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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。
In this paper, the finite element numerical calculation theory of large deformation nonlinear problems is described in detail, including the numerical calculation method of large deformation nonlinearity, the calculation of structural stability and the buckling problem. Secondly, the finite element software MSC.Marc was used to analyze the stability of the vertical tail structure under the condition of the helicopter blocked right sliding load. The structure of the vertical tail was optimized and the structure of the final thickness was optimized Stability analysis. The calculation results show that the instability phenomenon occurs in the root of the cauda of the tail, and no instability occurs in other areas. Finally, through careful analysis and checking of the results of stability analysis, this paper gives a numerical analysis method of the buckling stability of the composite structure after bearing, which accumulates experience for the development of helicopter composite simulation technology.