A thorough understanding of the effects of sloshing on aircraft dynamic loads is of great relevance for the future design of flexible aircraft to be able to reduce their structural mass and environmental impact. Indeed, the high vertical accelerations caused by the vibrations of the structure can lead to the fragmentation of the fuel free surface. Fluid impacts on the tank ceiling are potentially a new source of damping for the structure that has hardly been considered before when computing the dynamic loads of the wings. This work aims at applying recently developed reduced-order models of sloshing to the case of a research wing to investigate their effects on the wing aeroelastic response under pre-critical and post-critical conditions. The vertical sloshing dynamics is considered using neural networks trained with experimental data from a scaled tank and then integrated into the aeroelastic system following a suitable scaling procedure. The results concern the aeroelastic response of the wing to gust input under pre-critical (flutter) conditions as well as post-critical conditions highlighting the onset of limit cycle oscillations caused by sloshing, the only nonlinear phenomenon modelled in the present simulation framework. Moreover, the load alleviation performances will be assessed for a typical landing input.

彻底了解晃荡对飞机动态载荷的影响对于未来设计柔性飞机以减少其结构质量和环境影响具有重要意义。实际上，由结构振动引起的高垂直加速度会导致无燃料表面的破碎。在计算机翼的动态载荷时，对油箱顶的流体冲击可能是结构阻尼的新来源，以前几乎没有考虑过。这项工作旨在将最近开发的晃荡降阶模型应用于研究机翼的情况，以研究它们在临界前和临界后条件下对机翼气动弹性响应的影响。垂直晃动动力学是通过使用来自缩放罐的实验数据训练的神经网络来考虑的，然后按照合适的缩放程序集成到气动弹性系统中。结果涉及机翼在前临界（颤振）条件和后临界条件下对阵风输入的气动弹性响应，突出了由晃动引起的极限循环振荡的开始，这是目前模拟框架中建模的唯一非线性现象。此外，将对典型着陆输入的负载减轻性能进行评估。结果涉及机翼在前临界（颤振）条件和后临界条件下对阵风输入的气动弹性响应，突出了由晃动引起的极限循环振荡的开始，这是目前模拟框架中建模的唯一非线性现象。此外，将对典型着陆输入的负载减轻性能进行评估。结果涉及机翼在前临界（颤振）条件和后临界条件下对阵风输入的气动弹性响应，突出了由晃动引起的极限循环振荡的开始，这是目前模拟框架中建模的唯一非线性现象。此外，将对典型着陆输入的负载减轻性能进行评估。