旋翼气动特性分析及直升机配平计算

吕少杰; 魏靖彪; 刘宁; 曹义华

doi:10.13224/j.cnki.jasp.2017.10.022

旋翼气动特性分析及直升机配平计算

doi: 10.13224/j.cnki.jasp.2017.10.022

1.
中国人民解放军陆军航空兵研究所总体论证室,北京 101121
2.
中国人民解放军陆军后勤部战勤计划局，北京 100071
3.
北京航空航天大学航空科学与工程学院,北京 100191

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- 文章访问数: 750
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出版历程
- 收稿日期: 2016-03-14
- 刊出日期: 2017-10-28

Rotor aerodynamic characteristics analysis and helicopter trimming

摘要

摘要: 以UH-60A直升机为例,建立了适合用于准确细致地描述旋翼气动特性和直升机配平的旋翼气动模型。分别将动量理论模型和该旋翼气动模型代入直升机全机飞行动力学模型中，对算例直升机进行了配平，并与试飞数据和参考模型结果进行了对比，验证了该模型有效且精度更好。在此基础上，分析了不同前进比桨盘诱导速度、迎角和升阻比的分布。结果表明：随着前飞速度增加，诱导速度分布更加不对称，桨盘侧倾加剧；大速度前飞时后行桨叶气流分离区域变大，在反流区内外迎角分布将发生突变；由于空气压缩性和反流区作用，大速度前飞时前行桨叶桨尖处与反流区内升阻比较低。
- 直升机飞行力学 /
- 气动特性 /
- 诱导速度 /
- 升阻比 /
- 配平
Abstract: The UH60A rotor aerodynamic model suited to accurately predict the detail of rotor aerodynamic characteristics and helicopter trimming was established. The momentum element theory and the proposed rotor aerodynamic model were respectively embedded into the trimming procedure and applied to trim UH60A helicopter, the comparison among the computational results, test data and the referenced data indicated that the model was effective and more precise. On this basis, the distributions of induced velocity, angle of attack and liftdrag ratio on the rotor disk at various advance ratios were analyzed. The results show that with the increase of the advance ratios, the induced velocity distribution on rotor disk is more asymmetric and the rotor sideward incline is intensified. At high advance ratio, the flow separation region on the retreating blade side becomes large, the angle of attack distribution exhibits rapid change on the boundary of the reverse flow region. Due to effects of air compressibility and the reverse flow region, at high advance ratio, the lift to drag ratio is relatively low in the tip area of the advancing blade and the reverse flow region.
- helicopter flight dynamics /
- aerodynamic characteristics /
- induced velocity /
- liftdrag ratio /
- trim

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参考文献(20)

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