A method of manufacturing a composite structure includes providing a mandrel comprising a base part and at least one conical part. The base part comprises an elongate shaft. The base part of the mandrel comprises a cylindrical surface around a longitudinal axis of the base part. The at least one conical part extends from the cylindrical surface of the base part. The mandrel and a braiding machine are moved relative to one another such that fibre tows are braided over at least the base part of the mandrel. The mandrel and the braiding machine are arranged such that during the braiding process, none of the fibre tows intersect with a vertex of the at least one conical part of the mandrel.

A method of manufacturing a composite core can include: wrapping a mandrel in a mandrel wrapping process by securing a mandrel with a winding jig; orienting the composite material at a wrap angle to the mandrel; and depositing the composite material around a circumference of the mandrel. The method can further include assembling the wrapped mandrels in a tool and applying a pressure to the composite material during a curing cycle.

It is sometimes advantageous to coat or seal the mandrel before laying on, coating, or wrapping the mandrel with composite plastic material. This invention provides improved coating with improved function that is easily removable from the cured product. The effective coating materials are applied directly to the mandrel as a coat or as a film or tape. Thermally expandable coat or film also reduces manufacturing costs for composite plastic products.

A tank production system and method that can suppress peeling of normally wound fibers when fibers not wound at predetermined position are peeled off. The system includes a rotation unit that rotates a liner, a storage unit that has recorded thereon the number of revolutions of the liner, and a detection unit that detects abnormality in the position of the fibers wound on the outer periphery of the liner. The rotation unit, when abnormality in the position of the fibers is detected by the detection unit, refers to the number of revolutions of the liner recorded on the storage unit and rotates the liner in an opposite direction to the direction in which the fibers are wound, back to the number of revolutions of the liner at a point when the winding of fibers to form a fiber layer, which includes the fibers detected at the abnormal position, has started.

A core system for the production of a fiber composite component includes at least two core elements which are coupled to one another and are displaceable relative to one another. At least one core element has a surface which is oblique to a displacement direction. A method for producing the fiber composite component uses the core system.

A cascade for a jet engine thrust reverser is fabricated by co-consolidating pre-consolidated thermoplastic strongbacks and vanes. The strongbacks are reinforced with continuous fibers, and the vanes are reinforced with discontinuous fibers.

A composite pipe is disclosed. The composite pipe includes a thermoplastic inner layer and a tape layer. The tape layer is exterior to and bonded with the thermoplastic inner layer. The composite pipe also includes a protective layer formed exterior to the tape layer.

Methods and articles of manufacture are disclosed for pipes and Architectural shells and/or Panels (AP) of desired shapes, sizes, and curvatures that can be manufactured onsite or offsite. The disclosed pipes, Architectural shells and Panels, which use resin-impregnated fabrics in combination with spacer sheets, are easy to manufacture, inexpensive, fast to produce, and can easily be repaired, reinforced and refurbished.

A method for manufacturing a box-shaped structure for aircrafts, the structure extending along a longitudinal direction between a first longitudinal end and a second longitudinal end, and comprising: a first longitudinal wall; a second longitudinal wall facing the first wall and spaced from the first wall by a non-zero amount; a plurality of spars extending longitudinally and between said first wall and second wall; and at least one reinforcing rib arranged transversal to the spars at a transversal sector interposed between the first and the second longitudinal end; each spar has a spar cavity defining a lack of material extending longitudinally from an axial coordinate, which corresponds to the transversal sector, up to the second longitudinal end, so that the reinforcing rib can be easily inserted even after the integral coupling between the first wall, the second wall and the spars without compromising the structural properties of the box-shaped structure.

A method of producing, for example, handles for using in rolling stock or other transport situations, employs a flexible core mould that is coated with an impregnated glass fiber. The coated core mould is placed into a tool for curing, whereupon the rubber core is pulled out of the center of the resulting handle member after curing. The method helps create 3D shapes of any form and cross section in a cost effective manner and using a standardized methodology and process. Further, the method enables creation of a hollow and lightweight part. The method allows use of standard glass fiber instead of more specialized braided fiber of the prior art.