民用飞机副翼舱结构振动疲劳寿命预计

副翼舱是民用飞机重要部件之一，主要作用为连接副翼并对安装副翼提供支持，将副翼的气动载荷传递到主翼盒上。当受到气动力及其他激励时副翼舱结构产生结构振动响应。副翼舱结构振动疲劳寿命需满足民用飞机适航条款要求，为表明满足适航条款符合性，对随机动载荷激励下副翼舱结构进行振动疲劳寿命预计具有重要意义。以民用飞机副翼舱结构为研究对象，基于试飞实测应变数据、金属材料的随机振动S-N曲线和改进声疲劳寿命估算法，提出了一种适用于振动疲劳寿命预计的工程处理方法。通过飞行试验、有限元仿真、数据分析等相结合的方法进行副翼舱结构优化前后的振动疲劳寿命预计。副翼舱结构优化前损伤位置预测寿命最低为59飞行小时，符合实际损伤位置寿命情况。副翼舱结构优化后应力水平明显降低，寿命满足要求。结果表明：基于实测数据的副翼舱结构振动疲劳寿命预计方法有效，可作为振动疲劳寿命预计的工程处理方法。

Vibration fatigue life prediction of aileron cabin structure for civil aircraft

The aileron cabin is one of the important parts of civil aircraft. Its main function is to connect the aileron and provide support for the installation of the aileron, and transfer the aerodynamic load of the aileron to the main wing box. When subjected to aerodynamic forces and other excitations, the aileron cabin structure produces structural vibration response. The vibration fatigue life of the aileron cabin structure must meet the requirements of civil aircraft airworthiness clauses. In order to show compliance with the airworthiness clauses, it is of great significance to predict the vibration fatigue life of the aileron cabin structure under the excitation of random dynamic loads. Taking the aileron cabin structure of civil aircraft as the research object, an engineering treatment method suitable for vibration fatigue life prediction was proposed based on the measured strain data of flight test, the random vibration S-N curve of metal materials and the improved acoustic fatigue method. Through the combination of flight test, finite element simulation, data analysis, etc., the vibration fatigue life before and after optimization of the aileron cabin structure was predicted. Before the optimization of the aileron cabin structure, the predicted life of the damage location was less than 59 flight hours, which was close to the actual life. After the optimization of the aileron cabin structure, the stress level is significantly reduced, and the service life meets the requirements. The results show that the method for predicting the vibration fatigue life of the aileron cabin structure based on the measured data is effective and can be used as an engineering treatment method for the prediction of the vibration fatigue life.