A rotor system vibration absorber for use with a helicopter of other rotocraft is disclosed in which spring forces are provided by a plurality of elongated rods (73) arranged in a selected pattern. The rods are coupled at one end to a fixed base (79) that is coupled to a rotor hub (55), and at the other end to a tuning weight (81).

Rotor system vibration absorber

Embodiments of the present invention relate to a rocket or ballistic launch rotary wing air vehicle.

Rocket or ballistic launch rotary wing vehicle

The present invention relates to a device for reducing the vibrations of the rotor of a rotary-wing aircraft, having an oscillating mass (M1), elastically held radially on the hub (4) of the rotor in the vicinity of its axis (X-X) and fixed to an articulated rod (10) substantially longitudinal to said axis (X-X). According to the invention, said device includes: an adjustment oscillating mass (M2), mounted so that it can move on the rod (10) and having an adjustment position for which the frequency of the resonator formed by said oscillating masses (M1, M2) is matched to the frequency of said vibrations; and drive means (18) for bringing the adjustment oscillating mass (M2) into said adjustment position.

Device for reducing the vibrations generated by a lift rotor of a rotary-wing aircraft

An anti-torque mechanism which permits a full range of swashplate assembly motion. The anti-torque mechanism generally includes an anti-torque shaft and a compound bearing mounted thereto to provide five-degrees-of-freedom (spherical-linear-elastomeric) so as to permit a swashplate attachment point to move axially in response to pitch input; pivot in response to swashplate tilt; and move in/out in the radial direction.

Swashplate anti-torque mechanism

The rotating plate of the system is fixed in rotation with the rotor by a driver with two rigid driving tracks extending axially and diametrically opposite in being fixed in rotation with the rotor. Each track engages with one of two driving fingers fixed in rotation with the rotating plate and diametrically opposite on this latter. Each track has two webs between which one finger is engaged with the result of following on this track a rectilinear trajectory, parallel to the rotor axis and a circular arc trajectory centerd on this axis, respectively in the case of change of collective and cyclic pitch.

Swash-plates system for control of the pitch of rotor blades with rotating plate driver

Apparatus for controlling both collective and cyclic pitch of blades of a helicopter rotor comprises a non-rotating plate which is connected via a fixed caliper and servo controls to a fixed housing and to which is attached the internal ring of a ball race bearing. The external ring of the bearing carries a rotating plate, which is connected by means of rotating caliper or links to each of the rotors and by means of pitch rods to control levers for adjusting the pitch of the blades. The non-rotating plate is fixed to external armatures of laminated joint pieces which are mounted slidingly up and down a guide base. The collective pitch is controlled by sliding the assembly of non-rotating plate and joint pieces up or down the guide base while the cyclic pitch is controlled by inclining the assembly relative to the main rotor shaft. This inclination involves deformations in the laminated joints.

Apparatus for control of collective and cyclic pitch of the blades of a rotor

The invention relates to a device for damping the vibrations of a rotary-wing aircraft rotor. An annular weight is disposed concentrically of the rotor axis. This weight is supported by at least three resiliently deformable elements such as helical springs, radially biased in directions distributed regularly around the rotor axis. The inner ends of the springs directly bear on a part extending the rotor shaft axially. Their outer ends directly bear on the annular weight so that the spring apply statically balanced centrifugal thrusts to the annular weight. The springs are so still that they support the annular weight without substantially bending.

Resonator device for damping the vibrations of a rotor of a rotary-wing aircraft

The invention relates to a flapping restrainer device for the blades of a rotorcraft main rotor, and a rotor head comprising the same. The lower restrainers comprise a reciprocal star-shaped plate (32), having as many radial branches (33) as blades, and each one of the branches being engaged into a radial opening (6) of the hub (3). Outside the latter, the star-shaped plate (32) cooperates with supporting runners (47) integral with the blades. The upper restrainers comprise, for each blade, a stop which is retractable by the effect of the centrifugal force and which is composed of a lever (52), pivoting on a pivot (53) carried by the hub (3), and a first arm (55) of which constitutes a stop finger directed towards an upper supporting component (60) integral with the blade, while a second arm (56) carries a governor weight (57) and a nose (58) for support against a shoulder (59) integral with the hub (3).

Flapping restrainer device for rotorcraft rotor blades, and rotor head comprising said device

L'invention concerne un resonateur pour attenuer les vibrations d'un rotor de giravion. Ce resonateur est forme essentiellement par une masse annulaire 4, par exemple en forme de cloche aplatie, qui est supportee, et reliee a une fusee 2, prolongeant l'arbre du rotor au-dessus du moyeu 1, par au moins trois ressorts helicoidaux tels que 5a, prenant appui, interieurement sur la fusee 2, et exterieurement sur le bord interieur de la cloche 4; les ressorts tels que 5a sont precomprimes de facon a exercer des poussees centrifuges, equilibrees statiquement, sur le bord 4a de la cloche 4. L'invention est applicable par exemple au rotor principal d'un helicoptere.

Dispositif resonateur pour attenuer les vibrations d'un rotor de giravion

Le dispositif comprend un plateau non-tournant (40-41) qui est relie par un compas fixe (45) et des servocommandes a un carter fixe (2), et solidarise a la bague interne (23) d'un roulement a billes (22), dont la bague externe (25) constitue le plateau tournant, relie par des compas tournants au rotor et par des bielles de pas aux leviers de commande de pas des pales. The device comprises a non-rotating plate (40-41) which is connected by a fixed compass (45) and servo to a fixed casing (2), and secured to the inner ring (23) of a ball bearing ( 22), the outer ring (25) constitutes the turntable, connected by rotating compass to the rotor and by connecting rods of not the control levers of the blades. Le plateau non-tournant (40-41) est egalement solidarise aux armatures externes (21) d'articulationslamifiees (14) monteescoulissantes le long d'un guide-plateaux (3) par leurs armatures internes (18). The non-rotating plate (40-41) is also secured to the outer armatures (21) articulationslamifiees (14) monteescoulissantes along a disk guide (3) by their internal reinforcements (18). Le pas collectif est transmis par coulissement d'ensemble le long du guide-plateaux (3), tandis que le pas cyclique est transmis par inclinaison d'ensemble des plateaux par rapport a l'arbre (1) grâce aux deformations des articulations lamifiees (14). Collective pitch is transmitted by all sliding along the disk guide (3), while the cyclic pitch is transmitted by all the trays with respect to the tilt shaft (1) due to the deformations of the laminated joints ( 14). Application a l'equipement des rotors d'helicoptere. Application Equipment of helicopter rotors.

Robert Jean Suzzi

Papers

Apparatus for control of collective and cyclic pitch of the blades of a rotor

Resonator device for damping the vibrations of a rotor of a rotary-wing aircraft

Flapping restrainer device for rotorcraft rotor blades, and rotor head comprising said device

Dispositif resonateur pour attenuer les vibrations d'un rotor de giravion

Swash-plate device supported by a laminated elastomeric bearing for the pitch control of rotor blades