高轨星载天线热分析研究  

Thermal Analysis of High-orbit Space-borne Antenna

作　　者：包胜[1] 王超[1] 

机构地区：[1]中国电子科技集团公司第二十九研究所,四川成都610036

出　　处：《电子机械工程》2017年第4期35-37,41,共4页Electro-Mechanical Engineering

摘　　要：文中采用仿真与试验相结合的方法对小型高轨星载天线进行了热分析。首先,在相同的边界条件下,对天线进行了热仿真和热测试。结果对比表明,二者偏差较小,同时也验证了热仿真模型的可靠性。其次,采用热仿真方法研究了影响高轨星载天线静态温度的2个重要因素——太阳辐射角β及天线材料表面吸发比α/ε。相关结果可作为小型高轨星载天线开展无空间辐射的地面耐功率试验的重要依据,还可为天线热设计及热测试提供重要参考,可显著提高设计效率,减少反复,节约试验资源。Detailed thermal analysis of the small high-orbit space-borne antenna has been conducted by simu- lation and experimentation in this paper. First of all, the simulation and experimentation of the antenna are carried out under the same conditions. The comparison of the simulation and experimentation results show that their difference is very small, which verifies the reliability of the simulation model. Then, two important fac- tors affecting the static temperature of the antenna （ the solar incidence angle/3 and the rate of solar absorption to emissivity or/8） are studied. The corresponding results can be used as the important basis of the tolerable power experiment without space radiation of the high-orbit space-borne antenna and can also provide important reference for the thermal design and thermal test, which can significantly improve the design efficiency, save much design time and test resources.

关 键 词：星载天线 热分析 太阳辐射角 吸发比 

分 类 号：TN82[电子电信—信息与通信工程]