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Abstract

A method for damping vibrations in a tail boom of a rotary-wing aircraft includes the steps of detecting tail boom vibrations induced by external vibration excitation, and generating and introducing strains into the tail boom based on the detected tail boom vibrations. The strains are applied over a surface area and are out-of-phase with respect to the detected tail boom vibrations so as to damp the externally excited induced tail boom vibrations. In addition, a rotary-wing aircraft, includes a fuselage, a cockpit area integrated into the fuselage, a tail boom arranged on the fuselage and a tail boom vibration-damping device. The vibration-damping device has at least one sensor element configured to detect tail boom vibrations induced by external vibration excitation and at least one actuator configured to generate and introduce strains into the tail boom that are out-of-phase with respect to the induced tail boom vibrations, the actuator being functionally coupled to the sensor element, engaging with a tail boom structure at one side of the tail boom, and forming a flat-surfaced bond with the tail boom.

First Claim