航天器热平衡试验用大面阵外热流动态模拟系统设计及应用验证  

Design and application verification of large-area heat flow dynamic simulation systemin thermal balance test of spacecraft

作　　者：韩继广 陶晶亮 盖照亮 周国锋 陈丽 彭光东 HAN Jiguang;TAO Jingliang;GAI Zhaoliang;ZHOU Guofeng;CHEN Li;PENG Guangdong(Shanghai Institute of Spacecraft Equipment,Shanghai 200240,China)

机构地区：[1]上海卫星装备研究所

出　　处：《航天器环境工程》2019年第5期495-501,共7页Spacecraft Environment Engineering

摘　　要：针对航天器热平衡试验时采用固定式红外加热笼无法模拟超低热流的问题,文章研制了一种可在真空低温环境下长时间连续可靠运行的大面阵外热流动态模拟系统。该系统能够在不打开真空容器的情况下,通过动态调整红外加热笼与航天器表面之间的相对位置,同时实现航天器表面的高热流和超低热流模拟,高、低热流模拟的转换时间最短仅需3 min,所模拟的最低热流不大于20 W/m2。将该系统应用于某航天器热平衡试验,能够在低温工况有效降低航天器表面接收的外热流,使航天器表面温度和该表面上的单机温度降低3.5~10℃。For the simulation of the ultra-low heat flow in the thermal balance test of spacecraft, a large-area heat flowdynamic simulation system is developed to replace of the traditional fixed infrared heating cage, which is supposed to run continuously under high and low temperatures for a long time. The system can produce a high heat flow or an ultra-low heat flow on the spacecraft surface by adjusting the relative position of infrared heating cage with respect to the spacecraft surface without opening the vacuum tank. The minimum switch time between the two working conditions is no more than 3 min, and the minimum simulated heat flow is not more than 20 W/m^2 by using the system. The system was successfully applied in the thermal balance test of a spacecraft. It is shown that the system can effectively reduce the external heat flow received by the surface of the spacecraft in the low temperature condition, and reduce the surface temperature of the spacecraft in the low temperature condition, and the stand-alone temperature on the surface by 3.5~10 ℃.

关 键 词：航天器 热平衡试验 外热流 红外加热笼 机构设计 运动控制 仿真分析 

分 类 号：V416.5[航空宇航科学与技术—航空宇航推进理论与工程] TH122[机械工程—机械设计及理论]