Similar articles

Abstract: Rocket-based combined-cycle (RBCC) engines are known as the most promising type of engine with the potential to realize ‘single stage to orbit’ (SSTO). This will dramatically reduce the cost of space round trips and improve the physical experience of astronauts. However, sixty years after this concept was first proposed, no RBCC engine has completed a real flight. The challenges in RBCC development include ejector, scramjet, mode transition, and thermal protection technologies. However, great progress has been made in recent years, suggesting a bright future for these engines. In this paper, we review worldwide progress in the overall layout of RBCC engines. The working process of RBCC engines is introduced to show their distinctiveness among traditional engines. RBCC engines are classified as rectangular section or axisymmetric configuration engines and the development of both types in different countries is reviewed. The engine-airframe integration design and mission planning of RBCC powered aircraft systems are analyzed separately. Even though RBCC powered aircraft and their missions remain conceptual, the design and planning processes are important for RBCC development and space round trips in the future. RBCC study is a typical multi-disciplinary design process. Research addressing the problems encountered by RBCC studies will promote the development of a range of disciplines relevant to aerospace science.

In this paper, a review of RBCC (rocket based combined cycle) progress around the world has been considered with its multi-disciplinary technologies and its developments by different countries. The engine-airframe integration design and mission planning of the RBCC powered aircraft system have been analyzed separately and identified different problems to enhance the research and developments in other disciplines which are useful for aerospace technology.

火箭基组合循环发动机总体布局研究进展

[1]Anazadehsayed A, Gerdroodbary MB, Amini Y, et al., 2017. Mixing augmentation of transverse hydrogen jet by injection of micro air jets in supersonic crossflow. Acta Astronautica, 137:403-414.

[2]Bian JZ, 2014. Design and Coverage Analysis of Combined Dynamic Space-based Ground-to-ground Combat Aircraft. MS Thesis, Harbin Institute of Technology, Harbin, China (in Chinese).

[3]Bond RB, Edwards JR, 2003. CFD analysis of an independently fueled ramjet stream in an RBCC engine. 41st Aerospace Sciences Meeting and Exhibit.

[4]Bond RB, Edwards JR, 2004. Computational analysis of an independent ramjet stream in a combined cycle engine. AIAA Journal, 42(11):2276-2283.

[5]Butuk N, Huque Z, Lynch D, 1998. Optimization of an integrated inlet/ejector of an RBCC engine using collaborative optimization. Proceedings of the 34th AIAA/ASME/ SAE/ASEE Joint Propulsion Conference and Exhibit, Article No. 3567.

[6]Chojnacki KT, Hawk CW, 1993. An assessment of the rocket-based combined cycle propulsion system for earth-to-orbit transportation. Proceedings of the 29th Joint Propulsion Conference and Exhibit, Article No. 1831.

[7]Chorkawy G, Etele J, 2017. Exchange inlet optimization by genetic algorithm for improved RBCC performance. Acta Astronautica, 138:201-213.

[8]Choubey G, Pandey KM, 2018. Effect of variation of inlet boundary conditions on the combustion flow-field of a typical double cavity scramjet combustor. International Journal of Hydrogen Energy, 43(16):8139-8151.

[9]Cui P, Xu WW, Li QL, 2018. Numerical simulation of divergent rocket-based-combined-cycle performances under the flight condition of Mach 3. Acta Astronautica, 142: 162-169.

[10]Daines R, Segal C, 1998. Combined rocket and airbreathing propulsion systems for space-launch applications. Journal of Propulsion and Power, 14(5):605-612.

[11]Debonis JR, Yungster S, 1996. Rocket-based combined cycle engine technology development-inlet CFD validation and application. Proceedings of the 32nd Joint Propulsion Conference and Exhibit, Article No. 3145.

[12]Escher WJD, 1995. Rocket-based combined-cycle (RBCC) powered spaceliner class vehicles can advantageously employ vertical takeoff and landing (VTOL). Proceedings of the International Aerospace Planes and Hypersonics Technologies Conference.

[13]Escher WJD, Schnurstein RE, 1993. A retrospective on early cryogenic primary rocket subsystem designs as integrated into rocket-based combined-cycle (RBCC) engines. Proceedings of the 29th Joint Propulsion Conference and Exhibit.

[14]Etele J, Sislian JP, Parent B, 2005. Effect of rocket exhaust configurations on ejector performance in RBCC engines. Journal of Propulsion and Power, 21(4):656-666.

[15]Etele J, Waung T, Cerantola DJ, 2012. Exchange inlet design for rocket-based combined-cycle engines. Journal of Propulsion and Power, 28(5):1026-1036.

[16]Etele J, Hasegawa S, Ueda S, 2014. Experimental investigation of an alternative rocket configuration for rocket-based combined cycle engines. Journal of Propulsion and Power, 30(4):944-951.

[17]Faulkner RF, 2001. Integrated system test of an airbreathing rocket (ISTAR). Proceedings of the 10th AIAA/ NAL-NASDA-ISAS International Space Planes and Hypersonic Systems and Technologies Conference, Article No. 1812.

[18]Flornes BJ, Escher DWJ, 1966. A study of composite propulsion systems for advanced launch vehicle applications. Contract NAS7-377. The Marquardt Corporation, Van Nuys, California, USA.

[19]Fujikawa T, Tsuchiya T, Tomioka S, 2015. Multi-objective, multidisciplinary design optimization of TSTO space planes with RBCC engines. Proceedings of the 56th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, Article No. 0650.

[20]Gerdroodbary MB, Mokhtari M, Fallah K, et al., 2016. The influence of micro air jets on mixing augmentation of transverse hydrogen jet in supersonic flow. International Journal of Hydrogen Energy, 41(47):22497-22508.

[21]Gerdroodbary MB, Fallah K, Pourmirzaagha H, 2017a. Characteristics of transverse hydrogen jet in presence of multi air jets within scramjet combustor. Acta Astronautica, 132:25-32.

[22]Gerdroodbary MB, Amini Y, Ganji DD, et al., 2017b. The flow feature of transverse hydrogen jet in presence of micro air jets in supersonic flow. Advances in Space Research, 59(5):1330-1340.

[23]Gong CL, Han L, 2012. Optimization of ascent trajectory for RBCC-powered RLV. Journal of Solid Rocket Technology, 35(3):290-295 (in Chinese).

[24]Gong CL, Chen B, Gu LX, 2014. Design and optimization of RBCC powered suborbital reusable launch vehicle. Proceedings of the 19th AIAA International Space Planes and Hypersonic Systems and Technologies Conference.

[25]Huang W, 2015. Effect of jet-to-crossflow pressure ratio arrangement on turbulent mixing in a flowpath with square staged injectors. Fuel, 144:164-170.

[26]Huang W, Jin L, Yan L, et al., 2014a. Influence of jet-to-crossflow pressure ratio on nonreacting and reacting processes in a scramjet combustor with backward-facing steps. International Journal of Hydrogen Energy, 39(36):21242-21250.

[27]Huang W, Yan L, Tan JG, 2014b. Survey on the mode transition technique in combined cycle propulsion systems. Aerospace Science and Technology, 39:685-691.

[28]Huang W, Du ZB, Yan L, et al., 2018. Flame propagation and stabilization in dual-mode scramjet combustors: a survey. Progress in Aerospace Sciences, 101:13-30.

[29]Huang ZW, He GQ, Qin F, et al., 2016. Large eddy simulation of combustion characteristics in a kerosene fueled rocket-based combined-cycle engine combustor. Acta Astronautica, 127:326-334.

[30]Jing TT, He GQ, Qin F, et al., 2018. An innovative self-adaptive method for improving heat sink utilization efficiency of hydrocarbon fuel in regenerative thermal protection system of combined cycle engine. Energy Conversion and Management, 178:369-382.

[31]Kanda T, Kudo K, Kato K, et al., 2003. Scramjet mode tests of a combined cycle engine combustor. Proceedings of the 12th AIAA International Space Planes and Hypersonic Systems and Technologies.

[32]Kanda T, Tomioka S, Ueda S, et al., 2005. Design of Sub-scale Rocket-ramjet Combined Cycle Engine Model. JAXA Research & Development Report, 6:1-15.

[33]Kanda T, Kato K, Tani K, et al., 2006. Experimental study of a combined-cycle engine combustor in ejector-jet mode. Proceedings of the 44th AIAA Aerospace Sciences Meeting and Exhibit.

[34]Kanda T, Tani K, Kudo K, 2007. Conceptual study of a rocket-ramjet combined-cycle engine for an aerospace plane. Journal of Propulsion and Power, 23(2):301-309.

[35]Kodera M, Tomioka S, Ueda S, et al., 2012. Numerical analysis of scramjet mode operation of a RBCC engine. Proceedings of the 18th AIAA/3AF International Space Planes and Hypersonic Systems and Technologies Conference.

[36]Kodera M, Ogawa H, Tomioka S, et al., 2014. Multi-objective design and trajectory optimization of space transport systems with RBCC propulsion via evolutionary algorithms and pseudospectral methods. Proceedings of the 52nd Aerospace Sciences Meeting.

[37]Koelle DE, Kuczera H, 1989. Sänger II, an advanced launcher system for Europe. Acta Astronautica, 19(1):63-72.

[38]Kouchi T, Kobayashi K, Kudo K, et al., 2006. Performance of a RBCC combustor operating in ramjet mode. Proceedings of the 42nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit.

[39]Lee J, Krivanek TM, 2005. Design and fabrication of the ISTAR direct-connect combustor experiment at the NASA hypersonic tunnel facility. Proceedings of the 43rd AIAA Aerospace Sciences Meeting and Exhibit.

[40]Lehman M, Pal S, Santoro RJ, 2000. Experimental investigation of the RBCC rocket-ejector mode. Proceedings of the 36th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Article No. 372.

[41]Lentsch A, Taguchi H, Shepperd R, et al., 2001. Vehicle concepts for an ejector ramjet combined cycle engine. Proceedings of the 10th AIAA/NAL-NASDA-ISAS International Space Planes and Hypersonic Systems and Technologies Conference, p.2120-2130.

[42]Li SB, Wang ZG, Huang W, et al., 2018. Design and investigation on variable Mach number waverider for a wide-speed range. Aerospace Science and Technology, 76:291-302.

[43]Lin BB, Pan HL, Qin F, et al., 2014. Effects of fuel-lean primary rocket on bypass ratio in RBCC ejector mode. Proceedings of 50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference.

[44]Ma JX, Chang JT, Ma JC, et al., 2018. Mathematical modeling and characteristic analysis for over-under turbine based combined cycle engine. Acta Astronautica, 148:141-152.

[45]Minato R, 2016. Advantage of ethanol fuel for gas generator cycle air turbo ramjet engine. Aerospace Science and Technology, 50:161-172.

[46]Muller S, Hawk CW, Bakker PG, et al., 2001. Mixing of supersonic jets in a strutjet propulsion system. Journal of Propulsion and Power, 17(5):1129-1131.

[47]Murzionak A, Etele J, 2014. Rapid supersonic performance estimation for a novel RBCC engine inlet. Aerospace Science and Technology, 32(1):51-59.

[48]Mutzman R, Murphy S, 2011. X-51 development: a chief engineer’s perspective. Proceedings of the 17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference.

[49]OUSD (Office of the Under Secretary of Defense (Comptroller)), 2018. National defense budget estimates for FY 2019. Technical Report, United States of America Department of the Defense. https://comptroller.defense.gov/portals/45/documents/defbudget/fy2019/fy19_green_book.pdf

[50]Ogawa H, Kodera M, Tomioka S, et al., 2014. Multi-phase trajectory optimisation for access-to-space with RBCC-powered TSTO via surrogated-assisted hybrid evolutionary algorithms incorporating pseudo-spectral methods. Proceedings of the 19th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, Article No. 2360.

[51]Oike M, Kamijo K, Tanaka D, et al., 1999. LACE for rocket-based combined-cycle. Proceedings of the 37th Aerospace Sciences Meeting and Exhibit.

[52]Olds JR, 1996. Options for flight testing rocket-based combined-cycle (RBCC) engines. Proceedings of the 32nd Joint Propulsion Conference and Exhibit, p.693-700.

[53]Olds JR, Lee H, 1996. Application of a new economic analysis tool to a two-stage-to-orbit RBCC launch vehicle design. Proceedings of the 6th Symposium on Multidisciplinary Analysis and Optimization.

[54]Olds JR, Bradford JE, 1997. SCCREAM (simulated combined-cycle rocket engine analysis module):a conceptual RBCC engine design tool. Proceedings of the 33rd Joint Propulsion Conference and Exhibit.

[55]Pastrone D, Sentinella MR, 2008. Evolutionary algorithm based approach for RBCC engines optimization. Proceedings of the 44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit.

[56]Pastrone D, Sentinella MR, 2009. Multi-objective optimization of rocket-based combined-cycle engine performance using a hybrid evolutionary algorithm. Journal of Propulsion and Power, 25(5):1140-1145.

[57]Peebles C, 2008. Road to Mach 10: Lessons Learned from the X-43a Flight Research Program. American Institute of Aeronautics and Astronautics, Inc., Reston, USA.

[58]Perkins HD, Thomas SR, Pack WD, et al., 1997. Mach 5 to 7 RBCC propulsion system testing at NASA-LeRC HFT. Proceedings of the 35th Aerospace Sciences Meeting and Exhibit, Article No. 3472.

[59]Perkins HD, Thomas SR, DeBonis JR, 1998. Rocket-based combined cycle propulsion system testing. Journal of Propulsion and Power, 14(6):1065-1067.

[60]Quinn JE, 2002. Oxidizer selection for the ISTAR program (liquid oxygen versus hydrogen peroxide). Proceedings of the 38th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Article No. 4206.

[61]Quinn JE, 2003. ISTAR: project status and ground test engine design. Proceedings of the 39th AIAA/ASME/SAE/ ASEE Joint Propulsion Conference and Exhibit, Article No. 5235.

[62]Riva G, Reggiori A, Daminelli G, 2007. Hypersonic inlet studies for a small scale rocket-based combined-cycle engine. Journal of Propulsion and Power, 23(6):1160-1167.

[63]Shayler DJ, 2017. Linking the Space Shuttle and Space Stations: Early Docking Technologies from Concept to Implementation. Springer, Cham, Germany, p.1-9.

[64]Shi L, He GQ, Qin F, et al., 2013. Numerical investigation of effects of boundary layer bleed on a RBCC inlet in ejector mode. Proceedings of the 49th AIAA/ASME/SAE/ASEE Joint Propulsion Conference.

[65]Shi L, He GQ, Liu PJ, et al., 2016. A rocket-based combined-cycle engine prototype demonstrating comprehensive component compatibility and effective mode transition. Acta Astronautica, 128:350-362.

[66]Shi L, He GQ, Qin F, et al., 2018. Rocket-based combined-cycle inlet researches in northwestern polytechnical university. Proceedings of the 9th International Conference on Mechanical and Aerospace Engineering, p.151-156.

[67]Siebenhaar A, Bulman MJ, Sasso SE, et al., 1994. Strutjet-powered Reusable Launch Vehicles. SEE, Pennsylvania State University, NASA Propulsion Engineering Research Center, USA, p.122-134. https://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19950002765.pdf

[68]Steffen JrCJ, Smith TD, Yungster S, et al., 1997. Rocket based combined-cycle analysis using NPARC. Proceedings of the 36th AIAA Aerospace Sciences Meeting and Exhibit, Article No. 954.

[69]Stemler JN, Bogar TJ, Farrell DJ, et al., 1999. Assessment of RBCC-powered VTHL SSTO vehicles. Proceedings of the 9th International Space Planes and Hypersonic Systems and Technologies Conference.

[70]Sziroczak D, Smith H, 2016. A review of design issues specific to hypersonic flight vehicles. Progress in Aerospace Sciences, 84:1-28.

[71]Takegoshi M, Tomioka S, Ueda S, et al., 2005. Firing-tests of a rocket combustor for combined cycle engine at various conditions. Proceedings of the 41st AIAA/ASME/SAE/ ASEE Joint Propulsion Conference and Exhibit.

[72]Takegoshi M, Tomioka S, Ueda S, et al., 2006. Performances of a rocket chamber for the combined-cycle engine at various conditions. Proceedings of the 14th AIAA/AHI Space Planes and Hypersonic Systems and Technologies Conference.

[73]Takegoshi M, Tomioka S, Ono F, et al., 2012. Injectors and combustion performance of rocket thruster for rocket-ramjet combined-cycle engine model. Proceedings of the 18th AIAA/3AF International Space Planes and Hypersonic Systems and Technologies Conference.

[74]Thomas SR, Perkins HD, Trefny CJ, 1997. Evaluation of an ejector ramjet based propulsion system for air-breathing hypersonic flight. 89th Symposium Sponsored by Propulsion and Energetics Panel of NATO Advisory Geoup for Aerospace Research and Development.

[75]Thomas SR, Palac DT, Trefny CJ, et al., 2001. Performance evaluation of the NASA GTX RBCC flowpath. Proceedings of the 15th International Symposium on Airbreathing Engines.

[76]Trefny CJ, Roche JM, 2002. Performance validation approach for the GTX air-breathing launch vehicle. Proceedings of the Combustion, Airbreathing Propulsion, Propulsion Systems Hazards, and Modelling and Simulation Subcommittees Joint Meeting.

[77]Wang HQ, He GQ, Liu PJ, 2007. Heat transfer analysis and thermal structure design of RBCC engines. Proceedings of the 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit.

[78]Wang HX, Yang QC, Xu X, 2017. Effect of thermal choking on ejection process in a rocket-based combined cycle engine. Applied Thermal Engineering, 116:197-204.

[79]Waung TS, 2010. An Ejector Air Intake Design Method for a Novel Rocket-based Combined-cycle Rocket Nozzle. MS Thesis, Carleton University, Ottawa, Ontario, Canada.

[80]Waung TS, Etele J, 2009. An ejector air intake design method for a novel RBCC rocket nozzle. Proceedings of the 45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit.

[81]Wei XG, Xue R, Qin F, et al., 2017. Research on shock wave characteristics in the isolator of central strut rocket-based combined cycle engine under Ma5.5. Acta Astronautica, 140:284-292.

[82]Williams NJ, 2010. A Performance Analysis of a Rocket Based Combined Cycle (RBCC) Propulsion System for Single-Stage-To-Orbit Vehicle Applications. MS Thesis, University of Tennessee, Knoxville, USA.

[83]Wood D, 2009. Investigations of an Innovative Combined Cycle Nozzle. MS Thesis, The University of Alabama, Huntsville, Alabama, USA.

[84]Wood D, 2013. Preliminary analysis of the rocket plug nozzle combined cycle (RPNCC) propulsion system. Proceedings of the 47th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition.

[85]Xue E, Hu CB, Lv X, et al., 2013. RBCC constant dynamic pressure booster trajectory design and propellant mass flowrate analysis for TSTO transportation system. Journal of Solid Rocket Technology, 36(2):155-160 (in Chinese).

[86]Xue R, He GQ, Wei XG, et al., 2017. Experimental study on combustion modes of a liquid kerosene fueled RBCC combustor. Fuel, 197:433-444.

[87]Yan DK, He GQ, Qin F, et al., 2018. Effect of the heat release on the component coordination in the rocket-based combined cycle engine. Acta Astronautica, 151:942-952.

[88]Yan L, Huang W, Zhang TT, et al., 2014. Numerical investigation of the nonreacting and reacting flow fields in a transverse gaseous injection channel with different species. Acta Astronautica, 105(1):17-23.

[89]Yang QC, Shi W, Chang JT, et al., 2015. Maximum thrust for the rocket-ejector mode of the hydrogen fueled rocket-based combined cycle engine. International Journal of Hydrogen Energy, 40(9):3771-3776.

[90]Ye JY, Pan HL, Qin F, et al., 2018. Investigation of RBCC performance improvements based on a variable geometry ramjet combustor. Acta Astronautica, 151:874-885.

[91]Yuen T, Etele J, 2011. Exchange inlet design for enhanced RBCC rocket-air mixing. Proceedings of the 47th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit.

[92]Yuen TSC, 2012. Simulation of a Rocket Base Combined Cycle Exchange Inlet at Subsonic Conditions. MS Thesis, Carleton University, Ottawa, Ontario, Canada.

[93]Yungster S, Trefny CJ, 1999. Analysis of a new rocket-based combined-cycle engine concept at low speed. Proceedings of the 35th Joint Propulsion Conference and Exhibit, Article No. 2393.

[94]Zhan H, Sun DC, Deng YP, 2008. Study on dynamic system scheme of launch vehicle based on RBCC. Journal of Solid Rocket Technology, 31(4):354-357 (in Chinese).

[95]Zhang CL, Chang JT, Zhang JL, et al., 2018a. Effect of continuous Mach number variation of incoming flow on ram–scram transition in a dual-mode combustor. Aerospace Science and Technology, 76:433-441.

[96]Zhang CL, Chang JT, Feng S, et al., 2018b. Investigation of performance and mode transition in a variable divergence ratio dual-mode combustor. Aerospace Science and Technology, 80:496-507.

[97]Zhang F, Zhang HQ, Wang B, 2016. Feasibility study of a DRBCC-powered single-stage-to-orbit launch vehicle. Proceedings of the 52nd AIAA/SAE/ASEE Joint Propulsion Conference.

[98]Zhang F, Zhang HQ, Wang B, 2018. Conceptual study of a dual-rocket-based-combined-cycle powered two-stage- to-orbit launch vehicle. Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, 232(5):944-957.

[99]Zhang JQ, Wang ZG, Li QL, 2017. Thermodynamic efficiency analysis and cycle optimization of deeply precooled combined cycle engine in the air-breathing mode. Acta Astronautica, 138:394-406.

[100]Zhang M, He GQ, Liu PJ, 2013. Performance improved by multistage rockets ejection in RBCC engine. Proceedings of the 44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit.

[101]Zhang Q, Wang B, Zhang G, et al., 2014. An analysis of RBCC realizability scheme: DRBCC. Rocket Propulsion, 40(5):1-7 (in Chinese).

[102]Zhang TT, Wang ZG, Huang W, et al., 2017. A design approach of wide-speed-range vehicles based on the cone-derived theory. Aerospace Science and Technology, 71: 42-51.

[103]Zhang ZZ, Liu PJ, Qin F, et al., 2018. Numerical and experimental investigation on the influence of inlet contraction ratio for a rocket-based combined cycle engine. Acta Astronautica, 149:1-10.

[104]Zhao ZT, Huang W, Li SB, et al., 2018a. Variable Mach number design approach for a parallel waverider with a wide-speed range based on the osculating cone theory. Acta Astronautica, 147:163-174.

[105]Zhao ZT, Huang W, Yan BB, et al., 2018b. Design and high speed aerodynamic performance analysis of vortex lift waverider with a wide-speed range. Acta Astronautica, 151:848-863.

[106]Zhong Y, Liu D, Wang C, 2018. Research progress of key technologies for typical reusable launcher vehicles. IOP Conference Series: Materials Science and Engineering, 449:012008.