Control System Design And Simulation Research Of An Unmanned Aerial Vehicle

At present,most of the mission load of industry UAVs is less than 10 kg and takeoff weight less than 60 kg,which cannot meet the requirement of flight platform mission payload between 20 ～ 200 kg for large-scale geographic mapping,hydrological survey,ocean survey,petroleum and mineral exploration.However,design a new UAV involving the overall design,aerodynamic design,structure design,strength design and control system design,and all the other aspects content.It also needs to get the airworthiness certification form CAAC,which will cause great stress for the enterprise in research time and costs.So,it is significant to research an UAV that alternative by a light sport aircraft.First of all,there is little relevant literature about this kind of research in domestic and abroad,so the research is academic.Secondly,it can save a lot of research time and costs by this method,and it is also easier to get the airworthiness certification from CAAC.Based on the above ideas,this research aims to design an automatic pilot system for a light sport aircraft and transform it into a UAV.And this paper studies the controller design of the automatic driving system which is the core content of this project.First,the paper studied and analyzed the technical characteristics of the UAV body,and calculated the aerodynamic derivative required by the aircraft dynamics model according to the basic parameters of the aircraft,then built the longitudinal and lateral-direction dynamics mode of the aircraft.At the same time,make the longitudinal and lateral-direction control system design indicators according to the relevant standards and combined with the aircraft flight quality requirements.Second,design the control system based on the longitudinal and lateral-directional dynamic model.The longitudinal control system design includes design of the Pitch Angle control system,Altitude Control System and Airspeed Control System.The lateral-directional control system design includes the design of Roll Angle Control System and the Yaw Angle Control System.The controller mainly adopts PID controller,and the design mainly completes in Simulink.The design covers the control content required by the normal flight of aircraft.Finally,compared the result that simulated under Simulink platform of the controller with the design indicators,which proves that the controller performance can meet the design indicators.