Patent application number | Description | Published |
20100032523 | AIRCRAFT FUSELAGE MADE FROM LONGITUDINAL PANELS AND METHOD OF PRODUCING SUCH A FUSELAGE - The invention relates to an aircraft fuselage comprising a nose cone, a tail section and a central section, the central section comprising longitudinal panels assembled directly with one another, at least one of these longitudinal panels having a length corresponding to the distance between the nose cone and the tail section in order to connect said nose cone with said tail section. | 02-11-2010 |
20100044513 | AIRCRAFT CABIN WINDOW ASSEMBLY METHOD - A method for assembling a cabin window to a bay in a side wall of an aircraft fuselage, the cabin window including an outer transparent element and at least one inner transparent element. A non-through hole is made in a portion of the side wall along the edge of the bay. Subsequently, the outer transparent element is positioned in the bay from the exterior of the fuselage. The element includes a first part which has a diameter greater than that of the bay and which is shaped to co-operate with the above mentioned portion such as to block the outer transparent element in the bay both laterally and longitudinally. A second part of the outer transparent element has a groover that projects into the fuselage. The outer transparent element and the at least one inner transparent element are welded to the fuselage using a strap which presses a seal against at least the fuselage and the inner wall of the groove. | 02-25-2010 |
20110017870 | SECTION OF AIRCRAFT FUSELAGE AND AIRCRAFT INCLUDING ONE SUCH SECTION - The invention relates to a section of fuselage for an aircraft, including frames and bays for receiving cabin windows. According the the disclosed embodiments, at least some of the frames include at least one frame segment that surrounds at least one bay, the frame segment having two branches that are disposed to the side of the bay. The ends of the branches are attached to each of the ends of the frame segment such as to form a Y. | 01-27-2011 |
20110185555 | METHOD FOR THE ORBITAL ASSEMBLY OF AIRCRAFT SECTIONS MADE OF COMPOSITE MATERIAL - A method for assembling two structural elements, at least one of the two structural elements being tube-shaped and including a skin made of a fiber-reinforced composite material. The ability of the element to adapt to the shape and perimeter of a junction interface is improved by providing longitudinal grooves distributed on the circumference of the junction interface. The grooves are of a sufficient length to provide the junction interface with the flexibility to accommodate, through relative radial movement of each portion located between two grooves, differences in shape and perimeter among the junction interfaces of the two structural elements. | 08-04-2011 |
Patent application number | Description | Published |
20100206986 | CURRENT RETURN NETWORK ELEMENT FOR AN AIRCRAFT - The invention relates to a current return network element ( | 08-19-2010 |
20110001006 | Process for making an aircraft having a floor - The method of fabricating an aircraft comprises the following steps:
| 01-06-2011 |
20110001008 | Aircraft floor of optimized compactness - An aircraft floor portion includes crossmembers. Each crossmember comprises a top partial crossmember and a bottom crossmember, with at least one gap being left between the top partial crossmember and the bottom partial crossmember of each crossmember. | 01-06-2011 |
20110147521 | METHOD OF CONSTRUCTING A FIXED-WING AIRCRAFT - The following steps are performed in the method of constructing an aircraft: taking a subassembly comprising two wings that are rigidly fastened together, and fitting it to a fuselage wall; and fastening the subassembly to the wall by means of fastener elements that are distinct from the subassembly and that present main axes that are vertical. | 06-23-2011 |
20120061513 | AIRCRAFT INCLUDING FLOOR SUPPORT CROSS-MEMBERS WITH BEARINGS INCLUDING A FLEXIBLE MATERIAL CONNECTING THE CROSS-MEMBER TO THE SUPPORT - An aircraft including: at least one floor cross-member; at least one support carrying the cross-member; and at least one bearing including at least one flexible material and connecting the cross-member to the support. | 03-15-2012 |
20120066907 | INSTALLATION FOR MAKING A FUSELAGE PORTION OF AN AIRCRAFT - In the method of making an aircraft a mandrel is caused to pass through frames carried by a magazine; and as it passes through, the frames are transferred onto the mandrel. | 03-22-2012 |
20120104170 | FUSELAGE ELEMENT COMPRISING A FUSELAGE SEGMENT AND JOINING MEANS - The invention relates to a fuselage element comprising a fuselage segment ( | 05-03-2012 |
20120211602 | FRAME FOR AN OPENING PROVIDED IN AN AIRCRAFT FUSELAGE - A frame of a door that is provided at an opening made in a fuselage of an aircraft that is delimited by a skin, whereby the frame that includes an upper longitudinal stiffener and a lower longitudinal stiffener provides the connection between two vertical substructures ( | 08-23-2012 |
20130118301 | AIRCRAFT COMPRISING A LINK ROD ONE PART OF WHICH IS MADE OF COMPOSITE - The link for an aircraft comprises at least two portions respectively made of metal and of composite material together forming a common section of a middle segment of the link in a plane perpendicular to a longitudinal direction of the link. | 05-16-2013 |
20130157017 | SECURE BEAM, IN PARTICULAR STRONG FRAME OF FUSELAGE, AND AIRCRAFT FUSELAGE PROVIDED WITH SUCH FRAMES - An arrangement for freeing the structures of fail-safe type from the damage tolerance criterion and to allow a significantly improved fatigue resistance, while producing a weight saving. This is provided by forming a composite hybrid structure in a configuration that makes it possible to combine the advantages of metal and of composite material. In a secure hybrid structure, at least two longitudinal structural spars are joined back to back by fastening means. One of the spars is metal and equipped with stability partitions, whereas another spar is made of a composite material with carbon fibers oriented in the direction of the forces to be predicted such that this spar exhibits a rigidity equivalent to that of the metal spar. | 06-20-2013 |
20130192433 | Method for disassembly of two elements welded by ultrasound and element able to be welded by ultrasound to another element to the implementation of said method - A method for disassembling two ultrasonically welded elements, one of the elements comprising, at a surface opposite the other element, an energy director that concentrates the heating during ultrasonic welding and forms a material junction between the two assembled elements after the ultrasonic welding. The method includes the steps of positioning a wire between the two assembled elements, so as to be secant to the energy director, said wire having suitable mechanical characteristics allowing it to cut the junction formed by the energy director and moving the wire between the two assembled elements so as to cut said junction. | 08-01-2013 |
20130334365 | AIRCRAFT WITH REDUCED ENVIRONMENTAL IMPACT - An aircraft with reduced environmental impact includes two turboprop engines mounted on the back of the aircraft at the rear thereof, and one acoustic masking device per turboprop engine. The acoustic masking device includes a masking element, such as a flap, which can move between a position in which it is retracted into the wing, and a position in which it is extended toward the rear of the wing. In the extended position, the flap intercepts the noise area generated toward the front by the turboprop engine, so as to reduce the perception of noise on the ground. | 12-19-2013 |
20140151500 | DEVICE FOR INTERMEDIATE FASTENING BETWEEN AN AIRCRAFT FUSELAGE AND AN AIRCRAFT LANDING GEAR - A device for intermediate fastening between an aircraft fuselage and an aircraft landing gear is provided. The device includes at least one semi-open support structure comprising a pair of webs, which are substantially parallel to each other. The webs comprise first support means intended to receive the main pivot shaft of the landing gear and second support means intended to receive the stay joint or joints of the landing gear. The device includes two support structures linked together by a central box structure. The central box structure includes a front wall, a rear wall and linking walls linking those two walls. | 06-05-2014 |
20140175215 | FLYING WING WITH SIDE CARGO COMPARTMENT - Optimization of the use of the available volume in a flying wing for commercial passenger transport, in particular for short- or medium-haul routes. A flying wing is provided including a passenger cabin together with at least one hold for the transport of luggage and/or goods, in which the hold is positioned laterally relative to said passenger cabin. | 06-26-2014 |
20140175218 | AIRPLANE WITH A FUSELAGE HAVING SIDE OUTGROWTH DELIMITING STORAGE SPACES - An aircraft of which the transversal section of the fuselage is reduced optimally at the price of a reduced carrying capacity of luggage or merchandise but adapted to short- and medium-haul type routes. The fuselage has for this purpose lateral protuberances defining storage areas arranged on either side of a passenger cabin and able to house luggage and/or merchandise, and/or onboard service equipment, and/or removable fuel tanks. | 06-26-2014 |
20140263836 | FISH JOINT DEVICE HAVING AN IMPROVED MECHANICAL HOLD - The invention relates to a fish joint device intended to attach securely first and second structural elements of an aircraft to one another, having two fishplates positioned either side of the structural elements, and attached to them by a set of fishplate through fastenings. According to the invention, the fish joint device includes at least one intermediate fish joint plate which is positioned between one of said fishplates and said structural elements which said intermediate plate partly covers, and which is attached to these elements by a set of intermediate plate through fastenings which includes the set of fishplate through fastenings. | 09-18-2014 |