TY - GEN
T1 - VIBRATION CONTROL OF A ROTOR-MAGNETIC BEARING SYSTEM ON THE MOVING BASE THROUGH H∞ CONTROL
AU - Zhang, Guorong
AU - Liu, Mingyang
AU - Zou, Hansen
AU - Wang, Xikui
AU - Xi, Guang
N1 - Publisher Copyright:
Copyright © 2023 by ASME.
PY - 2023
Y1 - 2023
N2 - Rotor-Active magnetic bearing(AMB) systems installed in an aircraft are supported by a moving base. An optimal controller is required to ensure the stability and ideal vibration response of the rotor-AMB system. In this paper, a rigid rotor-AMB system on an aircraft is modeled by the Lagrange principle. The moving base generates additional stiffness, damping and external forcing terms. H∞ control method is applied to design a controller and compare it with a decentralized PID controller. The flight maneuvers of the dive-pull up and horizontal turn are mainly studied. The results show that when the aircraft is in different flight maneuvers, the H∞ controller has a strong ability to resist base movement disturbance, and the rotor displacement of the H∞ controller is smaller than that of the PID controller. As the flight speed Va and maximum roll angle γm increase, the maximum rotor displacement of the H∞ controller remains almost unchanged, but the peak control current of the AMB also increases and may even exceed the maximum allowable value. Therefore, the effect of base movement disturbance should be fully considered during the design process of the AMB.
AB - Rotor-Active magnetic bearing(AMB) systems installed in an aircraft are supported by a moving base. An optimal controller is required to ensure the stability and ideal vibration response of the rotor-AMB system. In this paper, a rigid rotor-AMB system on an aircraft is modeled by the Lagrange principle. The moving base generates additional stiffness, damping and external forcing terms. H∞ control method is applied to design a controller and compare it with a decentralized PID controller. The flight maneuvers of the dive-pull up and horizontal turn are mainly studied. The results show that when the aircraft is in different flight maneuvers, the H∞ controller has a strong ability to resist base movement disturbance, and the rotor displacement of the H∞ controller is smaller than that of the PID controller. As the flight speed Va and maximum roll angle γm increase, the maximum rotor displacement of the H∞ controller remains almost unchanged, but the peak control current of the AMB also increases and may even exceed the maximum allowable value. Therefore, the effect of base movement disturbance should be fully considered during the design process of the AMB.
KW - Active magnetic bearing
KW - Aircraft maneuver
KW - Base movement
KW - H control
UR - https://www.scopus.com/pages/publications/85177203101
U2 - 10.1115/GT2023-102528
DO - 10.1115/GT2023-102528
M3 - 会议稿件
AN - SCOPUS:85177203101
T3 - Proceedings of the ASME Turbo Expo
BT - Structures and Dynamics - Emerging Methods in Engineering Design, Analysis, and Additive Manufacturing; Fatigue, Fracture, and Life Prediction; Probabilistic Methods; Rotordynamics; Structural Mechanics and Vibration
PB - American Society of Mechanical Engineers (ASME)
T2 - ASME Turbo Expo 2023: Turbomachinery Technical Conference and Exposition, GT 2023
Y2 - 26 June 2023 through 30 June 2023
ER -