To improve the flight efficiency and multi-mission adaptability of aircraft

a morphing wing framework for both high and low speed conditions is designed

and the position optimization and quantity arrangement of distributed drivers inside the morphing wing are studied. Firstly

based on a wing rib swing mechanism

a parallel linkage morphing wing mechanism with variable chord length

variable sweep

variable area

and variable aspect ratio was designed. Taking element size as the parameter

the aspect ratio and degree of wing rib swing were analyzed to obtain the variation curve of wing parameters. Then

a structure unit that contains the wing skeleton

actuator and flexible skin was chosen as the research object. Equivalent spring stiffness of the flexible skin was measured by an experimental method. Based on the principle of virtual work

a quasi-static mechanical analysis method was adopted to obtain the mechanical model of structure unit. Taking the deformation of the unit as the objective optimization function

the optimal driver position and initial state of the skin were obtained by the Matlab optimization toolbox fmincon function

and the experimental verification was carried out. Lastly

Ansys was used to simulate the coupling effect of multi-unit mechanism motion and elastic deformation

and the final equilibrium state of the mechanism under the layout of multiple drivers was obtained. The detailed structure of the morphing wing is designed and the prototype is fabricated and assembled. The results show that the balanced deformation of wing is related to the driver layout and structural stiffness. When the structural stiffness of the mechanism is enhanced

the deformation caused by distributed actuator and single actuator converges to the ideal value. The distributed drive will maximize the deformation

which is more suitable for the wing with low stiffness structure. Prototype of morphing wing can realize continuous deformation.