Dynamic measurement and correction of infrared radiation temperature for rocket motor exhaust plume
Jianhua Yi,
Zhihua Sun,
Changjian Wang,
Yi Xu,
Zhao Qin,
Haijian Li,
Fengqi Zhao
Affiliations
Jianhua Yi
Science and Technology on Combustion and Explosion Laboratory, Xi'an 710065, China; Xi'an Modern Chemistry Research Institute, Xi'an 710065, China; Corresponding authors at: Science and Technology on Combustion and Explosion Laboratory, Xi'an 710065, China.
Zhihua Sun
Science and Technology on Combustion and Explosion Laboratory, Xi'an 710065, China; Xi'an Modern Chemistry Research Institute, Xi'an 710065, China
Changjian Wang
Science and Technology on Combustion and Explosion Laboratory, Xi'an 710065, China; Xi'an Modern Chemistry Research Institute, Xi'an 710065, China
Yi Xu
Science and Technology on Combustion and Explosion Laboratory, Xi'an 710065, China; Xi'an Modern Chemistry Research Institute, Xi'an 710065, China
Zhao Qin
Science and Technology on Combustion and Explosion Laboratory, Xi'an 710065, China; Xi'an Modern Chemistry Research Institute, Xi'an 710065, China
Haijian Li
Science and Technology on Combustion and Explosion Laboratory, Xi'an 710065, China; Xi'an Modern Chemistry Research Institute, Xi'an 710065, China
Fengqi Zhao
Science and Technology on Combustion and Explosion Laboratory, Xi'an 710065, China; Xi'an Modern Chemistry Research Institute, Xi'an 710065, China; Corresponding authors at: Science and Technology on Combustion and Explosion Laboratory, Xi'an 710065, China.
The dynamic measurement and correction of infrared radiation temperature for rocket motor exhaust plume was established based on Stefan-Boltzmann formula under the assumption that the colorimetric temperature is regarded as the real value. The relationship between the spectral emissivity of the exhaust plume and time is obtained, and the temperature distribution measured by the infrared thermal imager is corrected in real time. During the stable working period of the rocket motor, the maximum value of the infrared radiation temperature distribution curve and the average value corresponding to the time are used to represent the maximum and average infrared radiation temperature of the motor exhaust plume field. This method is applicable to the real-time determination of the spectral emissivity of the exhaust plume and the accurate measurement of the infrared radiation temperature distribution at static or rocket sled flight state, and is of great significance to the development of the low-signature rocket motor and propellant charge.
