Panel multidomain assembly with T-stiffeners modelled as 2D domains#
- panels.multidomain.tstiff2d_1stiff_compression.tstiff2d_1stiff_compression(a, b, ys, bb, bf, defect_a, rho, 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)#
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 [castro2017Multidomain] .
- Parameters:
- afloat
Total length of the assembly (along \(x\)).
- bfloat
Total width of the assembly (along \(y\)).
- ysfloat
Position of the stiffener along \(y\).
- bbfloat
Stiffener’s base width.
- bffloat
Stiffener’s flange width.
- defect_afloat
Debonding defect/assembly length ratio.
- rhofloat
Material density.
- plytfloat
Ply thickness.
- laminaproplist or tuple
Orthotropic lamina properties: \(E_1, E_2, \nu_{12}, G_{12}, G_{13}, G_{23}\).
- stack_skinlist or tuple
Stacking sequence for the skin.
- stack_baselist or tuple
Stacking sequence for the stiffener’s base.
- stack_flangelist or tuple
Stacking sequence for the stiffener’s flange.
- Nxx_skinfloat
Skin load distributed at the assembly edge at \(x=0\).
- Nxx_basefloat
Stiffener’s base load distributed at the assembly edge at \(x=0\).
- Nxx_flangefloat
Stiffener’s flange load distributed at the assembly edge at \(x=0\).
- run_static_casebool, 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.
- rfloat or None, optional
Radius of the stiffened panel.
- m, nint, optional
Number of terms of the approximation function for the skin.
- mb, nbint, optional
Number of terms of the approximation function for the stiffener’s base.
- mf, nfint, optional
Number of terms of the approximation function for the stiffener’s flange.
- nx, ny, nxb, nyb, nxf, nyfint, optional
Define of integration points used for skin, stiffener’s base or flange; along x and y. Keeping
Nonewill use the default (seeShell).
Examples
The following example is one of the test cases:
- panels.multidomain.tstiff2d_1stiff_freq.tstiff2d_1stiff_freq(a, b, ys, bb, bf, defect_a, rho, plyt, laminaprop, stack_skin, stack_base, stack_flange, r=None, m=8, n=8, mb=None, nb=None, mf=None, nf=None)#
Frequency T-Stiffened Shell with possible defect at middle
For more details about each parameter and the aerodynamic formulation see Ref. [castro2016FlutterPanel] .
For more details about the theory involved on the assembly of panels, see [castro2017Multidomain] .
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:
- afloat
Total length of the assembly (along \(x\)).
- bfloat
Total width of the assembly (along \(y\)).
- ysfloat
Position of the stiffener along \(y\).
- bbfloat
Stiffener’s base width.
- bffloat
Stiffener’s flange width.
- defect_afloat
Debonding defect/assembly length ratio.
- rhofloat
Material density.
- plytfloat
Ply thickness.
- laminaproplist or tuple
Orthotropic lamina properties: \(E_1, E_2, \nu_{12}, G_{12}, G_{13}, G_{23}\).
- stack_skinlist or tuple
Stacking sequence for the skin.
- stack_baselist or tuple
Stacking sequence for the stiffener’s base.
- stack_flangelist or tuple
Stacking sequence for the stiffener’s flange.
- rfloat or None, optional
Radius of the stiffened panel.
- m, nint, optional
Number of terms of the approximation function for the skin.
- mb, nbint, optional
Number of terms of the approximation function for the stiffener’s base.
- mf, nfint, optional
Number of terms of the approximation function for the stiffener’s flange.
Examples
The following example is one of the test cases:
- panels.multidomain.tstiff2d_1stiff_flutter.tstiff2d_1stiff_flutter(a, b, ys, bb, bf, defect_a, rho, 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)#
Flutter of T-Stiffened Shell 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:
- afloat
Total length of the assembly (along \(x\)).
- bfloat
Total width of the assembly (along \(y\)).
- ysfloat
Position of the stiffener along \(y\).
- bbfloat
Stiffener’s base width.
- bffloat
Stiffener’s flange width.
- defect_afloat
Debonding defect/assembly length ratio.
- rhofloat
Material density.
- plytfloat
Ply thickness.
- laminaproplist or tuple
Orthotropic lamina properties: \(E_1, E_2, \nu_{12}, G_{12}, G_{13}, G_{23}\).
- stack_skinlist or tuple
Stacking sequence for the skin.
- stack_baselist or tuple
Stacking sequence for the stiffener’s base.
- stack_flangelist or tuple
Stacking sequence for the stiffener’s flange.
- air_speedfloat
Airflow speed.
- rho_airfloat
Air density.
- Machfloat
Mach number.
- speed_soundfloat
Speed of sound.
- flow“x” or “y”
Direction of airflow.
- Nxx_skinfloat
Skin load distributed at the assembly edge at \(x=0\).
- Nxx_basefloat
Stiffener’s base load distributed at the assembly edge at \(x=0\).
- Nxx_flangefloat
Stiffener’s flange load distributed at the assembly edge at \(x=0\).
- run_static_casebool, 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.
- rfloat or None, optional
Radius of the stiffened panel.
- m, nint, optional
Number of terms of the approximation function for the skin.
- mb, nbint, optional
Number of terms of the approximation function for the stiffener’s base.
- mf, nfint, optional
Number of terms of the approximation function for the stiffener’s flange.
Examples
The following example is one of the test cases: