Transactions of Nanjing University of Aeronautics & Astronautics
Research on Helicopter Active Vibration Elimination Electric Actuator System Based on x-LMS Algorithm
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Abstract:
When the helicopter flies forward， the aerodynamic environment will lead to the instantaneous asymmetry of aerodynamic load on the blades with different angles， which will form a large range of low-frequency vibration on the fuselage through the transmission of the infrastructure. To eliminate the vibration force with multi-directional amplitude variation， using the active control principle of structural response， an active vibration elimination electric actuator system based on the x-LMS algorithm is designed， and the vibration reduction experiment is carried out. Firstly， the scheme of two motors rotating in the same direction in a single actuator is established by comparison. Through the combination of actuators， the mathematical model of output force is deduced. Secondly， the system control block diagram of load phase difference cross-coupling is designed. For the phase outer loop with coupling， the parameter range that meets the requirements of the system stability margin is determined by the method of characteristic value of the feedback matrix， and then the optimal solution is found in the obtained parameter stability region according to the sensitivity function and input tracking performance. Then， a helicopter active vibration control system based on the x-LMS algorithm is proposed， and the damping effect of the system is verified by simulation. Finally， the experimental prototype is developed， the dynamic experiment and steady-state experiment are carried out， and the actual damping effect of the system is verified by the vibration elimination experiment.
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Project Supported:
This work was supported by the National Natural Science Foundation of China（No.52077100） and the Aviation Science Foundation（No.201958052001）.
Clc Number:
V11
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