Keywords:Unmanned Aerial Vehicle, Vertical Take-off and Landing, Airfoil
This paper present a design and development of a fixed-wing vertical take-off and landing unmanned aerial vehicle. Aircraft structure is designed based on tilt-rotor by using tree rotors system. Analyzed five airfoils using the XFLR5 program including S1223, E397, NACA-2411, FX-63137sm and Clark Y. The FX-63137sm is the best results for the wings and select the NACA-2411 for the empennage. Design a stabilize mechanism about the pitch axis using the servo-motor connected in a four-bar Linkage configuration. A stabilize mechanism for roll axis to cancel unbalance torque using four-bar linkage too. Finally, the propeller system is tested for thrust characteristic by the relationship between the control signal from the radio controller in the percentage of throttle and the trust from the motor-propeller system necessary for design an automatic flight controller. The relationship is linear, with a maximum power of 1,700 g when the throttle is in the maximum power position.
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