Buckling behavior of Rene 41 tubular panels for a hypersonic aircraft wing | Zendy

William L. Ko | Zendy; Roger A. Fields | Zendy; J. L. Shideler | Zendy

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Buckling behavior of Rene 41 tubular panels for a hypersonic aircraft wing

Author(s) -

William L. Ko,

Roger A. Fields,

J. L. Shideler

Publication year - 1986

Publication title -

28th structures, structural dynamics and materials conference

Language(s) - English

Resource type - Conference proceedings

DOI - 10.2514/6.1986-978

Subject(s) - wing , aerospace engineering , buckling , hypersonic speed , structural engineering , hypersonic flight , aeronautics , wing configuration , materials science , engineering

The buckling characteristics of Rene 41 tubular panels for a hypersonic aircraft wing were investigated. The panels were repeatedly tested for buckling characteristics using a hypersonic wing test structure and a universal tension/compression testing machine. The nondestructive buckling tests were carried out under different combined load conditions and in different temperature environments. The force/stiffness technique was used to determine the buckling loads of the panel. In spite of some data scattering, resulting from large extrapolations of the data fitting curve (because of the termination of applied loads at relatively low percentages of the buckling loads), the overall test data correlate fairly well with theoretically predicted buckling interaction curves. Also, the structural efficiency of the tubular panels was found to be slightly higher than that of beaded panels.

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