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.