Class / Patent application number | Description | Number of patent applications / Date published |
244132000 | Skin fastening devices | 23 |
20080302915 | Manufacturing Process Using Bladderless Mold Line Conformal Hat Stringer - Techniques for manufacturing structures that include composite hat stringers are disclosed. In one embodiment, a method of forming a composite structure includes placing a generally cured composite hat stringer on a tool, the hat stringer having a rigid mold line conformal surface for adjoining a generally uncured skin, positioning the skin adjacent to the rigid mold line conformal surface, coupling the skin to the rigid mold line conformal surface of the composite hat stringer, including applying a pressure to a surface of the skin to urge the skin into engagement with the composite hat stringer, and curing the skin. | 12-11-2008 |
20090152399 | LINE SYSTEM ARRANGEMENT IN AN AIRCRAFT OR SPACECRAFT HAVING A FUSELAGE - A line system arrangement in an aircraft or spacecraft having a fuselage includes at least one receiving region for receiving at least one component of a line system, wherein the at least one receiving region is accessible, at least in some sections, from outside the fuselage of the aircraft and spacecraft for installation and/or maintenance of the line system; and an aircraft or spacecraft with a corresponding arrangement. | 06-18-2009 |
20090173828 | Fastener - A fastener, of which severe strength is demanded and which can also be applied to a location, in which a flush surface equipment is taken into consideration, and which can be manufactured readily and quickly and reduced in manufacturing cost, is provided. A fastener ( | 07-09-2009 |
20090256028 | Fastening arrangement - The present invention discloses a two-part fastening arrangement for a surface element that is composed of a base element and a coupling element. The base element is constructed two-sided with a seat on its first side and a connecting pin projecting from its second side, with which a snap connection to the coupling element can be produced. The coupling element is also constructed two-sided with a seat on its first side and a pin receiver for the connecting pin of the base element on its second side, while the coupling element has an opening in which the pin receiver is resiliently arranged. | 10-15-2009 |
20100193638 | ANGULAR PROFILE FOR SKIN SECURING OF A BODY - The angular profile consists of sections ( | 08-05-2010 |
20100206989 | CORROSION-RESISTANT CONNECTION BETWEEN A FIRST COMPONENT AND SECOND COMPONENT - The invention relates to a connection | 08-19-2010 |
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 |
20100264273 | FUSELAGE STRUCTURE FOR AN AIRCRAFT FUSELAGE IN COMPOSITE MATERIAL AND AIRCRAFT EQUIPPED WITH SUCH A FUSELAGE STRUCTURE - A fuselage structure for an aircraft fuselage in composite material and an aircraft including such a fuselage structure. The fuselage structure provides savings in mass while allowing grounding of electric systems, and with which substantial mechanical stiffness characteristics may be guaranteed. In the fuselage structure attachment modules provide an assembling function as well as an electric function. | 10-21-2010 |
20100308171 | Method of Manufacturing Aircraft Using Temporary Fasteners - A temporary fastener and a method of attaching an aircraft skin to a frame using the temporary fastener during a step of the skin to frame assembly process. The fastener secures the skin to the structure while holes for permanent fasteners are drilled through the skin and frame; the fastener is flush mounted so that an automatic drill can drill the holes without interference. The temporary fastener can be removed after the permanent fastener holes are drilled, and before or after permanent fasteners are inserted within their respective holes. | 12-09-2010 |
20100308172 | INTERCONNECTION DEVICE CONNECTING AN AIRCRAFT INTERNAL STRUCTURE COMPONENT TO THE FUSELAGE OF THIS AIRCRAFT - An aircraft including at least one door for passengers to board the aircraft, and at least one interconnection device connecting an aircraft internal structure component and a skin of a fuselage of the aircraft, the interconnection device being positioned near an internal periphery of the door in a region subject to external knocks and including at least one region that is weakened in terms of compression so as to absorb the knocks experienced by an external face of the skin of the fuselage, the device also being configured to withstand tensile forces applies to an internal face of the skin of the fuselage by internal pressure inside the aircraft. | 12-09-2010 |
20110139932 | HIGH PULLOFF CAPABILITY HAT STRINGER - A structure may comprise a skin member and a hat stringer. The hat stringer may include a base portion and first and second webs extending outwardly from the base portion. Each one of the first and second webs may be comprised of a wrap laminate having wrap plies and a cover laminate having cover plies. The first and second webs may be interconnected by a cap. The hat stringer and skin member may be co-cured. | 06-16-2011 |
20110155854 | METHOD FOR THE MANUFACTURE OF A FIBER-REINFORCED COMPONENT, DEVICE FOR IMPLEMENTING THE METHOD, AND FIBER-REINFORCED COMPONENT - A method for the manufacture of a fiber-reinforced component includes heating a blank of a carbon-fiber-reinforced thermoplastic plastic material to at least a melting temperature of the thermoplastic plastic material; introducing the blank into an at least two-part moulding tool; forming the fiber-reinforced component by applying pressure on the blank using the moulding tool; and injecting a further thermoplastic plastic material into at least one edge region of the moulding tool so as to form an edge seal. | 06-30-2011 |
20110272525 | METHOD FOR COVERING LIGHT AIRCRAFT - The invention relates to a method for covering light aircraft and/or parts thereof with a polyester covering fabric, and to a dispersion hot-melt adhesive and to the use thereof for covering. The invention further relates to a light aircraft or to a part of the same which is covered with a polyester covering fabric by means of the method according to the invention. | 11-10-2011 |
20110284693 | Composite Stringer End Trim - A stringer having a stringer end trim that reduces pull-off forces in a stringer connection structure, including a stringer body; a stringer free edge provided on said stringer body; and a stringer end trim having at least one curvature provided in the stringer free edge forming the stringer connection structure. | 11-24-2011 |
20110297788 | SHELL COMPONENT FOR AN AIRCRAFT OR SPACECRAFT - The present invention provides a shell component for an aircraft or spacecraft. The shell component comprises a skin panel, a plurality of stringers which are arranged on the skin panel, a former which comprises a fibre composite material and is arranged over the stringers so as to cross said stringers, and a former connection structure which comprises a ductile material and a plurality of foot portions fixed to the skin panel. The foot portions each transition integrally into a shoulder portion fixed to the former over an associated fixing span, the fixing spans associated with the foot portions extending along the former substantially continuously over the stringers. | 12-08-2011 |
20120104170 | FUSELAGE ELEMENT COMPRISING A FUSELAGE SEGMENT AND JOINING MEANS - The invention relates to a fuselage element comprising a fuselage segment ( | 05-03-2012 |
20120234978 | LOAD TRANSFER DEVICES AT A STRINGER RUN-OUT - Device for transferring in an stiffened skin of an aircraft component made of a composite material the load of an stringer ( | 09-20-2012 |
20130043351 | CAP, FASTENING STRUCTURE USING THE SAME, AND AIRCRAFT INCLUDING THE FASTENING STRUCTURE - There is provided a cap capable of achieving enhanced safety by inhibiting the occurrence of sparks thereinside even if a lightning current has flowed through a fastener, a fastening structure using the same, and an aircraft including the fastening structure. A cap ( | 02-21-2013 |
20130082144 | AIRCRAFT THERMAL INSULATION - The invention provides an arrangement and methods for thermally insulating aircraft, particularly but not exclusively for when the aircraft is operating in extremely hot or cold conditions, and describes an aircraft skin construction including a foam-stiffened CFC sandwich panel forming part of the aircraft outer skin mounted to an underlying load bearing aircraft structure, wherein the panel at the mounting to the structure includes two outer layers of CFC material with an inner layer of foam material sandwiched therebetween. | 04-04-2013 |
20130112812 | Reducing Risk of Disbonding in Areas of Differing Strain - Technologies for reducing the risk of disbonding between two bonded members at areas of differing strain in the members are provided. Where the difference in strain between the two bonded members becomes excessing, movement of the members relative to each other may cause a traditional rigid adhesive to fail, resulting in a disbond or delamination in one or both composite members at the point of differing strain. Disbonding may be minimized or prevented by placing a compliant material, such as a thin sheet of rubber, between the structural members at the point of differing strain. The compliance of the material may allow the compliant material to deform enough to remain bonded to both structural members when subjected to a stress that might otherwise disbond or delaminate the bonded members. | 05-09-2013 |
20130313368 | AIRCRAFT, AIRFRAMES AND ASSOCIATED METHODS - Aircraft and airframes include a skin operatively coupled to a structural reinforcement member. The structural reinforcement member and the skin collectively define a run-out region that encompasses a terminal edge of the structural reinforcement member. Within the run-out region, the skin is more flexible than in adjacent portions of the skin. Methods include defining a region of increased flexibility of a skin relative to adjacent portions of the skin, and operatively coupling the skin to a structural reinforcement member. | 11-28-2013 |
20140117162 | CONNECTOR FOR SECURING DOUBLE SKIN PIPEWORK AND ASSEMBLY OBTAINED - A connector for securing floating double skin pipework to a structure includes means for securing to the structure, and an external body forming an outer channel and an internal tube forming an inner channel around the longitudinal axis of the connector. The means for securing to the structure includes a fixed connection backed up by a sliding connection along the longitudinal axis of the connector. The connector includes at least one bore for producing the fixed connection and at least one holding rail for producing the sliding connection. | 05-01-2014 |
20150034766 | TOOL FOR SIMULTANEOUSLY HOLDING SEVERAL ATTACHMENT CLIPS IN CONTACT WITH AN AIRCRAFT FUSELAGE FRAME ELEMENT - The subject matter disclosed herein discloses a system with attachment clips designed to fix an attachment element of an aircraft fuselage frame onto a fuselage skin and/or to stiffeners fitted onto this fuselage skin, the system also comprising tooling elements arranged alternately with the clips that they connect to each other, in order to reduce the fabrication time and cost of an aircraft fuselage. | 02-05-2015 |