为了给固体火箭发动机长尾喷管的热防护设计和改进提供理论依据和有益的参考,文中通过解剖某固体火箭发动机长尾喷管试验残骸,并对长尾喷管内衬残骸进行了测量和分析,给出了长尾喷管内衬的烧蚀规律。利用流场仿真的方法对长尾喷管流场进行了理论计算和分析,分析了长尾喷管内衬的烧蚀机理,分析表明凝相粒子的侵蚀是长尾喷管内衬局部烧蚀严重的主要原因。

In order to tail-pipe nozzle of solid rocket motor design and improvement of the thermal protection provide a theoretical basis and a useful reference, based on the anatomy of wreckage of a solid rocket motor's tail-pipe nozzle, inside lining of tail-pipe nozzle was measured and analyzed, given the ablation law of inside lining. Tail-pipe nozzle flow field is calculated and analyzed by using the method of flow field simulation. That analyzed ablation mechanism of tail-pipe nozzle inside lining; the analysis shows that condensed particle erosion is main reason for local serve ablation of tail-pipe nozzle inside lining.