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多推力室的气动谐振点火器研究 被引量:8

Research on gas dynamic resonance igniters of multithruster
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摘要 为了满足多推力室多次同步点火的需要,通过大量的空气气动谐振加热实验和理论分析,研制了两种利用气动谐振点火技术的多推力室点火器,即多管点火器和小点火器,给出了这两种点火器的系统结构、试验参数以及部分试验结果。这两种点火器都能在1秒内提供不同流量的火焰燃气,分别适用于较小推力室和较大推力室的点火。在实验室中进行的多次点火试验结果表明,这两种点火器都可以可靠地进行海平面上多推力室的多次同步点火。 To realize the multi-thruster ignition, two methods based on the gas dynamic resonance heating technology were presented. Based on numerous air resonance heating experiments and analytical work, two kinds of igniters (multi-tube igniter and small igniter) were developed and tested successfully. The system structure, experimental parameters and results were presented. The former can be fixed to smaller thrusters easily, and the latter can provide larger flame gas flux and ignite normal thrusters. Both were able to perform repetitious multi-thruster ignition simultaneously and reliably in one second at sea level.
出处 《推进技术》 EI CAS CSCD 北大核心 2002年第5期402-405,共4页 Journal of Propulsion Technology
基金 国家"八六三"基金资助项目(863 2 3 4 10) 航天科技创新基金2000年资助项目
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  • 1梁国柱.气动谐振管加热现象及其应用研究:博士学位论文[M].,2000.17-20.
  • 2北航宇航学院.气动谐振点火器研究总结报告[M].,1999..
  • 3梁国柱,博士学位论文,2000年,17页
  • 4北航宇航学院,气动谐振点火器研究总结报告,1999年
  • 5Hasen G A. Navier-Stokes solutions for an axisymmetric nozzle [R]. AIAA 81-1474R.
  • 6Lakshmanan B, Tiwari S N. Investigation of three-dimensional separation at wing/body junctions in supersonic flows using TVD MacCormack' s scheme[ R] . AIAA 93-0884.
  • 7Thomas P D, Middlecoff J F. Direct control of the grid distribution in meshes generated by elliptic equations[ J]. 4IAA J., 1980, 18(6).
  • 8Grau J C, Koenig W H. Temperature and pressure fluctuations in a resonance tube[R]. AIAA 80-0863.
  • 9梁国柱,张国舟,程显辰,马彬,张振鹏.液体火箭发动机气动谐振点火初步研究[J].推进技术,1999,20(4):13-16. 被引量:8
  • 10梁国柱,张振鹏,张国舟,程显辰.气动谐振管加热机理数值研究[J].北京航空航天大学学报,1999,25(6):692-695. 被引量:6

共引文献19

同被引文献39

  • 1郭红杰,梁国柱,马彬,张振鹏.爆震波点火技术基本特性实验[J].推进技术,2005,26(1):76-79. 被引量:9
  • 2宋雅娜,张国舟,周文禄,黄翔.新颖机动变轨化学火箭发动机头部研究[J].北京航空航天大学学报,2005,31(8):888-892. 被引量:2
  • 3童晓艳.[D].北京:北京航空航天大学,2002.
  • 4Zurawski R L, Green J M. Catalytic ignition of hydrogen and oxygen propellants[R]. AIAA-88-3300,1988
  • 5Fuller P N. Advanced ignition systems final report [R]. NASA N71-35152, NASA-CR-119928,1971
  • 6Immich H, Caporicci M. Status of the FESTIP rocket propulsion technology programme [R]. AIAA-97-3311,1997
  • 7Stabinsky L. Analytical and experimental study of resonance ignition tubes[R]. NASA N74-17646,1973
  • 8Bollinger L, Fong M, Edse R. Experimental measurements and theoretical analysis of detonation induction distances[J]. ARS Journal, 1961,31(5):588-595
  • 9Liou L C. Combustion-wave ignition for rocket engines[R]. NASA 92-20043,1992
  • 10Lockheed Martin. Allied Signal Aerospace, Rocketdyne. X-33 Phase II annual performance report[R]. NASA-CR-205695,1997

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