摘要
本文运用固体火箭发动机液体喷射熄火模型 ,确定了液体喷射熄火液量 ,研究了推进剂能量、压强指数、燃烧室压强、液体性质和喷射压降等多种因素的影响。
The liquid quantity required(LQR)for liquid quench of solid rocket motor was determined with the use of a theoretical model developed by the authors.LQR increases with propellant energy and decreases as the evaporation heat of liquid and the liquid pressure drop(the difference between injection pressure of liquid and chamber pressure)increase.The effects of the chamber pressure and burning rate pressure exponent of propellant on LQR merge into the effect of mass burning rate of propellant.Then LQR increases with increasing mass burning rate.The theoretical results are in good agreement with experimental data.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
1993年第3期255-258,共4页
Journal of Aerospace Power
基金
国家自然科学基金
