双组元统一推进系统加注混合比改进算法及应用  

Improved Algorithm and its Application of the Mixture Ratio of Propellant for Bipropellant-united Propulsion System

作　　者：定宇[1] 袁莉芳[1] 王庆华[1] 

机构地区：[1]北京空间飞行器总体设计部,北京100094

出　　处：《航天器工程》2011年第4期60-64,共5页Spacecraft Engineering

摘　　要：卫星双组元统一推进系统加注混合比,是确定卫星氧化剂和燃烧剂加注量的重要参数。正确地确定加注混合比可以减少卫星的呆重,增加推进剂余量和卫星寿命。文章在原有混合比计算的基础上,分析了在轨不同阶段的不同压力、温度条件下10N推力器和490N变轨发动机的流量情况和入口压力、氧化剂和燃烧剂压力变化情况,利用推力器和变轨发动机地面热试车试验数据和推进分系统气路检测数据,提出了卫星推进剂加注混合比的改进算法。改进的混合比计算方法与原有计算方法的主要区别,在于按照卫星在轨工作的不同阶段分别进行分析与统计,更加精确地确定了10N推力器及490N变轨发动机工作时的氧化剂与燃烧剂的流量。经在轨卫星变轨期间对推进剂消耗量及其混合比的实测验证,改进算法更接近在轨实测值,可作为双组元统一推进系统实施加注时的参考。The mixture ratio is the ratio of oxidizer to fuel,and it is the important parameter to calculate the amount of propellant.By choosing the right mixture ratio,unwanted weight can be less,and the life span of the satellite can be extended.On the basis of the old algorithmic method,the flux and pressure of the impulse thruster and the orbit motor in different phases and different temperatures are analyzed in this paper.By taking the ground hot-firing test result and gas circuit detection data into consideration,a new algorithm of the mixture ratio of propellant is provided.The difference between the new algorithm and the former one is to take states of different phases into consideration in order to determine the flux of propellant accurately.By measuring the practical mixture ratio of the satellite in orbit,the new algorithm performs well.The new algorithm of the mixture ratio provides a reference for the process of fuel loading of the bipropellant-united propulsion system satellites.

关 键 词：卫星 推进剂混合比 地面热试车 气路检测 

分 类 号：V430[航空宇航科学与技术—航空宇航推进理论与工程]