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为了考察固体火箭发动机塞式喷管的性能,设计了一套单元内喷管数为16、面积比为25的环簇式固体塞式喷管和一对比用钟型喷管,采用数值模拟方法预估了其推力性能.对塞式喷管进行了地面热态试验,测定了其推力性能.结果表明,环簇式塞式喷管地面燃气流动现象和推力性能的数值模拟结果与试验结果吻合.塞式喷管在地面上的推力效率达92.6%,比同面积比和长度的钟型喷管高9.1%,具有明显的高度补偿效应;但高空效率比用钟型喷管效率降低5.8%.
In order to investigate the performance of the solid rocket motor nozzle nozzle, a set of annular nozzle and nozzle nozzle with a number of nozzles in the unit of 16 and an area ratio of 25 were designed. The numerical simulation method The thrust performance of plug nozzle was estimated and its thrust performance was measured.The results show that the numerical simulation results of gas flow and thrust performance of ring plug nozzle coincide with the experimental results The thrust efficiency of plug nozzle on the ground is 92.6%, which is 9.1% higher than that of bell nozzle with the same area ratio and length, which has a significant height compensation effect, but the altitude efficiency is lower than that of bell nozzle by 5.8% .