作　　者： ; ; ;

机构地区： 西北工业大学

出　　处： 《固体火箭技术》 2012年第4期446-449,456,共5页

摘　　要： 介绍了大长径比战术导弹用固体发动机中产生的燃烧不稳定,分析了燃烧不稳定产生的机理,总结了国外典型的实验研究情况及其主要结论,以及国内固体发动机燃烧不稳定的状况。结合最新的研究进展,对燃烧不稳定的影响因素开展了深入分析:分析了声涡之间的耦合作用,重点讨论了声对涡的调制作用;分析了推进剂压强耦合对燃烧不稳定的影响,讨论了压强耦合响应函数的测试方法及其与推进剂配方之间的关系;分析了金属的分散燃烧及其凝相燃烧产物对燃烧不稳定的增益和阻尼作用。针对诸影响因素,提出了进一步的研究建议。 Combustion instability in tactical motors with large length to diameter ratio was discussed, and the mechanism of combustion instability was analyzed. Stability testing of full-scale tactical motors abroad and the main conclusions were summarized. Combustion instability in domestic motors was also introduced. Based on recent progress, the driving and damping mechanisms on combustion instability were analyzed, including the couple between acoustics and vortex, combustion response, distributed combustion and condensed products of aluminum. The chamber acoustic modes organizing and modulating the shedding phenomenon were also discussed. The suggestion of further research on combustion instability was presented.

关 键 词： 固体火箭发动机 燃烧不稳定 声涡耦合 燃烧响应

领　　域： [航空宇航科学与技术] [航空宇航科学技术]