Abstract: A rotor hub assembly for a helicopter includes a rotor hub operably connectable to a shaft of a helicopter. One or more flex beams extend through the rotor hub, with each end of each flex beam operably connectable to a rotor blade. One or more inner bearings are located at the rotor hub to spherically support the one or more flex beams in the rotor hub. A rotor assembly for a helicopter includes a rotor hub operably connectable to a shaft of a helicopter. One or more flex beams extending through the rotor hub and one or more inner bearings are located at the rotor hub to spherically support the one or more flex beams in the rotor hub. A plurality of rotor blades are operably connected to the ends of the one or more flex beams.

Abstract: A composite spar for a helicopter blade includes two or more layers of unidirectional laminate material. One or more upper plies of bi-directional laminate extend from an upper airfoil portion of the spar disposed between adjacent layers of the two or more layers of unidirectional laminate material. One or more lower plies of bi-directional laminate material extend from a lower airfoil portion of the spar disposed between adjacent layers of the two or more layers of unidirectional material. The upper plies and the lower plies overlap defining a crackstopper layer configured to prevent propagation of defects in the spar.

Abstract: An elastomeric spherical bearing includes a multiple of shims, at least two of which have different thicknesses. In one exemplary embodiment, each of the shims has a different thickness with a generally equivalent stress on each shim.

Abstract: An elastomeric spherical bearing includes a multiple of elastomeric layers with an essentially equivalent fatigue life.

Abstract: An elastomeric spherical bearing includes a multiple of shims, at least two of which have different thicknesses. In one exemplary embodiment, each of the shims has a different thickness with a generally equivalent stress on each shim.

Abstract: An elastomeric spherical bearing includes a multiple of shims, at least two of which have different thicknesses. In one exemplary embodiment, each of the shims has a different thickness with an essentially equivalent stress on each shim.

Abstract: A rotor hub assembly for a helicopter includes a rotor hub operably connectible to a shaft of a helicopter. One or more flex beams extend through the rotor hub, with each end of each flex beam operably connectible to a rotor blade. One or more inner bearings are located at the rotor hub to spherically support the one or more flex beams in the rotor hub. A rotor assembly for a helicopter includes a rotor hub operably connectible to a shaft of a helicopter. One or more flex beams extending through the rotor hub and one or more inner bearings are located at the rotor hub to spherically support the one or more flex beams in the rotor hub. A plurality of rotor blades are operably connected to the ends of the one or more flex beams.

Abstract: A composite spar for a helicopter blade includes two or more layers of unidirectional laminate material. One or more upper plies of bi-directional laminate extend from an upper airfoil portion of the spar disposed between adjacent layers of the two or more layers of unidirectional laminate material. One or more lower plies of bi-directional laminate material extend from a lower airfoil portion of the spar disposed between adjacent layers of the two or more layers of unidirectional material. The upper plies and the lower plies overlap defining a crackstopper layer configured to prevent propagation of defects in the spar.

Abstract: An elastomeric spherical bearing includes a multiple of shims, at least two of which have different thicknesses. In one exemplary embodiment, each of the shims has a different thickness with a generally equivalent stress on each shim.

Abstract: An elastomeric spherical bearing includes a multiple of elastomeric layers with an essentially equivalent fatigue life.

Abstract: A composite rotating swashplate for a helicopter rotor system which includes rotor blades with associated control rods. The control rods control the pitch of the rotor blades. The composite rotating swashplate according to the present invention includes an outer tubular ring with an inner tubular ring located within the outer ring. The outer ring is made from braids of tri-axial graphite fibers interwoven with unidirectional plies. The inner tubular ring is made from braided .+-.45 degree graphite fibers. A support ring is located within the outer ring and external to an inboard periphery of the inner tubular ring. A plurality of apertures are formed through the outer and inner rings. The apertures are adapted to receive the terminal ends of the control rods. Mounting bolts extend through at least one wall of the outer and inner rings and attach the terminal ends of the control rods to the swashplate.