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| On-Line Combustion Temperature Measurements of Solid Rocket Propellant by Using Radiation Spectroscopy |
| YANG Bin1*, GUO Hao-ran1, GUI Xin-yang1, LIU Xin2, WANG Zhi-xin2, CHEN Xiao-long3, LIU Pei-jin2 |
1. Institute of Particle and Two-Phase Flow Measurement, University of Shanghai for Science and Technology, Shanghai 200093, China
2. Science and Technology on Combustion, Internal Flow and Thermal-Structure Laboratory, Northwestern Polytechnical University, Xi’an 710072, China
3. Shanghai Space Propulsion Technology Research Institute, Shanghai 201109, China |
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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.
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Received: 2017-06-06
Accepted: 2017-11-20
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Corresponding Authors:
YANG Bin
E-mail: yangbin@usst.edu.cn
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