fedoo.constitutivelaw.ShellHomogeneous
- class ShellHomogeneous(material, thickness, k=1, name='', *, output_points=None, n_points=3)
- __init__(material, thickness, k=1, name='', *, output_points=None, n_points=3)
Methods
Return a dict with all the known ConstitutiveLaw (with a name).
ShellHomogeneous.get_local_frame([assembly])Return material frames, resolved at
assemblyGauss points.ShellHomogeneous.get_output_tensors(...[, ...])Return (6, thickness point, shell GP) tensors and point metadata.
ShellHomogeneous.get_strain(assembly, **kargs)Return the last computed strain associated to the given assembly.
ShellHomogeneous.get_stress(assembly, **kargs)Recover local stress at normalized thickness position(s).
ShellHomogeneous.initialize(assembly, pb)Initialize the constitutive law for the current problem.
ShellHomogeneous.integration_stresses(assembly)Actual thickness stresses, including elastic transverse shear.
Reset the constitutive law.
ShellHomogeneous.section_description([assembly])Numeric, material-independent information for saved shell recovery.
ShellHomogeneous.set_local_frame(local_frame)Define the material coordinate frame.
ShellHomogeneous.set_start(assembly, pb)Begin a new time iteration.
ShellHomogeneous.to_start(assembly, pb)Restart the current time iteration.
ShellHomogeneous.update(assembly, pb)Update shell stress from the strain computed by the weak form.
Mass per unit midsurface area.
Layer materials in stacking order; required for linear laminate recovery.
Output sampling count per layer, an integer of at least two.
Name of the constitutive law.
Normalized thickness positions saved when output position is None.
Mass moment of inertia per unit midsurface area.
Shell thickness.
Shear shape factor.
Tag set to True once the law is intialized.