Abstract: A ball bearing and housing assembly includes a shaft having a stepped bore extending therethrough. The stepped bore is defined by a first bore segment having an inboard cylindrical interior surface that has a first bore diameter. The first bore segment extends from a shaft end and terminates at a shoulder. The shoulder is axially located between a first radial centerline of a plurality of balls and an inner axial end. The stepped bore is further defined by a second bore segment having an outboard cylindrical interior surface that has second bore diameter. The second bore segment extends axially from the inner axial end towards the shaft end and terminates at the shoulder. The second bore diameter is greater than the first bore diameter. A fastener is fitted through the first bore segment and threaded into a housing.

Abstract: A ball bearing and housing assembly includes a shaft having a stepped bore extending therethrough. The stepped bore is defined by a first bore segment having an inboard cylindrical interior surface that has a first bore diameter. The first bore segment extends from a shaft end and terminates at a shoulder. The shoulder is axially located between a first radial centerline of a plurality of balls and an inner axial end. The stepped bore is further defined by a second bore segment having an outboard cylindrical interior surface that has second bore diameter. The second bore segment extends axially from the inner axial end towards the shaft end and terminates at the shoulder. The second bore diameter is greater than the first bore diameter. A fastener is fitted through the first bore segment and threaded into a housing.

Abstract: A ball bearing assembly includes a one piece outer ring having a first and second outer race and an exterior surface; and a one piece inner ring having a first and second inner race, the inner ring is integrally formed on a shaft. A first plurality of balls is disposed between the first outer race and the first inner race; and a second plurality of balls is disposed between the second outer race and the second inner race. The first plurality of balls has a first contact and the second plurality of balls has a second contact angle.

Abstract: An edge flap arrangement for an aircraft wing includes a main flap element and an actuator for moving the main flap element relative to the aircraft wing. A linkage arrangement supports the main flap element and includes a drop hinge link arrangement having a fixed strut secured to the aircraft wing and a drop link secured to the main flap element. The fixed strut and the drop link are connected by a hinge point having an hourglass bearing assembly having hourglass shaped rollers with a circular cross section symmetrical about a longitudinal axis, first and second axial ends, and an exterior surface. The exterior surface defines a concave engagement surface having a first radius of curvature R1 and a second radius of curvature which is greater than the first radius of curvature R1. The first radius of curvature is between 50 and 95 percent of the second radius of curvature.

Abstract: In one aspect, the present invention resides in an edge flap arrangement for an aircraft wing that has a main flap element and an actuator for moving the main flap element relative to the wing, a linkage arrangement that supports the main flap element from the aircraft wing for movement relative to the wing, the linkage arrangement including a drop link and a hinge point. The fixed strut and the drop link are pivotally connected by the hinge point. The hinge point includes a bearing. The bearing is an hourglass bearing assembly that has an inner raceway outer raceway. The outer raceway is positioned around the inner raceway. A plurality of rollers is disposed between the inner raceway and the outer raceway. The plurality of rollers, the outer raceway and/or the inner raceway are manufactured from CREN and/or CRES.

Abstract: A cage for an hourglass roller bearing includes an annular ring having a first axial face and a second axial face. A plurality of first rails extend from the first axial face and a plurality of second rails extend from the second axial face. The cage includes a plurality of pockets. Each of the plurality of pockets is defined by opposing circumferentially facing walls of at least one of adjacent pairs of the first rails and adjacent pairs of the second rails. The circumferentially facing walls are arcuately formed so that each of the plurality of pockets is cylindrical.

Abstract: A ball bearing includes an outer ring having at two outer raceways and an inner ring having two inner raceways. A plurality of balls is disposed in each of the two inner and outer raceways. The plurality of balls include load bearing balls and spacer balls. The spacer balls are disposed between the load bearing balls. Each of the load bearing balls has a single point of contact with each of the two inner and outer raceways. The load bearing balls are preloaded between the outer ring and the inner ring at predetermined force.

Abstract: An edge flap arrangement for an aircraft wing includes a main flap element and an actuator. A linkage arrangement supports the main flap. The linkage arrangement includes a drop hinge link arrangement. The drop hinge link arrangement includes a fixed strut and a drop link. The fixed strut and the drop link are pivotally connected by a hinge point. The hinge point includes an hourglass bearing. The hourglass bearing includes an inner member, an outer member, and a plurality of hourglass rollers. Any combination of the inner member, the outer member, and the hourglass rollers are fabricated from CREN, Cronidur 30, XD15NW, 422 Stainless Steel, CRES, and/or 440C Stainless Steel. A cage is disposed between the inner member and the outer member. The cage includes a plurality of first rails and a plurality of second rails. Opposing pairs of first rails and second rails define a plurality of pockets.

Abstract: An edge flap arrangement for an aircraft wing includes a main flap element and an actuator for moving the main flap element relative to the aircraft wing. A linkage arrangement supports the main flap element and includes a drop hinge link arrangement having a fixed strut secured to the aircraft wing and a drop link secured to the main flap element. The fixed strut and the drop link are connected by a hinge point having an hourglass bearing assembly having hourglass shaped rollers with a circular cross section symmetrical about a longitudinal axis, first and second axial ends, and an exterior surface. The exterior surface defines a concave engagement surface having a first radius of curvature R1 and a second radius of curvature which is greater than the first radius of curvature R1. The first radius of curvature is between 50 and 95 percent of the second radius of curvature.

Abstract: A guide mechanism, configured for use with a guided attack rocket, includes an inner housing partially disposed in an outer housing. The inner and outer housings each define a forward end and an aft end. A first angular contact bearing is positioned between the outer housing forward end and the inner housing forward end. A second angular contact bearing is positioned between the outer housing aft end and the inner housing aft end. A retaining nut is received over the inner housing forward end. The retaining nut preloads the first and second angular contact bearings. Each of the angular contact bearings includes an inner member disposed within an outer member. The outer member defines an outer raceway and the inner member defines an inner raceway. A plurality of rolling elements is disposed between the outer raceway and the inner raceway.

Abstract: A rolling element bearing includes an outer member having an outer member interior surface and an outer member exterior surface. The bearing includes an inner member having an inner member interior surface and an inner member exterior surface and a plurality of rolling elements disposed between the inner member and the outer member. The bearing includes a plurality of random-length slug separators. The separators are of a first length, a second length or a third length, which are not equal. One of the plurality of random-length slug separators is disposed adjacent to at least one of the plurality of rolling elements. The plurality of rolling elements are non-rhythmically spaced apart.

Abstract: A ball bearing includes an outer ring having at two outer raceways and an inner ring having two inner raceways. A plurality of balls is disposed in each of the two inner and outer raceways. The plurality of balls include load bearing balls and spacer balls. The spacer balls are disposed between the load bearing balls. Each of the load bearing balls has a single point of contact with each of the two inner and outer raceways. The load bearing balls are preloaded between the outer ring and the inner ring at predetermined force.

Abstract: A guide mechanism, configured for use with a guided attack rocket, includes an inner housing partially disposed in an outer housing. The inner and outer housings each define a forward end and an aft end. A first angular contact bearing is positioned between the outer housing forward end and the inner housing forward end. A second angular contact bearing is positioned between the outer housing aft end and the inner housing aft end. A retaining nut is received over the inner housing forward end. The retaining nut preloads the first and second angular contact bearings. Each of the angular contact bearings includes an inner member disposed within an outer member. The outer member defines an outer raceway and the inner member defines an inner raceway. A plurality of rolling elements is disposed between the outer raceway and the inner raceway.

Abstract: An edge flap arrangement is provided for an aircraft wing and includes a main flap element and an actuator for moving the main flap element relative to the wing. A linkage arrangement supports the main flap element from the aircraft wing for movement relative to the wing, and includes including a drop hinge link arrangement having a fixed strut secured to the aircraft wing and a drop link secured to the main flap element. The fixed strut and drop link are pivotally connected by a hinge point having a bearing installed therein. The bearing includes an outer race, an inner race and an annular seal assembly snap-fit into the outer race. The annular seal assembly includes first and second annular retaining rings and a resilient ring disposed between the first and second annular retaining rings.

Abstract: A cage for an hourglass roller bearing includes an annular ring having a first axial face and a second axial face. A plurality of first rails extend from the first axial face and a plurality of second rails extend from the second axial face. The cage includes a plurality of pockets. Each of the plurality of pockets is defined by opposing circumferentially facing walls of at least one of adjacent pairs of the first rails and adjacent pairs of the second rails. The circumferentially facing walls are arcuately formed so that each of the plurality of pockets is cylindrical.

Abstract: An edge flap arrangement for an aircraft wing includes a main flap element and an actuator. A linkage arrangement supports the main flap. The linkage arrangement includes a drop hinge link arrangement. The drop hinge link arrangement includes a fixed strut and a drop link. The fixed strut and the drop link are pivotally connected by a hinge point. The hinge point includes an hourglass bearing. The hourglass bearing includes an inner member, an outer member, and a plurality of hourglass rollers. Any combination of the inner member, the outer member, and the hourglass rollers are fabricated from CREN, Cronidur 30, XD15NW, 422 Stainless Steel, CRES, and/or 440C Stainless Steel. A cage is disposed between the inner member and the outer member. The cage includes a plurality of first rails and a plurality of second rails. Opposing pairs of first rails and second rails define a plurality of pockets.

Abstract: A rolling element bearing includes an outer member having an outer member interior surface and an outer member exterior surface. The bearing includes an inner member having an inner member interior surface and an inner member exterior surface and a plurality of rolling elements disposed between the inner member and the outer member. The bearing includes a plurality of random-length slug separators. The separators are of a first length, a second length or a third length, which are not equal. One of the plurality of random-length slug separators is disposed adjacent to at least one of the plurality of rolling elements. The plurality of rolling elements are non-rhythmically spaced apart.

Abstract: In one aspect, the present invention resides in an edge flap arrangement for an aircraft wing that has a main flap element and an actuator for moving the main flap element relative to the wing, a linkage arrangement that supports the main flap element from the aircraft wing for movement relative to the wing, the linkage arrangement including a drop link and a hinge point. The fixed strut and the drop link are pivotally connected by the hinge point. The hinge point includes a bearing. The bearing is an hourglass bearing assembly that has an inner raceway outer raceway. The outer raceway is positioned around the inner raceway. A plurality of rollers is disposed between the inner raceway and the outer raceway. The plurality of rollers, the outer raceway and/or the inner raceway are manufactured from CREN and/or CRES.

Abstract: A duplex bearing is configured for use with a nuclear reactor control rod drive mechanism. The duplex includes an outer member and an inner member wherein each defines an interior surface and an exterior surface. The outer member interior surface defines a first and second outer raceway; and the inner member defines a first and second inner raceway. A first plurality of load-carrying rolling elements and a first plurality of spacer rolling elements are disposed in a first annular cavity defined between the first inner raceway and first outer raceway. A second plurality of load-carrying rolling elements and a second plurality of spacer rolling elements are disposed in a second annular cavity defined between the second inner raceway and the second outer raceway. The duplex bearing is configured to operate with sealed de-ionized water exhibiting a temperature in the range of up to about 1200° F. as a sole lubricant.

Abstract: An edge flap arrangement is provided for an aircraft wing and includes a main flap element and an actuator for moving the main flap element relative to the wing. A linkage arrangement supports the main flap element from the aircraft wing for movement relative to the wing, and includes including a drop hinge link arrangement having a fixed strut secured to the aircraft wing and a drop link secured to the main flap element. The fixed strut and drop link are pivotally connected by a hinge point having a bearing installed therein. The bearing includes an outer race, an inner race and an annular seal assembly snap-fit into the outer race. The annular seal assembly includes first and second annular retaining rings and a resilient ring disposed between the first and second annular retaining rings.