飞机大迎角飞行问题研究综述  

Review of the Study on High-angle-of-attack Flight Problems of Aircraft

作　　者：张子军[1] 赵彤 孙烨 李宏信[1] ZHANG Zijun;ZHAO Tong;SUN Ye;LI Hongxin(The General and Aerodynamic Design Department,AVIC Shenyang Aircraft Design and Research Institute,Shenyang 110000,China;College of Aviation,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)

机构地区：[1]航空工业沈阳飞机设计研究所总体气动部,沈阳110000 [2]南京航空航天大学航空学院,南京210016

出　　处：《航空工程进展》2022年第3期74-85,共12页Advances in Aeronautical Science and Engineering

摘　　要：近距格斗在未来的空战格斗中仍不可避免,大迎角下精准且快速的机头指向能力是空优战斗机必须具备的基本特征,对提升飞机本身的生存能力和夺取制空权具有重要意义。本文根据国内外战斗机的大迎角飞行特点,对大迎角气动特性、风洞试验方法、气动力建模方法、非线性飞行动力学特性分析方法、大迎角控制律设计、飞行试验等方法进行了综合论述,对未来大迎角飞行问题的研究方向进行了展望。The close combat in air battle is still inevitable in future. The accurate and agile nose-pointing capability at high-angle-of-attack is still essential and significant for fighter to survive and gain air superiority. According to the high-angle-of-attack flight characteristics of fighter at home and abroad,the high-angle-of-attack aerodynamic,wind tunnel experiments method,aerodynamic modeling method,nonlinear flight dynamics analysis method,high-angle-of-attack control law design and flight test are reviewed. The research direction of high-angle-of-attack flight in the future is prospected.

关 键 词：气动力建模 大迎角动力学分析 控制律设计 失速 尾旋 

分 类 号：V212[航空宇航科学与技术—航空宇航推进理论与工程] V271.4