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 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 createFlapsSBW(parentWingCPACS, parentWingVAMPzero, myFlap):
'''
This is the main export method for the wings flaps
@todo: it is possible that the inner flap overlaps the kink area
'''
cpacsPath = '/cpacs/vehicles/aircraft/model/wings/wing[' + parentWingVAMPzero.id + ']'
cpacsWing = getObjfromXpath(parentWingCPACS, cpacsPath)
cpacsComponentSegment = cpacsWing.get_componentSegments(
).get_componentSegment()[0]
myFlaps = []
#===========================================================================
# 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])
yFus = parentWingVAMPzero.yFuselage.getValue()
span = parentWingVAMPzero.span.getValue() / 2.
etaFus = yFus / span
etaKink = parentWingVAMPzero.etaKink.getValue()
cRoot = parentWingVAMPzero.cRoot.getValue()
cKink = calcChordLengthAtEta(etaKink, parentWingVAMPzero, cpacsWing)
phiLE = parentWingVAMPzero.phiLE.getValue()
innerFlapArea = myFlap.refAreaInnerFlap.getValue()
outerFlapArea = myFlap.refAreaOuterFlap.getValue()
#===========================================================================
# OuterFlap
#===========================================================================
sparOffset = 0.08
# maxX is the maximum extension of the flap
maxX = cRoot * (1. - (xsiSparRoot + sparOffset)) / 2.
newOuterFlapArea = innerFlapArea + outerFlapArea
cRootOuterFlap = cRoot * (1. - (xsiSparRoot + sparOffset))
#===========================================================================
# Determine the total flap span by iteration
#===========================================================================
calcArea = 0.
spanOuterFlap = 0.
absSparOffset = sparOffset * cKink
# Obtain the maxEtaValue. This is forwarded from the ailerons export routine.
maxEta = myFlap.maxEta.getValue() - 0.02
# the tip root length is a function of the span (as the xsi location of the spar changes)
while abs(calcArea - newOuterFlapArea) > 0.1:
spanOuterFlap += .01
cTipOuterFlap = calcChordLengthAtEta(
etaFus + spanOuterFlap / span, parentWingVAMPzero, cpacsWing
) * (1 - xsiSpar_interp(etaFus + spanOuterFlap / span)) - absSparOffset
oldcalcArea = calcArea
calcArea = spanOuterFlap * (cRootOuterFlap + cTipOuterFlap) / 2.
if calcArea < oldcalcArea:
log.warning(
'VAMPzero FLAP: Outer Flap Area can not be established decreasing spar offset by 2% chord!'
)
sparOffset = sparOffset - 0.02
calcArea = 0.
spanOuterFlap = 0.
absSparOffset = sparOffset * cKink
break
if spanOuterFlap / span + etaFus > maxEta:
log.warning(
'VAMPzero FLAP: Outer Flap overlaps with the aileron decreasing spar offset by 2% chord!'
)
sparOffset = sparOffset - 0.02
calcArea = 0.
spanOuterFlap = 0.
absSparOffset = sparOffset * cRoot
break
while abs(calcArea - newOuterFlapArea) > 0.1:
spanOuterFlap += .01
cTipOuterFlap = calcChordLengthAtEta(
etaKink + spanOuterFlap / span, parentWingVAMPzero, cpacsWing) * (
1 -
xsiSpar_interp(etaKink + spanOuterFlap / span)) - absSparOffset
oldcalcArea = calcArea
calcArea = spanOuterFlap * (cRootOuterFlap + cTipOuterFlap) / 2.
if calcArea < oldcalcArea:
log.warning(
'VAMPzero FLAP: Outer Flap Area can not be established! Continuing with outerArea = %s'
% str(calcArea))
newOuterFlapArea = calcArea
break
if spanOuterFlap / span + etaFus > maxEta:
log.warning(
'VAMPzero FLAP: Outer Flap overlaps with the aileron! Continuing with outerArea = %s'
% str(calcArea))
newOuterFlapArea = calcArea
break
#===========================================================================
# Determine the number of flaps
# The aspect ratio of a flap should not be higher than 6.
#===========================================================================
nOuterFlaps = spanOuterFlap**2. / (newOuterFlapArea * 6.)
log.debug(
'VAMPzero FLAP: Exporting %s Flaps outboard of the engine for an area of %s m2.'
% (str(nOuterFlaps), str(newOuterFlapArea)))
#===========================================================================
# 1 Flap
#===========================================================================
if nOuterFlaps <= 1.:
# the inner border eta is located at the kink
innerEtaLE = etaFus + 0.05
innerXsiLE = xsiSparRoot + sparOffset
# the outer border eta is determined from the span of the outer flap
outerEtaLE = etaFus + 0.05 + spanOuterFlap / span
outerXsiLE = 1 - (cTipOuterFlap / calcChordLengthAtEta(
outerEtaLE, parentWingVAMPzero, cpacsWing))
#Fowler Motion is restricted to 75% of the flap depth
innerX = (1. - innerXsiLE) * calcChordLengthAtEta(
innerEtaLE, parentWingVAMPzero, cpacsWing) * 0.5
outerX = (1. - outerXsiLE) * calcChordLengthAtEta(
outerEtaLE, parentWingVAMPzero, cpacsWing) * 0.5
myFlaps.append(
createFlap('outerFlap1',
parentWingVAMPzero.id,
innerEtaLE,
innerXsiLE,
outerEtaLE,
outerXsiLE,
maxX,
appendInnerCruiseRoller=True,
type='flap',
innerX=innerX,
outerX=outerX))
#===========================================================================
# 2 Flaps
#===========================================================================
elif nOuterFlaps > 1. and nOuterFlaps <= 2.:
# the inner border eta is located at the kink
innerEtaLE = etaFus + 0.05
innerXsiLE = xsiSparKink + sparOffset
# the outer border eta is determined from the half span of the total outer flap
outerEtaLE = etaFus + 0.05 + spanOuterFlap / (2 * span)
outerXsiLE = xsiSpar_interp(
outerEtaLE) + absSparOffset / calcChordLengthAtEta(
outerEtaLE, parentWingVAMPzero, cpacsWing)
#Fowler Motion is restricted to 75% of the flap depth
innerX = (1. - innerXsiLE) * calcChordLengthAtEta(
innerEtaLE, parentWingVAMPzero, cpacsWing) * 0.5
outerX = (1. - outerXsiLE) * calcChordLengthAtEta(
outerEtaLE, parentWingVAMPzero, cpacsWing) * 0.5
myFlaps.append(
createFlap('outerFlap1',
parentWingVAMPzero.id,
innerEtaLE,
innerXsiLE,
outerEtaLE,
outerXsiLE,
maxX,
type='flap',
innerX=innerX,
outerX=outerX))
# new inner is the old outer
innerEtaLE = outerEtaLE
innerXsiLE = outerXsiLE
# the outer border eta is determined from the full span of the total outer flap
outerEtaLE = etaFus + 0.05 + spanOuterFlap / span
outerXsiLE = 1 - (cTipOuterFlap / calcChordLengthAtEta(
outerEtaLE, parentWingVAMPzero, cpacsWing))
#Fowler Motion is restricted to 75% of the flap depth
innerX = (1. - innerXsiLE) * calcChordLengthAtEta(
innerEtaLE, parentWingVAMPzero, cpacsWing) * 0.5
outerX = (1. - outerXsiLE) * calcChordLengthAtEta(
outerEtaLE, parentWingVAMPzero, cpacsWing) * 0.5
myFlaps.append(
createFlap('outerFlap2',
parentWingVAMPzero.id,
innerEtaLE,
innerXsiLE,
outerEtaLE,
outerXsiLE,
maxX,
appendInnerCruiseRoller=True,
type='flap',
innerX=innerX,
outerX=outerX))
#===========================================================================
# n Flaps
#===========================================================================
elif nOuterFlaps > 2.:
n = int(ceil(nOuterFlaps))
# First Flap
# the inner border eta is located at the kink
innerEtaLE = etaFus + 0.05
innerXsiLE = xsiSparKink + sparOffset
# the outer border eta is determined from the half span of the total outer flap
outerEtaLE = etaFus + 0.05 + spanOuterFlap / (n * span)
outerXsiLE = xsiSpar_interp(
outerEtaLE) + absSparOffset / calcChordLengthAtEta(
outerEtaLE, parentWingVAMPzero, cpacsWing)
#Fowler Motion is restricted to 75% of the flap depth
innerX = (1. - innerXsiLE) * calcChordLengthAtEta(
innerEtaLE, parentWingVAMPzero, cpacsWing) * 0.5
outerX = (1. - outerXsiLE) * calcChordLengthAtEta(
outerEtaLE, parentWingVAMPzero, cpacsWing) * 0.5
myFlaps.append(
createFlap('outerFlap1',
parentWingVAMPzero.id,
innerEtaLE,
innerXsiLE,
outerEtaLE,
outerXsiLE,
maxX,
type='flap',
innerX=innerX,
outerX=outerX))
for i in range(2, n):
# nth Flap
# new inner is the old outer
innerEtaLE = outerEtaLE
innerXsiLE = outerXsiLE
# the outer border eta is determined from the full span of the total outer flap
outerEtaLE = innerEtaLE + spanOuterFlap / n / span
outerXsiLE = xsiSpar_interp(
outerEtaLE) + absSparOffset / calcChordLengthAtEta(
outerEtaLE, parentWingVAMPzero, cpacsWing)
#Fowler Motion is restricted to 75% of the flap depth
innerX = (1. - innerXsiLE) * calcChordLengthAtEta(
innerEtaLE, parentWingVAMPzero, cpacsWing) * 0.5
outerX = (1. - outerXsiLE) * calcChordLengthAtEta(
outerEtaLE, parentWingVAMPzero, cpacsWing) * 0.5
myFlaps.append(
createFlap('outerFlap' + str(i),
parentWingVAMPzero.id,
innerEtaLE,
innerXsiLE,
outerEtaLE,
outerXsiLE,
maxX,
appendInnerCruiseRoller=True,
type='flap',
innerX=innerX,
outerX=outerX))
# Last Flap
# new inner is the old outer
innerEtaLE = outerEtaLE
innerXsiLE = outerXsiLE
# the outer border eta is determined from the full span of the total outer flap
outerEtaLE = etaFus + 0.05 + spanOuterFlap / span
outerXsiLE = 1 - (cTipOuterFlap / calcChordLengthAtEta(
outerEtaLE, parentWingVAMPzero, cpacsWing))
#Fowler Motion is restricted to 75% of the flap depth
innerX = (1. - innerXsiLE) * calcChordLengthAtEta(
innerEtaLE, parentWingVAMPzero, cpacsWing) * 0.5
outerX = (1. - outerXsiLE) * calcChordLengthAtEta(
outerEtaLE, parentWingVAMPzero, cpacsWing) * 0.5
myFlaps.append(
createFlap('outerFlap' + str(n),
parentWingVAMPzero.id,
innerEtaLE,
innerXsiLE,
outerEtaLE,
outerXsiLE,
maxX,
appendInnerCruiseRoller=True,
type='flap',
innerX=innerX,
outerX=outerX))
#===============================================================================
# Output to Spoiler
# as the spoiler is relying on data of the flaps some basic information is written
# back to the the VAMPzero components
#===============================================================================
parentWingVAMPzero.spoiler.outerEta = parameter(
parent=parentWingVAMPzero.spoiler,
value=outerEtaLE,
unit='',
status='calc',
doc=
'The outermost eta coordinate of all flaps. This overlaps with the outer eta coordinate of the spoiler'
)
spoilerChord = maxX
parentWingVAMPzero.spoiler.chord = parameter(
spoilerChord,
'm',
'calc',
'The absolute chord of the spoiler: 5% of the kink chord length + 50% of the innerFlap Chord length',
parent=parentWingVAMPzero.spoiler)
#===========================================================================
# Output to CPACS
#===========================================================================
if type(cpacsComponentSegment.get_controlSurfaces()) == NoneType:
cpacsComponentSegment.set_controlSurfaces(controlSurfacesType())
if type(cpacsComponentSegment.get_controlSurfaces().
get_trailingEdgeDevices()) == NoneType:
cpacsComponentSegment.get_controlSurfaces().set_trailingEdgeDevices(
trailingEdgeDevicesType())
log.debug('VAMPzero SLAT: Exporting %s Flaps to CPACS.' %
(str(len(myFlaps))))
for flap in myFlaps:
cpacsComponentSegment.get_controlSurfaces().get_trailingEdgeDevices(
).add_trailingEdgeDevice(flap)
def createFlapsSBW(parentWingCPACS, parentWingVAMPzero, myFlap):
'''
This is the main export method for the wings flaps for the strut braced wing.
The SBW does not feature any inner flaps as no kink exists
@todo: it is possible that the inner flap overlaps the kink area
'''
cpacsPath = '/cpacs/vehicles/aircraft/model/wings/wing[' + parentWingVAMPzero.id + ']'
cpacsWing = getObjfromXpath(parentWingCPACS, cpacsPath)
cpacsComponentSegment = cpacsWing.get_componentSegments().get_componentSegment()[0]
myFlaps = []
# 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)
yFus = parentWingVAMPzero.yFuselage.getValue()
span = parentWingVAMPzero.span.getValue() / 2.
etaFus = yFus / span
etaKink = parentWingVAMPzero.etaKink.getValue()
cRoot = parentWingVAMPzero.cRoot.getValue()
cKink = calcChordLengthAtEta(etaKink, parentWingVAMPzero, cpacsWing)
innerFlapArea = myFlap.refAreaInnerFlap.getValue()
outerFlapArea = myFlap.refAreaOuterFlap.getValue()
# OuterFlap
sparOffset = 0.08
# maxX is the maximum extension of the flap
maxX = cRoot * (1. - (xsis[0] + sparOffset)) /2.
newOuterFlapArea = innerFlapArea + outerFlapArea
cRootOuterFlap = cRoot * (1. - (xsis[0] + sparOffset))
# Determine the total flap span by iteration
calcArea = 0.
spanOuterFlap = 0.
absSparOffset = sparOffset * cKink
# Obtain the maxEtaValue. This is forwarded from the ailerons export routine.
maxEta = myFlap.maxEta.getValue() - 0.02
# the tip root length is a function of the span (as the xsi location of the spar changes)
while abs(calcArea - newOuterFlapArea) > 0.1:
spanOuterFlap += .01
cTipOuterFlap = calcChordLengthAtEta(etaFus + spanOuterFlap / span, parentWingVAMPzero, cpacsWing) * (1 - xsiSpar_interp(etaFus + spanOuterFlap / span)) - absSparOffset
oldcalcArea = calcArea
calcArea = spanOuterFlap * (cRootOuterFlap + cTipOuterFlap) / 2.
if calcArea < oldcalcArea:
log.warning('VAMPzero FLAP: Outer Flap Area can not be established decreasing spar offset by 2% chord!')
sparOffset = sparOffset - 0.02
calcArea = 0.
spanOuterFlap = 0.
absSparOffset = sparOffset * cKink
break
if spanOuterFlap / span + etaFus > maxEta:
log.warning('VAMPzero FLAP: Outer Flap overlaps with the aileron decreasing spar offset by 2% chord!')
sparOffset = sparOffset - 0.02
calcArea = 0.
spanOuterFlap = 0.
absSparOffset = sparOffset * cRoot
break
while abs(calcArea - newOuterFlapArea) > 0.1:
spanOuterFlap += .01
cTipOuterFlap = calcChordLengthAtEta(etaFus + spanOuterFlap / span, parentWingVAMPzero, cpacsWing) * (1 - xsiSpar_interp(etaFus + spanOuterFlap / span)) - absSparOffset
oldcalcArea = calcArea
calcArea = spanOuterFlap * (cRootOuterFlap + cTipOuterFlap) / 2.
if calcArea < oldcalcArea:
log.warning('VAMPzero FLAP: Outer Flap Area can not be established! Continuing with outerArea = %s' % str(calcArea))
newOuterFlapArea = calcArea
break
if spanOuterFlap / span + etaFus + 0.06 > maxEta:
log.warning('VAMPzero FLAP: Outer Flap overlaps with the aileron! Continuing with outerArea = %s' % str(calcArea))
newOuterFlapArea = calcArea
break
# Determine the number of flaps
# The aspect ratio of a flap should not be higher than 6.
nOuterFlaps = spanOuterFlap ** 2. / (newOuterFlapArea * 6.)
log.debug('VAMPzero FLAP: Exporting %s Flaps outboard of the engine for an area of %s m2.' % (str(nOuterFlaps), str(newOuterFlapArea)))
# 1 Flap
if nOuterFlaps <= 1.:
# the inner border eta is located at the kink
innerEtaLE = etaFus + 0.05
innerXsiLE = xsis[0] + sparOffset
# the outer border eta is determined from the span of the outer flap
outerEtaLE = etaFus + 0.05 + spanOuterFlap / span
outerXsiLE = 1 - (cTipOuterFlap / calcChordLengthAtEta(outerEtaLE, parentWingVAMPzero, cpacsWing))
#Fowler Motion is restricted to 75% of the flap depth
innerX = (1. - innerXsiLE) * calcChordLengthAtEta(innerEtaLE, parentWingVAMPzero, cpacsWing) * 0.5
outerX = (1. - outerXsiLE) * calcChordLengthAtEta(outerEtaLE, parentWingVAMPzero, cpacsWing) * 0.5
myFlaps.append(createFlap('outerFlap1', parentWingVAMPzero.id, innerEtaLE, innerXsiLE, outerEtaLE, outerXsiLE, maxX, appendInnerCruiseRoller=True, type='flap', innerX=innerX, outerX=outerX))
# 2 Flaps
elif nOuterFlaps > 1. and nOuterFlaps <= 2.:
# the inner border eta is located at the kink
innerEtaLE = etaFus + 0.05
innerXsiLE = xsis[2] + sparOffset
# the outer border eta is determined from the half span of the total outer flap
outerEtaLE = etaFus + 0.05 + spanOuterFlap / (2*span)
outerXsiLE = xsiSpar_interp(outerEtaLE) + absSparOffset / calcChordLengthAtEta(outerEtaLE, parentWingVAMPzero, cpacsWing)
#Fowler Motion is restricted to 75% of the flap depth
innerX = (1. - innerXsiLE) * calcChordLengthAtEta(innerEtaLE, parentWingVAMPzero, cpacsWing) * 0.5
outerX = (1. - outerXsiLE) * calcChordLengthAtEta(outerEtaLE, parentWingVAMPzero, cpacsWing) * 0.5
myFlaps.append(createFlap('outerFlap1', parentWingVAMPzero.id, innerEtaLE, innerXsiLE, outerEtaLE, outerXsiLE, maxX, type='flap', innerX=innerX, outerX=outerX))
# new inner is the old outer
innerEtaLE = outerEtaLE
innerXsiLE = outerXsiLE
# the outer border eta is determined from the full span of the total outer flap
outerEtaLE = etaFus + 0.05 + spanOuterFlap / span
outerXsiLE = 1 - (cTipOuterFlap / calcChordLengthAtEta(outerEtaLE, parentWingVAMPzero, cpacsWing))
#Fowler Motion is restricted to 75% of the flap depth
innerX = (1. - innerXsiLE) * calcChordLengthAtEta(innerEtaLE, parentWingVAMPzero, cpacsWing) * 0.5
outerX = (1. - outerXsiLE) * calcChordLengthAtEta(outerEtaLE, parentWingVAMPzero, cpacsWing) * 0.5
myFlaps.append(createFlap('outerFlap2', parentWingVAMPzero.id, innerEtaLE, innerXsiLE, outerEtaLE, outerXsiLE, maxX, appendInnerCruiseRoller=True, type='flap', innerX=innerX, outerX=outerX))
# n Flaps
elif nOuterFlaps > 2. :
n = int(ceil(nOuterFlaps))
# First Flap
# the inner border eta is located at the kink
innerEtaLE = etaFus + 0.05
innerXsiLE = xsis[2] + sparOffset
# the outer border eta is determined from the half span of the total outer flap
outerEtaLE = etaFus + 0.05 + spanOuterFlap / (n*span)
outerXsiLE = xsiSpar_interp(outerEtaLE) + absSparOffset / calcChordLengthAtEta(outerEtaLE, parentWingVAMPzero, cpacsWing)
#Fowler Motion is restricted to 75% of the flap depth
innerX = (1. - innerXsiLE) * calcChordLengthAtEta(innerEtaLE, parentWingVAMPzero, cpacsWing) * 0.5
outerX = (1. - outerXsiLE) * calcChordLengthAtEta(outerEtaLE, parentWingVAMPzero, cpacsWing) * 0.5
myFlaps.append(createFlap('outerFlap1', parentWingVAMPzero.id, innerEtaLE, innerXsiLE, outerEtaLE, outerXsiLE, maxX, type='flap', innerX=innerX, outerX=outerX))
for i in range(2, n):
# nth Flap
# new inner is the old outer
innerEtaLE = outerEtaLE
innerXsiLE = outerXsiLE
# the outer border eta is determined from the full span of the total outer flap
outerEtaLE = innerEtaLE + spanOuterFlap / n / span
outerXsiLE = xsiSpar_interp(outerEtaLE) + absSparOffset / calcChordLengthAtEta(outerEtaLE, parentWingVAMPzero, cpacsWing)
#Fowler Motion is restricted to 75% of the flap depth
innerX = (1. - innerXsiLE) * calcChordLengthAtEta(innerEtaLE, parentWingVAMPzero, cpacsWing) * 0.5
outerX = (1. - outerXsiLE) * calcChordLengthAtEta(outerEtaLE, parentWingVAMPzero, cpacsWing) * 0.5
myFlaps.append(createFlap('outerFlap' + str(i), parentWingVAMPzero.id, innerEtaLE, innerXsiLE, outerEtaLE, outerXsiLE, maxX, appendInnerCruiseRoller=True, type='flap', innerX=innerX, outerX=outerX))
# Last Flap
# new inner is the old outer
innerEtaLE = outerEtaLE
innerXsiLE = outerXsiLE
# the outer border eta is determined from the full span of the total outer flap
outerEtaLE = etaFus + 0.05 + spanOuterFlap / span
outerXsiLE = 1 - (cTipOuterFlap / calcChordLengthAtEta(outerEtaLE, parentWingVAMPzero, cpacsWing))
#Fowler Motion is restricted to 75% of the flap depth
innerX = (1. - innerXsiLE) * calcChordLengthAtEta(innerEtaLE, parentWingVAMPzero, cpacsWing) * 0.5
outerX = (1. - outerXsiLE) * calcChordLengthAtEta(outerEtaLE, parentWingVAMPzero, cpacsWing) * 0.5
myFlaps.append(createFlap('outerFlap' + str(n), parentWingVAMPzero.id, innerEtaLE, innerXsiLE, outerEtaLE, outerXsiLE, maxX, appendInnerCruiseRoller=True, type='flap', innerX=innerX, outerX=outerX))
# Output to Spoiler
# as the spoiler is relying on data of the flaps some basic information is written
# back to the the VAMPzero components
parentWingVAMPzero.spoiler.outerEta = parameter(parent=parentWingVAMPzero.spoiler, value=outerEtaLE, unit='', status='calc', doc='The outermost eta coordinate of all flaps. This overlaps with the outer eta coordinate of the spoiler')
spoilerChord = maxX
parentWingVAMPzero.spoiler.chord = parameter(spoilerChord, 'm', 'calc', 'The absolute chord of the spoiler: 5% of the kink chord length + 50% of the innerFlap Chord length', parent=parentWingVAMPzero.spoiler)
# Output to CPACS
if type(cpacsComponentSegment.get_controlSurfaces()) == NoneType:
cpacsComponentSegment.set_controlSurfaces(controlSurfacesType())
if type(cpacsComponentSegment.get_controlSurfaces().get_trailingEdgeDevices()) == NoneType:
cpacsComponentSegment.get_controlSurfaces().set_trailingEdgeDevices(trailingEdgeDevicesType())
log.debug('VAMPzero SLAT: Exporting %s Flaps to CPACS.' % (str(len(myFlaps))))
for flap in myFlaps:
cpacsComponentSegment.get_controlSurfaces().get_trailingEdgeDevices().add_trailingEdgeDevice(flap)
def createFlapsAdvDoubleTrapezoid(parentWingCPACS, parentWingVAMPzero, myFlap):
'''
This is the main export method for the wings flaps
@todo: it is possible that the inner flap overlaps the kink area
'''
cpacsPath = '/cpacs/vehicles/aircraft/model/wings/wing[' + parentWingVAMPzero.id + ']'
cpacsWing = getObjfromXpath(parentWingCPACS, cpacsPath)
cpacsComponentSegment = cpacsWing.get_componentSegments().get_componentSegment()[0]
myFlaps = []
# 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])
yFus = parentWingVAMPzero.yFuselage.getValue()
span = parentWingVAMPzero.span.getValue() / 2.
etaFus = yFus / span
etaKink = parentWingVAMPzero.etaKink.getValue()
cRoot = parentWingVAMPzero.cRoot.getValue()
cKink = calcChordLengthAtEta(etaKink, parentWingVAMPzero, cpacsWing)
phiLE = parentWingVAMPzero.phiLE.getValue()
innerFlapArea = myFlap.refAreaInnerFlap.getValue()
outerFlapArea = myFlap.refAreaOuterFlap.getValue()
# InnerFlap
# Determine the number of flaps
# The aspect ratio of a flap should not be higher than 9.
sparOffset = 0.08
if phiLE > 0.:
# if the wing is backward swept the chord of the inner flap equals the chord at kink behind the rear spar + sparOffset
cInnerFlap = cKink * (1. - (xsiSparKink + sparOffset))
elif phiLE < 0.:
# if the wing is forward swept the chord of the inner flap is similar to the chord of the root section behind the spar + 20%
cInnerFlap = cRoot * (1. - (xsiSparFuselage + 0.2))
# maxX is the maximum extension of the flap
maxX = cInnerFlap / 2.
# The area of the innerFlap is determined by the chord and span
# The difference in the area will be substituted by the outerFlap Area
spanInnerFlap = (etaKink - etaFus) * span
newInnerFlapArea = cInnerFlap * spanInnerFlap
deltaArea = innerFlapArea - newInnerFlapArea
nInnerFlaps = spanInnerFlap ** 2. / (newInnerFlapArea * 9.)
log.debug('VAMPzero FLAP: Exporting %s Flaps inside of the engine for an area of %s m2.' % (str(nInnerFlaps), str(innerFlapArea)))
if nInnerFlaps < 1.:
# the inner border eta is located at the intersection with the fuselage
innerEtaLE = etaFus
# the inner border xsi is determined from the wing chord at the fuselage station (which equals CRoot)
innerXsiLE = 1. - (cInnerFlap / cRoot)
# the outer border eta is determined from the span of the inner flap
outerEtaLE = etaKink
# the outer xsi location is found from the avg chord and the chord length at that station
outerXsiLE = 1. - (cInnerFlap / cKink)
myFlaps.append(createFlap('innerFlap', parentWingVAMPzero.id, innerEtaLE, innerXsiLE, outerEtaLE, outerXsiLE, maxX, type='innerFlap', innerX=maxX, outerX=maxX))
elif nInnerFlaps > 1. and nInnerFlaps <= 2.:
# First Flap
# the inner border eta is located at the intersection with the fuselage
innerEtaLE = etaFus
# the inner border xsi is determined from the wing chord at the fuselage station (which equals CRoot)
innerXsiLE = 1. - (cInnerFlap / cRoot)
# the outer border eta is determined from the span of the inner flap
outerEtaLE = etaFus + (etaKink - etaFus) / 2.
# the outer xsi location is found from the avg chord and the chord length at that station
outerXsiLE = 1. - (cInnerFlap / calcChordLengthAtEta(outerEtaLE, parentWingVAMPzero, cpacsWing))
myFlaps.append(createFlap('innerFlap1', parentWingVAMPzero.id, innerEtaLE, innerXsiLE, outerEtaLE, outerXsiLE, maxX, type='innerFlap', innerX=maxX, outerX=maxX))
# Second Flap
# new inner is old outer
innerEtaLE = outerEtaLE
# new outer is kink
outerEtaLE = etaKink
# new inner is old outer
innerXsiLE = outerXsiLE
# new outer is kink
outerXsiLE = 1. - (cInnerFlap / cKink)
myFlaps.append(createFlap('innerFlap2', parentWingVAMPzero.id, innerEtaLE, innerXsiLE, outerEtaLE, outerXsiLE, maxX, type='flap', innerX=maxX, outerX=maxX))
# OuterFlap
newOuterFlapArea = outerFlapArea + deltaArea
cRootOuterFlap = cKink * (1. - (xsiSparKink + sparOffset))
# Determine the total flap span by iteration
calcArea = 0.
spanOuterFlap = 0.
absSparOffset = sparOffset * cKink
# Obtain the maxEtaValue. This is forwarded from the ailerons export routine.
maxEta = myFlap.maxEta.getValue() - 0.02
# the tip root length is a function of the span (as the xsi location of the spar changes)
while abs(calcArea - newOuterFlapArea) > 0.1:
spanOuterFlap += .01
cTipOuterFlap = calcChordLengthAtEta(etaKink + spanOuterFlap / span, parentWingVAMPzero, cpacsWing) * (1 - xsiSpar_interp(etaKink + spanOuterFlap / span)) - absSparOffset
oldcalcArea = calcArea
calcArea = spanOuterFlap * (cRootOuterFlap + cTipOuterFlap) / 2.
if calcArea < oldcalcArea:
log.warning('VAMPzero FLAP: Outer Flap Area can not be established decreasing spar offset by 2% chord!')
sparOffset = sparOffset - 0.02
calcArea = 0.
spanOuterFlap = 0.
absSparOffset = sparOffset * cKink
break
if spanOuterFlap / span + etaKink > maxEta:
log.warning('VAMPzero FLAP: Outer Flap overlaps with the aileron decreasing spar offset by 2% chord!')
sparOffset = sparOffset - 0.02
calcArea = 0.
spanOuterFlap = 0.
absSparOffset = sparOffset * cKink
break
while abs(calcArea - newOuterFlapArea) > 0.1:
spanOuterFlap += .01
cTipOuterFlap = calcChordLengthAtEta(etaKink + spanOuterFlap / span, parentWingVAMPzero, cpacsWing) * (1 - xsiSpar_interp(etaKink + spanOuterFlap / span)) - absSparOffset
oldcalcArea = calcArea
calcArea = spanOuterFlap * (cRootOuterFlap + cTipOuterFlap) / 2.
if calcArea < oldcalcArea:
log.warning('VAMPzero FLAP: Outer Flap Area can not be established! Continuing with outerArea = %s' % str(calcArea))
newOuterFlapArea = calcArea
break
if spanOuterFlap / span + etaKink > maxEta:
log.warning('VAMPzero FLAP: Outer Flap overlaps with the aileron! Continuing with outerArea = %s' % str(calcArea))
newOuterFlapArea = calcArea
break
# Determine the number of flaps
# The aspect ratio of a flap should not be higher than 9.
nOuterFlaps = spanOuterFlap ** 2. / (newOuterFlapArea * 9.)
log.debug('VAMPzero FLAP: Exporting %s Flaps outboard of the engine for an area of %s m2.' % (str(nOuterFlaps), str(newOuterFlapArea)))
# 1 Flap
if nOuterFlaps <= 1.:
# the inner border eta is located at the kink
innerEtaLE = etaKink
innerXsiLE = xsiSparKink + sparOffset
# the outer border eta is determined from the span of the outer flap
outerEtaLE = etaKink + spanOuterFlap / span
outerXsiLE = 1 - (cTipOuterFlap / calcChordLengthAtEta(outerEtaLE, parentWingVAMPzero, cpacsWing))
#Fowler Motion is restricted to 75% of the flap depth
innerX = (1. - innerXsiLE) * calcChordLengthAtEta(innerEtaLE, parentWingVAMPzero, cpacsWing) * 0.5
outerX = (1. - outerXsiLE) * calcChordLengthAtEta(outerEtaLE, parentWingVAMPzero, cpacsWing) * 0.5
myFlaps.append(createFlap('outerFlap1', parentWingVAMPzero.id, innerEtaLE, innerXsiLE, outerEtaLE, outerXsiLE, maxX, appendInnerCruiseRoller=True, type='flap', innerX=innerX, outerX=outerX))
# 2 Flaps
elif nOuterFlaps > 1. and nOuterFlaps <= 2.:
# the inner border eta is located at the kink
innerEtaLE = etaKink
innerXsiLE = xsiSparKink + sparOffset
# the outer border eta is determined from the half span of the total outer flap
outerEtaLE = etaKink + spanOuterFlap / (2. * span)
outerXsiLE = xsiSpar_interp(outerEtaLE) + absSparOffset / calcChordLengthAtEta(outerEtaLE, parentWingVAMPzero, cpacsWing)
#Fowler Motion is restricted to 75% of the flap depth
innerX = (1. - innerXsiLE) * calcChordLengthAtEta(innerEtaLE, parentWingVAMPzero, cpacsWing) * 0.5
outerX = (1. - outerXsiLE) * calcChordLengthAtEta(outerEtaLE, parentWingVAMPzero, cpacsWing) * 0.5
myFlaps.append(createFlap('outerFlap1', parentWingVAMPzero.id, innerEtaLE, innerXsiLE, outerEtaLE, outerXsiLE, maxX, type='flap', innerX=innerX, outerX=outerX))
# new inner is the old outer
innerEtaLE = outerEtaLE
innerXsiLE = outerXsiLE
# the outer border eta is determined from the full span of the total outer flap
outerEtaLE = etaKink + spanOuterFlap / span
outerXsiLE = 1 - (cTipOuterFlap / calcChordLengthAtEta(outerEtaLE, parentWingVAMPzero, cpacsWing))
#Fowler Motion is restricted to 75% of the flap depth
innerX = (1. - innerXsiLE) * calcChordLengthAtEta(innerEtaLE, parentWingVAMPzero, cpacsWing) * 0.5
outerX = (1. - outerXsiLE) * calcChordLengthAtEta(outerEtaLE, parentWingVAMPzero, cpacsWing) * 0.5
myFlaps.append(createFlap('outerFlap2', parentWingVAMPzero.id, innerEtaLE, innerXsiLE, outerEtaLE, outerXsiLE, maxX, appendInnerCruiseRoller=True, type='flap', innerX=innerX, outerX=outerX))
# n Flaps
elif nOuterFlaps > 2. :
n = int(ceil(nOuterFlaps))
# First Flap
# the inner border eta is located at the kink
innerEtaLE = etaKink
innerXsiLE = xsiSparKink + sparOffset
# the outer border eta is determined from the half span of the total outer flap
outerEtaLE = etaKink + spanOuterFlap / n / span
outerXsiLE = xsiSpar_interp(outerEtaLE) + absSparOffset / calcChordLengthAtEta(outerEtaLE, parentWingVAMPzero, cpacsWing)
#Fowler Motion is restricted to 75% of the flap depth
innerX = (1. - innerXsiLE) * calcChordLengthAtEta(innerEtaLE, parentWingVAMPzero, cpacsWing) * 0.5
outerX = (1. - outerXsiLE) * calcChordLengthAtEta(outerEtaLE, parentWingVAMPzero, cpacsWing) * 0.5
myFlaps.append(createFlap('outerFlap1', parentWingVAMPzero.id, innerEtaLE, innerXsiLE, outerEtaLE, outerXsiLE, maxX, type='flap', innerX=innerX, outerX=outerX))
for i in range(2, n):
# nth Flap
# new inner is the old outer
innerEtaLE = outerEtaLE
innerXsiLE = outerXsiLE
# the outer border eta is determined from the full span of the total outer flap
outerEtaLE = innerEtaLE + spanOuterFlap / n / span
outerXsiLE = xsiSpar_interp(outerEtaLE) + absSparOffset / calcChordLengthAtEta(outerEtaLE, parentWingVAMPzero, cpacsWing)
#Fowler Motion is restricted to 75% of the flap depth
innerX = (1. - innerXsiLE) * calcChordLengthAtEta(innerEtaLE, parentWingVAMPzero, cpacsWing) * 0.5
outerX = (1. - outerXsiLE) * calcChordLengthAtEta(outerEtaLE, parentWingVAMPzero, cpacsWing) * 0.5
myFlaps.append(createFlap('outerFlap' + str(i), parentWingVAMPzero.id, innerEtaLE, innerXsiLE, outerEtaLE, outerXsiLE, maxX, appendInnerCruiseRoller=True, type='flap', innerX=innerX, outerX=outerX))
# Last Flap
# new inner is the old outer
innerEtaLE = outerEtaLE
innerXsiLE = outerXsiLE
# the outer border eta is determined from the full span of the total outer flap
outerEtaLE = etaKink + spanOuterFlap / span
outerXsiLE = 1 - (cTipOuterFlap / calcChordLengthAtEta(outerEtaLE, parentWingVAMPzero, cpacsWing))
#Fowler Motion is restricted to 75% of the flap depth
innerX = (1. - innerXsiLE) * calcChordLengthAtEta(innerEtaLE, parentWingVAMPzero, cpacsWing) * 0.5
outerX = (1. - outerXsiLE) * calcChordLengthAtEta(outerEtaLE, parentWingVAMPzero, cpacsWing) * 0.5
myFlaps.append(createFlap('outerFlap' + str(n), parentWingVAMPzero.id, innerEtaLE, innerXsiLE, outerEtaLE, outerXsiLE, maxX, appendInnerCruiseRoller=True, type='flap', innerX=innerX, outerX=outerX))
# Output to Spoiler
# as the spoiler is relying on data of the flaps some basic information is written
# back to the the VAMPzero components
parentWingVAMPzero.spoiler.outerEta = parameter(outerEtaLE, '', 'calc', 'The outermost eta coordinate of all flaps. This overlaps with the outer eta coordinate of the spoiler', parent=parentWingVAMPzero.spoiler)
spoilerChord = 0.05 * cKink + 0.5 * cInnerFlap
parentWingVAMPzero.spoiler.chord = parameter(spoilerChord, 'm', 'calc', 'The absolute chord of the spoiler: 5% of the kink chord length + 50% of the innerFlap Chord length', parent=parentWingVAMPzero.spoiler)
# Output to CPACS
if type(cpacsComponentSegment.get_controlSurfaces()) == NoneType:
cpacsComponentSegment.set_controlSurfaces(controlSurfacesType())
if type(cpacsComponentSegment.get_controlSurfaces().get_trailingEdgeDevices()) == NoneType:
cpacsComponentSegment.get_controlSurfaces().set_trailingEdgeDevices(trailingEdgeDevicesType())
log.debug('VAMPzero SLAT: Exporting %s Flaps to CPACS.' % (str(len(myFlaps))))
for flap in myFlaps:
cpacsComponentSegment.get_controlSurfaces().get_trailingEdgeDevices().add_trailingEdgeDevice(flap)
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)