高比冲小推力脉冲爆震火箭发动机特性研究#br#

PDF (PC)

Like

Knowledge

Characteristics of Pulse Detonation Rocket Engine with High Specific Impulse and Small Thrust Demand

Abstract

References

Metrics

Abstract

Cite this article

share this article

References

Related Articles 15

Metrics

Comments

Recommended 10

doi:10.3969/j.issn.1674 1579.2022.06.009

Abstract: The problem of continuous thrust orbit transfer has become one of the research hotspots in the aerospace field in recent years.This problem has also promoted the development of high specific impulse and small thrust engines. The pulse detonation engine based on detonation combustion has the characteristics of high thermal efficiency, high specific impulse and simple structure. The related performance research is carried out. First, the mathematical model of the detonation technology is given, and the analysis method of the equal volume cycle model is introduced. Then the numerical results of the CEA model and the simulation results are compared to verify the reliability of the designed detonation model. And different external gas working fluids, nozzle configurations, and respective simulation analysis of engine internal flow field and performance analysis are carried out under 0.1atm, 0.01atm, 0.001atm ambient pressure. The result analysis shows that the pulse detonation engine can meet the requirements of high specific impulse and small thrust, and the convergent expansion nozzle has the greatest gain in engine performance. As the ambient pressure decreases, the engine thrust increases.

Key words: pulse detonation rocket engine, specific impulse, thrust, detonation wave, numerical simulation

CLC Number:

V430

LIU Xiang, NIE Wansheng, ZHANG Haoha, ZHOU Siyin . Characteristics of Pulse Detonation Rocket Engine with High Specific Impulse and Small Thrust Demand[J].Aerospace Contrd and Application, 2022, 48(6): 67-75.

0
/ Save 0 / Recommend

Add to citation manager EndNote|Reference Manager|ProCite|BibTeX|RefWorks

URL: https://journal01.magtech.org.cn/Jwk3_kjkzjs/EN/10.3969/j.issn.1674 1579.2022.06.009

https://journal01.magtech.org.cn/Jwk3_kjkzjs/EN/Y2022/V48/I6/67

Viewed

Full text

From	Others	local

Times	4	55
Rate	7%	93%

Abstract

121

Just accepted	Online first	Issue

0	0	121

	From	Others

	Times	121
	Rate	100%

Cited

Web of Science	Crossref	ScienceDirect	Search for Citations in Google Scholar >>


This page requires you have already subscribed to WoS.

Shared

[1]	WANG Jiqin, LIU Peixu, LIU Wei, GAO Jun, WANG Weizong. Experimental Study of Ablative Z-Pinch Pulsed Plasma Thruster System [J]. Aerospace Contrd and Application, 2024, 50(5): 92-.
[2]	MA Xue, GUO Tingrong, GUO Jianxin, LIU Xiaoxiang. Station-Keeping Scheme of Electric Propulsion Geostationary Spacecraft with Double Robotic Arms [J]. Aerospace Contrd and Application, 2024, 50(5): 69-76.
[3]	LIU Jiang, JIA Yinghong. Integrated Orbit and Attitude Control of Spacecraft with Deviated Centroid and Finite Thrust [J]. Aerospace Contrd and Application, 2024, 50(4): 45-54.
[4]	TU Zihan, MAO Wei, HU Yanlin, YAO Zhaopu. Magnetic Circuit Design Method Based on Size Optimization in Hall Thrusters [J]. Aerospace Contrd and Application, 2024, 50(2): 117-126.
[5]	GENG Jie, WEN Wen, LI Wei, LIU Rui, WANG Yufeng. Dynamic Modeling of All Electric Propulsion Satellite with Thruster Point Assembly Mechanism [J]. Aerospace Contrd and Application, 2024, 50(1): 17-24.
[6]	MA Haochen, SONG Yan, LIU Zexin, LIU Qiang, WANG Shangmin, WEI Liqiu, YU Daren. Modeling and Analysis of Filtering Unit for High Power Hall Thruster [J]. Aerospace Contrd and Application, 2021, 47(4): 109-114.
[7]	ZHANG Wei, WANG Meng, CHEN Yang, FU Tuoqu, LIU Xuhui, YANG Rui, YAO Zhaopu. Experimental Investigation on Transient Startup of ADNBased Thruster [J]. Aerospace Contrd and Application, 2021, 47(4): 63-67.
[8]	LI Jiahui, HAN Yajie, LI Yong, XIA Guangqing, LIU Xuhui, SUN Anbang, SUN Bin, HAN Daoman, LU Chang. Progress of RF Ion Thruster [J]. Aerospace Contrd and Application, 2021, 47(4): 21-30.
[9]	REN Shiyong, YU Yusong, WANG Xudong, CHEN Jun, LIU Xuhui, ZHANG Zhen. Modeling and Operating Characteristics Simulation of Self Pressurized Butane Micro Propulsion System [J]. Aerospace Contrd and Application, 2021, 47(4): 76-84.
[10]	LIU Xuhui, ZHOU Haohao, GENG Jinyue, JIA Hanwu, CHEN Maolin, XIN Youmei. Analysis of Structure Parameters and Beam Extraction Efficiency of Electrospray Thruster [J]. Aerospace Contrd and Application, 2021, 47(4): 68-75.
[11]	LI Zhonglin, ZHOU Cheng, ZHANG Yue, XIA Guangqing, SUN Bin. Development of Electrodeless Lorentz Force Thruster [J]. Aerospace Contrd and Application, 2021, 47(4): 31-40.
[12]	HUANG Wendong, GENG Jinyue, YAN Hao, LIU Xuhui, SUN Surong, WANG Haixing. Review on Ignition and Acceleration Mechanisms in a Micro Cathode Arc Thruster [J]. Aerospace Contrd and Application, 2021, 47(4): 10-20.
[13]	WANG Qun, WU Peiya, CHEN Zhihua, ZHOU Zhongze, LI Guangxu. Mutually Exclusive Design of Control System and Fault Disposal [J]. Aerospace Contrd and Application, 2021, 47(1): 87-92.
[14]	GUO Da-Wei, CHENG Mou-Sen, LI Xiao-Kang, CHE Bi-Xuan. Experiment Validation of a Novel Fast Pulsed Gas Valve for Inductive Pulsed Plasma Thruster [J]. , 2018, 44(3): 50-55.
[15]	LIU Qi, YANG Lei, HUANG Yu-Ping, ZHENG Zai-Ping, ZHAO Xu- . TwoDimensional ParticleinCell Modeling and Numerical Simulation on the Discharge and Ionization of Pulsed Plasma Thruster [J]. , 2018, 44(2): 67-72.

Just accepted

Online first

Just accepted

Online first