Flight Control System Of The Small Ground Effect UAV

Ground effect plane is a special aviatic tool that changes the aerodynamic characteristics of the wing based on the ground effect principle to increase the lift of the wing so that it can stably fly close to the ground or water surface in the ground effect area.From the current research and development status of ground effect plane both at home and abroad,although various countries have mastered certain techniques for ground effect plane research,their stability during flying cannot be soluted due to their particularity of flying close to ground/water surface.Therefore,it is even rarer to apply this kind of aircraft to the field of unmanned aerial vehicle.However,as time goes by,mamy countries have improved their technologies and theories in information technology,and computational fluid dynamics has also made breakthrough progress.Researching on the ground effect unmanned aerial vehicle through aerodynamics has gradually become a trend of development of the times.At the same time,the flight control system as a key part of control system of the ground effect unmanned aerial vehicle needs to complete real-time monitoring,mission of managing,data of acquiring and processing during the entire flight of the ground effect unmanned aerial vehicle.Therefore,the ground effect unmanned aerial vehicle control system which has high efficiency and good stability still has considerable research value.Firstly,this thesis introduced many simulation methods applied in aerodynamics simulation comparatively.Secondly,the relevant principles of computational fluid dynamics and the numerical solution process are briefly outlined.Then the “Kitty Hawk”effect plane developed by Russia was chosen as a prototype to simulate the flying process of a smal-scale unmanned aerial vehicle,and its aerodynamic characterist ics were analyzed and studied.In specific implementation,the three-dimensional model of the prototype was built by CATIA.The model was then meshed into the ANSYS and finally imported into FLUENT for numerical calculations.The results were analyzed for aerodynamic characteristics.Based on the results of the previous aerodynamic simulation,the model of NFD-S288 ICON A5 was selected as the amphibious model aircraft to improve the hardware and software of the ground effect unmanned aerial vehicle system.In the hardware,the flight control and mission management are separately controlled,and two STM32F103ZET6 chips are used as the master controller.The overall plan of the flight control system is determined to be based on the dual-chip system,the aim is to accomplish the task of flying steadily and controling algorithm of the ground effect unmanned aerial vehicle.The main control module,onboard sensor module,servo module and combination height measurement module of the ground effect unmanned aerial vehicle flight control system are established on this platform,and the design of system is completed according to the modularized idea;the design of the software is to serve the functions of the hardware modules.Therefore,according to the design idea of the hardware modules,the underlying unit module of software driver was designed.Finally,based on the inherent characteristics of the ground effect unmanned aerial vehicle,the strapdown inertial navigation system algorithm,the heading angle data fusion algorithm,and the altitude information fusion algorithm are used to analyze the attitude,speed,position,and other information of the ground effect unmanned aerial vehicle during flying.The deviation of the data is simulated by MATLAB.Simulation results show that the deviation of the ground effect UAV flight control system is within a reasonable range.The design of this system is reasonable and has long-term value of researching.