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论文:2022,Vol:40,Issue(2):401-406 |
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引用本文： |
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韩江旭, 刘南, 史晓鸣, 郭晋, 王松, 于贤鹏. 连续式跨声速风洞中带真实舵机的舵面颤振试验[J]. 西北工业大学学报 |
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HAN Jiangxu, LIU Nan, SHI Xiaoming, GUO Jin, WANG Song, YU Xianpeng. Flutter test of rudder with real servo actuator in continuous transonic wind tunnel[J]. Northwestern polytechnical university |
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| 连续式跨声速风洞中带真实舵机的舵面颤振试验 |
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| 韩江旭1,2, 刘南2, 史晓鸣3, 郭晋2, 王松2, 于贤鹏2 |
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1. 北京航空航天大学, 北京 100191;
2. 中国航空工业空气动力研究院, 辽宁 沈阳 110034;
3. 上海机电工程研究所, 上海 201109 |
| 摘要: |
| 颤振风洞试验是研究飞行器跨声速颤振特性的重要方法和手段，相比暂冲式风洞，连续式跨声速风洞的长时间运行能力和负压运行能力等优势非常适合开展颤振试验研究。重点突破连续式跨声速风洞颤振安全防护技术以及振动信号处理和分析技术，结合安全防护控制软件、防喘阀快速降速压和防护格栅网等手段，能够对模型和风洞起到良好的保护作用，利用谱峰值倒数外插能够在试验过程中获得较为可靠的颤振边界，为试验安全性起到良好的支撑作用。针对根部固支和舵机支撑(包括机械舵机和真实舵机)2种边界条件，利用定马赫数阶梯变速压和连续变速压2种方式开展了舵面颤振试验。结果表明:阶梯变速压和连续变速压2种方式得到的颤振边界非常接近，颤振速压差别不超过5%;真实舵机的作用对舵面颤振特性的影响很难通过数值计算方法获得，风洞试验是研究该问题的重要手段，试验结果表明反馈作用可以提高颤振速压，对所提舵面模型颤振速压提高约10%。 |
| 关键词:
颤振
风洞试验
连续式跨声速风洞
真实舵机
舵面
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| Flutter test of rudder with real servo actuator in continuous transonic wind tunnel |
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| HAN Jiangxu1,2, LIU Nan2, SHI Xiaoming3, GUO Jin2, WANG Song2, YU Xianpeng2 |
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1. Beihang University, Beijing 100191, China;
2. AVIC Aerodynamics Research Institute, Shenyang 110034, China;
3. Shanghai Electro-Mechanical Engineering Institute, Shanghai 201109, China |
| Abstract: |
| Flutter wind tunnel test is an important approach of investigation of transonic flutter characteristics of flight vehicle. Comparing with the blow-down wind tunnel, the long-running and low dynamic pressure capabilities of continuous transonic wind tunnel are very suitable for flutter test. The flutter safety protection and analysis of dynamic signals are developed. The safety protection control software, rapid reduction of Mach number and dynamic pressure, model debris catch screen are integrated, which can provide safety protection of test model and wind tunnel. During the test process, the flutter boundary can be achieved by interpolating the reciprocal of spectrum peak. The flutter tests of rudder are conduct through two methods of step and continuous varying dynamic pressure. It is illustrated that the error of flutter dynamic pressure is relatively small, less than 5% between the two methods. Meanwhile, the feedback effect of the real servo actuator on the flutter characteristics is hard to be obtained via numerical simulation. It is demonstrated that the flutter dynamic pressure has been increased by 10% due to the feedback effect. |
| Key words:
flutter
wind tunnel test
transonic continuous wind tunnel
real servo actuator
rudder
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| 收稿日期: 2021-07-11
修回日期:
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| DOI: 10.1051/jnwpu/20224020401 |
| 基金项目: 航空科学基金（2018ZA27007）资助 |
| 通讯作者: 刘南(1989-),中国航空工业空气动力研究院高级工程师,主要从事气动弹性设计、数值模拟和风洞试验技术研究。e-mail:aeroelasticliu@163.com
Email：aeroelasticliu@163.com |
| 作者简介: 韩江旭(1976-),北京航空航天大学博士研究生,主要从事气动弹性风洞试验技术研究。
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| 作者相关文章 |
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| 韩江旭 在本刊中的所有文章 |
| 刘南 在本刊中的所有文章 |
| 史晓鸣 在本刊中的所有文章 |
| 郭晋 在本刊中的所有文章 |
| 王松 在本刊中的所有文章 |
| 于贤鹏 在本刊中的所有文章 |
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1．许行之, 高亚奎, 章卫国.考虑助力器动力学的舵系统结构非线性颤振特性分析[J]. 西北工业大学学报, 2015,33(3): 472-477 |
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