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  

Numerical Study on Influence of Fuselage and Stabilizer on Control Surface Efficiency and Interference Characteristics for a Hypersonic Waverider-Derived Configuration

作　　者：李晓鹏[1] 宋文萍[1] 韩忠华[1] 朱震[1] 

机构地区：[1]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

出　　处：《西北工业大学学报》2014年第5期693-699,共7页Journal of Northwestern Polytechnical University

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。In this paper, the hypersonic flow around waverider-derived vehicle has been numerically simulated by solving Reynolds-averaged 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 and control surface, and the existence of the waverider-derived 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 distance between stabilizer and control surface;（3） under the angle of attack of 4°, 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 control surface efficiency;therefore, to reduce the amount of interference on the horizontal control surface effectiveness, the stabilizer should be mounted in vertical position as high up as possible;（4） with the presence of the body, the root 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 some quantitative and qualitative value to waverider-derived hypersonic vehicle design.

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 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]