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_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_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_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_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_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_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)