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本文提出了一个复合固体推进剂的综合燃烧模型和相应的数学处理方法。该模型对凝聚相反应作了更细微的分析,特别重视和强调了各种热量传递对燃烧所起的作用,并以推进剂中处于连续相的粘合剂线性分解速度表示推进剂的线性燃速。根据此模型编制程序并进行了大量计算。计算结果与实验符合得很好。对AP/HTPB多级配推进剂的计算结果中,相对误差小于10％的占80％,对Ae/AP/HTPB推进剂则占90％以上。
This paper presents a comprehensive solid propellant combustion model and the corresponding mathematical approach. The model gives a more detailed analysis of the cohesion phase, with special emphasis and emphasis on the effects of various heat transfers on combustion. The linear decomposition rate of the propellant in the continuous phase of the propellant is expressed as the linear combustion rate of the propellant speed. According to this model programming and a lot of calculations. The calculated results are in good agreement with the experiment. For the AP / HTPB multi-stage propellant, 80% of the relative error is less than 10% and over 90% of the Ae / AP / HTPB propellant.