高超声速变形飞行器翼面变形模式分析
彭悟宇1，杨涛1，涂建秋2，丰志伟1,张斌1
（1.国防科学技术大学 航天科学与工程学院，湖南 长沙 410073；2.中国运载火箭研究院 战术武器事业部，北京
100076）
摘要：为了提高高超声速翼身组合式飞行器的射程，研究了采用不同翼面变形模式时，飞行器在马赫数3~8内的气动特性和翼面效率。针对典型的轴对称翼身组合式外形，采用Navier-Stokes（N-S）方程进行数值模拟，对伸缩、变后掠和二维折叠三种变形模式下的外形在超声速~高超声速来流条件下进行了模拟，并对升阻比、翼面单位面积升阻比和操稳特性进行了分析。结果表明：在超声速及高超声速范围内，变后掠变形模式在宽速域内升阻比提高明显，同时具备优良的翼面效率及操稳特性，在马赫数3~8范围内具有最优的综合性能。研究成果对高超声速翼身组合式变形飞行器布局的设计具有一定的指导意义。
关键词：变形飞行器；高超声速；翼面变形模式；升阻比；操稳比
中图分类号：V211 文献标志码：A 文章编号：
Analysis of the deformation modes of the hypersonic morphing
wing aircraft
PENG Wuyu1, YANG Tao1, TU Jianqiu2, FENG Zhiwei1, ZHANG Bin1
(1. College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073, China;
2. Tactical Weapons Division, China Academy of Launch Vehicle Technology, Beijing 100076, China)
Abstract: Aiming at improving the range of wing-body combination aircraft at hypersonic flow conditions. The aerodynamic characteristics and wing efficiency of morphing tactical missile with different deformation modes were studied. Navier-Stokes equations were used to simulate the flow field, the lift-to-drag ratio, wing efficiency, stability and controllability of different deformation modes as telescopic, variable sweep and two-dimensional folding are compared. It shows that under the condition of supersonic and hyper-sonic flow, take the results all in consideration, the variable sweep wing mode does better than the other two modes. The conclusion can offer some valuable guidance to the research and application of hypersonic morphing aircraft aerodynamic configuration.
Keywords: morphing aircraft; hypersonic; wing deformation modes; lift-to-drag ratio; stability