一种用于振动疲劳试验研究的典型翼面模拟件
On a Typical Wing Surface Simulator used in Vibration Fatigue Experiment

为开展飞机典型翼面结构振动疲劳问题及相关试验技术的研究，参考某型飞机垂尾翼面设计了其模拟件。在有限元分析软件Abaqus中建立其有限元模型，进行该模拟件的动力学分析和优化，使其模拟某飞机垂尾的前三阶模态。结合模态振型分析，给出一种确定单点振动载荷最优加载点的方法。窄带随机试验结果表明，模拟件达到了设计要求，可以用于某飞机垂尾翼面振动疲劳问题及相关试验技术的研究。
In order to carry out vibration fatigue problem study of aircraft typical wing surface structure and relevant experimental technology, referring to vertical tail wing of a certain type of aircraft, a typical wing surface simulator was designed. A finite element model was established first by using finite element analysis software ABAQUS, based on which, dynamic analysis and optimization of this simulator was carried out. The first three modes of vibration of aircraft vertical tail wing can be simulated. Based on modal vibration mode analysis, a method was presented to determine the optimal loading point of single point vibration load. Narrow band random experimental results show that this simulator can meet the design requirements and can be used in vibration fatigue problem study of a certain type aircraft vertical wing surface and relevant experimental technology