一种用于模拟侧滑角影响的限流喷管设计  

Design of Restrict Flow Nozzle for Simulating Influence of Sideslip Angle

作　　者：李前虎[1] 李纲[1] 王国锐[1] 

机构地区：[1]中国空空导弹研究院,河南洛阳471009

出　　处：《航空兵器》2014年第1期44-47,共4页Aero Weaponry

摘　　要：为研究侧滑对双下侧进气固冲发动机性能的影响,可在连管试验系统上通过使用一系列不同喉径的限流喷管来改变固冲发动机左右进气道流量,从而近似模拟侧滑时的进气状态。本文详细论述了这种限流喷管设计过程,并通过阿牛巴流量计对限流喷管实际流量进行了标定。结果表明,限流喷管的设计方法正确,使用该方法可以改变发动机左右进气道流量。In order to study the influence of sideslip on the solid rocket ramjet motor , a series of dif-ferent throat dimension restrict flow nozzles can be used on direct -connect test system to change gas flow of each air inlet and simulate the inlet status approximately .How to design the restrict flow nozzle is dis-cussed in detail in this paper, and it has been calibrated by Annubar flowmeter in the actual airflow .The results show that the method of designing restrict flow nozzle is correct , and it can change right and left in-let flow of motor.

关 键 词：固冲发动机 侧滑角 限流喷管 连管试验 

分 类 号：V435.11[航空宇航科学与技术—航空宇航推进理论与工程]