大型民用飞机缝翼全尺寸静力试验载荷设计

研究了大型民用飞机前缘缝翼全尺寸静力试验载荷设计技术，以实现对缝翼结构安全性的考核和强度分析方法的验证。针对前缘缝翼尺寸小、曲率大、受载工况复杂的特点，提出了试验基准载荷筛选、试验实施载荷转换和试验加载方案优化的方法，形成了一套符合适航要求的试验载荷设计流程。基于最小安全裕度原则进行试验基准载荷的筛选，建立试验加载局部坐标系将气动分布载荷转换成试验集中载荷，为了准确模拟机翼大变形状态下缝翼的受载状态，对试验载荷进行斜加载。与理论载荷的对比分析结果表明了试验载荷设计的有效性，试验结果表明了所形成的载荷设计技术可以实现对前缘缝翼结构静强度的适航验证。

Load design for full scale static test of slat on large civil aircraft

To examine the safety of the slat structure on large civil aircraft and verify the feasibility of its strength analysis, load design techniques for full scale static test are studied. To address the characteristics of slats such as small size, large curvature and complex load conditions, methods of baseline loads screening, test loads transfer and optimization are proposed, creating a set of load design processes that meet the requirements of airworthiness. Based on the principle of minimum margin of safety, baseline loads were selected. Aerodynamic distribution loads were converted into concentrated loads by setting up local coordinate system. Oblique loads were used to accurately simulate load conditions of slat under large deformation of the wing. The results of comparative analysis with theoretical loads showed the validity of the test load.Test results showed that load design techniques in this paper can be used for the verification of the airworthiness of slat's strength successfully.