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

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