Patent application number | Description | Published |
20080292849 | LAMINATE SHEET, IN PARTICULAR FOR FUSELAGE SKIN SHEETS FOR AIRCRAFTS - A laminate sheet, in particular for use as a fuselage skin includes thin aluminium alloy sheets layered on top of one another with each two aluminium alloy sheets being adhesively bonded to one another at least in regions by an adhesive layer which includes at least one unidirectional fibreglass insert impregnated with a curable synthetic resin. | 11-27-2008 |
20100192377 | METHOD FOR PRODUCING A FUSELAGE AIRFRAME OF AN AIRCRAFT - Disclosed is a method for producing a fuselage of an aircraft, wherein several fuselage sections that are arranged one behind another are joined together, comprises the following steps:
| 08-05-2010 |
20100230539 | PRESSURE BULKHEAD AND METHOD FOR SUBDIVISION OF AN AIRCRAFT OR SPACECRAFT - The present invention provides a pressure bulkhead for subdivision of an aircraft or spacecraft into an internal and an external pressure region. The pressure bulkhead comprises a pressure plate having an edge shaped so as to correspond to an inner contour of the aircraft or spacecraft, a supporting means which tiltably supports the edge on the inner contour, and a seal which seals the edge with the inner contour. A further aspect of the invention provides a method for subdivision of an aircraft or spacecraft into an internal and an external pressure region. Firstly, a pressure plate is provided that has an edge shaped so as to correspond to an inner contour of the aircraft or spacecraft. In further steps, the edge is tiltably supported on the inner contour and sealed with the inner contour. | 09-16-2010 |
20100237194 | TRANSVERSE SPLICING PLATE FOR CREATING A FUSELAGE, AND A METHOD FOR CONNECTING TWO, IN PARTICULAR WOUND, CFP FUSELAGE SECTIONS - A transverse splicing plate for producing a fuselage of an aircraft by connecting several CFP fuselage sections that have in particular been produced in the winding method, in each case by forming a transverse seam, wherein the flexible transverse splicing plate is of a multilayer construction, in other words it comprises a multitude of plate segments arranged one above the other, wherein each of the plate segments comprises a multitude of longitudinal slits, each being able independently of each other to make small radial bending movements in order to cause tolerance compensation in radial direction between the fuselage sections to be joined, in which tolerance compensation a sliding movement between the sub-plates of the plate segments arranged one above the other takes place in axial direction of the barrel-shaped fuselage sections, and wherein on the inside the ends of the fuselage sections comprise chamfers; as well as a method for producing a connection between two CFP fuselage sections, which have preferably been produced in the winding method, by means of a transverse splicing plate according to the invention. | 09-23-2010 |
20100237195 | STRUCTURAL COMPONENT AND METHOD FOR STIFFENING AN EXTERNAL SKIN - The present invention provides a structural component for an aircraft or a space craft having an outer skin and a first reinforcing element which runs on the outer skin along a first spatial direction. A second reinforcing element runs over the first reinforcing element in a second spatial direction. A foot element supports the second reinforcing element on the outer skin, the foot element having a feed-through opening in which the first reinforcing element is held in a positive manner. From another point of view, a method is provided for reinforcing an outer skin of an aircraft or space craft, in which a first reinforcing element is attached to the outer skin along a first spatial direction. A foot element having a feed-through opening is attached over the first reinforcing element such that the first reinforcing element is held positively in the feed-through opening. A second reinforcing element is attached to the foot element in a second spatial direction over the first reinforcing element. | 09-23-2010 |
20100252684 | FUSELAGE CELL STRUCTURE OF AN AIRPLANE FOR THE SIMPLIFIED INSTALLATION AND ATTACHMENT OF FASTENERS FOR FASTENING CONDUITS - The invention relates to a fuselage cell structure of an aircraft for the simplified installation and attachment of at least one fastener for at least one conduit, the fuselage cell structure having a large number of reinforcing elements formed in particular using an aluminium alloy material. According to the invention, the reinforcing elements within the fuselage cell structure are provided with at least one groove in which the fasteners can be secured by producing a combined pressing and clamping fit creating a positive fit at least in certain regions. For this purpose, the fasteners can have at the lower face thereof, for example, two retaining feet which can be spread apart and attached by driving a fixing element into the groove. The reinforcing elements are continuous stringers preferably produced by extrusion and cross-bars, the required grooves being simultaneously extruded during the production process. | 10-07-2010 |
20110233334 | STRUCTURE, ESPECIALLY A FUSELAGE STRUCTURE OF AN AIRCRAFT OR A SPACECRAFT - The present invention provides a fuselage structure ( | 09-29-2011 |