Conceptual Design of Hybrid UAV

Abstract

Hybrid aircrafts are unique type of aircrafts that combine the hover capability of helicopters with the speed and range of airplanes. In this work, we propose a novel hybrid aircraft based on the fixed-wing airplane and quad rotor structures. A complete mathematical model of the aircraft, in helicopter, transition and airplane flight modes is presented. Finally, simulation results are presented in order to illustrate performances of the proposed controller. The proposed UAV structure configuration is similar to V-22 osprey however it is designed based on the propeller thrust instead of jet-engines In any hybrid aircraft, the transition between hover flight and cruise flight is the most difficult regime to achieve and convertible rotor aircraft are no exception to this The design has been developed as UAV which is propelled by motors which has all the abilities of flight controls equipped in a single body. Which has a specification of weight up to 4kg's Future work will consist of creating a more detailed model for lift and drag. Nomenclature Q=dynamic pressure =fluid density = true airspeed A is the aspect ratio, M = Mach number CL = lift coefficient Cd=coefficient of drag G = climb gradient í µí»™= turn rate. Meff = Effective Mach number Re=Reynolds number Cr=root chord Ct=tip root Cm=pitching moment