Shell property utils module (pyfe3d.shellprop_utils)

Highly based on the composites. module.

pyfe3d.shellprop_utils.isotropic_plate(thickness, E, nu, offset=0.0, calc_scf=True, rho=0.0)

Read data for an isotropic plate

ShellProp object is returned based on the inputs given.

Parameters:

thicknessfloat

Plate thickness.

Efloat

Young modulus.

nufloat, optional

Poisson’s ratio.

rhofloat, optional

Material density

offsetfloat, optional

Offset along the normal axis about the mid-surface, which influences the extension-bending coupling (B matrix).

calc_scfbool, optional

If True, use ShellProp.calc_scf() to compute shear correction factors, otherwise the default value of 5/6 is used.

pyfe3d.shellprop_utils.laminated_plate(stack, plyt=None, laminaprop=None, rho=0.0, plyts=None, laminaprops=None, rhos=None, offset=0.0, calc_scf=True)

Read a laminate stacking sequence data.

ShellProp object is returned based on the inputs given.

Parameters:

stacklist

Angles of the stacking sequence in degrees.

plytfloat, optional

When all plies have the same thickness, plyt can be supplied.

laminaproptuple, optional

When all plies have the same material properties, laminaprop can be supplied.

rhofloat, optional

Uniform material density to be used for all plies.

plytslist, optional

A list of floats with the thickness of each ply.

laminapropslist, optional

A list of tuples with a laminaprop for each ply.

rhoslist, optional

A list of floats with the material density of each ply.

offsetfloat, optional

Offset along the normal axis about the mid-surface, which influences the laminate properties.

calc_scfbool, optional

If True, use ShellProp.calc_scf() to compute shear correction factors, otherwise the default value of 5/6 is used

Notes

plyt or plyts must be supplied laminaprop or laminaprops must be supplied

For orthotropic plies, the laminaprop should be:

laminaprop = (E11, E22, nu12, G12, G13, G23)

For isotropic plies, the laminaprop should be:

laminaprop = (E, nu)

pyfe3d.shellprop_utils.read_laminaprop(laminaprop, rho=0)

Returns a MatLamina object based on an input laminaprop tuple

Parameters:

laminaproplist or tuple

For the most general case of tri-axial stress, use a tuple containing the following entries:

laminaprop = (e1, e2, nu12, g12, g13, g23, e3, nu13, nu23)

For isotropic materials aiming calculations with tri-axial stresses, use:

g = e/(2*(1+nu))
laminaprop = (e, e, nu, g, g, g, e, nu, nu)

For orthotropic materials with in-plane stresses the user can only supply:

laminaprop = (e1, e2, nu12, g12, g13, g23)

For isotropic materials with in-plane stresses the user can only supply:

laminaprop = (e, nu) # new

symbol	value
e1	Young Modulus in direction 1
e2	Young Modulus in direction 2
nu12	12 Poisson’s ratio
g12	12 Shear Modulus
g13	13 Shear Modulus
g23	23 Shear Modulus
e3	Young Modulus in direction 3
nu13	13 Poisson’s ratio
nu23	23 Poisson’s ratio

rhofloat, optional

Material density

Returns:

matlamMatLamina

A MatLamina object.