Abstract
This research will try to design a low cost of fixed-wing unmanned aerial vehicle (UAV) using low-cost material that able to fly autonomously. Six parameters of UAV’s structure will be optimized based on basic airframe configuration, wing configuration, straight wing, tail configuration, fuselage material, and propeller location. The resulted and manufactured prototype of fixed-wing UAV will be tested in autonomous fight tests. Based on the flight test, the developed UAV can successfully fly autonomously following the trajectory command. The result shows that low-cost material can be used as a body part of fixed-wing UAV.
Highlights
Utilization of Unmanned aerial vehicle (UAV) has grown significantly especially for fixed wing and rotary wing type
The UAV is controlled by the pilot in the ground control station
Conventional tail configurations are the most common configuration used in UAVs
Summary
Utilization of Unmanned aerial vehicle (UAV) has grown significantly especially for fixed wing and rotary wing type. UAV can fly autonomously based on programmed flight plans into the flight controller board. Many users/hobbyist build fixedwing Unmanned Aerial Vehicle (UAV) by themselves, they have to design, calculate aerodynamic performance, and manufacture the UAV by themselves. They have to decide which mechanical and electrical components needed in order to build the UAV that can perform as intended. The parameters are basic airframe configuration, wing configuration, straight wing, tail configuration, fuselage material, and propeller location. Six design configuration structures will be considered i.e., basic airframe configuration, wing configuration, straight wing, tail configuration, fuselage material, and propeller location.
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