固体火箭发动机气动喉部的推力调控特性  

Thrust Control Features for Aerodynamic Throat for Solid Rocket Motor

作　　者：谢侃[1] 李博[1] 郭常超[1] 王宁飞[1] 

机构地区：[1]北京理工大学宇航学院,北京100081

出　　处：《推进技术》2015年第2期194-199,共6页Journal of Propulsion Technology

基　　金：航天支撑技术基金;航天科技创新基金(CASC200903)

摘　　要：为了研究固体火箭发动机气动喉部推力调节的一般规律,利用氮气作为介质对气动喉部喷管进行了冷流实验研究。研究了该种喷管的扼流性能,二次流嘴的面积、个数对其扼流性能的影响以及空腔容积与喷管压强调节时间的关系。掌握了气动喉部喷管的有效喉部面积随流量比变化的一般规律。结果表明,二次流与主流流量比越大,气动喉部面积越小。小的面积比具有更高的扼流性能,而当流量比大于0.4时,面积比对扼流性能无明显影响。空腔体积越小压强调节时间越短。Adjust：In order to study the general rules of the thrust control features for aerodynamic throat for solid rocket motor, a cold-flow test research was performed on the aerodynamic nozzle throat using the nitrogen as working gas. Firstly, the choke performance of the aerodynamic throat was studied. Then, the performance of throat modification was studied considering the influence of area and number of secondary flow injectors. Final-ly,the relation about the volume of cavity with adjustment time of nozzle was also studied. The general law of ef-fective throat area along with the flow rate change was obtained through study. The results show that the larger the flow ratio of the secondary flow and main flow is, the smaller the pneumatic throat area is. The smaller area ratio has higher choke performance,and the influence of area is not obvious when the flow rate is greater than 0.4. Be-sides,the smaller the cavity volume is,the shorter the accommodation time of pressure is.

关 键 词：固体火箭发动机 气动喉部 二次流 冷流实验 

分 类 号：V430[航空宇航科学与技术—航空宇航推进理论与工程]