Design of flap/spoiler follower mechanism for civil aircraft

With the gradual development of the lift device to a simple and efficient direction, the drooped spoiler has become an emerging lift device. The drooped spoiler can improve the aerodynamic performance of the wing by reducing the air flow separation and increase the lift coefficient, which requires the spoiler to deflect a certain angle following the downward deflection of the flap. Aiming at this requirement, this paper proposes a design method of spoiler follower mechanism based on the relative pole method. The applicability and correctness of the method are verified by kinematics simulation. Moreover, the kinematic characteristics of the simple four-bar linkage and the complex four-bar linkage are compared, and the results show that the complex four-bar linkage is more stable in the motion process.