Fauzi, Wahyu Aji Artha (2026) Rancang bangun sistem avionic pada folded wing unmanned aerial vehicle (UAV) berbasis remote control. Other thesis, Institut Teknologi Sepuluh Nopember.
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Abstract
Penelitian ini bertujuan merancang sistem Avionic pada Folded Wing Unmanned Aerial Vehicle (UAV) berbasis Remote Control yang mampu beroperasi sesuai tujuan perancangan dengan dukungan Ground Control System (GCS), serta mengintegrasikan sistem Avionic yang meliputi Flight Controller Pixhawk 2.4.8, GPS, Telemetry 433 MHz, Receiver, Servo, ESC Hobbywing Skywalker 50A, motor BLDC Emax ECO II 2807, Power Module, dan baterai Li-Po 4S 1500 mAh untuk mendukung fungsi navigasi, komunikasi, distribusi daya, serta kendali penerbangan UAV. Metode penelitian meliputi observasi, studi literatur, perancangan sistem, pemilihan komponen, perakitan sistem Avionic, konfigurasi Mission Planner, serta pengujian bertahap berupa Bench Test, Ground Test, dan Flight Test. Bench Test dilakukan untuk mengevaluasi performa sistem propulsi melalui pengukuran thrust pada berbagai tingkat throttle, Ground Test untuk menguji komunikasi Telemetry, Remote Control, dan sistem daya, sedangkan Flight Test dilakukan untuk mengevaluasi kestabilan penerbangan dan jangkauan komunikasi. Hasil pengujian menunjukkan bahwa sistem propulsi menghasilkan thrust sebesar 0,322 kgf pada throttle 25%, 0,642 kgf pada 50%, 1,138 kgf pada 75%, dan 1,678 kgf pada 100%, dengan selisih performa terhadap spesifikasi pabrikan hanya berkisar 0,62–3,48%, sehingga menunjukkan bahwa sistem propulsi bekerja sesuai karakteristik yang diharapkan. Thrust maksimum menghasilkan rasio Thrust-to-Weight (T/W) sebesar 1,49 terhadap berat UAV 1,1412 kg, sehingga memenuhi kebutuhan gaya dorong untuk penerbangan. Pengujian Telemetry dan Remote Control menunjukkan koneksi yang stabil pada jarak 5–300 m, mulai melemah pada jarak 400 m, dan mengalami failsafe pada jarak 500 m. Sistem daya menghasilkan arus maksimum sebesar 53,6 A pada tegangan 14,8 V, sedangkan Flight Test membuktikan bahwa UAV mampu melakukan take-off, manuver, dan landing secara stabil selama sekitar 5 menit. Hasil tersebut menunjukkan bahwa sistem Avionic yang dirancang telah memenuhi tujuan penelitian dan layak diterapkan pada Folded Wing UAV berbasis Remote Control.
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This research aims to design an Avionic system for a Remote Control-based Folded Wing Unmanned Aerial Vehicle (UAV) capable of operating according to the design objectives with the support of a Ground Control System (GCS). The proposed Avionic system integrates a Pixhawk 2.4.8 Flight Controller, GPS, 433 MHz Telemetry, Receiver, Servos, Hobbywing Skywalker 50A Electronic Speed Controller (ESC), Emax ECO II 2807 Brushless DC (BLDC) motor, Power Module, and a 4S 1500 mAh Li-Po battery to support navigation, communication, power distribution, and UAV flight control. The research methodology consisted of observation, literature review, system design, component selection, Avionic system assembly, Mission Planner configuration, and staged testing, including Bench Test, Ground Test, and Flight Test. The Bench Test was conducted to evaluate the propulsion system performance by measuring thrust at various throttle levels, the Ground Test evaluated the performance of the Telemetry, Remote Control, and power systems, while the Flight Test assessed flight stability and communication range. The experimental results showed that the propulsion system produced 0.322 kgf of thrust at 25% throttle, 0.642 kgf at 50%, 1.138 kgf at 75%, and 1.678 kgf at 100%. The Bench Test indicated that the propulsion system performance differed from the manufacturer's specifications by only 0.62–3.48%, demonstrating that it operated according to the expected characteristics. The maximum thrust produced a Thrust-to-Weight Ratio (T/W) of 1.49 for a UAV weighing 1.1412 kg, indicating sufficient thrust for flight operations. Telemetry and Remote Control testing demonstrated stable communication within a range of 5–300 m, signal degradation at 400 m, and failsafe activation at 500 m. The power system delivered a maximum current of 53.6 A at a voltage of 14.8 V, while the Flight Test confirmed that the UAV successfully performed stable take-off, maneuvering, and landing with an effective flight duration of approximately 5 minutes. These results indicate that the designed Avionic system successfully achieved the research objectives and is suitable for implementation in a Remote Control-based Folded Wing UAV.
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