def execute(self):
"""
generate cross sections at every spanwise node of the st3d vartree
"""
# clear list of outputs!
self.cs2d = []
ni = self.st3d.x.shape[0]
for i in range(ni):
x = self.st3d.x[i]
# print 'adding section at r/R = %2.2f' % x
st2d = CrossSectionStructureVT()
st2d.s = x * self.blade_length
st2d.DPs = []
try:
airfoil = self.surface.interpolate_profile(
x)[:, [0, 1]] * self.blade_length
st2d.airfoil.initialize(airfoil)
except:
pass
for ir, rname in enumerate(self.st3d.regions):
reg = getattr(self.st3d, rname)
if reg.thickness[i] == 0.:
print 'zero thickness region!', rname
# continue
DP0 = getattr(self.st3d, 'DP%02d' % ir)
DP1 = getattr(self.st3d, 'DP%02d' % (ir + 1))
r = st2d.add_region(rname.upper())
st2d.DPs.append(DP0[i])
r.s0 = DP0[i]
r.s1 = DP1[i]
for lname in reg.layers:
lay = getattr(reg, lname)
if lay.thickness[i] > 1.e-5:
l = r.add_layer(lname)
# try:
lnamebase = lname.translate(None, digits)
st2d.add_material(lnamebase,
self.get_material(lname).copy())
# except:
# raise RuntimeError('Material %s not in materials list' % lname)
l.materialname = lnamebase
l.thickness = max(0., lay.thickness[i])
try:
l.angle = lay.angle[i]
except:
l.angle = 0.
st2d.DPs.append(DP1[i])
for ir, rname in enumerate(self.st3d.webs):
reg = getattr(self.st3d, rname)
if reg.thickness[i] == 0.:
continue
r = st2d.add_web(rname.upper())
try:
DP0 = getattr(self.st3d, 'DP%02d' % self.st3d.iwebs[ir][0])
except:
DP0 = getattr(
self.st3d, 'DP%02d' %
(len(self.st3d.regions) + self.st3d.iwebs[ir][0] + 1))
try:
DP1 = getattr(self.st3d, 'DP%02d' % self.st3d.iwebs[ir][1])
except:
DP1 = getattr(
self.st3d, 'DP%02d' %
(len(self.st3d.regions) + self.st3d.iwebs[ir][1] + 1))
r.s0 = DP0[i]
r.s1 = DP1[i]
for lname in reg.layers:
lay = getattr(reg, lname)
if lay.thickness[i] > 1.e-5:
l = r.add_layer(lname)
try:
lnamebase = lname.translate(None, digits)
st2d.add_material(lnamebase,
self.get_material(lname).copy())
except:
raise RuntimeError(
'Material %s not in materials list' % lname)
l.materialname = lnamebase
l.thickness = max(0., lay.thickness[i])
try:
l.angle = lay.angle[i]
except:
l.angle = 0.
self.cs2d.append(st2d)
def make_cs2d():
cs2d = CrossSectionStructureVT()
cs2d.airfoil.initialize(np.loadtxt('ffaw3301.dat'))
# DEFINE MATERIALS
uniax = MaterialProps()
uniax.E1 = 40e9
uniax.E2 = 10e9
uniax.E3 = 10e9
uniax.nu12 = 0.28
uniax.nu13 = 0.28
uniax.nu23 = 0.4
uniax.G12 = 4e9
uniax.G13 = 4e9
uniax.G23 = 3.571e9
uniax.rho = 1900
uniax.materialname = 'uniax'
biax = MaterialProps()
biax.E1 = 12e9
biax.E2 = 12e9
biax.E3 = 10e9
biax.nu12 = 0.5
biax.nu13 = 0.28
biax.nu23 = 0.28
biax.G12 = 10e9
biax.G13 = 3.8e9
biax.G23 = 3.8e9
biax.rho = 1890
biax.materialname = 'biax'
triax = MaterialProps()
triax.E1 = 20e9
triax.E2 = 10e9
triax.E3 = 10e9
triax.nu12 = 0.5
triax.nu13 = 0.28
triax.nu23 = 0.28
triax.G12 = 7.5e9
triax.G13 = 4e9
triax.G23 = 4e9
triax.rho = 1860
triax.materialname = 'triax'
core = MaterialProps()
core.E1 = 50e6
core.E2 = 50e6
core.E3 = 50e6
core.nu12 = 0.4
core.nu13 = 0.4
core.nu23 = 0.4
core.G12 = 17.857e6
core.G13 = 17.857e6
core.G23 = 17.857e6
core.rho = 80
core.materialname = 'core'
# add materials to airfoil
cs2d.add_material('uniax', uniax)
cs2d.add_material('biax', biax)
cs2d.add_material('triax', triax)
cs2d.add_material('core', core)
# --------
# Region 1: TE
# --------
r = cs2d.add_region('REGION01')
r.s0 = -1.00
r.s1 = -0.90
l = r.add_layer('l1')
l.thickness = .006
l.angle = 0
l.materialname = 'TRIAX'
l.plyname = 'Ply01'
# --------
# Region 2: TE sandwich
# --------
r = cs2d.add_region('REGION02')
r.s0 = -0.90
r.s1 = -0.50
l = r.add_layer('l1')
l.thickness = .002
l.angle = 0
l.materialname = 'TRIAX'
l.plyname = 'Ply02'
l = r.add_layer('l2')
l.thickness = .015
l.angle = 0
l.materialname = 'CORE'
l.plyname = 'Ply03'
l = r.add_layer('l3')
l.thickness = .002
l.angle = 0
l.materialname = 'TRIAX'
l.plyname = 'Ply04'
# --------
# Region 3: spar cap
# --------
r = cs2d.add_region('REGION03')
r.s0 = -0.50
r.s1 = -0.20
l = r.add_layer('l1')
l.thickness = .004
l.angle = 0
l.materialname = 'UNIAX'
l.plyname = 'Ply02'
# --------
# Region 4: LE edge sandwich
# --------
r = cs2d.add_region('REGION04')
r.s0 = -0.20
r.s1 = 0.20
l = r.add_layer('l1')
l.thickness = .002
l.angle = 0
l.materialname = 'TRIAX'
l.plyname = 'Ply06'
l = r.add_layer('l2')
l.thickness = .010
l.angle = 0
l.materialname = 'CORE'
l.plyname = 'Ply07'
l = r.add_layer('l3')
l.thickness = .002
l.angle = 0
l.materialname = 'TRIAX'
l.plyname = 'Ply08'
# -----------
# Regions 5-8
# -----------
r = cs2d.add_region('REGION05')
cs2d.REGION05 = cs2d.REGION03.copy()
cs2d.REGION05.s0 = 0.20
cs2d.REGION05.s1 = 0.50
r = cs2d.add_region('REGION06')
cs2d.REGION06 = cs2d.REGION02.copy()
cs2d.REGION06.s0 = 0.5
cs2d.REGION06.s1 = 0.9
r = cs2d.add_region('REGION07')
cs2d.REGION07 = cs2d.REGION01.copy()
cs2d.REGION07.s0 = 0.9
cs2d.REGION07.s1 = 1.0
# --------
# Webs
# --------
r = cs2d.add_web('WEB00')
r.s0 = 1.
r.s1 = -1.
l = r.add_layer('l1')
l.thickness = .002
l.angle = 0
l.materialname = 'BIAX'
l.plyname = 'Ply09'
r = cs2d.add_web('WEB01')
r.s0 = -.5
r.s1 = 0.5
l = r.add_layer('l1')
l.thickness = .002
l.angle = 0
l.materialname = 'BIAX'
l.plyname = 'Ply09'
l = r.add_layer('l2')
l.thickness = .010
l.angle = 0
l.materialname = 'CORE'
l.plyname = 'Ply10'
l = r.add_layer('l3')
l.thickness = .002
l.angle = 0
l.materialname = 'BIAX'
l.plyname = 'Ply11'
r = cs2d.add_web('WEB02')
cs2d.WEB02 = cs2d.WEB01.copy()
cs2d.WEB02.s0 = -0.2
cs2d.WEB02.s1 = 0.2
# =============================================================================
### REMESH AIRFOIL, CREATE BECAS INPUT FILES
# =============================================================================
# Number of mesh points along the airfoil. Should be higher as the number of
# points in the airfoil input file
b = CS2DtoBECAS()
b.cs2d = cs2d
b.total_points = 150
# dominant regions: spar caps
b.dominant_elsets = ['REGION03', 'REGION05']
b.path_shellexpander = '/Users/frza/svn/BECAS/shellexpander/src'
b.run()
return b
def execute(self):
"""
generate cross sections at every spanwise node of the st3d vartree
"""
# clear list of outputs!
self.cs2d = []
ni = self.st3d.x.shape[0]
for i in range(ni):
x = self.st3d.x[i]
# print 'adding section at r/R = %2.2f' % x
st2d = CrossSectionStructureVT()
st2d.s = x * self.blade_length
st2d.DPs = []
try:
airfoil = self.surface.interpolate_profile(x)[:, [0, 1]] * self.blade_length
st2d.airfoil.initialize(airfoil)
except:
pass
for ir, rname in enumerate(self.st3d.regions):
reg = getattr(self.st3d, rname)
if reg.thickness[i] == 0.:
print 'zero thickness region!', rname
# continue
DP0 = getattr(self.st3d, 'DP%02d' % ir)
DP1 = getattr(self.st3d, 'DP%02d' % (ir + 1))
r = st2d.add_region(rname.upper())
st2d.DPs.append(DP0[i])
r.s0 = DP0[i]
r.s1 = DP1[i]
for lname in reg.layers:
lay = getattr(reg, lname)
if lay.thickness[i] > 1.e-5:
l = r.add_layer(lname)
# try:
lnamebase = lname.translate(None, digits)
st2d.add_material(lnamebase, self.get_material(lname).copy())
# except:
# raise RuntimeError('Material %s not in materials list' % lname)
l.materialname = lnamebase
l.thickness = max(0., lay.thickness[i])
try:
l.angle = lay.angle[i]
except:
l.angle = 0.
st2d.DPs.append(DP1[i])
for ir, rname in enumerate(self.st3d.webs):
reg = getattr(self.st3d, rname)
if reg.thickness[i] == 0.:
continue
r = st2d.add_web(rname.upper())
try:
DP0 = getattr(self.st3d, 'DP%02d' % self.st3d.iwebs[ir][0])
except:
DP0 = getattr(self.st3d, 'DP%02d' % (len(self.st3d.regions) + self.st3d.iwebs[ir][0] + 1))
try:
DP1 = getattr(self.st3d, 'DP%02d' % self.st3d.iwebs[ir][1])
except:
DP1 = getattr(self.st3d, 'DP%02d' % (len(self.st3d.regions) + self.st3d.iwebs[ir][1] + 1))
r.s0 = DP0[i]
r.s1 = DP1[i]
for lname in reg.layers:
lay = getattr(reg, lname)
if lay.thickness[i] > 1.e-5:
l = r.add_layer(lname)
try:
lnamebase = lname.translate(None, digits)
st2d.add_material(lnamebase, self.get_material(lname).copy())
except:
raise RuntimeError('Material %s not in materials list' % lname)
l.materialname = lnamebase
l.thickness = max(0., lay.thickness[i])
try:
l.angle = lay.angle[i]
except:
l.angle = 0.
self.cs2d.append(st2d)
def make_cs2d():
cs2d = CrossSectionStructureVT()
cs2d.airfoil.initialize(np.loadtxt('ffaw3301.dat'))
# DEFINE MATERIALS
uniax = MaterialProps()
uniax.E1 = 40e9
uniax.E2 = 10e9
uniax.E3 = 10e9
uniax.nu12 = 0.28
uniax.nu13 = 0.28
uniax.nu23 = 0.4
uniax.G12 = 4e9
uniax.G13 = 4e9
uniax.G23 = 3.571e9
uniax.rho = 1900
uniax.materialname = 'uniax'
biax = MaterialProps()
biax.E1 = 12e9
biax.E2 = 12e9
biax.E3 = 10e9
biax.nu12 = 0.5
biax.nu13 = 0.28
biax.nu23 = 0.28
biax.G12 = 10e9
biax.G13 = 3.8e9
biax.G23 = 3.8e9
biax.rho = 1890
biax.materialname = 'biax'
triax = MaterialProps()
triax.E1 = 20e9
triax.E2 = 10e9
triax.E3 = 10e9
triax.nu12 = 0.5
triax.nu13 = 0.28
triax.nu23 = 0.28
triax.G12 = 7.5e9
triax.G13 = 4e9
triax.G23 = 4e9
triax.rho = 1860
triax.materialname = 'triax'
core = MaterialProps()
core.E1 = 50e6
core.E2 = 50e6
core.E3 = 50e6
core.nu12 = 0.4
core.nu13 = 0.4
core.nu23 = 0.4
core.G12 = 17.857e6
core.G13 = 17.857e6
core.G23 = 17.857e6
core.rho = 80
core.materialname = 'core'
# add materials to airfoil
cs2d.add_material('uniax', uniax)
cs2d.add_material('biax', biax)
cs2d.add_material('triax', triax)
cs2d.add_material('core', core)
# --------
# Region 1: TE
# --------
r = cs2d.add_region('REGION01')
r.s0 = -1.00
r.s1 = -0.90
l = r.add_layer('l1')
l.thickness = .006
l.angle = 0
l.materialname = 'TRIAX'
l.plyname = 'Ply01'
# --------
# Region 2: TE sandwich
# --------
r = cs2d.add_region('REGION02')
r.s0 = -0.90
r.s1 = -0.50
l = r.add_layer('l1')
l.thickness = .002
l.angle = 0
l.materialname = 'TRIAX'
l.plyname = 'Ply02'
l = r.add_layer('l2')
l.thickness = .015
l.angle = 0
l.materialname = 'CORE'
l.plyname = 'Ply03'
l = r.add_layer('l3')
l.thickness = .002
l.angle = 0
l.materialname = 'TRIAX'
l.plyname = 'Ply04'
# --------
# Region 3: spar cap
# --------
r = cs2d.add_region('REGION03')
r.s0 = -0.50
r.s1 = -0.20
l = r.add_layer('l1')
l.thickness = .004
l.angle = 0
l.materialname = 'UNIAX'
l.plyname = 'Ply02'
# --------
# Region 4: LE edge sandwich
# --------
r = cs2d.add_region('REGION04')
r.s0 = -0.20
r.s1 = 0.20
l = r.add_layer('l1')
l.thickness = .002
l.angle = 0
l.materialname = 'TRIAX'
l.plyname = 'Ply06'
l = r.add_layer('l2')
l.thickness = .010
l.angle = 0
l.materialname = 'CORE'
l.plyname = 'Ply07'
l = r.add_layer('l3')
l.thickness = .002
l.angle = 0
l.materialname = 'TRIAX'
l.plyname = 'Ply08'
# -----------
# Regions 5-8
# -----------
r = cs2d.add_region('REGION05')
cs2d.REGION05 = cs2d.REGION03.copy()
cs2d.REGION05.s0 = 0.20
cs2d.REGION05.s1 = 0.50
r = cs2d.add_region('REGION06')
cs2d.REGION06 = cs2d.REGION02.copy()
cs2d.REGION06.s0 = 0.5
cs2d.REGION06.s1 = 0.9
r = cs2d.add_region('REGION07')
cs2d.REGION07 = cs2d.REGION01.copy()
cs2d.REGION07.s0 = 0.9
cs2d.REGION07.s1 = 1.0
# --------
# Webs
# --------
r = cs2d.add_web('WEB00')
r.s0 = 1.
r.s1 = -1.
l = r.add_layer('l1')
l.thickness = .002
l.angle = 0
l.materialname = 'BIAX'
l.plyname = 'Ply09'
r = cs2d.add_web('WEB01')
r.s0 = -.5
r.s1 = 0.5
l = r.add_layer('l1')
l.thickness = .002
l.angle = 0
l.materialname = 'BIAX'
l.plyname = 'Ply09'
l = r.add_layer('l2')
l.thickness = .010
l.angle = 0
l.materialname = 'CORE'
l.plyname = 'Ply10'
l = r.add_layer('l3')
l.thickness = .002
l.angle = 0
l.materialname = 'BIAX'
l.plyname = 'Ply11'
r = cs2d.add_web('WEB02')
cs2d.WEB02 = cs2d.WEB01.copy()
cs2d.WEB02.s0 = -0.2
cs2d.WEB02.s1 = 0.2
# =============================================================================
### REMESH AIRFOIL, CREATE BECAS INPUT FILES
# =============================================================================
# Number of mesh points along the airfoil. Should be higher as the number of
# points in the airfoil input file
b = CS2DtoBECAS()
b.cs2d = cs2d
b.total_points = 150
# dominant regions: spar caps
b.dominant_elsets = ['REGION03', 'REGION05']
b.path_shellexpander = '/Users/frza/svn/BECAS/shellexpander/src'
b.run()
return b
