A method for manufacturing a shaft (1) in which linking members (3) are provided to ends of a cylindrical member (2) including: polishing end surfaces of a metal sheet; a bending step for bending the metal sheet into a cylindrical or arcuate shape; butting together the polished end surfaces of the metal sheet, the end surfaces facing each other in a state in which the metal sheet has been bent into the cylindrical shape, or disposing a plurality of the metal sheets that are bent into an arcuate shape so as to form a cylindrical shape and butting together the polished end surfaces of the metal sheets, and then heating the butted portions so that the butted portions are diffusion-joined, thereby forming the cylindrical member (2); cooling the post-diffusion-joining-step cylindrical member (2); and joining the linking members (3) to the ends of the cylindrical member (2).

A ducted-rotor aircraft includes a fuselage, first and second ducts, and a spindle that is coupled to the fuselage. Each duct includes a rotor having a plurality of blades. The first and second ducts are coupled to opposed ends of the spindle. The spindle is rotatably coupled to the fuselage with first and second bearings. The first bearing is configured to react to radial loads and the second bearing is configured to react to both radial and axial loads. The spindle includes a shaft, first and second fittings secured to opposed ends of the shaft, and first and second attachment interfaces that are attachable to the first and second ducts. The attachment interfaces may be integral with the fittings. Alternatively, the fittings may be configured to be secured to the attachment interfaces with fasteners.

A ducted-rotor aircraft includes a fuselage, first and second ducts, and a spindle that is coupled to the fuselage. Each duct includes a rotor having a plurality of blades. The first and second ducts are coupled to opposed ends of the spindle. The spindle is rotatably coupled to the fuselage with first and second bearings. The first bearing is configured to react to radial loads and the second bearing is configured to react to both radial and axial loads. The spindle includes a shaft, first and second fittings secured to opposed ends of the shaft, and first and second attachment interfaces that are attachable to the first and second ducts. The attachment interfaces may be integral with the fittings. Alternatively, the fittings may be configured to be secured to the attachment interfaces with fasteners.

A drive shaft has a central tubular portion formed of a polymer composite with imbedded fibers. It extends between a first end and a second end. The central tubular portion has an outer peripheral surface. There is at least one ring on the outer peripheral surface of the central tubular portion. A method of repairing a composite material tube includes the steps of (a) identifying a damaged area on a composite tube, and (b) placing a patch on a surface of the tube and over the damaged area.

A machine includes a liquid lubrication system and a shaft, the shaft being rotatable about a rotation axis, the shaft including a first part, a second part engaged coaxially with the first part, and a journal bearing between the first part and the second part, the first part being rotatable relative to the second part about the rotation axis, a helical feature disposed between the first part and the second part and configured to define a helical pump between the first part and the second part, the pump being hydraulically connected to the liquid lubrication system, the journal bearing being disposed adjacent to the helical feature.

An aircraft drive shaft including an outer shaft having a first diameter configured to couple a first gearbox and a second gearbox to provide power transfer between the two gearboxes, an inner shaft concentric with the outer shaft and having a second diameter configured to provide structural support to the outer shaft, a gap defined between an outer peripheral surface of the inner shaft and an inner peripheral surface of the outer shaft, wherein the gap is sized according to a ballistic projectile cross-section size that the aircraft is considered to encounter on an upcoming mission, and a sleeve located at least at first end of the outer shaft connecting the outer shaft to the inner shaft.

A wheel bearing device (1) including: an outer member (2) on the inner periphery of which an outer-side rolling surface (2c/2d) is formed; an inner member (3) on the outer periphery of which an inner-side rolling surface (3c/3d) is formed; and a plurality of rolling bodies (41) interposed between the rolling surfaces (2c/2d/3c/3d) of the outer member (2) and the inner member (3). The wheel bearing device having a spline hole (3b) formed in a through hole (3h) of the inner member (3). The spline hole includes a guide groove (3G) formed on an inner circumferential surface thereof. A guide plate (8G) of a finishing broach (8) passes through the guide groove in the inner periphery of the spline hole (3b).

To provide a method of manufacturing a shaft for a steering device, the shaft including a spline shaft part to be coupled with an input shaft, a stopper part to be coupled with an output shaft, and an intermediate shaft part that couples the spline shaft part with the stopper part. The method includes: a step of forming a hole part recessed in an axial direction from one end of a pillar-shaped material by forging; and a step of pressing the material in which the hole part has been formed into a die to perform drawing in a radial direction on a portion of the material at which the spline shaft part and the intermediate shaft part are formed, and prolonging a length along the axial direction of the hole part at the same time by forging.

To provide a method of manufacturing a shaft for a steering device, the shaft including a spline shaft part to be coupled with an input shaft, a stopper part to be coupled with an output shaft, and an intermediate shaft part that couples the spline shaft part with the stopper part. The method includes: a step of forming a hole part recessed in an axial direction from one end of a pillar-shaped material by forging; and a step of pressing the material in which the hole part has been formed into a die to perform drawing in a radial direction on a portion of the material at which the spline shaft part and the intermediate shaft part are formed, and prolonging a length along the axial direction of the hole part at the same time by forging.

A system for manufacturing a drive shaft assembly comprises a welding apparatus configured to weld a tube to an end fitting to form the drive shaft assembly having an annular weld. A transport apparatus is configured to transport the drive shaft assembly away from the welding apparatus. A knurling apparatus receives the drive shaft assembly from the transport apparatus. The knurling apparatus is configured to knurl the weld of the drive shaft assembly. The knurling apparatus includes a pair of knurling plates having textured surfaces in facing relationship. One of the knurling plates is configured to move relative to the other of the knurling plates to roll the drive shaft assembly between the textured surfaces, thereby knurling the weld to improve an appearance and texture of the outer surface of the drive shaft assembly.