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用自行研制的激光冲击强化处理 (LSP)装置对两种重要航空铝合金结构材料 70 5 0T74 5 1,70 5 0T74 5 2冲击强化试验 ,进行了疲劳寿命对比试验。给出了反映疲劳应力水平与结构件寿命对应关系的σm N曲线。结果表明 ,在6 7 3MPa的加载应力水平下 ,激光冲击处理后 70 5 0T74 5 1结构材料的疲劳寿命提高到未经处理的 4 35 % ,而70 5 0T74 5 2在 81 4MPa的应力水平下提高到 5 18%。并对试件进行了激光冲击处理机理的研究 ,结果显示试件表面具有较大的残余压应力和较高的位错密度
The impact fatigue tests of two kinds of important aviation aluminum alloy structural materials, 70 5 0T74 5 1, 70 5 0T74 5 2, were carried out with the self-developed laser shock treatment (LSP) device. The σm N curve reflecting the corresponding relationship between the fatigue stress level and the life of the structure is given. The results show that under the loading stress of 6 7 3MPa, the fatigue life of the 70 5 0T74 5 1 structure after laser shock treatment is increased to 435% of the untreated one, while that of the 70 5 0T74 5 2 under the stress level of 81 4MPa Increase to 5 18%. The laser shock treatment mechanism was also studied. The results show that the specimen has a larger residual compressive stress and a higher dislocation density