环喉环簇塞式喷管推力矢量控制研究  

Study on thrust vector control of clustered plug nozzle

作　　者：琚春光[1] 刘宇[1] 

机构地区：[1]北京航空航天大学宇航学院,北京100083

出　　处：《固体火箭技术》2007年第4期306-310,共5页Journal of Solid Rocket Technology

基　　金：国家自然科学基金资助项目(50476002)

摘　　要：针对环喉环簇塞式喷管发动机的结构特点,提出了二次流喷射实现推力矢量控制的方案,并用数值方法研究了二次流的总温、总压、位置、角度、流量、喷射孔的数量以及孔间距等工作参数对推力矢量控制性能的影响。结果表明,侧向力与二次流的总温、总压、流量成正比关系;多孔比单孔的喷射效果好,孔与孔的间距要适当;逆向喷射比顺向喷射产生的侧向力大;喷射孔位置的选取受工作压比的影响很大。Based on the structure characteristics of clustered plug nozzle, a scheme that using secondary injection to realize thrust vector control was put forward, The effects of some working parameters on thrust vector control performance were investigated by means of numerical simulation method, such as total temperature, total pressure, position, angle, mass flow, number of injection holes, pitch of holes and so on. The results show that the side force is directly proportional to total temperature, total pressure and mass flow of secondary flow; the injection effect of multiple holes is better than that of single hole,the pitch of holes is suitable; the side force of reverse injection is bigger than that of forward injection; the working pressure ratio has great effects on the location selection of injection holes.

关 键 词：火箭发动机 塞式喷管 推力矢量控制 二次喷射 

分 类 号：V431[航空宇航科学与技术—航空宇航推进理论与工程]