Abstract

A design scheme is considered: a cylindrical shell, which is loaded concentrated through the frame. A classical mathematical model is used for the adopted calculation scheme. Based on the mathematical model, the initial problem is analytically solved and an effective algorithm for multiparameter solution of the corresponding boundary value is constructed. The results of a quantitative analysis of the stress-strain state for the aircraft body are presented.

中文翻译：

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机体在转向载荷下的应力应变状态研究

摘要

考虑一种设计方案：圆柱壳，集中加载通过框架。采用经典的数学模型作为计算方案。在数学模型的基础上，对初始问题进行了解析求解，构造了有效的多参数求解相应边界值的算法。给出了飞机机身应力应变状态的定量分析结果。