摘要
针对吸气式高超声速巡航飞行器超燃冲压发动机的空气流量设计问题,通过受力分析、能量守恒和比冲定义等基本原理,提出了面向总体设计的空气流量数学模型,给出了验证算例并且结合实例从定量和定性角度分别对空气流量进行了对比和分析。研究结果表明,面向总体设计的空气流量数学模型简洁正确可靠;采用碳氢燃料和空中发射所需要的空气流量明显减小;航程和巡航速度对空气流量的影响趋势异步,二者需要最优化折中;巡航飞行时随着飞行器质量的减小,应有适当空气溢流或恰当减小燃烧化学当量比。
With regard to air mass flux characteristic of scramjet for airbreathing hypersonic flight vehicle,mathematical model of design-oriented air mass flux characteristic was derived by means of force analysis,energy conservation principle,specific impulse definition and so on. What＇s more,design-oriented air mass flux characteristic was contrasted and analyzed in combination with instance in terms of quantitative and qualitative analysis. The results show that air mass flux obviously decreases by making use of hydrocarbon fuel and air launch. Variation trend of cruising range was contrary to that of cruising speed,which requires optimization about the both parameters. Air overflow and appropriate equivalent specific fuel consumption were required with mass reduction during cruise flight.
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2014年第3期315-319,共5页
Journal of Solid Rocket Technology
基金
航天技术支撑基金(2013-HT-XGD-014)
