def test_freq_Stiffener2D():
print('Testing frequency analysis for StiffPanelBay with a 2D Stiffener')
spb = StiffPanelBay()
spb.a = 1.
spb.b = 0.5
spb.stack = [0, 90, 90, 0]
spb.plyt = 1e-3 * 0.125
spb.laminaprop = (142.5e9, 8.7e9, 0.28, 5.1e9, 5.1e9, 5.1e9)
spb.model = 'plate_clt_donnell_bardell'
spb.mu = 1.3e3
spb.m = 11
spb.n = 12
spb.add_panel(y1=0, y2=spb.b / 2., plyt=spb.plyt)
spb.add_panel(y1=spb.b / 2., y2=spb.b, plyt=spb.plyt)
spb.add_bladestiff2d(ys=spb.b / 2.,
m1=14,
n1=11,
bf=0.08,
fstack=[0, 90, 90, 0] * 5,
fplyt=spb.plyt,
flaminaprop=spb.laminaprop)
k0 = spb.calc_k0(silent=True)
M = spb.calc_kM(silent=True)
eigvals, eigvecs = freq(k0, M, silent=True)
assert np.isclose(eigvals[0].real, 137.97927190657148, atol=0.01, rtol=0)
def test_lb_Stiffener2D():
print('Testing linear buckling for StiffPanelBay with a 2D Stiffener')
spb = StiffPanelBay()
spb.a = 1.
spb.b = 0.5
spb.stack = [0, 90, 90, 0]
spb.plyt = 1e-3 * 0.125
spb.laminaprop = (142.5e9, 8.7e9, 0.28, 5.1e9, 5.1e9, 5.1e9)
spb.model = 'plate_clt_donnell_bardell'
spb.mu = 1.3e3
spb.m = 15
spb.n = 16
spb.add_panel(y1=0, y2=spb.b / 2., plyt=spb.plyt, Nxx=-1.)
spb.add_panel(y1=spb.b / 2., y2=spb.b, plyt=spb.plyt, Nxx_cte=1000.)
spb.add_bladestiff2d(ys=spb.b / 2.,
m1=14,
n1=11,
bf=0.05,
fstack=[0, 90, 90, 0],
fplyt=spb.plyt,
flaminaprop=spb.laminaprop)
k0 = spb.calc_k0(silent=True)
kG = spb.calc_kG0(silent=True)
eigvals, eigvecs = lb(k0, kG, silent=True)
assert np.isclose(eigvals[0].real, 301.0825234, atol=0.1, rtol=0)
def test_freq_Stiffener2D():
print('Testing frequency analysis for StiffPanelBay with a 2D Stiffener')
spb = StiffPanelBay()
spb.a = 1.
spb.b = 0.5
spb.stack = [0, 90, 90, 0]
spb.plyt = 1e-3*0.125
spb.laminaprop = (142.5e9, 8.7e9, 0.28, 5.1e9, 5.1e9, 5.1e9)
spb.model = 'plate_clt_donnell_bardell'
spb.mu = 1.3e3
spb.m = 11
spb.n = 12
spb.add_panel(y1=0, y2=spb.b/2., plyt=spb.plyt)
spb.add_panel(y1=spb.b/2., y2=spb.b, plyt=spb.plyt)
spb.add_bladestiff2d(ys=spb.b/2., m1=14, n1=11, bf=0.08,
fstack=[0, 90, 90, 0]*5, fplyt=spb.plyt,
flaminaprop=spb.laminaprop)
k0 = spb.calc_k0(silent=True)
M = spb.calc_kM(silent=True)
eigvals, eigvecs = freq(k0, M, silent=True)
assert np.isclose(eigvals[0].real, 137.97927190657148, atol=0.01, rtol=0)
def test_freq_Stiffener1D():
print('Testing frequency analysis for StiffPanelBay with a 1D Stiffener')
spb = StiffPanelBay()
spb.a = 2.
spb.b = 0.5
spb.stack = [0, 90, 90, 0]
spb.plyt = 1e-3 * 0.125
spb.laminaprop = (142.5e9, 8.7e9, 0.28, 5.1e9, 5.1e9, 5.1e9)
spb.model = 'plate_clt_donnell_bardell'
spb.mu = 1.3e3
spb.m = 15
spb.n = 16
spb.add_panel(y1=0, y2=spb.b / 2., plyt=spb.plyt)
spb.add_panel(y1=spb.b / 2., y2=spb.b, plyt=spb.plyt)
spb.add_bladestiff1d(ys=spb.b / 2.,
Fx=0.,
bf=0.08,
fstack=[0, 90, 90, 0] * 5,
fplyt=spb.plyt,
flaminaprop=spb.laminaprop)
k0 = spb.calc_k0(silent=True)
M = spb.calc_kM(silent=True)
eigvals, eigvecs = freq(k0, M, silent=True, num_eigvalues=10)
assert np.isclose(eigvals[0].real, 79.5906673583, atol=0.1, rtol=0)
def test_lb_Stiffener2D():
print('Testing linear buckling for StiffPanelBay with a 2D Stiffener')
spb = StiffPanelBay()
spb.a = 1.
spb.b = 0.5
spb.stack = [0, 90, 90, 0]
spb.plyt = 1e-3*0.125
spb.laminaprop = (142.5e9, 8.7e9, 0.28, 5.1e9, 5.1e9, 5.1e9)
spb.model = 'plate_clt_donnell_bardell'
spb.mu = 1.3e3
spb.m = 15
spb.n = 16
spb.add_panel(y1=0, y2=spb.b/2., plyt=spb.plyt, Nxx=-1.)
spb.add_panel(y1=spb.b/2., y2=spb.b, plyt=spb.plyt, Nxx_cte=1000.)
spb.add_bladestiff2d(ys=spb.b/2., m1=14, n1=11, bf=0.05,
fstack=[0, 90, 90, 0],
fplyt=spb.plyt, flaminaprop=spb.laminaprop)
k0 = spb.calc_k0(silent=True)
kG = spb.calc_kG0(silent=True)
eigvals, eigvecs = lb(k0, kG, silent=True)
assert np.isclose(eigvals[0].real, 301.0825234, atol=0.1, rtol=0)
def test_dynamic_with_TStiff2D():
print('Testing dynamic analysis with TStiff2D')
spb = StiffPanelBay()
spb.a = 2.
spb.b = 1.
spb.stack = [0, 90, 90, 0]
spb.plyt = 1e-3 * 0.125
spb.laminaprop = (142.5e9, 8.7e9, 0.28, 5.1e9, 5.1e9, 5.1e9)
spb.model = 'plate_clt_donnell_bardell'
spb.m = 12
spb.n = 13
spb.mu = 1.3e3
spb.add_panel(y1=0, y2=spb.b / 2., plyt=spb.plyt)
spb.add_panel(y1=spb.b / 2., y2=spb.b, plyt=spb.plyt)
bb = spb.b / 5.
bf = bb
stiff = spb.add_tstiff2d(ys=spb.b / 2.,
bf=bf,
bb=bb,
fstack=[0, 90, 90, 0] * 2,
fplyt=spb.plyt * 1.,
flaminaprop=spb.laminaprop,
bstack=[0, 90, 90, 0] * 1,
bplyt=spb.plyt * 1.,
blaminaprop=spb.laminaprop,
mb=12,
nb=13,
mf=12,
nf=13)
k0 = spb.calc_k0()
M = spb.calc_kM()
eigvals, eigvecs = freq(k0, M, silent=True)
def test_dynamic_with_BladeStiff2D():
print('Testing dynamic analysis with TStiff2D')
spb = StiffPanelBay()
spb.a = 2.
spb.b = 1.
spb.stack = [0, 90, 90, 0]
spb.plyt = 1e-3*0.125
spb.laminaprop = (142.5e9, 8.7e9, 0.28, 5.1e9, 5.1e9, 5.1e9)
spb.model = 'plate_clt_donnell_bardell'
spb.m = 10
spb.n = 10
spb.mu = 1.3e3
spb.add_panel(y1=0, y2=spb.b/2., plyt=spb.plyt)
spb.add_panel(y1=spb.b/2., y2=spb.b, plyt=spb.plyt)
bb = spb.b/5.
bf = bb
stiff = spb.add_bladestiff2d(ys=spb.b/2., bf=bf, bb=bb,
fstack=[0, 90, 90, 0]*2,
fplyt=spb.plyt*1., flaminaprop=spb.laminaprop,
bstack=[0, 90, 90, 0]*1,
bplyt=spb.plyt*1., blaminaprop=spb.laminaprop,
mf=10, nf=10)
k0 = spb.calc_k0()
M = spb.calc_kM()
eigvals, eigvecs = freq(k0, M, silent=True)
spb.plot_skin(eigvecs[:, 0], filename='tmp_test_bladestiff2d_dynamic_skin.png',
colorbar=True)
spb.plot_stiffener(eigvecs[:, 0], si=0, region='flange',
filename='tmp_test_bladestiff2d_dynamic_stiff_flange.png', colorbar=True)
assert np.isclose(eigvals[0], 25.865835238236173, atol=0.01, rtol=0.001)
def test_static_with_BladeStiff2D():
print('Testing linear statics with BladeStiff2D')
spb = StiffPanelBay()
spb.a = 2.
spb.b = 1.
spb.m = 12
spb.n = 13
spb.stack = [0, +45, -45, 90, -45, +45, 0]
spb.plyt = 1e-3 * 0.125
spb.laminaprop = (142.5e9, 8.7e9, 0.28, 5.1e9, 5.1e9, 5.1e9)
spb.add_panel(y1=0, y2=spb.b / 2., plyt=spb.plyt)
spb.add_panel(y1=spb.b / 2., y2=spb.b, plyt=spb.plyt)
bb = spb.b / 5.
bf = bb
stiff = spb.add_bladestiff2d(ys=spb.b / 2.,
bf=bf,
bb=bb,
fstack=[0, 90, 90, 0] * 8,
fplyt=spb.plyt * 1.,
flaminaprop=spb.laminaprop,
bstack=[0, 90, 90, 0] * 4,
bplyt=spb.plyt * 1.,
blaminaprop=spb.laminaprop,
mf=17,
nf=16)
stiff.flange.forces.append(
[stiff.flange.a / 2., stiff.flange.b, 0., 0., 1000.])
spb.calc_k0()
fext = spb.calc_fext()
inc, cs = static(spb.k0, fext, silent=True)
wpanelmin = spb.uvw_skin(cs[0])[2].min()
#NOTE repeated call on purpose to evaluate if cs[0] is being messed up
# somewhere
wpanelmin = spb.uvw_skin(cs[0])[2].min()
wflangemax = spb.uvw_stiffener(cs[0], 0, region='flange')[2].max()
#NOTE repeated call on purpose
wflangemax = spb.uvw_stiffener(cs[0], 0, region='flange')[2].max()
assert np.isclose(wpanelmin, -0.30581458201781481, atol=1.e-4, rtol=0.001)
assert np.isclose(wflangemax, 0.331155797371884, atol=1.e-4, rtol=0.001)
spb.plot_skin(cs[0],
filename='tmp_test_bladestiff2d_static_skin.png',
colorbar=True,
vec='w',
clean=False)
spb.plot_stiffener(
cs[0],
si=0,
region='flange',
filename='tmp_test_bladestiff2d_stiff_static_flange.png',
colorbar=True,
clean=False)
def test_bladestiff2d_lb():
print('Testing linear buckling with BladeStiff2D')
spb = StiffPanelBay()
spb.a = 2.
spb.b = 1.
spb.stack = [0, +45, -45, 90, -45, +45]
spb.plyt = 1e-3 * 0.125
spb.laminaprop = (142.5e9, 8.7e9, 0.28, 5.1e9, 5.1e9, 5.1e9)
spb.model = 'plate_clt_donnell_bardell'
spb.m = 17
spb.n = 16
Nxx = -50.
spb.add_panel(y1=0, y2=spb.b / 2., plyt=spb.plyt, Nxx=Nxx)
spb.add_panel(y1=spb.b / 2., y2=spb.b, plyt=spb.plyt, Nxx=Nxx)
bb = spb.b / 5.
bf = bb
stiff = spb.add_bladestiff2d(ys=spb.b / 2.,
bf=bf,
bb=bb,
fstack=[0, 90, 90, 0] * 8,
fplyt=spb.plyt * 1.,
flaminaprop=spb.laminaprop,
bstack=[0, 90, 90, 0] * 4,
bplyt=spb.plyt * 1.,
blaminaprop=spb.laminaprop,
mf=17,
nf=16)
spb.calc_k0()
spb.calc_kG0()
eigvals, eigvecs = lb(spb.k0, spb.kG0, silent=True)
spb.plot_skin(eigvecs[:, 0],
filename='tmp_test_bladestiff2d_lb_skin.png',
colorbar=True)
spb.plot_stiffener(eigvecs[:, 0],
si=0,
region='flange',
filename='tmp_test_bladestiff2d_lb_stiff_flange.png',
colorbar=True)
calc = eigvals[0] * Nxx
spb.plot_skin(eigvecs[:, 0],
filename='tmp_test_bladestiff2d_lb_skin.png',
colorbar=True,
vec='w',
clean=False)
assert np.isclose(calc, -759.05689868085778, atol=0.0001, rtol=0.001)
def test_Lee_and_Lee_table4():
print('Testing Lee and Lee Table 4')
# Lee and Lee. "Vibration analysis of anisotropic plates with eccentric
# stiffeners". Computers & Structures, Vol. 57, No. 1, pp. 99-105,
# 1995.
models = (('model4', 0.00208, 0.0060, 138.99917796302756),
('model5', 0.00260, 0.0075,
175.00597239286196), ('model7', 0.00364, 0.0105, 205.433509024))
for model, hf, bf, value in models:
spb = StiffPanelBay()
spb.model = 'plate_clt_donnell_bardell'
spb.mu = 1.500e3 # plate material density in kg / m^3
spb.laminaprop = (128.e9, 11.e9, 0.25, 4.48e9, 1.53e9, 1.53e9)
spb.stack = [0, -45, +45, 90, 90, +45, -45, 0]
plyt = 0.00013
spb.plyt = plyt
spb.a = 0.5
spb.b = 0.250
spb.m = 14
spb.n = 15
hf = hf
bf = bf
n = int(hf / plyt)
fstack = [0] * (n // 4) + [90] * (n // 4) + [90] * (n //
4) + [0] * (n // 4)
# clamping
spb.w1rx = 0.
spb.w2rx = 0.
spb.w1ry = 0.
spb.w2ry = 0.
spb.add_panel(y1=0, y2=spb.b / 2.)
spb.add_panel(y1=spb.b / 2., y2=spb.b)
spb.add_bladestiff1d(mu=spb.mu,
ys=spb.b / 2.,
bb=0.,
bf=bf,
fstack=fstack,
fplyt=plyt,
flaminaprop=spb.laminaprop)
k0 = spb.calc_k0(silent=True)
M = spb.calc_kM(silent=True)
eigvals, eigvecs = freq(k0, M, silent=True)
herz = eigvals[0].real / 2 / np.pi
assert np.isclose(herz, value, atol=0.001, rtol=0.001)
def test_tstiff2d_lb():
#NOTE reference values taken from
# compmech.panel.assembly.tstiff2d_1stiff_compression
a_b_list = [0.5, 2., 10.]
ref_values = [-152.607275551, -80.15391295315146, -79.39137361313862]
for a_b, ref_value in zip(a_b_list, ref_values):
print('Testing linear buckling')
spb = StiffPanelBay()
spb.b = 1.
spb.a = spb.b * a_b
spb.stack = [0, +45, -45, 90, -45, +45]
spb.plyt = 1e-3 * 0.125
spb.laminaprop = (142.5e9, 8.7e9, 0.28, 5.1e9, 5.1e9, 5.1e9)
spb.model = 'plate_clt_donnell_bardell'
spb.m = 12
spb.n = 13
Nxx = -10.
spb.add_panel(y1=0, y2=spb.b / 2., plyt=spb.plyt, Nxx=Nxx)
spb.add_panel(y1=spb.b / 2., y2=spb.b, plyt=spb.plyt, Nxx=Nxx)
bb = spb.b / 5.
if False:
stiff = spb.add_tstiff2d(ys=spb.b / 2.,
bf=bb / 2,
bb=bb,
fstack=[0, 90, 90, 0] * 8,
fplyt=spb.plyt * 1.,
flaminaprop=spb.laminaprop,
bstack=[0, 90, 90, 0] * 4,
bplyt=spb.plyt * 1.,
blaminaprop=spb.laminaprop,
mb=13,
nb=12,
mf=13,
nf=12,
Nxxf=Nxx)
spb.calc_k0()
spb.calc_kG0()
eigvals, eigvecs = lb(spb.k0, spb.kG0, silent=True)
calc = eigvals[0] * Nxx
assert np.isclose(calc, ref_value, rtol=0.05)
def test_dynamic_with_BladeStiff2D():
print('Testing dynamic analysis with TStiff2D')
spb = StiffPanelBay()
spb.a = 2.
spb.b = 1.
spb.stack = [0, 90, 90, 0]
spb.plyt = 1e-3 * 0.125
spb.laminaprop = (142.5e9, 8.7e9, 0.28, 5.1e9, 5.1e9, 5.1e9)
spb.model = 'plate_clt_donnell_bardell'
spb.m = 10
spb.n = 10
spb.mu = 1.3e3
spb.add_panel(y1=0, y2=spb.b / 2., plyt=spb.plyt)
spb.add_panel(y1=spb.b / 2., y2=spb.b, plyt=spb.plyt)
bb = spb.b / 5.
bf = bb
stiff = spb.add_bladestiff2d(ys=spb.b / 2.,
bf=bf,
bb=bb,
fstack=[0, 90, 90, 0] * 2,
fplyt=spb.plyt * 1.,
flaminaprop=spb.laminaprop,
bstack=[0, 90, 90, 0] * 1,
bplyt=spb.plyt * 1.,
blaminaprop=spb.laminaprop,
mf=10,
nf=10)
k0 = spb.calc_k0()
M = spb.calc_kM()
eigvals, eigvecs = freq(k0, M, silent=True)
spb.plot_skin(eigvecs[:, 0],
filename='tmp_test_bladestiff2d_dynamic_skin.png',
colorbar=True)
spb.plot_stiffener(
eigvecs[:, 0],
si=0,
region='flange',
filename='tmp_test_bladestiff2d_dynamic_stiff_flange.png',
colorbar=True)
assert np.isclose(eigvals[0], 25.865835238236173, atol=0.01, rtol=0.001)
def test_freq_models():
print('Testing frequency analysis for StiffPanelBay with 2 plates')
# From Table 4 of
# Lee and Lee. "Vibration analysis of anisotropic plates with eccentric
# stiffeners". Computers & Structures, Vol. 57, No. 1, pp. 99-105,
# 1995.
for model in [
'plate_clt_donnell_bardell', 'cpanel_clt_donnell_bardell',
'kpanel_clt_donnell_bardell'
]:
spb = StiffPanelBay()
spb.a = 0.5
spb.b = 0.250
spb.plyt = 0.00013
spb.laminaprop = (128.e9, 11.e9, 0.25, 4.48e9, 1.53e9, 1.53e9)
spb.stack = [0, -45, +45, 90, 90, +45, -45, 0]
spb.model = model
spb.r = 1.e6
spb.alphadeg = 0.
spb.mu = 1.5e3
spb.m = 9
spb.n = 10
# clamping
spb.w1rx = 0.
spb.w2rx = 0.
spb.w1ry = 0.
spb.w2ry = 0.
spb.add_panel(0, spb.b / 2., plyt=spb.plyt)
spb.add_panel(spb.b / 2., spb.b, plyt=spb.plyt)
k0 = spb.calc_k0(silent=True)
M = spb.calc_kM(silent=True)
eigvals, eigvecs = freq(k0, M, silent=True)
ref = [
85.12907802 - 0.j, 134.16422850 - 0.j, 206.77295186 - 0.j,
216.45992453 - 0.j, 252.24546171 - 0.j
]
assert np.allclose(eigvals[:5] / 2 / np.pi, ref, atol=0.1, rtol=0)
def test_static_with_BladeStiff2D():
print('Testing linear statics with BladeStiff2D')
spb = StiffPanelBay()
spb.a = 2.
spb.b = 1.
spb.m = 12
spb.n = 13
spb.stack = [0, +45, -45, 90, -45, +45, 0]
spb.plyt = 1e-3*0.125
spb.laminaprop = (142.5e9, 8.7e9, 0.28, 5.1e9, 5.1e9, 5.1e9)
spb.add_panel(y1=0, y2=spb.b/2., plyt=spb.plyt)
spb.add_panel(y1=spb.b/2., y2=spb.b, plyt=spb.plyt)
bb = spb.b/5.
bf = bb
stiff = spb.add_bladestiff2d(ys=spb.b/2., bf=bf, bb=bb,
fstack=[0, 90, 90, 0]*8,
fplyt=spb.plyt*1., flaminaprop=spb.laminaprop,
bstack=[0, 90, 90, 0]*4,
bplyt=spb.plyt*1., blaminaprop=spb.laminaprop,
mf=17, nf=16)
stiff.flange.forces.append([stiff.flange.a/2., stiff.flange.b, 0., 0., 1000.])
spb.calc_k0()
fext = spb.calc_fext()
inc, cs = static(spb.k0, fext, silent=True)
wpanelmin = spb.uvw_skin(cs[0])[2].min()
#NOTE repeated call on purpose to evaluate if cs[0] is being messed up
# somewhere
wpanelmin = spb.uvw_skin(cs[0])[2].min()
wflangemax = spb.uvw_stiffener(cs[0], 0, region='flange')[2].max()
#NOTE repeated call on purpose
wflangemax = spb.uvw_stiffener(cs[0], 0, region='flange')[2].max()
assert np.isclose(wpanelmin, -0.30581458201781481, atol=1.e-4, rtol=0.001)
assert np.isclose(wflangemax, 0.331155797371884, atol=1.e-4, rtol=0.001)
spb.plot_skin(cs[0], filename='tmp_test_bladestiff2d_static_skin.png', colorbar=True, vec='w', clean=False)
spb.plot_stiffener(cs[0], si=0, region='flange',
filename='tmp_test_bladestiff2d_stiff_static_flange.png', colorbar=True, clean=False)
def test_static_with_TStiff2D():
print('Testing static analysis with TStiff2D')
spb = StiffPanelBay()
spb.a = 2.
spb.b = 1.
spb.stack = [0, +45, -45, 90, -45, +45, 0]
spb.plyt = 1e-3*0.125
spb.laminaprop = (142.5e9, 8.7e9, 0.28, 5.1e9, 5.1e9, 5.1e9)
spb.model = 'plate_clt_donnell_bardell'
spb.m = 12
spb.n = 13
spb.add_panel(y1=0, y2=spb.b/2., plyt=spb.plyt)
spb.add_panel(y1=spb.b/2., y2=spb.b, plyt=spb.plyt)
bb = spb.b/5.
bf = bb
stiff = spb.add_tstiff2d(ys=spb.b/2., bf=bf, bb=bb,
fstack=[0, 90, 90, 0]*8,
fplyt=spb.plyt*1., flaminaprop=spb.laminaprop,
bstack=[0, 90, 90, 0]*4,
bplyt=spb.plyt*1., blaminaprop=spb.laminaprop,
mb=14, nb=13, mf=13, nf=12)
stiff.flange.forces.append([spb.a/2., bf, 0., 0., 1000.])
k0 = spb.calc_k0()
fext = spb.calc_fext()
inc, cs = static(spb.k0, fext, silent=True)
wpanelmin = spb.uvw_skin(cs[0])[2].min()
wbasemin = spb.uvw_stiffener(cs[0], 0, region='base')[2].min()
wflangemax = spb.uvw_stiffener(cs[0], 0, region='flange')[2].max()
spb.plot_skin(cs[0], filename='tmp_test_tstiff2d_static_skin.png',
colorbar=True, vec='w', clean=False)
spb.plot_stiffener(cs[0], si=0, region='base',
filename='tmp_test_tstiff2d_static_stiff_base.png', colorbar=True,
vec='w', clean=False)
spb.plot_stiffener(cs[0], si=0, region='flange',
filename='tmp_test_tstiff2d_static_stiff_flange.png', colorbar=True,
clean=False)
def test_Lee_and_Lee_table4():
print('Testing Lee and Lee Table 4')
# Lee and Lee. "Vibration analysis of anisotropic plates with eccentric
# stiffeners". Computers & Structures, Vol. 57, No. 1, pp. 99-105,
# 1995.
models = (
('model4', 0.00208, 0.0060, 138.99917796302756),
('model5', 0.00260, 0.0075, 175.00597239286196),
('model7', 0.00364, 0.0105, 205.433509024))
for model, hf, bf, value in models:
spb = StiffPanelBay()
spb.model = 'plate_clt_donnell_bardell'
spb.mu = 1.500e3 # plate material density in kg / m^3
spb.laminaprop = (128.e9, 11.e9, 0.25, 4.48e9, 1.53e9, 1.53e9)
spb.stack = [0, -45, +45, 90, 90, +45, -45, 0]
plyt = 0.00013
spb.plyt = plyt
spb.a = 0.5
spb.b = 0.250
spb.m = 14
spb.n = 15
hf = hf
bf = bf
n = int(hf/plyt)
fstack = [0]*(n//4) + [90]*(n//4) + [90]*(n//4) + [0]*(n//4)
# clamping
spb.w1rx = 0.
spb.w2rx = 0.
spb.w1ry = 0.
spb.w2ry = 0.
spb.add_panel(y1=0, y2=spb.b/2.)
spb.add_panel(y1=spb.b/2., y2=spb.b)
spb.add_bladestiff1d(mu=spb.mu, ys=spb.b/2., bb=0., bf=bf,
fstack=fstack, fplyt=plyt, flaminaprop=spb.laminaprop)
k0 = spb.calc_k0(silent=True)
M = spb.calc_kM(silent=True)
eigvals, eigvecs = freq(k0, M, silent=True)
herz = eigvals[0].real/2/np.pi
assert np.isclose(herz, value, atol=0.001, rtol=0.001)
def test_lb_Stiffener1D():
print('Testing linear buckling for StiffPanelBay with a 1D Stiffener')
spb = StiffPanelBay()
spb.a = 1.
spb.b = 0.5
spb.stack = [0, 90, 90, 0]
spb.plyt = 1e-3*0.125
spb.laminaprop = (142.5e9, 8.7e9, 0.28, 5.1e9, 5.1e9, 5.1e9)
spb.model = 'plate_clt_donnell_bardell'
spb.mu = 1.3e3
spb.m = 15
spb.n = 16
spb.add_panel(y1=0, y2=spb.b/2., plyt=spb.plyt, Nxx=-1.)
spb.add_panel(y1=spb.b/2., y2=spb.b, plyt=spb.plyt, Nxx_cte=1000.)
spb.add_bladestiff1d(ys=spb.b/2., Fx=0., bf=0.05, fstack=[0, 90, 90, 0],
fplyt=spb.plyt, flaminaprop=spb.laminaprop)
spb.lb(silent=True)
assert np.isclose(spb.eigvals[0].real, 297.54633249887456)
def test_freq_Stiffener1D():
print('Testing frequency analysis for StiffPanelBay with a 1D Stiffener')
spb = StiffPanelBay()
spb.a = 1.
spb.b = 0.5
spb.stack = [0, 90, 90, 0]
spb.plyt = 1e-3*0.125
spb.laminaprop = (142.5e9, 8.7e9, 0.28, 5.1e9, 5.1e9, 5.1e9)
spb.model = 'plate_clt_donnell_bardell'
spb.mu = 1.3e3
spb.m = 15
spb.n = 16
spb.add_panel(y1=0, y2=spb.b/2., plyt=spb.plyt)
spb.add_panel(y1=spb.b/2., y2=spb.b, plyt=spb.plyt)
spb.add_bladestiff1d(ys=spb.b/2., Fx=0., bf=0.08, fstack=[0, 90, 90, 0]*5,
fplyt=spb.plyt, flaminaprop=spb.laminaprop)
spb.freq(silent=True, atype=4)
assert np.isclose(spb.eigvals[0].real, 81.9342050889)
def test_freq_models():
print('Testing frequency analysis for StiffPanelBay with 2 plates')
# From Table 4 of
# Lee and Lee. "Vibration analysis of anisotropic plates with eccentric
# stiffeners". Computers & Structures, Vol. 57, No. 1, pp. 99-105,
# 1995.
for model in ['plate_clt_donnell_bardell',
'cpanel_clt_donnell_bardell',
'kpanel_clt_donnell_bardell']:
spb = StiffPanelBay()
spb.a = 0.5
spb.b = 0.250
spb.plyt = 0.00013
spb.laminaprop = (128.e9, 11.e9, 0.25, 4.48e9, 1.53e9, 1.53e9)
spb.stack = [0, -45, +45, 90, 90, +45, -45, 0]
spb.model = model
spb.r = 1.e6
spb.alphadeg = 0.
spb.mu = 1.5e3
spb.m = 9
spb.n = 10
# clamping
spb.w1rx = 0.
spb.w2rx = 0.
spb.w1ry = 0.
spb.w2ry = 0.
spb.add_panel(0, spb.b/2., plyt=spb.plyt)
spb.add_panel(spb.b/2., spb.b, plyt=spb.plyt)
k0 = spb.calc_k0(silent=True)
M = spb.calc_kM(silent=True)
eigvals, eigvecs = freq(k0, M, silent=True)
ref = [85.12907802-0.j, 134.16422850-0.j, 206.77295186-0.j,
216.45992453-0.j, 252.24546171-0.j]
assert np.allclose(eigvals[:5]/2/np.pi, ref, atol=0.1, rtol=0)
def test_Lee_and_Lee_table4():
print('Testing Lee and Lee Table 4')
# Lee and Lee. "Vibration analysis of anisotropic plates with eccentric
# stiffeners". Computers & Structures, Vol. 57, No. 1, pp. 99-105,
# 1995.
models = (
('model4', 0.00208, 0.0060, 138.801067988),
('model5', 0.00260, 0.0075, 174.624343202),
('model7', 0.00364, 0.0105, 205.433509024))
for model, hf, bf, value in models:
spb = StiffPanelBay()
spb.model = 'plate_clt_donnell_bardell'
spb.mu = 1.500e3 # plate material density in kg / m^3
spb.laminaprop = (128.e9, 11.e9, 0.25, 4.48e9, 1.53e9, 1.53e9)
spb.stack = [0, -45, +45, 90, 90, +45, -45, 0]
plyt = 0.00013
spb.plyt = plyt
spb.a = 0.5
spb.b = 0.250
spb.m = 14
spb.n = 15
hf = hf
bf = bf
n = int(hf/plyt)
fstack = [0]*(n//4) + [90]*(n//4) + [90]*(n//4) + [0]*(n//4)
# clamping
spb.w1rx = 0.
spb.w2rx = 0.
spb.w1ry = 0.
spb.w2ry = 0.
spb.add_panel(y1=0, y2=spb.b/2.)
spb.add_panel(y1=spb.b/2., y2=spb.b)
spb.add_bladestiff1d(mu=spb.mu, ys=spb.b/2., bb=0., bf=bf,
fstack=fstack, fplyt=plyt, flaminaprop=spb.laminaprop)
spb.freq(atype=4, silent=True, reduced_dof=False)
assert np.isclose(spb.eigvals[0].real/2/np.pi, value)
def test_tstiff2d_lb():
#NOTE reference values taken from
# compmech.panel.assembly.tstiff2d_1stiff_compression
a_b_list = [0.5, 2., 10.]
ref_values = [-152.607275551, -80.15391295315146, -79.39137361313862]
for a_b, ref_value in zip(a_b_list, ref_values):
print('Testing linear buckling')
spb = StiffPanelBay()
spb.b = 1.
spb.a = spb.b * a_b
spb.stack = [0, +45, -45, 90, -45, +45]
spb.plyt = 1e-3*0.125
spb.laminaprop = (142.5e9, 8.7e9, 0.28, 5.1e9, 5.1e9, 5.1e9)
spb.model = 'plate_clt_donnell_bardell'
spb.m = 12
spb.n = 13
Nxx = -10.
spb.add_panel(y1=0, y2=spb.b/2., plyt=spb.plyt, Nxx=Nxx)
spb.add_panel(y1=spb.b/2., y2=spb.b, plyt=spb.plyt, Nxx=Nxx)
bb = spb.b/5.
if False:
stiff = spb.add_tstiff2d(ys=spb.b/2., bf=bb/2, bb=bb,
fstack=[0, 90, 90, 0]*8,
fplyt=spb.plyt*1., flaminaprop=spb.laminaprop,
bstack=[0, 90, 90, 0]*4,
bplyt=spb.plyt*1., blaminaprop=spb.laminaprop,
mb=13, nb=12, mf=13, nf=12, Nxxf=Nxx)
spb.calc_k0()
spb.calc_kG0()
eigvals, eigvecs = lb(spb.k0, spb.kG0, silent=True)
calc = eigvals[0]*Nxx
assert np.isclose(calc, ref_value, rtol=0.05)
def test_freq_Stiffener1D():
print('Testing frequency analysis for StiffPanelBay with a 1D Stiffener')
spb = StiffPanelBay()
spb.a = 2.
spb.b = 0.5
spb.stack = [0, 90, 90, 0]
spb.plyt = 1e-3*0.125
spb.laminaprop = (142.5e9, 8.7e9, 0.28, 5.1e9, 5.1e9, 5.1e9)
spb.model = 'plate_clt_donnell_bardell'
spb.mu = 1.3e3
spb.m = 15
spb.n = 16
spb.add_panel(y1=0, y2=spb.b/2., plyt=spb.plyt)
spb.add_panel(y1=spb.b/2., y2=spb.b, plyt=spb.plyt)
spb.add_bladestiff1d(ys=spb.b/2., Fx=0., bf=0.08, fstack=[0, 90, 90, 0]*5,
fplyt=spb.plyt, flaminaprop=spb.laminaprop)
k0 = spb.calc_k0(silent=True)
M = spb.calc_kM(silent=True)
eigvals, eigvecs = freq(k0, M, silent=True, num_eigvalues=10)
assert np.isclose(eigvals[0].real, 79.5906673583, atol=0.1, rtol=0)
from compmech.stiffpanelbay import StiffPanelBay
spb = StiffPanelBay()
spb.a = 2.
spb.b = 1.
spb.r = 10.
spb.stack = [0, 90, 90, 0, -45, +45]
spb.plyt = 1e-3*0.125
spb.laminaprop = (142.5e9, 8.7e9, 0.28, 5.1e9, 5.1e9, 5.1e9)
spb.model = 'cpanel_clt_donnell_bardell'
spb.mu = 1.3e3
spb.m = 13
spb.n = 14
spb.add_panel(y1=0, y2=spb.b/3., plyt=spb.plyt, Nxx=-100.)
spb.add_panel(y1=spb.b/3., y2=2*spb.b/3., plyt=spb.plyt, Nxx=-100.)
spb.add_panel(y1=2*spb.b/3., y2=spb.b, plyt=spb.plyt, Nxx=-100.)
spb.add_bladestiff1d(ys=spb.b/3., Fx=-100., bf=0.05,
fstack=[0, 90, 90, 0]*4, fplyt=spb.plyt,
flaminaprop=spb.laminaprop)
spb.add_bladestiff1d(ys=2*spb.b/3., Fx=-100., bf=0.05,
fstack=[0, 90, 90, 0]*4, fplyt=spb.plyt,
flaminaprop=spb.laminaprop)
spb.lb(silent=False)
print 'Fx', spb.bladestiff1ds[0].Fx
print 'ys', spb.bladestiff1ds[0].ys
print 'bf', spb.bladestiff1ds[0].bf
print 'df', spb.bladestiff1ds[0].df
from compmech.stiffpanelbay import StiffPanelBay spb = StiffPanelBay() spb.a = 2. spb.b = 1. spb.r = 2. spb.stack = [0] spb.plyt = 1e-3*1.6 E = 71.e9 nu = 0.33 G = E/(2.*(1. + nu)) spb.laminaprop = (E, E, nu, G, G, G) spb.model = 'cpanel_clt_donnell_bardell' spb.m = 22 spb.n = 22 spb.u1tx = 0. spb.u1rx = 1. spb.u2tx = 0. spb.u2rx = 1. spb.u1ty = 0. spb.u1ry = 1. spb.u2ty = 0. spb.u2ry = 1. spb.v1tx = 0. spb.v1rx = 1. spb.v2tx = 0. spb.v2rx = 1. spb.v1ty = 0. spb.v1ry = 1. spb.v2ty = 0.
from compmech.stiffpanelbay import StiffPanelBay spb = StiffPanelBay() spb.a = 2. spb.b = 1. spb.r = 2. spb.stack = [0, 90, 90, 0, -45, +45] spb.plyt = 1e-3*0.125 spb.laminaprop = (142.5e9, 8.7e9, 0.28, 5.1e9, 5.1e9, 5.1e9) spb.model = 'cpanel_clt_donnell_bardell' spb.m = 15 spb.n = 16 spb.u1tx = 0. spb.u1rx = 1. spb.u2tx = 0. spb.u2rx = 1. spb.u1ty = 0. spb.u1ry = 1. spb.u2ty = 0. spb.u2ry = 1. spb.v1tx = 0. spb.v1rx = 1. spb.v2tx = 0. spb.v2rx = 1. spb.v1ty = 0. spb.v1ry = 1. spb.v2ty = 0. spb.v2ry = 1. spb.w1tx = 0. spb.w1rx = 1.