def createRudder(parentVtpCPACS, parentVtpVAMPzero, myRudder):
"""
This is the main export method for the wings aileron
"""
cpacsPath = "/cpacs/vehicles/aircraft/model/wings/wing[" + parentVtpVAMPzero.id + "]"
cpacsVtp = getObjfromXpath(parentVtpCPACS, cpacsPath)
cpacsComponentSegment = cpacsVtp.get_componentSegments().get_componentSegment()[0]
# ===========================================================================
# Header
# ===========================================================================
myName = stringBaseType(None, None, None, "rudder")
myDescription = stringBaseType(None, None, None, "rudder from VAMPzero")
myParentUID = stringUIDBaseType(None, None, "True", None, "vtp_Cseg")
# ===========================================================================
# Outer Shape
# With the rudder this is pretty simple as it is supposed to cover
# the same span as the VTP
# ===========================================================================
# the inner border eta is determined from the rooYLocation of the Rudder and the vtp span
vtpSpan = parentVtpVAMPzero.span.getValue() / 2.0
innerEtaLE = 0.0
outerEtaLE = 1.0
innerXsiLE = myRudder.cRoot.getValue() / parentVtpVAMPzero.cRoot.getValue()
outerXsiLE = myRudder.cTip.getValue() / parentVtpVAMPzero.cTip.getValue()
# start writing back
myleadingEdgeShape = leadingEdgeShapeType(
relHeightLE=doubleBaseType(valueOf_=str(0.5)),
xsiUpperSkin=doubleBaseType(valueOf_=str(0.85)),
xsiLowerSkin=doubleBaseType(valueOf_=str(0.85)),
)
innerBorder = controlSurfaceBorderTrailingEdgeType(
etaLE=doubleBaseType(valueOf_=str(innerEtaLE)),
xsiLE=doubleBaseType(valueOf_=str(innerXsiLE)),
leadingEdgeShape=myleadingEdgeShape,
)
outerBorder = controlSurfaceBorderTrailingEdgeType(
etaLE=doubleBaseType(valueOf_=str(outerEtaLE)),
xsiLE=doubleBaseType(valueOf_=str(outerXsiLE)),
leadingEdgeShape=myleadingEdgeShape,
)
myOuterShape = controlSurfaceOuterShapeTrailingEdgeType(innerBorder=innerBorder, outerBorder=outerBorder)
cpacsRudder = trailingEdgeDeviceType(
uID="rudderUID", name=myName, description=myDescription, parentUID=myParentUID, outerShape=myOuterShape
)
createPath(cpacsRudder, "rudder")
if type(cpacsComponentSegment.get_controlSurfaces()) == NoneType:
cpacsComponentSegment.set_controlSurfaces(controlSurfacesType())
if type(cpacsComponentSegment.get_controlSurfaces().get_trailingEdgeDevices()) == NoneType:
cpacsComponentSegment.get_controlSurfaces().set_trailingEdgeDevices(trailingEdgeDevicesType())
cpacsComponentSegment.get_controlSurfaces().get_trailingEdgeDevices().add_trailingEdgeDevice(cpacsRudder)
def createStabilizer(parentHtpCPACS, parentHtpVAMPzero, myElevator):
'''
This is the main export method for the stabilizer, i.e. the whole htp as control surface
'''
cpacsPath = '/cpacs/vehicles/aircraft/model/wings/wing[' + parentHtpVAMPzero.id + ']'
cpacsHtp = getObjfromXpath(parentHtpCPACS, cpacsPath)
cpacsComponentSegment = cpacsHtp.get_componentSegments(
).get_componentSegment()[0]
#===========================================================================
# Header
#===========================================================================
myName = stringBaseType(None, None, None, 'stabilizer')
myDescription = stringBaseType(None, None, None,
'stabilizer exported from VAMPzero')
myParentUID = stringUIDBaseType(None, None, 'True', None,
parentHtpVAMPzero.id)
#===========================================================================
# Outer Shape
#===========================================================================
innerEtaLE = 0.
innerXsiLE = 0.
outerEtaLE = 1.
outerXsiLE = 0.
# start writing back
#myleadingEdgeShape = leadingEdgeShapeType(relHeightLE=doubleBaseType(valueOf_=str(0.5)), xsiUpperSkin=doubleBaseType(valueOf_=str(0.85)), xsiLowerSkin=doubleBaseType(valueOf_=str(0.85)))
innerBorder = controlSurfaceBorderTrailingEdgeType(
etaLE=doubleBaseType(valueOf_=str(innerEtaLE)),
xsiLE=doubleBaseType(valueOf_=str(innerXsiLE)))
outerBorder = controlSurfaceBorderTrailingEdgeType(
etaLE=doubleBaseType(valueOf_=str(outerEtaLE)),
xsiLE=doubleBaseType(valueOf_=str(outerXsiLE)))
myOuterShape = controlSurfaceOuterShapeTrailingEdgeType(
innerBorder=innerBorder, outerBorder=outerBorder)
cpacsStabilizer = trailingEdgeDeviceType(uID='stabilizerUID',
name=myName,
description=myDescription,
parentUID=myParentUID,
outerShape=myOuterShape)
createPath(cpacsStabilizer, 'stabilizer')
if type(cpacsComponentSegment.get_controlSurfaces()) == NoneType:
cpacsComponentSegment.set_controlSurfaces(controlSurfacesType())
if type(cpacsComponentSegment.get_controlSurfaces().
get_trailingEdgeDevices()) == NoneType:
cpacsComponentSegment.get_controlSurfaces().set_trailingEdgeDevices(
trailingEdgeDevicesType())
cpacsComponentSegment.get_controlSurfaces().get_trailingEdgeDevices(
).add_trailingEdgeDevice(cpacsStabilizer)
def createFlap(name,
parentUID,
innerEtaLE,
innerXsiLE,
outerEtaLE,
outerXsiLE,
maxX,
appendInnerCruiseRoller=False,
type='flap',
innerX=0.,
outerX=0.):
log.debug('VAMPzero FLAP: Creating Flap: %s' % (str(name)))
log.debug('VAMPzero FLAP: innerEtaLE: %s' % str(innerEtaLE))
log.debug('VAMPzero FLAP: outerEtaLE: %s' % str(outerEtaLE))
log.debug('VAMPzero FLAP: innerXsiLE: %s' % str(innerXsiLE))
log.debug('VAMPzero FLAP: outerXsiLE: %s' % str(outerXsiLE))
myName = stringBaseType(None, None, None, name)
myDescription = stringBaseType(None, None, None, 'innerFlap from VAMPzero')
myParentUID = stringUIDBaseType(None, None, 'True', None, parentUID)
myleadingEdgeShape = leadingEdgeShapeType(
relHeightLE=doubleBaseType(valueOf_=str(0.2)),
xsiUpperSkin=doubleBaseType(valueOf_=str(0.5)),
xsiLowerSkin=doubleBaseType(valueOf_=str(0.95)))
innerBorder = controlSurfaceBorderTrailingEdgeType(
etaLE=doubleBaseType(valueOf_=str(innerEtaLE)),
etaTE=doubleBaseType(valueOf_=str(innerEtaLE)),
xsiLE=doubleBaseType(valueOf_=str(innerXsiLE)),
leadingEdgeShape=myleadingEdgeShape)
outerBorder = controlSurfaceBorderTrailingEdgeType(
etaLE=doubleBaseType(valueOf_=str(outerEtaLE)),
etaTE=doubleBaseType(valueOf_=str(outerEtaLE)),
xsiLE=doubleBaseType(valueOf_=str(outerXsiLE)),
leadingEdgeShape=myleadingEdgeShape)
myOuterShape = controlSurfaceOuterShapeTrailingEdgeType(
innerBorder=innerBorder, outerBorder=outerBorder)
myStructure = wingComponentSegmentStructureType()
myFlap = trailingEdgeDeviceType(uID=name + 'UID',
name=myName,
description=myDescription,
parentUID=myParentUID,
outerShape=myOuterShape,
structure=myStructure)
createFlapStructure(myFlap,
maxX,
innerXsiLE,
outerXsiLE,
appendInnerCruiseRoller,
type=type,
innerX=innerX,
outerX=outerX)
return myFlap
def createStabilizer(parentHtpCPACS, parentHtpVAMPzero, myElevator):
"""
This is the main export method for the stabilizer, i.e. the whole htp as control surface
"""
cpacsPath = "/cpacs/vehicles/aircraft/model/wings/wing[" + parentHtpVAMPzero.id + "]"
cpacsHtp = getObjfromXpath(parentHtpCPACS, cpacsPath)
cpacsComponentSegment = cpacsHtp.get_componentSegments().get_componentSegment()[0]
# ===========================================================================
# Header
# ===========================================================================
myName = stringBaseType(None, None, None, "stabilizer")
myDescription = stringBaseType(None, None, None, "stabilizer exported from VAMPzero")
myParentUID = stringUIDBaseType(None, None, "True", None, parentHtpVAMPzero.id)
# ===========================================================================
# Outer Shape
# ===========================================================================
innerEtaLE = 0.0
innerXsiLE = 0.0
outerEtaLE = 1.0
outerXsiLE = 0.0
# start writing back
# myleadingEdgeShape = leadingEdgeShapeType(relHeightLE=doubleBaseType(valueOf_=str(0.5)), xsiUpperSkin=doubleBaseType(valueOf_=str(0.85)), xsiLowerSkin=doubleBaseType(valueOf_=str(0.85)))
innerBorder = controlSurfaceBorderTrailingEdgeType(
etaLE=doubleBaseType(valueOf_=str(innerEtaLE)), xsiLE=doubleBaseType(valueOf_=str(innerXsiLE))
)
outerBorder = controlSurfaceBorderTrailingEdgeType(
etaLE=doubleBaseType(valueOf_=str(outerEtaLE)), xsiLE=doubleBaseType(valueOf_=str(outerXsiLE))
)
myOuterShape = controlSurfaceOuterShapeTrailingEdgeType(innerBorder=innerBorder, outerBorder=outerBorder)
cpacsStabilizer = trailingEdgeDeviceType(
uID="stabilizerUID", name=myName, description=myDescription, parentUID=myParentUID, outerShape=myOuterShape
)
createPath(cpacsStabilizer, "stabilizer")
if type(cpacsComponentSegment.get_controlSurfaces()) == NoneType:
cpacsComponentSegment.set_controlSurfaces(controlSurfacesType())
if type(cpacsComponentSegment.get_controlSurfaces().get_trailingEdgeDevices()) == NoneType:
cpacsComponentSegment.get_controlSurfaces().set_trailingEdgeDevices(trailingEdgeDevicesType())
cpacsComponentSegment.get_controlSurfaces().get_trailingEdgeDevices().add_trailingEdgeDevice(cpacsStabilizer)
def createFlap(name, parentUID, innerEtaLE, innerXsiLE, outerEtaLE, outerXsiLE, maxX, appendInnerCruiseRoller=False, type='flap', innerX=0., outerX=0.):
log.debug('VAMPzero FLAP: Creating Flap: %s' % (str(name)))
log.debug('VAMPzero FLAP: innerEtaLE: %s' % str(innerEtaLE))
log.debug('VAMPzero FLAP: outerEtaLE: %s' % str(outerEtaLE))
log.debug('VAMPzero FLAP: innerXsiLE: %s' % str(innerXsiLE))
log.debug('VAMPzero FLAP: outerXsiLE: %s' % str(outerXsiLE))
myName = stringBaseType(None, None, None, name)
myDescription = stringBaseType(None, None, None, 'innerFlap from VAMPzero')
myParentUID = stringUIDBaseType(None, None, 'True', None, parentUID)
myleadingEdgeShape = leadingEdgeShapeType(relHeightLE=doubleBaseType(valueOf_=str(0.2)), xsiUpperSkin=doubleBaseType(valueOf_=str(0.5)), xsiLowerSkin=doubleBaseType(valueOf_=str(0.95)))
innerBorder = controlSurfaceBorderTrailingEdgeType(etaLE=doubleBaseType(valueOf_=str(innerEtaLE)), etaTE=doubleBaseType(valueOf_=str(innerEtaLE)), xsiLE=doubleBaseType(valueOf_=str(innerXsiLE)), leadingEdgeShape=myleadingEdgeShape)
outerBorder = controlSurfaceBorderTrailingEdgeType(etaLE=doubleBaseType(valueOf_=str(outerEtaLE)), etaTE=doubleBaseType(valueOf_=str(outerEtaLE)), xsiLE=doubleBaseType(valueOf_=str(outerXsiLE)), leadingEdgeShape=myleadingEdgeShape)
myOuterShape = controlSurfaceOuterShapeTrailingEdgeType(innerBorder=innerBorder, outerBorder=outerBorder)
myStructure = wingComponentSegmentStructureType()
myFlap = trailingEdgeDeviceType(uID=name + 'UID', name=myName, description=myDescription, parentUID=myParentUID, outerShape=myOuterShape, structure=myStructure)
createFlapStructure(myFlap, maxX, innerXsiLE, outerXsiLE, appendInnerCruiseRoller, type=type, innerX=innerX, outerX=outerX)
return myFlap
def createElevator(parentHtpCPACS, parentHtpVAMPzero, myElevator):
"""
This is the main export method for the htp elevator
"""
cpacsPath = "/cpacs/vehicles/aircraft/model/wings/wing[" + parentHtpVAMPzero.id + "]"
cpacsHtp = getObjfromXpath(parentHtpCPACS, cpacsPath)
cpacsComponentSegment = cpacsHtp.get_componentSegments().get_componentSegment()[0]
# ===========================================================================
# Header
# ===========================================================================
myName = stringBaseType(None, None, None, "elevator")
myDescription = stringBaseType(None, None, None, "elevator from VAMPzero")
myParentUID = stringUIDBaseType(None, None, "True", None, parentHtpVAMPzero.id)
# ===========================================================================
# Outer Shape
# ===========================================================================
# the inner border eta is determined from the rooYLocation of the Elevator and the htp span
htpSpan = parentHtpVAMPzero.span.getValue() / 2.0
innerEtaLE = myElevator.rootYLocation.getValue() / htpSpan
# the inner border xsi is determined from the Root Chord and the Chord of the Htp at the location
phiLE = parentHtpVAMPzero.phiLE.getValue()
phiTE = parentHtpVAMPzero.phiTE.getValue()
x1 = tan(phiLE * rad) * htpSpan * innerEtaLE
x2 = tan(phiTE * rad) * htpSpan * innerEtaLE
cInnerWing = (x2 + parentHtpVAMPzero.cRoot.getValue()) - x1
innerXsiLE = 1 - (myElevator.cRoot.getValue() / cInnerWing)
# The outer border eta station is set to the inner eta plus the span of the elevator
outerEtaLE = innerEtaLE + myElevator.span.getValue() / htpSpan
# The outer border xsi is determined in the same way as the inner border xsi
x1 = tan(phiLE * rad) * htpSpan * outerEtaLE
x2 = tan(phiTE * rad) * htpSpan * outerEtaLE
cOuterWing = (x2 + parentHtpVAMPzero.cRoot.getValue()) - x1
outerXsiLE = 1 - (myElevator.cTip.getValue() / cOuterWing)
# start writing back
myleadingEdgeShape = leadingEdgeShapeType(
relHeightLE=doubleBaseType(valueOf_=str(0.5)),
xsiUpperSkin=doubleBaseType(valueOf_=str(0.85)),
xsiLowerSkin=doubleBaseType(valueOf_=str(0.85)),
)
innerBorder = controlSurfaceBorderTrailingEdgeType(
etaLE=doubleBaseType(valueOf_=str(innerEtaLE)),
xsiLE=doubleBaseType(valueOf_=str(innerXsiLE)),
leadingEdgeShape=myleadingEdgeShape,
)
outerBorder = controlSurfaceBorderTrailingEdgeType(
etaLE=doubleBaseType(valueOf_=str(outerEtaLE)),
xsiLE=doubleBaseType(valueOf_=str(outerXsiLE)),
leadingEdgeShape=myleadingEdgeShape,
)
myOuterShape = controlSurfaceOuterShapeTrailingEdgeType(innerBorder=innerBorder, outerBorder=outerBorder)
cpacsElevator = trailingEdgeDeviceType(
uID="elevatorUID", name=myName, description=myDescription, parentUID=myParentUID, outerShape=myOuterShape
)
createPath(cpacsElevator, "elevator")
if type(cpacsComponentSegment.get_controlSurfaces()) == NoneType:
cpacsComponentSegment.set_controlSurfaces(controlSurfacesType())
if type(cpacsComponentSegment.get_controlSurfaces().get_trailingEdgeDevices()) == NoneType:
cpacsComponentSegment.get_controlSurfaces().set_trailingEdgeDevices(trailingEdgeDevicesType())
cpacsComponentSegment.get_controlSurfaces().get_trailingEdgeDevices().add_trailingEdgeDevice(cpacsElevator)
def createElevator(parentHtpCPACS, parentHtpVAMPzero, myElevator):
'''
This is the main export method for the htp elevator
'''
cpacsPath = '/cpacs/vehicles/aircraft/model/wings/wing[' + parentHtpVAMPzero.id + ']'
cpacsHtp = getObjfromXpath(parentHtpCPACS, cpacsPath)
cpacsComponentSegment = cpacsHtp.get_componentSegments(
).get_componentSegment()[0]
#===========================================================================
# Header
#===========================================================================
myName = stringBaseType(None, None, None, 'elevator')
myDescription = stringBaseType(None, None, None, 'elevator from VAMPzero')
myParentUID = stringUIDBaseType(None, None, 'True', None,
parentHtpVAMPzero.id)
#===========================================================================
# Outer Shape
#===========================================================================
# the inner border eta is determined from the rooYLocation of the Elevator and the htp span
htpSpan = parentHtpVAMPzero.span.getValue() / 2.
innerEtaLE = myElevator.rootYLocation.getValue() / htpSpan
# the inner border xsi is determined from the Root Chord and the Chord of the Htp at the location
phiLE = parentHtpVAMPzero.phiLE.getValue()
phiTE = parentHtpVAMPzero.phiTE.getValue()
x1 = tan(phiLE * rad) * htpSpan * innerEtaLE
x2 = tan(phiTE * rad) * htpSpan * innerEtaLE
cInnerWing = (x2 + parentHtpVAMPzero.cRoot.getValue()) - x1
innerXsiLE = 1 - (myElevator.cRoot.getValue() / cInnerWing)
# The outer border eta station is set to the inner eta plus the span of the elevator
outerEtaLE = innerEtaLE + myElevator.span.getValue() / htpSpan
# The outer border xsi is determined in the same way as the inner border xsi
x1 = tan(phiLE * rad) * htpSpan * outerEtaLE
x2 = tan(phiTE * rad) * htpSpan * outerEtaLE
cOuterWing = (x2 + parentHtpVAMPzero.cRoot.getValue()) - x1
outerXsiLE = 1 - (myElevator.cTip.getValue() / cOuterWing)
# start writing back
myleadingEdgeShape = leadingEdgeShapeType(
relHeightLE=doubleBaseType(valueOf_=str(0.5)),
xsiUpperSkin=doubleBaseType(valueOf_=str(0.85)),
xsiLowerSkin=doubleBaseType(valueOf_=str(0.85)))
innerBorder = controlSurfaceBorderTrailingEdgeType(
etaLE=doubleBaseType(valueOf_=str(innerEtaLE)),
xsiLE=doubleBaseType(valueOf_=str(innerXsiLE)),
leadingEdgeShape=myleadingEdgeShape)
outerBorder = controlSurfaceBorderTrailingEdgeType(
etaLE=doubleBaseType(valueOf_=str(outerEtaLE)),
xsiLE=doubleBaseType(valueOf_=str(outerXsiLE)),
leadingEdgeShape=myleadingEdgeShape)
myOuterShape = controlSurfaceOuterShapeTrailingEdgeType(
innerBorder=innerBorder, outerBorder=outerBorder)
cpacsElevator = trailingEdgeDeviceType(uID='elevatorUID',
name=myName,
description=myDescription,
parentUID=myParentUID,
outerShape=myOuterShape)
createPath(cpacsElevator, 'elevator')
if type(cpacsComponentSegment.get_controlSurfaces()) == NoneType:
cpacsComponentSegment.set_controlSurfaces(controlSurfacesType())
if type(cpacsComponentSegment.get_controlSurfaces().
get_trailingEdgeDevices()) == NoneType:
cpacsComponentSegment.get_controlSurfaces().set_trailingEdgeDevices(
trailingEdgeDevicesType())
cpacsComponentSegment.get_controlSurfaces().get_trailingEdgeDevices(
).add_trailingEdgeDevice(cpacsElevator)
def createElevator(parentHtpCPACS, parentHtpVAMPzero, myElevator):
'''
This is the main export method for the htp elevator
'''
cpacsPath = '/cpacs/vehicles/aircraft/model/wings/wing[' + parentHtpVAMPzero.id + ']'
cpacsHtp = getObjfromXpath(parentHtpCPACS, cpacsPath)
cpacsComponentSegment = cpacsHtp.get_componentSegments().get_componentSegment()[0]
#===========================================================================
# Header
#===========================================================================
myName = stringBaseType(None, None, None, 'elevator')
myDescription = stringBaseType(None, None, None, 'elevator from VAMPzero')
myParentUID = stringUIDBaseType(None, None, 'True', None, parentHtpVAMPzero.id)
#===========================================================================
# Outer Shape
#===========================================================================
# the inner border eta is determined from the rooYLocation of the Elevator and the htp span
htpSpan = parentHtpVAMPzero.span.getValue() / 2.
innerEtaLE = myElevator.rootYLocation.getValue() / htpSpan
# the inner border xsi is determined from the Root Chord and the Chord of the Htp at the location
# the inner border xsi is determined from the Root Chord and the Chord of the Htp at the location
cTipHtp = parentHtpVAMPzero.cTip.getValue()
cRootHtp = parentHtpVAMPzero.cRoot.getValue()
cInnerWing = cRootHtp - (cRootHtp - cTipHtp)*innerEtaLE
innerXsiLE = 1 - (myElevator.cRoot.getValue() / cInnerWing)
if innerXsiLE < 0.2:
parentHtpVAMPzero.log.warning('VAMPzero EXPORT: The Elevator tap inner border is larger than the available chord')
parentHtpVAMPzero.log.warning('VAMPzero EXPORT: The Elevator tap inner border is now set to 0.1')
innerXsiLE = 0.2
# The outer border eta station is set to the inner eta plus the span of the elevator
outerEtaLE = innerEtaLE + myElevator.span.getValue() / htpSpan
# The outer border xsi is determined in the same way as the inner border xsi
cOuterWing = cRootHtp - (cRootHtp - cTipHtp)*outerEtaLE
outerXsiLE = 1 - (myElevator.cTip.getValue() / cOuterWing)
if outerXsiLE < 0.2:
parentHtpVAMPzero.log.warning('VAMPzero EXPORT: The Elevator tap outer border is larger than the available chord')
parentHtpVAMPzero.log.warning('VAMPzero EXPORT: The Elevator tap outer border is now set to 0.1')
outerXsiLE = 0.2
# start writing back
myleadingEdgeShape = leadingEdgeShapeType(relHeightLE=doubleBaseType(valueOf_=str(0.5)), xsiUpperSkin=doubleBaseType(valueOf_=str(0.85)), xsiLowerSkin=doubleBaseType(valueOf_=str(0.85)))
innerBorder = controlSurfaceBorderTrailingEdgeType(etaLE=doubleBaseType(valueOf_=str(innerEtaLE)), xsiLE=doubleBaseType(valueOf_=str(innerXsiLE)), leadingEdgeShape=myleadingEdgeShape)
outerBorder = controlSurfaceBorderTrailingEdgeType(etaLE=doubleBaseType(valueOf_=str(outerEtaLE)), xsiLE=doubleBaseType(valueOf_=str(outerXsiLE)), leadingEdgeShape=myleadingEdgeShape)
myOuterShape = controlSurfaceOuterShapeTrailingEdgeType(innerBorder=innerBorder, outerBorder=outerBorder)
cpacsElevator = trailingEdgeDeviceType(uID='elevatorUID', name=myName, description=myDescription, parentUID=myParentUID, outerShape=myOuterShape)
createPath(cpacsElevator, 'elevator')
if type(cpacsComponentSegment.get_controlSurfaces()) == NoneType:
cpacsComponentSegment.set_controlSurfaces(controlSurfacesType())
if type(cpacsComponentSegment.get_controlSurfaces().get_trailingEdgeDevices()) == NoneType:
cpacsComponentSegment.get_controlSurfaces().set_trailingEdgeDevices(trailingEdgeDevicesType())
cpacsComponentSegment.get_controlSurfaces().get_trailingEdgeDevices().add_trailingEdgeDevice(cpacsElevator)
def createAileron(parentWingCPACS, parentWingVAMPzero, myAileron):
'''
This is the main export method for the wings aileron
'''
cpacsPath = '/cpacs/vehicles/aircraft/model/wings/wing[' + parentWingVAMPzero.id + ']'
cpacsWing = getObjfromXpath(parentWingCPACS, cpacsPath)
cpacsComponentSegment = cpacsWing.get_componentSegments().get_componentSegment()[0]
# Header
myName = stringBaseType(None, None, None, 'aileron')
myDescription = stringBaseType(None, None, None, 'aileron from VAMPzero')
myParentUID = stringUIDBaseType(None, None, 'True', None, 'wing_Cseg')
# Initialization, i.e. fetching values throughout the code
xsis = []
etas = []
for i in range(3,7):
try:
xsis.append(eval(cpacsComponentSegment.get_structure().get_spars().get_sparPositions().get_sparPosition()[i].get_xsi().valueOf_))
etas.append(eval(cpacsComponentSegment.get_structure().get_spars().get_sparPositions().get_sparPosition()[i].get_eta().valueOf_))
except IndexError:
pass
xsiSpar_interp = scipy.interpolate.interp1d(etas, xsis)
sparOffset = 0.1
wingSpan = parentWingVAMPzero.span.getValue() / 2.
# Outer Shape
# The outer border eta station is set to 96 percent
outerEtaLE = 0.96
# The outer chord station is determined from the wing's chord at eta = 0.96
# and the rear spar location + the spar offset
outerXsiLE = xsiSpar_interp(0.96) + sparOffset
outerWingChord = calcChordLengthAtEta(outerEtaLE, parentWingVAMPzero, cpacsWing)
cTip = (1 - outerXsiLE) * outerWingChord
# now we need to determine the necessary span for the aileron by gently increasing the span
# this is an iterative process as the chord of the aileron is a function of the inbound span
aileronArea = parentWingVAMPzero.aileron.refArea.getValue()
delta = 0.01
calcArea = 0.
while abs(calcArea - aileronArea) > 0.1:
if delta > outerEtaLE:
parentWingVAMPzero.log.warning('VAMPzero EXPORT: Cannot determine the span of the aileron')
parentWingVAMPzero.log.warning('VAMPzero EXPORT: aileronArea= '+str(aileronArea))
parentWingVAMPzero.log.warning('VAMPzero EXPORT: Decreasing Spar Offset')
sparOffset = sparOffset - 0.02
delta = 0.01
innerEtaLE = outerEtaLE - delta
innerXsiLE = xsiSpar_interp(innerEtaLE) + sparOffset
innerWingChord = calcChordLengthAtEta(innerEtaLE, parentWingVAMPzero, cpacsWing)
cRoot = (1 - innerXsiLE) * innerWingChord
calcArea = (cTip + cRoot) / 2 * (outerEtaLE - innerEtaLE) * wingSpan
delta += 0.005
# start outer shape
myleadingEdgeShape = leadingEdgeShapeType(relHeightLE=doubleBaseType(valueOf_=str(0.5)), xsiUpperSkin=doubleBaseType(valueOf_=str(0.85)), xsiLowerSkin=doubleBaseType(valueOf_=str(0.85)))
innerBorder = controlSurfaceBorderTrailingEdgeType(etaLE=doubleBaseType(valueOf_=str(innerEtaLE)), etaTE=doubleBaseType(valueOf_=str(innerEtaLE)), xsiLE=doubleBaseType(valueOf_=str(innerXsiLE)), leadingEdgeShape=myleadingEdgeShape)
outerBorder = controlSurfaceBorderTrailingEdgeType(etaLE=doubleBaseType(valueOf_=str(outerEtaLE)), etaTE=doubleBaseType(valueOf_=str(outerEtaLE)), xsiLE=doubleBaseType(valueOf_=str(outerXsiLE)), leadingEdgeShape=myleadingEdgeShape)
myOuterShape = controlSurfaceOuterShapeTrailingEdgeType(innerBorder=innerBorder, outerBorder=outerBorder)
# structure
myStructure = wingComponentSegmentStructureType()
cpacsAileron = trailingEdgeDeviceType(uID='aileronUID', name=myName, description=myDescription, parentUID=myParentUID, outerShape=myOuterShape, structure=myStructure)
createAileronStructure(cpacsAileron)
# Forward information about innerEtaLE to the flap
parentWingVAMPzero.flap.maxEta = parameter(value=innerEtaLE, doc='This it the inner position of the aileron, the flap may not exceed it')
# moveables
deltaEta = outerEtaLE - innerEtaLE
innerParentXsi = xsiSpar_interp(innerEtaLE + 0.3 * deltaEta) + 0.02
outerParentXsi = xsiSpar_interp(innerEtaLE + 0.7 * deltaEta) + 0.02
createPath(cpacsAileron, 'aileron')
createTracks(cpacsAileron, 'aileron')
createActuators(cpacsAileron, 'aileron', [innerParentXsi, outerParentXsi])
if type(cpacsComponentSegment.get_controlSurfaces()) == NoneType:
cpacsComponentSegment.set_controlSurfaces(controlSurfacesType())
if type(cpacsComponentSegment.get_controlSurfaces().get_trailingEdgeDevices()) == NoneType:
cpacsComponentSegment.get_controlSurfaces().set_trailingEdgeDevices(trailingEdgeDevicesType())
cpacsComponentSegment.get_controlSurfaces().get_trailingEdgeDevices().add_trailingEdgeDevice(cpacsAileron)
def createAileron(parentWingCPACS, parentWingVAMPzero, myAileron):
'''
This is the main export method for the wings aileron
'''
cpacsPath = '/cpacs/vehicles/aircraft/model/wings/wing[' + parentWingVAMPzero.id + ']'
cpacsWing = getObjfromXpath(parentWingCPACS, cpacsPath)
cpacsComponentSegment = cpacsWing.get_componentSegments(
).get_componentSegment()[0]
#===========================================================================
# Header
#===========================================================================
myName = stringBaseType(None, None, None, 'aileron')
myDescription = stringBaseType(None, None, None, 'aileron from VAMPzero')
myParentUID = stringUIDBaseType(None, None, 'True', None, 'wing_Cseg')
#===========================================================================
# Initialization, i.e. fetching values throughout the code
#===========================================================================
xsiSparRoot = eval(cpacsComponentSegment.get_structure().get_spars(
).get_sparPositions().get_sparPosition()[3].get_xsi().valueOf_)
xsiSparFuselage = eval(cpacsComponentSegment.get_structure().get_spars(
).get_sparPositions().get_sparPosition()[4].get_xsi().valueOf_)
xsiSparKink = eval(cpacsComponentSegment.get_structure().get_spars(
).get_sparPositions().get_sparPosition()[5].get_xsi().valueOf_)
xsiSparTip = eval(cpacsComponentSegment.get_structure().get_spars(
).get_sparPositions().get_sparPosition()[6].get_xsi().valueOf_)
etaSparRoot = eval(cpacsComponentSegment.get_structure().get_spars(
).get_sparPositions().get_sparPosition()[3].get_eta().valueOf_)
etaSparFuselage = eval(cpacsComponentSegment.get_structure().get_spars(
).get_sparPositions().get_sparPosition()[4].get_eta().valueOf_)
etaSparKink = eval(cpacsComponentSegment.get_structure().get_spars(
).get_sparPositions().get_sparPosition()[5].get_eta().valueOf_)
etaSparTip = eval(cpacsComponentSegment.get_structure().get_spars(
).get_sparPositions().get_sparPosition()[6].get_eta().valueOf_)
xsiSpar_interp = scipy.interpolate.interp1d(
[etaSparRoot, etaSparFuselage, etaSparKink, etaSparTip],
[xsiSparRoot, xsiSparFuselage, xsiSparKink, xsiSparTip])
sparOffset = 0.1
wingSpan = parentWingVAMPzero.span.getValue() / 2.
#===========================================================================
# Outer Shape
#===========================================================================
# The outer border eta station is set to 96 percent
outerEtaLE = 0.96
# The outer chord station is determined from the wing's chord at eta = 0.96
# and the rear spar location + the spar offset
outerXsiLE = xsiSpar_interp(0.96) + sparOffset
outerWingChord = calcChordLengthAtEta(outerEtaLE, parentWingVAMPzero,
cpacsWing)
cTip = (1 - outerXsiLE) * outerWingChord
# now we need to determine the necessary span for the aileron by gently increasing the span
# this is an iterative process as the chord of the aileron is a function of the inbound span
aileronArea = parentWingVAMPzero.aileron.refArea.getValue()
delta = 0.01
calcArea = 0.
while abs(calcArea - aileronArea) > 0.1:
if delta > outerEtaLE:
parentWingVAMPzero.log.warning(
'VAMPzero EXPORT: Cannot determine the span of the aileron')
parentWingVAMPzero.log.warning('VAMPzero EXPORT: aileronArea= ' +
str(aileronArea))
parentWingVAMPzero.log.warning(
'VAMPzero EXPORT: Decreasing Spar Offset')
sparOffset = sparOffset - 0.02
delta = 0.01
innerEtaLE = outerEtaLE - delta
innerXsiLE = xsiSpar_interp(innerEtaLE) + sparOffset
innerWingChord = calcChordLengthAtEta(innerEtaLE, parentWingVAMPzero,
cpacsWing)
cRoot = (1 - innerXsiLE) * innerWingChord
calcArea = (cTip + cRoot) / 2 * (outerEtaLE - innerEtaLE) * wingSpan
delta += 0.005
# start outer shape
myleadingEdgeShape = leadingEdgeShapeType(
relHeightLE=doubleBaseType(valueOf_=str(0.5)),
xsiUpperSkin=doubleBaseType(valueOf_=str(0.85)),
xsiLowerSkin=doubleBaseType(valueOf_=str(0.85)))
innerBorder = controlSurfaceBorderTrailingEdgeType(
etaLE=doubleBaseType(valueOf_=str(innerEtaLE)),
etaTE=doubleBaseType(valueOf_=str(innerEtaLE)),
xsiLE=doubleBaseType(valueOf_=str(innerXsiLE)),
leadingEdgeShape=myleadingEdgeShape)
outerBorder = controlSurfaceBorderTrailingEdgeType(
etaLE=doubleBaseType(valueOf_=str(outerEtaLE)),
etaTE=doubleBaseType(valueOf_=str(outerEtaLE)),
xsiLE=doubleBaseType(valueOf_=str(outerXsiLE)),
leadingEdgeShape=myleadingEdgeShape)
myOuterShape = controlSurfaceOuterShapeTrailingEdgeType(
innerBorder=innerBorder, outerBorder=outerBorder)
# structure
myStructure = wingComponentSegmentStructureType()
cpacsAileron = trailingEdgeDeviceType(uID='aileronUID',
name=myName,
description=myDescription,
parentUID=myParentUID,
outerShape=myOuterShape,
structure=myStructure)
createAileronStructure(cpacsAileron)
# Forward information about innerEtaLE to the flap
parentWingVAMPzero.flap.maxEta = parameter(
value=innerEtaLE,
doc=
'This it the inner position of the aileron, the flap may not exceed it'
)
# moveables
deltaEta = outerEtaLE - innerEtaLE
innerParentXsi = xsiSpar_interp(innerEtaLE + 0.3 * deltaEta) + 0.02
outerParentXsi = xsiSpar_interp(innerEtaLE + 0.7 * deltaEta) + 0.02
createPath(cpacsAileron, 'aileron')
createTracks(cpacsAileron, 'aileron')
createActuators(cpacsAileron, 'aileron', [innerParentXsi, outerParentXsi])
if type(cpacsComponentSegment.get_controlSurfaces()) == NoneType:
cpacsComponentSegment.set_controlSurfaces(controlSurfacesType())
if type(cpacsComponentSegment.get_controlSurfaces().
get_trailingEdgeDevices()) == NoneType:
cpacsComponentSegment.get_controlSurfaces().set_trailingEdgeDevices(
trailingEdgeDevicesType())
cpacsComponentSegment.get_controlSurfaces().get_trailingEdgeDevices(
).add_trailingEdgeDevice(cpacsAileron)
def createRudder(parentVtpCPACS, parentVtpVAMPzero, myRudder):
'''
This is the main export method for the wings aileron
'''
cpacsPath = '/cpacs/vehicles/aircraft/model/wings/wing[' + parentVtpVAMPzero.id + ']'
cpacsVtp = getObjfromXpath(parentVtpCPACS, cpacsPath)
cpacsComponentSegment = cpacsVtp.get_componentSegments(
).get_componentSegment()[0]
#===========================================================================
# Header
#===========================================================================
myName = stringBaseType(None, None, None, 'rudder')
myDescription = stringBaseType(None, None, None, 'rudder from VAMPzero')
myParentUID = stringUIDBaseType(None, None, 'True', None, 'vtp_Cseg')
#===========================================================================
# Outer Shape
# With the rudder this is pretty simple as it is supposed to cover
# the same span as the VTP
#===========================================================================
# the inner border eta is determined from the rooYLocation of the Rudder and the vtp span
vtpSpan = parentVtpVAMPzero.span.getValue() / 2.
innerEtaLE = 0.
outerEtaLE = 1.
innerXsiLE = myRudder.cRoot.getValue() / parentVtpVAMPzero.cRoot.getValue()
outerXsiLE = myRudder.cTip.getValue() / parentVtpVAMPzero.cTip.getValue()
# start writing back
myleadingEdgeShape = leadingEdgeShapeType(
relHeightLE=doubleBaseType(valueOf_=str(0.5)),
xsiUpperSkin=doubleBaseType(valueOf_=str(0.85)),
xsiLowerSkin=doubleBaseType(valueOf_=str(0.85)))
innerBorder = controlSurfaceBorderTrailingEdgeType(
etaLE=doubleBaseType(valueOf_=str(innerEtaLE)),
xsiLE=doubleBaseType(valueOf_=str(innerXsiLE)),
leadingEdgeShape=myleadingEdgeShape)
outerBorder = controlSurfaceBorderTrailingEdgeType(
etaLE=doubleBaseType(valueOf_=str(outerEtaLE)),
xsiLE=doubleBaseType(valueOf_=str(outerXsiLE)),
leadingEdgeShape=myleadingEdgeShape)
myOuterShape = controlSurfaceOuterShapeTrailingEdgeType(
innerBorder=innerBorder, outerBorder=outerBorder)
cpacsRudder = trailingEdgeDeviceType(uID='rudderUID',
name=myName,
description=myDescription,
parentUID=myParentUID,
outerShape=myOuterShape)
createPath(cpacsRudder, 'rudder')
if type(cpacsComponentSegment.get_controlSurfaces()) == NoneType:
cpacsComponentSegment.set_controlSurfaces(controlSurfacesType())
if type(cpacsComponentSegment.get_controlSurfaces().
get_trailingEdgeDevices()) == NoneType:
cpacsComponentSegment.get_controlSurfaces().set_trailingEdgeDevices(
trailingEdgeDevicesType())
cpacsComponentSegment.get_controlSurfaces().get_trailingEdgeDevices(
).add_trailingEdgeDevice(cpacsRudder)