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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。
In this paper, through the design, test and theoretical analysis of a two-component variable thrust liquid rocket motor equipped with an adjustable injector and an adjustable venturi, the pressure P, venturi pressure recovery R, Syringe needle valve displacement h_i, propellant flow rate G and component ratio r, oxygen coefficient α, combustion efficiency c and specific impulse I_s, thrust F, stability, response time t_p with the control voltage signal changes regularity.