg]
@param twist: twist of the outer wing section [deg]
@param etakf: dimensionless span coordinate [-]
@param strUID: the CPACS-uID of the wing
'''
# sections and positionings will be created, all existing sections and positionings will be deleted
mySections = wingSectionsType()
myPositionings = positioningsType()
# calc Lvl 1 parameters
taperRatio = (cTip / cRoot)
cRoot, cKink, cTip = calcWing(span, Sref, taperRatio, phiLE, etakf, dfus)
# calc length from span, sweep and dihedral
sweep_rad = phiLE / 180. * pi
dihedral_rad = dihedral / 180. * pi
# trying to correct the commented statement that uses dfus. will try to use yfus
# length1 = dfus / 2.
length1 = yfus
length2 = (etakf * span / 2. -
length1) / cos(sweep_rad) / cos(dihedral_rad)
length3 = span / 2. * (1 - etakf) / cos(sweep_rad) / cos(dihedral_rad)
# Increase (or reduce the twist by 4deg as that is the overall angle of incidence of the wing)
twist = twist - 4.
twistgrad = twist / (span / 2.)
twist1 = twistgrad * length1
twist2 = twistgrad * etakf * (span / 2.)
twist3 = twist
createWingSection(mySections, tcRoot / 0.09, 0., 0., 0., cRoot, 1., cRoot,
0., 0., 0., 'NACA0009', 1, strUID + '_Sec1',
strUID + '_Sec1', strUID + '_Sec1')
createWingSection(mySections, tcRoot / 0.18, 0., 0., 0., cRoot, 1., cRoot,
0., 0., 0., 'NACA653218', 1, strUID + '_Sec2',
strUID + '_Sec2', strUID + '_Sec2')
createWingSection(mySections, tcTip / 0.18, 0., 0., 0., cKink, 1., cKink,
0., twist2, 0., 'NACA653218', 1, strUID + '_Sec3',
strUID + '_Sec3', strUID + '_Sec3')
createWingSection(mySections, tcTip / 0.18, 0., 0., 0., cTip, 1., cTip, 0.,
twist3, 0., 'NACA653218', 1, strUID + '_Sec4',
strUID + '_Sec4', strUID + '_Sec4')
createPositioning(myPositionings,
str(id) + '_Pos1', None,
str(id) + '_Sec1', 0., 0., 0., id)
createPositioning(myPositionings,
str(id) + '_Pos2',
str(id) + '_Sec1',
str(id) + '_Sec2', length1, 0., 0., id)
createPositioning(myPositionings,
str(id) + '_Pos3',
str(id) + '_Sec2',
str(id) + '_Sec3', length2, phiLE, dihedral, id)
createPositioning(myPositionings,
str(id) + '_Pos4',
str(id) + '_Sec3',
str(id) + '_Sec4', length3, phiLE, dihedral, id)
myWing.set_sections(mySections)
myWing.set_positionings(myPositionings)
createWingSegments(myWing, strUID, 3)
createComponentSegment(myWing, strUID)
etafus = yfus / (span / 2.)
# Ribs outboard of the Fuselage section are placed at 0.8 m distance
nouterRibs = int(ceil((0.95 - etafus - 0.05) * span / 2. / 0.8))
createRibs(myWing.get_componentSegments().get_componentSegment()[0],
strUID,
'advDoubletrapezoid',
etaFus=etafus,
nRibs=nouterRibs,
etaEng=etaEng,
span=span / 2.)
createSpars(myWing.get_componentSegments().get_componentSegment()[0],
strUID,
'advDoubletrapezoid',
length1 / (span / 2.),
etakf / cos(dihedral_rad),
cTip=cTip,
cRoot=cRoot)
createShell(myWing.get_componentSegments().get_componentSegment()[0],
strUID, 'advDoubletrapezoid')
createWingFuselageAttachment(
myWing.get_componentSegments().get_componentSegment()[0], strUID,
'advDoubletrapezoid')
# Estimate ribNum of outer Rib
iRib = int(span * (0.85 - etaEng) / (2 * 0.8)) - 1
createTanks(myWing.get_componentSegments().get_componentSegment()[0],
strUID,
'advDoubletrapezoid',
nRib=iRib)
# calc wing position
tauK = cTip / cKink
etar = dfus / span
# XN25F = calcXN25F(cRoot, span, phiLE, etar, etakf, tauK, taperRatio)
# xRoot.py = calcXRoot(xMAC25, XN25F)
# set wing x - position and twist
myWing.get_transformation().get_translation().set_x(
doubleBaseType(None, None, None, str(xRoot)))
myWing.get_transformation().get_rotation().set_y(
doubleBaseType(None, None, None, str(4.)))
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 createPath(parent,
typeOfSeg='aileron',
uID='controlSurface',
innerX='0.',
outerX='0.',
innerHingeXsi='0.8',
outerHingeXsi='0.8'):
if typeOfSeg == 'aileron':
innerHingeXsi = 0.75
innerRelHeight = 0.2
outerHingeXsi = 0.75
outerRelHeight = 0.2
steps = createStepsAileron()
if typeOfSeg == 'elevator':
innerHingeXsi = 0.75
innerRelHeight = 0.2
outerHingeXsi = 0.75
outerRelHeight = 0.2
steps = createStepsAileron()
if typeOfSeg == 'stabilizer':
innerHingeXsi = 0.25
innerRelHeight = 0.5
outerHingeXsi = 0.25
outerRelHeight = 0.5
steps = createStepsAileron()
if typeOfSeg == 'rudder':
innerHingeXsi = 0.75
innerRelHeight = 0.2
outerHingeXsi = 0.75
outerRelHeight = 0.2
steps = createStepsAileron()
if typeOfSeg == 'flap' or typeOfSeg == 'innerFlap':
innerHingeXsi = innerHingeXsi
innerRelHeight = 0.5
outerHingeXsi = outerHingeXsi
outerRelHeight = 0.5
steps = createStepsFlaps(innerX, outerX)
if typeOfSeg == 'slat':
innerHingeXsi = innerHingeXsi
innerRelHeight = 0.5
outerHingeXsi = outerHingeXsi
outerRelHeight = 0.5
steps = createStepsSlats(innerX, outerX)
innerHinge = controlSurfaceHingePointType(
hingeXsi=doubleBaseType(valueOf_=str(innerHingeXsi)),
hingeRelHeight=doubleBaseType(valueOf_=str(innerRelHeight)))
outerHinge = controlSurfaceHingePointType(
hingeXsi=doubleBaseType(valueOf_=str(outerHingeXsi)),
hingeRelHeight=doubleBaseType(valueOf_=str(outerRelHeight)))
myPath = controlSurfacePathType(innerHingePoint=innerHinge,
outerHingePoint=outerHinge,
steps=steps)
parent.set_path(myPath)
def createStrutBracedWing(myWing, id, cTip, cRoot, span, Sref, phiLE, dihedral, twist, xMAC25, etaFus, etaStrut, tcRoot, tcTip, xRoot, strUID):
'''
This method creates a double trapezoid wing geometry in the 'myWing' parameter.
@author: Jonas Jepsen
@param myWing: wings CPACS object
@param id: the VAMPzero-id of the wing
@param cTip: length of chord at wing tip [m]
@param cRoot: length of chord at wing root [m]
@param span: span of the wing [m]
@param Sref: reference area [m^2]
@param phiLE: sweep angle at the leading edge [deg]
@param dihedral: dihedralangle of the wing [deg]
@param twist: twist of the outer wing section [deg]
@param etakf: dimensionless span coordinate [-]
@param strUID: the CPACS-uID of the wing
'''
mySections = wingSectionsType()
myPositionings = positioningsType()
# calc Lvl 1 parameters
taperRatio = (cTip/cRoot)
cRoot = calcWing(b=span, S=Sref, tau=taperRatio, eF=etaFus)
cStrut = cRoot+(cTip-cRoot)*(etaStrut-etaFus)/(1-etaFus)
cTip = taperRatio * cRoot # cRoot was updated in the last step
# calc length from span, sweep and dihedral
sweep_rad = phiLE/180. * pi
dihedral_rad = dihedral/180. * pi
length1 = (etaFus*span/2.)
length2 = (etaStrut-etaFus)*span/2/cos(sweep_rad)/cos(dihedral_rad)
length3 = span/2.*(1-etaStrut)/cos(sweep_rad)/cos(dihedral_rad)
# Increase (or reduce the twist by 4deg as that is the overall angle of incidence of the wing)
incidenceAngle = 4.
twist = twist + incidenceAngle
twistgrad = twist / (span / 2.)
twist2 = twistgrad * length2
twist3 = twist
createWingSection(mySections, tcRoot/0.09, 0.,0.,0., cRoot,1.,cRoot, 0.,incidenceAngle,0., 'NACA0009', 1, strUID + '_Sec1', strUID + '_Sec1', strUID + '_Sec1')
createWingSection(mySections, tcRoot / 0.18, 0.,0.,0., cRoot,1.,cRoot, 0.,incidenceAngle,0., 'NACA653218', 1, strUID + '_Sec2', strUID + '_Sec2', strUID + '_Sec2')
createWingSection(mySections, tcRoot / 0.18, 0.,0.,0., cStrut,1.,cStrut, 0.,twist2,0., 'NACA653218', 1, strUID + '_Sec3', strUID + '_Sec3', strUID + '_Sec3')
createWingSection(mySections, tcTip / 0.18, 0.,0.,0., cTip,1.,cTip, 0.,twist3,0., 'NACA653218', 1, strUID + '_Sec4', strUID + '_Sec4', strUID + '_Sec4')
createPositioning(myPositionings,str(id) + '_Pos1',None, str(id) + '_Sec1',0.,0.,0.,id)
createPositioning(myPositionings,str(id) + '_Pos2',str(id) + '_Sec1',str(id) + '_Sec2',length1,0.,0.,id)
createPositioning(myPositionings,str(id) + '_Pos3',str(id) + '_Sec2',str(id) + '_Sec3',length2,phiLE,dihedral,id)
createPositioning(myPositionings,str(id) + '_Pos4',str(id) + '_Sec3',str(id) + '_Sec4',length3,phiLE,dihedral,id)
myWing.set_sections(mySections)
myWing.set_positionings(myPositionings)
createWingSegments(myWing, strUID, 3)
createComponentSegment(myWing, strUID)
# Ribs outboard of the Fuselage section are placed at 0.8 m distance
nouterRibs = int(ceil((0.95 - etaFus - 0.05) * span / 2. / 0.8))
createRibs(myWing.get_componentSegments().get_componentSegment()[0], strUID, 'strutBracedWing', etaFus=etaFus, nRibs=nouterRibs, etaStrut=etaStrut, span=span / 2., phi25 = phiLE)
createSpars(myWing.get_componentSegments().get_componentSegment()[0], strUID, 'strutBracedWing', etaFus=etaFus, cTip=cTip, cRoot=cRoot)
createShell(myWing.get_componentSegments().get_componentSegment()[0], strUID, 'strutBracedWing')
iRib = int(span * (0.9 - etaStrut) / (2 * 0.8)) - 1
if iRib == 1:
iRib = 2
createTanks(myWing.get_componentSegments().get_componentSegment()[0], strUID, typeOfSeg='strutBracedWing', nRib=iRib)
createWingFuselageAttachment(myWing.get_componentSegments().get_componentSegment()[0], strUID, 'advDoubletrapezoid')
# set wing x - position and twist
myWing.get_transformation().get_translation().set_x(doubleBaseType(valueOf_=str(xRoot)))
def createDoubleTrapezoidWing(myWing, id, cTip, cRoot, span, Sref, phiLE,
dihedral, twist, xMAC25, etakf, strUID):
'''
This method creates a double trapezoid wing geometry in the 'myWing' parameter.
@author: Jonas Jepsen
@param myWing: wings CPACS object
@param id: the VAMPzero-id of the wing
@param cTip: length of chord at wing tip [m]
@param cRoot: length of chord at wing root [m]
@param span: span of the wing [m]
@param Sref: reference area [m^2]
@param phiLE: sweep angle at the leading edge [deg]
@param dihedral: dihedralangle of the wing [deg]
@param twist: twist of the outer wing section [deg]
@param etakf: dimensionless span coordinate [-]
@param strUID: the CPACS-uID of the wing
'''
# sections and positionings will be created, all existing sections and positionings will be deleted
mySections = wingSectionsType()
myPositionings = positioningsType()
# calc Lvl 1 parameters
taperRatio = (cTip / cRoot)
cRoot, cKink, cTip = calcWing(span, Sref, taperRatio, phiLE, etakf)
createWingSection(mySections, 0., 0., 0., cRoot, 1., cRoot, 0., 0., 0.,
'NACA653218', 1, strUID + '_Sec1', strUID + '_Sec1',
strUID + '_Sec1')
createWingSection(mySections, 0., 0., 0., cKink, 1., cKink, 0., 0., 0.,
'NACA653218', 1, strUID + '_Sec2', strUID + '_Sec2',
strUID + '_Sec2')
createWingSection(mySections, 0., 0., 0., cTip, 1., cTip, 0., twist, 0.,
'NACA653218', 1, strUID + '_Sec3', strUID + '_Sec3',
strUID + '_Sec3')
# calc length from span, sweep and dihedral
sweep_rad = phiLE / 180. * pi
dihedral_rad = dihedral / 180. * pi
length1 = (etakf * span / 2.) / cos(sweep_rad) / cos(dihedral_rad)
length2 = span / 2. * (1 - etakf) / cos(sweep_rad) / cos(dihedral_rad)
createPositioning(myPositionings,
str(id) + '_Pos1', None,
str(id) + '_Sec1', 0., 0., 0., id)
createPositioning(myPositionings,
str(id) + '_Pos2',
str(id) + '_Sec1',
str(id) + '_Sec2', length1, phiLE, dihedral, id)
createPositioning(myPositionings,
str(id) + '_Pos3',
str(id) + '_Sec2',
str(id) + '_Sec3', length2, phiLE, dihedral, id)
myWing.set_sections(mySections)
myWing.set_positionings(myPositionings)
createWingSegments(myWing, strUID, 2)
createComponentSegment(myWing, strUID)
# calc wing position
tauk = cTip / cKink
myLambda = span**2 / Sref
sweep_rad = 35. / 180. * pi
tanPhi25a = calcPhi25a(sweep_rad, taperRatio, tauk, etakf, span, cRoot)
tanPhi25i = calcPhi25i(sweep_rad, taperRatio, tauk, etakf, span, cRoot)
Xef = calcXef(cRoot, myLambda, tanPhi25i, tanPhi25a, etakf, taperRatio,
tauk)
xRoot = calcXRoot(xMAC25, Xef, cRoot)
# set wing x - position
myWing.get_transformation().get_translation().set_x(
doubleBaseType(None, None, None, str(xRoot)))
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)
