Patent ID: 9114875
Filing Date: 2015-08-25
Classification: B64C

Abstract:
1. A lead lag damper for a rotor unit of a rotary wing aircraft, the rotor unit having a rotor and a hub, the damper comprising: a first side configured to couple to the hub with a central axis of the first side being generally coaxial with a central axis of the hub; a second side spaced from the first side and being opposed to the first side; linking means at the second side to link the second side to a plurality of blades of the rotor; and an essentially cylindrical damper body extending between the first side and the second side and comprising an elastomer material, the lead lag damper being a spring/damping system which is axially preloaded, so that the lead lag damper acts in a homogenous manner in inplane eigenmodes of the rotor.