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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    Title :

    Preliminary Assessment of the Weight of the Aircraft Fuselage as a Result of the Transition to Composite Materials


    Additional title:

    Russ. Aeronaut.


    Contributors:

    Published in:

    Russian Aeronautics ; 63 , 3 ; 386-396


    Publication date :

    2020-09-01


    Size :

    11 pages




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English




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