A kit is described that comprises a device adapted to dampen the vibrations transmitted by the rotor to the fuselage; the device comprises two first elements movable along a first axis; two second elements rotatable about the first axis; a first inerter with a first female screw, a first screw, and first rollers rotatable about respective second axes and around the first axis with respect to the first female screw and first screw; a second inerter with a second female screw, a second screw operatively connected to the second female screw; and a plurality of second rollers rotatable about second axes and around the first axis with respect to the second female screw and second screw; the first and second female screws defining the first threaded elements, and the first and second screws defining the second threaded elements; or the first and second screws defining the first threaded elements and the first and second female screws defining the second threaded elements.

There is provided a translational inerter assembly for damping movement of a flight control surface of an aircraft with a support structure. The translational inerter assembly includes a press fit element rotatably disposed within the flight control surface. The translational inerter assembly further includes an inertia element disposed in the press fit element. The translational inerter assembly further includes a torsion bar coupled to the inertia element and to the support structure of the aircraft, such that when the flight control surface rotates, the inertia element translates, and movement of the flight control surface is dampened.

The invention provides a vibration isolation device configured to support a structure, comprising: an air mount having a base part mounted on a reference structure and a vibration isolated part, and an inverted pendulum device, wherein a lower end of the inverted pendulum device is mounted on the vibration isolated part of the air mount and an upper end of the inverted pendulum device support the structure to be supported, wherein the vibration isolation device comprises a stiffness adjustment device configured to adjust the stiffness of the inverted pendulum device.

A novel rotation vibration damper and to vibration absorbers having the damper for wind turbines or other high and, relative to the height thereof, narrow installations or buildings. The disclosure particularly relates to vibration absorbers comprising at least one oscillating mass on a pendulum cable or pendulum rod, wherein the mass is caused to vibrate by an excitation frequency which can be damped by a rotation damper and, in particular, a rotating eddy current magnet damper which forms part of the absorber.

A dual rack and pinion rotational inerter, configured to dampen the flutter of a flight control member of an aircraft, includes an inertial wheel and a brake member disposed on an inertial wheel. The brake member moves between a retracted position and a deployed position based on a rotational velocity of the inertial wheel. The brake member moves to the retracted position when the rotational velocity of the inertial wheel is slower than a predetermined threshold velocity to allow the rotation of the inertial wheel. When the rotational velocity of the inertial wheel is at least as fast as the predetermined threshold velocity, however, the brake member deploys to yieldingly resist the rotation of the inertial wheel. In either position, the inertial wheel causes the inerter to dampen the flutter.

A novel vibration absorber for damping vibrations of a building or a machine installation having an inherent frequency of preferably below 1 Hz, preferably below 0.5 Hz, in particular, <0.25 Hz, as may occur, for example, in wind turbines or also other tall slim buildings or installations. The vibration absorber which, besides a main mass which is fixed per se and is moved along a track analogous or similar to a pendulum mass, has a substantially smaller, variably adjustable rotating flywheel mass, which can be moved with the main mass on the track thereof and with the aid of which the frequency of the absorber can be finely adjusted or adapted.

An overhead line damper capable of suppressing a lift force that an overhead line receives due to wind is provided. A damper 1 for an overhead line that is provided at an overhead line L2 includes a clamping mechanism (a pair of hinge pieces 21a and 21b) that is fitted to an outer circumferential surface of the overhead line L2, and a rotary member 4 with a lower part attached to weights 3a and 3b, and an upper part rotatably attached to the clamping mechanism, and the clamping mechanism has a regulation part (an opening part 24) that regulates a rotation range of the rotary member 4 so that the weights 3a and 3b rotate within an angle range from 20 degrees to 40 degrees inclusive in a vertical direction.

An anti-tail buffet device leverages existing rotorcraft components to attenuate a tailboom's lateral ringing from air buffeting. Anti-buffet masses are tuned to the tailboom's lateral-bending or torsional natural frequency such that when lateral motion occurs, the response at this frequency is cancelled by the anti-buffet system, preventing this vibration from entering into the tailboom structure. Motion stops prevent over-travel. The mass of the tail rotor actuator is soft-mounted, such that its natural frequency is equal to the tailboom's lateral-bending or torsional natural frequency. When lateral loading occurs on the tail rotor disk, the lateral response at this frequency is attenuated by the soft-mounted tail rotor actuator, thereby preventing the vibration in the tailboom structure.

A damping system for damping rotary movements of a tailing arm. The system includes a chassis, a main shaft, and a rotary damping mechanism. The rotary damping mechanism includes a first externally-threaded gear attached fixedly to the main shaft, a guide rail attached fixedly to the chassis, a linear shock absorber, an internally-threaded gear associated with the first externally-threaded gear, and a first actuator configured to decouple the first externally-threaded gear from the linear shock absorber and couple the first externally-threaded gear with the linear shock absorber.

To provide a rotary inertia mass damper, which is capable of reducing an axial reaction force that is generated due to vibration having an excessive acceleration to the extent possible when the vibration is input, and of preventing breakage of the damper itself or a construction, provided is a rotary inertia mass damper, including: a first coupling portion, which is fixed to a first structure; a second coupling portion, which is coupled to a second structure; a screw shaft, which has one axial end connected to the first coupling portion and retained so as to be non-rotatable; a fixed barrel, which has a hollow portion for receiving the screw shaft, and is connected to the second coupling portion; and a rotary body, which is retained so as to be freely rotatable relative to the fixed barrel, is threadedly engaged with the screw shaft, and is configured to reciprocally rotate in accordance with advancing and retreating movement of the screw shaft relative to the fixed barrel. A torque limiting member is provided between an axial end of the screw shaft and the first coupling portion, and is configured to, when a rotational torque that exceeds a predetermined value is applied to the screw shaft, allow rotation of the screw shaft relative to the first coupling portion to reduce a rotation angle of the rotary body.