| 双转子涡喷发动机吞吸导弹喷流飞行模拟试验 |
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| 引用本文： | 左汉中.双转子涡喷发动机吞吸导弹喷流飞行模拟试验[J].航空学报,1987,8(8):436-440. |
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| 作者姓名： | 左汉中 |
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| 作者单位： | 飞机试验研究中心 |
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| 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。
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| 收稿时间： | 1986-08-07; |
THE FLIGHT TEST OF TWIN-SPOOL TURBOJET ENGINE SIMULATING THE INGESTION OF MISSILE EXHAUST |
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| Zuo Hanzhong.THE FLIGHT TEST OF TWIN-SPOOL TURBOJET ENGINE SIMULATING THE INGESTION OF MISSILE EXHAUST[J].Acta Aeronautica et Astronautica Sinica,1987,8(8):436-440. |
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| Authors: | Zuo Hanzhong |
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| Institution: | China Flight Test Research Centre |
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| 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. |
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