二元喉道倾斜矢量喷管调节方法  

Studies on Control Method of Two Dimensional Fluidic Throat Skewing Vectoring Nozzle

作　　者：李克新[1] 额日其太[1] 韩景[1] 

机构地区：[1]北京航空航天大学能源与动力工程学院,北京100191

出　　处：《推进技术》2012年第6期946-950,共5页Journal of Propulsion Technology

摘　　要：利用数值模拟方法,对二元喉道倾斜矢量喷管的调节方法进行了研究。研究结果表明,当喉道注气流量不变,随着扩张段注气流量逐渐增大,喷管内出现三种典型流动状态。当扩张段注气流量比较小时,喉道处声速线的形状和位置没有明显变化,在扩张段注气口前面形成亚声速区域;当喷管扩张段注气流量比较大时,喷管中出现了强激波系和上下贯通的亚声速区域,这时喷管内的流动损失最大,推力系数最低;进一步增大扩张段注气流量,声速线会从喷管喉道移动到喉道注气口和扩张段注气口之间,出现典型的喉道倾斜现象。单独控制流量系数可通过保持扩张段注气流量不变,改变喉道注气流量来实现;矢量角的控制可通过保持喉道注气流量不变,改变扩张段注气流量来实现。The numerical simulation was applied to study the control method of two dimensional fluidic throat skewing vec- toring nozzle. The results show that,when the throat section gas injection flow rate is unchanged, three typical states appear in the nozzle with the increase of the divergent section gas injection flow rate. When the flow rate of the divergent section gas in- jection is relatively small, the shape and position of sonic line in the nozzle throat have not been significantly changed,and a subsonic region appeares in the front of the divergent section gas injection. When the flow rate of the divergent section gas in- jection is relatively large, strong shock waves and large subsonic regions appear in the nozzle, with the maximum flow lost and the minimum thrust coefficient. With further increase for the flow rate of the divergent section gas injection, sonic line moves from the nozzle throat to a location between throat and divergent section gas injection which lead to the typical throat skewing. The flow coefficient can be controlled by keeping the divergent section gas injection flow rate unchanged and changing the throat section gas injection flow rate. The vector angle can be controlled by keeping the throat section gas injection flow rate unchanged and changing the divergent section gas injection flow rate.

关 键 词：矢量喷管 流体控制 喉道倾斜 调节 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]