A fuselage structure splice may include a panel having an edge and a strap connected to the first panel along the panel edge. A strap surface not in contact with the panel tapers toward the panel with distance from the panel edge. A stringer is mounted on the panel and extends away from the edge of the panel and has a flange mounted to the panel. A fitting has a stringer base portion and a strap base portion. The stringer base portion is connected to the stringer flange and extends along a first line extending in a plane normal to the panel edge. The strap base portion of the fitting is mounted on the strap surface and extends along a second line in the plane. The second line is transverse to the first line and the strap base portion of the fitting has a constant thickness along the second line.

A joining method for connecting at least two thermoplastic workpieces is provided to permit the joining even of non-transparent carbon fiber reinforced plastics parts by means of laser welding, in which a splice is produced at the edge regions of the workpieces and the workpieces are subsequently positioned relative to one another in such a manner that the opposite splice regions bound a seam region. Connecting bodies are then inserted into the seam region and heated by means of local heat input by laser beam such that a fixed integrally bonded connection forms between the workpieces and the connecting bodies.

Methods and apparatuses for performing automated operations using a high-density robotic cell. An apparatus comprises a first plurality of robotic devices; a second plurality of robotic devices; and a control system. Each of the second plurality of robotic devices is coupled to a single function end effector. The control system controls the second plurality of robotic devices to concurrently perform tasks at a plurality of locations on an assembly, while the first plurality of robotic devices independently maintain a clamp-up at each of the plurality of locations.

A tolerance compensation subassembly in the form of a tolerance compensation element or a tolerance compensation region to improve the production, maintenance and repair of aircraft. The tolerance compensation subassembly contains an actuator which is formed from an electro-active polymer so that the tolerance compensation subassembly is electrically switchable between a fixed state and a non-fixed state. As a result, automation of the assembly of aircraft components on each other can be enabled or facilitated.

To provide an aircraft that can efficiently improve speed performance and fuel efficiency, the aircraft is an aircraft capable of forward flight and hovering, and includes a lift generating part, a frame for holding the lift generating part, and a loadable object provided on the frame and to be mounted. The front projection area of the frame and the mounting part during forward flight is smaller than the front projection area of the frame and the mounting part during hovering.

A system for modular aircraft includes at least a common component, wherein the at least a common component includes at least a flight component. The system includes at least a modular component, wherein the at least modular component includes at least a fuselage component and a collar component. The system includes at least an interface component, wherein the at least an interface component is configured to connect the at least a common component at a first end to the at least a modular component at a second end.

A wall covering panel for a nose of an aircraft. The panel comprises a rigid carrying framework preferably having an alveolar structure obtained by 3-D printing, a décor carried by the carrying framework and an acoustically and thermally insulating padding fixed to the carrying framework, and also attachments for fixing the carrying framework to the primary structure of the aircraft. Preferably, the panel also integrates systems, such as electrical route portions or ventilation route portions that traverse the panel from one side to the other or lead to an outlet equipment item also integrated in the panel. Only the carrying structure of the panel, which carries the décor, the insulating padding and any route portions and equipment items, is fixed to the primary structure of the aircraft. The number of attachments is low; the kitting-out and the finishing of the nose of the aircraft are greatly simplified.

A method for constructing at least two fleets of aircraft of different families for which each aircraft has a front part comprising windows, a framing of the windows and a windshield front fairing, comprising, for each aircraft, constructing a module composed of the framing of all of the windows allowing outward visibility from the cockpit and of the windshield front fairing whose form is identical and constant for all the aircraft of the fleets and independent of a form of the fuselages thereof, and constructing a section of fuselage of which at least a part of an edge of the fuselage is of a form identical to an edge of the module, such that the module can be assembled directly with the contiguous fuselage section, whatever the aircraft of the fleets.

A method for producing a structural section of a vehicle comprises the steps of providing multiple separate skin panels of a fiber-reinforced plastic having an inner side, an outer side and a border running peripherally around the respective skin panel; arranging at least one stiffening component of a fiber-reinforced plastic on each skin panel, on the respective inner side; integrally connecting the respective at least one stiffening component to the skin panels concerned to form a structural component; arranging at least two structural components on a carrier, so that at least regions of the borders of the structural components concerned are in surface-area contact; and integrally connecting the regions of the borders that are in surface-area contact to one another.

A fuselage for an aircraft includes a pressure deck assembly extending along a roll axis of the fuselage. The pressure deck assembly includes longitudinal beams and a pressure deck. The longitudinal beams extend lengths along the roll axis of the fuselage. The pressure deck extends between the longitudinal beams along the lengths of the longitudinal beams. The pressure deck is compliant along a pitch axis of the fuselage. The fuselage includes a bulkhead extending along a yaw axis of the fuselage. The bulkhead is joined to the pressure deck assembly at a corner joint. The fuselage includes a compression chord extending a length along the pitch axis of the fuselage. The compression chord is joined between the pressure deck assembly and the bulkhead at the corner joint such that the compression chord extends on an outside of the corner joint.