Some embodiments provide a core member for a composite panel that includes a hollow cell network structure, such as a honeycomb arrangement for example, and reinforced plastic strips positioned on a portion of the continuous honeycomb structure. The honeycomb structure and the solid plastic strips may be fastened together using heat and/or pressure applications. Additionally, the method for the production of the core member is provided.

A method for providing a honeycomb core assembly that includes obtaining a honeycomb core having at least first and second cells that each define a cell interior having an open bottom and an open top, contacting the honeycomb core with a liquid foaming adhesive, contacting a hardening agent with the liquid foaming adhesive, and allowing the hardening agent and liquid foaming adhesive to react to harden and form a first barrier member that spans the cell interior of the first cell and a second barrier member that spans the cell interior of the second cell, thereby forming the honeycomb core assembly.

A method for assembling two parts, referred to as first and second parts, the first part being produced from composite material with fibrous reinforcement embedded in a thermosetting or thermoplastic matrix, the method comprising the steps of: obtaining the first part comprising, on all or part of an outer surface, a first amorphous thermoplastic film; positioning the first part and the second part such that the first amorphous thermoplastic film is placed opposite the second part; introducing a thermosetting resin between the first amorphous thermoplastic film and the second part; at least partially polymerising the thermosetting resin. When the two parts comprise an amorphous thermoplastic film, the parts are positioned such that the respective amorphous thermoplastic films are placed opposite each other, and the thermosetting resin is introduced between the amorphous thermoplastic films.

In a method for manufacturing a honeycomb core by a domed bonding layer, a bonding sheet is, upon bonding of each cell, heated with hot air to form a uniform bonding layer on an end surface of each honeycomb cell, thereby providing a lightweight honeycomb core having stable strength. In the method for manufacturing the honeycomb core, a technique including the doming step of pumping, when bonding molding is performed for a core in which multiple ribs are connected to form an assembly of cells by means of a flat thermally-weldable bonding sheet laid on an upper surface of the core, upward hot air upwardly into the cells to form a dome-shaped bonding layer at the bonding sheet on an upper surface of each cell, the rupturing step of pumping downward hot air from above to the vicinity of the top of the dome-shaped bonding layer to rupture the bonding layer, and the thermal welding step of forming a uniform bonding layer on upper edge portions of the cells by means of meltability and surface tension.

Provided is a technique for forming a honeycomb sandwich composite material which is easy and can be automated. The honeycomb sandwich composite material 30 comprises a honeycomb core 20, an FRP lower portion, and an FRP upper portion. A first prepreg sheet laminate 21 serves as the FRP upper portion. A second prepreg sheet laminate 22 serves as the FRP lower portion. A jig 10 having a concave 11 corresponding to the upside-down shape of the honeycomb 20 is used in the shaping step and the curing step. The laminate 21 is shaped so as to correspond to the concave 11 by a hot drape device (S15), the honeycomb core is disposed upside-down (S16), and the laminate 22 is placed thereon (S17). Without removing the mold, curing is effected by an autoclave device, the mold is removed after curing, and the composite material is turned upside-down.

A method and apparatus for fabricating a composite structure. The method comprises defining a shape for the composite structure with a first face sheet. The method places core sections on the shape defined by the first face sheet. The method places an adhesive in a group of joint cavities. The method places a second face sheet on the core sections placed on the first face sheet, wherein the first face sheet, the core sections, and the second face sheet, define a structural assembly in which the group of joint cavities are present. The method cures the structural assembly with the adhesive in the group of joint cavities to fabricate the composite structure in which the adhesive fills the group of joint cavities when the adhesive is cured.

A test coupon having node bonds is disclosed. In some aspects, the method includes a first foil and a second foil, stripes of adhesive serially disposed across a width of the first foil or the second foil and coupling the first foil and second foil to one another to form node bonds, and a first adherend coupled to the first foil and a second adherend coupled to the second foil such that the first foil and the second foil are provided between the first adherend and the second adherend, the first adherend and the second adherend being connectable to load blocks of a test apparatus capable of loading the test coupon to determine characteristics of each of the node bonds formed from the stripes of adhesive. A method for testing node bonds and a related apparatus are also disclosed.

A process for manufacturing an apron board of a high-speed rail equipment cabin using a composite material is disclosed. The material includes aramid fiber honeycomb, PET foam, 3K twill carbon fiber flame retardant prepreg, unidirectional carbon fiber flame retardant prepreg, glass fiber flame retardant prepreg, aramid flame retardant prepreg, and 300 g/m.sup.2 single component medium temperature curing blue epoxy adhesive. The process includes manufacturing an apron main plate (3); manufacturing apron-board trim strips (1, 2), wherein there are two apron-board trim strips (1) and two apron-board trim strips (2); and obtaining the apron board through the apron main plate (3) and the apron-board trim strips (1, 2), wherein the two apron-board trim strips (1) are respectively stuck at two opposite sides of the apron main plate (3), the two apron-board trim strips (2) are respectively stuck at another two opposite sides of the apron main plate (3).

A blocker door assembly for use in a gas turbine engine includes a facesheet including a plurality of openings to facilitate noise attenuation and a body portion coupled to the facesheet. The body portion includes a backsheet integrally formed with a honeycomb core, wherein the body portion is molded from a thermoplastic material.

A method and apparatus for fabricating a composite structure. The method comprises defining a shape for the composite structure with a first face sheet. The method places core sections on the shape defined by the first face sheet. The method places an adhesive in a group of joint cavities. The method places a second face sheet on the core sections placed on the first face sheet, wherein the first face sheet, the core sections, and the second face sheet, define a structural assembly in which the group of joint cavities are present. The method cures the structural assembly with the adhesive in the group of joint cavities to fabricate the composite structure in which the adhesive fills the group of joint cavities when the adhesive is cured.