旋翼桨叶结冰对直升机飞行性能的影响

Effects of rotor blade icing on helicopter flight performance

采用由翼型冰风洞试验推导而来的工程公式,将旋翼结冰模型嵌入离散格式的旋翼气动模型,分别计算结冰后每个桨盘网格区域的翼型升、阻力系数的增量和挥舞系数的增量,建立了结冰后的UH-60A直升机飞行力学模型.结合发动机功率数据,通过改变结冰条件,研究了不同结冰参数对最大平飞速度、最大垂直爬升率和最大爬升率的影响.结果表明:在环境温度为0^-10℃时,降低环境温度会严重降低飞行性能;液态水含量对所选性能指标有一定影响;水滴直径对最大平飞速度的影响较小,对爬升性能的影响可忽略不计;飞行性能指标随结冰时间呈线性下降趋势.

Based on the rotor icing tunnel derivation formula,and combining with the rotor icing model and discrete rotor aerodynamics model,the lift force,drag force and flapping incremental coefficient of each rotor disk area were calculated,the UH-60 Ahelicopter nonlinear flight dynamics model in icing condition was established.Combined with the engine power data,the effect of icing-related variables on the maximum level flight speed,maximum vertical climb rate and the maximum climb rate were studied in detail by changing the icing conditions.Results show that,when the atmospheric temperature is between 0℃and-10℃,lowering atmospheric temperature can severely degrade the flight performance;liquid water content has a certain influence on the selected performance indexes;median volumetric diameter has little effect on the maximum level flight speed,and the impact on climb performance can be neglected;the flight performance indexes linearly decline with icing time.