Exemplo n.º 1
0
def createComponentSegment(parent, parentUID, fromElement='_Sec1_Elem1'):
    '''
    Used for generation of componentSegments within a wing
    create numOfComponentSegs in a wing
    @param parent: wingType object, Sections-object will be added here
    @param parentUID:  UID of parent object [string]
    '''
    #===========================================================================
    # Create Component Segement
    #===========================================================================
    myUID = parentUID + '_Cseg'
    myName = stringBaseType(valueOf_= parentUID + '_CSeg')
    myDescr = stringBaseType(valueOf_= parentUID + '_CSeg')
    myFromElem = stringBaseType(valueOf_=parentUID + fromElement)
    index = str(len(parent.get_sections().get_section()))
    myToElem = stringBaseType(valueOf_=parentUID + '_Sec' + index + '_Elem1')
    myStructure = wingComponentSegmentStructureType()
    
    #===========================================================================
    # Back to CPACS
    #===========================================================================
    myComponentSegments = componentSegmentsType()
    myComponentSegment = componentSegmentType(uID=myUID, name=myName, description=myDescr, fromElementUID=myFromElem, toElementUID=myToElem, structure=myStructure)
    myComponentSegments.add_componentSegment(myComponentSegment)
    parent.set_componentSegments(myComponentSegments)
Exemplo n.º 2
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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
Exemplo n.º 3
0
def createComponentSegment(parent, parentUID, fromElement='_Sec1_Elem1'):
    '''
    Used for generation of componentSegments within a wing
    create numOfComponentSegs in a wing
    @param parent: wingType object, Sections-object will be added here
    @param parentUID:  UID of parent object [string]
    '''
    #===========================================================================
    # Create Component Segement
    #===========================================================================
    myUID = parentUID + '_Cseg'
    myName = stringBaseType(None, None, None, parentUID + '_CSeg')
    myDescr = stringBaseType(None, None, None, parentUID + '_CSeg')
    myFromElem = stringBaseType(None, None, None, parentUID + fromElement)
    index = str(len(parent.get_sections().get_section()))
    myToElem = stringBaseType(None, None, None,
                              parentUID + '_Sec' + index + '_Elem1')
    myStructure = wingComponentSegmentStructureType()

    #===========================================================================
    # Back to CPACS
    #===========================================================================
    myComponentSegments = componentSegmentsType()
    myComponentSegment = componentSegmentType(None, None, None, myUID, myName,
                                              myDescr, myFromElem, myToElem,
                                              myStructure, None, None)
    myComponentSegments.add_componentSegment(myComponentSegment)
    parent.set_componentSegments(myComponentSegments)
Exemplo n.º 4
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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
Exemplo n.º 5
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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
Exemplo n.º 6
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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
Exemplo n.º 7
0
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)
Exemplo n.º 8
0
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)