某型飞机ZL114A铝合金支架断裂失效分析  

Fracture Failure Analysis of ZL114A Aluminum Alloy Bracket of an Aircraft

作　　者：李召华 许永春 LI Zhao-hua;XU Yong-chun(Aviation Maintenance NCO Academy,Air Force Engineering University,Xinyang 464000,Henan,China;Henan Aerospace Precision Manufacturing Co.,Ltd.,Xinyang 464000,Henan,China)

机构地区：[1]空军工程大学航空机务士官学校,河南信阳464000 [2]河南航天精工制造有限公司,河南信阳464000

出　　处：《铸造》2023年第4期443-446,共4页Foundry

摘　　要：针对某型飞机ZL114A铝合金支架开裂的现象,主要采用了化学成分分析、断口分析、组织分析、力学性能测试等方法,分析了其开裂原因。结果表明:铝合金支架的化学成分符合HB962—2001要求,强度、硬度均符合标准,而塑性不达标。经过分析,认为开裂是由于铸造过程中未进行有效变质处理,导致在铸造过程中生成了粗大的针状相,从而降低了材料的塑性,在拆卸时受到一次性较大冲击载荷时,在轴孔受力部位形成裂纹。In this paper,in view of the cracking phenomenon of a certain aircraft ZL114A aluminum alloy bracket,the cracking cause was analyzed mainly using chemical composition analysis,fracture analysis,microstructure analysis,mechanical properties test and other methods,.The results showed that the chemical composition of the aluminum alloy bracket met the requirements of HB962—2001,the strength and hardness met the standards,but the plasticity was not up to the standard.After analysis,it is considered that the cracking was due to the fact that there was no effective modification treatment in the casting process,which led to the formation of coarse acicular phase in the casting process,thus reducing the plasticity of the material.When being subjected to a one-time large impact load during disassembly,the cracks were formed in the bearing part of the shaft hole.

关 键 词：ZL114A 断裂 显微组织 失效分析 

分 类 号：TG146.21[一般工业技术—材料科学与工程]