直升机防除冰系统人工结冰试验

为掌握结冰条件下直升机旋翼、发动机、进气道防除冰系统的性能规律，在不同液态水含量和大气温度下，开展了地面和悬停两种状态直升机人工结冰试验，研究旋翼、发动机、进气道防除冰系统在结冰环境中的相互影响。研究发现:受旋翼旋转影响，右发进气道较左发更容易结冰；发动机低功率状态下，防冰性能较差，状态升高后，防冰性能改善；旋翼结冰导致发动机状态升高，使进气道表面温度较无结冰时仍有上升。同时，旋翼上周期性的"结冰-脱除"，导致发动机参数振荡，振荡周期受环境条件影响不大，而振幅与液态水含量近似呈线性关系。

Artificial icing tests of the helicopter anti-icing system

In order grasp the working characteristics of anti-icing systems of the helicopter rotor, the turboshaft engine and the inlet under icing conditions, the helicopter artificial icing tests were conducted. The icing tests were conducted in different liquid water contents, at different temperatures, and under both ground and hovering conditions. The interaction between the rotor, the engine and the inlet anti-icing systems was studied. It is found that the right inlet ices easier than the left side due to rotor rotating. The inlet has a poor anti-icing performance when the engine works under low power condition, and its performance improves when the engine power rises. The engine power condition rises after rotor icing, leading to a higher inlet temperature than that in the dry air. The periodical icing-shedding on the rotor results in an engine parameter fluctuation. The fluctuation period is hardly affected by the environmental condition, while the fluctuation amplitude changes linearly with the liquid water content.