Vibration damper, in particular for a helicopter rotor

Details Vibration damper, in particular for a helicopter rotor Vibration damper, in particular for a helicopter rotor

1996-12-04

1999-11-09

Schwartz, Christopher P.

Brakes

Internal-resistance motion retarder

Cylinder structure

F16F 900

Patent

active

059796189

ABSTRACT:
The present invention relates to a vibration damper, in particular for a helicopter rotor, the damper comprising a driving element having a "main" axis and a rigid element, and including a damping assembly functionally interconnecting the driving element and the rigid element to damp vibrations in at least one direction perpendicular to said main axis. The damper includes a hydraulic damper device having first and second sets of plane laminations each having its plane perpendicular to the main axis, the laminations of the first and second sets being interleaved and narrowly spaced apart so as to present viscous damping zones each situated between one of the laminations of the first set and one of the laminations of the second set. The damper includes an elastic element having low stiffness parallel to the main axis so as to decouple compression excitation between the driving element and the rigid element.

REFERENCES:
patent: 2502322 (1950-03-01), Iredell, Jr.
patent: 2555347 (1951-06-01), Lee
patent: 3947007 (1976-03-01), Pelat
patent: 4773632 (1988-09-01), Hartel
patent: 4957279 (1990-09-01), Thorn
patent: 5286013 (1994-02-01), Seymour
patent: 5366193 (1994-11-01), Lindsay
patent: 5373920 (1994-12-01), Valdivia et al.
patent: 5692728 (1997-12-01), Shiozawa

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