The present disclosure pertains to a window panel for a body structure of a vehicle, especially an airframe of an aircraft or spacecraft, including a first skin which extends over a first side of the panel to form an outer skin of the vehicle body structure; a second skin which extends over a second side of the panel to form an inner skin of the vehicle body structure; and a core, especially a foam core, located between and covered by the first and second skins in a sandwich structure. The window panel includes at least one window aperture formed through the first layer, the core, and the second layer. The core may be confined to or extends over a limited extent, region or part of the panel. Thus, the first skin and/or the second skin may extend over or cover a greater area of the panel than the core.

A laminated sheet includes a base cloth layer having a porous structure obtained by impregnating a woven fabric, which has a tear strength by a trapezoid method of 150 N or more in the longitudinal direction and 100 N or more in the lateral direction, with a resin composition containing a polyurethane resin and an organic flame retardant, and a skin layer layered on the base cloth layer, and has plural air holes penetrating in the thickness direction.

An acoustic liner for a turbine engine, the acoustic liner includes a support layer that includes a set of partitioned cavities with open faces, a perforated sheet that includes a set of perforations with corresponding inlets, the perforated sheet supported by the support layer such that perforations are in overlying relationship with the open faces to form paired perforations and cavities that define acoustic resonator cells, and a coating applied to the perforated sheet.

A ballistic composite armor article includes a multi-layer hard armor sheet that has at least first and second unidirectional yarn monolayers. The second unidirectional yarn monolayer is transversely oriented with respect to the first unidirectional yarn monolayer, and there is at least one polymeric binder layer arranged adjacent to and stabilizing at least one of the first and second unidirectional yarn monolayers. The yarns of the first and second unidirectional yarn monolayers include respective fiber bundles that have a lateral spread factor ranging from negative lateral spread to a positive lateral spread of less than 306%.

Composite articles comprising a porous prepreg or core layer and a powder coated layer thereon are described. In some instances, a thermoplastic composite article comprises a porous core layer comprising a web of reinforcing fibers held together by a thermoplastic material, and a powder coated layer disposed on the porous core layer, in which a particle size of the powder coated layer is selected to provide an interface between the powder coated layer and the porous core layer, wherein at least 50% by weight of the disposed powder coated layer is present above the interface.

A panel (1) has a layered structure including: a first outer layer (2), an intermediate layer (3), and a second outer layer (4). The second outer layer (4) has a buckling stress lower than a buckling stress of the first outer layer (2), and the first outer layer (2) and the second outer layer (4) each have a compression failure stress higher than the buckling stress of the second outer layer (4).

A method of forming a structural connection between a spar cap 14 and an aerodynamic fairing 12. A composite comprising an uncured matrix and a compressible solid is applied between the spar cap and fairing and is then compressed and cured to adhere the fairing to the spar cap. The cured matrix composite has a void volume of at least 20%. The high void volume means that as the fairing is compressed into place and compresses the composite, it has space in which to deform so as not to place undue stress on the fairing and to produce a lightweight connection.

A fibre-metal composite panel is formed from a thermoplastic panel and a metal plate, in which the thermoplastic panel and the metal plate are bonded using a chemical crosslinking agent, and the thermoplastic panel is fibre-reinforced. The chemical crosslinking agent has a thermoplastic polyurethane elastomer. Furthermore, a multilayer fibre-metal composite panel and a structural part for a vehicle are provided. A method is provided for manufacturing the fibre-metal composite panel and the multilayer fibre-metal composite panel.

A porosity gradient fibrous preform includes a first fabric-resin layer having a first plurality of fibers and a first resin and a second fabric-resin layer having a second plurality of fibers and a second resin, the second fabric-resin layer being positioned further outward from a center of the porosity gradient fibrous preform than the first fabric-resin layer. The first resin is different from the second resin so as to generate sequentially increasing porosity in the preform prior to a CVI densification step. The sequentially increasing porosity can be achieved, for example, by selecting resins for each layer with sequentially increasing moisture content, by selecting resins for each layer with sequentially decreasing char yield, and/or adding black carbon powder to interior located fabric-resin layers.

A laminated adhesive tape includes a substrate comprising two or more plies of thin, flexible material, the substrate having a first major surface and a second major surface opposite the first major surface. A polymeric laminating composition comprising a polymer and an alkyl ketene dimer binds the two or more plies and a pressure sensitive adhesive carried on the first major surface. In a further aspect, a method of making a laminated adhesive tape is provided.