Stability Analysis of Thin-Walled Perforated Composite Columns Using Finite Element Method

Area of Science:

• Mechanical Engineering
• Materials Science
• Structural Engineering

Background:

• Perforated composite structures, particularly carbon fiber reinforced polymer (CFRP) components, are vital in aerospace for weight reduction and maintainability.
• Open holes or cut-outs are common in structural elements like aircraft wing ribs, necessitating an understanding of their stability under load.

Purpose of the Study:

• To numerically investigate the stability and postbuckling behavior of CFRP composite perforated columns under compressive load.
• To analyze the influence of cut-out parameters, including spacing ratio, opening ratio, hole shape, and layer arrangement, on column stability.

Main Methods:

• Finite element analysis was performed using Abaqus software to simulate the behavior of CFRP channel profiles with three distinct cut-out types.
• Key parameters such as spacing ratio (S/D0), opening ratio (D/D0), hole shape, and ply arrangement were systematically varied.

Main Results:

• The study identified optimal combinations of parameters that yield the highest critical buckling load for perforated composite columns.
• Analysis revealed that the column's stability and postbuckling performance are highly sensitive to the composite's layer configuration, the opening ratio, and the shape of the cut-outs.

Conclusions:

• The optimal design of perforated composite columns requires careful consideration of cut-out geometry and material layup.
• Numerical simulations provide valuable insights into the complex stability behavior of weakened composite structures, guiding efficient design for aerospace applications.