Abstract
To address issues such as excessive 1/rev low-frequency vibration of the rotor and track split caused by blade dissimilarity， a closed-loop vibration control algorithm for rotors based on blade track constraints was developed. Firstly， a rotor aeroelastic coupling model with flexible blades was established， with parameters set to simulate the dissimilarity of blades in engineering applications， thereby generating track split phenomena and vibration imbalance characteristics. Secondly， taking the harmonic components of rotor vibration as the control objective， the collective pitch variation of individual blades as the control input， and the track difference as the constraint condition， a set of constrained optimization problems was constructed to solve for the optimal control inputs. Then， through numerical simulations， the control algorithm without track constraints was compared， and the results demonstrate that introducing track constraints not only significantly reduced the amplitude of low-frequency vibrations but also confined the track difference within a specified range， verifying the effectiveness of the constrained control algorithm. Finally， further experimental validation was conducted by establishing a rotor system test platform， adapting the control algorithm into a Simulink model， and integrating corresponding hardware devices to build a software-hardware architecture. Execution of the control algorithm under different flight conditions shows that vibrations were reduced by over 60% in all cases， with track differences constrained near the set value and achieving a maximum reduction of 73%.