涡流阀调节特性冷流实验研究  

Cold Flow Test Investigation on Modulation Property of Fluidic Vortex Valve

作　　者：孙兵 杨振华 权维利 戚军 

机构地区：[1]中国航天科工集团第六研究院第41所,呼和浩特010010

出　　处：《弹箭与制导学报》2014年第6期107-109,共3页Journal of Projectiles,Rockets,Missiles and Guidance

摘　　要：涡流阀方案是实现固体发动机推力调节的一种很有前途的技术途径。文中利用冷流实验系统开展了涡流阀控制流的流量和压强对调节能力和响应特性影响的冷流实验研究。研究结果表明:控制流的压强决定了涡流阀调节压强;提高控制流压强和流量有利于提高涡流阀调节能力和响应性能;在压强变化量一致的情况下,提高控制流压强和流量有利于提高涡流阀响应性能。研究结论可为涡流阀固体变推力发动机的性能分析和设计提供实验支撑。Vortex valve is a promising approach to realize solid rocket motor thrust modulation. Effects of the flow rate and the pressure of control flow on regulative capability and response characteristics were discussed through cold flow test system. The results show that the operated pressure of vortex valve when the control flow was injected was determined by the pressure of control flow,the regulating ability and response characteristics of vortex valve were improved with the increase of flow rate and pressure of the control flow,under the same pressure variation,response performance of vortex valve were improved with the increase of the flow rate and the pressure of the control flow. The results can provide experimental support for analysis and design of variable thrust solid rocket motor based on vortex valve.

关 键 词：推力调节 涡流阀 冷流实验 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]