CLASSICAL LAMINATION THEORY

a simple solver

Classical Lamination Theory is a method to solve the stresses and strains of complex structures built from layers of anisotropic materials.
We normally refer to these materials as composites.
This simple solver computes the stresses and strains of composite materials using a python program in the back end.

All it needs is the answers to a few questions:

*This site is intended for educational purposes only, results are not guaranteed to be accurate.

What are your ply properties?

Ply "P1" Properties:

E1 Value GPa
E2 Value GPa
ν12 Value
G12 Value GPa
Thickness mm

How are your plies stacked?

Layup angle for each ply in stack
(top to bottom use pattern X/X/X/X)
Ply layers input
(align layup value with plies P1, P2, etc., use pattern PX/PX/PX/PX)

Layup Example for 0/45/-45/-45/45/0 and P1/P2/P3/P4/P5/P6

What loads is your laminate under?

Load in X direction (Nx) N
Load in Y direction (Ny) N
Shear Load (Nxy) N
Moment about X axis (Mx) Nm
Moment about Y axis (My) Nm
Moment about XY axis (Mxy) Nm

*Loads are per unit width (per metre)

Plane Loads

Moment Loads

packages = [ "matplotlib", "numpy" ]

ε_x
ε_y
γ_xy
K_x
K_y
K_xy

CLASSICAL LAMINATION THEORY

a simple solver

What are your ply properties?

Ply "P1" Properties:

Ply "P2" Properties:

Ply "P3" Properties:

Ply "P4" Properties:

Ply "P5" Properties:

Ply "P6" Properties:

How are your plies stacked?

What loads is your laminate under?

Calculate