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Dynamic Characteristics of Combustion Mode Transitions in a Strut-Based Scramjet Combustor Model

机译：基于Strut的Scramjet燃烧器模型中燃烧模式转变的动态特性

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摘要

This note presents the first results of the dynamic characteristics of combustion mode transition in a liquid-fueled strut-based scramjet combustor to support real hypersonic flight dynamics and control system design. Combustion experiments were performed under the incoming airflow conditions P_0 = 1.97 MPa, T_0 = 1590 K, and inflow Mach number = 2.5.
机译：本说明介绍了在基于液体的基于支撑的超燃冲压燃烧器中燃烧模式转变的动态特性的初步结果，以支持实际的超音速飞行动力学和控制系统设计。在进入的气流条件P_0 = 1.97 MPa，T_0 = 1590 K和流入马赫数= 2.5的条件下进行燃烧实验。

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  • 来源
    《Journal of propulsion and power》 |2013年第5期|1244-1248|共5页
  • 作者

    Wen Bao; Qingchun Yang; Juntao Chang; Youhai Zong; Jichao Hu;

  • 作者单位

    Harbin Institute of Technology, Heilongjiang 150001, People's Republic of China College of Astronautics Youyi Xilu 127;

    Harbin Institute of Technology, Heilongjiang 150001, People's Republic of China College of Astronautics Youyi Xilu 127;

    Harbin Institute of Technology, Heilongjiang 150001, People's Republic of China College of Astronautics Youyi Xilu 127;

    Harbin Institute of Technology, Heilongjiang 150001, People's Republic of China College of Astronautics Youyi Xilu 127;

    Harbin Institute of Technology, Heilongjiang 150001, People's Republic of China College of Astronautics Youyi Xilu 127;

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