Structure intended to stiffen a component made of thermosetting composite material by being fitted to at least one of its surfaces, including: at least one longitudinal body, with first and second longitudinal edge faces on opposite sides, and first and second lateral faces on opposite sides; at least one base including at least one mounting base, each base having a plate and first and second tongues which delimit, with the plate, a housing for at least one body, the first and second tongues extending from a main face of the plate and being pressed respectively against the first and second lateral faces of the body. Each mounting base has a plate which is secured to the first longitudinal edge face of a body and which is intended to be pressed against the surface of the component to be stiffened. Each body and each base are made of thermosetting composite material.

A method of joining a non-metallic pipe to a metallic pipe. The pipe may be wrapped with one or more sheets of reinforcement material (e.g., pre-impregnated fiberglass, carbon fiber, or aramid fiber) and then fitted with an adapter or fitting that is connectable to a metallic pipe. The reinforcement material may be heated using a heating apparatus which allows the material to bond to the pipe to strengthen the joint.

A tooling device for producing a planar structural component for an aircraft has a moulding tool part with a contour surface for receiving a planar semi-finished product, a heating device for heating the semi-finished product, a film produced from an elastically deformable material and a clamping system with a first clamping device arranged on a first longitudinal side of the contour surface , and a second clamping device arranged on a second longitudinal side of the contour surface located opposite the first longitudinal side. The film is couplable to the clamping devices by the edge regions thereof and, when it is coupled to the clamping devices, covers the contour surface of the moulding tool part. The film is elastically deformable relative to the contour surface by the first and/or the second clamping device to press the semi-finished product in a planar manner against the contour surface for deforming purposes.

Provided is a method for manufacturing a fiber reinforced plastic molded body, the method including: performing thermocompression molding, by using a molding die, on a molding precursor which is obtained by arranging a prepreg including a thermosetting resin and a fiber around a thermoplastic solid body.

A method of forming a barrel portion including obtaining a mandrel shaped to define at least an inner surface of a barrel portion of the bat, wrapping a first plurality of layers of fiber composite material about the mandrel, placing a removable material over a first portion of the first plurality of layers, and wrapping a second plurality of layers of fiber composite material over the removable material and the portion of the first plurality of layers not covered by the removable material for form an assembly. The method further includes separating the mandrel from the assembly, inserting an expandable member within the assembly, inserting the assembly into a barrel-forming mold, and molding the assembly in a single molding cycle, curing the first and second layers with the removable material to form the barrel portion of the bat, and removing the removable material and the member from the barrel portion.

A composite material molded product has a hollow portion, a bent portion, or a curved portion in a transverse section thereof. When the composite material molded product has, for example, a bent portion, a surface on an inside of the bent portion is a pressed surface. A mold includes a pressing body that is thermally expandable and has an outer surface shape corresponding to a shape of a pressed surface, and a mold main body including a cavity accommodating the laminate and the pressing body inside, the cavity including an inner surface shape corresponding to a shape other than the pressed surface. The cavity is sealed in a state that the pressing body is disposed in the cavity. The laminate is accommodated in a molding space formed between an inner surface of the cavity and an outer surface of the pressing body.

A curable resin composition contains a curable resin that comprises at least one non-aromatic epoxy compound, at least one non-aromatic oxetane compound, or a mixture thereof, one or more curing agents selected from Lewis acid:Lewis base complexes, and a cure accelerating amount of one or more anhydride compounds. A method accelerating the cure of a curable resin composition, comprising adding a cure accelerating amount of one or more anhydride compounds to a curable resin composition comprising a curable resin that comprises at least one non-aromatic epoxy compound or non-aromatic oxetane compound and a curing agent that comprises one or more Lewis acid-base complexes. The composition and method are useful in making fiber reinforced resin matrix composite articles.

Described herein are methods and systems for forming composite stringer assemblies or, more specifically, for shaping composite charges while forming these stringer assemblies. A system comprises a bladder, having a bladder core, and a bladder skin. The bladder core is formed from foam. The bladder skin is formed from an elastic material and encloses the bladder core. When a composite stringer assembly is formed, the bladder is positioned over a charge base. The charge base later becomes a stringer base, such as a fuselage section or a wing skin. A charge hat is then positioned over the bladder and is conformed to the bladder. A combination of the bladder skin and the bladder core provides support during this forming operation and later while the stringer assembly is cured. In some examples, the bladder core is collapsible for the removal of the bladder from the cavity of the stringer assembly.

A method and a device for producing a reinforcing profile from at least one layer (1, 2, 3) cut out of a preimpregnated fibrous web are described, said layer (1, 2, 3) being applied to a mould core (4) determining the profile shape, being retained on the mould core (4) in the application region (6), and being pressed progressively onto the mould core, starting from this application region (6), transversely to the profile longitudinal direction, as far as the profile longitudinal edges. In order to create advantageous production conditions, it is proposed that the layer (1, 2, 3) be pressed incrementally progressively so as to be shaped onto the mould core (4), in the longitudinal direction thereof, with the aid of moulding punches (8) that are arranged offset with respect to one another both in the circumferential direction and in the longitudinal direction of the mould core (4) and are able to be forced in the direction of the moulding faces of the mould core (4).

A method for forming a composite material that includes a product portion and a surplus portion formed on an end side of the product portion. The method includes placing in a forming jig having a forming surface the composite material before curing; and curing the composite material placed in the forming jig. The forming jig has a surplus forming section provided between the forming surface and the surplus portion. The surplus forming section is shaped in such a manner as to become thicker toward the outside of the composite material. The placing of the composite material includes mounting the surplus portion of the composite material on the surplus forming section to lift the surplus portion with respect to the product portion.