Abstract: The suspension device comprises, for linking the base (5b) of the transmission gearbox to the fuselage (6), two parallel rods (14), articulated (15) onto lateral supports (16) fixed to opposite sides of the base (5b) and extending on the same side of the transmission gearbox to their link (19) to structural supports (20) of the fuselage (6). Elastic links (17) provide the suspension at least in the direction perpendicular to the rods (14). In a variant, the rods (14) are linked to the fuselage (6) being articulated on a transverse flexible bar, equipped as required with a central flapping mass, or on transverse levers articulated onto one another by a central articulation and onto the structure. Application to uni-or bidirectional, focal-point and, as appropriate, antiresonant suspension of helicopter main rotors.

Abstract: The present invention relates to a rotor arrangement for rotary-wing aircraft, comprising at least one pair of opposite blades mounted on a common one-piece beam, which is twistable, flexible and whose median part rotates with the shaft of the rotor.According to the invention, this arrangement is characterized in that said beam is mounted on the shaft of the rotor by means of an articulation enabling it to pivot, in limited manner, about an axis transverse to said beam and at right angles to said rotor shaft.The invention is applied to rotors for helicopters.

Abstract: The invention relates to a two-bladed tail rotor arrangement for gyroplanes and helicopters, comprising two plates fixed to a rotary shaft, between which are embedded the median portion of a flat flexible spar. On the ends of the said spar are fitted two shells which form the rotor blades and whose cross-section evolves in the blade root area to become circular, whereby the said shells are terminated by cylindrical sleeves fixed by bonding to flanges which are connected by elastic blocks to two plates. The rotor boss assembly can be provided with a cylindrical fairing.

Abstract: A suspension system is disclosed for reducing vibration between the rotor and the structure of a rotary-wing aircraft having a reduction-gear train coextensive with the shaft of the lift rotor. The housing of said gear train is supported by tie-rods and by a flexible beam having its mid-point attached to said housing and its extremities attached to the aircraft structure through the medium of flexible blocks. The beam may be made of metal or a composite material.

Abstract: A rotor for a rotating wing aircraft has a star-shaped hub each arm of which supports a blade. The yoke between each blade and arm is a two tine fork constituted by a continuation of the blade root.

Abstract: An improved rotor for a helicopter comprises a yoke at the inner end of each arm engaging the rotor hub by way of a spherical abutment.