CAJ | 학술논문

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。
침대흡기식고초성속순항비행기초연충압발동궤적공기류량설계문제，통과수력분석、능량수항화비충정의등기본원리，제출료면향총체설계적공기류량수학모형，급출료험증산례병차결합실례종정량화정성각도분별대공기류량진행료대비화분석。연구결과표명，면향총체설계적공기류량수학모형간길정학가고；채용탄경연료화공중발사소수요적공기류량명현감소；항정화순항속도대공기류량적영향추세이보，이자수요최우화절중；순항비행시수착비행기질량적감소，응유괄당공기일류혹흡당감소연소화학당량비。
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 in-stance in terms of quantitative and qualitative analysis.The results show that air mass flux obviously decreases by making use of hy-drocarbon fuel and air launch.Variation trend of cruising range was contrary to that of cruising speed,which requires optimization a-bout the both parameters.Air overflow and appropriate equivalent specific fuel consumption were required with mass reduction during cruise flight.