小推力推进系统启动过程仿真分析  

Simulation Analysis on Start Process of Low-thrust Propulsion System

作　　者：杨林涛 沈赤兵[1] Yang Lin-tao;Shen Chi-bing(Science and Technology on Scramjet Laboratory,College of Aerospace Science,National University of Defense Technology,Changsha,410073)

机构地区：[1]国防科技大学空天科学学院高超声速冲压发动机技术重点实验室

出　　处：《导弹与航天运载技术》2019年第5期48-52,共5页Missiles and Space Vehicles

基　　金：国家自然科学基金(11572346)

摘　　要：针对多台推力器启动耦合对响应特性的不利影响,采用AMESim仿真软件建立小推力推进系统仿真模型,仿真分析了工作时序对多台推力器启动过程响应特性的影响,并分析了室压超调量和响应时间的变化规律。结果表明:多台推力器同时启动,会延长系统响应时间,增大室压超调量,对系统工作产生不利影响;燃料管路响应快,但流量超调量较大,不利于流量快速稳定;氧化剂管路流量波动剧烈,需要更长的时间达到稳定;合理地选取启动间隔时间,能有效降低多台推力器启动耦合作用,提升系统启动过程快速响应能力。In view of the adverse effects of the coupling of multiple thrusters on the response characteristics, the simulation model of low-thrust propulsion system is built based on AMESim simulation software. The influence of working timing on the response characteristics of multiple thrusters is analyzed, and the changes of chamber pressure overshoot and response time are analyzed. The results show that the simultaneous activation of multiple thrusters will prolong the response time of the system and increase the overshoot of the chamber pressure, which will adversely affect the work of the system. The fuel line responds quickly, but the flow overshoot is large, which is not conducive to the fast and stable flow. The flow of the oxidant pipeline fluctuates violently and takes a longer time to achieve stability. A reasonable selection of starting interval time can effectively reduce the coupling effect of multiple thrusters and improve the quick response ability of the system during start process.

关 键 词：液体火箭发动机 小推力推进系统 启动过程 响应特性 

分 类 号：V434[航空宇航科学与技术—航空宇航推进理论与工程]