The invention relates to a belt drive assembly for a drive train of a helicopter, comprising a drive shaft that can be functionally connected to a crankshaft of a drive machine of the helicopter, wherein the drive shaft is functionally connected to a belt disk via a torsional vibration damper, wherein the belt disk can rotate via a bearing mechanism on a bearing shaft connected to the drive shaft for conjoint rotation therewith, wherein the belt disk can receive a belt that is functionally connected to a rotor system of the helicopter.

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).

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.

A power transmission device includes a first rotary member, a second rotary member, and a damper mechanism. The first rotary member includes a chamber in an interior thereof. The second rotary member is disposed to be rotatable relative to the first rotary member. The damper mechanism is configured to elastically couple the first rotary member and the second rotary member in a rotational direction. The damper mechanism includes a first damper part disposed inside the chamber and configured to transmit power together with the first rotary member therebetween, a second damper part disposed outside the chamber and radially inward of the first damper part and configured to transmit the power together with the second rotary member therebetween, and an intermediate member including an inertia portion disposed outside the chamber and configured to couple the first damper part and the second damper part.

The invention relates to a belt drive assembly for a drive train of a helicopter, comprising a drive shaft that can be functionally connected to a crankshaft of a drive machine of the helicopter, wherein the drive shaft is functionally connected to a belt disk via a torsional vibration damper, wherein the belt disk can rotate via a bearing mechanism on a bearing shaft connected to the drive shaft for conjoint rotation therewith, wherein the belt disk can receive a belt that is functionally connected to a rotor system of the helicopter.

According to one embodiment, a damper device includes a rotator, a first oscillator, a second oscillator, and two rollers, for example. The rotator is provided with a first opening. The second oscillator includes two guide surfaces recessed in a direction closer to a first center of rotation and a transmitting part capable of moving along the first opening. The two rollers each include a ring supported by the first oscillator and a shaft extending along a second center of rotation inside the ring and rotatably supported by the ring. The shaft comes into contact with a corresponding one of the two guide surfaces of the second oscillator pushed outward in the radial direction by centrifugal force, rolls along the corresponding one of the two guide surfaces by oscillation of the first oscillator, and is pushed by the corresponding one of the two guide surfaces in the circumferential direction.

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.

According to one embodiment, a damper device includes a rotator, a first oscillator, a second oscillator, and two rollers, for example. The rotator is provided with a first opening. The second oscillator includes two guide surfaces recessed in a direction closer to a first center of rotation and a transmitting part capable of moving along the first opening. The two rollers each include a ring supported by the first oscillator and a shaft extending along a second center of rotation inside the ring and rotatably supported by the ring. The shaft comes into contact with a corresponding one of the two guide surfaces of the second oscillator pushed outward in the radial direction by centrifugal force, rolls along the corresponding one of the two guide surfaces by oscillation of the first oscillator, and is pushed by the corresponding one of the two guide surfaces in the circumferential direction.

According to one embodiment, a damper device includes a rotator, a first oscillator, a second oscillator, and two rollers, for example. The rotator is provided with a first opening. The second oscillator includes two guide surfaces recessed in a direction closer to a first center of rotation, and a transmitting part capable of moving along the first opening. The two rollers are rotatably supported by the first oscillator, come into contact with the respective two guide surfaces of the second oscillator pushed outward in the radial direction by centrifugal force generated by rotation of the rotator, and roll along the respective two guide surfaces by oscillation of the first oscillator and are pushed by the respective two guide surfaces in the circumferential direction. The second oscillator is capable of translation in the radial direction with the two guide surfaces supported by the respective two rollers.

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.