Determination and comparison of buckling load of thin sheet metal plates by classical techniques and by Finite Element techniques
Keywords:
Classical Stress analysis , Buckling, Structural Analysis, Finite Element AnalysisAbstract
Thin sheet metals are a common structural element in aerospace structures because major portions of these structures are covered by thin sheet metals. While it is desirable to eliminate compressive stresses in thin sheet metals in flight structures, total elimination of such stresses is not possible. Consequently, buckling analysis of thin sheet metals is a necessary component of aircraft structural analysis.
Analysis & Design of Flight Vehicle Structures (originally written by Dr. Bruhn of Purdue University in 1965 and significantly revised by Dr. Wolf of General Motors Research Laboratories in 1973) was the classical reference textbook for stress analysis of aircrafts before the wide availability of Finite Element software. The classical solutions are based on the theory of elastic stability of thin sheets that don’t all have exact solutions and are impossible to implement without the use of computerized techniques in a reasonable time, and consequently, tables and graphs were developed to provide approximate solutions. More accurate solutions can be obtained by the use of computer-based Finite Element software that leads to lighter and yet safe designs. In this article, comparisons of solutions obtained by graphical techniques based on the theory of Elastic Stability and those obtained by Finite Element techniques are presented.
The techniques illustrated in this article were used in an “Advanced Mechanics of Materials” course. The teaching technique involved verifying the Finite Element results by comparing them to results for scenarios where classical solutions were available in Bruhn.
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