Abstract
The problem of the selecting the optimal lay-up stacking of polymer composite materials for the load-bearing elements of the rear part of fuselage structure is considered. The comparison of two approaches to the design of the load-bearing elements is carried out. The first of them is the use of multilayered composite material for the load-bearing elements, the stacking angles of which is selected from a given discrete set, and the second is the use of composite material with a continuous range of variables in fabric lay-up angles. As a result design optimization, it is shown that using an optimization method with a continuous range of lay-angles allows reducing the weight of the load-bearing elements by 12.79%
Highlights
The task of reducing the weight of aircraft structures is one of the most important at the entire stage of its development
The object of research in this paper is the tail section of the DA-62 aircraft, which is a twinengine monoplane with a T-shaped tail
Polymer composite material based on epoxy resin and carbon fabric was selected as the applied materials in the design of the DA-62 aircraft, which allowed for high strength and low weight of the structure
Summary
The task of reducing the weight of aircraft structures is one of the most important at the entire stage of its development. An effective tool for reducing the weight of aircraft structures is the use of composite materials with high specific strength and stiffness characteristics. The use of composites should be based not just on the mechanical replacement of traditional metal materials with composite materials, but take into account their features – primarily the anisotropy of characteristics. The creation of composite structures should be based on the widespread use of modern methods of numerical modeling and optimization [1, 2]. The aim of this work is to reduce the weight of the composite load-bearing elements of the fuselage of a light aircraft while maintaining their required strength using optimization methods
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