fedoo.constitutivelaw.ShellHomogeneousNonLinear

class ShellHomogeneousNonLinear(material, thickness, n_thickness_points=5, k=1, name='', *, output_points=None, n_points=3)

Homogeneous shell integrated from nonlinear plane-stress material points.

The membrane and bending response is obtained by calling a private copy of material at Gauss–Legendre points through the thickness. The material must support the standard Fedoo "2Dstress" constitutive-law interface. Transverse shear retains the elastic Reissner–Mindlin treatment used by ShellHomogeneous.

This implementation is restricted to small-strain material laws. For plasticity (or any law needing a plane-stress return mapping) use a Simcoon law, e.g. fedoo.constitutivelaw.Simcoon("EPICP", props); the pedagogical ElastoPlasticity is 3D-only and does not support "2Dstress".

Parameters:

• material (ConstitutiveLaw or str) – Plane-stress-compatible material law or its registered name.

• thickness (float) – Shell thickness.

• n_thickness_points (int, default=5) – Number of Gauss–Legendre points through the thickness.

• k (float, default=1) – Transverse shear correction factor.

• name (str, optional) – Name of the shell constitutive law.

__init__(material, thickness, n_thickness_points=5, k=1, name='', *, output_points=None, n_points=3)

Methods

ShellHomogeneousNonLinear.compute_area_density()
ShellHomogeneousNonLinear.compute_rotary_density()
ShellHomogeneousNonLinear.get_all()	Return a dict with all the known ConstitutiveLaw (with a name).
ShellHomogeneousNonLinear.get_local_frame([...])	Return material frames, resolved at assembly Gauss points.
ShellHomogeneousNonLinear.get_output_tensors(...)	Return (6, thickness point, shell GP) tensors and point metadata.
ShellHomogeneousNonLinear.get_shell_stiffness_matrix()
ShellHomogeneousNonLinear.get_strain(...)	Return the last computed strain associated to the given assembly.
ShellHomogeneousNonLinear.get_stress(...)	Recover local stress at normalized thickness position(s).
ShellHomogeneousNonLinear.get_stress_distribution(...)	Return stresses through the thickness at one shell Gauss point.
ShellHomogeneousNonLinear.initialize(...)	Initialize the constitutive law for the current problem.
ShellHomogeneousNonLinear.integration_stresses(...)	Actual thickness stresses, including elastic transverse shear.
ShellHomogeneousNonLinear.reset()	Reset the constitutive law.
ShellHomogeneousNonLinear.section_description([...])	Numeric, material-independent information for saved shell recovery.
ShellHomogeneousNonLinear.set_local_frame(...)	Define the material coordinate frame.
ShellHomogeneousNonLinear.set_start(assembly, pb)	Begin a new time iteration.
ShellHomogeneousNonLinear.to_start(assembly, pb)	Restart the current time iteration.
ShellHomogeneousNonLinear.update(assembly, pb)	Update shell stress from the strain computed by the weak form.

ShellHomogeneousNonLinear.area_density	Mass per unit midsurface area.
ShellHomogeneousNonLinear.layer_materials	Layer materials in stacking order; required for linear laminate recovery.
ShellHomogeneousNonLinear.n_points	Output sampling count per layer, an integer of at least two.
ShellHomogeneousNonLinear.name	Name of the constitutive law.
ShellHomogeneousNonLinear.output_points	Normalized thickness positions saved when output position is None.
ShellHomogeneousNonLinear.rotary_density	Mass moment of inertia per unit midsurface area.
ShellHomogeneousNonLinear.thickness	Shell thickness.
ShellHomogeneousNonLinear.k	Shear shape factor.
ShellHomogeneousNonLinear.is_initialized	Tag set to True once the law is intialized.