Systems and methods are provided for fabricating acoustic panels. One embodiment is a method comprising acquiring a core of acoustic cells, and fabricating a facesheet covering the core by: dispensing a base layer of material atop the acoustic cells while leaving openings into each of the acoustic cells, covering the openings by applying a liner of porous material atop the base layer, dispensing a cap layer of material atop liner while leaving gaps in the cap layer over the acoustic cells, and fusing the cap layer to the liner by directly radiating laser energy onto locations where the cap layer has been dispensed.

Systems and methods are provided for acoustic paneling. One embodiment is a method for fabricating an acoustic panel. The method includes receiving a sheet of thermoplastic paper, stamping/conforming the sheet into rows that each comprise a three dimensional shape, and transforming the sheet into a multi-celled core. Transforming the sheet includes identifying fold lines separating the rows, folding the sheet at the fold lines in a pleat fold, thereby uniting upper surfaces of adjacent rows and uniting lower surfaces of adjacent rows; and compressing the rows of the folded sheet together in the presence of heat, causing adjacent rows to fuse together into cells. The method further includes applying a backing sheet to the core, and applying a facesheet to a surface of the core that includes openings which direct a portion of airflow across the facesheet into the cells, resulting in acoustic control.

An inflatable or gas-filled insulation panel comprises an envelope having two outer sheets sealed together along edges of the sheets and at least one of the sheets has an outer reflective surface. The envelope encases a plurality of internal films that include a polymeric film having a plurality of reflective stripes disposed thereon and spaced apart on the films. Seals are formed along the gaps or areas between the reflective stripes on the films by application of heat and pressure, which causes the films to seal to each other and the outer sheets at spaced apart intervals. A channel is formed between the outer edges of the films and the outer sheets, and a valve, disposed at an end of the panel, is in fluid communication with the channel for the injection of a fluid, such as an inert gas or air, to inflate panel.

A system and method for temporarily sealing holes in a perforated material layer of a composite acoustic panel so as to reduce potential migration of a release agent through the holes during a curing process and to reduce ingression of water through the holes during a subsequent testing process. The release agent is applied to a tool, the barrier layer is arranged over the release agent, and a lay-up of elements, beginning with the perforated layer, are arranged over the barrier layer prior to heating the lay-up to form the panel. The barrier layer may be a substantially solid film, such as a plastic or nylon film, having a width of at least approximately twelve inches and a low vapor permeability with regard to the release agent. After the testing process is complete, the barrier layer may be peeled from the panel.

A honeycomb-like core member that can be easily manufactured is disclosed, and a structure using such core member is disclosed. The core member has a plurality of flat plate members (a plurality of first flat plates and a plurality of second flat plates), each of which includes a comb teeth portion that has a plurality of notches, which are open in the long side of a rectangular shape of the flat plate member and extend parallel to the short side of the rectangular shape of the flat plate member. The notches are engaged with each other so that the plate members cross each other, and thus, a plurality of hexagonal-cylinder-shaped first cylinder portions and a plurality of triangular-cylinder-shaped second cylinder portions are formed by the plate members.

The invention is characterized by a semifinished composite structure product with the at least two layers, of which the at least one layer, in which the continuous fibers are contained, is heated such that the matrix of thermoplastic material is heated within at least one first surface region to or above a melting temperature that can be assigned to the thermoplastic material, and the matrix of thermoplastic material is kept to a temperature below the melting temperature within a second surface region directly adjoining the first surface region. The semifinished composite structure product is heated in this way so that the moldable thermoplastic, continuous fiber-reinforced composite structure in which the continuous fibers within the first surface region are movable relative to each other and those within the second surface region are spatially fixed relative to each other.

A Sandwich panel with a core structure, in particular with a honeycomb-shaped core structure, and plane-parallel cover layers applied to both sides of this core structure, to form a floor surface in a fuselage airframe of an aircraft, the core structure having at least one recess into which at least one reinforcing structure is integrated, wherein the at least one reinforcing structure is formed with at least one core, said core having at least one recess into which a stopper is introduced, into which at least one attachment element can be introduced to attach at least one further component to the sandwich panel, and a plurality of prepreg strips which each have a uniform fiber running direction being wound around the core. In addition, the invention relates to a method for the production of a sandwich panel according to the invention.

Embodiments disclosed herein relate to polymer resins having a first thermoset and one or more additional components (e.g., a second thermoset and/or a thermoplastic), composite laminates including the same, methods of making and using the same, and composite laminate structures including the same.

Embodiments described herein relate to a composite structures or sandwiches that may have a relatively high bending stiffness and may have a relatively light weight as well as related methods of use and fabrication of the composite sandwiches. For example, a composite sandwich may include a core structure sandwiched between a two composite skins.

Embodiments described herein relate to a composite structures or sandwiches that may have a relatively high bending stiffness and may have a relatively light weight as well as related methods of use and fabrication of the composite sandwiches. For example, a composite sandwich may include a core structure sandwiched between a two composite skins.