In this study, the aim was to evaluate the vibration suppression performance of the partially covered equidistant multi-ring hard coating damping treatment for the cylindrical shell structure in aviation power equipment. A continuous rectangular pulse function was presented to describe the local thickness variation of arbitrary coating proportion and arbitrary number of coating rings. A semi-analytical unified solution procedure was established by combining the rectangular pulse function, the generalized Jacobi polynomials, and the Rayleigh-Ritz method. The stiffness coefficient k = 10¹³ N/m² and the truncation number N = 8 were found to be large enough to achieve an accurate and efficient solution of the vibration analysis of the shell. The modal loss factor generally increased with the increase of the coating proportion ranging from 0.0 to 1.0 for all the circumferential wave numbers. The modal loss factor increased roughly linear with the coating proportion for all the circumferential wave numbers. And the modal loss factor was increased with the circumferential wave number, and the greater the number of circumferential waves, the greater the rate of change. The increase of the ring number was not always beneficial for vibration reduction of the shell, while the modal loss factor increased roughly linear with the coating proportion. The increased ring number and coating proportion tend more to exhibit an obvious incremental damping effect under larger circumferential wave number.

本研究旨在评估航空动力设备圆柱壳结构部分覆盖等距多环硬质涂层阻尼处理的减振性能。提出了连续矩形脉冲函数来描述任意涂层比例和任意涂层环数的局部厚度变化。结合矩形脉冲函数、广义Jacobi多项式和Rayleigh-Ritz方法，建立了半解析统一求解过程。刚度系数k  = 10 ¹³  N/m ²和截断数N  = 8 被发现足够大，足以实现壳体振动分析的准确有效的求解。对于所有周向波数，模态损耗因子通常随着涂层比例的增加而增加，范围从0.0到1.0。对于所有周向波数，模态损耗因子与涂层比例大致呈线性增加。并且模态损耗因子随着周向波数的增加而增大，且周向波数越多，变化率越大。环数的增加并不总是有利于壳体的减振，而模态损耗因子与涂层比例大致呈线性增加。增加的环数和涂层比例在较大的周向波数下更容易表现出明显的增量阻尼效应。