飞机过冷大水滴结冰探测器设计及试验  

Design and experiment of aircraft SLD icing detector

作　　者：周灿[1] 葛俊锋[1] 叶林[1] 许一飞[1] 邹建红[1] 

机构地区：[1]华中科技大学自动化学院,武汉430074

出　　处：《仪器仪表学报》2013年第10期2213-2218,共6页Chinese Journal of Scientific Instrument

基　　金：国家自然科学基金与中国民用航空局联合资助项目(60939001);国家自然科学基金(61104202)资助项目

摘　　要：为捕获飞机过冷大水滴(SLD)结冰,设计了一种由前梭、凹槽和后梭连接而组成的SLD探测器。通过对该探测器几何结构的参数化、FENSAP-ICE软件的结冰数值模拟和结冰试验验证,确定了该探测器较优的结构参数。在常规的液滴下,SLD探测器的前梭结冰而后梭不结冰;在SLD下,探测器的前梭、后梭均结冰,据此可捕捉和区分SLD结冰。作为关键技术之一,该SLD探测器的设计有利于解决飞机SLD结冰探测难题。To capture aircraft supercooled large droplet （SLD） ic.ing, a SLD detector was designed, whic.h mainly con- sists of a front-shuttle, a back-shuttle and a groove connecting them. The geometric structure of the detector is param- eterized,the icing numerical simulation is performed with FENSAP-ICE software and the icing test verifieation is car- tied out ; and the better structure parameters of the detector are determined. For the normal droplets, the ice would ac- crete on the front-shuttle rather than on the back-shuttle. For the SLDs,however, the ice would accrete on both shut- ties,which could be used to capture and identify SLD icing. As a critieal technique,the design of the SLD detector will benefit to solve the difficulty of aircraft icing detection under the SLD environment.

关 键 词：飞机结冰探测 SLD结冰探测器 参数化设计 数值模拟 

分 类 号：V248.1[航空宇航科学与技术—飞行器设计]