AIRBUS OPERATIONS (SAS) Patent applications |
Patent application number | Title | Published |
20160122037 | SAFETY DEVICE FOR AN EXTENSION SOCKET - A socket system for the protection against lightening of an aircraft disposed between a connection terminal of the aircraft and an end connector of a generator set powered by a power supply cable having several electrical conductors includes an extension socket connected between the end connector and the connection terminal and a safety device including in a housing made of electrically insulating material, and clipping means designed to clip an electrical signal. The installation of such a safety device prevents the propagation of an electrical overvoltage beyond the safety device. | 05-05-2016 |
20160107763 | METHOD AND DEVICE FOR ASSISTING THE MANAGEMENT OF PROCEDURES, NOTABLY OF FAILURES OF SYSTEMS OF AN AIRCRAFT - The device includes a centralized warning system able to detect failures of systems of the aircraft and to display procedure lines on a screen, a procedure line including a text giving an indication of an action to be executed at least in the case of a failure, a semantic analysis module for determining from a current procedure line if the action to be executed is associated with a controllable control button and for implementing a semantic analysis of the text of the procedure line using word recognition and in order to derive therefrom indications relative to the controllable control button, these indications including at least an identification of the control button, and a warning unit receiving these indications and being able to warn a member of the crew. | 04-21-2016 |
20160101906 | MEMBRANE TYPE STOPPER - A stopper for a tank having an opening includes a body which is provided to be fixed in the opening and which has a hole, a membrane which is fixed to the body and of which a portion completely blocks the hole, a core which is fixed to the portion of the membrane which blocks the hole, and stop means which are provided to permit a movement of the core between a blocking position which corresponds to the non-broken membrane which blocks the hole, and an open position which corresponds to the broken membrane which is spaced apart from the hole, and to keep the core fixedly joined to the body in an open position. The knowledge of the characteristics of the membrane enables the force from which the stopper opens to be known. | 04-14-2016 |
20160091296 | METHOD FOR DETECTING A STRAND GAP IN FIBER FABRIC AND A DEVICE FOR ITS IMPLEMENTATION - A method for detecting a spacing defect between two adjacent strands of a layer of a fiber fabric includes displacement of an inductive sensor relative to the fiber fabric, and identification of a defect based on a signal generated by the inductive sensor. The invention also relates to a device for its implementation. | 03-31-2016 |
20160031563 | FOLDABLE GUIDING VENTILATOR COVER FOR AN AIRCRAFT ENGINE ASSEMBLY - For gains in terms of aerodynamic performance levels, an aircraft engine assembly includes a turbomachine, a fastening strut for the turbomachine, and at least one foldable ventilator cover which surrounds the turbomachine and which includes: a first cover sector which includes a first end portion which is mounted so as to be articulated to the fastening strut, along a first articulation axis, and a second cover sector which includes a first end portion which is mounted so as to be articulated to a second end portion of the first cover sector, along a second articulation axis parallel with the first articulation axis. The second end portion is mounted so as to be guided at one side and the other thereof by a thrust inverter cover of the engine assembly and an air inlet structure of this assembly, respectively. | 02-04-2016 |
20160027309 | Method And Device For Determining An Operational Distance Of An Unspecified Termination Segment Of An Aircraft Flight Plan - The device includes a receiving unit for receiving at least a start point of an unspecified termination segment, an orientation of the unspecified termination segment and a start point of a following segment, a first computation unit for calculating a median plane passing through the start point of the following segment and perpendicular to this following segment, a second computation unit for calculating an operational distance, called calculated operational distance, as a function of the position of the start point of the unspecified termination segment relative to the median plane, using geometric data, and a transmission unit for providing at least one user means with the calculated operational distance. | 01-28-2016 |
20150375866 | Aeroplane Equipped With An Internal Escape Hatch Incorporating A Pressure Regulating System - An aeroplane includes an external skin and an internal bulkhead delimiting a cabin, and an escape opening passing through the external skin and the internal bulkhead. The escape opening is closed off by an external escape hatch disposed flush with the external skin. The aeroplane also includes an internal escape hatch that closes off the escape opening disposed flush with the internal bulkhead, and pressure regulating means capable of automatically triggering an opening of the internal escape hatch or a part of the internal escape hatch when a pressure differential on both sides of the internal escape hatch exceeds a determined value. | 12-31-2015 |
20150375845 | AEROPLANE EQUIPPED WITH AN INTERNAL ESCAPE HATCH HAVING A DOUBLE OPENING CONTROLLER - An aeroplane includes an escape opening passing through an external skin and an internal bulkhead. The escape opening is closed off by an external escape hatch having an external opening controller. The aeroplane further includes an internal escape hatch that closes off said escape opening flush with the internal bulkhead, and kept closed by at least one catch movable between a locked state and unlocked state, a first opening controller that controls the passage from the locked state to the unlocked state of the catch being accessible from inside the aeroplane, and a second opening controller that controls the passage from the locked state to the unlocked state of the catch being positioned such that the actuation of the external opening controller of the external escape hatch or the passage of the external escape hatch from the closed position to the open position causes the second opening controller to be actuated. | 12-31-2015 |
20150367947 | AIRCRAFT PROPULSION ASSEMBLY COMPRISING AT LEAST ONE BRUSH SEAL RESISTANT TO HIGH-TEMPERATURE - A seal is interposed between two surfaces of an aircraft propulsion assembly. The seal includes at least two layers each comprising a plurality of strands made of a heat-resistant material, the strands of a first layer being oriented in a first orientation and the strands of a second layer being oriented in a second orientation different than the first orientation. | 12-24-2015 |
20150321742 | STIFFENER FOR AN AIRCRAFT FUSELAGE, METHOD FOR MANUFACTURING SAME, AND AIRCRAFT FUSELAGE EQUIPPED WITH SUCH A STIFFENER - This stiffener is intended for a fuselage. It comprises a hollow section that can be trapezoidal, with a base attached to the fuselage or to the floor, high enough rising sides and a top side contributing to the rigidity and cohesion of the stiffener. A direct assembly with the fuselage is possible. The base is made of two edges provided one on the other or in front of the other. This rigid stiffener, in spite of its discontinuous section, can be manufactured by simple foldings of a planar metal sheet at the beginning. | 11-12-2015 |
20150307198 | ASSEMBLY FOR AN AIRCRAFT COMPRISING A MOVEABLE ACCESS PANEL - An assembly for an aircraft with an engine includes an attachment device intended to support the engine, a pod intended to surround the engine and including a cover, joints intended to allow articulation of the cover and allow movement of the cover relative to the attachment device between a closed position and an open position, and at least one access panel mounted moveably on the cover between a closed position, in which the access panel extends continuously between the cover and the attachment device when the cover is in the closed position, and an open position in which the access panel is remote from its closed position. The assembly includes a handle which can be operated from the outside of the cover between a first position and a second position, and a transmission system provided to move said or each access panel from its closed position to its open position. | 10-29-2015 |
20150306683 | SURFACE MACHINING DEVICE FOR A CELLULAR STRUCTURE - A device for machining a slot on a surface of a cellular structure includes a machining head that includes a chassis, a rotary tool rotating about a tool axis perpendicular to the direction of the slot, two guide wheels arranged on either side of the rotary tool that have a plurality of teeth configured and positioned such that they penetrate the cells of an alignment of the cellular structure. The machining head includes a link between the chassis and at least one guide wheel that enables a degree of freedom in a lateral direction parallel to the tool axis such that the guide wheel is movable in relation to the rotary tool in the lateral direction. | 10-29-2015 |
20150262124 | ARTIFICIAL INTELLIGENCE SYSTEM AND METHOD FOR PROCESSING MULTILEVEL BILLS OF MATERIALS - A bill of material (BOM) management system is provided using artificial intelligence for processing a product data or configuration change of a product between a plurality of functional domains using a dynamic link and a semantic network having product knowledge about the change via a network. A Decompose/Recompose/Multi-arrange (DRM) process module manages product configuration information of the product by performing a decompose process, a recompose process, and a multi-arrange process, wherein the decompose process performs grouping of the product elements based on the product knowledge of the semantic network, the recompose process performs regrouping of the product elements in a selected domain context, and the multi-arrange process performs rearranging of the product elements to facilitate a different product structure of the BOM in the different functional domain. | 09-17-2015 |
20150253150 | DEVICE FOR DETERMINING NAVIGATION PARAMETERS OF AN AIRCRAFT DURING A LANDING PHASE - A device for determining navigation parameters of an aircraft during a landing phase includes a video system including at least one digital video camera arranged on the aircraft, the digital video camera being configured to generate on the aircraft current video data relating to at least one characteristic point on the Earth, whose coordinates are known, and a data processing unit including an extended Kalman filter and configured to determine the navigation parameters on the basis of current navigation data of the aircraft, arising from a satellite navigation system, current inertial data of the aircraft, as well as said video data. | 09-10-2015 |
20150219048 | ASSEMBLY DEVICE FOR DOUBLE-SKINNED AIRCRAFT FUEL PIPES - An assembly device between two sections of a double-skinned fuel pipe of an aircraft has a clamp for assembling the internal pipes, a coupling device for assembling the external pipes, a fitting extending between the ends of the external pipes of the first and second sections, with a shape complementary to the shape of an internal portion of the coupling device, and such that its section through any cutting plane perpendicular to the longitudinal axis common to the coupling device and the external pipes contains the smallest surface delimited by: a line corresponding to the intersection of the internal surface of the coupling device with this cutting plane and a straight line cutting said line at two points, this straight line being tangential to the orthogonal projection in this cutting plane, of the internal surface of the external pipes of the first or of the second section. | 08-06-2015 |
20150204675 | METHOD AND SYSTEM FOR AUTOMATICALLY MODIFYING A LATERAL FLIGHT PLAN OF AN AIRCRAFT - A system for automatically modifying a lateral flight plan of an aircraft includes modifying means adapted to modify the flight plan by an action to chosen among the following actions: deleting, adding and moving at least one waypoint of an initial flight plan (T | 07-23-2015 |
20150192927 | METHOD AND DEVICE FOR GUIDING AN AIRCRAFT DURING A LOW LEVEL FLIGHT - The guidance device of the aircraft includes a unit for constructing a flight trajectory of the aircraft, which adapts the height of the flight trajectory to a downstream relief so as to allow the aircraft to clear this downstream relief by implementing a rectilinear climb at maximum rate of climb of the aircraft, along a rectilinear lateral direction corresponding to the direction of the aircraft at the moment of the triggering of the maneuver. | 07-09-2015 |
20150175252 | Method For Producing A Central Wing Box - A method for producing a central wing box including an upper panel, a lower panel, a front longeron, a rear longeron and four corners, wherein at least one panel and one longeron are obtained from a single flat metal wall which is bent along a bending line at approximately 90° which corresponds to a corner connecting said panel to said longeron. | 06-25-2015 |
20150112583 | METHOD AND DEVICE FOR REVISING A LOW-ALTITUDE FLIGHT PHASE OF A FLIGHT PATH OF AN AIRCRAFT - A device for revising a low-altitude flight phase of a flight path of an aircraft includes an input unit configured to allow an operator to input parameters to define an intermediate flight section (Si) which has to be inserted into a low-altitude flight phase, and a processing unit configured to calculate a profile relating to the intermediate flight section (Si) using input parameters, and to automatically insert this profile into the flight phase between a first upstream part (P | 04-23-2015 |
20150090047 | Method For Testing A Batch Of Material Used For Obtaining Layers Of Fibres Intended For Manufacturing A Composite Material Component - A method for testing a batch of material used to obtain layers of fibres includes taking a specimen from the batch of material, exerting a tensile force on the specimen, heating the specimen so as to relax the fibres if the specimen contains stresses, after a predetermined period of time, no longer heating and no longer exerting the tensile force on the specimen, measuring a residual extension of the specimen which corresponds to a variation in length of at least a part of the specimen in the direction of the tensile force, before and after the tensile force, and considering the batch of material not to be compliant if the residual extension exceeds a given threshold. | 04-02-2015 |
20150084491 | Electronics Cabinet With Ventilation System - A cabinet designed to accommodate at least one item of electronic equipment and a system for interconnecting such a cabinet with the external networks for blowing and extracting air. The system includes at least one of a blowing inlet and an extracting outlet including a plurality of orifices and at least one hollow structural upright as a part of the blowing circuit or of the extracting circuit. | 03-26-2015 |
20150034767 | Method For Regulating The De-Icing Of A Leading Edge Of An Aircraft And Device For Its Implementation - A method of regulating the de-icing of a leading edge of an aircraft includes regulating the flow of air used for de-icing by at least a first regulator valve in accordance with two regulation levels, a first regulation level corresponding to the regulated position of the first regulator valve and a second regulation level corresponding to the fully open position of the first regulator valve. A de-icing device enables implementation of the regulation method. | 02-05-2015 |
20140361924 | ON-BOARD METEOROLOGICAL RADAR HAVING A ROTATING ANTENNA - A meteorological radar installed on board an aircraft, including a mechanical support fixed to a bulkhead of a nose of the aircraft, wherein an antenna is mounted on the mechanical support to enable turning mobility around an axis of rotation. The antenna includes a pedestal, on which at least one blade, extending radially along the axis of rotation, is installed. A free side of the blade, along which a plurality of radiating elements is distributed, perceptibly has the shape of a portion of conic in a plane including the axis of rotation. Because the blade is mobile only in rotation along the axis of rotation, and the selection of the emission/reception direction is performed electronically, not mechanically, the space and length requirements of the meteorological radar are fixed, whether the meteorological radar is in operation or not, and are determined based on the eccentricity and parameter of the conic. | 12-11-2014 |
20140346280 | System And Method For Controlling An Aircraft - A system for controlling an aircraft control parameter including a control interface including a mobile element configured to move on a travel, of which at least two portions are separated by a neutral position; a return element bringing the mobile element back to the neutral position when it is not actuated; and an interaction element, and a control unit configured to memorize an item of information corresponding to a first position of the mobile element at an instant of activation of the interaction element; and generate a setpoint of the aircraft control parameter, as a function of a control associated with the first position of the mobile element for which said information has been memorized; or a current position of the mobile element, when this current position is situated on the same portion of travel as the first position and is more remote than the latter from the neutral position. | 11-27-2014 |
20140343763 | METHOD AND DEVICE FOR DISPLAYING THE PERFORMANCE OF AN AIRCRAFT WHEN CLIMBING AND/OR DESCENDING - The display device ( | 11-20-2014 |
20140343762 | DEVICE AND METHOD TO INCREASE PILOT FOCUS - An interactive task organizer application may encourage a pilot to be more alert and engaged while operating the aircraft, despite that automation has made the job more passive. The interactive task organizer application may have access to flight data, and may use this data to create a virtual environment that encourages pilots to perform flight related tasks and to make visible explicit mission goals at a global and local level. | 11-20-2014 |
20140343760 | METHOD AND DEVICE FOR AUTOMATICALLY DETERMINING AN OPTIMIZED APPROACH AND/OR DESCENT PROFILE - A method and device for automatically determining an optimised approach and/or descent profile for an aircraft are provided. The device comprises means for optimising an approach and/or descent profile of an aircraft avoiding long and steep geometric segments, the device to this end inserting an idle segment, if it satisfies the restrictions, in the profile relating to the descent phase and/or to the approach phase, wherein said idle segment can be followed by a geometric segment. | 11-20-2014 |
20140334922 | AIRCRAFT TURBOJET NACELLE - The invention relates to an aircraft turbojet nacelle including a cowling assembly ( | 11-13-2014 |
20140321944 | GUIDING DEVICE WHICH IS INTENDED TO BE INTERPOSED BETWEEN A DEVICE FOR FIXING COMPONENTS OF AN ASSEMBLY, AND A DEVICE FOR PROTECTING THE FIXING DEVICE - An assembly comprising at least two non-metal components which are fixed to each other using at least one fixing system. The fixing system includes a fixing device with a fixing element which is provided with a head and a rod, and a crimping ring which is in contact with one of the components. A protection device is a part of the fixing system which delimits a cavity for confining gas around a portion of the device comprising the crimping ring. In order to improve the repeatability of the operation for positioning the protection device, a guiding device is provided which includes an assembly element on the portion of the fixing device, and an element for guiding the protection device. | 10-30-2014 |
20140318474 | METHOD AND DEVICE FOR VISUALLY SCARING ANIMAL SPECIES, IN PARTICULAR BIRD SPECIES - A device for visually scaring animal species, in particular bird species includes means for generating at least one visual signal including at least one image, varying in size over time, which simulates approach via an increase in the size of the image. For example, the visual signal includes one of the following images: eyes, a disc, and a spiral. | 10-30-2014 |
20140288815 | METHOD AND DEVICE FOR DETERMINING THE RISK OF COLLISION ON THE GROUND OF AN AIRCRAFT - This method of determining the risks of collision of an aircraft ( | 09-25-2014 |
20140288732 | Automatic Piloting Method And System For An Aircraft - The automatic piloting system includes an element for automatically supplying a computation unit, when the aircraft is guided according to a descending corrected speed and a new corrected speed which is greater than the corrected speed used for guidance of the aircraft is input by the pilot, with a predetermined maximum Mach number which replaces the current Mach number and which is intended to form, together with the new input corrected speed, a pair of speeds which is taken into account by the computation unit for determining the guidance instructions for the aircraft. | 09-25-2014 |
20140278292 | Method for coupling non-destructive inspection data for a material or structure to an analysis tool - A computer aided method is provided for coupling non-destructive inspection data for a material or structure to an analysis tool. The method includes receiving a voxel data representation of a damaged area of the material or structure, and generating a finite element mesh based on the voxel data representation. The finite element mesh includes a plurality of nodes, each node corresponding to one or more voxels of the voxel data representation. The method further includes integrating damage information from the voxel data representation into the finite element mesh by applying at least one integration rule, the damage information indicating whether or not a given voxel has sustained damage. Damage information for areas of the finite element mesh that do not include damage information is interpolated by applying at least one interpolation rule. A finite element model including a finite element mesh having damage information associated therewith is output. | 09-18-2014 |
20140277857 | METHODS, SYSTEMS AND COMPUTER READABLE MEDIA FOR ARMING AIRCRAFT RUNWAY APPROACH GUIDANCE MODES - Methods, systems, and computer readable media are disclosed for direct arming aircraft runway approach guidance modes, for example and without limitation, for aircraft operational. In some aspects, a method for directly arming a runway approach guidance mode of an aircraft includes displaying on a display unit an airport, selecting the airport and selecting an active runway for final approach, displaying an path toward the selected final approach runway, selecting the final approach runway, displaying on the display unit at least one symbol associated with at least one runway approach guidance mode, and arming at least one of the at least one runway approach guidance mode. | 09-18-2014 |
20140263836 | FISH JOINT DEVICE HAVING AN IMPROVED MECHANICAL HOLD - The invention relates to a fish joint device intended to attach securely first and second structural elements of an aircraft to one another, having two fishplates positioned either side of the structural elements, and attached to them by a set of fishplate through fastenings. According to the invention, the fish joint device includes at least one intermediate fish joint plate which is positioned between one of said fishplates and said structural elements which said intermediate plate partly covers, and which is attached to these elements by a set of intermediate plate through fastenings which includes the set of fishplate through fastenings. | 09-18-2014 |
20140251529 | Method for producing an extruded stiffened panel, and device for implementing same - A method for producing a part made of a composite material, including a skin and at least one stiffener made of strips, which are in turn made of one or more plies of fibers impregnated with a non-polymerized resin. The method includes the steps of: producing a preform of the part by pulling the strips through a die for shaping and positioning the skin and the stiffeners, a polymerization core being provided between a first strip and a second strip prior to the passage thereof through the die; and pressing the resulting preform in a hot press for a duration dt while applying a pressure P and at a temperature T for polymerizing the resin of the strips in the hot press over a pressing length L that is shorter than the length of the panel. | 09-11-2014 |
20140236396 | METHOD AND SYSTEM FOR DETECTING JAMMING AND/OR UNCONTROLLED MOVEMENT OF AN AIRCRAFT CONTROL SURFACE - A system for detecting jamming and/or uncontrolled movement of an aircraft control surface includes first means for estimating the value of at least one parameter of an equation simulating the feedback loop dynamic of the control surface, according to a recursive autoregressive method with exogenous variable of RARX type in a recursive least squares way, and second means for detecting jamming and/or uncontrolled movement of the control surface, according to the estimated parameter value by the application of a decision test in the parametric space. | 08-21-2014 |
20140222256 | A METHOD OF ASSISTING PILOTING AN AIRCRAFT BY ADAPTING THE DISPLAY OF SYMBOLS - The invention relates to a method of assisting piloting an aircraft. The method is performed when the real position of a symbol for display lies outside the display limit of the screen. The symbol is representative of a parameter associated with the dynamic behavior of the aircraft (FPV, . . . ) or liable to influence said behavior (FD, . . . ). The symbol possesses two components, and the first component is to be given precedence on display over the second component. In the method, the display of the symbol depends firstly on the orthogonal projection (FPV-lock) of the real position (FPV) of the symbol onto the axis of the first component, and secondly on the position of said projection relative to the display limit of the screen. Such a display makes it possible to give reliable information to the pilot. | 08-07-2014 |
20140216635 | METHOD FOR ASSEMBLING ELEMENTS OF COMPOSITE MATERIAL FOR AIRCRAFTS, WITH STRESS RELAXATION IN THE ELEMENTS - The invention relates to a method of assembling composite material parts ( | 08-07-2014 |
20140210258 | ELECTRICAL CABINET OF AN AIRCRAFT INCORPORATING AN IMPROVED ELECTRICAL CONNECTION SYSTEM - An electrical cabinet of an aircraft is provided. The electrical cabinet includes at least one motherboard including on a first face sockets into which are plugged PCB boards ensuring one or more electrical functions, the said electrical cabinet being linked to the electrical circuit of the aircraft organized as various electrical harnesses by way of an electrical connection system, characterized in that the electrical connection system comprises at the level of the second face of the motherboard at least one additional layer, the free face of the last additional layer comprising sockets each ensuring electrical connection with an electrical harness of the aircraft, the additional layer or layers comprising tracks which make it possible to reorganize the electrical circuits emanating from the sockets intended for the PCB boards so as to render them compliant with the sockets intended for the harnesses of the aircraft. | 07-31-2014 |
20140209742 | AIRCRAFT ELECTRICAL CORE - An electrical core of an aircraft is provided. The electrical core includes at least one shelf on which is disposed at least one module containing components and comprising at least one input able to be linked to at least one power supply cable and at least one output able to be linked to at least one output cable. In the module, the output cable or cables travel under or in the shelf disposed under the module. | 07-31-2014 |
20140209740 | AIRCRAFT COCKPIT, IN PARTICULAR THE FRONT PORTION OF AN AIRCRAFT COCKPIT - A device for mixing at least two separate streams of components which, when mixed, form a combined fluid stream. The device comprises a conduit with at least two separate passageways leading to exit openings at an end face of the conduit. Each passageway communicates with a separate component stream and is arranged to direct the separate component stream in a downstream direction. The exit openings each have a predetermined cross-sectional flow area. A separate channel is located at a downstream end of each passageway exit opening. The channels are arranged to redirect the flow from each passageway to an axial direction. A single mixing chamber communicates with all of the separate channels, the mixing chamber being arranged to receive each of the component streams at an upstream end thereof and to permit a mixing of the component streams. An outlet is arranged downstream of the mixing chamber through which the combined fluid stream is dispensed. | 07-31-2014 |
20140209739 | METHOD AND DEVICE FOR LATERAL CONTROL OF A TAXIING AIRCRAFT - The device includes, but is not limited to a calculating unite for automatically applying, if conditions for turning of the aircraft are met, a symmetrical braking value at a brake assembly, then in the course of the turn automatically distributing this symmetrical braking value in differential braking between braking device of the left main landing gear and braking device of the right main landing gear of the aircraft, as a function of current directional command orders, in such a way as to maintain a constant overall braking level, at least for directional command orders below a predetermined threshold. | 07-31-2014 |
20140203146 | Method And Device For Using Hot Air To De-Ice The Leading Edges Of A Jet Aircraft - A de-icing device includes a hot air circuit including an inlet for hot air bled from an engine, and a duct connecting the inlet to an outlet of the circuit which opens towards the leading edge. The device also includes electrical heating means associated with the duct, and control means for controlling the heating means connected to detection means that detect the temperature of the hot air downstream of the heating means and are able to activate these if the detected temperature of the bled air is below a value corresponding to a minimum temperature required for de-icing, increased by a predetermined margin. The range of temperatures of the hot air supplied to the leading edge is lowered overall, whereas the minimum de-icing temperature is assured. Composite materials can be used near the leading edge without being damaged. | 07-24-2014 |
20140197217 | MOUNTING DEVICE FOR AIRCRAFT SUPPLY SYSTEMS - A mounting device for aircraft supply systems comprises a cross member and at least one support module including a body having a shape complementary to that of a cross member. The body includes a structure for securing an aircraft supply system, an opening, and a pin, wherein the opening forms a guide that is able to receive a portion of the pin. The cross member includes grooves that are regularly spaced apart in the direction of elongation of said cross member. The pin has a shape complementary to that of the grooves and has a lip transverse to the direction of elongation of the pin. The support module is anchored to the cross member by the pin being inserted into the opening, the pin engaging with one of the grooves, as far as an anchoring position in which the lip is in contact with the support module. | 07-17-2014 |
20140183298 | FLEXIBLE LINKING DEVICE FOR AN AIRCRAFT PROPULSION SYSTEM - A linking device including two hinge pins and having flexibility allowing vibrations between these two shafts to be filtered. The device includes a stack of plates connected to one another by layers of elastomer material. Plates of a first type are coupled to one of the shafts in relation to the movements parallel to the plates, while the plates of a second type are coupled to the other shaft in relation to the movements parallel to the plates, so as to allow relative movement of the shafts parallel to the plates. This linking device may be used in particular as a connecting rod, spreader beam or three-point shackle used in connecting a turbine engine to a pylon in a propulsion system of an aircraft such as an airplane. | 07-03-2014 |
20140177146 | FLIGHT DATA RECORDER - The invention relates to a flight data recorder. It is equipped with capsules designed to break at determined depths. The capsules release hydraulic tracing elements, generating a luminous streak in the water, when they are broken, so that the searches for the flight data recorders, or black boxes, are made easier. | 06-26-2014 |
20140168907 | OVERHEAD PANEL FOR AN AIRCRAFT COCKPIT AND AIRCRAFT INCLUDING SUCH A PANEL - The invention relates to an overhead panel able to be positioned in an aircraft cockpit, which includes an assembly of independent submodules ( | 06-19-2014 |
20140168871 | ELECTRONICS STRUCTURE COMPRISING AT LEAST ONE BARRIER IMPERMEABLE TO FINE PARTICLES - An electronics structure includes at least one barrier impermeable to fine particles, interposed between at least one Electrical and/or Electronics (“E & E”) system and the frame of the structure. The barrier delimits, with the frame and the E & E system, a first area isolated from the outside of the electronics structure. The structure makes it possible to isolate sensitive electrical and electronic components from fine particles such as dust dispersed outside the electronics structure. | 06-19-2014 |
20140166809 | Improved Aircraft Windshield Assembly - An aircraft windshield assembly includes at least one window pane, a frame against which the pane bears, at least one flange for clamping the pane against the frame, and at least one cavity delimited between the pane, the frame and the flange. A member of profiled cross-section substantially fills the cavity and over at least part of its periphery has formations in relief in the form of flutes which with a facing surface define seal-forming baffles. | 06-19-2014 |
20140165337 | FIBRE LAYING MACHINE COMPRISING A ROLLER WITH PIVOTING RINGS - A fibre laying machine includes a laying head with a roller able to pivot about an axis of rotation and to apply a plurality of preimpregnated fibres to an application surface by rolling over the application surface. The fibres are distributed along a lower generatrix of the roller and in contact with an exterior surface of the roller over an angle of wrap. The roller includes a cylindrical body, pivoting rings around the body, and means for immobilizing the pivoting rings with respect to the body in a direction parallel to the axis of rotation. | 06-19-2014 |
20140165285 | TOILET AREA FOR AN AIRCRAFT CABIN, IN PARTICULAR FOR A FLYING WING AIRCRAFT - A toilet area for an aircraft cabin comprising an access door and housing a toilet bowl. The toilet area also comprises an evacuation exit, the access door occupying a closed position in the toilet area in a toilet configuration and a folded position in the toilet area in an evacuation configuration. Usage in particular in a flying wing aircraft is provided. | 06-19-2014 |
20140159949 | AIRCRAFT COMPRISING AN ONBOARD WEATHER RADAR ANTENNA PROVIDED WITH INCLINED PANELS - An aircraft comprising a fuselage and a radome fixed to the fuselage. The radome defines a housing and the fuselage comprises a sealed bulkhead closing the housing. A weather radar antenna comprises a main panel. A plurality of peripheral panels are arranged around the main panel, inclined from a planar surface of the main panel and located on the same side of the planar surface. The housing contains the antenna which is mounted on the fuselage through a mechanical support fixed to the fuselage and to the weather radar antenna on the same side of the planar surface as the peripheral panels. A bird strike shield is located between the antenna and the sealed bulkhead. The shield comprises a dome with a top and a base, the base being fixed to the aircraft fuselage. An opening is formed at the top of the dome through which the mechanical support passes. | 06-12-2014 |
20140158828 | AIRCRAFT COMPRISING A WING BOX AND A FUSELAGE PROVIDED WITH A CONNECTING DEVICE CONNECTED TO THE WING BOX - An aircraft comprising a wing box and a fuselage provided with a connecting device configured to be connected to the wing box and to transmit thereto stresses undergone by the fuselage during manoeuvres of the aircraft are provided. The connecting device is formed by a keel beam and a keel beam panel connected to the beam via a connecting portion of the beam, that is moreover provided with a main portion extending in a first, generally longitudinal direction and a transfer portion extending in a second direction different from the first direction and configured to be connected to the box. The main, transfer and connecting portions are configured to direct a major part of the stresses received by the beam in the second direction and transmit said major part of the stresses to the box by compression. | 06-12-2014 |
20140151500 | DEVICE FOR INTERMEDIATE FASTENING BETWEEN AN AIRCRAFT FUSELAGE AND AN AIRCRAFT LANDING GEAR - A device for intermediate fastening between an aircraft fuselage and an aircraft landing gear is provided. The device includes at least one semi-open support structure comprising a pair of webs, which are substantially parallel to each other. The webs comprise first support means intended to receive the main pivot shaft of the landing gear and second support means intended to receive the stay joint or joints of the landing gear. The device includes two support structures linked together by a central box structure. The central box structure includes a front wall, a rear wall and linking walls linking those two walls. | 06-05-2014 |
20140150902 | Dual Regulation Level Valve And De-Icing Device For An Air Inlet Of An Aircraft Engine Nacelle Incorporating Said Valve - A valve for regulating the pressure of a gas flow in a duct according to two pressure levels includes a gate whose position is controlled by an actuator with two chambers and a first control means with a first set point pressure P1 making it possible to position the gate in a first regulated position by comparing a pressure P | 06-05-2014 |
20140147270 | Aircraft Nacelle Comprising A Reinforced Connection Between An Air Intake And A Means Of Propulsion - An aircraft nacelle includes an air intake, connected to a means of propulsion, which defines a longitudinal direction, an outer wall, an inner duct including an annular flange connected, by means of connecting elements, to the means of propulsion, and a forward frame and a rear frame which connects the outer wall and the inner duct. | 05-29-2014 |
20140145863 | METHOD AND DEVICE FOR AIDING THE MONITORING OF A TURBINE ENGINE OF AN AIRCRAFT - The device displays on one and the same indicator ( | 05-29-2014 |
20140141705 | PASSIVE DEVICE FOR GENERATING A FILM OF COLD AIR IN CONTACT WITH AN OUTER SURFACE OF AN AIRCRAFT - An aircraft includes a first outer surface exposed to a hot air flow flowing in a flow direction and a device for generating a film of cold air in contact with a region to be protected of the first outer surface. The device includes a cold air outlet arranged upstream of the region to be protected as seen in the flow direction, and an inlet arranged at a second outer surface of the aircraft in contact with cold air. The inlet is arranged such that a pressure gradient exists between the inlet and the outlet so as to generate a natural flow of cold air from the inlet to the outlet as well as means to cause said inlet to communicate with said outlet. | 05-22-2014 |
20140141644 | Cutting Plate For Joining Together Wiring Harnesses Of Electrical Cables On An Aircraft - A cutting plate includes a planar interface able to accept electrical connectors, two ramps for supporting harnesses and two lateral walls, the dimensions of the interface and of the two ramps in a longitudinal direction being adapted to suit the number of connectors of the cutting plate and the dimensions in the directions other than the longitudinal direction and the dimensions of the lateral walls conforming to standard dimensions. | 05-22-2014 |
20140140864 | HYDRAULIC MOTOR-PUMP-ARRANGEMENT AND HYDRAULIC SYSTEM FOR A VEHICLE - An arrangement for selectively making available hydraulic power in separate hydraulic circuits comprises two displacement machines, two free-wheels and a drive unit that is preferably arranged between the displacement machines. The free-wheels block in opposite directions and are coupled to the displacement machines. Consequently, the first displacement machine is driven in a first rotating direction of the drive unit while the second displacement machine is only driven in a second, opposite rotating direction of the drive unit. This makes it possible to realize an intermittent operation for selectively making available additional hydraulic power in separate hydraulic subsystems by choosing the rotating direction accordingly. This arrangement can reduce the weight and the complexity of a hydraulic system. | 05-22-2014 |
20140136091 | METHOD AND DEVICE FOR ENSURING THE ACCURACY AND THE INTEGRITY OF AN AIRCRAFT POSITION ON THE GROUND - An assist device for ensuring the accuracy and integrity of position information of an aircraft on the ground includes means for determining in the airport (AE) a zone (ZP) of insensitivity to multipath GPS signals, the zone (ZP) having a rectangular shape, which is determined relative to the threshold (O) of the runway, and which has a length (L | 05-15-2014 |
20140136027 | MANAGEMENT SYSTEM FOR AIRCRAFT - Said system ( | 05-15-2014 |
20140130062 | METHODS, SYSTEMS AND COMPUTER READABLE MEDIA FOR ESTABLISHING A COMMUNICATION LINK BETWEEN SOFTWARE SIMULATION MODELS - Methods, systems, and computer readable media for automatic connection of software simulation models, for example and without limitation, for engineering simulation use in aircraft development are disclosed. According to one aspect, a method for establishing a communication link between software simulation models includes initiating communication between the software simulation models and a publish subscribe mechanism, classifying a quality of service indicator for each of the software simulation models, comparing the quality of service indicator associated with two software simulation models, and connecting the software simulation models based on the comparison of the quality of service indicators. | 05-08-2014 |
20140117162 | CONNECTOR FOR SECURING DOUBLE SKIN PIPEWORK AND ASSEMBLY OBTAINED - A connector for securing floating double skin pipework to a structure includes means for securing to the structure, and an external body forming an outer channel and an internal tube forming an inner channel around the longitudinal axis of the connector. The means for securing to the structure includes a fixed connection backed up by a sliding connection along the longitudinal axis of the connector. The connector includes at least one bore for producing the fixed connection and at least one holding rail for producing the sliding connection. | 05-01-2014 |
20140110529 | AIRCRAFT FUSELAGE AND METHOD FOR CONSTRUCTING A FLOOR IN SUCH A FUSELAGE - Such a fuselage includes cross-members adapted for the formation of a floor, at least one of said cross-members including an upper part, a lower part, linkage for the lower part to the upper part, and at least one opening for the passage of systems which is delimited between the lower part and the upper part. The upper part of the cross-member is fastened to the fuselage and is dimensioned so as to bear the stresses to which said cross-member may be subjected when the aircraft remains on the ground. The lower part is fastened to the upper part so as to reinforce it such that when assembled, the upper part and the lower part are adapted to bear the stresses to which the cross-member may be subjected in flight conditions of the aircraft. | 04-24-2014 |
20140107873 | METHOD AND SYSTEM FOR MANAGING AUTOMATIC GUIDANCE OF AN AIRCRAFT DURING A COMPLETE ENGINES FAILURE - A method and system for managing automatic guidance of an aircraft during a complete engine failure. Said system includes means for monitoring engines so as to be able to detect a complete failure of the engines; means for detecting whether the aircraft is in flight; means for detecting whether the aircraft is in a different guidance mode from a guidance mode configured to make the aircraft descend with a reduced engine thrust and a fixed speed; and control means for automatically bringing guidance means of the aircraft into a guidance configuration compatible with the situation associated with the complete failure of the engines. | 04-17-2014 |
20140102625 | METHOD FOR FIBRE PLACEMENT WITH THE AID OF A TEMPERATURE-REGULATED ROLLER - A method for fibre placement with the aid of a roller is provided. The roller is able to pivot about a rotation axis and to lay a plurality of first pre-impregnated fibres on second pre-impregnated fibres of a laying surface by rolling over said laying surface. The first fibres being distributed along a lower generatrix of the roller and being in contact with an outer surface of said roller over a contact arc. The method includes cooling the first pre-impregnated fibres in contact with the roller so as to enable them to slide on the outer surface of the roller and heating the second pre-impregnated fibres of the laying surface that are located at the front of the roller so as to promote the adhesion of the first fibres to the second fibres of the laying surface. | 04-17-2014 |
20140081609 | METHOD OF SIMULATION OF UNSTEADY AERODYNAMIC LOADS ON AN EXTERNAL AIRCRAFT STRUCTURE - The invention relates to a method for simulating the unsteady aerodynamic loads being exerted on the external structure of an aircraft, notably in the context of a simulation of the buffeting of a wing surface in an airflow. The method includes a step of measurement of pressure ( | 03-20-2014 |
20140081482 | METHOD AND DEVICE FOR AUTOMATICALLY MANAGING THE SPACING OF AT LEAST ONE FOLLOWING AIRCRAFT BEHIND AT LEAST ONE TARGET AIRCRAFT - The system ( | 03-20-2014 |
20140072775 | METHOD FOR PRODUCING A PROFILE THAT HAS A RE-ENTRANT ANGLE IN A COMPOSITE MATERIAL FROM A STACK OF LAYERS OF FIBRES - A method for producing, in a composite material, a component that has a re-entrant angle, includes stacking layers of fibres which have been pre-impregnated with a resin so as to obtain a preform and placing the preform in a tooling fixture in order to subject it to a polymerization cycle including a temperature cycle, with a temperature-increase phase and at least one soak at which the temperature is maintained, and a pressure cycle on the outside of the tooling fixture with a pressure-increase phase and a pressure-hold phase, with the layers of pre-impregnated fibres being able to slip against one another when the temperature of the temperature cycle is equal to or higher than a threshold temperature Tf dependent on the resin. The temperature-increase phase includes a soak at a temperature higher than or equal to Tf, the soak beginning before the end of the pressure-increase phase. | 03-13-2014 |
20140069987 | PROCESS AND SYSTEM FOR FRICTION STIR WELDING OF A STIFFENER ON AN AIRCRAFT PANEL - Process for linear transparency friction stir welding of a flange of a stiffener onto at least one panel for an aircraft, wherein a weld bead is made along the flange of the stiffener and wherein the weld bead extends in cross-section from a first lateral edge to an opposite second lateral edge of the stiffener flange. System for the implementation of the above welding process, which includes three welding heads arranged as a triangle, each of which includes a rotating pin as well as a shoulder extending at the base of said rotating pin. | 03-13-2014 |
20140064968 | Propeller for an aircraft engine comprising means for reducing noise at middle and high frequencies and improving the acoustic perception - Enriching and balancing the acoustic spectrum radiated by a propeller by introducing a differential pitch angle on certain blades of the propeller. Modifying the acoustic spectrum makes it possible to render the propeller noise more pleasant to the human ear. | 03-06-2014 |
20140064877 | ASSEMBLY OF TWO PARTS MADE OF COMPOSITE MATERIAL - An assembly of parts, at least one of which is made of composite material, includes at least one fastener including a body and also two stops, between which the parts held by the fastener are disposed, holes formed in the parts held by the fastener, the body of the fastener being accommodated in the holes, the holes having a diameter adapted to that of the body of the fastener so as to allow transmission of forces by the parts and the fastener hammering together. The stops of the fastener exert a compressive force C that makes it possible to obtain transmission of forces by adhesion between the parts held by the fastener. | 03-06-2014 |
20140042803 | Unknown - A switched-mode power supply device includes a charger ( | 02-13-2014 |
20140042272 | CENTRE PEDESTAL FOR AIRCRAFT COCKPIT AND AIRCRAFT COMPRISING SUCH A PEDESTAL - The invention relates to an aircraft cockpit centre pedestal for the attachment of control and instrumentation equipment for this aircraft, wherein the centre pedestal includes an equipment module including controls connected to at least one first electrical connector, and a single-piece frame including an upper face provided with a recess including at least one second electrical connector installed at the bottom of the recess and connected to computers onboard this aircraft in which this equipment module is installed, the at least one first electrical connector of the equipment module being inserted into at least one second electrical connector so as to connect the controls of the equipment module and these onboard computers. The invention also relates to an aircraft including such a pedestal. | 02-13-2014 |
20140039731 | METHOD AND DEVICE FOR AIDING THE MANAGEMENT OF THE FLIGHT OF AN AIRCRAFT - The device comprises servocontrol means which automatically control, in a combined manner, an automatic thrust system of the aircraft and airbrakes of the aircraft, as a supplement to usual means for steering the vertical trajectory, so that the aircraft attains a speed setpoint and/or altitude setpoint, at the location defined by a geographical constraint. | 02-06-2014 |
20140037400 | Assembly Comprising A Device For Locking A Fastening - An assembly includes a support fastened to a structure by a fastening element extending along a fastening axis. and includes a bore for the passage of the fastening element. The fastening element includes a surface for driving in rotation. The assembly includes a device for locking the fastening element in rotation including a moveable end resting against the surface for driving in rotation the fastening element. The locking device is configured so that, at rest, the moveable end enters into the volume normally occupied by the surface of the fastening element. The locking device is placed between the support and the fastening element so as to be deformed elastically by the surface when the fastening element is put in place in the bore of the support. The moveable end includes locking shapes capable of interacting with the external shapes of the driving surface to stop the fastening element from rotating. | 02-06-2014 |
20140033225 | METHOD FOR MONITORING THE COORDINATED EXECUTION OF SEQUENCED TASKS BY AN ELECTRONIC CARD COMPRISING AT LEAST TWO PROCESSORS SYNCHRONIZED TO TWO DIFFERENT CLOCKS - A method for monitoring the coordinated execution of sequenced tasks by an electronic device including a main electronic card including at least one main processor synchronized to a main clock and at least one auxiliary electronic card including at least one auxiliary processor synchronized to an auxiliary clock, includes
| 01-30-2014 |
20140033224 | METHOD FOR MONITORING THE COORDINATED EXECUTION OF SEQUENCED TASKS BY AN ELECTRONIC CARD COMPRISING AT LEAST TWO PROCESSORS SYNCHRONIZED TO ONE AND THE SAME CLOCK - A method for monitoring the coordinated execution of sequenced tasks by an electronic card including at least one first processor (PP | 01-30-2014 |
20140027957 | DEVICE FOR MANUFACTURING A COMPOSITE PART INCLUDING A BELL AND ASSOCIATED METHOD - The main purpose of the invention is a device for manufacturing a composite part, comprising a mould, designed to be associated with a reinforcement of the composite part comprising a preform, into which the resin forming the matrix of the composite part will be injected, possibly a support element on which the mould is supported, a preform vacuum creation membrane supported on the mould and/or the support element, if there is one; characterised in that it also comprises a vacuum chamber covering the vacuum creation membrane, the vacuum chamber comprising a flexible wall designed to apply a mechanical pressure to the vacuum creation membrane. | 01-30-2014 |
20140027573 | AIRCRAFT FUSELAGE STRUCTURAL ELEMENT WITH VARIABLE CROSS-SECTION - An aircraft fuselage structural element has the general form of an elongated profile and includes a web and at least one flange. The at least one flange has a curved cross-section tangent to the web. Use in a profile to increase the residual compressive strength after impact. | 01-30-2014 |
20140021310 | WIRING SUPPORT FOR AIRCRAFT - The support ( | 01-23-2014 |
20140001284 | Panel for the acoustic treatment comprising hot air ducts and at least one stabilization chamber | 01-02-2014 |
20130340528 | DEVICE FOR EXCITING A LANDING GEAR OF AN AIRCRAFT WHILE ON THE GROUND - A device for exciting a landing gear of an aircraft while it is on the ground. The device includes an oblong bracing foot, a movable support on which the oblong foot is mounted and an arrangement for setting the gear into vibration. | 12-26-2013 |
20130334365 | AIRCRAFT WITH REDUCED ENVIRONMENTAL IMPACT - An aircraft with reduced environmental impact includes two turboprop engines mounted on the back of the aircraft at the rear thereof, and one acoustic masking device per turboprop engine. The acoustic masking device includes a masking element, such as a flap, which can move between a position in which it is retracted into the wing, and a position in which it is extended toward the rear of the wing. In the extended position, the flap intercepts the noise area generated toward the front by the turboprop engine, so as to reduce the perception of noise on the ground. | 12-19-2013 |
20130333857 | HEAT EXCHANGER INCORPORATED INTO A WALL OF AN AIRCRAFT - An aircraft includes at least one wall delimiting a first zone (I) of the aircraft which is thermally insulated from the outside of the aircraft and a second zone (E) contained within the aircraft which is not thermally insulated with respect to the outside of the aircraft and a heat exchanger inside which a heat transfer fluid circulates, wherein the wall includes at least one duct inside which the heat transfer fluid circulates so as to act as a heat exchanger. | 12-19-2013 |
20130333475 | DEVICE AND METHOD FOR PICKLING AND SIMULTANEOUSLY CHECKING A PART BY ACOUSTIC MEANS - A device for implementing a method for pickling/stripping and for simultaneously non-destructively checking a part ( | 12-19-2013 |
20130323425 | Device and method for forming a microstructured coating on a substrate such as an aircraft element - A device for forming a microstructured coating on a substrate. The device includes a microstructured band that can be moved by rolling without slipping on the substrate and going around main pressure application elements assembled on a chassis, and secondary pressure application elements assembled on the chassis so as to be in contact with an inner face of the band in a zone of a strand of the band delimited by said main pressure application elements, this zone being exposed to the action of a curing apparatus that accelerates curing of a curable material designed to form said coating. A method for forming a microstructured coating using the above-mentioned device. | 12-05-2013 |
20130320149 | SUPPORT FOR ROUTING CONDUITS IN AN AIRCRAFT WING - A routing support ( | 12-05-2013 |
20130320135 | AFT AERODYNAMIC FAIRING WITH IMPROVED THERMAL RESISTANCE FOR A PYLON FOR ATTACHING AN AIRCRAFT PROPELLING ASSEMBLY - An aft aerodynamic fairing for a pylon for attaching an aircraft propelling assembly, including a caisson structure, a heat-shield floor, as well as a support structure for this floor comprising linking parts arranged to link two side edges of this floor to the caisson structure. The linking parts of each side edge of the floor are configured so as to allow travelling motion of the side edge relative to the caisson structure in a corresponding direction included in a plane orthogonal to a longitudinal direction of the fairing. The linking parts form a sliding link between the floor and the caisson structure, reducing the stresses induced by the deformations of these elements in use. | 12-05-2013 |
20130317691 | METHOD OF VERIFYING THE CONSISTENCY OF VALUES GIVEN BY AN INCIDENCE PROBE OF AN AIRCRAFT - The invention pertains to a method and apparatus for verifying the consistency of the values given by an angle of attack probe of an aircraft. The method and apparatus verifies the proper operation of the angle of attack probe by using the aircraft's vertical load factor measurement provided by an accelerometer to estimate the angle of attack and then comparing the estimated angle of attach with the measure angle of attack. | 11-28-2013 |
20130307324 | Energy supply network; method and aircraft or spacecraft - An energy supply network, especially for an aircraft or spacecraft, including a first coupling device, the first coupling device being configured to couple the energy supply network to an external energy source, a first high voltage direct current, HVDC, segment, the first HVDC segment being coupled to the first coupling device and a second HVDC segment, the second HVDC segment being coupled to the first coupling device. Also provided is a corresponding method and an aircraft or spacecraft incorporating such an energy supply network. | 11-21-2013 |
20130306795 | AIRCRAFT FUSELAGE FRAME ELEMENT - The subject of the invention is an aircraft fuselage frame element ( | 11-21-2013 |
20130305917 | SECURED LOCKING CORSET FOR SHUTTER CONTROLLED BY ACTUATOR, IN PARTICULAR ACTUATOR CORSET FOR AIRCRAFT DOOR AND LOCKING METHOD - A secure corset is applied in particular to the immobilization in the maximum opening position of an aircraft landing gear cage hatch. The corset has two half-shells that are able to enclose the piston of the actuator having an axis coincident with the common longitudinal axis of the half-shells once they are closed around the piston. Locking pins are able to hold the half-shells around the actuator. The corset also has a casing secured to at least one of the half-shells and equipped with a hooking unit that is able to be coupled to a fixed point on the structure. A structure for varying the distance between the casing and the hooking unit are able to move the hooking unit away from or towards the corset along the common longitudinal axis of the half-shells. | 11-21-2013 |
20130305817 | METHOD OF MEASURING LOADINGS IN JOINS IN A HIGH-TEMPERATURE ENVIRONMENT AND INSTRUMENTED SHAFT FOR IMPLEMENTATION, IN PARTICULAR FOR REAR ATTACHMENT OF AIRCRAFT TURBOJET - The invention aims to produce an instrumentation making it possible to measure the loadings which pass through mechanical joins between two mechanical structures, so as to best evaluate the dimensions and masses without impairing their mechanical properties of a secure transfer of load. To this end, the invention proposes introducing into the zones of transit of the loadings an instrumented component of the form that favours the measurement of shear and its installation. In one embodiment, a zone of transit of loadings consists of an instrumentalized hollow shaft which takes the form of a cylinder ( | 11-21-2013 |
20130305238 | METHOD FOR UPDATING A SOFTWARE APPLICATION HOSTED BY AN EQUIPMENT ITEM ON BOARD AN AIRCRAFT - A method for updating a software application stored in an equipment item on board an aircraft. The method comprises downloading update files to an on-board dataloader, checking the integrity and authenticity of the new software application version, transmitting this new software application version to the equipment item concerned, storing the new software application version in question into a standby memory zone of said equipment item, while this equipment item is still controlled by a previous version of said software application stored in an active memory zone, distinct from said standby memory zone, and finally, switching said standby and active memory zones, said equipment item being then controlled by the new software application version stored in the active memory zone after the memory zones have been switched. | 11-14-2013 |
20130304283 | Method for controlling the piloting of an aircraft - A method for controlling the piloting of an aircraft comprising the steps of receiving at least one first instruction for modification of a current velocity vector of the aircraft, determining a target velocity vector of the aircraft, on the basis of said at least one first instruction received, and determining, on the basis at least of said target velocity vector, at least one actuation command intended for at least one actuator of the aircraft in order to modify the movement of the aircraft according to said at least one first instruction received. | 11-14-2013 |
20130299636 | KEEL BEAM OF AN AIRCRAFT - A keel beam connected to a central wing box of an aircraft and ensuring the connection between a front structure and a rear structure of an aircraft is characterized in that it includes, on the one hand, a U-shaped body with a horizontal base and two solid lateral walls, and on the other hand, a cover which has a U shape oriented in the same manner as the body, with a base in the lower portion and curved edges, the ends of which are oriented upward so that each curved edge includes an outer surface flattened against and fixed to the inner surface of the lateral walls in order to define, with the body, a closed section, the cover including openings for accessing the inside of the keel beam. | 11-14-2013 |
20130292515 | OVERPRESSURE DOOR FOR AN AIRCRAFT - The overpressure door, of axial type, includes a hatch configured to pivot about an axis between a closed position and an open position and an aerodynamic appendage securely attached to the hatch. The aerodynamic appendage makes it possible to produce a deflection of the external flow in the open position of the hatch of the door. | 11-07-2013 |
20130276964 | METHOD FOR PRODUCING A CURVED PROFILE MADE FROM A COMPOSITE MATERIAL FROM A RECTILINEAR PREFORM OF FIBER WEBS - A method for producing a curved profile from a rectilinear preform of preimpregnated fiber webs, including stacking webs on the deformable mandrel and winding the deformable mandrel and the stacked webs on a bending tool along an axis of rotation (X), the profile including a stack of N webs, at least one first part of the profile being positioned in a plane perpendicular to the axis of rotation (X) and at least one second part parallel to the axis (X) whereof a face can be in contact with the bending tool. The method includes stacking the N fiber webs on the deformable mandrel, generating a heat gradient between the face and the rest of the preform that is hotter than the face, bending, in a single phase, the N webs inserted between the deformable mandrel and the bending tool, and polymerizing the N bent webs. | 10-24-2013 |
20130274992 | Method, devices and program for computer-aided preventive diagnostics of an aircraft system, using critical event charts - Aided preventive diagnostics of an aircraft system, comprising a plurality of subsystems at least one of which comprises a subsystem configured for monitoring and notifying a detected event, using critical event charts. After receiving a message notifying the occurrence of said detected event, a minimal diagnostic set relative to said at least one detected event, comprising a plurality of elements each represented by a node of said critical event chart is created, each element of said minimal diagnostic set being determined according to at least one logical implication relation of said critical event chart with a node representing said at least one received notification message. At least some of the elements of said minimal diagnostic set are then ranked, said ranked elements forming part of said diagnostic report. | 10-17-2013 |
20130274991 | Method, devices and program for computer-aided analysis of the failure tolerance of an aircraft system, using critical event charts - Aided analysis of the failure tolerance of an aircraft system, comprising a plurality of subsystems at least one of which comprises a monitoring unit and notification of a detected event, using critical event charts. After selecting at least one receivable notification message represented by a node of the critical event chart, elements of the minimal diagnostic set capable of resulting in the generation of the at least one selected notification message are identified, the identified elements forming part of the failure tolerance report. | 10-17-2013 |
20130269312 | DEVICE FOR CONTROLLING A VARIABLE SECTION NOZZLE OF AN AIRCRAFT - A control device for controlling a variable section nozzle of an aircraft power plant, the variable section nozzle including one or several movable parts capable of modifying the nozzle section and connected by a mechanical transmission chain to an actuator. The control device includes a system for regulating the power plant connected to a control member configured to control the actuator. The control device includes a single control member, an immobilization unit configured to immobilize all the movable parts which are deactivated only when the regulation system controls the positional change of the movable part or parts and a determination unit configured to determine the actual position of the movable part or parts. | 10-17-2013 |
20130264428 | METHOD OF SEPARABLY COUPLING A PROPULSION MODULE AND A CARRIAGE MODULE OF AN AIRCRAFT, AND MODULAR AIRCRAFT IMPLEMENTING SAME - According to one embodiment, a modular aircraft includes a propulsion module dedicated to flight, combining avionic equipment—wing structures assembly, flight deck, engines, tail unit—and a module dedicated to the carriage of passengers and/or goods. These modules include external cells extending longitudinally along a main axis and having tubular end parts of the same outline in the region of two disconnectable-coupling structures, one axial-coupling structure for keeping an end face of the propulsion module against an end face of the carriage module, and one radial-coupling structure for keeping an end face of the propulsion module against an end face of the carriage module. The wing structures assembly of the propulsion module includes two wing structures having opposite sweeps which are connected at the end and by a longitudinal connecting spar. | 10-10-2013 |
20130264424 | AIRCRAFT DOOR INSTALLATION - An aircraft exterior door installation with a door attached to an airframe. A damper is arranged to damp motion of the door as it is opened by rotating it away from the airframe. A coupling mechanism couples the damper with the door over an opening damping range and decouples the damper from the door at the end of the opening damping range. The damper does not damp the motion of the door as it opens beyond the opening damping range. Instead of damping the door over its full range of motion, it is only damped over a limited inner range of its motion. A further advantage of decoupling the door and the damper is that the damper does not need to extend into the airflow to the same extent as the door, thus minimising aerodynamic drag. | 10-10-2013 |
20130263966 | THREE-DIMENSIONAL SURFACE WEAVING - A weaving process for direct manufacture of three-dimensional structures with bidimensional walls with corners, without the need for sewing or other assembly between two ridges. The weaving is made by transforming weft threads into warp threads for making at least one face. The process is particularly adapted for the weaving of reinforcing elements for composite structures of corner fitting type. | 10-10-2013 |
20130261920 | METHOD AND SYSTEM FOR CONTROLLING AIRCRAFT BRAKING ON A RUNWAY - A method to control braking of an aircraft on a landing runway including: selecting a dummy runway state corresponding to a level of adhesion of wheels of the aircraft to a runway which is lower, over an entire speed range of the aircraft while braking on a runway, than an adhesion level of the wheels of the aircraft to the landing runway; calculating a set point of a deceleration value for the aircraft on the landing runway based on the landing runway for the selected dummy runway state, wherein the calculated set point corresponds to maximum braking value of the aircraft, and controlling the braking of the aircraft using the set point. | 10-03-2013 |
20130261877 | METHOD AND DEVICE FOR VERIFYING THE CONSISTENCY OF THE SIDESLIP PROBES OF AN AIRCRAFT - The invention pertains to a method for verifying the consistency of the values (β1,β2,β3) given by the sideslip probes (1,2,3) of an aircraft and to a device implementing this method. This method is noteworthy in that it consists in consolidating the values of two sideslip probes by using the value of the incidence α. | 10-03-2013 |
20130249712 | METHOD AND DEVICE FOR DISPLAYING METEOROLOGICAL DATA ON AN AIRCRAFT SCREEN - A method and a device for displaying meteorological data on an aircraft screen including generating and displaying on the screen an automatic dynamic transition between a start view and an arrival view, preferably in perspective. The dynamic transition corresponds to a successive display of views between the start view and the arrival view, each view including a symbol indicating the current position of the aircraft and meteorological data. | 09-26-2013 |
20130249158 | MACHINING TOOL FOR AN AIRCRAFT FUSELAGE FRAME - A tool for machining a curved profile along an axis of rotation X, said curved profile comprising at least one first section along a plane perpendicular to the axis of rotation X and at least one second section parallel to the axis of rotation X. The tool includes blocks, each having a clamping surface against which the profile can take support. The blocks include positioning elements against which the first section and the second section of the profile can take support, and an apparatus arranged to immobilize the profile which is adapted to occupy a first activated state, wherein it immobilizes the profile, and a second deactivated state, wherein it does not immobilize the profile. The tool includes manual presses for maintaining the profile flattened against the positioning elements until the profile immobilizing apparatus is in the activated state. | 09-26-2013 |
20130247025 | Method and device for optimizing data updates in operationally approved software applications of aircraft - Optimizing data updates in an operationally approved software application of aircraft, comprising a first software component using a second software component. Following the receipt of a software component comprising an update of said second software component, said received software component is analyzed and a class of the update of said second software component is determined. Depending on said class, the update of said second software component is transmitted to said first software component and/or to a central download system. If the update of said second software component is transmitted to said first software component, said second software component is updated and a configuration report showing said update is created. | 09-19-2013 |
20130242088 | DEVICE AND METHOD FOR DETECTING DISCHARGES - A method and a device for detecting an edge glow phenomenon in a composite panel, including at least one cable for introducing current into the said composite panel, at least one current return cable, at least one insulating panel bracketed to the composite panel, and means for detecting an edge glow on an outer surface of the said composite panel. | 09-19-2013 |
20130241159 | SEALING DEVICE AND METHOD - A sealing device is suitable, for example, for conducting verification and testing of fluid-tightness, and includes a body supporting an end piece equipped with a gasket. The gasket presents an outer surface in which at least one area is in the form of a truncated cone. A sealing method concerns the sealing of an aircraft pipe presenting an opening arranged behind a wall, with the aid of a sealing device as described above. | 09-19-2013 |
20130240682 | DEVICE FOR ATTACHING AN ELECTRICAL HARNESS IN AN AIRCRAFT - A device for attaching an electrical harness on a structure of an aircraft comprising a support connected to the structure, the harness following a path direction, characterized in that it comprises a body with at least two jaws, at least one of the jaws being movable along a reference plane perpendicular to the path direction between a first open position in which they enable the insertion of at least one harness and a second closed position in which they keep the inserted harness or harnesses in position, and on the other hand, a retainer strip in the form of a blade whose ends are connected to the support allowing for the jaws to be maintained in closed position and the body to be flattened against the support. | 09-19-2013 |
20130240667 | Aircraft comprising fairings for correcting its dissymmetry or lateral asymmetry - An aircraft having an asymmetry or a lateral geometric dissymmetry and comprising at least one pair of wings to each of which are fixed at least one fairing, each fairing comprising a surface connected to the lower surface of the wing and extending longitudinally in the direction of a longitudinal axis of the fuselage. The surface of at least one of the fairings has at least one local geometric deformation which is suitable for producing a corrective rolling moment to compensate for the undesirable rolling moment produced by the asymmetry or the lateral dissymmetry of the aircraft. | 09-19-2013 |
20130238511 | SYSTEM AND METHOD FOR END-OF-LIFE PROCESSING OF AN AIRFRAME - A method to develop a plan to dismantle an airframe including: enhancing a digital mock-up model (DMU) of the airframe with data identifying hazardous materials in parts of the airframe; positioning at least one cut through the DMU of the airframe; based on the position of the cut, identifying intersections between the cut and fluid conduits identified in the DMU of the airframe; analyzing the identified intersections of the fluid conduits and data regarding hazardous waste fluids in the conduits of the airframe to identify the conduits having the hazardous waste which would be ruptured by the positioned cut, and generating a report of the identified conduits that would be ruptured and have the hazardous waste. | 09-12-2013 |
20130238171 | METHOD AND DEVICE FOR DISPLAYING SPEED INFORMATION ON AN AIRCRAFT - The display device ( | 09-12-2013 |
20130234352 | METHOD OF MANUFACTURING A PART MADE OF COMPOSITE MATERIAL AND TOOL FOR THE IMPLEMENTATION THEREOF - A method and apparatus for manufacturing a composite material part from a preform of fibers pre-impregnated with resin. The method includes laying the preform on a laying surface of a tool with a peripheral shoulder, covering the preform with a conforming plate delimited by a peripheral edge which extends beyond the peripheral flank of the preform over the entire periphery of the preform, using shims calibrated to position the conforming plate, the shims being arranged between the support surface of the peripheral shoulder and the peripheral edge of the conforming plate, removing the calibrated shims, arranging a seal connecting the conforming plate and the tool all around the preform, and polymerizing the preform. | 09-12-2013 |
20130233975 | METHOD AND APPARATUS FOR IMPROVED LATERAL CONTROL OF AN AIRCRAFT ON THE GROUND DURING TAKEOFF - A method and apparatus for carrying out a symmetric deflection of the spoilers so as to reduce the lift of the aircraft during a takeoff roll thereby improving lateral and directional control on the ground. | 09-12-2013 |
20130233474 | METHOD OF MANUFACTURING A CURVED PROFILE MADE OF COMPOSITE MATERIAL FROM A RECTILINEAR PREFORM OF FIBER PLIES - A method of manufacturing a curved profile from a rectilinear preform of pre-impregnated fiber plies. The method includes stacking plies on a deformable mandrel and winding the deformable mandrel and the stacked plies on a bending tool along a rotation axis, the profile comprising a stack of N plies. At least one first section of the profile is arranged along a plane perpendicular to the axis of rotation and at least one second section is arranged in a plane parallel to the axis. The method includes the steps of stacking the N plies of fibers on the deformable mandrel, bending in a single step the N plies sandwiched between the deformable mandrel and the bending tool and polymerizing the bent N plies. The curved profile comprises M plies with fibers oriented at A° relative to a longitudinal direction and M+/−5% plies with fibers oriented at −A°. | 09-12-2013 |
20130233470 | METHOD FOR OBTAINING A COMPOSITE MATERIAL PART INCORPORATING A TENSIONING STEP OF THE FILAMENTS AND TOOL FOR ITS IMPLEMENTATION - A method for obtaining a composite material part from a preform of layers of fibers pre-impregnated with resin stacked on top of one another on a tool, the preform being delimited by a lower surface, an upper surface, and a peripheral flank. The method includes attaching to the tool, after the last layer has been laid, a peripheral part comprising a wing adapted to cover the peripheral edge of the upper surface, so as to create, in the periphery of the preform, a peripheral cavity adjacent to the flank of the preform and, before the polymerization phase, to withdraw the gas present in the peripheral cavity so as to tension filaments of the preform by exerting a traction force at the ends of the filaments. | 09-12-2013 |
20130228655 | METHOD AND DEVICE FOR FITTING OUT AN AIRCRAFT NOSE COMPARTMENT IN AN AVIONICS BAY - An aerodynamic body, with at least one ancillary flap arranged such that it can be moved on the aerodynamic body with the aid of a guide mechanism, and with a drive device for purposes of actuating the ancillary flap, the guide mechanism having a pivotal articulation, by which the ancillary flap is articulated on the aerodynamic body such that it can be extended, and which is arranged in a rear region of the ancillary flap as viewed in the flow direction. | 09-05-2013 |
20130228651 | METHOD FOR BOARDING AND UNLOADING OF PASSENGERS OF AND AIRCRAFT WITH REDUCED IMMOBILISATION TIME OF THE AIRCRAFT, AIRCRAFT AND AIR TERMINAL FOR ITS IMPLEMENTATION - Methods for transferring a payload such as passengers and/or luggage and/or freight between an airport and a cabin of an aircraft are provided. Air terminals, aircraft and removable cabin modules suitable for implementing these methods are also provided. An aircraft is provided which includes a removable cabin module. A docking module is also provided for transferring a removable cabin module between an aircraft and an airport. A method for modifying the internal configuration of the cabin of such an aircraft by replacing a removable cabin module of the aircraft is also provided. | 09-05-2013 |
20130224000 | Panel for the acoustic treatment comprising hot air ducts and at least one annular channel - An aircraft nacelle comprising a lip extended by an inner conduit forming an air intake, a front frame delimiting with said lip an annular channel wherein hot air circulates, as well as a panel for acoustic treatment comprising, from outside inwardly, an acoustic resistive layer, at least one honeycomb structure, and a reflective layer, as well as ducts for channeling hot air with each one inlet communicating with the annular channel and one outlet communicating with the inner conduit, wherein the panel for acoustic treatment comprises, upstream from the ducts, an annular channel which extends over at least a portion of the nacelle circumference, at least one conduit providing communication between said annular channel and the upstream annular channel, and a plurality of ducts that open into said downstream annular channel, the panel for acoustic treatment being connected to the front frame in regard to the annular channel. | 08-29-2013 |
20130221157 | AIRCRAFT ENGINE PYLON AFT AERODYNAMIC FAIRING - An aircraft engine pylon aft aerodynamic fairing includes upper spars, transverse stiffening ribs, lower spars and a trailing edge where the upper spars and lower spars join together. In this fairing, a profiled structure is formed according to a profile open to the outside of the fairing. In a first end portion, the profiled structure comes to be enclosed between an end portion of the lower spars and the ends of at least one transverse stiffening ribs flush with the lower spars. This structure extends between the lower spars and the upper spars over a straight central portion inclined relative to the first end portion, and comes in a second end portion flush against a portion of the upper spars, parallel to the first end. | 08-29-2013 |
20130221156 | AIRCRAFT NOSE STRUCTURE AND CORRESPONDING AIRCRAFT - This aircraft nose structure comprises frames ( | 08-29-2013 |
20130219402 | ROBUST SYSTEM CONTROL METHOD WITH SHORT EXECUTION DEADLINES - A method of controlling a system comprising the following steps:
| 08-22-2013 |
20130216771 | METHOD AND DEVICE FOR STIFFENER PROTECTION, AND CORRESPONDING COMPOSITE PANEL - A composite panel with protected parallel stiffeners has a multiply front face coming to an edge and extending between two lateral flanks of outside plies, symmetrically relative to a median plane (Pm). A device for protecting each stiffener includes a structural section that caps the stiffener symmetrically relative to this median plane (Pm). This structural section includes a so-called upper section formed above the edge and configured to envelop a space above the edge, a so-called lower section framing the lateral flanks by means of longitudinal walls (Pi) fastened to these flanks, and an intermediate section bearing at least partially on the edge via transverse walls (Pb) so as to minimize the propagation of impact forces to the lower section. | 08-22-2013 |
20130211632 | Detection of aircraft descent anomaly - An aircraft ground or sea approach anomaly detection method. The method includes the steps of characterizing a flight phase of the aircraft, determining a prohibited flight envelope, defining a set of prohibited vertical speeds of the aircraft for given altitudes in relation to the ground or the sea, as a function of the flight phase of the aircraft characterized, and detecting a ground approach anomaly of the aircraft as a function of a current vertical speed and altitude in relation to the ground or the sea of the aircraft, in relation to the prohibited flight envelope determined. | 08-15-2013 |
20130200904 | METHOD AND ARCHITECTURE FOR DETECTING INACCESSIBLE ELECTRICAL ANOMALIES BY MEANS OF REFLECTOMETRY - Detection and location of electrical faults in a network of metal structures which can receive electric cables and allow return of current by the cables. The reflectometry-based method involves injecting a probe signal into a cable coupled to the structures and analyzing the signal reflected by the anomalies. A conductive element is provided for carrying the probe signal at a constant distance from each structure. In one aspect, an insulated conductive element is arranged inside the metal structure and is built into a longitudinal groove in a surface for receiving a longitudinal plastic holder wedged into the structure. The reflected signal from the conductive element is compared to a threshold above which an anomaly is detected, and the anomaly is located by topological correlation. The invention is useful for airplane raceways having a composite skin. | 08-08-2013 |
20130197727 | METHOD AND DEVICE FOR AIDING THE PILOTING OF AN AIRCRAFT DURING A LANDING PHASE - Method and device for aiding the piloting of an airplane during a landing phase for ensuring, during rollout on a landing runway, that in the nominal case the airplane will stop level with a selected exit, while guaranteeing that in the case of a fault the airplane will stop before the end of the runway. | 08-01-2013 |
20130197726 | METHOD AND DEVICE FOR DISPLAYING TRIM INFORMATION ON AN AIRPLANE DURING A TAKE-OFF - A method and device for displaying trim information on an airplane during a take-off, for determining and displaying a precise trim setpoint which enables the pilot, by following the displayed information, to carry out a manual take-off which is optimized from the performance point of view. | 08-01-2013 |
20130192433 | Method for disassembly of two elements welded by ultrasound and element able to be welded by ultrasound to another element to the implementation of said method - A method for disassembling two ultrasonically welded elements, one of the elements comprising, at a surface opposite the other element, an energy director that concentrates the heating during ultrasonic welding and forms a material junction between the two assembled elements after the ultrasonic welding. The method includes the steps of positioning a wire between the two assembled elements, so as to be secant to the energy director, said wire having suitable mechanical characteristics allowing it to cut the junction formed by the energy director and moving the wire between the two assembled elements so as to cut said junction. | 08-01-2013 |
20130192345 | DEVICE FOR CARRYING OUT TESTS ON AT LEAST ONE FLUID CIRCUIT OF AN AIRCRAFT - A device for carrying out a test on a fluid circuit of an aircraft including a test unit which includes, at the inlet, at least one means of connection to a pressurized gas supply connected to means for regulating the pressure of the gas provided by the supply as a function of the test to be carried out and, at the outlet, at least two connection means connected to the means for regulating the pressure of the gas, wherein at least two connection means have different dimensions tailored to a range of pressures or a given pressure. | 08-01-2013 |
20130192045 | DEVICE AND METHOD FOR ASSEMBLING BRACKETS IN AN AIRCRAFT STRUCTURE - The invention relates to a positioning device for assembling parts on a structure. More specifically, the invention relates to a positioning device designed for assembling fixed brackets to an aircraft structure. A laser projector is fastened directly on the rigid aircraft structure; its position is therefore stable in relation to the latter, even if said structure undergoes slight deformations. The position of the projector is determined accurately by utilizing targets, which are also fastened to the primary structure. The invention also relates to a method for implementing this device. | 08-01-2013 |
20130191087 | METHOD OF CALCULATING DYNAMIC PRESSURE AT THE LEVEL OF AN AIRCRAFT SURFACE - The invention is aimed at a method simulating the aerodynamic flow around an aircraft, so as to detect the aerodynamic loads exerted on a predetermined surface of the aircraft. The method includes a phase of determining a value denoted QA of global dynamic pressure at the level of the predetermined surface of the aircraft. The method includes steps of carrying out simulations of aerodynamic flow around the predetermined surface of the aircraft for given environmental conditions, on the basis of a mesh produced around the shape of the aircraft, determining a local dynamic pressure qA around the predetermined surface of the aircraft, and then calculating the global dynamic pressure QA. | 07-25-2013 |
20130190949 | VEHICLE ENERGY CONTROL SYSTEM - A system for controlling energy of a vehicle, for example an aircraft, comprising a control interface able to be in at least one first and one second state, the first state being an instruction state in which the interface generates at least a first instruction for speed of variation of a current energy of the vehicle and the second state being a resting state in which it gives no instruction, the interface furthermore being configured to return into the second state after having been brought into the first state. | 07-25-2013 |
20130184900 | VEHICLE ENERGY CONTROL SYSTEM WITH A SINGLE INTERFACE - A system for controlling energy of a vehicle, for example an aircraft, characterized in that it comprises:
| 07-18-2013 |
20130184899 | METHOD FOR THE AUTOMATIC MONITORING OF AIR OPERATIONS NECESSITATING GUARANTEED NAVIGATION AND GUIDANCE PERFORMANCE - A method is disclosed for automatic monitoring of a flight management assembly of an aircraft implementing air operations necessitating guaranteed navigation and guidance performance, wherein flight path data generated by first and second flight management systems respectively, are compared in order to check their consistency; first and second flight management systems transmit their flight path data to a third flight management system; the third flight management system receives a current position of the aircraft, calculates deviations between this current position and a flight path depending on the flight path data received from the first and second flight management systems, which it utilizes only if they are identical, and calculates, according to these deviations, guidance commands for slaving onto this flight path. Monitoring can compare deviations and guidance commands received from the first second and third flight management systems in order to be able to detect an inconsistency between them. | 07-18-2013 |
20130183513 | WALL MADE FROM A COMPOSITE MATERIAL REINFORCED SO AS TO LIMIT THE SPREAD OF A CRACK IN A DIRECTION - The invention relates to a wall made from a composite material comprising at least two layers of fibers ( | 07-18-2013 |
20130181509 | Interface device between an electrical network and consumer systems - An interface device between an electrical network and energy consumer systems, including an input converter with a first winding connected on one side with a reverse blocking module and on the other with a first semiconductor chopper device, second and third windings having an end connected to output converters via first and second reverse blocking modules, and another end connected to the output converters, via a switching cell, a fourth winding having an end to be connected to the network, via a second semiconductor chopper device; and a control module for the semiconductor chopper devices. The interface device also includes a buffer capacitor having a first end connected to the output converters, and another end, to which a reference voltage is applied, isolated from the network; and a power reserve having an end to be connected to the network and another end connected to the fourth winding. | 07-18-2013 |
20130181441 | ANTI-BUCKLING COUPLING DEVICE FOR PIPING - The invention relates to a coupling device for a duct ( | 07-18-2013 |
20130180642 | Self-stiffened composite panel and process for making same - The invention provides a self-stiffened composite panel including an external skin, an internal skin superposed on the external skin, which covers an internal face of the external skin and at least one stiffener protruding inwards relatively to the internal skin which extends along a longitudinal direction, characterised in that the stiffener is made as one piece with the internal skin and consists of a portion of the internal skin which is located at distance from the external skin. The invention also provides a process for making such a self-stiffened panel. | 07-18-2013 |
20130179842 | METHOD AND SYSTEM FOR MONITORING A GRAPHICAL INTERFACE IN AN AIRCRAFT COCKPIT - The invention relates in particular to a method and a system for monitoring a graphical interface in a computer system of an aircraft cockpit. The method comprises, in addition to the display of a graphical interface of a client application based on a tree structure of graphical interaction objects composing said graphical interface, the following steps: obtaining a plurality of graphical interaction objects having a tree-structure organization; creating and adding, to said obtained tree structure, at least one new graphical interaction object defining a critical graphical display zone; modifying the tree-structure dependency of at least one critical graphical interaction object, of the obtained tree structure to make it dependent from the new graphical interaction object defining the critical zone; and performing critical monitoring only of the critical graphical objects attached to the critical zone. | 07-11-2013 |
20130175388 | METHOD AND DEVICE FOR DRIVING AT LEAST ONE LANDING GEAR WHEEL OF AN AIRCRAFT BY MEANS OF A WHEEL MOTOR - The invention relates to a device for driving at least one landing gear wheel of an aircraft by means of a wheel motor, which is intended to be used in the stage when the aircraft is traveling on the ground, said aircraft having turbojet engines ( | 07-11-2013 |
20130174918 | Bleeding System - A bleeding system includes an open conduit and, upstream, a control controlling the hydraulic fluid flow, toward the open conduit. The bleeding system includes a dismountable connection device including connection means adapted to be connected to the bleeding system; an outlet adapted to be connected to a pipe; a first central portion including the connection means, a cylindrical bearing, and a conduit extending from the connection means up to the surface of the cylindrical bearing; and an annular second portion including a bore adapted to pivot on the cylindrical bearing, at least one conduit connecting the outlet and the surface of the bore. The first portion and/or the annular portion include a groove ensuring the hydraulic fluid flows between the conduits. The central portion includes a section arranged between the connection means and the cylindrical bearing to ensure the connection of the connection device to the bleeding system. | 07-11-2013 |
20130166111 | METHOD FOR CONTROLLING A HIGH-LIFT DEVICE OR A FLIGHT CONTROL SURFACE, SYSTEM AND AIRCRAFT OR SPACECRAFT - The present invention discloses a method for controlling a high-lift device or a flight control surface of an aircraft or spacecraft, especially with a system according to the present invention, comprising the steps of receiving, at at least one first control unit, a command signal from a commander unit via a data network, providing a primary control signal to at least one secondary control unit via the data network, wherein the primary control signal depends on the received command signal, receiving, at the at least one second control unit, a sensor signal of one or more sensors of the high-lift device or flight control surface, and providing a secondary control signal to one or more actuators of the high-lift device or flight control surface, wherein the secondary control signal depends on the received sensor signal. Furthermore, the present invention discloses a system and an aircraft or spacecraft. | 06-27-2013 |
20130161579 | REMOTE-PIVOTING METHOD AND TOOL FOR IMPLEMENTING SAME - A method and a tool for remotely pivoting an element mounted in a structure is provided. The method includes exerting a lever effect on the element by way of a control bearing on the structure coupled to a connection engaged with the element to cause it to pivot in a pivoting plane. The method also includes applying an angular offset to this connection in a plane different from the pivoting plane, in which the lever effect is produced, in order to render the control remotely operable. | 06-27-2013 |
20130161446 | HINGING CRADLE FOR FAN COWLS SUPPORTED BY SAID COWLS IN CLOSED POSITION - The invention relates to an engine assembly for aircraft in which the coupling device comprises a fore aerodynamic structure having a cradle equipped with an aerodynamic cowling, the cradle being hinge mounted on the air intake of the engine, and the fan cowls being mounted to move on the cradle so as to be able to occupy an open position as well as a closed position in which they are supported by the air intake and by a thrust reverser. According to the invention, when the cowls are in open position, the cradle adopts a first configuration in which its aft end rests on a span of the engine mounting structure, and when the cowls are in closed position, the cradle, borne by said cowls, adopts a second configuration in which it is lacking any direct mechanical link with the other elements of the engine mounting structure. | 06-27-2013 |
20130161123 | Standardised insulation device for an aircraft and processes of making and using thereof - An insulation device for an aircraft, comprising a blanket comprising a layer of insulation filling enclosed in a cover and having provision areas for the passage of aircraft components, these areas being devoid of insulation filling and being formed by a surface junction of two opposite faces of the cover inducing a recess in at least one face. The insulation device comprises an associated detachable complementary assembly to cover at least one of the provision areas, the assembly comprising a portion of insulation filling shaped to fit into the corresponding recess, and a retention arrangement for retaining this portion of filling. The retention arrangement is provided with a detachable arrangement for fixing the detachable complementary assembly on at least one face of the cover. | 06-27-2013 |
20130160768 | OXYGEN SUPPLY SYSTEM INTENDED IN PARTICULAR FOR THE FLIGHT CREW OF AN AIRCRAFT - This system is intended for supplying oxygen in particular for the flight crew of an aircraft. It comprises an oxygen source, an oxygen mask as well as a circuit connecting the oxygen source to the said oxygen mask. | 06-27-2013 |
20130160295 | METHOD, APPARATUS AND COMPUTER PROGRAM PRODUCT FOR DETERMINING THE STRAIN INDUCED AT A SELECTED POINT IN A STIFFENED PANEL STRUCTURE IN RESPONSE TO A LOAD, TAKING INTO ACCOUNT ONE OR MORE OUT OF PLANE (OOP) EFFECTS - A method, apparatus and computer program product is disclosed for determining the strain induced at a selected point in a stiffened panel structure in response to a load, taking into account one or more out of plane (OOP) effects. | 06-27-2013 |
20130157017 | SECURE BEAM, IN PARTICULAR STRONG FRAME OF FUSELAGE, AND AIRCRAFT FUSELAGE PROVIDED WITH SUCH FRAMES - An arrangement for freeing the structures of fail-safe type from the damage tolerance criterion and to allow a significantly improved fatigue resistance, while producing a weight saving. This is provided by forming a composite hybrid structure in a configuration that makes it possible to combine the advantages of metal and of composite material. In a secure hybrid structure, at least two longitudinal structural spars are joined back to back by fastening means. One of the spars is metal and equipped with stability partitions, whereas another spar is made of a composite material with carbon fibers oriented in the direction of the forces to be predicted such that this spar exhibits a rigidity equivalent to that of the metal spar. | 06-20-2013 |
20130156427 | AFDX NETWORK WITH A PASSIVE OPTICAL NETWORK - The present invention concerns an AFDX network which is extended by a passive optical network or PON. The AFDX network comprises an AFDX switch to which are connected a plurality of equipments. The AFDX switch constitutes the optical line termination and said equipments constitute the optical network terminations of the PON. The PON broadcasts over the downlink, to all said equipments, every AFDX frame output by said AFDX switch. It also multiplexes over the uplink the AFDX frames transmitted by the same equipments. The invention also concerns an μAFDX network using a PON. | 06-20-2013 |
20130151147 | METHOD AND DEVICE FOR AUTOMATICALLY MONITORING ON AN AIRCRAFT AN IDENTIFICATION CODE OF A GROUND STATION OF A NAVIGATION SYSTEM - A monitoring device is provided. The monitoring device includes means for verifying whether an identifier received from a ground station of a radionavigation system is among the identifiers of the ground stations situated in a monitoring zone around the current horizontal position of the aircraft. | 06-13-2013 |
20130147239 | HEADREST FOR AN AIRCRAFT PILOT'S SEAT AND SEAT COMPRISING A SUCH HEADREST - A headrest includes a first part referred to as the lower part, equipped with a connecting unit enabling an adjustable connection of the headrest to the seat back of a pilot seat, and a second part referred to as the upper part, located opposite the lower part, as well as a front face intended to serve as a support surface for the head of a user. A receptacle, connected to the mask, stores an oxygen mask and/or a supply line. The upper part of the headrest forms a hinged cover on the lower part of the headrest and it closes the receptacle. A seat, a cockpit, and an aircraft include such headrest. | 06-13-2013 |
20130146710 | AIRCRAFT NOSE STRUCTURE WITH LANDING GEAR COMPARTMENT - An aircraft nose structure includes a fuselage and a pressuretight bulkhead fixed at its periphery to the fuselage and transversely dividing the fuselage into a pressurized upper zone and an unpressurized lower zone for accommodating retractable nose landing gear. The pressuretight bulkhead includes a floor of the pressurized upper zone, and a substantially flat rear panel extending between a rear edge of the floor and the fuselage. The floor and the rear panel are fixed laterally to the fuselage. The fuselage includes an exterior wall and reinforcing transverse frames to which the exterior wall is fixed. In line with the pressuretight bulkhead, at least some of the transverse reinforcing frames extend along the outline of the pressurized upper zone and constitute members that reinforce the pressuretight bulkhead. | 06-13-2013 |
20130146709 | AIRCRAFT NOSE AND NOSE LANDING GEAR BAY STRUCTURE - An aircraft nose structure includes a fuselage, a floor for a pressurized space and a nose landing gear bay arranged under the floor, on the opposite side to the space. The bay includes walls that form a pressure barrier, of which there are two lateral panels mechanically secured to the floor by load-reacting members, an upper panel adjacent to the floor and extending between the lateral panels, and a rear panel extending between the upper panel and the fuselage. | 06-13-2013 |
20130146393 | METHOD FOR PRODUCING AN ACOUSTIC TREATMENT PANEL - A method for producing an acoustic treatment panel, including:
| 06-13-2013 |
20130145770 | SUBSTITUTION DEVICE FOR AIRCRAFT ENGINE - A substitution device for replacing a turbojet type of aircraft engine, with a nacelle comprising protective covers, and a support mast having two engine mounts, each of said protective covers being mounted to pivot between an open position and a closed position, said substitution device comprising a body, two anchors attaching to the engine mounts of the engine support mast, and bearing portions adapted to receive support portions belonging to the protective covers. A method for installing such a substitution device in a nacelle, which makes it possible to close the engine covers and authorize the movement of the aircraft. | 06-13-2013 |
20130142565 | DEVICE AND METHOD FOR ASSEMBLING TWO SHELL ELEMENTS MADE FROM A COMPOSITE MATERIAL - A device and method for assembling two structural elements made from a composite material is provided. The device includes two cylindrical flanged receptacles, each pierced by an aperture perpendicular to the axis of the cylinder, and a shaft that can be introduced into said apertures. The device also includes bearing means, which bear on the interior surfaces of the cylindrical receptacles and can maintain tension in the shaft when the shaft extends through the apertures in the two receptacles. The device includes means of placing the shaft under tension. | 06-06-2013 |
20130138272 | INTERACTIVE DIALOG DEVICE BETWEEN AN OPERATOR OF AN AIRCRAFT AND A GUIDANCE SYSTEM OF SAID AIRCRAFT - The dialog device includes a display screen, on which are displayed three graphic representations, which are respectively associated with the three control axes of the aircraft, each of said graphic representations comprising a plurality of portions, each of which is associated with a guidance mode of the associated control axis, so that all the possible guidance modes of the guidance system are thus represented, this representation highlighting the fact that the guidance modes are active exclusively on a given guidance axis. | 05-30-2013 |
20130135779 | CABLING OF AN AIRCRAFT CIRCUIT BREAKER PANEL - A distribution panel aboard an aircraft includes sites intended for the installation of functional electrical circuit breakers of which at least one of the sites is not occupied by a functional circuit breaker. The functional circuit breakers are wired up to a monitoring system via monitoring cabling so as to monitor a state of the circuit breakers. The at least one site not occupied by a functional circuit breaker is occupied by a nonfunctional circuit breaker, termed a false circuit breaker. The false circuit breaker is able to deliver a state signal and is wired up to the monitoring system by the monitoring cabling in a manner identical to that of a functional circuit breaker. | 05-30-2013 |
20130135202 | INTERACTIVE DIALOG DEVICE BETWEEN AN OPERATOR OF AN AIRCRAFT AND A GUIDANCE SYSTEM OF SAID AIRCRAFT - Interactive dialog device between an operator of an aircraft and a guidance system of the aircraft. The dialog device includes an interaction on a screen which represents, on the one hand, a playback element indicating the value of a guidance setpoint of the guidance system of the aircraft, and on the other hand, a control element which can be grasped and moved along a curve by an operator to modify the value of the guidance setpoint. | 05-30-2013 |
20130134259 | FRONT STRUCTURE OF AN AIRCRAFT FUSELAGE COMPRISING LANDING GEAR - A front structure of an aircraft fuselage comprising landing gear pivoting about a main shaft and a stay shaft. The front structure also comprises a first reinforcing frame and a second reinforcing frame, the main shaft and the stay shaft being respectively connected to the first and second frames, and a device for the mechanical connection and transfer of forces connecting the stay shaft and the main shaft and transferring to the main shaft a portion of the forces induced by the wheels of the landing gear onto the stay shaft, the second frame and said device being perpendicular to one another. | 05-30-2013 |
20130126671 | Unknown - There is provided an aircraft folding seat ( | 05-23-2013 |
20130112808 | COMPACT IMPROVED AIRCRAFT LANDING GEAR - A breaker strut of an aircraft landing gear, including means to adjust the length of at least one of its lower and upper portions and/or a space allowing a nesting of the lower and upper portions in the folded position of the strut. A landing gear including such a strut and/or retraction means including two slider-crank mechanisms which are phase shifted by a non-zero angle φ allowing a reduction of the variations of torque C applied to the undercarriage of the gear as it moves between the lowered and raised states of the latter. | 05-09-2013 |
20130110327 | Method And Device For Controlling Engine Speed Of An Aircraft During A Take-Off | 05-02-2013 |
20130110324 | Energy Protection Device For An Aircraft | 05-02-2013 |
20130108837 | METHOD OF MANUFACTURING A STRUCTURE COMPRISING A SKIN AND STIFFENERS | 05-02-2013 |
20130105622 | AFT PYLON FAIRING FOR AIRCRAFT ENGINE SUSPENSION SYSTEM, COMPRISING A HEAT SHIELD CAPABLE OF EXPANDING FREELY | 05-02-2013 |
20130105217 | ELECTRICAL HARNESS EQUIPPED WITH A DEVICE TO SPACE ITS ELECTRICAL CONDUCTORS AT THE LEVEL OF A PARTITION PASSAGE | 05-02-2013 |
20130103233 | AUTOMATIC LANDING METHOD AND DEVICE FOR AN AIRCRAFT ON A STRONG SLOPE RUNWAY - The device ( | 04-25-2013 |
20130099057 | IMPACT RESISTANT AND DAMAGE TOLERANT AIRCRAFT FUSELAGE - Aircraft fuselage section ( | 04-25-2013 |
20130099052 | METHOD FOR ADJUSTING THE DOORS OF A LANDING GEAR BAY, AND ASSOCIATED DOOR - The aim of the invention is to allow the set of doors to be adjusted without increasing the number of landing gear retraction/extension manoeuvres, by incorporating a specific entrance in the fairing ( | 04-25-2013 |
20130098471 | Aircraft nacelle comprising a hot air supply device for a panel combining acoustic and frost treatments - The object of the invention is an aircraft nacelle comprising a lip extended by an inner conduit forming an air intake, a front frame delimiting with said lip annular channel within which hot air circulates, and a panel for acoustic treatment comprising, from outside inwardly, an acoustic resistive layer, at least one honeycomb structure and one reflective layer as well as ducts for channeling hot air, at least one conduit with opening which opens into annular channel being provided for carrying hot air up to the panel for acoustic treatment, wherein opening is used for channeling hot air in direction which forms an angle β of less than 60° with hot air flow direction into annular channel. | 04-25-2013 |
20130097998 | THRUST REVERSER FOR AN AIRCRAFT HAVING SEMI-RECESSED TURBOFAN ENGINES - A jet propulsion unit of an aircraft, which comprises a turbofan engine ( | 04-25-2013 |
20130092309 | PROCESS AND DEVICE FOR WELDING A THERMOPLASTIC STIFFENER - The invention relates to a device for welding a stiffener to a skin. The stiffener has a stiffener foot with a bearing surface parallel to the skin surface and a stiffener flange projecting away from the plane of the bearing surface. The device includes a metallic support includes a seating surface matching the shape of the receiving side; a groove which accommodates a flange of the stiffener inserted in the groove; an insulative supporting structure for positioning a bearing surface against the receiving side; and a conformal panel for applying pressure forcing said bearing surface against said receiving side. A heater temporarily raises the temperature of bearing surface of the stiffener and the adjacent receiving side of the skin to above the melting point of the matrix when pressure is applied thereby welding the stiffener to the skin. | 04-18-2013 |
20130084792 | METHOD OF INTEGRATING AN AVIONICS BAY AND FLOOR STRUCTURE FOR IMPLEMENTATION - An integrated avionics bay in a floor area can be provided with adequate ventilation. The structure of an aircraft cockpit floor is able to integrate at least one bay, with a walking floor in the cockpit, a structural volume and a bay integrated in a space of the liberated structural volume. The bay as integrated in a horizontal position in this space includes a peripheral frame with at least one protective cover with a direct access to the bay at the floor level and a lower wall with a rear face access. Side openings formed in the frame can couple with vertical walls to allow fresh air blowing from the rear wall of the bay via a flow from rearwards to upwards to reach the top cover and an air extraction by an upper surface extractor. | 04-04-2013 |
20130082138 | VENTILATION SYSTEM, AIR BLOWING AND EXTRACTION CIRCUITS OF SUCH A SYSTEM, AS WELL AS AN AIRCRAFT AVIONICS BAY - A ventilation system for an avionics bay has two strut assemblies for stiffening the floor of the cockpit, each strut assembly being arranged symmetrically regarding to the central plane of the aircraft, and means of distribution of the blowing air in the cabinets of the bay from the strut assemblies. The extraction circuit includes exhaust ducts integrated in the cabinets and couples together by tight inter-cabinets junctions in an overall configuration of maximized compactness. | 04-04-2013 |
20130081248 | PROCESS FOR THE DESTRUCTION OF A BLIND FASTENER AND DEVICE FOR ITS IMPLEMENTATION - A method is provided for destroying a blind fastener joining at least two parts. The blind fastener includes, but is not limited to a body situated in the holes provided in the joined parts, with a head at each end thereof, and portions of which protrude above the level of the holes. The method also includes, but is not limited to withdrawing the accessible head of the fastener, and creating a hole that passes through the fastener. An insertion device is configured to restrain the remainder of the fastener in the hole, which has an elongated body having a diameter smaller than or equal to that of the hole and an expandable head at one end thereof The insertion device for restraining the remainder of the fastener being immobilised or capable of only limited movement relative to the joined parts, and expelling the remainder of the fastener from the holes. | 04-04-2013 |
20130080137 | CONVERSION METHOD AND SYSTEM - A computer-implemented method for converting a representation of a system into a behaviour model of the system is provided. The method can be used to convert a schematic diagram into a behavioural model. | 03-28-2013 |
20130079958 | METHOD AND SYSTEM FOR DETERMINING THE POSITION OF AN AIRCRAFT DURING ITS APPROACH TO A LANDING RUNWAY - A method for guiding an aircraft during its final approach to a landing runway, whereby the aircraft is guided during its approach by aircraft position information obtained from an GNSS satellite navigation system, wherein: prior to the start of the final approach a first time t | 03-28-2013 |
20130077279 | ELECTRICAL DEVICES MODULE FOR AN AVIONICS BAY - A module in the form of a pallet or a closed container includes a grouping together of the electrical devices in an avionics bay, in which the electrical devices are interconnected and attached so as to facilitate the mounting and thus limit the time it takes to mount the electrical devices in the avionics bay. | 03-28-2013 |
20130075535 | ELECTRICAL RUDDER CONTROL SYSTEM FOR AN AIRCRAFT - The rudder control system ( | 03-28-2013 |
20130075153 | ASSEMBLY COMPRISING A RACEWAY AND A BRANCHING DEVICE, AND ASSOCIATED BRANCHING DEVICE - The invention essentially relates to an assembly ( | 03-28-2013 |
20130068898 | CABLE RACEWAY SUPPORT DEVICE FOR AN AIRCRAFT, IN PARTICULAR AN AIRCRAFT WITH A STRUCTURE AT LEAST PARTLY FORMED FROM A COMPOSITE MATERIAL - A cable raceway support device for an aircraft, formed from an electrically conductive material, comprising a pedestal having a fastening plane for the fastening of the device onto a primary structure and also having, on a support face which is an opposite face to the fastening plane, at least one pair of jaws having at least one electrical contact enabling a sliding electrical contact to be formed and the support face has a contact that projects, and also has a jaw overhanging the support face, the jaw forming with part of the pedestal the pair of jaws forming a stirrup-shaped clamp comprising a base and two branches, one branch of the clamp merging with the pedestal, and the other branch of the clamp corresponding to the jaw and bearing a second contact facing the first contact. | 03-21-2013 |
20130067450 | METHOD OF UPGRADING AN AIRCRAFT - An aircraft including a network of computers on board the aircraft, software applications loaded onto the computers of the network of computers. This method includes interrogating the computers of the network of computers on board the aircraft to know the configuration of the software applications loaded into the computers of the network of computers on board the aircraft, analyzing the configuration by at least one computer, identifying the software applications for which there exists a more recent version than the version loaded onto the network of computers on board the aircraft, computing a new software configuration for the aircraft by a computer on the ground, constructing a set of software applications, integrating updated software applications corresponding to a more recent version of a software application loaded into the computers of the network of computers on board the aircraft, loading the new configuration onto the computers on board the aircraft. | 03-14-2013 |
20130066488 | METHOD AND DEVICE FOR AUTOMATICALLY ESTIMATING AN AIRSPEED OF AN AIRCRAFT - Method and device for automatically estimating an airspeed of an aircraft | 03-14-2013 |
20130062470 | DEVICE FOR LINKING A STRINGER AND A FRAME OF AN AIRCRAFT STRUCTURE - A device for linking a frame and a stringer of an aircraft structure, including a first portion connected to a support surface of a frame, a second portion connected to a support surface of a stringer and a third portion referred to as intermediary portion connecting the first portion to the second portion. The second portion is connected to the intermediary portion by means of an articulation allowing for a relative movement between the two portions along a rotation axis perpendicular to the support surface of the stringer. The first portion is connected to the intermediary portion by means of an articulation allowing for a relative movement between the two portions along a rotation axis parallel to the support surface of the frame and to the support surface of the stringer. | 03-14-2013 |
20130060970 | CONNECTION SYSTEM AND SIMULATOR USING SUCH A CONNECTION SYSTEM - A system for connecting a plurality of plugs to a computer system, such as a simulator, which includes: a plurality of channels that are each connected to a plug and are selectively configurable in a first mode, for acquiring a signal that is present on the plug, or in a second mode for applying a signal to the plug; and a unit that is connected to the computer system by an information system and configured so as to control, in the channels configured in the second mode, application of a signal on the basis of data received from the computer system and so as to send data, representing signals that are measured by the configured channels in the first mode, to the computer system. | 03-07-2013 |
20130057059 | METHOD AND DEVICE FOR PROTECTING AN AUTOTRANSFORMER FOR AN AIRCRAFT - The invention relates to a method for protecting a multi-phase autotransformer for an aircraft, including the steps of receiving ( | 03-07-2013 |
20130056591 | MULTIFUNCTIONAL COMB TO SECURE METALLIC PIPING AND METHOD FOR SECURING SUCH PIPING - A multifunctional comb includes an upper half-comb provided to be mounted on a support and a lower half-comb provided to be mounted on the support through the upper half-comb and a screw system. The half-combs have arches facing each other to grip the piping. In addition, each of the half-combs has at least two half-bores located in front of each other to form bores of the comb, as well as inter-arches connecting faces. The half-bores, the arches and the connecting faces are continuously covered by an electrically conductive coating in order to ensure the plating function. Moreover, the half-bores, the upper half-comb and the bottom half-comb include structure coupled to the half-combs that can be secured to the support respectively in a temporary and permanent way. | 03-07-2013 |
20130056582 | LANDING GEAR MOUNTED UNDER AN AIRCRAFT WING - A landing gear mounted under an aircraft wing is provided. The aircraft can comprise a fuselage and wings each comprising at least one longitudinal spar connected to a wing box being part of the structure of the fuselage. The landing gear can comprise one leg that pivots, on its upper end, around a rotation axis to occupy at least one extended position and one retracted position and which is provided, on its lower end, with rolling means, the leg being connected, on its upper end, to the longitudinal spar of said wing. The landing gear can also comprise at least one inclined front strut connected, on its lower end, to said leg and connected, on its upper end, to the structure of the fuselage thru connecting means. The connecting means can comprise a sliding bearing crossed by at least one part of the upper end of said strut. | 03-07-2013 |
20130043720 | METHOD AND DEVICE FOR PROTECTING AN AUTOTRANSFORMER FOR AN AIRCRAFT - The invention relates to a method for protecting a multi-phase autotransformer for an aircraft, including the steps of receiving ( | 02-21-2013 |
20130043348 | METHOD FOR ASSEMBLING WINDOW COAMING ON A FUSELAGE, COAMING TO BE USED, AND AIRCRAFT FUSELAGE PROVIDED WITH SUCH COAMING - A reduction of the multiple costs of manufacture, assembly use, and upkeep connected with the assembly of window frames on aircraft fuselages. To this end, the invention provides a particular shape for the frames connected to the fuselage skin according to a specific assembly method. The shape enables, among other things, the window frames to be fitted onto the skin by means of adhesion and also frames to be dispensed with between the fuselage and the window. In one embodiment, composite material window frame has a wall totally in the shape of a crown that is connected, through co-adhesion, to the inner surface of the fuselage skin, also made of composite material. The skin is cut into a window-receiving opening, and the frame has a T-shaped cross section, wherein the bar of the “T” that forms the crown includes two portions having substantially equal lengths “T.” | 02-21-2013 |
20130042428 | WINDSCREEN-WIPER BLADE HAVING MODIFIABLE VERTICAL FLEXIBILITY - Wiper blade for a surface of double curvature type, the said wiper blade including a flexible longitudinal wiper and means for exerting a bearing force at at least one point of the said wiper along a direction Z mainly normal to the surface, also including a longitudinal part, attached to the wiper at several points, and means to vary over time and in at least one segment of the longitudinal rod the rigidity in bending of this longitudinal rod in a plane XZ normal to the surface between previously chosen values. | 02-21-2013 |
20130040117 | WALL REINFORCED COMPOSITE MATERIAL - A wall panel of composite material including at least two carbon fiber layers oriented parallel to the plane of the panel and embedded in a resin matrix. At least one reinforcement mesh is inserted between the two fiber layers. The mesh has at least a first series of linear elements with a section greater than or equal to 0.07 mm | 02-14-2013 |
20130035809 | METHOD AND SYSTEM FOR DETERMINING FLIGHT PARAMETERS OF AN AIRCRAFT - According to the invention, the system for determining, in real time, flight parameters of an aircraft, in the course of a flight of the latter, comprises an extended Kalman filter ( | 02-07-2013 |