战斗机大迎角气动特性研究技术的发展与应用  

Development and application of aerodynamic research technologies for fighters at high angle of attack

作　　者：王海峰[1] 展京霞 陈科[1] 陈翔 陈梓钧 WANG Haifeng;ZHAN Jingxia;CHEN Ke;CHEN Xiang;CHEN Zijun(Chengdu Aircraft Design&Research Institute,Chengdu 610091,China)

机构地区：[1]成都飞机设计研究所,成都610091

出　　处：《空气动力学学报》2022年第1期1-25,共25页Acta Aerodynamica Sinica

摘　　要：飞机布局的大迎角气动特性是决定飞行包线左边界的主要因素之一。飞行包线左边界区域的扩展增强了飞机的大迎角机动性和敏捷性,但是同时也极大地挑战着飞机的安全。几十年来,随着大迎角飞行研究技术的发展,战斗机飞行不断突破失速迎角附近及以上区域,将飞行左边界左移,扩大了飞行包线,减少了飞行限制,挖掘了战斗机的作战潜能。本文对战斗机大迎角飞行相关的气动特性研究技术,包括流动机理研究、数值计算方法研究、风洞气动试验、气动建模与数据库构建、气动与控制综合验证等关键技术的发展与应用进行了阐述。基于这些技术的发展,结合工程实践经验,提出了战斗机大迎角气动特性研究的整体思路和方法,包括大迎角气动力预先设计、气动力获取、气动力表达、气动力综合分析和气动-运动-控制一体化验证五个部分,以供相关装备研制参考。Left boundary of the flight envelope is mainly determined by high angle of attack aerodynamic characteristics of the aircraft layout.The expansion of the left boundary of flight envelope enhances the aircraft’s mobility and agility,but it also greatly challenges flight safety.Over the past decades,with the development of flight research technologies for high angle of attack,fighters continuously broke through the flight regime near and above the stalling angle of attack,which pushed left boundary more,expanded flight envelope,reduced flight restrictions,and squeezed more flight potential.This paper elaborates the development and application of key technologies related to high angle of attack aerodynamics including researches on the flow mechanism,numerical computations,wind tunnel tests,aerodynamic modeling and database construction,and integrated verification of aerodynamics and control laws.Along with the author’s engineering practice,a systematic and close-loop aerodynamic design and analysis method for flighters at high angle of attack is proposed,consisting of five major parts including pre-design,data-acquisition,aerodynamic force expression,integrated analysis,and integrated aerodynamics/motion/control test,which would be used as reference for related equipment development.

关 键 词：大迎角 非线性非定常气动力 风洞试验 气动力模型 气动-运动-控制综合试验 

分 类 号：V211.24[航空宇航科学与技术—航空宇航推进理论与工程]