Abstract

The conventional finite element method can be used for modeling the multiscale phenomenon of the interaction of Lamb waves with matrix cracks, but it requires a lot of computational resources. In the present investigation, appropriate damage models are used to model the reduction in the stiffness of the ply in which the matrix crack has occurred. Moreover, the interactions of Lamb waves with matrix cracks, which have been modeled as a local reduction in stiffness, are being studied. Furthermore, in a Glass Fiber Reinforced Plastic (GFRP) laminate with a [0/90/90/0] lay-up, Lamb waves of various frequencies and with So (symmetric) and Ao (asymmetric) modes are transmitted along the fiber and across the fiber directions, respectively. As a result, such waves are recorded at two points, 75 and 225 mm from the site of excitation. For two different crack densities, such as 1 crack/mm and 4 cracks/mm, the healthy and damaged laminate signals of similar mode are compared. The amplitudes of the received signals are reduced upon interaction of these waves with damage (with degraded stiffness values), indicating that So modes of Lamb waves are much more susceptible to damages at higher frequencies of 100, 150, and 200 kHz compared to Ao modes. Furthermore, for a given crack density, equivalent damage models are validated by comparing these signals to cracked laminate signals of similar frequencies and modes. During the study, it was revealed that equivalent damage models are perfectly appropriate for modeling matrix cracks of any density as a local loss in stiffness in the damaged crossply GFRP laminate.

Highlights

  • Composites are utilized to lower the ultimate weight of aeronautical structures, such as space antennas, mirrors, and other optical instruments

  • Afterward, cracked and damaged laminate signals of similar modes and frequencies are compared for a specific crack density to validate the equivalent damage models

  • Intricate in-plane and out-of-plane displacement patterns have been introduced over the thickness of the laminate using constraint equations to excite a specific Lamb wave mode

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Summary

INTRODUCTION

Composites are utilized to lower the ultimate weight of aeronautical structures, such as space antennas, mirrors, and other optical instruments. Composite materials have high specific strength, high specific stiffness, extended fatigue life, low density, and flexibility to the structure’s intended application. Damage mechanics must be understood to design applications that are both durable and cost-effective. As a result of service damage, the behavior of composite materials will change. Non-destructive evaluation (NDE) of components and structures is done with Lamb waves. Such waves are extremely susceptible to damage and have the potential to propagate through a wide range of thicknesses. The application of Lamb waves in structural health monitoring (SHM) is promising since it enables cost-effective, continuous, and automated monitoring of engineering systems’ stability.. Composite materials can lose stiffness and other mechanical characteristics as a result of damage. Using various models, [0/90/90/0] lay-up is taken with different crack densities during Lamb wave simulation and its subsequent mathematical modeling for Young’s modulus of damaged laminate

FINITE ELEMENT MODEL
CALCULATION OF YOUNG’S MODULI OF DAMAGED LAMINATES
One-dimensional model to calculate Young’s modulus Ex of a damaged laminate
NUMERICAL ANALYSIS OF LAMB WAVES
Details of FE model
Verification of velocity of Lamb waves
RESULT
88 Coinciding
VALIDATION OF DAMAGE MODELS
SENSITIVITY OF EQUIVALENT DAMAGE MODELS
VIII. FUTURE SCOPE
CONCLUSIONS
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