摘要
为提高飞行器机载精密仪器的性能,设计了一种基于被动散热与主动控温的温控系统。该系统采用热管和辐射涂层作为被动散热装置将仪器内热量传出,再利用半导体制冷器和保温层进行第一级控温,并利用电加热装置进行第二级控温,最后设计控制逻辑进行控温。搭建了验证实验台,测试了不同工况下温控系统的温控精度。结果表明,在不同环境温度和温控系统设定温度工况下,该温控系统的温控精度均在±0.1℃以内。
To improve the performance of aircraft precision instrument,a temperature control system with passive heat dissipation and active temperature control was designed.In the system,the heat pipe and radiation coating were used as passive radiator to transfer the heat from the instrument.The first stage temperature control was established by semiconductor cooler and insulation layer,and the second stage temperature control was established by electric heating device.The control logic was designed to control temperature.A verification test platform was built,and the temperature control accuracy of the temperature control system under different operating conditions was tested.The result shows that the temperature control accuracy of the system is within±0.1℃under the conditions of different environmental temperatures and system setting temperatures.
作者
李阳
常守金
胡海涛
孙浩然
赖展程
刘善敏
LI Yang;CHANG Shoujin;HU Haitao;SUN Haoran;LAI Zhancheng;LIU Shanmin(Institute of Refrigeration and Cryogenics Engineering,Shanghai Jiao Tong University,Shanghai 200240,China;Shanghai Microsatellite Engineering Center,Shanghai 201203,China)
出处
《化工学报》
EI
CAS
CSCD
北大核心
2020年第S01期77-82,共6页
CIESC Journal
基金
上海市“科技创新行动计划”(19142203000)
航天一院高校联合创新基金项目(CALT201803)。
关键词
飞行器
传热
辐射
半导体制冷器
温控
实验验证
aircraft
heat transfer
radiation
semiconductor cooler
temperature control
experimental validation
