A method and apparatus for processing fuselage sections. The apparatus comprises a cradle system, a metrology system, and a controller. The cradle system holds a first fuselage section and applies forces to the first fuselage section to change a current shape of the first fuselage section. The metrology system makes measurements of the current shape of the first fuselage section. The controller receives the measurements from the metrology system, identifies the forces needed to change the current shape of the first fuselage section towards a desired shape for connecting the first fuselage section to a second fuselage section, and sends commands to the cradle system to apply the forces to change the current shape of the first fuselage section towards the desired shape.

A method and apparatus for processing fuselage sections. The apparatus comprises a cradle system, a metrology system, and a controller. The cradle system holds a first fuselage section and applies forces to the first fuselage section to change a current shape of the first fuselage section. The metrology system makes measurements of the current shape of the first fuselage section. The controller receives the measurements from the metrology system, identifies the forces needed to change the current shape of the first fuselage section towards a desired shape for connecting the first fuselage section to a second fuselage section, and sends commands to the cradle system to apply the forces to change the current shape of the first fuselage section towards the desired shape.

In an illustrative embodiment, an aircraft galley ducting assembly provides airflow to at least one compartment of an aircraft galley monument. The ducting assembly may include a supply air duct that provides a supply airflow path to a compartment that includes an inlet port mounted to a compartment surface. A return air duct may provide an exit airflow path for return air that has circulated throughout the compartment and includes an outlet port mounted to the compartment surface. An airflow adjustment apparatus with an airflow adjustment surface is positioned within the supply airflow path of the supply air duct or the exit airflow path of the return air duct to cause a modification of airflow properties for air passing across or through the airflow adjustment surface.

In an illustrative embodiment, an aircraft galley ducting assembly provides airflow to at least one compartment of an aircraft galley monument. The ducting assembly may include a supply air duct that provides a supply airflow path to a compartment that includes an inlet port mounted to a compartment surface. A return air duct may provide an exit airflow path for return air that has circulated throughout the compartment and includes an outlet port mounted to the compartment surface. An airflow adjustment apparatus with an airflow adjustment surface is positioned within the supply airflow path of the supply air duct or the exit airflow path of the return air duct to cause a modification of airflow properties for air passing across or through the airflow adjustment surface.

An apparatus for forming a nacelle leading edge includes an actuation assembly, a punch, and a die. The punch is in communication with the actuation assembly and annularly disposed about a first axis. The punch is configured to mate with an interior surface of a preform. The die is in communication with the actuation assembly and disposed within the first axis. The die is configured to retain an exterior surface of the preform. The actuation assembly is configured to effect relative motion between the punch and the preform. The actuation assembly is configured to offset the punch so that the punch is annularly disposed about a second axis, different than the first axis.

A method is provided for forming an annular object. This method includes: providing a frustoconical preform extending axially along an axis, wherein a sidewall of the frustoconical preform is angularly offset from the axis by a preform angle; externally drawing the frustoconical preform over an outer surface of a punch and an outer surface of a die clamp to provide an externally drawn body, wherein the outer surface of the die clamp is angularly offset from the axis by a die clamp angle that is different than the preform angle; mating a die with the die clamp to provide a die assembly, wherein the externally drawn body is clamped radially between the die and the die clamp; and translating the die assembly axially along the axis and into a bore of the punch to at least partially internally draw the externally drawn body against an inner surface of the punch.

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 a metal beam may comprise: clamping first and second portions of the metal beam in a substantially fixed and in a position whereat the metal beam is rotatable about three axes; applying a net bending force to the clamped second portion of the metal beam at a predetermined angle; sensing twisting of the second portion of the metal beam resulting from the net bending force; and modulating the angle at which the net force is applied to reduce the twisting of the metal beam. As a result, the net bending force is moved toward the shear center and toward being along the principal axis of the metal beam.

A method for manufacturing an aircraft leading edge panel, includes a step of overmoulding a coating onto a sheet positioned in a cavity of a mould, which cavity is delimited by a shaping surface which exhibits an optimized surface finish. The coating includes, after the overmoulding step, an exterior face which corresponds to the exterior face of the panel that is to be obtained and which exhibits an optimized surface finish conferred by the shaping surface of the mould. A panel may be obtained using this method and a leading edge includes at least one such panel. Because of the optimized surface finish of the exterior surface thereof, the panel contributes to extending the regions of laminar flow.