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 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 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 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)))
