Problem Description

Study the effect of ply stacking sequences on the flexural behaviour of composite laminates.

Different stacking sequences to be compared are$-$

Unidirectional laminates: $0\frac{}{0}\frac{}{0}\frac{}{0}\frac{?}{0}\frac{}{0}\frac{}{0}\frac{}{0}$

Quasi$-$isotropic Laminate: $0\frac{}{90}\frac{}{45}\frac{}{-}\frac{45}{-}45\frac{}{+}45\frac{}{90}\frac{?}{0}$

Material Properties to be used: Carbon$/$Epoxy Unidirectional from ANSYS Workbench Library

Specimen Dimensions:

Length: $125$ mm $($Span$)+10$ mm overhang on each side, Width: $25$ mm $,$ Thickness: $3$ mm

Support$/$loading pin dimensions: $3$ mm diameter and loading pin $6$ mm diameter

Load: $10$ N to $100$ N

Methodology:

Create the composite laminate using ACP Pre module of ANSYS

Perform simulation of flexural behaviour using static structural module

Report Contents

Load deflection curves of two laminates

Maximum displacement plot of two laminate

Do it in ansys workbench