Computation of nozzle flow in a N 2O/HTPB hybrid rocket motor

Hui Tian; Guobiao Cai

Computation of nozzle flow in a N ₂O/HTPB hybrid rocket motor

Hui Tian^*
, Guobiao Cai

^*Corresponding author for this work

School of Astronautics

School of Astronautics

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution › peer-review

Abstract

Propellant performance of N ₂O/HTPB were studied firstly. Vacuum specific impulse is bound up with a oxidizer-to-fuel ratio and expansion ratio. Numerical solutions of full Navier-Stokes equations with chemical reaction flow were obtained for a nozzle flow of the N ₂O/HTPB hybrid rocket motor. Lower-Upper decomposition scheme and MUSCL-type and Van Leer approach were used. A chemical reaction model with 12 species and 16 elementary reactions was presented. The nozzle entrance condition was obtained by thermal calculation. The nozzle flow under optimum oxidizer-to-fuel ratio were calculated. which will be useful for the hybrid rocket motor design.

Original language	English
Title of host publication	Collection of Technical Papers - 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference
Pages	3646-3653
Number of pages	8
State	Published - 2007
Event	43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference - Cincinnati, OH, United States Duration: 8 Jul 2007 → 11 Jul 2007

Publication series

Name	Collection of Technical Papers - 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference
Volume	4

Conference

Conference	43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference
Country/Territory	United States
City	Cincinnati, OH
Period	8/07/07 → 11/07/07

Cite this

@inproceedings{28ef96205334457aaa95a9a21a061066,

title = "Computation of nozzle flow in a N 2O/HTPB hybrid rocket motor",

abstract = "Propellant performance of N 2O/HTPB were studied firstly. Vacuum specific impulse is bound up with a oxidizer-to-fuel ratio and expansion ratio. Numerical solutions of full Navier-Stokes equations with chemical reaction flow were obtained for a nozzle flow of the N 2O/HTPB hybrid rocket motor. Lower-Upper decomposition scheme and MUSCL-type and Van Leer approach were used. A chemical reaction model with 12 species and 16 elementary reactions was presented. The nozzle entrance condition was obtained by thermal calculation. The nozzle flow under optimum oxidizer-to-fuel ratio were calculated. which will be useful for the hybrid rocket motor design.",

author = "Hui Tian and Guobiao Cai",

year = "2007",

language = "英语",

isbn = "1563479036",

series = "Collection of Technical Papers - 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference",

pages = "3646--3653",

booktitle = "Collection of Technical Papers - 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference",

note = "43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference ; Conference date: 08-07-2007 Through 11-07-2007",

}

Tian, H & Cai, G 2007, Computation of nozzle flow in a N ₂O/HTPB hybrid rocket motor. in Collection of Technical Papers - 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference. Collection of Technical Papers - 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference, vol. 4, pp. 3646-3653, 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference, Cincinnati, OH, United States, 8/07/07.

Computation of nozzle flow in a N ₂O/HTPB hybrid rocket motor. / Tian, Hui ; Cai, Guobiao.
Collection of Technical Papers - 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference. 2007. p. 3646-3653 (Collection of Technical Papers - 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference; Vol. 4).

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution › peer-review

TY - GEN

T1 - Computation of nozzle flow in a N 2O/HTPB hybrid rocket motor

AU - Tian, Hui

AU - Cai, Guobiao

PY - 2007

Y1 - 2007

N2 - Propellant performance of N 2O/HTPB were studied firstly. Vacuum specific impulse is bound up with a oxidizer-to-fuel ratio and expansion ratio. Numerical solutions of full Navier-Stokes equations with chemical reaction flow were obtained for a nozzle flow of the N 2O/HTPB hybrid rocket motor. Lower-Upper decomposition scheme and MUSCL-type and Van Leer approach were used. A chemical reaction model with 12 species and 16 elementary reactions was presented. The nozzle entrance condition was obtained by thermal calculation. The nozzle flow under optimum oxidizer-to-fuel ratio were calculated. which will be useful for the hybrid rocket motor design.

AB - Propellant performance of N 2O/HTPB were studied firstly. Vacuum specific impulse is bound up with a oxidizer-to-fuel ratio and expansion ratio. Numerical solutions of full Navier-Stokes equations with chemical reaction flow were obtained for a nozzle flow of the N 2O/HTPB hybrid rocket motor. Lower-Upper decomposition scheme and MUSCL-type and Van Leer approach were used. A chemical reaction model with 12 species and 16 elementary reactions was presented. The nozzle entrance condition was obtained by thermal calculation. The nozzle flow under optimum oxidizer-to-fuel ratio were calculated. which will be useful for the hybrid rocket motor design.

UR - https://www.scopus.com/pages/publications/36749086508

M3 - 会议稿件

AN - SCOPUS:36749086508

SN - 1563479036

SN - 9781563479038

T3 - Collection of Technical Papers - 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference

SP - 3646

EP - 3653

BT - Collection of Technical Papers - 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference

T2 - 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference

Y2 - 8 July 2007 through 11 July 2007

ER -

Computation of nozzle flow in a N ₂O/HTPB hybrid rocket motor

Abstract

Publication series

Conference

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