| 面向先进战斗机研制的风洞模型飞行试验技术 |
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| 引用本文： | 岑飞,聂博文,刘志涛,郭林亮,孙海生,李清. 面向先进战斗机研制的风洞模型飞行试验技术[J]. 航空学报, 2020, 41(6): 523444-523444. DOI: 10.7527/S1000-6893.2019.23444 |
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| 作者姓名： | 岑飞 聂博文 刘志涛 郭林亮 孙海生 李清 |
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| 作者单位： | 1. 清华大学 自动化系, 北京 100084;2. 中国空气动力研究与发展中心 低速空气动力研究所, 绵阳 621000;3. 国防科技大学 智能科学学院, 长沙 410073 |
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| 基金项目： | 新一代人工智能重大项目;信息化部工业转型升级专项;国家自然科学基金;清华大学自主科研计划 |
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| 摘 要： | 高机动性先进战斗机气动布局与飞控系统设计面临愈加严峻的流动/运动/控制耦合问题，大迎角飞行以及推力矢量等高新技术应用也使其在研制过程中面临更高的技术风险，风洞模型飞行试验是实现飞行器气动/飞行/控制一体化研究、降低研制技术风险的重要手段。介绍了低速风洞模型飞行试验技术原理及国内外发展现状，对试验技术主要特点及其在支撑先进战斗机研制中的作用、应用范围、应用阶段以及面临的主要挑战进行了分析，为试验技术发展和应用提供参考。发展和应用低速风洞模型飞行试验技术，有利于充分挖掘战斗机的气动性能与控制性能，降低试飞风险，是新一代战斗机研制、新技术工程化应用的重要支撑技术。
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| 关 键 词： | 风洞试验 飞行试验 飞行控制 大迎角 高机动性 |
| 收稿时间： | 2019-09-03 |
| 修稿时间： | 2019-10-21 |
Wind tunnel model flight test technique for advanced fighter aircraft design |
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| CEN Fei,NIE Bowen,LIU Zhitao,GUO Linliang,SUN Haisheng,LI Qing. Wind tunnel model flight test technique for advanced fighter aircraft design[J]. Acta Aeronautica et Astronautica Sinica, 2020, 41(6): 523444-523444. DOI: 10.7527/S1000-6893.2019.23444 |
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| Authors: | CEN Fei NIE Bowen LIU Zhitao GUO Linliang SUN Haisheng LI Qing |
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| Affiliation: | 1. Department of Automation, Tsinghua University, Beijing 100084, China;2. Low Speed Aerodynamics Institute, China Aerodynamics Research and Development Center, Mianyang 621000, China;3. College of Mechatronics and Automation, National University of Defense Technology, Changsha 410073, China |
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| Abstract: | The design of aerodynamic configuration and control system for high maneuverability fighter aircraft has encountered severe problems regarding to flow/motion/control coupling. Furthermore, application of radical technologies makes it face higher technical risks during the development process. Wind tunnel model flight test is a significant approach to studying the aerodynamics/dynamics/control characteristic of aircraft and to reducing the technical risks. The principle of low speed wind tunnel model flight test technology and its state-of-the-arts are introduced. The main characteristics of the test and its role in supporting the development of advanced fighter aircraft, application stage, and main challenges are analyzed, providing guidelines for the development and application of the test technique. The development and application of low-speed wind tunnel model flight test technology is a promising way to understand and optimize the aerodynamic characteristics and control performance of fight aircraft. It has become an important supporting technology for developing new generation fighters, reducing risks for flight test of full-scale aircraft, and accelerating the process of new technologies applying to industry. |
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| Keywords: | wind tunnel test flight test flight control high angle of attack high maneuverability |
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