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

Rocket or ballistic launch rotary wing vehicle

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

A flexible beam rotor assembly for an aircraft includes a rotor spar having an axis of rotation and a hole through which the axis of rotation passes. A spindle has a teetering connection to the rotor spar, the teetering connection having a teetering axis above the rotor spar at the rotor axis of rotation. A spindle housing is nonrotatably mounted to the aircraft and rotatably receives the spindle. The spindle housing and spindle protrude through the hole in the rotor spar and are tiltable in response to pilot control on a left-right spindle pivot axis and a fore-aft spindle pivot axis. The left-right spindle pivot axis and the fore-aft spindle pivot axis are located below the teetering axis and above the rotor at the rotor axis of rotation. A pylon is pivotally mounted to the fuselage for fore and aft movement relative to the fuselage to absorb vibration due to rotation of the rotor during forward flight of the aircraft. The spindle housing is attached to the pylon by a universal joint. A pair of pylon arms are pivotally connected to a lower end of the pylon. A pair of pushrods are pivotally connected between the pylon arms and the spindle housing. The pylon, spindle housing, arms, and pushrods form a parallelogram which allows the spindle to move fore and aft to absorb vibration without changing spindle tilt.

Rotor head for rotary wing aircraft

A cyclic swashplate device for controlling rotorcraft blade pitch is disclosed for application to rotorcraft swashplates, in particular, in helicopters. A cyclic swashplate device controls the rotorcraft blade pitch. The device ( 10 ′), with rotating ( 10 ′) and non-rotating ( 14 ′) cyclic swashplates is designed in such a way that at least one of the two disks includes a modular link fitting assembly ( 46, 42 ) ensuring the links with the disk ( 12′, 14 ′) and the pitch connecting rods ( 6 ) and/or at least one driving device or with the pilot control devices ( 17 ) and/or at least one retaining device. Interconnecting fittings are attached rigidly and separately to an annular device, such as one of the rings ( 31′, 30 ′) of a bearing ( 21 ′) on the corresponding disk ( 14′, 12 ′).

Blade pitch control disk device for a rotorcraft rotor

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

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.

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

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. 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). 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). Application a l'equipement des rotors d'helicoptere.

Michel Victor Russier

Papers

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

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

Dispositif à plateaux cycliques montés sur articulations lamifiées pour la commande du pas des pales d'un rotor