| 某型飞机主起落架固定螺栓应力腐蚀裂纹扩展寿命估算及解决方法 |
| |
| 引用本文： | 付长安,张显余,朱卫国.某型飞机主起落架固定螺栓应力腐蚀裂纹扩展寿命估算及解决方法[J].飞机设计,2010,30(6):23-25. |
| |
| 作者姓名： | 付长安 张显余 朱卫国 |
| |
| 作者单位： | 空军航空大学航空机械工程系,吉林长春,130022 |
| |
| 摘 要： | 某型飞机主起落架固定螺栓是机翼上部框架与支柱外筒的主要连接件,据外场统计,从飞机使用至今该螺栓共断裂228件,断裂部位绝大多数在M33×1.5一端,螺纹根部至3扣之间。螺栓断裂时有的经过2 150个起落,而有的仅有几个起落。此问题的发生直接影响到飞机的飞行安全。本文应用应力腐蚀开裂和腐蚀疲劳的理论,计算分析了螺栓断裂的原因,同时提出了解决该问题的方法。
|
| 关 键 词： | 应力腐蚀 裂纹扩展速率 延迟断裂 |
Estimation of Stress Corrosion Crack Propagation Life of Fixed Bolt in the Main Landing Gear of a Certain Aircraft |
| |
| FU Chang-an,ZHANG Xian-yu,ZHU Wei-guo.Estimation of Stress Corrosion Crack Propagation Life of Fixed Bolt in the Main Landing Gear of a Certain Aircraft[J].Aircraft Design,2010,30(6):23-25. |
| |
| Authors: | FU Chang-an ZHANG Xian-yu ZHU Wei-guo |
| |
| Institution: | FU Chang-an,ZHANG Xian-yu,ZHU Wei-guo(Department of Aeronautical and Mechanical Engineering,Air Force Aviation University,Changchun 130022,China) |
| |
| Abstract: | The fixed bolt of a certain aircraft main landing gear is main bridge piece connecting the wing bulkhead with the pillar outside sleeve.According to the outfield statistics,this type of bolt break 288 from the airplane used until now,the break spot is mainly on the end of M33？？1.5,between the thread root and three buckles.Sometimes the bolt breaks after 2150 taking off and landing,but sometimes only several times.This problem has a direct effect on aircraft？？s flight safety.In this paper,using the theory of stress corrosion cracking and corrosion fatigue,the bolt break reason is analyzed,simultaneously the solution is given. |
| |
| Keywords: | stress corrosion crack propagation rate delayed fracture |
| 本文献已被 CNKI 维普 万方数据 等数据库收录！ |
|
