气动除冰飞机结冰风洞试验技术

Icing wind tunnel test technology for pneumatic de-icing aircraft

民用飞机为获得型号合格证,应按照有关结冰适航规章条款进行结冰适航验证,结冰风洞试验是获取临界冰形的有效途径。本文以Y12F飞机结冰风洞试验实际工程过程为例,总结与分析了气动除冰飞机结冰风洞试验的模型设计、气动除冰套模拟、试验状态转换、试验流程、冰形测量等关键技术,并给出代表性试验结果。试验结果表明:在典型最大结冰条件下,除冰套工作正常,除冰套循环工作期间正常除冰;除冰套工作间歇,机翼前缘结冰表现为前缘形成较为光滑、厚度约为5～6mm的冰帽,上翼面产生1道高度为3～4mm的冰脊,下翼面形成3道2～4mm的冰脊。

Civil aircraft should conduct icing airworthiness certification according to relevant icing airworthiness regulation requirements in order to obtain the type certificate,and icing wind tunnel test is the effective way to get the critical ice shape. Based on an engineering application of icing wind tunnel test for the Y12F aircraft, test techniques are summarized and analyzed, such as the test model design, simulation of the pneumatic de-icing system, test status transformation, test process, ice shape measurement and so on. A typical test result is represented in the end, which indicates that the pneumatic de-icing system could run effectively under the typical maximum icing condition, and ice could be removed during the work cycle of the system. There would be ice accretion during the interval of system running. Ice formed at the leading edge is always smooth, and the thickness of the ice is from 5 to 6mm. There is an obvious ice ridge about 3 to 4mm thick on the upper surface, and three ice ridges about 2 to 4mm thick accrete on the lower surface.