电工技术学报  2023, Vol. 38 Issue (1): 131-139    DOI: 10.19595/j.cnki.1000-6753.tces.211461
电工理论 |
高速滑动电接触电枢表面动态磨损过程研究
李白, 鲁军勇, 谭赛, 张永胜, 蔡喜元
海军工程大学舰船综合电力技术国防科技重点实验室 武汉 430074
Research on Dynamic Wear Process of Armature Surface in High-Speed Sliding Electric Contact
Li Bai, Lu Junyong, Tan Sai, Zhang Yongsheng, Cai Xiyuan
National Key Laboratory of Science and Technology on Vessel Integrated Power System Naval University of Engineering Wuhan 430074 China
全文: PDF (2650 KB)   HTML
输出: BibTeX | EndNote (RIS)      
摘要 电枢是电磁发射装置的关键部件,其表面磨损是引起发射过程中转捩的原因之一,同时磨损也会严重削弱电枢本体的力学性能,影响发射安全性,因此有必要对高速滑动电接触电枢表面的动态磨损过程进行深入分析。首先,分析电枢表面产生磨损的机理,厘清相关耦合因素;其次,考虑表面磨损量变化、温度升高及电枢尾翼向外扩张过程中反向受力的影响,建立电枢尾翼磨损量的理论计算模型,研究其磨损规律;最后,考虑电磁场-温度场-应力场-磨损等耦合因素建立三维有限元计算模型,对电枢尾翼磨损量进行更为准确的分析。结果表明:①电枢表面磨损量是在电因素及力因素的共同作用下产生的;②考虑了表面磨损量变化、温度及电枢尾翼向外扩张过程中反向受力等因素影响后,分析得到电枢表面磨损量较不考虑时小19.5%,但考虑后与实测值更为接近,证明了分析过程中上述影响因素不可忽略;③相比理论分析模型中对电枢尾翼法向力分量及反向受力的近似计算方法,有限元模型更为精确,其计算得到电枢尾翼磨损量与实测值也更为接近,验证了所建立模型的准确性。该文所建立模型及分析结果对于后续优化电枢结构、提高枢轨接触性能及保证发射安全性具有重要意义。
服务
把本文推荐给朋友
加入我的书架
加入引用管理器
E-mail Alert
RSS
作者相关文章
李白
鲁军勇
谭赛
张永胜
蔡喜元
关键词 电磁发射装置电枢滑动电接触表面磨损多物理场耦合    
Abstract:Armature is a key component of the electromagnetic launcher. During the dynamic launch process, its surface will be seriously worn, which will bring the following two problems: ① After the armature is worn and melted, it will form an aluminum layer in the bore, which will attach to the rail surface, increase the surface roughness, and affect the contact state between armature and rail during the subsequent launch process; ② After the tail is worn, the mechanical property that the armature can withstand is greatly weakened, which affects the launch safety. Therefore, it is of great significance to analyze the dynamic wear process of the armature surface in the high-speed sliding electrical contact process for controlling its surface wear, optimizing the armature structure, and improving the armature rail contact performance.
First of all, by studying the physical process between the armature and rail during dynamic launch process, the results show that under the combined action of Joule heat and friction heat during the launch process, the armature surface temperature will rise sharply. Once it exceeds the material melting point, it will melt and cause wear. Therefore, the wear of the armature surface is caused by the combined action of electrical factors and force factors. Through the analysis of the muzzle armature X-ray photos in the early stage, it is concluded that the wear of the armature surface is not uniform from the tail end to the front end. In fact, the wear of the tail end of the armature is the largest, and the closer to the head, the smaller the wear is, which is approximately linear. On the basis of the above analysis results, taking into account the influence of surface wear changes, temperature rise and reverse force during the outward expansion of the armature tail, a theoretical calculation model for the wear of the armature tail is established, and its wear laws are studied. The average wear of the end of the armature tail is obtained. Then, the equal volume conversion method is used to convert the model into a linear wear model, and then the real wear of the end of the tail is obtained. The results show that:, After considering the influence of factors such as the change of surface wear amount, temperature and reverse force during the outward expansion of the armature tail, the analysis shows that the armature surface wear amount is 19.5% less than that when it is not considered, but it is closer to the measured value after considering, which proves that the above influence factors cannot be ignored in the analysis process. Finally, considering electromagnetic field temperature field stress field wear and other coupling factors, a three-dimensional finite element calculation model is established to more accurately analyze the wear amount of the armature tail, and the finite element is compared with the theoretical calculation results. The results show that the finite element model is more accurate than the approximate calculation method for the normal force component and reverse force of the armature tail in the theoretical analysis model, The calculated wear of the armature tail is closer to the measured value, which verifies the accuracy of the model. The model and analysis results established in this paper will help to optimize the armature structure, improve the contact performance between the armature and the rail, and ensure the safety of projectile launching in the bore.
Key wordsElectromagnetic launcher    armature    sliding electric contact    surface wear    coupling of multiple physical fields   
收稿日期: 2021-09-14     
PACS: TM359.4  
基金资助:国家自然科学基金(51925704,51877214,51607187,51907203)和湖北省自然科学基金(2020CFB341)资助项目
通讯作者: 鲁军勇,男,1978年生,教授,博士生导师,研究方向为电磁发射技术、直线电机设计及控制技术。E-mail:jylu2019@163.com   
作者简介: 李白,男,1989年生,助理研究员,研究方向为电磁发射技术。E-mail:libai1203@163.com
引用本文:   
李白, 鲁军勇, 谭赛, 张永胜, 蔡喜元. 高速滑动电接触电枢表面动态磨损过程研究[J]. 电工技术学报, 2023, 38(1): 131-139. Li Bai, Lu Junyong, Tan Sai, Zhang Yongsheng, Cai Xiyuan. Research on Dynamic Wear Process of Armature Surface in High-Speed Sliding Electric Contact. Transactions of China Electrotechnical Society, 2023, 38(1): 131-139.
链接本文:  
https://dgjsxb.ces-transaction.com/CN/10.19595/j.cnki.1000-6753.tces.211461          https://dgjsxb.ces-transaction.com/CN/Y2023/V38/I1/131