基于频响函数识别直升机尾传动轴系非线性的方法

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Abstract

A method for identifying nonlinear modal parameters of the tail drive shaft system of a helicopter based on the tested frequency response functions was proposed.Using the linear modal analysis and in accordance with the response amplitude linearization theory, the nonlinear modal parameters of the tail drive shaft system were identified by the stepped sine sweep test in order to obtain the frequency response functions at different excitation levels.The results show that the first-order natural frequency of the tail drive shaft system decreases by about 2%, while the damping ratio increases by about 1.5 times, as the amplitude of the excitation force increases.Multiple sets of test analyses were performed under the same state and the results are consistent.The approach for identifying the modal parameters of the nonlinearity of the tail drive shaft system lays a foundation for further research on the dynamic characteristics of the helicopter tail drive shaft system.

Key words： helicopter tail drive shaft system frequency response function nonlinear modal modal test

Received: 29 January 2019 Published: 15 July 2020

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	Articles by authors
	SHAN Weidong1
	ZANG Chaoping1
	ZHANG Genbei1
	WANG Ping2
	ZOU Yachen2
	NI De2

Cite this article:

SHAN Weidong1,ZANG Chaoping1,ZHANG Genbei1, et al. Method for identifying the nonlinearity of a helicopter tail drive shaft system based on frequency response functions[J]. JOURNAL OF VIBRATION AND SHOCK, 2020, 39(14): 102-108.

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http://jvs.sjtu.edu.cn/EN/ OR http://jvs.sjtu.edu.cn/EN/Y2020/V39/I14/102

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