差动活塞式燃气自增压系统参数设计方法  

Parameter design method on a differential piston warm gas self-pressurization system

作　　者：方忠坚[1] 刘洌 梁国柱[1] FANG Zhongjian LIU Lie LIANG Guozhu(School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100083, China)

机构地区：[1]北京航空航天大学宇航学院,北京100083

出　　处：《北京航空航天大学学报》2017年第1期61-70,共10页Journal of Beijing University of Aeronautics and Astronautics

摘　　要：针对基于单组元肼类物质为工质的液体姿轨控发动机差动活塞式燃气自增压系统,分析了系统的工作原理,提出了系统的参数设计方法,建立了系统的参数设计流程,给出了系统的起动压力计算模型和自锁状态计算方法,并进行了实例研究。结果表明:系统最低起动压力与压力放大贮箱气体腔初始体积、活塞摩擦力和推进剂贮箱初始气垫体积直接相关;系统自锁后,推进剂贮箱压力的设计状态受推进剂贮箱所允许的最大压力上偏差和流量调节器与推进剂贮箱间的压降所约束;推进剂贮箱的工作压力范围是可以根据需要通过燃气自增压系统的设计来保证的。This paper studies the working principle of the differential piston warm gas self-pressurization system of liquid attitude and divert control engines working with monopropellant-hydrazine,based on which a parametric design method and the corresponding design process of the system parameters are presented. New models of the system starting pressure and system self-locking state are also introduced. A case study is carried out and results show that the minimum system starting pressure is directly related to the initial volume of the gas chamber,the friction force of the piston,and the initial volume of the air cushion of the propellant tank;the design state of the propellant tank pressure after the system self-locking is constrained by the upper pressure deviation allowed by the propellant tank and the pressure drop between liquid regulator and propellant tank; the range of working pressure of the propellant tank can be guaranteed by the design of the pressurization system.

关 键 词：差动活塞 燃气自增压系统 液体姿轨控发动机 单组元 参数设计 

分 类 号：V434.23[航空宇航科学与技术—航空宇航推进理论与工程]