铰链式下垂前缘机构设计与动力学仿真研究

下垂前缘是一种结构简单的增升装置，能够有效降低气动噪声和减小机构的运动空间，已被应用于A380 和A350XW。为了实现下垂前缘按照给定要求定轴转动，需要设计一种机构型式，因此提出一种基于四连杆形式的铰链式下垂前缘机构的设计方法。根据设计输入要求建立下垂前缘机构的线架模型，并对该机构进行运动学和刚柔耦合动力学仿真，得到机构运动过程中角度变化参数和该机构运动过程中的驱动力矩和铰链点载荷。结果表明：随着驱动臂匀速转动，铰链式下垂前缘能够平稳下偏26°；两个驱动平面的最大驱动力矩的比值接近3∶2，且侧撑杆的设置使驱动处的横向受载得到了改善，该机构型式设计合理，为现代民用飞机设计提供了参考依据。

Research on Design and Dynamics Simulation of Hinged Drooping Leading Edge Mechanism

The drooping front is a simple lifting device, which can effectively reduce the aerodynamic noise and the motion space of the mechanism. It has been applied to A380 and A350XW. In order to realize the fixed-axis rotation of the drooping front according to the given requirements, a design method of hinged drooping front mechanism based on four-link is proposed. In this paper, according to the card position requirements of takeoff and landing, based on the position relationship of the reference point on the leading edge, the motion axis is obtained by mathematical analysis. Combined with the size and motion angle requirements of the driving mechanism of the droop leading edge, the frame model of the droop leading edge mechanism is calculated. On this basis, according to the kinematics simulation of the mechanism, the changes of the transmission angle and the rocker arm angle with the motion angle of the driving arm during the movement of the mechanism are clarified. Further, through the rigid-flexible coupling dynamics simulation of the drooping front mechanism, the driving torque and the hinge point load during the movement of the mechanism are obtained. The results show that with the uniform rotation of the driving arm, the hinged droop front can be steadily reduced by 26° ; The ratio of the maximum driving torque of the two driving planes is close to 3 : 2, indicating that the force transmission performance is good, the load distribution is reasonable, and the lateral load at the driving position is improved by the setting of the side strut. The proposed design method provides a new idea for the design of hinged droop leading edge mechanism, which has good reference significance in modern civil aircraft design.