A method of joining two panels of an airframe or fuselage structure of an aircraft or spacecraft, including: preparing an edge region of a first panel to form a first joining surface; preparing an edge region of a second panel to form a second joining surface; aligning the panels with one another such that the joining surfaces abut or interface one another forming a joint area; and joining the panels at the joining surfaces in the joint area. In an embodiment, the preparing steps include machining, and cutting, the edge regions of the first and second panels in a single operation to form the first and second joining surfaces substantially simultaneously. In another embodiment, the first and second joining surfaces are substantially planar and extend at an oblique angle with respect to a primary plane or surface of the respective first and second panels.

Provided is a bonding apparatus including a bonding stage 83 for heating a substrate (lead frame) 61 placed on the upper surface thereof or a semiconductor die 63 mounted on the substrate (lead frame) 61, an imaging device 20 arranged above the bonding stage 83 to image the substrate 61 placed on the bonding stage 83 or the semiconductor die 63 mounted on the substrate 61, and a standing wave generating device 35 for generating an ultrasonic standing wave in the space between the upper surface of the bonding stage 83 and the imaging device 20. This improves the accuracy of image position detection by the imaging device with a simple structure.

The present invention relates to a method for providing a braze alloy layered product comprising the following steps: applying at least one silicon source and at least one boron source on at least a part of a surface of a substrate, wherein the at least one boron source and the at least one silicon source are oxygen free except for inevitable amounts of contaminating oxygen, and wherein the substrate comprises a parent material having a solidus temperature above 1100 C.; heating the substrate having the applied boron source and the applied silicon source to a temperature lower than the solidus temperature of the parent material of the substrate; and cooling the substrate having the applied boron source and the applied silicon source, and obtaining the braze alloy layered product. The present invention relates further to a braze alloy layered product, a method for providing a brazed product, a method for providing a coated product, and uses of the braze alloy layered product.

A method for forming an electrical connection to a microscale electrically conductive fiber material electrode element, such as a carbon fiber electrode element of a Pb-acid battery, comprises pressure impregnating into the fiber material an electrically conductive lug material, such as molten Pb metal, to surround and/or penetrate fibers and form an electrical connection to the fiber material and provide a lug for external connection of the electrode element. Other methods of forming a lug for external connection are also disclosed.

A method for bonding a first substrate and a second substrate includes: forming a protrusion at a partial region of the first substrate; measuring a position of the first substrate after the protrusion is formed in the first substrate; and bonding the first substrate and the second substrate by contacting the protrusion of the first substrate with a surface of the second substrate to form a contact region and enlarging the contact region.

A substrate stacking apparatus that stacks first and second substrates on each other, by forming a contact region where the first substrate held by a first holding section and the second substrate held by a second holding section contact each other, at one portion of the first and second substrates, and expanding the contact region from the one portion by releasing holding of the first substrate by the first holding section, wherein an amount of deformation occurring in a plurality of directions at least in the first substrate differs when the contact region expands, and the substrate stacking apparatus includes a restricting section that restricts misalignment between the first and second substrates caused by a difference in the amount of deformation. In the substrate stacking apparatus above, the restricting section may restrict the misalignment such that an amount of the misalignment is less than or equal to a prescribed value.

A method for manufacturing a shaft, whereby a hollow shaft in which linking members are joined at both ends of a cylindrical member (a pipe member) can be manufactured more efficiently. A method for manufacturing a shaft in which linking members are provided to end parts of a cylindrical member, wherein the method comprises: a preparation step for preparing the cylindrical member, in which male threaded portions are formed at the end parts; a screwing step in which the linking members, which have female threaded portions to be screwed onto the male threaded portions, are screwed onto the male threaded portions; and a diffusion-joining step in which opposing end surfaces of the linking members and the cylindrical member are heated in a state of being pressed against each other by the tightening produced by the screwed-on linking members, and the opposing end surfaces are diffusion-joined.

A highly reliable bonded structure having excellent thermal fatigue resistance characteristics and thermal stress relaxation characteristics is provided. The bonded structure of the present invention comprises a first member, a second member capable of being bonded to the first member, and a bonding part interposed between a first bond surface at the first member side and a second bond surface at the second member side to bond the first member and the second member. The bonding part has at least a bonding layer, a reinforcing layer, and an intermediate layer. The bonding layer is composed of an intermetallic compound and bonded to the first bond surface.

A method for the manufacture of a blisk drum is described. Disc forging for inertia welding together are provided with sacrificial material whose shape and position is selectively provided such that, on completion of the inertia welding process, integral blades can be fashioned from the sacrificial material. Other components such as buckets and balancing lands may also be provided from the sacrificial material.

A bonding target member 1 having a solid bonding material 3 with aluminum as a main component is interposed between a metal member 2 and a ceramic member 4 and an elastic member 12 are pressurized by a pressurizing section 13 and a bonding tool section 15 of a resonator 14 in a vertical direction. The bonding tool section 15 of the resonator 14 resonates with sound vibration or ultrasound vibration transmitted from an oscillator 16. An interfacial portion between the metal member 2 and the bonding material 3 with aluminum as a main component and an interfacial portion between the bonding material 3 with aluminum as a main component and the ceramic member 4 each receive pressurization and vibration energy to be bonded together. The metal member 2 and the ceramic member 4 can be bonded together at ordinary temperature in the atmosphere with the bonding material 3 with aluminum as a main component. When the ceramic member 4 has a thickness resistant to pressurization and vibration energy at the time of bonding to resist crack, the elastic member 12 may be disposed on a metal member 2 side, or may not be used.