某型飞机机翼前缘抗鸟撞结构设计与试验验证

Design and experimental verification of a wing leading edge structure

针对某型飞机机翼前缘抗鸟撞性能不满足适航要求的问题,采用"数值仿真-试验验证-再仿真"的研究思路,对该结构进行了抗鸟撞优化设计。首先,通过有限元数值仿真,分别对具有三角板结构和前墙结构的两种新型前缘结构抗鸟撞能力进行了分析。仿真结果表明:具有前墙结构的机翼前缘抗鸟撞能力优于原始结构和带三角板结构的机翼前缘;在鸟撞过程中,这种具有前墙结构的机翼前缘通过利用破损蒙皮继续变形吸能的方式提高了结构的抗鸟撞性能。基于此,对带前墙结构的机翼前缘进行了抗鸟撞试验,一方面验证了数值模拟方法的准确性,另一方面验证了前墙结构的抗鸟撞效果。最后,采用数值仿真方法对带前墙结构的机翼前缘结构进行了参数分析,得到了前缘蒙皮厚度和前墙厚度与结构抗鸟撞性能的关系,并基于结构承载和抗鸟撞能力的综合要求,确定了最终结构参数。分析表明,优化后的机翼前缘结构不仅满足抗鸟撞要求,而且实现结构减重30%。

In order to improve the anti-bird strike performance of a wing leading edge to meet the airworthiness requirements, the simulation-test-simulation methodology was adopted for the optimization of the leading edge. Firstly, the anti-bird strike responses of two kinds of the new leading edges, with the triangular plate structure and the front wall structure, respectively, were investigated via finite element simulation. The simulation results show the anti-bird strike performance of the leading edge with the front wall structure is better than those of the leading edges with the original structure and the triangular plate structure. During the bird strike process, the front wall structure can utilize the damaged skin’s deformation to absorb energy, thus leading to the improvement of the anti-bird strike performance of the leading edge. The experiment was then carried out to verify not only the accuracy of the numerical simulation method but also the ability of the front wall structure against bird strike. Then, the validated model was used to analyze the influence of the leading edge structural parameters. With the weight reduction of 30%, the optimized wing leading edge structure with the front wall achieved a good performance of anti-bird strike.