Have a personal or library account? Click to login
Baseline-Free Detection of Progressive Fatigue Damage Using Nonlinear Ultrasonic Guided Waves Cover

Baseline-Free Detection of Progressive Fatigue Damage Using Nonlinear Ultrasonic Guided Waves

Open Access
|Oct 2025

Figures & Tables

Figure 1.

Dispersion curves of (a) phase velocity and (b) group velocity for Aluminum-5152 with 2 mm thickness.
Dispersion curves of (a) phase velocity and (b) group velocity for Aluminum-5152 with 2 mm thickness.

Figure 2.

The experiment setup and facilities, (a) the fatigue machine to produce crack (b) the cracked Aluminium plate (c) The forced convection oven to control temperature (d) the optical microscope for the crack inspection.
The experiment setup and facilities, (a) the fatigue machine to produce crack (b) the cracked Aluminium plate (c) The forced convection oven to control temperature (d) the optical microscope for the crack inspection.

Figure 3.

The signal acquisition system of the nonlinear guided wave-based method.
The signal acquisition system of the nonlinear guided wave-based method.

Figure 4.

The amplitude of the (d) fundamental frequency and (e) second harmonic before the fatigue test and after 320k cycles.
The amplitude of the (d) fundamental frequency and (e) second harmonic before the fatigue test and after 320k cycles.

Figure 5.

The crack effect on the fundamental and second harmonic frequency.
The crack effect on the fundamental and second harmonic frequency.

Figure 6.

Optical microscope images of fatigue crack ar at: (a) 300k cycles, (b) 320k cycles, (c) 340k cycles.
Optical microscope images of fatigue crack ar at: (a) 300k cycles, (b) 320k cycles, (c) 340k cycles.

Figure 7.

(a) The second harmonic parameters versus fatigue cycles under 20° environments. (b) The second harmonic parameters versus fatigue cycles under 30° and 40° environments.
(a) The second harmonic parameters versus fatigue cycles under 20° environments. (b) The second harmonic parameters versus fatigue cycles under 30° and 40° environments.

Figure 8.

(a) The second harmonic parameters versus fatigue cycles were obtained by specimens (a) T2, and (b)T3.
(a) The second harmonic parameters versus fatigue cycles were obtained by specimens (a) T2, and (b)T3.

Fatigue test details on different specimens under different temperatures_

Stage of fatigue testT1T2T3Working temperature
10k0k0k20-40°
2100k100k100k
3200k200k200k
4300k300k300k
5320k350k400k
6340k370k420k
7360k 440k

Crack length of different fatigue stage on specimens T1, T2, and T3_

SpecimensT1(mm)T2(mm)T3(mm)
Num of stagecyclesalarcyclesalarcyclesalar
10k000k000k00
2100k00100k00100k00
3200k00200k00200k00
4300k0.421.78300k00300k00
5320k0.442.4350k0.81.3400k0.60
6340k2.116.97370k1.933.90420k3.270
7360k4.0511.4 440k6.711.4
DOI: https://doi.org/10.2478/fas-2024-0009 | Journal eISSN: 2300-7591 | Journal ISSN: 2081-7738
Language: English
Page range: 119 - 130
Published on: Oct 14, 2025
Published by: ŁUKASIEWICZ RESEARCH NETWORK – INSTITUTE OF AVIATION
In partnership with: Paradigm Publishing Services
Publication frequency: 1 issue per year

© 2025 Yuhang Pan, Zahra Sharif Khodaei, M.H. Aliabadi, published by ŁUKASIEWICZ RESEARCH NETWORK – INSTITUTE OF AVIATION
This work is licensed under the Creative Commons Attribution-NonCommercial-NoDerivatives 3.0 License.