Numerical simulation of composite solid propellant rocket motor exhaust plume

Zheng Li; Hong Jun Xiang; Xiao Ying Zhang

doi:10.7673/j.issn.1006-2793.2014.01.007

Numerical simulation of composite solid propellant rocket motor exhaust plume

Zheng Li^*
, Hong Jun Xiang
, Xiao Ying Zhang

^*Corresponding author for this work

School of Astronautics

Beihang University

Research output: Contribution to journal › Article › peer-review

10 Scopus citations

Abstract

The CEA(Chemical Equilibrium with Applications)was used to calculate the equilibrium composition of composite propellant and inlet parameter of the nozzle. Then numerical simulations of solid rocket motor nozzle and exhaust plume flow-field were carried using FLUENT software. The 2D axisymmetric Navier-Stokes equations were solved by time-marching method and AUSM spatial discretization scheme. The k-ε turbulence model, chemical kinetics and Lagrange method were taken to describe turbulence, H₂, CO, HCl afterburning and gas-particle(Al₂O₃)interaction in the exhaust plume. The calculation was made at different altitude and Mach number. The flow-fields under different conditions were described. The results show that: the afterburning of H₂, CO and HCl has significantly influence on the plume flow-field, the flow-field expands along with the increasing of altitude, and the wave number is reduced with the increasing of Mach number.

Original language	English
Pages (from-to)	37-42
Number of pages	6
Journal	Guti Huojian Jishu/Journal of Solid Rocket Technology
Volume	37
Issue number	1
DOIs	https://doi.org/10.7673/j.issn.1006-2793.2014.01.007
State	Published - 2014

Keywords

Afterburn
Composite propellant
Exhaust plume
Solid rocket motor
Two phase flow

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Cite this

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title = "Numerical simulation of composite solid propellant rocket motor exhaust plume",

abstract = "The CEA(Chemical Equilibrium with Applications)was used to calculate the equilibrium composition of composite propellant and inlet parameter of the nozzle. Then numerical simulations of solid rocket motor nozzle and exhaust plume flow-field were carried using FLUENT software. The 2D axisymmetric Navier-Stokes equations were solved by time-marching method and AUSM spatial discretization scheme. The k-ε turbulence model, chemical kinetics and Lagrange method were taken to describe turbulence, H2, CO, HCl afterburning and gas-particle(Al2O3)interaction in the exhaust plume. The calculation was made at different altitude and Mach number. The flow-fields under different conditions were described. The results show that: the afterburning of H2, CO and HCl has significantly influence on the plume flow-field, the flow-field expands along with the increasing of altitude, and the wave number is reduced with the increasing of Mach number.",

keywords = "Afterburn, Composite propellant, Exhaust plume, Solid rocket motor, Two phase flow",

author = "Zheng Li and Xiang, \{Hong Jun\} and Zhang, \{Xiao Ying\}",

year = "2014",

doi = "10.7673/j.issn.1006-2793.2014.01.007",

language = "英语",

volume = "37",

pages = "37--42",

journal = "Guti Huojian Jishu/Journal of Solid Rocket Technology",

issn = "1006-2793",

publisher = "Journal of Solid Rocket Technology",

number = "1",

}

TY - JOUR

T1 - Numerical simulation of composite solid propellant rocket motor exhaust plume

AU - Li, Zheng

AU - Xiang, Hong Jun

AU - Zhang, Xiao Ying

PY - 2014

Y1 - 2014

N2 - The CEA(Chemical Equilibrium with Applications)was used to calculate the equilibrium composition of composite propellant and inlet parameter of the nozzle. Then numerical simulations of solid rocket motor nozzle and exhaust plume flow-field were carried using FLUENT software. The 2D axisymmetric Navier-Stokes equations were solved by time-marching method and AUSM spatial discretization scheme. The k-ε turbulence model, chemical kinetics and Lagrange method were taken to describe turbulence, H2, CO, HCl afterburning and gas-particle(Al2O3)interaction in the exhaust plume. The calculation was made at different altitude and Mach number. The flow-fields under different conditions were described. The results show that: the afterburning of H2, CO and HCl has significantly influence on the plume flow-field, the flow-field expands along with the increasing of altitude, and the wave number is reduced with the increasing of Mach number.

AB - The CEA(Chemical Equilibrium with Applications)was used to calculate the equilibrium composition of composite propellant and inlet parameter of the nozzle. Then numerical simulations of solid rocket motor nozzle and exhaust plume flow-field were carried using FLUENT software. The 2D axisymmetric Navier-Stokes equations were solved by time-marching method and AUSM spatial discretization scheme. The k-ε turbulence model, chemical kinetics and Lagrange method were taken to describe turbulence, H2, CO, HCl afterburning and gas-particle(Al2O3)interaction in the exhaust plume. The calculation was made at different altitude and Mach number. The flow-fields under different conditions were described. The results show that: the afterburning of H2, CO and HCl has significantly influence on the plume flow-field, the flow-field expands along with the increasing of altitude, and the wave number is reduced with the increasing of Mach number.

KW - Afterburn

KW - Composite propellant

KW - Exhaust plume

KW - Solid rocket motor

KW - Two phase flow

UR - https://www.scopus.com/pages/publications/84897135150

U2 - 10.7673/j.issn.1006-2793.2014.01.007

DO - 10.7673/j.issn.1006-2793.2014.01.007

M3 - 文章

AN - SCOPUS:84897135150

SN - 1006-2793

VL - 37

SP - 37

EP - 42

JO - Guti Huojian Jishu/Journal of Solid Rocket Technology

JF - Guti Huojian Jishu/Journal of Solid Rocket Technology

IS - 1

ER -

Numerical simulation of composite solid propellant rocket motor exhaust plume

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Keywords

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