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.

A thin-walled organic-matrix composite product reinforced by yarns, the yarns compromising hybrid yarns, the hybrid yarns having a core made of a first material having a density less than 1500 kg/m3 and a cover covering the core, the cover being produced from a second material, the second material being different from the first material and having a longitudinal Young's modulus greater than 25 GPa, and the composite product having at least one ribbed face, the ribs being created at least partially by the hybrid yarns.

A method of making an aircraft blade is provided. The method comprises the steps of: assembling two or more fibre-reinforced thermoplastic composite parts into a blade assembly; and welding the fibre-reinforced thermoplastic composite parts together utilising an additional thermoplastic located at least at locations where the parts will abut when assembled. The additional thermoplastic has a melting or softening temperature lower than a melting temperature of each of the fibre-reinforced thermoplastic composite parts being assembled. The step of welding comprises heating the blade assembly to a temperature above the melting/softening temperature of the additional thermoplastic and below the melting temperature of each of the fibre-reinforced thermoplastic composite parts so as to melt/soften the additional thermoplastic and thereby weld the fibre-reinforced thermoplastic composite parts together to form the aircraft blade.

A method of making an aircraft blade is provided. The method comprises the steps of: assembling two or more fibre-reinforced thermoplastic composite parts into a blade assembly; and welding the fibre-reinforced thermoplastic composite parts together utilising an additional thermoplastic located at least at locations where the parts will abut when assembled. The additional thermoplastic has a melting or softening temperature lower than a melting temperature of each of the fibre-reinforced thermoplastic composite parts being assembled. The step of welding comprises heating the blade assembly to a temperature above the melting/softening temperature of the additional thermoplastic and below the melting temperature of each of the fibre-reinforced thermoplastic composite parts so as to melt/soften the additional thermoplastic and thereby weld the fibre-reinforced thermoplastic composite parts together to form the aircraft blade.

A fiber-reinforced resin component comprises a first part having a plurality of first fiber layers impregnated in a matrix resin and a second part having a plurality of second fiber layers impregnated in the matrix resin. The second part is bonded to the first part via an adhesive layer. The fiber-reinforced resin component further comprises a plurality of connecting fibers that connect the first part and the second part. One end portion of the connecting fibers is sandwiched between the first fiber layers, and the other end portion of the connecting fibers is sandwiched between the second fiber layers.

A fiber-reinforced resin component comprises a first part having a plurality of first fiber layers impregnated in a matrix resin and a second part having a plurality of second fiber layers impregnated in the matrix resin. The second part is bonded to the first part via an adhesive layer. The fiber-reinforced resin component further comprises a plurality of connecting fibers that connect the first part and the second part. One end portion of the connecting fibers is sandwiched between the first fiber layers, and the other end portion of the connecting fibers is sandwiched between the second fiber layers.

A system and a method for securing a first composite panel to a second composite panel include a latch assembly having one or more latches. The latch assembly is configured to be secured to one of the first composite panel or the second composite panel. One or more strikes are configured to retain at least a portion of the one or more latches. The one or more strikes are configured to be secured to the other of the first composite panel or the second composite panel.

A system and a method for securing a first composite panel to a second composite panel include a latch assembly having one or more latches. The latch assembly is configured to be secured to one of the first composite panel or the second composite panel. One or more strikes are configured to retain at least a portion of the one or more latches. The one or more strikes are configured to be secured to the other of the first composite panel or the second composite panel.

The embodiment includes: a planar graphite heater; a clamp device that moves the graphite heater, which is arranged between a first bonding surface W1a of a first composite material member and a second bonding surface of a second composite material member facing the first bonding surface, in a traveling direction with the graphite heater being in contact with the first bonding surface and the second bonding surface; and a control unit that controls the graphite heater to heat the first bonding surface and the second bonding surface while the graphite heater is in contact with the first bonding surface and the second bonding surface.

The embodiment includes: a planar graphite heater; a clamp device that moves the graphite heater, which is arranged between a first bonding surface W1a of a first composite material member and a second bonding surface of a second composite material member facing the first bonding surface, in a traveling direction with the graphite heater being in contact with the first bonding surface and the second bonding surface; and a control unit that controls the graphite heater to heat the first bonding surface and the second bonding surface while the graphite heater is in contact with the first bonding surface and the second bonding surface.