Abstract: An aircraft has a fuselage that defines an interior cabin and an exterior; a first housing located along one side of the fuselage exterior; a second housing located along the second side of the fuselage exterior; and an active vibration control system for limiting fuselage vibration, the vibration control system comprising a plurality of sensors located in the cabin; a controller in signal receiving relation with the sensor means; first actuator means located in the first housing and second actuator means located in the second housing and wherein the actuator means are in signal receiving relation with the controller.

Abstract: An active noise control system (20) which generates via an electronic controller (22) a canceling signal(s) which are responsive to a signal from an error sensor(s) (28) to drive a speaker (30) or array of speakers. Each speaker (30) is contained within an enclosure (33) and is inversely and rigidly mounted therein. The enclosure (33) attaches to the trim panels (25) attached to the closed structure (34) and the canceling sound wave form is directed primarily toward the interior surface (36) of the trim (25). Preferably, the speaker(s) (30) are flexibly suspended with mounts (38) to the trim (25). The enclosure (33) preferably includes planar wave guide means such as escapeways (40) for initially directing the canceling sound wave form (anti-noise) in a plane substantially parallel to the surface of the trim (25).