摘要
某型飞机腹鳍连接角材在外场使用中疲劳性能不能满足飞机寿命要求,为了解决这个问题,本研究在原结构的基础上,设计改进结构,通过有限元分析和疲劳对比试验,复现了原结构结构故障,试验件开裂位置与形式与外场实际一致,验证了改进结构的有效性,改进结构能够满足该型飞机疲劳寿命要求。
It has been found in aircraft in service that the fatigue performance of the original and improved structures of ventral fin connection can not meet the requirement of aircraft life.In this paper,to solve this problem,we design the original structure with optimization.Both of the finite element analysis and fatigue comparisons tests are performed on the original and improved structures.The structures faults are recurred in the improved structures.The positions and forms of crack are both consistent with the actual practice,and the following results can be obtained:firstly,the improved structure is valid,and secondly,it can satisfy the requirement of the fatigue life of aircrafts.
引文
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