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为了研究冲压发动机燃烧室的热防护性能,用类比法计算了整体式固体火箭冲压发动机燃烧室壁面的烧蚀,其中考虑了热解气流对烧蚀的影响,并将国外有关固体火箭发动机喷管烧蚀计算时所用经验参数(指前因子)通过换算转换到冲压发动机燃烧室烧蚀计算中。计算结果符合物理规律,并与试验结果符合较好。该项研究为冲压发动机燃烧室热防护层的设计提供了有效的分析手段。
In order to study the thermal protection performance of the ramjet engine, the ablation of the wall of the combustion chamber of the solid rocket ramjet engine was calculated by the analogy method. The effects of the pyrolytic gas flow on the ablation were considered. The empirical parameters used in the ablation calculation (the pre-factor) are converted into the ablation calculation of the ramjet combustion chamber by conversion. The calculated results accord with the laws of physics and accord with the test results well. This study provides an effective means of analysis for the design of the thermal armor for stamped engine combustors.