Abstract: Provided is an improved method, system, and computer program product to implement simulation for photonic devices. A composite, multi-domain simulation model is disclosed, with connected domain-specific representations that allow the use of the most relevant simulator technology for a given domain. The model has external connection points either expressed as actual ports or virtual ones, embodied by simulator API calls in the model.

Abstract: During implementing a composite metal part by compaction of an insert having reinforcing fibers in a metal body or container, gas used for compaction may enter the cavity formed in the container for receiving the insert between a lid covering the insert and the container, which can prevent or degrade compaction and diffusion welding of fiber sheaths of the insert therebetween and/or with walls of the cavity. To solve this problem, the present method includes initiating isostatic compaction by a phase including raising and maintaining temperature, followed by a phase including hot-feeding pressurized gas, and machining an assembly to obtain the part. The temperature raising phase includes a diffusion pre-welding of material rigidly connecting the pressure-adjusted walls of the lid and the container. The method can be used for designing parts having a tensile and compression resistance, such as parts for aircraft landing gear.

Abstract: The present invention relates to a method of fabricating a metal link rod (6) that is longitudinally reinforced in its thickness by fiber reinforcement (2), the method comprising the following steps: making a metal blank including at least one longitudinal housing (11, 12) leading into an edge face of the blank; inserting fiber reinforcement (2) in the housing; connecting the fiber reinforcement to the blank by metal diffusion around the fibers of the fiber reinforcement (2); and finishing the blank in order to obtain a link rod (6). The invention also provides a link rod having a metal matrix in which reinforcing fibers are embedded that extend on either side of a longitudinal axis (X) of the link rod, the fibers leading into an edge face of the link rod.

Abstract: During implementing a composite metal part by compaction of an insert having reinforcing fibers in a metal body or container, gas used for compaction may enter the cavity formed in the container for receiving the insert between a lid covering the insert and the container, which can prevent or degrade compaction and diffusion welding of fiber sheaths of the insert therebetween and/or with walls of the cavity. To solve this problem, the present method includes initiating isostatic compaction by a phase including raising and maintaining temperature, followed by a phase including hot-feeding pressurized gas, and machining an assembly to obtain the part. The temperature raising phase includes a diffusion pre-welding of material rigidly connecting the pressure-adjusted walls of the lid and the container. The method can be used for designing parts having a tensile and compression resistance, such as parts for aircraft landing gear.

Abstract: The invention relates to a mechanical part made from a metal preform presenting at least one housing (5) that extends longitudinally relative to a preferred direction for the application of forces to the mechanical part in service, and into at least one piece of fiber reinforcement is inserted and then bonded to the blank by hot isostatic compression, wherein the piece of fiber reinforcement (10) presents a chamfered end (12).

Abstract: The present invention relates to a method of fabricating a metal link rod (6) that is longitudinally reinforced in its thickness by fiber reinforcement (2), the method comprising the following steps: making a metal blank including at least one longitudinal housing (11, 12) leading into an edge face of the blank; inserting fiber reinforcement (2) in the housing; connecting the fiber reinforcement to the blank by metal diffusion around the fibers of the fiber reinforcement (2); and finishing the blank in order to obtain a link rod (6). The invention also provides a link rod having a metal matrix in which reinforcing fibers are embedded that extend on either side of a longitudinal axis (X) of the link rod, the fibers leading into an edge face of the link rod.

Abstract: A process for manufacturing a component with an insert made of a composite is disclosed. The composite includes a metal matrix, within which ceramic fibers extend. The insert is made of a composite which is obtained from a plurality of coated filaments, each filament includes a ceramic fiber coated with a metal sheath. The process includes winding a bundle or bonded sheet of coated filaments around a body of revolution perpendicular to the axis of rotation of said body. The insert is then subjected to a hot isostatic pressing step in a container. The process is applied to the manufacture of aeronautical turbomachine components.

Abstract: A process for manufacturing reinforcing parts (14) for leading edges (10) and/or trailing edges (12) of fan blades (1) is described. In particular, this invention relates to the use of the SPF/DB (<<Super Plastic Forming/Diffusion Bonding >>) process for this type of non-hollow part.

Abstract: A process for manufacturing a bonded sheet with a plurality of coated filaments, which include a ceramic fiber coated with a metal sheath, includes placing the filaments beside one another in one and the same plane, and welding the filaments together by laser spot welding.

Abstract: A process for manufacturing a tubular component with an insert made of a metal matrix composite, within which ceramic fibers extend, includes a draping step, in which a bonded sheet of coated filaments is draped around a metal mandrel. Each filament includes a ceramic fiber coated with a metal sheath, and the filaments are bonded by spot welds.

Abstract: A method of fabricating a hollow mechanical part includes a step of depositing an anti-diffusion substance in a predefined pattern on at least one face of primary parts to be assembled together. The depositing step is performed by applying a layer of anti-diffusion substance including a powder over a surface of the face of the primary parts; and by localized sintering of the anti-diffusion substance in the predefined pattern by the heating that results from localized application of a laser beam along a track.

Abstract: Process for manufacturing a component with an insert made of a composite comprising a metal matrix, within which ceramic fibers extend, the insert made of a composite being obtained from a plurality of coated filaments, each comprising a ceramic fiber coated with a metal sheath, characterized in that it comprises the manufacture of an insert with a step of winding a bundle or bonded sheet of coated filaments around a body of revolution perpendicular to the axis of rotation of said body. The insert is then subjected to a hot isostatic pressing step in a container. The process is applied to the manufacture of aeronautical turbomachine components.

Abstract: Process for manufacturing a tubular component comprising an insert made of a metal matrix composite, within which ceramic fibers extend, characterized in that it includes a draping step, in which a bonded sheet of coated filaments is draped around a metal mandrel, each filament comprising a ceramic fiber coated with a metal sheath, and the filaments being bonded by spot welds.

Abstract: Process for manufacturing a coiled insert of coated filaments, each filament comprising a ceramic fiber coated with a metal sheath, characterized in that it includes a step of winding a sheet of coated filaments onto a piece, in which step, at the start of winding, a metal shim for catching the internal part of the insert is coiled and, at the end of winding, a metal shim for catching the external part of the insert is coiled. The process is applied to the manufacture of aeronautical turbomachine components.

Abstract: The invention relates to a process for manufacturing a bonded sheet comprising a plurality of coated filaments, which comprise a ceramic fiber coated with a metal sheath, characterized in that the filaments are placed beside one another in one and the same plane, and the filaments are welded together by laser spot welding. The invention also relates to the device for implementing the process and to the sheet obtained. The process applies to the manufacture of components in the field of aeronautical turbomachines.

Abstract: A process for manufacturing reinforcing parts (14) for leading edges (10) and/or trailing edges (12) of fan blades (1) is described. In particular, this invention relates to the use of the SPF/DB (<<Super Plastic Forming/Diffusion Bonding >>) process for this type of non-hollow part.

Abstract: A method for producing parts including at least one internal cavity. In the method at least two metal sheets are diffusion bonded; then the bonded metal sheets are bent; and then each of internal cavities is inflated by superplastic forming. The method is carried out by a mold allowing at least one first part to be diffusion bonded and then bent while inflating at least one second part by superplastic forming during a single operation, whereby the mold is heated. The method can be applied, e.g., to the field of aeronautics.

Abstract: The method of fabricating a hollow mechanical part of the invention includes a step b) of depositing an anti-diffusion substance in a predefined pattern on at least one face of primary parts to be assembled together.

Abstract: While one preform (A) is being shaped between two dies (4, 11), another preform (B) is being prepared by heating in a compartment (14) on a lower die (5) similar to the preceding one (4). When the preform (A) has been shaped, a mobile section (3) of the furnace is lifted to release the upper die (11) and make it possible to place the new preform (B) and its lower die (5) beneath it. Thus, when one preform has been shaped, the following one is already prepared by heating.

Abstract: While one preform (A) is being shaped between two dies (4, 11), another preform (B) is being prepared by heating in a compartment (14) on a lower die (5) similar to the preceding one (4). When the preform (A) has been shaped, a mobile section (3) of the furnace is lifted to release the upper die (11) and make it possible to place the new preform (B) and its lower die (5) beneath it. Thus, when one preform has been shaped, the following one is already prepared by heating.