微泵驱动流体回路主动热控系统在轨测试试验研究  

The flight experiments of active thermal control system with micro-mechanical pumped fluid loop

作　　者：曹建光[1] 顾燕萍[1] 陈钢[1] 孙伟伟[1] 王江[1] 刘冈云[1] CAO Jianguang;GU Yanping;CHEN Gang;SUN Weiwei;WANG Jiang;LIU Gangyun(Shanghai Institute of Satellite Engineering, Shanghai 201100, China)

机构地区：[1]上海卫星工程研究所,上海201100

出　　处：《航天器环境工程》2017年第4期343-349,共7页Spacecraft Environment Engineering

基　　金：国家863重大专项课题(编号:2013AA8073034);上海市科研技术项目(编号:14QB1404200)

摘　　要：简要概述了"浦江一号"卫星流体回路系统的设计方案和地面测试试验情况,并在此基础上详细介绍了在轨开展的流体回路系统的开环和闭环控制测试,以及微泵A和微泵B的长寿命测试。在轨测试结果表明:微泵驱动流体回路系统各部组件满足空间环境使用要求;系统软、硬件在轨各项性能长期稳定良好;流体回路系统可以实现航天器热量的快速收集与传输,具有灵活的热管理能力。This paper reviews the design scheme and the ground test results of the launched fluid loopsystem,focusing on the flight experiment scheme and the corresponding results.The flight experiment of thedeveloped fluid loop system includes the open-loop test,the closed-loop test and the on-orbit long life test of twomicro-mechanical pumps.The experiment results indicate that all components of the developed fluid loopsystem can meet the requirements of the space environment;the hardware and software performance of thesystem is long-time stable on the orbit;the micro-mechanical pumped fluid loop system has a flexible thermalmanagement capacity,in that it achieves a rapid heat collection and heat transfer for the spacecraft.

关 键 词：主动热控 微泵 流体回路 在轨测试试验 

分 类 号：V57[航空宇航科学与技术—航空宇航推进理论与工程]