Topology Optimization Of Adaptive Wing Composite Compliant Mechanism

The application research of the compliant mechanism of the leading and rear edges of the wings has become a hot spot in aircraft design.Compared to the traditional wings,adaptive wings can automatically change the leading and rear edge structures shape as the flight conditions change,thereby the flight performance of aircraft can be improved.At present,the research on topology optimization of the compliant mechanism of the leading and rear edges of the wings is mainly based on isotropic materials.Compared with isotropic materials,fiber-reinforced composite materials have superior material properties and are widely employed in aircraft structures.The compliant mechanisms of composite wings are more advantageous in terms of structural weight reduction and engineering applications.Firstly,this paper gives a brief introduction to the development history of flexible wings and the research situation in China and abroad,Secondly,the principle of continuum topology optimization is introduced.The topology optimization interpolation model of single-phase material and multi-phase material of rigid and flexible structure is discussed and established respectively.Some numerical instability phenomena and processing methods in the process of topology optimization are investigated in detail.Thirdly,the basic principle of Discrete Material Optimization(DMO)method is introduced.By the use of the DMO method,the topological optimization design of the rigid and compliant structures of composite materials are carried out in combination with the alternating active phase algorithm.Finally,the NACA2418 standard airfoil leading edge is taken as the research object,and the topology optimization design of single-phase material and composite compliant mechanism of leading edge are completed respectively in terms of DMO method.The DMO method is combined with the topology optimization to select the deviation of the actual displacement and the target displacement of the 10 coordinate points on the initial curve of the leading edge as the objective function,and the interpolation formulas of DMO method is utilized to establish the composite material optimization model,which is solved by the OC optimization criterion method.The MATLAB codes are compiled to calculate the optimization problem and a distinct result image is obtained.The CATIA software is used to model the topology image in three dimensions,which is imported into Hyperworks software for simulation analysis to verify the feasibility of the method.