def createFuselagePositionings(parent, nose,cabin,tail, lnose,lcabin,ltail, strUID, strName):
'''
This method is used to create the positioning of the sections of a fuselage.
It calculates the sweep and length.
@author: Jonas Jepsen
@param parent: could be any Type holding a positioningsType. Here [fuselageType]
@param myRQSi: crosssection data
@param strUID: UID of this Positioning [string]
@param strName: Name of this Positioning [string]
'''
myPositionings = positioningsType()
# countAll counts the total amount of cross sections for this fuselage
countAll = 0
for part in [[nose,lnose],[cabin,lcabin],[tail,ltail]]:
# lastPos is used to calc the lenght of a Segment from the absolute position
# reset lastPos to 0 after each part because positions are given in relative koordinates from 0 to 1 in each part (nose,cabine and tail)
lastPos = 0.
# create positionings
for cs in part[0]:
countAll += 1
pos = cs[0]*part[1]
# create Positionings
if countAll <= 1:
createPositioning(myPositionings, strUID+'_Pos'+str(countAll),None,strUID+'_Sec'+str(countAll),pos,90.,0.,strName+'_Position'+str(countAll))
else:
createPositioning(myPositionings, strUID+'_Pos'+str(countAll),strUID+'_Sec'+str(countAll-1),strUID+'_Sec'+str(countAll),pos-lastPos,90.,0.,strName+'_Position'+str(countAll))
lastPos = pos
parent.set_positionings(myPositionings)
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 createDoubleTrapezoidWing(myWing, id, cTip, cRoot, span, Sref, phiLE, dihedral, twist, xMAC25, etakf, strUID):
'''
This method creates a double trapezoid wing geometry in the 'myWing' parameter.
@author: Jonas Jepsen
@param myWing: wings CPACS object
@param id: the VAMPzero-id of the wing
@param cTip: length of chord at wing tip [m]
@param cRoot: length of chord at wing root [m]
@param span: span of the wing [m]
@param Sref: reference area [m^2]
@param phiLE: sweep angle at the leading edge [deg]
@param dihedral: dihedralangle of the wing [deg]
@param twist: twist of the outer wing section [deg]
@param etakf: dimensionless span coordinate [-]
@param strUID: the CPACS-uID of the wing
'''
# sections and positionings will be created, all existing sections and positionings will be deleted
mySections = wingSectionsType()
myPositionings = positioningsType()
# calc Lvl 1 parameters
taperRatio = (cTip/cRoot)
cRoot, cKink, cTip = calcWing(span, Sref, taperRatio, phiLE, etakf)
createWingSection(mySections, 0.,0.,0., cRoot,1.,cRoot, 0.,0.,0., 'NACA653218', 1, strUID + '_Sec1', strUID + '_Sec1', strUID + '_Sec1')
createWingSection(mySections, 0.,0.,0., cKink,1.,cKink, 0.,0.,0., 'NACA653218', 1, strUID + '_Sec2', strUID + '_Sec2', strUID + '_Sec2')
createWingSection(mySections, 0.,0.,0., cTip,1.,cTip, 0.,twist,0., 'NACA653218', 1, strUID + '_Sec3', strUID + '_Sec3', strUID + '_Sec3')
# calc length from span, sweep and dihedral
sweep_rad = phiLE/180. * pi
dihedral_rad = dihedral/180. * pi
length1 = (etakf*span/2.)/cos(sweep_rad)/cos(dihedral_rad)
length2 = span/2.*(1-etakf)/cos(sweep_rad)/cos(dihedral_rad)
createPositioning(myPositionings,str(id) + '_Pos1',None, str(id) + '_Sec1',0.,0.,0.,id)
createPositioning(myPositionings,str(id) + '_Pos2',str(id) + '_Sec1',str(id) + '_Sec2',length1,phiLE,dihedral,id)
createPositioning(myPositionings,str(id) + '_Pos3',str(id) + '_Sec2',str(id) + '_Sec3',length2,phiLE,dihedral,id)
myWing.set_sections(mySections)
myWing.set_positionings(myPositionings)
createWingSegments(myWing, strUID, 2)
createComponentSegment(myWing, strUID)
# calc wing position
tauk = cTip/cKink
myLambda = span**2/Sref
sweep_rad = 35./180.*pi
tanPhi25a = calcPhi25a(sweep_rad, taperRatio, tauk, etakf, span, cRoot)
tanPhi25i = calcPhi25i(sweep_rad, taperRatio, tauk, etakf, span, cRoot)
Xef = calcXef(cRoot, myLambda, tanPhi25i, tanPhi25a, etakf, taperRatio, tauk)
xRoot = calcXRoot(xMAC25, Xef, cRoot)
# set wing x - position
myWing.get_transformation().get_translation().set_x(doubleBaseType(None, None, None,str(xRoot)))
def createTrapezoidWing(myWing, id, tcRoot, tcTip, cTip, cRoot, span, phiLE,
dihedral, twist, strUID):
'''
This method creates a trapezoid wing geometry in the 'myWing' parameter.
@author: Jonas Jepsen
@param myWing: wings CPACS object
@param id: the VAMPzero-id of the wing
@param cTip: length of chord at wing tip [m]
@param cRoot: length of chord at wing root [m]
@param span: span of the wing [m]
@param phiLE: sweep angle at the leading edge [deg]
@param dihedral: dihedralangle of the wing [deg]
@param twist: twist of the outer wing section [deg]
@param strUID: the CPACS-uID of the wing
'''
# sections and positionings will be created, all existing sections and positionings will be deleted
mySections = wingSectionsType()
myPositionings = positioningsType()
createWingSection(mySections, tcRoot / 0.09, 0., 0., 0., cRoot, 1., cRoot,
0., 0., 0., 'NACA0009', 1, strUID + '_Sec1',
strUID + '_Sec1', strUID + '_Sec1')
createWingSection(mySections, tcTip / 0.09, 0., 0., 0., cTip, 1., cTip, 0.,
twist, 0., 'NACA0009', 1, strUID + '_Sec2',
strUID + '_Sec2', strUID + '_Sec2')
# calc length from span, sweep and dihedral
sweep_rad = phiLE / 180. * pi
dihedral_rad = dihedral / 180. * pi
length = (span / 2.) / cos(sweep_rad) / cos(
dihedral_rad) # @todo: provide dihedral
createPositioning(myPositionings,
str(id) + '_Pos1', None,
str(id) + '_Sec1', 0., 0., 0., id)
createPositioning(myPositionings,
str(id) + '_Pos2',
str(id) + '_Sec1',
str(id) + '_Sec2', length, phiLE, dihedral, id)
myWing.set_sections(mySections)
myWing.set_positionings(myPositionings)
createWingSegments(myWing, strUID, 1)
createComponentSegment(myWing, strUID)
createSpars(myWing.get_componentSegments().get_componentSegment()[0],
strUID, 'trapezoid')
createShell(myWing.get_componentSegments().get_componentSegment()[0],
strUID, 'trapezoid')
createRibs(parent=myWing.get_componentSegments().get_componentSegment()[0],
parentUID=id,
typeOfSeg='trapezoid')
def createStrut(myWing, id, tcRoot, tcTip, cTip, cRoot, span, phiLE, dihedral, twist, xRoot, yRoot, etaStrut, strUID):
'''
This method creates a trapezoid wing geometry in the 'myWing' parameter.
@author: Jonas Jepsen
@param myWing: wings CPACS object
@param id: the VAMPzero-id of the wing
@param cTip: length of chord at wing tip [m]
@param cRoot: length of chord at wing root [m]
@param span: span of the wing [m]
@param phiLE: sweep angle at the leading edge [deg]
@param dihedral: dihedralangle of the wing [deg]
@param twist: twist of the outer wing section [deg]
@param strUID: the CPACS-uID of the wing
'''
# sections and positionings will be created, all existing sections and positionings will be deleted
mySections = wingSectionsType()
myPositionings = positioningsType()
incidence_angle = 2.
createWingSection(mySections, tcRoot / 0.09, 0., 0., 0., cRoot, 1., cRoot, 0., incidence_angle, 0., 'NACA0009', 1, strUID + '_Sec1', strUID + '_Sec1', strUID + '_Sec1')
createWingSection(mySections, tcRoot / 0.09, 0., 0., 0., cRoot, 1., cRoot, dihedral, incidence_angle, 0., 'NACA0009', 1, strUID + '_Sec2', strUID + '_Sec2', strUID + '_Sec2')
createWingSection(mySections, tcTip / 0.09, 0., 0., 0., cTip, 1., cTip, dihedral, incidence_angle, 0., 'NACA0009', 1, strUID + '_Sec3', strUID + '_Sec3', strUID + '_Sec3')
createPositioning(myPositionings, str(id) + '_Pos1', None, str(id) + '_Sec1', 0., 0., 0., id)
createPositioning(myPositionings, str(id) + '_Pos2', str(id) + '_Sec1', str(id) + '_Sec2', yRoot, 0., 0., id)
createPositioning(myPositionings, str(id) + '_Pos3', str(id) + '_Sec2', str(id) + '_Sec3', span, phiLE, dihedral, id)
myWing.set_sections(mySections)
myWing.set_positionings(myPositionings)
createWingSegments(myWing, strUID, 2)
createComponentSegment(myWing, strUID, fromElement='_Sec2_Elem1')
createRibs(myWing.get_componentSegments().get_componentSegment()[0], strUID, 'strut', etaStrut=etaStrut)
createSpars(myWing.get_componentSegments().get_componentSegment()[0], strUID, 'strut')
createShell(myWing.get_componentSegments().get_componentSegment()[0], strUID, 'strut')
createWingFuselageAttachment(myWing.get_componentSegments().get_componentSegment()[0], strUID, typeOfSeg='strut')
createWingWingAttachment(myWing.get_componentSegments().get_componentSegment()[0], strUID, typeOfSeg='strut')
# set wing x - position and twist
myWing.get_transformation().get_translation().set_x(doubleBaseType(None, None, None, str(xRoot)))
#myWing.get_transformation().get_translation().set_y(doubleBaseType(None, None, None, str(yRoot)))
def createUCAVWing(myWing, id, cTip, cRoot, span, Sref, phiLE, dihedral, etakf, strUID):
'''
This method creates a ucav wing geometry in the 'myWing' parameter.
@param myWing: wings CPACS object
@param cTip: length of chord at wing tip [m]
@param cRoot: length of chord at wing root [m]
@param span: span of the wing [m]
@param Sref: reference area [m^2]
@param phiLE: sweep angle at the leading edge [deg]
@param dihedral: dihedralangle of the wing [deg]
@param etakf: dimensionless span coordinate [-]
@param strUID:
'''
# sections and positionings will be created, all existing sections and positionings will be deleted
mySections = wingSectionsType()
myPositionings = positioningsType()
# calc Lvl 1 parameters
cRoot, cKink, cTip,etaD = calcWing(span, Sref, phiLE, etakf)
createWingSection(mySections, 0.,0.,0., cRoot,1.,cRoot, 0.,0.,0., 'NACA0000', 1, strUID + '_Sec1', strUID + '_Sec1', strUID + '_Sec1')
createWingSection(mySections, 0.,0.,0., cKink,1.,cKink, 0.,0.,0., 'NACA0000', 1, strUID + '_Sec2', strUID + '_Sec2', strUID + '_Sec2')
createWingSection(mySections, 0.,0.,0., cTip,1.,cTip, 0.,0.,0., 'NACA0000', 1, strUID + '_Sec3', strUID + '_Sec3', strUID + '_Sec3')
#Tip Section rather short
createWingSection(mySections, 0.,0.,0., 0.01,1.,0.01, 0.,0.,0., 'NACA0000', 1, strUID + '_Sec4', strUID + '_Sec4', strUID + '_Sec4')
# calc length from span, sweep and dihedral
sweep_rad = phiLE/180. * pi
dihedral_rad = dihedral/180. * pi
length1 = (etakf*span/2.)/cos(sweep_rad)/cos(dihedral_rad) # @todo: provide dihedral
length2 = span/2.*(1-etakf-etaD)/cos(sweep_rad)/cos(dihedral_rad) # @todo: provide dihedral
length3 = span/2.*etaD/cos(sweep_rad)/cos(dihedral_rad) # @todo: provide dihedral
createPositioning(myPositionings,str(id) + '_Pos1',None, str(id) + '_Sec1',0.,0.,0.,id)
createPositioning(myPositionings,str(id) + '_Pos2',str(id) + '_Sec1',str(id) + '_Sec2',length1,phiLE,dihedral,id)
createPositioning(myPositionings,str(id) + '_Pos3',str(id) + '_Sec2',str(id) + '_Sec3',length2,phiLE,dihedral,id)
createPositioning(myPositionings,str(id) + '_Pos4',str(id) + '_Sec3',str(id) + '_Sec4',length3,phiLE,dihedral,id)
myWing.set_sections(mySections)
myWing.set_positionings(myPositionings)
createWingSegments(myWing, strUID, 3)
def createFuselagePositionings(parent, nose, cabin, tail, lnose, lcabin, ltail,
strUID, strName):
'''
This method is used to create the positioning of the sections of a fuselage.
It calculates the sweep and length.
@author: Jonas Jepsen
@param parent: could be any Type holding a positioningsType. Here [fuselageType]
@param myRQSi: crosssection data
@param strUID: UID of this Positioning [string]
@param strName: Name of this Positioning [string]
'''
myPositionings = positioningsType()
# countAll counts the total amount of cross sections for this fuselage
countAll = 0
for part in [[nose, lnose], [cabin, lcabin], [tail, ltail]]:
# lastPos is used to calc the lenght of a Segment from the absolute position
# reset lastPos to 0 after each part because positions are given in relative koordinates from 0 to 1 in each part (nose,cabine and tail)
lastPos = 0.
# create positionings
for cs in part[0]:
countAll += 1
pos = cs[0] * part[1]
# create Positionings
if countAll <= 1:
createPositioning(myPositionings,
strUID + '_Pos' + str(countAll), None,
strUID + '_Sec' + str(countAll), pos, 90.,
0., strName + '_Position' + str(countAll))
else:
createPositioning(myPositionings,
strUID + '_Pos' + str(countAll),
strUID + '_Sec' + str(countAll - 1),
strUID + '_Sec' + str(countAll),
pos - lastPos, 90., 0.,
strName + '_Position' + str(countAll))
lastPos = pos
parent.set_positionings(myPositionings)
def createTrapezoidWing(myWing, id, tcRoot, tcTip, cTip, cRoot, span, phiLE, dihedral, twist, strUID):
'''
This method creates a trapezoid wing geometry in the 'myWing' parameter.
@author: Jonas Jepsen
@param myWing: wings CPACS object
@param id: the VAMPzero-id of the wing
@param cTip: length of chord at wing tip [m]
@param cRoot: length of chord at wing root [m]
@param span: span of the wing [m]
@param phiLE: sweep angle at the leading edge [deg]
@param dihedral: dihedralangle of the wing [deg]
@param twist: twist of the outer wing section [deg]
@param strUID: the CPACS-uID of the wing
'''
# sections and positionings will be created, all existing sections and positionings will be deleted
mySections = wingSectionsType()
myPositionings = positioningsType()
createWingSection(mySections, tcRoot / 0.09, 0., 0., 0., cRoot, 1., cRoot, 0., 0., 0., 'NACA0009', 1, strUID + '_Sec1', strUID + '_Sec1', strUID + '_Sec1')
createWingSection(mySections, tcTip / 0.09, 0., 0., 0., cTip, 1., cTip, 0., twist, 0., 'NACA0009', 1, strUID + '_Sec2', strUID + '_Sec2', strUID + '_Sec2')
# calc length from span, sweep and dihedral
sweep_rad = phiLE / 180. * pi
dihedral_rad = dihedral / 180. * pi
length = (span / 2.) / cos(sweep_rad) / cos(dihedral_rad) # @todo: provide dihedral
createPositioning(myPositionings, str(id) + '_Pos1', None, str(id) + '_Sec1', 0., 0., 0., id)
createPositioning(myPositionings, str(id) + '_Pos2', str(id) + '_Sec1', str(id) + '_Sec2', length, phiLE, dihedral, id)
myWing.set_sections(mySections)
myWing.set_positionings(myPositionings)
createWingSegments(myWing, strUID, 1)
createComponentSegment(myWing, strUID)
createSpars(myWing.get_componentSegments().get_componentSegment()[0], strUID, 'trapezoid')
createShell(myWing.get_componentSegments().get_componentSegment()[0], strUID, 'trapezoid')
createRibs(parent=myWing.get_componentSegments().get_componentSegment()[0], parentUID=id, typeOfSeg='trapezoid')
def createStrut(myWing, id, tcRoot, tcTip, cTip, cRoot, span, phiLE, dihedral,
twist, xRoot, yRoot, etaStrut, strUID):
'''
This method creates a trapezoid wing geometry in the 'myWing' parameter.
@author: Jonas Jepsen
@param myWing: wings CPACS object
@param id: the VAMPzero-id of the wing
@param cTip: length of chord at wing tip [m]
@param cRoot: length of chord at wing root [m]
@param span: span of the wing [m]
@param phiLE: sweep angle at the leading edge [deg]
@param dihedral: dihedralangle of the wing [deg]
@param twist: twist of the outer wing section [deg]
@param strUID: the CPACS-uID of the wing
'''
# sections and positionings will be created, all existing sections and positionings will be deleted
mySections = wingSectionsType()
myPositionings = positioningsType()
incidence_angle = 2.
createWingSection(mySections, tcRoot / 0.09, 0., 0., 0., cRoot, 1., cRoot,
0., incidence_angle, 0., 'NACA0009', 1, strUID + '_Sec1',
strUID + '_Sec1', strUID + '_Sec1')
createWingSection(mySections, tcRoot / 0.09, 0., 0., 0., cRoot, 1., cRoot,
dihedral, incidence_angle, 0., 'NACA0009', 1,
strUID + '_Sec2', strUID + '_Sec2', strUID + '_Sec2')
createWingSection(mySections, tcTip / 0.09, 0., 0., 0., cTip, 1., cTip,
dihedral, incidence_angle, 0., 'NACA0009', 1,
strUID + '_Sec3', strUID + '_Sec3', strUID + '_Sec3')
createPositioning(myPositionings,
str(id) + '_Pos1', None,
str(id) + '_Sec1', 0., 0., 0., id)
createPositioning(myPositionings,
str(id) + '_Pos2',
str(id) + '_Sec1',
str(id) + '_Sec2', yRoot, 0., 0., id)
createPositioning(myPositionings,
str(id) + '_Pos3',
str(id) + '_Sec2',
str(id) + '_Sec3', span, phiLE, dihedral, id)
myWing.set_sections(mySections)
myWing.set_positionings(myPositionings)
createWingSegments(myWing, strUID, 2)
createComponentSegment(myWing, strUID, fromElement='_Sec2_Elem1')
createRibs(myWing.get_componentSegments().get_componentSegment()[0],
strUID,
'strut',
etaStrut=etaStrut)
createSpars(myWing.get_componentSegments().get_componentSegment()[0],
strUID, 'strut')
createShell(myWing.get_componentSegments().get_componentSegment()[0],
strUID, 'strut')
createWingFuselageAttachment(
myWing.get_componentSegments().get_componentSegment()[0],
strUID,
typeOfSeg='strut')
createWingWingAttachment(
myWing.get_componentSegments().get_componentSegment()[0],
strUID,
typeOfSeg='strut')
# set wing x - position and twist
myWing.get_transformation().get_translation().set_x(
doubleBaseType(None, None, None, str(xRoot)))
def createAdvDoubleTrapezoidWing(myWing, id, cTip, cRoot, span, Sref, dfus,
phiLE, dihedral, twist, xMAC25, etakf, strUID,
yfus, xRoot, etaEng, tcRoot, tcTip):
'''
This method creates a double trapezoid wing geometry in the 'myWing' parameter.
** Introduced a linear twist distribution from *0* at root to *twist* at tip
@author: Jonas Jepsen
@param myWing: wings CPACS object
@param id: the VAMPzero-id of the wing
@param cTip: length of chord at wing tip [m]
@param cRoot: length of chord at wing root [m]
@param span: span of the wing [m]
@param Sref: reference area [m^2]
@param dfus: fuselage diameter [m]
@param phiLE: sweep angle at the leading edge [deg]
@param dihedral: dihedralangle of the wing [deg]
@param twist: twist of the outer wing section [deg]
@param etakf: dimensionless span coordinate [-]
@param strUID: the CPACS-uID of the wing
'''
# sections and positionings will be created, all existing sections and positionings will be deleted
mySections = wingSectionsType()
myPositionings = positioningsType()
# calc Lvl 1 parameters
taperRatio = (cTip / cRoot)
cRoot, cKink, cTip = calcWing(span, Sref, taperRatio, phiLE, etakf, dfus)
# calc length from span, sweep and dihedral
sweep_rad = phiLE / 180. * pi
dihedral_rad = dihedral / 180. * pi
# trying to correct the commented statement that uses dfus. will try to use yfus
# length1 = dfus / 2.
length1 = yfus
length2 = (etakf * span / 2. -
length1) / cos(sweep_rad) / cos(dihedral_rad)
length3 = span / 2. * (1 - etakf) / cos(sweep_rad) / cos(dihedral_rad)
# Increase (or reduce the twist by 4deg as that is the overall angle of incidence of the wing)
twist = twist - 4.
twistgrad = twist / (span / 2.)
twist1 = twistgrad * length1
twist2 = twistgrad * etakf * (span / 2.)
twist3 = twist
createWingSection(mySections, tcRoot / 0.09, 0., 0., 0., cRoot, 1., cRoot,
0., 0., 0., 'NACA0009', 1, strUID + '_Sec1',
strUID + '_Sec1', strUID + '_Sec1')
createWingSection(mySections, tcRoot / 0.18, 0., 0., 0., cRoot, 1., cRoot,
0., 0., 0., 'NACA653218', 1, strUID + '_Sec2',
strUID + '_Sec2', strUID + '_Sec2')
createWingSection(mySections, tcTip / 0.18, 0., 0., 0., cKink, 1., cKink,
0., twist2, 0., 'NACA653218', 1, strUID + '_Sec3',
strUID + '_Sec3', strUID + '_Sec3')
createWingSection(mySections, tcTip / 0.18, 0., 0., 0., cTip, 1., cTip, 0.,
twist3, 0., 'NACA653218', 1, strUID + '_Sec4',
strUID + '_Sec4', strUID + '_Sec4')
createPositioning(myPositionings,
str(id) + '_Pos1', None,
str(id) + '_Sec1', 0., 0., 0., id)
createPositioning(myPositionings,
str(id) + '_Pos2',
str(id) + '_Sec1',
str(id) + '_Sec2', length1, 0., 0., id)
createPositioning(myPositionings,
str(id) + '_Pos3',
str(id) + '_Sec2',
str(id) + '_Sec3', length2, phiLE, dihedral, id)
createPositioning(myPositionings,
str(id) + '_Pos4',
str(id) + '_Sec3',
str(id) + '_Sec4', length3, phiLE, dihedral, id)
myWing.set_sections(mySections)
myWing.set_positionings(myPositionings)
createWingSegments(myWing, strUID, 3)
createComponentSegment(myWing, strUID)
etafus = yfus / (span / 2.)
# Ribs outboard of the Fuselage section are placed at 0.8 m distance
nouterRibs = int(ceil((0.95 - etafus - 0.05) * span / 2. / 0.8))
createRibs(myWing.get_componentSegments().get_componentSegment()[0],
strUID,
'advDoubletrapezoid',
etaFus=etafus,
nRibs=nouterRibs,
etaEng=etaEng,
span=span / 2.)
createSpars(myWing.get_componentSegments().get_componentSegment()[0],
strUID,
'advDoubletrapezoid',
length1 / (span / 2.),
etakf / cos(dihedral_rad),
cTip=cTip,
cRoot=cRoot)
createShell(myWing.get_componentSegments().get_componentSegment()[0],
strUID, 'advDoubletrapezoid')
createWingFuselageAttachment(
myWing.get_componentSegments().get_componentSegment()[0], strUID,
'advDoubletrapezoid')
# Estimate ribNum of outer Rib
iRib = int(span * (0.85 - etaEng) / (2 * 0.8)) - 1
createTanks(myWing.get_componentSegments().get_componentSegment()[0],
strUID,
'advDoubletrapezoid',
nRib=iRib)
# calc wing position
tauK = cTip / cKink
etar = dfus / span
# XN25F = calcXN25F(cRoot, span, phiLE, etar, etakf, tauK, taperRatio)
# xRoot.py = calcXRoot(xMAC25, XN25F)
# set wing x - position and twist
myWing.get_transformation().get_translation().set_x(
doubleBaseType(None, None, None, str(xRoot)))
myWing.get_transformation().get_rotation().set_y(
doubleBaseType(None, None, None, str(4.)))
def createStrutBracedWing(myWing, id, cTip, cRoot, span, Sref, phiLE, dihedral, twist, xMAC25, etaFus, etaStrut, tcRoot, tcTip, xRoot, strUID):
'''
This method creates a double trapezoid wing geometry in the 'myWing' parameter.
@author: Jonas Jepsen
@param myWing: wings CPACS object
@param id: the VAMPzero-id of the wing
@param cTip: length of chord at wing tip [m]
@param cRoot: length of chord at wing root [m]
@param span: span of the wing [m]
@param Sref: reference area [m^2]
@param phiLE: sweep angle at the leading edge [deg]
@param dihedral: dihedralangle of the wing [deg]
@param twist: twist of the outer wing section [deg]
@param etakf: dimensionless span coordinate [-]
@param strUID: the CPACS-uID of the wing
'''
mySections = wingSectionsType()
myPositionings = positioningsType()
# calc Lvl 1 parameters
taperRatio = (cTip/cRoot)
cRoot = calcWing(b=span, S=Sref, tau=taperRatio, eF=etaFus)
cStrut = cRoot+(cTip-cRoot)*(etaStrut-etaFus)/(1-etaFus)
cTip = taperRatio * cRoot # cRoot was updated in the last step
# calc length from span, sweep and dihedral
sweep_rad = phiLE/180. * pi
dihedral_rad = dihedral/180. * pi
length1 = (etaFus*span/2.)
length2 = (etaStrut-etaFus)*span/2/cos(sweep_rad)/cos(dihedral_rad)
length3 = span/2.*(1-etaStrut)/cos(sweep_rad)/cos(dihedral_rad)
# Increase (or reduce the twist by 4deg as that is the overall angle of incidence of the wing)
incidenceAngle = 4.
twist = twist + incidenceAngle
twistgrad = twist / (span / 2.)
twist2 = twistgrad * length2
twist3 = twist
createWingSection(mySections, tcRoot/0.09, 0.,0.,0., cRoot,1.,cRoot, 0.,incidenceAngle,0., 'NACA0009', 1, strUID + '_Sec1', strUID + '_Sec1', strUID + '_Sec1')
createWingSection(mySections, tcRoot / 0.18, 0.,0.,0., cRoot,1.,cRoot, 0.,incidenceAngle,0., 'NACA653218', 1, strUID + '_Sec2', strUID + '_Sec2', strUID + '_Sec2')
createWingSection(mySections, tcRoot / 0.18, 0.,0.,0., cStrut,1.,cStrut, 0.,twist2,0., 'NACA653218', 1, strUID + '_Sec3', strUID + '_Sec3', strUID + '_Sec3')
createWingSection(mySections, tcTip / 0.18, 0.,0.,0., cTip,1.,cTip, 0.,twist3,0., 'NACA653218', 1, strUID + '_Sec4', strUID + '_Sec4', strUID + '_Sec4')
createPositioning(myPositionings,str(id) + '_Pos1',None, str(id) + '_Sec1',0.,0.,0.,id)
createPositioning(myPositionings,str(id) + '_Pos2',str(id) + '_Sec1',str(id) + '_Sec2',length1,0.,0.,id)
createPositioning(myPositionings,str(id) + '_Pos3',str(id) + '_Sec2',str(id) + '_Sec3',length2,phiLE,dihedral,id)
createPositioning(myPositionings,str(id) + '_Pos4',str(id) + '_Sec3',str(id) + '_Sec4',length3,phiLE,dihedral,id)
myWing.set_sections(mySections)
myWing.set_positionings(myPositionings)
createWingSegments(myWing, strUID, 3)
createComponentSegment(myWing, strUID)
# Ribs outboard of the Fuselage section are placed at 0.8 m distance
nouterRibs = int(ceil((0.95 - etaFus - 0.05) * span / 2. / 0.8))
createRibs(myWing.get_componentSegments().get_componentSegment()[0], strUID, 'strutBracedWing', etaFus=etaFus, nRibs=nouterRibs, etaStrut=etaStrut, span=span / 2., phi25 = phiLE)
createSpars(myWing.get_componentSegments().get_componentSegment()[0], strUID, 'strutBracedWing', etaFus=etaFus, cTip=cTip, cRoot=cRoot)
createShell(myWing.get_componentSegments().get_componentSegment()[0], strUID, 'strutBracedWing')
iRib = int(span * (0.9 - etaStrut) / (2 * 0.8)) - 1
if iRib == 1:
iRib = 2
createTanks(myWing.get_componentSegments().get_componentSegment()[0], strUID, typeOfSeg='strutBracedWing', nRib=iRib)
createWingFuselageAttachment(myWing.get_componentSegments().get_componentSegment()[0], strUID, 'advDoubletrapezoid')
# set wing x - position and twist
myWing.get_transformation().get_translation().set_x(doubleBaseType(valueOf_=str(xRoot)))
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 createStrutBracedWing(myWing, id, cTip, cRoot, span, Sref, phiLE, dihedral, twist, xMAC25, etaFus, etaStrut, tcRoot, tcTip, xRoot, strUID):
'''
This method creates a double trapezoid wing geometry in the 'myWing' parameter.
@author: Jonas Jepsen
@param myWing: wings CPACS object
@param id: the VAMPzero-id of the wing
@param cTip: length of chord at wing tip [m]
@param cRoot: length of chord at wing root [m]
@param span: span of the wing [m]
@param Sref: reference area [m^2]
@param phiLE: sweep angle at the leading edge [deg]
@param dihedral: dihedralangle of the wing [deg]
@param twist: twist of the outer wing section [deg]
@param etakf: dimensionless span coordinate [-]
@param strUID: the CPACS-uID of the wing
'''
mySections = wingSectionsType()
myPositionings = positioningsType()
# calc Lvl 1 parameters
taperRatio = (cTip/cRoot)
#cRoot, cFuselage, cTip = calcWing(span, Sref, taperRatio, phiLE, etaFus)
cStrut = cRoot+(cTip-cRoot)*(etaStrut-etaFus)/(1-etaFus)
# calc length from span, sweep and dihedral
sweep_rad = phiLE/180. * pi
dihedral_rad = dihedral/180. * pi
length1 = (etaFus*span/2.)
length2 = (etaStrut-etaFus)*span/2/cos(sweep_rad)/cos(dihedral_rad)
length3 = span/2.*(1-etaStrut)/cos(sweep_rad)/cos(dihedral_rad)
# Increase (or reduce the twist by 4deg as that is the overall angle of incidence of the wing)
incidenceAngle = 4.
twist = twist + incidenceAngle
twistgrad = twist / (span / 2.)
twist2 = twistgrad * length2
twist3 = twist
createWingSection(mySections, tcRoot/0.09, 0.,0.,0., cRoot,1.,cRoot, 0.,incidenceAngle,0., 'NACA0009', 1, strUID + '_Sec1', strUID + '_Sec1', strUID + '_Sec1')
createWingSection(mySections, tcRoot / 0.18, 0.,0.,0., cRoot,1.,cRoot, 0.,incidenceAngle,0., 'NACA653218', 1, strUID + '_Sec2', strUID + '_Sec2', strUID + '_Sec2')
createWingSection(mySections, tcRoot / 0.18, 0.,0.,0., cStrut,1.,cStrut, 0.,twist2,0., 'NACA653218', 1, strUID + '_Sec3', strUID + '_Sec3', strUID + '_Sec3')
createWingSection(mySections, tcTip / 0.18, 0.,0.,0., cTip,1.,cTip, 0.,twist3,0., 'NACA653218', 1, strUID + '_Sec4', strUID + '_Sec4', strUID + '_Sec4')
createPositioning(myPositionings,str(id) + '_Pos1',None, str(id) + '_Sec1',0.,0.,0.,id)
createPositioning(myPositionings,str(id) + '_Pos2',str(id) + '_Sec1',str(id) + '_Sec2',length1,0.,0.,id)
createPositioning(myPositionings,str(id) + '_Pos3',str(id) + '_Sec2',str(id) + '_Sec3',length2,phiLE,dihedral,id)
createPositioning(myPositionings,str(id) + '_Pos4',str(id) + '_Sec3',str(id) + '_Sec4',length3,phiLE,dihedral,id)
myWing.set_sections(mySections)
myWing.set_positionings(myPositionings)
createWingSegments(myWing, strUID, 3)
createComponentSegment(myWing, strUID)
# Ribs outboard of the Fuselage section are placed at 0.8 m distance
nouterRibs = int(ceil((0.95 - etaFus - 0.05) * span / 2. / 0.8))
createRibs(myWing.get_componentSegments().get_componentSegment()[0], strUID, 'strutBracedWing', etaFus=etaFus, nRibs=nouterRibs, etaStrut=etaStrut, span=span / 2., phi25 = phiLE)
createSpars(myWing.get_componentSegments().get_componentSegment()[0], strUID, 'strutBracedWing', etaFus=etaFus, cTip=cTip, cRoot=cRoot)
createShell(myWing.get_componentSegments().get_componentSegment()[0], strUID, 'strutBracedWing')
iRib = int(span * (0.9 - etaStrut) / (2 * 0.8)) - 1
if iRib == 1:
iRib = 2
createTanks(myWing.get_componentSegments().get_componentSegment()[0], strUID, typeOfSeg='strutBracedWing', nRib=iRib)
createWingFuselageAttachment(myWing.get_componentSegments().get_componentSegment()[0], strUID, 'advDoubletrapezoid')
# set wing x - position and twist
myWing.get_transformation().get_translation().set_x(doubleBaseType(None, None, None, str(xRoot)))
def createUCAVWing(myWing, id, cTip, cRoot, span, Sref, phiLE, dihedral, etakf, strUID):
"""
This method creates a ucav wing geometry in the 'myWing' parameter.
@param myWing: wings CPACS object
@param cTip: length of chord at wing tip [m]
@param cRoot: length of chord at wing root [m]
@param span: span of the wing [m]
@param Sref: reference area [m^2]
@param phiLE: sweep angle at the leading edge [deg]
@param dihedral: dihedralangle of the wing [deg]
@param etakf: dimensionless span coordinate [-]
@param strUID:
"""
# sections and positionings will be created, all existing sections and positionings will be deleted
mySections = wingSectionsType()
myPositionings = positioningsType()
# calc Lvl 1 parameters
cRoot, cKink, cTip, etaD = calcWing(span, Sref, phiLE, etakf)
createWingSection(
mySections,
0.0,
0.0,
0.0,
cRoot,
1.0,
cRoot,
0.0,
0.0,
0.0,
"NACA0000",
1,
strUID + "_Sec1",
strUID + "_Sec1",
strUID + "_Sec1",
)
createWingSection(
mySections,
0.0,
0.0,
0.0,
cKink,
1.0,
cKink,
0.0,
0.0,
0.0,
"NACA0000",
1,
strUID + "_Sec2",
strUID + "_Sec2",
strUID + "_Sec2",
)
createWingSection(
mySections,
0.0,
0.0,
0.0,
cTip,
1.0,
cTip,
0.0,
0.0,
0.0,
"NACA0000",
1,
strUID + "_Sec3",
strUID + "_Sec3",
strUID + "_Sec3",
)
# Tip Section rather short
createWingSection(
mySections,
0.0,
0.0,
0.0,
0.01,
1.0,
0.01,
0.0,
0.0,
0.0,
"NACA0000",
1,
strUID + "_Sec4",
strUID + "_Sec4",
strUID + "_Sec4",
)
# calc length from span, sweep and dihedral
sweep_rad = phiLE / 180.0 * pi
dihedral_rad = dihedral / 180.0 * pi
length1 = (etakf * span / 2.0) / cos(sweep_rad) / cos(dihedral_rad) # @todo: provide dihedral
length2 = span / 2.0 * (1 - etakf - etaD) / cos(sweep_rad) / cos(dihedral_rad) # @todo: provide dihedral
length3 = span / 2.0 * etaD / cos(sweep_rad) / cos(dihedral_rad) # @todo: provide dihedral
createPositioning(myPositionings, str(id) + "_Pos1", None, str(id) + "_Sec1", 0.0, 0.0, 0.0, id)
createPositioning(
myPositionings, str(id) + "_Pos2", str(id) + "_Sec1", str(id) + "_Sec2", length1, phiLE, dihedral, id
)
createPositioning(
myPositionings, str(id) + "_Pos3", str(id) + "_Sec2", str(id) + "_Sec3", length2, phiLE, dihedral, id
)
createPositioning(
myPositionings, str(id) + "_Pos4", str(id) + "_Sec3", str(id) + "_Sec4", length3, phiLE, dihedral, id
)
myWing.set_sections(mySections)
myWing.set_positionings(myPositionings)
createWingSegments(myWing, strUID, 3)
def createDoubleTrapezoidWing(myWing, id, cTip, cRoot, span, Sref, phiLE,
dihedral, twist, xMAC25, etakf, strUID):
'''
This method creates a double trapezoid wing geometry in the 'myWing' parameter.
@author: Jonas Jepsen
@param myWing: wings CPACS object
@param id: the VAMPzero-id of the wing
@param cTip: length of chord at wing tip [m]
@param cRoot: length of chord at wing root [m]
@param span: span of the wing [m]
@param Sref: reference area [m^2]
@param phiLE: sweep angle at the leading edge [deg]
@param dihedral: dihedralangle of the wing [deg]
@param twist: twist of the outer wing section [deg]
@param etakf: dimensionless span coordinate [-]
@param strUID: the CPACS-uID of the wing
'''
# sections and positionings will be created, all existing sections and positionings will be deleted
mySections = wingSectionsType()
myPositionings = positioningsType()
# calc Lvl 1 parameters
taperRatio = (cTip / cRoot)
cRoot, cKink, cTip = calcWing(span, Sref, taperRatio, phiLE, etakf)
createWingSection(mySections, 0., 0., 0., cRoot, 1., cRoot, 0., 0., 0.,
'NACA653218', 1, strUID + '_Sec1', strUID + '_Sec1',
strUID + '_Sec1')
createWingSection(mySections, 0., 0., 0., cKink, 1., cKink, 0., 0., 0.,
'NACA653218', 1, strUID + '_Sec2', strUID + '_Sec2',
strUID + '_Sec2')
createWingSection(mySections, 0., 0., 0., cTip, 1., cTip, 0., twist, 0.,
'NACA653218', 1, strUID + '_Sec3', strUID + '_Sec3',
strUID + '_Sec3')
# calc length from span, sweep and dihedral
sweep_rad = phiLE / 180. * pi
dihedral_rad = dihedral / 180. * pi
length1 = (etakf * span / 2.) / cos(sweep_rad) / cos(dihedral_rad)
length2 = span / 2. * (1 - etakf) / cos(sweep_rad) / cos(dihedral_rad)
createPositioning(myPositionings,
str(id) + '_Pos1', None,
str(id) + '_Sec1', 0., 0., 0., id)
createPositioning(myPositionings,
str(id) + '_Pos2',
str(id) + '_Sec1',
str(id) + '_Sec2', length1, phiLE, dihedral, id)
createPositioning(myPositionings,
str(id) + '_Pos3',
str(id) + '_Sec2',
str(id) + '_Sec3', length2, phiLE, dihedral, id)
myWing.set_sections(mySections)
myWing.set_positionings(myPositionings)
createWingSegments(myWing, strUID, 2)
createComponentSegment(myWing, strUID)
# calc wing position
tauk = cTip / cKink
myLambda = span**2 / Sref
sweep_rad = 35. / 180. * pi
tanPhi25a = calcPhi25a(sweep_rad, taperRatio, tauk, etakf, span, cRoot)
tanPhi25i = calcPhi25i(sweep_rad, taperRatio, tauk, etakf, span, cRoot)
Xef = calcXef(cRoot, myLambda, tanPhi25i, tanPhi25a, etakf, taperRatio,
tauk)
xRoot = calcXRoot(xMAC25, Xef, cRoot)
# set wing x - position
myWing.get_transformation().get_translation().set_x(
doubleBaseType(None, None, None, str(xRoot)))
def createAdvDoubleTrapezoidWing(myWing, id, cTip, cRoot, span, Sref, dfus, phiLE, dihedral, twist, xMAC25, etakf, strUID, yfus, xRoot, etaEng, tcRoot, tcTip):
'''
This method creates a double trapezoid wing geometry in the 'myWing' parameter.
** Introduced a linear twist distribution from *0* at root to *twist* at tip
@author: Jonas Jepsen
@param myWing: wings CPACS object
@param id: the VAMPzero-id of the wing
@param cTip: length of chord at wing tip [m]
@param cRoot: length of chord at wing root [m]
@param span: span of the wing [m]
@param Sref: reference area [m^2]
@param dfus: fuselage diameter [m]
@param phiLE: sweep angle at the leading edge [deg]
@param dihedral: dihedralangle of the wing [deg]
@param twist: twist of the outer wing section [deg]
@param etakf: dimensionless span coordinate [-]
@param strUID: the CPACS-uID of the wing
'''
# sections and positionings will be created, all existing sections and positionings will be deleted
mySections = wingSectionsType()
myPositionings = positioningsType()
# calc Lvl 1 parameters
taperRatio = (cTip / cRoot)
cRoot, cKink, cTip = calcWing(span, Sref, taperRatio, phiLE, etakf, dfus)
# calc length from span, sweep and dihedral
sweep_rad = phiLE / 180. * pi
dihedral_rad = dihedral / 180. * pi
# trying to correct the commented statement that uses dfus. will try to use yfus
# length1 = dfus / 2.
length1 = yfus
length2 = (etakf * span / 2. - length1) / cos(sweep_rad) / cos(dihedral_rad)
length3 = span / 2.*(1 - etakf) / cos(sweep_rad) / cos(dihedral_rad)
# Increase (or reduce the twist by 4deg as that is the overall angle of incidence of the wing)
twist = twist - 4.
twistgrad = twist / (span / 2.)
twist1 = twistgrad * length1
twist2 = twistgrad * etakf * (span / 2.)
twist3 = twist
createWingSection(mySections, tcRoot / 0.09, 0., 0., 0., cRoot, 1., cRoot, 0., 0., 0., 'NACA0009', 1, strUID + '_Sec1', strUID + '_Sec1', strUID + '_Sec1')
createWingSection(mySections, tcRoot / 0.18, 0., 0., 0., cRoot, 1., cRoot, 0., 0., 0., 'NACA653218', 1, strUID + '_Sec2', strUID + '_Sec2', strUID + '_Sec2')
createWingSection(mySections, tcTip / 0.18, 0., 0., 0., cKink, 1., cKink, 0., twist2, 0., 'NACA653218', 1, strUID + '_Sec3', strUID + '_Sec3', strUID + '_Sec3')
createWingSection(mySections, tcTip / 0.18, 0., 0., 0., cTip, 1., cTip, 0., twist3, 0., 'NACA653218', 1, strUID + '_Sec4', strUID + '_Sec4', strUID + '_Sec4')
createPositioning(myPositionings, str(id) + '_Pos1', None, str(id) + '_Sec1', 0., 0., 0., id)
createPositioning(myPositionings, str(id) + '_Pos2', str(id) + '_Sec1', str(id) + '_Sec2', length1, 0., 0., id)
createPositioning(myPositionings, str(id) + '_Pos3', str(id) + '_Sec2', str(id) + '_Sec3', length2, phiLE, dihedral, id)
createPositioning(myPositionings, str(id) + '_Pos4', str(id) + '_Sec3', str(id) + '_Sec4', length3, phiLE, dihedral, id)
myWing.set_sections(mySections)
myWing.set_positionings(myPositionings)
createWingSegments(myWing, strUID, 3)
createComponentSegment(myWing, strUID)
etafus = yfus / (span / 2.)
# Ribs outboard of the Fuselage section are placed at 0.8 m distance
nouterRibs = int(ceil((0.95 - etafus - 0.05) * span / 2. / 0.8))
createRibs(myWing.get_componentSegments().get_componentSegment()[0], strUID, 'advDoubletrapezoid', etaFus=etafus, nRibs=nouterRibs, etaEng=etaEng, span=span / 2.)
createSpars(myWing.get_componentSegments().get_componentSegment()[0], strUID, 'advDoubletrapezoid', length1 / (span / 2.), etakf / cos(dihedral_rad), cTip=cTip, cRoot=cRoot)
createShell(myWing.get_componentSegments().get_componentSegment()[0], strUID, 'advDoubletrapezoid')
createWingFuselageAttachment(myWing.get_componentSegments().get_componentSegment()[0], strUID, 'advDoubletrapezoid')
# Estimate ribNum of outer Rib
iRib = int(span * (0.85 - etaEng) / (2 * 0.8)) - 1
createTanks(myWing.get_componentSegments().get_componentSegment()[0], strUID, 'advDoubletrapezoid', nRib=iRib)
# calc wing position
tauK = cTip / cKink
etar = dfus / span
# XN25F = calcXN25F(cRoot, span, phiLE, etar, etakf, tauK, taperRatio)
# xRoot.py = calcXRoot(xMAC25, XN25F)
# set wing x - position and twist
myWing.get_transformation().get_translation().set_x(doubleBaseType(valueOf_=str(xRoot)))
myWing.get_transformation().get_rotation().set_y(doubleBaseType(valueOf_=str(4.)))