包名,李大海,刘红艳.无人直升机主桨毂中央件疲劳试验加载技术研究[J].装备环境工程,2022,19(11):84-94. BAO Ming,LI Da-hai,LIU Hong-yan.Loading Technology about Main Rotor Hub of Unmanned Helicopter in Fatigue Test[J].Equipment Environmental Engineering,2022,19(11):84-94.
无人直升机主桨毂中央件疲劳试验加载技术研究
Loading Technology about Main Rotor Hub of Unmanned Helicopter in Fatigue Test
  
DOI:10.7643/issn.1672-9242.2022.11.012
中文关键词:  旋翼构型  无人直升机  主桨毂中央件  疲劳试验加载技术  调试方法  离心力加载  试验加载精度中图分类号:V216.3 文献标识码:A 文章编号:1672-9242(2022)11-0084-11
英文关键词:rotor configuration  unmanned helicopter  main rotor hub  fatigue test loading technology  debug method  centrifugal force loading mode  test loading accuracy
基金项目:
作者单位
包名 中国直升机设计研究所,江西 景德镇 333001 
李大海 中国直升机设计研究所,江西 景德镇 333001 
刘红艳 中国直升机设计研究所,江西 景德镇 333001 
AuthorInstitution
BAO Ming China Helicopter Research and Development Institute, Jiangxi Jingdezhen 333001, China 
LI Da-hai China Helicopter Research and Development Institute, Jiangxi Jingdezhen 333001, China 
LIU Hong-yan China Helicopter Research and Development Institute, Jiangxi Jingdezhen 333001, China 
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中文摘要:
      首先基于2种不同旋翼构型无人直升机主桨毂中央件的结构形式和承载特点,介绍了现代无人直升机中央件疲劳试验加载技术及调试方法。随后对比分析了中央件疲劳试验中2种不同的离心力加载形式,给试验载荷(包括相位、位移和精度等)、试验频率及试验运行状态等方面带来的影响。最后,针对上述分析结果提出解决办法,为优化试验方案,提高试验加载精度,提升试验效率,保障中央件在地面疲劳试验中合理承载、传载及准确评估其结构疲劳寿命等提供了可靠的试验技术支撑,同时也为今后类似结构的主桨毂中央件地面疲劳试验技术发展提供了极有价值的参考和借鉴。
英文摘要:
      Firstly, based on the structural style and the bearding characteristics of the main rotor hub about two different rotor configurations from unmanned helicopter, some new methods of loading and debugging technology about main rotor hub fatigue test for unmanned helicopter are introduced. Then, by analyzing the two different centrifugal force loading mode, some effects about test load (including phase difference, displacement, and precision), test frequency, and test running status can be gotten through the result. Finally, some solutions for aforementioned analytical results are put forward, which can not only solve the problem of lower loading accuracy, guarantee the test running smoothly and loading reasonably in the fatigue test, accurately assess its fatigue life span, but also provide great valuable reference for the development of similar main rotor hub ground fatigue test technology about unmanned helicopter.
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