Characteristic analysis of RBCC engine at Mach number 0 to 8

LIU Hao

doi:10.7638/kqdlxxb-2021.0132

English Version Journal Login

您当前的位置：

首页 >

文章列表页 >

Characteristic analysis of RBCC engine at Mach number 0 to 8

更新时间：2026-05-28

- Characteristic analysis of RBCC engine at Mach number 0 to 8
- Vol. 40, Issue 1, Pages: 165-180(2022)
- 作者机构：
  
  西安航天动力研究所,西安,710100
- 作者简介：
- 基金信息：
- DOI：10.7638/kqdlxxb-2021.0132
  CLC： V430
- Published：2022
- 稿件说明：
移动端阅览
刘昊. 马赫数0至8范围RBCC发动机特性[J]. 空气动力学学报, 2022, 40(1): 165−180.

LIU Hao. Characteristic analysis of RBCC engine at Mach number 0 to 8[J]. 2022, 40(1): 165-180.
刘昊. 马赫数0至8范围RBCC发动机特性[J]. 空气动力学学报, 2022, 40(1): 165−180. DOI： 10.7638/kqdlxxb-2021.0132

LIU Hao. Characteristic analysis of RBCC engine at Mach number 0 to 8[J]. 2022, 40(1): 165-180. DOI： 10.7638/kqdlxxb-2021.0132.

摘要

为获得飞行马赫数

= 0～8 RBCC发动机特性及结构调节规律，基于试验数据，建立了采用控制体法，考虑热完全气体效应、化学平衡流动效应、黏性损失及热损失等影响的发动机特性分析模型，并通过发动机自由射流试验获得的推力、比冲数据对所建立的发动机特性分析模型进行确认。完成二元中心火箭布局变结构模型RBCC发动机火箭引射模态、火箭冲压模态及冲压模态特性仿真，定量获得了飞行动压、马赫数、攻角、当量比、火箭流量等因素变化对发动机性能影响；并针对给定模拟飞行弹道，完成

= 0～8 RBCC发动机特性计算，给出了进气道收缩比、燃烧室扩张比、尾喷管扩张比、发动机总面积比随飞行马赫数及工作模态变化规律。研究表明：1）火箭引射模态，马赫数每增加1，推力、比冲增加约18.2%，火箭推力增益增加约15%；2）火箭冲压模态，火箭流量越大，火箭推力增益越小，且获得正的火箭推力增益范围越窄；3）

= 2模态转换点，发动机性能及结构参数均存在间断，确保推力及结构参数的连续调节、匹配应是模态转换规律制定的关注点；4）模拟弹道下，进气道收缩比、燃烧室扩张比、尾喷管扩张比、发动机总面积比在

= 0～8范围内分别变化6.17、4.26、30.38、8.94倍。

Abstract

In order to obtain the characteristics and structural regulation law of the RBCC (Rocket-Based Combined-Cycle) engine in a flight Mach number range of

= 0～8

an engine characteristic analysis model is established based on experimental data

which adopts the control volume method and takes into account the effects of heat complete gas

chemical equilibrium flow

viscosity loss

heat loss

etc. The model is then ver

ified using the thrust and specific impulse data obtained in a free-jet experiment. Characteristics of the RBCC engine of two-dimensional variable structures are analyzed for three operation modes

i.e. the injector operation mode

the ramjet operation mode and the rocket ramjet mode. Effects of the flight dynamic pressure

Mach number

angle of attack

equivalent ratio and rocket flow rate on the performance of the model engine are quantitatively obtained. A characteristic analysis is carried out for the

= 0～8 RBCC engine along a simulated trajectory

and variations with the flight Mach number at different engine operation modes are given for the air inlet contraction ratio

combustor expansion ratio

nozzle expansion ratio

total area ratio. The results show that: 1) Under the ejector operation mode

for every increasement of one in the flight Mach number

the engine thrust and specific impulse are increased by about 18.2%

and the rocket thrust gain is increased by about 15%. 2) Under the ramjet operation mode

with the increase of the rocket flow rate

the rocket thrust gain decreases

and the larger the rocket flow rate is

the narrower the positive rocket thrust gain range is. 3) During the operation mode transformation at

= 2

the performance and structural parameters of the engine are both discontinoues

thus special attention needs to be put for the continuous adjustment of the thrust and structural parameters of the engine. 4) Under the given simulated trajectory

the inlet contraction ratio

the combustor expansion ratio

the nozzle expansion ratio and the engine total area ratio vary 6.17

4.26

30.38

8.94 times in the range of

= 0～8

respectively.

关键词

Keywords

references

ESCHER W, SCHNURSTEIN R. A retrospective on early cryogenic primary rocket subsystem designs as integrated into rocket-based combined-cycle (RBCC) engines[C]//29th Joint Propulsion Conference and Exhibit, Monterey, CA. Reston, Virginia: AIAA, 1993. AIAA-93-1944. doi:10.2514/6.1993-1944

CARL EHRLICH J. Early studies of RBCC applications and lessons learned for today[C]//36th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Las Vegas, NV. Reston, Virginia: AIAA, 2000. AIAA-2000-3105. doi:10.2514/6.2000-3105

CZYSZ P, LITTLE M. Rocket Based Combined Cycle engine (RBCC) - A propulsion system for the 21st century[C]//Proc of the 5th International Aerospace Planes and Hypersonics Technologies Conference, Munich, Germany. Reston, Virginia: AIAA, 1993. AIAA-93-5096. doi:10.2514/6.1993-5096

ESCHER W J D. A US history of airbreathing/rocket combined-cycle (RBCC) propulsion for powering future aerospace transports, with a look ahead to the year 2020[R ] . ISABE-99-7028, 1999: 1-38. https://ntrs.nasa.gov/api/citations/19990062726/downloads/19990062726.pdf

MCDANIEL J C, CHELLIAH H, GOYNE C P, et al. US national center for hypersonic combined cycle propulsion-an overview[C]//16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference, HYTASP-17: Program Overview III, 2009. AIAA 2009-7280, 2009: 1-18. doi:10.2514/6.2009-7280

TANI K, TOMIOKA S, KATO K, et al. Current status of researches of the combined cycle engine at JAXA[R]. ISABE-2011-1334, 2011: 1-8.

ZHANG T T, WANG Z G, HUANG W, et al. The overall layout of rocket-based combined-cycle engines: a review[J]. Journal of Zhejiang University-SCIENCE A, 2019, 20(3): 163-183. DOI:10.1631/jzus.A1800684

ZHANG M, ZHANG M Z, LIU H. Progress and analysis of rocket based combined cycle(RBCC) propulsion system[J]. Science Technology Review, 2020, 38(12): 54-68. (in Chinese)

ESCHER W, PRYOR D, HYDE E. Development of a 12-thrust chamber kerosene/oxygen primary rocket subsystem for an early (1964) air-augmented rocket ground test system[C]//9th International Space Planes and Hypersonic Systems and Technologies Conference, Norfolk, VA. Reston, Virginia: AIAA, 1999. AIAA 1999-4896. doi:10.2514/6.1999-4896

HYDE E, ESCHER W, RODDY J. Marquardt’s Mach 4.5 supercharged ejector ramjet high-performance aircraft engine project[C]//36th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Las Vegas, NV. Reston, Virginia: AIAA, 2000. AIAA 2000-3109. doi:10.2514/6.2000-3109

RATEKIN G, GOLDMAN A, ORTWERTH P, et al. Rocketdyne RBCC engine concept development[C]//14th International Symposium on Air Breathing Engines, 1999 . ISABE-99-7179.

BULMAN M, SIEBENHAAR A. The strutjet engine-Exploding the myths surrounding high speed airbreathing propulsion[C]//31st Joint Propulsion Conference and Exhibit, San Diego, CA. Reston, Virginia: AIAA, 1995. AIAA-95-2475. doi:10.2514/6.1995-2475

THOMAS S R, PALAC D T, TREFNY C J, et al. Performance evaluation of the NASA GTX RBCC flowpath[C ] //5th International Symposium on Airbreathing Engines, 2001. ISABE-2001-1070. ISABE-2001-1070. https://ntrs.nasa.gov/api/citations/20010092480/downloads/20010092480.pdf?attachment=true

FOSTER R, ESCHER W, ROBINSON J. Studies of an extensively axisymmetric rocket based combined cycle (RBCC) engine powered single-stage-to-orbit (SSTO) vehicle[C]//25th Joint Propulsion Conference, Monterey, CA Reston, Virginia: AIAA, 1989. AIAA-89-2294. doi:10.2514/6.1989-2294

OLDS J, BRADFORD J, CHARANIA A, et al. Hyperion-An SSTO vision vehicle concept utilizing rocket-based combined cycle propulsion[C]//9th International Space Planes and Hypersonic Systems and Technologies Conference, Norfolk, VA. Reston, Virginia: AIAA, 1999. AIAA 1999-4944. doi:10.2514/6.1999-4944

STEMLER J N, BOGAR T J, FARRELL D J, et al. Assessment of RBCC-powered VTHL SSTO vehicles[C]//9th International Space Planes and Hypersonic Systems and Technologies Conference, Norfolk, VA, U. S. A., 1999. AIAA 99-4947. doi:10.2514/6.1999-4947

ROCHE J M, MCCURDY D R. Preliminary sizing of vertical take-off rocket-based combined-cycle powered launch vehicles[C ] // Space Transportation and Safety: Combustion. Monterey, CA, 2000. NASA/TM-2001-21066. E-12503-1. NAS 1.15: 210668. https://ntrs.nasa.gov/api/citations/20010017162/downloads/20010017162.pdf

O’BRIEN T, LEWIS M. Transonic through hypersonic performance of an RBCC engine-airframe integrated vehicle[C]//10th AIAA/NAL-NASDA-ISAS International Space Planes and Hypersonic Systems and Technologies Conference, Kyoto, Japan. Reston, Virginia: AIAA, 2001. doi: 10.2514/6.2001-1919

CULVER G. Performance comparison of RBCC- and TBCC-based reusable launch vehicles with enhancing technologies[C]//39th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Huntsville, Alabama. Reston, Virginia: AIAA, 2003. AIAA-2003-5035. doi: 10.2514/6.2003-5035

KRIVANEK T M, ROCHE J M, RIEHL J P, et al. Affordable flight demonstration of the GTX air-breathing SSTO vehicle concept[R ] . NASA/TM-2003-212315, 2003. https://ntrs.nasa.gov/api/citations/20030055618/downloads/20030055618.pdf

HANK J, FRANKE M, EKLUND D. TSTO reusable launch vehicles using airbreathing propulsion[C]//42nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference Exhibit, Sacramento, California. Reston, Virigina: AIAA, 2006: 1-19. AIAA-2006-4962. doi:10.2514/6.2006-4962

YOUNG D, KOKAN T, TANNER C, et al. Lazarus: A SSTO hypersonic vehicle concept utilizing RBCC and HEDM propulsion technologies[C]//14th AIAA/AHI Space Planes and Hypersonic Systems and Technologies Conference, Canberra, Australia. Reston, Virginia: AIAA, 2006. AIAA-2006-8099. doi:10.2514/6.2006-8099

STEELANT J, VARVILL R, WALTON C, et al. Achievements obtained for sustained hypersonic flight within the LAPCAT-II project[C]//20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, Glasgow, Scotland. Reston, Virginia: AIAA, 2015. AIAA-2008-2578. doi:10.2514/6.2015-3677

FALEMPIN F, BOUCHEZ M, PERRILLAT V. LAPCAT 2-Axisymmetric concept for a Mach 8 cruiser preliminary design and performance assessment[C]//16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference, Bremen, Germany. Reston, Virginia: AIAA, 2009. AIAA-2009-7437. doi:10.2514/6.2009-7437

KOTHARI A, LIVINGSTON J, TARPLEY C, et al. Rocket based combined cycle hypersonic vehicle design for orbital access[C]//17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, San Francisco, California. Reston, Virigina: AIAA, 2011: 1-26. AIAA-2011-2338. doi:10.2514/6.2011-2338

Quinn J E. ISTAR: Project status and ground test engine design[R ] . AIAA-2003-5235, 2003: 1-12. https://ntrs.nasa.gov/api/citations/20030065949/downloads/20030065949.pdf

OLDS J, BRADFORD J. SCCREAM (simulated combined-cycle rocket engine analysis module): A conceptual RBCC engine design tool[C ] //33rd Joint Propulsion Conference and Exhibit, Seattle, WA. Reston, Virginia: AIAA, 1997. AIAA-97-2760. http://www.ssdl.gatech.edu/sites/default/files/ssdl-files/papers/conferencePapers/AIAA-1997-2760.pdf doi:10.2514/6.1997-2760

BRADFORD J, OLDS J. Improvements and enhancements to SCCREAM, a conceptual RBCC engine analysis tool[C]//34th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Cleveland, OH. Reston, Virginia: AIAA, 1998. AIAA-98-3775. doi:10.2514/6.1998-3775

OLDS J R, BRADFORD J E. SCCREAM: A conceptual rocket-based combined-cycle engine performance analysis tool[J]. Journal of Propulsion and Power, 2001, 17(2): 333-339. DOI:10.2514/2.5746

OLDS J R. Launch vehicle systems analysis[R ] . NASA-Marshall Grant NAG8-1302, 1999. https://ntrs.nasa.gov/api/citations/19990025901/downloads/19990025901.pdf

MCKAMEY R, LANDRUM D. A one-dimensional engineering model for the evaluation of rocket-based combined cycle engine performance[C]//37th Joint Propulsion Conference and Exhibit, Salt Lake City, UT. Reston, Virginia: AIAA, 2001. AIAA-2001-3462. doi:10.2514/6.2001-3462

HUANG S H, HE H Q, HE G Q, et al. Conceptual design model of rocket base combined cycle propulsion system[J]. Journal of Propulsion Technology, 2003, 24(1): 1-5. (in Chinese)

LV X, LIU P J, HE G Q. Study on RBCC motor performance analysis method[J]. Journal of Solid Rocket Technology, 2007, 30(2): 120-123. (in Chinese)

LYU X, HE G Q, LIU P J, et al. Improvements to RBCC engine performance analysis model[J]. Journal of Solid Rocket Technology, 2010, 33(4): 387-390. (in Chinese)

WANG H X, XU X. Research on performance iterative algorithm of rocket based combined cycle engine[J]. Journal of Rocket Propulsion, 2015, 41(1): 56-62, 89. (in Chinese)

AN J N. Investigation of rocket-based combined cycle engine ejector mode[D]. Changsha: National University of Defense Technology, 2011. (in Chinese)

YE Z Y. Concept analyses and operation mode of RBCC engine[J]. Journal of Rocket Propulsion, 2003, 29(1): 8-12. (in Chinese)

HUANG W, LUO S B, WANG Z G. Performance analysis of RBCC engine[J]. Journal of Rocket Propulsion, 2007, 33(5): 6-10. (in Chinese)

ZHANG M Z, LI B, WANG J, et al. Thinking about RBCC propulsion system[J]. Journal of Rocket Propulsion, 2013, 39(1): 1-7. (in Chinese)

ZHANG M Z, ZHANG M, YAN J F, et al. Discussion about work modal of RBCC power system[J]. Journal of Rocket Propulsion, 2015, 41(2): 1-6. (in Chinese)

LU Y Y, ZHANG M Z, YAN J F. Influences of shock wave in rocket nozzle on RBCC performance[J]. Journal of Rocket Propulsion, 2013, 39(5): 46-50, 97. (in Chinese)

LIU H, WANG J. Discussion of rocket thrust augmentation for RBCC engine[J]. Journal of Rocket Propulsion, 2017, 43(1): 18-23. (in Chinese)

LIU H L. Trajectory simulation and optimization of self-seeking artillery missile[D]. Taiyuan: North University of China, 2019. (in Chinese)

LIANG D W, LI B, RONG W. Thermodynamic characteristics of thermally perfect gas and solution of N-S equations[J]. Journal of Nanjing University of Aeronautics Astronautics, 2003, 35(4): 424-429. (in Chinese)

GORDON S, MCBRIDE B J. Computer program for calculation of complex chemical equilibrium compositions and applications. Part 1: Analysis [R ] . NASA Reference Publication 1311, 1994. https://ntrs.nasa.gov/api/citations/19950013764/downloads/19950013764.pdf

Views

下载量

CSCD

Alert me when the article has been cited

提交

Tools

Publicity Resources

Effect of DBD plasma excitation on aerodynamic characteristics of the NACA 0012 airfoil

Hydrogen combustion experiments of a fullpath scramjet at a Mach 10 condition of high enthalpy shock tunnel

Progress in high-speed high-temperature turbulence research

Numerical simulation on gust responses of high aspect ratio aircraft

Research progress on noise reduction of centrifugal fans

Related Author

YAO Cheng

LI Yiwen

WANG Zhongming

GAO Yongxin

WANG Rongchao

WU Hengyi

WEI Baoxi

YANG Fujiang

Related Institution

College of Civil Engineering, Hefei University of Technology, Hefei

Science and Technology on Plasma Dynamics Laboratory, Air Force Engineering University, Xi’an

China Academy of Aerospace Aerodynamics, Beijing

Engineering and Materials Science Center, University of Science and Technology of China, Hefei

Beijing Power Machinery Institute, Beijing

AI问答

⁰