# OS-V: 0530 Composite Shell Bending

This problem discusses about the composite shells two- or three-layer plate subjected to a sinusoidal distributed load, as described by Pagano (1969).

The resulting transverse shear and axial stresses through the thickness of the plate are compared to analytical solutions using classical laminated plate theory (CPT) and linear elasticity theory.

## Benchmark Model

Two models have been considered - composite plate with two and three-ply layers.
• For the two-layer model, top layer is in 90° and bottom layer is in 0°.
• For the three-layer model, the top and bottom layer are in 0° orientation and the middle ply is in 90° orientation.
The material properties are:
Property
Value
EL
25*106 lb/in2 (172.4 GPa)
ET
1.0*106 lb/in2 (6.90 GPa)
GLT
0.5*106 lb/in2 (3.45 GPa)
GTT
0.2*106 lb/in2 (0.2 GPa)
VLT = VTT
0.25
Where,
L
Signifies the direction parallel to the fibers
T
Signifies the transverse direction
Limit stresses and limit strains used are:
Stress Value Xt Xc Yt Yc S
GPa 2.07*10-4 -8.28*10-5 3.45*10-6 -1.03*10-5 6.89*10-6
lb/in2 30.0 -12.0 0.5 -1.5 1.0

## Results

For plate with S=4:

## Model Files

Refer to Access the Model Files to download the required model file(s).

The model files used in this problem include:
• composite-shells-2-plys-2nd-order-span-4.fem
• composite-shell-1st-order_span-4.fem

## Reference

Exact Solutions for Composite Laminates in Cylindrical Bending by N.J. Pagano, Washington University, St. Louis, MO (May 7, 1969)

Nonlinear finite element shell formulation accounting for large membrane strains by Thomas J.R. Hughes and Eric Carnoy, Stanford University (1982)