弹体旋转对超音速射流元件的影响研究  

Effects of missile rotation on supersonic fluidic element

作　　者：王玉芳[1] 杨树兴[1] 徐勇[1] 毛雪瑞[1] 

机构地区：[1]北京理工大学机电工程学院,北京100081

出　　处：《固体火箭技术》2005年第3期161-164,共4页Journal of Solid Rocket Technology

基　　金：教育部跨世纪人才培养计划基金(100762021)

摘　　要：研究了弹体旋转对超音速射流元件(SFE)的内部流场结构及输出推力特性的影响,并采用二维N-S方程以及RNGκ-ε湍流模型,用计算流体力学(CFD)数值模拟方法和滑移网格技术进行了数值模拟。结果表明,弹体旋转对超音速射流元件内部流场结构几乎没有影响,而对姿态控制发动机的控制推力大小和方向的影响不容忽视。所得结论可为旋转弹姿态控制系统的总体设计以及超音速射流元件的结构及气动参数选择提供依据。The effects of missile rotation on the irmer flow field and the output thrust characteristic of supersonic fluidic elements （SFE） were investigated. By using the two-dimensional Navier- Stokes equations and RiNG k-ε turbulent model, numerical simulation method of computational fluid dynamics （CFD） and technique of sliding grids were used for numerical simulation . The results show that the missile rotation has hardly effect on inner flow field structure of SFE, but some effects on the control thrust of attitude control motors both in magnitude and in direction. These conclusions can be used for system design of rotating missile in the attitude control system and selection of structure and pneumatic parameters for supersonic fluidic elements.

关 键 词：超音速射流元件 计算流体力学 弹体旋转 N—S方程 数值模拟 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]