含铝HTPB固液混合推进燃料燃烧性能研究

推进技术 ›› 2018, Vol. 39 ›› Issue (6): 1412-1419.

含铝HTPB固液混合推进燃料燃烧性能研究

陈苏杭,唐乐,许志伟,张伟,沈瑞琪,叶迎华

南京理工大学化工学院，江苏南京 210094,南京理工大学化工学院，江苏南京 210094,南京理工大学化工学院，江苏南京 210094,南京理工大学化工学院，江苏南京 210094,南京理工大学化工学院，江苏南京 210094,南京理工大学化工学院，江苏南京 210094

发布日期:2021-08-15
作者简介:陈苏杭，男，博士生，研究领域为固液混合推进燃料配方设计。E-mail: chensuhang_nust@126.com 通讯作者:沈瑞琪，男，博士，教授，研究领域为含能材料和化学推进技术。
基金资助:
中央高校基本科研业务费专项资金资助(30918011315)。

Study on Combustion Performance of HTPB-Based Fuels Containing Aluminum Particles for Hybrid Propellant

School of Chemical Engineering，Nanjing University of Science and Technology，Nanjing 210094，China,School of Chemical Engineering，Nanjing University of Science and Technology，Nanjing 210094，China,School of Chemical Engineering，Nanjing University of Science and Technology，Nanjing 210094，China,School of Chemical Engineering，Nanjing University of Science and Technology，Nanjing 210094，China,School of Chemical Engineering，Nanjing University of Science and Technology，Nanjing 210094，China and School of Chemical Engineering，Nanjing University of Science and Technology，Nanjing 210094，China

Published:2021-08-15

摘要/Abstract

摘要： 为了研究铝粒子对HTPB固液混合推进燃料退移速率的影响，采用透明燃烧室实验系统，开展了含不同粒径(平均粒径分别为100nm，500nm和50μm)、不同质量分数(5wt%，10wt%和15wt%)的铝粒子HTPB燃料退移速率测试和分析，获取了燃烧室压力为1MPa下的含铝HTPB燃料的瞬时退移速率随氧气质量密流变化的曲线。研究结果表明，随着氧气质量密流的增加，含铝HTPB燃料的退移速率增加；当氧气质量密流为250 ~ 375 kg/(m2·s)和铝粒子含量为5wt %时，平均粒径为500nm比平均粒径为100nm和50μm的含铝HTPB燃料退移速率高；当铝粒子平均粒径为500nm时，含铝HTPB燃料的退移速率随着铝粒子含量的增加而增加。

关键词: 固液混合推进燃料；铝粒子；燃烧特性；退移速率

Abstract: In order to investigate the effects of the aluminum particles on the combustion performance of HTPB-based fuels for hybrid propellant， a transparent combustion chamber experimental system was used in this study. HTPB-based fuel containing different particle size (average size is 100nm， 500nm and 50μm) and different mass fraction (5wt%， 10wt% and 15wt%) of aluminum particle respectively were tested and analyzed. The curves of regression rate vs. oxygen mass flux for HTPB-based fuel containing aluminum particles were obtained under the combustion chamber pressure of 1.0MPa. The results showed that the regression rate of HTPB-based fuel containing aluminum particles increased with the increase of the oxygen mass flux. The regression rate of HTPB-based fuel containing 5wt% 500nm aluminum particles was higher than that of HTPB-based fuel containing 5wt% 100nm and 50μm aluminum particles under oxygen flux 250 ~ 375kg/(m2·s). The regression rate of HTPB-based fuel containing 500nm aluminum particles increased with the increase of aluminum particle content.

Key words: Hybrid propulsion fuel；Aluminum particles；Combustion characteristic；Regression rate

陈苏杭,唐乐,许志伟,张伟,沈瑞琪,叶迎华. 含铝HTPB固液混合推进燃料燃烧性能研究[J]. 推进技术, 2018, 39(6): 1412-1419.

CHEN Su-hang,TANG Yue,XU Zhi-wei,ZHANG Wei,SHEN Rui-qi,YE Ying-hua. Study on Combustion Performance of HTPB-Based Fuels Containing Aluminum Particles for Hybrid Propellant[J]. Journal of Propulsion Technology, 2018, 39(6): 1412-1419.

参考文献

[1] Chiaverini M J. Fundamentals of Hybrid Rocket Combustion and Propulsion[M]. USA: American Institute of Aeronautics and Astronautics, 2000.
[2] 蔡国飙. 固液混合火箭发动机技术综述与展望 [J]. 推进技术, 2012, 33(6): 831-839. (CAI Guo-biao. Development and Application of Hybrid Rocket Motor Technology: Overview and Prospect[J]. Journal of Propulsion Technology, 2012, 33(6): 831-839.)
[3] 田辉, 吴俊峰, 俞南嘉, 等. 采用N2O与含金属HTPB燃料固液火箭发动机燃速试验研究[J]. 推进技术, 2014, 35(3): 413-421. (TIAN Hui, WU Jun-feng, YU Nan-jia, et al. Experimental Research of Regression Rate of N2O and Metalized HTPB Hybrid Rocket Motor[J]. Journal of Propulsion Technology, 2014, 35(3): 413-421.)
[4] Cantwell B, Karabeyoglu A, Altman D. Recent Advances in Hybrid Propulsion [J]. International Journal of Energetic Materials and Chemical Propulsion, 2010, 9(4): 305-326.
[5] Paravan C, Reina A, Sossi A, et al. Time-Resolved Regression Rate of Innovative Hybrid Solid Fuel Formulations[C]. Munich: the European Conference for Aero-Space Sciences, 2013.
[6] Karabeyoglu A, Zilliac G, Cantwell B J, et al. Scale-Up Tests of High Regression Rate Paraffin-Based Hybrid Rocket Fuels[J]. Journal of Propulsion and Power, 2004, 20(6): 1037-45.
[7] Karabeyoglu A, Zilliac G, Castellucci P, et al. Development of High-Burning-Rate Hybrid-Rocket -Fuel Flight Demonstrators [R]. AIAA 2003-5196.
[8] Karabeyoglu A, Stevens J, Geyzel D, et al. High Performance Hybrid Upper Stage Motor[R]. AIAA 2011-6025.
[9] Carmicino C, Sorge A R. The Effects of Oxidizer Injector Design on Hybrid Rockets Combustion Stability[R].AIAA 2006-4677.
[10] Sorge A R. Influence of a Conical Axial Injector on Hybrid Rocket Performance[J]. Journal of Propulsion and Power, 2006, 22(5): 984-95.
[11] Deluca L T, Rossettini L, Kappenstein C, et al. Ballistic Characterization of ALH3-Based Propellants for Solid and Hybrid Rocket Propulsion[R]. AIAA 2009-4874.
[12] Risha G, Ulas A, Boyer E, et al. Combustion of HTPB-Based Solid Fuels Containing Nano-Sized Energetic Powder in a Hybrid Rocket Motor[R]. AIAA 2001-3535.
[13] Risha G A, Boywe E, Wehrman R B. Performance Comparison of HTPB-Based Solid Fuels Containing Nano-Sized Energetic Powder in a Cylindrical Hybrid Rocket Motor[R]. AIAA 2002-3576.
[14] Risha G, Boywe E, Wehrman R, et al. Nano-Sized Aluminum and Boron-Based Solid Fuel Characterization in a Hybrid Rocket Engine [R]. AIAA 2003-4593.
[15] Deluca L, Galfetti L, Colombo G, et al. Time-Resolved burning of Solid Fuels for Hybrid Rocket Propulsion[C]. Saint Petersburg: the European Conference for Aero-space Sciences, 2011.
[16] Deluca L, Galfetti L, Maggi F, et al. Characterization of HTPB-Based Solid Fuel Formulations: Performance, Mechanical Properties, and Pollution[J]. Acta Astronautica, 2013, 92(2): 150-62.
[17] Shark S C, Zaseck C R, Pourpoint T L, et al. Performance and Flame Visualization of Dicyclopentadiene Rocket Propellants with Metal Hydride Additives[J]. Journal of Propulsion and Power, 2016, 32(4): 869-81.
[18] Karabeyoglu M A, Cantwell B J, Zilliac G. Development of Scalable Space-Time Averaged Regression Rate Expressions for Hybrid Rockets[J]. Journal of Propulsion & Power, 2015, 23(4): 737-47.
[19] Gramer D, Taagen T. Low Cost Surface Regression Sensor for Hybrid Fuels, Solid Propellants, and Ablatives [R]. AIAA 2001-3529.
[20] Chiaverini M J, Serin N, Johnson D K, et al. Regression Rate Behavior of Hybrid Rocket Solid Fuels[J]. Journal of Propulsion and Power, 2000, 16(1): 125-32.
[21] 秦钊. 固体燃料燃烧性能测试系统与HTPB基燃料的点火/燃烧特性研究 [D]. 南京:南京理工大学, 2015.
[22] 唐乐, 许志伟, 陈苏杭, 等. 固液混合推进石蜡燃料的性质及燃烧性能研究[J]. 推进技术, 2017, 38(9): 2138-2145. (TANG Yue, XU Zhi-wei, CHEN Su-hang, et al. Study on Properties and Combustion Performance of Paraffin Fuels for Hybrid Rocket Propulsion[J]. Journal of Propulsion Technology, 2017, 38(9): 2138-2145.)
[23] Gordon S, Mcbride B J. Computer Program for Calculation of Complex Chemical Equilibrium Compositions and Applications[M]. USA: NASA Reference Publication, 1994.
[24] Kubota N. Propellants and Explosives: Thermochemical Aspects of Combustion[M]. Manhattan: John Wiley & Sons, 2015.
[25] Favarò F M, Sirignano W A, Manzoni M, et al. Regression Rate Modeling for Hybrid Rocket Combustion[C]. Munich: the European Conference for Aero-Space Sciences, 2013.　　　　　　　　　　　　　*　收稿日期:2017-05-22；修订日期:2017-08-03。基金项目:中央高校基本科研业务费专项资金资助(30918011315)。作者简介:陈苏杭,男,博士生,研究领域为固液混合推进燃料配方设计。E-mail: chensuhang_nust@126.com通讯作者:沈瑞琪,男,博士,教授,研究领域为含能材料和化学推进技术。E-mail: rqshen@njust.edu.cn(编辑:朱立影)