An acoustic structure presenting a front surface and a back surface is provided. The acoustic structure includes a support layer comprising the back surface, a honeycomb core comprising a thickness defined between a back and a front, and a plurality of walls that define a plurality of honeycomb cells, wherein the plurality of honeycomb cells extend through the thickness of the honeycomb core opening out toward at least the front, and wherein the back of the honeycomb core is affixed to the support layer, a mesh layer affixed to the front of the honeycomb core, and a knit fabric layer affixed to the mesh layer and conforming to the front surface of the acoustic structure.

Processes for forming fiber reinforced composite aircraft components, i.e., aircraft components formed of a cured fiber-reinforced resin, are provided. According to specific embodiments, a finished surface of the composite aircraft component can be achieved by providing in-mold coating of the cured fiber-reinforced resin by a dried and cured film layer of a water-based primer paint material to thereby achieve a composite aircraft component having an exterior surface that does not necessarily require further finishing.

The invention relates to a pre-impregnated fibre-reinforced composite material in laminar form, obtained impregnating a fibrous mass with a polymeric binder composition and intended to be subjected to successive forming and complete curing operations to produce a fibre-reinforced composite material. The polymeric binder composition comprises one or more resins chosen in the group consisting of siloxane resins and silsesquioxane resins, and can optionally comprise one or more organic resins. The polymeric binder composition appears as a liquid with viscosity between 55000 and 10000 mPas at temperatures between 50° C. and 70° C. The polymeric binder composition forms a polymeric binder matrix, not cross-linked or only partially cross-linked, that fills the interstices of the fibrous mass. The invention also relates to a method for making said pre-impregnated fibre-reinforced composite material in laminar form. The invention also relates to a manufactured article obtained by hot forming and complete curing of the aforesaid pre-impregnated fibre-reinforced composite material, as well as a method for making said manufactured article.

The invention relates to a method for producing an absorbing sound insulation motor vehicle trim element having a four-layered structure made from a first foam layer, a second foam layer, a non-woven foam layer and a non-woven fabric layer. The invention further relates to an absorbing sound insulation motor vehicle trim element.

A synthetic resin skin material composite, including: a urethane resin skin material including a urethane resin skin layer provided at one surface of a substrate; and a cushion layer that is placed at a surface on an opposite side of the substrate from the surface of the urethane resin skin material at which the urethane resin skin layer is provided; in which the urethane resin skin material has recesses at a side of the urethane resin skin layer, and each of the recesses has a depth in a thickness direction of the synthetic resin skin material composite, such that the recesses extend from the urethane resin skin layer into the cushion layer beyond an interface between the urethane resin skin material and the cushion layer that is present in a region without a recess, as well as a method of producing a synthetic resin skin material composite.

A composite structure of a cargo body and a method of making the same are disclosed. The composite structure includes at least one electrical grid embedded within fiber-reinforced polymer (FRP) layers. The embedded electrical grid includes a plurality of conductive fibers and a plurality of insulating fibers integrated into a polymer matrix of the FRP layers. The embedded electrical grid may be used for power distribution, structural strengthening and stiffness, and/or puncture detection.

Forming systems and assemblies as disclosed herein comprise a composite material comprising a structural component and a resin component combined with the reinforcing component. A forming element is disposed within the composite material and has a coefficient of thermal expansion that is greater than that of the composite material. The forming element is positioned to provide a desired integral structural reinforcement and/or surface feature to the composite. The composite material may comprise one or more passages extending from a surface thereof to the forming element. The composite material may be cured by heat to take a set configuration and then allowed to cool. The cooling of the composite material and the forming element enables the forming element to contract relative to the composite material and become delaminated therefrom to facilitate easy removal, and thereby provide an improved method and assembly for making structural reinforcing features in composite structures.

This invention relates to a wind turbine blade component, a method of manufacturing such a wind turbine blade component and a wind turbine blade comprising the wind turbine blade component. The wind turbine blade component comprising a stack of layers arranged in a first group and in a second group, wherein the layers of each group has the same width. The layers of each group is continuously offset in an edgewise direction to form a tapered edge profile. The first group of layers may be arranged relative to the second group, or in an alternating order. The layers of the first group may further have a first length which is greater than a second length of the layers of the second group.

A heated composite structure and a method for forming a heated composite structure. The structure includes carbon fibers embedded within a thermoplastic matrix. The carbon fibers are connected with first and second electrodes that are configured to be connected with an electric source such that applying current to the electrodes causes current to flow through the embedded carbon fibers to provide resistive heating sufficient to heat the composite structure to impede formation of ice on the composite structure.

In an aspect of the invention there is provided a blast protection panel, comprising a package of fibre-reinforced resin sheets, each sheet having a dominant unidirectional fibre orientation, said package of fibre-reinforced resin sheets formed in packed stacks, each stack comprising at least four fibre-reinforced resin sheets with dominant unidirectional fibres oriented, within said each stack, alternatingly at about right angles relative to each other; and said each stack packed against adjacent stacks, said adjacent stacks comprising sheets with dominant unidirectional fibres oriented at acute angles relative said each stack thereby forming a delamination interface.