| Abstrakt: |
The problem of reducing the weight of aircraft structures, while maintaining the rest of the material properties, is urgent. Carbon fiber polymer matrix composite materials are used in such applications due to their light weight and high strength. Due to the need to develop radiation-resistant, heat-resistant, lightweight materials from carbon-carbon composite materials (CCCM), in this article, calculations of the stress-strain state (SSS) of a prototype frame by the finite element method were carried out. A detailed description of the initial data of the prototype of the frame was given and the loads acting on the structure were indicated. The physical and mechanical characteristics of the materials used in the construction were given, including the characteristics of carbon fiber based on filament, based on unidirectional carbon tape impregnated with a binder, and based on carbon fiber using epoxy prepreg. The authors created a loading scheme for a finite element model (FEM) of a prototype frame. The calculations allowed to determine the values of the structure rigidity, the prototype frame stability, critical load, stability margin, rigidity of the shell. Comparison of FEM in the initial state and after the loss of stability is given. Conclusions were made about the need to use beam finite elements that simulate a system of spiral, annular and longitudinal ribs of the mesh structure. [ABSTRACT FROM AUTHOR] |
