Rotor and an aircraft provided with such a rotor

A rotor designed to contribute at least in part to the lift and/or to the propulsion of an aircraft, the rotor comprising a hub and at least three lift assemblies that are movable together in rotation about an axis of rotation of the rotor, each lift assembly comprising a root and a lift member that extends in the span direction from the root towards an end, the root being attached to the hub by a mobility and retention member and being secured to the lift member, each mobility and retention member conferring on each lift assembly a degree of freedom to move relative to the hub about at least a lead-lag axis and a pitch axis, each lift assembly being positioned circumferentially between two adjacent lift assemblies, each lift assembly being connected to the two adjacent lift assemblies respectively by a first damper and by a second damper, and for each lift assembly:

• a first plane contains the lead-lag axis and is orthogonal to the pitch axis of the lift assembly;
• the first damper is hinged to the lift assembly at least about a first axis parallel to the lead-lag axis of the lift assembly;
• the second damper is hinged to the lift assembly at least about a second axis parallel to the lead-lag axis of the lift assembly;
• the first axis is situated in a volume lying between the first plane of the lift assembly and the axis of rotation, the second axis being positioned outside the volume;
• and
• the root includes a shackle fastened to the mobility and retention member and a fitting fastened to the lift assembly between the shackle and the end, the fitting comprising two L-shaped plates, each L-shaped plate presenting an orifice through which the second axis passes, and the fitting is configured to limit a flapping movement of the lift assembly.

A rotor designed to contribute at least in part to the lift and/or to the propulsion of an aircraft, the rotor comprising a hub and at least three lift assemblies that are movable together in rotation about an axis of rotation of the rotor, each lift assembly comprising a root and a lift member that extends in the span direction from the root towards an end, the root being attached to the hub by a spherical abutment and being secured to the lift member, each spherical abutment conferring on each lift assembly a degree of freedom to move relative to the hub about at least a lead-lag axis and a pitch axis, each lift assembly being positioned circumferentially between two adjacent lift assemblies, each lift assembly being connected to the two adjacent lift assemblies respectively by a first damper and by a second damper, and for each lift assembly:

• a first plane contains the lead-lag axis and is orthogonal to the pitch axis of the lift assembly;
• the first damper is hinged to the lift assembly at least about a first axis parallel to the lead-lag axis of the lift assembly;
• the second damper is hinged to the lift assembly at least about a second axis parallel to the lead-lag axis of the lift assembly;
• the first axis is situated in a volume lying between the first plane of the lift assembly and the axis of rotation, the second axis being positioned outside the volume;
• and
• the root includes a shackle fastened to the spherical abutment and a fitting fastened to the lift assembly between the shackle and the end, the fitting comprising two L-shaped plates, each L-shaped plate presenting an orifice through which the second axis passes, the two L-shaped plates hold between them an intermediate connection member, and the intermediate member including a fork connected to a pitch rod and at least one orifice through which the first axis passes.