A bonded joint for use in bonding composite materials is provided and includes a composite rib having electrically conductive properties and a composite structure having electrically conductive properties. An electrically conductive preform is provided that facilitates a bond between the composite rib and the composite structure. A mesh composition that bonds the composite rib to the preform and that bonds the preform to the composite structure is provided and is electrically conductive to conduct current between the composite rib and the composite structure.

Provided are a welding device and a welding method that can avoid occurrence of a clearance in a side region of a member and suppress occurrence of a failure of the member due to such a clearance. The embodiment includes: an electrode 11 configured to supply electricity to an electroconductive element 23 arranged between members 21, 22 and configured to generate heat by current conduction; and a pressing element 12 arranged in a side region of one member 22 of the members 21, 22 and configured to press the electroconductive element 23 while elastically being in close contact with the one member 22. Further, the pressing element 12 comes into close contact with the one member 22 by being pushed against the electroconductive element 23 and expanding in a direction orthogonal to a pushing direction.

A joining method and assembly for an aircraft. To improve the characteristics or permit hitherto impossible connections between thermoplastic and thermoset components, a multi-material joining method is disclosed in which a thermoplastic connecting region is formed on the thermoplastic component. The connecting region is connected to the thermoset component by interdiffusion. For this purpose, the uncured second component is brought into contact with the connecting region and heat is supplied. An interdiffusion layer is formed which fixedly connects the second component and the connecting region to one another and thus joins the first component to the second component.

A joining method for connecting at least two thermoplastic workpieces is provided to permit the joining even of non-transparent carbon fiber reinforced plastics parts by means of laser welding, in which a splice is produced at the edge regions of the workpieces and the workpieces are subsequently positioned relative to one another in such a manner that the opposite splice regions bound a seam region. Connecting bodies are then inserted into the seam region and heated by means of local heat input by laser beam such that a fixed integrally bonded connection forms between the workpieces and the connecting bodies.

A bonded composite joint includes a first carbon fiber-reinforced polymer (CFRP) panel; a second CFRP panel; a corrugated structure placed between the first and second CFRP panels; and an adhesive placed between the first and second CFRP panels and in contact with the corrugated structure. The corrugated structure has a shape defined by a given wavelength λ.

Provided is a welding method including: a sheet disposition process of disposing a first and a second protection sheet such that the first and the second protection sheet come into contact with a first and a second composite material and disposing an energization sheet such that the energization sheet comes into contact with the first and the second protection sheet; and a welding process of applying a voltage to a pair of electrode portions disposed at the energization sheet and welding the first and the second composite material, the energization sheet contains the carbon fiber base material oriented in a first predetermined direction connecting the pair of electrode portions, and the first and the second protection sheet contain the carbon fiber base material oriented in a second predetermined direction that substantially perpendicularly intersects the first predetermined direction.

Aircraft stringers having carbon fiber reinforced plastic (CFRP) material reinforced flanges are disclosed. An example stringer to be coupled to a skin of an aircraft comprises a flange. The flange includes a first portion of a first stiffening segment. The flange further includes a first portion of a second stiffening segment coupled to the first portion of the first stiffening segment. The flange further includes a CFRP reinforcement segment coupled to the first portion of the first stiffening segment and to the first portion of the second stiffening segment. The CFRP reinforcement segment strengthens the first portion of the first stiffening segment and the first portion of the second stiffening segment.

A method for thermoforming a bicycle frame component includes the steps of: (A) preparing first and second casings both made of a thermoplastic material, the first casing having a first abutment surface, the second casing having a second abutment surface; (B) preparing a reinforcing unit; (C) abutting the first and second abutment surfaces against each other, and then placing the reinforcing unit at a junction of the first and second casings; and (D) thermally bonding the reinforcing unit to the first and second casings such that the first and second casings are joined to form the bicycle frame component. A bicycle frame component is also disclosed.

A microwave heating device includes a variable frequency microwave power supply, a waveguide launcher, and a fixture to contain a material to be heated, with the fixture located directly adjacent to the end of the launcher. All heating occurs in the near-field region, i.e., no cavity modes or standing waves are established within the fixture. This condition may be insured by keeping the thickness of the fixture or workpiece under one wavelength (at all microwave frequencies being used). The launcher is preferably a horn configured to spread the microwave power laterally over a selected area while maintaining a single propagating mode. The invention may be used to enhance catalytic reactions for research and other purposes. Alternatively, the invention may be configured to perform spot curing or repair operations involving adhesives and composites.

A method of assembly of a carbon fiber space frame structure eliminates the need for gusset plates at the j oints of the space frame structure. The elimination of the gusset plates at the j oints of the space frame structure reduces the weight of the space frame structure and eliminates stresses that occur at the j oints due to gusset plates attached at the j oints.