The present invention relates to a sandwich panel and a method of manufacturing the same. The sandwich panel according to the present invention has high density and improved physical properties such as flexural strength, flexural modulus, bending strength and lightening weighting ratio and is suitable for use in various consumer products or industrial materials.

The present invention relates to a sandwich panel and a method of manufacturing the same. The sandwich panel according to the present invention has high density and improved physical properties such as flexural strength, flexural modulus, bending strength and lightening weighting ratio and is suitable for use in various consumer products or industrial materials.

The present invention provides a laminate material having a polyester film and a web of polyester fibers cohesively bonded directly thereto, such that portions of the fibers are bonded to the polyester film and portions of the fibers are free from the polyester film. The invention may also include a glass reinforced polymer layer formed on the laminated facer where the polymer of the glass reinforced polymer layer is commingled with the nonwoven of the laminated facer. The laminate may further include a second polymer layer having a thickness joined to the fiber layer and/or a layer of hot melt adhesive applied to the polyester fibers. Also presented is a composite material having a polyester film, a layer of polyester fibers bonded to the second polymer layer; a second polymer layer joined to the polyester film; and a glass reinforced polymer layer formed on the laminated facer, where the polymer of the class reinforced polymer layer is commingled with the nonwoven of the laminated facer.

A method for manufacturing deicing acoustic skin for an aircraft acoustic panel, using a fiber spacing device. The manufacturing method includes at least one step for manufacturing a layer assembly having a deicing layer supplied with electrically conductive fibers embedded in a resin and two insulating layers arranged on either side of the deicing layer, and a baking step. The method provides for fitting, during baking, a spacing device on the layer assembly, the spacing device having pins passing through said layer assembly, perforations being produced at the locations of the pins after the withdrawal of the spacing device, the fitting of the spacing device making it possible to produce perforations with desired sizes and shapes, in a simple and effective manner, and with a reduced manufacturing duration.

Fiber reinforced composites are made by infusing a mass of reinforcing fibers with a resin composition (11). A thin sheet (6) of nano-sized monofilaments (7) is applied on at least one major surface of a fiber mass. The resin composition (11) is subsequently hardened to form the composite. This method produces a composite having a very smooth surface. Printout of the reinforcing fiber is greatly reduced without the need to mask it through the application of thick coatings or additional layers of material.

A method to prepare a composite laminate object containing an extrusion grade 7xxx Al substrate and a fiber-reinforced polypropylene layer adhesively laminated to the substrate; is provided. The process includes shaping and cutting an extruded 7xxx aluminum to a profile, assembling a layered arrangement of the 7xxx Al profile as substrate, an adhesive film and a fiber reinforced polypropylene preform, heating the layered arrangement to a temperature of 160-175 C. to melt the polypropylene and activate the adhesive film, applying pressure to at least a surface of the fiber reinforced polypropylene preform to mold the preform to the shape of the extruded 7xxxAl substrate and obtain a semi-finished laminate object, cooling the semi-finished laminate object to 90 C., optionally, cooling the semi-finished laminate object to room temperature for inventory storage; heat treating the semi-finished laminate object at 90 C. for 2 to 8 hours; and then heat treating the semi-finished laminate object at 130 C. to 150 C. for 8 to 16 hours; and cooling the heat treated object to obtain the composite laminate object.

A heated floor panel assembly for aircraft includes an impact layer made from a 2-D or 3-D woven high temperature thermoplastic fiber matrix impregnated with a resin. The impact layer can further include woven metallic fibers. The assembly also includes a stack of structural layers, a heating layer, and a core layer for absorbing shear stress.

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 composite ballistics protective textile structure comprises at least a textile element and one or more textile or thermoplastic matrix elements. The first textile element comprises unidirectional yarn fibers or flat strips. The second textile element comprises flat strip elements consisting of unidirectional yarns or thermoplastic films. Additional elements comprise thermoplastic matrix arrangements, based on rubber, elastomeric polymers or being laminated with thermoplastic films, for stabilizing the structure and reducing bullet trauma impacts.

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.