A hybrid carbon/fiberglass structural component or beam for an aircraft is constructed with layers of strips of glass fibers interspersed with layers of strips of unidirectional carbon fibers where the carbon fibers are oriented only in alignment with or along the longitudinal direction of the length of the beam thereby adding strength and stiffness to the beam while reducing weight and manufacturing costs.

The present application relates to a hybrid component and a method for producing the same. The proposed hybrid component comprises a basic element (2) having at least one portion which is formed as a laminate (3) from a plastics foam and a fiber composite plastic.

Provided herein are waterproof fabrics that include a base fabric having a body-facing surface and an outward-facing surface, and a hydrophobic, waterproof barrier disposed on the outward-facing surface of the base fabric, a seam through the waterproof fabric, and a waterproof tape disposed on an outward-facing surface of the hydrophobic, waterproof barrier and aligned to seal the seam against water ingress. The base fabric may be a wicking fabric or may be treated with a compound that enhances wicking, and the hydrophobic, waterproof barrier may include a plastic polymer, polyurethane, polyethylene, and/or polytetrafluoroethylene. The waterproof fabrics also may include an abrasion-resistant coating and/or a durable water repellant (DWR) agent disposed on an outward-facing surface of the hydrophobic, waterproof barrier, and one or both of the abrasion-resistant coating and/or DWR agent may be discontinuous. Also provided are methods of making a waterproof fabric.

A flooring product has multiple planar single piece substrate components, each with opposing straight longitudinal and lateral edges. A first lateral edge of a second of the substrate components abuts a first lateral edge of a first of the substrate components to form a common seam. The first and second of the substrate components are adjacent relative to a sequential array of multiple substrate components running parallel to the pair of longitudinal edges. The product has a pair of laminate component affixed to each side of each of the substrate components continuously over the sequential array thereof. The laminate components strengthen the product in relation to bearing a load applied to the second surface thereof and each of the common seams. The flooring product may be cut to lengths for accommodating overall lengths of recreational vehicles, trailers or manufactured housing units and thus reduces manufacturing costs associated therewith.

A thermal insulating structure includes: at least two first multilayer vacuum insulators that adjoin each other and that cover a to-be-insulated surface; a retainer that is fixed to the to-be-insulated surface and that protrudes from a boundary between the first multilayer vacuum insulators; a second multilayer vacuum insulator that extends along the boundary and that covers the boundary, the second multilayer vacuum insulator including a through-hole formed therein, in which the retainer is inserted; and a keep plate that is fixed to the retainer and that holds the second multilayer vacuum insulator and the first multilayer vacuum insulators.

Anti-paint cracking systems are provided as part of a painted aerospace component (e.g., a fuselage, an engine nacelle, a wing, an empennage, a fairing and the like) having a pair of adjacent structural panels defining therebetween a joint space having a lengthwise extent and a finished paint topcoat covering an exterior surface of the adjacent structural panels and the joint space therebetween. The anti-paint cracking system will thus be associated with the joint space along the lengthwise extent thereof and positioned below the finished paint topcoat. The anti-paint cracking system will include a joint sealant positioned in the joint space and an adhesive tape or a fibrous tape formed of a fiber composite material applied over the joint space and the joint sealant positioned therein.

A flooring product has multiple planar single piece substrate components, each with opposing straight longitudinal and lateral edges. A first lateral edge of a second of the substrate components abuts a first lateral edge of a first of the substrate components to form a common seam. The first and second of the substrate components are adjacent relative to a sequential array of multiple substrate components running parallel to the pair of longitudinal edges. The product has a pair of laminate component affixed to each side of each of the substrate components continuously over the sequential array thereof. The laminate components strengthen the product in relation to bearing a load applied to the second surface thereof and each of the common seams. The flooring product may be cut to lengths for accommodating overall lengths of recreational vehicles, trailers or manufactured housing units and thus reduces manufacturing costs associated therewith.

An aircraft composite panel assembly includes a first panel having upper and lower faces, the lower face having a recess on a first side of the panel, a second panel having upper and lower faces, the lower face having an outward projection at a first side of the panel, the outward projection received on the recess forming a lower continuous face; and a forward stack of plies of composite material bonded to the upper face of the first panel, the forward stack of plies having an edge overlapping the first side of the first panel, and the number of plies of the forward stack of plies decreasing toward the opposite side of the first side of the first panel.

A composite stiffener is fabricated using preforms of laminated, unidirectional composite tape. The stiffener includes a void that is reinforced by a filler wrapped with a structural adhesive. The surfaces of the preforms surrounding the void include a layer of composite fabric which is bonded to the filler by the adhesive, thereby increasing the toughness of stiffeners around the void and improving pull-off strength of the stiffener.

A transport, driving or pressing belt, comprising at least one belt material having a lower and an upper face limited by two longitudinal edges and two transverse edges running obliquely with respect to the main extension direction of the belt, the belt material being closed and the longitudinal edges being folded down, and a method for manufacturing a transport, driving or pressing belt. To ensure high tensile strength over the complete belt length and avoid an edge tearing of the first belt material at the longitudinal edges, the transverse edges of a first belt material lie against each other in abutting relationship, and a second belt material is arranged centrically on the first belt material at least in the region of the transverse edges. The second belt material here nearly covers a width of 50% of the first belt material and is centrically glued with the first belt material.