航空学报 > 1987, Vol. 8 Issue (8): 436-440

双转子涡喷发动机吞吸导弹喷流飞行模拟试验

左汉中   

  1. 飞机试验研究中心
  • 收稿日期:1986-08-07 修回日期:1900-01-01 出版日期:1987-08-25 发布日期:1987-08-25

THE FLIGHT TEST OF TWIN-SPOOL TURBOJET ENGINE SIMULATING THE INGESTION OF MISSILE EXHAUST

Zuo Hanzhong   

  1. China Flight Test Research Centre
  • Received:1986-08-07 Revised:1900-01-01 Online:1987-08-25 Published:1987-08-25

摘要: 一、前言 空空导弹发射,特别是半主动制导型导弹发射,要求载机跟踪目标一段距离。因此载机的发动机常常不可避免的要吸入导弹喷流废气,从而影响发动机稳定工作,严重时引起发动机喘振停车。这不仅贻误战机,危及安全,而且也使新机设计武器布局变得难以进行,因此研究解决这一问题具有重要的现实意义。

Abstract: This paper introduces briefly simulating method of the ingestion of missile exhaust and simulating transient temperature field feature.Also the paper discussed the response of twin-spool turbojet engine to temperature transients.The inlet temperature rise rate was from 2500℃ per second to 7500℃. per second.The test were conducted at engine military and rated condition.