Abstract: An apparatus comprising a spinner fairing assembly comprising a spinner configured to be fixed relative to a gimbaled yoke coupled to a mast system, and a spinner base configured to be fixed relative to the mast system. A spinner fairing assembly comprising a spinner aligned along a first axis, and a spinner base aligned along a second axis and configured to interface with the spinner, wherein the spinner is configured to transition between a neutral position and a canted position with respect to the spinner base, wherein the first axis and the second axis are coincident in the neutral position, and wherein the first axis and the second axis are not coincident and meet at an origin within the spinner in the canted position.

Abstract: A rotary system and method to control feathering and centrifugal forces of a rotor blade during flight. The rotary system having a hub assembly, which includes a hollow yoke arm to receive a spindle section of the rotor blade. A tension-torsion strap extends through the hollow yoke arm and couples the rotor blade and the hub assembly. The method includes allowing the spindle section of the rotor blade to pivot within the hollow yoke arm and controlling rotational and centrifugal movement of the rotor blade with the tension-torsion strap.

Abstract: An apparatus comprising a rotor hub system comprising a floating plate, a plurality of drive link trunnions each comprising a pivoting arm and positioned radially about the floating plate, wherein each drive link trunnion is coupled to the floating plate via the pivoting arm, and a housing disposed about the floating plate, coupled to each of the drive link trunnions, and configured to couple to a mast. Included is an apparatus comprising a floating plate, a plurality of drive link trunnions each comprising a pivoting arm and positioned radially about the floating plate, wherein each drive link trunnion is coupled to the floating plate via the pivoting arm, and wherein the drive link trunnions are configured to move the floating plate in response to a force applied to the drive link trunnions, and a housing disposed about the floating plate and coupled to each of the drive link trunnions.

Abstract: A drive mechanism for a rotary aircraft includes an outer drive member having a plurality of drive trunnions extending therefrom; a middle drive member resiliently coupled to the outer drive member; and an inner drive member resiliently coupled to the middle drive member.

Abstract: An apparatus comprising a rotor hub system comprising a floating plate, a plurality of drive link trunnions each comprising a pivoting arm and positioned radially about the floating plate, wherein each drive link trunnion is coupled to the floating plate via the pivoting arm, and a housing disposed about the floating plate, coupled to each of the drive link trunnions, and configured to couple to a mast. Included is an apparatus comprising a floating plate, a plurality of drive link trunnions each comprising a pivoting arm and positioned radially about the floating plate, wherein each drive link trunnion is coupled to the floating plate via the pivoting arm, and wherein the drive link trunnions are configured to move the floating plate in response to a force applied to the drive link trunnions, and a housing disposed about the floating plate and coupled to each of the drive link trunnions.

Abstract: An aircraft rotor constant-velocity drive system having a differential mechanism that includes a drive disk configured to be integral in rotation with a mast, an upper member at least partially located above the drive disk, a lower member at least partially located below the drive disk, and at least one link connecting the upper member and the lower member to the drive disk such that the drive disk drives the upper member and the lower member in rotation with the drive disk and that the upper member and the lower member are allowed to rotate differently with respect to the drive disk. The link having opposing end joints and a central joint that pivotally engages the drive disk. The system also having a gimbal device configured to drive a rotor hub and to allow gimbaling of the rotor hub with respect to a mast.

Abstract: A rotary system and method to control feathering and centrifugal forces of a rotor blade during flight. The rotary system having a hub assembly, which includes a hollow yoke arm to receive a spindle section of the rotor blade. A tension-torsion strap extends through the hollow yoke arm and couples the rotor blade and the hub assembly. The method includes allowing the spindle section of the rotor blade to pivot within the hollow yoke arm and controlling rotational and centrifugal movement of the rotor blade with the tension-torsion strap.

Abstract: A constant-velocity drive system for a rotary-wing aircraft rotor comprising a differential torque-splitting mechanism and a gimbal mechanism is disclosed. A rotary-wing aircraft having a rotary-wing aircraft rotor comprising a differential torque-splitting mechanism and a gimbal mechanism is disclosed.

Abstract: A centrifugal force bearing having a means for providing a steady pitching moment is disclosed. The centrifugal force bearing may optionally comprise a coning means. A rotor system having the centrifugal force bearing is disclosed. A rotary-wing aircraft having the centrifugal force bearing is disclosed.

Abstract: A torque coupling (13) for a rotor head (11) of a rotary-wing aircraft has upper and lower plates (29, 31) configured for rotation with a rotor mast (19). Drive links (33) pivotally connected to the upper and lower plates (29, 31) pivot about a pivot axis generally parallel to and radially offset from an axis of rotation of the plates. Each link (33) is engaged with adjacent drive links (33) to form a continuous ring of links, such that motion of one link (33) about its pivot axis causes motion in an opposite direction of each adjacent link (33) about its pivot axis. Drive elements (25) connect the drive links (33) to an assembly configured to receive rotor blades. The drive elements (25) may be components of a universal joint, a multiple trailing-link configuration, a pad-bearing configuration, or another type of articulating assembly.

Abstract: A torque coupling for a rotor head of a rotary-wing aircraft is configured for rotation with a mast and for causing rotation of an attached yoke. The coupling has trunnions that rotate with the mast and extend generally radially. Pad-bearing assemblies each have a central member coupled to one of the trunnions with a laminated spherical bearing and have laminated pad bearings affixed to opposing sides of the central member. The laminated bearings have alternating rigid and elastomeric layers. A bearing mount is affixed to each pad bearing and is connected to a yoke for rotating the yoke with the mast. The pad-bearing assemblies allow for relative motion between each central member and the associated trunnion and between each central member and the bearing mounts through elastic shear deformation, and this allows for gimballing of the attached yoke relative to the mast.

Abstract: An assembly for providing flexure to a blade of a rotary blade system includes an upper support plate having an upper curved surface, a lower support plate having a lower curved surface, and a yoke positioned therebetween. At least one of the upper and lower yoke surfaces has a layer of cushioning material positioned thereon and secured thereto. An alternate embodiment includes an assembly for providing flexure to a blade of a rotary blade system, including, an upper support plate having an upper curved surface, a lower support plate having a lower curved surface, and a yoke positioned therebetween and directly contacting the support plates wherein one of the curved surfaces is a non-circular arc that does not form part of the circumference of a circle. Another alternate embodiment includes a similar assembly having a twist-shank type of yoke for providing rotation of attached blades about their respective pitch axes.

Abstract: A centrifugal force bearing having a means for providing a steady pitching moment is disclosed. The centrifugal force bearing may optionally comprise a coning means. A rotor system having the centrifugal force bearing is disclosed. A rotary-wing aircraft having the centrifugal force bearing is disclosed.

Abstract: A torque coupling for a rotor head of a rotary-wing aircraft is configured for rotation with a mast and for causing rotation of an attached yoke. The coupling has trunnions that rotate with the mast and extend generally radially. Pad-bearing assemblies each have a central member coupled to one of the trunnions with a laminated spherical bearing and have laminated pad bearings affixed to opposing sides of the central member. The laminated bearings have alternating rigid and elastomeric layers. A bearing mount is affixed to each pad bearing and is connected to a yoke for rotating the yoke with the mast. The pad-bearing assemblies allow for relative motion between each central member and the associated trunnion and between each central member and the bearing mounts through elastic shear deformation, and this allows for gimballing of the attached yoke relative to the mast.

Abstract: A constant-velocity drive system for a rotary-wing aircraft rotor comprising a differential torque-splitting mechanism and a gimbal mechanism is disclosed. A rotary-wing aircraft having a rotary-wing aircraft rotor comprising a differential torque-splitting mechanism and a gimbal mechanism is disclosed.

Abstract: A torque coupling (13) for a rotor head (11) of a rotary-wing aircraft has upper and lower plates (29, 31) configured for rotation with a rotor mast (19). Drive links (33) pivotally connected to the upper and lower plates (29, 31) pivot about a pivot axis generally parallel to and radially offset from an axis of rotation of the plates. Each link (33) is engaged with adjacent drive links (33) to form a continuous ring of links, such that motion of one link (33) about its pivot axis causes motion in an opposite direction of each adjacent link (33) about its pivot axis. Drive elements (25) connect the drive links (33) to an assembly configured to receive rotor blades. The drive elements (25) may be components of a universal joint, a multiple trailing-link configuration, a pad-bearing configuration, or another type of articulating assembly.

Abstract: An assembly for providing flexure to a blade of a rotary blade system includes an upper support plate having an upper curved surface, a lower support plate having a lower curved surface, and a yoke positioned therebetween. At least one of the upper and lower yoke surfaces has a layer of cushioning material positioned thereon and secured thereto. An alternate embodiment includes an assembly for providing flexure to a blade of a rotary blade system, including, an upper support plate having an upper curved surface, a lower support plate having a lower curved surface, and a yoke positioned therebetween and directly contacting the support plates wherein one of the curved surfaces is a non-circular arc that does not form part of the circumference of a circle. Another alternate embodiment includes a similar assembly having a twist-shank type of yoke for providing rotation of attached blades about their respective pitch axes.