Abstract
During the flight tests of Z-11 helicopter, the previous method for active vibration control of helicopter suffered from the problems of slow convergence speed and big residual vibration. In order to mitigate these problems, a new method was proposed on the basis of the previous one. Here, a new error channel modeling method is used, which is named the prior error channel identification strategy. And the active control process and the error channel identification process are simplified to improve performance of the system. Besides, the complexity of the method is reduced. Active vibration control simulations were performed based on a simplified model of helicopter fuselage. The simulation results show that the proposed method has lower residual vibration, faster convergence speed, and better capacity for resisting disturbance compared with the previous method. Finally, an active control of structure response experiment was conducted on a free-free beam, and good inhibitory effect of the vibration response of the free-free beam was obtained. The results illustrate that the proposed method based on the prior error channel identification strategy is effective.
Highlights
Excessive vibration on a helicopter airframe can cause physical and psychological discomfort to passengers and crew, fatigue and damage to the aircraft structure and on-board equipment, and decreased operational capabilities of the aircraft [1, 2]
In order to study thecharacteristics of the proposed method and check out its effectiveness in helicopter active control of structure response (ACSR), three kinds of simulations are performed based on MATLAB
As shown in the figure, the extraneous force is loaded at the node 94 to simulate the exciting force on the rotor hub; the control force is loaded at the node 109; the acceleration response of the node 37 is used as the error signal, to evaluate the effectiveness of the active control system in vibration reduction
Summary
Excessive vibration on a helicopter airframe can cause physical and psychological discomfort to passengers and crew, fatigue and damage to the aircraft structure and on-board equipment, and decreased operational capabilities of the aircraft [1, 2]. Active vibration control approaches for helicopter such as higher harmonic control (HHC), individual blade control (IBC), actively controlled flaps (ACF), active twist rotor (ATR), and active control of structure response (ACSR) can suppress unwanted vibration adaptively and make up for the weaknesses of passive techniques [6,7,8,9]. In order to improve the performance of Eriksson’s method, Zhang et al introduced a third adaptive filter to eliminate the bad effect of the error channel identification process on the active control process [21]. Based on of Zhang’s method, Yang et al introduced a fixed filter to eliminate the influence of the active control process on the error channel identification process [19].
Sign-in/Register to view highlights & summary Sign-in/Register to access full text options 
Free) 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a call
