def setUp(self):
self.mat = TransverseIsotropicPlyMaterial(name='exmat2',
E11=130000.,
E22=4650.,
G12=4650.,
nu12=0.35,
nu23=0.45,
a11t=0.15e-6,
a22t=28.7e-6,
t=0.13,
F11t=1200.,
F11c=1000.,
F22t=50.,
F22c=120.,
F12s=75.)
self.angles = [
45, -45, 0, 90, 0, 90, 45, -45, 0, 90, 90, 0, -45, 45, 90, 0, 90,
0, -45, 45
]
plydef = [(a, self.mat) for a in self.angles]
self.lam = clt.Laminate(plydef)
self.lamd = clt.Laminate(plydef)
for layer in self.lamd.layers:
layer.set_matrix_failure(True)
self.load = np.array([308.3, -22.2, 449.2, 0, 0, 0])
self.sol = self.lam.get_linear_response(self.load)
self.sold = self.lamd.get_linear_response(self.load)
# put into it's own class!
layup = clt.stacking_to_layup2(self.angles)
self.ulam = clt.UnorderedLaminate(layup, self.mat)
self.ulamd = clt.UnorderedLaminate(layup, self.mat)
#self.ulamd = plainstrength.make_degraded_laminate(self.ulam)
for layer in self.ulamd.layers:
layer.set_matrix_failure(True)
def setUp(self):
self.mat = TransverseIsotropicPlyMaterial(name='exmat2',
E11=130000.,
E22=4650.,
G12=4650.,
nu12=0.35,
nu23=0.45,
a11t=0.15e-6,
a22t=28.7e-6,
t=0.13,
F11t=1200.,
F11c=1000.,
F22t=50.,
F22c=120.,
F12s=75.)
self.angles = [
45, -45, 0, 90, 0, 90, 45, -45, 0, 90, 90, 0, -45, 45, 90, 0, 90,
0, -45, 45
]
plydef = [(a, self.mat) for a in self.angles]
self.lam = clt.Laminate(plydef)
self.lamd = clt.Laminate(plydef)
for layer in self.lamd.layers:
layer.set_matrix_failure(True)
self.load = np.array([308.3, -22.2, 449.2, 0, 0, 0])
self.sol = self.lam.get_linear_response(self.load)
self.sold = self.lamd.get_linear_response(self.load)
def test_ex(self):
# test Ex for [0_3/90 laminate], T300/5208
# Tsai Eq. 4.15
lam = clt.Laminate([(0., self.cfrp_t300), (0., self.cfrp_t300),
(0., self.cfrp_t300), (90., self.cfrp_t300)])
ref = 138880.
val = lam.Ex()
self.assertAlmostEqual(val, ref)
def test_nu(self):
# test Ex for [0_3/90 laminate], T300/5208
# Tsai Eq. 4.15
lam = clt.Laminate([(0., self.cfrp_t300), (0., self.cfrp_t300),
(0., self.cfrp_t300), (90., self.cfrp_t300)])
ref = 0.054
val = lam.nuxy()
self.assertAlmostEqual(val, ref)
def test_layer_A3(self):
# compare matrix norm of matrix A of one-ply laminate
# Tsai Table 4.1
# E-glass, 90°
lam_kfrp_45 = clt.Laminate([(45., self.kfrp)])
expect = np.array([[2.97e3, 2.40e3, 2.22e3], [2.40e3, 2.97e3, 2.22e3],
[2.22e3, 2.22e3, 2.45e3]])
result = lam_kfrp_45.A()
assert_allclose(result, expect, 1e-2)
def test_layer_A1(self):
# compare matrix norm of matrix A of one-ply laminate
# Tsai Table 4.1
# B(4), 0°
lam_bfrp_0 = clt.Laminate([(0., self.bfrp)])
expect = np.array([[25.62e3, 0.53e3, 0], [0.53e3, 2.32e3, 0.],
[0., 0., 0.7e3]])
result = lam_bfrp_0.A()
assert_allclose(result, expect, 1e-2)
def test_layer_A2(self):
# compare matrix norm of matrix A of one-ply laminate
# Tsai Table 4.1
# E-glass, 90°
lam_gfrp_90 = clt.Laminate([(90., self.gfrp)])
expect = np.array([[1.05e3, 0.27e3, 0.], [0.27e3, 4.90e3, 0.],
[0., 0., 0.52e3]])
result = lam_gfrp_90.A()
assert_allclose(result, expect, atol=10)
def setUp(self):
# aerospatiale example, C6
angles = (45, -45, 0, 90, 0, 90, 45, -45, 0, 90, 90, 0, -45, 45, 90, 0,
90, 0, -45, 45)
plydef = [(a, self.mat) for a in angles]
self.lam = clt.Laminate(plydef)
self.load = np.array([308.3, -22.2, 449.2, 0, 0, 0])
self.sol = self.lam.get_linear_response(self.load)
self.temp = 0.
def test_d(self):
# (2/2/2/2)
# exampe mts006, D5
pd2 = [0, 45, -45, 90, 90, -45, 45, 0]
pd2 = [(angle, self.mat1) for angle in pd2]
lam = clt.Laminate(pd2)
# Qbar, 0 deg
expect = 10.0 * np.array([[858, 123, 55], [123, 194, 55],
[55, 55, 151]])
assert_allclose(lam.D(), expect, atol=6)
def setUp(self):
mat10 = Material(E11=38000., E22=9000., G12=3600., nu12=0.32, t=1.)
mat15 = Material(E11=38000., E22=9000., G12=3600., nu12=0.32, t=1.5)
self.lam = clt.Laminate([(15, mat15), (-30, mat10), (-15, mat15),
(30, mat10)])
# mload = np.array([2000, 1000, 500, 0, 0, 0]) # used in text
mload = np.array([1000, 500, 250, 0, 0, 0]) # used in calculations
self.sol = self.lam.get_linear_response(mload)
def test_clt_a0_temp(self):
# result sould be alpha_t
plydef = [(0., self.m11)]
lam = clt.Laminate(plydef)
mload = np.zeros(6)
temps = 1.
sol = lam.get_linear_response(mload, temps)
# s: array(6). s[0] = a11t, s[1] = a22t, rest 0
expect = np.array([self.m1.a11t, self.m1.a22t, 0., 0., 0., 0.])
assert_array_almost_equal(sol.eps_kappa(), expect)
def test_clt_a0_nx(self):
# result sould be alpha_t
#m11 = self.m11
plydef = [(0., self.m11)]
lam = clt.Laminate(plydef)
mload = np.array([1, 0, 0, 0, 0, 0])
#temps = 0.
sol = lam.get_linear_response(mload) #, mload)lam.solve(mload, temps)
expect = np.array(
[1. / self.m11.E11, -self.m11.nu12 / self.m11.E11, 0., 0., 0., 0.])
assert_allclose(sol.eps_kappa(), expect, rtol=1e-6)
def test_kappa(self):
# (2/2/2/2)
# exampe mts006, D5
pd2 = [0, 45, -45, 90, 90, -45, 45, 0]
pd2 = [(angle, self.mat1) for angle in pd2]
lam = clt.Laminate(pd2)
# Qbar, 0 deg
load = np.array([0, 0, 0, 100, 0, -50])
#temp = 0.
expect = np.array([0, 0, 0, 13.82e-3, 2.283e-3, -38.98e-3])
sol = lam.get_linear_response(load)
assert_allclose(sol.eps_kappa(), expect, atol=0.001)
def setUp(self):
mat25 = Material(E11=45000.,
E22=10000.,
G12=4500.,
a11t=5e-6,
a22t=20e-6,
nu12=0.31,
t=1.)
self.lam = clt.Laminate([(90, mat25), (0, mat25), (90, mat25)])
self.mload = np.zeros(6)
self.dtemp = -100
self.sol = self.lam.get_linear_response(self.mload, self.dtemp)
def setUp(self):
# hsb 37103-03 B 1991, example
# G23 = 0.5*E22/(1. + nu23) = 4600
# => nu23 = (0.5 E22/G23) - 1
self.mat = TransverseIsotropicPlyMaterial(name='T300_Epoxy',
E11=141000.,
E22=9400.,
G12=4600.,
nu12=0.30,
nu23=0.46875,
t=0.25)
#
self.plydef = [(0., self.mat), (90., self.mat), (90., self.mat),
(0., self.mat)]
#
self.lam = clt.Laminate(self.plydef)
def setUp(self):
mat = TransverseIsotropicPlyMaterial(E11=53780,
E22=17930,
nu12=0.25,
G12=8620,
a11t=6.3e-6,
a22t=20.52e-6,
t=0.127,
F11t=1035,
F11c=1035,
F22t=27.6,
F22c=138,
F12s=41.4)
sseq = [0] + [90] * 10 + [0]
self.lam = clt.Laminate([(a, mat) for a in sseq])
dtemp = 1
self.sol = self.lam.get_linear_response(
np.zeros(6),
dtemp) #clt.linear_solve(self.lam, np.zeros(6), dtemp)
class BerthelotExample_14_4_3_1(unittest.TestCase):
mat3 = TransverseIsotropicPlyMaterial(E11=46000.,
E22=10000.,
G12=4600.,
nu12=0.31,
t=3.)
mat5 = TransverseIsotropicPlyMaterial(E11=46000.,
E22=10000.,
G12=4600.,
nu12=0.31,
t=5.)
lam = clt.Laminate([(45, mat3), (0, mat5)])
expect_qbar45 = 1000 * np.array([[20.481, 11.282, 9.192],
[11.282, 20.482, 9.192],
[9.192, 9.192, 12.716]])
expect_a = 1000 * np.array([[296.35, 49.676, 27.576],
[49.676, 112.51, 27.576],
[27.576, 27.576, 61.147]])
expect_b = 1000 * np.array([[198.75, -60.87, -68.94],
[-60.87, -77.01, -68.94],
[-68.94, -68.94, -60.87]])
def test_symm(self):
self.assertFalse(self.lam.is_symmetric())
def test_layer_angle(self):
# second layer, 45
self.assertEqual(self.lam.layers[0].angle(), math.radians(45))
def test_qbar45(self):
layer = self.lam.layers[0]
assert_allclose(layer.Qbar(), self.expect_qbar45, 1e-4)
def test_a(self):
assert_allclose(self.lam.A(), self.expect_a, 1e-4)
def test_b(self):
assert_allclose(self.lam.B(), self.expect_b, 1e-4)
def setUp(self):
carbon = TransverseIsotropicPlyMaterial(t=0.04,
E11=207000.,
E22=7600.,
G12=5000.,
nu12=0.3,
a22t=30e-6,
a11t=0,
name="ESDU 94003 Carbon")
alu = TransverseIsotropicPlyMaterial(t=1.0,
E11=73000.,
E22=73000.,
G12=28100.,
nu12=0.3,
a11t=22e-6,
a22t=22e-6,
name="ESDU 94003 Alu")
stacking = [(0., carbon), (15., carbon), (0., carbon), (-15., carbon),
(0., carbon), (0., alu), (0., carbon), (-15., carbon),
(0., carbon), (15., carbon), (0., carbon)]
self.lam = clt.Laminate(stacking)
def setUp(self):
#
self.mat = TransverseIsotropicPlyMaterial(name='T300_Epoxy',
E11=135000.,
E22=10000.,
G12=5000.,
nu12=0.27,
nu23=0.30,
a11t=-0.6e-6,
a22t=40.0e-6,
t=0.125,
Xt=1450.,
Xc=1400.,
Yt=55.,
Yc=170.,
Sl=90.)
#
self.plydef = [(20., self.mat), (-20., self.mat), (20., self.mat),
(-20., self.mat)]
#
self.lam = clt.Laminate(self.plydef)
def setUp(self):
self.lam = clt.Laminate([(0, MAT), (90, MAT)])
def test_replace_layers(self):
lam = clt.Laminate([(0, MAT), (90, MAT)])
newlayers = (clt.Layer(lam, 45, MAT), clt.Layer(lam, -45, MAT))
self.assertRaises(AttributeError, setattr, lam, 'layers', newlayers)
def test_add_layer(self):
lam = clt.Laminate([(0, MAT), (90, MAT)])
newlayer = clt.Layer(lam, 45, MAT)
self.assertRaises(TypeError, tuple.__add__, lam.layers, newlayer)
def test_set_illegal_property(self):
lam = clt.Laminate([(0, MAT), (90, MAT)])
self.assertRaises(AttributeError, setattr, lam, 'otto', 2000)
def test_clt_init(self):
# mech. load only,
plydef = [(angle, self.m1) for angle in (0, 90, 0)]
# plydef is a list of (alpha, t, mat) tuples
lam = clt.Laminate(plydef)
self.assertEqual(lam.thickness(), 0.75)
def setUp(self):
"""elastic properties: table 3.2, strength values: table 8.3
thermal and moisture expansion properties: table 4.4
"""
self.cfrp_t300 = TransverseIsotropicPlyMaterial(
t=0.125,
E11=181000.,
E22=10300.,
G12=7170.,
nu12=0.28,
a11t=0.02e-6,
a22t=22.5e-6,
b11m=0.,
b22m=0.6,
F11t=1500.,
F11c=1500.,
F22t=40.,
F22c=246.,
F12s=68.,
name="CFRP/T300/N5208",
verbose_name=
"T300/N5208, from Tsai, Theory of composites design, Tables 3.2, 4.4, 8.3"
)
self.bfrp = TransverseIsotropicPlyMaterial(
t=0.125,
E11=204000.,
E22=18500.,
G12=5590.,
nu12=0.23,
a11t=6.1e-6,
a22t=30.3e-6,
b11m=0.,
b22m=0.6,
F11t=1260.,
F11c=-2500.,
F22t=61.,
F22c=-202.,
F12s=67.,
name="BFRP/B(4)/N5505",
verbose_name=
"BFRP/B(4)/N5505, from Tsai, Theory of composites design, Table 3.2"
)
self.cfrp_as = TransverseIsotropicPlyMaterial(
t=0.125,
E11=138000.,
E22=8960.,
G12=7100.,
nu12=0.30,
a11t=-0.3e-6,
a22t=28.1e-6,
b11m=0.,
b22m=0.44,
F11t=1447.,
F11c=-1447.,
F22t=52.,
F22c=-206.,
F12s=93.,
name="CFRP/AS/3501",
verbose_name=
"CFRP/AS/3501, from Tsai, Theory of composites design, Table 3.2")
self.gfrp = TransverseIsotropicPlyMaterial(
t=0.125,
E11=38600.,
E22=8270.,
G12=4140.,
nu12=0.26,
a11t=8.6e-6,
a22t=22.1e-6,
b11m=0.,
b22m=0.6,
F11t=1062.,
F11c=-610.,
F22t=31.,
F22c=-118.,
F12s=72.,
name="GFRP/E-Glass/Epoxy",
verbose_name=
"GFRP/E-Glass/Epoxy, from Tsai, Theory of composites design, Table 3.2"
)
self.kfrp = TransverseIsotropicPlyMaterial(
t=0.125,
E11=76000.,
E22=5500.,
G12=2300.,
nu12=0.34,
a11t=-4.0e-6,
a22t=79.0e-6,
b11m=0.,
b22m=0.6,
F11t=1400.,
F11c=-235.,
F22t=12.,
F22c=-53.,
F12s=34.,
name="KFRP/Kev-49/Epoxy",
verbose_name=
"KFRP/Kev-49/Epoxy, from Tsai, Theory of composites design, Table 3.2"
)
self.cfrtp = TransverseIsotropicPlyMaterial(
t=0.125,
E11=134000.,
E22=8900.,
G12=5100.,
nu12=0.28,
F11t=2130.,
F11c=-1100.,
F22t=80.,
F22c=-200.,
F12s=160.,
name="CFRTP/AS4/PEEK",
verbose_name=
"CFRTP/AS4/PEEK, from Tsai, Theory of composites design, Table 3.2"
)
self.cfrp_im6 = TransverseIsotropicPlyMaterial(
t=0.125,
E11=203000.,
E22=11200.,
G12=8400.,
nu12=0.32,
F11t=3500.,
F11c=-1540.,
F22t=56.,
F22c=-150.,
F12s=98.,
name="CFRP/IM6/Epoxy",
verbose_name=
"CFRP/IM6/Epoxy, from Tsai, Theory of composites design, Table 3.2"
)
self.cfrp_t300_4 = TransverseIsotropicPlyMaterial(
t=0.1,
E11=148000.,
E22=9650.,
G12=4550.,
nu12=0.3,
F11t=1314.,
F11c=-1200.,
F22t=43.,
F22c=-168.,
F12s=48.,
name="CFRP/T300/Fbrt_934/4-mil_tp",
verbose_name=
"CFRP/T300/Fbrt_934/4-mil_tp, from Tsai, Theory of composites design, Table 3.2"
)
self.ccrp_t300_13 = TransverseIsotropicPlyMaterial(
t=0.325,
E11=74000.,
E22=74000.,
G12=4550.,
nu12=0.05,
F11t=499.,
F11c=-352.,
F22t=458.,
F22c=-352.,
F12s=46.,
name="CCRP/T300/Fbrt_934/13-mil_c",
verbose_name=
"CCRP/T300/Fbrt_934/13-mil_c, from Tsai, Theory of composites design, Table 3.2"
)
self.ccrp_t300_7 = TransverseIsotropicPlyMaterial(
t=0.175,
E11=66000.,
E22=66000.,
G12=4100.,
nu12=0.04,
F11t=375.,
F11c=-279.,
F22t=368.,
F22c=-278.,
F12s=46.,
name="CCRP/T300/Fbrt_934/7-mil_c",
verbose_name=
"CCRP/T300/Fbrt_934/7-mil_c, from Tsai, Theory of composites design, Table 3.2"
)
self.lam = clt.Laminate([(0., self.cfrp_t300)])
def test_change_laminate_reference(self):
other_laminate = clt.Laminate([(34, MAT), (42, MAT)])
layer = self.lam.layers[0]
self.assertRaises(AttributeError, setattr, layer, '_laminate',
other_laminate)
