A torsional vibration damper includes a rotational axis, an input part mounted about the rotational axis, an output part rotatable about the rotational axis to a limited extent relative to the input part; a spring device opposing rotation of the output part relative to the input part, a first cam mechanism, and a first intermediate element. The first intermediate element is arranged for radial displacement by the first cam mechanism when the output part rotates relative to the input part. The first intermediate element has a first intermediate element first part, and a first intermediate element second part. In an example embodiment, the damper includes a second cam mechanism and a second intermediate element arranged to be radially displaced by the second cam mechanism when the output part rotates relative to the input part. The spring device is arranged between the first intermediate element and the second intermediate element.

A torque ripple compensating device for an internal combustion engine is provided. The torque ripple compensating device comprises a first member, a second member, and a third member. The first member is in driving engagement with an output of the internal combustion engine. The second member is in driving engagement with the first member. The third member is in driving engagement with the second member. An angular deviation between the first member and the third member causes a cyclical acceleration of the third member. The cyclical acceleration of the third member applies a torque to the output of the internal combustion engine through the first member. The torque ripple compensating device is able to be passively or dynamically adapted for both an amplitude and a phase of a torque ripple while minimizing an interference with an operation of the internal combustion engine.

A torque fluctuation inhibiting device includes a mass body. The mass body disposed to be rotatable with a rotor and be rotatable relatively to the rotor. Each of a plurality of centrifugal elements is radially movable by a centrifugal force that acts thereon in rotation of the rotor and the mass body. When a relative displacement is produced between the rotor and the mass body in a rotational direction while the centrifugal force is acting on the each of the plurality of centrifugal elements, each of a plurality of cam mechanisms converts the centrifugal force into a circumferential force directed to reduce the relative displacement. A plurality of restriction members allow the plurality of centrifugal elements to move in actuation of the plurality of cam mechanisms, and restrict the plurality of centrifugal elements from moving radially inward in non-actuation of the plurality of cam mechanisms.

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.

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 torque ripple compensating device for an internal combustion engine is provided. The torque ripple compensating device comprises a first member, a second member, and a third member. The first member is in driving engagement with an output of the internal combustion engine. The second member is in driving engagement with the first member. The third member is in driving engagement with the second member. An angular deviation between the first member and the third member causes a cyclical acceleration of the third member. The cyclical acceleration of the third member applies a torque to the output of the internal combustion engine through the first member. The torque ripple compensating device is able to be passively or dynamically adapted for both an amplitude and a phase of a torque ripple while minimizing an interference with an operation of the internal combustion engine.

A cushioning mechanism of a heat sealing device applied in a film wrapping machine has a leading cylinder, an elastic unit, a first cushioning plate, a second cushioning plate, and a cushioning component. The elastic unit, the first cushioning plate, and the second cushioning plate are sequentially disposed on the leading cylinder along an axial direction of the leading cylinder; the first cushioning plate and the leading cylinder rotate synchronously. The cushioning component has a cushioning groove and a cushioning protrusion respectively formed on the first cushioning plate and the second cushioning plate. When the second cushioning plate is rotated, the cushioning protrusion presses one of two groove walls of the cushioning groove such that the first cushioning plate can rotate synchronously with the second cushioning plate for transmission or move relative to the leading cylinder to compress the elastic unit for cushioning.

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).

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.