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Ultimate Strength of Aircraft Structures

[+] Author Affiliations
Todd Coburn

California State Polytechnic University Pomona, Pomona, CAUS Technical, Fullerton, CA

Paper No. IMECE2014-39986, pp. V001T01A033; 9 pages
doi:10.1115/IMECE2014-39986
From:
  • ASME 2014 International Mechanical Engineering Congress and Exposition
  • Volume 1: Advances in Aerospace Technology
  • Montreal, Quebec, Canada, November 14–20, 2014
  • Conference Sponsors: ASME
  • ISBN: 978-0-7918-4642-1
  • Copyright © 2014 by ASME

abstract

Strength analysis of aircraft structures focuses on static strength, fatigue, and damage tolerance of the materials. Countless hours are invested in quantifying the static strength, which is allowed to fully yield under ultimate loads so that the structure can be designed as light and efficient as possible. This analysis is critical to a lightweight initial design, but is also of great importance in the evaluation of engineering modifications and repairs. Analysis of the critical sections often resorts to plastic bending analysis, and use of E.F. Bruhn’s Iterative Slice Method, or Cozzone’s Simplified Method for Symmetric Sections, is often employed. Yet these methods fall short when the critical section includes thin flanges that buckle or cripple prior to ultimate failure, as is generally the case for frames, floor beams, stringers, and other structural members used on aircraft. This paper presents a solution to this shortfall, and introduces a hybrid procedure for calculating the ultimate strength of a cross section that accounts for material non-linearity, flange stability, and other effects.

Copyright © 2014 by ASME

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