某型飞机襟翼导轨支架开裂原因  

Cracking reasons of a certain type of aircraft flap track bracket

作　　者：赵晨迪 孙一 杨秀锋 罗博 ZHAO Chendi;SUN Yi;YANG Xiufeng;LUO Bo(Maintenance Department,Civil Aviation Flight University of China,Guanghan 618307,China;Aircraft Repair&Overhaul Plant,Civil Aviation Flight University of China,Guanghan 618307,China)

机构地区：[1]中国民用航空飞行学院机务处,广汉618307 [2]中国民用航空飞行学院飞机修理厂,广汉618307

出　　处：《理化检验（物理分册）》2023年第7期43-46,共4页Physical Testing and Chemical Analysis(Part A:Physical Testing)

基　　金：中央高校基本科研业务费专项资金资助项目(J2023-039);四川省通用航空器维修工程技术研究中心项目(GAMRC2021YB05)。

摘　　要：某型通用飞机在飞行时其左侧襟翼导轨支架发生开裂。采用宏观观察、化学成分分析、扫描电镜分析、硬度测试及有限元分析等方法研究了该支架开裂的原因。结果表明:裂纹起源于襟翼导轨支架下部拐点的尖角处,断口呈疲劳条带特征,说明该支架发生了疲劳开裂;襟翼收放产生的交变应力和高循环次数是造成支架疲劳开裂的主要原因。采用安装加强补片的方法可以提高支架应力集中区域的强度。The left flap track bracket of a certain type of general aircraft cracked during flight.The reasons for the cracking of the scaffold were studied by macroscopic observation,chemical composition analysis,scanning electron microscopy analysis,hardness testing and finite element analysis.The results show that the cracks originated from the sharp corner of the lower inflection point of the flap track bracket and the fracture showed the characteristics of fatigue strips,indicating that the bracket had fatigue cracking.The alternating stress caused by flap retraction and high cycle times were the main causes of fatigue cracking of the bracket.Installing reinforcement patches could improve the strength of the stress concentration area of the bracket.

关 键 词：襟翼导轨支架 2A12铝合金 疲劳开裂 应力集中 有限元分析 

分 类 号：TB31[一般工业技术—材料科学与工程] TG115.2[金属学及工艺—物理冶金]