IN R. & M. 1761 the behaviour of a tube of rectangular cross section under torsional loading was investigated with the object of using the results to estimate the corresponding behaviour of a skin‐covered wing, whose normally complex structure renders a more direct calculation impracticable. It is natural therefore to have recourse to the same simplification when it is a question of estimating the effects of introducing discontinuities in the wing cover, The discontinuities discussed in this article are meant to include major gaps in the skin cover such as would be occasioned by the housing of petrol tanks or undercarriage wheels. In the equivalent rectangular tube such gaps are most conveniently represented by the removal of the top and bottom panels over the relevant portion of the span, the torque being transmitted across the gap by shears in the two side members or spars.
Williams, D. (1938), "Openings in Stressed‐Skin Wings: The Effect of Cover Discontinuities on the Strength and Stiffness of Stressed‐Skin Wings", Aircraft Engineering and Aerospace Technology, Vol. 10 No. 1, pp. 3-6. https://doi.org/10.1108/eb030260
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