| 悬停状态共轴双旋翼桨叶扭转气动特性 |
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| 引用本文： | 邵伟平,何敏桃,郝永平.悬停状态共轴双旋翼桨叶扭转气动特性[J].航空动力学报,2014,29(11):2606-2612. |
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| 作者姓名： | 邵伟平 何敏桃 郝永平 |
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| 作者单位： | 沈阳理工大学 机械工程学院 辽宁省先进制造与装备重点实验室, 沈阳 110159;沈阳理工大学 机械工程学院 辽宁省先进制造与装备重点实验室, 沈阳 110159;沈阳理工大学 机械工程学院 辽宁省先进制造与装备重点实验室, 沈阳 110159 |
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| 基金项目： | 国家自然科学基金(50975183) |
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| 摘 要： | 针对桨叶气动性能的提高,建立了一套基于悬停状态的共轴双旋翼桨叶扭转设计方法.在该方法中,设定单旋翼桨叶扭转几何安装角,通过仿真验证,合理的桨叶扭转,可提高旋翼性能7.0%;根据桨尖涡对桨叶的影响,以及共轴双旋翼气动特性,分别对桨尖几何安装角及上下旋翼几何安装角进行修正,实现悬停状态共轴双旋翼桨叶扭转设计.最后,对所设计的共轴双旋翼进行模拟仿真,结果表明该扭转翼较未经扭转的矩形翼升力提高了10.3%.
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| 关 键 词： | 悬停 桨叶扭转 诱导速度 迎角 几何安装角 |
| 收稿时间： | 2013/7/15 0:00:00 |
Blade-twist aerodynamic characteristics of coaxial rotors in hover |
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| SHAO Wei-ping,HE Min-tao and HAO Yong-ping.Blade-twist aerodynamic characteristics of coaxial rotors in hover[J].Journal of Aerospace Power,2014,29(11):2606-2612. |
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| Authors: | SHAO Wei-ping HE Min-tao and HAO Yong-ping |
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| Affiliation: | Key Laboratory Advanced Manufacture and Equipment of Liaoning Province, School of Mechanical Engineering, Shenyang Ligong University, Shenyang 110159, China;Key Laboratory Advanced Manufacture and Equipment of Liaoning Province, School of Mechanical Engineering, Shenyang Ligong University, Shenyang 110159, China;Key Laboratory Advanced Manufacture and Equipment of Liaoning Province, School of Mechanical Engineering, Shenyang Ligong University, Shenyang 110159, China |
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| Abstract: | To meet the improvement of blade aerodynamic performance, blade-twist of coaxial rotors in hover design method was proposed.In this method, geometric installation angle was set for single rotor blade-twist, and the simulation results show reasonable blade-twist design can improve the rotor performance by 7.0%.In order to achieve hover coaxial rotor blade-twist design, the installation angle of upper and lower blade tips and rotors must be corrected, according to the blade tip vortex's impact, as well as coaxial rotor aerodynamic characteristics. Finally, the simulation results of coaxial rotors method show wing-twist lift is increased by 10.3% than that without twist of rectangular wing. |
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| Keywords: | hover blade-twist induced velocity angle of attack geometric installation angle |
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