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Yazdanpanah, M., Nateghi, A. (2023). Active Control of Suspension Oscillations in Aircraft by using NARMA-L2 Neural Controller. Electronic and Cyber Defense, 19(2), 41-55.
Milad Yazdanpanah; Alireza Nateghi. "Active Control of Suspension Oscillations in Aircraft by using NARMA-L2 Neural Controller". Electronic and Cyber Defense, 19, 2, 2023, 41-55.
Yazdanpanah, M., Nateghi, A. (2023). 'Active Control of Suspension Oscillations in Aircraft by using NARMA-L2 Neural Controller', Electronic and Cyber Defense, 19(2), pp. 41-55.
Yazdanpanah, M., Nateghi, A. Active Control of Suspension Oscillations in Aircraft by using NARMA-L2 Neural Controller. Electronic and Cyber Defense, 2023; 19(2): 41-55.

Active Control of Suspension Oscillations in Aircraft by using NARMA-L2 Neural Controller

مکانیک هوافضا
Article 4, Volume 19, Issue 2 - Serial Number 72, September 2023, Pages 41-55    PDF (1.91 M)
Document Type: Dynamics, Vibrations, and Control
Authors
Milad Yazdanpanah* 1; Alireza Nateghi2
1Corresponding author: Ph.D. Student, Faculty of Electrical Engineering, Science and Research Branch, Islamic Azad University, Tehran, Iran
2Associate Professor, Faculty of Electrical and Computer Engineering, Shahid Sattari University of Aeronautical Engineering, Tehran, Iran
Receive Date: 18 November 2022,  Revise Date: 06 January 2023,  Accept Date: 20 February 2023 
Abstract
Small vibrations (Shimmy) are lateral and torsional vibrations in the aircraft wheel that excites itself and cause instability in fast functions; which can damage the aircraft's landing gear and its fuselage, as well as, in commercial aviation, this may harm passengers. Therefore, controlling and damping these vibrations is essential. For this purpose, the present study has designed a controller using the NARMA-L2 type neural method to prevent small vibrations in the aircraft's landing gear. The controller as mentioned above has a high capability against parameter uncertainties and external disturbances. To check the performance of the proposed controller, the vibration response of the system was simulated by MATLAB software, and its efficiency was measured by comparing the results obtained from RCTM and Proportional-Integral-Derivative (PID) controllers. The obtained results show a significant improvement in the performance of the closed-loop system with an effective reduction of vibrations as a result of using the proposed controller.
Keywords
Neural Controller; NARMA L-2; Active Control; Suspension Oscillations; Aircraft
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