飞机结构强度试验差动式加载方法研究

Research on Differential Loading Method for Aircraft Structural Strength Test

多轮多支柱起落架结构飞机的结构强度试验,由于起落架加载空间狭小,起落架载荷施加困难。为解决此问题,提出一种差动式加载方法,通过设计特殊杠杆将作动筒设置于两个相邻起落架之间,形成一种加载二力杆,顺利实现所有起落架的载荷施加,且满足拉压双向交变载荷施加需求。该方法一次安装到位,空间占用率低,极大缩减了试验换装周期。通过软件仿真模拟了差动式加载方法在多轮多支柱起落架上的应用,且该方法已经成功应用到某型飞机全机疲劳试验。仿真和应用结果表明,差动式加载方法完全能够实现多轮多支柱起落架的拉压双向交变载荷的施加,为类似复杂区域多结构试验件的考核提供一定的参考。

For the structural strength test of multi-wheel multi-pillar landing gear structure aircraft, the landing gear load is difficult due to the narrow loading space of the landing gear. So a differential loading method was proposed. A loading force bar was formed by designing the lever to be actuated between two adjacent landing gears, which could meet the application requirement of the two-way alternating load of all the landing gears. The method was installed in place at one time, and the space occupancy rate was low, which greatly reduced the test dressing period. The application of the differential loading method on the multi-wheel multi-pillar landing gear was simulated by software simulation, and the method had been successfully applied to the full-machine fatigue test of a certain type of aircraft. The simulation and application results show that the differential loading method can fully realize the application of the two-wheel alternating load of the multi-wheel multi-pillar landing gear, which provides reference for the assessment of multi-structure test pieces in similar complex areas.