Study On Adaptive Control Law Design Of Active Control For Helicopter Vibration

Reducing the vibration level of helicopter fuselage during flight is always one of the most key problems in the development of helicopter. Due to the excellent adaptability, flexibility and the efficiency in vibration reduction, active control system have become a new technology which can be relied on in seeking more efficient vibration methods. Based on original hardware, control law of reliability, efficiency and quickness can rapidly reach control objective, reduce computation difficulty, raise control efficiency.In this paper, the main research is aimed at those control methods in which system can be identified among active control of structural responses on helicopter fuselage. Time Averaged Gradient Method without identifying error path is investigated and modified. The Simultaneous Equations Method which identifies error path and modifies control filter coefficients by changing output of control filter is investigated, and is generalized to Multi Input Multi Output system. Adaptive feedforward control based on online identifying error path, online identifying error path IIR model by clearing bad influence of disturbance, and combine adaptive feedforward control method are investigated in the paper.The effectiveness of the mentioned methods which are used in active control of helicopter fuselage vibration, concluding single input single output control and multi input multi output control, are verified by the simulations.