def test_shell_lb():
for model in [
'plate_clpt_donnell_bardell',
'cylshell_clpt_donnell_bardell',
]:
# ssss
s = Shell()
s.m = 12
s.n = 12
s.stack = [0, 90, -45, +45, +45, -45, 90, 0]
s.plyt = 0.125e-3
s.laminaprop = (142.5e9, 8.7e9, 0.28, 5.1e9, 5.1e9, 5.1e9)
s.model = model
s.a = 2.
s.b = 1.
s.r = 1.e8
s.Nxx = -1
eigvals, eigvecs = lb(s.calc_kC(), s.calc_kG(), silent=True)
assert np.isclose(eigvals[0], 157.5369886, atol=0.1, rtol=0)
s.Nxx = 0
s.Nyy = -1
eigvals, eigvecs = lb(s.calc_kC(), s.calc_kG(), silent=True)
assert np.isclose(eigvals[0], 58.1488566, atol=0.1, rtol=0)
# ssfs
s = Shell()
s.y2u = 1
s.y2v = 1
s.y2w = 1
s.m = 12
s.n = 13
s.stack = [0, 90, -45, +45]
s.plyt = 0.125e-3
s.laminaprop = (142.5e9, 8.7e9, 0.28, 5.1e9, 5.1e9, 5.1e9)
s.model = model
s.a = 1.
s.b = 0.5
s.r = 1.e8
s.Nxx = -1
eigvals, eigvecs = lb(s.calc_kC(), s.calc_kG(), silent=True)
assert np.isclose(eigvals[0], 15.8106238, atol=0.1, rtol=0)
s.x2u = 1
s.x2v = 1
s.x2w = 1
s.y2u = 0
s.y2v = 0
s.y2w = 0
s.Nxx = 0
s.Nyy = -1
eigvals, eigvecs = lb(s.calc_kC(), s.calc_kG(), silent=True)
assert np.isclose(eigvals[0], 14.046, atol=0.1, rtol=0)
plot_shell(s, eigvecs[:, 0], vec='w')
def test_lb_isotropic():
#NOTE ssss boundary conditions by default
s = Shell()
s.m = 12
s.n = 12
s.stack = [0, 90, -45, +45, +45, -45, 90, 0]
thickness = 1e-3
E = 70e9
nu = 0.33
s.a = 2.
s.b = 1.
s.r = 2.
# compression
# it is possible to apply any static load if necessary
s.Nxx = -1
# shear
s.Nxy = -1
s.plyt = thickness
s.laminaprop = (E, E, nu)
s.model = 'cylshell_clpt_donnell_bardell'
# radius
eigvals, eigvecs = lb(s.calc_kC(), s.calc_kG(), silent=True)
plot_shell(s, eigvecs[:, 0], vec='w', filename='example_isotropic.png')
def test_calc_linear_buckling():
E11 = 71.e9
nu = 0.33
plyt = 0.007
lam = read_stack([0], plyt=plyt, laminaprop=(E11, E11, nu))
ans = {
'edge-based': 41.85273,
'cell-based': 6.98852939,
'cell-based-no-smoothing': 4.921956
}
for prop_from_nodes in [True, False]:
for k0s_method in [
'edge-based', 'cell-based', 'cell-based-no-smoothing'
]:
mesh = read_mesh(
os.path.join(THISDIR, 'nastran_plate_16_nodes.dat'))
for tria in mesh.elements.values():
tria.prop = lam
for node in mesh.nodes.values():
node.prop = lam
k0 = calc_k0(mesh, prop_from_nodes)
add_k0s(k0, mesh, prop_from_nodes, k0s_method, alpha=0.2)
# running static subcase first
dof = 5
n = k0.shape[0] // 5
fext = np.zeros(n * dof, dtype=np.float64)
fext[mesh.nodes[4].index * dof + 0] = -500.
fext[mesh.nodes[7].index * dof + 0] = -500.
fext[mesh.nodes[5].index * dof + 0] = -1000.
fext[mesh.nodes[6].index * dof + 0] = -1000.
# boundary conditions
def bc(K):
for i in [1, 10, 11, 12]:
for j in [0, 1, 2]:
K[mesh.nodes[i].index * dof + j, :] = 0
K[:, mesh.nodes[i].index * dof + j] = 0
for i in [2, 3, 4, 5, 6, 7, 8, 9]:
for j in [1, 2]:
K[mesh.nodes[i].index * dof + j, :] = 0
K[:, mesh.nodes[i].index * dof + j] = 0
bc(k0)
k0 = coo_matrix(k0)
d = solve(k0, fext, silent=True)
kG = calc_kG(d, mesh, prop_from_nodes)
bc(kG)
kG = coo_matrix(kG)
eigvals, eigvecs = lb(k0, kG, silent=True)
print('k0s_method, eigvals[0]', k0s_method, eigvals[0])
assert np.isclose(eigvals[0], ans[k0s_method])
def test_lb_orthotropic():
#NOTE ssss boundary conditions by default
s = Shell()
s.m = 12
s.n = 12
s.stack = [0, 90, -45, +45, +45, -45, 90, 0]
s.plyt = 0.125e-3
s.laminaprop = (142.5e9, 8.7e9, 0.28, 5.1e9, 5.1e9, 5.1e9)
s.model = 'cylshell_clpt_donnell_bardell'
s.a = 2.
s.b = 1.
# radius
s.r = 2.
# compression
s.Nxx = -1
# shear
s.Nxy = -1
eigvals, eigvecs = lb(s.calc_kC(), s.calc_kG(), silent=True)
plot_shell(s, eigvecs[:, 0], vec='w')
val = fu/(N**0.5-1)
for i in ids_corner:
fext[mesh.nodes[i].index*dof + 0] = val/2
for i in ids_middle:
fext[mesh.nodes[i].index*dof + 0] = val
print('fext.sum()', fext.sum())
d = solve(k0, fext, silent=True)
# running linear buckling case
vec = d[0::dof]
print('u.min()', vec.min())
kG = calc_kG(d, mesh, prop_from_nodes)
bc(kG)
kG = coo_matrix(kG)
eigvals, eigvecs = lb(k0, kG, silent=True)
print('eigvals[0]', eigvals[0])
xyz = np.array([n.xyz for n in nodes])
ind = np.lexsort((xyz[:, 1], xyz[:, 0]))
xyz = xyz[ind]
nodes = np.array(list(nodes))[ind]
pick = [n.index for n in nodes]
vec = eigvecs[2::dof, 0]
levels = np.linspace(vec.min(), vec.max(), 16)
import matplotlib.pyplot as plt
import matplotlib.cm as cm
plt.figure(dpi=100, figsize=(6, 3))
nx = int(N**0.5)
def test_plate_from_zero():
# Plate geometry and laminate data
a = 0.406
b = 0.254
E1 = 1.295e11
E2 = 9.37e9
nu12 = 0.38
G12 = 5.24e9
G13 = 5.24e9
G23 = 5.24e9
plyt = 1.9e-4
laminaprop = (E1, E2, nu12, G12, G13, G23)
angles = [0, 45, -45, 90, 90, -45, 45, 0]
# Generating Mesh
# ---
import numpy as np
from scipy.spatial import Delaunay
xs = np.linspace(0, a, 8)
ys = np.linspace(0, b, 8)
points = np.array(np.meshgrid(xs, ys)).T.reshape(-1, 2)
tri = Delaunay(points)
# Using Meshless Package
# ---
from scipy.sparse import coo_matrix
from composites.laminate import read_stack
from structsolve import solve, lb
from meshless.espim.read_mesh import read_delaunay
from meshless.espim.plate2d_calc_k0 import calc_k0
from meshless.espim.plate2d_calc_kG import calc_kG
from meshless.espim.plate2d_add_k0s import add_k0s
mesh = read_delaunay(points, tri)
nodes = np.array(list(mesh.nodes.values()))
prop_from_nodes = True
nodes_xyz = np.array([n.xyz for n in nodes])
# **Applying properties
# applying heterogeneous properties
for node in nodes:
lam = read_stack(angles, plyt=plyt, laminaprop=laminaprop)
node.prop = lam
# **Defining Boundary Conditions**
#
DOF = 5
def bc(K, mesh):
for node in nodes[nodes_xyz[:, 0] == xs.min()]:
for dof in [1, 3]:
j = dof - 1
K[node.index * DOF + j, :] = 0
K[:, node.index * DOF + j] = 0
for node in nodes[(nodes_xyz[:, 1] == ys.min()) |
(nodes_xyz[:, 1] == ys.max())]:
for dof in [2, 3]:
j = dof - 1
K[node.index * DOF + j, :] = 0
K[:, node.index * DOF + j] = 0
for node in nodes[nodes_xyz[:, 0] == xs.max()]:
for dof in [3]:
j = dof - 1
K[node.index * DOF + j, :] = 0
K[:, node.index * DOF + j] = 0
# **Calculating Constitutive Stiffness Matrix**
k0s_method = 'cell-based'
k0 = calc_k0(mesh, prop_from_nodes)
add_k0s(k0, mesh, prop_from_nodes, k0s_method, alpha=0.2)
bc(k0, mesh)
k0 = coo_matrix(k0)
# **Defining Load and External Force Vector**
def define_loads(mesh):
loads = []
load_nodes = nodes[(nodes_xyz[:, 0] == xs.max())
& (nodes_xyz[:, 1] != ys.min()) &
(nodes_xyz[:, 1] != ys.max())]
fx = -1. / (nodes[nodes_xyz[:, 0] == xs.max()].shape[0] - 1)
for node in load_nodes:
loads.append([node, (fx, 0, 0)])
load_nodes = nodes[(nodes_xyz[:, 0] == xs.max()) & (
(nodes_xyz[:, 1] == ys.min()) | (nodes_xyz[:, 1] == ys.max()))]
fx = -1. / (nodes[nodes_xyz[:, 0] == xs.max()].shape[0] - 1) / 2
for node in load_nodes:
loads.append([node, (fx, 0, 0)])
return loads
n = k0.shape[0] // DOF
fext = np.zeros(n * DOF, dtype=np.float64)
loads = define_loads(mesh)
for node, force_xyz in loads:
fext[node.index * DOF + 0] = force_xyz[0]
print('Checking sum of forces: %s' %
str(fext.reshape(-1, DOF).sum(axis=0)))
# **Running Static Analysis**
d = solve(k0, fext, silent=True)
total_trans = (d[0::DOF]**2 + d[1::DOF]**2)**0.5
print('Max total translation', total_trans.max())
# **Calculating Geometric Stiffness Matrix**
kG = calc_kG(d, mesh, prop_from_nodes)
bc(kG, mesh)
kG = coo_matrix(kG)
# **Running Linear Buckling Analysis**
eigvals, eigvecs = lb(k0, kG, silent=True)
print('First 5 eigenvalues')
print('\n'.join(map(str, eigvals[:5])))
assert np.allclose(eigvals[:5], [
1004.29332981,
1822.11577078,
2898.3728806,
2947.17499169,
3297.54959342,
])