Abstract: Based on the helicopter rotor fluid damper work principle, elastic stiffness and loss coefficient expression were deduced. According to the parameters of rotor model the structure of liquid elastic damper was designed to meet the requirements, and fluid dynamics of elastic damper was tested for verification. Results show that the capacity of energy dissipation and dynamic characteristics of fluidelastic damper are better than that of elastomeric damper. Meanwhile, the consistency between tests and calculation results can ensure the validity and rationality of the theory and method which have been used in the design. The present study offers theory method to engineer helicopter rotor fluidelastic dampers.

Key words: vibration and wave, aircraft vibration, helicopter, rotor, fluidelastic damper, dynamic characteristics, loss factor

摘要： 基于直升机旋翼液弹阻尼器的工作原理的分析，推导弹性刚度和损耗系数的表达式。根据旋翼模型参数设计满足指标要求的液弹阻尼器结构，并用液弹阻尼器动力学试验进行验证。试验结果表明液弹阻尼器具有较粘弹阻尼器更稳定的动力学性能和更强的减振能力；试验结果与设计计算结果的比较验证理论推导和设计方法的合理性。从而为直升机旋翼液弹阻尼器的研制提供理论依据。

关键词: 振动与波, 航空器振动, 直升机, 旋翼, 液弹阻尼器, 动力学性能, 损耗系数