A method for making a fuselage section comprises the steps of assembling a support system. The support system comprises fiber reinforced composite material and includes at least three frames and six stringers. The support system is partially cured such that the support system attains about eighty percent of its fully cured strength. A skin comprising fiber reinforced composite material is globally positioned such that an inner surface of the skin corresponds to an outer surface of the support system. The skin and the support system are fully cured together. The support system is assembled on a skeleton assembly tool having a bonding surface corresponding to an inner surface of the skin.

A composite part includes a first structural element. The composite part includes a second structural element joined at an intersection with the first structural element to form a fillet. The composite part further includes reinforcement webbing wrapped around the first structural element proximate the fillet.

A method for bonding composite structures which includes providing a first and second composite substrate and coupling a co-cure prepreg tape having chemically protected polymerizable functional groups onto a surface of both the first and second composite substrates. The first and second composite substrates are then cured to the co-cure prepreg tape at a first temperature to form a co-cure prepreg tape portion where the first and second composite substrates are fully cured and the co-cure prepreg tape is partially cured. The co-cure prepreg tape portion of the first composite substrate is then coupled to the co-cure prepreg tape portion of the second composite substrate and a deprotection initiator is applied to facilitate deprotection of the chemically protected polymerizable functional groups and cure the co-cure prepreg tape portion of the first and second composite substrates to form a single covalently bonded composite structure.

A method for manufacturing a joined body according to an embodiment of the present disclosure is a method for manufacturing a joined body in which composite materials in which fibers are impregnated with resins are heated and joined to each other. The method includes: a step of aligning the composite material with each of a plurality of molding dies, heating the molding dies, and semi-curing the resins of the composite materials; and a step of joining the composite materials to each other by combining and heating the molding dies with which the composite materials are aligned after semi-curing the resins of the composite materials. The molding dies used when semi-curing the resins of the composite materials and the molding dies used when joining the composite materials to each other are the same.

A system for depositing a composite filler material into a channel of a composite structure includes an end-effector configured to extrude a bead of the filler material into the channel. The filler material can comprise a first group of relatively long fibers, a second group of relatively short fibers and a resin. A drive system is configured to move the end-effector relative to the channel, and a position sensor is configured to detect the position of the bead relative to the channel. A controller is configured to operate the drive system in response to the detected position and to operate the end-effector to heat and compress the filler material so as to orient the longer fibers in a substantially longitudinal direction relative to the channel and the shorter fibers in substantially random directions relative to the channel when the bead is extruded into the channel.

Aspects of the present invention relate to systems and methods for customizing microwave energy distribution within a chamber to accommodate various load characteristics. Aspects of the present invention customized configurations of ports, deflectors, waveguides, conducting rods, and slots to shape and distribute energy.

The present invention relates to a method for producing thermosetting components from two or more semifinished composite-material products with textile fibre reinforcement and matrix material, wherein the semifinished composite-material products are fully consolidated, with the exception of local regions, and are brought into contact at the partially consolidated (gelled) regions (201, 211, 221, 241) such that the matrix material of the partially consolidated regions (201, 211, 221, 241) bonds and the regions joined together in this way are subsequently fully consolidated. Furthermore, a device which is suitable for producing the semifinished composite-material products is disclosed.

A method of forming a composite article may include initially curing a composite laminate at an initial temperature to an initial cure stage of 30-50 percent of full cure and beyond a gel point to form an initially-cured composite laminate. The method may initially include heating the initially-cured composite laminate to an intermediate temperature higher than the initial temperature and above a resin glass transition temperature. In addition, the method may include intermediately curing the composite laminate to an intermediate cure stage of 50-70 percent of full cure while on a final forming tool to form an intermediately-cured composite laminate. Furthermore, the method may include removing the intermediately-cured composite laminate from the final forming tool, and finally curing the intermediately-cured composite laminate at a final temperature higher than the intermediate temperature to a final cure stage.

Fiber-reinforced composite parts include select portions containing a plurality of co-aligned fiber. The parts are fabricated by placing substantially preforms into a mold cavity to form a layup, and compression molding the layup to consolidate the preforms to provide a fiber-reinforced composite part. Different sections of the part can be derived from preforms having different shapes and different compositions.

A semi-finished product including at least one vitrimer, a method of joining using the semi-finished product with a sub-component, a component produced by the method, and a method of debonding such component.