Repeat scanning technology for laser ultrasonic propagation imaging

2013 ◽  
Vol 24 (8) ◽  
pp. 085201 ◽  
Author(s):  
Jung-Ryul Lee ◽  
See Yenn Chong ◽  
Nitam Sunuwar ◽  
Chan Yik Park
2011 ◽  
Vol 49 (12) ◽  
pp. 1361-1371 ◽  
Author(s):  
Jung-Ryul Lee ◽  
He-Jin Shin ◽  
Chen Ciang Chia ◽  
Dipesh Dhital ◽  
Dong-Jin Yoon ◽  
...  

Materials ◽  
2019 ◽  
Vol 12 (23) ◽  
pp. 3992 ◽  
Author(s):  
Sang-Hyeon Kang ◽  
Dae-Hyun Han ◽  
Lae-Hyong Kang

We studied the detection and visualization of defects in a test object using a laser ultrasonic guided wave. The scan area is irradiated by a laser generated from a Nd:YAG 532 nm Q-switched laser generator through a galvanometer scanner. The laser irradiation causes the surface temperature to suddenly rise and then become temporarily adiabatic. The locally heated region reaches thermal equilibrium with the surroundings. In other words, heat energy propagates inside the object in the form of elastic energy through adiabatic expansion. This thermoelastic wave is typically acquired by a piezoelectric sensor, which is sensitive in the ultrasonic domain. A single piezoelectric sensor has limited coverage in the scan area, while multi-channel piezoelectric sensors require many sensors, large-scale wiring, and many channeling devices for use and installation. In addition, the sensors may not acquire signals due to their installed locations, and the efficiency may be reduced because of the overlap between the sensing areas of multiple sensors. For these reasons, the concept of a piezoelectric line sensor is adopted in this study for the first time. To verify the feasibility of the line sensor, I- and L-shaped sensors were attached to a steel structure, and the ultrasound signal from laser excitation was obtained. If the steel structure has defects on the back, the ultrasonic propagation image will be distorted in the defect area. Thus, we can detect the defects easily from the visualization image. Three defects were simulated for the test. The results show that the piezoelectric line sensor can detect defects more precisely and accurately compared to a single piezoelectric sensor.


Metals ◽  
2021 ◽  
Vol 11 (10) ◽  
pp. 1607
Author(s):  
Dong-Il Kim ◽  
Ku-Rak Jung ◽  
Yoon-Soo Jung ◽  
Jae-Yeol Kim

Pulse-echo laser ultrasonic propagation imaging is a nondestructive testing technique developed for composite materials and aluminum alloys used in aerospace. Although this method has been in usage for a considerable time, information of the detectable depth and the relationship between ultrasonic frequencies and the acoustic properties of metals is not readily available. Therefore, we investigate the A-scan and C-scan ultrasonic testing data of aluminum alloy, hot rolled steel, stainless steel, and copper alloy, which are used in aircraft bodies, frameworks, and gas pipelines. Experiments are performed with the pulse-width and excitation laser power fixed at 32 ns and approximately 4 W, respectively. The metal specimens include 24 artificial cylindrical defects with a diameter of 5 mm, located at depths of 1–12 mm on the front surface. The A-scan and C-scan data obtained at room temperature indicate the detectable depth for metals via the pulse-echo laser ultrasonic propagation imaging technique.


2012 ◽  
Vol 225 ◽  
pp. 121-126
Author(s):  
Seung Chan Hong ◽  
Jung Ryul Lee ◽  
See Yenn Chong ◽  
Chan Yik Park

A laser ultrasonic based nondestructive evaluation (NDE) technique has been widely used in aerospace industries for inspecting parts and structures made of composite materials. The thermoelastic regime is used for the ultrasonic generation, so no plasma is formed on the surface of composite structure. Generally, the service lifetime for an aircraft could be more than 25 years. Thus, the composite structures of the aircraft could be susceptible to laser pulse fatigue damage caused by the laser pulse energy of a laser ultrasonic generator in the long-term periodic maintenance inspection. In this paper, the effect of laser pulse fatigue on the mechanical characteristics of a carbon-fiber-reinforced polymer (CFRP) plate (USN175BX Carbon UD preprag) with the stacking sequence of [0/45/-45/90]s is investigated to verify the reliability of the use of a laser ultrasonic based NDE technique on the CFRP plate specimen inspection. A high-speed laser ultrasonic scanning system (400mm/s at the intervals of 0.4 mm) was setup to perform repeat scanning of 1300 times on a CFRP plate specimen with the scanning area of 70 mm x 60 mm. These repeat scanning times were set in consideration of the periodic maintenance inspection scheduled to be 1 time/week x 52 weeks/year x 25 years. A 532nm Q-switched continuous wave laser (QL) was used and set at the laser pulse energy levels of 0.6 mJ and 1.2 mJ. Lamb wave assessment based on pitch-catch method was proposed in this paper to monitor the mechanical characteristics of a composite specimen. In each completion of 100 times repeat scanning, the Young’s modulus of the scanning area was evaluated based on the group velocity of S0 Lamb wave mode. In addition, the surface condition of the scanning area was investigated by using a microscope.


Author(s):  
Enhi Sen ◽  
Osamu Saito ◽  
Nobuhiro Higuchi ◽  
Yoji Okabe

Abstract Honeycomb sandwich structures are widely used in aircraft owing to the superior characteristics, such as the light weight, the high specific bending stiffness and the high specific in-plane compressive strength. However the honeycomb sandwich structures are prone to have debonding damages at the interfaces between the skin and the honeycomb core, which degrades the mechanical properties largely. For inspection of damages in plate-like structures, the propagation of ultrasonic guided waves along the plate is effective. In this research, we attempted to detect the debonding at the skin/core interfaces in a honeycomb sandwich panel by using a laser ultrasonic visualization method. Debonding damages were artificially introduced in a sandwich panel consisting of two CFRP skin plates and an aluminum honeycomb core. Then, ultrasonic guided waves were excited in the panel through scanning of a laser irradiation on a surface of the plate and were received by a piezoelectric sensor installed on the same surface by using a laser ultrasonic visualizing inspector. As a result, we obtained visualization animations of the ultrasonic propagation behavior. From the change in the maximum amplitude distribution of the guided wave, we were able to identify the debonding damages at the skin/core interfaces in both the laser-irradiation side and the opposite side. Furthermore, a finite element analysis of the ultrasonic propagation in the honeycomb sandwich panel was conducted to confirm the phenomena observed in the experiments. From the calculation results, the mechanism of the observed phenomena was able to be clarified.


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