The Structural Design And Simulation Analysis Of Wing With Variable Swept Angle

Deformation intelligent vehicle has become a research hotspot at home and abroad.Through intelligent deformation technology,the shape parameters of aircraft can be changed to keep the best flight parameters during flight,and then improve the flight performance of aircraft.Common deformation modes in deformable intelligent aircraft include front and rear edge deformation,wing folding,wing torsion and wing sweep angle change.Among them,the deformation of variable swept wing belongs to the research of large deformation variant aircraft.It is very important to optimize the position and number of actuators in deformable wing structures.Optimizing the position of the actuator can make the deformed wing drive better,improve the utilization of the actuator and reduce the energy loss.Therefore,UAV variable swept wing technology is one of the most important topics in the field of intelligent aircraft research in recent years.The basic design idea of variable sweep wing technology is to rotate the wing forward and backward to change the sweep angle,so that the aircraft can take into account both the aerodynamic requirements of high-speed and low-speed flight,and expand the range of flight speed.Specifically,when the aircraft takes off,lands or needs to fly at low speed,the wing rotates forward to reduce the sweep angle,so as to improve the low-speed flight performance and shorten the landing and taxiing distance of the aircraft;when the aircraft needs to fly at high speed,the wing rotates backwards to increase the sweep angle,so as to reduce the flight resistance and improve the high-speed flight performance of the aircraft.Thus,the variable swept wing technology can solve the contradiction between high and low speeds of supersonic aircraft and improve the take-off and landing performance.By reviewing the research status of deformable wing at home and abroad,it is found that the deformable wing mechanism is large in volume and heavy in weight,and can not be directly reduced to be used in small UAVs.In this paper,a single crank and double rocker mechanism is designed to realize that the wing of a small UAV can be deformed in flight,to obtain the best aerodynamic force at different flight speeds,to save fuel and to improve cruise time.In this paper,a single crank and double rocker mechanism is designed around the realization mechanism and key technology of UAV maneuvering structure in intelligent deformable aircraft.The mechanism is simple,portable,and the transmission efficiency is high.It can realize the change of UAV sweep angle in flight according to environmental requirements.The realization of the whole mechanism drives the worm wheel and worm by motor,then drives the crank mechanism to move,and finally changes the flight state of theUAV wing.In this paper,the model of variable swept wing mechanism is established by using three-dimensional modeling software Pro/E.According to the reference size,the virtual prototyping technology ADAMS software is used to model the mechanism,and the angle difference between the two rockers is reduced to less than 0.72 degrees by optimizing the design.Then the three-dimensional model is built in Pro/E software by means of optimizing the size.The kinematics and dynamics of the model are analyzed by virtual prototyping software ADAMS,and the single crank and double rocker mechanism is optimized to further improve the synchronization of the wing.Then the strength of the rod is checked by the force simulation curve of the key parts in ADAMS simulation,and the feasibility of the mechanism is verified.Finally,ANSYS software is used to analyze the honeycomb structure for the hexagonal snake wing skin structure,which lays a foundation for the realization of UAV variable sweep wing.