The Method Of Partial Dynamic Equivalence And Aeroelasticity Research In Folding Wing Tip

At present,more and more researchers and research institutions have discovered the potential of folding wingtip technology and carried out a wide range of aeroelasticity studies.However,folding wingtip technology involves multi-variable,multi-disciplinary and multistrategy cross-optimization solution,so it has considerable complexity and calculation amount.In the light of the pneumatic folding wing tip elastic problems,is put forward based on the part of the dynamic equivalent method is simple and rapid for folding wing tip model of pneumatic flexible assessment and the technical development,at the same time,through to the wing model and parts of the equivalent plate model in the simulation results are validated preliminarily,and applied to the exhibition string than model and small folding wing tip aerodynamic elasticity research work.The effects of different folding design variables on the aero-elasticity of the folding wing-tip model were obtained.The specific content of this paper is as follows:Basic equation was deduced based on the elasticity of pneumatic folding wing tip plate model of structural dynamics equations of motion,and put forward the part according to the equation of dynamic equivalent method,uniform appearance and wing model was established,and the structure of the part quality and stiffness equivalent model of tablet,at the same time,through the simulation calculation contrast the characteristics of both structural dynamics and pneumatic elastic properties.The effectiveness of using partial dynamic equivalence method to carry out aeroelastic evaluation of large aspect ratio and small aspect ratio model is verified,and the feasibility of applying it to the development of folding wingtip technology is subsequently explored.Aerodynamic characteristics research was carried out by folding wing tips,different folding in subsonic aircraft wing Angle,different Mach number,and folding exhibition long aerodynamic characteristics under different Angle of attack has carried on the preliminary calculation,and through the literature research and the form of summarizing,supersonic aircraft XB-70-fold wingtip r&d process and flight performance.Thus,the application form of large/small aspect ratio wing folding wingtip is further established,which provides design reference and research direction for subsequent foldable wingtip models.To make the string than adaptive wing folding wing tip model and small aspect ratio wing active folding wing tip model of pneumatic elasticity change research,and will be part of the equivalent plate model and the wing model of structural dynamics analysis and aeroelasticity,comparing the calculation results preliminarily verified using part of the dynamic equivalent method of the feasibility of the technology development.At the same time for adaptive folding wing tip design fixed wing tips and active folding design,respectively,to carry out different folding design variables of pneumatic elastic analysis,including structural dynamics analysis,flutter analysis,flight load calculation,the discrete gust response,reveals the different folding design variables for the folding wing tip model of pneumatic elastic effect.It also provides a reference and design basis for the subsequent research on folding wingtip technology.