Abstract: The present invention provides a mechanism (90) for damping vibrations to prevent coupling of vibration modes of the carrier structure (106) with vibration modes of a rotor (100) secured to said carrier structure (106). The mechanism comprises a support (3) suitable for being fastened to said rotor (100) and at least one resonator (1) including a mass (5) carried by said support (3) via mobile mounting means (6) for mounting said mass (5) to move on said support (3), said mechanism (90) including damper means (8) for damping the resonator (1), which means are interposed between the resonator (1) and an engagement member (9) on said support (3).

Abstract: The invention provides a vibration filter mechanism for aircraft equipment. A weighted lever arm (5) is hinged via bearings (22, 23) associated respectively with a first structure connected to a fuselage and with a second structure connected to the equipment (12). Deformable means (7) oppose pivoting movement of the lever arm. The lever arm (5) is arranged as a one-piece fork that comprises a pair of branches (19, 20) that are interconnected by a crossbar (21) and that are hinged to the bearings (22, 23) about spaced-apart parallel pivot axes (A1, A2). The fork carries a torsion shaft (24) that extends between the branches (19, 20) at their free ends (9), the torsion shaft (24) constituting the weight weighting the lever arm (5) and the deformable means (7) of the mechanism.

Abstract: A device (10) for reducing vibration of a main rotor (1) having a support (20) and a plurality of heavy elements (30) and of rollers (50). Each heavy element (30) includes two first openings (31) respectively at least partially in registration with two second openings (22) of the support (20. Each roller (50) passes through a first opening (31) and a second opening (22). The device (10) has link means (60) for connecting the support (20) to the hub (2). A drive shaft (70) and a drive means (80) rotate at a first speed of rotation (V1) greater than a second speed of rotation (V2) of the hub (2). The drive shaft (70) rotates about an axis of rotation (AX1) of the support (20). The link means (60) is connected to the support (20) by a link member (90) enabling the support (20) to rotate about the axis of rotation (AX1) relative to the link means (60).

Abstract: The invention provides a mechanism for attenuating torque pulsations between an engine (2) and a rotor (1) of a rotorcraft. Torsion means (5) are interposed between the driving and driven shafts and comprise a torsion shaft (6) axially engaged with the drive shaft (3) and the driven shaft (4) an inlet shaft (9) and an outlet shaft (10) respectively engaged with the drive and driven shafts (3, 4) a lever system (7) that extends radially relative to the torsion shaft (6) and that has the inlet and outlet shafts (9, 10) hinged thereto via points (11, 12) that are spaced apart; and a mass (8) carried by said lever arm (7) at its free end (13) radially farthest away from the axis along which the torsion shaft (6) extends.

Abstract: An insulating coating (1) with high damping power and suitable for being fastened to a structure (2). The coating comprises a dissipater mesh made up of a plurality of dissipater elements (3) and of nodes (4) with the bottom end (4?) of each node being fastened to said structure (2). Each dissipater element is secured to first and second nodes (6, 7). The bottom ends (4?) of said nodes (4) project from said dissipater elements (3) so as to be suitable for creating an empty space (5) between the dissipater elements (3) and said structure (2). In addition, at least one dissipater element (3) is provided with at least one branch (10, 20) provided with a heavy element (30, 31, 32). The heavy element (30, 31, 32) has a first mass that is greater than or equal to a second mass of said branch (10, 20).

Abstract: A mechanical transmission system for a rotorcraft, including a supercritical transmission shaft and an active magnetic damper secured to the structure of the rotorcraft via a mechanical damper is provided.

Abstract: A framework fixed to the structure of a vehicle, which framework carries a generally planar seat proper via mobility structure for providing the seat proper with mobility relative to the framework. The seat proper is rigid and is suspended from the framework via a deformable structure which is deformable in at least one of the dimensions of the plane of the seat proper. The plane of the framework for supporting the seat proper is disposed above the plane of the seat proper that is supported by the framework, so as to impart a pendular type structure to the structure providing mobility to the seat proper relative to the framework.

Abstract: Described is a blade (10) extending longitudinally from a root (11) of the blade (10) to a free end (12) of the blade (10), the blade (10) being provided with an incorporated resonator (20) for reducing the drag movements (F1, F2) of the blade (10), the resonator (20) being provided with a closed tank (30) that is partially filled with a liquid (50). Furthermore, the resonator (20) includes a central tube (40) immersed inside the tank (30), the tank (30) and the central tube (40) being arranged in a longitudinal direction (Y) of the blade (10), the central tube (40) having first and second ends (41, 42) that communicate with the tank (30) so that the liquid (50) can move from the tank (30) into the central tube (40), and vice versa.

Abstract: A blade (10) extending longitudinally from a root (11) of the blade (10) to a free end (12) of the blade (10), the blade (10) having a resonator (13) incorporated therein to reduce the drag movements (F1, F2) of the blade (10), the resonator (13) being provided with a solid and movable heavy element (30) and with resilient retaining element (20) secured to the heavy element (30) and to the blade (10). Furthermore, the resonator (13) includes guide element (40) in which the heavy element (30) is capable of oscillating (F1?, F2?) longitudinally, the guide element (40) being arranged in a longitudinal direction (D1) of the blade.

Abstract: An energy absorber element comprises an absorber portion having first and second distal ends and having a first elongate element and a second elongate element facing the first elongate element and connected to the second element solely at the first and second distal ends, a first anchor point secured to the first distal end of the absorber portion, and a second anchor point secured to the second distal end of the absorber portion, wherein each of the first and second elongate elements includes a succession of straight-line segments parallel to one another and at least one circularly-arcuate segment such that at least two successive straight-line segments are connected together by one of the at least one circularly-arcuate segment.

Abstract: A crashworthy seat for a vehicle comprises a stand including a first and a second foot connected mechanically to a first and a second vertical support leg; a pan connected by the stand to a floor wherein the first and the second feet are disposed on each side of the pan, the pan including a seat proper and a seat back, wherein the seat back has a support element secured to the first and the second vertical support legs configured to support the seat back a guide element configured to guide the pan in translation; an energy absorber device; a first anchor point secured to the first distal end of the absorber portion; and a second anchor point secured to the second distal end of the absorber portion.

Abstract: An anti-vibratory device with rotary compensation weights includes two sets of two identical rotors with respective eccentric compensation weights, the units being symmetrically disposed in relation to an axis of symmetry and the axes of rotation of the rotors being parallel between themselves and orthogonal in relation to the axis of symmetry; and a rotational drive system for the rotors. Advantageously, the device includes controllable mobile equipment carrying the drive system and being able to slide along the axis of symmetry in order to drive the dephasing of the rotors with eccentric compensation weights associated with the sets.

Abstract: The present invention relates to an absorbent covering having high damping power, the covering being secured to a structure (20) and being provided with an absorbent layer (10) of elastic material (4). Remarkably, said absorbent layer (10) comprises a dissipater mesh arranged in the elastic material (4) and constituted by a plurality of nodes (2) and of dissipater elements (1), which dissipater elements are advantageously elliptical in shape.

Abstract: A device is provided for suspending a battery (20) of an aircraft, the device including at least one spring (41, 54); the device further includes an adjustment element enabling the stiffness of the spring to be adjusted.

Abstract: The present invention relates to an absorbent covering (1) having high damping power, secured on a structure (2) and comprising a dissipater mesh made up of a plurality of dissipating elements (3) and of nodes (4) each having its bottom end (4?) secured on said structure (2). In remarkable manner, said bottom ends (4?) of said nodes (4) project from said dissipating elements (3) so as to leave an empty space (5) between the dissipating elements (3) and said structure (2), said absorbent covering (1) including main absorbent elements (6) arranged in said empty space (5), each of said main absorbent elements (6) being secured firstly to a bottom face (3?) of a said dissipating element (3) and secondly to said structure (2).

Abstract: The invention relates to a mechanical transmission system for a rotorcraft, the system including a supercritical transmission shaft (10) and an active magnetic damper (17 to 20) secured to the structure (34) of the aircraft via a mechanical damper (50).

Abstract: An antivibration device for reducing the vibration of a structure, includes a stationary casing, mounted on the structure, and first and second sets each including two contra-rotary rotors having eccentric flyweights, the flyweights and the rotors being disposed respectively in first and second mutually parallel planes, the centers of rotation of the contra-rotary rotors representing the corners of a rectangular parallelogram in the second plane, and the axes of rotation of the contra-rotary rotors being mutually parallel and orthogonal to the first plane. In addition, it includes a stationary main motor secured to the casing with a through shaft having a first end driving the contra-rotary rotors of the first set and a second end driving the contra-rotary rotors of the second set.

Abstract: A device is provided for suspending a battery (20) of an aircraft, the device including at least one spring (41, 54); the device further includes an adjustment element enabling the stiffness of the spring to be adjusted.

Abstract: The present invention relates to an absorbent covering having high damping power, the covering being secured to a structure (20) and being provided with an absorbent layer (10) of elastic material (4). Remarkably, said absorbent layer (10) comprises a dissipater mesh arranged in the elastic material (4) and constituted by a plurality of nodes (2) and of dissipater elements (1), which dissipater elements are advantageously elliptical in shape.

Abstract: An antivibration device for reducing the vibration of a structure, includes a stationary casing, mounted on the structure, and first and second sets each including two contra-rotary rotors having eccentric flyweights, the flyweights and the rotors being disposed respectively in first and second mutually parallel planes, the centers of rotation of the contra-rotary rotors representing the corners of a rectangular parallelogram in the second plane, and the axes of rotation of the contra-rotary rotors being mutually parallel-and orthogonal to the first plane. In addition, it includes a stationary main motor secured to the casing with a through shaft having a first end driving the contra-rotary rotors of the first set and a second end driving the contra-rotary rotors of the second set.