摘要
本文对含铝 18.5%、 16%的 PU和 HTPB推进剂进行了液体喷射熄火研究。结果表明 :可靠熄火用液量随推进剂能量增加而增加 ;随着射流压降的增加 ,熄火速率和用液量分别增加和减少 ;燃烧室压强升高 ,用液量增加 ;除熄火用液量外 ,存在一个无因次参数 ,它综合反映了推进剂能量和燃速特性、喷射工况、液体性质、燃烧压强等对熄火过程的作用。对液体喷射熄火燃面用 SEM观察发现 ,氧化剂含量减少 ,燃面呈多孔状 。
The extinction process of three kinds of aluminized composite propellants by liquid injection has been experimentally investigated,according to the liquid quench model of solid propellant proposed by the authors.The experimental results indicate that(1)The liquid quantity requirment(LQR in g/cm 2)for reliable extinction varies significantly with the energy of propellant in the relationship of LQR ∝ 0 1Q f(Q f〔kJ/g〕the heat relased by the propellan at constant volume);(2)The extinction speed increases and LQR decreases with increasing liquid injection pressure drop;(3)LQR increases with increasing combustion chamber pressure for propellants having positive pressure exponents.In addition to LQR,there exists a non-dimensional parameter which summarizes the effects of energy and burning rate characteritics of propellants,liquid injection pressure drop,liquid properties and combustion chamber pressure on the liquid uqench process.If the parameter is less than a critical value,the extinction of propellant by liquid injection is not obtainable.The examination by means of the scanning electron microscopy demonstrates that the appearance of the burning surface quenched by liquid are different from those by extinguished by rapid depressurization.The surface profile is porous and a lot of oxidizer particles are dissolved during liquid quenching.This fact exerts an influence on the reignition of the quenched burning surface for stop/restart solid rocket motors.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
1991年第2期97-100,共4页
Journal of Aerospace Power
基金
国家自然科学基金 (高技术 )资助项目
