| AIRBUS OPERATIONS (SAS) Patent applications |
| Patent application number | Title | Published |
|---|
| 20120128443 | DEVICE FOR MECHANICALLY LINKING AT LEAST TWO PARTS HAVING COAXIAL BORES - A device for mechanically linking with a rotating axis at least two parts, which is configured to extend in a longitudinal direction in coaxial bores formed respectively in the at least two parts hinged in relation to each other around the axis. The device includes: a cylindrical body including at least one end portion including at least one longitudinal slot, the cylindrical body including in the longitudinal direction a cylindrical bore extended by a frusto-conical bore extending in the at least one end portion configured to be located in another bore; an insert of frusto-conical shape substantially complementary to the frusto-conical bore, the insert including a tapped aperture extending in the longitudinal direction when the insert is accommodated in the frusto-conical bore, and a screw with a threaded end configured to cooperate by screwing with the tapped aperture of the insert allowing to lock the cylindrical body in the another bore and making a rotoide joint around axis. | 05-24-2012 |
| 20120126060 | METHOD OF FABRICATING AN AIRCRAFT PART BY INFUSING RESIN - The method of fabricating an aircraft part comprises the steps of placing in a stack comprising a preform at least one layer of a material that presents permeability to a predetermined resin that is less than the permeability of a portion of the preform that is the closest to the layer; and placing a resin presence sensor on a side of the layer that is remote from the preform. | 05-24-2012 |
| 20120126059 | SEALING DEVICE BETWEEN A CROSS MEMBER AND INSULATION BLANKET PROVIDED AT AN AIRCRAFT FUSELAGE - An insulation blanket to be connected at the inside surface ( | 05-24-2012 |
| 20120119761 | METHOD OF ELECTRICALLY CHARACTERIZING A COMPOSITE MATERIAL FOR MANUFACTURING AN AIRCRAFT - In the method of electrically characterizing a composite material for manufacturing an aircraft, the following steps are performed: compressing two spacers against at least one test piece made of a composite material; determining an electrical resistance value for the assembly formed by the spacers and the test piece; and deducing from said value a value for the electrical resistance of the composite material. | 05-17-2012 |
| 20120119572 | AIRCRAFT INCLUDING PIECES OF ELECTRICAL EQUIPMENT AND PARTS MADE OF COMPOSITE MATERIAL - The aircraft includes at least one piece of equipment and a composite material part to which the equipment is connected. It is arranged in such a manner that a fault current circuit of the equipment passes via the part. | 05-17-2012 |
| 20120106114 | BACKPLANE ELECTRONIC CIRCUIT BOARD OF AN ELECTRONIC APPARATUS, IN PARTICULAR FOR AN AIRCRAFT - A backplane electronic circuit board of an electronic apparatus ( | 05-03-2012 |
| 20120104184 | AIRCRAFT COMPRISING A DEVICE FOR INFLUENCING THE DIRECTIONAL STABILITY OF THE AIRCRAFT, AND A METHOD FOR INFLUENCING THE DIRECTIONAL STABILITY OF THE AIRCRAFT - An aircraft including a device for influencing the directional stability of the aircraft is provided. The device includes a control-input device; a flight control device; a sensor device for acquiring the rotation rates, including the yaw rates, of the aircraft; and at least one actuator, which is coupled with ailerons, spoilers, an elevator and a rudder. The flight control device includes a control function generating adjusting commands for the actuators for controlling the aircraft according to control commands. The aircraft includes two tail-mounted flaps, each including an actuator connected with the flight control device, situated symmetrically to each other and on opposite sides of the fuselage, and movable between retracted and extended positions. The control function is designed such that the adjusting commands that are generated on the basis of the control commands depending on the acquired rotation rates include adjusting commands to the actuators of the tail-mounted flaps. | 05-03-2012 |
| 20120104173 | DEVICE FOR SHUTTING A JETTISONING CIRCUIT OF AN AIRCRAFT - A device for shutting an aircraft jettisoning circuit includes a coupling endpiece. The endpiece carries a sealing gasket and means suitable for modifying a dimension of the gasket. | 05-03-2012 |
| 20120104170 | FUSELAGE ELEMENT COMPRISING A FUSELAGE SEGMENT AND JOINING MEANS - The invention relates to a fuselage element comprising a fuselage segment ( | 05-03-2012 |
| 20120104167 | FUSELAGE ELEMENT COMPRISING A FUSELAGE SEGMENT AND JUNCTION MEANS, FUSELAGE PORTION, FUSELAGE AND AIRCRAFT - The invention relates to a fuselage element ( | 05-03-2012 |
| 20120104160 | AERODYNE INCLUDING MOTORIZED UNDERCARRIAGES - The aerodyne, e.g. an airplane, includes: an auxiliary power unit suitable for producing electricity; a first electricity distributor connected to the unit; at least one flight propulsion engine including an electricity generator; at least one undercarriage motor, the motor enabling the aerodyne to taxi; and a second electricity distributor connected to the generator and to the undercarriage motor in order to transmit electricity from the generator to the motor independently of the first distributor. | 05-03-2012 |
| 20120102842 | AIRCRAFT LATCH COMPRISING A HOOK AND A HANDLE - An aircraft latch including an operating lever; and adjustable means for adjusting an angle of inclination of the lever in a closed position of the latch, the means being controllable on the lever. | 05-03-2012 |
| 20120102719 | ATTACHMENT INTERFACE DEVICE FOR ATTACHING MOBILE EQUIPMENT TO AN AIRCRAFT STRUCTURE - An interface device for attaching mobile equipment ( | 05-03-2012 |
| 20120101793 | METHOD, DEVICES AND COMPUTER PROGRAM FOR ASSISTING IN THE DIAGNOSTIC OF AN AIRCRAFT SYSTEM, USING FAILURE CONDITION GRAPHS - The invention in particular has as an object aid in diagnosis of a system of an aircraft, comprising a plurality of sub-systems at least one of which comprises means for monitoring and notification of at least one detected event, using graphs of feared events. After a message of notification of occurrence of the said detected event has been received ( | 04-26-2012 |
| 20120098155 | CURVED STRUCTURAL PART MADE OF COMPOSITE MATERIAL AND A PROCESS FOR MANUFACTURING SUCH A PART - A process for manufacturing a curved structural part includes fabricating a mold of the curved structural part having at least two faces that form a male mold section between a minimum radius of curvature of the curved structural part and another radius of curvature belonging to one of the two faces, preparing a stack of multidirectional fibers of one or more fiber plies oriented ±α or 90° in relation to a longitudinal direction of the curved structural part, cutting a first multidirectional strip in the stack extending longitudinally and having a width at least equal to a maximum width of the curved structural part, applying the first multidirectional strip over the mold to gradually conform the first multidirectional strip to the mold, applying the first multidirectional strip on the face having the minimum radius of curvature, and pressing and tightening the first multidirectional strip over the other faces. | 04-26-2012 |
| 20120097794 | AIRCRAFT PANEL COMPRISING AN OPENING EQUIPPED WITH A SURROUND - The subject of the invention is an aircraft panel, notably a fuselage panel of the aircraft, comprising at least one opening equipped with a surround intended to accept a closing-off device that closes off the opening, the panel comprising at least one exterior surface, the surround surrounding the opening being fixed to the panel, forming an interface for fitting the closing-off device, and comprising at least one lip extending towards the centre of the opening, the lip supporting the closing-off device, and the surround having an external face interposed between the exterior surface of the panel and the closing-off device; the panel is characterized in that the surround comprises fixing means which work by gripping the edge of the opening of the panel. | 04-26-2012 |
| 20120097793 | SURROUND FOR AN OPENING MADE IN AN AIRCRAFT PANEL, AND METHOD OF FITTING IT - The subject of the invention is a surround for an opening made in a panel of an aircraft, notably a fuselage panel of the aircraft. The panel comprises at least one exterior surface, the surround is fixed to the panel, forming an interface for fitting a closing-off device, and comprises at least one lip extending towards the centre of the opening. The lip supports the closing-off device and has at least one external face interposed between the external surface of the panel and the closing-off device. The surround is characterized in that it is made of at least two independent components joined together, a first component comprising the lip and a second component being fixed to the panel. | 04-26-2012 |
| 20120097261 | AIRCRAFT COVER INCLUDING MEANS FOR LIMITING THE SCOOP PHENOMENA OF PNEUMATIC TYPE - An aircraft nacelle includes at its outside wall a cowl moveable relative to the nacelle so as to block or unblock an opening. The cowl includes an articulation and locking/unlocking elements distant from the upstream edge of the cowl that include elements for limiting the appearance of scooping phenomena. The limiting elements include at least one lock integral with the rest of the nacelle or respectively the cowl that can occupy a locked state in which part of the lock interferes with the cowl or respectively the rest of the nacelle and prevents a deformation that includes a radial component of the cowl, and another free state in which the part no longer interferes with the cowl or respectively the rest of the nacelle and allows the opening movement of the cowl, with the switch from one state to the next being generated by a gas pressure variation. | 04-26-2012 |
| 20120097260 | AIRCRAFT COVER INCLUDING MEANS FOR LIMITING THE SCOOP PHENOMENA OF ELECTROMAGNETIC TYPE - An aircraft nacelle includes at its outside wall a cowl that can move relative to the rest of the nacelle so as to block or unblock an opening. The cowl includes an articulation relative to the rest of the nacelle and locking/unlocking elements distant from the upstream edge of the cowl that includes elements for limiting the appearance of scooping phenomena. The limiting elements include at least one electromagnetic torque, having one element integral with the rest of the nacelle and the other element integral with the cowl, with at least one of these two elements emitting a magnetic field that generates a force of attraction on the other element, and the surfaces of the two elements of the electromagnetic torque that are flattened against one another are arranged in planes having at least one component in the radial direction. | 04-26-2012 |
| 20120092193 | Method And Device For Aiding The Managing Of Air Operations With Required Navigation And Guidance Performance - The device ( | 04-19-2012 |
| 20120091285 | AIRCRAFT NACELLE INCLUDING A CONTINUE JOINT AREA BETWEEN AN OUTER WALL AND A FRONT FRAME - An aircraft nacelle includes a lip that is extended inside the nacelle by an inside wall that delimits a pipe that empties at a power plant and outside of the nacelle by an outside wall, a first frame called a front frame that connects the inside wall and the outside wall, delimiting an annular pipe with the lip, and a second frame called a rear frame that connects the inside wall and the outside wall close to the power plant, characterized in that it includes at least one junction zone—at at least one cross-section of the nacelle along a plane that contains the longitudinal axis of the nacelle—an element that constitutes at least one part of the outside wall and at least one part of the front frame and that includes an offset whose shapes are suitable for accommodating a panel that forms the lip. | 04-19-2012 |
| 20120090695 | AIRCRAFT NACELLE INCLUDING AT LEAST ONE RADIAL PARTITION BETWEEN TWO CONDUCTS - An aircraft nacelle that makes it possible to channel a stream of air in a longitudinal direction and that includes at least two panels ( | 04-19-2012 |
| 20120090694 | AIRCRAFT NACELLE INCLUDING A REAR FRAME INCLINED TO THE REAR - An aircraft nacelle includes a lip whose surface contacts with the aerodynamic streams extends inside the nacelle by an inside wall that delimits a layer that empties at a power plant and outside of the nacelle by an outside wall, a first front frame connects the inside and outside walls, delimiting an annular pipe with the lip, and a rear frame connects the inside and outside walls at a junction zone between the inside pipe and power plant pipe, for a given cross-section of the nacelle along a plane that contains the longitudinal axis of the nacelle, a point A at the intersection between the rear frame and the inside wall, and a point B at the intersection between the rear frame and the outside wall, with B being offset toward the rear of the nacelle relative to A over more than 50% of the rear frame's periphery. | 04-19-2012 |
| 20120090693 | ACOUSTIC PROCESSING PANEL, MORE PARTICULARLY ADAPTED FOR AN AIR INTAKE IN AN AIRCRAFT NACELLE - An acoustic treatment panel that is connected to an air intake of an aircraft nacelle, includes at least one acoustically resistive structure ( | 04-19-2012 |
| 20120080582 | SPIGOT-TYPE FASTENER PROVIDED WITH AT LEAST ONE MEANS FOR MEASURING THE FORCE GENERATED BY AN AIRCRAFT ENGINE - The invention relates to a spigot-type fastener ( | 04-05-2012 |
| 20120080566 | CABLE SECURING DEVICE - The subject of the invention is a cable securing device comprising a base, a housing having an interior and an exterior surface and two spaced-apart edges allowing a plurality of cables to be inserted into the said housing, and a tongue connecting the two edges so as to hold the cables in the housing. The said tongue is connected removably at one end, known as the free end, to the first edge. The tongue comprises at least one orifice capable of engaging with a pin provided on the exterior surface of the housing. The interior surface of the tongue comprises a touch-and-close structure capable of engaging with a touch-and-close structure provided on the exterior surface of the housing. | 04-05-2012 |
| 20120080555 | TAKE-UP DEVICE FOR THRUST FORCES WITH CONNECTING RODS FOR AIRCRAFT ENGINE ATTACHMENT PYLON, INTEGRATING THREE ALIGNED BALL JOINTS - The present invention relates to a take-up device for thrust forces ( | 04-05-2012 |
| 20120080554 | AIRCRAFT ENGINE ATTACHMENT PYLON COMPRISING TWO FRONT WING SYSTEM ATTACHMENTS WITH ORTHOGONAL SHEARING PINS - The present invention relates to an aircraft assembly ( | 04-05-2012 |
| 20120078596 | METHOD FOR VERIFYING THE VALIDITY OF THE SIMULATION OF A SYSTEM AND CORRESPONDING DEVICE - In order to verify, using a processor, the validity of a simulation of a system, a method includes providing first data representative, in a computer language, of at least one expected property of the simulation, providing second data representative, in the computer language, of the at least one property obtained by the simulation, and determining an item of information representative of the validity of the simulation on the basis of the first data and the second data. | 03-29-2012 |
| 20120074932 | NONDESTRUCTIVE INSPECTION OF A STRUCTURE IN AN AIRCRAFT - The invention relates to a non-destructive inspection method using eddy currents for detecting flaws in a metal structure ( | 03-29-2012 |
| 20120073262 | AIR DISCHARGING DEVICE FOR AN AIRCRAFT DOUBLE-FLOW TURBINE ENGINE - An air discharging device ( | 03-29-2012 |
| 20120069519 | FLUID-COOLED ELECTRICAL EQUIPMENT, AVIONIC RACK TO RECEIVE SUCH EQUIPMENT AND AIRCRAFT EQUIPPED WITH SUCH RACKS - This invention relates to a fluid-cooled electronic equipment item, an avionic rack to receive such an equipment item and an aircraft equipped with such racks. | 03-22-2012 |
| 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 |
| 20120065921 | METHOD AND DEVICE FOR TESTING INPUT/OUTPUT INTERFACES OF AVIONIC MODULES OF IMA TYPE - Input/output interfaces of avionic modules of IMA type in a device including several modules is tested. A system includes at least one application employed by a set of computer modules. This set includes the computer module (a first module), and at least one other computer modul (at least one second module). A system test is associated with the at least one system for functionally testing the set of computer modules according to the system. The system test includes at least one elementary system test for functionally testing at least one input/output interface of the first module. The execution of the at least one elementary system test is independent of the at least one second module. At least one result of execution of the at least one elementary system test is transmitted to a maintenance computer distinct from the computer modules of the plurality of computer modules. | 03-15-2012 |
| 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 |
| 20120060938 | AIRCRAFT NACELLE COMPRISING A REINFORCED OUTER WALL - An aircraft nacelle includes a wall that delimits an inside pipe ( | 03-15-2012 |
| 20120060755 | DEVICE FOR DEPOSITION OF FIBERS UPON A FRAME WITH CONCAVE CIRCULAR SECTIONS - A device for deposition of fibers on a support ( | 03-15-2012 |
| 20120056760 | Method And Device For Automatically Determining An Erroneous Height Value Of A Radioaltimeter Mounted On An Aircraft - Method and device for automatically determining an erroneous height value of a radio altimeter mounted on an aircraft. The device ( | 03-08-2012 |
| 20120056033 | PYLON FOR ATTACHING AN AIRCRAFT TURBINE ENGINE COMPRISING ALIGNED FRONT WING TIES - The invention relates to a pylon for attaching a turbine engine for an aircraft, having a rigid structure ( | 03-08-2012 |
| 20120055008 | METHOD FOR JOINING TOGETHER AIRCRAFT PARTS - In the method of fastening aircraft parts together, the following steps are performed:
| 03-08-2012 |
| 20120041951 | METHOD AND DEVICE FOR TRANSMITTING GEOGRAPHICAL DATA ON AN AIRCRAFT - The invention relates to a device ( | 02-16-2012 |
| 20120040159 | STRUCTURAL COMPOSITE PANEL FOR AN AIRCRAFT INCLUDING A PROTECTION AGAINST HIGH ENERGY IMPACTS - A structural panel consisting of a stratified composite material includes one face exposed to impacts and further includes a layer consisting of a hyper-elastic material bonded adhesively to its other face. According to this embodiment, debris striking the exposed face of this composite panel will have some of its energy dissipated by the local rupture of the composite skin, while the rest of the energy is absorbed by the deformation of the layer of hyper-elastic material that captures the debris and expels it again. | 02-16-2012 |
| 20120025604 | ELECTRICAL POWER SUPPLY SYSTEM FOR AN AIRCRAFT - The invention relates to an electrical power supply system for an aircraft comprising at least one main generator ( | 02-02-2012 |
| 20120024468 | METHOD FOR MANUFACTURING A STIFFENED PANEL OF COMPOSITE MATERIAL - A process for the production of a stiffened panel made of composite material, includes the stages of depositing the fibers that constitute the panel on a rigid device ( | 02-02-2012 |
| 20120024455 | METHOD FOR MANUFACTURING A STIFFENED PANEL OF COMPOSITE MATERIAL - A process for the production of a stiffened panel made of composite material includes the stages of depositing the fibers that constitute the panel on a rigid device, depositing at least one stiffener, covering the unit with a sealed wall, and then polymerizing, and providing—for each stiffener—a rigid counter-mold in contact with the convex surface of the stiffener, covering the zone(s) of the panel that is/are not covered by the stiffener with at least one band sufficiently rigid to transmit compression forces by allowing play between the band and the stiffener, and then depositing a seal such that the seal, the band, and the rigid counter-mold form the sealed wall, whereby the seal is able to have two states, a first malleable state during application so that it adapts to the profile of the lateral edges of the stiffeners, and a hardened state to ensure transmission of compression forces in a manner essentially identical to the rigid counter-molds or to the bands arranged on either side of the seal so as not to generate a pressure gradient. | 02-02-2012 |
| 20120023900 | AIRCRAFT NACELLE - The invention relates to an aircraft nacelle comprising a cowling, an engine housed in an internal volume of the cowling and at least one thrust reverser, an air passage duct ( | 02-02-2012 |
| 20120023727 | Tools For Manufacturing A Composite Panel, In Particular Of An Aircraft Fuselage - A tool equipment for manufacturing a panel in a composite material, in particular for an aircraft fuselage. | 02-02-2012 |
| 20120022725 | Method And Device For Updating A Target Altitude For An Emergency Descent Of An Aircraft - Method and device for updating a target altitude for an emergency descent of an aircraft. | 01-26-2012 |
| 20120022724 | Automatic Management Method And Device Of A Lateral Trajectory For An Emergency Descent Of An Aircraft - Automatic management method and device of a lateral trajectory for an emergency descent of an aircraft. | 01-26-2012 |
| 20120022723 | Method And Device For Determining And Updating A Target Altitude For An Emergency Descent Of An Aircraft - Method and device for determining and updating a target altitude for an emergency descent of an aircraft | 01-26-2012 |
| 20120022720 | METHOD AND DEVICE FOR PROTECTING SOFTWARE COMMANDS IN AN AIRCRAFT COCKPIT - The invention in particular has as an object the control of execution of software commands of a data-processing system in an aircraft cockpit comprising means for allowing a user to call up these commands. For these purposes, the means making it possible to call up these commands initially are locked ( | 01-26-2012 |
| 20120018580 | Insulating blanket for an aircraft and assembly integrating such a blanket - This invention proposes an insulation blanket for an aircraft, the said blanket coming in the form of a strip of insulation material of elongated shape having two more or less parallel longitudinal edges ( | 01-26-2012 |
| 20120018577 | ENGINE MOUNTING WITH AN ADAPTED LOAD/DEFORMATION CURVE - The invention relates to a mounting for attaching an engine to an aircraft structure, said mounting including a metal spring and being adapted for fulfilling the following conditions: the stiffness of the mounting for load values falling within a predetermined range ([CA, CB]) is less than the stiffness of the mounting for load values that fall below or above the predetermined range; considering a first load value (CS | 01-26-2012 |
| 20120018576 | LINKING DEVICE FOR LINKING A FIRST BODY TO A SECOND BODY, IN PARTICULAR FOR AN AIRCRAFT ENGINE ASSEMBLY | 01-26-2012 |
| 20120017514 | Aircraft opening window and aircraft equipped with at least one such window - The invention relates to an aircraft opening window comprising at least one pane ( | 01-26-2012 |
| 20120016540 | Method And Device For Aiding The Control Of Guiding Modes Transitions Of An Aircraft - The device includes means ( | 01-19-2012 |
| 20120015595 | AIRCRAFT VENTILATION SYSTEM - This ventilation system is intended for an aircraft comprising a structure bearing an exterior wall and an interior covering. | 01-19-2012 |
| 20120015213 | Fabrication Method Of Composite Components And Thus Obtained Components - During the cooking of a composite component ( | 01-19-2012 |
| 20120012218 | INTERIOR COVERING DEVICE FOR AN AIRCRAFT CABIN INCORPORATING AT LEAST ONE SYSTEM - The invention relates to a device for interior covering ( | 01-19-2012 |
| 20120009372 | STRUCTURAL PANEL WITH INTEGRATED STIFFENING - The invention relates to the field of structural panels, more specifically, but not exclusively, to the field of aircraft fuselage panels. | 01-12-2012 |
| 20120007010 | AIRCRAFT INCLUDING A FUEL VALVE AND A CONTROL ACTUATOR FASTENED TO THE VALVE - The aircraft comprises:
| 01-12-2012 |
| 20120006943 | AIRCRAFT INCLUDING A FUEL PUMP FASTENED TO A TANK PANEL - The aircraft includes:
| 01-12-2012 |
| 20120006940 | METHOD FOR REALIZATION OF AN AIRCRAFT STRUCTURE AND RESULTING STRUCTURE - An aircraft structure includes a skin ( | 01-12-2012 |
| 20120001025 | Device for fastening systems for an aircraft, adapted in particular to be used in relation to a window - The invention relates to a device for fastening systems in an aircraft. | 01-05-2012 |
| 20120000266 | EXPANSION TOOL AND METHOD FOR COLD EXPANSION OF HOLES - A method for cold expansion of a hole formed in a work piece. The method comprises providing a body comprising at least a cylindrically shaped part having an inner hole in axial direction of the body. The body further comprises along its circumferential direction a plurality of members which are movable in radial direction of the body, such that the outer diameter of the cylindrical part of the body can be changed. The method comprises introducing the body into the hole formed in the work piece; inserting a core into the inner hole of the cylindrically shaped part, wherein at least one of the core or the inner hole comprises a portion having changing diameter and the inner hole and the core get into contact with respect to each other upon insertion of the core, such that in dependency of the insertion depth of the core into the inner hole in axial direction the members move in radial direction outwardly and the outer diameter of the cylindrical part of the body increases and, accordingly, acts on the inner circumference of the hole formed in the work piece so that a boundary zone of the hole is compressed, which leads to a compression or hardening and, accordingly, to the introduction of compressive stress in the boundary zone. The inner hole and the core have a polygonal cross section in a direction perpendicular to the longitudinal axis, and the hole formed in the work piece is expanded over the entire thickness of the work piece in which the hole is formed. | 01-05-2012 |
| 20110315823 | FIXATION MECHANISM FOR INSTALLING THERMAL INSULATION SHEETS IN AN AIRCRAFT BODY - The invention relates to a device for holding an insulating blanket and for fastening systems in an aircraft, comprising a base having two ends from each of which an arm extends. | 12-29-2011 |
| 20110315813 | TURBOMACHINE SUPPORT PYLON FOR AIRCRAFT - The invention relates to an aircraft support pylon ( | 12-29-2011 |
| 20110314788 | Aircraft Turbine Engine And Use Of Such A Turbine Engine - The invention relates to an aircraft turbine engine and to the use of such a turbine engine. According to the invention, the turbine engine (la) comprises a means for shifting the axis (la-la) of the blower ( | 12-29-2011 |
| 20110309197 | DEVICE FOR HOLDING AN INSULATING BLANKET AND FOR FASTENING SYSTEMS ADAPTED TO BE MOUNTED IN AN AIRCRAFT - This device is intended for an aircraft comprising frames, a skin and connecting pieces between the skin and the frames, referred to as clips. | 12-22-2011 |
| 20110309196 | DEVICE FOR HOLDING AN INSULATING BLANKET AND FOR FASTENING TWO-PARTS SYSTEMS - This device for holding an insulating blanket and for fastening systems in an aircraft comprises a base ( | 12-22-2011 |
| 20110309193 | AERO-ACOUSTIC OPTIMISATION METHOD FOR COMPLEX-SECTION MECHANICAL PARTS AND CORRESPONDING MECHANICAL PART AND LANDING GEAR - The invention is intended to reduce the drag caused by a complex-section part in an airflow, for example the landing gear of an aircraft, making it possible to optimise the lift/drag ratio and to reduce the aerodynamic noise by reducing the local noise source combined with a global optimisation of the aeroplane related to the reduction in drag. To do so, the invention provides for the shaping of the complex part, masking its form with a special casing. | 12-22-2011 |
| 20110303302 | NACELLE COMPRISING AN AIR ENTRANCE IN A CAP - An aircraft nacelle includes an outside wall ( | 12-15-2011 |
| 20110300381 | Novel stable aqueous dispersions of high performance thermoplastic polymer nanoparticles and their uses as film generating agents - Novel aqueous dispersions of thermoplastic polymers suitable for generation of films, notably for the sizing of fibers for facilitating their handling and for making composite materials. | 12-08-2011 |
| 20110299993 | COMPOSITE STRUCTURAL MEMBER WITH PROGRESSIVE RIGIDITY - The invention relates to a composite structural member with fiber reinforcement and its application in the production of a wing box for aircraft. More specifically, it relates to a composite structural member ( | 12-08-2011 |
| 20110299062 | DEVICE AND METHOD FOR DETECTING AND MEASURING WIND FOR AN AIRCRAFT - The invention relates to a device for detecting and measuring wind at the front of an aircraft, said device comprising a lidar for the cyclic measurement of wind speeds at least a couple of measuring points located at the same distance, so-called measuring distance, from the nose of the aircraft. The invention is characterised in that it is suitable for measuring wind speeds, at each cycle, by means of the lidar, at a plurality of couples of measuring points ( | 12-08-2011 |
| 20110297787 | DUAL FUNCTION DOOR FOR AN AIRCRAFT ENGINE NACELLE - The invention relates to a door ( | 12-08-2011 |
| 20110296676 | System For Attaching Two Components Together, Such As An Aircraft Engine And The Mounting Pylon Thereof - The invention relates to a system for attaching two components together, such as an aircraft engine and the mounting pylon thereof. According to the invention, at least two of the front ( | 12-08-2011 |
| 20110296151 | METHOD AND DEVICE FOR INCREMENTAL CONFIGURATION OF IMA TYPE MODULES - The invention in particular has as an object the incremental configuration of an IMA-type module, the module comprising temporal and hardware resources as well as an operating system allowing a segregated running of at least two applications with the aid of at least one part of the resources. After having obtained ( | 12-01-2011 |
| 20110295588 | METHOD AND DEVICE FOR SIMULATING A SOFTWARE APPLICATION TO EXECUTE IN A SYSTEM - A method for simulation of a software program able to be run in a system and to control at least one action on expiration of a counter of the system, includes:
| 12-01-2011 |
| 20110295574 | DEVICE FOR BALANCING A SIMULATION PLATFORM, AND ASSOCIATED METHOD - The invention relates to balancing a simulation platform ( | 12-01-2011 |
| 20110295448 | SYSTEM ABOARD AN AIRCRAFT - The invention relates to a device aboard an aircraft comprising output means ( | 12-01-2011 |
| 20110292842 | METHOD AND DEVICE FOR SYNCHRONIZATION AND TIME-STAMPING FOR EQUIPMENT IN A COMMUNICATION NETWORK OF AFDX TYPE - The invention has in particular as an object the synchronization of a local clock of an equipment item in a communication network according to synchronization frames emitted by a reference equipment item and transmitted via a switch. After it has received ( | 12-01-2011 |
| 20110291325 | PROCESS FOR THE REALIZATION OF A STIFFENER MADE OF COMPOSITE MATERIAL WITH AN OMEGA SECTION - A process for the production of a stiffener made of composite material that includes a central part with wings on both sides such that when the wings are resting against an element to be reinforced, the central part is separated from the element to be reinforced, with the process including producing a flat strip ( | 12-01-2011 |
| 20110290947 | Automatic Method And Device For Aiding The Piloting Of An Airplane - The device ( | 12-01-2011 |
| 20110290936 | METHOD OF MANUFACTURE BY SUPERPLASTIC FORMING AND BY FISHPLATING OF A RIB FOR AN AERODYNAMIC FAIRING OF AN AIRCRAFT ENGINE MOUNTING PYLON - The present invention relates to a method of manufacture of a group of transverse internal stiffening ribs ( | 12-01-2011 |
| 20110290935 | METHOD OF MANUFACTURE BY SUPERPLASTIC FORMING AND BY FISHPLATING OF A RIB FOR AN AERODYNAMIC FAIRING OF AN AIRCRAFT ENGINE MOUNTING PYLON - The present invention relates to a method of manufacture of a stiffening transverse internal rib for an aerodynamic fairing of an engine mounting device, including:
| 12-01-2011 |
| 20110290933 | AIRCRAFT INCLUDING AN UNDERCARRIAGE MOTOR - The aircraft includes at least one engine suitable for propelling the aircraft in flight, at least one motor of an undercarriage, and automatic means arranged to cause the aircraft to taxi under drive directly from the engine, while simultaneously using the motor for taxiing, other than during takeoff or landing. | 12-01-2011 |
| 20110290784 | HEATING SYSTEM HAVING AT LEAST ONE ELECTROTHERMAL HEATING LAYER, A STRUCTURAL COMPONENT HAVING SUCH A HEATING LAYER, A HEATING METHOD AND A METHOD FOR PRODUCING A SEMI-FINISHED COMPONENT OR A COMPONENT HAVING A HEATING DEVICE - A heating system including an energy supply device, wherein the heating system includes a base heating device having an insulation layer, with an electrothermal base heating layer arranged thereon and with an electrical connecting device by way of which the energy supply device is connected to the base heating layer. The heating system includes an additional heating device having an insulation layer, with an electrothermal additional heating layer arranged thereon and with an electrical connecting device by way of which the energy supply device is connected to the additional heating layer. The energy supply device is connected to the heating layers by way of the connecting devices and in the activation phase, current is supplied during at least a partial period of time to the additional heating layer so that the base heating layer generates heat permanently, while the additional heating layer generates heat in the partial period of time. | 12-01-2011 |
| 20110282822 | SYSTEM FOR SELECTING AN ITEM OF DATA REPRESENTING A PARAMETER OF THE AIR, ENGINE CONTROL SYSTEM, AIRCRAFT COMPRISING SUCH SYSTEMS AND ASSOCIATED METHOD - A system and method for selecting a datum representative of an air parameter, including a plurality of sources each capable of delivering a datum representative of a measured value of the parameter. The system includes: a mechanism for determining, for at least some sources, a number of other sources from the plurality of sources in agreement with a source in question; and a mechanism for selecting the datum selected from the data delivered by the sources for which the determined agreement number is the maximum. An engine control system, or an aircraft can include such a system or implement such a method. | 11-17-2011 |
| 20110276199 | FLIGHT CONTROL SYSTEM AND AIRCRAFT COMPRISING IT - A flight control system for an aircraft, in which control commands are transmitted between a flight control module ( | 11-10-2011 |
| 20110272852 | METHOD FOR PRODUCING A CONCAVE-SHAPED IN PARTICULAR U-SHAPED PIECE IN A COMPOSITE MATERIAL AND DEVICE FOR CARRYING OUT THE SAME - A process for manufacturing a piece made of composite material with a hollow form and including a fiber preform ( | 11-10-2011 |
| 20110270471 | Control Panel For An Aircraft - The control panel ( | 11-03-2011 |
| 20110266399 | Method And Device For Reducing Actual Loads Generated On Airplane By An Aerodynamic Disturbance - According to the invention, the device ( | 11-03-2011 |
| 20110266389 | PIN SYSTEM FOR THE CONNECTION ASSEMBLY OF AN ENGINE PYLON UNDERNEATH A WING OF AN AIRCRAFT - The invention relates to a connection assembly of an engine pylori underneath an aircraft wing, the wing being provided with a fitting ( | 11-03-2011 |
| 20110264308 | Method And Device For Automatically Estimating An Air Speed Of An Aircraft - The device ( | 10-27-2011 |
| 20110260375 | PROCESS FOR MANUFACTURING A PIECE THAT IS MADE OF COMPOSITE MATERIAL AND DEVICE FOR ITS IMPLEMENTATION - A process for manufacturing a piece made of composite material that includes fibers that are immersed in a resin matrix, whereby the piece is placed in a first chamber with at least one flexible wall. The process includes a thermal cycle with essentially a first phase ( | 10-27-2011 |
| 20110253843 | Air Intake Arrangement For An Aircraft - The invention relates to an arrangement ( | 10-20-2011 |
| 20110253841 | METHOD AND SYSTEM FOR CHECKING THE FORMATION OF ICE ON AN AIRCRAFT IN FLIGHT - The invention relates to a method for checking the formation of ice on an aircraft in flight, characterized in that the method comprises:
| 10-20-2011 |
| 20110253840 | METHOD FOR INSTALLING AN INERTIAL REFERENCE UNIT IN AN AIRCRAFT, AND AIRCRAFT EQUIPPED IN THIS WAY - The invention relates to a method for installing an inertial reference unit in an aircraft, in which: a reference unit support ( | 10-20-2011 |
| 20110251791 | Method And Device For Updating The Position Of An Aircraft - Method and device for updating the position of an aircraft | 10-13-2011 |
| 20110249399 | MODULAR ASSEMBLY FOR FASTENING ELECTRONIC MODULES - The invention relates to a modular assembly for fastening electronic modules carried on board an aircraft, characterized in that it comprises:
| 10-13-2011 |
| 20110248116 | ATTACHMENT PYLON FOR AIRCRAFT TURBOSHAFT ENGINE, COMPRISING A REAR FLAP WITH MOBILE INCIDENCE - The invention relates to an aircraft engine assembly, comprising a turboshaft engine with a propeller as well as an attachment pylon ( | 10-13-2011 |
| 20110246160 | METHOD AND DEVICE FOR DEVELOPMENT AND CERTIFICATION OF TRAINING SIMULATORS FOR AIRCRAFT PILOTING AND RESULTING SIMULATION DEVICE - The invention in particular has as an object a method and a device for developing and qualifying a part of the software component of a training simulator for operating a vehicle. Software modules developed for an engineering simulator, modeling the performance of a part of the vehicle, are integrated ( | 10-06-2011 |
| 20110242724 | ELECTRICAL DISTRIBUTION METHOD AND DEVICE FOR AN AIRCRAFT ENGINE IGNITION SYSTEM - The device for electrical distribution in an ignition system of an engine ( | 10-06-2011 |
| 20110239855 | SINGLE EFFECT HYDRAULIC CYLINDER - The invention belongs to the field of single-effect hydraulic cylinders. It relates to a device that makes it possible to limit the pressure in the pressurization chamber of a single-effect cylinder when the rod thereof is in a particular range of longitudinal positions of safety, while respecting the operating safety of the device, that is, in the case that the power supply of the pilot valves of the distributors and of the hydraulic pump is cut, the rod of the cylinder remains in its position if this position does not lie within the safety position range | 10-06-2011 |
| 20110226903 | DE-ICING DEVICE COMPRISING MEANS FOR DETECTION OF A LEAKAGE IN A HOT AIR SUPPLY SYSTEM - A device for defrosting a leading edge of an aircraft, includes at least one opening ( | 09-22-2011 |
| 20110226660 | METHOD OF MAKING A CORE COMPRISING AN ENVELOPE CONTAINING GRANULAR AND/OR POWDERY PRODUCTS, DEVICE AND CORE OBTAINED - A process for the production of a core that can be used for the manufacturing of a part that is made of composite material, whereby the core consists of at least one powdered and/or granular product ( | 09-22-2011 |
| 20110219267 | METHODS AND DEVICES FOR CONFIGURATION VALIDATION OF A COMPLEX MULTI-ELEMENT SYSTEM - The object of the invention is in particular the validation of configuration of a system comprising a plurality of elements, at least one reference being associated with each element of the said plurality of elements. After at least one reference key has been calculated ( | 09-08-2011 |
| 20110218783 | METHOD AND TOOL FOR AIDED AIRCRAFT DESIGN USING A CRITERION OF OPERATIONAL AVAILABILITY - The invention concerns a method for the computer-aided design of an aeronautic system forming all or part of an aircraft, using a criterion of maintenance time cost over a given period of use. The cost is computed as the weighted sum ( | 09-08-2011 |
| 20110218701 | METHOD AND DEVICE FOR CONFIGURING AN ON-BOARD MAINTENANCE INFORMATION SYSTEM IN AN AIRCRAFT - The invention in particular has as an object the configuring of an on-board maintenance information system in an aircraft, the information system comprising a first ( | 09-08-2011 |
| 20110212637 | BASE FOR AN ELECTRONIC CARD AND ASSOCIATED EXTRACTION DEVICE | 09-01-2011 |
| 20110210229 | STRUCTURAL ROD INCORPORATING A VIBRATION FILTRATION MODE - A structural rod has a primary rod that has an axial cavity and a secondary rod inside the axial cavity so that the secondary rod is able to move inside the axial cavity along the direction of the longitudinal axis of the rod. The primary rod has a bearing for fastening the structural rod at the first end in a rigid manner and is not fastened rigidly to the structure at the second end. Conversely, the secondary rod has a bearing for fastening the structural rod at the second end in a rigid manner and is not fastened rigidly to the structure at the first end. The primary and secondary rods are joined through one or more intermediate linkage elements made of a deformable and elastic material. | 09-01-2011 |
| 20110208415 | SYSTEM ONBOARD AN AIRCRAFT CONNECTED WITH A FLIGHT PLAN - The invention relates to a method and an evaluation system onboard an aircraft connected with a flight plan ( | 08-25-2011 |
| 20110206508 | Method And Device For Improving Performances Of An Aircraft Comprising At Least One Propeller Engine Without Propeller Fairing - Method and device for improving performance of an aircraft comprising at least one propeller engine without propeller fairing. | 08-25-2011 |
| 20110205712 | ELECTRONIC MODULE AND ELECTRONIC ASSEMBLY COMPRISING SUCH A MODULE - The invention relates to an electronic module ( | 08-25-2011 |
| 20110204179 | ENGINE PYLON FOR AIRCRAFT - An engine pylon for an aircraft that includes a primary structure including aircraft mounting points arranged symmetrically relative to a middle vertical longitudinal plane of the pylon. The primary structure is asymmetrical relative to the middle vertical longitudinal plane and has respective fundamental modes of vibration in a vertical direction that are uncoupled from the fundamental modes of vibration thereof in a transverse direction. | 08-25-2011 |
| 20110203858 | LAND VEHICLE PROVIDED WITH AN INTERNAL AIR FLOW PROPULSION SYSTEM - A land vehicle including an internal air flow propulsion system, a body, and a cabin, and having a plane situated substantially in the center of the vehicle and perpendicular to a longitudinal axis of the vehicle and separating the body into front and rear parts with respect to the vehicle travel direction. The propulsion system includes: an air intake situated on surfaces of the body front part; the air intakes connected to at least one propulsion unit by at least one air suction circuit so as to suck in air that flows at walls; the propulsion unit being connected to at least one air ejection orifice by at least one ejection circuit, the sucked-in air being accelerated and ejected by the propulsion unit towards the outside via the at least one ejection orifice to generate a propulsion force to move the vehicle. The air intakes are defined and distributed on the surfaces of the front part of the chassis to suck in air by the Coanda effect. | 08-25-2011 |
| 20110203343 | Method To Achieve A Stiffened Curved Metallic Structure And Structure Obtained Accordingly - The invention relates to a process for making a reinforced curved metallic structure, made from a heavy-gauge or plate-gauge sheet of an aluminium alloy containing scandium. | 08-25-2011 |
| 20110202931 | METHOD, COMPUTER PROGRAM AND DEVICE FOR SUPERVISING A SCHEDULER FOR MANAGING THE SHARING OF PROCESSING TIME IN A MULTI-TASK COMPUTER SYSTEM - The invention in particular has as an object supervising a scheduler for the management of processing time sharing in a multitask data-processing system comprising a computation unit having a standard execution mode and a preferred execution mode for executing a plurality of applications. The execution time for the said plurality of applications is divided into a plurality of periods and a minimal time for access per period to the said computation unit is determined for at least one application of the said plurality of applications. For at least one period, the said preferred execution mode is associated with the said at least one application and the said at least one application is executed according to at least the said minimal time for access to the said computation unit. For the said at least one period, the said standard execution mode is associated with the applications of the said plurality of applications and at least any one of the applications of the said plurality of applications is executed. | 08-18-2011 |
| 20110202547 | METHOD AND DEVICE ENABLING THE FUNCTIONAL EXPLOITATION, IN AN AIRCRAFT, OF A LARGE AMOUNT OF INFORMATION COMING FROM DIFFERENT SOURCES - The invention has as an object the functional use, in an aircraft, of a great number of information items originating from different sources. The invention thus makes it possible to obtain information items originating from at least one information items group, the said information items obtained to be processed by at least one function called up in a system of the aircraft. After at least one information item has been identified and selected in the said at least one information items group according to at least one predetermined link combining a reference to the said at least one function called up with a reference to the said at least one information item, the said at least one information item is transmitted to the said at least one function called up. | 08-18-2011 |
| 20110202207 | Method And Device For Automatically Protecting An Aircraft Against An Excessive Descent Rate - The device ( | 08-18-2011 |
| 20110200336 | AVIONICS EQUIPMENT WITH OPTICAL CONTACT AND AVIONICS SYSTEM COMPRISING SUCH EQUIPMENT - An avionics device able to be installed on board an aircraft, including means of processing information and a connector able to receive and/or transmit information, the aforementioned connector including an electrical coupling interface able to transmit and/or receive information in the form of electrical signals, and an electro-optical connection interface able to convert electrical signals into optical signals and to transmit information in the form of optical signals and/or receive information in the form of optical signals and convert these optical signals into electrical signals. | 08-18-2011 |
| 20110199253 | Method And Device For Monitoring Radioaltimetric Heights Of An Aircraft - The device comprises means for generating an auxiliary height (HA) of an aircraft (AC) and for determining, with the aid of this auxiliary height (HA), an error in incoherent data which are received from two radioaltimeters. | 08-18-2011 |
| 20110198445 | CONNECTION ASSEMBLY FOR AT LEAST ONE ITEM OF ELECTRONIC EQUIPMENT IN AN AIRCRAFT - The invention relates to an assembly for connection ( | 08-18-2011 |
| 20110196881 | METHOD AND DEVICE FOR MANAGING INFORMATION IN AN AIRCRAFT - The object of the invention is in particular a method and a device for managing information in an aircraft, comprising at least one device for restituting information for the crew and a plurality of equipment items adapted to transmit information items capable of being restituted on the restitution device. After a plurality of information items from the said plurality of equipment items has been acquired and a context has been determined ( | 08-11-2011 |
| 20110194269 | CONNECTION ASSEMBLY WITH FRONT CABLING FOR AT LEAST ONE ITEM OF ELECTRONIC EQUIPMENT IN AN AIRCRAFT - The invention relates to a connection assembly ( | 08-11-2011 |
| 20110193724 | SYSTEM AND METHOD FOR MANAGING AUDIO WARNING MESSAGES IN AN AIRCRAFT - The present invention relates to a system ( | 08-11-2011 |
| 20110192167 | NOISE CONTROL CHEVRON FOR A NOZZLE, AND NOZZLE AND TURBOSHAFT ENGINE PROVIDED WITH SUCH A CHEVRON - According to the invention, the shape of each of said chevrons is defined: by two lateral sides ( | 08-11-2011 |
| 20110187562 | Method And Device For Preventing An Anti-Collision System On Board An Airplane From Emitting Alarms, During An Altitude Capture Maneuver - According to the invention, the device ( | 08-04-2011 |
| 20110187561 | Method And Device For Preventing An Anti-Collision System On Board An Airplane From Emitting Alarms, During An Altitude Capture Maneuver - According to the invention, the device ( | 08-04-2011 |
| 20110184595 | Method And Device For Aiding The Piloting Of An Aircraft During A Final Approach Phase - Method and device for aiding the piloting of an aircraft during a final approach phase. | 07-28-2011 |
| 20110182723 | TURBOMACHINE AIRCRAFT PROPELLER - The invention relates to an aircraft propeller ( | 07-28-2011 |
| 20110180665 | AIRCRAFT FUSELAGE ELEMENT - The invention relates to an aircraft fuselage element. According to the invention, -said fuselage element being a one-piece component, it comprises a closed wall ( | 07-28-2011 |
| 20110179767 | COOLING DEVICE FOR AIRCRAFT PROPELLER - The invention relates to an aircraft propeller ( | 07-28-2011 |
| 20110174930 | FUSE LINK DEVICE BETWEEN A MOBILE PART AND A FIXED PART OF AN AIRCRAFT NACELLE - The object of the invention is an aircraft nacelle that comprises at least one part, called a door ( | 07-21-2011 |
| 20110174918 | DEVICE FOR FASTENING A TURBOPROP, PREFERABLY UNDER AN AIRCRAFT WING - The present invention relates to an engine assembly for an aircraft comprising an attachment means, a turboprop on an attachment mast, this means including a plurality of front engine attachments ( | 07-21-2011 |
| 20110168839 | DEVICE FOR CONNECTING AN AIR INLET WITH AN AIRCRAFT NACELLE ACTUATOR ASSEMBLY - An aircraft nacelle includes an air intake that makes it possible to channel the air in a pipe in the direction of a pipe of a power plant that is arranged in the extension of the pipe, whereby the pipe of the air intake includes at least one panel that integrates an acoustic treatment with an acoustically resistive porous layer that is in contact with the aerodynamic stream that enters into the nacelle, at least one alveolar structure, and a reflective or impermeable layer that forms the rear surface of the panel, a flange that ensures the connection between the air intake and the power plant including at least one wing that is connected to the air intake by a number of connecting elements, characterized in that some of the connecting elements have axes that are secant with the edge of the panel that delimits the pipe of the air intake. | 07-14-2011 |
| 20110166772 | METHOD AND DEVICE FOR PROCESSING A REQUEST MESSAGE RECEIVED IN AN AIRCRAFT, FROM GROUND CONTROL, VIA A DATA TRANSMISSION SYSTEM - A method for processing a request message received (E | 07-07-2011 |
| 20110166723 | METHOD AND DEVICE FOR AIDING THE PILOTING OF AN AIRCRAFT DURING A LANDING - Method and device for aiding the piloting of an aircraft during a landing phase. The device ( | 07-07-2011 |
| 20110162081 | METHOD AND DEVICE FOR PROTECTING THE INTEGRITY OF DATA TRANSMITTED OVER A NETWORK - A method of transmitting data over a network, from a sending application to a receiving application, including: coding the data, by the sending application, by implementing a predefined rule; detecting alteration of at least one item of data transmitted, by the receiving application, by implementing the predefined rule; and in case an alteration of a data item is detected, restoring the altered data item. In the course of the coding, in the course of the alteration detection, and in the course of the restoration, a cyclic redundancy check or an encryption can be implemented. | 06-30-2011 |
| 20110160936 | METHOD AND DEVICE FOR ACCESSING THE DOCUMENTATION OF AN AIRCRAFT ACCORDING TO ALARMS GENERATED THEREIN - The invention in particular has as an object a method and a device for accessing the documentation of an aircraft according to alarms generated therein, the documentation comprising at least one document modifiable independently of the manufacturer of the aircraft. After having received ( | 06-30-2011 |
| 20110157222 | DATA PROCESSING AND DISPLAY SYSTEM - A data processing and display system includes processing and display means adapted for displaying, from a more secured domain and on a same screen of a display processing device, information data from one or more less secured domains and active data from the more secured domain as a superimposition. | 06-30-2011 |
| 20110155846 | ANCILLARY DEVICE WITH AN AIR TURBINE FOR TAXIING AN AIRCRAFT ON THE GROUND - Device for driving at least one wheel of an aircraft landing gear, which includes at least one turbine machine incorporated into the landing gear of the aircraft. Advantageously, the turbine machine is a pneumatic turbine. | 06-30-2011 |
| 20110154108 | SYSTEM AND PROCESS FOR SIMULATION OR TEST EXPLOITING DATA FROM MONITORING PORTS - The present invention relates to a system for simulating/testing an aeronautic computer network architecture, especially installed on board an aircraft, and to a corresponding method. | 06-23-2011 |
| 20110148665 | Method And A Device For Detecting Lack Of Reaction From The Crew Of An Aircraft To An Alarm Related To A Path - A method and a device for detecting lack of reaction of the crew of an aircraft to an alarm related to a path. | 06-23-2011 |
| 20110147534 | MEASUREMENT INSTRUMENT SUPPORT INTERPOSED BETWEEN A DRIVE UNIT AND AN AIR INTAKE OF AN AIRCRAFT NACELLE - An aircraft nacelle includes an air intake ( | 06-23-2011 |
| 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 |
| 20110139940 | WAVE ATTENUATION PANEL INSERTED BETWEEN THE MOTOR AND AIR INLET OF AN AIRCRAFT NACELLE - An aircraft nacelle includes an air intake for channeling air flow in the direction of a power plant. The air intake includes an inside pipe that forms an aerodynamic surface in contact with the air flow and is extended toward the rear by an aerodynamic surface of a pipe of the power plant. The nacelle includes a wave attenuation panel which limits or prevents the propagation of at least one wave produced during the pumping of the power plant and includes a layer that is in contact with the air flow that can allow passage of the at least one wave, at least one alveolar structure, and a reflective or impermeable layer, wherein the wave attenuation panel is inserted between the air intake and the power plant, and the layer that is in contact with the air flow ensures the continuity of the aerodynamic surfaces that are arranged downstream and upstream and the wave attenuation panel includes inserts that can be inserted between the air intake and the power plant so as not to crush the wave attenuation panel. | 06-16-2011 |
| 20110139927 | PANEL FOR AN AIR INTAKE OF AN AIRCRAFT NACELLE THAT ENSURES OPTIMIZED ACOUSTIC TREATMENT AND FROST TREATMENT - An acoustic treatment panel includes an acoustically resistive layer that defines a surface of an aircraft that is in contact with an aerodynamic stream, a reflective layer ( | 06-16-2011 |
| 20110139430 | HEAT DISSIPATION SYSTEM - A system for dissipating heat generated by an electronic system, for example an electronic device in an aircraft. The system includes a housing including an external lid covering the electronic system and configured to be in contact with a first cold source, and a second cold source located inside the external lid. The housing includes an internal lid located inside the external lid and covering the electronic system, the second cold source being located between the internal and external lids. | 06-16-2011 |
| 20110135472 | AERODYNAMIC FLIGHT CONTROL SURFACE SAID OF CROCODILE STYLE FOR AIRCRAFT - A trailing edge aerodynamic airfoil of a load-bearing aerodynamic surface of an aircraft of the crocodile type has two airfoil flaps, with each flap being integral in a forward section with a rotational shaft that determines the axis of rotation of the airfoil flap. In a position called the zero setting, the airfoil flaps are essentially joined and form a rear section of the load-bearing surface, and each airfoil flap is movable in translation independently of the other airfoil flap, relative to the load-bearing surface, with each flap being entrained in rotation relative to the load-bearing surface around its axis of rotation by the motion in translation. The ends of the rotational shaft have extensions guided by runners fastened to these ends and acting conjointly with racks fastened to the load-bearing surface. | 06-09-2011 |
| 20110133489 | AIRCRAFT NACELLE INCORPORATING A HOOD CLOSURE DEVICE THAT IS INDEPENDENT OF THE LOCKING MECHANISM - An aircraft nacelle includes, on its outside surface, at least one opening that is blocked by at least one movable part ( | 06-09-2011 |
| 20110133034 | AIRCRAFT NACELLE INCORPORATING A DEVICE FOR PROTECTING AN ACCESS FLAP FOR A LOCKING SYSTEM - An aircraft includes a part defining an aerodynamic surface against which flows an air stream, with at least one hood able to block an opening made at the aerodynamic surface, kept in the closed position by at least one locking mechanism, and an access flap for the locking mechanism, pivoting relative to the hood around an axis substantially parallel to the flow direction of the air stream and including elements for keeping it flattened against the hood, characterized in that it includes a device for protection of the access flap that includes a coverage plate that pivots around an axis of rotation, and which is able to occupy a first position in which it projects relative to the aerodynamic surface and another position in which after pivoting around the axis of rotation, it is flattened against the outside surface of the access flap such that the protective device limits the appearance of a scoop phenomenon. | 06-09-2011 |
| 20110132548 | CYLINDRICAL COMPOSITE PART TAPE LAYING MACHINE - The invention concerns a layup machine, economic in terms of capital costs, for producing large-sized cylindrical panels made of composite material covering an angular sector less than 360° and allowing high layup productivity. The device of the invention allows a fixed cylindrical mandrel to be placed on the machine's table and the tape laying head to be moved over the surface of this mandrel, the actuator carriage supporting said tape laying head moving around the mandrel along an at least partially circular track. | 06-09-2011 |
| 20110130896 | Method and Device For Determining A Takeoff Trajectory Allowing To Maximize The Takeoff Weight Of An Aircraft - The device comprises means for automatically determining an auxiliary takeoff trajectory (T | 06-02-2011 |
| 20110127376 | SYSTEM FOR OPENING AND CLOSING THE DOOR OF AN AIRCRAFT LANDING GEAR COMPARTMENT - The invention concerns a system for opening and closing a door ( | 06-02-2011 |
| 20110127375 | Method for monitoring a no-back device of an adjustable horizontal trim actuator, corresponding system and aircraft - The present invention relates to a method and a system for monitoring of an actuator equipped with a no-back device or no-back brake and in particular an adjustable horizontal trim actuator provided in aircraft. | 06-02-2011 |
| 20110127353 | AIRCRAFT NACELLE THAT INCORPORATES A THRUST REVERSAL DEVICE - An aircraft nacelle in which a power plant with an outside surface ( | 06-02-2011 |
| 20110119891 | METHOD FOR ASSEMBLING A PIECE OF METAL MATERIAL TO A PIECE OF COMPOSITE MATERIAL - Process for assembling a first part made of metal material and a second part made of composite material, by an attachment element, which includes: —pre-piercing the parts to form a recess with a diameter D | 05-26-2011 |
| 20110116916 | DEVICE FOR SHROUDING AN AIRCRAFT NACELLE - An aircraft nacelle includes an air intake followed at the upper part by a part that is integral with the mast, called a cap, and at least one door with a curved profile that includes a stiffening device arranged at the edge upstream from the door and which includes:
| 05-19-2011 |
| 20110114796 | DEVICE FOR SHROUDING AN AIRCRAFT NACELLE - An aircraft nacelle includes an air intake ( | 05-19-2011 |
| 20110114787 | ACOUSTIC TREATMENT PANEL WITH INTEGRAL CONNECTING REINFORCEMENT - An acoustic treatment panel includes, from the inside to the outside, a reflective layer ( | 05-19-2011 |
| 20110109576 | METHOD OF ADAPTING DISPLAY PARAMETERS OF A DISPLAY DEVICE, IN PARTICULAR AN ON-BOARD DISPLAY DEVICE IN AN AIRCRAFT - A method for adapting display parameters of a display device ( | 05-12-2011 |
| 20110108665 | METHOD AND DEVICE FOR IMPLEMENTING THE THRUST REVERSERS OF AN AIRCRAFT - Method and device for implementing the thrust reversers of an aircraft. According to the invention, the following successive steps are carried out automatically: deployment (E | 05-12-2011 |
| 20110106366 | METHOD AND DEVICE FOR ACCESSING MAINTENANCE FUNCTIONS OF AN AIRCRAFT FROM A MOBILE MAINTENANCE TERMINAL - The invention in particular has as an object to access maintenance functions of an aircraft from a mobile maintenance terminal. First of all, the situation of the aircraft is determined ( | 05-05-2011 |
| 20110102198 | AIRCRAFT CONTROL CABIN WITH AVIONICS DISPLAY DEVICE - This aircraft control cabin comprises an avionics display device with multiple fixed screens ( | 05-05-2011 |
| 20110094663 | METHOD FOR PRODUCING A STIFFENER ON A SURFACE OF AN ELEMENT TO BE STIFFENED - A method for the production of a stiffener on a surface of an element that is to be made rigid, whereby at least one of the two is made of a composite material that is not completely polymerized, whereby the stiffener includes—in a transverse direction—two contact zones with the surface between which the stiffener and the element to be made rigid form a cavity that empties out at least one of the ends of the stiffener, includes using a core that is placed in the cavity and removed from the cavity after polymerization. The core has a first part that has a low expansion coefficient to ensure the geometric precision required and at least one second part that has a significant elongation coefficient to make possible the extraction of the part by traction on one of the ends of the second part so as to cause a contraction of its cross-section. | 04-28-2011 |
| 20110088383 | HYDRAULIC SYSTEM FOR AIRCRAFT - A hydraulic system for aircraft wherein at least one circuit includes two hydraulic pumps, at least one of which is driven by an engine that may suffer uncontained failure that can damage hydraulic lines close to the pump, is equipped with pressure sensors for the hydraulic fluid in the lines close to the pump and a sensor for the hydraulic fluid level in a hydraulic tank of the circuit supplied by the pump. A control system for a cut-out valve installed on a suction line wherein the fluid arrives at the pump includes logic that determines the occurrence of an uncontained engine failure requiring the isolation of the pumps from line elements that may have been damaged from measurements of the fluid pressures in the lines, from measurement of the level of fluid in the tank and from information supplied late by a uncontained engine failure detection system to command the closure of the cut-out valve. The disclosed embodiments allow achieving a simplified hydraulic architecture wherein two independent circuits are supplied by two pumps each mounted on propulsion engines. | 04-21-2011 |
| 20110087712 | METHOD OF PROCESS MANAGEMENT IN A COLLABORATIVE SERVICE-ORIENTED FRAMEWORK - A method for process management in a collaborative service-oriented workshop for processing objects associated with data representing real data or processes, each object including a structure for storing links to other objects. After determining at least one function and at least one piece of information enabling the execution of the at least one function, an object including at least one reference to the at least one function and the at least one piece of information is created. | 04-14-2011 |
| 20110080176 | PART OF A VEHICLE AND VEHICLE COMPRISING SUCH PART - It concerns a vehicle part comprising electric cables ( | 04-07-2011 |
| 20110077803 | METHOD AND DEVICE FOR DETECTING PILOTING CONFLICTS BETWEEN THE CREW AND THE AUTOPILOT OF AN AIRCRAFT - According to the invention, the method comprises checking (in | 03-31-2011 |
| 20110071710 | METHOD AND DEVICE FOR DETECTING AN ERRONEOUS SPEED GENERATED BY AN AIR DATA INERTIAL REFERENCE SYSTEM - Method and device for detecting an erroneous speed generated by an air data inertial reference system. The device ( | 03-24-2011 |
| 20110067501 | DEVICE FOR MEASURING A PATTERN OF FORCES AND MOMENTS GENERATED BY AN AIRCRAFT PROPULSION SYSTEM - A device for measuring a pattern of the forces and moments ( | 03-24-2011 |
| 20110066763 | METHOD FOR GENERATING INTERFACE CONFIGURATION FILES FOR COMPUTERS OF AN AVIONIC PLATFORM - The invention relates to a method for configuring interfaces of computers belonging to an avionic platform. The platform implements a plurality of avionic functions which may exchange functional messages, each functional message comprising one or more parameters. Each avionic function is implemented by means of software modules hosted by computers. For each software module hosted by a computer, signal occurrences are generated for transmitting all the parameters of the functional messages of the function associated with the software module, this on the different communications media. Next all the occurrences are grouped per functional system, parameter and communications medium in order to configure the interfaces of these computers. | 03-17-2011 |
| 20110066656 | METHOD FOR THE TRACEABILITY OF DATA IN A COLLABORATIVE SERVICE-ORIENTED FRAMEWORK - A method for data management in a collaborative service-oriented workshop for processing objects associated with data representing actual data or processes. After selecting at least one first object including at least one first link, to a second object separate from the first object, at least one second link to a third object is accessed, the second link being included in one of the first and second objects, the third object being separate from the first and second objects. A link is then established between the data associated with the third object and the other of the first and third objects. | 03-17-2011 |
| 20110066370 | METHOD AND DEVICE FOR AIDING THE NAVIGATION OF AN AIRCRAFT FLYING AT A LOW ALTITUDE - A method and device for aiding the navigation of an aircraft flying at low altitude as described. The device ( | 03-17-2011 |
| 20110066306 | METHOD AND SYSTEM FOR IMPROVING THE PERFORMANCE OF AN AIRCRAFT UPON TAKE OFF - A method and system for improving aircraft performances during take-off is described. The system ( | 03-17-2011 |
| 20110064343 | Ball slide bearing and connecting device associated with a mast for hooking a gas turbine engine under an aircraft wing comprising such a bearing - A ball slide bearing ( | 03-17-2011 |
| 20110063137 | INSTALLATION FOR DETECTING AND DISPLAYING THE FAILURES OF THE FUNCTIONAL SYSTEMS OF AN AIRCRAFT - An installation for detecting and displaying the failures of the functional systems of an aircraft is described. The installation can include both a general alarm system ( | 03-17-2011 |
| 20110063136 | METHOD AND DEVICE FOR CENTRALIZED MANAGEMENT OF WARNINGS IN AN AIRCRAFT COMPRISING SEVERAL WARNING PRESENTATION INTERFACES - The invention in particular has as an object a method and a device for centralized management of warnings in an aircraft comprising a centralized system for management of warnings ( | 03-17-2011 |
| 20110060729 | METHOD FOR DATA MANAGEMENT IN A COLLABORATIVE SERVICE-ORIENTED WORKSHOP - A method for data management in a collaborative service-oriented workshop for processing objects associated with data representing real data or processes. After accessing at least one datum representing real data or processes stored in a remote device, at least one characteristic piece of information is extracted from the at least one datum according to a predetermined parameter. The at least one characteristic piece of information and a link to the at least one datum are then stored in an object associated with the at least one datum, the object being stored in a centralized storage area. | 03-10-2011 |
| 20110060485 | METHOD AND DEVICE FOR OPTIMIZING A TAKEOFF PROCEDURE OF AN AIRCRAFT - An optimization method and device for a take-off procedure of an aircraft. The device ( | 03-10-2011 |
| 20110060483 | DEVICE FOR AIDING THE NAVIGATION AND GUIDANCE OF AN AIRCRAFT, AND SYSTEM COMPRISING SUCH A DEVICE - Device for aiding the navigation and guidance of an aircraft, and system comprising such a device. The device ( | 03-10-2011 |
| 20110057073 | REST MODULE WITH A FIRST PARTIAL MODULE WITH DIRECT ACCESS TO A POSSIBLE SECOND PARTIAL MODULE - The invention relates to a rest module for accommodating a least one crew member of an aircraft, wherein the module comprises a first partial module. Further on the first partial module comprises a first section and a second section; wherein the first section and the second section are spatially divided. The first section comprises a first opening, a second opening and a third opening, wherein the three openings are different from each other. The first opening is adapted for providing an access from an above located area of the aircraft, the second opening is adapted for providing an access from the first section to a second partial module and the third opening is adapted for providing a separate access from the first section to the second section. | 03-10-2011 |
| 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 |
| 20110056066 | METHOD OF PREPARING THE CONNECTION BETWEEN TWO FUSELAGE SECTIONS OF AN AIRCRAFT - A method is provided for connecting two fuselage sections. A less complicated and time consuming method was found by using High-Speed-Drilling (HSD) for a group of final bore holes through the outer skin of at least one fuselage section and/or the coupling using one drilling template preferably without any pilot drilling. | 03-10-2011 |
| 20110054719 | METHOD FOR DRAMATICALLY REDUCING THE TAKE-OFF RUN OF AN AIRCRAFT - According to the invention, during take-off, the aircraft (AC) is given an attitude (θ | 03-03-2011 |
| 20110050517 | AIRCRAFT ANTENNA - A wireless communication device for an aircraft that includes at least one antenna, for example a wide-band antenna, and a transparent multilayered substrate, for example a side glazing, a front glazing or a porthole of the aircraft, adapted for receiving the at least one antenna. At least a portion of one layer of the substrate is at least partially reflective to electromagnetic waves transmitted or received by the at least one antenna, wherein the at least one portion of the layer of the substrate is located at least partially opposite the at least one antenna. The at least one portion of the layer of the substrate can be a de-icing or defogging heating film. | 03-03-2011 |
| 20110047960 | DUAL-FLOW TURBINE ENGINE FOR AIRCRAFT WITH LOW NOISE EMISSION - The invention relates to a dual-flow turbine engine for an aircraft with low noise emission, wherein the opening ( | 03-03-2011 |
| 20110046926 | METHOD OF DETERMINING A STIFF VALUE OF AN AERODYNAMIC COEFFICIENT - The invention relates to a method for determination of a rigid value of an aerodynamic coefficient of an aircraft, in which measurements are made in a wind tunnel on a model of the said aircraft and, on the basis of these measurements, at least one value, known as flexible model value, of this aerodynamic coefficient is determined, characterized in that a rigid value of the aerodynamic coefficient is calculated on the basis of the said flexible model value(s) and a correction taking into account the flexibility of the model. A plurality of flexible model values is determined on the basis of measurements made by varying the parameter q/E and maintaining the angle of incidence at a constant value, and the correction consists in an extrapolation operation providing a value of the aerodynamic coefficient corresponding to q/E=0. As a variant, a single flexible model is determined and the correction consists in adjusting the said value with the aid of a correction factor. | 02-24-2011 |
| 20110046823 | PROCESS AND DEVICE FOR OPTIMISING THE PERFORMANCE OF AN AIRCRAFT IN THE PRESENCE OF A LATERAL DISSYMETRY - A process and device for optimising the performance of an aircraft in the presence of a lateral dissymmetry is disclosed. The device ( | 02-24-2011 |
| 20110046819 | METHOD AND SYSTEM FOR DEACTIVATING A STEERING SYSTEM OF AN AIRCRAFT'S FRONT LANDING GEAR - A method for deactivating a steering system of a front landing gear of an aircraft, including detecting an activated status of the steering system, detecting a pilot control unit in neutral position, detecting towing conditions of the aircraft, detecting a rotational movement of the nose gear, and deactivating the steering system when operations to are verified. The disclosed embodiments also concern a system for implementing this method. | 02-24-2011 |
| 20110042526 | METHOD FOR REDUCING THE TAKEOFF RUN OF AN AIRCRAFT - The method of the invention comprises imparting to the flaps ( | 02-24-2011 |
| 20110042513 | ENERGY-ABSORBING STRUCTURAL ELEMENT MADE OF A COMPOSITE MATERIAL AND AIRCRAFT FUSELAGE HAVING SAID ABSORBER - An aircraft fuselage has at least one reinforcement frame ( | 02-24-2011 |
| 20110036949 | STRUCTURAL MEMEBER OF AN AIRCRAFT HAVING A HOLLOW PART AND INDICATOR OF ICE FORMATION IN SUCH A HOLLOW PART - A structural element of an aircraft includes a hollow part. An indicator provides a visual indication, for example by moving, if ice forms in a given region of the hollow part. | 02-17-2011 |
| 20110036941 | Aircraft with a wing movable along the longitudinal axis of th fuselage - The aircraft has a fuselage, a wing integral with the fuselage in a middle section in a longitudinal direction of the fuselage, and a tail assembly integral with the fuselage. The wing has a rigid central chamber at the fuselage determined in front by a front spar, in the rear by a rear spar, and laterally by root ribs of the wing. The wing is mounted to be movable longitudinally in translation relative to the fuselage between an extreme forward position Xav and an extreme rearward position Xar so that the center of gravity of the aircraft can be displaced longitudinally to be positioned precisely at any time relative to the point of application of the resultant of the aerodynamic lift forces. The wing is mounted to be movable relative to the fuselage through the intermediary of at least two parallel beams, parallel to the longitudinal axis of the fuselage and integral with the fuselage at the rear/forward bulkhead of the fuselage located on each side of the rigid central chamber. | 02-17-2011 |
| 20110030339 | Multifunctional propulsive system for an airplane - A propulsive system for aircraft that has a jet engine and a nacelle surrounding the aforementioned jet engine. The nacelle has a front section fixed relative to the jet engine, and a rear extremity behind the front section, and has a rear section with two petals hinged relative to the front section. Each of the two petals in a position called zero-setting forms an extension of the front section of the nacelle in which the inside and outside surfaces of the petals and, respectively, determine the aerodynamic forms of the rear section, which are in geometric continuity with the inside and outside surfaces and, respectively, that determine the aerodynamic forms of the front section. The petals can be set individually at a positive or negative setting angle to put into play the reverser, APU, air brake, vectorial, and taxiing modes of the propulsive system. | 02-10-2011 |
| 20110029165 | METHOD FOR DETERMINING THE SPEED AT WHICH AN AIRCRAFT BREAKS FREE OF THE GROUND EFFECT - According to the invention, during take-off, the aircraft (AC) is given the tail strike attitude (θ | 02-03-2011 |
| 20110029159 | METHOD AND DEVICE FOR REDUCING ON AN AIRCRAFT LATERAL EFFECTS OF A TURBULENCE - A method and device for reducing on an aircraft lateral effects of a turbulence. The device ( | 02-03-2011 |
| 20110024556 | Aircraft with yaw control by differential drag - An aircraft having an elongated fuselage and a lifting surface fastened to the fuselage. The aircraft has a device for controlling the torque around the yaw axis GZ of the aircraft in which aerodynamic forms that have devices to generate aerodynamic drag are fastened to each end of the lifting surface at non-zero distances from each side of a vertical plane of symmetry XZ of the aircraft. The drag-generating devices are commanded to produce a different aerodynamic drag at each of the two ends to generate a yaw torque on the aircraft. The aerodynamic forms, for example, have winglets improving the aerodynamics of the lifting surface, and provided with aerodynamic drag generators. | 02-03-2011 |
