高超声速机体/推进一体化试验设备概述  

An overview of hypersonic aero-propulsion integration test facilities

作　　者：吴颖川[1] 贺元元[1] 张小庆[1] 毛雄兵[1] WU Yingchuan;HE Yuanyuan;ZHANG Xiaqing;MAO Xiongbing(Science and Technology on Scramjet Laboralory,Hypervelocity Aerodynamics Institute of China Aerodynamics Research&Development Center,Mianyang 621000,China)

机构地区：[1]中国空气动力研究与发展中心高超声速冲压发动机技术重点实验室,绵阳621000

出　　处：《科技导报》2020年第12期96-102,共7页Science & Technology Review

摘　　要：回顾了高超声速推进地面设备及任务的发展历程,明确了设备分类,简述了直连式超声速燃烧试验台、燃烧加热高超声速高温风洞、电弧加热超声速燃烧试验台、高超声速高焓激波试验台、脉冲燃烧风洞等试验设备的原理、主要结构和基本参数。通过对不同设备特点的分析,指出脉冲燃烧风洞是开展高超声速机体/推进一体化试验的理想设备。The history of hypersonic propulsion facilities and tasks are briefly reviewed in this paper,the operating principle,main structures and basic parameters of these reclassified facilities are also surveyed,including direct-connect supersonic combustion test facility,combustion-heated high temperature tunnel,arc-heated scramjet test facility,high enthalpy shockwave facility and combustion-heated impulse tunnel.After an analysis of the characteristics of different facilities,it is pointed out that the combustion-heated impulse tunnel is the ideal facility for aero-propulsion integration test.

关 键 词：高超声速推进设备 机体/推进一体化 脉冲燃烧风洞 

分 类 号：V23[航空宇航科学与技术—航空宇航推进理论与工程] V43