Airbus Helicopters

Aerospatiale Societe Nationale Industrielle

Eurocopter France

Societe Anonyme Dite: Eurocopter France

Ecole Naitonale Supérieure D'arts Et Métiers—e.n.s.a.m

Societe Anonyme Dite: Aerospatiale Societe Nationale Industrielle

Ecole Nationale Superieure D'arts Et Metiers (ensam)

Tomasz Krysinski

Francois Malburet

Jean P Jalaguier

Laurent Girard

Pierre Michel

François Malburet

An aircraft () provided with a main gearbox () fastened to a load-bearing structure () via at least three suspension bars (). An active vibration absorber () is fastened around each suspension bar (), each vibration absorber () being provided with a first mass () connected to the associated suspension bar () via first resilient means (), and with a second mass () connected to the first mass () via second resilient means (), said vibration absorber () having a force generator () interposed between the first mass () and the second mass () and inputting a control force on being instructed by a control unit () as a function of information coming from at least one first measurement sensor () for sensing monitoring parameters for monitoring the associated suspension bar.

Aircraft provided with a device for reducing vibration, and a method therefor

System for minimizing the dynamic excitation at the center of gravity of the fuselage of a helicopter, this excitation being brought about by the forces transmitted between the main transmission box and the fuselage, these two components being joined together by suspension bars which each have an elastic linkage device. According to the invention, each elastic linkage device (2) comprises a cylinder (10), subdivided into two chambers (11, 12) by a piston (13) connected by springs to the two corresponding opposite internal faces (10a, 10b) of the cylinder (10), and the chambers (11, 12) of the cylinder (10) are additionally connected to one another by a pipe (17) which has a small cross section compared with that of the cylinder (10). A computer (6) pilots the movement of liquid in said pipe (17).

System for minimizing the dynamic excitation of a helicopter

A gunsight device for a rotating-wing aircraft having a hollow rotor hub (1), on which there are radially mounted blades constituting said rotating wing, and which is connected to the main transmission box (2) by a drive shaft coaxial with the rotor of the aircraft. The device includes a nonrotating gunsight head (3) mounted, by means of a support (4), at the free upper end (5a) of a nonrotating mast (5) arranged coaxially inside the hub (1) and the drive shaft of the rotor, the other end (5b) of which mast is fixed into the main transmission box (2), a rolling contact bearing (6) coaxial with the rotor axis being provided between the hub (1) and the mast (5). A suspension (7), intended to filter out the excitations in roll and in pitch to which said gunsight head (3) is subjected, is provided between the base (4a) of the support (4) of the gunsight head (3) and the upper end (5 a) of the mast (5).

Gunsight device for rotating-wing aircraft

The present invention relates to a device for elastic linking between two parts (3, 5) in order to filter the vibratory excitations which are transmitted from one to the other, comprising:

Method and device for filtering the vibratory excitations transmitted

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Marseille, France

Tomasz Krysinski