Simulation and research of thermo elastic state of a three-layer compound shell

Abstract

The emergence and development of cities were accompanied by Technical progress in the fields of construction, architecture, and urban planning encouraging architects, designers, and other engineering specialists to use new, modern, and effective materials and structures in their activities. It is important to solve the problem of creating structures from elements that have low material consumption, the required indicators of strength, reliability, durability, and high manufacturability. The solution to this problem lies in the improvement of general structural schemes of buildings and their calculation methods, in the development of effective structural elements, and the use of new, including high-strength, materials. Such modern constructions include multi-layer shells and plates made of composite materials. A peculiarity of the calculation of multilayer structures from composite materials is that the assumptions about the straight normal and plane sections and the classical theory built based on these hypotheses cannot be applied, because it leads to significant errors in the results. In this article, the finite-shear model of shell theory is used in the calculation of thin-walled multilayer structures in combination with modern numerical methods. The purpose of this article is to simulate the operation of multilayer shells and plates that work under the influence of force and temperature influences. The effect of transverse shear deformation on the thermoelastic equilibrium of the shell system "cylinder-cone" is investigated.

Some peculiarities in the work of the multilayer structure were revealed by comparing the solutions obtained according to the refined model and within the framework of the Kirchhoff-Leav hypotheses. The shell was calculated with different options for fixing the ends:

1) articulated-movable support at x=0 and clamping at x=L;

2) a free edge at x=0 and pinching at x=L;

3) articulated-moving support at x=0 and articulated-fixed at x=L;

4) clamping at x=0 and x=L;

5) hinged and stationary support at x=0 and clamping at x=L;

6) hinged-fixed support with an absolutely rigid out-of-plane diaphragm at the end at x=0 and x=L.