Nozzle flow computation of classical hybrid rocket motors

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

Nozzle flow computation of classical hybrid rocket motors

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

2 引用（Scopus）

摘要

Numerical solutions of full Navier-Stokes equations with chemical reaction flow were established for the nozzle flow of the LOX/HTPB hybrid rocket motor. Lower-Upper decomposition scheme and MUSCL-type and VanLeer approach were used. A chemical reaction model with 8 components and 10 elementary reactions was presented. The nozzle entrance condition was obtained by thermodynamic calculation. The nozzle flows under several different oxidizer mass flow rates and grain length were calculated. The relationship between oxidizer mass flow rate and specific impulse was analyzed, which will be useful for the hybrid rocket motor design.

源语言	英语
页（从-至）	142-146
页数	5
期刊	Hangkong Dongli Xuebao/Journal of Aerospace Power
卷	20
期	1
出版状态	已出版 - 2月 2005

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title = "Nozzle flow computation of classical hybrid rocket motors",

abstract = "Numerical solutions of full Navier-Stokes equations with chemical reaction flow were established for the nozzle flow of the LOX/HTPB hybrid rocket motor. Lower-Upper decomposition scheme and MUSCL-type and VanLeer approach were used. A chemical reaction model with 8 components and 10 elementary reactions was presented. The nozzle entrance condition was obtained by thermodynamic calculation. The nozzle flows under several different oxidizer mass flow rates and grain length were calculated. The relationship between oxidizer mass flow rate and specific impulse was analyzed, which will be useful for the hybrid rocket motor design.",

keywords = "Aerospace propulsion system, Hybrid propellant rockets, Nozzle flow, Performance calculation, Rate of combustion, Thermodynamic calculations",

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

year = "2005",

month = feb,

language = "英语",

volume = "20",

pages = "142--146",

journal = "Hangkong Dongli Xuebao/Journal of Aerospace Power",

issn = "1000-8055",

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TY - JOUR

T1 - Nozzle flow computation of classical hybrid rocket motors

AU - Tian, Hui

AU - Cai, Guo Biao

AU - Wang, Hui Yu

AU - Zhang, Zhen Peng

PY - 2005/2

Y1 - 2005/2

N2 - Numerical solutions of full Navier-Stokes equations with chemical reaction flow were established for the nozzle flow of the LOX/HTPB hybrid rocket motor. Lower-Upper decomposition scheme and MUSCL-type and VanLeer approach were used. A chemical reaction model with 8 components and 10 elementary reactions was presented. The nozzle entrance condition was obtained by thermodynamic calculation. The nozzle flows under several different oxidizer mass flow rates and grain length were calculated. The relationship between oxidizer mass flow rate and specific impulse was analyzed, which will be useful for the hybrid rocket motor design.

AB - Numerical solutions of full Navier-Stokes equations with chemical reaction flow were established for the nozzle flow of the LOX/HTPB hybrid rocket motor. Lower-Upper decomposition scheme and MUSCL-type and VanLeer approach were used. A chemical reaction model with 8 components and 10 elementary reactions was presented. The nozzle entrance condition was obtained by thermodynamic calculation. The nozzle flows under several different oxidizer mass flow rates and grain length were calculated. The relationship between oxidizer mass flow rate and specific impulse was analyzed, which will be useful for the hybrid rocket motor design.

KW - Aerospace propulsion system

KW - Hybrid propellant rockets

KW - Nozzle flow

KW - Performance calculation

KW - Rate of combustion

KW - Thermodynamic calculations

UR - https://www.scopus.com/pages/publications/14844347871

M3 - 文章

AN - SCOPUS:14844347871

SN - 1000-8055

VL - 20

SP - 142

EP - 146

JO - Hangkong Dongli Xuebao/Journal of Aerospace Power

JF - Hangkong Dongli Xuebao/Journal of Aerospace Power

IS - 1

ER -

Nozzle flow computation of classical hybrid rocket motors

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