摘要
从理论、实验两个方面，对固体火箭发动机快速降压、液体喷射及二者联合等三种熄火方案进行了分析和探讨；通过比较认识到：快速降压与液体喷射联合熄火方案对于解决高能、高含铝量（小于２０％）的复合推进剂熄火问题具有独到的优点；结合某预研型号发动机对联合熄火方案进行了实际应用的可行性分析，结果可行。
n this study, quick depressurization, liquid injection and combining quick depressurization with liquid injection extinguish methods for solid rocket motors are discussed theoretically and experimentally. By the comparison, it is recongnized that the third method has original advantages in solving the extinguish for high energy aluminized propellant (the content of aluminium is less than 20 percent). Combining some advanced research model motor, the practical application feasibility of the concerned extinguish method is analysised' The analysis result is regarded as practicable.
出处
《推进技术》
EI
CAS
CSCD
北大核心
1995年第5期49-53,共5页
Journal of Propulsion Technology
关键词
固体推进剂
火箭发动机
熄火
可行性研究
Solid propellant rocket engine, Flameout, Thrust control, Feasibility study
