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基于硅化合物改性聚氨酯涂层的NACA0012飞机机翼结冰风洞试验研究

A Wind Tunnel Experimental Study of Icing on NACA0012 Aircraft Airfoil with Silicon Compounds Modified Polyurethane Coatings.

作者信息

Przybyszewski Bartlomiej, Kozera Rafal, Krawczyk Zuzanna D, Boczkowska Anna, Dolatabadi Ali, Amer Adham, Sztorch Bogna, Przekop Robert E

机构信息

Faculty of Materials Science and Engineering, Warsaw University of Technology, 141 Woloska Str., 02-507 Warsaw, Poland.

Technology Partners Foundation, 5A Pawinskiego Str., 02-106 Warsaw, Poland.

出版信息

Materials (Basel). 2021 Sep 29;14(19):5687. doi: 10.3390/ma14195687.

DOI:10.3390/ma14195687
PMID:34640083
原文链接:https://pmc.ncbi.nlm.nih.gov/articles/PMC8510011/
Abstract

Ice formation on the aerodynamic surfaces of an aircraft is regarded as a major problem in the aerospace industry. Ice accumulation may damage parts, sensors and controllers and alter the aerodynamics of the airplane, leading to a range of undesired consequences, including flight delays, emergency landings, damaged parts and increased energy consumption. There are various approaches to reducing ice accretion, one of them being the application of icephobic coatings. In this work, commercially available polyurethane-based coatings were modified and deposited on NACA 0012 aircraft airfoils. A hybrid modification of polyurethane (PUR) topcoats was adopted by the addition of nanosilica and three-functional spherosilicates (a variety of silsesqioxane compound), which owe their unique properties to the presence of three different groups. The ice accretion on the manufactured nanocomposites was determined in an icing wind tunnel. The tests were performed under three different icing conditions: glaze ice, rime ice and mixed ice. Furthermore, the surface topography and wetting behavior (static contact angle and contact angle hysteresis) were investigated. It was found that the anti-icing properties of polyurethane nanocomposite coatings strongly depend on the icing conditions under which they are tested. Moreover, the addition of nanosilica and spherosilicates enabled the reduction of accreted ice by 65% in comparison to the neat topcoat.

摘要

飞机气动表面结冰被视为航空航天工业中的一个重大问题。积冰可能会损坏部件、传感器和控制器,并改变飞机的空气动力学性能,导致一系列不良后果,包括航班延误、紧急降落、部件损坏和能耗增加。有多种减少积冰的方法,其中之一是应用疏冰涂层。在这项工作中,对市售的聚氨酯基涂层进行了改性,并将其沉积在NACA 0012飞机机翼上。通过添加纳米二氧化硅和三官能球形硅酸盐(一种倍半硅氧烷化合物)对聚氨酯(PUR)面漆进行了混合改性,这三种不同的基团赋予了它们独特的性能。在结冰风洞中测定了所制备的纳米复合材料上的积冰情况。测试在三种不同的结冰条件下进行: glaze ice、rime ice和mixed ice。此外,还研究了表面形貌和润湿行为(静态接触角和接触角滞后)。结果发现,聚氨酯纳米复合涂层的防冰性能在很大程度上取决于测试时的结冰条件。此外,与纯面漆相比,添加纳米二氧化硅和球形硅酸盐可使积冰减少65%。

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