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干涉连接是航空复合材料结构件的主要连接方式,然而不恰当的干涉量会导致孔周围区域产生损伤,从而严重影响整个连接结构的静强度和疲劳强度。分析了干涉连接过程连接板的受力形式,建立了基于干涉量的孔边应力分布模型。在此基础上,结合Yamada准则建立了孔边损伤萌生模型,利用特征曲线法界定了材料损伤区域传播的极限位置;其次,针对CFRP材料(碳纤维增强复合材料)的特点,利用ABAQUS软件对干涉连接过程损伤的萌生及扩展进行仿真模拟;最后,对不同孔径不同干涉量条件下的损伤萌生和损伤扩展结果进行对比分析,验证了损伤萌生模型的准确性。
Interference connection is the main way of connecting aerostructures. However, improper interference can damage the surrounding area and seriously affect the static strength and fatigue strength of the whole structure. The force form of the interference plate is analyzed, and the hole-edge stress distribution model based on the interference is established. On the basis of this, a hole edge damage initiation model was established based on Yamada criterion, and the limit position of material damage propagation was defined by the characteristic curve method. Secondly, according to the characteristics of CFRP material (carbon fiber reinforced composites), the interference connection Finally, the damage initiation and damage expansion under different interferences with different aperture were compared and analyzed, and the accuracy of damage initiation model was verified.