Abstract:

An active control system for helicopter structure response is studied, which includes a servo inertial force generator (SIFG), an electro hydraulic servo controller and an adaptive controller. Following the modelling of the SIFG and the design of the electro hydraulic controller, an adaptive controller is built using RLS algorithm. The response induced by the disturbance is reconstructed and used as the reference signal required by adaptive filtering algorithm, and a method for measuring and recovering the stability of the algorithm is made.The vibration reduction of a passive absorber and the SIFG is compared for a forward flight helicopter with a constant rotor speed and variant rotor speeds. It is concluded that the SIFG with adaptive vibration controller can provide better results for different flight conditions.

Key words: adaptive control, str uctural vibration, helicopter