def test_reduced_dof_freq_plate():
models = ['plate_clt_donnell_bardell', 'cpanel_clt_donnell_bardell']
for model in models:
print(
'Test reduced_dof solver, prestress=True, model={0}'.format(model))
p = Panel()
p.model = model
p.a = 1.
p.b = 0.5
p.r = 100.
p.alphadeg = 0.
p.stack = [0, 90, -45, +45]
p.plyt = 1e-3 * 0.125
p.laminaprop = (142.5e9, 8.7e9, 0.28, 5.1e9, 5.1e9, 5.1e9)
p.mu = 1.3e3
p.m = 11
p.n = 12
p.Nxx = -60.
p.Nyy = -5.
k0 = p.calc_k0(silent=True)
M = p.calc_kM(silent=True)
kG0 = p.calc_kG0(silent=True)
k0 += kG0
eigvals, eigvecs = freq(k0,
M,
sparse_solver=True,
reduced_dof=False,
silent=True)
reduced_false = eigvals[0]
freq(k0, M, sparse_solver=True, reduced_dof=True, silent=True)
reduced_true = eigvals[0]
assert np.isclose(reduced_false, reduced_true, rtol=0.001)
def test_reduced_dof_freq_plate():
models = ['plate_clt_donnell_bardell',
'cpanel_clt_donnell_bardell']
for model in models:
print('Test reduced_dof solver, prestress=True, model={0}'.format(model))
p = Panel()
p.model = model
p.a = 1.
p.b = 0.5
p.r = 100.
p.alphadeg = 0.
p.stack = [0, 90, -45, +45]
p.plyt = 1e-3*0.125
p.laminaprop = (142.5e9, 8.7e9, 0.28, 5.1e9, 5.1e9, 5.1e9)
p.mu = 1.3e3
p.m = 11
p.n = 12
p.Nxx = -60.
p.Nyy = -5.
k0 = p.calc_k0(silent=True)
M = p.calc_kM(silent=True)
kG0 = p.calc_kG0(silent=True)
k0 += kG0
eigvals, eigvecs = freq(k0, M, sparse_solver=True, reduced_dof=False, silent=True)
reduced_false = eigvals[0]
freq(k0, M, sparse_solver=True, reduced_dof=True, silent=True)
reduced_true = eigvals[0]
assert np.isclose(reduced_false, reduced_true, rtol=0.001)
def test_freq():
for model in ['plate_clt_donnell_bardell',
'plate_clt_donnell_bardell_w',
'cpanel_clt_donnell_bardell',
'kpanel_clt_donnell_bardell']:
for atype in [3, 4]:
print('Frequency Analysis, atype={0}, model={1}'.format(
atype, model))
p = Panel()
p.model = model
p.bc_ssss()
p.a = 1.
p.b = 0.5
p.r = 1.e8
p.alphadeg = 0.
p.stack = [0, 90, -45, +45]
p.plyt = 1e-3*0.125
p.laminaprop = (142.5e9, 8.7e9, 0.28, 5.1e9, 5.1e9, 5.1e9)
p.mu = 1.3e3
p.m = 11
p.n = 12
p.Nxx = -60.
p.Nyy = -5.
p.freq(sparse_solver=True, reduced_dof=False, silent=True,
atype=atype)
if atype == 3:
if '_w' in model:
assert np.allclose(p.eigvals[0], 19.9271684726)
else:
assert np.allclose(p.eigvals[0], 17.8587479369)
elif atype == 4:
if '_w' in model:
assert np.allclose(p.eigvals[0], 40.3728103572)
else:
assert np.allclose(p.eigvals[0], 39.3147553173)
def test_panel_fkG_num_Fnxny():
for model in ['plate_clt_donnell_bardell', 'cpanel_clt_donnell_bardell']:
print('Checking fkG_num for model {0}'.format(model))
# ssss
p = Panel()
p.a = 8.
p.b = 4.
p.r = 1.e8
p.stack = [0, 90, 90, 0, -45, +45]
p.plyt = 1e-3 * 0.125
p.laminaprop = (142.5e9, 8.7e9, 0.28, 5.1e9, 5.1e9, 5.1e9)
p.model = model
p.Nxx = -1.
p.m = 8
p.n = 9
p.u1ty = 1
p.u2ty = 1
p.u2tx = 1
p.v1tx = 0
p.v2tx = 1
p.v1ty = 1
p.v2ty = 1
num = 1000.
f = 0.
for i in range(int(num)):
if i == 0 or i == num - 2:
fx = p.Nxx * p.b / (num - 1.) / 2.
else:
fx = p.Nxx * p.b / (num - 1.)
p.add_force(x=p.a,
y=i * p.b / (num - 1.),
fx=fx,
fy=0.,
fz=0.,
cte=True)
f += fx
p.static(silent=True)
c = p.analysis.cs[0]
p.lb(silent=True)
assert np.isclose(p.eigvals[0], 4.5290911349518801, atol=0.01, rtol=0)
nx = 9
ny = 9
Fnxny = p.F
p.lb(silent=True, c=c, Fnxny=Fnxny, nx=nx, ny=ny)
assert np.isclose(p.eigvals[0], 4.532851973656947, atol=0.01, rtol=0)
nx = 12
ny = 10
Fnxny = np.array([[p.F] * ny] * nx)
p.lb(silent=True, c=c, Fnxny=Fnxny, nx=nx, ny=ny)
assert np.isclose(p.eigvals[0], 4.532851973656947, atol=0.01, rtol=0)
def test_panel_fkG_num_Fnxny():
for model in ['plate_clt_donnell_bardell',
'cpanel_clt_donnell_bardell']:
print('Checking fkG_num for model {0}'.format(model))
# ssss
p = Panel()
p.a = 8.
p.b = 4.
p.r = 1.e8
p.stack = [0, 90, 90, 0, -45, +45]
p.plyt = 1e-3*0.125
p.laminaprop = (142.5e9, 8.7e9, 0.28, 5.1e9, 5.1e9, 5.1e9)
p.model = model
p.Nxx = -1.
p.m = 8
p.n = 9
p.u1ty = 1
p.u2ty = 1
p.u2tx = 1
p.v1tx = 0
p.v2tx = 1
p.v1ty = 1
p.v2ty = 1
num = 1000.
f = 0.
for i in range(int(num)):
if i == 0 or i == num - 2:
fx = p.Nxx*p.b/(num-1.)/2.
else:
fx = p.Nxx*p.b/(num-1.)
p.add_force(x=p.a, y=i*p.b/(num-1.), fx=fx, fy=0., fz=0.,
cte=True)
f += fx
p.static(silent=True)
c = p.analysis.cs[0]
p.lb(silent=True)
assert np.isclose(p.eigvals[0], 4.5290911349518801, atol=0.01, rtol=0)
nx = 9
ny = 9
Fnxny = p.F
p.lb(silent=True, c=c, Fnxny=Fnxny, nx=nx, ny=ny)
assert np.isclose(p.eigvals[0], 4.532851973656947, atol=0.01, rtol=0)
nx = 12
ny = 10
Fnxny = np.array([[p.F]*ny]*nx)
p.lb(silent=True, c=c, Fnxny=Fnxny, nx=nx, ny=ny)
assert np.isclose(p.eigvals[0], 4.532851973656947, atol=0.01, rtol=0)
def test_panel_aero():
for model in ['plate_clt_donnell_bardell',
'plate_clt_donnell_bardell_w',
'cpanel_clt_donnell_bardell']:
for atype in [1, 2]:
print('Flutter Analysis Piston Theory, atype={0}, model={1}'.
format(atype, model))
p = Panel()
p.model = model
p.a = 1.
p.b = 0.5
p.r = 1.e8
p.alphadeg = 0.
p.stack = [0, 90, -45, +45]
p.plyt = 1e-3*0.125
E2 = 8.7e9
p.laminaprop = (142.5e9, E2, 0.28, 5.1e9, 5.1e9, 5.1e9)
p.mu = 1.5e3
p.m = 8
p.n = 9
# pre-stress applied when atype == 1
p.Nxx = -60.
p.Nyy = -5.
# testing commong methodology based on betastar
if atype == 1:
betasstar = np.linspace(150, 350, 40)
elif atype == 2:
betasstar = np.linspace(670, 690, 40)
betas = betasstar/(p.a**3/E2/(len(p.stack)*p.plyt)**3)
p.beta = betas[0]
p.freq(atype=1, reduced_dof=False, sparse_solver=False,
silent=True)
out = np.zeros((len(betasstar), p.eigvals.shape[0]),
dtype=p.eigvals.dtype)
for i, beta in enumerate(betas):
p.beta = beta
p.freq(atype=2, reduced_dof=False, sparse_solver=False,
silent=True)
eigvals = p.eigvals*p.a**2/(np.pi**2*sum(p.plyts))*np.sqrt(p.mu/E2)
out[i, :] = eigvals
ind = np.where(np.any(out.imag != 0, axis=1))[0][0]
if atype == 1:
if not model.endswith('_w'):
assert np.isclose(betas[ind], 347.16346, atol=0.1, rtol=0)
else:
assert np.isclose(betas[ind], 174.27885, atol=0.1, rtol=0)
elif atype == 2:
if not model.endswith('_w'):
assert np.isclose(betas[ind], 728.625, atol=0.1, rtol=0)
else:
assert np.isclose(betas[ind], 728.625, atol=0.1, rtol=0)
def test_panel_field_outputs():
m = 7
n = 6
#TODO implement for conical panels
strain_field = dict(exx=None, eyy=None, gxy=None, kxx=None, kyy=None, kxy=None)
stress_field = dict(Nxx=None, Nyy=None, Nxy=None, Mxx=None, Myy=None, Mxy=None)
for model in ['plate_clt_donnell_bardell',
'cpanel_clt_donnell_bardell']:
p = Panel()
p.model = model
p.u1tx = 1
p.u1ty = 1
p.u2ty = 1
p.v1tx = 0
p.v2tx = 0
p.v1ty = 0
p.v2ty = 0
p.a = 2.
p.b = 1.
p.r = 1.e5
p.stack = [0, -45, +45, 90, +45, -45, 0, 0]
p.plyt = 1e-3*0.125
p.laminaprop = (142.5e9, 8.7e9, 0.28, 5.1e9, 5.1e9, 5.1e9)
p.nx = m
p.ny = n
p.m = m
p.n = n
P = 1000.
npts = 100
p.forces_inc = []
for y in np.linspace(0, p.b, npts):
p.forces_inc.append([0., y, P/(npts-1.), 0, 0])
p.forces_inc[0][2] /= 2.
p.forces_inc[-1][2] /= 2.
p.static()
c = p.analysis.cs[0]
Ns = p.stress(c, gridx=50, gridy=50)
es = p.strain(c, gridx=50, gridy=50)
for k, v in strain_field.items():
if v is None:
strain_field[k] = es.get(k).min()
else:
assert np.isclose(strain_field[k], es.get(k).min(), rtol=0.05)
p.plot(c, vec=k, filename='tmp_test_panel_strain_field_%s.png' % k)
for k, v in stress_field.items():
if v is None:
stress_field[k] = Ns.get(k).min()
else:
assert np.isclose(stress_field[k], Ns.get(k).min(), rtol=0.05)
p.plot(c, vec=k, filename='tmp_test_panel_stress_field_%s.png' % k)
def test_panel_freq():
for model in [
'plate_clt_donnell_bardell', 'plate_clt_donnell_bardell_w',
'cpanel_clt_donnell_bardell', 'kpanel_clt_donnell_bardell'
]:
for prestress in [True, False]:
print('Frequency Analysis, prestress={0}, model={1}'.format(
prestress, model))
p = Panel()
p.model = model
p.a = 1.
p.b = 0.5
p.r = 1.e8
p.alphadeg = 0.
p.stack = [0, 90, -45, +45]
p.plyt = 1e-3 * 0.125
p.laminaprop = (142.5e9, 8.7e9, 0.28, 5.1e9, 5.1e9, 5.1e9)
p.mu = 1.3e3
p.m = 11
p.n = 12
p.Nxx = -60.
p.Nyy = -5.
k0 = p.calc_k0(silent=True)
M = p.calc_kM(silent=True)
if prestress:
kG0 = p.calc_kG0(silent=True)
k0 += kG0
eigvals, eigvecs = freq(k0,
M,
sparse_solver=True,
reduced_dof=False,
silent=True)
if prestress:
if '_w' in model:
assert np.isclose(eigvals[0], 19.9272, rtol=0.001)
else:
assert np.isclose(eigvals[0], 17.85875, rtol=0.001)
else:
if '_w' in model:
assert np.isclose(eigvals[0], 40.37281, rtol=0.001)
else:
assert np.isclose(eigvals[0], 39.31476, rtol=0.001)
def test_fint():
m = 6
n = 6
for model in ['plate_clt_donnell_bardell',
'cpanel_clt_donnell_bardell'
]:
p = Panel()
p.model = model
p.w1tx = 0
p.w1rx = 1
p.u1tx = 1
p.u1ty = 1
p.u2ty = 1
p.a = 2.
p.b = 1.
p.r = 1.e5
p.stack = [0, 90, -45, +45]
p.plyt = 1e-3*0.125
p.laminaprop = (142.5e9, 8.7e9, 0.28, 5.1e9, 5.1e9, 5.1e9)
p.nx = m
p.ny = n
p.m = m
p.n = n
P = 1000.
npts = 100
p.forces_inc = []
for y in np.linspace(0, p.b, npts):
p.forces_inc.append([0., y, P/(npts-1.), 0, 0])
p.forces_inc[0][2] /= 2.
p.forces_inc[-1][2] /= 2.
p.forces.append([p.a/2., p.b/2., 0, 0, 0.001])
p.static(NLgeom=True, silent=True)
c = p.analysis.cs[0]
p.plot(c, vec='w', filename='tmp_test_non_linear.png', colorbar=True)
p.uvw(p.analysis.cs[0])
assert np.isclose(p.w.max(), 0.000144768080125, rtol=0.001)
def test_panel_freq():
for model in ['plate_clt_donnell_bardell',
'plate_clt_donnell_bardell_w',
'cpanel_clt_donnell_bardell',
'kpanel_clt_donnell_bardell']:
for prestress in [True, False]:
print('Frequency Analysis, prestress={0}, model={1}'.format(
prestress, model))
p = Panel()
p.model = model
p.a = 1.
p.b = 0.5
p.r = 1.e8
p.alphadeg = 0.
p.stack = [0, 90, -45, +45]
p.plyt = 1e-3*0.125
p.laminaprop = (142.5e9, 8.7e9, 0.28, 5.1e9, 5.1e9, 5.1e9)
p.mu = 1.3e3
p.m = 11
p.n = 12
p.Nxx = -60.
p.Nyy = -5.
k0 = p.calc_k0(silent=True)
M = p.calc_kM(silent=True)
if prestress:
kG0 = p.calc_kG0(silent=True)
k0 += kG0
eigvals, eigvecs = freq(k0, M, sparse_solver=True, reduced_dof=False, silent=True)
if prestress:
if '_w' in model:
assert np.isclose(eigvals[0], 19.9272, rtol=0.001)
else:
assert np.isclose(eigvals[0], 17.85875, rtol=0.001)
else:
if '_w' in model:
assert np.isclose(eigvals[0], 40.37281, rtol=0.001)
else:
assert np.isclose(eigvals[0], 39.31476, rtol=0.001)
def test_kT():
mns = [[4, 4], [4, 5], [4, 6], [5, 5], [5, 6], [6, 6],
[8, 9], [9, 8]]
for m, n in mns:
for model in ['plate_clt_donnell_bardell',
'cpanel_clt_donnell_bardell']:
p = Panel()
p.model = model
p.w1tx = 0
p.u1tx = 1
p.u1ty = 1
p.u2ty = 1
p.a = 2.
p.b = 0.5
p.r = 10
p.stack = [0, 90, -45, +45]
p.plyt = 1e-3*0.125
p.laminaprop = (142.5e9, 8.7e9, 0.28, 5.1e9, 5.1e9, 5.1e9)
p.m = m
p.n = n
p.nx = m
p.ny = n
P = 1000.
npts = 5
p.forces_inc = []
for y in np.linspace(0, p.b, npts):
p.forces_inc.append([0., y, P/(npts-1.), 0, 0])
p.forces_inc[0][2] /= 2.
p.forces_inc[-1][2] /= 2.
k0 = p.calc_k0(silent=True)
kT = p.calc_kT(c=np.zeros(p.get_size()), silent=True)
error = np.abs(kT-k0).sum()
assert error < 1.e-7
def test_kT():
mns = [[4, 4], [4, 5], [4, 6], [5, 5], [5, 6], [6, 6], [8, 9], [9, 8]]
for m, n in mns:
for model in [
'plate_clt_donnell_bardell', 'cpanel_clt_donnell_bardell'
]:
p = Panel()
p.model = model
p.w1tx = 0
p.u1tx = 1
p.u1ty = 1
p.u2ty = 1
p.a = 2.
p.b = 0.5
p.r = 10
p.stack = [0, 90, -45, +45]
p.plyt = 1e-3 * 0.125
p.laminaprop = (142.5e9, 8.7e9, 0.28, 5.1e9, 5.1e9, 5.1e9)
p.m = m
p.n = n
p.nx = m
p.ny = n
P = 1000.
npts = 5
p.forces_inc = []
for y in np.linspace(0, p.b, npts):
p.forces_inc.append([0., y, P / (npts - 1.), 0, 0])
p.forces_inc[0][2] /= 2.
p.forces_inc[-1][2] /= 2.
k0 = p.calc_k0(silent=True)
kT = p.calc_kT(c=np.zeros(p.get_size()), silent=True)
error = np.abs(kT - k0).sum()
assert error < 1.e-7
def test_fint():
m = 6
n = 6
for model in ['plate_clt_donnell_bardell', 'cpanel_clt_donnell_bardell']:
p = Panel()
p.model = model
p.w1tx = 0
p.w1rx = 1
p.u1tx = 1
p.u1ty = 1
p.u2ty = 1
p.a = 2.
p.b = 1.
p.r = 1.e5
p.stack = [0, 90, -45, +45]
p.plyt = 1e-3 * 0.125
p.laminaprop = (142.5e9, 8.7e9, 0.28, 5.1e9, 5.1e9, 5.1e9)
p.nx = m
p.ny = n
p.m = m
p.n = n
P = 1000.
npts = 100
p.forces_inc = []
for y in np.linspace(0, p.b, npts):
p.forces_inc.append([0., y, P / (npts - 1.), 0, 0])
p.forces_inc[0][2] /= 2.
p.forces_inc[-1][2] /= 2.
p.forces.append([p.a / 2., p.b / 2., 0, 0, 0.001])
p.static(NLgeom=True, silent=True)
c = p.analysis.cs[0]
p.plot(c, vec='w', filename='tmp_test_non_linear.png', colorbar=True)
p.uvw(p.analysis.cs[0])
assert np.isclose(p.w.max(), 0.000144768080125, rtol=0.001)
def test_panel_aero():
for model in [
'plate_clt_donnell_bardell', 'plate_clt_donnell_bardell_w',
'cpanel_clt_donnell_bardell'
]:
for atype in [1, 2]:
print(
'Flutter Analysis Piston Theory, atype={0}, model={1}'.format(
atype, model))
p = Panel()
p.model = model
p.a = 1.
p.b = 0.5
p.r = 1.e8
p.alphadeg = 0.
p.stack = [0, 90, -45, +45]
p.plyt = 1e-3 * 0.125
E2 = 8.7e9
p.laminaprop = (142.5e9, E2, 0.28, 5.1e9, 5.1e9, 5.1e9)
p.mu = 1.5e3
p.m = 8
p.n = 9
# pre-stress applied when atype == 1
p.Nxx = -60.
p.Nyy = -5.
# testing commong methodology based on betastar
if atype == 1:
betasstar = np.linspace(150, 350, 40)
elif atype == 2:
betasstar = np.linspace(670, 690, 40)
betas = betasstar / (p.a**3 / E2 / (len(p.stack) * p.plyt)**3)
p.beta = betas[0]
p.freq(atype=1,
reduced_dof=False,
sparse_solver=False,
silent=True)
out = np.zeros((len(betasstar), p.eigvals.shape[0]),
dtype=p.eigvals.dtype)
for i, beta in enumerate(betas):
p.beta = beta
p.freq(atype=2,
reduced_dof=False,
sparse_solver=False,
silent=True)
eigvals = p.eigvals * p.a**2 / (
np.pi**2 * sum(p.plyts)) * np.sqrt(p.mu / E2)
out[i, :] = eigvals
ind = np.where(np.any(out.imag != 0, axis=1))[0][0]
if atype == 1:
if not model.endswith('_w'):
assert np.isclose(betas[ind], 347.16346, atol=0.1, rtol=0)
else:
assert np.isclose(betas[ind], 174.27885, atol=0.1, rtol=0)
elif atype == 2:
if not model.endswith('_w'):
assert np.isclose(betas[ind], 728.625, atol=0.1, rtol=0)
else:
assert np.isclose(betas[ind], 728.625, atol=0.1, rtol=0)
def add_panel(self, y1, y2, stack=None, plyts=None, plyt=None,
laminaprops=None, laminaprop=None, model=None, mu=None, **kwargs):
"""Add a new panel to the current panel bay
Parameters
----------
y1 : float
Position of the first panel edge along `y`.
y2 : float
Position of the second panel edge along `y`.
stack : list, optional
Panel stacking sequence. If not given the stacking sequence of the
bay will be used.
plyts : list, optional
Thicknesses for each panel ply. If not supplied the bay ``plyts``
attribute will be used.
plyt : float, optional
Unique thickness to be used for all panel plies. If not supplied
the bay ``plyt`` attribute will be used.
laminaprops : list, optional
Lamina properties for each panel ply.
laminaprop : list, optional
Unique lamina properties for all panel plies.
model : str, optional
Not recommended to pass this parameter, but the user can use a
different model for each panel. It is recommended to defined
``model`` for the bay object.
mu : float, optional
Panel material density. If not given the bay density will be used.
Notes
-----
Additional parameters can be passed using the ``kwargs``.
"""
p = Panel()
p.m = self.m
p.n = self.n
p.a = self.a
p.b = self.b
p.r = self.r
p.y1 = y1
p.y2 = y2
p.d = 0.
p.model = model if model is not None else self.model
p.stack = stack if stack is not None else self.stack
p.plyt = plyt if plyt is not None else self.plyt
p.plyts = plyts if plyts is not None else self.plyts
p.laminaprop = laminaprop if laminaprop is not None else self.laminaprop
p.laminaprops = laminaprops if laminaprops is not None else self.laminaprops
p.mu = mu if mu is not None else self.mu
p.u1tx = self.u1tx
p.u1rx = self.u1rx
p.u2tx = self.u2tx
p.u2rx = self.u2rx
p.v1tx = self.v1tx
p.v1rx = self.v1rx
p.v2tx = self.v2tx
p.v2rx = self.v2rx
p.w1tx = self.w1tx
p.w1rx = self.w1rx
p.w2tx = self.w2tx
p.w2rx = self.w2rx
p.u1ty = self.u1ty
p.u1ry = self.u1ry
p.u2ty = self.u2ty
p.u2ry = self.u2ry
p.v1ty = self.v1ty
p.v1ry = self.v1ry
p.v2ty = self.v2ty
p.v2ry = self.v2ry
p.w1ty = self.w1ty
p.w1ry = self.w1ry
p.w2ty = self.w2ty
p.w2ry = self.w2ry
for k, v in kwargs.items():
setattr(p, k, v)
self.panels.append(p)
def test_panel_lb():
for model in [
'plate_clt_donnell_bardell', 'plate_clt_donnell_bardell_w',
'cpanel_clt_donnell_bardell', 'kpanel_clt_donnell_bardell'
]:
print('Linear buckling for model {0}'.format(model))
# ssss
p = Panel()
p.m = 12
p.n = 13
p.stack = [0, 90, -45, +45]
p.plyt = 0.125e-3
p.laminaprop = (142.5e9, 8.7e9, 0.28, 5.1e9, 5.1e9, 5.1e9)
p.model = model
p.a = 1.
p.b = 0.5
p.r = 1.e8
p.alphadeg = 0.
p.Nxx = -1
k0 = p.calc_k0(silent=True)
kG0 = p.calc_kG0(silent=True)
eigvals, eigvecs = lb(k0, kG0, silent=True)
if '_w' in model:
assert np.isclose(eigvals[0], 88.47696, atol=0.1, rtol=0)
else:
assert np.isclose(eigvals[0], 85.2912, atol=0.1, rtol=0)
p.Nxx = 0
p.Nyy = -1
k0 = p.calc_k0(silent=True)
kG0 = p.calc_kG0(silent=True)
eigvals, eigvecs = lb(k0, kG0, silent=True)
if '_w' in model:
assert np.isclose(eigvals[0], 26.45882, atol=0.1, rtol=0)
else:
assert np.isclose(eigvals[0], 25.17562, atol=0.1, rtol=0)
# ssfs
p = Panel()
p.u2ty = 1
p.v2ty = 1
p.w2ty = 1
p.u2ry = 1
p.v2ry = 1
p.m = 12
p.n = 13
p.stack = [0, 90, -45, +45]
p.plyt = 0.125e-3
p.laminaprop = (142.5e9, 8.7e9, 0.28, 5.1e9, 5.1e9, 5.1e9)
p.model = model
p.a = 1.
p.b = 0.5
p.r = 1.e8
p.alphadeg = 0.
p.Nxx = -1
k0 = p.calc_k0(silent=True)
kG0 = p.calc_kG0(silent=True)
eigvals, eigvecs = lb(k0, kG0, silent=True)
if '_w' in model:
assert np.isclose(eigvals[0], 17.14427, atol=0.1, rtol=0)
else:
assert np.isclose(eigvals[0], 15.842356, atol=0.1, rtol=0)
p.u2tx = 1
p.v2tx = 1
p.w2tx = 1
p.u2rx = 1
p.v2rx = 1
p.u2ty = 0
p.v2ty = 0
p.w2ty = 0
p.u2ry = 0
p.v2ry = 0
p.Nxx = 0
p.Nyy = -1
k0 = p.calc_k0(silent=True)
kG0 = p.calc_kG0(silent=True)
eigvals, eigvecs = lb(k0, kG0, silent=True)
if '_w' in model:
assert np.isclose(eigvals[0], 15.809986, atol=0.1, rtol=0)
else:
assert np.isclose(eigvals[0], 13.9421988, atol=0.1, rtol=0)
def test_panel_lb():
for model in ['plate_clt_donnell_bardell',
'plate_clt_donnell_bardell_w',
'cpanel_clt_donnell_bardell',
'kpanel_clt_donnell_bardell']:
print('Linear buckling for model {0}'.format(model))
# ssss
p = Panel()
p.m = 12
p.n = 13
p.stack = [0, 90, -45, +45]
p.plyt = 0.125e-3
p.laminaprop = (142.5e9, 8.7e9, 0.28, 5.1e9, 5.1e9, 5.1e9)
p.model = model
p.a = 1.
p.b = 0.5
p.r = 1.e8
p.alphadeg = 0.
p.Nxx = -1
k0 = p.calc_k0(silent=True)
kG0 = p.calc_kG0(silent=True)
eigvals, eigvecs = lb(k0, kG0, silent=True)
if '_w' in model:
assert np.isclose(eigvals[0], 88.47696, atol=0.1, rtol=0)
else:
assert np.isclose(eigvals[0], 85.2912, atol=0.1, rtol=0)
p.Nxx = 0
p.Nyy = -1
k0 = p.calc_k0(silent=True)
kG0 = p.calc_kG0(silent=True)
eigvals, eigvecs = lb(k0, kG0, silent=True)
if '_w' in model:
assert np.isclose(eigvals[0], 26.45882, atol=0.1, rtol=0)
else:
assert np.isclose(eigvals[0], 25.17562, atol=0.1, rtol=0)
# ssfs
p = Panel()
p.u2ty = 1
p.v2ty = 1
p.w2ty = 1
p.u2ry = 1
p.v2ry = 1
p.m = 12
p.n = 13
p.stack = [0, 90, -45, +45]
p.plyt = 0.125e-3
p.laminaprop = (142.5e9, 8.7e9, 0.28, 5.1e9, 5.1e9, 5.1e9)
p.model = model
p.a = 1.
p.b = 0.5
p.r = 1.e8
p.alphadeg = 0.
p.Nxx = -1
k0 = p.calc_k0(silent=True)
kG0 = p.calc_kG0(silent=True)
eigvals, eigvecs = lb(k0, kG0, silent=True)
if '_w' in model:
assert np.isclose(eigvals[0], 17.14427, atol=0.1, rtol=0)
else:
assert np.isclose(eigvals[0], 15.842356, atol=0.1, rtol=0)
p.u2tx = 1
p.v2tx = 1
p.w2tx = 1
p.u2rx = 1
p.v2rx = 1
p.u2ty = 0
p.v2ty = 0
p.w2ty = 0
p.u2ry = 0
p.v2ry = 0
p.Nxx = 0
p.Nyy = -1
k0 = p.calc_k0(silent=True)
kG0 = p.calc_kG0(silent=True)
eigvals, eigvecs = lb(k0, kG0, silent=True)
if '_w' in model:
assert np.isclose(eigvals[0], 15.809986, atol=0.1, rtol=0)
else:
assert np.isclose(eigvals[0], 13.9421988, atol=0.1, rtol=0)
def test_lb():
for model in ['plate_clt_donnell_bardell',
'plate_clt_donnell_bardell_w',
'cpanel_clt_donnell_bardell',
'kpanel_clt_donnell_bardell']:
print('Linear buckling for model {0}'.format(model))
# ssss
p = Panel()
p.bc_ssss()
p.m = 12
p.n = 13
p.stack = [0, 90, -45, +45]
p.plyt = 0.125e-3
p.laminaprop = (142.5e9, 8.7e9, 0.28, 5.1e9, 5.1e9, 5.1e9)
p.model = model
p.a = 1.
p.b = 0.5
p.r = 1.e8
p.alphadeg = 0.
p.Nxx = -1
p.lb(silent=True)
if '_w' in model:
assert np.allclose(p.eigvals[0], 88.4769618837)
else:
assert np.allclose(p.eigvals[0], 85.2911727144)
p.Nxx = 0
p.Nyy = -1
p.lb(silent=True)
if '_w' in model:
assert np.allclose(p.eigvals[0], 26.4588171556)
else:
assert np.allclose(p.eigvals[0], 25.1756170679)
# ssfs
p = Panel()
p.bc_ssfs()
p.m = 12
p.n = 13
p.stack = [0, 90, -45, +45]
p.plyt = 0.125e-3
p.laminaprop = (142.5e9, 8.7e9, 0.28, 5.1e9, 5.1e9, 5.1e9)
p.model = model
p.a = 1.
p.b = 0.5
p.r = 1.e8
p.alphadeg = 0.
p.Nxx = -1
p.lb(silent=True)
if '_w' in model:
assert np.allclose(p.eigvals[0], 17.1442703121)
else:
assert np.allclose(p.eigvals[0], 15.8423562314)
p.bc_sfss()
p.Nxx = 0
p.Nyy = -1
p.lb(silent=True)
if '_w' in model:
assert np.allclose(p.eigvals[0], 15.8099861083)
else:
assert np.allclose(p.eigvals[0], 13.9421987614)
