| Fatigue damage is one of the main forms of aircraft failure during its usage. Reinforced plate structure is widely used in the structural design of modern aircraft. In this paper, by taking reinforced structures in aircraft as research objects, the fatigue damage problem of reinforced structures with cracks is investigated from three aspects, mainly including:The finite element model of reinforced plates was established using MSC.Patran and then the stress distribution was analyzed for different reinforced plates with stiffeners of different width and height. After this, the effect of the stiffener width and height on the fatigue life of the reinforced plates with cracks was analyzed using MSC.Fatigue.The influences of the stiffener width and the stiffener height on stress intensity factors were analyzed by considering these two parameters as single variables and changing them separately. Then the crack size at nodes where the most serious fatigue crack growth occurred was investigated. Through curve fitting of the crack size and the stiffener thickness or the stiffener height, the ideal thickness and height of stiffeners were drawn from the crack growth curve.By changing the distance between the hole and the crack of the model, the effect of the hole location on the stress intensity factors was obtained. The results show that as the distance between the hole and the crack decreases, the fatigue damage at the crack tip becomes more serious and the stress intensity factor becomes larger.This paper can provide a reference for engineering practices. |
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