碳氢燃料超燃冲压发动机燃烧室控制试验  

Experimental on control of liquid hydrocarbon fueled scramjet combustor

作　　者：吴先宇[1] 陈晖[1] 刘睿[1] 丁猛[1] 王振国[1] 

机构地区：[1]国防科技大学航天与材料工程学院,长沙410073

出　　处：《航空动力学报》2008年第8期1541-1545,共5页Journal of Aerospace Power

摘　　要：设计了超燃冲压发动机燃烧室控制回路,采用基于可调气蚀文氏管的燃料流量调节系统动态调节燃料流量,根据反馈的推力和隔离段压强等测量数据进行燃烧室推力增益控制和燃烧室-隔离段干扰控制,并在直连式超燃冲压发动机试验系统上进行了推力单水平控制试验和推力多水平/燃烧室-隔离段交互控制试验.试验表明:燃料流量调节系统工作稳定,文氏管按指令行程作动,流量调节过程清晰;测量推力随流量变化基本上同步变化;对目标推力增益和燃烧室-隔离段交互的控制有效,并为进一步深入研究超燃冲压发动机燃烧室控制问题奠定了基础.The control loop of scramjet combustor was designed to control the thrust force increment and combustor-isolator interaction （CII） by feedback of force and isolator pressure measurements, where the fuel mass flow was regulated by fuel mass flow control system based on controllable cavitating Venturi. On the direct-connect test System, two ex- periments were conducted to implement single level thrust force control and multi-level thrust force/CII control, respectively. The test results show that： the fuel mass flow control system works reliably with fuel regulated accurately by directed movement of Venturi; the thrust force varies with fuel mass flow almost synchronously; and the thrust force increment and CII are controlled efficiently. This work lays a foundation for further study of scramjet combustor control.

关 键 词：超燃冲压发动机 燃烧室 控制 直连式试验 

分 类 号：V434[航空宇航科学与技术—航空宇航推进理论与工程]