Abstract: A method for manufacturing at least a portion of a box structure obtained from an outer skin and a plurality of sections each having a joining face in contact with the outer skin. The method comprises a step of positioning the sections on a mold, a step of obtaining a flat fiber preform having a thickness substantially equal to the outer skin, a step of placing a central portion of the fiber preform on the sections positioned on a first face of the mold and a step of forming a lateral extension of the fiber preform to press the fiber preform against a forming surface. A central wingbox obtained by the method is provided and a forming tool for carrying out the method.

Abstract: The invention concerns an augmented vision system (1) comprising: a displaying device (3) comprising: a fixing element (31) for coupling the displaying device (3) to a head-mountable component (90) configured to be positioned in front of a 5 face (102) of a user (100), and a display body (32) being coupled to said fixing element (31) by means of a pivoting link (321, 322, 323) providing a rotation of the display body with respect to the fixing element around a rotational axis (38); the display body (32) comprising 10 a display (33) configured to display thermal data and/or images provided by a thermal sensing device (2); and a first surface portion (325) configured to enter in contact with a forehead of a user, when said head-mountable component (90) is positioned in front of the face of the user, so as to rotate the display 15 body (32) to a predefined angular positioning (381) around the rotational axis (38).

Abstract: The invention concerns an augmented vision system (1) comprising: a displaying device (3) comprising: a fixing element (31) for coupling the displaying device (3) to a head-mountable component (90) configured to be positioned in front of a 5 face (102) of a user (100), and a display body (32) being coupled to said fixing element (31) by means of a pivoting link (321, 322, 323) providing a rotation of the display body with respect to the fixing element around a rotational axis (38); the display body (32) comprising 10 a display (33) configured to display thermal data and/or images provided by a thermal sensing device (2); and a first surface portion (325) configured to enter in contact with a forehead of a user, when said head-mountable component (90) is positioned in front of the face of the user, so as to rotate the display 15 body (32) to a predefined angular positioning (381) around the rotational axis (38).

Abstract: An example device includes a first inductive antenna to activate a radio frequency identification (RFID) device and to receive an identification signal from the activated RFID device, a second inductive antenna to emulate the RFID device by transmitting the identification signal of the RFID device, a switch positioned between the first inductive antenna and the second inductive antenna, and a controller to selectively open the switch to decouple the first inductive antenna and the second inductive antenna or close the switch to couple the first inductive antenna and the second inductive antenna.

Abstract: An example device includes a first inductive antenna to activate a radio frequency identification (RFID) device and to receive an identification signal from the activated RFID device, a second inductive antenna to emulate the RFID device by transmitting the identification signal of the RFID device, a switch positioned between the first inductive antenna and the second inductive antenna, and a controller to selectively open the switch to decouple the first inductive antenna and the second inductive antenna or close the switch to couple the first inductive antenna and the second inductive antenna.

Abstract: A method of manufacturing an aircraft component, the component comprising a pair of covers joined by a pair of spars. The covers and spars form a closed box structure with four corners, each corner providing a transition between one of the covers and one of the spars. The method comprises: laying up a laminated sheet of fiber plies; and after the sheet has been laid up, folding the sheet to form the four corners and then joining the sheet to itself to provide the closed box structure.

Abstract: The present invention provides an aircraft structure comprising a first sub-structure, having a first box cross-section, a second sub-structure, having a second box cross-section, and a joint joining a first end region of the first sub-structure to second end region of the second sub-structure, wherein the joint comprises an overlap region where the end regions of the first and the second sub-structures overlap such that the first sub-structure is inside the second sub-structure. The present invention also provides an aircraft comprising such an aircraft structure and a method of manufacturing an aircraft structure.

Abstract: A modular structural assembly to form part of an aircraft wing that has an outer skin and a plurality of stringers is disclosed. The assembly includes a plurality of panels, each panel having a portion that forms part of the outer skin and at least one stringer integrally formed with said portion.

Abstract: This invention relates to the in-vacuum rotational device on a cylindrical magnetron sputtering source where the target or target elements of the target construction of such device are enabled to rotate without the need of a vacuum to atmosphere or vacuum to coolant dynamic seal. This invention relates to the use of the device in vacuum plasma technology where a plasma discharge, or any other appropriate source of energy such as arcs, laser, which can be applied to the target or in its vicinity would produce suitable coating deposition or plasma treatment on components of different nature. This invention also relates but not exclusively to the use of the device in sputtering, magnetron sputtering, arc, plasma polymerization, laser ablation and plasma etching. This invention also relates to the use of such devices and control during non-reactive and reactive processes, with or without feedback plasma process control.

Abstract: A structure comprising a stack of composite plies of fiber-reinforced matrix material. The structure includes reinforcing inserts and holes. Each reinforcing insert is embedded in the stack and bonded to the stack, and each hole passes through a respective one of the reinforcing inserts. A support layer is joined to each reinforcing insert. The support layer is formed from a different material to the composite plies and impregnated with the same matrix material as the composite plies. The support layer carries the inserts during the assembly of the structure, and can assist in a process of infusing and/or curing the stack.

Abstract: A method of forming composite components is described in which a composite lay-up is created using varying fibre types across the lay-up. This can adapt the lay-up to forming processes in regions of the lay-up to be formed and uses fibre types which give the greatest strength benefits in areas which do not need to be formed. Regions not requiring forming may have binders in them activated prior to a forming step or steps, after which the formed regions may be impregnated with a matrix and the component cured.

Abstract: A method of manufacturing an aircraft component, the component comprising a pair of covers joined by a pair of spars. The covers and spars form a closed box structure with four corners, each corner providing a transition between one of the covers and one of the spars. The method comprises: laying up a laminated sheet of fibre plies; and after the sheet has been laid up, folding the sheet to form the four corners and then joining the sheet to itself to provide the closed box structure.

Abstract: The present invention provides an aircraft structure comprising a first sub-structure, having a first box cross-section, a second sub-structure, having a second box cross-section, and a joint joining a first end region of the first sub-structure to second end region of the second sub-structure, wherein the joint comprises an overlap region where the end regions of the first and the second sub-structures overlap such that the first sub-structure is inside the second sub-structure. The present invention also provides an aircraft comprising such an aircraft structure and a method of manufacturing an aircraft structure.

Abstract: This invention relates to the in-vacuum rotational device on a cylindrical magnetron sputtering source where the target or target elements of the target construction of such device are enabled to rotate without the need of a vacuum to atmosphere or vacuum to coolant dynamic seal. This invention relates to the use of the device in vacuum plasma technology where a plasma discharge, or any other appropriate source of energy such as arcs, laser, which can be applied to the target or in its vicinity would produce suitable coating deposition or plasma treatment on components of different nature. This invention also relates but not exclusively to the use of the device in sputtering, magnetron sputtering, arc, plasma polymerisation, laser ablation and plasma etching. This invention also relates to the use of such devices and control during non-reactive and reactive processes, with or without feedback plasma process control.

Abstract: A modular structural assembly to form part of an aircraft wing that has an outer skin and a plurality of stringers is disclosed. The assembly includes a plurality of panels, each panel having a portion that forms part of the outer skin and at least one stringer integrally formed with said portion.

Abstract: The invention provides a cure tool 10, the tool having a working face 11 for placing a component 20 to be cured upon, wherein the tool is provided with a channel 12 along a length of the working face of the tool. The tool may be further provided with an inflatable member 15 in a length of the channel. The invention also provides a method for curing a component, a component that has been cured by the method and an aircraft comprising one or more components that have been cured by the method.

Abstract: The present invention provides a system and method for displaying exocentric views of an aircraft in a three-dimensional manner, wherein a pilot, or other user, can select from a plurality of different exocentric viewpoints. The user can thus see a three-dimensional rendering of the terrain, obstacles, and/or other images around the aircraft from vantage points other than the egocentric vantage point of most aircraft display systems. This enables the pilot to easily increase his or her situational awareness.

Abstract: A laminated automobile side glass includes an insert for engaging the window opening mechanism. The insert is molded for integration into the lamination layers, with a mechanism interface section, having a maximum thickness equal to the overall thickness of the glass. This mechanism interface section is arranged in a cutout of the window, so that the window presents a substantially continuous sheet without protrusions. The insert is formed to constitute substantially the entire engagement of the window with the opening mechanism, and to absorb the stresses imposed by vibration, opening and closing of the window, and the slamming of the automobile door.