| 直升机模型桨叶颤振试验研究 |
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| 引用本文： | 夏品奇,徐桂祺.直升机模型桨叶颤振试验研究[J].航空动力学报,1997,12(1):6-8,103. |
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| 作者姓名： | 夏品奇 徐桂祺 |
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| 作者单位： | 南京航空航天大学 |
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| 基金项目： | “八五”直升机关键技术预研项目 |
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| 摘 要： | 提出了直升机模型桨叶颤振试验技术及试验方法。通过激桨叶的扭转频率、测桨叶的挥舞响应，试验得到了桨叶颤振裕度与旋翼转速、桨叶弦向有效重心位置及桨叶扭转刚度之间的关系，即桨叶颤振裕度随旋翼转速的提高而降低；在相同转速下，桨叶扭转刚度越低或桨叶弦向有效重心位置越后，桨叶颤振裕度越小
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| 关 键 词： | 螺旋桨桨叶 颤振试验 模型试验 |
| 收稿时间： | 2/1/1996 12:00:00 AM |
| 修稿时间： | 4/1/1996 12:00:00 AM |
AN EXPERIMENTAL INVESTIGATION ON FLUTTER OF A HELICOPTER BLADE MODEL |
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| Xia Pinqi and Xu Guiqi.AN EXPERIMENTAL INVESTIGATION ON FLUTTER OF A HELICOPTER BLADE MODEL[J].Journal of Aerospace Power,1997,12(1):6-8,103. |
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| Authors: | Xia Pinqi and Xu Guiqi |
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| Institution: | 1st Dept.Nanjing University of Aeronautics and Astronautics, Nanjing 210016;1st Dept.Nanjing University of Aeronautics and Astronautics, Nanjing 210016 |
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| Abstract: | An experimental technique and method for flutter research of helicopter blade model are proposed.In the result of a series of experiments the relationships of blade flutter margin with rotor rotational speed,effective CG position of blade in chord and torsional stiffness of blade have been obtained.Some important conclusions have been reached. |
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| Keywords: | Propeller blades Flutter tests Model tests |
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