航天推进技术研究院主办
[1]崔 朋,徐万武,陈 健,等.火箭基组合循环燃烧组织研究现状[J].火箭推进,2015,41(04):1-7.
CUI Peng,XU Wanwu,CHEN Jian,et al.Research progress about rocket based combined cycle combustion organization[J].Journal of Rocket Propulsion,2015,41(04):1-7.
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CUI Peng,XU Wanwu,CHEN Jian,et al.Research progress about rocket based combined cycle combustion organization[J].Journal of Rocket Propulsion,2015,41(04):1-7.
火箭基组合循环燃烧组织研究现状
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
41
期数:
2015年04期
页码:
1-7
栏目:
专论与综述
出版日期:
2015-09-30
- Title:
- Research progress about rocket based combined cycle combustion organization
- 关键词:
- 火箭基组合循环（RBCC）; 燃烧组织; 燃料喷注方案; 二次燃烧; 热力喉道调节
- Keywords:
- rocket based combined cycle; combustion organization; fuel injection scheme; secondary combustion; adjustment of thermal throat
- 分类号:
- V439-34
- 文献标志码:
- A
- 摘要:
- 随着航天推进对高效性和经济性需求的增加，人们越来越希望能够研制出高推重比和高比冲的发动机。火箭基组合循环（RBCC）发动机融合了火箭发动机和冲压式发动机的优势，成为未来航空航天领域发展的重要方向。精确而高效的燃烧组织作为其关键技术之一，对RBCC宽速域内可靠运行具有重要意义。详细综述了RBCC燃烧组织的研究现状和进展，主要涉及燃料喷注方案、燃烧模式以及热力喉道调节3个方面。具体论述了不同工作模式下燃料的喷注方案以及热力喉道的调节技术，阐述了不同燃烧模式的研究进展，分析了RBCC燃烧组织研究过程中的难点和国内外在该方面的一些经验教训，指出了当前研究工作中存在的问题，并对研究思路提出了一些建议，以期对未来RBCC燃烧组织的研究提供一定的参考。
- Abstract:
- With the increased demand for efficiency and economy on aerospace propulsion, people are looking forward to developing an engine with high thrust-to-weight ratio and high specific impulse. Rocket based combined cycle (RBCC) engine becomes an important direction of development in the fields of aeronautics and astronautics, in which the advantages of rocket engine and ramjet engine are fused. Precise and highly efficient combustion organization is important for the wide range reliable operation and thrust increase of RBCC engine. In this paper, the fundamental concepts and principles of RBCC are introduced, and the research progress of combustion organization on RBCC is reviewed in the aspects of fuel injection scheme, combustion mode and thermal throat adjustment. The fuel injection schemes and thermal throat adjustment in different modes are discussed. The investigation situation of each combustion mode is elaborated. The difficulties and experience during the development of RBCC combustion organization are analyzed. Some suggestions for the study on RBCC in the future are given.
参考文献/References:
[1]OLDS J R. Two options for flight testing rocket-based combined-cycle engines[J]. Journal of Spacecraft and Ro-
ck ets, 1999, 36(5): 693-700.
[2]LAZAREV V. Structure of reusable hypersonic vehicles Problems of weight, cost and operating effectiveness,
AIAA 99-4865[R]. USA: AIAA, 1999.
[3]张鹏峰. 国外RBCC组合循环发动机发展趋势及关键技术[J]. 飞航导弹, 2013(8): 68-71.
[4]AOKI S, LEE J, MASUYA G. Aerodynamic experiment on an ejector-jet[J]. Journal of Propulsion and Power, 2005, 21(3): 496-503.
[5]QUINN J E. ISTAR: Project status and ground test engine design, AIAA 2003-5235[R]. USA: AIAA, 2003.
[6]CHASE G, MATT T, MARTIQUA P, et al. Investigation of rocket based combined cycle design modifications to improve Cmo and Cma at subsonic speeds, AIAA 2012- 2894[R]. New Orleans, USA: American Institute of Aeronautics and Astronautics, 2012.
[7]KOTHARI A P, LIVINGSTON J W, TARPLEY C, et al. A reusable, rocket and airbreathing combined cycle hypersonic vehicle design for access-to-space, AIAA 2010- 8905[R]. California, USA: American Institute of Aeronautics and Astronautics, 2010.
[8]SIEBENHAAR A, BULMAN M J. The strutjet engine: the overlooked option for space launch, AIAA 95-3124[R]. USA: AIAA, 1995.
[9]BULMAN M, SIEBENHAAR A. The strutjet engine: exploding the myths surrounding high speed airbreathing propulsion, AIAA 95-2475[R]. USA: AIAA, 1995.
[10]SIEBENHAAR A, BULMAN M J, BONNAR D. The role of the strutjet engine in new global and space markets, IAF 98-S.5.04[R]. [S.l.]: IAF, 1998.
[11]刘洋, 何国强, 刘佩进, 等. RBCC组合循环推进系统研究现状和进展[J]. 固体火箭技术, 2009, 32(3): 288- 93.
[12]汤祥, 何国强, 秦飞, 等. 轴对称结构RBCC发动机超燃模态试验和数值模拟[J]. 固体火箭技术, 2012, 35(2): 166-70.
[13]徐朝启, 何国强, 刘佩进, 等. RBCC发动机亚燃模态一次火箭引导燃烧的实验[J]. 航空动力学报, 2013, 28(3): 567-72.
[14]刘佩进, 何国强, 李宇飞. RBCC 引射火箭模态二次燃烧实验[J]. 推进技术, 2004, 25(1): 75-7.
[15]KANDA T, KATO K, TANI K, et al. Experimental study of a combined-cycle engine combustor in ejector-jet mode, JAXA-RR-07-011[R]. Japan: JAXA, 2008.
[16]KOUCHI T, KOBAYASHI K, KUDO K, et al. Performance of a RBCC combustor operating in ramjet mode, AIAA-2006-4867 [R]. USA: AIAA, 2006.
[17]李鹏飞, 何国强, 秦飞, 等. 轴对称结构RBCC发动机超燃模态性能分析[J]. 固体火箭技术, 2011, 34(6): 728-33.
[18]KODERA M, TOMIOKA S, UEDA S, et al. Numerical analysis of scramjet mode operation of a RBCC engine [R]. USA: AIAA, 2012.
[19]MASAO T, SADATAKE T, MASATOSHI K, et al. Mach 8 flight condition tests of rocket-ramjet combined-cycle engine model[R]. USA: AIAA, 2013.
[20]SIEBERIHAAR A, BUHNAN M, NORRIS R, et al. Development and testing of the aerojet strutjet combustor, AIAA-99-4868[R]. USA: AIAA, 1999.
[21]DOBROWOLSKI A. Analysis of nonconstant area combustion and mixing in ramjet and rocket-ramjet hybrid engines[M]. Washington DC: National Aeronautics and Space Administration, 1966.
[22]STROUP K, PONTZER R. Advanced ramjet concepts, Volume I: Ejector ramjet systems demonstration, AFAPL-TR-67-118[R]. [S.l.]: AFAPL, 1968.
[23]RUSSELL R M, BROCCO D S, DAINES R L. Modeling and validation of an ejector primary rocket for shielded afterburning fuel injection[R]. USA: AIAA, 1999.
[24]BOND R B, EDWARDS D J R. CFD analysis of an independently fueled ramjet stream in an RBCC engine[R]. USA: AIAA, 2003.
[25]Daines R L, Matthew R L. Numerical analysis of the effects of combustion in rocket ejectors, AIAA 98-3772 [R]. USA: AIAA, 1998.
[26]LEHMAN M, PAL S, BRODA J C, et al. Raman spectroscopy based study of RBCC ejector mode performance[R]. USA: AIAA, 1999.
[27]MAN Z, GUO-QIANG H, PEI-JIN L. Performance improved by multistage rockets ejection in RBCC engine [R]. USA: AIAA, 2008.
[28]李强, 刘佩进, 陈剑. 一次燃气混合比对引射火箭二次燃烧火焰稳定的影响[J]. 固体火箭技术, 2009, 32(2): 427-430.
[29]FOELSCHE R O, TSA C Y, BAKOS R J. Experiments on a RBCC ejector scramjet with integrated, staged secondary-fuel injection, AIAA 99-2242[R]. USA: AIAA, 1999.
[30]黄生洪, 何洪庆, 何国强, 等. 构型及二次燃烧对RBCC引射模态推力性能的影响[J]. 空气动力学学报, 2005, 23(2): 139-43+72.
[31]YUNGSTER S, TREFNY C J. Analysis of a new ro-
cket-based comb ined-cycle engine concept at low speed [R]. USA: AIAA, 1999.
[32]EDWARDS J R, MCRAE D S, BOND R B. Three dimensional numerical simulation of rocket-based combined-cycle engine response during mode transition events, NASA/CR-2003-212193[M]. USA: NASA, 2003.
[33]JICHAO H, JUNTAO C, BAO W. Ignition and flame stabilization of a strut-jet RBCC combustor with small rocket exhaust[J]. The Scientific World Journal, 2014, 675498: 1-6.
[34]陆晋丽. 燃烧室结构变化对火箭引射模态性能影响研究[D]. 西安: 西北工业大学, 2007.
[35]吕翔, 何国强, 刘佩进, 等. RBCC火箭引射模态热力壅塞研究 [J]. 航空动力学报, 2008, 23(3): 563-9.
[36]MASUMOTO R, TOMIOKA S, YAMASAKI H. Study on transition of combustion modes in a dual-mode combustor [R]. USA: AIAA, 2009.
[37]王亚军, 何国强, 潘科玮, 等. RBCC亚燃模态热力喉道机理的数值模拟[J]. 推进技术, 2013, 34(7): 932-7.
[38]路媛媛, 张蒙正, 严俊峰. 火箭推力室喷管内激波对 RBCC 性能影响分析[J]. 火箭推进, 2013, 39(5): 46-50.
LU Yuanyuan, ZHANG Mengzheng, YAN Junfeng．Influences of shock wave in rocket nozzle on RBCC performance[J]. Journal of Rocket Propulsion, 2013, 39(5): 46-50．
[39]安佳宁, 徐万武. RBCC引射模态冷流试验研究[J]. 火箭推进, 2012, 38(4): 38-42．
AN Jianing, XU Wanwu. Cold flow experimental research of RBCC ejector modal[J]. Journal of Rocket Propulsion, 2012, 38(4): 38-42.
备注/Memo
收稿日期：2015-01-19；修回日期：2015-04-05 作者简介：崔朋（1990—），男，硕士，研究领域为火箭及其组合循环推进技术
更新日期/Last Update:
1900-01-01