Abstract: A rotor for a rotary wing aircraft having a single blade with a longitudinal pitch axis and that is hinge mounted on the rotary shaft for rotating the rotor, the hinge being about an axis that is transversal relative to the rotary shaft, said rotary wing describing a cone when its pitch angle is not zero, the rotor possessing a balancing flyweight device for balancing the resultant of the horizontal component of the lift force and of the rotary drag force of the blade, the device being mounted to rotate with the rotary wing about its rotary shaft and, under the effect of the centrifugal force to which it is subjected while the rotary wing is rotating, generating a horizontal force that is applied to the rotary shaft of the motor and that opposes the above-mentioned resultant with a magnitude of that is a function of the position of the flyweight(s) of the balancing device relative to the rotary shaft of the rotor.

Abstract: A rotor for a rotary wing aircraft having a single blade with a longitudinal pitch axis and that is hinge mounted on the rotary shaft for rotating the rotor, the hinge being about an axis that is transversal relative to the rotary shaft, said rotary wing describing a cone when its pitch angle is not zero, the rotor possessing a balancing flyweight device for balancing the resultant of the horizontal component of the lift force and of the rotary drag force of the blade, the device being mounted to rotate with the rotary wing about its rotary shaft and, under the effect of the centrifugal force to which it is subjected while the rotary wing is rotating, generating a horizontal force that is applied to the rotary shaft of the motor and that opposes the above-mentioned resultant with a magnitude of that is a function of the position of the flyweight(s) of the balancing device relative to the rotary shaft of the rotor.

Abstract: A rotary viscous damper, comprising a stator and a rotor defining between them a main chamber filled with a visco-elastic fluid, which can be of a thixotropic, dilatant, or Bingham, etc, or Magneto-Rheological nature, substantially radial paddles being disposed on each of said stator and rotor, said paddles dividing said main chamber into a plurality of chambers, and presenting means to create a fluid communication between the chambers through specifically shaped conduits that may be located at either the exterior, interior, upper or lower section of the damping chambers. Said damper further comprises at least one conical elastomeric bearing between the stator and the rotor to serve as dynamic sealing, as well as a guide between the stator and the rotor. A volume compensation device is also comprised in the said damper to accommodate fluid temperature changes. Self-lubricated bearings are also comprised in the said damper to guide the main shaft of the stator.

Abstract: An elastomeric bearing system capable of sustaining a high compressive load is adapted to connect the blades of a helicopter rotor to a rotor hub. The bearing system comprises first and second elastomeric bearing elements fixed at the opposite ends of a tie bar. Said first elastomeric bearing element comprises a rigid external housing having an internal truncated-tapered surface with its minor basis directed inwardly, a rigid internal housing having an external truncated-tapered surface with its minor basis directed inwardly, and a resilient body between said internal and external truncated-tapered surfaces. Said second elastomeric bearing element is constituted by a chevron sub-assembly, comprising two tapered elastomeric bearing elements disposed with their minor basis facing each other, both having an individual internal housing and a resilient body and sharing a common external housing with a double-taper internal surface, the internal housings being connected one another by fastening elements.

Abstract: The invention relates to an elastomeric bearing system capable of sustaining a high compressive load, thus allowing a pivot movement around an axis perpendicular to said load and adapted, in particular, to connect the blades of a helicopter rotor to a rotor hub. Such a bearing system comprises a first and a second elastomeric bearing element fixed at the opposite ends of a tie bar. Said first elastomeric bearing element comprises a rigid external housing having an internal truncated-tapered surface with its minor basis directed inwardly, a rigid internal housing having an external truncated-tapered surface with its minor basis directed inwardly, and a resilient body between said internal and external truncated-tapered surfaces.