A torsional vibration absorber for a vehicle is provided. The torsional vibration absorber including a front pilot bearing adapted to couple with a vehicle shaft. A spring member is coupled to the front pilot bearing. An inertia ring having an inner surface is operably coupled to the spring member, wherein the front pilot bearing is centrally disposed along the length of the inertia ring. A rear pilot bearing is adapted to couple with the vehicle shaft, the rear pilot bearing having a portion adjacent the inner surface at one end of the inertia ring.

A proprotor system operable for use on a tiltrotor aircraft having a helicopter flight mode and an airplane flight mode. The proprotor system includes a rotor hub and a plurality of proprotor blades coupled to the rotor hub such that each proprotor blade has three independent degrees of freedom relative to the rotor hub including blade pitch about a pitch change axis, blade flap about a flapping axis and lead-lag about a lead-lag axis. Each of a plurality of spherical bearings couples one of the proprotor blades with the rotor hub. In addition, each of a plurality of lead-lag dampers couples one of the proprotor blades with the rotor hub, wherein each lead-lag damper is aligned with the pitch change axis of the respective proprotor blade, thereby providing pitch independent lead-lag damping.

A torque transmission device for a motor vehicle includes a rotor carrier mounted rotatably about an axis of rotation, an input hub, an output hub, and a torsion damper. The rotor carrier has a fastening portion and a first flange portion. The fastening portion and the input hub are arranged on a first axial side of the first flange portion and are connected to the first flange portion. The torsion damper has an energy storage element and a damper output part, which includes a second flange portion and an actuating portion operatively connected to the energy storage element. The second flange portion is torque-transmittingly connected to the output hub and the actuating portion. The second flange portion is situated axially between the first flange portion and the output hub. The first flange portion has a through-opening through which the actuating portion passes.

There is provided a translational inerter assembly for damping movement of a flight control surface of an aircraft. The assembly has a press fit element fixedly disposed within a first end of the flight control surface and rotatably movable with the flight control surface. The assembly further has an inertia element coupled to and installed in the press fit element. The assembly further has a torsion bar having a torsion bar first end coupled to and installed in the inertia element, and having a torsion bar second end fixedly attached to a support structure of the aircraft. Rotation of the flight control surface causes translational movement of the inertia element, via the press fit element, along a hinge axis of the flight control surface and along the torsion bar, resulting in the translational inerter assembly damping movement of the flight control surface.

A bearing arrangement (30) comprises an inner support annulus (33), an outer support annulus (31), and a plurality of rollers (34) therebetween. At least one of the inner and the outer support annulus (33, 31) comprises one or more radially extending rigid supports (37) and one or more damping sectors (38a, 38b, 38c). The one or more rigid supports (37) are circumferentially interposed between one or more damping sectors (38a, 38b, 38c). Each damping sector (38a, 38b, 38c) comprises at least one damping member (39) comprising an elongate flexible member held rigidly at one or both ends thereof, such that vibrational movement of the inner or outer support annulus (33, 31) causes bending of the elongate flexible members (39).

The disclosure relates to a rotary damper (1) for reducing and in particular braking a rotational or pivotal movement of a second component rotatable relative to a first component. The rotary damper (1) includes a first damper component (2), which is in particular fixedly connected or connectable to the first part, a second damper component (3), which is particular fixedly connected or connectable to the first second part, and a damping mechanism (4). The first damper component (2) is rotatable relative to the second damper component (3). In a first direction of rotation, a rotational movement of the first damper component (2) relative to the second damper component (3) is or can be braked due to the damping mechanism (4). According to the disclosure, it is provided in particular that the rotary damper (1) further includes a coupling mechanism (5), which is configured so as to operatively connect the second damper component (3) to the damping mechanism (4) upon a movement of the first damper component (2) relative to the second damper component (3) in the first direction of rotation, and, upon a movement of the first damper component (2) relative to the second damper component (3) in a second direction opposite the first direction of rotation, to release and/or prevent an operative connection between the second damper component (3) and the damping mechanism (4).

In a transfer structure of a vehicle according to one aspect of the present invention, a drive shaft includes: a first power transfer shaft including a first end coupled to a differential device; a second power transfer shaft including a first end coupled to a second end of the first power transfer shaft through a first universal joint; and a third power transfer shaft including a first end coupled to a second end of the second power transfer shaft through a second universal joint and a second end to which a driving wheel is coupled, and dampers are provided on at least two respective power transfer shafts. Among these dampers, a predetermined damper arranged on the longest power transfer shaft out of the at least two power transfer shafts functions in a frequency region lower than a frequency region in which a remaining damper functions.

A damping connecting rod that can be converted into a rigid connecting rod in the case of abnormal vibrations. The damping connecting rod comprises a body having a cavity and a shaft inside the cavity, with a clevis associated with the body and allowing the clevis to be fixed to an element. The shaft can be longitudinally displaced inside the body or the body about the shaft. The connecting rod includes an arrangement for longitudinally immobilizing the shaft with respect to the clevis comprising at least one hook and at least one hollow, which are borne by two connecting rod pieces, respectively, which are configured to be displaced toward one another and with a shape such that, with the displacement of the pieces longitudinally with respect to one another, the hook driven into the corresponding hollow longitudinally immobilizes the shaft with respect to the clevis.

There is provided a translational inerter assembly for damping movement of a flight control surface of an aircraft. The assembly has a press fit element fixedly disposed within a first end of the flight control surface and rotatably movable with the flight control surface. The assembly further has an inertia element coupled to and installed in the press fit element. The assembly further has a torsion bar having a torsion bar first end coupled to and installed in the inertia element, and having a torsion bar second end fixedly attached to a support structure of the aircraft. Rotation of the flight control surface causes translational movement of the inertia element, via the press fit element, along a hinge axis of the flight control surface and along the torsion bar, resulting in the translational inerter assembly damping movement of the flight control surface.

A damper element for a vibration dampening system may be used in a body opening in a rotating blade in a turbine. The damper element includes a base member, and a spring-suspended bearing member having a disc spring fixedly coupled to the base member at a center of the disc spring, and a bearing member coupled to a first side of the disc spring at an outer portion thereof. The bearing member extends radially distal from the first side of the disc spring. With the disc spring in an elastically extended state under influence of a centrifugal force caused by rotation of the rotating blade at higher than a predefined rotational speed, the bearing member frictionally engages a first bearing surface to dampen vibration. The friction-based vibration dampening interface experiences a reduced impact of the centrifugal forces of the rotating blade by providing a counteracting force reduction using the spring.