Computational simulation of nonlinear L* Combustion instability in solid rockets

K. C. Tang, M. Q. Brewster

Research output: Contribution to conferencePaper

Abstract

L* instability in solid rocket motors is numerically modeled using a simplified kinetics combustion model coupled with a simplified L* combustor. A nonlinear combustion model (WSB) is used with low activation energy, bimolecular single-step reaction in the gas phase and high activation energy, zero-order decomposition in the condensed phase. Quasi-steady gas and condensed phase reaction (surface reaction) were assumed. The phenomenological Zeldovich-Novozhilov (ZN) approach was used. Classical linear L* analytical results are recovered. Several nonlinear behaviors are predicted computationally, many of which are similar to observed nonlinear L* instability behavior such as extinction, chuffing, limit-cycle (amplitude-limited) oscillations, and frequency shifting. Frequency shifting (or dual frequency oscillation) has been observed experimentally in double base propellant but attributed tentatively to the two-stage flame structure of these propellants. In the present model, dual-frequency behavior is manifested without including a two-stage flame structure.

Original languageEnglish (US)
StatePublished - Jan 1 1999
Event37th Aerospace Sciences Meeting and Exhibit, 1999 - Reno, United States
Duration: Jan 11 1999Jan 14 1999

Other

Other37th Aerospace Sciences Meeting and Exhibit, 1999
CountryUnited States
CityReno
Period1/11/991/14/99

Fingerprint

combustion stability
Rockets
rockets
combustion
Propellants
activation energy
Activation energy
oscillation
simulation
flames
double base propellants
Rocket engines
Surface reactions
vapor phases
Combustors
Gases
gas
oscillations
propellants
combustion chambers

ASJC Scopus subject areas

  • Space and Planetary Science
  • Aerospace Engineering

Cite this

Tang, K. C., & Brewster, M. Q. (1999). Computational simulation of nonlinear L* Combustion instability in solid rockets. Paper presented at 37th Aerospace Sciences Meeting and Exhibit, 1999, Reno, United States.

Computational simulation of nonlinear L* Combustion instability in solid rockets. / Tang, K. C.; Brewster, M. Q.

1999. Paper presented at 37th Aerospace Sciences Meeting and Exhibit, 1999, Reno, United States.

Research output: Contribution to conferencePaper

Tang, KC & Brewster, MQ 1999, 'Computational simulation of nonlinear L* Combustion instability in solid rockets', Paper presented at 37th Aerospace Sciences Meeting and Exhibit, 1999, Reno, United States, 1/11/99 - 1/14/99.
Tang KC, Brewster MQ. Computational simulation of nonlinear L* Combustion instability in solid rockets. 1999. Paper presented at 37th Aerospace Sciences Meeting and Exhibit, 1999, Reno, United States.
Tang, K. C. ; Brewster, M. Q. / Computational simulation of nonlinear L* Combustion instability in solid rockets. Paper presented at 37th Aerospace Sciences Meeting and Exhibit, 1999, Reno, United States.
@conference{bf3713bca7144d159507c91b5287cbbd,
title = "Computational simulation of nonlinear L* Combustion instability in solid rockets",
abstract = "L* instability in solid rocket motors is numerically modeled using a simplified kinetics combustion model coupled with a simplified L* combustor. A nonlinear combustion model (WSB) is used with low activation energy, bimolecular single-step reaction in the gas phase and high activation energy, zero-order decomposition in the condensed phase. Quasi-steady gas and condensed phase reaction (surface reaction) were assumed. The phenomenological Zeldovich-Novozhilov (ZN) approach was used. Classical linear L* analytical results are recovered. Several nonlinear behaviors are predicted computationally, many of which are similar to observed nonlinear L* instability behavior such as extinction, chuffing, limit-cycle (amplitude-limited) oscillations, and frequency shifting. Frequency shifting (or dual frequency oscillation) has been observed experimentally in double base propellant but attributed tentatively to the two-stage flame structure of these propellants. In the present model, dual-frequency behavior is manifested without including a two-stage flame structure.",
author = "Tang, {K. C.} and Brewster, {M. Q.}",
year = "1999",
month = "1",
day = "1",
language = "English (US)",
note = "37th Aerospace Sciences Meeting and Exhibit, 1999 ; Conference date: 11-01-1999 Through 14-01-1999",

}

TY - CONF

T1 - Computational simulation of nonlinear L* Combustion instability in solid rockets

AU - Tang, K. C.

AU - Brewster, M. Q.

PY - 1999/1/1

Y1 - 1999/1/1

N2 - L* instability in solid rocket motors is numerically modeled using a simplified kinetics combustion model coupled with a simplified L* combustor. A nonlinear combustion model (WSB) is used with low activation energy, bimolecular single-step reaction in the gas phase and high activation energy, zero-order decomposition in the condensed phase. Quasi-steady gas and condensed phase reaction (surface reaction) were assumed. The phenomenological Zeldovich-Novozhilov (ZN) approach was used. Classical linear L* analytical results are recovered. Several nonlinear behaviors are predicted computationally, many of which are similar to observed nonlinear L* instability behavior such as extinction, chuffing, limit-cycle (amplitude-limited) oscillations, and frequency shifting. Frequency shifting (or dual frequency oscillation) has been observed experimentally in double base propellant but attributed tentatively to the two-stage flame structure of these propellants. In the present model, dual-frequency behavior is manifested without including a two-stage flame structure.

AB - L* instability in solid rocket motors is numerically modeled using a simplified kinetics combustion model coupled with a simplified L* combustor. A nonlinear combustion model (WSB) is used with low activation energy, bimolecular single-step reaction in the gas phase and high activation energy, zero-order decomposition in the condensed phase. Quasi-steady gas and condensed phase reaction (surface reaction) were assumed. The phenomenological Zeldovich-Novozhilov (ZN) approach was used. Classical linear L* analytical results are recovered. Several nonlinear behaviors are predicted computationally, many of which are similar to observed nonlinear L* instability behavior such as extinction, chuffing, limit-cycle (amplitude-limited) oscillations, and frequency shifting. Frequency shifting (or dual frequency oscillation) has been observed experimentally in double base propellant but attributed tentatively to the two-stage flame structure of these propellants. In the present model, dual-frequency behavior is manifested without including a two-stage flame structure.

UR - http://www.scopus.com/inward/record.url?scp=84983184602&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=84983184602&partnerID=8YFLogxK

M3 - Paper

AN - SCOPUS:84983184602

ER -