Design And Optimization Of A Shear Sliding Skin Variable Sweep Wing Based On Thermal-fluid-solid Multi-field Coupling Analysis

The variable sweep wing can adjust the flight characteristics and improve the speed range by changing the sweep angle,which is very attractive to improve the Mach number of supersonic aircraft.However,when studying the variable sweep wing of high-speed aircraft,many scholars mostly adopt the rotary variable sweep wing rather than the shear variable sweep wing with better aerodynamic characteristics,because it is difficult to design such a shear variable sweep wing that can withstand the complex hydrodynamic and thermal environment under high-speed airflow and meet the requirements of the win g skin to adapt to deformation,there is still a wide research space for the shear variable sweep wing with high load.This paper focuses on the design and research of the shear variable sweep wing used in supersonic flight,sliding skinning schemes of shear-type variable sweep wing which can realize continuous aerodynamic shape change are proposed,and according to the determined scheme proposed the segmentation strategy of sliding skin surface.The skeleton mechanism is designed according to the deformation action of the skin sheets,and then the structural characteristics are analyzed and optimized by aerodynamic force and thermal analysis.First of all,analysis of the shear type variable sweep wing deformation characteristics,puts forward the sliding skin of shear type variable sweep wing deformation scheme,establish the sliding skin segmentation strategy calculation model.By analyzing the aerodynamic characteristics of two-dimensional airfoil profile before and after wing skin deformation,which is verified that the skinning scheme satisfies the condition of continuous aerodynamic shape change and has the ability to optimize the flight characteristicsSecondly,the skeleton mechanism associated with the skin deformation is designed.According to the sliding skin deformation characteristics,the configuration of the associated mechanism was determined,and the kinematic characteristics of the reference points of each skin surface were calculated by kinematics.Based on the load transfer analysis,the structure of wing skeletons and the sealing structure between the sheets are preliminarily designed.The kinematics model and the stress of the skin sheets stitching in the process of deformation were verified by Recur Dyn simulation.Finally,considering the aerodynamic heating received at supersonic speeds,the thermal analysis model of the shear variable sweep wing structure was established.The heat transfer between the flow field and the skin,the heat distribution mechanism and the thermal modes of the st ructure were calculated by ANSYS numerical simulation,analysis of the dynamic characteristics of variable sweep wings with different flight speeds and different shapes.Based on this,the aerodynamic force of the structure was considered to calculate the stress condition of the structure.Based on the thermal fluid-solid coupling calculation results,the lightweight design of the variable sweep wing skeleton structure was carried out by using topology optimization,and the optimization results were verified by comparing the total strain energy.