Abstract
The problem of estimating the weight of the fuselage for the initial stages of design as a result of using new materials and new design solutions is considered. The approach is based on the V.A. Komarov's weight formula. A design method for estimating the CK coefficients of the load-carrying factor for real structures is proposed. The comparison of the CK for various components of loads in relation to conventional metal and composite structures is performed. A numerical analysis is performed in terms of a medium-haul aircraft.
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