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火药燃烧宽波段热辐射温度测量方法研究
引用本文:王艳平,曾丹,李素灵,刘英,张同来.火药燃烧宽波段热辐射温度测量方法研究[J].含能材料,2017,25(3):253-256.
作者姓名:王艳平  曾丹  李素灵  刘英  张同来
作者单位:1. 北京理工大学爆炸科学与技术国家重点实验室,北京100081;兵器工业安全技术研究所,北京100053;2. 兵器工业安全技术研究所,北京,100053;3. 北京理工大学爆炸科学与技术国家重点实验室,北京,100081
摘    要:为了准确测量火药燃烧时的高温瞬态火焰表面温度,利用辐射测温理论提出了火药燃烧宽波段热辐射测温方法,集成设计了高温瞬态温度测量系统,并采用单基发射药自由场条件下的燃烧试验,验证了高温瞬态温度测量系统的有效性和可靠性。结果表明,自由场条件下3m处的单基发射药燃烧火焰表面温度在1~10 kg等4种不同药量下实测为1500~1800℃,数据重复性较好,且测量结果与理论计算一致。

关 键 词:火药  热辐射  热通量传感器  发射药  燃烧温度
收稿时间:2016/6/15 0:00:00
修稿时间:2016/9/26 0:00:00

Research on Measurement Method of Propellant Combustion Temperature with Broadband Thermal Radiation
WANG Yan-ping,ZENG Dan,LI Su-ling,LIU Ying and ZHANG Tong-lai.Research on Measurement Method of Propellant Combustion Temperature with Broadband Thermal Radiation[J].Chinese Journal of Energetic Materials,2017,25(3):253-256.
Authors:WANG Yan-ping  ZENG Dan  LI Su-ling  LIU Ying and ZHANG Tong-lai
Affiliation:State Key Laboratory of Explosion Science and Technology, Beijing 100081, China ;Safety Technology Research Institute of Ordnance Industry, Beijing 100053, China,Safety Technology Research Institute of Ordnance Industry, Beijing 100053, China,Safety Technology Research Institute of Ordnance Industry, Beijing 100053, China,Safety Technology Research Institute of Ordnance Industry, Beijing 100053, China and State Key Laboratory of Explosion Science and Technology, Beijing 100081, China
Abstract:In order to accurately measure the transient high temperature of propellant combustion,the measurement method of broadband thermal radiation temperature for propellant combustion was studied on the thermal radiation theory.The high temperature transient measurement system was integrated;the validity and reliability of the temperature measurement system were verified by single-base propellant combustion test under free-field conditions.Results show that the flame temperatures are between 1500 ℃ and 1800 ℃ when the samples of propellant are placed 3 m away,and the data are repeatable and coincide with theory.
Keywords:propellant  thermal radiation  heat flux microsensor  single-base propellant  combustion temperature
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