为了掌握航空发动机进口支板表面的冰层生长机理和结冰规律，本文采用循环式低温风洞模拟高空结冰环境，并对 3 种不同复合材料支板 - 支板 A( 复合材料 + 金属包边 ) 、支板 B( 复合材料 + 涂层 ) 和支板 C( 蜂窝复合材料 + 涂层+ 气膜孔及沟槽 ) 进行结冰试验。 结果表明，支板表面的结冰宏观过程可分解为液态水滴撞击支板表面而发生的吸附、流动、冻结过程，这个过程受到液态水含量、平均水滴直径、来流速度、温度、持续时间的影响。 在一定温度和持续时间下，积冰种类会随来流速度的增大和平均水直径减小，逐渐由明冰向霜冰转变。 结冰量和脱落周期随气量和来流速度的增大而减小，但气量达到一定程度后不会再影响积冰的脱落尺寸。 综合比较，支板 C 在模拟的两种发动机典型状态慢车、中间推力下防冰效果最佳。 试验结果为发动机进口支板防冰设计提供一定的参考，并为飞机防除冰甚至空气系统优化提供较为翔实的理论支持。

To understand the mechanism of ice layer growth and icing patterns on the surface of an aircraft engine inlet support plate, this paper used a cyclic low-temperature wind tunnel to simulate a high-altitude icing environment and conducted icing tests on three different composite material support plates: support plate A (composite material+metal edge), support plate B (composite material+coating), and support plate C (honeycomb composite material+coating+gas film holes and grooves). The test results show that the macro process of icing on the support plate surface can be divided into the adsorption, flow and freezing process of liquid water droplets hitting the support plate surface, which is affected by the liquid water content, average water droplet diameter, incoming flow velocity, temperature and duration. At a certain temperature and duration, the type of ice accumulation will gradually transition from clear ice to frost ice as the inflow velocity increases and the average water diameter decreases. The amount of ice formation and the detachment period decrease with increasing air volume and inflow velocity, but the detachment size of ice formation will not be affected after the air volume reaches a certain level. Overall, support plate C has the best anti-icing effect under the simulated two typical engine states of idle and intermediate thrust. The test results provide a reference for the anti icing design of the engine inlet support plate and provide detailed theoretical support for aircraft anti-icing and even air system optimization.