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论文:2014,Vol:32,Issue(5):693-699 |
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引用本文： |
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李晓鹏, 宋文萍, 韩忠华, 朱震. 类乘波体飞行器机身与安定面对舵效影响及干扰机理研究[J]. 西北工业大学 |
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Li Xiaopeng, Song Wenping, Han Zhonghua, Zhu Zhen. Numerical Study on Influence of Fuselage and Stabilizer on ControlSurface Efficiency and Interference Characteristics for a Hypersonic Waverider-Derived Configuration[J]. Northwestern polytechnical university |
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| 类乘波体飞行器机身与安定面对舵效影响及干扰机理研究 |
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| 李晓鹏, 宋文萍, 韩忠华, 朱震 |
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| 西北工业大学 翼型叶栅空气动力学国家重点实验室, 陕西 西安 710072 |
| 摘要: |
| 基于Navier-Stokes方程,数值模拟了高超声速情况下,类乘波构形机身带安定面与舵面粘性绕流,找出关键参数对舵面效率的影响规律,并对其干扰机理进行了分析。研究结果表明:1安定面与舵面的水平距离、垂直距离、机身的存在都会对舵面效率产生影响;2在有机身和无机身的2种构型下,水平距离与垂直距离对舵面效率影响趋势一致,相对影响量也基本相同;3在攻角4°状态下,水平距离对舵面效率的干扰影响小,因此在水平舵面安装位置固定的情况下,为了增加飞行器纵向静稳定性,安定面可以适当地靠近水平舵面;而垂直距离对舵面效率的干扰影响较大,因此,为了减小干扰,安定面的安装位置尽可能地靠上一些;4由于机身的存在,舵面根部受到了机身低马赫数区较强的干扰,造成了舵面效率降低,与无机身的构型相比较,机身的存在使得舵面效率降低可达到20%,因而应该采取适当措施减小机身干扰。文中的研究结果可为高超声速飞行器布局设计提供定量与定性的参考依据。 |
| 关键词:
高超声速
舵面效率
安定面
舵面
乘波构形机身
Navier-Stokes方程
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| Numerical Study on Influence of Fuselage and Stabilizer on ControlSurface Efficiency and Interference Characteristics for a Hypersonic Waverider-Derived Configuration |
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| Li Xiaopeng, Song Wenping, Han Zhonghua, Zhu Zhen |
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| National Key Laboratory of Science and Technology on Aerodynamic Design and Research atNorthwestern Polytechnical University, Xi'an 710072, China |
| Abstract: |
| In this paper the hypersonic flow around waverider-Dlerived vehicle has been numerically simulated bysolving Reynoldsaveraged Navier Stokes equations.The influence of the key parameters on the control surface effi-ciency is obtained and the interference mechanism is explored.According to the simulation results and their analy-sis,some preliminary conclusions can be drawn:(1)the horizontal and vertical distance between stabilizer andcontrol surface,and the existence of the waverider-Dlerived vehicle's body will affect the control surface efficiency;(2) whether with or without fuselage,the same affecting trend are obtained by the horizontal and vertical distancebetween stabilizer and control surface;(3) under the angle of attack of 40,the horizontal distance has little dis-turbance on control surface efficiency;in order to increase the longitudinal static stability of the vehicle,the stabi-lizer can be mounted reasonably close to the control surface;the vertical distance has large influence on the controlsurface efficiency;therefore,to reduce the amount of interference on the horizontal control surface effectivenessthe stabilizer should be mounted in vertical position as high up as possible;(4) with the presence of the body theroot part of control surface is strongly interfered with by the body's lower Mach number region,hence nearly 20%efficiency is lost compared with the condition without the body.Preliminary conclusion,we believe,are of somequantitative and qualitative value to waverider-Dlerived hypersonic vehicle design. |
| Key words:
angle of attack
aerodynamic configurations
computer simulation
control surfaces
efficienc hyper-sonic vehicles
Mach number
mesh generation
Navier Stokes equations
numerical methods
pres-sure distribution
schematic diagrams;body of waverider-derived vehicle
control surface effective-ness
stabilizer
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| 收稿日期: 2013-10-15
修回日期:
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| DOI: |
| 通讯作者:
Email： |
| 作者简介: 李晓鹏(1982-)西北工业人学博士研究生，主要从事气动设计与计算流体力学研究。
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