Analysis And Research Of Small Scale Unmanned Helicopter And Its Flight Control System

Advantage of the helicopter is the capable of vertical take-off and landing, side tofly, hovering, etc. Due to the flexibility of changing their flight strategy, even in arestricted area for fixed-wing aircraft, the helicopter can be free flying and hovering inthe air for a long time. So small scale unmanned helicopter with autonomous flightcapability is popular used in military and civilian aspects, for example, geographydetection and aerial, combat attack, and so on. However, the unmanned helicopter is anonlinear, strong coupling and non-stable dynamical system, it’s susceptible interferedby the wind. So the unmanned helicopter flight control technology has become a hottopic to universities and research institutions in many countries.This paper firstly analyzed the domestic and international research cases, thenintroduced the flight principle and characteristics of small scale unmanned helicopter,established the mathematical model, analyzed pressure distribution of body surfaceusing fluid simulation software, discussed using fuzzy adaptive PID in small scaleunmanned helicopter’s pitch control and did some simulation. At last, designed theflight control hardware system, including power modules, barometric altimeter module,gesture sensing module, satellite positioning module and data memory module, then didproduction and testing to some modules.In the aspect of flow field simulation, firstly drew the model in CATIA, thenmeshed the model using ANSYS ICEM CFD, get the small scale unmanned helicopterbody’s unstructured volume mesh, imported the grid data into ANSYS FUENT tocalculate, finally got the pressure distribution of the fuselage surface.In the research of pitch control, designed a fuzzy adaptive PID controller usingfuzzy control toolbox which provided by MATLAB, after programming and operating,got the step response of controller. Compared with the traditional PID method, fuzzyadaptive PID control algorithm was proved more effective.In the aspect of flight control hardware system, used TMS320F2812as the flightcontrol computer, after fully taking weak capacity of load carrying and battery poweredinto account, chose L3G4200D and LSM303DLHC as the gesture sensor, choseMS5611-01BA03as the barometric altimeter. Moreover, chose BD navigation andpositioning chip with independent intellectual property rights as the satellite positioningmodule, and a detailed analysis of its performance and testing was provided. In the aspect of software architecture, completed the work that using minimumsystem board to analyze and test every modules.