An Investigation of Classical Panel Stiffener Buckling Methods for Modern Airframe Applications

<p>Classical methods for buckling assessment of aircraft panels reinforced by bulb-stiffened flanges differ regarding symmetric versus asymmetric cross-sections. The present research addresses a number of classical derivations of methods with a focus on the work of Dwight Windenburg as published in "The Elastic Stability of Tee Stiffeners" and the expansion of his work to asymmetric sections by E. F Bruhn in Analysis and Design of Aerospace Vehicle Structures. Vagueness in the relevance of geometric symmetry of the bulb exists between Windenburg's plate theory approach, and the accepted industry standard applications defined in the methods of Bruhn. The results presented trace the bibliographic history of sizing bulb-stiffeners to achieve the highest critical stress obtainable by the web, and verify the two sizing procedures theoretically and using Finite Element Analysis software. The results suggest that the theoretical approach presented by Windenburg is correct as stated; however the FEA results suggest that the claim made by Bruhn's and Windenburg's sizing process is inadequate.</p>

Name thesis:degree_name

Master of Aerospace Engineering

Level thesis:degree_level

Thesis - Open Access

Discipline thesis:degree_discipline

Aerospace Engineering

Year

2008

Author dc:creator

• Holt, Ryan Timothy

Contributors dc:contributor

• James Ladesic
• Frank Radosta
• Frederique Drullion

• panel stiffener
• buckling
• airframe
• Aerospace Engineering

Repository record dc:identifier

https://commons.erau.edu/db-theses/86

OAI identifier oai:identifier

oai:commons.erau.edu:db-theses-1122