Abstract:

The rejection of so-called blade harmonic disturbances generated by the mainrotor of helicopters and atmospheric turbulence is an important problem which should be considered in the design of future helicopters. In this paper, we applied robust control theory to the design of an active vibration isolation system which effectively restricts the influence of blade harmonics on the fuselage at the first and second harmonic frequencies, as well as el, iminates the static relative displacement between the mainrotor and fuselage under ascent or descent acceleration.

Key words: helicopter, active vibration isolation system, robust control