Patent ID: 6772979
Filing Date: 2004-08-10
Classification: B64C

Abstract:
A method for reducing vibratory motions of a fuselage of an aircraft, said vibratory motions being engendered by engines of said aircraft which comprises two fixed wings which are symmetric with respect to said fuselage, each of said wings being provided with control surfaces articulated to its trailing edge and bearing at least one of said engines, said method comprising:(a) associating at least one accelerometer with at least one of said engines; (b) measuring accelerations undergone by said at least one of said engines in at least one direction transverse to said at least one of said engines, wherein said direction is horizontal, that is to say lateral with respect to said aircraft; (c) with the aid of the accelerometric measurements thus obtained, determining at least one oscillatory control command which, applied to at least one control surface of the the one of said wings bearing said at least one of said engines, is able to counteract the vibratory motions of said at least one of said engines in said direction; and (d) applying said control command to said at least one control surface.