含铝复合推进剂燃速计算研究  

A CALCULATION RESEARCH ON BURNING RATE OF ALUMINIZED COMPOSITE PROPELLANT

作　　者：刘德辉[1] 彭培根[2] 

机构地区：[1]湖南长沙国防科学技术大学5系503室,410073 [2]国防科学技术大学

出　　处：《航空动力学报》1993年第1期69-71,共3页Journal of Aerospace Power

摘　　要：本文专门探讨了利用 PEM模型计算含铝复合推进剂的燃速和压强指数。文中提出一种确定假想推进剂配方的新方法 ,并以此为基础建立了一个扩展和改进的 PEM模型 。A research has been completed by appling PEM model to combustion simulation of aluminized propellants.The effects of aluminium particles on the surface energy of the propellant are taken into consideration so simply as the heat sink PEM model of J.P.Renie et al,but a new method to determine the pseudopropellant′s formulations is presented in this paper,thereby an extended and modified PEM model is developed.According to this model,the burning rates and pressure exponents of aluminized propellants are calculated.The results show that our model makes the calculated results of burning rates and pressure exponents more approach to their experimental data as compared with the heat sink PEM model of J.P.Renie et al.

关 键 词：固体推进剂 燃烧模型 燃速预测 

分 类 号：V435.12[航空宇航科学与技术—航空宇航推进理论与工程]