面向先进战斗机研制的风洞模型飞行试验技术

岑飞; 聂博文; 刘志涛; 郭林亮; 孙海生; 李清

doi:10.7527/S1000-6893.2019.23444

航空学报 >

2020 , Vol. 41 >Issue 6: 523444 - 523444

DOI: https://doi.org/10.7527/S1000-6893.2019.23444

流体力学与飞行力学

面向先进战斗机研制的风洞模型飞行试验技术

岑飞 ,
聂博文 ,
刘志涛 ,
郭林亮 ,
孙海生 ,
李清

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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

收稿日期: 2019-09-03

修回日期: 2019-10-21

网络出版日期: 2019-10-31

基金资助

国家自然科学基金（61771281）；新一代人工智能重大项目（2018AAA0101605）；2018年工业化和信息化部工业转型升级专项（ZB1825005）；清华大学自主科研计划（2018Z05JZY015）

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Wind tunnel model flight test technique for advanced fighter aircraft design

CEN Fei ,
NIE Bowen ,
LIU Zhitao ,
GUO Linliang ,
SUN Haisheng ,
LI Qing

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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

Received date: 2019-09-03

Revised date: 2019-10-21

Online published: 2019-10-31

Supported by

National Natural Science Foundation of China(61771281); New Generation Artificial Intelligence Major Project of China(2018AAA0101605); 2018 Industrial Internet Innovation and Development Project(ZB1825005); Tsinghua University Initiative Scientific Research Program(2018Z05JZY015)

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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。

关键词： 风洞试验; 飞行试验; 飞行控制; 大迎角; 高机动性

本文引用格式

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

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.

Key words： wind tunnel test; flight test; flight control; high angle of attack; high maneuverability

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