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模拟飞机结构经历的“地面腐蚀+空中疲劳”过程,分析腐蚀影响系数法(C(t)曲线)的物理意义,提出将其当量成疲劳寿命的衰减;在考虑腐蚀环境与疲劳载荷耦合作用的基础上,提出腐蚀-疲劳交替作用下金属结构的剩余寿命预测模型.以2A12-T4铝合金标准实验件为研究对象,以预腐蚀疲劳和腐蚀-疲劳交替实验结果为依据,验证了模型的计算结果.
The physical meaning of the corrosion influence coefficient method (C (t) curve) is simulated to simulate the “ground corrosion + air fatigue” process experienced by the aircraft structure, and its equivalent to the attenuation of fatigue life is proposed. When the corrosion environment is considered to be coupled with the fatigue load On the basis of this, the residual life prediction model of the metal structure under alternating corrosion-fatigue effect was put forward. The 2A12-T4 aluminum alloy standard experimental piece was taken as the research object. Based on the experimental results of pre-corrosion fatigue and corrosion-fatigue alternation, The calculation results.