飞机后缘复合材料夹层结构的稳定性计算方法

Stability Calculation Method of Aircraft Trailing Edge Composite Sandwich Structure

针对飞机后缘复合材料夹层结构稳定性计算没有工程方法的问题,利用飞机后缘夹层结构跨厚比大的特性,对结构适当简化,基于弹性结构的功能原理推导出一种飞机后缘复合材料夹层结构的稳定性计算方法,并通过数值算例将本文方法和有限元方法进行对比。结果表明,本文方法可行。

There is no method to calculate the structure stability of wing trailing edge with composite sandwich.The aircraft wing trailing edge with composite sandwich structures is simplified by the characteristics of large length to thickness ratio in this paper. A stability calculation method concerned on composite sandwich structures was deduced by elastic structure functional principle. The results comparison between engineering method and numerical method is given ifnally.