| 引用本文: | 陈钰,宗群,张秀云,窦立谦.直升机旋翼振动主动控制方法研究进展[J].哈尔滨工业大学学报,2023,55(8):1.DOI:10.11918/202210097 |
| CHEN Yu,ZONG Qun,ZHANG Xiuyun,DOU Liqian.Research progress of active vibration control methods for helicopter rotor[J].Journal of Harbin Institute of Technology,2023,55(8):1.DOI:10.11918/202210097 |
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| 摘要: |
| 直升机特有的旋翼动力学结构使其拥有极高的战略发展价值,但旋翼在工作过程中产生的振动问题也对直升机的飞行性能造成了严重影响,因此,研究旋翼振动控制方法对直升机性能提升有重大意义。针对由直升机主旋翼工作而引发的机身振动控制问题,首先,从旋翼引起机身振动的原因以及振动的频率特征出发,分析了主动振动控制的原理。其次,基于直升机振动的周期性质,将振动控制方法划分为频域控制和时域控制,并对频域方法以及时域方法中的时域高阶谐波方法、鲁棒方法、智能方法以及其相关试验成果展开综述及总结。另外,针对振动传递抑制技术进行了简单介绍,并对国内研究机构的主动振动控制试验进行了梳理。最后,归纳了振动控制方法存在的不足,并在此基础上指出了直升机主动控制方法的未来发展方向,应进一步深入针对稳定飞行状态的鲁棒自适应控制和针对全飞行状态的智能自学习控制方法研究,并开展面向性能提升的综合主动控制系统设计。 |
| 关键词: 直升机 旋翼 振动载荷 减振方法 主动控制 飞行试验 |
| DOI：10.11918/202210097 |
| 分类号:TU398+.9 |
| 文献标识码:A |
| 基金项目:国家自然科学基金(4,6) |
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| Research progress of active vibration control methods for helicopter rotor |
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CHEN Yu,ZONG Qun,ZHANG Xiuyun,DOU Liqian
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(School of Electrical and Information Engineering, Tianjin University, Tianjin 300072, China)
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| Abstract: |
| The rotor dynamic structure of a helicopter presents a high value of strategic development. As the vibration caused by rotor operation negatively impacts flying performance, the exploration of rotor vibration control methods is perceived as vital to the improvement of helicopter performance. Regarding the key frontier problem, the principle of active vibration control is scrutinized with the cause of fuselage vibration by rotor and the frequency characteristics of vibration considered. Then, the overall framework of helicopter active vibration control is described. The control methods are divided into frequency-domain and time-domain control on the basis of the periodic property of helicopter vibration. The higher harmonic control method, robust method, and intelligent method are reviewed and summarized, coupled with the related test results. Furthermore, vibration transfer suppression technology is briefly introduced, and active vibration control tests conducted home and abroad are reviewed. By summarizing the shortcomings of vibration control methods, the future research directions for active control methods are suggested: robust adaptive control for stable flight states, intelligent self-learning control for full flight states, and the design of integrated active control systems for performance improvement should be conducted. |
| Key words: helicopter rotor vibration loads vibration reduction method active control flight test |
