Traditional climbing is being sought out by more indoor climbers, however the issue that has arisen is that the only way to learn the method is through trial and error in the outdoors on real rock. An indoor-traditional climbing device (I-TCD) makes it possible to learn how to climb Traditionally in a safe environment with hands on instruction. Provided herein is a cover/shield for an I-TCD that allows not only for the placement of multiple kinds of gear within the I-TCD body, but it allows the climber to fall on that gear placement safely to determine the quality of their gear placement, without the risk of falling upon the I-TCD body. Therefore, the cover/shield provides an angled feature to reduce direct impact injuries while increasing the opportunity for climbers who wish to learn how to climb traditionally.

Composite laminates fabricated from one or more respective laminae of composite material (e.g., fiber-reinforced polymers) may be pre-formed and fully cured, yet configured to be selectively conformable to a desired radius of curvature. To repair a damaged composite structure, a plurality of such composite laminates may be bonded together to form a repair part that may be bolted to or otherwise secured to the damaged composite structure, thereby repairing the structure using repair parts that may match the parent material of the damaged composite structure. Methods of forming said repair parts from a plurality of such composite laminates may provide advantages in costs and lead time, over conventional techniques. Kits may include a plurality of such pre-formed and cured composite laminates that may be stacked and combined together in a plurality of different arrangements to create a customizable repair part for a given damaged composite structure.

Advanced single vacuum bag (ASVB) fabrication methods and assemblies are provided to manufacture and repair polymer composites whereby a rigid check plate is mounted over an uncured laminate by a thermally collapsible check plate stand. The check plate stand thereby maintains a gap between the check plate and the uncured laminate during first stage processing conditions, yet is capable of thermally collapsing during subsequent second stage processing conditions to thereby allow the check plate to fall into compressive contact with the uncured laminate After the check plate collapses onto the uncured laminate, the compressive force of the check plate will be transferred to the laminate to consolidate the laminate as desired and thereby form an at least partially cured polymer composite structure of high quality.

In the expansion held prepeg composite (100) disclosed herein, using a flexible and expandable tubular core (101), one or more set of fibers are linearly placed over the circumference of the tubular core (101); and one or more set of fibers with predetermined tensions are wound over the linear fibers to create an expansion held prepeg composite (100). At least one of the set of fibers is precoated with resin. The tension of wrapping of each subsequent set of fibers is higher than its precedent wound layer. A bladder tube is inserted into the tubular core (101) of the expansion held prepeg composite 100. The expansion held prepeg composite (100) is a held in the desired three dimensional shape. Compressed air is introduced into the bladder tube and cured. At least one of the sets of fiber must be impregnated with resin.

A method for manufacturing a part layer-upon-layer using Additive Manufacturing technology, the method including: printing the part together with an elastomeric enclosure shaped thereto leaving a gap free of material therebetween, the elastomeric enclosure including at least one opening; heating the ensemble of the printed part and elastomeric enclosure or keeping an operating printing temperature; applying vacuum by the at least one opening of the elastomeric enclosure so that the elastomeric enclosure deflates thus exerting pressure to the printed part; and maintaining the printed part under vacuum and heat during a predefined time.

Described are methods and systems for a composite structure that allows for out of autoclave curing. Due to the layout of the composite structure, voids within the composite structure, formed out of autoclave, is reduced. The composite structure includes a composite laminate and one or more infusion films. The composite laminate includes a plurality of fiber tows that each include a plurality of fiber strands and a resin. The resin has a first viscosity within a first temperature range. The infusion film is disposed on a surface of the composite laminate and has a second viscosity lower than the first viscosity within the first temperature range. Methods of curing the composite structure are also described.

A multi-material iron type golf club head is disclosed. More specifically, the golf club head may have a first metallic portion, a second metallic portion, and a lightweight portion. The first metallic portion and the second metallic portion collectively define all external surfaces of the golf club head. The lightweight portion may be located within an interior cavity of the golf club head and may contact and support the striking face, the topline portion, the rear wall portion, and the sole portion of the golf club head.

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.

Composite laminates fabricated from one or more respective laminae of composite material (e.g., fiber-reinforced polymers) may be pre-formed and fully cured, yet configured to be selectively conformable to a desired radius of curvature. To repair a damaged composite structure, a plurality of such composite laminates may be bonded together to form a repair part that may be bolted to or otherwise secured to the damaged composite structure, thereby repairing the structure using repair parts that may match the parent material of the damaged composite structure. Methods of forming said repair parts from a plurality of such composite laminates may provide advantages in costs and lead time, over conventional techniques. Kits may include a plurality of such pre-formed and cured composite laminates that may be stacked and combined together in a plurality of different arrangements to create a customizable repair part for a given damaged composite structure.

A controlled shear vacuum forming method that includes forming a three-dimensional (3D) structure from a preform material on a molding tool using restraints during vacuuming to prevent wrinkling. The restraints are withdrawn during vacuuming to allowing the preform material to come into contact with the sidewalls of the molding tool in a gradual manner. Such forming method is particularly suitable for forming wing spars with bent sections and/or curved contours.