脉冲发动机建压段瞬态燃速模型  

Transient burning rate model for pressurization of a pulsed solid rocket motor

作　　者：任明浩[1] 李世鹏[1] 王宁飞[1] 

机构地区：[1]北京理工大学宇航学院,北京100081

出　　处：《推进技术》2010年第3期276-280,288,共6页Journal of Propulsion Technology

基　　金：国防基础预研项目(B2220060060)

摘　　要：针对脉冲发动机工作时间短,压强高的特性,对建压阶段的瞬变燃烧过程进行了模型研究。该模型基于非稳态凝聚相能量方程,并耦合气相热反馈为求解该能量方程的边界条件,从而引入压强对燃烧过程的作用。模型中压强的变化规律由同样条件下的试验p-t曲线拟合得到。通过模型计算,可以对建压过程中推进剂表面温度随时间的变化规律、各压强下的瞬态燃速做出预测,结果与试验数据较好地吻合。用该瞬态燃速进行建压段内弹道仿真,与稳态数据相比,更接近实测曲线,表明该模型可以用于脉冲发动机建压段的瞬态燃速的预估。A transient burning rate model is developed to study the pressurization of a pulsed solid rocket motor with the characteristics of short action time and high pressure.The model is based on the unsteady energy equation for condensed phase,and coupled with the heat feedback from gas phase as the boundary condition,accordingly,and the effect of pressure is considered.An increasing p-t curve used in this model is given by the experimental data from the same test condition.The surface temperature vs.time and transient burning rate under each pressure are perdicted by the results of the model,which exhibits good agreement with experimental data.This model is suitable to predict the transient burning rates in the process of pressurization of a plused motor.The p-t curve simulated with the transient burning rates from this model is more accurate,compared with that by the model employing the steady burning rates.

关 键 词：脉冲发动机+ 固体火箭推进剂 建压过程+ 瞬态燃速模型+ 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]