Experimental research on propulsive performance of the pulse detonation rocket engine with a fluidic nozzle

Qibin Zhang; Ke Wang; Rongxiao Dong; Wei Fan; Wei Lu; Yongjia Wang

doi:10.1016/j.energy.2018.10.165

Experimental research on propulsive performance of the pulse detonation rocket engine with a fluidic nozzle

Qibin Zhang, Ke Wang, Rongxiao Dong, Wei Fan, Wei Lu, Yongjia Wang

School of Power and Energy

Northwestern Polytechnical University Xian

Research output: Contribution to journal › Article › peer-review

24 Scopus citations

Abstract

To explore an effective way for the nozzle design of a pulse detonation rocket engine (PDRE), theoretical and experimental researches have been carried out. The exhaust process and optimal converging/diverging area ratios of a nozzle were theoretically analyzed. Pressure and velocity fluctuations of the exhaust flow were considered to be the major issues. A fluidic solution which employs nitrogen flows in the nozzle throat and divergent section has been tested. The fluidic nozzle is able to adjust the effective area ratios according to the incoming flow. The effective convergent area ratio varied from 2.0 to 2.2, and the divergent one varied from 5.0 to 1.8. It is proved that the fluidic nozzle effectively improved the propulsive performance of the engine. A maximum average thrust increase of 137.8% was obtained in proper conditions.

Original language	English
Pages (from-to)	1267-1275
Number of pages	9
Journal	Energy
Volume	166
DOIs	https://doi.org/10.1016/j.energy.2018.10.165
State	Published - 1 Jan 2019

Keywords

Detonation
Fluidic injection
Nozzle design
Propulsion

UN SDGs

This output contributes to the following UN Sustainable Development Goals (SDGs)

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10.1016/j.energy.2018.10.165

Cite this

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title = "Experimental research on propulsive performance of the pulse detonation rocket engine with a fluidic nozzle",

abstract = "To explore an effective way for the nozzle design of a pulse detonation rocket engine (PDRE), theoretical and experimental researches have been carried out. The exhaust process and optimal converging/diverging area ratios of a nozzle were theoretically analyzed. Pressure and velocity fluctuations of the exhaust flow were considered to be the major issues. A fluidic solution which employs nitrogen flows in the nozzle throat and divergent section has been tested. The fluidic nozzle is able to adjust the effective area ratios according to the incoming flow. The effective convergent area ratio varied from 2.0 to 2.2, and the divergent one varied from 5.0 to 1.8. It is proved that the fluidic nozzle effectively improved the propulsive performance of the engine. A maximum average thrust increase of 137.8% was obtained in proper conditions.",

keywords = "Detonation, Fluidic injection, Nozzle design, Propulsion",

author = "Qibin Zhang and Ke Wang and Rongxiao Dong and Wei Fan and Wei Lu and Yongjia Wang",

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doi = "10.1016/j.energy.2018.10.165",

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TY - JOUR

T1 - Experimental research on propulsive performance of the pulse detonation rocket engine with a fluidic nozzle

AU - Zhang, Qibin

AU - Wang, Ke

AU - Dong, Rongxiao

AU - Fan, Wei

AU - Lu, Wei

AU - Wang, Yongjia

PY - 2019/1/1

Y1 - 2019/1/1

N2 - To explore an effective way for the nozzle design of a pulse detonation rocket engine (PDRE), theoretical and experimental researches have been carried out. The exhaust process and optimal converging/diverging area ratios of a nozzle were theoretically analyzed. Pressure and velocity fluctuations of the exhaust flow were considered to be the major issues. A fluidic solution which employs nitrogen flows in the nozzle throat and divergent section has been tested. The fluidic nozzle is able to adjust the effective area ratios according to the incoming flow. The effective convergent area ratio varied from 2.0 to 2.2, and the divergent one varied from 5.0 to 1.8. It is proved that the fluidic nozzle effectively improved the propulsive performance of the engine. A maximum average thrust increase of 137.8% was obtained in proper conditions.

AB - To explore an effective way for the nozzle design of a pulse detonation rocket engine (PDRE), theoretical and experimental researches have been carried out. The exhaust process and optimal converging/diverging area ratios of a nozzle were theoretically analyzed. Pressure and velocity fluctuations of the exhaust flow were considered to be the major issues. A fluidic solution which employs nitrogen flows in the nozzle throat and divergent section has been tested. The fluidic nozzle is able to adjust the effective area ratios according to the incoming flow. The effective convergent area ratio varied from 2.0 to 2.2, and the divergent one varied from 5.0 to 1.8. It is proved that the fluidic nozzle effectively improved the propulsive performance of the engine. A maximum average thrust increase of 137.8% was obtained in proper conditions.

KW - Detonation

KW - Fluidic injection

KW - Nozzle design

KW - Propulsion

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U2 - 10.1016/j.energy.2018.10.165

DO - 10.1016/j.energy.2018.10.165

M3 - 文章

AN - SCOPUS:85057173673

SN - 0360-5442

VL - 166

SP - 1267

EP - 1275

JO - Energy

JF - Energy

ER -

Experimental research on propulsive performance of the pulse detonation rocket engine with a fluidic nozzle

Abstract

Keywords

UN SDGs

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