Linear Buckling, Non-Linear Buckling And Post-Buckling Analysis of Columns And Plates

Project Abstract / Summary : In this project, analyses of simple columns with four different end boundary conditions using Euler’s theory are analysed and the results are verified numerically using the finite element software package ANSYS Version 15. Also, the analysis of simple beam columns with initial geometric imperfections and post-buckling behaviour of these columns is performed. Results are compared with the Southwell plot. The numerical results agree well with theoretical results for this initial geometrical imperfection case. An attempt is also made to find the critical buckling loads and also their associated buckled mode shapes for simple plates with simply supported edge boundary conditions using linear and non-linear post-buckling analyses. These numerical results also agree well with empirical formulae provided by Needham and Gerard’s methods. Since most of today’s aircraft structures are made of composite materials, an analysis of composite square laminates with circular and elliptical cut-outs are also presented. Their critical buckling loads and buckled mode shapes are determined.
The importance of performing such an analysis is quite essential in that every single exterior structural component of an aircraft are made of plates. Knowing exactly under what conditions they may be expected to buckle can prove to be invaluable to the designer.

Why did you choose to work on this project topic : Ask any layman, the design of which aircraft part is most crucial to its success. The general response would be that of the wings or of the fuselage. Their design is critical all right, but there is still an unsung component, which, if fails, would put an end to hundreds of lives aboard the plane, needless to say, the amount of cargo and end a million-dollar project.
It is the landing gear, which acts as a column, that is responsible for the safe landings of all aeroplanes whizzing over our heads. It is because these column structures take impact loads-loads which other structural components can barely hope to withstand. Hence, we have made it a point to perform the most important structural design project in the aircraft industry, i.e., the case of buckling of a column. Indeed, if that is true of a column, the analysis of the aircraft skin (which is made up of plates) is important too. They need to remain intact during the course of the flight, supporting aerodynamic loads without giving way to buckling. Hence, given the gravity of the matter under consideration, we decided to choose this project.

Project Category : Mechanical / Automobile / Aeronautical
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Institute/College Name: PARK COLLEGE OF ENGINEERING AND TECHNOLOGY
City: COIMBATORE
State: TAMIL NADU
Participating Team From: Final Year