The Scheme Design Of The Uav Morphing Wing And Simulation Analysis

With the rapid development of new technologies and the growing demand aboutthe aircraft flight efficiency in various environments, multitasking ability and flexibility,the research on smart morphing wing is drawing more and more attention from manyresearchers in many countries. The morphing wing changes wing sweep angle, wingarea, etc during the flight process to improve the aircraft’s flying efficiency and increasethe flexibility of aircraft. Many research institutions at home and abroad studied thesmart morphing wing and achieved a degree of research results, in order to obtain theleading position in this field in the future. In this paper, using the UAV wing as theresearch object, through a combination of shape memory alloy actuator and institutions,established a smart morphing wing solutions and virtual prototype.In this paper, firstly, the re-configuration of the wing of the morphing aircraft wasresearched, put forward deformation scheme of variable sweep. According to the motionand load characteristics of variable sweep angle in the mechanism scheme, researchedthe characteristics of shape memory alloy in the shape memory alloy wire-drivenvariable swept angle structure, on the basis of this, the shape memory alloy actuator wasdesigned and the model was established, designed and simulated the coaxialmagneto-rheological fluid brake. completed the full program variable sweep anglestructure design.Researched the stretched out structure scheme of the morphing wing, completed acomparative analysis of the structure of variable span, including screw guide railstructure, rack and pinion structure, shear hinge unit combination structure. Determinedto use the shear hinge unit combination structure as the scheme of variable wing span,researched the shear hinge unit combination structure and completed the geometricdesign and mechanical analysis and the design of the shear hinge unit, completed thedeformation of wing span scheme.Integrated the variable sweep angle for the design of programs and the variablespan schemes, and completed the design of the entire three-dimensional deformationmodel programs and the establishment of the entire program and the virtual prototypemodel. The problem of spanwise rigidity of structure deformation in smart morphingwing was checked. Through the contact stress analysis of finite element software, thestress between three sections of the wing is simulated, and determined the stressdistribution in the structure. According to the characteristics of the stress distribution,used the ADMAS software to do the kinematics analysis of the deformation mechanism.Simulated the kinematics of the deformation mechanism, through the simulation analysis to the deformation mechanism in the actual use of the process provides areference.