基于并联贮箱结构的卫星推进剂剩余量测量方法  

The Residual Propellant Gauging and Estimation Method on Spacecraft Parallel Tank Configuration

作　　者：魏延明[1] 宋涛[1] 梁军强[1] 

机构地区：[1]北京控制工程研究所,北京100190

出　　处：《空间控制技术与应用》2010年第4期25-30,共6页Aerospace Control and Application

摘　　要：星上推进系统推进剂剩余量测量是卫星在轨管理的重要工作,事关卫星剩余寿命估计和离轨时机的选择,对于提高卫星效率具有重大的意义.中国现有的推进剂剩余量计算方法只适用于传统的双贮箱结构,不适用于桁架式卫星平台的多贮箱并联结构,为此必须开发新的计算方法,同时提高计算精度.比较多种推进剂剩余量测量方法,重点论述两种可用于并联贮箱结构的测量方法.Estimation the propellant resources of unmanned spacecraft through operational life is important to successful disposal manoeuvre and orbit lifetime maximization. The most popular methods of propellant estimation are presented in the paper. Advantanges and problems of each method are discussed and compared. It is shown that the error of propellant estimation by GIM（ gas injection method） and TPGT （thermal propellant gauging technique）is proportional to the propellant fill level, their measurement accuracy are superior to the BK（book-keeping） and PVT （ pressure, volume, temperature） methods, and both can be used for parallel tank configuration. The mathematical model for the TPGT is also derived.

关 键 词：卫星推进系统 并联贮箱 推进剂 剩余量测量方法 

分 类 号：V43[航空宇航科学与技术—航空宇航推进理论与工程]