Abstract: A conformal bearing assembly includes an bearing housing, an elastomeric member and a bearing element. The bearing assembly is mounted between and inner and outer telescopic member. The elastomeric member allows the bearing element to substantially conform to the adjacent telescopic member irrespective of minor manufacturing inconsistencies along the adjacent telescopic member. Contact pressure between the bearing element and the adjacent telescopic member is thereby more evenly distributed which minimizes regions of interference and or clearance which may otherwise result in undesirable wear characteristics of the telescopic system.

Abstract: A conformal bearing assembly includes an bearing housing, an elastomeric member and a bearing element. The bearing assembly is mounted between and inner and outer telescopic member. The elastomeric member allows the bearing element to substantially conform to the adjacent telescopic member irrespective of minor manufacturing inconsistencies along the adjacent telescopic member. Contact pressure between the bearing element and the adjacent telescopic member is thereby more evenly distributed which minimizes regions of interference and or clearance which may otherwise result in undesirable wear characteristics of the telescopic system.

Abstract: A structural interlock (40) for inhibiting relative rotation between mating elements (20, 42) characterized by a plurality of grooves (50) being formed in one of the mating elements, and a mechanism (60) for producing a nominal contact pressure on the contact area (A.sub.1 thru A.sub.8) between the mating element, which contact pressure elastically deforms the other of the mating elements into the grooves (50), and is less than the material yield strength of either of the mating elements. In the preferred embodiment, the grooves (50) are radially oriented and an applied compressive load produces a nominal contact pressure which is about 80% of the material yield strength.

Abstract: A monolithic structural member (10) operative for reacting steady and vibratory bending moment loads M about an applied loads axis X and having a specially configured cross-sectional configuration for providing improved flaw tolerance. The cross-sectional configuration (10) includes a central connecting element (18) and at least one pair of structural ribs (14a, 14b) being integrally formed with the central connecting element (18) and projecting outwardly thereof. The structural ribs (14a, 14b) are, furthermore disposed in the tensile field produced by the steady portion of the bending moment loads M and are proximal to the centroid C.sub.T of the cross-section (10). The cross-sectional configuration (10) defined by the structural ribs and connecting element produces a partial inertia ratio I.sub.X /I.sub.Y greater than or equal to 1.0, which partial inertia ratio I.sub.X /I.sub.Y has the advantageous effect of retarding or arresting crack propagation in the structural member (10).

Abstract: A mounting arrangement (60) for coupling a control rod (38) to a stationary swashplate member (32) of a helicopter swashplate assembly (30) wherein the mounting arrangement (60) is characterized by a specially configured stationary swashplate member (32) and a trunnion fitting (62) for mounting in combination therewith. More specifically, the stationary swashplate member (32) includes a horizontal web (74) disposed between an inner ring segment (72.sub.IR) and an outer ring segment (72.sub.OR), wherein the horizontal web (74) includes an aperture (78) and defines a mounting surface (74.sub.S). The trunnion fitting (62) includes a base (64) defining a mounting surface (64.sub.S) and a pair of mounting ears (66) having aligned apertures (66.sub.O). The mounting surface (64.sub.S) of the trunnion fitting (62) engages the mounting surface (74.sub.S) of the horizontal web (74) such that the mounting ears (66) are disposed through the aperture (78) of the horizontal web (74).

Abstract: A composite cuff structure (40) for mounting the root end (14e) of a rotor blade assembly (14) to the radial arms (24a, 24b) of a rotor assembly yoke (24) and for accommodating a twist disparity therebetween. The composite cuff structure (40) is generally tubular in shape and is fabricated from a composite material having reinforcing fibers (70) disposed in a binding matrix. The composite cuff structure (40), furthermore, includes a blade-receiving sleeve portion (42), a yoke mounting portion (44), spanwise fold portions (46) and sidelobe portions (48), which portions (42, 44, 46, 48) are structurally integrated to form a unitary body. The blade-receiving sleeve portion (42) is disposed in combination with the root end (14e) of the rotor blade assembly (14) and includes first and second blade mounting segments (42a, 42b), which define a rotor blade attachment plane P.sub.B.

Abstract: An axisymmetric elastomeric bearing assembly (30) for an articulated rotor hub assembly (10), which axisymmetric elastomeric bearing assembly (30) is disposed in combination with a rotor assembly yoke (24) and hub retention member (12) of the rotor hub assembly (10) and is operative for accommodating the multi-directional displacement of a rotor blade assembly (14) thereof. The axisymmetric elastomeric bearing assembly (30) includes a central bearing element (32) having a spherical bearing surface (32s) defining a bearing focal point (30f) and spherical elastomeric elements (34) bonded to the spherical bearing surface (32s) on opposing sides of the bearing focal point (30f). Each of the spherical elastomeric elements (34) have a plurality of alternating layers of elastomer and nonresilient shims (36, 38) which have a center of curvature which is coincident with the bearing focal point (30f) and disposed at increasing radii therefrom.

Abstract: A rotor blade subassembly for a rotor assembly having ducted, coaxial counter-rotating rotors includes a flexbeam, an integrated torque tube/spar member, and an aerodynamic fairing or rotor blade. The flexbeam is a laminated composite structure that reacts centrifugal loads and a majority of the bending loads of the rotor assembly. The flexbeam has a spanwise predetermined linear twist so that the pretwisted flexbeam is unstrained during specified forward flight conditions. The integrated torque tube/spar member is formed as a continuous, filament wound tubular composite structure having high torsional and bending stiffness that provides a continuous torsional load path and facilitates load coupling between the rotor blade and the pretwisted flexbeam. The spar segment of the functions as the primary structural member of the rotor blade subassembly and, is operative to react all bending, torsional, shear, and centrifugal dynamic loads of the rotor assembly.

Abstract: A snubber assembly for a rotor assembly having ducted, coaxial counter-rotating rotors that is design optimized to facilitate utilization of a self-aligning bearing and for installation inboard of the corresponding flexbeam-to-rotor hub attachment joint, thereby enhancing accessibility and reducing maintenance costs. The rotor hub of the rotor assembly is design optimized for securing the snubber assembly in combination therewith and includes a plurality of arms, each arm forming an outboard clevis for attaching the rotor assembly flexbeam to the rotor hub. Inboard of the clevis, each rotor hub arm includes an outboard internal bulkhead having a bolt hole therethrough and an inboard internal bulkhead having a bolt hole therethrough. The inboard and outboard internal bulkheads in combination define a bearing cavity and an internal cavity for securing the snubber assembly in combination with the rotor hub.

Abstract: An integrated spline/cone seat subassembly for a rotor assembly that is design optimized to minimize the radial dimensions of the rotor shafts, the rotor shaft bearings, the transmission housing, and the swashplate subassemblies thereof. The integrated subassembly includes a rotor hub having a shaft aperture with a plurality of hub splines extend radially inwardly therefrom. The lower portion of each hub spline has an outwardly tapered portion that makes a predetermined angle with respect to the hub centerline. The integrated subassembly further includes a rotor shaft having a primary shaft portion of a first diameter, an end shaft portion having an intermediate second diameter less than the first diameter, and a conic transition portion that makes a predetermined angle with respect to the rotor shaft axis. The end shaft portion has a plurality of shaft splines extending radially outwardly therefrom that defines a third diameter that is equal to the first diameter.