摘要
本文分析了液体喷射作用下固体推进剂熄火机理,提出了液体喷射熄火物理模型“对双基、聚氨酯复合推进剂进行了实验研究。结果表明:推进剂的能量特征是可靠熄火用液量的决定因素,用液量随推进剂能量升高而显著增加;当液体喷射压强增大时,熄火用液量和熄火速率分别下降和升高,熄火用液量与燃烧压强的关系随推进剂压强指数而变,即n〉0时,随压强上升而增加,反之则下降;液体性质对用液量有较大影响,选择合适的添加剂改变液体物性可望大幅度减少熄火用液量。
This paper proposes a physical model for the liquid quench of solid propel-lant and presents the results of an experimental study of extinguishment of solid propellant motor by liquid injection. The effects of several variables, such as propellant energy characteristics, injection pressure drop, chamber pressure and additive in liquid,on the liquid quantity requirement for the extinction of propellant have been studied. The results indicate that all of these factors exert an influence on the liquid quench characteristics. The propellant energy is a predominant factor for the liquid quantity requirement (LQR), i.e., LQR increases with increasing propellant energy. As the injection pressure drop increases, LQR decreases and the depressurization rate increases. The relationship between LQR and the chamber pressure varies with the burning rate pressure exponent (n), i.e., when n>0, LQR inceases with increasing chamber pressure; conversly, n<0, LQR decreases. The liquid properties exert an important effect on LQR . The additive selected appropriately in liquid significately reduces LQR.
出处
《宇航学报》
EI
CAS
CSCD
北大核心
1992年第1期68-74,共7页
Journal of Astronautics
基金
国家自然科学基金(高技术)资助项目
关键词
固体推进剂
燃烧
熄火
Solid rocket motor, Solid propellant, Extinguishment, Liquid injection .
