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 |
20100258676 | AIRCRAFT INCLUDING STIFFENER EDGE JUNCTIONS AND METHOD FOR PRODUCING ONE SUCH AIRCRAFT - A system for transmitting stresses at the intersection between a reinforcing frame and a stiffener in a fuselage and to a method for producing one such system. An aircraft fuselage includes stiffeners interrupted by reinforcing frames. At aforementioned interruptions, the stresses experienced by the stiffeners must be transmitted despite the presence of the reinforcing frames. Known solutions are difficult to manufacture and install and do not provide a simple stress transmission path when produced solely from composite materials. In order to solve this problem, the disclosed embodiments include the creation of battens that cover the ends of consecutive sections of a stiffener and the skin of the fuselage, extending under the reinforcing frame in order to join aforementioned two consecutive sections. | 10-14-2010 |
20100297390 | SELF-STABILISED STIFFENER ENABLING ELEMENT RECOVERY - A stiffener for a structure submitted to tensile and/or compression and/or shear stresses, that includes a shaped section including: a contact area with an element to be stiffened having a closed cross-section and providing stability, the aforementioned area including first and second legs; and a core normal to the element to be stiffened that provides a support surface capable of element recovery, the aforementioned core being formed by one of the two legs. Application in aircraft structures. | 11-25-2010 |
20130015602 | PROCESS FOR THE PRODUCTION OF A DOUBLE-CURVED PANELAANM BERNADET; PhilippeAACI ColomiersAACO FRAAGP BERNADET; Philippe Colomiers FRAANM GIUSEPPIN; LaurentAACI FinhanAACO FRAAGP GIUSEPPIN; Laurent Finhan FR - A process for the production of an aircraft panel made of double-curved composite material, with the panel being obtained from a three-dimensional preform that includes fibers that are distributed in a defined arrangement, includes manufacturing a flat fiber preform ( | 01-17-2013 |
20130146709 | AIRCRAFT NOSE AND NOSE LANDING GEAR BAY STRUCTURE - An aircraft nose structure includes a fuselage, a floor for a pressurized space and a nose landing gear bay arranged under the floor, on the opposite side to the space. The bay includes walls that form a pressure barrier, of which there are two lateral panels mechanically secured to the floor by load-reacting members, an upper panel adjacent to the floor and extending between the lateral panels, and a rear panel extending between the upper panel and the fuselage. | 06-13-2013 |
20130146710 | AIRCRAFT NOSE STRUCTURE WITH LANDING GEAR COMPARTMENT - An aircraft nose structure includes a fuselage and a pressuretight bulkhead fixed at its periphery to the fuselage and transversely dividing the fuselage into a pressurized upper zone and an unpressurized lower zone for accommodating retractable nose landing gear. The pressuretight bulkhead includes a floor of the pressurized upper zone, and a substantially flat rear panel extending between a rear edge of the floor and the fuselage. The floor and the rear panel are fixed laterally to the fuselage. The fuselage includes an exterior wall and reinforcing transverse frames to which the exterior wall is fixed. In line with the pressuretight bulkhead, at least some of the transverse reinforcing frames extend along the outline of the pressurized upper zone and constitute members that reinforce the pressuretight bulkhead. | 06-13-2013 |