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飞机机体结构疲劳失效几乎都发生在紧固件孔的孔边位置,结构疲劳断裂会导致飞机出现灾难性的事故,PHM技术可用于预报疲劳故障何时可能发生,从而实现自助式保障,降低使用和保障费用。基于失效物理模型,建立连接件疲劳寿命的预测方法,方法首先求解含孔构件的应力严重系数和疲劳缺口系数,然后对应变-寿命曲线的弹性段进行了修正使局部应力应变法同时适用于高、低周疲劳寿命的预测。结果表明,建立的疲劳寿命预测方法的计算结果与疲劳试验结果相比误差小于17%,说明了方法的有效性。
Fatigue failure of the fuselage structure almost always occurs at the hole edge of the fastener hole and structural fatigue failure can lead to a catastrophic aircraft accident. PHM technology can be used to predict when a fatigue failure may occur, thus enabling self-service protection and reducing the use of And security costs. Based on the failure physics model, a method for predicting the fatigue life of the connector is established. The method firstly solves the stress coefficient and the fatigue gap coefficient of the member with holes, and then modifies the elastic section of the strain - life curve so that the local stress-strain method can be applied to high , Low cycle fatigue life prediction. The results show that the proposed fatigue life prediction method is less than 17% error compared with the fatigue test results, which shows the effectiveness of the method.