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_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 tstiff2d_1stiff_flutter(a, b, ys, bb, bf, defect_a, mu, plyt, laminaprop, stack_skin, stack_base, stack_flange, air_speed=None, rho_air=None, Mach=None, speed_sound=None, flow='x', Nxx_skin=None, Nxx_base=None, Nxx_flange=None, run_static_case=True, r=None, m=8, n=8, mb=None, nb=None, mf=None, nf=None): r"""Flutter of T-Stiffened Panel with possible defect at middle For more details about each parameter and the aerodynamic formulation see Ref. [castro2016FlutterPanel]_ . The panel assembly looks like:: skin _________ _____ _________ | | | | | | | | | p01 | p02 | p03 | | | | | |_________|_____|_________| | p04 | p05 | p06 | /\ x |_________|_____|_________| | | | | | | | | | | | | p07 | p08 | p09 | | | | | | | | | |_________|_____|_________| loaded edge base flange _____ _____ | | | | | | | | | p10 | | p11 | | | | | |_____| |_____| | p12 | | p13 | |_____| |_____| | | | | | | | | | p14 | | p15 | | | | | | | | | |_____| |_____| loaded edge loaded edge Parameters ---------- a : float Total length of the assembly (along `x`). b : float Total width of the assembly (along `y`). ys : float Position of the stiffener along `y`. bb : float Stiffener's base width. bf : float Stiffener's flange width. defect_a : float Debonding defect/assembly length ratio. mu : float Material density. plyt : float Ply thickness. laminaprop : list or tuple Orthotropic lamina properties: `E_1, E_2, \nu_{12}, G_{12}, G_{13}, G_{23}`. stack_skin : list or tuple Stacking sequence for the skin. stack_base : list or tuple Stacking sequence for the stiffener's base. stack_flange : list or tuple Stacking sequence for the stiffener's flange. air_speed : float Airflow speed. rho_air : float Air density. Mach : float Mach number. speed_sound : float Speed of sound. flow : "x" or "y" Direction of airflow. Nxx_skin : float Skin load distributed at the assembly edge at `x=0`. Nxx_base : float Stiffener's base load distributed at the assembly edge at `x=0`. Nxx_flange : float Stiffener's flange load distributed at the assembly edge at `x=0`. run_static_case : bool, optional If True a static analysis is run before the linear buckling analysis to compute the real membrane stress state along the domain, otherwise it is assumed constant values of `N_{xx}` for all components. r : float or None, optional Radius of the stiffened panel. m, n : int, optional Number of terms of the approximation function for the skin. mb, nb : int, optional Number of terms of the approximation function for the stiffener's base. mf, nf : int, optional Number of terms of the approximation function for the stiffener's flange. Examples -------- The following example is one of the test cases: .. literalinclude:: ../../../../../compmech/panel/assembly/tests/test_tstiff2d_assembly.py :pyobject: test_tstiff2d_1stiff_flutter """ defect = defect_a * a has_defect = True if defect > 0 else False defect = 0.33*a if defect == 0 else defect # to avoid weird domains aup = (a - defect)/2. alow = (a - defect)/2. bleft = b - ys - bb/2. bright = ys - bb/2. mb = m if mb is None else mb nb = n if nb is None else nb mf = m if mf is None else mf nf = n if nf is None else nf # skin panels p01 = Panel(group='skin', Nxx=Nxx_skin, x0=alow+defect, y0=ys+bb/2., a=aup, b=bleft, r=r, m=m, n=n, plyt=plyt, stack=stack_skin, laminaprop=laminaprop, mu=mu, rho_air=rho_air, speed_sound=speed_sound, Mach=Mach, V=air_speed, flow=flow) p02 = Panel(group='skin', Nxx=Nxx_skin, x0=alow+defect, y0=ys-bb/2., a=aup, b=bb, r=r, m=m, n=n, plyt=plyt, stack=stack_skin, laminaprop=laminaprop, mu=mu, rho_air=rho_air, speed_sound=speed_sound, Mach=Mach, V=air_speed, flow=flow) p03 = Panel(group='skin', Nxx=Nxx_skin, x0=alow+defect, y0=0, a=aup, b=bright, r=r, m=m, n=n, plyt=plyt, stack=stack_skin, laminaprop=laminaprop, mu=mu, rho_air=rho_air, speed_sound=speed_sound, Mach=Mach, V=air_speed, flow=flow) # defect p04 = Panel(group='skin', Nxx=Nxx_skin, x0=alow, y0=ys+bb/2., a=defect, b=bleft, r=r, m=m, n=n, plyt=plyt, stack=stack_skin, laminaprop=laminaprop, mu=mu, rho_air=rho_air, speed_sound=speed_sound, Mach=Mach, V=air_speed, flow=flow) p05 = Panel(group='skin', Nxx=Nxx_skin, x0=alow, y0=ys-bb/2., a=defect, b=bb, r=r, m=m, n=n, plyt=plyt, stack=stack_skin, laminaprop=laminaprop, mu=mu, rho_air=rho_air, speed_sound=speed_sound, Mach=Mach, V=air_speed, flow=flow) p06 = Panel(group='skin', Nxx=Nxx_skin, x0=alow, y0=0, a=defect, b=bright, r=r, m=m, n=n, plyt=plyt, stack=stack_skin, laminaprop=laminaprop, mu=mu, rho_air=rho_air, speed_sound=speed_sound, Mach=Mach, V=air_speed, flow=flow) # p07 = Panel(group='skin', Nxx=Nxx_skin, x0=0, y0=ys+bb/2., a=alow, b=bleft, r=r, m=m, n=n, plyt=plyt, stack=stack_skin, laminaprop=laminaprop, mu=mu, rho_air=rho_air, speed_sound=speed_sound, Mach=Mach, V=air_speed, flow=flow) p08 = Panel(group='skin', Nxx=Nxx_skin, x0=0, y0=ys-bb/2., a=alow, b=bb, r=r, m=m, n=n, plyt=plyt, stack=stack_skin, laminaprop=laminaprop, mu=mu, rho_air=rho_air, speed_sound=speed_sound, Mach=Mach, V=air_speed, flow=flow) p09 = Panel(group='skin', Nxx=Nxx_skin, x0=0, y0=0, a=alow, b=bright, r=r, m=m, n=n, plyt=plyt, stack=stack_skin, laminaprop=laminaprop, mu=mu, rho_air=rho_air, speed_sound=speed_sound, Mach=Mach, V=air_speed, flow=flow) # stiffeners p10 = Panel(group='base', Nxx=Nxx_base, x0=alow+defect, y0=ys-bb/2., a=aup, b=bb, r=r, m=mb, n=nb, plyt=plyt, stack=stack_base, laminaprop=laminaprop, mu=mu) p11 = Panel(group='flange', Nxx=Nxx_flange, x0=alow+defect, y0=0, a=aup, b=bf, m=mf, n=nf, plyt=plyt, stack=stack_flange, laminaprop=laminaprop, mu=mu) # defect p12 = Panel(group='base', Nxx=Nxx_base, x0=alow, y0=ys-bb/2., a=defect, b=bb, r=r, m=mb, n=nb, plyt=plyt, stack=stack_base, laminaprop=laminaprop, mu=mu) p13 = Panel(group='flange', Nxx=Nxx_flange, x0=alow, y0=0, a=defect, b=bf, m=mf, n=nf, plyt=plyt, stack=stack_flange, laminaprop=laminaprop, mu=mu) # p14 = Panel(group='base', Nxx=Nxx_base, x0=0, y0=ys-bb/2., a=alow, b=bb, r=r, m=mb, n=nb, plyt=plyt, stack=stack_base, laminaprop=laminaprop, mu=mu) p15 = Panel(group='flange', Nxx=Nxx_flange, x0=0, y0=0, a=alow, b=bf, m=mf, n=nf, plyt=plyt, stack=stack_flange, laminaprop=laminaprop, mu=mu) # boundary conditions p01.u1tx = 1 ; p01.u1rx = 1 ; p01.u2tx = 0 ; p01.u2rx = 1 p01.v1tx = 1 ; p01.v1rx = 1 ; p01.v2tx = 0 ; p01.v2rx = 1 p01.w1tx = 1 ; p01.w1rx = 1 ; p01.w2tx = 0 ; p01.w2rx = 1 p01.u1ty = 1 ; p01.u1ry = 1 ; p01.u2ty = 1 ; p01.u2ry = 1 p01.v1ty = 1 ; p01.v1ry = 1 ; p01.v2ty = 0 ; p01.v2ry = 1 p01.w1ty = 1 ; p01.w1ry = 1 ; p01.w2ty = 0 ; p01.w2ry = 1 p02.u1tx = 1 ; p02.u1rx = 1 ; p02.u2tx = 0 ; p02.u2rx = 1 p02.v1tx = 1 ; p02.v1rx = 1 ; p02.v2tx = 0 ; p02.v2rx = 1 p02.w1tx = 1 ; p02.w1rx = 1 ; p02.w2tx = 0 ; p02.w2rx = 1 p02.u1ty = 1 ; p02.u1ry = 1 ; p02.u2ty = 1 ; p02.u2ry = 1 p02.v1ty = 1 ; p02.v1ry = 1 ; p02.v2ty = 1 ; p02.v2ry = 1 p02.w1ty = 1 ; p02.w1ry = 1 ; p02.w2ty = 1 ; p02.w2ry = 1 p03.u1tx = 1 ; p03.u1rx = 1 ; p03.u2tx = 0 ; p03.u2rx = 1 p03.v1tx = 1 ; p03.v1rx = 1 ; p03.v2tx = 0 ; p03.v2rx = 1 p03.w1tx = 1 ; p03.w1rx = 1 ; p03.w2tx = 0 ; p03.w2rx = 1 p03.u1ty = 1 ; p03.u1ry = 1 ; p03.u2ty = 1 ; p03.u2ry = 1 p03.v1ty = 0 ; p03.v1ry = 1 ; p03.v2ty = 1 ; p03.v2ry = 1 p03.w1ty = 0 ; p03.w1ry = 1 ; p03.w2ty = 1 ; p03.w2ry = 1 p04.u1tx = 1 ; p04.u1rx = 1 ; p04.u2tx = 1 ; p04.u2rx = 1 p04.v1tx = 1 ; p04.v1rx = 1 ; p04.v2tx = 1 ; p04.v2rx = 1 p04.w1tx = 1 ; p04.w1rx = 1 ; p04.w2tx = 1 ; p04.w2rx = 1 p04.u1ty = 1 ; p04.u1ry = 1 ; p04.u2ty = 1 ; p04.u2ry = 1 p04.v1ty = 1 ; p04.v1ry = 1 ; p04.v2ty = 0 ; p04.v2ry = 1 p04.w1ty = 1 ; p04.w1ry = 1 ; p04.w2ty = 0 ; p04.w2ry = 1 p05.u1tx = 1 ; p05.u1rx = 1 ; p05.u2tx = 1 ; p05.u2rx = 1 p05.v1tx = 1 ; p05.v1rx = 1 ; p05.v2tx = 1 ; p05.v2rx = 1 p05.w1tx = 1 ; p05.w1rx = 1 ; p05.w2tx = 1 ; p05.w2rx = 1 p05.u1ty = 1 ; p05.u1ry = 1 ; p05.u2ty = 1 ; p05.u2ry = 1 p05.v1ty = 1 ; p05.v1ry = 1 ; p05.v2ty = 1 ; p05.v2ry = 1 p05.w1ty = 1 ; p05.w1ry = 1 ; p05.w2ty = 1 ; p05.w2ry = 1 p06.u1tx = 1 ; p06.u1rx = 1 ; p06.u2tx = 1 ; p06.u2rx = 1 p06.v1tx = 1 ; p06.v1rx = 1 ; p06.v2tx = 1 ; p06.v2rx = 1 p06.w1tx = 1 ; p06.w1rx = 1 ; p06.w2tx = 1 ; p06.w2rx = 1 p06.u1ty = 1 ; p06.u1ry = 1 ; p06.u2ty = 1 ; p06.u2ry = 1 p06.v1ty = 0 ; p06.v1ry = 1 ; p06.v2ty = 1 ; p06.v2ry = 1 p06.w1ty = 0 ; p06.w1ry = 1 ; p06.w2ty = 1 ; p06.w2ry = 1 p07.u1tx = 1 ; p07.u1rx = 1 ; p07.u2tx = 1 ; p07.u2rx = 1 p07.v1tx = 0 ; p07.v1rx = 1 ; p07.v2tx = 1 ; p07.v2rx = 1 p07.w1tx = 0 ; p07.w1rx = 1 ; p07.w2tx = 1 ; p07.w2rx = 1 p07.u1ty = 1 ; p07.u1ry = 1 ; p07.u2ty = 1 ; p07.u2ry = 1 p07.v1ty = 1 ; p07.v1ry = 1 ; p07.v2ty = 0 ; p07.v2ry = 1 p07.w1ty = 1 ; p07.w1ry = 1 ; p07.w2ty = 0 ; p07.w2ry = 1 p08.u1tx = 1 ; p08.u1rx = 1 ; p08.u2tx = 1 ; p08.u2rx = 1 p08.v1tx = 0 ; p08.v1rx = 1 ; p08.v2tx = 1 ; p08.v2rx = 1 p08.w1tx = 0 ; p08.w1rx = 1 ; p08.w2tx = 1 ; p08.w2rx = 1 p08.u1ty = 1 ; p08.u1ry = 1 ; p08.u2ty = 1 ; p08.u2ry = 1 p08.v1ty = 1 ; p08.v1ry = 1 ; p08.v2ty = 1 ; p08.v2ry = 1 p08.w1ty = 1 ; p08.w1ry = 1 ; p08.w2ty = 1 ; p08.w2ry = 1 p09.u1tx = 1 ; p09.u1rx = 1 ; p09.u2tx = 1 ; p09.u2rx = 1 p09.v1tx = 0 ; p09.v1rx = 1 ; p09.v2tx = 1 ; p09.v2rx = 1 p09.w1tx = 0 ; p09.w1rx = 1 ; p09.w2tx = 1 ; p09.w2rx = 1 p09.u1ty = 1 ; p09.u1ry = 1 ; p09.u2ty = 1 ; p09.u2ry = 1 p09.v1ty = 0 ; p09.v1ry = 1 ; p09.v2ty = 1 ; p09.v2ry = 1 p09.w1ty = 0 ; p09.w1ry = 1 ; p09.w2ty = 1 ; p09.w2ry = 1 # base up p10.u1tx = 1 ; p10.u1rx = 1 ; p10.u2tx = 1 ; p10.u2rx = 1 p10.v1tx = 1 ; p10.v1rx = 1 ; p10.v2tx = 1 ; p10.v2rx = 1 p10.w1tx = 1 ; p10.w1rx = 1 ; p10.w2tx = 1 ; p10.w2rx = 1 p10.u1ty = 1 ; p10.u1ry = 1 ; p10.u2ty = 1 ; p10.u2ry = 1 p10.v1ty = 1 ; p10.v1ry = 1 ; p10.v2ty = 1 ; p10.v2ry = 1 p10.w1ty = 1 ; p10.w1ry = 1 ; p10.w2ty = 1 ; p10.w2ry = 1 # flange up p11.u1tx = 1 ; p11.u1rx = 1 ; p11.u2tx = 0 ; p11.u2rx = 1 p11.v1tx = 1 ; p11.v1rx = 1 ; p11.v2tx = 0 ; p11.v2rx = 1 p11.w1tx = 1 ; p11.w1rx = 1 ; p11.w2tx = 0 ; p11.w2rx = 1 p11.u1ty = 1 ; p11.u1ry = 1 ; p11.u2ty = 1 ; p11.u2ry = 1 p11.v1ty = 1 ; p11.v1ry = 1 ; p11.v2ty = 1 ; p11.v2ry = 1 p11.w1ty = 1 ; p11.w1ry = 1 ; p11.w2ty = 1 ; p11.w2ry = 1 # base mid p12.u1tx = 1 ; p12.u1rx = 1 ; p12.u2tx = 1 ; p12.u2rx = 1 p12.v1tx = 1 ; p12.v1rx = 1 ; p12.v2tx = 1 ; p12.v2rx = 1 p12.w1tx = 1 ; p12.w1rx = 1 ; p12.w2tx = 1 ; p12.w2rx = 1 p12.u1ty = 1 ; p12.u1ry = 1 ; p12.u2ty = 1 ; p12.u2ry = 1 p12.v1ty = 1 ; p12.v1ry = 1 ; p12.v2ty = 1 ; p12.v2ry = 1 p12.w1ty = 1 ; p12.w1ry = 1 ; p12.w2ty = 1 ; p12.w2ry = 1 # flange mid p13.u1tx = 1 ; p13.u1rx = 1 ; p13.u2tx = 1 ; p13.u2rx = 1 p13.v1tx = 1 ; p13.v1rx = 1 ; p13.v2tx = 1 ; p13.v2rx = 1 p13.w1tx = 1 ; p13.w1rx = 1 ; p13.w2tx = 1 ; p13.w2rx = 1 p13.u1ty = 1 ; p13.u1ry = 1 ; p13.u2ty = 1 ; p13.u2ry = 1 p13.v1ty = 1 ; p13.v1ry = 1 ; p13.v2ty = 1 ; p13.v2ry = 1 p13.w1ty = 1 ; p13.w1ry = 1 ; p13.w2ty = 1 ; p13.w2ry = 1 # base low p14.u1tx = 1 ; p14.u1rx = 1 ; p14.u2tx = 1 ; p14.u2rx = 1 p14.v1tx = 1 ; p14.v1rx = 1 ; p14.v2tx = 1 ; p14.v2rx = 1 p14.w1tx = 1 ; p14.w1rx = 1 ; p14.w2tx = 1 ; p14.w2rx = 1 p14.u1ty = 1 ; p14.u1ry = 1 ; p14.u2ty = 1 ; p14.u2ry = 1 p14.v1ty = 1 ; p14.v1ry = 1 ; p14.v2ty = 1 ; p14.v2ry = 1 p14.w1ty = 1 ; p14.w1ry = 1 ; p14.w2ty = 1 ; p14.w2ry = 1 # flange low p15.u1tx = 1 ; p15.u1rx = 1 ; p15.u2tx = 1 ; p15.u2rx = 1 p15.v1tx = 0 ; p15.v1rx = 1 ; p15.v2tx = 1 ; p15.v2rx = 1 p15.w1tx = 0 ; p15.w1rx = 1 ; p15.w2tx = 1 ; p15.w2rx = 1 p15.u1ty = 1 ; p15.u1ry = 1 ; p15.u2ty = 1 ; p15.u2ry = 1 p15.v1ty = 1 ; p15.v1ry = 1 ; p15.v2ty = 1 ; p15.v2ry = 1 p15.w1ty = 1 ; p15.w1ry = 1 ; p15.w2ty = 1 ; p15.w2ry = 1 conn = [ # skin-skin dict(p1=p01, p2=p02, func='SSycte', ycte1=0, ycte2=p02.b), dict(p1=p01, p2=p04, func='SSxcte', xcte1=0, xcte2=p04.a), dict(p1=p02, p2=p03, func='SSycte', ycte1=0, ycte2=p03.b), dict(p1=p02, p2=p05, func='SSxcte', xcte1=0, xcte2=p05.a), dict(p1=p03, p2=p06, func='SSxcte', xcte1=0, xcte2=p06.a), dict(p1=p04, p2=p05, func='SSycte', ycte1=0, ycte2=p05.b), dict(p1=p04, p2=p07, func='SSxcte', xcte1=0, xcte2=p07.a), dict(p1=p05, p2=p06, func='SSycte', ycte1=0, ycte2=p06.b), dict(p1=p05, p2=p08, func='SSxcte', xcte1=0, xcte2=p08.a), dict(p1=p06, p2=p09, func='SSxcte', xcte1=0, xcte2=p09.a), dict(p1=p07, p2=p08, func='SSycte', ycte1=0, ycte2=p08.b), dict(p1=p08, p2=p09, func='SSycte', ycte1=0, ycte2=p09.b), # skin-base dict(p1=p02, p2=p10, func='SB'), dict(p1=p05, p2=p12, func='SB', has_defect=has_defect), # defect dict(p1=p08, p2=p14, func='SB'), # base-base dict(p1=p10, p2=p12, func='SSxcte', xcte1=0, xcte2=p12.a), dict(p1=p12, p2=p14, func='SSxcte', xcte1=0, xcte2=p14.a), # base-flange dict(p1=p10, p2=p11, func='BFycte', ycte1=p10.b/2., ycte2=0), dict(p1=p12, p2=p13, func='BFycte', ycte1=p12.b/2., ycte2=0), dict(p1=p14, p2=p15, func='BFycte', ycte1=p14.b/2., ycte2=0), # flange-flange dict(p1=p11, p2=p13, func='SSxcte', xcte1=0, xcte2=p13.a), dict(p1=p13, p2=p15, func='SSxcte', xcte1=0, xcte2=p15.a), ] panels = [p01, p02, p03, p04, p05, p06, p07, p08, p09, p10, p11, p12, p13, p14, p15] skin = [p01, p02, p03, p04, p05, p06, p07, p08, p09] assy = PanelAssembly(panels) size = assy.get_size() valid_conn = [] for connecti in conn: if connecti.get('has_defect'): # connecting if there is no defect continue valid_conn.append(connecti) k0 = assy.calc_k0(valid_conn) c = None if (run_static_case and not (Nxx_skin is None and Nxx_base is None and Nxx_flange is None)): fext = np.zeros(size) for p in [p07, p08, p09, p14, p15]: Nforces = 100 fx = p.Nxx*p.b/(Nforces-1.) for i in range(Nforces): y = i*p.b/(Nforces-1.) if i == 0 or i == (Nforces - 1): p.add_force(0, y, fx/2., 0, 0) else: p.add_force(0, y, fx, 0, 0) fext[p.col_start: p.col_end] = p.calc_fext(silent=True) incs, cs = static(k0, -fext, silent=True) c = cs[0] kM = assy.calc_kM() kG = assy.calc_kG0(c=c) kA = 0 for p in skin: # TODO the current approach has somewhat hiden settings # check this strategy: # - define module aerodynamics # - function calc_kA inside a module piston_theory # - pass piston_theory parameters and compute kA kA += p.calc_kA(size=size, row0=p.row_start, col0=p.col_start, silent=True, finalize=False) assert np.any(np.isnan(kA.data)) == False assert np.any(np.isinf(kA.data)) == False kA = csr_matrix(make_skew_symmetric(kA)) eigvals, eigvecs = freq((k0 + kG + kA), kM, tol=0, sparse_solver=True, silent=True, sort=True, reduced_dof=False, num_eigvalues=25, num_eigvalues_print=5) if run_static_case: return assy, c, eigvals, eigvecs else: return assy, eigvals, eigvecs
def cylinder_blade_stiffened_compression_lb_Nxx_from_static(height, r, stack, stack_blades, width_blades, plyt, laminaprop, npanels, Nxxs_skin, Nxxs_blade, m=8, n=8, num_eigvalues=20): """Linear buckling analysis with a Nxx calculated using static analysis See :func:`.create_cylinder_blade_stiffened` for most parameters. Parameters ---------- Nxxs_skin : list A Nxx for each skin panel. Nxxs_blade : list A Nxx for each blade stiffener. num_eigvalues : int Number of eigenvalues to be extracted. Returns ------- assy, c, eigvals, eigvecs : tuple Assembly, static results, eigenvalues and eigenvectors. Examples -------- The following example is one of the test cases: .. literalinclude:: ../../../../../compmech/panel/assembly/tests/test_cylinder.py :pyobject: test_cylinder_blade_stiffened_compression_lb_Nxx_from_static """ assy, conns = create_cylinder_blade_stiffened(height=height, r=r, stack=stack, stack_blades=stack_blades, width_blades=width_blades, plyt=plyt, laminaprop=laminaprop, npanels=npanels, m=m, n=n) if len(Nxxs_skin) != npanels: raise ValueError('The length of "Nxxs_skin" must be the same as "npanels"') if len(Nxxs_blade) != npanels: raise ValueError('The length of "Nxxs_blade" must be the same as "npanels"') i_skin = -1 i_blade = -1 for p in assy.panels: p.u2tx = 1 if 'skin' in p.group: i_skin += 1 p.Nxx = Nxxs_skin[i_skin] elif 'blade' in p.group: i_blade += 1 p.Nxx = Nxxs_blade[i_blade] #TODO improve application of distributed loads for p in assy.panels: Nforces = 1000 fx = p.Nxx*p.b/(Nforces-1.) for i in range(Nforces): y = i*p.b/(Nforces-1.) if i == 0 or i == (Nforces-1): fx_applied = fx/2. else: fx_applied = fx p.add_force(p.a, y, fx_applied, 0, 0) fext = assy.calc_fext(silent=True) k0 = assy.calc_k0(conns, silent=True) incs, cs = static(k0, fext, silent=True) c = cs[0] kG = assy.calc_kG0(c=c, silent=True) eigvals = eigvecs = None eigvals, eigvecs = lb(k0, kG, tol=0, sparse_solver=True, silent=True, num_eigvalues=num_eigvalues, num_eigvalues_print=5) return assy, c, eigvals, eigvecs
def tstiff2d_1stiff_compression(a, b, ys, bb, bf, defect_a, mu, plyt, laminaprop, stack_skin, stack_base, stack_flange, Nxx_skin, Nxx_base, Nxx_flange, run_static_case=True, r=None, m=8, n=8, mb=None, nb=None, mf=None, nf=None, nx=None, ny=None, nxb=None, nyb=None, nxf=None, nyf=None): r"""Linear Buckling of T-Stiffened panel with debonding defect The panel assembly looks like:: skin _________ _____ _________ | | | | | | | | | p01 | p02 | p03 | | | | | |_________|_____|_________| | p04 | p05 | p06 | /\ x |_________|_____|_________| | | | | | | | | | | | | p07 | p08 | p09 | | | | | | | | | |_________|_____|_________| loaded edge base flange _____ _____ | | | | | | | | | p10 | | p11 | | | | | |_____| |_____| | p12 | | p13 | |_____| |_____| | | | | | | | | | p14 | | p15 | | | | | | | | | |_____| |_____| loaded edge loaded edge For more details about the theory involved, see [castro2017AssemblyModels]_. Parameters ---------- a : float Total length of the assembly (along `x`). b : float Total width of the assembly (along `y`). ys : float Position of the stiffener along `y`. bb : float Stiffener's base width. bf : float Stiffener's flange width. defect_a : float Debonding defect/assembly length ratio. mu : float Material density. plyt : float Ply thickness. laminaprop : list or tuple Orthotropic lamina properties: `E_1, E_2, \nu_{12}, G_{12}, G_{13}, G_{23}`. stack_skin : list or tuple Stacking sequence for the skin. stack_base : list or tuple Stacking sequence for the stiffener's base. stack_flange : list or tuple Stacking sequence for the stiffener's flange. Nxx_skin : float Skin load distributed at the assembly edge at `x=0`. Nxx_base : float Stiffener's base load distributed at the assembly edge at `x=0`. Nxx_flange : float Stiffener's flange load distributed at the assembly edge at `x=0`. run_static_case : bool, optional If True a static analysis is run before the linear buckling analysis to compute the real membrane stress state along the domain, otherwise it is assumed constant values of `N_{xx}` for all components. r : float or None, optional Radius of the stiffened panel. m, n : int, optional Number of terms of the approximation function for the skin. mb, nb : int, optional Number of terms of the approximation function for the stiffener's base. mf, nf : int, optional Number of terms of the approximation function for the stiffener's flange. nx, ny, nxb, nyb, nxf, nyf : int, optional Define of integration points used for skin, stiffener's base or flange; along x and y. Keeping ``None`` will use the default (see :class:`.Panel`). Examples -------- The following example is one of the test cases: .. literalinclude:: ../../../../../compmech/panel/assembly/tests/test_tstiff2d_assembly.py :pyobject: test_tstiff2d_1stiff_compression """ defect = defect_a * a has_defect = True if defect > 0 else False defect = 0.33*a if defect == 0 else defect # to avoid weird domains aup = (a - defect)/2. alow = (a - defect)/2. bleft = b - ys - bb/2. bright = ys - bb/2. mb = m if mb is None else mb nb = n if nb is None else nb mf = m if mf is None else mf nf = n if nf is None else nf nx = m if nx is None else nx ny = n if ny is None else ny nxb = mb if nxb is None else nxb nyb = nb if nyb is None else nyb nxf = mf if nxf is None else nxf nyf = nf if nyf is None else nyf # skin panels p01 = Panel(group='skin', Nxx=Nxx_skin, x0=alow+defect, y0=ys+bb/2., a=aup, b=bleft, r=r, m=m, n=n, plyt=plyt, stack=stack_skin, laminaprop=laminaprop, mu=mu, nx=nx, ny=ny) p02 = Panel(group='skin', Nxx=Nxx_skin, x0=alow+defect, y0=ys-bb/2., a=aup, b=bb, r=r, m=m, n=n, plyt=plyt, stack=stack_skin, laminaprop=laminaprop, mu=mu, nx=nx, ny=ny) p03 = Panel(group='skin', Nxx=Nxx_skin, x0=alow+defect, y0=0, a=aup, b=bright, r=r, m=m, n=n, plyt=plyt, stack=stack_skin, laminaprop=laminaprop, mu=mu, nx=nx, ny=ny) # defect p04 = Panel(group='skin', Nxx=Nxx_skin, x0=alow, y0=ys+bb/2., a=defect, b=bleft, r=r, m=m, n=n, plyt=plyt, stack=stack_skin, laminaprop=laminaprop, mu=mu, nx=nx, ny=ny) p05 = Panel(group='skin', Nxx=Nxx_skin, x0=alow, y0=ys-bb/2., a=defect, b=bb, r=r, m=m, n=n, plyt=plyt, stack=stack_skin, laminaprop=laminaprop, mu=mu, nx=nx, ny=ny) p06 = Panel(group='skin', Nxx=Nxx_skin, x0=alow, y0=0, a=defect, b=bright, r=r, m=m, n=n, plyt=plyt, stack=stack_skin, laminaprop=laminaprop, mu=mu, nx=nx, ny=ny) # p07 = Panel(group='skin', Nxx=Nxx_skin, x0=0, y0=ys+bb/2., a=alow, b=bleft, r=r, m=m, n=n, plyt=plyt, stack=stack_skin, laminaprop=laminaprop, mu=mu, nx=nx, ny=ny) p08 = Panel(group='skin', Nxx=Nxx_skin, x0=0, y0=ys-bb/2., a=alow, b=bb, r=r, m=m, n=n, plyt=plyt, stack=stack_skin, laminaprop=laminaprop, mu=mu, nx=nx, ny=ny) p09 = Panel(group='skin', Nxx=Nxx_skin, x0=0, y0=0, a=alow, b=bright, r=r, m=m, n=n, plyt=plyt, stack=stack_skin, laminaprop=laminaprop, mu=mu, nx=nx, ny=ny) # stiffeners p10 = Panel(group='base', Nxx=Nxx_base, x0=alow+defect, y0=ys-bb/2., a=aup, b=bb, r=r, m=mb, n=nb, plyt=plyt, stack=stack_base, laminaprop=laminaprop, mu=mu, nx=nxb, ny=nyb) p11 = Panel(group='flange', Nxx=Nxx_flange, x0=alow+defect, y0=0, a=aup, b=bf, m=mf, n=nf, plyt=plyt, stack=stack_flange, laminaprop=laminaprop, mu=mu, nx=nxf, ny=nyf) # defect p12 = Panel(group='base', Nxx=Nxx_base, x0=alow, y0=ys-bb/2., a=defect, b=bb, r=r, m=mb, n=nb, plyt=plyt, stack=stack_base, laminaprop=laminaprop, mu=mu, nx=nxb, ny=nyb) p13 = Panel(group='flange', Nxx=Nxx_flange, x0=alow, y0=0, a=defect, b=bf, m=mf, n=nf, plyt=plyt, stack=stack_flange, laminaprop=laminaprop, mu=mu, nx=nxf, ny=nyf) # p14 = Panel(group='base', Nxx=Nxx_base, x0=0, y0=ys-bb/2., a=alow, b=bb, r=r, m=mb, n=nb, plyt=plyt, stack=stack_base, laminaprop=laminaprop, mu=mu, nx=nxb, ny=nyb) p15 = Panel(group='flange', Nxx=Nxx_flange, x0=0, y0=0, a=alow, b=bf, m=mf, n=nf, plyt=plyt, stack=stack_flange, laminaprop=laminaprop, mu=mu, nx=nxf, ny=nyf) # boundary conditions p01.u1tx = 1 ; p01.u1rx = 1 ; p01.u2tx = 0 ; p01.u2rx = 1 p01.v1tx = 1 ; p01.v1rx = 1 ; p01.v2tx = 0 ; p01.v2rx = 1 p01.w1tx = 1 ; p01.w1rx = 1 ; p01.w2tx = 0 ; p01.w2rx = 1 p01.u1ty = 1 ; p01.u1ry = 1 ; p01.u2ty = 1 ; p01.u2ry = 1 p01.v1ty = 1 ; p01.v1ry = 1 ; p01.v2ty = 0 ; p01.v2ry = 1 p01.w1ty = 1 ; p01.w1ry = 1 ; p01.w2ty = 0 ; p01.w2ry = 1 p02.u1tx = 1 ; p02.u1rx = 1 ; p02.u2tx = 0 ; p02.u2rx = 1 p02.v1tx = 1 ; p02.v1rx = 1 ; p02.v2tx = 0 ; p02.v2rx = 1 p02.w1tx = 1 ; p02.w1rx = 1 ; p02.w2tx = 0 ; p02.w2rx = 1 p02.u1ty = 1 ; p02.u1ry = 1 ; p02.u2ty = 1 ; p02.u2ry = 1 p02.v1ty = 1 ; p02.v1ry = 1 ; p02.v2ty = 1 ; p02.v2ry = 1 p02.w1ty = 1 ; p02.w1ry = 1 ; p02.w2ty = 1 ; p02.w2ry = 1 p03.u1tx = 1 ; p03.u1rx = 1 ; p03.u2tx = 0 ; p03.u2rx = 1 p03.v1tx = 1 ; p03.v1rx = 1 ; p03.v2tx = 0 ; p03.v2rx = 1 p03.w1tx = 1 ; p03.w1rx = 1 ; p03.w2tx = 0 ; p03.w2rx = 1 p03.u1ty = 1 ; p03.u1ry = 1 ; p03.u2ty = 1 ; p03.u2ry = 1 p03.v1ty = 0 ; p03.v1ry = 1 ; p03.v2ty = 1 ; p03.v2ry = 1 p03.w1ty = 0 ; p03.w1ry = 1 ; p03.w2ty = 1 ; p03.w2ry = 1 p04.u1tx = 1 ; p04.u1rx = 1 ; p04.u2tx = 1 ; p04.u2rx = 1 p04.v1tx = 1 ; p04.v1rx = 1 ; p04.v2tx = 1 ; p04.v2rx = 1 p04.w1tx = 1 ; p04.w1rx = 1 ; p04.w2tx = 1 ; p04.w2rx = 1 p04.u1ty = 1 ; p04.u1ry = 1 ; p04.u2ty = 1 ; p04.u2ry = 1 p04.v1ty = 1 ; p04.v1ry = 1 ; p04.v2ty = 0 ; p04.v2ry = 1 p04.w1ty = 1 ; p04.w1ry = 1 ; p04.w2ty = 0 ; p04.w2ry = 1 p05.u1tx = 1 ; p05.u1rx = 1 ; p05.u2tx = 1 ; p05.u2rx = 1 p05.v1tx = 1 ; p05.v1rx = 1 ; p05.v2tx = 1 ; p05.v2rx = 1 p05.w1tx = 1 ; p05.w1rx = 1 ; p05.w2tx = 1 ; p05.w2rx = 1 p05.u1ty = 1 ; p05.u1ry = 1 ; p05.u2ty = 1 ; p05.u2ry = 1 p05.v1ty = 1 ; p05.v1ry = 1 ; p05.v2ty = 1 ; p05.v2ry = 1 p05.w1ty = 1 ; p05.w1ry = 1 ; p05.w2ty = 1 ; p05.w2ry = 1 p06.u1tx = 1 ; p06.u1rx = 1 ; p06.u2tx = 1 ; p06.u2rx = 1 p06.v1tx = 1 ; p06.v1rx = 1 ; p06.v2tx = 1 ; p06.v2rx = 1 p06.w1tx = 1 ; p06.w1rx = 1 ; p06.w2tx = 1 ; p06.w2rx = 1 p06.u1ty = 1 ; p06.u1ry = 1 ; p06.u2ty = 1 ; p06.u2ry = 1 p06.v1ty = 0 ; p06.v1ry = 1 ; p06.v2ty = 1 ; p06.v2ry = 1 p06.w1ty = 0 ; p06.w1ry = 1 ; p06.w2ty = 1 ; p06.w2ry = 1 if run_static_case: p07.u1tx = 1 ; p07.u1rx = 1 ; p07.u2tx = 1 ; p07.u2rx = 1 else: p07.u1tx = 0 ; p07.u1rx = 1 ; p07.u2tx = 1 ; p07.u2rx = 1 p07.v1tx = 0 ; p07.v1rx = 1 ; p07.v2tx = 1 ; p07.v2rx = 1 p07.w1tx = 0 ; p07.w1rx = 1 ; p07.w2tx = 1 ; p07.w2rx = 1 p07.u1ty = 1 ; p07.u1ry = 1 ; p07.u2ty = 1 ; p07.u2ry = 1 p07.v1ty = 1 ; p07.v1ry = 1 ; p07.v2ty = 0 ; p07.v2ry = 1 p07.w1ty = 1 ; p07.w1ry = 1 ; p07.w2ty = 0 ; p07.w2ry = 1 if run_static_case: p08.u1tx = 1 ; p08.u1rx = 1 ; p08.u2tx = 1 ; p08.u2rx = 1 else: p08.u1tx = 0 ; p08.u1rx = 1 ; p08.u2tx = 1 ; p08.u2rx = 1 p08.v1tx = 0 ; p08.v1rx = 1 ; p08.v2tx = 1 ; p08.v2rx = 1 p08.w1tx = 0 ; p08.w1rx = 1 ; p08.w2tx = 1 ; p08.w2rx = 1 p08.u1ty = 1 ; p08.u1ry = 1 ; p08.u2ty = 1 ; p08.u2ry = 1 p08.v1ty = 1 ; p08.v1ry = 1 ; p08.v2ty = 1 ; p08.v2ry = 1 p08.w1ty = 1 ; p08.w1ry = 1 ; p08.w2ty = 1 ; p08.w2ry = 1 if run_static_case: p09.u1tx = 1 ; p09.u1rx = 1 ; p09.u2tx = 1 ; p09.u2rx = 1 else: p09.u1tx = 0 ; p09.u1rx = 1 ; p09.u2tx = 1 ; p09.u2rx = 1 p09.v1tx = 0 ; p09.v1rx = 1 ; p09.v2tx = 1 ; p09.v2rx = 1 p09.w1tx = 0 ; p09.w1rx = 1 ; p09.w2tx = 1 ; p09.w2rx = 1 p09.u1ty = 1 ; p09.u1ry = 1 ; p09.u2ty = 1 ; p09.u2ry = 1 p09.v1ty = 0 ; p09.v1ry = 1 ; p09.v2ty = 1 ; p09.v2ry = 1 p09.w1ty = 0 ; p09.w1ry = 1 ; p09.w2ty = 1 ; p09.w2ry = 1 # base up p10.u1tx = 1 ; p10.u1rx = 1 ; p10.u2tx = 1 ; p10.u2rx = 1 p10.v1tx = 1 ; p10.v1rx = 1 ; p10.v2tx = 1 ; p10.v2rx = 1 p10.w1tx = 1 ; p10.w1rx = 1 ; p10.w2tx = 1 ; p10.w2rx = 1 p10.u1ty = 1 ; p10.u1ry = 1 ; p10.u2ty = 1 ; p10.u2ry = 1 p10.v1ty = 1 ; p10.v1ry = 1 ; p10.v2ty = 1 ; p10.v2ry = 1 p10.w1ty = 1 ; p10.w1ry = 1 ; p10.w2ty = 1 ; p10.w2ry = 1 # flange up p11.u1tx = 1 ; p11.u1rx = 1 ; p11.u2tx = 0 ; p11.u2rx = 1 p11.v1tx = 1 ; p11.v1rx = 1 ; p11.v2tx = 0 ; p11.v2rx = 1 p11.w1tx = 1 ; p11.w1rx = 1 ; p11.w2tx = 0 ; p11.w2rx = 1 p11.u1ty = 1 ; p11.u1ry = 1 ; p11.u2ty = 1 ; p11.u2ry = 1 p11.v1ty = 1 ; p11.v1ry = 1 ; p11.v2ty = 1 ; p11.v2ry = 1 p11.w1ty = 1 ; p11.w1ry = 1 ; p11.w2ty = 1 ; p11.w2ry = 1 # base mid p12.u1tx = 1 ; p12.u1rx = 1 ; p12.u2tx = 1 ; p12.u2rx = 1 p12.v1tx = 1 ; p12.v1rx = 1 ; p12.v2tx = 1 ; p12.v2rx = 1 p12.w1tx = 1 ; p12.w1rx = 1 ; p12.w2tx = 1 ; p12.w2rx = 1 p12.u1ty = 1 ; p12.u1ry = 1 ; p12.u2ty = 1 ; p12.u2ry = 1 p12.v1ty = 1 ; p12.v1ry = 1 ; p12.v2ty = 1 ; p12.v2ry = 1 p12.w1ty = 1 ; p12.w1ry = 1 ; p12.w2ty = 1 ; p12.w2ry = 1 # flange mid p13.u1tx = 1 ; p13.u1rx = 1 ; p13.u2tx = 1 ; p13.u2rx = 1 p13.v1tx = 1 ; p13.v1rx = 1 ; p13.v2tx = 1 ; p13.v2rx = 1 p13.w1tx = 1 ; p13.w1rx = 1 ; p13.w2tx = 1 ; p13.w2rx = 1 p13.u1ty = 1 ; p13.u1ry = 1 ; p13.u2ty = 1 ; p13.u2ry = 1 p13.v1ty = 1 ; p13.v1ry = 1 ; p13.v2ty = 1 ; p13.v2ry = 1 p13.w1ty = 1 ; p13.w1ry = 1 ; p13.w2ty = 1 ; p13.w2ry = 1 # base low p14.u1tx = 1 ; p14.u1rx = 1 ; p14.u2tx = 1 ; p14.u2rx = 1 p14.v1tx = 1 ; p14.v1rx = 1 ; p14.v2tx = 1 ; p14.v2rx = 1 p14.w1tx = 1 ; p14.w1rx = 1 ; p14.w2tx = 1 ; p14.w2rx = 1 p14.u1ty = 1 ; p14.u1ry = 1 ; p14.u2ty = 1 ; p14.u2ry = 1 p14.v1ty = 1 ; p14.v1ry = 1 ; p14.v2ty = 1 ; p14.v2ry = 1 p14.w1ty = 1 ; p14.w1ry = 1 ; p14.w2ty = 1 ; p14.w2ry = 1 # flange low if run_static_case: p15.u1tx = 1 ; p15.u1rx = 1 ; p15.u2tx = 1 ; p15.u2rx = 1 else: p15.u1tx = 0 ; p15.u1rx = 1 ; p15.u2tx = 1 ; p15.u2rx = 1 p15.v1tx = 0 ; p15.v1rx = 1 ; p15.v2tx = 1 ; p15.v2rx = 1 p15.w1tx = 0 ; p15.w1rx = 1 ; p15.w2tx = 1 ; p15.w2rx = 1 p15.u1ty = 1 ; p15.u1ry = 1 ; p15.u2ty = 1 ; p15.u2ry = 1 p15.v1ty = 1 ; p15.v1ry = 1 ; p15.v2ty = 1 ; p15.v2ry = 1 p15.w1ty = 1 ; p15.w1ry = 1 ; p15.w2ty = 1 ; p15.w2ry = 1 conn = [ # skin-skin dict(p1=p01, p2=p02, func='SSycte', ycte1=0, ycte2=p02.b), dict(p1=p01, p2=p04, func='SSxcte', xcte1=0, xcte2=p04.a), dict(p1=p02, p2=p03, func='SSycte', ycte1=0, ycte2=p03.b), dict(p1=p02, p2=p05, func='SSxcte', xcte1=0, xcte2=p05.a), dict(p1=p03, p2=p06, func='SSxcte', xcte1=0, xcte2=p06.a), dict(p1=p04, p2=p05, func='SSycte', ycte1=0, ycte2=p05.b), dict(p1=p04, p2=p07, func='SSxcte', xcte1=0, xcte2=p07.a), dict(p1=p05, p2=p06, func='SSycte', ycte1=0, ycte2=p06.b), dict(p1=p05, p2=p08, func='SSxcte', xcte1=0, xcte2=p08.a), dict(p1=p06, p2=p09, func='SSxcte', xcte1=0, xcte2=p09.a), dict(p1=p07, p2=p08, func='SSycte', ycte1=0, ycte2=p08.b), dict(p1=p08, p2=p09, func='SSycte', ycte1=0, ycte2=p09.b), # skin-base dict(p1=p02, p2=p10, func='SB'), dict(p1=p05, p2=p12, func='SB', has_defect=has_defect), # defect dict(p1=p08, p2=p14, func='SB'), # base-base dict(p1=p10, p2=p12, func='SSxcte', xcte1=0, xcte2=p12.a), dict(p1=p12, p2=p14, func='SSxcte', xcte1=0, xcte2=p14.a), # base-flange dict(p1=p10, p2=p11, func='BFycte', ycte1=p10.b/2., ycte2=0), dict(p1=p12, p2=p13, func='BFycte', ycte1=p12.b/2., ycte2=0), dict(p1=p14, p2=p15, func='BFycte', ycte1=p14.b/2., ycte2=0), # flange-flange dict(p1=p11, p2=p13, func='SSxcte', xcte1=0, xcte2=p13.a), dict(p1=p13, p2=p15, func='SSxcte', xcte1=0, xcte2=p15.a), ] panels = [p01, p02, p03, p04, p05, p06, p07, p08, p09, p10, p11, p12, p13, p14, p15] assy = PanelAssembly(panels) size = sum([3*p.m*p.n for p in panels]) valid_conn = [] for connecti in conn: if connecti.get('has_defect'): # connecting if there is no defect continue valid_conn.append(connecti) k0 = assy.calc_k0(valid_conn) c = None if run_static_case: fext = np.zeros(size) for p in [p07, p08, p09, p14, p15]: Nforces = 100 fx = p.Nxx*p.b/(Nforces-1.) for i in range(Nforces): y = i*p.b/(Nforces-1.) if i == 0 or i == (Nforces - 1): p.add_force(0, y, fx/2., 0, 0) else: p.add_force(0, y, fx, 0, 0) fext[p.col_start: p.col_end] = p.calc_fext(silent=True) incs, cs = static(k0, -fext, silent=True) c = cs[0] kG = assy.calc_kG0(c=c) eigvals = eigvecs = None eigvals, eigvecs = lb(k0, kG, tol=0, sparse_solver=True, silent=True, num_eigvalues=25, num_eigvalues_print=5) if run_static_case: return assy, c, eigvals, eigvecs else: return assy, eigvals, eigvecs