PID Controller Design Based on BPNN for Helicopter Vibration Attenuation

In recent years, trailing-edge flaps piezo-actuated has been considered a valid approach for the design of active rotor controller aiming at the attenuation of helicopter vibration and at the improvement of rotor performance. The paper study a hinged helicopter rotor model with TEF as modeling object, a control-oriented model suitable for controller design is established, comparing foreign data and system identicification. In this paper, a vibration reduction control algorithm consists of two partsPID for controller design and BPNN (back propagation neural network) for the online adjustment of the controller parameters and improve the self-adaptability of the system. The numerical Simulation results show that compared with H∞ control strategy, the method combining PID and BPNN has better vibration reduction effect.