%0 Journal Article
%T 高超声速变形飞行器翼面变形模式分析
%A 彭悟宇
%A 杨涛
%A 涂建秋
%A 丰志伟
%A 张斌&lt
%A /br&gt
%A PENG Wuyu
%A YANG Tao
%A TU Jianqiu
%A FENG Zhiwei
%A ZHANG Bin
%J 国防科技大学学报
%D 2018
%R 10.11887/j.cn.201803003
%X 为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及高超声速来流条件下进行模拟，并对升阻比、翼面单位面积升阻比和操稳特性进行分析。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，其在马赫数3~8范围内具有最优的综合性能。研究成果能对高超声速翼身组合式变形飞行器布局设计提供参考，具有一定的指导意义。</br>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 at Mach number from 3 to 8 were studied. The Navier Stokes equations were used to simulate the flow field, and the lift to drag ratio, wing efficiency, stability and controllability of different deformation modes as telescopic, variable sweep and two dimensional folding were compared. Results show that under the condition of supersonic and hyper sonic flow, the variable sweep wing mode improves the lift to drag ratio significantly, and at the same time, it has excellent wing efficiency and stability and controllability. The mode performs best at the Mach number from 3 to 8. The conclusion can offer some valuable guidance to the research and application of hypersonic morphing aircraft aerodynamic configuration.
%K 变形飞行器 高超声速 翼面变形模式 升阻比 操稳比&lt
%K /br&gt
%K morphing aircraft hypersonic wing deformation modes lift-to-drag ratio stability and controllability
%U http://journal.nudt.edu.cn/gfkjdxxb/ch/reader/view_abstract.aspx?file_no=201803003&flag=1