Computation of combustion in hybrid rocket motor using a boundary layer theory

Hui Tian; Guo Biao Cai; Hui Yu Wang; Zhen Peng Zhang

Computation of combustion in hybrid rocket motor using a boundary layer theory

Hui Tian^*
, Guo Biao Cai
, Hui Yu Wang
, Zhen Peng Zhang

^*此作品的通讯作者

宇航学院

Beihang University

科研成果: 期刊稿件 › 文章 › 同行评审

5 引用（Scopus）

摘要

A boundary layer numerical solution was used for the computation of combustion in hybrid rocket motor according to the boundary burning theory. Various values of mass transfer number and oxidizer mass flux were considered in the calculation. The regression rate of the solid fuel was formularized based on the calculation. The results show a good agreement with the related references and are useful for the further study.

源语言	英语
页（从-至）	379-382
页数	4
期刊	Tuijin Jishu/Journal of Propulsion Technology
卷	23
期	5
出版状态	已出版 - 10月 2002

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引用此

@article{7327bf4996e245a88ffdacf95dee3b3f,

title = "Computation of combustion in hybrid rocket motor using a boundary layer theory",

abstract = "A boundary layer numerical solution was used for the computation of combustion in hybrid rocket motor according to the boundary burning theory. Various values of mass transfer number and oxidizer mass flux were considered in the calculation. The regression rate of the solid fuel was formularized based on the calculation. The results show a good agreement with the related references and are useful for the further study.",

keywords = "Boundary layer combustion, Hybrid propellant rocket motor, Propellant burning rate, Solid liquid propellant",

author = "Hui Tian and Cai, \{Guo Biao\} and Wang, \{Hui Yu\} and Zhang, \{Zhen Peng\}",

year = "2002",

month = oct,

language = "英语",

volume = "23",

pages = "379--382",

journal = "Tuijin Jishu/Journal of Propulsion Technology",

issn = "1001-4055",

publisher = "China Aerospace Science and Industry Corp",

number = "5",

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TY - JOUR

T1 - Computation of combustion in hybrid rocket motor using a boundary layer theory

AU - Tian, Hui

AU - Cai, Guo Biao

AU - Wang, Hui Yu

AU - Zhang, Zhen Peng

PY - 2002/10

Y1 - 2002/10

N2 - A boundary layer numerical solution was used for the computation of combustion in hybrid rocket motor according to the boundary burning theory. Various values of mass transfer number and oxidizer mass flux were considered in the calculation. The regression rate of the solid fuel was formularized based on the calculation. The results show a good agreement with the related references and are useful for the further study.

AB - A boundary layer numerical solution was used for the computation of combustion in hybrid rocket motor according to the boundary burning theory. Various values of mass transfer number and oxidizer mass flux were considered in the calculation. The regression rate of the solid fuel was formularized based on the calculation. The results show a good agreement with the related references and are useful for the further study.

KW - Boundary layer combustion

KW - Hybrid propellant rocket motor

KW - Propellant burning rate

KW - Solid liquid propellant

UR - https://www.scopus.com/pages/publications/0036819669

M3 - 文章

AN - SCOPUS:0036819669

SN - 1001-4055

VL - 23

SP - 379

EP - 382

JO - Tuijin Jishu/Journal of Propulsion Technology

JF - Tuijin Jishu/Journal of Propulsion Technology

IS - 5

ER -

Computation of combustion in hybrid rocket motor using a boundary layer theory

摘要

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引用此