def test_import_thick_TE2(self):
"""
Import and prepare a multi-section wing with a thick trailing edge
along where the middle airfoil has no thick trailing edge.
"""
fn = './test_io/vsp_wing_thick_TE2_v3.5.0.stp'
vsp_import = ImportVSP(fn)
self.assertFalse(vsp_import.has_invalid)
self.assertEqual(vsp_import.num_bodies, 1)
def test_import_thick_TE1(self):
"""
Import and prepare a multi-section wing with a thick trailing edge
along the entire span.
"""
fn = './test_io/vsp_wing_thick_TE1_v3.5.0.stp'
vsp_import = ImportVSP(fn)
self.assertFalse(vsp_import.has_invalid)
self.assertEqual(vsp_import.num_bodies, 1)
from afem.config import Settings from afem.exchange import ImportVSP from afem.graphics import Viewer Settings.log_to_console() fn = '../models/777-200LR.stp' vsp_import = ImportVSP(fn) gui = Viewer() gui.add(*vsp_import.all_bodies) gui.start()
def test_import_777_200LR(self):
fn = './test_io/777-200LR.stp'
vsp_import = ImportVSP(fn)
self.assertFalse(vsp_import.has_invalid)
self.assertEqual(vsp_import.num_bodies, 7)
Settings.log_to_console()
# Inputs
fname = r'..\models\hwb_nosplit.stp'
# Length of flight deck from nose.
fd_length = 10. * 12.
# Cabin length as absolute value (> 1) or percent root chord ( < 1)
cabin_length = 0.7
# Cabin width
cabin_width = 50. * 12.
# Bay width
bay_width = 8. * 12.
# Import model
vsp_import = ImportVSP()
vsp_import.import_step(fname)
wing = vsp_import.get_body('Wing_Body')
other_wing = vsp_import.get_body('Wing_Body.1')
vtail = vsp_import.get_body('Vertical_Tails')
other_vtail = vsp_import.get_body('Vertical_Tails.2')
for body in [wing, other_wing, vtail, other_vtail]:
body.set_transparency(0.5)
body.set_color(0.5, 0.5, 0.5)
# Construction geometry
root_chord = wing.sref.v_iso(0.)
GroupAPI.create_group('wing group')
# Centerbody structure
from afem.config import Settings
from afem.exchange import ImportVSP
from afem.graphics import Viewer
from afem.structure import *
Settings.log_to_console()
# Set units to inch.
Settings.set_units('in')
# Import model
fn = r'../models/simple_wing.stp'
vsp_import = ImportVSP(fn)
wing = vsp_import.get_body('WingGeom')
# Build structure
wingbox = GroupAPI.create_group('wing box')
fspar = SparByParameters('front spar', 0.15, 0., 0.15, 1., wing).part
rspar = SparByParameters('rear spar', 0.70, 0., 0.70, 1., wing).part
RibByPoints('root rib', fspar.p1, rspar.p1, wing)
RibByPoints('tip rib', fspar.p2, rspar.p2, wing)
RibsAlongCurveByDistance('rib',
rspar.cref,
30,
fspar.shape,
rspar.shape,
wing,
d1=30,
d2=-30)
internal_parts = wingbox.get_parts()
skin = SkinByBody('skin', wing).part
from afem.config import Settings
from afem.exchange import ImportVSP
from afem.geometry import *
from afem.graphics import Viewer
from afem.smesh import *
from afem.structure import *
from afem.topology import *
Settings.log_to_console()
# Import model
fname = '../models/uniform_wing.stp'
vsp = ImportVSP(fname)
wing = vsp['Wing']
# Reference curves using wing reference surface generated from modified
# OpenVSP
cref1 = wing.sref.u_iso(0.25)
cref2 = wing.sref.u_iso(0.65)
# Plane at rear spar to cut ribs with. The will enable the 1-D beam to be
# properly fused.
aft_pln = wing.extract_plane(0.65, 0., 0.65, 1.)
# Ribs
xz_pln = PlaneByAxes(axes='xz').plane
ribs = RibsAlongCurveByDistance('Rib',
cref1,
16.,
cref1,
cref2,
Settings.log_to_console()
# Inputs
fname = r'..\..\models\hwb_nosplit.stp'
# Length of flight deck from nose.
fd_length = 10. * 12.
# Cabin length as absolute value (> 1) or percent root chord ( < 1)
cabin_length = 0.7
# Cabin width
cabin_width = 50. * 12.
# Bay width
bay_width = 8. * 12.
# Import model
vsp_import = ImportVSP()
vsp_import.import_step(fname)
wing = vsp_import['Wing_Body']
other_wing = vsp_import['Wing_Body.1']
vtail = vsp_import['Vertical_Tails']
other_vtail = vsp_import['Vertical_Tails.2']
for body in [wing, other_wing, vtail, other_vtail]:
body.set_transparency(0.5)
body.set_color(0.5, 0.5, 0.5)
# Construction geometry
root_chord = wing.sref.v_iso(0.)
GroupAPI.create_group('wing group')
# Centerbody structure
step = StepWrite('AP203', 'in')
step.transfer(the_mesh.shape)
step.write('supersonic.step')
# Export the mesh (nodes and elements) to a bulk data file
the_mesh.export_nastran('supersonic.bdf')
if __name__ == '__main__':
# Set units to inch and log to console
Settings.set_units('in')
Settings.log_to_console()
# Import OpenVSP model
fname = r'..\models\supersonic.stp'
vsp_import = ImportVSP(fname)
# A few notes about importing an OpenVSP STEP model:
# 1) If the model comes from the modified version that includes metadata
# then the OpenVSP components can be identified by type and retrieved
# by name. Otherwise the import methods just tries to make solid
# bodies from the components and gives them a generic name.
# 2) The import process attempts to sew the faces of the OpenVSP
# components together to form solids.
# 3) If a surface is found to be planar, it is replaced with a plane
# before sewing. This helps eliminate some degenerated edges.
# 4) Faces sharing the same domain are unified. If flat wing caps are
# used, this usually results in a single face for the entire cap
# rather than two faces split between the upper and lower surface.
# View the model
step = StepWrite('AP203', 'in')
step.transfer(the_shape)
step.write('supersonic.step')
# Export the mesh (nodes and elements) to a bulk data file
afem.exchange.nastran.export_bdf(the_mesh, 'supersonic.bdf')
if __name__ == '__main__':
# Set units to inch and log to console
Settings.set_units('in')
Settings.log_to_console()
# Import OpenVSP model
fname = r'..\models\supersonic.stp'
vsp_import = ImportVSP(fname)
# A few notes about importing an OpenVSP STEP model:
# 1) If the model comes from the modified version that includes metadata
# then the OpenVSP components can be identified by type and retrieved
# by name. Otherwise the import methods just tries to make solid
# bodies from the components and gives them a generic name.
# 2) The import process attempts to sew the faces of the OpenVSP
# components together to form solids.
# 3) If a surface is found to be planar, it is replaced with a plane
# before sewing. This helps eliminate some degenerated edges.
# 4) Faces sharing the same domain are unified. If flat wing caps are
# used, this usually results in a single face for the entire cap
# rather than two faces split between the upper and lower surface.
# View the model
from afem.config import Settings
from afem.exchange import ImportVSP
from afem.geometry import *
from afem.graphics import Viewer
from afem.smesh import *
from afem.structure import *
from afem.topology import *
Settings.log_to_console()
# Import model
fname = '../models/uniform_wing.stp'
vsp = ImportVSP(fname)
wing = vsp.get_body('Wing')
# Reference curves using wing reference surface generated from modified
# OpenVSP
cref1 = wing.sref.u_iso(0.25)
cref2 = wing.sref.u_iso(0.65)
# Plane at rear spar to cut ribs with. The will enable the 1-D beam to be
# properly fused.
aft_pln = wing.extract_plane(0.65, 0., 0.65, 1.)
# Ribs
xz_pln = PlaneByAxes(axes='xz').plane
ribs = RibsAlongCurveByDistance('Rib',
cref1,
16.,
cref1,
cref2,
