dubi̇ted Duzce University Journal of Science and Technology 2148-2446 Duzce University 10.29130/dubited.1177711 Engineering Mühendislik Active Vibration Control of Landing Gear System İniş Takımı Sisteminin Aktif Titreşim Kontrolü https://orcid.org/0000-0002-9707-8271 Demircioglu Ufuk SIVAS SCIENCE AND TECHNOLOGY UNIVERSITY https://orcid.org/0000-0003-0682-2016 Eker Sefa Burhan SIVAS SCIENCE AND TECHNOLOGY UNIVERSITY https://orcid.org/0000-0001-6914-5222 Yıldız Ali Suat SIVAS SCIENCE AND TECHNOLOGY UNIVERSITY 07 31 2024 12 3 1692 1701 09 20 2022 01 14 2024 Copyright © 2013, Duzce University Journal of Science and Technology 2013 Duzce University Journal of Science and Technology

The vibration of the aircraft when taxing, landing, and taking off is a great problem. Vibration induced due to the dynamic interaction of aircraft with the ground causes serious problems. Therefore, the vibration should be reduced or completely absorbed if possible by some external means. So, in this study active vibration control of an aircraft LG is investigated. The equation of motion of the aircraft LG system is obtained by Newton’s second law and simulated in MATLAB/Simulink environment. Two different controllers are fitted to the landing gear system. Proportional, integral derivative (PID) and Linear Quadratic Regulator (LQR) controllers are used in controlling active suspension structure. In the study, vertical displacement and acceleration of the fuselage are set as objective since it has harmful effects on the performance of the pilot’s capability. Simulation is run under B grade road and bump road for passive and active systems simultaneously. The performance of controllers is compared to one another and also with that of a passive system. From the results, it was obtained that under bump road excitation, LQR and PID controllers make 57.32% and 53.34% improvement in fuselage displacement, respectively. Similarly, under B Grade road, compared to passive systems LQR and PID controllers improve the vertical acceleration of the fuselage by 92.86% and 53.55% respectively.

Uçağın iniş ve kalkış sırasındaki titreşimi büyük bir problemdir. Uçağın yerle dinamik etkileşimi nedeniyle oluşan titreşim ciddi sorunlara neden olur. Bu nedenle, titreşim azaltılmalı veya mümkünse bazı harici yollarla tamamen absorbe edilmelidir. Bu nedenle bu çalışmada bir uçağın aktif titreşim kontrolü incelenmiştir. Uçağın hareket denklemi Newton'un ikinci yasası ile elde edilmiş ve MATLAB/Simulink ortamında simüle edilmiştir. İniş takımı sistemine iki farklı kontrolör takılmıştır. Aktif sistem için oransal, integral türev (PID) ve doğrusal ikinci dereceden regülatör (LQR) kontrolörü kullanılmıştır. Çalışmada, pilotun kabiliyet performansı üzerinde zararlı etkileri olduğu için gövdenin dikey yer değiştirmesi ve ivmelenmesi hedef olarak belirlenmiştir. Simülasyon, pasif ve aktif sistemler için B sınıfı yol ve tümsek yol altında aynı anda koşturulmuştur. Kontrolörlerin performansı birbirlerine ve ayrıca pasif bir sistemin performansına göre karşılaştırılmıştır. Sonuçlardan, tümsek yol uyarımı altında, LQR ve PID kontrolörlerinin gövde deplasmanında sırasıyla %57.32 ve %53.34 iyileştirme elde edilmiştir. Benzer şekilde B yol profili altında, pasif sistemlere kıyasla LQR ve PID kontrolörlerinin gövdenin dikey ivmesini sırasıyla %92.86 ve %53.55 oranında iyileştirdiği de elde edilmiştir.

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