| 摘要 |
The invention relates to a rotor for a rotorcraft having foldable hinged blades, the rotor comprising a hub ( 10 ), each blade being connected to the hub via a sleeve, each sleeve being hinged about a pitch axis ( 15 ) relative to the hub, the rotor including a respective lag damper ( 14 ) associated with each blade, each damper being hinged both to the hub and to the corresponding sleeve, the rotor including a system for controlling the pitch of the blades via respective pitch levers ( 16 ) secured to each of the sleeves; the rotor includes two abutments designed to co-operate with tooling for blocking the pitch of the blades, a first abutment presenting a bearing surface ( 35, 36 ) matching a shape of revolution about an axis ( 18 ) of revolution, and a second abutment ( 33, 39, 70 ) designed to act axially along said axis of revolution.
|
