The present invention provides a laminated plate capable of not only achieving a reduced weight and an increased rigidity but also improving a sound absorbing performance, and a method for manufacturing the same. A laminated plate (1) is supposed to include a core layer (2) including a plate-shaped paper honeycomb structure (4) and a pair of fiber reinforcement layers (3) sandwiching the paper honeycomb structure (4) from both sides in a thickness direction and integrated with the paper honeycomb structure 4. The through-holes (5) of the paper honeycomb structure (4) are filled with a foam resin (6), and the core layer (2) is made up of the paper honeycomb structure 4 and the foam resin (6) filled in the through-holes (5). When the foam resin (6) is filled in the through-holes (5) of the paper honeycomb structure (4), the foam resin plate (6A) is pushed into the through-holes (5) as a filling material by utilizing a compression force of a mold (11).

In a preferred embodiment, a composite panel with a smooth outer surface, ready for painting with or without addition of primer, may be created by constructing a panel layup assembly upon a mold, the panel layup assembly including a composite panel having a core and a resin formulation, and a release film between the mold and the composite panel, where a smooth release surface of the release film is in contact with the composite panel upon construction; initiating curing of the composite panel at a first temperature within a lowermost ten percent of a curing temperature range of the resin formulation; continuing curing of the composite panel at a second temperature above the lowermost ten percent of the curing temperature range; and completing curing of the composite panel at a third temperature below the second temperature.

A method of making an aircraft acoustic structural panel (10) begins with preforming a core honeycomb laminate (12) having preformed foam (3) bonded inside cells (14) thereof by a distinct adhesive (2). The preformed honeycomb laminate (12) is then stacked between opposite top and bottom structural outer laminates (16,18). The stacked honeycomb laminate (12) and outer structural laminates (16,18) are then compressed together under heat and pressure into a unitary structural panel (10) having the core honeycomb laminate (12) integrally bonded between outer skins (20,22). The outer laminates (16,18) may include imperforate acoustic septums (4) bounding the core honeycomb laminate (12) followed by an outer honeycomb (5) and structural fiber layers (6,7,8) defining the outer skins (20,22).

A composite sandwich panel assembly including an open area core, a high gloss surface sheet, and a structural skin. The open are core defines a plurality of pores and has a first face and an opposing second face. The high gloss surface sheet is adhered to the first face of the open area core by a first adhesive layer. The high gloss surface sheet has a high gloss surface. The structural skin is adhered to the second face of the open area core by a second adhesive layer. A process for forming the composite sandwich panel assembly includes positioning the high gloss surface sheet, joining the first face of the open area core to the high gloss surface sheet with a first adhesive layer intermediate therebetween, and joining the structural skin to the second face of the open area core with a second adhesive layer intermediate therebetween.

A composite structure for interior lining includes a honeycomb structure having a first main surface and a second main surface, a first nonwoven layer of fibers bonded to the honeycomb structure at the first main surface or the second main surface. The honeycomb structure and the first nonwoven layer of fibers include thermoplastic polymeric materials. The honeycomb structure is provided from an uncut flat body and includes a plurality of honeycomb cells, and the honeycomb cells are delimited by walls. A film, including a thermoplastic polymeric material, is located in the composite structure between the first nonwoven layer of fibers and the honeycomb structure and/or bonded to the honeycomb structure at the main surface opposite to the main surface at which the first nonwoven layer of fibers is bonded to the honeycomb structure.

The present invention addresses the problem of providing a method for molding, using a honeycomb core, a composite material structure that is high-quality, low cost, and leaves less voids. The present disclosure addresses the problem of providing a method for molding, using a honeycomb core, a composite material structure with which it is possible to reduce dimples in a composite material skin at low cost. According to a method for molding a composite material structure of the present disclosure, an uncured composite material honeycomb sandwich panel in which prepreg is laminated on upper and lower surfaces of a honeycomb core via an adhesive is covered with a vacuum bag and placed in an autoclave. After that, the vacuum bag is evacuated and, while the evacuation is being continued, is heated and pressurized by the autoclave to cure a matrix resin of the prepreg and achieve adhesion to the honeycomb core.

A method of making an aircraft acoustic structural panel (10) begins with preforming a core honeycomb laminate (12) having preformed foam (3) bonded inside cells (14) thereof by a distinct adhesive (2). The preformed honeycomb laminate (12) is then stacked between opposite top and bottom structural outer laminates (16,18). The stacked honeycomb laminate (12) and outer structural laminates (16,18) are then compressed together under heat and pressure into a unitary structural panel (10) having the core honeycomb laminate (12) integrally bonded between outer skins (20,22). The outer laminates (16,18) may include imperforate acoustic septums (4) bounding the core honeycomb laminate (12) followed by an outer honeycomb (5) and structural fiber layers (6,7,8) defining the outer skins (20,22).

A honeycomb sandwich sheet or panel, based on thermoplastic polypropylene, includes a structure having two flat outer films, at the top and bottom, welded to at least two inner or central thermoformed blister films, repeated in a regular and continuous pattern, wherein the at least two inner thermoformed films are welded to each other.

An impact attenuation system comprises an aluminum honeycomb sheet having a top surface and a bottom surface. The aluminum honeycomb sheet defines a plurality of approximately hexagonally shaped cells. The bottom surface defines a single sheet of contiguous cells and the top surface defines two or more islands of contiguous cells separated by one or more slits. At least a portion of one or both of the top surface and bottom surface may be covered by a polymer skin. The polymer skin may comprise carbon fibers and/or fiberglass.

Embodiments disclosed herein relate to composite laminate structures including a polymer layer having sp.sup.2 carbon-containing material and improved heat release properties, and methods of making the same.