Mathematical Models and Methods for Calculating the Stress-Strain State of Aircraft Panels from Composite Materials Taking into Account the Production Technology
L. M. Gavva, В. В. Фирсанов
Abstract
Abstract The relations of the mathematical model for studying the stress-strain state of structurally anisotropic panels made of composite materials are given. The mathematical model of the reinforcing element is clarified under conditions of one-sided contact with the skin. The influence of panels manufacturing technology is taken into account: residual temperature stresses and prestressing of reinforcing fibers. Based on the Lagrange variational principle, an eighth-order resolving equation and natural boundary conditions are obtained. A class of exact solutions of boundary value problems is considered. In the MATLAB operating environment, a software package has been developed. The results of the numerical implementation of the solution and the results of field experiments are presented.