In helicopter rotor active vibration and noise reduction technology, smart torsional rotors based on Macro Fiber Composite (MFC) are considered as one of the most promising methods due to their lack of any additional mechanical components. Currently, most Active Torsion Rotor (ATR) vibration and noise reduction technologies based on MFC are still in the theoretical research stage. This paper uses MFC as the actuator and proposes a simple dual Least Mean Square (LMS) frequency-domain adaptive Higher Harmonic Control (HHC) algorithm for the smart torsional rotor based on the NACA23012 airfoil. Vibration and noise active closed-loop control experiments are conducted in a 3.4 m×2.4 m open-circuit wind tunnel. Compared to traditional frequency-domain HHC algorithms, the computational effort for single harmonic control is reduced by 5.5 to 11 times. Under various conditions, such as rotor speeds from 150 r/min to 210 r/min, wind speeds from 5 m/s to 10 m/s, and rotor shaft tilt angles of 0° and 8°, the controller reduces vibration levels by 27.24% to 58.55%. At a rotor speed of 210 r/min, wind speed of 10 m/s, and rotor shaft tilt angle of 0°, the controller can reduce noise levels by about 2.5 dB to 3.2 dB.

This study introduces a novel approach for coupled aeroelastic analysis of panel subjected to supersonic airflow, utilizing Add-On Acoustic Black Hole (AABH) to mitigate panel flutter. Employing Galerkin’s method to discretize aeroelastic equation of panel and leveraging finite element method to derive a reduced discrete model of AABH, this study effectively couples two substructures via interface displacement. Investigation into the interactive force highlights the modal effective mass, frequency discrepancy between oscillation and AABH mode, and modal damping ratio as critical factors influencing individual AABH mode in flutter suppression. The selection of effective AABH modes, closely linked to these factors, directly influences the accuracy of simulations. The results reveal that AABH notably enhances the panel’s critical flutter boundary by 14.6%, a significant improvement over the 3.6% increase afforded by equivalent mass. Furthermore, AABH outperforms both the tuned mass damper and nonlinear energy sink in flutter suppression efficacy. By adjusting the AABH’s geometrical parameters to increase the accumulative modal effective mass within the pertinent frequency range, or choosing a suitable installation position for AABH, its performance in flutter suppression is further optimized. These findings not only underscore the AABH’s potential in enhancing aeroelastic stability but also provide a foundation for its optimal design.