On-Line Combustion Temperature Measurements of Solid Rocket Propellant by Using Radiation Spectroscopy

Bin Yang; Hao Ran Guo; Xin Yang Gui; Xin Liu; Zhi Xin Wang; Xiao Long Chen; Pei Jin Liu

doi:10.3964/j.issn.1000-0593(2018)06-1958-05

On-Line Combustion Temperature Measurements of Solid Rocket Propellant by Using Radiation Spectroscopy

Bin Yang, Hao Ran Guo, Xin Yang Gui, Xin Liu, Zhi Xin Wang, Xiao Long Chen, Pei Jin Liu

School of Astronautics

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

9 Scopus citations

Abstract

For the high combustion temperature measurement in harsh environment, the radiation spectroscopy method was proposed to realize the online measurement of combustion temperature of solid rocket propellant. The radiation spectrums in the range of 200~1 100 nm of solid rocket propellant flame in high pressure experimental combustor were obtained by fiber-optic spectrometer. Their representative characteristics were summarized, and the corresponding combustion temperature was determined by the Planck radiation law and the spectral fitting method. The paper provides important reference for combustion diagnostics and mechanism of solid rocket propellant.

Translated title of the contribution	利用辐射光谱法在线测量固体火箭推进剂燃烧温度
Original language	English
Pages (from-to)	1958-1962
Number of pages	5
Journal	Guang Pu Xue Yu Guang Pu Fen Xi/Spectroscopy and Spectral Analysis
Volume	38
Issue number	6
DOIs	https://doi.org/10.3964/j.issn.1000-0593(2018)06-1958-05
State	Published - 1 Jun 2018

Keywords

Combustion diagnostics
Radiation spectroscopy
Solid rocket propellant
Thermometry

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10.3964/j.issn.1000-0593(2018)06-1958-05

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title = "On-Line Combustion Temperature Measurements of Solid Rocket Propellant by Using Radiation Spectroscopy",

abstract = "For the high combustion temperature measurement in harsh environment, the radiation spectroscopy method was proposed to realize the online measurement of combustion temperature of solid rocket propellant. The radiation spectrums in the range of 200~1 100 nm of solid rocket propellant flame in high pressure experimental combustor were obtained by fiber-optic spectrometer. Their representative characteristics were summarized, and the corresponding combustion temperature was determined by the Planck radiation law and the spectral fitting method. The paper provides important reference for combustion diagnostics and mechanism of solid rocket propellant.",

keywords = "Combustion diagnostics, Radiation spectroscopy, Solid rocket propellant, Thermometry",

author = "Bin Yang and Guo, {Hao Ran} and Gui, {Xin Yang} and Xin Liu and Wang, {Zhi Xin} and Chen, {Xiao Long} and Liu, {Pei Jin}",

year = "2018",

month = jun,

day = "1",

doi = "10.3964/j.issn.1000-0593(2018)06-1958-05",

language = "英语",

volume = "38",

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journal = "Guang Pu Xue Yu Guang Pu Fen Xi/Spectroscopy and Spectral Analysis",

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TY - JOUR

T1 - On-Line Combustion Temperature Measurements of Solid Rocket Propellant by Using Radiation Spectroscopy

AU - Yang, Bin

AU - Guo, Hao Ran

AU - Gui, Xin Yang

AU - Liu, Xin

AU - Wang, Zhi Xin

AU - Chen, Xiao Long

AU - Liu, Pei Jin

PY - 2018/6/1

Y1 - 2018/6/1

N2 - For the high combustion temperature measurement in harsh environment, the radiation spectroscopy method was proposed to realize the online measurement of combustion temperature of solid rocket propellant. The radiation spectrums in the range of 200~1 100 nm of solid rocket propellant flame in high pressure experimental combustor were obtained by fiber-optic spectrometer. Their representative characteristics were summarized, and the corresponding combustion temperature was determined by the Planck radiation law and the spectral fitting method. The paper provides important reference for combustion diagnostics and mechanism of solid rocket propellant.

AB - For the high combustion temperature measurement in harsh environment, the radiation spectroscopy method was proposed to realize the online measurement of combustion temperature of solid rocket propellant. The radiation spectrums in the range of 200~1 100 nm of solid rocket propellant flame in high pressure experimental combustor were obtained by fiber-optic spectrometer. Their representative characteristics were summarized, and the corresponding combustion temperature was determined by the Planck radiation law and the spectral fitting method. The paper provides important reference for combustion diagnostics and mechanism of solid rocket propellant.

KW - Combustion diagnostics

KW - Radiation spectroscopy

KW - Solid rocket propellant

KW - Thermometry

UR - http://www.scopus.com/inward/record.url?scp=85054700022&partnerID=8YFLogxK

U2 - 10.3964/j.issn.1000-0593(2018)06-1958-05

DO - 10.3964/j.issn.1000-0593(2018)06-1958-05

M3 - 文章

AN - SCOPUS:85054700022

SN - 1000-0593

VL - 38

SP - 1958

EP - 1962

JO - Guang Pu Xue Yu Guang Pu Fen Xi/Spectroscopy and Spectral Analysis

JF - Guang Pu Xue Yu Guang Pu Fen Xi/Spectroscopy and Spectral Analysis

IS - 6

ER -

On-Line Combustion Temperature Measurements of Solid Rocket Propellant by Using Radiation Spectroscopy

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Keywords

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