Study On Telescopic Morphing Wing With Continue Wing Surface

In recent years,variable configuration aircraft has attracted wide attention in the field of scientific research.The variable configuration aircraft improves the flight efficiency of the aircraft by changing the shape of the aircraft,enabling it to achieve optimal flight performance in different flight environments.At present,the morphing of the variable configuration aircraft is mainly reflected in the morphing of the wing.This paper designs a morphing wing that increases the wing area and aspect ratio after the morphing is completed and ensures the continuity and integrity of the aerodynamic shape of the wing.The scheme and structural design of the morphing were accomplished.The kinematics,dynamics and aerodynamic analysis were completed.The prototype of the morphing wing was developed and its deployable function was verified.According to the design requirements of the aircraft to improve the lift-to-drag ratio of the wing and ensure the continuity of the airfoil,a variety of spanwise morphing and wing section morphing schemes were designed and compared,and the overall design scheme was finally determined.Considering the characteristic of the skin folding during the morphing process,a method of segmentation of the skin was studied,and the optimal segmentation scheme was determined with the largest internal space.The internal mechanism of the morphing wing was designed.Finally,the freedom analysis of the whole set of morphing wing mechanisms was carried out to ensure the feasibility of the mechanism principle.The kinematics model of the airfoil deployable mechanism is established,and its position,velocity and acceleration equations are established.The reference point position equation derived from the derivation and the given reference point parameters are used to synthesize the scale of the mechanism,and the optimization objectives and constraints are given.Thus,a set of structural parameters are determined in the numerical solution of multiple sets of structural dimensions;finally,the obtained structural parameters are substituted into the kinematics equation,and the analysis results are graphically processed by MATLAB to analyze the deployable performance of the mechanism.On the basis of kinematics analysis,the dynamic model of the airfoil deployable mechanism is established,and the position,velocity and acceleration mapping relationship between each moving components and the original moving components in the mechanism are analyzed in turn.The rigid body dynamics model of the airfoil deployable mechanism is established by using the virtual work principle,in order to analyzes the change of the driving force during the deployment of the morphing wing.Finally,complete the structural design of the telescopic morphing wing prototype,the processing and overall assembly of the principle prototype was completed to verify the deployable function.The result proves that the morphing wing mechanism can be smoothly deployed under the driving of three sets of screw nut mechanism,and has the function of increasing the wing area and the aspect ratio.The ADAMS software was used to simulate the kinematics and dynamics of the airfoil deployable mechanism to verify the correctness of the established kinematics and dynamics model;design and build a virtual prototype model of the telescopic mophing wing.Using FLUENT to study the lift-drag characteristics of the wing,compare the aerodynamic performance between the wings after morphing and the original wing.Especially,compare the aerodynamic performance between the morphing wing with continuous skin and the morphing wing without continuous skin.Simulation results show that after increasing wingspan,the lift-to-drag ratio of the morphing wing is significantly improved.The aerodynamic performance of the two types of telescopic wings is basically the same,but in the case of a small angle of attack,a telescopic wing with continuous surface provides a greater lift-to-drag ratio gain than that without continuous surface.