固体火箭发动机喷管的烧蚀预示是喷管结构分析的重要一环。
Ablation prediction of solid rocket motor nozzle is an important link for nozzle structure analysis.
在单元数足够多时，环簇式塞式喷管可比相同面积比的钟形喷管的尺寸更小，重量更轻，推力效率更高；
When numbers of the inner nozzle are enough, plug nozzle has less size, less weight and higher thrust efficiency than the bell nozzle under same area ratio.
结果表明，内喷管喉径是影响环簇式塞式喷管尺寸大小的最主要设计参数；
The results show that throat diameter of the inner nozzle is the most important design parameter influencing structure size of the annular clustered plug nozzle.
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