Primary Instability of a Panel of Integral Construction with Unflanged Stiffeners

Author:

Yusuff Syed

Abstract

SummaryA theory of primary failure of compression panels of integral construction with unflanged stiffeners is presented, involving rotation, or translation, or rotation and translation of the stiffeners with the corresponding distortion of the sheet without deformation of the cross sections in their own planes. The investigation shows that the failure may occur generally either by pure torsion of the stiffener with the associated lateral distortion of the sheet or by pure flexure in accordance with whichever mode yields a smaller stress. The theory is compared with the test results covering a fairly wide range of the dimensions involved. The theory is in complete agreement with the experiments. The accuracy of the result thus obtained indicates that the fillets at the junction of the skin and the stiffener are not important and their effects may safely be disregarded.

Publisher

Cambridge University Press (CUP)

Reference10 articles.

1. Wallis M. and Holmes J. A. G. (1954). Integrally Machined Panels : Compression Panels. B.A.C. Report No. 56/3. June 1954.

2. Primary Instability Open Section Stringers Attached to Sheet;Levy;Journal of the Institute of Aeronautical Sciences,1948

3. Keen E. D. (1953). Integral Construction. The Journal of the Royal Aeronautical Society, April 1953.

4. The Manufacture and Testing of an Integrally Constructe Spar Box. Report No. P.S.7. January 1954. Short Bros and Harland Ltd., Belfast.

5. Integral Construction A Survey and an Experiment

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