The present disclosure includes calculating coordinates of a midpoint of one of a plurality of first tool teaching points and the subsequent first tool teaching point, and calculating coordinates of a midpoint of one of a plurality of second tool teaching points that corresponds to the one first tool teaching point and the subsequent second tool teaching point, calculating an inter-midpoint distance between the midpoint of the first tool teaching points and the midpoint of the corresponding second tool teaching points, determining whether the inter-midpoint distance is within a given tolerance range, and reporting, when the inter-midpoint distance is out of the given tolerance range, the corresponding first tool teaching points and second tool teaching points as poor.

The subject matter described herein relates to methods and systems for fast imprinting of nanometer scale features in a workpiece. According to one aspect, a system for producing nanometer scale features in a workpiece is disclosed. The system includes a die having a surface with at least one nanometer scale feature located thereon. A first actuator moves the die with respect to the workpiece such that the at least one nanometer scale feature impacts the workpiece and imprints a corresponding at least one nanometer scale feature in the workpiece.

A method and apparatus for processing fuselage sections. A first fuselage section is held in a cradle system. A current shape of the first fuselage section in the cradle system is measured. Forces to change the current shape of the first fuselage section to a desired shape for connecting the first fuselage section to a second fuselage section are identified. The forces identified are applied using a system to change the current shape of the first fuselage section towards the desired shape.

A machine tool provided with a tool spindle and a work table for supporting a workpiece for plastic forming on a workpiece with a tool attached to the tool spindle. The partially curved tool is has a moving mechanism to move the tool spindle relative to the workpiece, a spindle rotating motor to turn the tool spindle relative to the workpiece, a movement control unit to control the moving mechanism to move the tool along the workpiece while pressing a curved portion on the surface to be machined, and a turn control unit to control the spindle rotating motor to orient a normal line of the curved portion toward the surface of the workpiece at a reference position taken as a reference.

A method of forming a component by applying a forming load to a blank of material against a mandrel, wherein the mandrel defines the shape of the component to be formed and applying a forming load as a combination of a localised force and localised friction heating.

A stretch forming device includes a die and gripping portions gripping both end portions of an elongate material. The cross-sectional shape of the die has a curved shape bulging a central side of a forming surface; the length in a longitudinal direction of the elongate material is less than that of the forming surface; a second die having a second forming surface along the forming surface is installed removably on a central portion of the forming surface; and the stretch forming device has a first mode wherein, when the second die is installed on the forming surface, only the second die is pressed against the elongate material while a tensile force is applied to the elongate material, and a second mode wherein, when the second die is removed from the forming surface, the die is pressed against the elongate material while a tensile force is applied to the elongate material.

A method for manufacturing a ring includes clamping a first region of a metal sheet against a mandrel, and, while the first region of the metal sheet is clamped against the mandrel, bending the metal sheet around the mandrel to join opposite end faces of the metal sheet and form the ring shaped to the mandrel. A system for manufacturing a ring from a metal sheet includes (a) a mandrel having a ring-shaped surface, (b) a clamp facing the ring-shaped surface and configured to clamp a first region of a metal sheet to the mandrel, and (c) a plurality of dies configured to bend the metal sheet around the mandrel, while the clamp clamps the first region to the mandrel, to join opposite end faces of the metal sheet and form a ring shaped to the ring-shaped surface.

Flanges formed on sheet metal parts to increase the part stiffness or create mating surface for further assembly are created in an incremental sheet forming process using forming tool and supporting tool that move along a specified tool path so as to gradually deform a peripherally-clamped sheet metal work piece into the desired geometry. With two universal tools moving along the designed toolpath on the both sides of the part, the process is very flexible. Process time is can also be reduced by utilizing an accumulative double-sided incremental hole-flanging strategy, in which the flange is formed in only one step.

The present disclosure provides a floating block of a hub shaping mold. The floating block can include: at least one inner support member having a first side and a second side opposite to each other, wherein the first side of the at least one inner support member can include a first arc surface, and at least one first bulge can be arranged on the first arc surface; at least one outer pressing member having a first side and a second side opposite to each other, wherein the first side of the at least one outer pressing member can include a second arc surface matched with the first arc surface, at least one second bulge can be arranged on the second arc surface, and the at least one first bulge and the at least one second bulge can be arranged in a staggered manner.

An aerodynamic component of a gas turbine engine is provided and is fittable to a shell having a shell shape. The aerodynamic component includes a body having a component shape initially deviating from the shell shape prior to an assembly operation in which the aerodynamic component is to be fit to the shell. Deviation of the component shape from the shell shape aids in an establishment of a final desired shape of the aerodynamic component following the assembly operation.