Systems and methods for assembling elongate composite structures are disclosed. The systems include a first rigid elongate cure tool defining a first elongate support surface for supporting a first elongate charge of composite material (FEC), a second rigid elongate cure tool defining a second elongate support surface for supporting a second elongate charge of composite material (SEC), and a flexible elongate caul plate. The systems further include a vacuum compaction film, a translation structure, and a vacuum source. Methods according to the present disclosure include positioning a vacuum compaction film, positioning a flexible elongate caul plate, and positioning an FEC. The methods further include positioning an SEC, contacting a region of the FEC with a region of the SEC, sealing the vacuum compaction film, evacuating the enclosed volume to generate an elongate composite assembly, and heating the elongate composite assembly to define the elongate composite structure.

Composite laminate structures are produced using partially cured parts. Partial curing of the parts is achieved by applying a catalyst to regions of the parts that are to be fully cured. These regions cure at a lower-than-normal temperature while remaining regions of the part remain uncured, allowing them to be co-bonded or co-cured to other structures.

An endless belt includes a band-shaped belt main body made of a vulcanized rubber, and a coupling part that is made of a thermoplastic resin and is provided between both end parts of the belt main body, wherein the vulcanized rubber of the both end parts of the belt main body and the thermoplastic resin of the coupling part are chemically bonded to each other.

Systems and methods are provided for utilizing stringer end caps. One embodiment is a method of forming a stringer. The method includes laying up a stringer preform comprising fiber-reinforced material, placing the stringer preform onto a skin panel preform, bonding an end cap to the stringer preform and the skin panel preform, and co-curing the stringer preform and the skin panel preform while the end cap is bonded to the stringer preform and the skin panel preform, resulting in a composite part that includes the end cap.

Systems and methods for assembling elongate composite structures are disclosed. The systems include a first rigid elongate cure tool defining a first elongate support surface for supporting a first elongate charge of composite material (FEC), a second rigid elongate cure tool defining a second elongate support surface for supporting a second elongate charge of composite material (SEC), and a flexible elongate caul plate. The systems further include a vacuum compaction film, a translation structure, and a vacuum source. Methods according to the present disclosure include positioning a vacuum compaction film, positioning a flexible elongate caul plate, and positioning an FEC. The methods further include positioning an SEC, contacting a region of the FEC with a region of the SEC, sealing the vacuum compaction film, evacuating the enclosed volume to generate an elongate composite assembly, and heating the elongate composite assembly to define the elongate composite structure.

Provided are a rubber sheet member joining device and method. At least one opposing surface of a pair of gripping parts is provided with a contact member having a contact surface projecting toward an other opposing surface of the pair of gripping parts; the pair of gripping parts grip ranges in proximity to end surfaces in a state in which end surfaces project from the one opposing surface toward the other opposing surface; the total of end surface projection amounts of the end surfaces from the opposing surfaces is set to be a predetermined length larger than a separation distance between the opposing surfaces when the contact member is sandwiched between the opposing surfaces; and by bringing the contact member into a state of being sandwiched between the opposing surfaces, the movement of the gripping parts in proximity to each other is stopped and the end surfaces are joined together.

A method for surface preparation of composite substrates prior to adhesive bonding. A curable surface treatment layer containing blocked isocyanate compounds is applied onto a curable composite substrate, followed by co-curing. The surface treatment layer may be a resin layer without fibers or a removal peel ply composed of resin-impregnated fabric. After surface preparation, the composite substrate is provided with a chemically-active, bondable surface that can be adhesively bonded to another composite substrate to form a covalently-bonded structure.

Composite fabrication system and associated methods. In one embodiment, a composite fabrication system comprises a molding tool that includes a forming surface at least partially disposed within a constrained space, and a foamable material that expands inside of the constrained space to form an expanded material that presses a layup of one or more composite layers against the molding tool. The composite fabrication system further comprises a curing device configured to cure the layup to form a composite part, and a cutting wire embedded in the constrained space that is heated and configured to cut the expanded material into pieces that are removable from the constrained space.

An apparatus for processing an elongated structure includes a mold within which an uncross-linked rubber material is placed, at least one heating unit configured to heat the mold, and a pressure device configured to press the rubber material using the mold heated by the heating unit to promote shaping the rubber material by the mold while proceeding the cross-linking of the rubber material. The heating unit includes a central heating device configured to heat a longitudinal central portion of the mold, multiple cooling devices configured to cool two longitudinal end portions of the mold, multiple intermediate heating devices configured to heat two intermediate portions between the longitudinal central portion and the longitudinal end portions of the mold, heat shield plates disposed between the central heating device and the intermediate heating devices, and heat shield plates disposed between the cooling devices and the intermediate heating devices.

Composite fabrication system and associated methods. In one embodiment, a composite fabrication system comprises a molding tool that includes a forming surface at least partially disposed within a constrained space, and a foamable material that expands inside of the constrained space to form an expanded material that presses a layup of one or more composite layers against the molding tool. The composite fabrication system further comprises a curing device configured to cure the layup to form a composite part, and a cutting wire embedded in the constrained space that is heated and configured to cut the expanded material into pieces that are removable from the constrained space.