民用飞机后机身全尺寸静力试验与有限元分析  

Full-scale static test and analysis for civil aircraft rear fuselage

作　　者：朱正义[1] 任宇康 Zhu Zhengyi;Ren Yukang(Shanghai Aircraft Design and Research Institute,Shanghai,201210,China)

机构地区：[1]上海飞机设计研究院,上海201210

出　　处：《机械设计与制造工程》2021年第5期70-74,共5页Machine Design and Manufacturing Engineering

摘　　要：根据后机身载荷包线对后机身全尺寸静力试验载荷进行筛选,完成从理论载荷到试验加载载荷的设计,提出了试验边界模拟、试验加载模拟等关键方法,完成了发动机失效工况和机动平衡两种危险工况的试验。建立了有限元分析模型,基于试验加载载荷进行有限元计算,得到理论位移和应变值。试验测量结果表明,试验测量得到的位移和应变值与理论值符合性良好,试验结果可作为某型民用飞机复合材料后机身结构的强度验证依据,验证的有限元分析方法可应用于结构优化设计。The full-scale static test verification technology of a civil aircraft composite rear fuselage is studied,which provides a verification method for the airworthiness verification of the rear fuselage structure.According to the load envelope of the rear fuselage,the full-scale static test load of the rear fuselage is screened,and the design from the theoretical load to the test load is completed.The key methods of test boundary simulation and test load simulation are proposed,and the tests of engine failure condition and dynamic balance condition are completed.The finite element analysis model is established.Based on the test load,the theoretical displacement and the theoretical strain of the structure are obtained.The test results show that the measured values of displacement and strain are in good agreement with the theoretical results.The test results can be used as the strength verification basis for the composite rear fuselage structure of a civil aircraft.The verified finite element analysis method can be applied to the structural optimization design.

关 键 词：民用飞机 静力试验 后机身 载荷处理 

分 类 号：V258[一般工业技术—材料科学与工程]