A method for manufacturing a rivet connection of a fiber composite component. The method includes positioning a first component which contains a fiber composite material in an overlap joint with a second component, laser-drilling a shared through-hole at least through the fiber composite material of the first component, inserting a rivet into the through-hole and fixing the rivet to the first and to the second component.

Embodiments are directed to systems and methods for two or more cured composite assemblies that are bonded together to form a tubular composite structure, wherein each of the cured composite assemblies do not have a tubular shape. The tubular composite structure may form a spar for an aerodynamic component, for example. The two or more cured composite assemblies may comprise carbon or fiberglass composite materials or a combination of materials. Each of the cured composite assemblies may further comprise axial edges that are configured to be bonded to another of the cured composite assemblies, wherein the axial edges have a sloped shape. An adhesive agent may be applied on the axial edges for bonding two cured composite assemblies. Alternatively, or additionally, one or more fasteners may be used to attach the axial edges of at least two cured composite assemblies.

A laser welded structure is formed by laser welding together a resin molded body formed from a thermoplastic polymer alloy containing a crystalline resin and an amorphous resin and a metal body made of a metal. A glass transition temperature of the amorphous resin is lower than a melting start temperature of the crystalline resin.

The manufacture of structural elements for aircraft requires the use of complex and costly methods, particularly in the case of parts of elongate overall shape and variable thickness or cross section made of composite material. The disclosure herein proposes to overcome this problem by a method that allows the manufacture of a structural part from a preform made of composite material of simple shape obtained by pultrusion and of one or more reinforcing elements made of composite material and secured by cocuring with the preform to a region of this preform which region is to be reinforced.

According to one aspect of the present invention, there is provided a hollow structure body having a hollow structure, in which a first shaped product constituted by a first fiber-reinforced resin material containing first reinforcing fibers and a first matrix resin and a second shaped product constituted by a second fiber-reinforced resin material containing second reinforcing fibers and a second matrix resin are combined, wherein in an arbitrary cross section in a direction perpendicular to an axial direction of the hollow structure, a ratio Sc/St between compressive strength Sc of a structure in the first shaped product and tensile strength St of a structure in the second shaped product satisfies formula (1):
(σc/σt)*(Hc/Ht)<(Sc/St)<(σt/σc)*(Hc/Ht)  formula (1).

A part made of a fiber-reinforced composite material includes a structure made from a set of fibers supported in a thermosetting resin and a peel ply across all or part of the outer surface of the structure. The part has a gradient of polymerization at the interface between the structure and the peel ply. Also, methods for making such a part and methods for bonding such parts.

A method of producing a composite article is disclosed that includes generating composite plies from a low tack composite prepreg material, connecting, by an ultrasonic welding device, two or more of the composite plies by increasing their tackiness to form a composite stack, and forming, by a compression molding device, a composite article from the composite stack.

A composite structure is fabricated using a preform comprising a stack of unidirectional prepreg plies that are stitched together. During curing of the prepreg, the stitches melt and dissolve.

A method for making a gas-tight container (1) in elastomeric material comprises: providing two or more separate elastomeric portions (2, 3), cleaning and/or roughening the gluing surfaces (6) of the gluing edges (5), applying an adhesive (7) onto the previously cleaned, degreased and/or roughened gluing surfaces (6), assembling the portions (2, 3) to form the container (1) and inserting between the gluing surfaces (6) a raw elastomeric tape (8) not yet cured, applying a cold pressure on the overlapped gluing edges (5), heating the overlapped gluing edges (5) to thermally activate the curing of the raw tape (8), cooling the gluing areas.

A method for manufacturing of a part made of composite material including pre-compacting to a predetermined shape of a mixture of a first thermosetting resin with discontinuous long fibers so as to form a first preform, pre-curing the first preform until an intermediate conversion stage corresponding to a solidification of said first resin, contacting the first preform with a second preform including a fiber structure of continuous fibers impregnated with a second thermosetting resin, polymerizing the first and second preforms so as to form a part made of composite material including a body made of composite material including reinforcement made of continuous fibers consolidated by an organic matrix provided with a portion made of composite material including reinforcement made of discontinuous long fibers consolidated by an organic matrix.