Abstract
Dent-repaired fatigue performance of thin sheet specimens under coupled multi-stage damage with impact and pre-fatigue was investigated. Different damage combinations of fatigue, impact and repair were performed to simulate actual service of aircraft. Residual fatigue life after repairing is 27.8% higher than that of unrepaired, axial strain field during fatigue loading is redistributed after repairing. Fatigue life reduction is found to be sensitive to damage sequence. For specimens with certain cycles of pre-fatigue, dent repairing could not restore fatigue life. A life prediction model based on strain distribution and damage accumulative theory is proposed, which is of strong engineering significance.
Sign-in/Register to access full text options 
Free) 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a call
