Abstract: A vibration attenuator for a rotor is rotatable about a mast axis and has a frame configured for rotation about the mast axis relative to the rotor. A first mass is axially translatable in a first direction relative to the frame parallel to a first axis, and a first biasing force urges the first mass toward a first-mass rest position in which the first mass is symmetric about the mast axis. A second mass is axially translatable in a second direction relative to the frame parallel to a second axis, and a second biasing force urges the second mass toward a second-mass rest position in which the second mass is symmetric about the mast axis. A selected first or second mass moves radially outward from the rest position to oppose vibrations in the rotor.

Abstract: The present invention includes a damper assembly, method and kit to provide dampening to an airframe comprising: a mass to dampen the vibration of the airframe; one or more wire rope isolators having a first and a second portion, wherein the mass is attached to the one or more wire rope isolators and the mass is isolated from the airframe by the one or more wire rope isolators; and a first fastener and a second fastener, wherein the first fasteners attaches to the first portion of the wire rope isolator to the mass, and the second fastener attaches the second portion of the wire rope isolator to the airframe to dampen vibration of the airframe.

Abstract: A wing airframe for a wing of a tiltrotor aircraft includes a wing airframe core assembly and a wing skin assembly disposed on the wing airframe core assembly. The wing skin assembly includes an outer skin and a damping sublayer, the damping sublayer interposed between the outer skin and the wing airframe core assembly. The tiltrotor aircraft includes a pylon assembly subject to aeroelastic movement during forward flight. The wing is subject to deflection in response to the aeroelastic movement of the pylon assembly.

Abstract: According to one embodiment, an empennage attachment system features an aft attachment mechanism and a forward attachment system. The aft attachment mechanism is configured to be coupled to a tail section of a body of an aircraft and to an empennage proximate to an aft spar of the empennage. The aft attachment mechanism defines a pitch axis such that the aft attachment mechanism allows the empennage to rotate about the pitch axis. The forward attachment system is configured to be coupled to the tail section of the body and to the empennage proximate to a forward spar of the empennage. The forward attachment system is configured to restrict rotation of the empennage about the pitch axis to an allowable range of motion.

Abstract: A liquid inertia vibration elimination (LIVE) system having an upper end cap, a lower end cap, a spindle located between the upper end cap and the lower end cap, and an external tube connected between the upper end cap and the lower end cap.

Abstract: According to one embodiment, an empennage attachment system features an aft attachment mechanism and a forward attachment system. The aft attachment mechanism is configured to be coupled to a tail section of a body of an aircraft and to an empennage proximate to an aft spar of the empennage. The aft attachment mechanism defines a pitch axis such that the aft attachment mechanism allows the empennage to rotate about the pitch axis. The forward attachment system is configured to be coupled to the tail section of the body and to the empennage proximate to a forward spar of the empennage. The forward attachment system is configured to restrict rotation of the empennage about the pitch axis to an allowable range of motion.