A metal-carbon fiber reinforced plastic composite comprising a metal member of a ferrous material or ferrous alloy, a resin layer provided on at least one surface of the metal member and including a thermoplastic resin, and carbon fiber reinforced plastic provided on a surface of the resin layer and including a carbon fiber material and a matrix resin having thermoplasticity, a glass transition point Tg1 or melting point Tm1 of the resin layer being higher than a glass transition point Tg2 or melting point Tm2 of the carbon fiber reinforced plastic, in which metal-carbon fiber reinforced plastic composite, an AC impedance at a frequency 1 Hz when immersing the metal-carbon fiber reinforced plastic composite in an aqueous solution containing sodium chloride in 5 mass % is 110.sup.7 or more.

Provided is a technology for imparting a design having a higher degree of freedom than in the related art to a composite material product including a woven fabric, which is formed of a thread made of a specific fiber (carbon fiber, glass fiber, aramid fiber), and a resin. As a first step, a specific fiber cloth (100), which is the woven fabric formed of the thread made of a specific fiber, and a backing sheet (200) formed of a thermoplastic resin are stacked. Subsequently, embroidery is performed with an embroidery thread (300) to form a design on a front surface of the specific fiber cloth (100). The embroidery thread (300) is made of the specific fiber, and penetrates through the specific fiber cloth (100) and the backing sheet (200). Then, the specific fiber cloth (100) and the backing sheet (200) are sandwiched between resin sheets (400) each formed of a thermoplastic resin, and the whole is cured by an RFI method.

An additively manufactured (AM) hybrid composite structure is disclosed. The AM hybrid composite structure includes a first portion and a second portion. The second portion includes one or more AM elements which are configured to enable integration of the second portion with the first portion to form an integrated component including both the second portion and the first portion. A method of manufacturing a hybrid composite structure is disclosed. The method includes manufacturing a first portion, and additively manufacturing a second portion. The step of additively manufacturing the second portion includes co-printing one or more AM elements. The method further includes using the one or more AM elements as a part of a tool to integrate the first portion with the second portion, and forming an integrated component including both the first portion and the second portion.

A method for manufacturing a structural assembly comprising at least two assembly components interconnected by means of a thermoplastic plastics material, and useful in the field of aviation or space travel. First, a first assembly component and a second assembly component are provided and arranged so as to form an arrangement. Second, the arrangement is subjected to creep forming at a temperature which is selected in such a way that the thermoplastic plastics material melts at least in part during the creep forming so as to connect the first assembly component and the second assembly component. The invention further relates to structural assemblies, in particular for an aircraft or spacecraft, and to an aircraft or spacecraft comprising a structural assembly of this type.

A composite duct with reinforcement comprises an inner ply, an outer ply, and a plurality of cellular core rings. The inner ply forms a channel with a circular cross-section. The plurality of cellular core rings is positioned at set intervals along a length of the composite duct and between the inner ply and the outer ply.

A method for producing a lower part of a rear spoiler of a motor vehicle includes providing at least one insert part and fibers, arranging the fibers and the at least one insert part in a mold, and incorporating a matrix into the mold. The method further includes molding the lower part of the rear spoiler in the mold, wherein the insert parts are laminated into the structure of the lower part, and milling the insert part after the molding of the lower part.

An enclosure part for an information handling system is disclosed that may include materials formed together into a rectangular shape. The enclosure part may have a void on a core side and a flatness equal to or less than 0.5 mm. The materials may include a sheet of carbon fiber, a piece of non-woven carbon fiber, and a piece of non-woven glass fiber. A method for manufacturing an enclosure part using through-plane temperature control may include inserting into a mold a sheet of carbon fiber and a piece of non-woven carbon fiber, heat pressing the sheet of carbon fiber with the piece of non-woven carbon fiber, and cooling a first portion of the mold including the sheet of carbon fiber and the piece of non-woven carbon fiber more quickly than a second portion of the mold including the sheet of carbon fiber, and removing the enclosure part from the mold.

An enclosure part for an information handling system is disclosed that may include materials formed together into a rectangular shape. The enclosure part may have a void on a core side and a flatness equal to or less than 0.5 mm. The materials may include a sheet of carbon fiber, a piece of non-woven carbon fiber, and a non-woven glass fiber. A method for manufacturing an enclosure part using through-plane temperature control may include inserting into a mold a sheet of carbon fiber and a piece of non-woven carbon fiber, heat pressing the sheet of carbon fiber with the piece of non-woven carbon fiber, and cooling a first portion of the mold including the sheet of carbon fiber and the piece of non-woven carbon fiber more quickly than a second portion of the mold including the sheet of carbon fiber, and removing the enclosure part from the mold.

Methods and apparatus to couple a decorative layer to a panel via a high-bond adhesive layer are disclosed. An example apparatus includes a panel, a high-bond adhesive layer fixed to the panel, a liner fixed to the high-bond adhesive layer that is fixed to the panel, and a first decorative layer removably coupled to the liner that is fixed to the high-bond adhesive layer via a second adhesive layer. The high-bond adhesive layer is to impede at least one of gas or vapor from escaping the panel to deter the at least one of gas or vapor from exerting a pressure on the first decorative layer to deter a portion of the first decorative layer from separating from the panel.

Methods and systems are provided for fabricating a composite structure. In one example, the composite structure may include a honeycomb core sandwiched between face sheets. An edge of the honeycomb core may be abraded and a top face sheet may be perforated. As such, a likelihood of delamination of the composite structure during a curing step may be reduced.