直升机复合材料结构屈曲稳定性数值计算研究  

The Research on Buckling Analysis of Helicopter Caudal Segment Composite Structure under Load

作　　者：李玉成[1] 齐德胜[2] 韩刘[2] 安静波[1] 

机构地区：[1]哈尔滨玻璃钢研究院,哈尔滨150036 [2]中航工业哈尔滨飞机工业集团有限责任公司,哈尔滨150066

出　　处：《纤维复合材料》2011年第2期20-25,共6页Fiber Composites

摘　　要：本文首先详细描述了大变形非线性问题的有限元数值计算理论,包括大变形非线性数值计算方法、结构稳定性计算和屈曲问题。其次采用有限元软件MSC.Marc在直升机受阻右侧滑载荷条件下对垂尾结构进行了稳定性数值分析计算,主要对垂尾进行了优化结构下的结构和厚度圆整后结果的结构进行了稳定性分析。计算结果表明:垂尾前缘根部出现失稳现象,而其它区域没有失稳现象出现。最后本文通过细致的分析、校核稳定性分析计算结果,给出了复合材料结构承载后屈曲稳定性数值分析方法,为直升机复合材料仿真技术的发展积累了经验。Firstly, this paper minutely described the finite element numerical calculation theory of nonlinear problem, including the large deformation nonlinear numerical calculation, the structure stability analysis and buckling analysis. Sec- ondly, stability numerical analysis was made on caudal segment structure when the helicopter was under the resistance right slip load using MSC. Marc, mainly to fin under the optimized structure and thickness round structure. Calculation results showed that instability phenomenon appeared on fin front, and other arrears had no instability buckling. Finally, this paper gave composite structure buckling analysis method by careful analysis and checking stability analysis results. It can accu- mulate the experience for the development of technology in helicopter.

关 键 词：复合材料 大变形非线性 屈曲稳定性分析 

分 类 号：V214.8[航空宇航科学与技术—航空宇航推进理论与工程]