Study on low burning rate NEPE propellant

X. Li; Y. Liu; W. Yao; H. Tan

Study on low burning rate NEPE propellant

X. Li^*, Y. Liu, W. Yao, H. Tan

^*此作品的通讯作者

材料学院

Beijing Institute of Technology

科研成果: 期刊稿件 › 文章 › 同行评审

5 引用（Scopus）

摘要

A low burning rate NEPE propellant were investigated by means of adding some burning rate inhibitors and adjusting its composition. The compatibility of additives with nitrite ester, combustion properties of the propellant and the standard specific pulse of φ40 rocket motor were measured. It was observed that the burning rate of the propellant could be depressed by more bigger particle diameter AP, low ratio of NG/DEGDN, less AP content and presence of burning rate inhibitors. The burning rate under 4.0MPa could be 4.7mm/s, and standard specific pulse was 2239.3N · s/kg without additives.

源语言	英语
页（从-至）	1-3+9
期刊	Huozhayao Xuebao/Chinese Journal of Explosives and Propellants
卷	24
期	3
出版状态	已出版 - 2001

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title = "Study on low burning rate NEPE propellant",

abstract = "A low burning rate NEPE propellant were investigated by means of adding some burning rate inhibitors and adjusting its composition. The compatibility of additives with nitrite ester, combustion properties of the propellant and the standard specific pulse of φ40 rocket motor were measured. It was observed that the burning rate of the propellant could be depressed by more bigger particle diameter AP, low ratio of NG/DEGDN, less AP content and presence of burning rate inhibitors. The burning rate under 4.0MPa could be 4.7mm/s, and standard specific pulse was 2239.3N · s/kg without additives.",

keywords = "Combustion property, High energy solid propellant, Low burning rate propellant",

author = "X. Li and Y. Liu and W. Yao and H. Tan",

year = "2001",

language = "English",

volume = "24",

pages = "1--3+9",

journal = "Huozhayao Xuebao/Chinese Journal of Explosives and Propellants",

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TY - JOUR

T1 - Study on low burning rate NEPE propellant

AU - Li, X.

AU - Liu, Y.

AU - Yao, W.

AU - Tan, H.

PY - 2001

Y1 - 2001

N2 - A low burning rate NEPE propellant were investigated by means of adding some burning rate inhibitors and adjusting its composition. The compatibility of additives with nitrite ester, combustion properties of the propellant and the standard specific pulse of φ40 rocket motor were measured. It was observed that the burning rate of the propellant could be depressed by more bigger particle diameter AP, low ratio of NG/DEGDN, less AP content and presence of burning rate inhibitors. The burning rate under 4.0MPa could be 4.7mm/s, and standard specific pulse was 2239.3N · s/kg without additives.

AB - A low burning rate NEPE propellant were investigated by means of adding some burning rate inhibitors and adjusting its composition. The compatibility of additives with nitrite ester, combustion properties of the propellant and the standard specific pulse of φ40 rocket motor were measured. It was observed that the burning rate of the propellant could be depressed by more bigger particle diameter AP, low ratio of NG/DEGDN, less AP content and presence of burning rate inhibitors. The burning rate under 4.0MPa could be 4.7mm/s, and standard specific pulse was 2239.3N · s/kg without additives.

KW - Combustion property

KW - High energy solid propellant

KW - Low burning rate propellant

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M3 - Article

AN - SCOPUS:0034959110

SN - 1007-7812

VL - 24

SP - 1-3+9

JO - Huozhayao Xuebao/Chinese Journal of Explosives and Propellants

JF - Huozhayao Xuebao/Chinese Journal of Explosives and Propellants

IS - 3

ER -

Study on low burning rate NEPE propellant

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