An aircraft panel production method has: a step in which a holding jig holds a body panel, which has a plurality of plate-like members having a curved cross-sectional shape, such that the cross section of the body panel has an upwardly bulging curved shape; a step in which the plate-like members of the body panel held by the holding jig are overlapped with each other and the overlapping portions are joined by a rivet; a step in which the holding jig, which is holding the body panel of which the plate-like members have been joined to each other, is moved; and a step in which a frame that follows the curved shape of the body panel is joined, by a rivet, to the plate-like members of the body panel which is held by the holding jig which has been moved.

Systems and methods are provided for fastening via a swage tool. One embodiment is a method for fastening via a swage tool, the method including selecting a hole located at a part; aligning an axis of a lockbolt collar with a center of the hole; placing the lockbolt collar flush against the part at a first end of the hole; and swaging the lockbolt collar onto a lockbolt that has been driven through the hole.

A fastening device for feeding fasteners to a workpiece and for joining it, the fastening device comprising a fastening tool, a fastening device system. The fastening device including a magazine arrangement mounted on the fastening tool. The magazine arrangement having a magazine for holding a fastener, a magazine plate, and a base plate. The magazine plate includes a plate body and a closure arrangement with a closure slider adapted to move between an open position and a closed position, and a toggle mechanism adapted to move the closure slider from the closed position to the open position.

The invention relates to an atomizer unit of a minimal quantity lubrication system (3) for cooling and/or lubricating a chip-removing machining process between a tool (5) and a workpiece (6) at a machining station, wherein the atomizer unit (2) has a chamber arrangement (8) with a chamber arrangement interior (9), at least one first supply duct (10) for supplying a first compressed air stream (11) into and through the chamber arrangement interior (9) to a continuation duct (12) and an injection valve (13) for injecting a coolant and/or lubricant (4) into an injection region (14) into the first compressed air stream (11) in the chamber arrangement interior (9). It is proposed that the atomizer unit (2) has at least one second supply duct (15) for supplying a second compressed air stream (16) into and through the chamber arrangement interior (9) to the continuation duct (12), wherein the atomizer unit (2) is configured such that the second compressed air stream (16) joins the first compressed air stream (11), and any coolant and/or lubricant (4) injected into the first compressed air stream (11), downstream of the injection region (14) to form a transport stream (17) for transporting the injected coolant and/or lubricant (4), and wherein the transport stream (17) is conveyed through the continuation duct (12) to the machining station (7).

A manufacturing system employing a bifurcated backbone having an upper plate and lower plate, with a longitudinal slot between the upper and lower plate. A plurality of actuator groups are mounted longitudinally adjacent the slot. A carrier supports a panel for longitudinal translation into the slot and the carrier is configured to pulse longitudinally in the slot relative to the plurality of actuator groups during a sequence of fabrication operations by the plurality of actuator groups on the panel.

A clamping method includes a step (S3) for applying, by a first support portion disposed on one surface side of a plurality of superposed members and a second support portion disposed on the other surface side of the plurality of members, a predetermined first pressure to the plurality of members, and sandwiching the plurality of members; a step (S4) for forming a through hole with respect to the plurality of members by a cutting tool with the first pressure; a step (S5) for applying a predetermined second pressure to the plurality of members after the through hole is formed, and sandwiching the plurality of members by the first and second support portions, the second pressure being lower than the first pressure; and a step (S6) for fixing a fastening part inserted into the through hole to the plurality of members by a riveting device with the second pressure applied.

A device for inserting the blind fastener in the fastening site, a pulling and extracting device for swaging the blind fastener in the fastening site and a passive compliance device that binds the inserting device to the pulling and extracting device. The passive compliance device allows the installation of the bind fastener without sensors.

To simplify the structure of a holding fixture which holds the shape of the aircraft panel and conveys the aircraft panel, an object is to ensure shape accuracy required in the manufacturing process and hold an aircraft panel in an appropriate shape, in combination with a holding fixture. A shape holding fixture includes: a plurality of support units configured to be positioned on a lower surface side of an aircraft panel, and provided at intervals along a one-axis direction, the aircraft panel being held by a holding fixture configured to grip an edge portion of the aircraft panel; and a shape holding unit provided to each of the plurality of support units, including a rod which supports the aircraft panel from the lower surface side of the aircraft panel, and configured to adjust a position where the rod comes into contact with the aircraft panel to support the aircraft panel, corresponding to the shape of the aircraft panel.

An object is to provide a holding fixture fixing apparatus which can ensure positioning accuracy and shape accuracy of a moving holding fixture, thus allowing an aircraft panel to be assembled with high accuracy. A holding fixture fixing apparatus includes a plurality of fixing units configured to support and fix a holding fixture, which holds a fuselage panel having a curved shape in cross section, from a lower surface of the holding fixture, the fixing units being provided on an installation surface, wherein the plurality of fixing units are provided corresponding to at least four corners of the lower surface of the holding fixture.

A component manufacturing method includes a step in which a robot for attachment gripping a long frame presses the frame against a tabular skin and a step in which, in a state in which the frame is pressed against the skin, a robot for riveting gripping a first rivet inserts the first rivet into a first through-hole formed in the skin and a second through-hole formed in the frame. In the step, the robot for riveting changes a position in the gripped first rivet in a direction perpendicular to an axial direction of the first rivet according to a force received by the first rivet from the skin or the frame.