直升机模型桨叶颤振试验研究
AN EXPERIMENTAL INVESTIGATION ON FLUTTER OF A HELICOPTER BLADE MODEL
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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。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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Key words:
- Propeller blades /
- Flutter tests /
- Model tests
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