固体火箭发动机熄火方案可行性研究

推进技术 ›› 1995, Vol. 16 ›› Issue (5): 49-53.

固体火箭发动机熄火方案可行性研究

方锡惠,胡保朝

远安三江航天集团研究所;远安三江航天集团研究所

发布日期:2021-08-15

A STUDY ON EXTINGUISH FEASIBILITY METHOD OF SOLID ROCKET MOTORS

China Sanjiang Space Group, Research Inst., Yuan’an, 444200;China Sanjiang Space Group, Research Inst., Yuan’an, 444200

Published:2021-08-15

摘要/Abstract

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。

关键词: 固体推进剂火箭发动机;熄火;推力控制;可行性研究

Abstract: 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.

Key words: Solid propellant rocket engine;Flameout;Thrust control;Feasibility study

方锡惠,胡保朝. 固体火箭发动机熄火方案可行性研究[J]. 推进技术, 1995, 16(5): 49-53.