某飞机腹板构件结构改进及试验验证

Structure Improvement and Experimental Validation of Aircraft Web Plate

针对某型飞机腹板构件较早的发生筋条疲劳破坏,运用仿真分析和试验的手段进行结构改进。首先建立腹板构件有限元模型,对腹板构件应力分布和疲劳寿命进行计算,分析筋条疲劳破坏的原因;其次依据刚度分配原则对结构进行改进,有限元计算结果表明改进设计降低了筋条应力水平,提高了腹板构件的疲劳寿命;最后对原结构试件和改进后结构试件进行疲劳对比试验,试验结果验证了有限元模型的准确性和结构改进的有效性。

For fatigue failure occurring in a stiffener of an aircraft web plate earlier,the structure of the web plate is improved by means of simulation analysis and experimental validation.Firstly,the web plate dynamic model is set up,the causes of fatigue failure are analyzed by calculating the stress distribution and fatigue life of the web plate.Secondly,an improvement design is conducted on the original structure of the web plate based on principle of stiffness distribution.The finite element calculation result shows that improved design decreases the maximum stress of the stiffener and improves the fatigue life of the web plate.Finally,by comparing the fatigue tests of original structure and improved structure,the results verify the accuracy of finite element model and the effectiveness of the improvement.