膨胀循环液体火箭发动机推力调节阀仿真研究  

Simulation of thrust regulating valve of expansion cycle liquid rocket engine

作　　者：付军锋[1] 赵凤红[1] 

机构地区：[1]北京航天动力研究所,北京100076

出　　处：《火箭推进》2013年第6期12-18,59,共8页Journal of Rocket Propulsion

基　　金：中国航天科技集团公司支撑项目(2011JY01)

摘　　要：根据某膨胀循环液体火箭发动机推力调节阀的结构及工作原理,通过理论分析建立了推力调节阀的数学模型,并利用AMEsim软件构建了推力调节阀的仿真计算模型,对其进行了仿真计算。计算了发动机额定工况、高工况和低工况参数下推力调节阀内部各压力及流量参数,并对推力室室压、调节阀出口压力和氢主文氏管入口压力变化引起的调节阀主阀流量变化趋势进行了计算分析,得到了调节阀内部各压力参数及流量的变化规律。Based on the structure and principle of thrust regulating valve of an expansion cycle liquid rocket engine, the mathematic model was established through theoretical analyze. The numeri-cal simulation model of thrust regulating valve was built with AMEsim software. The pressure and flow parameters of the thrust regulating valve were calculated under normal working condition, high working condition and low working condition of liquid rocket engine. The flow change trend of main valve in the regulating valve, caused by the change of the pressure in thrust chamber, outlet pressure of thrust regulating valve and inlet pressure of hydrogen main cavitation venturi, was calculated and analyzed. The pressure parameters and flow change law in the regulating valve were obtained. The simulation result is helpful for optimization design of the thrust regulating valve.

关 键 词：液体火箭发动机 推力调节阀 AMESIM 仿真 

分 类 号：V432-34[航空宇航科学与技术—航空宇航推进理论与工程]