The effect of heating on the mass of load-carrying structures is analyzed using the weight Komarov formula in the framework of the design calculations by examples of a panel and spar. The results obtained have been compared with the data on real structures of supersonic passenger aircraft and aerospace aircraft of reusable transport systems.Weight is a major factor in aircraft design as well as one of the main criteria being used. The structure, which takes all spectrum of acting loads, accounts for the greatest share of aircraft weight. There are tens and even hundreds of the so-called weight equations to estimate the structure mass at the early design stages. Let us apply the general-purpose Komarov weight equation [1] in the following form:
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