The present invention essentially relates to a method for assembling a beam and a structural element of an aircraft seat, characterised in that it comprises: a step of producing at least one recess in an inner face of a beam passage area of the structural element, a step of inserting the beam into the beam passage area, and a step of deforming the beam such that a deformed portion of the beam penetrates into the recess of the beam passage area.

A system includes a plurality of forming roller sets comprising an inner forming roller and an outer forming roller, each inner forming roller rotatable about an inner forming roller axis, each outer forming roller rotatable about an outer forming roller axis, each forming roller set being adjustable between an engagement configuration and a disengagement configuration, each forming roller set forming a profile on the ring component based on a forming roller set profile of the forming roller set, the system also including an actuating unit which controls the engagement and a disengagement of the forming roller sets with the ring component.

A processing device processes a frame-shaped workpiece which extends in a prescribed extension direction, and includes, integrally, a plate-shaped web surface portion, a plate-shaped first flange portion that bends and extends from one end of the web surface portion, and a plate-shaped second flange portion which bends from the other end of the web surface portion and extends in the opposite direction to the first flange portion. The processing device includes a shaping device which conveys the workpiece in the extension direction, and an exit side pinch roll device provided further downstream, in the workpiece conveying flow direction, than the shaping device. The exit side pinch roll device includes a first roll which presses a central region of an upper surface side of the web surface portion, and a second roll which presses a central region of a lower surface side of the web surface portion.

A processing device processes a frame-shaped workpiece which extends in a prescribed extension direction, and includes, integrally, a plate-shaped web surface portion, a plate-shaped first flange portion that bends and extends from one end of the web surface portion, and a plate-shaped second flange portion which bends from the other end of the web surface portion and extends in the opposite direction to the first flange portion. The processing device includes a shaping device which conveys the workpiece in the extension direction, and an exit side pinch roll device provided further downstream, in the workpiece conveying flow direction, than the shaping device. The exit side pinch roll device includes a first roll which presses a central region of an upper surface side of the web surface portion, and a second roll which presses a central region of a lower surface side of the web surface portion.

A method for forming large titanium parts includes forming bends into a titanium plate for form a bent part. The bent part is then roll-formed to form contours into the bent part. The surfaces of the contoured part are rough-machined, and the part is then secured to a bladed form fixture. The bladed form fixture comprises a plurality of header boards that secure the part to the fixture. The fixture part is placed in a thermal vacuum furnace and a stress-relieving operation is performed. The part is removed from the fixture and final machining takes place.

A method for forming large titanium parts includes forming bends into a titanium plate for form a bent part. The bent part is then roll-formed to form contours into the bent part. The surfaces of the contoured part are rough-machined, and the part is then secured to a bladed form fixture. The bladed form fixture comprises a plurality of header boards that secure the part to the fixture. The fixture part is placed in a thermal vacuum furnace and a stress-relieving operation is performed. The part is removed from the fixture and final machining takes place.

A fuselage heat exchanger having channels for dissipating waste heat generated by fuel cells that power unmanned aerial vehicles (UAVs) or drones. A heat exchanger built into the fuselage can dissipate such waste heat. Coolant flowing through channels embedded within an aircraft fuselage panel dissipates heat to airflow around the outer surface of the fuselage.

A method of forming a component by applying a forming load to a blank of material against a mandrel, wherein the mandrel defines the shape of the component to be formed and applying a forming load as a combination of a localised force and localised friction heating.

A method of forming a component by applying a forming load to a blank of material against a mandrel, wherein the mandrel defines the shape of the component to be formed and applying a forming load as a combination of a localised force and localised friction heating.

Said induction moulding device comprises an inductor configured to deform by induction a portion of an electrically conductive part, the inductor comprising a first power terminal, a second power terminal and at least one inductive portion electrically connecting the first power terminal and the second power terminal, the inductive portion being intended to induce an induced current in the electrically conductive part, the inductive portion extending in a longitudinal direction in which a supply current is intended to flow between the first power terminal and the second power terminal, the inductive portion comprising at least one notch defining a narrowing of a cross section of said inductive portion perpendicular to the longitudinal direction.