Aircraft Skin Structure Vibration Suppression Based on Piezoelectric-Abh Hybrid Control Approach

The thin-walled structure of aircraft is susceptible to vibrations caused by aerodynamic loads, which can impact the performance and longevity of the electronic equipment integrated with it. To effectively reduce this wideband structural vibration, a novel hybrid vibration suppression approach is proposed in this paper. This approach combines a piezoelectric active control technique with a passive control technique using ABH (Acoustic Black Hole) effect. Both the ABHs and the piezoelectric elements were specifically designed for a simplified thin-walled structure, which serves as the skin for the electronic equipment. The study focuses on vibration responses in the frequency range of 5 to 2000 Hz, analyzing the effects of the proposed hybrid vibration control method. Simulation results indicate that the piezoelectric active control technique effectively mitigates the mode vibration response of the main skin structure. Additionally, the ABH, combined with damping materials, passively suppresses vibrations in the middle to high frequency range. The theoretical basis for the starting operation frequency due to the ABH effect is also discussed. This hybrid control system is designed to be easily implemented in engineering applications due to its straightforward control algorithm.