Computation of combustion chamber and nozzle flow in N2O/HTPB hybrid rocket motors

Tian Hui; Cai Guobiao

Computation of combustion chamber and nozzle flow in N₂O/HTPB hybrid rocket motors

Tian Hui^*
, Cai Guobiao

^*Corresponding author for this work

School of Astronautics

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

Abstract

Numerical solutions of full Navier-Stokes equations with chemical reaction flow were obtained for a combustion chamber and nozzle flow of the N ₂O/HTPB hybrid rocket motor. Lower-Upper decomposition scheme and MUSCL-type and VanLeer approach were used. Two steps chemistry model were adopted. A chemical reaction model with 10 species and 11 elementary reactions was presented The combustion chamber and the nozzle flow at different time were calculated. The combustion character was analyzed by the result, which will be useful for the hybrid rocket motor design. Copyright IAF/IAA. All rights reserved.

Original language	English
Title of host publication	International Astronautical Federation - 58th International Astronautical Congress 2007
Pages	5938-5942
Number of pages	5
State	Published - 2007
Event	58th International Astronautical Congress 2007 - Hyderabad, India Duration: 24 Sep 2007 → 28 Sep 2007

Publication series

Name	International Astronautical Federation - 58th International Astronautical Congress 2007
Volume	9

Conference

Conference	58th International Astronautical Congress 2007
Country/Territory	India
City	Hyderabad
Period	24/09/07 → 28/09/07

Cite this

@inproceedings{3d4cbb4b772d464dbed745dee5f1b6b6,

title = "Computation of combustion chamber and nozzle flow in N2O/HTPB hybrid rocket motors",

abstract = "Numerical solutions of full Navier-Stokes equations with chemical reaction flow were obtained for a combustion chamber and nozzle flow of the N 2O/HTPB hybrid rocket motor. Lower-Upper decomposition scheme and MUSCL-type and VanLeer approach were used. Two steps chemistry model were adopted. A chemical reaction model with 10 species and 11 elementary reactions was presented The combustion chamber and the nozzle flow at different time were calculated. The combustion character was analyzed by the result, which will be useful for the hybrid rocket motor design. Copyright IAF/IAA. All rights reserved.",

author = "Tian Hui and Cai Guobiao",

year = "2007",

language = "英语",

isbn = "9781605601502",

series = "International Astronautical Federation - 58th International Astronautical Congress 2007",

pages = "5938--5942",

booktitle = "International Astronautical Federation - 58th International Astronautical Congress 2007",

note = "58th International Astronautical Congress 2007 ; Conference date: 24-09-2007 Through 28-09-2007",

}

Hui, T & Guobiao, C 2007, Computation of combustion chamber and nozzle flow in N₂O/HTPB hybrid rocket motors. in International Astronautical Federation - 58th International Astronautical Congress 2007. International Astronautical Federation - 58th International Astronautical Congress 2007, vol. 9, pp. 5938-5942, 58th International Astronautical Congress 2007, Hyderabad, India, 24/09/07.

Computation of combustion chamber and nozzle flow in N₂O/HTPB hybrid rocket motors. / Hui, Tian ; Guobiao, Cai.
International Astronautical Federation - 58th International Astronautical Congress 2007. 2007. p. 5938-5942 (International Astronautical Federation - 58th International Astronautical Congress 2007; Vol. 9).

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

TY - GEN

T1 - Computation of combustion chamber and nozzle flow in N2O/HTPB hybrid rocket motors

AU - Hui, Tian

AU - Guobiao, Cai

PY - 2007

Y1 - 2007

N2 - Numerical solutions of full Navier-Stokes equations with chemical reaction flow were obtained for a combustion chamber and nozzle flow of the N 2O/HTPB hybrid rocket motor. Lower-Upper decomposition scheme and MUSCL-type and VanLeer approach were used. Two steps chemistry model were adopted. A chemical reaction model with 10 species and 11 elementary reactions was presented The combustion chamber and the nozzle flow at different time were calculated. The combustion character was analyzed by the result, which will be useful for the hybrid rocket motor design. Copyright IAF/IAA. All rights reserved.

AB - Numerical solutions of full Navier-Stokes equations with chemical reaction flow were obtained for a combustion chamber and nozzle flow of the N 2O/HTPB hybrid rocket motor. Lower-Upper decomposition scheme and MUSCL-type and VanLeer approach were used. Two steps chemistry model were adopted. A chemical reaction model with 10 species and 11 elementary reactions was presented The combustion chamber and the nozzle flow at different time were calculated. The combustion character was analyzed by the result, which will be useful for the hybrid rocket motor design. Copyright IAF/IAA. All rights reserved.

UR - https://www.scopus.com/pages/publications/55949137252

M3 - 会议稿件

AN - SCOPUS:55949137252

SN - 9781605601502

T3 - International Astronautical Federation - 58th International Astronautical Congress 2007

SP - 5938

EP - 5942

BT - International Astronautical Federation - 58th International Astronautical Congress 2007

T2 - 58th International Astronautical Congress 2007

Y2 - 24 September 2007 through 28 September 2007

ER -

Computation of combustion chamber and nozzle flow in N₂O/HTPB hybrid rocket motors

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