Full Text:   <2739>

Summary:  <1858>

CLC number: V43

On-line Access: 2017-01-24

Received: 2016-07-04

Revision Accepted: 2016-08-22

Crosschecked: 2017-01-05

Cited: 0

Clicked: 4059

Citations:  Bibtex RefMan EndNote GB/T7714


Zhong Lv


Zhi-xun Xia


-   Go to

Article info.
Open peer comments

Journal of Zhejiang University SCIENCE A 2017 Vol.18 No.2 P.106-112


Preliminary experimental study on solid-fuel rocket scramjet combustor

Author(s):  Zhong Lv, Zhi-xun Xia, Bing Liu, Li-ya Huang

Affiliation(s):  Science and Technology on Scramjet Laboratory, National University of Defense Technology, Changsha 410073, China

Corresponding email(s):   zxxia@nudt.edu.cn

Key Words:  Solid fuel, Rocket scramjet, Dual combustor, Direct-connect experiment

Zhong Lv, Zhi-xun Xia, Bing Liu, Li-ya Huang. Preliminary experimental study on solid-fuel rocket scramjet combustor[J]. Journal of Zhejiang University Science A, 2017, 18(2): 106-112.

@article{title="Preliminary experimental study on solid-fuel rocket scramjet combustor",
author="Zhong Lv, Zhi-xun Xia, Bing Liu, Li-ya Huang",
journal="Journal of Zhejiang University Science A",
publisher="Zhejiang University Press & Springer",

%0 Journal Article
%T Preliminary experimental study on solid-fuel rocket scramjet combustor
%A Zhong Lv
%A Zhi-xun Xia
%A Bing Liu
%A Li-ya Huang
%J Journal of Zhejiang University SCIENCE A
%V 18
%N 2
%P 106-112
%@ 1673-565X
%D 2017
%I Zhejiang University Press & Springer
%DOI 10.1631/jzus.A1600489

T1 - Preliminary experimental study on solid-fuel rocket scramjet combustor
A1 - Zhong Lv
A1 - Zhi-xun Xia
A1 - Bing Liu
A1 - Li-ya Huang
J0 - Journal of Zhejiang University Science A
VL - 18
IS - 2
SP - 106
EP - 112
%@ 1673-565X
Y1 - 2017
PB - Zhejiang University Press & Springer
ER -
DOI - 10.1631/jzus.A1600489

Liquid or gaseous fuel scramjet technology has made great progress, and there has been some research attention to solid-fuel scramjet. A new scramjet configuration using solid fuel as propellant, namely solid-fuel rocket scramjet, is tested experimentally. It consists of two combustors. One is a rocket combustor used as gas generator, and the other is a supersonic combustor used for secondary combustion. The experiment simulates a flight Mach number of 4 at high altitude (stagnation temperature and pressure are 1170 K and 1.16 MPa, respectively), and metalized solid fuel is used as propellant. The results reveal that fuel-rich gas from the gas generator can burn with air in the supersonic combustor. Preliminary evaluation results show that the combustion efficiency of the propellant is about 90%, and the total pressure recovery coefficient in the supersonic combustor is about 0.6. These results indicate that the configuration of solid-fuel rocket scramjet is feasible.


创新点: 1. 提出固体火箭超燃冲压发动机构型方案,并开展固体火箭超燃冲压发动机燃烧室直连式实验研究;2. 验证了固体火箭超燃冲压发动机构型可行;3. 初步评估了固体火箭超燃冲压发动机燃烧室的工作性能。
方法:1. 通过直连式实验测定固体火箭超燃冲压发动机燃烧室的工作参数(图2、3和4);2. 通过实验现象(图8)和数据处理,确定燃气发生器产生的富燃燃气可以在超声速燃烧室中燃烧,进而确定固体火箭超燃冲压发动机方案的可行性;3. 初步确定发动机燃烧室的工作性能(公式(6)和(7))。
结论: 1. 燃气发生器中产生的富燃燃气可以在超声速燃烧室中燃烧,固体火箭超燃冲压发动机构型方案可行;2. 初步评估了固体火箭超燃冲压发动机燃烧室的工作性能,总压恢复系数约为0.6,燃烧效率约为90%;3.燃气发生器产生的部分一次燃气沉积于燃气发生器喉部,使燃气发生器的工作压力增加,进而引起富燃燃气质量流量的增加;4. 燃烧室中的总压损失主要集中在富燃燃气入口处,总压损失主要由射流引起的激波和燃气二次燃烧引起。


Darkslateblue:Affiliate; Royal Blue:Author; Turquoise:Article


[1]Angus, W.J., 1991. An Investigation into the Performance Characteristics of a Solid Fuel Scramjet Propulsion Device. MS Thesis, Naval Postgraduate School, Monterey, USA.

[2]Bao, W., Yang, Q.C., Chang, J.T., et al., 2013. Dynamic characteristics of combustion mode transitions in a strut-based scramjet combustor model. Journal of Propulsion and Power, 29(5):1244-1248.

[3]Ben-Yakar, A., Natan, B., Gany, A., 1998. Investigation of a solid fuel scramjet combustor. Journal of Propulsion and Power, 14(4):447-455.

[4]Brieschenk, S., O’Byrne, S., Kleine, H., 2013. Laser-induced plasma ignition studies in a model scramjet engine. Combustion and Flame, 160(1):145-148.

[5]Curran, E.T., Murthy, S.N.B., 2000. Scramjet Propulsion. The American Institute of Aeronautics and Astronautics, Reston, USA, p.588-593.

[6]Fry, R.S., 2004. A century of ramjet propulsion technology evolution. Journal of Propulsion and Power, 20(1):27-58.

[7]Glagolev, A.I., Zubkov, A.I., Panov, Y.A., 1967. Supersonic flow past a gas jet obstacle emerging from a plate. Fluid Dynamics, 2(3):60-64.

[8]Glagolev, A.I., Zubkov, A.I., Panov, Y.A., 1968. Interaction between a supersonic flow and gas issuing from a hole in a plane. Fluid Dynamics, 3(2):99-103.

[9]Gordon, S., McBride, B.J., 1994. Computer Program for Calculation of Complex Chemical Equilibrium Compositions and Applications, I. Analysis. NASA Reference Publication, USA.

[10]Huang, W., 2014. Design exploration of three-dimensional transverse jet in a supersonic crossflow based on data mining and multi-objective design optimization approaches. International Journal of Hydrogen Energy, 39(8):3914-3925.

[11]Huang, W., 2015. A survey of drag and heat reduction in supersonic flows by a counterflowing jet and its combinations. Journal of Zhejiang University-SCIENCE A (Applied Physics & Engineering), 16(7):551-561.

[12]Huang, W., Yan, L., 2013. Progress in research on mixing techniques for transverse injection flow fields in supersonic crossflows. Journal of Zhejiang University-SCIENCE A (Applied Physics & Engineering), 14(8):554-564.

[13]Huang, W., Li, M.H., Ding, F., et al., 2016. Supersonic mixing augmentation mechanism induced by a wall-mounted cavity configuration. Journal of Zhejiang University-SCIENCE A (Applied Physics & Engineering), 17(1):45-53.

[14]Li, J.P., Song, W.Y., Xing, Y., et al., 2008. Influences of geometric parameters upon nozzle performances in scramjets. Chinese Journal of Aeronautics, 21(6):506-511.

[15]Miller, W., McClendon, S., Burkes, W., 1981. Design approaches for variable flow ducted rockets. 17th Joint Propulsion Conference, Colorado Springs, USA.

[16]Saraf, S., Gany, A., 2007. Testing metalized solid fuel scramjet combustor. 18th International Symposium on Air Breathing Engines, p.1176-1187.

[17]van Driest, E.R., 2003. Turbulent boundary layer in compressible fluid. Journal of Spacecraft and Rockets, 40(6):1012-1028.

[18]Wang, L.H., Wu, Z.W., Chi, H.W., et al., 2015. Numerical and experimental study on the solid-fuel scramjet combustor. Journal of Propulsion and Power, 31(2):685-693.

[19]Wang, Z.G., Wang, H.B., Sun, M.B., 2014. Review of cavity-stabilized combustion for scramjet applications. Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, 228(14):2718-2735.

[20]Witt, M.A., 1989. Investigation into the Feasibility of Using Solid Fuel Ramjets for High Supersonic Low Hypersonic Tactical Missiles. MS Thesis, Naval Postgraduate School, Monterey, USA.

[21]Yi, S.H., Chen, Z., 2015. Review of recent experimental studies of the shock train low field in the isolator. Acta Physica Sinica, 64(19):0199401 (in Chinese).

[22]Yu, G., Li, J.G., Zhao, J.R., et al., 1998. Hydrogen-air supersonic combustion study by strut injectors. 34th AIAA/ ASME/SAE/ASEE Joint Propulsion Conference and Exhibit.

Open peer comments: Debate/Discuss/Question/Opinion


Please provide your name, email address and a comment

Journal of Zhejiang University-SCIENCE, 38 Zheda Road, Hangzhou 310027, China
Tel: +86-571-87952783; E-mail: cjzhang@zju.edu.cn
Copyright © 2000 - 2024 Journal of Zhejiang University-SCIENCE