Abstract: A cutting insert according to one embodiment of the present invention comprises an upper surface, a lower surface, a lateral surface, a cutting edge, and a fastening hole, wherein the cutting edge includes a main cutting edge, a nose R part connected to the main cutting edge, and a sub-cutting edge connected to the nose R part, the upper surface includes a land part adjacent to the cutting edge, an inclined surface downwardly inclined from the land part, and an upper surface bottom part extending from the inclined surface, first and second protrusion parts are formed respectively, in which the first protrusion part is connected to a main cutting edge land part and formed on a main cutting edge inclined surface at a portion at which a nose R part inclined surface ends and the second protrusion part is connected to a sub-cutting edge land part and formed on a sub-cutting edge inclined surface at a portion at which the nose R part inclined surface ends, and no protrusion is present on the nose R part inclined su

Abstract: A method of forming an annular wick for a heat pipe is disclosed. The method includes forming a plurality of layers of wick material around an elongate rod; placing the elongate rod and the layers of wick material into a central die opening of an annular die assembly; placing the rod, the layers of wick material, and the annular die assembly into a central clamp opening of a clamp, where the clamp is configured to hold the rod, the layers of wick material, and the annular die assembly together; and heating the rod, the layers of wick material, the annular die assembly, and the clamp to a temperature sufficient to thermally expand the rod toward the central die opening of the annular die assembly to compress the layers of wick material between the rod and the central die opening of the annular die assembly.

Abstract: Wafer level proximity sensors are formed by processing a silicon substrate wafer and a silicon cap wafer separately, bonding the cap wafer to the substrate wafer to form a bonded wafer sandwich, and then selectively thinning the silicon substrate wafer and silicon cap wafer. The silicon substrate wafer is thinned first, and an interconnect structure of through-silicon vias is formed within the thinned silicon substrate wafer. The silicon cap wafer is then thinned to expose openings facing an area of the thinned silicon substrate wafer where a photosensitive region is location and facing an area of the thinned silicon substrate wafer where an emitter die is to be installed. After emitter die installation, the openings in the thinned silicon cap wafer are filled with a transparent material. The thinned silicon cap wafer further includes an opaque light barrier to block light transmission between the openings.

Abstract: A jig set for placing an insulated circuit board on a cooling surface of a cooling unit, and a method for placing the insulated circuit board on the cooling surface using the jet set. The jig set includes: a positioning jig configured to be disposed on the cooling surface, and having an opening corresponding to a size of the insulated circuit board in a plan view, to thereby define a fixing area for housing the insulated circuit board therein; a height control jig including a control part shaped to be fitted into the fixing area of the positioning jig, the control part having, at a lower end thereof, a pressing surface for pressing an upper surface of the insulated circuit board located in the fixing area toward the cooling surface; and a positioning weight configured to apply, to the positioning jig, a pressure toward the cooling surface.

Abstract: An aircraft skin alignment system includes at least one support structure to support one or more aircraft skins and one or more assembly tools; the one or more assembly tools having a holding mechanism to releasably engage with a first aircraft skin; a pulling mechanism to apply a pulling force to the first aircraft skin; and an edge locator; the pulling mechanism is to pull the first aircraft skin such that a first edge of the first aircraft skin abuts the edge locator, the edge locator preventing the first edge from being pulled past the edge locator; and one or more tool holes can be drilled into the first aircraft skin such that the one or more tool holes are aligned based on an edge index due to a position of the edge locator.

Abstract: A system, method and apparatus are proposed to assist in assembling the frame, attaching the skin, and performing other tasks in manufacturing an airship and constructing other structures that are otherwise challenging, inefficient, or unsuitable for humans to perform, and/or that traditionally require significant investments in capital intensive manufacturing facilities. Several embodiments are proposed in which these and other recurring manufacturing tasks can be performed safely and efficiently with the assistance of autonomous, semi-autonomous, and/or human-directed robots, acting independently and in robot swarms.

Abstract: A cutting tool with sufficient stiffness of a body is provided. A cutting tool 10 includes a body 100 in which a discharge groove 120 for guiding and discharging chips is formed, and a cutting insert 200 fastened and fixed on a distal end side of the body 100. The cutting insert 200 includes a first surface 210 through which a through-hole 230 is opened, and a major cutting edge 231 formed so as to extend straight at an end part of the first surface 210. A protrusion portion 130 protruding so as to cover part of the first surface 210 of the cutting insert 200 from outside is formed at the body 100. A clearance hole 170 is formed so as to extend from a surface of the body 100 opposite the cutting insert 200 toward a corner cutting edge 242 when viewed from the distal end side along a central axis AX1.

Abstract: A sleeve removal tool for removing a split sleeve embedded in a structure includes a main rod, a nose cap, a housing, and a nut. The main rod includes a main threaded portion and a neck portion. The nose cap is configured to removably couple to the neck portion of the main rod and to removably couple to a flare of the split sleeve embedded in the structure. The housing includes a non-marking foot. The housing is configured to at least partially surround the main rod. The nut is configured to be threaded onto the main threaded portion of the main rod, wherein threading the nut onto the main threaded portion of the main rod forces the housing against the structure and forces the main rod away from the structure, thereby removing the split sleeve from the structure.

Abstract: Disclosed herein is a hoist tool including a hoist frame and a base structure. The hoist frame includes a structural framework having a first end and a second end and at least one first rotation-enabling coupling at the second end of the structural framework. The base structure includes at least one second rotation-enabling coupling configured to engage with the at least one first rotation-enabling coupling of the hoist frame. The at least one second rotation-enabling coupling of the base structure defines a rolling axis. The hoist frame is selectively movable by the hoist to position the at least one first rotation-enabling coupling into engagement with the at least one second rotation-enabling coupling and when coupled and when the assembled structure is coupled to the hoist frame, the hoist frame is selectively rotatable about the rolling axis, relative to the base structure, to enable a rollover of the assembled structure.

Abstract: A transport and assembly alignment tool, for prefabrication, transport and/or erection/assembly of a plurality of arcuate segments or near identical modules into a large annular or toroidal structure includes one or more alignment fixtures that have a matched pair of mating alignment members. The alignment members each have a first circularity and/or axial alignment member which aligns to a second circularity and/or axial alignment member. The first circularity and/or axial alignment member is held in alignment with the second circularity and/or axial alignment member by a radially extending alignment feature to establish circumferential alignment thereof and are locked together by locking means. The first axial alignment member is rigidly secured to a first one of the arcuate segments proximate to one circumferential end thereof and the second axial alignment member rigidly secured to a second one of the arcuate segments proximate to one circumferential end thereof.

Abstract: A levelling machine includes a pair of spaced apart rail assemblies, a gantry assembly and a face mill assembly. The spaced apart rail assemblies define an x axis. The gantry assembly is moveably attached to the pair of spaced apart rail assemblies whereby the gantry assembly defines a y axis. The gantry assembly is moveable in the x axis along the pair of spaced apart rail assemblies. The face mill assembly is moveably attached to the gantry assembly and is moveable in the y axis along the gantry assembly. The face mill assembly has a plurality of saw blades, the saw blades being generally in an x-y plane defined by the x axis and y axis. The saw blades have a plurality of teeth that extend downwardly generally in a z axis. The face mill assembly is moveable in the z axis.

Abstract: A separation tool is configured to extract an end cap from a main body of a turbine component. The separation tool includes a first body with a first base and a first holding portion that projects from the base and a second body with a second base and a second holding portion. The first and second bodies are separable from each other and are configured to form a contoured gap when the first and second bodies are positioned against each other in a side-by-side configuration. In addition, the first and second bodies are configured so that when the first and second bodies are brought together, a first side wall of the gap is convex and a second side wall of the gap opposing the first side wall is concave.

Abstract: The present disclosure relates to an insert and system of installing the same. The insert includes a tapered core and a cylinder. The core releasably secures to an installation device which includes a depth stop or a depth control to control the installation depth of the insert. The insert may be provided in a tray that allows for easier handling of the inserts and installation thereof in installation holes, for example in a hydraulic manifold. In some cases, the core includes a threaded hole to releasably secure the insert to the installation device, thus allowing the installation device to pull the core into the cylinder. The core and cylinder may be made of metallic materials such as steels, steel alloys and others. In some cases the insert can withstand blow out pressures of 40,000 psi or higher.

Abstract: Improved thermal detachment driven by leverage from: improved electrical locus targeting allows electron density to define Optimal Regions balancing the resistance and heat whereby, detachment systems are shifted and realigned coaxially and placed closer to the ends of subject coils while being hermetically sealed, manufacturing steps are taught. to show how system is made.

Abstract: A cassette handle includes a body, a first foot, and a second foot. When in a position following the application of a force to the body, the first foot and the second foot can engage a cassette for semiconductor wafers or samples. When in another position following the removal of the applied force, or absent an application of a force to the body, the first foot and the second foot are disengaged from the cassette. Recesses and/or markers on the first foot and the second foot indicate when the first foot and the second foot are correctly engaged with the cassette. Where the cassette handle includes both recesses and markers, the markers may be inset within the recesses.

Abstract: A vehicle includes an electric chassis provided with a navigation device and a vehicle body to be connected to the electric chassis. The navigation device is configured to control the electric chassis to travel according to a predetermined path. A vehicle final assembly line includes: a vehicle body positioning device, configured to position the vehicle body on the electric chassis to connect the vehicle body to the electric chassis at a marriage station when the navigation device controls the electric chassis to travel to the marriage station according to the predetermined path, and control the vehicle body and the electric chassis that are connected to each other to travel to a plurality of assembly stations in sequence according to the predetermined path so as to complete assembly of the vehicle at the plurality of assembly stations, and the assembled vehicle leaves the line at an end-of-line station.

Abstract: A method of manufacturing an object by joining a first component and a second component. The first component comprises metal powder with a first alloy composition and a first soluble binder, and the second component comprises metal powder with a second alloy composition and a second soluble binder. They may further comprise ceramic powder. At least one of the surfaces to be joined is dissolved before they are brought in contact, or a mixture of metal powder with a third alloy composition and a dissolved third binder is arranged there between. The chemical differences between the first, second, and third alloy compositions are within predetermined limits. The components are sintered or oxidized together whereby it is possible to obtain an object wherein the transitions between the material phases from the joined components are close to inconspicuous when analysed with scanning electron microscopy.

Abstract: A method of joining a wing skin to a structural element of an aircraft wing. A locating through hole is formed in the structural element, extending along a path between a first side of the structural element and a second side of the structural element. A spark containment cap is attached to the first side of the structural element to covering an opening of the locating through hole. A portion of the wing skin is positioned on the second side of the structural element. A fastening through hole having a larger diameter than the locating through hole is formed through both the wing skin and the structural element and along the path of the locating through hole. A fastener is inserted into the fastening through hole and the structural element secured to the wing skin, an end of the fastener being covered by the spark containment cap.

Abstract: A tool and method for positioning a sealing member in an aircraft wing assembly by using first and second holes in a first component of the aircraft wing assembly and first and second holes in a second component of the aircraft wing assembly as positioning reference points, wherein a positional relationship of the first and second holes in the first component matches a positional relationship of the first and second holes in the second component.

Abstract: A multi-story manufacturing facility includes a movement mechanism configured to move, to a second story above a first story, a main body of an aircraft assembled on the first story, and after one or more components have been attached to the main body on the second story, move, to a third story above the second story, the main body with the one or more components attached.