塞锥截短对塞式喷管性能影响的实验

王一白; 覃粒子; 刘宇; 王长辉

塞锥截短对塞式喷管性能影响的实验

北京航空航天大学宇航学院, 北京 100083

基金项目: 国家863资助项目

详细信息

作者简介:
王一白 (1976-),男,河南新乡人,讲师,wangyibai@buaa.edu.cn.

中图分类号: V 430
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- 被引次数: 0
出版历程
- 收稿日期: 2007-01-15
- 网络出版日期: 2008-01-31

Effects of truncation on thrust performance of aerospike nozzles

School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100083, China

摘要

摘要: 为了研究塞锥截短对塞式喷管性能的影响,对截短率为80%、40%、30%和20%的塞式喷管进行了冷流实验.介绍了实验系统的组成和推力测量方式,得到了不同塞锥截短率的推力系数效率的高度特性曲线.实验结果表明:截短率越小,效率越低,不同截短率的效率差别随着压强比的增加而减小;随着截短率增大,截短率对效率的影响程度逐渐降低.截短率太小,性能损失较大;截短率太大,塞锥的尺寸增大,而性能提高却不明显.通常的取值范围是30%~40%.
- 塞式喷管 /
- 推力系数效率 /
- 截短率
Abstract: To discuss the performance effects of plug truncation ratios, cold-flow tests were performed for 80%, 40%, 30% and 20% truncated aerospike nozzles by employing cold air as propellant. The test system apparatus and thrust measurement were introduced. The experimental altitude characteristics curves of the thrust coefficient efficiency were obtained. The results show that the efficiency of aerospike nozzles with bigger truncation ratios is higher than with smaller ratios, and the distinction of different truncations was minished with the pressure ratio increasing. The influence degree of the truncation on the thrust coefficient efficiency falls down by increasing the ratio. The performance loss is more due to selecting too small value of the truncation ratio. With too big ratio value the length of plug is much long, and the weight of plug increases much, but the nozzle performance elevates a little. Generally the truncation ratios can be chosen from 30% to 40%.
- aerospike nozzle /
- thrust coefficient efficiency /
- truncation ratio

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参考文献(1)

[1] Angelino G. Approximate method for plug nozzle design [J]. AIAA Journal, 1964, 2(10): 1834-1835 [2] Hagemann G,Immich H, Terhardt M. Flow phenomena in advanced rocket nozzles—the plug nozzle . AIAA Paper 98-3522, 1998 [3] Immich H, Nasuti F, Onofri M, et al. Experimental and numerical analysis of linear plug nozzles . AIAA Paper 98-1603, 1998 [4] Onofri M. Plug nozzles: summary of flow features and engine performance . AIAA Paper 2002-0584, 2002 [5] 王长辉,刘宇,戴梧叶.塞锥型面简化与截短对塞式喷管性能的影响[J]. 推进技术, 2002, 23(5): 438-440 Wang Changhui, Liu Yu, Dai Wuye. Effects of plug contour simplification and truncation on linear plug nozzle[J]. Journal of Propulsion Technology, 2002, 23(5): 438-440(in Chinese) [6] 覃粒子.塞式喷管型面设计与优化 .北京:北京航空航天大学宇航学院, 2004 Qin Lizi. Contour design and optimization of aerospike nozzles . Beijing: School of Astronantics,Beijing University of Aeronautics and Astronautics, 2004 (in Chinese) [7] 廖云飞,刘宇,王长辉.单元二维直排塞式喷管冷流实验[J]. 北京航空航天大学学报, 2005, 31(9): 958-962 Liao Yunfei, Liu Yu, Wang Changhui. Cold-flow tests on 1-cell 2D linear plug nozzle[J]. Journal of Beijing University of Aeronautics and Astronautics, 2005, 31(9): 958-962(in Chinese) [8] 王一白,刘宇,覃粒子.塞式喷管与当量钟型喷管性能的实验测定和分析[J]. 推进技术, 2002, 23(5): 428-432 Wang Yibai, Liu Yu, Qin Lizi. Experimental mensuration and analysis of aerospike nozzles and bell nozzle performance[J]. Journal of Propulsion Technology, 2002, 23(5): 428-432(in Chinese) [9] 琚春光,刘宇,韩非. 塞式喷管性能损失分析[J]. 北京航空航天大学学报, 2005, 31(11): 1222-1225 Ju Chunguang, Liu Yu, Han Fei. Performance loss analysis on aerospike nozzles[J]. Journal of Beijing University of Aeronautics and Astronautics, 2005, 31(11): 1222-1225(in Chinese)

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