The following paper discusses the transient thermal stresses set up in a cellular wing structure when the aircraft is subjected to a change of speed or of altitude. It is found rftac for nings with little or no insulation (fie maximum stress in the wing is usually between 70 per cent and 85 per cent of the value given by Young's modulus for webs × coefficient of expansion for the skin × external temperature change: it is therefore concluded that of the metallic materials, the combination of Hfcht alloy webs with a steel skin is admirable in its effect in reducing the thermal stresses. The analysis used is exact within the limits of its assumptions and comparisons are made with an earlier solution of the same problem by Hoff, who used an approximate method.
Parkes, E.W. (1953), "Transient Thermal Stresses in Wings: An Assessment of the Stresses in a Cellular Wing Structure Which Undergoes a Change of Temperature", Aircraft Engineering and Aerospace Technology, Vol. 25 No. 12, pp. 373-378. https://doi.org/10.1108/eb032367
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