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<p>This paper presents a damage detection method using a Lamb wave-based diagnostic approach with piezoelectric (PZT) sensors for CFRP-laminated plates currently used in aircraft. The damage detection algorithm converted PZT sensor signals received from both undamaged and damaged plates into periodic signals using a sinusoidal Gaussian function, calculated scatter signals, and determined group velocity through the Hilbert transform. Damage location was estimated using a mapping function, and damage size was visualized by generating a circular function. The 700&#xa0;mm × 700&#xa0;mm CFRP-laminated plate specimens with 30, 40, and 50 plies, actually used in aircraft structures, were prepared. A total of 18 damage detection experiments were conducted, acquiring 36 cell signal data. This study successfully demonstrated damage detection on CFRP-laminated plates with errors less than 4.3%, with ranges of 2.8–15.2&#xa0;mm for 30 plies, 1.1–13.8&#xa0;mm for 40 plies, and 2.8–18.1&#xa0;mm for 50 plies. The damage detection method developed in this study is expected to be applied to the maintenance of operational aircraft, contributing to the management of their structural integrity.</p>

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Damage Detection in Aircraft Composite Panels Using Damage Detection Algorithms Based on Lamb Waves

  • 期刊论文

  • 发表日期：

    2025年1月18日

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  • Jibeom Jung,
  • Dong-Hyeop Kim,
  • Sang-Woo Kim,
  • Soo-Yong Lee

摘要

This paper presents a damage detection method using a Lamb wave-based diagnostic approach with piezoelectric (PZT) sensors for CFRP-laminated plates currently used in aircraft. The damage detection algorithm converted PZT sensor signals received from both undamaged and damaged plates into periodic signals using a sinusoidal Gaussian function, calculated scatter signals, and determined group velocity through the Hilbert transform. Damage location was estimated using a mapping function, and damage size was visualized by generating a circular function. The 700 mm × 700 mm CFRP-laminated plate specimens with 30, 40, and 50 plies, actually used in aircraft structures, were prepared. A total of 18 damage detection experiments were conducted, acquiring 36 cell signal data. This study successfully demonstrated damage detection on CFRP-laminated plates with errors less than 4.3%, with ranges of 2.8–15.2 mm for 30 plies, 1.1–13.8 mm for 40 plies, and 2.8–18.1 mm for 50 plies. The damage detection method developed in this study is expected to be applied to the maintenance of operational aircraft, contributing to the management of their structural integrity.