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随着航天技术的发展,烧蚀冷却技术在空间化学小推力液体火箭发动机上得到了广泛的应用.对于烧蚀冷却的推力室必须解决以下诸问题:a.材料中温度的计算,b.材料烧蚀速率的计算,c.材料侵蚀速率的计算,d.烧蚀冷却对发动机比冲的影响. 本文的目的在于介绍我们对上述四个问题所做的一些工作.由于问题本身的复杂性,以上诸问题的精确答案是难以得到的.我们只是通过近似的理论分析以及大量实验数据的归纳提出了近似的、经验的、估算性的结果,以供设计类似条件下的烧蚀冷却推力室参考.
With the development of aerospace technology, ablation cooling technology has been widely used in space chemistry small thrust liquid rocket engine.For the ablation cooling thrust chamber, the following problems must be solved: a. Calculation of temperature in material, b. Calculation of ablation rate, c. Calculation of material erosion rate, d. Influence of ablation cooling on specific impulse of the engine The purpose of this paper is to introduce some of the work we did on the above four issues.Because of the complexity of the problem itself, The exact answers to the above questions are hard to come by. We only present approximate, empirical and estimation results through approximate theoretical analysis and extensive induction of experimental data for reference to ablative cooling thrust chambers under similar design conditions .