固体塞式喷管二次喷射推力矢量控制  

Thrust vector control for solid plug nozzle based on secondary injection

作　　者：琚春光[1] 刘宇[1] 廖云飞[1] 

机构地区：[1]北京航空航天大学宇航学院,北京100083

出　　处：《推进技术》2007年第1期78-81,共4页Journal of Propulsion Technology

基　　金：国家自然科学基金资助项目(50476002)

摘　　要：结合塞式喷管的结构特点,选用流体二次喷射的方法,在应用迎风格式求解N-S方程的基础上,对固体塞式喷管发动机的推力矢量控制进行了初步研究。考察了工作压比、流体二次喷射的角度和流量对固体塞式喷管的高度特性以及流体二次喷射产生的侧向力的影响。结果表明,流体二次喷射的推力矢量控制方法可以增加塞式喷管的轴向力;流体二次喷射产生的侧向力与二次喷射的流量和角度成正变关系;塞式喷管轴向力的增加随着二次流流量的增加而增加,但是二次流对轴向力的增加与二次流喷射的角度成反变关系。According to the structure characteristics of plug nozzles, the numerical simulations of the thrust vector control plug nozzle based on the secondary injection for solid rocket motors have been finished by employing the upwind-scheme methodology to solve Navier-Stockes equation. The attentions were paid on the effects of the three main parameters the working pressure ratio, the angle and the flow mass of secondary injection on plug nozzle performance and the force for thrust vector control. The results indicate that the secondary injection could increase the plug nozzle performance in a certain, the force in the direction of the axis is positive to the flow mass of the secondary injection and is negative to the angle. The force for thrust vector control produced by the secondary injection gets bigger with the increase of flow mass and angle.

关 键 词：固体推进剂火箭发动机 塞式喷管 推力矢量控制 二次喷射 

分 类 号：V435.23[航空宇航科学与技术—航空宇航推进理论与工程]