期刊文献+

Investigation of dual ignition for a detonation-driven shock tunnel in forward driving mode 被引量:1

原文传递
导出
摘要 A detonation-driven shock tunnel is useful as a ground test facility for hypersonic flow research.The forward detonation driving mode is usually used to achieve high-enthalpy flows due to its strong driving capability.Unfortunately,the strong detonation wave front results in diaphragm fragments that disturb the test flow and scratch the nozzle or test models.In this study,a dual ignition system was developed to burst a metal diaphragm without fragmentation in the forward driving mode.A series of experiments were conducted to validate the proposed technique.The influences of the delay time setting on the test conditions were investigated in detail.Numerical simulations were also conducted to obtain a better understanding of the wave processes in the shock tube.The results showed that the dual ignition system solved the diaphragm issues in the forward driving mode.The test time was shortened due to the additional ignition close to the primary diaphragm;the smaller the delay time,the shorter the effective test time.However,a small amount of time loss is considered worthwhile because the severe diaphragm problems have been solved.
出处 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2020年第5期1468-1475,共8页 中国航空学报(英文版)
基金 supported by the National Natural Science Foundation of China (Nos. 11402275,11727901 and 11472280)
  • 相关文献

参考文献4

二级参考文献19

  • 1罗也凡,毕志献.脉冲型风洞用加速度计测力天平[J].气动实验与测量控制,1996,10(1):59-64. 被引量:4
  • 2Sasoh A, Morgan R G, Littleton B N, et al. High-enthalpy expansion tube experiments with gas injection, AIAA J, 2000, 38:2253-2259.
  • 3Neely A J, Stalker R J, Paull A. High enthalpy hypervelocity flows of air and argon in an expansion tube. Aeronaut J, 1991, 95:175-186.
  • 4Resler E L, Bloxsom D E. Very High Mach Number Flows by Un- steady Flows Principles. Graduate School of Aeronautical Engineer-ing, Cornell University, limited circulation monograph, 1952.
  • 5Trimpi R L. A preliminary theoretical study of the expansion tube: A new device for producing high-enthalpy short duration hypersonic gas flows. NASA Technical Report TR-133. 1962.
  • 6Jiang Z, Zhao W, Wang C, et al. Study on forward detonation driver for high enthalpy shock tunnels. AIAA J, 2002, 40:2009-2016.
  • 7Bird G A. A note on combustion driven tubes. Royal Aircraft Estab- lishment, AGARD Report 146. 1957.
  • 8Yu H R, Esser, B, Lenartz M, et al. Gaseous detonation driver for a shock tunnel. Shock Waves, 1992, 2:245-254.
  • 9Zhao W, Jiang Z, Saito T, et al. Performance of a detonation driven shock tunnel. Shock Waves, 2005, 14:53-59.
  • 10Yu H R, Chen H, Zhao W. Advances in detonation driving tech- niques for a shock tube/tunnel. Shock Waves, 2006, 15:399405.

共引文献23

同被引文献5

引证文献1

二级引证文献5

相关作者

内容加载中请稍等...

相关机构

内容加载中请稍等...

相关主题

内容加载中请稍等...

浏览历史

内容加载中请稍等...
;
使用帮助 返回顶部