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 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 createSpoilers(parentWingCPACS, parentWingVAMPzero, mySpoiler):
'''
This is the main export method for the wing's spoilers
* It assumes a constant absolut chord for all spoilers
* Spoiler start outboard and move inboard close behind the rearspar
* They are rectangular
'''
cpacsPath = '/cpacs/vehicles/aircraft/model/wings/wing[' + parentWingVAMPzero.id + ']'
cpacsWing = getObjfromXpath(parentWingCPACS, cpacsPath)
cpacsComponentSegment = cpacsWing.get_componentSegments().get_componentSegment()[0]
mySpoilers = []
#===========================================================================
# Initialization, i.e. fetching values throughout the code
#===========================================================================
span = parentWingVAMPzero.span.getValue() / 2.
etaKink = parentWingVAMPzero.etaKink.getValue()
yFus = parentWingVAMPzero.yFuselage.getValue()
etaFus = yFus / span
spoilerArea = mySpoiler.refArea.getValue()
spoilerChord = mySpoiler.chord.getValue()
spoilerOuterEta = mySpoiler.outerEta.getValue()
sparOffset = 0.02
#===========================================================================
# Rear spar locations
#===========================================================================
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])
#===========================================================================
# Outer Spoilers
#===========================================================================
outerSpan = (spoilerOuterEta - etaKink) * span
outerArea = spoilerChord * outerSpan
nOuterSpoiler = outerSpan ** 2 / (outerArea * 2.)
log.debug('VAMPzero SPOILER: Exporting %s Spoiler outside of the kink for an area of %s m2.' % (str(nOuterSpoiler), str(outerArea)))
#===========================================================================
# 1 Spoiler
#===========================================================================
if nOuterSpoiler <= 1.:
# The outer eta of the leading Edge is correspondent to the outerEta of the spoiler
outerEtaLE = spoilerOuterEta
# The inner eta of the leading edge is the outer eta minus the span of the outer spoiler
innerEtaLE = spoilerOuterEta - outerSpan / span
# The inner and outer Xsi coordinate of the leading edge are defined by the rear spar location and the sparOffset
outerXsiLE = xsiSpar_interp(outerEtaLE) + sparOffset
innerXsiLE = xsiSpar_interp(innerEtaLE) + sparOffset
spoilerPhi = calcPhiLESpoiler(outerEtaLE, innerEtaLE, outerXsiLE, innerXsiLE, parentWingVAMPzero, cpacsWing)
deltaEta = sin(spoilerPhi) * spoilerChord
deltaXsi = cos(spoilerPhi) * spoilerChord
outerEtaTE = outerEtaLE - deltaEta / span
outerXsiTE = outerXsiLE + deltaXsi / calcChordLengthAtEta(outerEtaTE, parentWingVAMPzero, cpacsWing)
innerEtaTE = innerEtaLE - deltaEta / span
innerXsiTE = innerXsiLE + deltaXsi / calcChordLengthAtEta(innerEtaTE, parentWingVAMPzero, cpacsWing)
# We do not want the spoiler to overlap the kink as the inner Spoilers will start here
if innerEtaTE < etaKink:
innerEtaTE = etaKink
innerXsiTE = innerXsiLE + spoilerChord / calcChordLengthAtEta(innerEtaTE, parentWingVAMPzero, cpacsWing)
mySpoilers.append(createSpoiler('OuterSpoiler1', parentWingVAMPzero.id, innerEtaLE, innerEtaTE, innerXsiLE, innerXsiTE, outerEtaLE, outerEtaTE, outerXsiLE, outerXsiTE))
#===========================================================================
# 2 Spoiler
#===========================================================================
elif nOuterSpoiler > 1. and nOuterSpoiler <= 2.:
# The outer eta of the leading Edge is correspondent to the outerEta of the spoiler
outerEtaLE = spoilerOuterEta
# The inner eta of the leading edge is the outer eta minus the span of the outer spoiler
innerEtaLE = spoilerOuterEta - outerSpan / span / 2.
# The inner and outer Xsi coordinate of the leading edge are defined by the rear spar location and the sparOffset
outerXsiLE = xsiSpar_interp(outerEtaLE) + sparOffset
innerXsiLE = xsiSpar_interp(innerEtaLE) + sparOffset
spoilerPhi = calcPhiLESpoiler(outerEtaLE, innerEtaLE, outerXsiLE, innerXsiLE, parentWingVAMPzero, cpacsWing)
deltaEta = sin(spoilerPhi) * spoilerChord
deltaXsi = cos(spoilerPhi) * spoilerChord
outerEtaTE = outerEtaLE - deltaEta / span
outerXsiTE = outerXsiLE + deltaXsi / calcChordLengthAtEta(outerEtaTE, parentWingVAMPzero, cpacsWing)
innerEtaTE = innerEtaLE - deltaEta / span
innerXsiTE = innerXsiLE + deltaXsi / calcChordLengthAtEta(innerEtaTE, parentWingVAMPzero, cpacsWing)
mySpoilers.append(createSpoiler('OuterSpoiler2', parentWingVAMPzero.id, innerEtaLE, innerEtaTE, innerXsiLE, innerXsiTE, outerEtaLE, outerEtaTE, outerXsiLE, outerXsiTE))
# old outer is new inner
outerEtaLE = innerEtaLE
# new inner is min next to kink
innerEtaLE = spoilerOuterEta - outerSpan / span
# The inner and outer Xsi coordinate of the leading edge are defined by the rear spar location and the sparOffset
outerXsiLE = xsiSpar_interp(outerEtaLE) + sparOffset
innerXsiLE = xsiSpar_interp(innerEtaLE) + sparOffset
spoilerPhi = calcPhiLESpoiler(outerEtaLE, innerEtaLE, outerXsiLE, innerXsiLE, parentWingVAMPzero, cpacsWing)
deltaEta = sin(spoilerPhi) * spoilerChord
deltaXsi = cos(spoilerPhi) * spoilerChord
outerEtaTE = outerEtaLE - deltaEta / span
outerXsiTE = outerXsiLE + deltaXsi / calcChordLengthAtEta(outerEtaTE, parentWingVAMPzero, cpacsWing)
innerEtaTE = innerEtaLE - deltaEta / span
innerXsiTE = innerXsiLE + deltaXsi / calcChordLengthAtEta(innerEtaTE, parentWingVAMPzero, cpacsWing)
# We do not want the spoiler to overlap the kink as the inner Spoilers will start here
if innerEtaTE < etaKink:
innerEtaTE = etaKink
innerXsiTE = innerXsiLE + spoilerChord / calcChordLengthAtEta(innerEtaTE, parentWingVAMPzero, cpacsWing)
mySpoilers.append(createSpoiler('OuterSpoiler1', parentWingVAMPzero.id, innerEtaLE, innerEtaTE, innerXsiLE, innerXsiTE, outerEtaLE, outerEtaTE, outerXsiLE, outerXsiTE))
#===========================================================================
# n Spoiler
#===========================================================================
elif nOuterSpoiler > 2.:
n = int(ceil(nOuterSpoiler))
# The outer eta of the leading Edge is correspondent to the outerEta of the spoiler
outerEtaLE = spoilerOuterEta
# The inner eta of the leading edge is the outer eta minus the span of the outer spoiler
innerEtaLE = outerEtaLE - outerSpan / span / n
# The inner and outer Xsi coordinate of the leading edge are defined by the rear spar location and the sparOffset
outerXsiLE = xsiSpar_interp(outerEtaLE) + sparOffset
innerXsiLE = xsiSpar_interp(innerEtaLE) + sparOffset
spoilerPhi = calcPhiLESpoiler(outerEtaLE, innerEtaLE, outerXsiLE, innerXsiLE, parentWingVAMPzero, cpacsWing)
deltaEta = sin(spoilerPhi) * spoilerChord
deltaXsi = cos(spoilerPhi) * spoilerChord
outerEtaTE = outerEtaLE - deltaEta / span
outerXsiTE = outerXsiLE + deltaXsi / calcChordLengthAtEta(outerEtaTE, parentWingVAMPzero, cpacsWing)
innerEtaTE = innerEtaLE - deltaEta / span
innerXsiTE = innerXsiLE + deltaXsi / calcChordLengthAtEta(innerEtaTE, parentWingVAMPzero, cpacsWing)
mySpoilers.append(createSpoiler('OuterSpoiler' + str(n), parentWingVAMPzero.id, innerEtaLE, innerEtaTE, innerXsiLE, innerXsiTE, outerEtaLE, outerEtaTE, outerXsiLE, outerXsiTE))
for i in range(2, n):
# old outer is new inner
outerEtaLE = innerEtaLE
# new inner is min next to kink
innerEtaLE = outerEtaLE - outerSpan / span / n
# The inner and outer Xsi coordinate of the leading edge are defined by the rear spar location and the sparOffset
outerXsiLE = xsiSpar_interp(outerEtaLE) + sparOffset
innerXsiLE = xsiSpar_interp(innerEtaLE) + sparOffset
spoilerPhi = calcPhiLESpoiler(outerEtaLE, innerEtaLE, outerXsiLE, innerXsiLE, parentWingVAMPzero, cpacsWing)
deltaEta = sin(spoilerPhi) * spoilerChord
deltaXsi = cos(spoilerPhi) * spoilerChord
outerEtaTE = outerEtaLE - deltaEta / span
outerXsiTE = outerXsiLE + deltaXsi / calcChordLengthAtEta(outerEtaTE, parentWingVAMPzero, cpacsWing)
innerEtaTE = innerEtaLE - deltaEta / span
innerXsiTE = innerXsiLE + deltaXsi / calcChordLengthAtEta(innerEtaTE, parentWingVAMPzero, cpacsWing)
mySpoilers.append(createSpoiler('OuterSpoiler' + str(n - i + 1), parentWingVAMPzero.id, innerEtaLE, innerEtaTE, innerXsiLE, innerXsiTE, outerEtaLE, outerEtaTE, outerXsiLE, outerXsiTE))
# old outer is new inner
outerEtaLE = innerEtaLE
# new inner is min next to kink
innerEtaLE = spoilerOuterEta - outerSpan / span
# The inner and outer Xsi coordinate of the leading edge are defined by the rear spar location and the sparOffset
outerXsiLE = xsiSpar_interp(outerEtaLE) + sparOffset
innerXsiLE = xsiSpar_interp(innerEtaLE) + sparOffset
spoilerPhi = calcPhiLESpoiler(outerEtaLE, innerEtaLE, outerXsiLE, innerXsiLE, parentWingVAMPzero, cpacsWing)
deltaEta = sin(spoilerPhi) * spoilerChord
deltaXsi = cos(spoilerPhi) * spoilerChord
outerEtaTE = outerEtaLE - deltaEta / span
outerXsiTE = outerXsiLE + deltaXsi / calcChordLengthAtEta(outerEtaTE, parentWingVAMPzero, cpacsWing)
innerEtaTE = innerEtaLE - deltaEta / span
innerXsiTE = innerXsiLE + deltaXsi / calcChordLengthAtEta(innerEtaTE, parentWingVAMPzero, cpacsWing)
# We do not want the spoiler to overlap the kink as the inner Spoilers will start here
if innerEtaTE < etaKink:
innerEtaTE = etaKink
innerXsiTE = innerXsiLE + spoilerChord / calcChordLengthAtEta(innerEtaTE, parentWingVAMPzero, cpacsWing)
mySpoilers.append(createSpoiler('OuterSpoiler1', parentWingVAMPzero.id, innerEtaLE, innerEtaTE, innerXsiLE, innerXsiTE, outerEtaLE, outerEtaTE, outerXsiLE, outerXsiTE))
#===============================================================================
# Inner Spoilers
#===============================================================================
deltaArea = spoilerArea - outerArea
noExport = False
if deltaArea <= 0.:
log.warning('VAMPzero SPOILER: Outboard Spoiler area already exceeds the required spoiler area by: %s' % str(deltaArea))
noExport = True
calcArea = 0.
maxInnerArea = (etaKink - etaFus) * span * spoilerChord
if maxInnerArea >= deltaArea and noExport == False:
innerSpan = 0.
while True:
innerSpan += .01
oldArea = calcArea
calcArea = innerSpan * spoilerChord
# This is the break condition that should be hit normally
if abs(deltaArea - calcArea) < 0.1:
break
if innerSpan > (etaKink - etaFus) * span:
log.warning('VAMPzero SPOILER: The spoiler span of the inner spoiler exceeds the available span betweent fuselage and kink, continuing with calcArea = %s' % str(calcArea))
break
if oldArea > calcArea:
log.warning('VAMPzero SPOILER: Inner spoiler area apparently reached a maximum, continuing with calcArea = %s' % str(calcArea))
break
elif noExport == False:
log.warning('VAMPzero SPOILER: There is not sufficient space for the inner spoiler(s) between the kink and the fuselage!')
spoilerChord = deltaArea / ((etaKink - etaFus) * span)
innerSpan = (etaKink - etaFus) * span
calcArea = deltaArea
log.warning('VAMPzero SPOILER: The spoilerchord will be enlarged to %s!' % str(spoilerChord))
if noExport == True:
nInnerSpoiler = 0
log.debug('VAMPzero SPOILER: Exporting %s Spoiler inside of the kink.' % (str(nInnerSpoiler)))
else:
nInnerSpoiler = innerSpan ** 2 / (calcArea * 3.)
log.debug('VAMPzero SPOILER: Exporting %s Spoiler inside of the kink for an area of %s m2.' % (str(nInnerSpoiler), str(calcArea)))
#===========================================================================
# 1 Spoiler
#===========================================================================
if nInnerSpoiler == 0:
pass
elif nInnerSpoiler <= 1:
# The outer eta of the leading Edge to the eta of the kink
outerEtaLE = etaKink
# The inner eta of the leading edge is the outer eta minus the span of the inner spoiler
innerEtaLE = outerEtaLE - innerSpan / span
# The outer Xsi at the leading Edge is defined by the sparLocation of the Kink
outerXsiLE = xsiSpar_interp(outerEtaLE) + sparOffset
# The innner Xsi remains an absolute chord of the spoiler
chordInnerSpoiler = (1-outerXsiLE) * calcChordLengthAtEta(outerEtaLE, parentWingVAMPzero, cpacsWing)
innerXsiLE = 1 - chordInnerSpoiler / calcChordLengthAtEta(innerEtaLE, parentWingVAMPzero, cpacsWing)
# Eta Coordinates stay constant
# Xsi Coordinates are shifted by spoilerChord
outerEtaTE = outerEtaLE
outerXsiTE = outerXsiLE + spoilerChord / calcChordLengthAtEta(outerEtaTE, parentWingVAMPzero, cpacsWing)
innerEtaTE = innerEtaLE
innerXsiTE = innerXsiLE + spoilerChord / calcChordLengthAtEta(innerEtaTE, parentWingVAMPzero, cpacsWing)
mySpoilers.append(createSpoiler('InnerSpoiler1', parentWingVAMPzero.id, innerEtaLE, innerEtaTE, innerXsiLE, innerXsiTE, outerEtaLE, outerEtaTE, outerXsiLE, outerXsiTE))
#===========================================================================
# 2 Spoiler
#===========================================================================
elif nInnerSpoiler > 1. and nInnerSpoiler <= 2.:
# First inner spoiler
# The outer eta of the leading Edge to the eta of the kink
outerEtaLE = etaKink
# The inner eta of the leading edge is the outer eta minus the span of the inner spoiler
innerEtaLE = outerEtaLE - innerSpan / span / 2.
# The outer Xsi at the leading Edge is defined by the sparLocation of the Kink
outerXsiLE = xsiSpar_interp(outerEtaLE) + sparOffset
# The innner Xsi remains an absolute chord of the spoiler
chordInnerSpoiler = (1-outerXsiLE) * calcChordLengthAtEta(outerEtaLE, parentWingVAMPzero, cpacsWing)
innerXsiLE = 1 - chordInnerSpoiler / calcChordLengthAtEta(innerEtaLE, parentWingVAMPzero, cpacsWing)
# Eta Coordinates stay constant
# Xsi Coordinates are shifted by spoilerChord
outerEtaTE = outerEtaLE
outerXsiTE = outerXsiLE + spoilerChord / calcChordLengthAtEta(outerEtaTE, parentWingVAMPzero, cpacsWing)
innerEtaTE = innerEtaLE
innerXsiTE = innerXsiLE + spoilerChord / calcChordLengthAtEta(innerEtaTE, parentWingVAMPzero, cpacsWing)
mySpoilers.append(createSpoiler('InnerSpoiler2', parentWingVAMPzero.id, innerEtaLE, innerEtaTE, innerXsiLE, innerXsiTE, outerEtaLE, outerEtaTE, outerXsiLE, outerXsiTE))
# Second inner spoiler
# old inner becomes new outer
outerEtaLE = innerEtaLE
# The inner eta of the leading edge is the outer eta minus the span of the inner spoiler
innerEtaLE = outerEtaLE - innerSpan / span / 2.
# The outer Xsi at the leading Edge is defined by the sparLocation of the Kink
outerXsiLE = xsiSpar_interp(outerEtaLE) + sparOffset
# The innner Xsi remains an absolute chord of the spoiler
chordInnerSpoiler = (1-outerXsiLE) * calcChordLengthAtEta(outerEtaLE, parentWingVAMPzero, cpacsWing)
innerXsiLE = 1 - chordInnerSpoiler / calcChordLengthAtEta(innerEtaLE, parentWingVAMPzero, cpacsWing)
# Eta Coordinates stay constant
# Xsi Coordinates are shifted by spoilerChord
outerEtaTE = outerEtaLE
outerXsiTE = outerXsiLE + spoilerChord / calcChordLengthAtEta(outerEtaTE, parentWingVAMPzero, cpacsWing)
innerEtaTE = innerEtaLE
innerXsiTE = innerXsiLE + spoilerChord / calcChordLengthAtEta(innerEtaTE, parentWingVAMPzero, cpacsWing)
mySpoilers.append(createSpoiler('InnerSpoiler1', parentWingVAMPzero.id, innerEtaLE, innerEtaTE, innerXsiLE, innerXsiTE, outerEtaLE, outerEtaTE, outerXsiLE, outerXsiTE))
#===========================================================================
# Output to CPACS
#===========================================================================
if type(cpacsComponentSegment.get_controlSurfaces()) == NoneType:
cpacsComponentSegment.set_controlSurfaces(controlSurfacesType())
if type(cpacsComponentSegment.get_controlSurfaces().get_spoilers()) == NoneType:
cpacsComponentSegment.get_controlSurfaces().set_spoilers(spoilersType())
log.debug('VAMPzero Spoiler: Exporting %s Spoilers to CPACS.' % (str(len(mySpoilers))))
for spoiler in mySpoilers:
cpacsComponentSegment.get_controlSurfaces().get_spoilers().add_spoiler(spoiler)
def createSlats(parentWingCPACS, parentWingVAMPzero, mySlat):
'''
This is the main export method for the wing's slats
It assumes a constant absolut chord for all slats.
At the engine position a 5% span gap is included for the slats
Slats end 5% prior to the wing tip
'''
cpacsPath = '/cpacs/vehicles/aircraft/model/wings/wing[' + parentWingVAMPzero.id + ']'
cpacsWing = getObjfromXpath(parentWingCPACS, cpacsPath)
cpacsComponentSegment = cpacsWing.get_componentSegments().get_componentSegment()[0]
mySlats = []
# Initialization, i.e. fetching values throughout the code
yFus = parentWingVAMPzero.yFuselage.getValue()
span = parentWingVAMPzero.span.getValue() / 2.
etaFus = yFus / span
slatArea = mySlat.refArea.getValue()
# The absolut chord of all slats is equal it is determined by the
# total slat area over the remaining span
# the remaining span is the span minus the fuselage section minus 5% around the engine
# and 5% at the tip
cSlat = slatArea / ((1.0 - etaFus - 0.1) * span)
if cSlat > calcChordLengthAtEta(etaFus, parentWingVAMPzero, cpacsWing) * 0.075:
log.warning('VAMPzero SLAT: The slat chord is larger than 7.5% of the wing\'s chord at the fuselage intersection.')
# Inner Wing Slats
# At first inner wing slats are defined. These do only extend up to the engine
# a plus minus 2.5% span are reserved for the slats
# Note the calculation is only valid for nEngine == 2
# The aspect ratio of a slat should not be higher than 5.5
etaEngine = parentWingVAMPzero.etaEngine.getValue()
innerSpan = span * (etaEngine - 0.025 - etaFus)
innerArea = innerSpan * cSlat
nInnerSlats = innerSpan ** 2. / (innerArea * 5.5)
log.debug('VAMPzero SLAT: Exporting %s Slats inside of the engine for an area of %s m2.' % (str(nInnerSlats), str(innerArea)))
# 1 Slat
if nInnerSlats <= 1.:
# the inner border eta is located at the Fuselage
innerEtaTE = etaFus
innerXsiTE = cSlat / calcChordLengthAtEta(innerEtaTE, parentWingVAMPzero, cpacsWing)
# the outer border eta is determined from the span of the outer flap
outerEtaTE = etaFus + innerSpan / span
outerXsiTE = cSlat / calcChordLengthAtEta(outerEtaTE, parentWingVAMPzero, cpacsWing)
#Slats extend 50% of their chord lenght
innerX = innerXsiTE * calcChordLengthAtEta(innerEtaTE, parentWingVAMPzero, cpacsWing) * 0.5
outerX = outerXsiTE * calcChordLengthAtEta(outerEtaTE, parentWingVAMPzero, cpacsWing) * 0.5
mySlats.append(createSlat('InnerSlat1', parentWingVAMPzero.id, innerEtaTE, innerXsiTE, outerEtaTE, outerXsiTE, innerX=innerX, outerX=outerX))
# 2 Slats
elif nInnerSlats > 1. and nInnerSlats < 2.:
# the inner border eta is located at the Fuselage
innerEtaTE = etaFus
innerXsiTE = cSlat / calcChordLengthAtEta(innerEtaTE, parentWingVAMPzero, cpacsWing)
# the outer border eta is determined from the span of the outer flap
outerEtaTE = etaFus + innerSpan / 2. / span
outerXsiTE = cSlat / calcChordLengthAtEta(outerEtaTE, parentWingVAMPzero, cpacsWing)
#Slats extend 50% of their chord lenght
innerX = innerXsiTE * calcChordLengthAtEta(innerEtaTE, parentWingVAMPzero, cpacsWing) * 0.5
outerX = outerXsiTE * calcChordLengthAtEta(outerEtaTE, parentWingVAMPzero, cpacsWing) * 0.5
mySlats.append(createSlat('InnerSlat1', parentWingVAMPzero.id, innerEtaTE, innerXsiTE, outerEtaTE, outerXsiTE, innerX=innerX, outerX=outerX))
# new inner is the old outer
innerEtaLE = outerEtaTE
innerXsiLE = outerXsiTE
# the outer border eta is determined from the full span of the total outer flap
outerEtaLE = etaFus + innerSpan / span
outerXsiLE = cSlat / calcChordLengthAtEta(outerEtaTE, parentWingVAMPzero, cpacsWing)
#Slats extend 50% of their chord lenght
innerX = innerXsiTE * calcChordLengthAtEta(innerEtaTE, parentWingVAMPzero, cpacsWing) * 0.5
outerX = outerXsiTE * calcChordLengthAtEta(outerEtaTE, parentWingVAMPzero, cpacsWing) * 0.5
mySlats.append(createSlat('InnerSlat2', parentWingVAMPzero.id, innerEtaLE, innerXsiLE, outerEtaLE, outerXsiLE, innerX=innerX, outerX=outerX))
else:
log.warning('VAMPzero EXPORT: Need more inner slats')
# Outer Wing Slats
# Determine the number of remaining slats
# The aspect ratio of a slat should not be higher than 5.5
slatArea = slatArea - innerArea
calcArea = 0.
spanSlat = 0.
while abs(calcArea - slatArea) > 0.5:
spanSlat += .01
calcArea = spanSlat * cSlat
# Determine the number of slats
# The aspect ratio of a slats should not be higher than 5.5
nSlats = spanSlat ** 2. / (slatArea * 5.5)
log.debug('VAMPzero SLAT: Exporting %s Slats outboard of the engine for an area of %s m2.' % (str(nSlats), str(slatArea)))
# 1 Slat
if nSlats <= 1.:
# the inner border eta is located at the Fuselage
innerEtaTE = etaEngine + 0.025
innerXsiTE = cSlat / calcChordLengthAtEta(innerEtaTE, parentWingVAMPzero, cpacsWing)
# the outer border eta is determined from the span of the outer flap
outerEtaTE = innerEtaTE + spanSlat / span
outerXsiTE = cSlat / calcChordLengthAtEta(outerEtaTE, parentWingVAMPzero, cpacsWing)
#Slats extend 50% of their chord lenght
innerX = innerXsiTE * calcChordLengthAtEta(innerEtaTE, parentWingVAMPzero, cpacsWing) * 0.5
outerX = outerXsiTE * calcChordLengthAtEta(outerEtaTE, parentWingVAMPzero, cpacsWing) * 0.5
mySlats.append(createSlat('OuterSlat1', parentWingVAMPzero.id, innerEtaTE, innerXsiTE, outerEtaTE, outerXsiTE, innerX=innerX, outerX=outerX))
# 2 Slats
elif nSlats > 1. and nSlats < 2.:
# the inner border eta is located at the Fuselage
innerEtaTE = etaEngine + 0.025
innerXsiTE = cSlat / calcChordLengthAtEta(innerEtaTE, parentWingVAMPzero, cpacsWing)
# the outer border eta is determined from the span of the outer flap
outerEtaTE = innerEtaTE + spanSlat / 2. / span
outerXsiTE = cSlat / calcChordLengthAtEta(outerEtaTE, parentWingVAMPzero, cpacsWing)
#Slats extend 50% of their chord lenght
innerX = innerXsiTE * calcChordLengthAtEta(innerEtaTE, parentWingVAMPzero, cpacsWing) * 0.5
outerX = outerXsiTE * calcChordLengthAtEta(outerEtaTE, parentWingVAMPzero, cpacsWing) * 0.5
mySlats.append(createSlat('OuterSlat1', parentWingVAMPzero.id, innerEtaTE, innerXsiTE, outerEtaTE, outerXsiTE, innerX=innerX, outerX=outerX))
# new inner is the old outer
innerEtaTE = outerEtaTE
innerXsiTE = outerXsiTE
# the outer border eta is determined from the full span of the total outer flap
outerEtaTE = innerEtaTE + spanSlat / span
outerXsiTE = cSlat / calcChordLengthAtEta(outerEtaTE, parentWingVAMPzero, cpacsWing)
#Slats extend 50% of their chord lenght
innerX = innerXsiTE * calcChordLengthAtEta(innerEtaTE, parentWingVAMPzero, cpacsWing) * 0.5
outerX = outerXsiTE * calcChordLengthAtEta(outerEtaTE, parentWingVAMPzero, cpacsWing) * 0.5
mySlats.append(createSlat('OuterSlat2', parentWingVAMPzero.id, innerEtaTE, innerXsiTE, outerEtaTE, outerXsiTE, innerX=innerX, outerX=outerX))
# n Slats
else:
# the inner border eta is located at the Fuselage
n = int(ceil(nSlats))
innerEtaTE = etaEngine + 0.025
innerXsiTE = cSlat / calcChordLengthAtEta(innerEtaTE, parentWingVAMPzero, cpacsWing)
# First Slat
# the outer border eta is determined from the span of the outer flap
outerEtaTE = innerEtaTE + spanSlat / n / span
outerXsiTE = cSlat / calcChordLengthAtEta(outerEtaTE, parentWingVAMPzero, cpacsWing)
#Slats extend 50% of their chord lenght
innerX = innerXsiTE * calcChordLengthAtEta(innerEtaTE, parentWingVAMPzero, cpacsWing) * 0.5
outerX = outerXsiTE * calcChordLengthAtEta(outerEtaTE, parentWingVAMPzero, cpacsWing) * 0.5
mySlats.append(createSlat('OuterSlat1', parentWingVAMPzero.id, innerEtaTE, innerXsiTE, outerEtaTE, outerXsiTE, innerX=innerX, outerX=outerX))
for i in range(2, n):
# new inner is the old outer
innerEtaTE = outerEtaTE
innerXsiTE = outerXsiTE
# the outer border eta is determined from the full span of the total outer flap
outerEtaTE = innerEtaTE + spanSlat / n / span
outerXsiTE = cSlat / calcChordLengthAtEta(outerEtaTE, parentWingVAMPzero, cpacsWing)
#Slats extend 50% of their chord lenght
innerX = innerXsiTE * calcChordLengthAtEta(innerEtaTE, parentWingVAMPzero, cpacsWing) * 0.5
outerX = outerXsiTE * calcChordLengthAtEta(outerEtaTE, parentWingVAMPzero, cpacsWing) * 0.5
mySlats.append(createSlat('OuterSlat' + str(i), parentWingVAMPzero.id, innerEtaTE, innerXsiTE, outerEtaTE, outerXsiTE, innerX=innerX, outerX=outerX))
# Last Slat
# new inner is the old outer
innerEtaTE = outerEtaTE
innerXsiTE = outerXsiTE
# the outer border eta is determined from the full span of the total outer flap
outerEtaTE = innerEtaTE + spanSlat / n / span
outerXsiTE = cSlat / calcChordLengthAtEta(outerEtaTE, parentWingVAMPzero, cpacsWing)
#Slats extend 50% of their chord lenght
innerX = innerXsiTE * calcChordLengthAtEta(innerEtaTE, parentWingVAMPzero, cpacsWing) * 0.5
outerX = outerXsiTE * calcChordLengthAtEta(outerEtaTE, parentWingVAMPzero, cpacsWing) * 0.5
mySlats.append(createSlat('OuterSlat' + str(n), parentWingVAMPzero.id, innerEtaTE, innerXsiTE, outerEtaTE, outerXsiTE, innerX=innerX, outerX=outerX))
# Output to CPACS
if type(cpacsComponentSegment.get_controlSurfaces()) == NoneType:
cpacsComponentSegment.set_controlSurfaces(controlSurfacesType())
if type(cpacsComponentSegment.get_controlSurfaces().get_leadingEdgeDevices()) == NoneType:
cpacsComponentSegment.get_controlSurfaces().set_leadingEdgeDevices(leadingEdgeDevicesType())
log.debug('VAMPzero SLAT: Exporting %s Slats to CPACS.' % (str(len(mySlats))))
for slat in mySlats:
cpacsComponentSegment.get_controlSurfaces().get_leadingEdgeDevices().add_leadingEdgeDevice(slat)
def createSpoilers(parentWingCPACS, parentWingVAMPzero, mySpoiler):
'''
This is the main export method for the wing's spoilers
* It assumes a constant absolut chord for all spoilers
* Spoiler start outboard and move inboard close behind the rearspar
* They are rectangular
'''
cpacsPath = '/cpacs/vehicles/aircraft/model/wings/wing[' + parentWingVAMPzero.id + ']'
cpacsWing = getObjfromXpath(parentWingCPACS, cpacsPath)
cpacsComponentSegment = cpacsWing.get_componentSegments(
).get_componentSegment()[0]
mySpoilers = []
#===========================================================================
# Initialization, i.e. fetching values throughout the code
#===========================================================================
span = parentWingVAMPzero.span.getValue() / 2.
etaKink = parentWingVAMPzero.etaKink.getValue()
yFus = parentWingVAMPzero.yFuselage.getValue()
etaFus = yFus / span
spoilerArea = mySpoiler.refArea.getValue()
spoilerChord = mySpoiler.chord.getValue()
spoilerOuterEta = mySpoiler.outerEta.getValue()
sparOffset = 0.02
#===========================================================================
# Rear spar locations
#===========================================================================
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])
#===========================================================================
# Outer Spoilers
#===========================================================================
outerSpan = (spoilerOuterEta - etaKink) * span
outerArea = spoilerChord * outerSpan
nOuterSpoiler = outerSpan**2 / (outerArea * 2.)
log.debug(
'VAMPzero SPOILER: Exporting %s Spoiler outside of the kink for an area of %s m2.'
% (str(nOuterSpoiler), str(outerArea)))
#===========================================================================
# 1 Spoiler
#===========================================================================
if nOuterSpoiler <= 1.:
# The outer eta of the leading Edge is correspondent to the outerEta of the spoiler
outerEtaLE = spoilerOuterEta
# The inner eta of the leading edge is the outer eta minus the span of the outer spoiler
innerEtaLE = spoilerOuterEta - outerSpan / span
# The inner and outer Xsi coordinate of the leading edge are defined by the rear spar location and the sparOffset
outerXsiLE = xsiSpar_interp(outerEtaLE) + sparOffset
innerXsiLE = xsiSpar_interp(innerEtaLE) + sparOffset
spoilerPhi = calcPhiLESpoiler(outerEtaLE, innerEtaLE, outerXsiLE,
innerXsiLE, parentWingVAMPzero,
cpacsWing)
deltaEta = sin(spoilerPhi) * spoilerChord
deltaXsi = cos(spoilerPhi) * spoilerChord
outerEtaTE = outerEtaLE - deltaEta / span
outerXsiTE = outerXsiLE + deltaXsi / calcChordLengthAtEta(
outerEtaTE, parentWingVAMPzero, cpacsWing)
innerEtaTE = innerEtaLE - deltaEta / span
innerXsiTE = innerXsiLE + deltaXsi / calcChordLengthAtEta(
innerEtaTE, parentWingVAMPzero, cpacsWing)
# We do not want the spoiler to overlap the kink as the inner Spoilers will start here
if innerEtaTE < etaKink:
innerEtaTE = etaKink
innerXsiTE = innerXsiLE + spoilerChord / calcChordLengthAtEta(
innerEtaTE, parentWingVAMPzero, cpacsWing)
mySpoilers.append(
createSpoiler('OuterSpoiler1', parentWingVAMPzero.id, innerEtaLE,
innerEtaTE, innerXsiLE, innerXsiTE, outerEtaLE,
outerEtaTE, outerXsiLE, outerXsiTE))
#===========================================================================
# 2 Spoiler
#===========================================================================
elif nOuterSpoiler > 1. and nOuterSpoiler <= 2.:
# The outer eta of the leading Edge is correspondent to the outerEta of the spoiler
outerEtaLE = spoilerOuterEta
# The inner eta of the leading edge is the outer eta minus the span of the outer spoiler
innerEtaLE = spoilerOuterEta - outerSpan / span / 2.
# The inner and outer Xsi coordinate of the leading edge are defined by the rear spar location and the sparOffset
outerXsiLE = xsiSpar_interp(outerEtaLE) + sparOffset
innerXsiLE = xsiSpar_interp(innerEtaLE) + sparOffset
spoilerPhi = calcPhiLESpoiler(outerEtaLE, innerEtaLE, outerXsiLE,
innerXsiLE, parentWingVAMPzero,
cpacsWing)
deltaEta = sin(spoilerPhi) * spoilerChord
deltaXsi = cos(spoilerPhi) * spoilerChord
outerEtaTE = outerEtaLE - deltaEta / span
outerXsiTE = outerXsiLE + deltaXsi / calcChordLengthAtEta(
outerEtaTE, parentWingVAMPzero, cpacsWing)
innerEtaTE = innerEtaLE - deltaEta / span
innerXsiTE = innerXsiLE + deltaXsi / calcChordLengthAtEta(
innerEtaTE, parentWingVAMPzero, cpacsWing)
mySpoilers.append(
createSpoiler('OuterSpoiler2', parentWingVAMPzero.id, innerEtaLE,
innerEtaTE, innerXsiLE, innerXsiTE, outerEtaLE,
outerEtaTE, outerXsiLE, outerXsiTE))
# old outer is new inner
outerEtaLE = innerEtaLE
# new inner is min next to kink
innerEtaLE = spoilerOuterEta - outerSpan / span
# The inner and outer Xsi coordinate of the leading edge are defined by the rear spar location and the sparOffset
outerXsiLE = xsiSpar_interp(outerEtaLE) + sparOffset
innerXsiLE = xsiSpar_interp(innerEtaLE) + sparOffset
spoilerPhi = calcPhiLESpoiler(outerEtaLE, innerEtaLE, outerXsiLE,
innerXsiLE, parentWingVAMPzero,
cpacsWing)
deltaEta = sin(spoilerPhi) * spoilerChord
deltaXsi = cos(spoilerPhi) * spoilerChord
outerEtaTE = outerEtaLE - deltaEta / span
outerXsiTE = outerXsiLE + deltaXsi / calcChordLengthAtEta(
outerEtaTE, parentWingVAMPzero, cpacsWing)
innerEtaTE = innerEtaLE - deltaEta / span
innerXsiTE = innerXsiLE + deltaXsi / calcChordLengthAtEta(
innerEtaTE, parentWingVAMPzero, cpacsWing)
# We do not want the spoiler to overlap the kink as the inner Spoilers will start here
if innerEtaTE < etaKink:
innerEtaTE = etaKink
innerXsiTE = innerXsiLE + spoilerChord / calcChordLengthAtEta(
innerEtaTE, parentWingVAMPzero, cpacsWing)
mySpoilers.append(
createSpoiler('OuterSpoiler1', parentWingVAMPzero.id, innerEtaLE,
innerEtaTE, innerXsiLE, innerXsiTE, outerEtaLE,
outerEtaTE, outerXsiLE, outerXsiTE))
#===========================================================================
# n Spoiler
#===========================================================================
elif nOuterSpoiler > 2.:
n = int(ceil(nOuterSpoiler))
# The outer eta of the leading Edge is correspondent to the outerEta of the spoiler
outerEtaLE = spoilerOuterEta
# The inner eta of the leading edge is the outer eta minus the span of the outer spoiler
innerEtaLE = outerEtaLE - outerSpan / span / n
# The inner and outer Xsi coordinate of the leading edge are defined by the rear spar location and the sparOffset
outerXsiLE = xsiSpar_interp(outerEtaLE) + sparOffset
innerXsiLE = xsiSpar_interp(innerEtaLE) + sparOffset
spoilerPhi = calcPhiLESpoiler(outerEtaLE, innerEtaLE, outerXsiLE,
innerXsiLE, parentWingVAMPzero,
cpacsWing)
deltaEta = sin(spoilerPhi) * spoilerChord
deltaXsi = cos(spoilerPhi) * spoilerChord
outerEtaTE = outerEtaLE - deltaEta / span
outerXsiTE = outerXsiLE + deltaXsi / calcChordLengthAtEta(
outerEtaTE, parentWingVAMPzero, cpacsWing)
innerEtaTE = innerEtaLE - deltaEta / span
innerXsiTE = innerXsiLE + deltaXsi / calcChordLengthAtEta(
innerEtaTE, parentWingVAMPzero, cpacsWing)
mySpoilers.append(
createSpoiler('OuterSpoiler' + str(n), parentWingVAMPzero.id,
innerEtaLE, innerEtaTE, innerXsiLE, innerXsiTE,
outerEtaLE, outerEtaTE, outerXsiLE, outerXsiTE))
for i in range(2, n):
# old outer is new inner
outerEtaLE = innerEtaLE
# new inner is min next to kink
innerEtaLE = outerEtaLE - outerSpan / span / n
# The inner and outer Xsi coordinate of the leading edge are defined by the rear spar location and the sparOffset
outerXsiLE = xsiSpar_interp(outerEtaLE) + sparOffset
innerXsiLE = xsiSpar_interp(innerEtaLE) + sparOffset
spoilerPhi = calcPhiLESpoiler(outerEtaLE, innerEtaLE, outerXsiLE,
innerXsiLE, parentWingVAMPzero,
cpacsWing)
deltaEta = sin(spoilerPhi) * spoilerChord
deltaXsi = cos(spoilerPhi) * spoilerChord
outerEtaTE = outerEtaLE - deltaEta / span
outerXsiTE = outerXsiLE + deltaXsi / calcChordLengthAtEta(
outerEtaTE, parentWingVAMPzero, cpacsWing)
innerEtaTE = innerEtaLE - deltaEta / span
innerXsiTE = innerXsiLE + deltaXsi / calcChordLengthAtEta(
innerEtaTE, parentWingVAMPzero, cpacsWing)
mySpoilers.append(
createSpoiler('OuterSpoiler' + str(n - i + 1),
parentWingVAMPzero.id, innerEtaLE, innerEtaTE,
innerXsiLE, innerXsiTE, outerEtaLE, outerEtaTE,
outerXsiLE, outerXsiTE))
# old outer is new inner
outerEtaLE = innerEtaLE
# new inner is min next to kink
innerEtaLE = spoilerOuterEta - outerSpan / span
# The inner and outer Xsi coordinate of the leading edge are defined by the rear spar location and the sparOffset
outerXsiLE = xsiSpar_interp(outerEtaLE) + sparOffset
innerXsiLE = xsiSpar_interp(innerEtaLE) + sparOffset
spoilerPhi = calcPhiLESpoiler(outerEtaLE, innerEtaLE, outerXsiLE,
innerXsiLE, parentWingVAMPzero,
cpacsWing)
deltaEta = sin(spoilerPhi) * spoilerChord
deltaXsi = cos(spoilerPhi) * spoilerChord
outerEtaTE = outerEtaLE - deltaEta / span
outerXsiTE = outerXsiLE + deltaXsi / calcChordLengthAtEta(
outerEtaTE, parentWingVAMPzero, cpacsWing)
innerEtaTE = innerEtaLE - deltaEta / span
innerXsiTE = innerXsiLE + deltaXsi / calcChordLengthAtEta(
innerEtaTE, parentWingVAMPzero, cpacsWing)
# We do not want the spoiler to overlap the kink as the inner Spoilers will start here
if innerEtaTE < etaKink:
innerEtaTE = etaKink
innerXsiTE = innerXsiLE + spoilerChord / calcChordLengthAtEta(
innerEtaTE, parentWingVAMPzero, cpacsWing)
mySpoilers.append(
createSpoiler('OuterSpoiler1', parentWingVAMPzero.id, innerEtaLE,
innerEtaTE, innerXsiLE, innerXsiTE, outerEtaLE,
outerEtaTE, outerXsiLE, outerXsiTE))
#===============================================================================
# Inner Spoilers
#===============================================================================
deltaArea = spoilerArea - outerArea
noExport = False
if deltaArea <= 0.:
log.warning(
'VAMPzero SPOILER: Outboard Spoiler area already exceeds the required spoiler area by: %s'
% str(deltaArea))
noExport = True
calcArea = 0.
maxInnerArea = (etaKink - etaFus) * span * spoilerChord
if maxInnerArea >= deltaArea and noExport == False:
innerSpan = 0.
while True:
innerSpan += .01
oldArea = calcArea
calcArea = innerSpan * spoilerChord
# This is the break condition that should be hit normally
if abs(deltaArea - calcArea) < 0.1:
break
if innerSpan > (etaKink - etaFus) * span:
log.warning(
'VAMPzero SPOILER: The spoiler span of the inner spoiler exceeds the available span betweent fuselage and kink, continuing with calcArea = %s'
% str(calcArea))
break
if oldArea > calcArea:
log.warning(
'VAMPzero SPOILER: Inner spoiler area apparently reached a maximum, continuing with calcArea = %s'
% str(calcArea))
break
elif noExport == False:
log.warning(
'VAMPzero SPOILER: There is not sufficient space for the inner spoiler(s) between the kink and the fuselage!'
)
spoilerChord = deltaArea / ((etaKink - etaFus) * span)
innerSpan = (etaKink - etaFus) * span
calcArea = deltaArea
log.warning(
'VAMPzero SPOILER: The spoilerchord will be enlarged to %s!' %
str(spoilerChord))
if noExport == True:
nInnerSpoiler = 0
log.debug(
'VAMPzero SPOILER: Exporting %s Spoiler inside of the kink.' %
(str(nInnerSpoiler)))
else:
nInnerSpoiler = innerSpan**2 / (calcArea * 3.)
log.debug(
'VAMPzero SPOILER: Exporting %s Spoiler inside of the kink for an area of %s m2.'
% (str(nInnerSpoiler), str(calcArea)))
#===========================================================================
# 1 Spoiler
#===========================================================================
if nInnerSpoiler == 0:
pass
elif nInnerSpoiler <= 1:
# The outer eta of the leading Edge to the eta of the kink
outerEtaLE = etaKink
# The inner eta of the leading edge is the outer eta minus the span of the inner spoiler
innerEtaLE = outerEtaLE - innerSpan / span
# The outer Xsi at the leading Edge is defined by the sparLocation of the Kink
outerXsiLE = xsiSpar_interp(outerEtaLE) + sparOffset
# The innner Xsi remains an absolute chord of the spoiler
chordInnerSpoiler = (1 - outerXsiLE) * calcChordLengthAtEta(
outerEtaLE, parentWingVAMPzero, cpacsWing)
innerXsiLE = 1 - chordInnerSpoiler / calcChordLengthAtEta(
innerEtaLE, parentWingVAMPzero, cpacsWing)
# Eta Coordinates stay constant
# Xsi Coordinates are shifted by spoilerChord
outerEtaTE = outerEtaLE
outerXsiTE = outerXsiLE + spoilerChord / calcChordLengthAtEta(
outerEtaTE, parentWingVAMPzero, cpacsWing)
innerEtaTE = innerEtaLE
innerXsiTE = innerXsiLE + spoilerChord / calcChordLengthAtEta(
innerEtaTE, parentWingVAMPzero, cpacsWing)
mySpoilers.append(
createSpoiler('InnerSpoiler1', parentWingVAMPzero.id, innerEtaLE,
innerEtaTE, innerXsiLE, innerXsiTE, outerEtaLE,
outerEtaTE, outerXsiLE, outerXsiTE))
#===========================================================================
# 2 Spoiler
#===========================================================================
elif nInnerSpoiler > 1. and nInnerSpoiler <= 2.:
# First inner spoiler
# The outer eta of the leading Edge to the eta of the kink
outerEtaLE = etaKink
# The inner eta of the leading edge is the outer eta minus the span of the inner spoiler
innerEtaLE = outerEtaLE - innerSpan / span / 2.
# The outer Xsi at the leading Edge is defined by the sparLocation of the Kink
outerXsiLE = xsiSpar_interp(outerEtaLE) + sparOffset
# The innner Xsi remains an absolute chord of the spoiler
chordInnerSpoiler = (1 - outerXsiLE) * calcChordLengthAtEta(
outerEtaLE, parentWingVAMPzero, cpacsWing)
innerXsiLE = 1 - chordInnerSpoiler / calcChordLengthAtEta(
innerEtaLE, parentWingVAMPzero, cpacsWing)
# Eta Coordinates stay constant
# Xsi Coordinates are shifted by spoilerChord
outerEtaTE = outerEtaLE
outerXsiTE = outerXsiLE + spoilerChord / calcChordLengthAtEta(
outerEtaTE, parentWingVAMPzero, cpacsWing)
innerEtaTE = innerEtaLE
innerXsiTE = innerXsiLE + spoilerChord / calcChordLengthAtEta(
innerEtaTE, parentWingVAMPzero, cpacsWing)
mySpoilers.append(
createSpoiler('InnerSpoiler2', parentWingVAMPzero.id, innerEtaLE,
innerEtaTE, innerXsiLE, innerXsiTE, outerEtaLE,
outerEtaTE, outerXsiLE, outerXsiTE))
# Second inner spoiler
# old inner becomes new outer
outerEtaLE = innerEtaLE
# The inner eta of the leading edge is the outer eta minus the span of the inner spoiler
innerEtaLE = outerEtaLE - innerSpan / span / 2.
# The outer Xsi at the leading Edge is defined by the sparLocation of the Kink
outerXsiLE = xsiSpar_interp(outerEtaLE) + sparOffset
# The innner Xsi remains an absolute chord of the spoiler
chordInnerSpoiler = (1 - outerXsiLE) * calcChordLengthAtEta(
outerEtaLE, parentWingVAMPzero, cpacsWing)
innerXsiLE = 1 - chordInnerSpoiler / calcChordLengthAtEta(
innerEtaLE, parentWingVAMPzero, cpacsWing)
# Eta Coordinates stay constant
# Xsi Coordinates are shifted by spoilerChord
outerEtaTE = outerEtaLE
outerXsiTE = outerXsiLE + spoilerChord / calcChordLengthAtEta(
outerEtaTE, parentWingVAMPzero, cpacsWing)
innerEtaTE = innerEtaLE
innerXsiTE = innerXsiLE + spoilerChord / calcChordLengthAtEta(
innerEtaTE, parentWingVAMPzero, cpacsWing)
mySpoilers.append(
createSpoiler('InnerSpoiler1', parentWingVAMPzero.id, innerEtaLE,
innerEtaTE, innerXsiLE, innerXsiTE, outerEtaLE,
outerEtaTE, outerXsiLE, outerXsiTE))
#===========================================================================
# Output to CPACS
#===========================================================================
if type(cpacsComponentSegment.get_controlSurfaces()) == NoneType:
cpacsComponentSegment.set_controlSurfaces(controlSurfacesType())
if type(cpacsComponentSegment.get_controlSurfaces().get_spoilers()
) == NoneType:
cpacsComponentSegment.get_controlSurfaces().set_spoilers(
spoilersType())
log.debug('VAMPzero Spoiler: Exporting %s Spoilers to CPACS.' %
(str(len(mySpoilers))))
for spoiler in mySpoilers:
cpacsComponentSegment.get_controlSurfaces().get_spoilers().add_spoiler(
spoiler)
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 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 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 createSpoilersSBW(parentWingCPACS, parentWingVAMPzero, mySpoiler):
'''
This is the main export method for the wing's spoilers
* It assumes a constant absolut chord for all spoilers
* Spoiler start outboard and move inboard close behind the rearspar
* They are rectangular
'''
cpacsPath = '/cpacs/vehicles/aircraft/model/wings/wing[' + parentWingVAMPzero.id + ']'
cpacsWing = getObjfromXpath(parentWingCPACS, cpacsPath)
cpacsComponentSegment = cpacsWing.get_componentSegments().get_componentSegment()[0]
mySpoilers = []
# Initialization, i.e. fetching values throughout the code
span = parentWingVAMPzero.span.getValue() / 2.
yFus = parentWingVAMPzero.yFuselage.getValue()
etaFus = yFus / span
spoilerArea = mySpoiler.refArea.getValue()
spoilerChord = mySpoiler.chord.getValue()
spoilerOuterEta = mySpoiler.outerEta.getValue()
sparOffset = 0.02
# Rear spar locations
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)
# Outer Spoilers
outerSpan = (spoilerOuterEta - etaFus) * span
#outerArea = spoilerChord * outerSpan
#nOuterSpoiler = outerSpan ** 2 / (outerArea * 2.)
#log.debug('VAMPzero SPOILER: Exporting %s Spoiler outside of the kink for an area of %s m2.' % (str(nOuterSpoiler), str(outerArea)))
calcArea = 0.
maxInnerArea = (spoilerOuterEta - etaFus) * span * spoilerChord
innerSpan = 0.
while True:
innerSpan += .01
oldArea = calcArea
calcArea = innerSpan * spoilerChord
# This is the break condition that should be hit normally
if abs(spoilerArea - calcArea) < 0.1:
break
if innerSpan > (spoilerOuterEta - etaFus) * span:
log.warning('VAMPzero SPOILER: The spoiler span of the spoiler exceeds the available span between fuselage and kink, continuing with calcArea = %s' % str(calcArea))
break
if oldArea > calcArea:
log.warning('VAMPzero SPOILER: Spoiler area apparently reached a maximum, continuing with calcArea = %s' % str(calcArea))
break
nSpoiler = innerSpan ** 2 / (calcArea * 3.)
log.debug('VAMPzero SPOILER: Exporting %s Spoiler inside of the kink for an area of %s m2.' % (str(nSpoiler), str(calcArea)))
# 1 Spoiler
if nSpoiler <= 1.:
# The outer eta of the leading Edge is correspondent to the outerEta of the spoiler
outerEtaLE = spoilerOuterEta
# The inner eta of the leading edge is the outer eta minus the span of the outer spoiler
innerEtaLE = spoilerOuterEta - outerSpan / span
# The inner and outer Xsi coordinate of the leading edge are defined by the rear spar location and the sparOffset
outerXsiLE = xsiSpar_interp(outerEtaLE) + sparOffset
innerXsiLE = xsiSpar_interp(innerEtaLE) + sparOffset
spoilerPhi = calcPhiLESpoiler(outerEtaLE, innerEtaLE, outerXsiLE, innerXsiLE, parentWingVAMPzero, cpacsWing)
deltaEta = sin(spoilerPhi) * spoilerChord
deltaXsi = cos(spoilerPhi) * spoilerChord
outerEtaTE = outerEtaLE - deltaEta / span
outerXsiTE = outerXsiLE + deltaXsi / calcChordLengthAtEta(outerEtaTE, parentWingVAMPzero, cpacsWing)
innerEtaTE = innerEtaLE - deltaEta / span
innerXsiTE = innerXsiLE + deltaXsi / calcChordLengthAtEta(innerEtaTE, parentWingVAMPzero, cpacsWing)
# We do not want the spoiler to overlap the kink as the inner Spoilers will start here
if innerEtaTE < etaFus:
innerEtaTE = etaFus
innerXsiTE = innerXsiLE + spoilerChord / calcChordLengthAtEta(innerEtaTE, parentWingVAMPzero, cpacsWing)
mySpoilers.append(createSpoiler('Spoiler1', parentWingVAMPzero.id, innerEtaLE, innerEtaTE, innerXsiLE, innerXsiTE, outerEtaLE, outerEtaTE, outerXsiLE, outerXsiTE))
# 2 Spoiler
elif nSpoiler > 1. and nSpoiler <= 2.:
# The outer eta of the leading Edge is correspondent to the outerEta of the spoiler
outerEtaLE = spoilerOuterEta
# The inner eta of the leading edge is the outer eta minus the span of the outer spoiler
innerEtaLE = spoilerOuterEta - outerSpan / span / 2.
# The inner and outer Xsi coordinate of the leading edge are defined by the rear spar location and the sparOffset
outerXsiLE = xsiSpar_interp(outerEtaLE) + sparOffset
innerXsiLE = xsiSpar_interp(innerEtaLE) + sparOffset
spoilerPhi = calcPhiLESpoiler(outerEtaLE, innerEtaLE, outerXsiLE, innerXsiLE, parentWingVAMPzero, cpacsWing)
deltaEta = sin(spoilerPhi) * spoilerChord
deltaXsi = cos(spoilerPhi) * spoilerChord
outerEtaTE = outerEtaLE - deltaEta / span
outerXsiTE = outerXsiLE + deltaXsi / calcChordLengthAtEta(outerEtaTE, parentWingVAMPzero, cpacsWing)
innerEtaTE = innerEtaLE - deltaEta / span
innerXsiTE = innerXsiLE + deltaXsi / calcChordLengthAtEta(innerEtaTE, parentWingVAMPzero, cpacsWing)
mySpoilers.append(createSpoiler('Spoiler2', parentWingVAMPzero.id, innerEtaLE, innerEtaTE, innerXsiLE, innerXsiTE, outerEtaLE, outerEtaTE, outerXsiLE, outerXsiTE))
# old outer is new inner
outerEtaLE = innerEtaLE
# new inner is min next to kink
innerEtaLE = spoilerOuterEta - outerSpan / span
# The inner and outer Xsi coordinate of the leading edge are defined by the rear spar location and the sparOffset
outerXsiLE = xsiSpar_interp(outerEtaLE) + sparOffset
innerXsiLE = xsiSpar_interp(innerEtaLE) + sparOffset
spoilerPhi = calcPhiLESpoiler(outerEtaLE, innerEtaLE, outerXsiLE, innerXsiLE, parentWingVAMPzero, cpacsWing)
deltaEta = sin(spoilerPhi) * spoilerChord
deltaXsi = cos(spoilerPhi) * spoilerChord
outerEtaTE = outerEtaLE - deltaEta / span
outerXsiTE = outerXsiLE + deltaXsi / calcChordLengthAtEta(outerEtaTE, parentWingVAMPzero, cpacsWing)
innerEtaTE = innerEtaLE - deltaEta / span
innerXsiTE = innerXsiLE + deltaXsi / calcChordLengthAtEta(innerEtaTE, parentWingVAMPzero, cpacsWing)
# We do not want the spoiler to overlap the kink as the inner Spoilers will start here
if innerEtaTE < etaFus:
innerEtaTE = etaFus
innerXsiTE = innerXsiLE + spoilerChord / calcChordLengthAtEta(innerEtaTE, parentWingVAMPzero, cpacsWing)
mySpoilers.append(createSpoiler('Spoiler1', parentWingVAMPzero.id, innerEtaLE, innerEtaTE, innerXsiLE, innerXsiTE, outerEtaLE, outerEtaTE, outerXsiLE, outerXsiTE))
# n Spoiler
elif nSpoiler > 2.:
n = int(ceil(nSpoiler))
# The outer eta of the leading Edge is correspondent to the outerEta of the spoiler
outerEtaLE = spoilerOuterEta
# The inner eta of the leading edge is the outer eta minus the span of the outer spoiler
innerEtaLE = outerEtaLE - outerSpan / span / n
# The inner and outer Xsi coordinate of the leading edge are defined by the rear spar location and the sparOffset
outerXsiLE = xsiSpar_interp(outerEtaLE) + sparOffset
innerXsiLE = xsiSpar_interp(innerEtaLE) + sparOffset
spoilerPhi = calcPhiLESpoiler(outerEtaLE, innerEtaLE, outerXsiLE, innerXsiLE, parentWingVAMPzero, cpacsWing)
deltaEta = sin(spoilerPhi) * spoilerChord
deltaXsi = cos(spoilerPhi) * spoilerChord
outerEtaTE = outerEtaLE - deltaEta / span
outerXsiTE = outerXsiLE + deltaXsi / calcChordLengthAtEta(outerEtaTE, parentWingVAMPzero, cpacsWing)
innerEtaTE = innerEtaLE - deltaEta / span
innerXsiTE = innerXsiLE + deltaXsi / calcChordLengthAtEta(innerEtaTE, parentWingVAMPzero, cpacsWing)
mySpoilers.append(createSpoiler('Spoiler' + str(n), parentWingVAMPzero.id, innerEtaLE, innerEtaTE, innerXsiLE, innerXsiTE, outerEtaLE, outerEtaTE, outerXsiLE, outerXsiTE))
for i in range(2, n):
# old outer is new inner
outerEtaLE = innerEtaLE
# new inner is min next to kink
innerEtaLE = outerEtaLE - outerSpan / span / n
# The inner and outer Xsi coordinate of the leading edge are defined by the rear spar location and the sparOffset
outerXsiLE = xsiSpar_interp(outerEtaLE) + sparOffset
innerXsiLE = xsiSpar_interp(innerEtaLE) + sparOffset
spoilerPhi = calcPhiLESpoiler(outerEtaLE, innerEtaLE, outerXsiLE, innerXsiLE, parentWingVAMPzero, cpacsWing)
deltaEta = sin(spoilerPhi) * spoilerChord
deltaXsi = cos(spoilerPhi) * spoilerChord
outerEtaTE = outerEtaLE - deltaEta / span
outerXsiTE = outerXsiLE + deltaXsi / calcChordLengthAtEta(outerEtaTE, parentWingVAMPzero, cpacsWing)
innerEtaTE = innerEtaLE - deltaEta / span
innerXsiTE = innerXsiLE + deltaXsi / calcChordLengthAtEta(innerEtaTE, parentWingVAMPzero, cpacsWing)
mySpoilers.append(createSpoiler('Spoiler' + str(n - i + 1), parentWingVAMPzero.id, innerEtaLE, innerEtaTE, innerXsiLE, innerXsiTE, outerEtaLE, outerEtaTE, outerXsiLE, outerXsiTE))
# old outer is new inner
outerEtaLE = innerEtaLE
# new inner is min next to kink
innerEtaLE = spoilerOuterEta - outerSpan / span
# The inner and outer Xsi coordinate of the leading edge are defined by the rear spar location and the sparOffset
outerXsiLE = xsiSpar_interp(outerEtaLE) + sparOffset
innerXsiLE = xsiSpar_interp(innerEtaLE) + sparOffset
spoilerPhi = calcPhiLESpoiler(outerEtaLE, innerEtaLE, outerXsiLE, innerXsiLE, parentWingVAMPzero, cpacsWing)
deltaEta = sin(spoilerPhi) * spoilerChord
deltaXsi = cos(spoilerPhi) * spoilerChord
outerEtaTE = outerEtaLE - deltaEta / span
outerXsiTE = outerXsiLE + deltaXsi / calcChordLengthAtEta(outerEtaTE, parentWingVAMPzero, cpacsWing)
innerEtaTE = innerEtaLE - deltaEta / span
innerXsiTE = innerXsiLE + deltaXsi / calcChordLengthAtEta(innerEtaTE, parentWingVAMPzero, cpacsWing)
# We do not want the spoiler to overlap the kink as the inner Spoilers will start here
if innerEtaTE < etaFus:
innerEtaTE = etaFus
innerXsiTE = innerXsiLE + spoilerChord / calcChordLengthAtEta(innerEtaTE, parentWingVAMPzero, cpacsWing)
mySpoilers.append(createSpoiler('Spoiler1', parentWingVAMPzero.id, innerEtaLE, innerEtaTE, innerXsiLE, innerXsiTE, outerEtaLE, outerEtaTE, outerXsiLE, outerXsiTE))
# Output to CPACS
if type(cpacsComponentSegment.get_controlSurfaces()) == NoneType:
cpacsComponentSegment.set_controlSurfaces(controlSurfacesType())
if type(cpacsComponentSegment.get_controlSurfaces().get_spoilers()) == NoneType:
cpacsComponentSegment.get_controlSurfaces().set_spoilers(spoilersType())
log.debug('VAMPzero Spoiler: Exporting %s Spoilers to CPACS.' % (str(len(mySpoilers))))
for spoiler in mySpoilers:
cpacsComponentSegment.get_controlSurfaces().get_spoilers().add_spoiler(spoiler)
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 createSlats(parentWingCPACS, parentWingVAMPzero, mySlat):
'''
This is the main export method for the wing's slats
It assumes a constant absolut chord for all slats.
At the engine position a 5% span gap is included for the slats
Slats end 5% prior to the wing tip
'''
cpacsPath = '/cpacs/vehicles/aircraft/model/wings/wing[' + parentWingVAMPzero.id + ']'
cpacsWing = getObjfromXpath(parentWingCPACS, cpacsPath)
cpacsComponentSegment = cpacsWing.get_componentSegments().get_componentSegment()[0]
mySlats = []
#===========================================================================
# Initialization, i.e. fetching values throughout the code
#===========================================================================
yFus = parentWingVAMPzero.yFuselage.getValue()
span = parentWingVAMPzero.span.getValue() / 2.
etaFus = yFus / span
slatArea = mySlat.refArea.getValue()
# The absolut chord of all slats is equal it is determined by the
# total slat area over the remaining span
# the remaining span is the span minus the fuselage section minus 5% around the engine
# and 5% at the tip
cSlat = slatArea / ((1.0 - etaFus - 0.1) * span)
if cSlat > calcChordLengthAtEta(etaFus, parentWingVAMPzero, cpacsWing) * 0.075:
log.warning('VAMPzero SLAT: The slat chord is larger than 7.5% of the wing\'s chord at the fuselage intersection.')
#===========================================================================
# Inner Wing Slats
# ----------------
#
# At first inner wing slats are defined. These do only extend up to the engine
# a plus minus 2.5% span are reserved for the slats
# Note the calculation is only valid for nEngine == 2
# The aspect ratio of a slat should not be higher than 5.5
#===========================================================================
etaEngine = parentWingVAMPzero.etaEngine.getValue()
innerSpan = span * (etaEngine - 0.025 - etaFus)
innerArea = innerSpan * cSlat
nInnerSlats = innerSpan ** 2. / (innerArea * 5.5)
log.debug('VAMPzero SLAT: Exporting %s Slats inside of the engine for an area of %s m2.' % (str(nInnerSlats), str(innerArea)))
#===========================================================================
# 1 Slat
#===========================================================================
if nInnerSlats <= 1.:
# the inner border eta is located at the Fuselage
innerEtaTE = etaFus
innerXsiTE = cSlat / calcChordLengthAtEta(innerEtaTE, parentWingVAMPzero, cpacsWing)
# the outer border eta is determined from the span of the outer flap
outerEtaTE = etaFus + innerSpan / span
outerXsiTE = cSlat / calcChordLengthAtEta(outerEtaTE, parentWingVAMPzero, cpacsWing)
#Slats extend 50% of their chord lenght
innerX = innerXsiTE * calcChordLengthAtEta(innerEtaTE, parentWingVAMPzero, cpacsWing) * 0.5
outerX = outerXsiTE * calcChordLengthAtEta(outerEtaTE, parentWingVAMPzero, cpacsWing) * 0.5
mySlats.append(createSlat('InnerSlat1', parentWingVAMPzero.id, innerEtaTE, innerXsiTE, outerEtaTE, outerXsiTE, innerX=innerX, outerX=outerX))
#===========================================================================
# 2 Slats
#===========================================================================
elif nInnerSlats > 1. and nInnerSlats < 2.:
# the inner border eta is located at the Fuselage
innerEtaTE = etaFus
innerXsiTE = cSlat / calcChordLengthAtEta(innerEtaTE, parentWingVAMPzero, cpacsWing)
# the outer border eta is determined from the span of the outer flap
outerEtaTE = etaFus + innerSpan / 2. / span
outerXsiTE = cSlat / calcChordLengthAtEta(outerEtaTE, parentWingVAMPzero, cpacsWing)
#Slats extend 50% of their chord lenght
innerX = innerXsiTE * calcChordLengthAtEta(innerEtaTE, parentWingVAMPzero, cpacsWing) * 0.5
outerX = outerXsiTE * calcChordLengthAtEta(outerEtaTE, parentWingVAMPzero, cpacsWing) * 0.5
mySlats.append(createSlat('InnerSlat1', parentWingVAMPzero.id, innerEtaTE, innerXsiTE, outerEtaTE, outerXsiTE, innerX=innerX, outerX=outerX))
# new inner is the old outer
innerEtaLE = outerEtaTE
innerXsiLE = outerXsiTE
# the outer border eta is determined from the full span of the total outer flap
outerEtaLE = etaFus + innerSpan / span
outerXsiLE = cSlat / calcChordLengthAtEta(outerEtaTE, parentWingVAMPzero, cpacsWing)
#Slats extend 50% of their chord lenght
innerX = innerXsiTE * calcChordLengthAtEta(innerEtaTE, parentWingVAMPzero, cpacsWing) * 0.5
outerX = outerXsiTE * calcChordLengthAtEta(outerEtaTE, parentWingVAMPzero, cpacsWing) * 0.5
mySlats.append(createSlat('InnerSlat2', parentWingVAMPzero.id, innerEtaLE, innerXsiLE, outerEtaLE, outerXsiLE, innerX=innerX, outerX=outerX))
else:
log.warning('VAMPzero EXPORT: Need more inner slats')
#===========================================================================
# Outer Wing Slats
# ----------------
#
# Determine the number of remaining slats
# The aspect ratio of a slat should not be higher than 5.5
#===========================================================================
slatArea = slatArea - innerArea
calcArea = 0.
spanSlat = 0.
while abs(calcArea - slatArea) > 0.5:
spanSlat += .01
calcArea = spanSlat * cSlat
#===========================================================================
# Determine the number of slats
# The aspect ratio of a slats should not be higher than 5.5
#===========================================================================
nSlats = spanSlat ** 2. / (slatArea * 5.5)
log.debug('VAMPzero SLAT: Exporting %s Slats outboard of the engine for an area of %s m2.' % (str(nSlats), str(slatArea)))
#===========================================================================
# 1 Slat
#===========================================================================
if nSlats <= 1.:
# the inner border eta is located at the Fuselage
innerEtaTE = etaEngine + 0.025
innerXsiTE = cSlat / calcChordLengthAtEta(innerEtaTE, parentWingVAMPzero, cpacsWing)
# the outer border eta is determined from the span of the outer flap
outerEtaTE = innerEtaTE + spanSlat / span
outerXsiTE = cSlat / calcChordLengthAtEta(outerEtaTE, parentWingVAMPzero, cpacsWing)
#Slats extend 50% of their chord lenght
innerX = innerXsiTE * calcChordLengthAtEta(innerEtaTE, parentWingVAMPzero, cpacsWing) * 0.5
outerX = outerXsiTE * calcChordLengthAtEta(outerEtaTE, parentWingVAMPzero, cpacsWing) * 0.5
mySlats.append(createSlat('OuterSlat1', parentWingVAMPzero.id, innerEtaTE, innerXsiTE, outerEtaTE, outerXsiTE, innerX=innerX, outerX=outerX))
#===========================================================================
# 2 Slats
#===========================================================================
elif nSlats > 1. and nSlats < 2.:
# the inner border eta is located at the Fuselage
innerEtaTE = etaEngine + 0.025
innerXsiTE = cSlat / calcChordLengthAtEta(innerEtaTE, parentWingVAMPzero, cpacsWing)
# the outer border eta is determined from the span of the outer flap
outerEtaTE = innerEtaTE + spanSlat / 2. / span
outerXsiTE = cSlat / calcChordLengthAtEta(outerEtaTE, parentWingVAMPzero, cpacsWing)
#Slats extend 50% of their chord lenght
innerX = innerXsiTE * calcChordLengthAtEta(innerEtaTE, parentWingVAMPzero, cpacsWing) * 0.5
outerX = outerXsiTE * calcChordLengthAtEta(outerEtaTE, parentWingVAMPzero, cpacsWing) * 0.5
mySlats.append(createSlat('OuterSlat1', parentWingVAMPzero.id, innerEtaTE, innerXsiTE, outerEtaTE, outerXsiTE, innerX=innerX, outerX=outerX))
# new inner is the old outer
innerEtaTE = outerEtaTE
innerXsiTE = outerXsiTE
# the outer border eta is determined from the full span of the total outer flap
outerEtaTE = innerEtaTE + spanSlat / span
outerXsiTE = cSlat / calcChordLengthAtEta(outerEtaTE, parentWingVAMPzero, cpacsWing)
#Slats extend 50% of their chord lenght
innerX = innerXsiTE * calcChordLengthAtEta(innerEtaTE, parentWingVAMPzero, cpacsWing) * 0.5
outerX = outerXsiTE * calcChordLengthAtEta(outerEtaTE, parentWingVAMPzero, cpacsWing) * 0.5
mySlats.append(createSlat('OuterSlat2', parentWingVAMPzero.id, innerEtaTE, innerXsiTE, outerEtaTE, outerXsiTE, innerX=innerX, outerX=outerX))
else:
#===========================================================================
# n Slats
#===========================================================================
# the inner border eta is located at the Fuselage
n = int(ceil(nSlats))
innerEtaTE = etaEngine + 0.025
innerXsiTE = cSlat / calcChordLengthAtEta(innerEtaTE, parentWingVAMPzero, cpacsWing)
# First Slat
# the outer border eta is determined from the span of the outer flap
outerEtaTE = innerEtaTE + spanSlat / n / span
outerXsiTE = cSlat / calcChordLengthAtEta(outerEtaTE, parentWingVAMPzero, cpacsWing)
#Slats extend 50% of their chord lenght
innerX = innerXsiTE * calcChordLengthAtEta(innerEtaTE, parentWingVAMPzero, cpacsWing) * 0.5
outerX = outerXsiTE * calcChordLengthAtEta(outerEtaTE, parentWingVAMPzero, cpacsWing) * 0.5
mySlats.append(createSlat('OuterSlat1', parentWingVAMPzero.id, innerEtaTE, innerXsiTE, outerEtaTE, outerXsiTE, innerX=innerX, outerX=outerX))
for i in range(2, n):
# new inner is the old outer
innerEtaTE = outerEtaTE
innerXsiTE = outerXsiTE
# the outer border eta is determined from the full span of the total outer flap
outerEtaTE = innerEtaTE + spanSlat / n / span
outerXsiTE = cSlat / calcChordLengthAtEta(outerEtaTE, parentWingVAMPzero, cpacsWing)
#Slats extend 50% of their chord lenght
innerX = innerXsiTE * calcChordLengthAtEta(innerEtaTE, parentWingVAMPzero, cpacsWing) * 0.5
outerX = outerXsiTE * calcChordLengthAtEta(outerEtaTE, parentWingVAMPzero, cpacsWing) * 0.5
mySlats.append(createSlat('OuterSlat' + str(i), parentWingVAMPzero.id, innerEtaTE, innerXsiTE, outerEtaTE, outerXsiTE, innerX=innerX, outerX=outerX))
# Last Slat
# new inner is the old outer
innerEtaTE = outerEtaTE
innerXsiTE = outerXsiTE
# the outer border eta is determined from the full span of the total outer flap
outerEtaTE = innerEtaTE + spanSlat / n / span
outerXsiTE = cSlat / calcChordLengthAtEta(outerEtaTE, parentWingVAMPzero, cpacsWing)
#Slats extend 50% of their chord lenght
innerX = innerXsiTE * calcChordLengthAtEta(innerEtaTE, parentWingVAMPzero, cpacsWing) * 0.5
outerX = outerXsiTE * calcChordLengthAtEta(outerEtaTE, parentWingVAMPzero, cpacsWing) * 0.5
mySlats.append(createSlat('OuterSlat' + str(n), parentWingVAMPzero.id, innerEtaTE, innerXsiTE, outerEtaTE, outerXsiTE, innerX=innerX, outerX=outerX))
#===========================================================================
# Output to CPACS
#===========================================================================
if type(cpacsComponentSegment.get_controlSurfaces()) == NoneType:
cpacsComponentSegment.set_controlSurfaces(controlSurfacesType())
if type(cpacsComponentSegment.get_controlSurfaces().get_leadingEdgeDevices()) == NoneType:
cpacsComponentSegment.get_controlSurfaces().set_leadingEdgeDevices(leadingEdgeDevicesType())
log.debug('VAMPzero SLAT: Exporting %s Slats to CPACS.' % (str(len(mySlats))))
for slat in mySlats:
cpacsComponentSegment.get_controlSurfaces().get_leadingEdgeDevices().add_leadingEdgeDevice(slat)
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 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)
