A method for manufacturing an engineered stone, the method including: providing a mixture comprising at least a stone or stone like material and a binder; compacting the mixture; curing the binder; and further comprising printing a printed pattern on at least a top surface of the engineered stone.

Disclosed is a panel for an aircraft structure, including a laminated skin of layers of metal of which in each case two are joined together by a fibre-reinforced adhesive layer, as well as a laminated doubler of layers of metal and at least one fibre-reinforced adhesive layer in each case between two layers of metal, wherein the doubler has a smaller size of perimeter than the skin and is bonded to an outermost layer of metal of the laminated skin by a fibre-reinforced supplementary adhesive layer, with the feature that at least one part of the perimeter of the fibre-reinforced supplementary adhesive layer is staggered inwards relative to the corresponding perimeter of the doubler and that that part of the inwards-staggered perimeter of the fibre-reinforced supplementary adhesive layer is delimited by a glued edge. Also disclosed is a method for manufacturing such a panel.

A manifold for resin application, infusion, and/or injection is provided. The manifold comprises at least one inlet and a plurality of outlets. At least one outlet of the manifold comprises a valve that is operable to selectively dispense or terminate a flow of a resin from the outlet, and wherein the resin is supplied through the at least one inlet.

Disclosed is a method, a mould system and a mould part for a mould system, for manufacture of a component for a wind turbine blade. The mould part may have a moulding surface with a primary side section, a secondary side section, and a central portion between the primary side section and the secondary side section. The mould part has a primary connection interface configured to abut a secondary connection interface of a second mould part. The primary connection interface comprises a primary connection surface substantially perpendicular to the moulding surface. The primary connection interface comprising an outlet configured to be connected to a vacuum source.

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.

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.

This invention describes novel design and construction method for inflatable, pressure intensifier equipment that can be used for processing composites structures. The equipment can be used as a manufacturing and processing platform wherever low pressure and high temperature inputs are required in an enclosed volume.

A method of manufacturing a thermoplastic panel may comprise: laying up a panel preform within a consolidation assembly, the panel preform comprising a plurality of plies of material comprising thermoplastic resin and fiber; generating, via a hot bond unit, a vacuum environment within the consolidation assembly; and heating, via the hot bond unit and through a heated blanket within the consolidation assembly, the panel preform.

A method of manufacturing a thermoplastic panel may comprise: laying up a panel preform within a consolidation assembly, the panel preform comprising a plurality of plies of material comprising thermoplastic resin and fiber; generating, via a hot bond unit, a vacuum environment within the consolidation assembly; and heating, via the hot bond unit and through a heated blanket within the consolidation assembly, the panel preform.

A method for consolidating a thermoplastic component includes positioning a thermoplastic vacuum bagging film (e.g., PAEK or PEEK) over a thermoplastic preform (e.g., PPS or LM PAEK) to be consolidated, vacuum consolidating the thermoplastic component with the thermoplastic vacuum bagging film to form the thermoplastic component, and removing the thermoplastic vacuum bagging film from the consolidated thermoplastic component.