AIRBUS OPERATIONS (SOCIETE PAR ACTIONS SIMPLIFIEE) Patent applications |
Patent application number | Title | Published |
20130181092 | DEVICE AND METHOD FOR ASSEMBLING TWO SECTIONS OF AIRCRAFT FUSELAGE - Device for assembling two aircraft fuselage sections each comprising a skin and longitudinal stiffeners, the device comprising fishplates fishing couples of mutually aligned longitudinal stiffeners belonging respectively to said sections, each fishplate comprising two fishplate pieces each comprising at least one longitudinal sole plate intended to be fixed to a longitudinal stiffener, and a transverse support head, and at least one demountable connecting member able to mutually clamp the respective support heads of said fishplate pieces to allow a transmission of longitudinal forces between these fishplate pieces. | 07-18-2013 |
20130174572 | METHOD FOR COOLING A THERMAL PROTECTION FLOOR OF AN AFT AERODYNAMIC FAIRING OF A STRUCTURE FOR MOUNTING AN AIRCRAFT PROPULSION SYSTEM - A propulsion system for an aircraft, including a dual-flow turbojet and a mounting structure for mounting this turbojet on the wing surface or on the fuselage of an aircraft. The mounting structure includes an aft aerodynamic fairing including a thermal protection floor to protect the mounting structure from the heat of a primary airstream channelled by an exhaust nozzle of the turbojet, as well as an air inlet provided in a longitudinal aerodynamic wall washed by a secondary airstream of the turbojet and delimiting together with an other similar wall a cavity isolated from the secondary airstream for extracting a cooling airstream from the secondary airstream, and air circulation means fed by the air inlet and having at least one outlet aperture emerging in a space between the thermal protection floor and the exhaust nozzle. | 07-11-2013 |
20120321398 | DEVICE FOR REPAIR OF DEFECTS IN A STRUCTURE - A device for repairing defects in an internal layer of a structure, for example, an aircraft. The device includes a cylindrical body which rotates around its axial direction, a movement conversion device housed in the cylindrical body and assembled such that it is able to move in the axial direction, a configuration device able to cause the displacement of the conversion device by an axial traveling motion, and a cutting element coupled to the cylindrical body and to the conversion device such that the cutting element is able to be made to rotate by the cylindrical body and to be made to move with a radial displacement by the conversion device between a folded position and a deployed position through an opening defined in the cylindrical body in order to machine the internal layer with a cut which depends on the axial displacement of the conversion device. | 12-20-2012 |
20120319681 | DEVICE FOR DETECTION OF DEFECTS IN A RECESS - The invention relates to a device for the detection of defects in a recess, comprising a longitudinal hollow body ( | 12-20-2012 |
20120303747 | TRANSMISSION METHOD ON THE UPLINK OF AN AIRCRAFT - A method for transmitting data, between an on-board segment on board an aircraft and on the ground, via a plurality of access networks. The on-board segment transmits to the ground information providing the association between the access networks and the corresponding IP addresses of the aircraft via these different networks. This information is used by a segment on the ground to make up and update a look-up table between identifiers of the access network and IP addresses of the aircraft. For transmitting a packet on the uplink, the recipient IP address is selected from IP addresses appearing in the look-up table. | 11-29-2012 |
20120286125 | DEVICE FOR ATTACHING AN AIRCRAFT ENGINE, COMPRISING BLOCKS FOR CLAMPING AN ENGINE ATTACHMENT WITH A WEDGE EFFECT - A device for mounting an aircraft engine, including a rigid structure, an engine attachment including a connecting plate superposed to an associated connecting plate of said rigid structure, and means for mutually tightening said plates comprising at least one wedge-effect tightening block and corresponding bearing surfaces of said plates which are conformed so that, when each tightening block is applied against said bearing surfaces along a direction parallel to the plane of the contact surface between both of these plates, this block exerts by a wedge-effect a force for tightening these plates against each other along a direction perpendicular to said plane. | 11-15-2012 |
20120286090 | CONNECTION OF A FUSELAGE TO AN AIRCRAFT WING - A wing box rib ( | 11-15-2012 |
20120234970 | AIRCRAFT ENGINE ATTACHMENT PYLON - The invention relates to an aircraft engine attachment pylon, comprising a box formed by the assembly of a first spar ( | 09-20-2012 |
20120193472 | STAIRWAY FOR AN AIRCRAFT - A stairway used for gaining access from a theoretically horizontal lower level to a theoretically horizontal higher level, and including a succession of intermediate steps between these two levels. A subassembly of intermediate steps corresponding to the steps closest to the lower level is mobile between a first deployed position at which the lower intermediate steps are in the extension of other intermediate steps, and a raised position at which the lower intermediate steps are in a substantially vertical position. | 08-02-2012 |
20120070287 | PROPELLER FOR AN AIRCRAFT TURBINE ENGINE COMPRISING A VANE RETAINING RING MOUNTED ABOUT THE HUB - A propeller for an aircraft turbine engine comprising a plurality of vanes as well as a hub having a plurality of accommodating ports receiving the bases of said vanes, each vane base being rotatably mounted in its associated accommodating port. The propeller also has at least one vane retaining ring structure in the radial direction outwardly from the hub, being cladded around the latter. | 03-22-2012 |
20110270806 | CHECKING OF A COMMUNICATION SYSTEM FOR AN AIRCRAFT UNDER DEVELOPMENT - The invention relates to a method and a device for checking a communication system ( | 11-03-2011 |
20110208376 | ON-BOARD FLIGHT STRATEGY EVALUATION SYSTEM ABOARD AN AIRCRAFT - The invention relates to a process and an on-board system for evaluating flight strategies aboard an aircraft, linked with a flight plan ( | 08-25-2011 |
20110192933 | MAST FOR SECURING AN ENGINE TO AN AIRCRAFT WING - A securing mast for securing an engine to the wing of an aircraft, wherein the device includes two fasteners, a first eng of each fastener being secured to the engine and the second end of each fastener being secured to the wing, wherein the fasteners include hinged junction means capable of modifying the geometry of the aforementioned fasteners in order to modify a distance between the engine and the wing. | 08-11-2011 |
20110174921 | FLIGHT CONTROL SYSTEM FOR AN AIRCRAFT - The invention relates to a flight control system for an aircraft comprising control surfaces ( | 07-21-2011 |
20110127380 | ADVANCED AIRCRAFT COCKPIT - An aircraft cockpit that includes comfort and/or security adjustable equipment in which the adjustments are controlled by an adjustment management system so that, by the unique selection of a position desired by the pilot from at least two positions, the adjustment of each of the aforementioned members is modified from a current value to a predetermined value characteristic of the selected position and depending on the pilot. The data characteristic of the members adjustments controlled by the adjustment management system and depending on the pilot are stored in a mobile medium and read by a means for recognizing the aforementioned management system. The adjustments controlled by the adjustment management system can relate to piloting seats, piloting rudder bars, piloting armrests, individual aeration systems and individual lighting systems. | 06-02-2011 |
20110108662 | ATTACHMENT PYLON FOR AN AIRCRAFT TURBO-SHAFT ENGINE WITH CONCENTRIC HOT AIR CHANNELS - The invention relates to a pylon ( | 05-12-2011 |
20110101963 | CURRENT SENSOR - To produce an insulated current sensor for slaving power devices in the field of avionics, use is made of a magnetic core through which there passes an element traversed by a current to be measured. The magnetic core comprises a secondary winding across the terminals of which are connected an oscillator and a measurement device. The cooperation of the oscillator and of the measurement device makes it possible to circumvent all the traditional drifting of current sensors. | 05-05-2011 |
20110079679 | DEVICE FOR LOCKING AN ENGINE ON AN AIRCRAFT PYLON - The device for locking an engine ( | 04-07-2011 |
20110062135 | DE-ICING OR DEFOGGING SYSTEM FOR OPTICAL INSTRUMENT AND IMAGE ACQUISITION DEVICE PROVIDED WITH SAID SYSTEM - The disclosed embodiments relate to a defogging or de-icing system for an optical instrument including a protection housing. According to the disclosed embodiments, the system includes: a porthole covered on at least one face thereof with a heat conducting film provided at the edge of the useful area of said porthole, the porthole being mounted on the protection housing, heating members placed in contact with the film for heating said film, and a power supply circuit for the heating members. | 03-17-2011 |
20110047529 | METHOD FOR AUTOMATIC SCRIPT GENERATION FOR TESTING THE VALIDITY OF OPERATIONAL SOFTWARE OF A SYSTEM ONBOARD AN AIRCRAFT AND DEVICE FOR IMPLEMENTING THE SAME - Method for automatic script generation for testing the validity of operational software of a system onboard an aircraft and device for implementing the same. The aspects of the disclosed embodiments relate to a script generation method for testing the validity of operational software of a system onboard an aircraft, wherein it includes the following steps: a) identifications by a developer of valid test cases in an interactive manner by positioning an entry point and a stop point respectively at the start and at the end of a function of the operational software being tested. b) observing and recording states of variables of said function via the position of the stop point and the entry point. c) automatically generating a test script firstly by analyzing the states of variables observed during the identification of the test cases and secondly by generating a test script in the form of a source code. d) automatically executing in a test execution environment, tests for the generated test script. | 02-24-2011 |
20110047399 | METHOD AND SYSTEM FOR MANAGING ELECTRICAL POWER SUPPLY OUTAGES ON BOARD AN AIRCRAFT - A method of managing an electrical power supply outage on board an aircraft, including the following operations: —detection of an electrical power supply outage, —measurement of a duration of the power supply outage by measuring a discharge time of a capacitor and comparing this measured duration with a threshold duration, —saving a long outage indication when the duration of the outage is greater than a threshold duration. The disclosed embodiments also relates to a system implementing this method and including: —a circuit for detecting an electrical power supply outage, —a circuit for measuring a duration of the power supply outage, and—a circuit for managing indications able to manage emissions of signals according to the measured duration of the power supply outage. | 02-24-2011 |
20110016358 | METHOD FOR DEBUGGING OPERATIONAL SOFTWARE OF A SYSTEM ONBOARD AN AIRCRAFT AND DEVICE FOR IMPLEMENTING THE SAME - A method for debugging the program of operational software of an onboard system, including flagging the program by positioning flags along an execution path for dividing the aforementioned execution path into adjacent functional intervals; normal execution of the program; acquiring an execution condition of the program by flag condition vectors; when an error is detected, searching a faulty functional interval based on the flag condition vectors, reverse execution of the program in the aforementioned faulty functional interval, and determination and correction of the error. | 01-20-2011 |
20110015900 | METHOD OF ROUTING THE PHYSICAL LINKS OF AN AVIONICS PLATFORM - The invention relates to a method of routing the physical links of a avionics platform inside an aircraft. A physical link connects a plurality (N) of equipment units and is composed of one or more branches, where each branch of said link connects a sender equipment unit to a receiver equipment unit. The proposed method makes it possible to minimize the total cabling length of the platform and, where applicable, to choose among various positions of the equipment units inside the aircraft and/or various routing graphs. | 01-20-2011 |
20100300066 | TURBOJET ENGINE FOR AIRCRAFT - A turbojet engine for an aircraft that includes an engine provided in a nacelle and at least one heat exchanger for cooling down a hot fluid collected in the propulsion system of the turbojet engine before re-injecting the aforementioned partially-cooled hot flow into the aforementioned propulsion system, wherein at least one heat exchanger is a radial heat exchanger extending in the lower portion of the turbojet engine at a lower branching of the turbojet engine. | 12-02-2010 |
20100299559 | METHOD FOR PROCESSING THE VOLUME OF INFORMATION HANDLED DURING THE DEBUGGING PHASE OF OPERATIONAL SOFTWARE ONBOARD AN AIRCRAFT AND DEVICE FOR IMPLEMENTING THE SAME - A method for processing the volume of information handled during the debugging phase of an operational software onboard an aircraft includes: dividing the execution path of the operational software into functional intervals by placing progression points at each function of the program; placing control points associated with each progression point; normal execution of the program that includes: storing the execution state of the program at the location of each progression point, wherein the storage of an execution state results in the suppression of the execution state previously stored for said progression point; upon the detection of an error, searching the progression point corresponding to a faulty function; searching for a software start execution state; regenerating the start execution state; correcting the error in the faulty function; and re-executing the program. | 11-25-2010 |
20100292979 | METHOD FOR ASSISTANCE WITH THE CONSTRUCTION AND VALIDATION OF AN AVIONICS PLATFORM - The invention concerns a method for assisting the construction and validation of an avionics platform. It uses, on the one hand, a functional description of the platform using avionics functions, software modules suitable for executing these functions, and functional link occurrences between these modules and, on the other hand, a material description of this platform using calculation or communication items of equipment and physical links between these equipment. The method according to the invention enables to generate paths between the various items of equipment by using direct physical links and/or physical links belonging to one or more network(s), and subsequently to associate at least one such path to be each functional link occurrence. It also enables to associate to each software module an item of equipment adapted to host it. | 11-18-2010 |
20100292969 | METHOD FOR OPTIMISATION OF AN AVIONICS PLATFORM - The invention relates to a method for optimisation of the avionics platform of an aircraft, intended to implement a set of avionics functions. The association between the platform's functional architecture elements (functions, functional links) and the elements of its equipment architecture (equipment, network paths, direct physical links) are formalised by sets of constraints in the form of linear inequalities of decision variables. Certain segregation or co-location functional constraints are also envisaged. Optimisation of the avionics platform is achieved through the minimisation of cost functions which are linearly dependent on said decision variables. This minimisation under constraints is achieved in an effective manner by the Simplex algorithm. | 11-18-2010 |
20100287776 | METHOD FOR ASSEMBLING A PART OF A METAL MATERIAL AND A PART OF A COMPOSITE MATERIAL USING A FASTENER - A method for assembling a part of a metal material and a part of a composite material, the junction of the two parts being achieved through a fastener having a substantially constant section and received in a first hole formed in the part of a metal material and a second hole formed in the part of a composite material. According to the disclosed embodiments and before assembling the aforementioned parts, the method includes: an expansion step for generating a field of compression stresses at the periphery of the first hole and locally in the material constituting the part of a metal material using an expansion tool; a single boring step for making the first hole and the second hole with a diameter Ø | 11-18-2010 |
20100268517 | METHOD AND TOOL FOR SIMULATION OF THE AERODYNAMIC BEHAVIOUR OF AN AIRCRAFT IN FLIGHT CLOSE TO THE GROUND - The invention relates to a method of computer simulation of the aerodynamic behaviour of an aircraft ( | 10-21-2010 |
20100253692 | DISPLAY SYSTEM FOR AVIONIC AND NON-AVIONIC APPLICATIONS - The present invention relates to a display device for a glass cockpit of an aircraft, intended to provide video streams to a plurality of viewing screens of said glass cockpit, said aircraft being partitioned into a secured area, a so-called avionic world (AW), and a non-secured area, a so-called open world (OW), said system comprising at least one first port intended to receive first data to be displayed from a system ( | 10-07-2010 |
20100253125 | MULTIMODAL HEADREST FOR VEHICLE SEAT - The invention relates to a seat for a vehicle, that includes a headrest with a headstall for supporting the head of a passenger in the seat, wherein the occupant may or may not wear a protection helmet depending on the circumstances. The headstall can assume at least three stable positions: a first position for the cervical support of the head of the seat passenger in which the headrest provides a cervical support function with or without wearing a helmet; a second position for the occipital support of the head of the seat passenger in which the headrest provides an occipital support function without wearing a helmet; a third position for the occipital support of the head of the seat passenger in which the headrest provides an occipital support function while wearing a helmet. | 10-07-2010 |
20100230122 | AIRCRAFT FIRE EXTINGUISHING DEVICE AND MOUNTING METHOD - A fire extinguisher device for aircraft has a hanger structure ( | 09-16-2010 |
20100218172 | METHOD FOR SIMULATING A SYSTEM ON BOARD AN AIRCRAFT FOR TESTING AN OPERATING SOFTWARE PROGRAM AND DEVICE FOR IMPLEMENTING SAID METHOD - A method for simulating a real on-board system for testing an operating software program. The disclosed embodiments include preparation of a test to be carried out on the operating software program, by adding and/or removing control functions to/from a library; execution of the operating software program of the real on-board system in a simulated environment; simulation of a dedicated peripheral by activating functions from the library; transmission of the test results from the dedicated peripheral to the results folders stored on the host platform and recording of the aforementioned results. | 08-26-2010 |
20100215499 | BLADE RETAINING DEVICE FOR TURBO MACHINE PROPELLER - The invention concerns an aircraft turbomachine propeller comprising a plurality of blades ( | 08-26-2010 |
20100215498 | BLADE FOR TURBOMACHINE RECEIVING PART, COMPRISING AN AIRFOIL PART INCLUDING A MECHANICAL FUSE - The invention refers to a blade ( | 08-26-2010 |
20100209254 | VANE FOR AIRCRAFT TURBINE ENGINE RECEIVER, PROVIDED WITH TWO HOLLOW CORES LODGED IN ONE ANOTHER - The invention relates to a vane ( | 08-19-2010 |
20100206986 | CURRENT RETURN NETWORK ELEMENT FOR AN AIRCRAFT - The invention relates to a current return network element ( | 08-19-2010 |
20100201517 | DEVICE AND METHOD FOR PROTECTION AGAINST INTRUSION INTO THE LANDING GEAR HOUSING OF AIRCRAFT - The invention relates to a device for protection against intrusions into the landing gear housings of an aircraft, including at least one sensor, for at least one housing, covering at least one housing entry area and connected to a calculator ( | 08-12-2010 |
20100200631 | Secured device for a headset support - A device to support a headset along a wall of a vehicle, that includes a hook that has a base to receive a headband of the headset, with this base being intended to be fastened transversally to the wall by its back and being integral at the opposite front with an external element for holding the headband on the base. The hook has on opening between the back and the external element with a width I at least equal to the width of the headband, permitting the passage of the headband toward the base or during removal from the base. The aforementioned device has an anti-release element blocking the opening over a width at least large enough to prevent the passage of the headband through the opening. This anti-release element can be displaced by manual action directly on the anti-release element or through the headset into a release position to allow the passage of the headband. | 08-12-2010 |
20100198431 | MAINTENANCE COMPUTER SYSTEM FOR AN AIRCRAFT - A maintenance computer system for an aircraft, including a network partitioned into a secured avionics zone and an open zone. The system includes a first software module accommodated in the avionics zone and a second software module accommodated in the open zone, the first module configured to follow a fault-finding logic tree, and the second module configured to present an electronic maintenance document, with the path along the fault-finding logic tree followed by the first module automatically and synchronously generating a presentation by the second module of pages of the maintenance document associated respectively with nodes of the tree. | 08-05-2010 |
20100192540 | CLOSING SYSTEM FOR AN AIRCRAFT FAN SHROUD - A closing system for a fan cowling on a jet engine of an aircraft that has at least one assembly including a male contrivance integral with the cowling, and a female contrivance integral with the jet engine that has a lower element forming at least one first guide ramp and an upper element forming at least one second guide ramp, with the aforementioned female contrivance being suitable on the one hand for guiding the male contrivance during the opening and/or the closing of the fan cowling, and on the other hand providing a limitation of the radial and circumferential displacements of the male contrivance. | 08-05-2010 |
20100170999 | MORE ELECTRIC FLIGHT CONTROL SYSTEM ONBOARD AN AIRCRAFT - The invention relates to a more electric flight control system onboard an aircraft provided with flight control surfaces and means of controlling these surfaces, that comprises at least one local electro-hydraulic generator (HPP | 07-08-2010 |
20100170983 | Flight control system for an aircraft - Power takeoff means ( | 07-08-2010 |
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 |
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 |
20100136293 | Curved structural part made of composite material and a process for manufacturing such a part - The disclosed embodiments concern a curved structural part composed of a composite material with reinforced, continuous fibers whose cross section includes at least two wings, with said fibers extending from one wing to the other, with said structural part having a variation in the width of its section parallel to the local radius of curvature. The structural element that results from assembling the parts in the disclosed embodiments therefore has local widening of the section at the connections between the parts constituting a structural element, such as an aircraft fuselage frame, and widening at the connection with the floor profiles, if such a profile is used to make an aircraft fuselage structure. The disclosed embodiments also concern a process for manufacturing such a part, as well as a device for advantageously implementing such a process. | 06-03-2010 |
20100133377 | AIRPLANE WITH FLAT REAR FUSELAGE SAID QUEUE-DE-MORUE EMPENNAGE - An aircraft includes a fuselage having a shape elongated along a longitudinal axis X of the aircraft and at least one wing fixed to the fuselage between the front end and the rear end of the fuselage. The fuselage includes a substantially cylindrical central part and a rear tapered part on which a vertical empennage is fixed. Between a section connecting the rear part with the central part of the fuselage and the rear end the maximum width of each section of the fuselage is constant or increasing rearwards up to a maximum width L of the fuselage, the height of each section of the fuselage is decreasing rearwards in the direction of the negative X, so that the rear end of the fuselage forms a trailing edge having a small thickness which is substantially horizontal in an aircraft reference system and substantially rectilinear. | 06-03-2010 |
20100132378 | HYDRAULIC SYSTEM FOR TRANSMISSION OF FORCES BETWEEN AN AIRCRAFT TURBOPROP AND AN ATTACHMENT DEVICE - This invention relates to a force transmission system ( | 06-03-2010 |
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 |
20100102169 | FLOOR MADE OUT OF COMPOSITE MATERIAL FOR TRANSPORT VEHICLE AND PROCESS FOR MANUFACTURING PROCESS SUCH A FLOOR - The invention concerns a floor for a transport vehicle that can be attached to a vertical frame structure ( | 04-29-2010 |