Rancang Bangun Dan Analisa Sistem Kendali PID Pada Unmanned Aerial Vehicle (UAV) Fixed Wing

Mulia, Arifin (2016) Rancang Bangun Dan Analisa Sistem Kendali PID Pada Unmanned Aerial Vehicle (UAV) Fixed Wing. Undergraduate thesis, Institut Teknologi Sepuluh Nopember.

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Abstract

Aplikasi control sistem dalam bidang aeronautika semakin meningkat setiap harinya. Integrasi dari kedua cabang ilmu tersebut menghasilkan kendaraan tanpa awak atau sering disebut dengan UAV (Unmanned Aerial Vehicle). UAV diciptakan dari kolaborasi bidang ilmu aeronautika, instrumentasi, dan teknologi sistem kontrol. Pertama kali digunakan UAV hanya digunakan oleh militer, namun saat ini masyarakat civil juga menggunakan UAV dalam kehidupan sehari-hari. Pada penelitian Tugas Akhir ini dirancang dan dibangun sebuah pesawat Fixed wings UAV dengan missi aerial mapping. Tahapan dalam penelitian tugas akhir ini yaitu perancangan pesawat Fixed wing UAV, analisa struktur, dan kemudian perancangan sistem kontrol pesawat Fixed wings UAV. Perangkat lunak yang digunakan untuk menunjang penelitian ini yaitu perangkat lunak MATLAB Simulink, DATCOM dan CATIA. Dari penelitian ini disimpulkan bahwa hasil analisa struktur pada bagian sayap sebesar 2.21 Mpa. Hasil simulasi system control Konstanta PID gerak pitching diperoleh Kp =10, Ki = 14, dan Kd = 0.6. Gerak rolling diperoleh konstanta Kp = 0.45, Ki = 4, dan Kd = 0.8. Gerak yawing diperoleh konstanta Kp = 10, Ki =1.4, dan Kd = 8.5. Respon transient yang didapatkan dengan konstanta PID tersebut dihasilkan, untuk gerak pitch rise time = 0.265 detik, settling time = 4.07 detik, dan overshoot = 9.8%. Sedangakan untuk gerak rolling rise time = 0.0737 detik, settling time = 5.27 detik, dan overshoot = 6.8%. Untuk gerak yawing respon transient yang dihasilkan rise time = 0.0382 detik, settling time = 0.369 detik, dan overshoot = 12 %. ================================================================================ System control applications in the field of aeronautic is increase every day. The integration of these two branches of science produces unmanned aerial vehicle (UAV). Uav created from collaboration in the field aeronautical science, instrumentation, and control system technology. The first UAV is only used by millitary, but civil is now using uav for their work. In this final project was designed and built an Unmanned aerial vehicle Fixed Wing. Stages in this research is study of literature, CAD modelling fixed wing UAV, structural analysis, and design flight control system fixed wing uav. The software used to support this resarch is MATLAB Simulink, Datcom, and Catia. The result of this research structure of the wing of 2.21 Mpa. The result PID control system for pitching motion Kp = 10, Ki = 14, and Kd = 0.6. Rolling motion obtained Kp = 0.45, Ki =1.4, and Kd = 8.5. Yawing motion obtained Kp = 10, Ki = 1.4 and Kd = 8.5. Transient respond obtained from PID constanta for pitching motion rise time = 0.265 second, settling time = 4.07 second, and overshoot = 9.8%. Rolling motion, rise time = 0.0737 second, settling = 5.27 second, and overshoot 6.8%. Yawing motion, rise time = 0.0382 second, settling time = 0.369 second, and overshoot = 12%.

Item Type: Thesis (Undergraduate)
Additional Information: RSM 629.831 2 Mul r
Uncontrolled Keywords: Aerial Mapping; Drone; Fixed wing UAV; Pesawat Tanpa Awak
Subjects: T Technology > TJ Mechanical engineering and machinery
T Technology > TL Motor vehicles. Aeronautics. Astronautics
Divisions: Faculty of Industrial Technology > Mechanical Engineering > (S1) Undergraduate Theses
Depositing User: Mrs Anis Wulandari
Date Deposited: 07 Jun 2017 07:12
Last Modified: 27 Dec 2018 03:01
URI: http://repository.its.ac.id/id/eprint/41521

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