Contribution to the Structural Analysis of Swept Wings

Contribution to the Structural Analysis of Swept Wings THE St. Venant theory as applied to long beams of constant crosssection could generally be used with sufficient accuracy for the solution of the structures encountered in aircraft until the last few years. The wings of highspeed aircraft, with smaller aspect ratios, large angles of sweepback, and small thicknesschord ratios, introduce a new problem. There is an extensive literature on the subject, and all the methods which have been proposed are necessarily studies of redundant systems, the degree of redundancy varying according to the accuracy required. As these solutions require that the scantlings of the structure be known in advance, it was thought interesting to establish a simple method which would determine to a good approximation the skin thicknesses required. This is based on the application of the theorem of least work, which gives exact solutions of elasticity problems so long as all the terms in the strain energy expression are taken into account. http://www.deepdyve.com/assets/images/DeepDyve-Logo-lg.png Aircraft Engineering and Aerospace Technology Emerald Publishing

Contribution to the Structural Analysis of Swept Wings

Aircraft Engineering and Aerospace Technology, Volume 26 (7): 5 – Jul 1, 1954

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Publisher
Emerald Publishing
Copyright
Copyright © Emerald Group Publishing Limited
ISSN
0002-2667
DOI
10.1108/eb032441
Publisher site
See Article on Publisher Site

Abstract

THE St. Venant theory as applied to long beams of constant crosssection could generally be used with sufficient accuracy for the solution of the structures encountered in aircraft until the last few years. The wings of highspeed aircraft, with smaller aspect ratios, large angles of sweepback, and small thicknesschord ratios, introduce a new problem. There is an extensive literature on the subject, and all the methods which have been proposed are necessarily studies of redundant systems, the degree of redundancy varying according to the accuracy required. As these solutions require that the scantlings of the structure be known in advance, it was thought interesting to establish a simple method which would determine to a good approximation the skin thicknesses required. This is based on the application of the theorem of least work, which gives exact solutions of elasticity problems so long as all the terms in the strain energy expression are taken into account.

Journal

Aircraft Engineering and Aerospace TechnologyEmerald Publishing

Published: Jul 1, 1954

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