A method of forming sheet metal skins of the inner fixed structure of a blocker door thrust reverser assembly having convex and concave curvatures. The method includes plastically stretching a sheet of metal about a mandrel having a chordwise central first axis to form a substantially convex shape. The method further includes the addition of features after the substantially convex shape is formed to facilitate plastically stretching a portion or portions of the substantially convex shape into a substantially concave shape about an axis that is substantially parallel to the chordwise central first axis.

A driven member of a metal peening machine is disclosed. The metal peening machine is configured to drive the driven member into contact with a work surface of a metal workpiece to deform the metal workpiece. The driven member includes a shaft with an impact end. The driven member includes least one of a plurality of impact features, an impact feature with a non-flat impact surface, a non-round impact feature, and an asymmetrical impact feature that is coupled to and protrudes from the impact end of the shaft. The at least one of the plurality of impact features, the impact feature with a non-flat impact surface, the non-round impact feature, and the asymmetrical impact feature define at least one impact surface to be driven into contact with the work surface of the metal workpiece.

Method for manufacturing an aircraft door having a monolithic structure, including the following steps: producing a forged blank; die-cutting the forged blank between a substantially smooth lower die and an upper die defining cells, and producing a die-cut part with a cellular structure having an open face and a face closed by a wall; machining the internal walls of the cellular structure to define at least one recess delimited by a web connecting the closed face and the open face and by a base projecting substantially perpendicular to the web, on the open face of the die-cut part.

Method for manufacturing an aircraft door having a monolithic structure, including the following steps: producing a forged blank; die-cutting the forged blank between a substantially smooth lower die and an upper die defining cells, and producing a die-cut part with a cellular structure having an open face and a face closed by a wall; machining the internal walls of the cellular structure to define at least one recess delimited by a web connecting the closed face and the open face and by a base projecting substantially perpendicular to the web, on the open face of the die-cut part.

A method for manufacturing annular sectors of an air intake lip includes arranging a revolution-shaped blank facing a three-dimensional forming surface of a die of a hydroforming tool, the three-dimensional surface including at least two plunging cavities spaced from each other along a circumferential direction, forming an air intake lip preform in one piece by hydroforming the revolution-shaped blank on the three-dimensional surface of the die, the air intake lip preform having in section a U-shape and including a plurality of crenellated portions each delimited by a plunging cavity, the production of a plurality of cutouts in the air intake lip preform so as to divide the preform into a plurality of annular sectors, each cutout including the removal of a sacrificial portion at the level of a crenellated portion so as to form two adjacent assembly edges with one of the two adjacent assembly edges including a plunging.

A method of manufacturing a multi-sided or otherwise relatively three-dimensional formed structure for, e.g., an aerospace vehicle. A relatively planar base structure is constructed using a first construction technique. Features (e.g., ribs) are incorporated into the base structure using a second construction technique (e.g., additive or subtractive manufacturing) to create an intermediate structure. The intermediate structure is folded along fold-lines or otherwise physically formed to create the formed structure, such that some of the features are located within an internal space defined by the formed structure. Joints between the sides of the formed structure are welded, fastened, or otherwise secured. Separately constructed additional elements (e.g., bulkheads) may be incorporated into the structure. A closeout element may be added to the formed structure to further define and close the internal space. Throughout the process, the structures, features, and elements may be refined to desired tolerances.

A method for manufacturing a structural surface heat exchanger of preset or left-hand final shape for an aircraft includes the steps of forming, shaping and assembling, by welding or brazing, a first corrugated skin and a second smooth skin in order to obtain channels. Each channel is delimited by a corrugation of the first skin and the second smooth skin so as to form a structural surface heat exchanger of preset or left-hand final shape, wherein a fluid is configured to circulate in the channels and air is configured to circulate in contact with the second smooth skin.

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 method of forming an annular part includes forming a conical or frusto-conical preform with at least one open end, initiating an actuation means to cause relative coaxial movement only between a punch, a clamping means and a gripping means, thereby clamping a large diameter end of the preform in the clamping means and gripping a second small diameter end of the preform in the gripping means and the external surface of the punch to engage the internal surface of the preform, and causing relative co-axial movement between the gripping means and the punch so that the portion of the wall of the preform between the punch and the gripping means is formed over the leading edge of the punch.