摘要
给出了RBCC发动机推进效率、热效率及总效率等热力/推进效率计算方程,开展了特定条件下油气比、流量比及速度比等因素对发动机效率影响规律研究。结果表明,当燃油和火箭发动机推进剂种类、质量流量及飞行速度一定时,产生推力的RBCC发动机排气速度变化范围有限,且该范围可通过计算进行明确;在其他变量为定值的条件下,推进效率分别随油气比、流量比及速度比的增大呈单调增加的趋势;随着速度比减小,热效率、总效率增大。
According to the principle of rocket based combined cycle （RBCC） engine, the equations about propulsive, thermodynamic and total efficiencies of RBCC engine are presented pertinently in this paper. The factors which affect the efficiency of RBCC engine are discussed, and the influences of fuel/air ratio, velocity ratio and mass flow rate ratio on the engine efficiency under specified conditions have been obtained. The results show that, while the fuel, propellant, mass flow rate and flight speed are certain values, the exhaust velocity of RBCC engine changes only in a limited range which can be calculated. As the values of other variables keep constant, the propulsive efficiency goes up with the increase of fuel/air ratio, velocity ratio, and mass flow rate ratio separately, and thermal efficiency and total efficiency go up with the decrease of velocity ratio.
出处
《火箭推进》
CAS
2016年第6期31-35,共5页
Journal of Rocket Propulsion
基金
国家863项目2012AA7053026
关键词
RBCC发动机
热力/推进效率
计算分析
RBCC engine
thermodynamic/propulsive efficiencies
calculation and analysis
