| 高超声速变形飞行器翼面变形模式分析 |
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| 引用本文： | 彭悟宇,杨涛,涂建秋,丰志伟,张斌.高超声速变形飞行器翼面变形模式分析[J].国防科技大学学报,2018,40(3):15-21. |
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| 作者姓名： | 彭悟宇 杨涛 涂建秋 丰志伟 张斌 |
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| 作者单位： | 国防科技大学空天科学学院;中国运载火箭技术研究院 |
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| 基金项目： | 国防科技大学科研计划资助项目（JC-13-04） |
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| 摘 要： | 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。
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| 关 键 词： | 变形飞行器 高超声速 翼面变形模式 升阻比 操稳比 |
| 收稿时间： | 2017/4/10 0:00:00 |
Analysis on wing deformation modes of hypersonic morphing aircraft |
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| PENG Wuyu,YANG Tao,TU Jianqiu,FENG Zhiwei and ZHANG Bin.Analysis on wing deformation modes of hypersonic morphing aircraft[J].Journal of National University of Defense Technology,2018,40(3):15-21. |
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| Authors: | PENG Wuyu YANG Tao TU Jianqiu FENG Zhiwei and ZHANG Bin |
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| Institution: | 1. College of Aeronautics and Astronautics, National University of Defense Technology, Changsha 410073, China,1. College of Aeronautics and Astronautics, National University of Defense Technology, Changsha 410073, China,2. China Academy of Launch Vehicle Technology, Beijing 100076, China,1. College of Aeronautics and Astronautics, National University of Defense Technology, Changsha 410073, China and 1. College of Aeronautics and Astronautics, National University of Defense Technology, Changsha 410073, China |
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| 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 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. |
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| Keywords: | morphing aircraft hypersonic wing deformation modes lift-to-drag ratio stability and controllability |
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