Patent application number | Description | Published |
20100125967 | WIPER BLADE WITH ELECTROMAGNETIC COMMAND - The wiper blade for a surface of the type with a dual curvature, the wiper blade including a flexible blade element and a means of applying a pressing force to at least one point of the blade element in a direction Z mostly normal to the surface, also including means of varying the pressing force over time, at least some of the points, between pre-chosen positive and negative limit values, and means of commanding the pressing force. These means for bringing about local pressure or lift are electromagnetic. | 05-27-2010 |
20100127126 | WATER-RESIST MEANS FOR AIRCRAFT WINDOWS - The subject matter of the disclosed embodiments is a device for mounting a window glass including a seal covering a peripheral edge of the window glass and provided with a strip bearing against a peripheral flat of a frame of the window. The seal includes a flange engaging in the recess of the window and is provided with a squeegee lip bearing against the edge of the frame. | 05-27-2010 |
20100140410 | AIRCRAFT ICING INDICATOR - The icing indicator for an aircraft, of the type that can be directly and visually read by a pilot, includes means of installation at the surface of the fuselage and projecting therefrom, in combination with an already-existing device positioned above a through-hole in the fuselage, the device being modified to allow a power cable that powers the icing indicator to pass through the fuselage within its fastening. The icing indicator is preferably combined with a rain repellent spray device or on the spindle about which the windscreen wiper rotates. | 06-10-2010 |
20100163676 | AIRCRAFT WITH WINDSHIELD GLASS PLATES INTERCHANGEABLE BETWEEN DIFFERENT TYPES - An aircraft in which it is possible to replace windshield panes of the mineral type with windshield panes of the organic type and vice versa, without the frame of the aircraft structure having to be modified. The pane is held in place on the frame by a window pane retainer specific to the pane. The frame has no through-holes opening to the outside of the aircraft for fastening the pane. The window pane retainer specific to a pane of the organic type has pins passing through the acrylic panes. The disclosed embodiments also relate to a method of replacing a pane of a first type with a pane of a second type. | 07-01-2010 |
20100224729 | Device for installing windshield panes - A fastening device for at least one pair of window panes, especially aircraft windshield window panes, each having a window pane retainer equipped with a frame that is applied to the borders of receptacle openings for the window panes, wherein the frames have a pair of posts facing one another provided with matching profiles that can mate the aforementioned posts, one inside the other, in a fastening line of the window pane retainer on the common border to the openings that receive the pair of panes. | 09-09-2010 |
20110056718 | ANTI-LIGHTNING SYSTEM AND AIRCRAFT COMPRISING SUCH A SYSTEM - An anti-lightning system for a composite structure having an external surface liable to be subjected to an air flow, the aforementioned system including at least one electrically conducting strip and fasteners fastening the aforementioned strip to the structure, the aforementioned strip being electrically connected to an electrical earth for removing current. According the disclosed embodiments, the aforementioned strip has a shape intended to collaborate with a housing created at the aforementioned external surface so that the external surface of the strip lies flush with the aforementioned external surface of the structure, and the aforementioned fasteners include an upper part flush with the external surface of the strip. | 03-10-2011 |
20110278396 | MODULAR FLOOR SECTION FOR AIRCRAFT - The floor section for a vehicle cabin consists of a juxtaposition of profiled elements ( | 11-17-2011 |
20120132747 | UNDER-FLAP STIFFENER FOR AIRCRAFT - An assembly of longitudinal structural stiffeners for an aircraft including, in a front portion of the fuselage, a windscreen that is slightly recessed relative to the airplane nose, and a fuselage portion extending in alignment with the airplane nose up to the base of the windscreen. The stiffeners include a bending-resistance main plane and are arranged under the flap and connected to the fuselage along a force transfer line. For one or more of the stiffeners, the bending resistance main plane substantially coincides, at least a certain number of points of the fuselage force transfer line, with the plane predetermined by the local normal to the fuselage surface and the longitudinal axis of the airplane. A method is also provided for calculating the shape of the stiffeners. | 05-31-2012 |
20120325344 | DEVICE AND METHOD FOR MAINTAINING PARALLELISM BETWEEN THE TWO GLAZINGS OF AN AIRCRAFT DOUBLE GLAZING - Device intended for a double glazing including at least one outer glazing and one inner glazing separated by an intermediary space filled with a gas, used to isolate an inside environment from an outside environment, a pressure variation being liable to occur between these environments, for example in the case of an aircraft in flight, | 12-27-2012 |
20130009007 | Intermediate support structure for the cockpit of an aircraft - An intermediate support structure ( | 01-10-2013 |
20130042428 | WINDSCREEN-WIPER BLADE HAVING MODIFIABLE VERTICAL FLEXIBILITY - Wiper blade for a surface of double curvature type, the said wiper blade including a flexible longitudinal wiper and means for exerting a bearing force at at least one point of the said wiper along a direction Z mainly normal to the surface, also including a longitudinal part, attached to the wiper at several points, and means to vary over time and in at least one segment of the longitudinal rod the rigidity in bending of this longitudinal rod in a plane XZ normal to the surface between previously chosen values. | 02-21-2013 |
20130134259 | FRONT STRUCTURE OF AN AIRCRAFT FUSELAGE COMPRISING LANDING GEAR - A front structure of an aircraft fuselage comprising landing gear pivoting about a main shaft and a stay shaft. The front structure also comprises a first reinforcing frame and a second reinforcing frame, the main shaft and the stay shaft being respectively connected to the first and second frames, and a device for the mechanical connection and transfer of forces connecting the stay shaft and the main shaft and transferring to the main shaft a portion of the forces induced by the wheels of the landing gear onto the stay shaft, the second frame and said device being perpendicular to one another. | 05-30-2013 |
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 |
20130306795 | AIRCRAFT FUSELAGE FRAME ELEMENT - The subject of the invention is an aircraft fuselage frame element ( | 11-21-2013 |
20130320143 | CABIN WINDOW WITH PLANNED DEFORMATION, METHOD OF MANUFACTURING SUCH A WINDOW AND AIRCRAFT COMPRISING SUCH A WINDOW - The present invention relates to an aircraft window, of the type including a holding frame for securing the window to the fuselage of an aircraft and at least one pane mounted in the holding frame by a sealing system, the at least one pane having an inner surface and an outer surface, characterized in that: the pane includes, in a first state called the rest state, at least one concavity in its outer surface when there is no pressure difference between the outer surface and the inner surface of the pane, and the at least one concavity of the pane is at least partially eradicated in a second state in which there is a pressure difference between the outer surface and the inner surface of the pane. | 12-05-2013 |
20140069984 | SYSTEM FOR FRICTION STIR WELDING INCLUDING A MOBILE COUNTER-BEARING - System for friction stir welding of two parts which includes a welding unit which includes at least one welding head fitted with a rotating pin and a counter-bearing unit which has a support surface to support the parts against a pressure exerted by the welding head, and wherein each welding head can be moved relative to the support surface in a first direction parallel to an axis of rotation of the rotating pin and in a second direction orthogonal to the axis of rotation, and wherein the support surface can be moved in the second direction and is formed of two coaxial clamp rollers which are set apart from each other. | 03-13-2014 |
20140069987 | PROCESS AND SYSTEM FOR FRICTION STIR WELDING OF A STIFFENER ON AN AIRCRAFT PANEL - Process for linear transparency friction stir welding of a flange of a stiffener onto at least one panel for an aircraft, wherein a weld bead is made along the flange of the stiffener and wherein the weld bead extends in cross-section from a first lateral edge to an opposite second lateral edge of the stiffener flange. System for the implementation of the above welding process, which includes three welding heads arranged as a triangle, each of which includes a rotating pin as well as a shoulder extending at the base of said rotating pin. | 03-13-2014 |
20140186559 | SELF-STIFFENED SKIN FOR AIRCRAFT FUSELAGE INCLUDING STRINGERS WITH A CLOSED SECTION AND ASSOCIATED MANUFACTURING METHOD - Simplification of the manufacture of composite material fuselages for aircraft, as well as mass reduction of fuselage sections and space optimization inside such fuselage sections. To accomplish this, it is proposed to use stringers of a new type which have a closed transverse section, and which are thus able to be self-positioned relative to one another by being positioned edge-to-edge on a stringer supporting structure, such as the outer surface of a mandrel. The installation of the stringers in grooves of conjugate shape is by this means made unnecessary. The stringers have cut-outs located between circumferential frames, and are able to house utility systems. | 07-03-2014 |
20140319274 | AIRCRAFT INCLUDING A PASSENGER CABIN EXTENDING AROUND A SPACE DEFINED OUTSIDE THE CABIN AND INSIDE THE AIRCRAFT - The sealed bottoms of aircraft passenger cabin have to be fastened with heavily sized fasteners so as to withstand loads induced by the cabin pressurization. Besides, the increase in aircrafts seating capacity makes an increase in passenger cabin widths of interest. Such a width increase however makes the structure delimiting passenger cabin less resistant to efforts induced by the cabin pressurization. The present invention proposes an aircraft wherein the structure delimiting passenger cabin extends over 360 degrees around a space defined outside structure. The invention allows structure to be more resistant to loads induced by the cabin pressurization, while allowing to reduce or even to avoid the need for a sealed bottom, and while allowing to increase the space available for passengers. | 10-30-2014 |
20140346276 | SUPPORT PLATE FOR THE PASSAGE OF SYSTEMS BETWEEN TWO ZONES WITH DIFFERENT PRESSURIZATIONS OF AN AIRCRAFT - A support plate for the passage of systems between two zones at different pressurizations of an aircraft, in the region of a bulkhead separating the two zones. The support plate comprises a connection plate including at least one retaining element and at least one sealing joint and is provided with a plurality of holes intended for the passage of an assembly of systems which have to pass through said bulkhead. | 11-27-2014 |
20140361924 | ON-BOARD METEOROLOGICAL RADAR HAVING A ROTATING ANTENNA - A meteorological radar installed on board an aircraft, including a mechanical support fixed to a bulkhead of a nose of the aircraft, wherein an antenna is mounted on the mechanical support to enable turning mobility around an axis of rotation. The antenna includes a pedestal, on which at least one blade, extending radially along the axis of rotation, is installed. A free side of the blade, along which a plurality of radiating elements is distributed, perceptibly has the shape of a portion of conic in a plane including the axis of rotation. Because the blade is mobile only in rotation along the axis of rotation, and the selection of the emission/reception direction is performed electronically, not mechanically, the space and length requirements of the meteorological radar are fixed, whether the meteorological radar is in operation or not, and are determined based on the eccentricity and parameter of the conic. | 12-11-2014 |