DESIGN, PERFORMANCE EVALUATION AND CONTRIBUTION OF EACH COMPONENT OF DUCTED FAN UAV IN HOVER

摘要

The ducted fan UAV is designed to achieve high efficiency in hover. Momentum and blade elementrntheories are used for the blade design, and ideal twist and taper are adopted to reduce induced power.rnExperiment is constructed to investigate aerodynamic characteristic which is measured by 6 componentrnbalance. In hovering test, thrust and torque with various rotor rpm are measured and compared withrndesign parameter. Moment variation due to deflection of control flap is also investigated. Simulationrnmodel consists of duct, fan and fuselage. Stators and control flaps are not considered in this simulation.rnVariation of thrust and torque with rotational speed of fan is observed in hovering condition.rnAerodynamic characteristics of each component of UAV can be obtained by numerical simulation. Ductrnproduces thrust which is about 30% of total thrust. As the tip gap increases, the rotor and duct thrustrndecrease. When tip gap increases, vortex leakage is also increased and it makes the thrust decreased.rnThis paper described investigations on strut effect for the strut drag and the rotor thrust.