Buckling of Composite Shells — Lesson 3

This lesson covers the theory of composite shells, focusing on the buckling of shells. It explains how to develop a buckling solution for a Levy-supported finite shell panel and discusses the process of creating a program for the buckling of a composite cylinder. The lesson also provides an example of a problem involving a 3-layer cylindrical composite shell subjected to different conditions such as axial load, external pressure, and thermal temperature. It further explains how to develop codes for shell panels or cylindrical shells, the importance of error-free theoretical formulation, and the process of developing a 3-layer program. The lesson concludes with a discussion on the buckling of a cylindrical shell.

Video Highlights

02:23 - Theoretical formulation for shell panels or cylindrical shells.
04:55 - Converting material properties for 0 ̊ and 90 ̊.
06:45 - Evaluating the Q11, Q22, Q12, and Q66.
21:40 - Calculation of critical load for buckling.
23:55 - How to develop a solution for a Levy-type cylindrical panel.

Key Takeaways

- Understanding the buckling of shells and the development of a buckling solution for a Levy-supported finite shell panel is crucial in the study of composite shells.
- A 3-layer cylindrical composite shell can be subjected to different loads such as axial load, external pressure, or thermal temperature.
- Writing a MATLAB program to calculate the buckling parameters of a composite cylinder involves a step-by-step process that requires a clear understanding of the theoretical formulation.
- Developing codes for shell panels or cylindrical shells is possible with basic steps, but it requires confidence and precision to avoid errors.
- The development of a Levy-type solution based on classical shell theory involves a complex process that requires a deep understanding of the subject matter.