发动机燃气舵气动特性研究  

Study on Aerodynamic Characteristics of Gas Vane in Solid Rocket Motor

作　　者：房雷[1,2] 莫展[1,2] 杜长宝[1] 王君祺[1] 

机构地区：[1]中国空空导弹研究院,河南洛阳471009 [2]航空制导武器航空科技重点实验室,河南洛阳471009

出　　处：《航空兵器》2013年第4期34-36,60,共4页Aero Weaponry

摘　　要：采用仿真方法对某种矩形燃气舵推力矢量装置的气动特性进行研究,得到不同舵片配置、不同舵偏角下多种工况流场仿真结果。分析表明,该燃气舵在0°～20°舵偏角范围内,产生的垂直控制力、水平控制力均随舵偏角的增大而增大,垂直控制力与舵偏角具有较高的单调线性度,水平控制力随着舵偏角的增大,变化梯度呈逐渐增大的趋势。Numerical simulation is applied to study the aerodynamic performance of the rectangular gas vane thrust vectoring system and the flow field simulation results of working conditions under different vane configuration and different vane deflection angles are attained. The results show that both the vertical force and the horizontal force enhance with the increasing of the vane deflection angle, when the vane de- flection angle adds in the range of 0° -20°. The vertical force changes high linear monotone with the vane deflection angle, while the grads of the horizontal force augments as the aggrandizing of vane deflection angle.

关 键 词：推力矢量 燃气舵 气动特性 数值仿真 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]