大柔性飞机着陆响应抑制技术研究

Landing Response Suppression Technology for Large Flexible Aircraft

摘要:

现代大型客机、高空无人机多采用大展弦比机翼，飞行器使用大展弦比机翼可以有效减小能耗，但由于自身结构特性，在重力与气动力的作用下，会产生较大变形。为探究大柔性飞机着陆响应特性，以某型大展弦比无人机作为参考样机，结合机体有限元模型，建立考虑机体柔性的全机着陆动力学模型，分析机体弹性模态和机体初始姿态角对着陆载荷和机翼动响应的影响；基于响应面法建立代理模型，对起落架缓冲器参数进行优化设计。结果表明：对飞机着陆性能产生影响的主要是机体一阶模态；过大的机体初始姿态角会导致飞机着陆载荷和机翼动响应的增大，增加翼尖触地风险；对于大柔性飞机，适当增大起落架缓冲器设计行程有助于减小飞机着陆载荷以及机翼动响应。

Abstract:

Modern large airliners and high-altitude unmanned aerial vehicles predominantly utilize high aspect ratio wings. Aircraft equipped with high aspect ratio wings can effectively reduce energy consumption; however, due to their structural characteristics, they experience considerable deformation under the influence of gravity and aerodynamic force. In order to investigate the landing response characteristics of a large flexible aircraft, a comprehensive landing dynamics model was developed, taking into account the flexibility of the airframe. This model was based on a high aspect ratio UAV as a reference sample and was integrated with a finite element model of the airframe. The analysis focused on the effects of the elastic modes and the initial attitude angle of the airframe on the landing loads and the dynamic response of the wings. Utilizing the response surface method, a surrogate model was created to optimize the parameters of the landing gear buffers. The results indicate that for large flexible aircraft, increasing the design travel of the landing gear buffers is beneficial in reducing both the landing loads and the dynamic response of the wings.