Stationary response analysis of vibro-impact system with a unilateral nonzero offset barrier and viscoelastic damping under random excitations

2016 ◽  
Vol 86 (2) ◽  
pp. 891-909 ◽  
Author(s):  
Deli Wang ◽  
Wei Xu ◽  
Xudong Gu ◽  
Yongge Yang
Keyword(s):  
Viscoelastic Damping ◽  
Response Analysis ◽  
Stationary Response ◽  
Impact System

Response Analysis of van der Pol Vibro-Impact System with Coulomb Friction Under Gaussian White Noise

2018 ◽  
Vol 28 (13) ◽  
pp. 1830043 ◽  
Author(s):  
Meng Su ◽  
Wei Xu ◽  
Guidong Yang
Keyword(s):  
White Noise ◽  
Coulomb Friction ◽  
Gaussian White Noise ◽  
Original System ◽  
Stochastic Averaging ◽  
Response Analysis ◽  
State Variables ◽  
Van Der Pol ◽  
Impact System ◽  
The Impact

In this paper, the stationary response of a van der Pol vibro-impact system with Coulomb friction excited by Gaussian white noise is studied. The Zhuravlev nonsmooth transformation of the state variables is utilized to transform the original system to a new system without the impact term. Then, the stochastic averaging method is applied to the equivalent system to obtain the stationary probability density functions (pdfs). The accuracy of the analytical results obtained from the proposed procedure is verified by those from the Monte Carlo simulation based on the original system. Effects of different damping coefficients, restitution coefficients, amplitudes of friction and noise intensities on the response are discussed. Additionally, stochastic P-bifurcations are explored.

Dynamic Response Analysis for the Solar-Powered Aircraft Composite Wing Panel with Viscoelastic Damping Layer

2011 ◽  
Vol 105-107 ◽  
pp. 491-494
Author(s):  
Tie Jun Liu ◽  
Yong Zhang ◽  
Gang Li ◽  
Feng Hui Wang
Keyword(s):  
Dynamic Response ◽  
Vibration Isolation ◽  
Viscoelastic Damping ◽  
Response Analysis ◽  
Aircraft Wing ◽  
Maximum Displacement ◽  
Displacement Response ◽  
Stiffened Structures ◽  
Solar Powered ◽  
Wing Panel

In design of solar powered aircraft wing panel, vibration properties of wing panel should be considered, especially for the peak value of dynamic response. In this research, a viscoelastic damping layer is built for vibration isolation, wing panel finite element models of stiffened and no-stiffened structures base on fiber-reinforced laminates with damping layer in the middle are built. Natural frequency and displacement response are analyzed with different thickness of damping layer and structures. Result shows natural frequencies decrease as thickness increased, and that of laminates are lower than stiffened structure. The maximum displacement response value decreased when thickness increased and that of laminates is higher than structured with stiffer. The presented work is helpful for type selection and designing of solar powered aircraft wing panel.

scholarly journals Non-stationary response analysis of dynamic structural systems.

1986 ◽  
pp. 541-548
Author(s):  
Takahiro NAKAYAMA ◽  
Sadao KOMATSU ◽  
Naoyuki SUMIDA
Keyword(s):  
Response Analysis ◽  
Structural Systems ◽  
Stationary Response
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