Theoretical performance analysis of Mg/CO2 powdered rocket engine

Fang Li; Chun Bo Hu; Guo Qiang He

Theoretical performance analysis of Mg/CO₂ powdered rocket engine

Fang Li
, Chun Bo Hu
, Guo Qiang He

School of Astronautics

Northwestern Polytechnical University Xian

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

2 Scopus citations

Abstract

The theoretical performance of the powdered rocket engine is calculated theoretically in considering the specific impulse and the impact of factors. Compared with the traditional propulsion system, the powdered rocket engine has better specific impulse. In the calculation research of the performance of Mg and CO₂, the rules of burning pressure, starting temperature and oxidizer-to-fuel ratio (by mass) were obtained.

Original language	English
Pages (from-to)	414-418
Number of pages	5
Journal	Guti Huojian Jishu/Journal of Solid Rocket Technology
Volume	33
Issue number	4
State	Published - Aug 2010

Keywords

Burning temperature
Oxidizer-to-fuel ratio
Powdered rocket engine
Pressure
Specific impulse

Cite this

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title = "Theoretical performance analysis of Mg/CO2 powdered rocket engine",

abstract = "The theoretical performance of the powdered rocket engine is calculated theoretically in considering the specific impulse and the impact of factors. Compared with the traditional propulsion system, the powdered rocket engine has better specific impulse. In the calculation research of the performance of Mg and CO2, the rules of burning pressure, starting temperature and oxidizer-to-fuel ratio (by mass) were obtained.",

keywords = "Burning temperature, Oxidizer-to-fuel ratio, Powdered rocket engine, Pressure, Specific impulse",

author = "Fang Li and Hu, \{Chun Bo\} and He, \{Guo Qiang\}",

year = "2010",

month = aug,

language = "英语",

volume = "33",

pages = "414--418",

journal = "Guti Huojian Jishu/Journal of Solid Rocket Technology",

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T1 - Theoretical performance analysis of Mg/CO2 powdered rocket engine

AU - Li, Fang

AU - Hu, Chun Bo

AU - He, Guo Qiang

PY - 2010/8

Y1 - 2010/8

N2 - The theoretical performance of the powdered rocket engine is calculated theoretically in considering the specific impulse and the impact of factors. Compared with the traditional propulsion system, the powdered rocket engine has better specific impulse. In the calculation research of the performance of Mg and CO2, the rules of burning pressure, starting temperature and oxidizer-to-fuel ratio (by mass) were obtained.

AB - The theoretical performance of the powdered rocket engine is calculated theoretically in considering the specific impulse and the impact of factors. Compared with the traditional propulsion system, the powdered rocket engine has better specific impulse. In the calculation research of the performance of Mg and CO2, the rules of burning pressure, starting temperature and oxidizer-to-fuel ratio (by mass) were obtained.

KW - Burning temperature

KW - Oxidizer-to-fuel ratio

KW - Powdered rocket engine

KW - Pressure

KW - Specific impulse

UR - https://www.scopus.com/pages/publications/77958087134

M3 - 文章

AN - SCOPUS:77958087134

SN - 1006-2793

VL - 33

SP - 414

EP - 418

JO - Guti Huojian Jishu/Journal of Solid Rocket Technology

JF - Guti Huojian Jishu/Journal of Solid Rocket Technology

IS - 4

ER -

Theoretical performance analysis of Mg/CO₂ powdered rocket engine

Abstract

Keywords

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