The present invention provides a tool 1 for curing a composite component, the tool comprising a lay-up surface 8 for laying-up layers of an uncured composite component, a cover assembly 9 for moving in relation to the lay-up surface to cover a layed-up uncured composite component on the lay-up surface, the cover assembly comprising a sealable cover for sealing around the uncured composite component on the lay-up surface to form a sealed zone, and a vacuum port 25 for providing a vacuum to the sealed zone, wherein the tool further comprises at least one heating element 15, 53 within the sealed zone for heating the uncured composite component. The invention also provides a method of manufacturing a composite component and a composite component. The composite component may form at least part of a piece of aircraft furniture, such as an aircraft seat shell.

A fire resistant panel member and a related method for producing a fire resistant panel member where the panel member includes a first layer, a second layer covering at least a portion of a surface of the first layer, the first and second layers each comprising a pigmented polyester resin and a first organic peroxide, a third layer covering at least a portion of a surface of the second layer, a substantially rigid core member covering at least a portion of a surface of the third layer, and a fourth layer covering at least a portion of a surface of the core member, the third and fourth layers each comprising a polyester resin, a flame retardant, a second organic peroxide, and a fiber material, wherein the panel member is configured to have an ASTM E84 Class I fire and smoke rating.

A tool for preforming a fibrous preform, including an inflatable first membrane intended to accept the fibrous preform, a second membrane intended to attach to the first membrane via a fixing system in such a way as to form a fluidtight internal cavity between the first and second membranes, and an evacuation device for creating a vacuum in the internal cavity between the first membrane and the second membrane.

A method of manufacturing a foam molded product having a reinforcement layer including a short fiber provided on a surface layer. The method includes the following steps. In a fiber layer formation step, the short fiber is adhered to and deposited on a cavity surface of a mold to form a fiber layer. In a covering step, a silicone rubber sheet is arranged on the mold to cover the fiber layer. In a compression step, air is sucked between the silicone rubber sheet and the cavity surface to compress the fiber layer by the silicone rubber sheet and the cavity surface. In a molding preparation step, the silicone rubber sheet is removed from the fiber layer after compression, a foam material is suppled into a cavity of the mold, and the mold is clamped. In a molding step, the foam material in the cavity is foamed and cured.

A method for hardening a preform into a composite part is provided. The method comprises aligning a layup mandrel carrying a preform for insertion into an autoclave having an inner surface that is complementary to a contour of the preform. The layup mandrel is then sealed into the autoclave.

The present invention provides a tool 1 for curing a composite component, the tool comprising a lay-up surface 8 for laying-up layers of an uncured composite component, a cover assembly 9 for moving in relation to the lay-up surface to cover a layed-up uncured composite component on the lay-up surface, the cover assembly comprising a sealable cover for sealing around the uncured composite component on the lay-up surface to form a sealed zone, and a vacuum port 25 for providing a vacuum to the sealed zone, wherein the tool further comprises at least one heating element 15, 53 within the sealed zone for heating the uncured composite component. The invention also provides a method of manufacturing a composite component and a composite component. The composite component may form at least part of a piece of aircraft furniture, such as an aircraft seat shell.

A method for manufacturing an integrated hull by using 3D structure type fiber clothes and 3D vacuum infusion process includes: sequentially stacking at least one first fiber cloth, at least one core material and at least one second fiber cloth on a mold; deploying structural materials on the second fiber cloth; stacking the third fiber clothes to cover the structure materials and a part of the second fiber cloth, whereby the first fiber cloth, the core material, the second fiber cloth and the third fiber clothes are formed to a lamination; determining a pipe arrangement of vacuum pipes and first and second resin pipes; deploying a vacuum bag on the lamination and covering the first and second resin pipes and the vacuum pipe; executing the 3D vacuum infusion process; curing the resin; and executing a mold release process to complete an integrated hull.

A method of removing a vacuum bag from a composite mold. Removable strips are placed around the perimeter of the component parts and across the parts to create natural break points in the consumable materials used during manufacture of a composite product, e.g. wind turbine blade. The vacuum bag, and other consumable layers, are placed over the removable strip such that when the strips are pulled, the strip tears, in a controlled and complete manner, through each layer of consumables. This eliminates the need to use a knife/scissor to remove the finished product, thereby avoiding risk of injury.

A caul for debulking a composite part broadly includes opposing first and second surfaces, a plurality of through-holes, and a coating. The first surface may have a curvature complementary to a shape of the composite part. The through-holes pass through the caul from the first surface to the second surface. The coating may be a chemically inert material to ensure the caul does not affect the composite part. The caul is configured to be positioned against the composite part for debulking. The caul may be made out of silicone rubber or any other suitable material and may be reusable.

Systems and methods are provided for vacuum handling of composite parts. One embodiment is a method for performing vacuum securement of an object. The method includes covering the object with an impermeable membrane, locating a vacuum port at the impermeable membrane, and applying a negative pressure to the vacuum port that offsets air leaks between the impermeable membrane and the object.