复合推进剂中铝燃烧实验研究

推进技术 ›› 2016, Vol. 37 ›› Issue (8): 1579-1585.

复合推进剂中铝燃烧实验研究

刘鑫,刘佩进,金秉宁,杨天昊,魏祥庚

西北工业大学燃烧、热结构与内流场重点实验室，陕西西安 710072,西北工业大学燃烧、热结构与内流场重点实验室，陕西西安 710072,西北工业大学燃烧、热结构与内流场重点实验室，陕西西安 710072,西北工业大学燃烧、热结构与内流场重点实验室，陕西西安 710072,西北工业大学燃烧、热结构与内流场重点实验室，陕西西安 710072

发布日期:2021-08-15
作者简介:刘鑫，男，博士生，研究领域为航空宇航推进理论与工程。
基金资助:
国家自然科学基金(51206136)。

An Experimental Investigation of Aluminum

Science and Technology on Combustion，Internal Flow and Thermal-Structure Laboratory， Northwestern Polytechnical University，Xi’an 710072，China,Science and Technology on Combustion，Internal Flow and Thermal-Structure Laboratory， Northwestern Polytechnical University，Xi’an 710072，China,Science and Technology on Combustion，Internal Flow and Thermal-Structure Laboratory， Northwestern Polytechnical University，Xi’an 710072，China,Science and Technology on Combustion，Internal Flow and Thermal-Structure Laboratory， Northwestern Polytechnical University，Xi’an 710072，China and Science and Technology on Combustion，Internal Flow and Thermal-Structure Laboratory， Northwestern Polytechnical University，Xi’an 710072，China

Published:2021-08-15

摘要/Abstract

摘要： 采用长焦显微镜头和高速相机组合的光学拍摄方法，研究了不同压强下含铝复合推进剂中铝粒子在推进剂燃烧表面处和脱离燃面后的动态燃烧过程。分别在1MPa，3MPa和5MPa充满氮气的燃烧实验器中进行了实验。在3MPa和5MPa实验中，通过在镜头前增加不同透射率的中性密度滤波片解决了因铝滴燃烧发光过强导致相机成像过度曝光的问题。通过测定拍摄过程中相邻两张图片中同一粒径铝滴在不同位置，计算了不同粒径铝滴的随流运动速率。小粒径随流运动速率快，大粒径随流运动速率慢。实验中还得到了不同粒径铝滴在推进剂燃烧表面的团聚形成时间。1MPa实验下，200μm和150μm粒子的团聚时间分别约为8ms和6ms；3MPa下，300μm和200μm粒子的团聚时间分别约为5ms和3ms；5MPa下，300μm和150μm粒子的团聚时间分别约小于3ms和1ms。随着压强的增大，同一粒径团聚物的团聚时间缩短。在同一压强条件下，粒径越小的铝团聚物其所需团聚时间越短。

关键词: 复合推进剂；铝颗粒；燃烧；高速摄像；团聚

Abstract: For the research of the dynamic combustion process at the surface and out of the burning surface of aluminum in the AP/HTPB propellant，the optical imaging method with the long distance microscope and high-speed camera were used. Experiments were carried out under 1MPa，3MPa and 5MPa filled with nitrogen. Under 3MPa and 5MPa，through the adoption of the neutral density filter (NDFI) with different transmissions in front of the camera，the problem that the overexposure of camera imaging due to the strong light of aluminum droplet combustion was solved，and there was no this problem in 1MPa. Then the flow velocity with the combustion gas was calculated by measuring the various location of the same diameter aluminum drops in the adjacent two images. The flow velocity of small size drops is fast，and the flow velocity of large size drops is slow. The agglomeration time of the aluminum drops in the propellant burning surface was also obtained. In the 1MPa experiment，the agglomeration time of the 200μm and 150μm drops are about 8ms and 6ms. Under 3MPa，the agglomeration time of the 300μm and 200μm drops are about 5ms and 3ms. Under 5MPa，the agglomeration time of the 300μm and 150μm drops are less than 3ms and 1ms. When the pressure increases，the agglomeration time of the same diameter agglomerates becomes shorter. Under the same pressure，the time of the agglomeration with the smaller aluminum agglomerates is shorter.

Key words: Composite propellant；Aluminum particle；Combustion；High-speed photography；Agglomerate

刘鑫,刘佩进,金秉宁,杨天昊,魏祥庚. 复合推进剂中铝燃烧实验研究[J]. 推进技术, 2016, 37(8): 1579-1585.

LIU Xin,LIU Pei-jin,JIN Bing-ning,YANG Tian-hao,WEI Xiang-geng. An Experimental Investigation of Aluminum[J]. Journal of Propulsion Technology, 2016, 37(8): 1579-1585.

参考文献

[1] Luigi D L, Price E W. Summerfield M. Unsteady Burning and Combustion Stability of Solid Propellants[M]. Washington: Progress in Astronautics and Aeronautics, 1992.
[2] 王宁飞, 陈龙, 赵崇信, 等. 固体火箭燃烧室内微粒分布的实验研究[J]. 推进技术, 1995, 16(4): 24-27. (WANG Ning-fei, CHEN Long, ZHAO Chun-xin, et al. An Experimental Study on Distribution of Particulates in Solid Rocket Motors[J] . Journal of Propulsion Technology, 1995, 16 (4): 24-27.)
[3] Shimada T, Sekiguchi M, Sekino N. Flow Inside a Solid Rocket Motor with Relation to Nozzle Inlet Ablation [J]. AIAA Journal, 2007, 45(6): 1324-1332.
[4] Performance of Rocket Motors with Metallized Propellants[R]. AGARD, 230-WG-17, 1986.
[5] 张宏安, 叶定友, 侯晓. 固体火箭发动机凝聚相微粒分布研究现状[J]. 固体火箭技术, 2000, 23(3): 24-27.
[6] 唐金兰, 刘佩进. 火箭发动机原理[M]. 北京:国防工业出版社, 2013.
[7] Gallier S, Godfroy F. Aluminum Combustion Driven Instabilities in Solid Rocket Motors[J]. Journal of Propulsion and Power, 2009, 25(2): 509-521.
[8] Beckstead M W, Richards R S, Brewster B S. Distributed Combustion Effects on Particle Damping[J]. AIAA Journal, 1984, 22(3): 383-387.
[9] 金秉宁, 刘佩进, 杜小坤, 等. 复合推进剂中铝粉粒度对分布燃烧响应和粒子阻尼特性影响[J]. 推进技术, 2014, 35(12): 1701-1706. (JIN Bing-ning, LIU Pei-jin, DU Xiao-kun, et al. Effects of Different Aluminum Particle Sizes in Composite Propellant on Distributed Combustion Response and Particle Damping[J]. Journal of Propulsion Technology, 2014, 35(12): 1701-1706.)
[10] Tai-Kang Liu. Experimental and Model Study of Agglomeration of Burning Aluminized Propellants[J]. Journal of Propulsion and Power, 2005, 21(5): 797-806.
[11] Takahashi K, Oide S, Kuwahara T. Agglomeration Characteristics of Aluminum Particles in AP/AN Composite Propellants[J]. Propellants Explosives Pyrotechincs, 2013, 38(4): 555-562.
[12] Mullen J C, Brewster M Q. Reduced Agglomeration of Aluminum in Wide-Distribution Composite Propellants[J]. Journal of Propulsion and Power, 2011, 27(3): 650-661.
[13] Sambamurthi J K, Price E W, Sigman R K. Aluminum Agglomeration in Solid-Propellant Combustion[J]. AIAA Journal, 1984, 22(8): 1132-1138.
[14] Anand K V, Roy A, Mulla I, Experimental Data and Model Predictions of Aluminium Agglomeration in Ammonium Perchlorate-Based Composite Propellants Including Plateau-Burning Formulations[J]. Proceedings of the Combustion Institute, 2013, 34: 2139-2146.
[15] Glotov O G. Condensed Combustion Products of Aluminized Propellants. II. Evolution of Particles with Distance from the Burning Surface[J]. Combustion Explosion and Shock Waves, 2000, 36(4): 476-487.
[16] 刘鑫, 刘佩进, 关昱, 等, 复合推进剂铝的燃烧实验研究方法[J]. 固体火箭技术, 2015, 38(6): 833-836.
[17] Price E W, Sigman R K. Combustion of Aluminized Solid Propellants[M]. Washington: Progress in Astronautics and Aeronautics, 2000.
[18] Geisler R L. A Global View of the Use of Aluminum Fuel in Solid Rocket Motors[R]. AIAA 2002-3748.
[19] Price E W. Combustion of Metalized Propellants[M]. New York: Progress in Astronautics and Aeronautics, 1984. (编辑:朱立影)　　　　　　　　　　　　　*　收稿日期:2015-06-05；修订日期:2015-08-10。基金项目:国家自然科学基金(51206136)。作者简介:刘鑫,男,博士生,研究领域为航空宇航推进理论与工程。E-mail: liuxin02030601@163.com