航空学报 > 2007, Vol. 28 Issue (增): 35-41

超燃冲压发动机性能的初步分析

郑小梅,徐大军,蔡国飙   

  1. 北京航空航天大学 宇航学院
  • 收稿日期:2006-11-15 修回日期:2007-07-06 出版日期:2007-08-10 发布日期:2007-08-10
  • 通讯作者: 郑小梅

A Preliminary Study on Hypersonic Airbreathing Engine Performance

ZHENG Xiao-mei,XU Da-jun, CAI Guo-biao   

  1. School of Astronautics, Beiing University of Aeronautics and Astronautics
  • Received:2006-11-15 Revised:2007-07-06 Online:2007-08-10 Published:2007-08-10
  • Contact: ZHENG Xiaomei

摘要:

超燃冲压发动机是发展高超声速技术的关键,以其为动力装置的高超声速巡航导弹、高超声速飞机和空天飞机对于国防安全、未来空间作战和航天运输都有重要意义。用热力循环的方法对超燃冲压发动机的性能作了初步的分析,建立了超燃冲压发动机准一维性能计算分析模型,并分析了一些影响参数对发动机效率的影响。准一维的性能计算方法可作为多层次高超声速动力推进系统性能计算模型的第一层次的计算模型,具有简单、快捷的特点。影响参数的分析可应用于高超声速飞行器概念设计阶段飞行器主要的设计参数和飞行参数的计算和确定。

关键词: 高超声速飞行器, 超燃冲压发动机, 性能分析, 准一维

Abstract:

Scramjet is a key technology in developing the hypersonic vehicle. Hypersonic missiles, aircraft and aerospace plane are based on scramjet and significantly important to future space battle and transportation. Thermodynamic cycle efficiency of hypersonic airbreathing engine is analyzed using thermal engine closed cycle analysis, a quasi onedimensional performance calculation model of hypersonic airbreathing engines is developed by onedimensional flow approaches using the entire set of control volume conservation equations, and the influence of some potentially important parameters are analyzed. 

Key words: hypersonic , vehicle,  , scramjet,  , performance , calculation,  , quasi , onedimensional

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