The Trailing Edge Structure Design Of Camber Morphing Wing Based On Flexible Structure

The Camber morphing wing is one of the key technologies for the realization of morphing aircraft.The change of wing camber can bring advantages such as increased aircraft controllability,shortened take-off and landing distance,improved lift-to-drag ratio,increased range,and reduced energy consumption.At present,flaps and ailerons are used in traditional civil airliners to achieve the purpose of changing the camber of the wing,but the deformation of the traditional structure is discontinuous and the mass is large,so this paper proposes a structure based on the flexible structure of the trailing edge of the camber morphing wing design scheme and research its deformation performance.Aiming at the application of flexible structure in camber morphing wing,based on the purpose of realizing the deformation of camber morphing wing,this paper proposes a design scheme for the trailing edge of camber morphing wing based on fishbone flexible structure,applying zero poisson’s ratio fishbone flexible structure As a structure for achieving camber deformation,pneumatic muscles,smart actuators,are used for driving,and high-flexibility silicone rubber materials are used as skins to complete the overall structure design of the wing.the geometrically nonlinear chain beam constraint model is used to predict and analyze the deformability of the flexible structure,and analyze the influence of the change of the structural stiffness characteristics on the structure design under the condition of large deformation,and optimize the multi-scale size of the flexible structure part of the wing design.Based on the finite element analysis technology,the integrated model is simulated,and the nonlinear actuator pneumatic muscle is introduced as the driving device.The nonlinear output characteristics are simulated and restored in the finite element software,and the fishbone flexible structure with the large-flexibility skin model are established.The finite element model of the integrated sample of the camber morphing wing.The camber deformation of the wing under different driving forces and driving air pressure is simulated and analyzed.the deformation calculation results of the chain beam restraint model are compared,the error is analyzed,and the stiffness parameters of the chain beam restraint model are corrected.Manufacture camber morphing wing rib specimens for deformation verification test,manufacture fishbone flexible structure wing ribs,matching pneumatic muscles and high flexibility skins,assemble them into camber morphing wing samples and establish verification test devices.Non-load deformation,load-bearing deformation and repeat deformation of camber morphing wings are test to verify the deformation capacity,load-bearing deformation capacity and repeated deformation accuracy of the camber morphing wing model.Comparing test results with the simulation analysis,this paper analyzes the causes of errors and insufficient experimental deformation,proposes and applies improved methods to improve the design of the trailing edge of the camber morphing wing.