Design And Aeroelasticity Characteristics Analysis Of Flexible Wing With Variable Chordwise Camber

Since the invention of the aircraft,research on improving the aerodynamic performance of aircraft has been ongoing,the continuous advancement of materials science and manufacturing technology has provided the foundation for the current research of variable-camber wings.However,due to the limitations of its own mechanical structure and driving method,the chordwise bending mechanism of traditional rigid wing is complicated and heavy,which hinders the further improvement of the performance of the wing.Therefore,it is necessary to innovate the wing chord bending mechanism and the driving device design and analyze static and dynamic aerodynamic characteristics.This dissertation starts from the actual demand of wing’s camber variability.A cantilever beam type variable camber trailing edge using flexible material is proposed.The memory alloy wire is used as the drive,and the wing is continuously and smoothly curved in the chord direction under the driving force.Firstly,the study uses the constitutive equation of the memory alloy wire to obtain the relationship between the temperature and the tensile force of the memory alloy wire.Then,based on the chain beam constraint model,the flexible trailing edge of a large-deformed curved cantilever beam is statically modeled to obtain a model of force and flexible trailing edge deformation,thereby obtaining the trailing edge configuration under different forces.Numerical simulations were carried out in the Fluent environment,and the aerodynamic performance parameters such as the lift coefficient,drag coefficient,lift-drag ratio of the variable-camber wing proposed in this dissertation were compared with the traditional rigid wing.It is verified that its performance has obvious advantages over traditional wings.A three-degree-of-freedom aeroelastic model of the wing considering the flexibility of the chordwise mechanism is established.The aeroelastic stability of the flexibly variable-wing wing and the flutter characteristic are analyzed and discussed.The condition range under which the introduction of structural flexibility does not affect the critical flutter speed of system is obtained.