摘要
薄壁加筋结构是飞机尤其是直升机结构的典型构型,随着复合材料在直升机上的大量使用,研究复合材料加筋薄壁结构在开孔后的剪切屈曲和后屈曲问题的分析方法,提高分析进度,是直升机结构强度设计的技术关键。以复合材料开孔薄壁加筋板试验为基础,测试了加筋板剪切屈曲和后屈曲应变及载荷历程,仿真分析了试验结果,建立了一种以risk算法、Hashin失效准则的有限元分析模型,提供了一种复合材料开孔薄壁加筋板剪切屈曲和后屈曲分析的设计方法。
Thin -walled reinforced structure is a typical configuration of aircraft especially helicop- ter structure. Along with the use of composite materials on the helicopter, the composite stiffened thin - walled structure after the opening of the shear buckling and post - buckling analysis of prob- lem, improving the analysis progress, is the key technology of helicopter structural strength design. Based on the opening of composite materials thin walled stiffened plate test, this paper tested the stiffened plate shear buckling and post -buckling strain and load process , took simulation analysis of the test results, established a risk algorithms, Hashin failure criteria of finite element analysis model, provided a hole thin walled reinforced composite plates shear buckling and post - buckling a- nalysis design method.
出处
《直升机技术》
2018年第1期13-19,共7页
Helicopter Technique
关键词
复合材料
开孔
后屈曲
composite
thin - walled stiffened panels
post - buckling
