某型无人直升机机身框架断裂分析及优化计算

Fracture Analysis and Optimization Calculation of Fuselage Frame of An Unmanned Helicopter

以某型无人直升机机身框架为研究对象,分析断裂原因,采用三维建模,并应用有限元方法进行分析计算,得出断裂主要由应力集中所造成,与金相分析得出的结论一致。同时,采用增加腹板形式进行优化改进,并进行静态与动态分析。结果表明,应变明显减小,应力分布均匀且没有影响整体动态性能。分析和实际使用表明,框架强度明显提高,应力集中情况得到明显改善。

An unmanned helicopter fuselage frame as the research object, analyze the reason of the fracture by three-dimensional modeling and application of finite element method for calculation and analysis, the fracture mainly by the stress concentration caused by the metallographic analysis, the conclusion is consistent. Then, the optimization and improvement of the web form are carried out, and the static and dynamic analysis is carried out. The results show that the strain is obviously reduced, the stress distribution is uniform, and the overall dynamic performance is not affected. Analysis and practical application show that the strength of the frame is obviously improved, and the stress concentration situation has been improved obviously.