An aircraft panel with a laminate structure is provided that comprises a stack of a plurality of metal sheet layers, at least one fiber reinforced adhesive layer, and at least one cover segment. At least one outer layer of the metal sheet layers comprises at least two separate metal sheets that overlap with each other along their respective commonly adjoining edges, providing an overlapping joint of the two separate metal sheets. The at least one fiber reinforced adhesive layer comprises fiber elements embedded in a matrix structure. One of the at least one fiber reinforced adhesive layers is arranged between two adjacent metal sheet layers. Further, the at least one cover segment is arranged on an outside surface of the laminate structure, the cover segment covering a region of the overlapping joint. Still further, the at least one cover segment comprises at least one layer of reinforcement fibers.

According to one or more embodiments, a three-dimensional spacer fabric comprises a first knit layer, a second knit layer and monofilament spacer yarns extending between and connecting the first and second knit layers. The first knit layer comprises pillar stitches and lay in stitches working together to form the first knit layer and the second knit layer comprising a mesh fabric formed of a mirrored stitch formation. The spacer fabric has a compression force deflection, as measured by ISO3386-1, in the machine direction (MD) of 10 to 15 kPa. The spacer fabric can be secured to a trim material to form a trim cover.

A flexible pipe includes: an inner liner formed as a tube and having an outer surface and an inner surface defining an inner diameter; a reinforcement layer bonded to the inner liner and including at least a first ply of reinforcing tape helically wrapped in a first helical direction about the inner liner and a second ply of reinforcing tape helically wrapped about the first ply of reinforcing tape, the second ply of reinforcing tape helically wrapped in a second helical direction opposite to the first helical direction; and an outer jacket applied over and bonded to the reinforcement layer, the outer jacket including a thermoplastic. A reinforcing tape for use in the pipe or other applications includes: a plurality of reinforcing fibers and a matrix about the plurality of reinforcing fibers to hold the reinforcing fibers in the form of a tape, the matrix including thermoplastic and an additive to increase the impact resistance of the thermoplastic.

Method for connecting a first wood element (110) with a second wood element (120), wherein the first wood element (110) comprises at least one first main fiber direction (114), wherein the second wood element (120) comprises at least one second main fiber direction (124), wherein the first wood element (110) comprises a first side (111) cutting through the first main fiber direction (114), wherein the second wood element (120) comprises a first side (121) cutting through the second main fiber direction (124), the method having the following steps: arranging the first wood element (110) on the first side (111) at a distance to the first side (121) of the second wood element (120); introducing adhesive in the space between the first side (111) of the first wood element (110) and the first side (121) of the second wood element (120); and curing the adhesive.

Methods for fabricating Class-A components (CAC) include providing a molding precursor which includes a first and second skin layer each including a fiber reinforcing material embedded in a polymer matrix, a third layer between the first and second skin layers and including a third polymer matrix and a filler material interspersed therein. The fiber reinforcing materials include a plurality of substantially aligned carbon fibers having a plurality of low strength regions staggered with respect to the second axis. The method includes disposing a molding precursor within a die, compression molding the molding precursor in the die, wherein the die includes a punch configured to contact the second skin layer, opening the die to create a gap between the punch and an outer surface of the second skin layer, and injecting a Class-A finish coat precursor into the gap to create a class-A surface layer and form the CAC.

A fiber-reinforced member includes: a base member having a tubular region with an outer circumferential surface extending along and substantially in parallel with an axial direction; and a fiber-reinforced resin layer constituted of a tow prepreg wound in an overlapping manner to cover the outer circumferential surface of the base member along a predetermined direction crossing the axial direction when viewed in a radial direction of the base member, the tow prepreg serving as a widened tape-like member. The tape-like member constituting the fiber-reinforced resin layer has a portion having a fiber line extending along a direction crossing the predetermined direction. A size of a width of the tape-like member constituting the fiber-reinforced resin layer is not less than 100 times and not more than 400 times as large as a size of a thickness of the tape-like member constituting the fiber-reinforced resin layer in the radial direction.

The prefabricated floor panel can include at least two planar panel members being spaced apart by and sandwiching a core, the core having at least one undulated inner support extending along a longitudinal axis and having summit portions, valley portions, and intermediate portions each extending between corresponding summit and valley portions, each of the summit, valley, and intermediate portions having opposed side edges, a span of the at least one inner support being defined between the opposed side edges, each side edge abutting against a corresponding one of the panel members, the undulated inner support having at least one sheet of wood material, fibres of said sheet of wood material being oriented normal to the panel members and parallel to the span, the at least one undulated inner support being laterally sandwiched between inner ribs with the summits being disposed adjacent a first one of the inner ribs and the valleys being disposed adjacent a second, opposite one of the inner ribs, the inner ribs being planar and having a span being defined between opposed side edges, each side edge of the inner ribs abutting against a corresponding one of the panel members.

A tape-like dry fibrous reinforcement, the ‘Gapped UD reinforcement tape’, providing channels or flow-paths created by inclusion of a layer of separated fiber tows held by at least one adhesive layer. Hereby, quicker wetting of fibers with matrix is obtained, whereby improved composite materials can be economically produced. A method and apparatus for producing the Gapped UD tapes are also disclosed.

A composite wood panel is manufactured from thin wood laminae cut from wood unsuitable for peeler logs or dimensional lumber. A cold set adhesive is applied to the wood laminae and they are formed into a randomly oriented mat that is cold rolled into a thin, pliable cold rolled stock that can be corrugated. A hot set adhesive may also be applied to the laminae to improve strength of the composite wood panel. The hot set adhesive is set in a hot press after the cold rolled stock is produced.

A marine deck member with enhanced surface traction and the process for forming the same. The marine deck member comprises a sandwich-type composite panel made by a compression molding process. In such a process, the panel is made by subjecting a heated stack of layers of material to cold-pressing in a mold. The cellular core has a 2-D array of cells, each of the cells having an axis substantially perpendicular to the outer surfaces, and extending in the space between the layers or skins, with end faces open to the respective layers or skins. The surface traction of this type of composite panel can be enhanced for marine deck applications by controlled debossing, or embossing, of the first skin while it cools in the compression mold. The debossing effect can be effected by applying pressurized gas, e.g., pressurized air, onto the outer surface of the first skin while in the compression mold. The embossing can be effected by applying vacuum pressure on the outer surface of the first skin while in the compression mold.