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.

Abstract: A fiber composite component has a piezoelectric actuator or sensor integrated therein. Electric feed lines for the actuator or sensor are constructed in the form of electrically insulated thin wires which exit the fiber composite almost perpendicularly to the laminate layers, so that the fibers of the fiber composite component are not severed by the leading-out of the feed lines, but are slightly pushed apart.

Abstract: A fiber composite component has a piezoelectric actuator or sensor integrated therein. Electric feed lines for the actuator or sensor are constructed in the form of electrically insulated thin wires which exit the fiber composite perpendicularly to the laminate layers, so that the fibers of the fiber composite component are not severed by the leading-out of the feed lines, but are pushed apart.