基于热响应的卫星推进剂剩余量测量方法研究  

Research on Thermal Propellant Gauging System on Satellite

作　　者：江世臣[1] 付鑫[1] 康奥峰[1] 袁双[1] 林景松[1] 俞洁[2] 

机构地区：[1]上海卫星工程研究所空间机热一体化技术实验室,上海200240 [2]上海航天技术研究院,上海201109

出　　处：《上海航天》2014年第3期43-47,共5页Aerospace Shanghai

摘　　要：介绍了基于热响应法的卫星推进剂剩余量在轨测量方法的原理,给出了国外在Telstar 11,LM 3000,BSS601平台日本通信卫星,Turksat 1C卫星的应用情况。给出了将该方法用于国内卫星的设想,并归纳了推进剂在轨空间分布高精度仿真、带液条件下贮箱内复杂传热过程高精度热仿真、贮箱与整星耦合热分析仿真等关键技术。The principle of propellant gauging system on satellite based on thermal response was introduced in this paper.The applications of Telstar 11,LM 3000,BSS 601Japan telecommunication satellite and Turksat 1C satellite in abroad were given out.The imagine to apply the method into the satellite in domestic was put forward.The key technologies which were high accuracy simulation of propellant distribution on orbit,high accuracy simulation of the complicated heat transfer process in tank with liquid and thermal analysis simulation of the tank and the whole satellite coupled were concluded.

关 键 词：热响应 推进剂 剩余量 

分 类 号：V434[航空宇航科学与技术—航空宇航推进理论与工程]