Disclosed herein is a composite piston pin including a pipe-shaped outer layer made of reinforced fibers; an inner layer coupled to the outer layer along an inner surface of the outer layer, and made of reinforced fibers having lower elasticity than the outer layer; and a resin material including an epoxy resin composition and cyanate ester, and impregnated into the reinforced fibers of the outer layer and the inner layer.

A system for constructing a composite structure includes a braiding machine, a winding tool and a forming machine. The composite structure is constructed of a wound tubular braiding. The wound tubular braiding is constructed of a biaxial or triaxial tubular braid of unidirectional tape.

A method of manufacturing an armour layer of a flexible pipe for transporting fluid from a subsea location and apparatus are provided. The method comprises winding a first length of composite tape to form a first section of the armour layer and positioning an end region of the first length of composite tape over an end region of a second length of composite tape to form an overlapping tape section. Heat and pressure is applied to the overlapping tape section to form a joined overlapping tape section in which the first length of tape is joined to the second length of tape such that the joined overlapping tape section has a lap shear strength of at least 11 MPa. The joined overlapping tape section and the second length of composite tape are wound to form a second section of the armour layer.

The tube body intermediate includes: a carbon fiber disposed with respect to an outer circumferential surface of a mandrel such that the carbon fiber extends in an axial direction of the mandrel in a manner of being wound by less than one turn; and a first fixing member wound with respect to an outer circumferential surface of the mandrel such that the first fixing member extends in the axial direction of the mandrel in a manner of being wound over the carbon fiber by one or more turns in a circumferential direction.

A method of manufacturing a covered stent is disclosed. The method includes winding a first PTFE tape around a cylinder body of a jig, winding a second PTFE tape around a stent including the jig fitted therein, heating the stent in an oven, fitting the stent into upper and lower elastic members, fitting the elastic members into a mold, pressing the upper elastic member to bond the PTFE tapes to each other and to thus form a first film at a cylindrical body of the stent, taking the elastic members out of the mold, taking the stent out of the elastic members, removing the jig from the stent, forming a silicone coating layer at an expansion portion of the stent, and sewing the spaces in the expansion portion, the second PTFE tape, and the silicone coating layer to form a second film at the expansion portion.

Methods for producing an annular casing for an aircraft turbine engine are provided. The annular casing includes an annular body made from a composite material based on a first resin, and a fire-resistant outer layer which covers an external annular surface of the body and which is made from a composite material based on a self-extinguishing second resin. The method includes preparing a strip of a glass fabric preimpregnated with said second resin, this strip including woven fibres oriented in directions that are perpendicular to one another and inclined by an angle of approximately 45° with respect to the axis of elongation of the strip, and applying the strip to the external surface of the body so as to cover the entirety of this surface in a single pass of the strip around the body.

The invention relates to a can containing a liquid and/or a gaseous medium which has positive pressure or develops such during transport or storage, wherein the cylindrical can shell of the can consists mainly of paper or cardboard material and is closed at the bottom with a bottom element and at the top with a cover element, wherein the can withstands an internal pressure of at least 5 bar, wherein the innermost layer of the can shell consists of a straight-wound barrier layer having a longitudinally extending folded seam, wherein the barrier layer is a prefabricated laminate made of an inner diffusion-tight barrier film or an inner diffusion-tight barrier laminate and an outer kraft paper layer.

An assembly is configured for use in a system for forming filament windings on a vessel having a circumference and a length. The assembly includes an endless belt and first and second rollers. The endless belt is configured to wrap partially around the circumference of the vessel to contact and impart pressure on a filament winding disposed on an outside surface of the vessel. The endless belt moves around the first and second rollers. A space is disposed between the first and second rollers to allow a filament wind eye of the system to move in a reciprocal motion along the length of the vessel. A method of using a machine for forming filament windings on a vessel having a circumference and a length is also described.

A method for manufacturing a fiber reinforced structure includes the following. A mandrel of a first material comprises a hollow interior and an aperture that allows a fluid to enter the interior. A layer of a second material provided on the mandrel includes an uncured resin and fibers. The mandrel and the layer are placed in a mold cavity formed by a mold. A pressurized fluid is introduced into the interior of the mandrel via the aperture to generate a force acting to expand the mandrel outward. The mandrel is heated so that it becomes deformable and expand outward to press the layer against the mold. The layer is heated so that it cures. The mandrel is then heated to a temperature above its melting point of the first material so that it melts, after which it is removed.

Provided is a hollow carbon fiber tube formed by winding a composite material body. The composite material body includes a plurality of carbon fiber prepreg layers and at least one graphene-containing resin layer. Each of the at least one graphene-containing resin layer is disposed between two adjacent carbon fiber prepreg layers. The total thickness of the at least one graphene-containing resin layer is 1/15 to ⅓ of the thickness of the composite material body.