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振动疲劳问题在飞机薄板结构中广泛存在,严重时甚至会引起蒙皮撕裂。基于损伤力学理论框架,利用Python语言对ABAQUS进行了二次开发,实现了振动疲劳损伤形成和演化的过程模拟。针对飞机典型加筋壁板结构进行了振动疲劳损伤分析,模拟了损伤演化过程,并对加筋高度参数进行了优选。结果表明:不同的加筋形式有不同的优选加筋高度,C型加筋高度为30mm时振动疲劳寿命最高,L型加筋高度为45mm时振动疲劳寿命最高。最后通过振动疲劳试验对仿真分析结果进行了验证,表明所选取的加筋参数能够提高结构的抗振动疲劳能力,振动疲劳寿命的最大误差为31.63%。
The problem of vibration and fatigue is widespread in aircraft sheet structures and can even cause skin tearing in severe cases. Based on the theoretical framework of damage mechanics, the secondary development of ABAQUS was implemented by Python language, and the process simulation of the formation and evolution of vibration fatigue damage was realized. Vibration fatigue damage analysis was carried out on the typical reinforced stiffened wall structure of the aircraft, the damage evolution process was simulated, and the height parameter of reinforcement was optimized. The results show that the different reinforced forms have different optimal stiffener heights, the highest fatigue life is when the height of C stiffener is 30 mm, and the highest fatigue life is when the height of L stiffener is 45 mm. Finally, the results of the simulation analysis are verified by the vibration fatigue test, which shows that the selected parameters can improve the anti-vibration fatigue capacity of the structure. The maximum error of the vibration fatigue life is 31.63%.