亚博体育官网

亚博体育|即时比分|即时直播

登录    |    注册

您好,欢迎来到中国亚博体育资讯平台!

首页>《中国测试》期刊>本期导读>高超声速风洞Ma=5中劈尖试件的红外测温

高超声速风洞Ma=5中劈尖试件的红外测温

127    2019-07-26

¥0.00

全文售价

作者:张凤, 何康, 冯世杰, 张佳明, 王文瑞, 李泉水, 路彦珍, 刘福海, 赵飞, 王凤平

作者单位:北京科技大学, 北京 100083


关键词:红外测温;风洞;热电偶;发射率


摘要:

目前,红外测温技术在高温非稳态下的应用研究还不成熟,而红外测温技术的关键在于发射率的准确丈量。为了丈量高超声速气流下试件的温度,同时采取MCS640高温红外热像仪和GH3030高温合金热电偶对风洞马赫数5(Ma=5)中的超高强度合金结构钢D6AC劈尖试件进行温度丈量。首先,通过热电偶和红外热像仪组合的匹配法校正试件的发射率,再设置热像仪的发射率,测得试件驻点的温度变更曲线和试件在不同时刻的热图。实验测得试件驻点的最高温度为2 019.3 ℃,对分析资料的烧蚀性能和防热结构的可靠性提供了参考。实验证明,该测温方法可以用来丈量高超声速风洞中试件的温度。


Infrared temperature measurement of wedge shape specimen in the hypersonic wind tunnel at Ma = 5
ZHANG Feng, HE Kang, FENG Shijie, ZHANG Jiaming, WANG Wenrui, LI Quanshui, LU Yanzhen, LIU Fuhai, ZHAO Fei, WANG Fengping
University of Science and Technology Beijing, Beijing 100083, China
Abstract: At present, the application of infrared temperature measurement technology in the non-steady state at high temperature is not yet mature, and the key to infrared radiation temperature measurement lies in the accurate measurement of the emissivity. In order to measure the temperature of the specimen under hypersonic flow, the temperature of the wedge shape specimen of super strength alloy structural steel D6AC was measured by using the Lumasense MCS640 thermal imager and the GH3030 high temperature alloy thermocouple in the wind tunnel of Mach-number 5. Firstly, the emissivity of the specimen is corrected by the matching method of a thermocouple and an infrared thermal imager, and then the emissivity of the thermal imager is set. The temperature variation curve of the stagnation point of the specimen and the heat map of the specimen at different moments are measured. The maximum temperature of the test specimen at the stagnation point is 2019.3℃, which provides a reference for the ablation performance of the analysis material and the reliability of the heat protection structure. Experiments show that this kind of temperature measurement method can be used to measure the temperature of the specimen in the hypersonic wind tunnel.
Keywords: infrared temperature measurement;wind tunnel;thermocouple;emissivity
2019, 45(7):37-41  收稿日期: 2018-02-05;收到修改稿日期: 2018-03-16
基金项目: 国家重大科学仪器设备开发专项(2011YQ14014506,2011YQ14014507)
作者简介: 张凤(1992-),少女,陕西西安市人,硕士研究生,专业方向为物理学
参考文献
[1] 周嘉穗, 张扣立, 江涛, 等. 激波风洞温敏热图技术初步试验研究[J]. 实验流体力学, 2013, 27(5):79-82
[2] 孙晓刚, 李云红. 红外热像仪测温技术发展综述[J]. 激光与红外, 2008, 38(2):101-104
[3] 郭隆德.风洞非接触丈量技术[M].北京:国防工业出版社, 2013:120.
[4] 程丽鹏.红外热像仪的超高温度场丈量技术研究[D].太原:中北大学, 2017.
[5] 汪思国, 何显中, 王小蕾.红外成像图像数据处理软件及其应用[C]//中国空气动力学会,中国力学学会.流动显示2002全国流动显示学术会议, 2002:209-215.
[6] 孙晓刚, 戴景民. 多光谱辐射测温的理论研究[J]. 红外与毫米波学报, 1998, 17(3):221-225
[7] 李文军, 徐永达, 郑永军. 红外热像仪与名义热电偶丈量发射率的匹配法[J]. 中国测试, 2017, 43(6):12-15
[8] 白敬晨, 于庆波, 胡贤忠, 等. 基于红外热像仪的物体名义发射率丈量方法[J]. 东北大学学报(自然科学版), 2013, 34(12):1747-1750
[9] 关威, 刘建梅, 王琦, 等. 基于红外辐射计的物体光谱发射率丈量方法[J]. 火力与指挥控制, 2016, 41(11):163-166
[10] 王华伟.基于红外热成像的温度场丈量关键技术研究[D].北京:中国科学院大学, 2013.