Experimental Research of Regression Rate of N2O and Metalized HTPB Hybrid Rocket Motor

Journal of Propulsion Technology ›› 2014, Vol. 35 ›› Issue (3): 413-421.

• Material,Propellant and Fuel • Previous Articles Next Articles

Experimental Research of Regression Rate of N₂O and Metalized HTPB Hybrid Rocket Motor

School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100191, China

Published:2021-08-15

采用N2O与含金属HTPB燃料固液火箭发动机燃速试验研究

田辉,吴俊峰,俞南嘉,李君海,蔡国飙

（北京航空航天大学宇航学院,北京 100191）;（北京航空航天大学宇航学院,北京 100191）;（北京航空航天大学宇航学院,北京 100191）;（北京航空航天大学宇航学院,北京 100191）;（北京航空航天大学宇航学院,北京 100191）

作者简介:田辉(1978—),男,博士,副教授,研究领域为固液火箭发动机技术。E-mail:tianhui@buaa.edu.cn

Abstract

Abstract: Regression rate behavior of metalized fuel was investigated through motor experiments using the propellant of N₂O and HTPB fuel containing Al, Mg and carbon ingredients. Results of regression rate, combustion chamber pressure and combustion efficiency were obtained with three kinds of grains and multi-oxidizer mass flow rates. To analyze the effect of radiation heat flux on regression rate, equations were deduced to correlate and separate regression rate into two parts:one was convective evaluated by total mass flux and the other was radiative evaluated by radiative heat flux of condensed phase products. The radiation regression rate is about 30%~60% of total regression rate in all oxidizer to fuel mass ratio range except oxide-rich. The trends of radiation regression rate variation and its ratio to convective regression rate are analogous to condensed mass fraction of combustion products versus oxidizer to fuel mass ratio. And the regression rate generally increases with oxidizer mass flux. It also indicates that combustion efficiencies mostly between 80% and 97% are analogous to the normalized square value of theoretical combustion temperature in ranges around stoichiometric ratio and oxide-rich. 

Key words: Hybrid rocket motor; Combustion efficiency; Regression rate; Metalized solid fuel CLC number:V436.2Document code:AArticle number:1001-4055(2014)03-0413-09

摘要： 为了研究含金属固体燃料固液火箭发动机的燃速及发动机的工作特征,采用N₂O氧化剂与含Al,Mg和C的HTPB基固体燃料的固液发动机进行试验研究与分析,试验在3种尺寸药柱、多种氧化剂流量下进行,获得发动机的燃速、燃烧室压强及燃烧效率等参数。为分析辐射换热对燃速的影响,把燃速分成两部分并提出相应的分析式:一部分由对流换热控制的燃速,由通过药柱通道的总质量流率来衡量；另一部分由辐射换热控制,通过燃烧产物中凝相组分对固体燃料壁面的辐射换热量决定。对试验结果进行分析发现,除富氧的情况外,热辐射控制的燃速约占总燃速的30%~60%,辐射控制燃速与对流控制燃速的比例趋势与燃烧产物中凝相组分的质量分数随氧燃比的变化规律相似。同时,试验结果显示,试验燃速总体上随着固体药柱通道中氧化剂质量流率的增加而增大。发动机的燃烧效率绝大多数位于80%~97%的范围,在化学当量比附近和富氧范围内,随着燃烧温度的降低而降低,效率曲线与理论绝热燃烧温度值的平方相似。 

TIAN Hui, WU Jun-feng, YU Nan-jia, LI Jun-hai, CAI Guo-biao. Experimental Research of Regression Rate of N₂O and Metalized HTPB Hybrid Rocket Motor[J]. Journal of Propulsion Technology, 2014, 35(3): 413-421.

田辉,吴俊峰,俞南嘉,李君海,蔡国飙. 采用N2O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.

References

[1] Altman D, Holzman A.Overview and History of Hybrid Rocket Propulsion[A].In:Chiaverini M J, Kuo K K(Eds.).Fundamentals of Hybrid Rocket Combustion and Propulsion[M].Virginia:American Institute of Aeronautics and Astronautics Inc., 2007:1-33.
[2] Marxman G A, Wooldridge C E, Muzzy R J.Fundamentals of Hybrid Boundary Layer Combustion[R].AIAA 63-505.
[3] Marxman G A, Gilbert M.Turbulent Boundary Layer Combustion in Hybrid Rocket[C].New York:Ninth International Symposium on Combustion, Academic Press, 1963:371-383.
[4] Strand L D, Jones M D, Ray R L.Characterization of Hybrid Rocket Internal Heat Flux and HTPB Fuel Pyrolysis[R].AIAA 94-2876.
[5] Kosdon F J, Williams F A.Pressure Dependence of Nonmetalized Hybrid Fuel Regression Rate[J].AIAA Journal, 1967,5(4):774-777.
[6] Altman D, Humble R.Hybrid Rocket Propulsion System[A].In:Humble R W, Henry G N, Larson W J (Eds.).Space Propulsion Analysis and Design[M].New York:The McGraw-Hill Companies, Inc., 1995:365-441.
[7] Greatrix D R.Regression Rate Estimation for Standard-flow Hybrid Rocket Engines[J].Aerospace Science and Technology, 2009,3:358-363.
[8] Estey P N, Altman D, McFarlane J S.An Evaluation of Scaling Effects for Hybrid Rocket Motors[R].AIAA 91-2517.
[9] Gany A.Scale Effects in Hybrid Motors Under Similarity Conditions[R].AIAA 96-2846.
[10] Swami R D, Gany A.Analysis and Testing of Similarity and Scale Effects in Hybrid Rocket Motors[J].Acta Astronautica, 2003,2:619-628.
[11] Cai G, Zeng P, Li X, et al.Scale Effect of Fuel Regression Rate in Hybrid Rocket Motor[J].Aerospace Science and Technology, 2013,24:141-146.
[12] Lengelle G, Fourest B, Godon J C, et al.Condensed Phase Behavior and Ablation Rate of Fuels for Hybrid Rocket Propulsion[R].AIAA 93-2413.
[13] Chiaverini M J, Serin N, Johnson D K, et al.Regression Rate Behavior of Hybrid Rocket Solid Fuels[J].Journal of Propulsion and Power, 2000,6(1):125-132.
[14] Chiaverini M J, Kuo K K, Peretz A, et al.Regression-rate and Heat Transfer Correlations for Hybrid Rocket Combustion[J].Journal of Propulsion and Power, 2009,7(1):99-110.
[15] RAO Da-lin,ZHENG Yun-tao,LI Xin-tian, et al.Simulation and Optimization Design of Hybrid Rocket Motor[J].Journal of Propulsion Technology, 2010,1(5):513-518.(饶大林,郑赟韬,李新田,等.固液混合火箭发动机仿真与优化设计[J].推进技术,2010,31(5):513-518.)
[16] LI Xin-tian,ZENG Peng,TIAN Hui, et al.Instantaneous Fuel Regression Rate Analysis of Hybrid Rocket Motor Experiment[J].Journal of Propulsion Technology, 2012,3(2):211-215.(李新田,曾鹏,田辉,等.固液火箭发动机试验瞬时燃速分析方法[J].推进技术,2012,33(2):211-215.)
[17] Smoot L D, Price C F.Regression Rates of Metalized Hybrid Fuel Systems[J].AIAA Journal, 1966,4(5):910-915.
[18] Risha G A, Boyer E, Wehrman R B, et al.Performance Comparison of HTPB-based Solid Fuels Containing Nano-sized Energetic Powder in a Cylindrical Hybrid Rocket Motor[R].AIAA 2002-3576.
[19] Risha G A, Evans B, Boyer E, et al.Nano-sized Aluminum- and Boron-based Solid-fuel Characterization in a Hybrid Rocket Engine[R].AIAA 2003-4593.
[20] Farbar E, Louwers J, Kaya T.Investigation of Metallized and Nonmetallized Hydroxyl Terminated Polybutadiene/Hydrogen Peroxide Hybrid Rockets[J].Journal of Propulsion and Power,2007,3(2):476-486.
[21] Smoot L D, Price C F.Pressure Dependence of Hybrid Fuel Regression Rates[J].AIAA Journal,1967,5(1):102-106.
[22] Story G, Arves J.Flight Testing of Hybrid-Powered Vehicles[A].In:Chiaverini M J, Kuo K K (Eds.).Fundamentals of Hybrid Rocket Combustion and Propulsion[M].Virginia:American Institute of Aeronautics and Astronautics Inc., 2007:553-591.
[23] Strand L D, Ray R, Anderson F, et al.Hybrid Rocket Fuel Combustion and Regression Rate Study[R].AIAA 92-3302.
[24] Deluca L T, Galfetti L, Maggi F, et al.Characterization of HTPB-based Solid Fuel Formulation:Performance, Mechanical Properties, and Pollution[J].http://dx.doi.org/10.1016/j.actaastro.2012.05.002,3-4-2.
[25] Cai G.Development and Application of Hybrid Rocket Motor Technology:Overview and Prospect[J].Journal of Propulsion Technology, 2012,3(6):831-839.(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.)
[26] Li J, Luo Q.The Hybrid Sounding Rocket of ‘Beihang-2’[A].In:60th International Astronautical Congress 2009[C].Paris:International Astronautical Federation, 2009:8881-8889.

Experimental Research of Regression Rate of N₂O and Metalized HTPB Hybrid Rocket Motor

采用N2O与含金属HTPB燃料固液火箭发动机燃速试验研究

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