The invention relates to a fiber reinforced polymer composite material and a preparation method thereof, wherein the fiber reinforced polymer composite material comprises a polymeric resin matrix in a continuous phase, and chemical fiber fabric and reinforced fibers dispersed in the polymeric resin matrix, and the chemical fiber fabric covers the reinforced fibers so as to avoid exposure of the reinforced fibers to an outside surface of the composite material. The invention reduces or even avoids exposure of the reinforced fibers of the fiber reinforced polymer composite material, and can be used for manufacturing cable bridges, frames of doors, windows and curtain walls, etc. The method for preparing the fiber reinforced polymer composite material of the invention effectively improves the performance of the composite material and also reduces the cost of surface treatment and increases production efficiency.

A composite comprises: a reinforcing element (10), an adhesive layer (14) made from an adhesive composition, and an elastomeric body made from an elastomeric matrix comprising an ethylene/alpha-olefin type elastomer and/or a polychloroprene elastomer. The adhesive composition comprises a resin based: on a polyphenol comprising an aromatic ring bearing two hydroxyl functions in the meta position relative to one another, the two positions ortho to one of the hydroxyl functions being unsubstituted; and/or on a monophenol comprising a six-membered aromatic ring bearing a single hydroxyl function, the two ortho positions being unsubstituted, or an ortho position and the para position being unsubstituted, and on a compound comprising an aromatic ring bearing two functions, one of these functions being a hydroxymethyl function and the other being an aldehyde function or a hydroxymethyl function.

Provided are a method for preparing a unidirectionally aligned discontinuous fiber reinforcement composite material, a unidirectionally aligned discontinuous fiber reinforcement composite material, and a sandwich structure. The method for preparing a unidirectionally aligned discontinuous fiber reinforcement composite material comprises discontinuously aligning short fibers on a polymer substrate in one direction by using an air-laid method.

A method for producing a sandwich panel with a reinforced foam core includes inserting rod-shaped, thermoplastic reinforcing elements into a thermoplastic foam material such that the reinforcing elements extend through the foam material. End regions of the reinforcing elements project out of the foam material. The foam material is thermoformed to form a reinforced foam core, wherein the end regions of the reinforcing elements are integrally formed by applying temperature and pressure to the cover surfaces of the foam material and are bonded to the foam material in a fused connection. A thermoplastic cover layer is laminated on either side by applying temperature and pressure to the reinforced foam core on the cover surfaces of the foam material in order to form the sandwich panel, wherein the cover layers are bonded to the reinforced foam core in a fused connection.

Described are seat backs (102) for aircraft passenger seats (100). Such a seat back (102) can include a unitary structural core (112) formed as a single piece that includes a body (138) and a flange (140). The body (138) and the flange (140) can each include carbon fiber composite material. The flange (140) can include portions extending from the rearward-facing side (132) of the body respectively along a left lateral side edge, a top (134) side edge, and a right lateral side edge of the unitary structural core (112). The flange (140) can be non-tubular.

A method for producing a part made of a composite material having an organic matrix and a fibrous reinforcement, the method comprising the following steps: a) automatically draping, either in a planar arrangement or shaped over a three-dimensional cavity, at least one lamination (30, 31) comprising at least a first and second different dry plies, at least partially stacked to form a dry, planar or three-dimensional preform, each ply being fibrous and the plies mutually differing in terms of their structure, their positioning on the preform, the fibres composing them and/or the geometry of the ply, wherein at least one ply is laid in a non-woven form and has a plurality of unidirectional fibre layers laid on top of each other with a different angular orientation of the fibres, and/or at least one ply is woven; b) thermoforming the preform, the thermoforming step taking place, when the preform has been draped in a planar arrangement in step a), in a three-dimensional cavity of a first mold to impart a three-dimensional shape thereto; and c) impregnating, with at least one polymer, the preform thus thermoformed inside a mold, the preform being moved, if it is draped in a planar arrangement in step a), from the first thermoforming mold to a second mold for the impregnation step.

Presented are manufacturing control systems for composite-material structures, methods for assembling/operating such systems, and transfer molding techniques for predicting and ameliorating void conditions in fiber-reinforced polymer panels. A method for forming a composite-material construction includes receiving a start signal indicating a fiber-based preform is inside a mold cavity, and transmitting a command signal to inject pressurized resin into the mold to induce resin flow within the mold cavity and impregnate the fiber-based preform. An electronic controller receives, from a distributed array of sensors attached to the mold, signals indicative of pressure and/or temperature at discrete locations on an interior face of the mold cavity. The controller determines a measurement deviation between a calibrated baseline value and the pressure and/or temperature values for each of the discrete locations. If any one of the respective measurement deviations exceeds a calibrated threshold, a void signal is generated to flag a detected void condition.

A device to thermoform a composite component and injection over-moulding a shape on one face of the composite component in a mould. The mould includes a paired shaping die and punch between them defining a closed cavity. The shaping die is mounted on a transfer device. The transfer device includes a loading/unloading station to load/unload a blank onto/from the shaping die, and an injection and mould-closure station to close the mould and to inject between the punch and the shaping die. The shaping die includes a network of inductors to heat its moulding surface and a cooling network to cool the moulding surface by a circulation of a fluid. The loading/unloading station includes a placement device to place a radiating element facing the moulding surface of the shaping die.

A manufacturing method contemplates performing vacuum-assisted resin infusion to enclose an elongated core within a cured composite laminate without employing a mold. Not relying upon an external mold enables the process to be efficiently performed for core shapes that are manufactured in low volumes. Typical resin infusion processes utilize flow media that induces bag bridging during vacuum draw in order to provide gaps facilitating resin flow. However, popular flow media also tends to impart directional aggregate forces during vacuum draw, which forces can deform the core since no mold is being used. To avoid unequal and non-dispersed directional forces from deforming the elongated core, a flow media is employed that is configured to disperse and/or reduce such forces. Some such flow media may be knitted so as to allow overlapping strands to slide over one another. Other flow media may ensure that strands are interleaved so that no one strand or group of strands is disposed outwardly of other strands along a substantial length of the strands, thus dispersing bag bridging forces in several directions and avoiding directional aggregate forces. However, such flow media may have inhibited resin flow relative to popular high-flow flow media, and thus new strategies have been developed to ensure appropriate wetting of fibrous reinforcement. An adjustable brace can also be employed to restrain the elongated core from deflecting during application of vacuum and/or resin infusion.

A foam structural material includes a first core material and a reinforcing material. The first core material has a first portion of a linear groove part formed along an edge of the first core material. The reinforcing material has a first side fitted to the first portion of the linear groove part. The first portion of the linear groove part includes a first engagement plane. The first engagement plane is engaged with the reinforcing material and has one or a plurality of projections formed thereon.