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 %.
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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 > 21201-(S1) Undergraduate Thesis |
| Depositing User: | 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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