コード例 #1
0
ファイル: vtp.py プロジェクト: codingpoets/VAMPzero
    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)
コード例 #2
0
ファイル: htp.py プロジェクト: techtronics/VAMPzero
    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)
コード例 #3
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)
コード例 #4
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)
コード例 #5
0
ファイル: wing.py プロジェクト: techtronics/VAMPzero
    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()
コード例 #6
0
ファイル: strut.py プロジェクト: p-chambers/VAMPzero
    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')
コード例 #7
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()
コード例 #8
0
ファイル: strut.py プロジェクト: codingpoets/VAMPzero
    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")