def createHTP(CPACSObj, id, xRoot, zRoot, tcRoot, tcTip, cRoot, cTip, span, phiLE, dihedral, LoD=0, location=True):
if LoD == WING_LOD.NONE:
return
# just for now
cpacsPath = '/cpacs/vehicles/aircraft/model/wings/wing[' + id + ']'
# the next line is the one to use later on
# cpacsPath = '/cpacs/vehicles/aircraft/model[model]/wings/wing[' + self.id + ']'
# get the wing object from given cpacs path
myWing = getObjfromXpath(CPACSObj, cpacsPath)
myWing.set_name(stringBaseType(valueOf_='htp'))
strUID = createHeader(myWing, id)
myWing.set_symmetry('x-z-plane')
if location:
myWing.set_parentUID(stringUIDBaseType(isLink=True, valueOf_='fuselage'))
createTransformation(myWing, 'absGlobal', xRoot, 0., zRoot)
else:
myWing.set_parentUID(stringUIDBaseType(isLink=True, valueOf_='vtp'))
createTransformation(myWing, 'absGlobal', xRoot, 0., zRoot)
# call corresponding wing creation method
if LoD == WING_LOD.SINGLE:
createTrapezoidWing(myWing, id, tcTip, tcRoot, cTip, cRoot, span, phiLE, dihedral, 0., strUID)
if not location:
createWingWingAttachment(myWing.get_componentSegments().get_componentSegment()[0], strUID, targetUID='vtp_Cseg', typeOfSeg='ttail')
def createFuselageSection(parent,
dfus,
cs,
ProfUID,
UID='FLSec',
Name='FLSec',
descr='Fuselage Section'):
'''
Used for generation of a fuselage Section.
Creates all the sections given through myRQSi.
@author: Jonas Jepsen
@param parent: fuselageSectionsType object, fuselageSectionType-objects will be added here
@param crossSection: only one cross section from PrADO [x_rel,z-dist,height/2,width/2]
@param ProfUID: the ProfileUID for this section
@param UID: UID of this section [string]
@param Name: Name of this section [string]
@param descr: Description of this section [string]
'''
## ONLY ONE ELEMENT PER SECTION SUPPORTED
mySection = fuselageSectionType(uID=UID)
mySection.set_name(stringBaseType(None, None, None, Name))
mySection.set_description(stringBaseType(None, None, None, descr))
transZ = cs[1] * dfus
scaleX = cs[3] * dfus
scaleZ = cs[2] * dfus
createTransformation(mySection, 'absGlobal', 0., 0., transZ, 1., 1., 1.,
0., 0., 0.)
myElements = fuselageElementsType()
def createFuselageElement(parent,
sx,
sz,
profUID,
UID='FLElem',
Name='FLElem',
descr='Fuselage Element'):
'''
Used for the creation of a fuselage element from PrADO cross section
@author: Jonas Jepsen
@param parent: fuselageElementsType object, element will be added here
@param crossSection: the cross section parameters from PrADO [list] (see myRQS in PrADOlib/Fuselages.py)
@param profUID: the uID of the used Profile
@param UID: the UID of this element
@param Name: Name of this Element [string]
@param descr: Description of this Element [string]
'''
myElement = fuselageElementType(uID=UID)
myElement.set_name(stringBaseType(None, None, None, Name))
myElement.set_description(stringBaseType(None, None, None, descr))
myElement.set_profileUID(stringBaseType(None, None, None, profUID))
createTransformation(myElement, 'absGlobal', 0., 0., 0., 1., sx, sz,
0., 0., 0.)
parent.add_element(myElement)
createFuselageElement(myElements, scaleX, scaleZ, ProfUID,
UID + '_Elem' + str(1), Name + '_Elem' + str(1),
descr + '_Element' + str(1))
mySection.set_elements(myElements)
parent.add_section(mySection)
def createWingElement(parent,
tx,
ty,
tz,
sx,
sy,
sz,
rx,
ry,
rz,
AirfUID,
UID='WElem',
Name='WElem',
descr='Wing Element'):
'''
Used for the creation of a wing element from PrADO cross section
@param parent: wingElementsType object, element will be added here
@param crossSection: the cross section parameters from PrADO [list] (see myFQS in PrADOlib/Wings.py)
@param AirfUID: the uID of the used Profile
@param UID: the UID of this element
@param Name: Name of this Element [string]
@param descr: Description of this Element [string]
'''
myElement = wingElementType(uID=UID)
myElement.set_name(stringBaseType(valueOf_=Name))
myElement.set_description(stringBaseType(valueOf_=descr))
myElement.set_airfoilUID(stringBaseType(valueOf_=AirfUID))
# Translation
createTransformation(myElement, 'absGlobal', tx, ty, tz, sx, sy, sz,
rx, ry, rz)
parent.add_element(myElement)
def createFuselage(CPACSObj, id, dfus, lnose, lcabin, ltail, LoD=0):
# just for now
if LoD==FUSE_LOD.NONE:
return
cpacsPath = '/cpacs/vehicles/aircraft/model/fuselages/fuselage[' + id + ']'
# the next line is the one to use later on
#cpacsPath = '/cpacs/vehicles/aircraft/model[model]/fuselages/fuselage[' + self.id + ']'
# gets a list of all wing elements
myFuse = getObjfromXpath(CPACSObj,cpacsPath)
strUID = myFuse.get_uID()
myUID = strUID
myName = stringBaseType(valueOf_=id)
myDescr = stringBaseType(valueOf_=strUID)
myFuse.set_uID(myUID)
myFuse.set_name(myName)
myFuse.set_description(myDescr)
createTransformation(myFuse, 'absGlobal',0.,0.,0.)
if LoD==FUSE_LOD.A320:
nose = list(NOSE)
cabin = list(CABIN)
tail = list(TAIL)
# remove double values
cabin.pop(0)
tail.pop(0)
# sections will be created, all existing sections will be deleted
createFuselageSections(myFuse, nose,cabin,tail, dfus, strUID, strUID, strUID)
createFuselagePositionings(myFuse, nose,cabin,tail, lnose,lcabin,ltail, strUID, strUID)
createFuselageSegments(myFuse, strUID, len(nose)+len(cabin)+len(tail)-1)
elif LoD==FUSE_LOD.ZYL:
# sections will be created, all existing sections will be deleted
mySections = fuselageSectionsType()
#calc fuselage radius
#rfus = dfus/2.
# make fuselage configuration data [x_rel,z-dist,height/2,width/2]]
fuseConf = [0.,0.,0.5,0.5]
createFuselageSection(mySections, dfus, fuseConf, 'Circle', strUID+'_Sec1', strUID+'_Sec1', strUID+'_Sec1')
createFuselageSection(mySections, dfus, fuseConf, 'Circle', strUID+'_Sec2', strUID+'_Sec2', strUID+'_Sec2')
createFuselageSection(mySections, dfus, fuseConf, 'Circle', strUID+'_Sec3', strUID+'_Sec3', strUID+'_Sec3')
createFuselageSection(mySections, dfus, fuseConf, 'Circle', strUID+'_Sec4', strUID+'_Sec4', strUID+'_Sec4')
myFuse.set_sections(mySections)
myPositionings = positioningsType()
createPositioning(myPositionings,str(id) + '_Pos1',None, str(id) + '_Sec1',0.,90.,0.,id + '_Pos1')
createPositioning(myPositionings,str(id) + '_Pos2',str(id) + '_Sec1',str(id) + '_Sec2',lnose,90.,0,id + '_Pos2')
createPositioning(myPositionings,str(id) + '_Pos3',str(id) + '_Sec2',str(id) + '_Sec3',lcabin,90.,0,id + '_Pos3')
createPositioning(myPositionings,str(id) + '_Pos4',str(id) + '_Sec3',str(id) + '_Sec4',ltail,90.,0,id + '_Pos4')
myFuse.set_positionings(myPositionings)
createFuselageSegments(myFuse, strUID, 3)
def createFuselageElement(parent, sx,sz, profUID, UID='FLElem', Name='FLElem', descr='Fuselage Element'):
'''
Used for the creation of a fuselage element from PrADO cross section
@author: Jonas Jepsen
@param parent: fuselageElementsType object, element will be added here
@param crossSection: the cross section parameters from PrADO [list] (see myRQS in PrADOlib/Fuselages.py)
@param profUID: the uID of the used Profile
@param UID: the UID of this element
@param Name: Name of this Element [string]
@param descr: Description of this Element [string]
'''
myElement = fuselageElementType(uID = UID)
myElement.set_name(stringBaseType(valueOf_=Name))
myElement.set_description(stringBaseType(valueOf_=descr))
myElement.set_profileUID(stringBaseType(valueOf_=profUID))
createTransformation(myElement,'absGlobal', 0.,0.,0., 1.,sx,sz, 0.,0.,0.)
parent.add_element(myElement)
def createWingElement(parent, tx, ty, tz, sx, sy, sz, rx, ry, rz, AirfUID, UID='WElem', Name='WElem', descr='Wing Element'):
'''
Used for the creation of a wing element from PrADO cross section
@param parent: wingElementsType object, element will be added here
@param crossSection: the cross section parameters from PrADO [list] (see myFQS in PrADOlib/Wings.py)
@param AirfUID: the uID of the used Profile
@param UID: the UID of this element
@param Name: Name of this Element [string]
@param descr: Description of this Element [string]
'''
myElement = wingElementType(uID=UID)
myElement.set_name(stringBaseType(valueOf_=Name))
myElement.set_description(stringBaseType(valueOf_=descr))
myElement.set_airfoilUID(stringBaseType(valueOf_=AirfUID))
# Translation
createTransformation(myElement, 'absGlobal', tx, ty, tz, sx, sy, sz, rx, ry, rz)
parent.add_element(myElement)
def createHTP(CPACSObj,
id,
xRoot,
zRoot,
tcRoot,
tcTip,
cRoot,
cTip,
span,
phiLE,
dihedral,
LoD=0,
location=True):
if LoD == WING_LOD.NONE:
return
# just for now
cpacsPath = '/cpacs/vehicles/aircraft/model/wings/wing[' + id + ']'
# the next line is the one to use later on
# cpacsPath = '/cpacs/vehicles/aircraft/model[model]/wings/wing[' + self.id + ']'
# get the wing object from given cpacs path
myWing = getObjfromXpath(CPACSObj, cpacsPath)
myWing.set_name(stringBaseType(valueOf_='htp'))
strUID = createHeader(myWing, id)
myWing.set_symmetry('x-z-plane')
if location:
myWing.set_parentUID(
stringUIDBaseType(isLink=True, valueOf_='fuselage'))
createTransformation(myWing, 'absGlobal', xRoot, 0., zRoot)
else:
myWing.set_parentUID(stringUIDBaseType(isLink=True, valueOf_='vtp'))
createTransformation(myWing, 'absGlobal', xRoot, 0., zRoot)
# call corresponding wing creation method
if LoD == WING_LOD.SINGLE:
createTrapezoidWing(myWing, id, tcTip, tcRoot, cTip, cRoot, span,
phiLE, dihedral, 0., strUID)
if not location:
createWingWingAttachment(
myWing.get_componentSegments().get_componentSegment()[0],
strUID,
targetUID='vtp_Cseg',
typeOfSeg='ttail')
def createFuselageSection(parent, dfus, cs, ProfUID, UID='FLSec', Name='FLSec', descr='Fuselage Section'):
'''
Used for generation of a fuselage Section.
Creates all the sections given through myRQSi.
@author: Jonas Jepsen
@param parent: fuselageSectionsType object, fuselageSectionType-objects will be added here
@param crossSection: only one cross section from PrADO [x_rel,z-dist,height/2,width/2]
@param ProfUID: the ProfileUID for this section
@param UID: UID of this section [string]
@param Name: Name of this section [string]
@param descr: Description of this section [string]
'''
## ONLY ONE ELEMENT PER SECTION SUPPORTED
mySection = fuselageSectionType(uID=UID)
mySection.set_name(stringBaseType(valueOf_=Name))
mySection.set_description(stringBaseType(valueOf_=descr))
transZ = cs[1]*dfus
scaleX = cs[3]*dfus
scaleZ = cs[2]*dfus
createTransformation(mySection,'absGlobal',0.,0.,transZ, 1.,1.,1., 0.,0.,0.)
myElements = fuselageElementsType()
def createFuselageElement(parent, sx,sz, profUID, UID='FLElem', Name='FLElem', descr='Fuselage Element'):
'''
Used for the creation of a fuselage element from PrADO cross section
@author: Jonas Jepsen
@param parent: fuselageElementsType object, element will be added here
@param crossSection: the cross section parameters from PrADO [list] (see myRQS in PrADOlib/Fuselages.py)
@param profUID: the uID of the used Profile
@param UID: the UID of this element
@param Name: Name of this Element [string]
@param descr: Description of this Element [string]
'''
myElement = fuselageElementType(uID = UID)
myElement.set_name(stringBaseType(valueOf_=Name))
myElement.set_description(stringBaseType(valueOf_=descr))
myElement.set_profileUID(stringBaseType(valueOf_=profUID))
createTransformation(myElement,'absGlobal', 0.,0.,0., 1.,sx,sz, 0.,0.,0.)
parent.add_element(myElement)
createFuselageElement(myElements, scaleX,scaleZ, ProfUID, UID+'_Elem'+str(1), Name+'_Elem'+str(1), descr+'_Element'+str(1))
mySection.set_elements(myElements)
parent.add_section(mySection)
def createVTP(CPACSObj,
id,
xRoot,
zRoot,
tcRoot,
tcTip,
cRoot,
cTip,
span,
phiLE,
LoD=0):
if LoD == WING_LOD.NONE:
return
# just for now
cpacsPath = '/cpacs/vehicles/aircraft/model/wings/wing[' + id + ']'
# the next line is the one to use later on
# cpacsPath = '/cpacs/vehicles/aircraft/model[model]/wings/wing[' + self.id + ']'
# get the wing object from given cpacs path
myWing = getObjfromXpath(CPACSObj, cpacsPath)
myWing.set_name(stringBaseType(valueOf_='vtp'))
myWing.set_parentUID(stringUIDBaseType(isLink=True, valueOf_='fuselage'))
strUID = createHeader(myWing, id)
# rotate vertical tail to correct orientation
createTransformation(myWing, 'absGlobal', xRoot, 0., zRoot, 1., 1., 1.,
90., 0., 0.)
# As the vtp is not symmetrical span values must be dubbled for conversion
span = span * 2
# call corresponding wing creation method
if LoD == WING_LOD.SINGLE:
createTrapezoidWing(myWing,
id,
tcRoot,
tcTip,
cTip,
cRoot,
span,
phiLE,
dihedral=0,
twist=0.,
strUID=strUID)
def createWingSection(parent, thickness, tx, ty, tz, sx, sy, sz, rx, ry, rz, AirfUID, maxT, UID='WSec', Name='WSec', descr='Wing Section'):
'''
Used for generation of a wing Section.
Creates all the sections given through myQSi.
@param parent: wingSectionsType object, wingSectionType-objects will be added here
@param crossSection: only one cross section from PrADOs R1GEO**i (with ** as F,HL,SL,WL and i as wingindex)
@param AirfUID: the AirfoilUID for this section
@param maxT: the max profile thickness of this section
@param UID: UID of this section [string]
@param Name: Name of this section [string]
@param descr: Description of this section [string]
'''
# # ONLY ONE ELEMENT PER SECTION SUPPORTED
mySection = wingSectionType(uID=UID)
mySection.set_name(stringBaseType(None, None, None, Name))
mySection.set_description(stringBaseType(None, None, None, descr))
# Position of the Element
createTransformation(mySection, 'absGlobal', tx, ty, tz, sx, sy, sz, rx, ry, rz,)
myElements = wingElementsType()
def createWingElement(parent, tx, ty, tz, sx, sy, sz, rx, ry, rz, AirfUID, UID='WElem', Name='WElem', descr='Wing Element'):
'''
Used for the creation of a wing element from PrADO cross section
@param parent: wingElementsType object, element will be added here
@param crossSection: the cross section parameters from PrADO [list] (see myFQS in PrADOlib/Wings.py)
@param AirfUID: the uID of the used Profile
@param UID: the UID of this element
@param Name: Name of this Element [string]
@param descr: Description of this Element [string]
'''
myElement = wingElementType(uID=UID)
myElement.set_name(stringBaseType(valueOf_=Name))
myElement.set_description(stringBaseType(valueOf_=descr))
myElement.set_airfoilUID(stringBaseType(valueOf_=AirfUID))
# Translation
createTransformation(myElement, 'absGlobal', tx, ty, tz, sx, sy, sz, rx, ry, rz)
parent.add_element(myElement)
createWingElement(myElements, 0., 0., 0., 1., 1., thickness, 0., 0., 0., AirfUID, UID + '_Elem' + str(1), Name + '_Elem' + str(1), descr + '_Element' + str(1))
mySection.set_elements(myElements)
parent.add_section(mySection)
def createFuselageElement(parent,
sx,
sz,
profUID,
UID='FLElem',
Name='FLElem',
descr='Fuselage Element'):
'''
Used for the creation of a fuselage element from PrADO cross section
@author: Jonas Jepsen
@param parent: fuselageElementsType object, element will be added here
@param crossSection: the cross section parameters from PrADO [list] (see myRQS in PrADOlib/Fuselages.py)
@param profUID: the uID of the used Profile
@param UID: the UID of this element
@param Name: Name of this Element [string]
@param descr: Description of this Element [string]
'''
myElement = fuselageElementType(uID=UID)
myElement.set_name(stringBaseType(None, None, None, Name))
myElement.set_description(stringBaseType(None, None, None, descr))
myElement.set_profileUID(stringBaseType(None, None, None, profUID))
createTransformation(myElement, 'absGlobal', 0., 0., 0., 1., sx, sz,
0., 0., 0.)
parent.add_element(myElement)
def createWing(CPACSObj=None, zeroWing=None, id="1", LoD=0.):
"""
This function triggers the different export modes of the wing depending on the desired
level of detail.
Options include a single trapezoid, double trapezoid, advanced double trapezoid (that includes
a rectangular center fuselage section) and a strut-braced wing.
Please note, these are the internal guts of VAMPzero's CPACS export. A lot of the code
here is experimental and furthermore highly chaotic. In case of emergency contact Daniel or Jonas.
:param CPACSObj: The overall CPACS object of the export
:param zeroWing: The instance of the wing.
:param id: The id of the wing, mostly sth. like wing
:param LoD: The level of detail of the desired input.
:return: CPACSObj including a new wing
"""
if LoD == WING_LOD.NONE:
return
# just for now
cpacsPath = '/cpacs/vehicles/aircraft/model/wings/wing[' + id + ']'
# the next line is the one to use later on
# cpacsPath = '/cpacs/vehicles/aircraft/model[model]/wings/wing[' + self.id + ']'
# get the wing object from given cpacs path
cpacsWing = getObjfromXpath(CPACSObj, cpacsPath)
strUID = createHeader(cpacsWing, id)
cpacsWing.set_symmetry('x-z-plane')
cpacsWing.set_name(stringBaseType(valueOf_='wing'))
cpacsWing.set_parentUID(stringUIDBaseType(isLink=True,
valueOf_='fuselage'))
xRoot = zeroWing.xRoot.getValue()
zRoot = zeroWing.zRoot.getValue()
cRoot = zeroWing.cRoot.getValue()
cTip = zeroWing.cTip.getValue()
span = zeroWing.span.getValue()
dfus = zeroWing.aircraft.fuselage.dfus.getValue()
phiLE = zeroWing.phiLE.getValue()
dihedral = zeroWing.dihedral.getValue()
twist = zeroWing.twist.getValue()
Sref = zeroWing.refArea.getValue()
xMAC25 = zeroWing.xMAC25.getValue()
tcRoot = zeroWing.airfoilr.tc.getValue()
tcTip = zeroWing.airfoilt.tc.getValue()
try:
etakf = zeroWing.etaKink.getValue()
yFus = zeroWing.yFuselage.getValue()
etaEng = zeroWing.etaEngine.getValue()
etaFus = yFus / span * 2.
except AttributeError:
pass #As not all components that call this method have a kink
try:
yRoot = zeroWing.yRoot.getValue()
except AttributeError:
pass #As not all components that call this method have a kink
createTransformation(cpacsWing, 'absGlobal', xRoot, 0., zRoot)
# call corresponding wing creation method
if LoD == WING_LOD.SINGLE:
createTrapezoidWing(cpacsWing, id, tcRoot, tcTip, cTip, cRoot, span,
phiLE, dihedral, twist, strUID)
elif LoD == WING_LOD.DOUBLE:
createDoubleTrapezoidWing(cpacsWing, id, cTip, cRoot, span, Sref,
phiLE, dihedral, twist, xMAC25, etakf,
strUID)
elif LoD == WING_LOD.ADVDOUBLE:
createAdvDoubleTrapezoidWing(cpacsWing, id, cTip, cRoot, span, Sref,
dfus, phiLE, dihedral, twist, xMAC25,
etakf, strUID, yFus, xRoot, etaEng,
tcRoot, tcTip)
elif LoD == WING_LOD.UCAV:
createUCAVWing(cpacsWing, id, cTip, cRoot, span, Sref, phiLE, dihedral,
etakf, strUID)
elif LoD == WING_LOD.SBW:
print "dihedral", dihedral
etaStrut = zeroWing.aircraft.strut.etaStrut.getValue()
createStrutBracedWing(cpacsWing,
id=id,
cTip=cTip,
cRoot=cRoot,
span=span,
Sref=Sref,
phiLE=phiLE,
dihedral=dihedral,
twist=twist,
xMAC25=xMAC25,
etaFus=etaFus,
etaStrut=etaStrut,
tcRoot=tcRoot,
tcTip=tcTip,
xRoot=xRoot,
strUID=strUID)
elif LoD == WING_LOD.STRUT:
etaStrut = zeroWing.aircraft.strut.etaStrut.getValue()
createStrut(cpacsWing,
id=id,
cTip=cTip,
cRoot=cRoot,
span=span,
phiLE=phiLE,
dihedral=dihedral,
tcRoot=tcRoot,
tcTip=tcTip,
xRoot=xRoot,
yRoot=yRoot,
twist=twist,
etaStrut=etaStrut,
strUID=strUID)
def createFuselage(CPACSObj, id, dfus, lnose, lcabin, ltail, LoD=0):
# just for now
if LoD == FUSE_LOD.NONE:
return
cpacsPath = '/cpacs/vehicles/aircraft/model/fuselages/fuselage[' + id + ']'
# the next line is the one to use later on
#cpacsPath = '/cpacs/vehicles/aircraft/model[model]/fuselages/fuselage[' + self.id + ']'
# gets a list of all wing elements
myFuse = getObjfromXpath(CPACSObj, cpacsPath)
strUID = myFuse.get_uID()
myUID = strUID
myName = stringBaseType(None, None, None, id)
myDescr = stringBaseType(None, None, None, strUID)
myFuse.set_uID(myUID)
myFuse.set_name(myName)
myFuse.set_description(myDescr)
createTransformation(myFuse, 'absGlobal', 0., 0., 0.)
if LoD == FUSE_LOD.A320:
nose = list(NOSE)
cabin = list(CABIN)
tail = list(TAIL)
# remove double values
cabin.pop(0)
tail.pop(0)
# sections will be created, all existing sections will be deleted
createFuselageSections(myFuse, nose, cabin, tail, dfus, strUID, strUID,
strUID)
createFuselagePositionings(myFuse, nose, cabin, tail, lnose, lcabin,
ltail, strUID, strUID)
createFuselageSegments(myFuse, strUID,
len(nose) + len(cabin) + len(tail) - 1)
elif LoD == FUSE_LOD.ZYL:
# sections will be created, all existing sections will be deleted
mySections = fuselageSectionsType()
#calc fuselage radius
#rfus = dfus/2.
# make fuselage configuration data [x_rel,z-dist,height/2,width/2]]
fuseConf = [0., 0., 0.5, 0.5]
createFuselageSection(mySections, dfus, fuseConf, 'Circle',
strUID + '_Sec1', strUID + '_Sec1',
strUID + '_Sec1')
createFuselageSection(mySections, dfus, fuseConf, 'Circle',
strUID + '_Sec2', strUID + '_Sec2',
strUID + '_Sec2')
createFuselageSection(mySections, dfus, fuseConf, 'Circle',
strUID + '_Sec3', strUID + '_Sec3',
strUID + '_Sec3')
createFuselageSection(mySections, dfus, fuseConf, 'Circle',
strUID + '_Sec4', strUID + '_Sec4',
strUID + '_Sec4')
myFuse.set_sections(mySections)
myPositionings = positioningsType()
createPositioning(myPositionings,
str(id) + '_Pos1', None,
str(id) + '_Sec1', 0., 90., 0., id + '_Pos1')
createPositioning(myPositionings,
str(id) + '_Pos2',
str(id) + '_Sec1',
str(id) + '_Sec2', lnose, 90., 0, id + '_Pos2')
createPositioning(myPositionings,
str(id) + '_Pos3',
str(id) + '_Sec2',
str(id) + '_Sec3', lcabin, 90., 0, id + '_Pos3')
createPositioning(myPositionings,
str(id) + '_Pos4',
str(id) + '_Sec3',
str(id) + '_Sec4', ltail, 90., 0, id + '_Pos4')
myFuse.set_positionings(myPositionings)
createFuselageSegments(myFuse, strUID, 3)
def createWingSection(parent,
thickness,
tx,
ty,
tz,
sx,
sy,
sz,
rx,
ry,
rz,
AirfUID,
maxT,
UID='WSec',
Name='WSec',
descr='Wing Section'):
'''
Used for generation of a wing Section.
Creates all the sections given through myQSi.
@param parent: wingSectionsType object, wingSectionType-objects will be added here
@param crossSection: only one cross section from PrADOs R1GEO**i (with ** as F,HL,SL,WL and i as wingindex)
@param AirfUID: the AirfoilUID for this section
@param maxT: the max profile thickness of this section
@param UID: UID of this section [string]
@param Name: Name of this section [string]
@param descr: Description of this section [string]
'''
# # ONLY ONE ELEMENT PER SECTION SUPPORTED
mySection = wingSectionType(uID=UID)
mySection.set_name(stringBaseType(None, None, None, Name))
mySection.set_description(stringBaseType(None, None, None, descr))
# Position of the Element
createTransformation(
mySection,
'absGlobal',
tx,
ty,
tz,
sx,
sy,
sz,
rx,
ry,
rz,
)
myElements = wingElementsType()
def createWingElement(parent,
tx,
ty,
tz,
sx,
sy,
sz,
rx,
ry,
rz,
AirfUID,
UID='WElem',
Name='WElem',
descr='Wing Element'):
'''
Used for the creation of a wing element from PrADO cross section
@param parent: wingElementsType object, element will be added here
@param crossSection: the cross section parameters from PrADO [list] (see myFQS in PrADOlib/Wings.py)
@param AirfUID: the uID of the used Profile
@param UID: the UID of this element
@param Name: Name of this Element [string]
@param descr: Description of this Element [string]
'''
myElement = wingElementType(uID=UID)
myElement.set_name(stringBaseType(valueOf_=Name))
myElement.set_description(stringBaseType(valueOf_=descr))
myElement.set_airfoilUID(stringBaseType(valueOf_=AirfUID))
# Translation
createTransformation(myElement, 'absGlobal', tx, ty, tz, sx, sy, sz,
rx, ry, rz)
parent.add_element(myElement)
createWingElement(myElements, 0., 0., 0., 1., 1., thickness, 0., 0., 0.,
AirfUID, UID + '_Elem' + str(1), Name + '_Elem' + str(1),
descr + '_Element' + str(1))
mySection.set_elements(myElements)
parent.add_section(mySection)
def createWing(CPACSObj = None, zeroWing = None, id="1", LoD = 0.):
"""
This function triggers the different export modes of the wing depending on the desired
level of detail.
Options include a single trapezoid, double trapezoid, advanced double trapezoid (that includes
a rectangular center fuselage section) and a strut-braced wing.
Please note, these are the internal guts of VAMPzero's CPACS export. A lot of the code
here is experimental and furthermore highly chaotic. In case of emergency contact Daniel or Jonas.
:param CPACSObj: The overall CPACS object of the export
:param zeroWing: The instance of the wing.
:param id: The id of the wing, mostly sth. like wing
:param LoD: The level of detail of the desired input.
:return: CPACSObj including a new wing
"""
if LoD == WING_LOD.NONE:
return
# just for now
cpacsPath = '/cpacs/vehicles/aircraft/model/wings/wing[' + id + ']'
# the next line is the one to use later on
# cpacsPath = '/cpacs/vehicles/aircraft/model[model]/wings/wing[' + self.id + ']'
# get the wing object from given cpacs path
cpacsWing = getObjfromXpath(CPACSObj, cpacsPath)
strUID = createHeader(cpacsWing, id)
cpacsWing.set_symmetry('x-z-plane')
cpacsWing.set_name(stringBaseType(valueOf_='wing'))
cpacsWing.set_parentUID(stringUIDBaseType(isLink=True, valueOf_='fuselage'))
xRoot = zeroWing.xRoot.getValue()
zRoot = zeroWing.zRoot.getValue()
cRoot = zeroWing.cRoot.getValue()
cTip = zeroWing.cTip.getValue()
span = zeroWing.span.getValue()
dfus = zeroWing.aircraft.fuselage.dfus.getValue()
phiLE = zeroWing.phiLE.getValue()
dihedral = zeroWing.dihedral.getValue()
twist = zeroWing.twist.getValue()
Sref = zeroWing.refArea.getValue()
xMAC25 = zeroWing.xMAC25.getValue()
tcRoot = zeroWing.airfoilr.tc.getValue()
tcTip = zeroWing.airfoilt.tc.getValue()
try:
etakf = zeroWing.etaKink.getValue()
yFus = zeroWing.yFuselage.getValue()
etaEng = zeroWing.etaEngine.getValue()
etaFus = yFus/span*2.
except AttributeError:
pass #As not all components that call this method have a kink
try:
yRoot = zeroWing.yRoot.getValue()
except AttributeError:
pass #As not all components that call this method have a kink
createTransformation(cpacsWing, 'absGlobal', xRoot, 0., zRoot)
# call corresponding wing creation method
if LoD == WING_LOD.SINGLE:
createTrapezoidWing(cpacsWing, id, tcRoot, tcTip, cTip, cRoot, span, phiLE, dihedral, twist, strUID)
elif LoD == WING_LOD.DOUBLE:
createDoubleTrapezoidWing(cpacsWing, id, cTip, cRoot, span, Sref, phiLE, dihedral, twist, xMAC25, etakf, strUID)
elif LoD == WING_LOD.ADVDOUBLE:
createAdvDoubleTrapezoidWing(cpacsWing, id, cTip, cRoot, span, Sref, dfus, phiLE, dihedral, twist, xMAC25, etakf, strUID, yFus, xRoot, etaEng, tcRoot, tcTip)
elif LoD == WING_LOD.UCAV:
createUCAVWing(cpacsWing, id, cTip, cRoot, span, Sref, phiLE, dihedral, etakf, strUID)
elif LoD == WING_LOD.SBW:
etaStrut = zeroWing.aircraft.strut.etaStrut.getValue()
createStrutBracedWing(cpacsWing, id=id, cTip=cTip, cRoot=cRoot, span=span, Sref=Sref, phiLE=phiLE, dihedral=dihedral, twist=twist, xMAC25=xMAC25, etaFus=etaFus, etaStrut=etaStrut, tcRoot=tcRoot, tcTip=tcTip, xRoot=xRoot, strUID=strUID)
elif LoD == WING_LOD.SBWStraight:
etaStrut = zeroWing.aircraft.strut.etaStrut.getValue()
createStraightStrutBracedWing(cpacsWing, id=id, cTip=cTip, cRoot=cRoot, span=span, Sref=Sref, phiLE=phiLE, dihedral=dihedral, twist=twist, xMAC25=xMAC25, etaFus=etaFus, etaStrut=etaStrut, tcRoot=tcRoot, tcTip=tcTip, xRoot=xRoot, strUID=strUID)
elif LoD == WING_LOD.STRUT:
etaStrut = zeroWing.aircraft.strut.etaStrut.getValue()
createStrut(cpacsWing, id=id, cTip=cTip, cRoot=cRoot, span=span, phiLE=phiLE, dihedral=dihedral, tcRoot=tcRoot, tcTip=tcTip, xRoot=xRoot, yRoot=yRoot, twist=twist, etaStrut=etaStrut, strUID=strUID)