基于交叉簧片式铰链的变弯度机翼机构设计

Design of wing mechanism with variable camber based on cross-spring flexural pivots

为了研究机翼弦向连续变弯度的设计问题,提出由柔性后缘机构与刚性连杆驱动机构组成的机翼变弯度设计方案以及建模分析方法.基于交叉簧片式柔性铰链设计机翼机构构型.采用链式梁约束建模方法,建立柔性后缘机构的理论力学模型,得到其受力和变形的关系,并利用有限元仿真对理论力学模型进行验证.在力学模型的基础上,采用NSGA-II多目标遗传算法优化机翼机构的相关尺寸参数,提升机翼的气动特性.经优化,机翼巡航阶段的升阻比提升1.09%,起降阶段的升力系数提高2.54%.经实验验证了设计的变弯度机翼机构变弯度的精度和变弯度的范围.

In order to design airfoil mechanism with continuous variable camber,a morphing wing structure and modeling analysis was proposed by using flexible trailing edge mechanism and rigid connecting rod driving mechanism.The wing mechanism was based on cross-spring flexural pivots.The theoretical mechanics model of the flexible trailing edge mechanism was established by using chained beam constraint model,and the relationship between the force and deformation of the mechanism was also obtained.Then,compared the theoretical mechanics model with finite element model.On the basis of the mechanical model,In order to improve the aerodynamic characteristics of the wing mechanism,NSGA-II multi-objective genetic algorithm was used to optimize the dimension parameters of the mechanism.After optimization,the lift-drag ratio of the morphing wing in cruise stage is increased by 1.09%,and the lift coefficient in takeoff stage is increased by 2.54%.The deformation precision and deformation range of the airfoil mechanism were tested by experiments.