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Torsion of a Constrained Rectangular Box Section: An Experimental Investigation of the Stresses due to Torsion in a Rectangular Box Section with one end Constrained

Aircraft Engineering and Aerospace Technology

ISSN: 0002-2667

Article publication date: 1 February 1954

Abstract

The paper describes an investigation of the stresses due to torsion of a doubly‐symmetrical thin‐walled rectangular box section with four corner spar flanges. The box section was subjected to a pure torque at the free end. The other end of the box section was constrained to remain plane. The shear stresses in the top and bottom skins and in the vertical webs and the direct stresses in the corner spar flanges were measured. The measured values were compared with theoretical predictions using the ‘linear’ and ‘closely spaced rigid diaphragm’ assumptions. The torsional stiffness was also measured and compared with theory. The experimental results show the marked effect of buckling of the skin covering on the stresses in the flanges. They also illustrate the importance of using the secant modulus in calculations.

Citation

Green, W.L. and Gill, S.S. (1954), "Torsion of a Constrained Rectangular Box Section: An Experimental Investigation of the Stresses due to Torsion in a Rectangular Box Section with one end Constrained", Aircraft Engineering and Aerospace Technology, Vol. 26 No. 2, pp. 34-35. https://doi.org/10.1108/eb032390

Publisher

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MCB UP Ltd

Copyright © 1954, MCB UP Limited