Provided are a metal/CFRP composite structure which has lightweight and high strength by combining hot-pressed metal material(s) and carbon fiber reinforced plastic (CFRP) material(s), and its manufacturing method and apparatus. A metal blank material is heated to a temperature at which quenching is possible to obtain a first intermediate product quenched by hot-pressing. The first intermediate product, and a carbon fiber reinforced plastic (CFRP) prepreg comprising carbon fiber and uncured thermoset plastic are set into CFRP forming dies followed by press-forming the prepreg to obtain a secondary intermediate product having the CFRP in intimate contact with a surface of the first intermediate product. The CFRP and the first intermediate product are firmly adhered together by thermal curing of thermoset plastic located in the boundary of the CFRP and the first intermediate product, by subjecting the thermoset plastic contained in the CFRP prepreg to thermal curing.

Embodiments are described herein in the context of housings for electronic devices. In one embodiment, a housing can make use of an outer member, which can be formed of glass. The outer member can be secured with respect to other portions of the housing for the electronic device. The output member can also be protected at its edges by a protective side member. Still further, one or more antenna can be provided at least partially internal to the protective side member. The electronic devices can be portable and in some cases handheld.

Embodiments are described herein in the context of housings for electronic devices. In one embodiment, a housing can make use of an outer member, which can be formed of glass. The outer member can be secured with respect to other portions of the housing for the electronic device. The output member can also be protected at its edges by a protective side member. Still further, one or more antenna can be provided at least partially internal to the protective side member. The electronic devices can be portable and in some cases handheld.

A composite article lay up comprising a first layer of resin impregnated fiber material and a second layer of resin impregnated fiber material. An open cell material is layered between the first layer and the second layer. The open cell material has no resin during a first stage of a resin cure cycle. The open cell material has passages configured to flow volatiles formed during the first stage of the resin cure cycle. The open cell material is configured to fill with the resin during a second stage of the resin cure cycle. The open cell material is configured to form an integral structure with the first layer and the second layer as part of the composite article at the completion of the resin cure cycle.

A reinforcing fiber structure for a propeller blade made of composite material is woven as a single piece to have an airfoil, a spar portion, and an enlarged portion. The fiber structure includes a zone of non-interlinking extending between the front and rear edges of the airfoil, and extending between an intermediate zone and the bottom edge of said airfoil. The spar portion extends inside the airfoil in the zone of non-interlinking, the spar portion extending outside the airfoil through the bottom edge of said airfoil. The enlarged portion extends from the spar portion outside the airfoil. The airfoil includes skins that are not interlinked with each other in the zone of non-interlinking and that surround the spar portion. The skins define two housings present inside the airfoil on respective sides of the spar portion and opening out through the bottom edge of the airfoil.

A method for manufacturing, layer-upon-layer, an integral composite aeronautical structure, wherein the method comprises: (a) providing an additive manufacturing tool comprising a depositing mold shaping an aerodynamic surface and at least one head configured to be moved over the depositing mold and to deposit fibrous material reinforcement and/or meltable material; (b) depositing fibrous material reinforcement embedded within meltable material onto the depositing mold, at least one layer of a lower aerodynamic face-sheet being built thereby; (c) depositing meltable material onto at least a portion of the outer layer of the lower aerodynamic face-sheet, at least one layer of core structure being built thereby; and (d) depositing fibrous material reinforcement embedded within meltable material onto at least the outer layer of the core structure, at least one layer of an upper aerodynamic face-sheet being built thereby; wherein steps (b), (c) and (d) are performed using Additive Manufacturing technology.

A manufacturing method for a sealing gasket includes the following steps: S1, preparing raw material rubber and a first component, wherein the first component comprises a base body and a gluing layer, the gluing layer is attached to an upper surface of the base body; S2, placing the first component in an inner cavity of a forming mold, wherein the forming mold comprises an upper mold, a first main body surface of the upper mold is arc shaped, the forming mold further comprises a lower mold, and a second main body surface of the lower mold is arc shaped; S3, placing the raw material rubber in the inner cavity of the forming mold; and S4, vulcanizing the raw material rubber arranged in the inner cavity of the forming mold, such that the raw material rubber and the first component are integrated.

A constant velocity joint boot assembly includes a boot-can having an axially extending main cylindrical body, a radially extending transition portion, an axially extending and generally cylindrical mounting portion. The radially extending transition portion intersects the axially extending main cylindrical body and the generally cylindrical mounting portion. A flexible boot member may be attached to an inner surface of at least two of the cylindrical body, the transition portion and the mounting portion at a coupling region. A method of forming the flexible boot member includes first forming the boot in an outwardly extending conical shape, and then rolling and/or inverting a portion of the boot so that the boot arcs inwardly upon itself and forms a diaphragm.

A constant velocity joint boot assembly includes a boot-can having an axially extending main cylindrical body, a radially extending transition portion, an axially extending and generally cylindrical mounting portion. The radially extending transition portion intersects the axially extending main cylindrical body and the generally cylindrical mounting portion. A flexible boot member may be attached to an inner surface of at least two of the cylindrical body, the transition portion and the mounting portion at a coupling region. A method of forming the flexible boot member includes first forming the boot in an outwardly extending conical shape, and then rolling and/or inverting a portion of the boot so that the boot arcs inwardly upon itself and forms a diaphragm.

A composite element for the realization of protection devices of parts of the human body includes a matrix, a reinforcing element, at least partially embedded in the matrix, wherein the reinforcing element has at least one opening shaped so as to define an undercut between the matrix and the reinforcing element, such undercut being suitable for determining a mechanical constraint between the matrix and the reinforcement element.