推进剂调温过程数值模拟及控制方法研究  

Numerical simulation and control method research of propellant temperature regulation process

作　　者：王迪[1] 肖锋[1] 王金霞 张坤 WANG Di;XIAO Feng;WANG Jinxia;ZHANG Kun(Technical department,Xichang Satellite Launch Center,Liangshan 615000,China)

机构地区：[1]西昌卫星发射中心技术部,四川凉山615000

出　　处：《航天工程大学学报》2024年第1期48-56,共9页

摘　　要：基于三维流体计算方法,搭建了发射场推进剂储罐的仿真模型,对推进剂调温过程进行数值模拟,对调温过程中的三维流场结构进行了定量分析,对不同入口推进剂温度的调温过程进行定量计算,对调温精度的影响因素进行了定量分析;结合仿真结果,提出推进剂调温过程精确控制方法,并通过数值计算结果进行验证,对发射场的工作具有一定的指导意义。Based on the three-dimensional fluid calculation method,a simulation model of the propellant storage tank at the launch site was constructed.The numerical simulation accurately depicts the process of propellant temperature adjustment and quantitatively analyzes the three-dimensional flow field structure during this process.Furthermore,it calculates and quantitatively analyzes the temperature adjustment process for different inlet propellant temperatures,identifying key factors influencing temperature adjustment accuracy.Based on these simulation results,a precise control method for regulating propellant temperature is proposed and validated through numerical calculations,providing valuable guidance for launch site operations.

关 键 词：调温过程 流场结构 调温精度 控制方法 数值仿真 

分 类 号：V511[航空宇航科学与技术—航空宇航推进理论与工程]