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为了研究腐蚀环境对复合材料修补结构疲劳特性的影响,开展以某型飞机加速环境谱为基础的预腐蚀试验,并采用递进式的试验方法分别完成对未修补未腐蚀、修补但未腐蚀、又修补又腐蚀的试样疲劳裂纹扩展试验。利用试验数据计算了复合材料修补构型、腐蚀环境对裂纹尖端应力强度因子影响的修正系数,并确定了通过试验验证的修补结构疲劳裂纹扩展修正模型。该模型预测腐蚀环境下修补结构的疲劳寿命与试验值一致。试验数据和预测模型可为海军飞机复合材料修补结构的损伤容限设计提供参考。
In order to study the influence of corrosive environment on the fatigue characteristics of composite repaired structures, a pre-corrosive test based on the accelerated environment spectrum of a certain aircraft was carried out, and the progressive test methods were used to complete the uncorrected non-corrosive, repaired but non-corrosive, And repair and corrosion of the specimen fatigue crack growth test. The test data were used to calculate the correction coefficient of the composite structure and the influence of the corrosion environment on the stress intensity factor at the crack tip. The fatigue crack growth correction model of the repaired structure was confirmed by the experimental data. The model predicts the fatigue life of the repaired structure under the corrosive environment is consistent with the experimental value. The test data and prediction model can provide reference for the design of the damage tolerance of the composite repair structure of the Navy aircraft.