线性回归分析在液体火箭推进剂温度预测中的应用  

Application of Linear Regression Analysis on Liquid Rocket Propellant Temperature Predication

作　　者：李大鹏 朱平平 陈士强 潘辉 李若全 Li Da-peng;Zhu Ping-ping;Chen Shi-qiang;Pan Hui;Li Ruo-quan(Beijing Institute of Astronautical Systems Engineering,Beijing,100076)

机构地区：[1]北京宇航系统工程研究所

出　　处：《导弹与航天运载技术》2020年第1期43-47,共5页Missiles and Space Vehicles

摘　　要：为研究液体火箭推进剂温度贴壁式测量替代插入式测量方法,消除推进剂插入式测温方式的隐患,基于一维稳态平板壁面传热学原理,建立理论数学模型,将火箭推进剂液体与壁面、环境大气三者之间换热关系的二元方程问题简化为一元方程问题,采用最小二乘法线性拟合,得出依靠壁面温度拟合推进剂温度的线性关联式。回归分析及实例验证了模型的正确性,并讨论了环境温度与壁面温度偏差等因素对测量精度的影响。结果表明:稳态换热条件下,利用壁温线性拟合推算推进剂温度方法可行,精度满足要求。Adherent measurement of liquid rocket propellant temperature instead of insert measurement is investigated to avoid hazards.The theoretical model is established base on one-dimensional steady-state principle of flat wall heat transfer.The heat transfer relationships among propellant,wall,and enviroment,which are equations with two variables are smplified to a equation with one variable.The linear relation between propellant temperature and wall is derived by linear fitting using least square method.Correctness and effectiveness of the model are verified by living examples and regression analysis by which the influence of measurement error of enviroment temperature and wall temperature on result are discussed.The results show that the propellant temperature can be predicted by linear fitting using wall tempreature at steaty-state heat transfer condition and the precision meet the requirements.

关 键 词：液体火箭推进剂 线性回归 最小二乘法 壁面温度 

分 类 号：V434[航空宇航科学与技术—航空宇航推进理论与工程]