研究目的
To investigate the extent to which the fatigue behaviour of laser beam-welded AA6056-T6 butt joints with an already existing crack can be improved through the application of laser shock peening.
研究成果
Laser shock peening (LSP) was shown to be an effective technique for recovering the fatigue life of laser beam-welded AA6056-T6 butt joints with existing surface cracks. The application of LSP introduced compressive residual stresses that significantly retarded fatigue crack growth, recovering the fatigue life to the level of uncracked specimens. The study demonstrates the potential of LSP as a prophylactic residual stress engineering approach to extend the fatigue life of critical structures in ageing aircraft.
研究不足
The study focused on AA6056-T6 aluminium alloy and laser beam-welded butt joints. The effectiveness of LSP on other materials or joint configurations was not investigated. The accuracy of ultrasonic crack depth measurement was estimated as ±0.1 mm.
1：Experimental Design and Method Selection:
The study utilized laser shock peening (LSP) to improve the fatigue behaviour of laser beam-welded AA6056-T6 butt joints with existing cracks. Ultrasonic testing was used for in situ measurement of fatigue crack growth.
2：Sample Selection and Data Sources:
AA6056 sheet material with a thickness of
3：2 mm was used, cut into blanks and laser beam-welded in butt joint configurations. List of Experimental Equipment and Materials:
A Q-switched Nd:YAG laser for LSP, ultrasonic apparatus (Olympus OmniScan MX2) for crack measurement, and a Testronic 100-kN RUMUL resonant testing machine for fatigue tests.
4：Experimental Procedures and Operational Workflow:
Fatigue tests were conducted at room temperature under load-controlled conditions. LSP was applied to specimens with predefined crack depths.
5：Data Analysis Methods:
The crack depth was measured using ultrasonic testing, and residual stress profiles were determined using the hole drilling technique.
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