Odnos modalnog prigušenja kod simetričnog laminatnog kompozita pod uticajem pričvršćene mase primenom eksperimentalnog dizajna

Rahmane Abdelhafid

doi:10.5937/fme2103740a

Abstract

Nowadays, the use of composite materials has taken a large place in civilian industries as well as in military and aerospace industries. Therefore, significant investigations about their mechanical and physical properties are needed. The present study addresses the effect of attached mass on damping ratio of symmetric angle ply laminate composite. Furthermore, factor influencing the effect of attached mass on damping ratio of laminate composite are studied using Taguchi method. The considered factors parameters are: attached mass locations from the clamped edge, stacking sequences and boundary conditions. The results of this study indicate that the damping ratio of the laminate composite plates is sensitive to the attached mass, where the damping ratio is found to be proportional to the locations of the attached mass. The findings of this study indicate that the attached mass decreases frequency parameter and increase the damping ratio of the composite plate, if it is inserted at a point other than a nodal line. In addition, the paper presents a good correlation between the numerical results of the fundamental frequency obtained by the ANSYS software and those obtained experimentally.

Highlights

The composite materials are fabricated to have better engineering properties than the conventional ones, such as metals
In many engineering applications such as satellites systems and aviations, substructures are added to the structures. These attached masses have an effect on the response of the main structures, principally, the vibration behaviour [8,9,10]
5.1 Effect of the attached mass on modal damping and natural frequencies In Table 5 the experimental results of the fundamental frequencies of plates composite without attached mass as a function of lamination angle are given. These results are compared with the results of the finite element method (FEM) and good agreement is observed between the two results

Summary

Introduction

The composite materials are fabricated to have better engineering properties than the conventional ones, such as metals. Several authors have performed vibration analysis of laminated composite under various conditions of reinforcement and configuration [1,2,3,4,5,6,7]. In many engineering applications such as satellites systems and aviations, substructures are added to the structures. These attached masses have an effect on the response of the main structures, principally, the vibration behaviour [8,9,10]. Several studies have presented vibration analysis of composite materials with concentrated attached masses at separate locations under various arrangements and conditions of reinforcement. The free vibration of a supported laminated composite plate with distributed attached mass was presented by Alibeigloo et FME Transactions (2021) 49, 740-748 740

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