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 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_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)