星载微波探测仪探测头部热设计及验证  

Thermal Design and Verification of Spaceborne Microwave Detector Probe Head

作　　者：刘瑞 李宁杰 葛如飞 龙澄 王光辉 栾英宏 LIU Rui;LI Ningjie;GE Rufei;LONG Deng;WANG Guanghui;LUAN Yinghong(Shanghai Aerospace Electronic Technology Institute, Shanghai 201109, China)

机构地区：[1]上海航天电子技术研究所,上海201109

出　　处：《航天器工程》2021年第5期59-65,共7页Spacecraft Engineering

基　　金：国家民用航天空间基础设施中长期发展规划项目(D010101)。

摘　　要：星载微波探测仪采用主被动一体化探测方法,以提高探测精度和空间分辨率,是土壤水探测卫星的主载荷,探测仪的探测头部主要由主动单机和被动单机等组成,其中主动单机中的发送/接收(T/R)组件数量多、功耗大、阵面布局长达7m,被动单机中的接收机对温度波动敏感,同时探测头部构型复杂且各散热面外热流环境恶劣。针对探测头部热控难点及要求,开展了包括轨道外热流分析、散热面和传热路径的设计、热管网络布局,关键单机的精细化控温等工作,并结合热平衡试验结果对热设计方案进行了有效验证。仿真及试验结果表明:探测头部的温度水平、关键单机的温度梯度及每轨温度波动均满足要求,其中T/R组件温度梯度控制在≤12℃,被动接收机温度波动控制在±1℃/轨。该设计解决了大功耗T/R组件短时开机导致单机之间温差大、瞬时温升速率快,接收机温度波动大等技术难点,突破了高功率密度T/R组件全阵面热设计关键技术和被动接收机的高稳定度控温关键技术,实现了探测头部在轨全周期高精度、高稳定度热控,可为星载微波探测仪类载荷的热设计提供借鉴。Spaceborne microwave detector by using active and passive detection method to improve detection accuracy and spatial resolution,it is the main payload for soil water satellite.The probe head of microwave detector is composed of active and passive components,which include active T/R components with characteristics of numerous modules,large heat dissipation and 7m length layout scale,and passive receivers affected by temperature fluctuation.The configuration of probe head is complicated,and the external heat flux is extreme.Aiming at requirements of thermal design,the work including orbit heat flux analysis,heat dissipation paths design,layout of heat pipes,and precise thermal control of key components,is accomplished.The method of thermal design is validated by the results of TBT.The results of simulation and test show that the temperature level of probe head,temperature gradient of T/R components,and each-orbit temperature fluctuation of passive receivers can meet the requirements.And the temperature gradient of the T/R components controlled at less than 12℃,the temperature fluctuation of passive receiver controlled at±1℃per each orbit.This method solves the technique of temperature difference among components caused by the T/R components short-time start-up,short-time temperature rise rate,and temperature fluctuation of passive receivers.The key technique of high power density T/R components thermal design and high stability thermal control is breakthrough.And,the high precise and stabile thermal control of probe head in complete period cycle is achieved.This design method can provide guidance for thermal design of spaceborne microwave payload.

关 键 词：微波探测仪 探测头部 热设计 试验验证 

分 类 号：V443[航空宇航科学与技术—飞行器设计]