Пример #1
0
    def __init__(self, aircraft):
        '''
        initializes fuel object
        mostly used for documentation
        establishes link to the aircraft class
        '''
        component.__init__(self)
        self.id = 'fuel'
        self.aircraft = aircraft
        self.level = 2

        #Mass
        self.mFuelMAX = mFuelMAX()
        self.mFuelMAXcenterWT = mFuelMAXcenterWT()
        self.mFuelMAXinnerWT = mFuelMAXinnerWT()
        self.mFuelMAXouterWT = mFuelMAXouterWT()
        self.mFuelMAXTT = mFuelMAXTT()
        self.mFM = mFM(
            cpacsPath=
            '/cpacs/vehicles/aircraft/model/analyses/massBreakdown/fuel/massDescription/mass'
        )
        self.mFuelCLIMB = mFuelCLIMB()
        self.mFuelDESCENT = mFuelDESCENT()
        self.mFuelCR = mFuelCR()
        self.mFuelTO = mFuelTO()
        self.mFuelRES = mFuelRES()
        self.TrimTank = TrimTank()

        # CoG
        self.posCoG = posCoG()
        self.posCoGcenterWT = posCoGcenterWT()
        self.posCoGinnerWT = posCoGinnerWT()
        self.posCoGouterWT = posCoGouterWT()
        self.posCoGTT = posCoGTT()
Пример #2
0
    def __init__(self, aircraft):
        """
        initializes fuel object
        mostly used for documentation
        establishes link to the aircraft class
        """
        component.__init__(self)
        self.id = "fuel"
        self.aircraft = aircraft
        self.level = 2

        # Mass
        self.mFuelMAX = mFuelMAX()
        self.mFuelMAXcenterWT = mFuelMAXcenterWT()
        self.mFuelMAXinnerWT = mFuelMAXinnerWT()
        self.mFuelMAXouterWT = mFuelMAXouterWT()
        self.mFuelMAXTT = mFuelMAXTT()
        self.mFM = mFM(cpacsPath="/cpacs/vehicles/aircraft/model/analyses/massBreakdown/fuel/massDescription/mass")
        self.mFuelCLIMB = mFuelCLIMB()
        self.mFuelDESCENT = mFuelDESCENT()
        self.mFuelCR = mFuelCR()
        self.mFuelTO = mFuelTO()
        self.mFuelRES = mFuelRES()
        self.TrimTank = TrimTank()

        # CoG
        self.posCoG = posCoG()
        self.posCoGcenterWT = posCoGcenterWT()
        self.posCoGinnerWT = posCoGinnerWT()
        self.posCoGouterWT = posCoGouterWT()
        self.posCoGTT = posCoGTT()
Пример #3
0
    def __init__(self, aircraft):
        '''
        initializes fuselage object
        mostly used for documentation
        establishes link to the aircraft class
        @Method: Component Constructor
        '''
        component.__init__(self)
        self.id = 'fuselage'
        self.aircraft = aircraft
        self.level = 2

        #Mass
        self.mFuselage = mFuselage()
        self.mFurn = mFurn(
            cpacsPath='/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mFurnishing/massDescription/mass')
        self.mStructure = mStructure(
            cpacsPath='/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mStructure/mFuselagesStructure/mFuselageStructure/massDescription/mass')

        #CoG
        self.posCoG = posCoG(
            cpacsPath='/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mStructure/mFuselagesStructure/mFuselageStructure/massDescription/location/x')

        #Geometry
        self.xRoot = xRoot()# the fuselages origin
        self.dfus = dfus()
        self.lfus = lfus()#cpacsPath='/cpacs/toolspecific/joeFuMo/lfuselage')
        self.lcabin = lcabin()#cpacsPath='/cpacs/toolspecific/joeFuMo/deck/length')
        self.lcockpit = lcockpit()
        self.lnose = lnose()#cpacsPath='/cpacs/toolspecific/joeFuMo/lnose')
        self.ltail = ltail()#cpacsPath='/cpacs/toolspecific/joeFuMo/ltail')
        self.loverlay = loverlay()#cpacsPath='/cpacs/toolspecific/joeFuMo/loverlay')
        self.wetArea = wetArea()
        self.LoD = LoD()

        #Cabin
        self.nRow = nRow()
        self.nPaxR = nPaxR()
        self.nAisle = nAisle()
        self.nClasses = nClasses()
        self.refLayout = refLayout()#cpacsPath='/cpacs/toolspecific/joeFuMo/deck/refLayout',)
        self.refAbreast = refAbreast()#cpacsPath='/cpacs/toolspecific/joeFuMo/deck/refAbreast',)
        self.cargoDeck = cargoDeck()#cpacsPath='/cpacs/toolspecific/joeFuMo/cargoDeck')
        self.paxDensity = paxDensity()
        self.dcabin = dcabin()
        self.hcabin = hcabin()
        self.vcabin = vcabin()
        self.yFloor = yFloor()
        self.zFloor = zFloor()

        #Aerodynamics
        self.formFactor = formFactor()
        self.reynoldsNr = reynoldsNr()
        self.cfLAM = cfLAM()
        self.cfTURB = cfTURB()
        self.cD0c = cD0c()
        self.dragArea = dragArea()
        self.nLam = nLam()
Пример #4
0
    def __init__(self, wing):
        component.__init__(self)
        self.wing = wing
        self.id = 'slat'
        self.level = 3

        #Geometry Data        
        self.refArea = refArea()
        self.avgChord = avgChord()
Пример #5
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    def __init__(self, vtp):
        component.__init__(self)
        self.vtp = vtp
        self.id = 'rudder'
        self.level = 3

        #Geometry Data        
        self.refArea = refArea()
        self.span = span()
        self.cRoot = cRoot()
        self.cTip = cTip()
Пример #6
0
    def __init__(self, aircraft):
        '''
        @Method: Component Constructor
        '''
        component.__init__(self)
        self.id = 'pylon'
        self.aircraft = aircraft
        self.level = 2

        #Mass
        self.mPylon = mPylon()
Пример #7
0
    def __init__(self, vtp):
        component.__init__(self)
        self.vtp = vtp
        self.id = 'rudder'
        self.level = 3

        #Geometry Data
        self.refArea = refArea()
        self.span = span()
        self.cRoot = cRoot()
        self.cTip = cTip()
Пример #8
0
    def __init__(self, htp):
        component.__init__(self)
        self.htp = htp
        self.id = 'elevator'
        self.level = 3

        #Geometry Data        
        self.refArea = refArea()
        self.rootYLocation = rootYLocation()
        self.span = span()
        self.cRoot = cRoot()
        self.cTip = cTip()
Пример #9
0
    def __init__(self, aircraft):
        '''
        @Method: Component Constructor
        '''
        component.__init__(self)
        self.id = 'pylon'
        self.aircraft = aircraft
        self.level = 2

        #Mass
        self.mPylon = mPylon(
            cpacsPath='/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mStructure/mPylons/massDescription/mass')
Пример #10
0
    def __init__(self, wing):
        component.__init__(self)
        self.wing = wing
        self.id = 'aileron'
        self.level = 3

        #Geometry Data        
        self.refArea = refArea()
        self.span = span()
        self.tipYLocation = tipYLocation()
        self.cRoot = cRoot()
        self.cTip = cTip()
        self.taperRatio = taperRatio()
Пример #11
0
    def __init__(self, aircraft):
        '''
        @Method: Component Constructor
        '''
        component.__init__(self)
        self.id = 'systems'
        self.aircraft = aircraft
        self.level = 2

        #Mass
        self.mSystems = mSystems(
            cpacsPath='/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mSystems/massDescription/mass')
        self.posCoG = posCoG(
            cpacsPath='/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mSystems/massDescription/location/x')
Пример #12
0
    def __init__(self, aircraft):
        '''
        will initialize instance mainly used for documentation
        links to the aircraft instance
        initiates the airfoil class
        @Method: Component Constructor
        '''
        component.__init__(self)
        self.id = 'tool'
        self.aircraft = aircraft
        self.level = 2

        #===============================================================================
        #Aircraft stuff 
        #===============================================================================
        self.aircraftName = parameter(cpacsPath='/cpacs/vehicles/aircraft/model/name', value='VAMPzero')
        self.aircraftDES = parameter(cpacsPath='/cpacs/vehicles/aircraft/model/description', value='VAMPzero')
        #commented out due to introduction of xMAC25
        #self.refX             = parameter(cpacsPath = '/cpacs/vehicles/aircraft/model/reference/point/x',value='0.0')
        self.refY = parameter(cpacsPath='/cpacs/vehicles/aircraft/model/reference/point/y', value='0.0')
        self.refZ = parameter(cpacsPath='/cpacs/vehicles/aircraft/model/reference/point/z', value='0.0')

        #=======================================================================
        # Lifting Line
        #=======================================================================
        self.liliname = parameter(cpacsPath='/cpacs/toolspecific/liftingLine/tool/name', value='LIFTING_LINE')
        self.liliversion = parameter(cpacsPath='/cpacs/toolspecific/liftingLine/tool/version', value='2.3.1')
        self.liliuID = parameter(cpacsPath='/cpacs/toolspecific/liftingLine/aircraftModelUID',
                                 value='A320modelID')#@todo: Model ID is not available at Time of Construction
        self.liliSpaneling = parameter(
            cpacsPath='/cpacs/toolspecific/liftingLine/toolParameters/wingPanelings/wingPaneling[1]/spanwise',
            value='5')
        self.liliCpaneling = parameter(
            cpacsPath='/cpacs/toolspecific/liftingLine/toolParameters/wingPanelings/wingPaneling[1]/chordwise',
            value='5')

        self.lilimode = parameter(cpacsPath='/cpacs/toolspecific/liftingLine/toolParameters/archiveMode', value='1')
        #self.lilipolars       = parameter(cpacsPath = '/cpacs/toolspecific/liftingLine/performanceMaps',value='')


        #=======================================================================
        #Header Information 
        #=======================================================================
        self.name = parameter(cpacsPath='/cpacs/header/name', value='Export from')
        self.creator = parameter(cpacsPath='/cpacs/header/creator', value='VAMPzero')
        self.timestamp = parameter(cpacsPath='/cpacs/header/timestamp', value='2010-12-31T12:00:00')
        self.version = parameter(cpacsPath='/cpacs/header/version', value='0.1')
        self.version = parameter(cpacsPath='/cpacs/header/cpacsVersion', value='2.0')
Пример #13
0
    def __init__(self, aircraft):
        '''
        @Method: Component Constructor
        '''
        component.__init__(self)
        self.id = 'systems'
        self.aircraft = aircraft
        self.level = 2

        #Mass
        self.mSystems = mSystems(
            cpacsPath=
            '/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mSystems/massDescription/mass'
        )
        self.posCoG = posCoG(
            cpacsPath=
            '/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mSystems/massDescription/location/x'
        )
Пример #14
0
    def __init__(self, wing):
        component.__init__(self)
        self.wing = wing
        self.id = 'flap'
        self.level = 3

        #Geometry Data        
        self.refArea = refArea()
        self.avgChordInnerFlap = avgChordInnerFlap()
        self.spanInnerFlap = spanInnerFlap()
        self.refAreaInnerFlap = refAreaInnerFlap()
        self.refAreaOuterFlap = refAreaOuterFlap()
        self.avgChordOuterFlap = avgChordOuterFlap()
        self.spanOuterFlap = spanOuterFlap()

        #Aerodynamic Data
        self.dCLmaxTO = dCLmaxTO()
        self.dCLmaxL = dCLmaxL()
        self.dCDTO = dCDTO()
        self.dCDL = dCDL()
Пример #15
0
    def __init__(self, wing):
        component.__init__(self)
        self.wing = wing
        self.id = 'flap'
        self.level = 3

        #Geometry Data        
        self.refArea = refArea()
        self.avgChordInnerFlap = avgChordInnerFlap()
        self.spanInnerFlap = spanInnerFlap()
        self.refAreaInnerFlap = refAreaInnerFlap()
        self.refAreaOuterFlap = refAreaOuterFlap()
        self.avgChordOuterFlap = avgChordOuterFlap()
        self.spanOuterFlap = spanOuterFlap()

        #Aerodynamic Data
        self.dCLmaxTO = dCLmaxTO()
        self.dCLmaxL = dCLmaxL()
        self.dCDTO = dCDTO()
        self.dCDL = dCDL()
Пример #16
0
    def __init__(self, aircraft):
        '''
        @Method: Component Constructor
        '''
        component.__init__(self)
        self.id = 'landingGear'
        self.aircraft = aircraft
        self.level = 2

        #Parameters
        self.mLandingGear = mLandingGear(
            cpacsPath='/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mStructure/mLandingGears/massDescription/mass')
        self.eta = eta()
        self.xsi = xsi()
        self.xLandingGear = xLandingGear()
        self.yLandingGear = yLandingGear()
        self.zLandingGear = zLandingGear()
        self.xNoseGear = xNoseGear()

        #Aerodynamic
        self.dCDextendedLG = dCDextendedLG()
Пример #17
0
    def __init__(self, wing, position=''):
        component.__init__(self)
        self.wing = wing
        self.id = self.wing.id + position + 'airfoil'
        self.position = position
        self.level = 3

        self.aType = aType()

        #Geometry Data        
        self.tc = tc()
        self.ctm = ctm()

        #Aero Data
        self.reynoldsNr = reynoldsNr()
        self.clMAX = clMAX()


###################################################################################################
#EOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFE#
###################################################################################################
        
Пример #18
0
    def __init__(self, aircraft):
        '''
        @Method: Component Constructor
        '''
        component.__init__(self)
        self.id = 'landingGear'
        self.aircraft = aircraft
        self.level = 2

        #Parameters
        self.mLandingGear = mLandingGear()
        self.mNoseGear = mNoseGear()
        self.eta = eta()
        self.xsi = xsi()
        self.xLandingGear = xLandingGear(cpacsPath='/cpacs/vehicles/aircraft/model/landingGear/mainGears/mainGear/fuselageAttachment/translation/x')
        self.yLandingGear = yLandingGear(cpacsPath='/cpacs/vehicles/aircraft/model/landingGear/mainGears/mainGear/fuselageAttachment/translation/y')
        self.zLandingGear = zLandingGear(cpacsPath='/cpacs/vehicles/aircraft/model/landingGear/mainGears/mainGear/fuselageAttachment/translation/z')
        self.xNoseGear = xNoseGear(cpacsPath='/cpacs/vehicles/aircraft/model/landingGear/noseGears/noseGear/fuselageAttachment/translation/x')
        self.yNoseGear = yNoseGear(cpacsPath='/cpacs/vehicles/aircraft/model/landingGear/noseGears/noseGear/fuselageAttachment/translation/y')
        self.zNoseGear = zNoseGear(cpacsPath='/cpacs/vehicles/aircraft/model/landingGear/noseGears/noseGear/fuselageAttachment/translation/z')

        #Aerodynamic
        self.dCDextendedLG = dCDextendedLG()
Пример #19
0
    def __init__(self, aircraft):
        '''
        @Method: Component Constructor
        '''
        component.__init__(self)
        self.id = 'payload'
        self.aircraft = aircraft
        self.level = 2

        #Mass
        self.mPayload = mPayload(
            cpacsPath='/cpacs/vehicles/aircraft/model/analyses/massBreakdown/payload/massDescription/mass')
        self.mCargo = mCargo(
            cpacsPath='/cpacs/vehicles/aircraft/model/analyses/massBreakdown/payload/mCargo/massDescription/mass')
        self.paxSeats = paxSeats(cpacsPath='/cpacs/vehicles/aircraft/model/global/paxSeats')
        self.mPax = mPax()
        self.mSinglePax = mSinglePax()
        #Cog
        self.posCoG = posCoG()

        ###################################################################################################
        #EOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFE#
        ###################################################################################################
Пример #20
0
    def __init__(self, aircraft):
        '''
        @Method: Component Constructor
        '''
        component.__init__(self)
        self.id = 'payload'
        self.aircraft = aircraft
        self.level = 2

        #Mass
        self.mPayload = mPayload(
            cpacsPath=
            '/cpacs/vehicles/aircraft/model/analyses/massBreakdown/payload/massDescription/mass'
        )
        self.mCargo = mCargo(
            cpacsPath=
            '/cpacs/vehicles/aircraft/model/analyses/massBreakdown/payload/mCargo/massDescription/mass'
        )
        self.paxSeats = paxSeats(
            cpacsPath='/cpacs/vehicles/aircraft/model/global/paxSeats')
        self.mPax = mPax()
        self.mSinglePax = mSinglePax()
        #Cog
        self.posCoG = posCoG()
Пример #21
0
    def __init__(self, aircraft):
        '''
        will initialize instance mainly used for documentation
        links to the aircraft instance
        initiates the airfoil class
        @Method: Component Constructor
        '''
        component.__init__(self)
        self.id = 'strut'
        self.aircraft = aircraft
        self.level = 2

        # Mass
        self.mStrut = mStrut(
            cpacsPath=
            '/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mStructure/mWingsStructure/mWingStructure[4]/massDescription['
            + self.id + '_mass]/mass')
        self.parentUID = parameter(
            value=self.id,
            cpacsPath=
            '/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mStructure/mWingsStructure/mWingStructure[4]/massDescription['
            + self.id + '_mass]/parentUID')

        # Geometry
        self.refArea = refArea()
        self.expArea = expArea()
        self.wetArea = wetArea()
        self.aspectRatio = aspectRatio()
        self.span = span()
        self.depth = depth()
        self.active = active()
        self.taperRatio = taperRatio()
        self.tcAVG = tcAVG()
        self.cRoot = cRoot()
        self.cTip = cTip()
        self.cMAC = cMAC()
        self.yMAC = yMAC()
        self.xMAC = xMAC()
        self.xMAC25 = xMAC25()
        self.phiLE = phiLE()
        self.phiTE = phiTE()
        self.phi25 = phi25()
        self.phi50 = phi50()
        self.dihedral = dihedral()
        self.twist = twist()
        self.etaStrut = etaStrut()

        self.xRoot = xRoot()
        self.yRoot = yRoot()
        self.zRoot = zRoot()

        self.xTip = xTip()
        self.yTip = yTip()
        self.zTip = zTip()

        # Aerodynamics
        self.formFactor = formFactor()
        self.reynoldsNr = reynoldsNr()
        self.cfLAM = cfLAM()
        self.cfTURB = cfTURB()
        self.cD0c = cD0c()
        self.nLam = nLam()

        # Airfoil
        self.airfoilr = airfoil(self, position='root')
        self.airfoilt = airfoil(self, position='tip')
Пример #22
0
    def __init__(self, aircraft):
        '''
        will initialize instance mainly used for documentation
        links to the aircraft instance
        initiates the airfoil class
        '''
        component.__init__(self)
        self.id = 'htp'
        self.aircraft = aircraft
        self.level = 2

        self.UID = uID(cpacsPath='/cpacs/toolspecific/vampZero/htpUID')

        # Mass
        self.mHtp = mHtp(
            cpacsPath=
            '/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mStructure/mWingsStructure/mWingStructure[2]/massDescription['
            + self.id + '_mass]/mass')
        self.parentUID = parameter(
            value=self.id,
            cpacsPath=
            '/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mStructure/mWingsStructure/mWingStructure[2]/massDescription['
            + self.id + '_mass]/parentUID')

        # CoG
        self.posCoG = posCoG(
            cpacsPath=
            '/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mStructure/mWingsStructure/mWingStructure[2]/massDescription['
            + self.id + '_mass]/location/x')

        # Geometry
        self.refArea = refArea()
        self.refAreaTakeOff = refAreaTakeOff()
        self.refAreaCruise = refAreaCruise()
        self.refAreaLanding = refAreaLanding()
        self.expArea = expArea()
        self.wetArea = wetArea()
        self.aspectRatio = aspectRatio()
        self.span = span()
        self.taperRatio = taperRatio()
        self.tcAVG = tcAVG()
        self.cRoot = cRoot()
        self.cTip = cTip()
        self.cMAC = cMAC()
        self.yMAC = yMAC()
        self.xMAC = xMAC()
        self.xMAC25 = xMAC25()
        self.phiLE = phiLE()
        self.phiTE = phiTE()
        self.phi25 = phi25()
        self.phi50 = phi50()
        self.xRoot = xRoot()
        self.zRoot = zRoot()
        self.lHT = lHT()
        self.cHT = cHT()
        self.dihedral = dihedral()
        self.LoD = LoD()
        self.location = location()

        # Aerodynamic
        self.cLalpha = cLalpha()
        self.cLMAX = cLMAX()
        #self.cLMIN = cLMIN()
        self.cLMAXht = cLMAXht()
        self.CLalphaHTP_TO = CLalphaHTP_TO()
        self.CLalphaHTP_CR = CLalphaHTP_CR()
        self.CLalphaHTP_L = CLalphaHTP_L()
        self.formFactor = formFactor()
        self.reynoldsNr = reynoldsNr()
        self.cfLAM = cfLAM()
        self.cfTURB = cfTURB()
        self.cD0c = cD0c()
        self.nLam = nLam()
        self.detadalpha = detadalpha()
        self.DPR = DPR()

        # Airfoil
        self.airfoilr = airfoil(self)  # Root Airfoil
        self.airfoilt = airfoil(self)  # Tip  Airfoil

        # Elevator
        self.elevator = elevator(self)
Пример #23
0
    def __init__(self, aircraft):
        """
        will initialize instance mainly used for documentation
        links to the aircraft instance
        initiates the airfoil class
        @Method: Component Constructor
        """
        component.__init__(self)
        self.id = "strut"
        self.aircraft = aircraft
        self.level = 2

        # Mass
        self.mStrut = mStrut(
            cpacsPath="/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mStructure/mWingsStructure/mWingStructure[4]/massDescription["
            + self.id
            + "_mass]/mass"
        )
        self.parentUID = parameter(
            value=self.id,
            cpacsPath="/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mStructure/mWingsStructure/mWingStructure[4]/massDescription["
            + self.id
            + "_mass]/parentUID",
        )

        # Geometry
        self.refArea = refArea()
        self.expArea = expArea()
        self.wetArea = wetArea()
        self.aspectRatio = aspectRatio()
        self.span = span()
        self.depth = depth()
        self.active = active()
        self.taperRatio = taperRatio()
        self.tcAVG = tcAVG()
        self.cRoot = cRoot()
        self.cTip = cTip()
        self.cMAC = cMAC()
        self.yMAC = yMAC()
        self.xMAC = xMAC()
        self.xMAC25 = xMAC25()
        self.phiLE = phiLE()
        self.phiTE = phiTE()
        self.phi25 = phi25()
        self.phi50 = phi50()
        self.dihedral = dihedral()
        self.twist = twist()
        self.etaStrut = etaStrut()

        self.xRoot = xRoot()
        self.yRoot = yRoot()
        self.zRoot = zRoot()

        self.xTip = xTip()
        self.yTip = yTip()
        self.zTip = zTip()

        # Aerodynamics
        self.formFactor = formFactor()
        self.reynoldsNr = reynoldsNr()
        self.cfLAM = cfLAM()
        self.cfTURB = cfTURB()
        self.cD0c = cD0c()
        self.nLam = nLam()

        # Airfoil
        self.airfoilr = airfoil(self, position="root")
        self.airfoilt = airfoil(self, position="tip")
Пример #24
0
    def __init__(self, aircraft):
        '''
        will initialize instance mainly used for documentation
        links to the aircraft instance
        initiates the airfoil class
        @Method: Component Constructor
        '''
        component.__init__(self)
        self.id = 'vtp'
        self.aircraft = aircraft
        self.level = 2

        self.UID = uID(cpacsPath='/cpacs/toolspecific/vampZero/vtpUID')
		
        # Mass
        self.mVtp = mVtp(
            cpacsPath='/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mStructure/mWingsStructure/mWingStructure[3]/massDescription['+self.id+'_mass]/mass')
        self.parentUID = parameter(value=self.id, 
			cpacsPath='/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mStructure/mWingsStructure/mWingStructure[3]/massDescription['+self.id+'_mass]/parentUID')

        # CoG
        self.posCoG = posCoG(
            cpacsPath='/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mStructure/mWingsStructure/mWingStructure[3]/massDescription['+self.id+'_mass]/location/x')
		
        # Geometry
        self.refArea = refArea()
        self.refAreaTakeOff = refAreaTakeOff()
        self.refAreaLanding = refAreaLanding()
        self.expArea = expArea()
        self.wetArea = wetArea()
        self.aspectRatio = aspectRatio()
        self.span = span()
        self.taperRatio = taperRatio()
        self.tcAVG = tcAVG()
        self.cRoot = cRoot()
        self.cTip = cTip()
        self.cMAC = cMAC()
        self.yMAC = yMAC()
        self.xMAC = xMAC()
        self.phiLE = phiLE()
        self.phiTE = phiTE()
        self.phi25 = phi25()
        self.phi50 = phi50()
        self.xRoot = xRoot()
        self.zRoot = zRoot()
        self.lVT = lVT()
        self.cVT = cVT()
        self.LoD = LoD()

        # Aerodynamics
        self.cLalpha = cLalpha()
        self.cLMAX = cLMAX()
        self.formFactor = formFactor()
        self.reynoldsNr = reynoldsNr()
        self.cfLAM = cfLAM()
        self.cfTURB = cfTURB()
        self.cD0c = cD0c()
        self.nLam = nLam()

        # Airfoil
        self.airfoilr = airfoil(self)  # Root Airfoil
        self.airfoilt = airfoil(self)  # Tip  Airfoil

        # Rudder
        self.rudder = rudder(self)
Пример #25
0
    def __init__(self, aircraft):
        '''
        will initialize instance mainly used for documentation
        links to the aircraft instance
        initiates the airfoil class
        @Method: Component Constructor
        '''
        component.__init__(self)
        self.id = 'vtp'
        self.aircraft = aircraft
        self.level = 2

        self.UID = uID(cpacsPath='/cpacs/toolspecific/vampZero/vtpUID')

        # Mass
        self.mVtp = mVtp(
            cpacsPath=
            '/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mStructure/mWingsStructure/mWingStructure[3]/massDescription['
            + self.id + '_mass]/mass')
        self.parentUID = parameter(
            value=self.id,
            cpacsPath=
            '/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mStructure/mWingsStructure/mWingStructure[3]/massDescription['
            + self.id + '_mass]/parentUID')

        # CoG
        self.posCoG = posCoG(
            cpacsPath=
            '/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mStructure/mWingsStructure/mWingStructure[3]/massDescription['
            + self.id + '_mass]/location/x')

        # Geometry
        self.refArea = refArea()
        self.refAreaTakeOff = refAreaTakeOff()
        self.refAreaLanding = refAreaLanding()
        self.expArea = expArea()
        self.wetArea = wetArea()
        self.aspectRatio = aspectRatio()
        self.span = span()
        self.taperRatio = taperRatio()
        self.tcAVG = tcAVG()
        self.cRoot = cRoot()
        self.cTip = cTip()
        self.cMAC = cMAC()
        self.yMAC = yMAC()
        self.xMAC = xMAC()
        self.phiLE = phiLE()
        self.phiTE = phiTE()
        self.phi25 = phi25()
        self.phi50 = phi50()
        self.xRoot = xRoot()
        self.zRoot = zRoot()
        self.lVT = lVT()
        self.cVT = cVT()
        self.LoD = LoD()

        # Aerodynamics
        self.cLalpha = cLalpha()
        self.cLMAX = cLMAX()
        self.formFactor = formFactor()
        self.reynoldsNr = reynoldsNr()
        self.cfLAM = cfLAM()
        self.cfTURB = cfTURB()
        self.cD0c = cD0c()
        self.nLam = nLam()

        # Airfoil
        self.airfoilr = airfoil(self)  # Root Airfoil
        self.airfoilt = airfoil(self)  # Tip  Airfoil

        # Rudder
        self.rudder = rudder(self)
Пример #26
0
    def __init__(self, aircraft):
        '''
        will initialize instance mainly used for documentation
        links to the aircraft instance
        initiates the airfoil class
        @Method: Component Constructor
        '''
        component.__init__(self)
        self.id = 'wing'
        self.aircraft = aircraft
        self.level = 2
        self.UID = uID(cpacsPath='/cpacs/toolspecific/vampZero/wingUID')

        # Mass
        self.mWing = mWing(
            cpacsPath='/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mStructure/mWingsStructure/mWingStructure[1]/massDescription['+self.id+'_mass]/mass')
        self.parentUID = parameter(value=self.id, 
			cpacsPath='/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mStructure/mWingsStructure/mWingStructure[1]/massDescription['+self.id+'_mass]/parentUID')

        # CoG
        self.posCoG = posCoG(
            cpacsPath='/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mStructure/mWingsStructure/mWingStructure[1]/massDescription['+self.id+'_mass]/location/x')

        # Geometry
        self.location = location()		
        self.refArea = refArea(cpacsPath='/cpacs/vehicles/aircraft/model/reference/area')
        self.expArea = expArea()
        self.wetArea = wetArea()
        self.aspectRatio = aspectRatio()
        self.span = span()
        self.taperRatio = taperRatio()
        self.tcAVG = tcAVG()
        self.cRoot = cRoot()
        self.cTip = cTip()
        self.cMAC = cMAC(cpacsPath='/cpacs/vehicles/aircraft/model/reference/length')
        self.yMAC = yMAC()
        self.xMAC = xMAC()
        self.xMAC25 = xMAC25(cpacsPath='/cpacs/vehicles/aircraft/model/reference/point/x')
        self.phiLE = phiLE()
        self.phiTE = phiTE()
        self.phi25 = phi25()
        self.phi50 = phi50()
        self.dihedral = dihedral()
        self.twist = twist()
        self.xRoot = xRoot()
        self.zRoot = zRoot()
        self.LoD = LoD()
        self.etaKink = etaKink()
        self.etaEngine = etaEngine()

        # Aerodynamics
        self.cLalpha = cLalpha()
        self.cLMAX = cLMAX()
        self.formFactor = formFactor()
        self.reynoldsNr = reynoldsNr()  # cpacsPath='/cpacs/vehicles/aircraft/model/global/aeroPerformanceMap/reynoldsNumber')
        self.cfLAM = cfLAM()
        self.cfTURB = cfTURB()
        self.cD0c = cD0c()
        self.oswald = oswald()
        self.cDMINoffset = cDMINoffset()
        self.nLam = nLam()
        self.cDw = cDw()
        self.machDD = machDD()
        self.machCrit = machCrit()
        self.cM0CR = cM0CR()
        self.cM0TO = cM0TO()
        self.cM0L = cM0L()

        # Airfoil
        self.airfoilr = airfoil(self, position='root')
        self.airfoilt = airfoil(self, position='tip')

        # Aileron
        self.aileron = aileron(self)

        # Slat
        self.slat = slat(self)

        # Flap
        self.flap = flap(self)

        # Spoiler
        self.spoiler = spoiler(self)

        # CPACS Stuff for Export to higher Level
        self.xFuselage = xFuselage()
        self.yFuselage = yFuselage()
        self.zFuselage = zFuselage()
        self.cFuselage = cFuselage()

        self.xKink = xKink()
        self.yKink = yKink()
        self.zKink = zKink()
        self.cKink = cKink()

        self.xTip = xTip()
        self.zTip = zTip()
Пример #27
0
    def __init__(self):
        '''
        will initialize all values upon creation of the instance. Mainly used for documentation
        '''
        component.__init__(self)
        self.id = 'aircraft'
        self.level = 1

        self.modelUID = uID(cpacsPath='/cpacs/toolspecific/vampZero/aircraftModelUID')
        self.version  = parameter(value=0.1, cpacsPath='/cpacs/header/version')

        # Mass Data
        self.mLM = mLM(cpacsPath='/cpacs/vehicles/aircraft/model/analyses/massBreakdown/designMasses/mMLM/mass')
        self.mTOM = mTOM(cpacsPath='/cpacs/vehicles/aircraft/model/analyses/massBreakdown/designMasses/mTOM/mass')
        self.mZFW = mZFW(cpacsPath='/cpacs/vehicles/aircraft/model/analyses/massBreakdown/designMasses/mZFM/mass')
        self.oEM = oEM(cpacsPath='/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/massDescription/mass')
        self.oIM = oIM(
            cpacsPath='/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mOperatorItems/massDescription/mass')

        # CoG
        self.posCoG = posCoG(
            cpacsPath='/cpacs/vehicles/aircraft/model/analyses/massBreakdown/designMasses/mTOM/location/x')
        self.posNP = posNP()
        self.posCoGOEM = posCoGOEM()
        self.posCoGMIN = posCoGMIN()
        self.posCoGMAX = posCoGMAX()
        self.static_margin = static_margin()

        # Inertia
        self.massIXmTOM = massIXmTOM(
            cpacsPath='/cpacs/vehicles/aircraft/model/analyses/massBreakdown/designMasses/mTOM/massInertia/Jxx')
        self.massIYmTOM = massIYmTOM(
            cpacsPath='/cpacs/vehicles/aircraft/model/analyses/massBreakdown/designMasses/mTOM/massInertia/Jyy')
        self.massIZmTOM = massIZmTOM(
            cpacsPath='/cpacs/vehicles/aircraft/model/analyses/massBreakdown/designMasses/mTOM/massInertia/Jzz')
        self.massIXmZFW = massIXmZFW(
            cpacsPath='/cpacs/vehicles/aircraft/model/analyses/massBreakdown/designMasses/mZFM/massInertia/Jxx')
        self.massIYmZFW = massIYmZFW(
            cpacsPath='/cpacs/vehicles/aircraft/model/analyses/massBreakdown/designMasses/mZFM/massInertia/Jyy')
        self.massIZmZFW = massIZmZFW(
            cpacsPath='/cpacs/vehicles/aircraft/model/analyses/massBreakdown/designMasses/mZFM/massInertia/Jzz')
        self.massIXoEM = massIXoEM(
            cpacsPath='/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/massDescription/massInertia/Jxx')
        self.massIYoEM = massIYoEM(
            cpacsPath='/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/massDescription/massInertia/Jyy')
        self.massIZoEM = massIZoEM(
            cpacsPath='/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/massDescription/massInertia/Jzz')

        # Performance Data
        self.desRange = desRange() #@todo: set correct xpath (cpacsPath='/cpacs/vehicles/aircraft/model/global/designRange')
        self.machCR = machCR(cpacsPath='/cpacs/vehicles/aircraft/model/global/machCruise')
        self.altCR = altCR()
        self.sTOFL = sTOFL()
        self.sTOFLISA = sTOFLISA()
        self.sLFL = sLFL() #@todo: set correct xpath (cpacsPath='/cpacs/vehicles/aircraft/model/global/sFL')
        self.rangeType = rangeType()
        self.timeRES = timeRES()
        self.timeDESCENT = timeDESCENT()
        self.timeCLIMB = timeCLIMB()
        self.timeCR = timeCR()
        self.distRES = distRES()
        self.distDESCENT = distDESCENT()
        self.distCLIMB = distCLIMB()
        self.distCR = distCR()
        self.gammaCLIMB = gammaCLIMB()
        self.gammaDESCENT = gammaDESCENT()
        self.IASCLIMB = IASCLIMB()
        self.IASDESCENT = IASDESCENT()

        # Crew Data
        self.nPilot = nPilot()
        self.nCabinCrew = nCabinCrew()

        # Sizing Data
        self.wsTO = wsTO()
        self.wsL = wsL()
        self.wsMAX = wsMAX()
        self.twTO = twTO()
        self.twFAR20121a = twFAR25121a()
        self.twFAR20121b = twFAR25121b()
        self.twTOP25 = twTOP25()

        # Aerodynamics Data
        self.cLCR = cLCR()
        self.cLMAX = cLMAX()
        self.cLTO = cLTO()
        self.cLL = cLL()
        self.cDCR = cDCR()
        self.cDTO = cDTO()
        self.cDL = cDL()
        self.cD0 = cD0()
        self.loDCR = loDCR()
        self.loDTO = loDTO()
        self.loDLOI = loDLOI()
        self.loDCLIMB = loDCLIMB()
        self.oswald = oswald()
        self.cLROLL = cLROLL()

        # DOC
        self.aFactor = aFactor()
        self.inflation = inflation()
        self.USDexchangeEURO = USDexchangeEURO()
        self.tBlock = tBlock()
        self.tFlight = tFlight()
        self.utilization = utilization()
        self.costDepreciation = costDepreciation()
        self.costFuel = costFuel()
        self.costMaintenance = costMaintenance()
        self.costAircraftMaintenance = costAircraftMaintenance()
        self.costEngineMaintenance = costEngineMaintenance()
        self.costCrew = costCrew()
        self.costCap = costCap()
        self.costGround = costGround()
        self.costNavigation = costNavigation()
        self.costLanding = costLanding()
        self.costInterest = costInterest()
        self.costInsurance = costInsurance()
        self.costEmissionTrade = costEmissionTrade()
        self.flightCycles = flightCycles()
        self.priceFuel = priceFuel()
        self.priceAircraft = priceAircraft()
        self.DOC = DOC()
        self.COC = COC()
        self.COO = COO()
        self.C1 = C1()
        self.C2 = C2()
        self.aFactor = aFactor()
        self.costCap = costCap()
        self.flightCycles = flightCycles()

        #Stability
        #self.staticMargin = staticMargin()
        
        #Controllability
        #self.refAreaHtpMIN = refAreaHtpMIN()

        # Component Objects
        self.wing = wing(self)
        self.strut = strut(self)
        self.fuselage = fuselage(self)
        self.vtp = vtp(self)
        self.htp = htp(self)
        self.engine = engine(self)
        self.landingGear = landingGear(self)
        self.systems = systems(self)
        self.payload = payload(self)
        self.pylon = pylon(self)
        self.fuel = fuel(self)
        self.atmosphere = atmosphere(self)
        self.tool = tool(self)
Пример #28
0
    def __init__(self, aircraft):
        '''
        will initialize instance mainly used for documentation
        links to the aircraft instance
        initiates the airfoil class
        @Method: Component Constructor
        '''
        component.__init__(self)
        self.id = 'wing'
        self.aircraft = aircraft
        self.level = 2
        self.UID = uID(cpacsPath='/cpacs/toolspecific/vampZero/wingUID')

        # Mass
        self.mWing = mWing(
            cpacsPath=
            '/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mStructure/mWingsStructure/mWingStructure[1]/massDescription['
            + self.id + '_mass]/mass')
        self.parentUID = parameter(
            value=self.id,
            cpacsPath=
            '/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mStructure/mWingsStructure/mWingStructure[1]/massDescription['
            + self.id + '_mass]/parentUID')

        # CoG
        self.posCoG = posCoG(
            cpacsPath=
            '/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mStructure/mWingsStructure/mWingStructure[1]/massDescription['
            + self.id + '_mass]/location/x')

        # Geometry
        self.location = location()
        self.refArea = refArea(
            cpacsPath='/cpacs/vehicles/aircraft/model/reference/area')
        self.expArea = expArea()
        self.wetArea = wetArea()
        self.aspectRatio = aspectRatio()
        self.span = span()
        self.taperRatio = taperRatio()
        self.tcAVG = tcAVG()
        self.cRoot = cRoot()
        self.cTip = cTip()
        self.cMAC = cMAC(
            cpacsPath='/cpacs/vehicles/aircraft/model/reference/length')
        self.yMAC = yMAC()
        self.xMAC = xMAC()
        self.xMAC25 = xMAC25(
            cpacsPath='/cpacs/vehicles/aircraft/model/reference/point/x')
        self.phiLE = phiLE()
        self.phiTE = phiTE()
        self.phi25 = phi25()
        self.phi50 = phi50()
        self.dihedral = dihedral()
        self.twist = twist()
        self.xRoot = xRoot()
        self.zRoot = zRoot()
        self.LoD = LoD()
        self.etaKink = etaKink()
        self.etaEngine = etaEngine()

        # Aerodynamics
        self.cLalpha = cLalpha()
        self.cLMAX = cLMAX()
        self.formFactor = formFactor()
        self.reynoldsNr = reynoldsNr(
        )  # cpacsPath='/cpacs/vehicles/aircraft/model/global/aeroPerformanceMap/reynoldsNumber')
        self.cfLAM = cfLAM()
        self.cfTURB = cfTURB()
        self.cD0c = cD0c()
        self.oswald = oswald()
        self.cDMINoffset = cDMINoffset()
        self.nLam = nLam()
        self.cDw = cDw()
        self.machDD = machDD()
        self.machCrit = machCrit()
        self.cM0CR = cM0CR()
        self.cM0TO = cM0TO()
        self.cM0L = cM0L()

        # Airfoil
        self.airfoilr = airfoil(self, position='root')
        self.airfoilt = airfoil(self, position='tip')

        # Aileron
        self.aileron = aileron(self)

        # Slat
        self.slat = slat(self)

        # Flap
        self.flap = flap(self)

        # Spoiler
        self.spoiler = spoiler(self)

        # CPACS Stuff for Export to higher Level
        self.xFuselage = xFuselage()
        self.yFuselage = yFuselage()
        self.zFuselage = zFuselage()
        self.cFuselage = cFuselage()

        self.xKink = xKink()
        self.yKink = yKink()
        self.zKink = zKink()
        self.cKink = cKink()

        self.xTip = xTip()
        self.zTip = zTip()
Пример #29
0
    def __init__(self, aircraft):
        '''
        @Method: Component Constructor
        '''
        component.__init__(self)
        self.id = 'engine'
        self.aircraft = aircraft
        self.level = 2
        self.UID = uID(cpacsPath='/cpacs/toolspecific/vampZero/engineUID')


        #Mass
        self.mEngine = mEngine(
            cpacsPath='/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mPowerUnits/massDescription/mass')

        #CoG
        self.posCoG = posCoG()

        #Inertia
        self.massIX = massIX(
            cpacsPath='/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mPowerUnits/massDescription/massInertia/Jxx')
        self.massIY = massIY(
            cpacsPath='/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mPowerUnits/massDescription/massInertia/Jyy')
        self.massIZ = massIZ(
            cpacsPath='/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mPowerUnits/massDescription/massInertia/Jzz')

        #Geometry
        self.lEngine = lEngine(cpacsPath='/cpacs/vehicles/engines/engine/geometry/length')
        self.dEngine = dEngine(cpacsPath='/cpacs/vehicles/engines/engine/geometry/diameter')
        self.yEngine = yEngine(cpacsPath='/cpacs/vehicles/aircraft/model/engines/engine/transformation/translation/y')
        self.xEngine = xEngine(cpacsPath='/cpacs/vehicles/aircraft/model/engines/engine/transformation/translation/x')
        self.zEngine = zEngine(cpacsPath='/cpacs/vehicles/aircraft/model/engines/engine/transformation/translation/z')
        self.wetArea = wetArea()
        self.location = location()

        #Aerodynamics
        self.formFactor = formFactor()
        self.reynoldsNr = reynoldsNr()
        self.cfLAM = cfLAM()
        self.cfTURB = cfTURB()
        self.cD0c = cD0c()
        self.dCDOEI = dCDOEI()
        self.nLam = nLam()

        #Propulsion
        self.mDotEngine = mDotEngine()
        self.thrustTO = thrustTO(cpacsPath='/cpacs/vehicles/engines/engine/analysis/thrust00')
        self.thrustTOISA = thrustTOISA()
        self.thrustCR = thrustCR()
        self.nEngine = nEngine()
        self.sfcCR = sfcCR()
        self.sfcLOI = sfcLOI()
        self.bypassRatio = bypassRatio(cpacsPath='/cpacs/vehicles/engines/engine/analysis/bpr00')
        self.thrustTWDat = thrustTWDat(cpacsPath='/cpacs/toolspecific/tWDat/thrust00Scaling')
        self.etaCompr = etaCompr()
        self.etaFan = etaFan()
        self.etaProp = etaProp()
        self.etaTherm = etaTherm()
        self.etaTransm = etaTransm()
        self.etaTurb = etaTurb()
        self.TET = TET()
        self.OPR = OPR()
Пример #30
0
    def __init__(self, aircraft):
        '''
        will initialize instance mainly used for documentation
        links to the aircraft instance
        initiates the airfoil class
        '''
        component.__init__(self)
        self.id = 'htp'
        self.aircraft = aircraft
        self.level = 2

        self.UID = uID(cpacsPath='/cpacs/toolspecific/vampZero/htpUID')

        # Mass
        self.mHtp = mHtp(
            cpacsPath='/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mStructure/mWingsStructure/mWingStructure[2]/massDescription['+self.id+'_mass]/mass')
        self.parentUID = parameter(value=self.id, 
			cpacsPath='/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mStructure/mWingsStructure/mWingStructure[2]/massDescription['+self.id+'_mass]/parentUID')

        # CoG
        self.posCoG = posCoG(
            cpacsPath='/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mStructure/mWingsStructure/mWingStructure[2]/massDescription['+self.id+'_mass]/location/x')

        # Geometry
        self.refArea = refArea()
        self.refAreaTakeOff = refAreaTakeOff() 
        self.refAreaCruise = refAreaCruise() 
        self.refAreaLanding = refAreaLanding()        
        self.expArea = expArea()
        self.wetArea = wetArea()
        self.aspectRatio = aspectRatio()
        self.span = span()
        self.taperRatio = taperRatio()
        self.tcAVG = tcAVG()
        self.cRoot = cRoot()
        self.cTip = cTip()
        self.cMAC = cMAC()
        self.yMAC = yMAC()
        self.xMAC = xMAC()
        self.xMAC25 = xMAC25()
        self.phiLE = phiLE()
        self.phiTE = phiTE()
        self.phi25 = phi25()
        self.phi50 = phi50()
        self.xRoot = xRoot()
        self.zRoot = zRoot()
        self.lHT = lHT()
        self.cHT = cHT()
        self.dihedral = dihedral()
        self.LoD = LoD()
        self.location = location()

        # Aerodynamic
        self.cLalpha = cLalpha()
        self.cLMAX = cLMAX()
        #self.cLMIN = cLMIN()
        self.cLMAXht = cLMAXht()
        self.CLalphaHTP_TO = CLalphaHTP_TO()
        self.CLalphaHTP_CR = CLalphaHTP_CR()
        self.CLalphaHTP_L = CLalphaHTP_L()
        self.formFactor = formFactor()
        self.reynoldsNr = reynoldsNr()
        self.cfLAM = cfLAM()
        self.cfTURB = cfTURB()
        self.cD0c = cD0c()
        self.nLam = nLam()
        self.detadalpha = detadalpha()
        self.DPR = DPR()

        # Airfoil
        self.airfoilr = airfoil(self)  # Root Airfoil
        self.airfoilt = airfoil(self)  # Tip  Airfoil

        # Elevator
        self.elevator = elevator(self)
Пример #31
0
    def __init__(self, aircraft):
        '''
        @Method: Component Constructor
        '''
        component.__init__(self)
        self.id = 'engine'
        self.aircraft = aircraft
        self.level = 2
        self.UID = uID(cpacsPath='/cpacs/toolspecific/vampZero/engineUID')


        #Mass
        self.mEngine = mEngine(
            cpacsPath='/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mPowerUnits/massDescription/mass')

        #CoG
        self.posCoG = posCoG()

        #Inertia
        self.massIX = massIX(
            cpacsPath='/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mPowerUnits/massDescription/massInertia/Jxx')
        self.massIY = massIY(
            cpacsPath='/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mPowerUnits/massDescription/massInertia/Jyy')
        self.massIZ = massIZ(
            cpacsPath='/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mPowerUnits/massDescription/massInertia/Jzz')

        #Geometry
        self.lEngine = lEngine(cpacsPath='/cpacs/vehicles/engines/engine/geometry/length')
        self.dEngine = dEngine(cpacsPath='/cpacs/vehicles/engines/engine/geometry/diameter')
        self.yEngine = yEngine(cpacsPath='/cpacs/vehicles/aircraft/model/engines/engine/transformation/translation/y')
        self.xEngine = xEngine(cpacsPath='/cpacs/vehicles/aircraft/model/engines/engine/transformation/translation/x')
        self.zEngine = zEngine(cpacsPath='/cpacs/vehicles/aircraft/model/engines/engine/transformation/translation/z')
        self.wetArea = wetArea()
        self.location = location()

        #Aerodynamics
        self.formFactor = formFactor()
        self.reynoldsNr = reynoldsNr()
        self.cfLAM = cfLAM()
        self.cfTURB = cfTURB()
        self.cD0c = cD0c()
        self.dCDOEI = dCDOEI()
        self.nLam = nLam()

        #Propulsion
        self.mDotEngine = mDotEngine()
        self.thrustTO = thrustTO(cpacsPath='/cpacs/vehicles/engines/engine/analysis/thrust00')
        self.thrustTOISA = thrustTOISA()
        self.thrustCR = thrustCR()
        self.nEngine = nEngine()
        self.sfcCR = sfcCR()
        self.sfcLOI = sfcLOI()
        self.bypassRatio = bypassRatio(cpacsPath='/cpacs/vehicles/engines/engine/analysis/bpr00')
        self.thrustTWDat = thrustTWDat(cpacsPath='/cpacs/toolspecific/tWDat/thrust00Scaling')
        self.etaCompr = etaCompr()
        self.etaFan = etaFan()
        self.etaProp = etaProp()
        self.etaTherm = etaTherm()
        self.etaTransm = etaTransm()
        self.etaTurb = etaTurb()
        self.TET = TET()
        self.OPR = OPR()

        ###################################################################################################
        #EOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFEOFE#
        ###################################################################################################
Пример #32
0
    def __init__(self, aircraft):
        '''
        @Method: Component Constructor
        '''
        component.__init__(self)
        self.id = 'atmosphere'
        self.aircraft = aircraft
        self.level = 2

        #Airport Level
        self.hAP = hAP()
        self.aAP = aAP()
        self.pAP = pAP()
        self.rhoAP = rhoAP()
        self.sigmaAP = sigmaAP()
        self.TAP = TAP()
        self.deltaT = deltaT()

        #CruiseLevel
        self.aCR = aCR()
        self.EASCR = EASCR()
        self.hCR = hCR()
        self.MaCR = MaCR()
        self.myCR = myCR()
        self.nyCR = nyCR()
        self.qCR = qCR()
        self.rhoCR = rhoCR()
        self.sigmaCR = sigmaCR()
        self.TASCR = TASCR()
        self.TCR = TCR()

        #FL1500
        self.aFL1500 = aFL1500()
        self.EASFL1500 = EASFL1500()
        self.hFL1500 = hFL1500()
        self.MaFL1500 = MaFL1500()
        self.myFL1500 = myFL1500()
        self.nyFL1500 = nyFL1500()
        self.qFL1500 = qFL1500()
        self.rhoFL1500 = rhoFL1500()
        self.sigmaFL1500 = sigmaFL1500()
        self.TASFL1500 = TASFL1500()
        self.TFL1500 = TFL1500()

        #FL100
        self.aFL100 = aFL100()
        self.EASFL100 = EASFL100()
        self.hFL100 = hFL100()
        self.MaFL100 = MaFL100()
        self.myFL100 = myFL100()
        self.nyFL100 = nyFL100()
        self.qFL100 = qFL100()
        self.rhoFL100 = rhoFL100()
        self.sigmaFL100 = sigmaFL100()
        self.TASFL100 = TASFL100()
        self.TFL100 = TFL100()

        #Constants
        self.R_s = 287.05                # spezifische Gaskonstante der Luft
        self.kappa = 1.4                   # Adiabatenkoeff.
        self.g = 9.81                  # Erdbeschnleunigung
        self.beta = 1.458e-6              # Sutherland Konstante
        self.S_Sutherland = 110.4                 # [K] Sutherland Temperatur
        self.HA = [0, 11000, 20000]
        self.gammaH = [-0.0065, 0, 0.001]
        self.TA = [288.15, 216.65, 216.65]
        self.pA = [101325, 22620, 5469]
        self.rhoA = [1.225, 0.3637, 0.0879]
Пример #33
0
    def __init__(self, aircraft):
        '''
        will initialize instance mainly used for documentation
        links to the aircraft instance
        initiates the airfoil class
        @Method: Component Constructor
        '''
        component.__init__(self)
        self.id = 'tool'
        self.aircraft = aircraft
        self.level = 2

        #===============================================================================
        #Aircraft stuff
        #===============================================================================
        self.aircraftName = parameter(
            cpacsPath='/cpacs/vehicles/aircraft/model/name', value='VAMPzero')
        self.aircraftDES = parameter(
            cpacsPath='/cpacs/vehicles/aircraft/model/description',
            value='VAMPzero')
        #commented out due to introduction of xMAC25
        #self.refX             = parameter(cpacsPath = '/cpacs/vehicles/aircraft/model/reference/point/x',value='0.0')
        self.refY = parameter(
            cpacsPath='/cpacs/vehicles/aircraft/model/reference/point/y',
            value='0.0')
        self.refZ = parameter(
            cpacsPath='/cpacs/vehicles/aircraft/model/reference/point/z',
            value='0.0')

        #=======================================================================
        # Lifting Line
        #=======================================================================
        self.liliname = parameter(
            cpacsPath='/cpacs/toolspecific/liftingLine/tool/name',
            value='LIFTING_LINE')
        self.liliversion = parameter(
            cpacsPath='/cpacs/toolspecific/liftingLine/tool/version',
            value='2.3.1')
        self.liliuID = parameter(
            cpacsPath='/cpacs/toolspecific/liftingLine/aircraftModelUID',
            value='A320modelID'
        )  #@todo: Model ID is not available at Time of Construction
        self.liliSpaneling = parameter(
            cpacsPath=
            '/cpacs/toolspecific/liftingLine/toolParameters/wingPanelings/wingPaneling[1]/spanwise',
            value='5')
        self.liliCpaneling = parameter(
            cpacsPath=
            '/cpacs/toolspecific/liftingLine/toolParameters/wingPanelings/wingPaneling[1]/chordwise',
            value='5')

        self.lilimode = parameter(
            cpacsPath=
            '/cpacs/toolspecific/liftingLine/toolParameters/archiveMode',
            value='1')
        #self.lilipolars       = parameter(cpacsPath = '/cpacs/toolspecific/liftingLine/performanceMaps',value='')

        #=======================================================================
        #Header Information
        #=======================================================================
        self.name = parameter(cpacsPath='/cpacs/header/name',
                              value='Export from')
        self.creator = parameter(cpacsPath='/cpacs/header/creator',
                                 value='VAMPzero')
        self.timestamp = parameter(cpacsPath='/cpacs/header/timestamp',
                                   value='2010-12-31T12:00:00')
        self.version = parameter(cpacsPath='/cpacs/header/version',
                                 value='0.1')
        self.version = parameter(cpacsPath='/cpacs/header/cpacsVersion',
                                 value='2.0')