摘要
本文通过对装有可调喷注器和可调汽蚀文氏管的双组元变推力液体火箭发动机的设计,试验和理论分析,给出了压力P,文氏管压力恢复比R,喷注器针阀位移h_i,推进剂秒流量G和组元比r,余氧系数α,燃烧效率c及比冲I_s,推力F,稳定性,响应时间t_p等随控制电压信号改变的规律性。
A bipropellant throttling liquid rocket engine with controllable injector and throttling cavitating venturi has been designed,tested and analyzed.In result the relationships of pressure, pressure recovery coefficient of venturi, stroke of injector pintle, propellant flow rate and mixture ratio, combustion efficiency, specific impulse, thrust, stability and response time to control voltage signal are obtained and the corresponding plots and data are also presented.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
1989年第1期45-49,共5页
Journal of Aerospace Power
