| Citation: | ZHU Haozhe, HE Lidong, QIN Qingwang. Study on vibration control of wing cantilever beam structure based on active damping device[J]. Journal of Aerospace Power, 2026, 41（4）：20240412 doi: 10.13224/j.cnki.jasp.20240412
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In view of the problem of forced excitation and resonance of aircraft wings, a method was proposed to suppress the forced excitation and reduce the resonance of wings by applying the actuating force to the wing cantilever beam model using an active damping device (ADD), and theoretical derivation, simulation analysis, and experimental study were carried out for the suppression of forced vibration of the wings. Firstly, the actuator dynamics model of ADD was established to analyze the effectiveness of ADD in controlling the forced vibration of the wing; then, the modal analysis, force analysis and harmonic response analysis of the wing cantilever beam model were carried out using numerical simulation to optimize the actuator force output from the ADD; finally, the active suppression experimental bench of wing excitation based on ADD was constructed, and the effects of the control of modal vibration and vibration under wide-band excitation force of the wing cantilever beam before and after application of the ADD control were compared. The results showed that applying ADD control can effectively improve the wing force state and significantly reduce its stress and deformation; ADD significantly reduced the resonance amplitude of the wing, with a maximum reduction of up to 74.22%; within the 30—120 Hz frequency band, it effectively controlled wing vibrations, with a maximum reduction of up to 61.8%.
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