| 晁伟召,宋卓异,杨春秋,邱爽,赵宇航,黄小兰.某航空弹药尾翼传动部件振动环境断裂失效分析[J].装备环境工程,2024,21(10):53-61. CHAO Weizhao,SONG Zhuoyi,YANG Chunqiu,QIU Shuang,ZHAO Yuhang,HUANG Xiaolan.Analysis of Fracture Failure in a Tail Wing Transmission Component of Aviation Ammunition under Vibration Environment[J].Equipment Environmental Engineering,2024,21(10):53-61. |
| 某航空弹药尾翼传动部件振动环境断裂失效分析 |
| Analysis of Fracture Failure in a Tail Wing Transmission Component of Aviation Ammunition under Vibration Environment |
| 投稿时间：2024-05-20 修订日期：2024-07-06 |
| DOI：10.7643/issn.1672-9242.2024.10.007 |
| 中文关键词: 航空弹药 振动环境 失效分析 振动疲劳仿真 疲劳寿命 故障复现中图分类号:TJ410.3 文献标志码:A 文章编号:1672-9242(2024)10-0053-09 |
| 英文关键词:aviation ammunition vibration environment failure analysis vibration fatigue simulation fatigue life failure reproduction |
| 基金项目:装备预研项目(302060501) |
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| Author | Institution |
| CHAO Weizhao | Norinco Group Aviation Ammunition Institute, Harbin 150030, China |
| SONG Zhuoyi | Norinco Group Aviation Ammunition Institute, Harbin 150030, China |
| YANG Chunqiu | Norinco Group Aviation Ammunition Institute, Harbin 150030, China |
| QIU Shuang | Norinco Group Aviation Ammunition Institute, Harbin 150030, China |
| ZHAO Yuhang | Norinco Group Aviation Ammunition Institute, Harbin 150030, China |
| HUANG Xiaolan | Norinco Group Aviation Ammunition Institute, Harbin 150030, China |
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| 中文摘要: |
| 目的 某航空弹药尾翼传动部件在发动机热试车试验中出现断裂故障，需分析失效原因、实验室故障复现与结构优化设计，提升可靠性。方法 首先进行尾翼传动部件断口形貌分析，判断损伤性质。其次，通过频域振动疲劳仿真方法，分析不同状态尾翼传动部件应力损伤位置最大处的振动疲劳寿命，确认失效原因。再通过实验室试验复现外场试验故障模式，最后通过环境试验验证改进有效性。结果 模拟振动条件下，尾翼传动部件的最大损伤位置与断裂失效位置接近，锁定状态和非锁定状态振动疲劳仿真寿命分别为7 516 s和34 710 s，明晰了失效原因。通过实验室振动试验复现了故障，且机理一致，改进方法有效，并通过了试验考核。结论 失效分析、验证与改进方法充足有效，可以为同类装备振动环境故障处理参考。 |
| 英文摘要: |
| Fracture failure occurred in a tail wing transmission component of aviation ammunition during the hot test if engine, so the work aims to analyze the cause of the failure, reproduce the failure in the laboratory, and optimize the structure design to improve reliability. Firstly, the fracture morphology of the tail wing transmission component was analyzed to determine the nature of the damage. Secondly, the frequency domain vibration fatigue simulation method was used to analyze the vibration fatigue life of the maximum stress damage location of the tail wing transmission component in different states, and to confirm the cause of failure. Thirdly, the failure mode of the tail wing transmission component in the field was reproduced through laboratory test and finally, the effectiveness of the improvement was verified through environmental test. The maximum damage location of the tail wing transmission component under simulated vibration condition was close to the failure location, and the vibration fatigue simulation life in the locked state and unlocked state was 7 516 s and 34 710 s, respectively, clarifying the cause of failure. The failure was reproduced through laboratory vibration tests, and the mechanisms were consistent. The improvement methods were effective and passed the test evaluation. The methods of failure analysis, verification, and improvement are sufficient and effective, which can serve as a reference for handling failures of similar equipment under vibration environment. |
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