低温末级滑行过程中贮箱压力仿真分析和控制  

Tank Pressure Simulation and Control for Cryogenic Upper Stage during Coasting-flight Phase

作　　者：张青松 朱平平 崔垒 吴义田 宋征宇 ZHANG Qingsong;ZHU Pingping;CUI Lei;WU Yitian;SONG Zhengyu(Beijing Institute of Astronautical Systems Engineering,Beijing,100076;China Academy of Launch Vehicle Technology,Beijing,100076)

机构地区：[1]北京宇航系统工程研究所,北京100076 [2]中国运载火箭技术研究院,北京100076

出　　处：《导弹与航天运载技术（中英文）》2023年第2期20-24,共5页Missiles and Space Vehicles

摘　　要：根据长征八号(CZ-8)火箭二级浅箱起动飞行任务剖面的新特点,需要准确预示并控制在微重力、大气枕容积条件下低温贮箱内的压力变化规律。通过建立箭体姿态控制和低温两相流体力热耦合的贮箱压力仿真计算模型,对滑行过程中低温贮箱内推进剂晃动、气液之间的换热和蒸发冷凝过程进行仿真分析,获取了准确的氢箱气枕压力变化规律。同时提出了滑行段低温贮箱压力多专业协同耦合设计和控制方法,支撑了浅箱二次起动任务的顺利实施,并在飞行试验中得到了验证。According to the new characteristics of the shallow propellant condition in upper stage of the LM-8 rocket,it is necessary to accurately predict and control the pressure change law of the cryogenic propellant tank under the conditions of microgravity and large ullage volume.Through establishing the tank pressure simulation model of attitude control and two-phase fluid coupling,the propellant sloshing,heat transfer and evaporation and condensation process in cryogenic tank during coasting-flight are simulated and analyzed.On this basis,the accurate pressure variation law of the ullage is obtained,and the multi discipline coupling design and control method for the pressure of the cryogenic tank in the coasting-flight is proposed.This research supports the implementation of the secondary startup mission with shallow propellant and is verified in the flight.

关 键 词：低温末级 滑行段 推进剂晃动 箱压仿真 

分 类 号：V42[航空宇航科学与技术—飞行器设计]