Research On Aerodynamic Models And Flight Simulation For An Unmaned Aecrial Vehicle

A series of wind tunnel test and aerodynamic analysis for one unmanned aerial vehicle(UAV) model are carried out in this research,that not only provides help for the comprehensive analysis of this UVA's peformance,but also offers a kind of referring research model or way for other aircrafts.The wind tunnel test for different angels fo attack and sideslip of the UVA model was carried out in NH-2 low speed wind tunnle.Moreover,in order to choose the best canard aerofoil,four kinds of the canard were test in the wind tunnel.Another four kinds of aerodynamic configuration experiments were also carried out so as to analyse the characteristics of different aerodynamic configurations and choose the best aerodynamic configuration.By comparing the aerodynamic data of the test model with winglet and without winglet,lift enhancement effect of winglets can be confirmed. In this thesis, the aerodynamic model and aerodynamic models of rudder used in simulation both are built on numerous test data obtained through the wind tunnel tests.Based on the aerodynamic data of the model in different angels of attack and sideslip,the aerodynamic models decided by angel of attack and sideslip as well as lift coefficient are established through the method of fuzzy logic.The result shows the proper model structure and its applicable condition.Futhermore,the fuzzy logic model established above can predicte the aerodynamic force of test model in unknown attitude.Lastly,apply this fuzzy logic model to different aerodynamic configuration to indicate its reliablity.Based on the aerodynamic data related to the control surface of the UAV model,the aerodynamic models of rudder,elevator and aileron are established to conduct flight simulation.By means of mix model used in flight simulation,the hover state and steady flight state are simulated.