The existence of assembly error will have an impact on the kinematic accuracy and dynamic performance of mechanical system, which can not be ignored. Therefore, a dynamic simulation method of flap mechanism considering assembly error is established. Firstly, the motion digital prototype of flap mechanism and the rigid flexible coupling dynamic model considering the deformation of flap wing surface are established, and then when the error direction is fixed, by setting the deviation values of the two driving shafts, the influence on the driving torque of the flap mechanism and the load of key components under the working conditions of 2mm, 4mm and 6mm is explored. Then, through the eight error directions defined by the deviation function, the influence of the direction error of the drive shaft assembly on the driving torque of the flap mechanism is obtained when the error size is 6mm fixed. The results show that when the assembly deviation of the two driving shafts is in the three working conditions with the selected size, the flap trajectory basically coincides, and the driving torque of the inner mechanism increases by 10.19% when the error is 6 mm; When the size of the assembly error remains fixed, the change of the error direction will increase the driving torque of the flap mechanism. The dynamic simulation study can provide some theoretical guidance for the manufacturing and assembly of this type of high-lift device.

The sensitivity of each influencing parameter in the selected range of the complex multi-hinge space flap mechanism under typical fault conditions is studied, and the influence degree of each parameter and its dispersion on the driving torque of the mechanism is determined. Firstly, the rigid-flexible coupling dynamic model of the mechanism is established considering the flap deformation, and then the influence of four parameters that may cause mechanism failures, such as hinge friction, aerodynamic load, driving speed and assembly error, on the driving torque of the mechanism is explored. Then, the drive torque of the mechanism under each parameter value is given, finally, the sensitivity of each selected parameter is obtained by the direct de rivation method. The results show that the parameters are positively correlated with the driving torque, the aerodynamic load coefficient and hinge friction parameters are the most sensitive to the driving performance of the mechanism, while the driving speed is the smallest. After the aerodynamic load increased by 30%, the maximum driving torque of the inner mechanism increased by 28.8%; when the hinge friction parameter was in the range of 0~0.05, the maximum torque of the inner and outer mechanisms increased by 8.6% and 8.4% respectively. In engineering applications, the lubrication of each spherical hinge should be increased, the driving speed should be reduced, and the manufacturing and assembly accuracy should be improved.To a certain extent, it can prevent failures and improve the reliability of the flap mechanism.

Dynamics simulation of large civil aircraft complex multi-hinge space flap mechanism was studied, and a set of dynamics simulation modeling method of complex multi-hinge space flap mechanism based on Motionview was proposed. Firstly, a moving digital prototype of the complex multi-hinge space mechanism was constructed. The multi-point constraint RBE3 element was used to associate the intersection points of the rigid multi-hinge mechanism to the body of the flap surface considering flexibility, and the rigid-flexible coupling dynamic model of the flap mechanism was formed. The dynamics simulation of the mechanism was carried out under the aerodynamic load conditions of cruise, take-off and landing, the driving torque and hinge point load dynamics indexes of the complex multi-hinge space flap mechanism were obtained. The simulation results show that the driving arm of the inner mechanism bears most of the lateral load from the flap wing surface, the radial direction of the joints bearing at each hinge bears the aerodynamic pulling force from the flap wing surface. And the inner mechanism of the flap is the main bearing part, the load capacity of the inner rocker arm is almost four times that of the outer rocker arm. The dynamic simulation research can provide a certain reference for the design and improvement of the complex multi-hinge space flap mechanism.

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.