ASSESSMENT OF THE LOAD-BEARING CAPACITY OF A COMPOSITE AIRCRAFT STRUCTURE CONSISTING OF A METAL-POLYMER COMPOSITE MATERIAL AND A CLASSICAL METAL

The requirements for modern models of aviation equipment are constantly increasing, as a result of which it is necessary to look for new ways to solve the assigned engineering tasks through the use of new materials, new principles of manufacturing and assembly, as well as through an extraordinary approach to the design of the design of modern aircraft products. In this paper, the engineering methodology of power calculation and design of composite aircraft structures combining metal-polymer composite materials and metal materials is considered. As a composite structure under study, a fragment of an aircraft wing panel is considered, including a stringer made of a traditional structural material (metal) and a metal-polymer composite material skin attached to it. Metal- polymer composite material is a layered material consisting of metal sheets and layers of polymer composite material. Previously, in [1], the characteristics of the stress-strain state (SSS) of a single metal-polymer composite material and each layer in its package were investigated. In this paper, analytical and graphical dependences of the stress state of the elements of a composite structure on their ultimate deformations are obtained. The parameters of the composite panel of the wing, working on tension, and their effect on the stress-strain state, safety margin and load-bearing capacity are investigated. The obtained graphical dependences can be used for a preliminary assessment of the strength of an element of a composite structure at the stage of working out the design concept of an aircraft airframe assembly using a metal-polymer material.