Design of Transition Mode Control System of Tilt-Wing UAV
Tilt-Wing UAV (Unmanned Aerial Vehicle) is a type of aircraft which has wing that can be rotated. The tilt-wing mechanism is implemented to increase the performance of the aircraft. This aircraft is capable of doing vertical take-off and landing (VTOL) like a helicopter and flying horizontally like...
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| Format: | Final Project |
| Language: | Indonesia |
| Online Access: | https://digilib.itb.ac.id/gdl/view/21219 |
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| Institution: | Institut Teknologi Bandung |
| Language: | Indonesia |
| Summary: | Tilt-Wing UAV (Unmanned Aerial Vehicle) is a type of aircraft which has wing that can be rotated. The tilt-wing mechanism is implemented to increase the performance of the aircraft. This aircraft is capable of doing vertical take-off and landing (VTOL) like a helicopter and flying horizontally like an airplane. <br />
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This report will present the design of controller system of tilt-wing UAV. The design will be focused in the transition mode of the vehicle. Transition occurs between vertical flight and cruise flight and vice versa. <br />
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The aircraft is controlled using PID controller. PID constants are tuned empirically. By observing the vehicle’s orientation data from the IMU (inertial Measurement Unit) sensor, vehicle’s stability can be detected. <br />
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Based on the experiment, the PID constants responsible for a stable flight are, Kp = 0,5; Ki = 0,05; Kd = 0,01; for pitch and Kp = 2; Ki = 0,1; Kd = 0,01; for roll. These results hopefully will be useful in the developments of tilt-wing UAV. |
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