def cpacsImport(self,
path='.\\cpacs.xml',
TIXIHandle=None,
TIGLHandle=None):
'''
Overwrites the parameters cpacsImport method!
Will get the value for dfus from CPACS via TIGL functions
'''
if not TIXIHandle:
TIXIHandle = openTIXI(path)
if not TIGLHandle:
TIGLHandle = openTIGL(TIXIHandle,
self.parent.aircraft.modelUID.getValue())
if checkElement(TIXIHandle,
'/cpacs/vehicles/aircraft/model/fuselages/fuselage'):
lastSegment = getFuselageSegmentCount(TIGLHandle)
dmax = 0.
for i in range(lastSegment):
diameter = getFuselageDiameter(TIGLHandle, i + 1, 1.)
if diameter > dmax:
dmax = diameter
self.setValueFix(dmax)
self.importSuccess()
else:
self.importError()
def cpacsImport(self,
path='.\\cpacs.xml',
TIXIHandle=None,
TIGLHandle=None):
'''
Overwrites the parameters cpacsImport method!
Will get the value for lfus from CPACS via TIGL functions
'''
if not TIXIHandle:
TIXIHandle = openTIXI(path)
if not TIGLHandle:
TIGLHandle = openTIGL(TIXIHandle,
self.parent.aircraft.modelUID.getValue())
if checkElement(TIXIHandle,
'/cpacs/vehicles/aircraft/model/fuselages/fuselage'):
# get First Point from the Fuselage
x1, y1, z1 = getFuselagePoint(TIGLHandle, 1, 0., 0.)
lastSegment = getFuselageSegmentCount(TIGLHandle)
x2, y2, z2 = getFuselagePoint(TIGLHandle, lastSegment, 1., 0.)
self.setValueFix(x2 - x1)
self.importSuccess()
else:
self.importError()
def cpacsImport(self, path='.\\cpacs.xml', TIXIHandle=None, TIGLHandle=None):
'''
Overwrites the parameters cpacsImport method!
Will get the value for dfus from CPACS via TIGL functions
'''
if not TIXIHandle:
TIXIHandle = openTIXI(path)
if not TIGLHandle:
TIGLHandle = openTIGL(TIXIHandle, self.parent.aircraft.modelUID.getValue())
if checkElement(TIXIHandle, '/cpacs/vehicles/aircraft/model/fuselages/fuselage'):
lastSegment = getFuselageSegmentCount(TIGLHandle)
dmax = 0.
for i in range(lastSegment):
diameter = getFuselageDiameter(TIGLHandle, i+1,1.)
if diameter > dmax:
dmax = diameter
self.setValueFix(dmax)
self.importSuccess()
else:
self.importError()
def cpacsImport(self, path='.\\cpacs.xml', TIXIHandle=None, TIGLHandle=None):
'''
Imports the quarter chord sweep angle of the htp from TIGL. It takes the htp's first and last section and reads
y and y coordinates and from these calculates the htp sweep.
'''
wingIndex = 2
if not TIXIHandle:
TIXIHandle = openTIXI(path)
if not TIGLHandle:
TIGLHandle = openTIGL(TIXIHandle, self.parent.aircraft.modelUID.getValue())
lastSeg = getWingSegmentCount(TIGLHandle, wingIndex)
if checkElement(TIXIHandle, '/cpacs/vehicles/aircraft/model/wings/wing[2]'):
x1, y1, z1 = getWingUpperPoint(TIGLHandle, wingIndex, 1, 0., 0.25)
x2, y2, z2 = getWingUpperPoint(TIGLHandle, wingIndex, lastSeg, 1., 0.25)
#Length of the hypothenuse so we do not need atan
h = sqrt((x2 - x1) ** 2 + (y2 - y1) ** 2)
self.setValueFix(asin((x2 - x1) / h) / rad)
else:
self.importError()
def cpacsImport(self,
path='.\\cpacs.xml',
TIXIHandle=None,
TIGLHandle=None):
'''
Overwrites the parameters cpacsImport method!
Will get the value for the htp span from CPACS via TIGL functions
'''
if not TIXIHandle:
TIXIHandle = openTIXI(path)
if not TIGLHandle:
TIGLHandle = openTIGL(TIXIHandle,
self.parent.aircraft.modelUID.getValue())
if checkElement(TIXIHandle,
'/cpacs/vehicles/aircraft/model/wings/wing[2]'):
#get First Point from the WingRoot
wingIndex = 2
x1, y1, z1 = getWingUpperPoint(TIGLHandle, wingIndex, 1, 0, 0)
lastSegment = getWingSegmentCount(TIGLHandle, wingIndex)
x2, y2, z2 = getWingUpperPoint(TIGLHandle, wingIndex, lastSegment,
1, 0)
#todo: cpacsImport span: prototype version taking leading Edge Points
self.setValueFix((y2 - y1) * 2.)
self.importSuccess()
else:
self.importError()
def cpacsImport(self, path='.\\cpacs.xml', TIXIHandle=None, TIGLHandle=None):
'''
Overwrites the parameters cpacsImport method!
Will get the value for wingSpan from CPACS via TIGL functions
'''
if not TIXIHandle:
TIXIHandle = openTIXI(path)
if not TIGLHandle:
TIGLHandle = openTIGL(TIXIHandle, self.parent.aircraft.modelUID.getValue())
if checkElement(TIXIHandle, '/cpacs/vehicles/aircraft/model/wings/wing'):
#get First Point from the WingRoot
wingIndex = 1
x1, y1, z1 = getWingUpperPoint(TIGLHandle, wingIndex, 1, 0, 0)
lastSegment = getWingSegmentCount(TIGLHandle, wingIndex)
x2, y2, z2 = getWingUpperPoint(TIGLHandle, wingIndex, lastSegment, 1, 0)
#todo: cpacsImport span: prototype version taking leading Edge Points
self.setValueFix((y2 - y1) * 2.)
self.importSuccess()
else:
self.importError()
def cpacsImport(self,
path='.\\cpacs.xml',
TIXIHandle=None,
TIGLHandle=None):
'''
Retrieves the xRoot coordinate from TIGL. It will go for the main fuselage. The first sections x coordinate is read at eta and zeta
equal 0.
'''
if not TIXIHandle:
TIXIHandle = openTIXI(path)
if not TIGLHandle:
TIGLHandle = openTIGL(TIXIHandle,
self.parent.aircraft.modelUID.getValue())
if checkElement(TIXIHandle,
'/cpacs/vehicles/aircraft/model/fuselages/fuselage'):
self.log.debug('Importing fuselage x position...')
try:
# fuselage index is implicitly set to 1 in TIGL/tigl.py
x1, _, _ = getFuselagePoint(TIGLHandle, 1, 0, 0)
except Exception as e:
self.log.warning(str(e))
self.log.debug('Importing fuselage x position... {}'.format(x1))
self.setValueFix(x1)
self.importSuccess()
else:
self.importError()
def cpacsImport(self, path='.\\cpacs.xml'):
'''
Looks for parameter.CPACSPath in CPACSFilse defined by Path
Transfers Value is possible
Input Values will be set to 'fix'
'''
self.log.info('')
self.log.info(
"##############################################################################"
)
self.log.info("VAMPzero CPACS Import from %s" % path)
self.log.info("trying to import and fix parameters")
self.log.info(
"##############################################################################"
)
TIXIHandle = openTIXI(path)
modelUID = getText(TIXIHandle,
'/cpacs/toolspecific/vampZero/aircraftModelUID')
if modelUID is None:
self.log.info(
"VAMPzero IMPORT: No modelUID specified in the toolspecific Block"
)
try:
modelUID = self.modelUID.getValue()
self.log.info("VAMPzero IMPORT: loaded modelUID from VAMPzero")
except AttributeError:
modelUID = None
self.log.info(
"VAMPzero IMPORT: could not load modelUID from VAMPzero")
if modelUID is not None:
TIGLHandle = openTIGL(TIXIHandle, modelUID)
if TIGLHandle is not None:
self.log.debug(
"VAMPzero IMPORT: Opened TIXI and TIGL in Component")
else:
TIGLHandle = None
self.log.debug(
"VAMPzero IMPORT: Opened only TIXI in Component as no modelUID was specified"
)
self.importer(path, TIXIHandle, TIGLHandle)
self.log.info("VAMPzero IMPORT: done.")
closeXML(TIXIHandle)
def cpacsImport(self, path='.\\cpacs.xml', TIXIHandle=None, TIGLHandle=None):
'''
Overwrites the parameters cpacsImport method!
Will get the value for wingSpan from CPACS via TIGL functions
'''
def calcRootLength(tiglHandle, wingIndex):
'''
Calculates the length of the root section chord
'''
x1, y1, z1 = getWingUpperPoint(tiglHandle, wingIndex, 1, 0, 0)
x2, y2, z2 = getWingUpperPoint(tiglHandle, wingIndex, 1, 0, 1)
return pointDistance(x1, y1, z1, x2, y2, z2)
def calcTipLength(tiglHandle, wingIndex):
'''
Calculates the length of the tip section chord
'''
lastSegment = getWingSegmentCount(tiglHandle, wingIndex)
x1, y1, z1 = getWingUpperPoint(tiglHandle, wingIndex, lastSegment, 1, 0)
x2, y2, z2 = getWingUpperPoint(tiglHandle, wingIndex, lastSegment, 1, 1)
return pointDistance(x1, y1, z1, x2, y2, z2)
#===============================================================================
# main cpacsImport
#===============================================================================s
wingIndex = 1
if not TIXIHandle:
TIXIHandle = openTIXI(path)
if not TIGLHandle:
TIGLHandle = openTIGL(TIXIHandle, self.parent.aircraft.modelUID.getValue())
if checkElement(TIXIHandle, '/cpacs/vehicles/aircraft/model/wings/wing'):
rootC = calcRootLength(TIGLHandle, wingIndex)
tipC = calcTipLength(TIGLHandle, wingIndex)
self.setValueFix(tipC / rootC)
self.importSuccess()
else:
self.importError()
def cpacsImport(self, path=".\\cpacs.xml", TIXIHandle=None, TIGLHandle=None):
"""
Overwrites the parameters cpacsImport method!
Will get the value for taperRatio from CPACS via TIGL functions
"""
def calcRootLength(tiglHandle, wingIndex):
"""
Calculates the length of the root section chord
"""
x1, y1, z1 = getWingUpperPoint(tiglHandle, wingIndex, 1, 0, 0)
x2, y2, z2 = getWingUpperPoint(tiglHandle, wingIndex, 1, 0, 1)
return pointDistance(x1, y1, z1, x2, y2, z2)
def calcTipLength(tiglHandle, wingIndex):
"""
Calculates the length of the tip section chord
"""
lastSegment = getWingSegmentCount(tiglHandle, wingIndex)
x1, y1, z1 = getWingUpperPoint(tiglHandle, wingIndex, lastSegment, 1, 0)
x2, y2, z2 = getWingUpperPoint(tiglHandle, wingIndex, lastSegment, 1, 1)
return pointDistance(x1, y1, z1, x2, y2, z2)
# =======================================================================
#
# =======================================================================
# @todo: cpacsImport taperRatio: Think about an import logic for the different wings
wingIndex = 3
if not TIXIHandle:
TIXIHandle = openTIXI(path)
if not TIGLHandle:
TIGLHandle = openTIGL(TIXIHandle, self.parent.aircraft.modelUID.getValue())
if checkElement(TIXIHandle, "/cpacs/vehicles/aircraft/model/wings/wing[3]"):
rootC = calcRootLength(TIGLHandle, wingIndex)
tipC = calcTipLength(TIGLHandle, wingIndex)
self.setValueFix(tipC / rootC)
self.importSuccess()
else:
self.importError()
def cpacsImport(self, path='.\\cpacs.xml', TIXIHandle=None, TIGLHandle=None):
'''
Overwrites the parameters cpacsImport method!
'''
#@todo: cpacsImport taperRatio: Think about an import logic for the different wings
wingIndex = 2
if not TIXIHandle:
TIXIHandle = openTIXI(path)
if not TIGLHandle:
TIGLHandle = openTIGL(TIXIHandle, self.parent.aircraft.modelUID.getValue())
if checkElement(TIXIHandle, '/cpacs/vehicles/aircraft/model/wings/wing[2]'):
x1, y1, z1 = getWingUpperPoint(TIGLHandle, wingIndex, 1, 0, 0)
self.setValueFix(z1)
self.importSuccess()
else:
self.importError()
def cpacsImport(self, path='.\\cpacs.xml', TIXIHandle=None, TIGLHandle=None):
'''
Overwrites the parameters cpacsImport method!
'''
#@todo: cpacsImport taperRatio: Think about an import logic for the different wings
wingIndex = 2
if not TIXIHandle:
TIXIHandle = openTIXI(path)
if not TIGLHandle:
TIGLHandle = openTIGL(TIXIHandle, self.parent.aircraft.modelUID.getValue())
if checkElement(TIXIHandle, '/cpacs/vehicles/aircraft/model/wings/wing[2]'):
x1, y1, z1 = getWingUpperPoint(TIGLHandle, wingIndex, 1, 0, 0)
self.setValueFix(x1)
self.importSuccess()
else:
self.importError()
def cpacsImport(self, path='.\\cpacs.xml', TIXIHandle=None, TIGLHandle=None):
'''
Overwrites the parameters cpacsImport method!
Will get the value for refArea for HTP from CPACS via TIGL functions
'''
if not TIXIHandle:
TIXIHandle = openTIXI(path)
if not TIGLHandle:
TIGLHandle = openTIGL(TIXIHandle, self.parent.aircraft.modelUID.getValue())
#@todo: cpacsImport refArea: it is assumed that the htp is number 2 wing
if checkElement(TIXIHandle, '/cpacs/vehicles/aircraft/model/wings/wing[2]'):
area = getWingSurfaceArea(TIGLHandle, 2)
self.setValueFix(area)
self.importSuccess()
else:
self.importError()
def cpacsImport(self, path='.\\cpacs.xml', TIXIHandle=None, TIGLHandle=None):
'''
Retrieves the xRoot coordinate from TIGL. It will go for the main wing. The first sections x coordinate is read at eta and chord
equal 0.
'''
wingIndex = 1
if not TIXIHandle:
TIXIHandle = openTIXI(path)
if not TIGLHandle:
TIGLHandle = openTIGL(TIXIHandle, self.parent.aircraft.modelUID.getValue())
if checkElement(TIXIHandle, '/cpacs/vehicles/aircraft/model/wings/wing'):
x1, y1, z1 = getWingUpperPoint(TIGLHandle, wingIndex, 1, 0, 0)
self.setValueFix(x1)
self.importSuccess()
else:
self.importError()
def cpacsImport(self, path='.\\cpacs.xml', TIXIHandle=None, TIGLHandle=None):
'''
Retrieves the xRoot.py coordinate from TIGL. It will go for the vtp. The first sections x coordinate is read at eta and chord
equal 0.
'''
wingIndex = 3
if not TIXIHandle:
TIXIHandle = openTIXI(path)
if not TIGLHandle:
TIGLHandle = openTIGL(TIXIHandle, self.parent.aircraft.modelUID.getValue())
if checkElement(TIXIHandle, '/cpacs/vehicles/aircraft/model/wings/wing[3]'):
x1, y1, z1 = getWingUpperPoint(TIGLHandle, wingIndex, 1, 0, 0)
self.setValueFix(x1)
self.importSuccess()
else:
self.importError()
def cpacsImport(self, path='.\\cpacs.xml', TIXIHandle=None, TIGLHandle=None):
'''
Retrieves the xRoot coordinate from TIGL. It will go for the main fuselage. The first sections x coordinate is read at eta and zeta
equal 0.
'''
if not TIXIHandle:
TIXIHandle = openTIXI(path)
if not TIGLHandle:
TIGLHandle = openTIGL(TIXIHandle, self.parent.aircraft.modelUID.getValue())
if checkElement(TIXIHandle, '/cpacs/vehicles/aircraft/model/fuselages/fuselage'):
self.log.debug('Importing fuselage x position...')
try:
# fuselage index is implicitly set to 1 in TIGL/tigl.py
x1, _, _ = getFuselagePoint(TIGLHandle, 1, 0, 0)
except Exception as e:
self.log.warning(str(e))
self.log.debug('Importing fuselage x position... {}'.format(x1))
self.setValueFix(x1)
self.importSuccess()
else:
self.importError()
def cpacsImport(self, path='.\\cpacs.xml', TIXIHandle=None, TIGLHandle=None):
'''
Overwrites the parameters cpacsImport method!
Will get the value for lfus from CPACS via TIGL functions
'''
if not TIXIHandle:
TIXIHandle = openTIXI(path)
if not TIGLHandle:
TIGLHandle = openTIGL(TIXIHandle, self.parent.aircraft.modelUID.getValue())
if checkElement(TIXIHandle, '/cpacs/vehicles/aircraft/model/fuselages/fuselage'):
# get First Point from the Fuselage
x1, y1, z1 = getFuselagePoint(TIGLHandle, 1, 0., 0.)
lastSegment = getFuselageSegmentCount(TIGLHandle)
x2, y2, z2 = getFuselagePoint(TIGLHandle, lastSegment, 1., 0.)
self.setValueFix(x2 - x1)
self.importSuccess()
else:
self.importError()
def cpacsImport(self, path='.\\cpacs.xml'):
'''
Looks for parameter.CPACSPath in CPACSFilse defined by Path
Transfers Value is possible
Input Values will be set to 'fix'
'''
self.log.info('')
self.log.info("##############################################################################")
self.log.info("VAMPzero CPACS Import from %s" % path)
self.log.info("trying to import and fix parameters")
self.log.info("##############################################################################")
TIXIHandle = openTIXI(path)
modelUID = getText(TIXIHandle, '/cpacs/toolspecific/vampZero/aircraftModelUID')
if modelUID is None:
self.log.info("VAMPzero IMPORT: No modelUID specified in the toolspecific Block")
try:
modelUID = self.modelUID.getValue()
self.log.info("VAMPzero IMPORT: loaded modelUID from VAMPzero")
except AttributeError:
modelUID = None
self.log.info("VAMPzero IMPORT: could not load modelUID from VAMPzero")
if modelUID is not None:
TIGLHandle = openTIGL(TIXIHandle, modelUID)
if TIGLHandle is not None:
self.log.debug("VAMPzero IMPORT: Opened TIXI and TIGL in Component")
else:
TIGLHandle = None
self.log.debug("VAMPzero IMPORT: Opened only TIXI in Component as no modelUID was specified")
self.importer(path, TIXIHandle, TIGLHandle)
self.log.info("VAMPzero IMPORT: done.")
closeXML(TIXIHandle)
