固体火箭发动机塞式喷管数值模拟和热态试验  

Numerical simulation and hot test investigation of plug nozzle in solid rocket motor

作　　者：任军学[1] 刘宇[1] 廖云飞[1] 谢侃[1] 

机构地区：[1]北京航空航天大学宇航学院,北京100191

出　　处：《航空动力学报》2011年第6期1420-1425,共6页Journal of Aerospace Power

基　　金：国家自然科学基金(50476002)

摘　　要：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%.A clustered type of plug nozzle, with 16 unit nozzles and an area ratio of 25, and a compared bell nozzle were designed to gain the performance characteristics of plug nozzle. The thrust performances of the nozzles were evaluated with numerical simulation method. A ground hot test was done to measure the thrust performance the clustered plug nozzle. The result shows that the numerical simulation results of the flow phenomenon and thrust performance accord with the experimental results. The thrust efficient of the plug nozzle in ground reaches 92.6%and is 9.1% higher than the bell nozzle with the same area ratio and length, reflecting the altitude compensation effects of plug nozzle. However, its thrust efficient in high attitude is 5.8% lower than the compared bell nozzle.

关 键 词：固体火箭发动机 塞式喷管 推力特性 数值模拟 热态试验 

分 类 号：V430[航空宇航科学与技术—航空宇航推进理论与工程]