摘要
本文提出了一种固体推进剂瞬态燃烧模型。它考虑了凝相分布化学反应和辐射热流的深层吸收。以及燃面上的能量损失 ;在气相发展了空间分布厚火焰模型以求得有蒸汽掺混情况下的火焰热反馈。运用该模型能统一揭示快速降压、降热辐射和液体喷射等多种外界扰动下 ,推进剂的瞬变燃烧行为和熄火所需的临界参数。对液体喷射工况下进行的理论预示与实验结果相一致。
A transient burning model of solid propellants is proposed,in which the distributed reactions and deep absorption of external radiation are considered in the condensed phase.The heat loss due to boiling heat transfer induced by liquid jet impinged on burning surface is taken into consideration in the energy balance equation on the buring surface.A space wise thick flame model is developed to obtain the flame heat feedback under the conditions that the decreasing of chamber pressure and gas phase temperatures is caused by liquid injection and evaporation of liquid drops in gas phase,which is described by a submodel for internal ballistics of rocket motor durning liquid quench.The model can be used to describe the transient burning behaviors of solid propellants under the influence of external disturbances,such as rapid depressurization,deradiation or liquid injection,and to obtain the critical values required for extinction of solid propellants.The results from theoretical prediction indicate that whether the transient burning comes into extinction is not only dependent on the variation rate of the external disturbance,but also on the variation amplitude of the disturbance.The critical values of liquid injection pressure drops for extinction of two kinds of aluminized ammonium perchlorate hydroxyterminated polybutadiene propellants(16%Al and 18 5%Al)were obtained by experiments.The predicted results obtained from the transient burning model are in good agreement with the experimental data.The critical value of liquid injection pressure drop increases with increasing propellant energy and chamber pressure.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
1993年第3期250-254,共5页
Journal of Aerospace Power
基金
国家自然科学基金 (高技术 )资助项目
