| 摘要: |
| 为了掌握瓦状塞式喷管更多的特征,采用空气作为介质,对一瓦状塞式喷管进行了底部限流板、底部二次流及内喷管倾角对性能影响的冷流实验。研究结果表明:在低中空,底部压强一般比环境压强要低;塞式喷管底部加入二次流可以增加底部压强,但底部二次流对性能的影响在1%～2%以内,少量的二次流对增加性能的效果较好,而加入更多的二次流则效果有限;增大内喷管倾角,可以增大底部压强即增加底部推力,但存在一个最佳倾角,使最大效率最大;本次冷流实验的瓦状塞式喷管最高效率为96%,其高度补偿效果较为明显。 |
| 关键词: 塞式喷管火箭发动机 塞式喷管 喷管效率 研制试验 |
| DOI： |
| 分类号:V435 |
| 基金项目:国家“八六三”基金资助项目(863 2 3 4 10)。 |
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| Cold flow tests on tile shaped aerospike nozzle |
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DAI Wu ye, LIU Yu, MA Bin
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School of Astronautics, Beijing Univ of Aeronautics and Astronautics, Beijing 100083, China
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| Abstract: |
| To know more characteristics of tile shaped aerospike nozzles and to get more experimental data that can be used for the validation of numerical simulation and analysis, cold flow tests on a tile shaped aerospike nozzle were conducted. The results indicate that the base pressure is lower than the backpressure at low and middle altitude. The bleed can increase the base pressure, the effect of bleed on the performance is within 1%～2% and a little bleed is effective to improve the performance. The base pressure increases when the pitch angle becomes bigger and there is an optimum angle for the optimum performance. The maximum nozzle efficiency of the tile shaped nozzle tested here is 96%, and it has good altitude compensation. The tile shape aerospike nozzle should be attractive to study further. |
| Key words: Plug nozzle rocket engine Plug nozzle Nozzle efficiency Research test |
