Overall Scheme Design For Light And Small Rotor UAV

The non-powered autorotating rotor is used as the lifting surface and the control surface,and uses the propellers’ push/pull as the driving force.The structure of the light and small spin-rotor UAV is simple,the manufacturing and maintenance cost is low.The operation is simple,the flight control is easy to realize,and the low-altitude is good.Low speed performance and safety,and low requirements for take-off and landing,the spin-rotor UAV has its unique advantages compared to helicopters and fixed-wing aircraft.With the development of unmanned aerial vehicle technology and the continuous expansion of market demanded,the light and small spin-rotor UAV drones came into being.However,there are still few studies on the overall scheme design technology of the light and small spin-rotor UAV.And a complete and reliable overall solution has not yet been formed.According to the design requirements,the overall design technology of the light and small-sized spin-rotor UAV is studied in this paper.Firstly,the main parameters of the spin-rotor UAV are determined by referring to the overall parameter design method of helicopter,and the matching engine is selected.Secondly,the longitudinal aerodynamic force,aerodynamic moment and flight performance of the spin-rotor UAV are calculated.Finally,the mathematical model of the spin-rotor UAV is established,and the control characteristics of the spin-rotor UAV in the aspects of climb control,flat flight control and glide control are studied.The corresponding climb,flat flight and glide control loops and control laws are designed,which are available for the spin-rotor UAV.Through the research on the overall design scheme of the light and small-sized spin-rotor UAV,this paper completes the overall layout design of the spin-rotor UAV,establishes the mathematical model of the spin-rotor UAV,designs the control strategies of the climbing,flattening and sliding control of the spin-rotor UAV.The stability and validity of the longitudinal control system of the light and small spin-rotor UAV is verified by the flight simulation of the whole longitudinal profile.