Perancangan Sistem Kendali Attitude Pada Pesawat Tanpa Awak Tipe Sayap Tetap Dengan Metode Fuzzy-PID

S, Nico Natanael (2016) Perancangan Sistem Kendali Attitude Pada Pesawat Tanpa Awak Tipe Sayap Tetap Dengan Metode Fuzzy-PID. Undergraduate thesis, Institut Teknologi Sepuluh Nopember.

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Abstract

Dinamika sistem UAV tipe fixed-wing secara sederhana dibedakan atas gerak matra longitudinal dan gerak matra lateral direksional. Dari matrik keadaan diketahui bahwa karakteristik UAV LAPAN Surveillance 02 (LSU-02) milik LAPAN stabil statis, namun pada analisa open loop dan root locus didapatkan bahwa sistem tidak mampu mencapai set point dan cenderung berosilasi, hal tersebut sangat berbahaya bagi plant yang bergerak cepat seperti pesawat. Telah dirancang sistem pengendalian attitude pada UAV tipe fixedwing dengan metode Fuzzy-PID. Hasil simulasi menunjukkan bahwa sistem kendali berjalan dengan performa sangat baik pada kedua matra dengan selisih rata-rata integral time absolute error (ITAE) sebesar 0.0204 radian serta selisih ratarata integral absolute error (IAE) sebesar 0.0087 radian pada matra longitudinal dan selisih maximum overshoot sebesar 0.00082 radian serta settling time sebesar 0.3 detik pada matra lateral direksional. Secara keseluruhan sistem kendali FuzzyPID menunjukkan performa yang lebih baik dibandingkan PID fixed. ====================================================================================================== Fixed-Wing UAV dynamics system can be simplified to longitudinal dan lateral directional motion. State space of LAPAN Surveillance 02 (LSU-02) show that the system is controllable and staticly stable, but open loop and root locus analysis show that the system can’t reach the set point and trend to oscillating, that can be very dangerous for a plant that need rapid response like UAV system. Fuzzy-PID attitude control system for fixed-wing type UAV had been designed. Simulation results show that the control system have a good performance at both dimension, mean integral time absolute error (ITAE) difference of the system response is 0.0204 radians, mean integral absolute error (IAE) difference is 0.0087 radians at longitudinal motion and maximum overshoot difference of system response 0.00082 radian, settling time is 0.3 seconds at lateral directional motion. Generally, the simulation result show that Fuzzy-PID control system is better than fixed PID .

Item Type: Thesis (Undergraduate)
Additional Information: RSF 629.895 Nic p
Uncontrolled Keywords: Sistem kendali, longitudinal, lateral direksional, fixed-wing UAV, control system, longitudinal motion, lateral direction motion fixed-wing UAV
Subjects: T Technology > TJ Mechanical engineering and machinery > TJ223 PID controllers
Divisions: Faculty of Industrial Technology > Physics Engineering > 30201-(S1) Undergraduate Thesis
Depositing User: Yeni Anita Gonti
Date Deposited: 24 Jun 2020 03:39
Last Modified: 24 Jun 2020 03:39
URI: https://repository.its.ac.id/id/eprint/76212

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