Abstract: The present invention relates to a method of reducing the vibration of a lift and propulsion rotor (5) of a rotorcraft (1), the rotor having a plurality of airfoil assemblies (10) that perform rotary movement around a drive axis (AX) of the rotor (5), each airfoil assembly (10) comprising a blade (20) extending longitudinally from a root (22) suitable for being fastened to hinge means (4) of a hub (6) of said rotor (5) to a free end (21), a first distance (D1) extending between said free end (21) and said hinge means (4). In the method, said first distance (D1) is caused to vary cyclically so that the projection (TR) of the center of gravity (Cg) of a blade (20) on a horizontal plane (P) perpendicular to said drive axis (AX) and containing said hinge means (4) describes a circle.

Abstract: The present invention relates to a method of reducing the vibration of a lift and propulsion rotor (5) of a rotorcraft (1), the rotor having a plurality of airfoil assemblies (10) that perform rotary movement around a drive axis (AX) of the rotor (5), each airfoil assembly (10) comprising a blade (20) extending longitudinally from a root (22) suitable for being fastened to hinge means (4) of a hub (6) of said rotor (5) to a free end (21), a first distance (D1) extending between said free end (21) and said hinge means (4). In the method, said first distance (D1) is caused to vary cyclically so that the projection (TR) of the center of gravity (Cg) of a blade (20) on a horizontal plane (P) perpendicular to said drive axis (AX) and containing said hinge means (4) describes a circle.

Abstract: The present invention relates to problems of maintenance of elastomeric members. According to the invention, the elastomeric member is provided with at least one elastomeric layer 1 disposed between two rigid strength members 2. In addition, the elastomeric member is provided with graduations 5 located on its visible surface 7, presenting an angle of inclination relative to the rigid strength members 2, thus making it possible to evaluate and monitor propagation of a crack 6 merely by inspecting it visually.

Abstract: The present invention relates to a device for lashing down a rotorcraft wing, said wing being provided with at least first and second adjacent blades P and P?, the ends of said blades being provides with respective endpieces. In addition, the device comprises a main cord CP having a first end CPE1 fastened to first fastener means 5? arranged on a second end CPE2 secured to a second blade P? and having a second end CPE2 secured to a second fastener means M1 arranged on a first endpiece of the first blade P. The lashing-down endpiece includes first fastener means 5 for fastening to a first main cord CP and second fastener means M1 for fastening to a second main cord CP.

Abstract: A device for lashing down a rotorcraft wing, the wing being provided with at least first and second adjacent blades P and P?, the ends of the blades being provided with respective endpieces. In addition, the device includes a main cord CP having a first end CPE1 fastened to first fastener elements 5? arranged on a second endpiece of the second blade P? and having a second end CPE2 secured to second fastener elements M1 arranged on a first endpiece of the first blade P. The lashing-down endpiece includes first fastener elements 5 for fastening to a first main cord CP and second fastener elements M1 for fastening to a second main cord CP.

Abstract: The present invention relates to problems of maintenance of elastomeric members. According to the invention, the elastomeric member is provided with at least one elastomeric layer 1 disposed between two rigid strength members 2. In addition, the elastomeric member is provided with graduations 5 located on its visible surface 7, presenting an angle of inclination relative to the rigid strength members 2, thus making it possible to evaluate and monitor propagation of a crack 6 merely by inspecting it visually.