Affiliations: [a] State Key Laboratory of Mechanics and Control of
Mechanical Structures, Nanjing University of Aeronautics and Astronautics,
Nanjing, Jiangsu, China | [b] Department of Mechanical Engineering, Consortium for
Sound and Vibration Research, The Hong Kong Polytechnic University, Hung Hom,
Kowloon, Hong Kong, China
Correspondence:
[*]
Corresponding author: Hongli Ji, State Key Laboratory of
Mechanics and Control of Mechanical Structures, Nanjing University of
Aeronautics and Astronautics, Nanjing 210016, Jiangsu, China. Tel.: +86 25 848
911 23; Fax: +86 25 848 911 23; E-mail: [email protected]
Abstract: With the rapid development of the aerospace industry, the control of
aircraft structural vibration becomes increasingly important. Semi-active
vibration control method based on synchronized switch damping have been
attracted more attention due to its robustness compared with passive approaches
and simplicity compared with active approaches. In this paper, three SSD
semi-active control methods combined with a modal observer were applied to
multimodal vibration suppression of an aircraft panel with stiffeners, and
their effectiveness was verified by experimental results. A state observer was
built based on the experimentally identified state-space model of the panel.
Modal displacement of the panel was identified on line using the state observer
and used in switch control of different piezoelectric actuators. Since the
vibration characteristics of the panel with stiffeners was very complicated and
its natural frequencies were distributed densely, use of the identified modal
displacement as the reference signal for voltage switching in SSDI, SSDV and
SSDNC improved the control effect for some specific modes and simplified the
system. Good performances of vibration suppression were achieved in both
single-mode control and multimodal control.
