Optimal choice of composite fuselage cross-section form design

Aviation technics and technology


Dudchenko A. A.*, Canchaya Rojas . A.

Moscow Aviation Institute (National Research University), 4, Volokolamskoe shosse, Moscow, А-80, GSP-3, 125993, Russia

*e-mail: a_dudchenko@mail.ru


The present work deals with the method of the optimal choice of fuselage structure, which gives the minimum weight of the shell. The useful volume of a fuselage compartment is calculated depending on a pay load. Variants of cross-section fuselage structure are considered depending on the perception of external loading. The stress-deformed state of composite design is analyzed to estimate the maximum stress zone. The shell thickness is estimated by using conditions uniform strength.


fuselage cross-section; fuselage compartment; weight efficiency; structure thickness; structure calculation; design density


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