def load_external_libs():
try:
global tixi_h
tixi_h = tixiwrapper.Tixi()
print("TIXI version: ", tixi_h.version)
except Exception as e:
print("Could not load TIXI! Error message is: {}".format(e))
def main():
# Init TiXI
tixi_h = tixiwrapper.Tixi()
tixi_h.open('toolOutput.xml')
# Init TiGL
tigl_h = tiglwrapper.Tigl()
tigl_h.open(tixi_h, 'AircraftModel')
# Extract wing:
mgr = CCPACSConfigurationManager_get_instance()
aircraft_config = mgr.get_configuration(tigl_h._handle.value)
wing = aircraft_config.get_wing("wing")
wing_shape = wing.get_loft().shape()
# Do the slicing:
wing_section = slicing(wing_shape, 0.5)
# Discretize the section:
pnts, face_ids = discretize(wing_section, 1e-5)
# Plot results:
display, start_display, add_menu, add_function_to_menu = init_display()
display.DisplayShape(wing_shape, transparency=0.8, update=True)
display.DisplayShape(wing_section, color='red', update=True)
start_display()
plt.plot(pnts[:, 0], pnts[:, 2], '.')
plt.show()
def initialize(file):
global tixi, tigl
from tixi import tixiwrapper
from tigl import tiglwrapper
tixi = tixiwrapper.Tixi()
tixi.open(file)
tigl = tiglwrapper.Tigl()
tigl.open(tixi, 'AircraftModel')
from . import utils
global_namespace = globals()
for function in __all__:
global_namespace[function] = getattr(utils, function)
return tixi, tigl
def simple_test():
file_name = "tests/TestData/simpletest.cpacs.xml"
old_cpacs_file = tixiwrapper.Tixi()
new_cpacs_file = tixi3wrapper.Tixi3()
new_cpacs_file.open(file_name)
new_cpacs_file.setCacheEnabled(1)
new_cpacs_file.usePrettyPrint(1)
uid_manager.register_all_uids(new_cpacs_file)
uid_manager.fix_invalid_uids(new_cpacs_file)
fix_empty_elements(new_cpacs_file)
old_cpacs_file.openString(new_cpacs_file.exportDocumentAsString())
return TestCase(file_name, old_cpacs_file, new_cpacs_file)
def upgrade_2_to_3(cpacs_handle, args):
filename = args.input_file
if args.fix_errors:
file_has_changed = uid_manager.fix_invalid_uids(cpacs_handle)
file_has_changed = fix_empty_elements(cpacs_handle) or file_has_changed
file_has_changed = fix_guide_curve_profile_element_names(cpacs_handle) or file_has_changed
if file_has_changed:
logging.info("A fixed cpacs2 file will be stored to '%s'" % (filename + ".fixed"))
with open(filename + ".fixed", "w") as text_file:
text_file.write(cpacs_handle.exportDocumentAsString())
# copy cpacs file into tixi 2 to make tigl2 happy
old_cpacs_file = tixiwrapper.Tixi()
old_cpacs_file.openString(cpacs_handle.exportDocumentAsString())
change_cpacs_version(cpacs_handle, "3.0")
convert_cpacs_xml(cpacs_handle)
# perform geometric conversions using tigl
convert_geometry(filename, cpacs_handle, old_cpacs_file)
# -*- coding: utf-8 -*-
"""
Please read the function`s docstring :)
"""
import math
import bisect
import numpy as np
from tixi import tixiwrapper
from tigl import tiglwrapper
tixi = tixiwrapper.Tixi()
tixi.open('./aircraft.xml')
tigl = tiglwrapper.Tigl()
tigl.open(tixi, 'AircraftModel')
def get_airfoil_points(wing_uid, eta, npoints=25, *, method='geometric',
joint=True, normalize=False):
"""
Extracts an airfoil of the wing section defined by a relative coordinate eta.
Parameters
----------
wing_uid : string
uID of the wing ('wing', 'htp', 'vtp').
eta : float
Relative coordinate in spanwise direction, must be in range of [0, 1].
npoints : integer, optional
Number of points along upper/lower airfoil curve. (Default: 25)
method : string, optional
# SIMPLIFIED MASS ESTIMATION MODEL v1
from tixi import tixiwrapper
from tigl import tiglwrapper
# ----------------------------------------------------------------------------------------------------------------------
# CPACS
INFILE = './ToolInput/toolInput.xml'
tixi_h = tixiwrapper.Tixi()
tigl = tiglwrapper.Tigl()
tixi_h.open(INFILE)
tigl.open(tixi_h, '')
# ----------------------------------------------------------------------------------------------------------------------
# FIRST PART
mEngineDry = tixi_h.getDoubleElement('/cpacs/toolspecific/SimplifiedEngineModel/Outputs/EngineDryMass')
mEngine = mEngineDry * 1.24
mEngines = mEngine * 2
if tixi_h.checkElement('/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mPowerUnits') == 0:
tixi_h.createElement('/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM', 'mPowerUnits')
if tixi_h.checkElement('/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mPowerUnits/mEngines') == 0:
tixi_h.createElement('/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mPowerUnits','mEngines')
if tixi_h.checkElement('/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mPowerUnits/mEngines/mEngine[1]') == 0:
tixi_h.createElement('/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mPowerUnits/mEngines','mEngine')
if tixi_h.checkElement('/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mPowerUnits/mEngines/mEngine[1]/massDescription') == 0:
tixi_h.createElement('/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mPowerUnits/mEngines/mEngine[1]','massDescription')
if tixi_h.checkElement('/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mPowerUnits/mEngines/mEngine[1]/massDescription/mass') == 0:
tixi_h.createElement('/cpacs/vehicles/aircraft/model/analyses/massBreakdown/mOEM/mEM/mPowerUnits/mEngines/mEngine[1]/massDescription','mass')