Device for reducing the vibrations on the structure of a helicop

Details Device for reducing the vibrations on the structure of a helicop Device for reducing the vibrations on the structure of a helicop

1996-12-09

1998-07-07

Morano, S. Joseph

Aeronautics and astronautics

Aircraft, heavier-than-air

Helicopter or auto-rotating wing sustained, i.e., gyroplanes

244 75A, 188379, 188380, B64C 2706

Patent

active

057756376

ABSTRACT:
A device for reducing the vibrations generated on the structure of a helicopter. The helicopter includes a structure with a tail boom and a fin. The structure has a longitudinal vertical mid-plane. The helicopter also has a main lift and propulsion rotor which generate an aerodynamic flow passing through the rotor and induce vibrations on the structure. A damping device for reducing the vibrations has a longitudinal chamber which is equipped with at least one central restriction, which has two elastically urged mobile lateral walls and which is full of a fluid representing an oscillating mass. The damping device is mounted in the tail boom close to the fin so that the direction of travel of the oscillating mass is at least substantially orthogonal to the longitudinal vertical mid-plane.

REFERENCES:
patent: 3429051 (1969-02-01), Lutz et al.
patent: 4042070 (1977-08-01), Flannelly
patent: 4247061 (1981-01-01), Kuczynski et al.
patent: 4766984 (1988-08-01), Gaffey et al.
patent: 4974794 (1990-12-01), Aubry et al.
Patent Abstracts of Japan, vol. 10, No. 167, 13 Jun. 1986 (M-488); Abstract of Japanese Patent No. 61017736.

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