固体火箭超燃冲压发动机理论性能分析

doi:10.7527/S1000-6893.2022.26971

Abstract

Abstract:

Considering the dissociation of combustion products， this paper conducts research on modeling of the working process of the solid rocket scramjet using the Brayton cycle method. Then， the theoretical performance of the engine is analyzed， and the effects of flight parameters and fuel types on engine performance are studied. The flight envelope of scramjet engine is also discussed. The main conclusions are as follows. The performance of solid rocket scramjet decreases with the increase of flight Mach number and flight altitude. When the working equivalent ratio increases， the gravimetric impulse and volumetric impulse decrease， but the specific thrust increases gradually. When the working air-fuel ratio increases， the specific thrust decreases， but the gravimetric impulse and volumetric impulse increase gradually. In the range of air-fuel ratio from 5 to 27， the volumetric impulse of the engine fueled with solid propellant has obvious advantages， but the specific thrust and gravimetric impulse are inferior to the engine fueled with hydrogen and kerosene. Compared with that fueled with hydrogen and kerosene， the boron-based solid propellant scramjet can work in a wider range of Mach numbers， which indicates that the solid rocket scramjet has a potential of wide flight envelope.

Key words: solid rocket scramjet, high Mach number, dissociation, engine performance, solid propellant

CLC Number:

V435

Xiang ZHAO, Zhixun XIA, Chuanbo FANG, Likun MA, Chaolong LI, Yifan DUAN. Theoretical analysis of performance of solid rocket scramjet[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023, 44(5): 126971.

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References 37

1	ZHAO X， XIA Z X， MA L K， et al. Research progress on solid-fueled scramjet［J］. Chinese Journal of Aeronautics， 2022， 35（1）： 398-415.
2	李潮隆，夏智勋，马立坤，等. 固体火箭超燃冲压发动机性能试验［J］. 航空学报， 2022， 43（12）： 126075.
	LI C L， XIA Z X， MA L K， et al. Experiment on performance of solid rocket scramjet［J］. Acta Aeronautica et Astronautica Sinica， 2022， 43（12）： 126075 （in Chinese）.
3	赵翔，夏智勋，马立坤，等. 固体火箭超燃冲压发动机地面直连试验［J］. 航空兵器， 2018， 25（4）： 57-61.
	ZHAO X， XIA Z X， MA L K， et al. Direct-connected ground test of solid-fuel rocket scramjet［J］. Aero Weaponry， 2018， 25（4）： 57-61 （in Chinese）.
4	LI C L， ZHAO X， XIA Z X， et al. Influence of the vortex generator on the performance of solid rocket scramjet combustor［J］. Acta Astronautica， 2019， 164： 174-183.
5	YANG P N， XIA Z X， MA L K， et al. Experimental study on the influence of the injection structure on solid scramjet performance［J］. Acta Astronautica， 2021， 188： 229-238.
6	LV Z， XIA Z X， LIU B， et al. Experimental and numerical investigation of a solid-fuel rocket scramjet combustor［J］. Journal of Propulsion and Power， 2015， 32（2）： 273-278.
7	LI C L， XIA Z X， MA L K， et al. Performance evaluation for scramjet based on ground direct-connected test： A method investigation［J］. Aerospace Science and Technology， 2021， 117： 106895.
8	LIU J， WANG N f， WANG J， et al. Optimizing combustion performance in a solid rocket scramjet engine［J］. Aerospace Science and Technology， 2020， 99： 105560.
9	LI C L， XIA Z X， MA L K， et al. Numerical study on the solid fuel rocket scramjet combustor with cavity［J］. Energies， 2019， 12（7）： 1235.
10	HEISER W， PRATT D， DALEY D， et al. Hypersonic airbreathing propulsion［M］. Reston： AIAA， 1994.
11	王超. 超燃冲压发动机总体方案设计与优化研究［D］. 长沙：国防科技大学， 2011.
	WANG C. Design and optimization research on scramjet system scheme［D］. Changsha： National University of Defense Technology， 2011 （in Chinese）.
12	ROUX J A. Optimum freestream Mach number for maximum thrust flux for ideal ramjet/scramjet［J］. Journal of Thermophysics and Heat Transfer， 2012， 26（2）： 390-392.
13	ROUX J A. Parametric ideal scramjet cycle analysis［J］. Journal of Thermophysics and Heat Transfer， 2011， 25（4）： 581-585.
14	ROUX J A， SHAKYA N， CHOI J. Revised parametric ideal scramjet cycle analysis［J］. Journal of Thermophysics and Heat Transfer， 2013， 27（1）： 178-183.
15	YANG Q C， CHANG J T， BAO W. Thermodynamic analysis on specific thrust of the hydrocarbon fueled scramjet［J］. Energy， 2014， 76： 552-558.
16	ZHANG D， YANG S B， ZHANG S L， et al. Thermodynamic analysis on optimum performance of scramjet engine at high Mach numbers［J］. Energy， 2015， 90： 1046-1054.
17	ROUDAKOV A S， SEMENOV V L， HICKS J W. Recent flight test results of the joint CIAM-NASA Mach 6.5 scramjet flight program： AIAA-1998-1643［R］. Reston： AIAA， 1998.
18	SMART M K， HASS N E， PAULL A. Flight data analysis of the HyShot 2 scramjet flight experiment［J］. AIAA Journal， 2006， 44（10）： 2366-2375.
19	RONDEAU C M， JORRIS T R. X-51A scramjet demonstrator program： Waverider ground and flight test［R］. 2013.
20	PECNIK R， TERRAPON V E， HAM F， et al. Reynolds-averaged Navier-Stokes simulations of the HyShot II scramjet［J］. AIAA Journal， 2012， 50（8）： 1717-1732.
21	CHAPUIS M， FEDINA E， FUREBY C， et al. A computational study of the HyShot II combustor performance［J］. Proceedings of the Combustion Institute， 2013， 34（2）： 2101-2109.
22	FRY R S. A century of ramjet propulsion technology evolution［J］. Journal of Propulsion and Power， 2004， 20（1）： 27-58.
23	曾明，刘伟，邹建军. 空气动力学基础［M］. 北京：科学出版社， 2016.
	ZENG M， LIU W， ZOU J J. Aerodynamics fundamentals［M］. Beijing： Science Press， 2016 （in Chinese）.
24	WALTRUP P J， BILLIG F S. Structure of shock waves in cylindrical ducts［J］. AIAA Journal， 1973， 11（10）： 1404-1408.
25	SCHLICHTING H. Boundary-layer theory［M］. New York： McGraw-Hill Book Company， 1979.
26	ZHAO X， XIA Z X， LIU B， et al. Numerical study on solid-fuel scramjet combustor with fuel-rich hot gas［J］. Aerospace Science and Technology， 2018， 77： 25-33.
27	OU M， YAN L， TANG J f， et al. Thermodynamic performance analysis of ramjet engine at wide working conditions［J］. Acta Astronautica， 2017， 132： 1-12.
28	SULAIMAN A N B. Thermodynamic analysis of gas turbine［D］. Tronoh： University Teknologi Petronas， 2012.
29	LARSSON J， LAURENCE S， BERMEJO-MORENO I， et al. Incipient thermal choking and stable shock-train formation in the heat-release region of a scramjet combustor. Part II： Large eddy simulations［J］. Combustion and Flame， 2015， 162（4）： 907-920.
30	LAURENCE S J， LIEBER D， SCHRAMM J M， et al. Incipient thermal choking and stable shock-train formation in the heat-release region of a scramjet combustor. Part I： Shock-tunnel experiments［J］. Combustion and Flame， 2015， 162（4）： 921-931.
31	BOLENDER M A， DOMAN D B. Nonlinear longitudinal dynamical model of an air-breathing hypersonic vehicle［J］. Journal of Spacecraft and Rockets， 2007， 44（2）： 374-387.
32	Cantera. Cantera is an open-source suite of tools for problems involving chemical kinetics， thermodynamics， and transport processes［EB/OL］.［2022-02-24］. .
33	SCHRAMM J M， KARL S， HANNEMANN K， et al. Ground testing of the HyShot II scramjet configuration in HEG： AIAA-2008-2547［R］. Reston： AIAA， 2008.
34	NORDIN-BATES K， FUREBY C， KARL S， et al. Understanding scramjet combustion using LES of the HyShot II combustor［J］. Proceedings of the Combustion Institute， 2017， 36（2）： 2893-2900.
35	MCCLENDON S E， MILLER W H， HERTY C H. Fuel selection criteria for ducted rocket application： AIAA-1980-1120［R］. Reston： AIAA， 1980.
36	KUBOTA N， MIYATA K， KUWAHARA T， et al. Energetic solid fuels for ducted rockets （III）［J］. Propellants， Explosives， Pyrotechnics， 1992， 17（6）： 303-306.
37	陈斌斌. 含硼固冲补燃室燃烧过程与燃烧组织技术研究［D］. 长沙：国防科技大学， 2018.
	CHEN B B. Research on the combustion process and combustion technology of boron-based solid ducted rockets［D］. Changsha： National University of Defense Technology， 2018 （in Chinese）.

燃烧室处理方法	不考虑离解	化学平衡
来流静温/K	226.65	226.65
隔离段出口静温/K	1 511.2	1 511.2
燃烧室静温/K	2 651.7	2 429.0
来流总温/K	3 124.9	3 124.9
燃烧室总温/K	4 265.4	3 557.7

数据来源	获取方式	P₃/kPa	P₄/kPa
文献［21］	飞行试验测量	≈57	57~120
计算	等压燃烧	57	57
计算	气流速度恒定	57	85

试验	工况	数据来源	P₃/kPa	U₃/（m·s^-1）	T₃/K	Ma₄	P₄/kPa
飞行试验	H=32.5 km， Ma=7.7	文献［21］	≈57	≈1 800	≈1 500		57~120
	H=32.5 km， Ma=7.7	计算	57	1 718	1 423	1.73	85
	H=27.1 km， Ma=7.8	文献［21］	≈130	≈1 720	≈1 300
	H=27.1 km， Ma=7.8	计算	140	1 685	1 444	1.74	194
HEG XII	H=33.0 km， Ma=7.3	文献［21］	57	1 800	1 500	1.0~2.3	57~145
HEG XII	H=33.0 km， Ma=7.3	计算	47	1 632	1 313	1.63	76
HEG XIII	H=28.0 km， Ma=7.4	文献［21］	130	1 720	1 300	1.65~2.30	130~280
HEG XIII	H=28.0 km， Ma=7.4	计算	106	1 606	1 327	1.70	152

A/F	摩尔占比
A/F	CO	CO₂	H	H₂	H₂O	NO	N₂	O	OH	O₂
5	0.26	0	0	0.25	0	0	0.49	0	0	0
10	0.12	0.06	0	0.04	0.12	0	0.66	0	0	0
15	0.03	0.10	0	0	0.11	0.01	0.72	0	0.01	0.02

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Theoretical analysis of performance of solid rocket scramjet

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