| AIRBUS OPERATIONS (SAS) Patent applications |
| Patent application number | Title | Published |
|---|
| 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 |
| 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 |
| 20130034437 | FASTENING DEVICE PARTICULARLY SUITABLE FOR THE FASTENING BETWEEN AN AIR INTAKE AND AN ENGINE OF AN AIRCRAFT NACELLE - An aircraft nacelle includes a first conduit for an air inlet and a second conduit for an engine, arranged end to end and connected by an annular flange, attached to the air inlet, and an annular flange, attached to the engine. The annular flanges are connected by a plurality of passage holes in the annular flanges and arranged in line with each other. Rods are housed in the passage holes. For at least one rod, the passage hole of one of the annular flanges has a diameter greater than the diameter of the rod allowing the rod to move in case of deformation of one of the two conduits. An angle profile is inserted between the rod and a cylindrical portion adjacent to the annular flange and. is connected to the adjacent cylindrical portion through the intermediary of at least one means for absorbing eventual deformations in radial direction. | 02-07-2013 |
| 20130033036 | FASTENING DEVICE PARTICULARLY SUITABLE FOR THE FASTENING BETWEEN AN AIR INTAKE AND AN ENGINE OF AN AIRCRAFT NACELLE - A fastening device includes an annular flange connected to an air intake, an annular flange connected to a powerplant pressed against the annular flange and fastening elements that allow the annular flanges to be linked, and for at least a first fastening element, a blade is fitted between the fastening element and the annular flange, the blade consisting of at least a central part linked to the first fastening element, radially mobile relative to the annular flange, and at least one part offset for which at least radial centripetal displacement is limited relative to the annular flange, the two parts being offset along the direction of the circumference. | 02-07-2013 |
| 20130032669 | FASTENING DEVICE PARTICULARLY SUITABLE FOR THE FASTENING BETWEEN AN AIR INTAKE AND AN ENGINE OF AN AIRCRAFT NACELLE - An aircraft nacelle with a connecting device between a first conduit of an air intake and a second conduit of a motor, both conduits being arranged end-to-end, the connecting device including an annular flange connected to the air intake, an annular flange connected to the motor pressed against annular flange of the air intake, the flanges extending in a plane perpendicular to the longitudinal axis of the nacelle; bolt holes formed in annular flanges and disposed plumb to one another; and connecting elements located in bolt holes, for connecting the annular flanges, wherein at least one flange includes at least one opening interposed between a bolt hole and junction zone of the flange and/or between a bolt hole and outer edge of the flange. | 02-07-2013 |
| 20130030612 | METHOD AND DEVICE FOR AN OPTIMAL MANAGEMENT OF THE ENERGY OF AN AIRCRAFT - Method and device for an optimal management of the energy of an aircraft. | 01-31-2013 |
| 20130030611 | METHOD AND DEVICE FOR AN OPTIMAL MANAGEMENT OF THE VERTICAL TRAJECTORY OF AN AIRCRAFT - The device ( | 01-31-2013 |
| 20130030610 | Automatic Estimation Process And Device For A Flight Parameter Vector In An Aircraft, As Well As Detection Methods And Assemblies For A Failure Affecting Such A Vector - Automatic estimation process and device for a flight parameter vector in an aircraft, as well as detection methods and assemblies for a failure affecting such a vector. | 01-31-2013 |
| 20130026301 | NACELLE FOR VARIABLE SECTION NOZZLE PROPULSION UNIT - The invention relates to a nacelle for a variable area nozzle propulsion unit comprising a nacelle, hosting a turbofan jet engine, of dual-flow type. The propulsion unit includes: a fixed part, carried by the inboard half-nacelle defined by a vertical plane of symmetry of the nacelle; and a movable part carried by the outboard half-nacelle. The moving part containing or releasing part of the secondary flow, depending on its open or closed position. The moving part being able to move to a discrete number of positions including a closed position, an open position, and one or more intermediate positions so as to provide variable area nozzle configurations for the turbofan engine. | 01-31-2013 |
| 20130026299 | Method And Device For An Optimal Management Of The Slats, The Flaps And The Landing Gear Of An Aircraft - Method and device for an optimal management of the slats, the flaps and the landing gear of an aircraft. | 01-31-2013 |
| 20130026292 | STIFF PANEL FOR AIRCRAFT, COMPRISING STIFFENERS WITH NOTCHED CORES - A stiffened panel includes a panel at least one of whose surfaces is equipped with stiffeners each of which includes a base that is pressed against the surface of panel, as well as a core that is oriented orthogonally relative to the base and whose first longitudinal edge is integral to the latter. | 01-31-2013 |
| 20130026288 | Aircraft Comprising At Least One Net For Reducing Aerodynamic Noise From A Structural Element Of Said Aircraft - The invention relates to an aircraft comprising at least one net for reducing aerodynamic noise from a structural element of said aircraft. According to the invention, the flexible net ( | 01-31-2013 |
| 20130026287 | Method And Device For Detecting An Uncontrolled Movement Of An Aircraft Control Surface - Method and device for detecting an uncontrolled movement of an aircraft control surface. | 01-31-2013 |
| 20130024727 | METHOD FOR AUTOMATICALLY RELOADING SOFTWARE AND A DEVICE FOR AUTOMATICALLY RELOADING SOFTWARE - Method for automatically reloading software characterized in that it comprises: a step of detecting corruption (E | 01-24-2013 |
| 20130024165 | METHOD FOR DESIGNING STANDARDISED REPAIR KITS FOR AN AIRCRAFT FUSELAGE - A method for designing repair kits for a predefined area of the external/internal structure of an aircraft, the repair kits each including an external/internal structural part having predefined shape and size, suitable for being placed within the existing external/internal structure, instead of an equivalent shape including a damaged area, which can be removed or not, the method including creating a range of standardised repair kits, optimized according to an estimate of the most likely types of accidental damage in the studied area. | 01-24-2013 |
| 20130018533 | Method For Determining The Speed Air Aircraft And Aircraft Equipped With Means For ImplementationAANM Feau; JulienAACI ToulouseAACO FRAAGP Feau; Julien Toulouse FRAANM Francois; HugoAACI Saint-JeanAACO FRAAGP Francois; Hugo Saint-Jean FR - An aircraft is equipped with engines, each engine having at least one pod and one compressor/turbine hitch. The aircraft has at least one data processing unit and at least one system at the engine level. At least one engine is equipped with at least one static pressure probe for measuring the ambient air under the pod. Also, air static pressure probes are arranged at the engine levels, with one pressure probe at the output of the compressor, at least one rotation speed sensor, for example of a blower, and ambient air temperature probes at the air input or in any compression point. The processing unit is able, from measurements performed by such probes at the engine level, to supply to at least one of the systems at the engine level, determination data for the air speed of the aircraft. | 01-17-2013 |
| 20130015602 | PROCESS FOR THE PRODUCTION OF A DOUBLE-CURVED PANELAANM BERNADET; PhilippeAACI ColomiersAACO FRAAGP BERNADET; Philippe Colomiers FRAANM GIUSEPPIN; LaurentAACI FinhanAACO FRAAGP GIUSEPPIN; Laurent Finhan FR - A process for the production of an aircraft panel made of double-curved composite material, with the panel being obtained from a three-dimensional preform that includes fibers that are distributed in a defined arrangement, includes manufacturing a flat fiber preform ( | 01-17-2013 |
| 20130014840 | PRESSURISED HOT AIR DUCT OF AN AIRCRAFT EQUIPPED WITH A DEVICE FOR DETECTING AIR LEAKAGEAANM MILLET; GerardAACI PIBRACAACO FRAAGP MILLET; Gerard PIBRAC FRAANM BERNARD; XavierAACI BRUGESAACO FRAAGP BERNARD; Xavier BRUGES FRAANM NOECKER; MatthiasAACI TOURNEFEUILLEAACO FRAAGP NOECKER; Matthias TOURNEFEUILLE FR | 01-17-2013 |
| 20130009010 | SYSTEM FOR DRAINING WATER CONDENSATION IN AN AIRCRAFT - The invention relates to an aircraft comprising: | 01-10-2013 |
| 20120328846 | METHOD AND DEVICE FOR THE AUTOMATED PRODUCTION OF DRY FIBROUS PREFORMS - The invention relates to a device and a method for the realization of elongated textile preforms intended for manufacturing load-bearing composite members by means of a method using resin infusion. | 12-27-2012 |
| 20120328439 | Method For Balancing A Propulsive System Having Non-Hull Contra-Rotating Propellers - According to the invention, in order to eliminate or at least to reduce a possible unbalance of the propulsive system ( | 12-27-2012 |
| 20120328433 | Method For Balancing A Propulsive System Having Non-Hull Contra-Rotating Propellers - According to the invention, at least one of the counterweights ( | 12-27-2012 |
| 20120325344 | DEVICE AND METHOD FOR MAINTAINING PARALLELISM BETWEEN THE TWO GLAZINGS OF AN AIRCRAFT DOUBLE GLAZING - Device intended for a double glazing including at least one outer glazing and one inner glazing separated by an intermediary space filled with a gas, used to isolate an inside environment from an outside environment, a pressure variation being liable to occur between these environments, for example in the case of an aircraft in flight, | 12-27-2012 |
| 20120318924 | AIR INTAKE OF AN AIRCRAFT NACELLE THAT INCORPORATES A REINFORCED LIP WITH A DEFROST SYSTEM BY JOULE-EFFECT - An air intake of an aircraft nacelle includes: | 12-20-2012 |
| 20120318029 | PROCESS FOR THE PRODUCTION OF AN ACOUSTIC TREATMENT PANEL THAT INTEGRATES CHANNELS JUXTAPOSED WITH AN ALVEOLAR STRUCTURE - A process for the production of an acoustic treatment panel that includes an acoustically resistive layer ( | 12-20-2012 |
| 20120317782 | Process for the Production of a Panel for the Acoustic Treatment Incorporating the Frost Treatment Function with Hot Air - A process for the production of an acoustic treatment panel that can be connected at a surface of an aircraft, in particular at a leading edge such as an air intake of an aircraft nacelle, whereby the panel includes an acoustically resistive layer ( | 12-20-2012 |
| 20120316748 | Method And Device For Monitoring A Turbine Engine Of An Aircraft - The device includes means for determining a value illustrating a thermomechanical state (ET) of the turbine engine, means for comparing this value with at least one threshold (S | 12-13-2012 |
| 20120312459 | METHOD FOR MANUFACTURING A COMPOSITE MATERIAL CURVED PART, AND DEVICE FOR MANUFACTURING A COMPOSITE MATERIAL CURVED PART - The invention concerns a process for manufacturing a curved part of composite material, during which the layers of fibers of composite materials ( | 12-13-2012 |
| 20120312112 | DISENGAGEABLE INTERFACE MECHANISM BETWEEN A MOTORIZATION SYSTEM OF AN AIRCRAFT LANDING GEAR ASSEMBLY AND A WHEEL - A motorization mechanism for a wheel of a landing gear assembly, including an input gear driven by a motor-reducer unit; a pendulum element, carrying two intermediate gear wheels driven in rotation by this element, with the intermediate gear wheels having synchronized rotation blocking mechanisms such that the two intermediate gear wheels can be simultaneously engaged or simultaneously released. The angular displacement of the pendulum element around its rotation axis is limited by a first and a second adjustable stop. These adjustable stops are set so that when the pendulum element comes into contact with an adjustable stop, the blocking mechanism of the intermediate gear wheels is freed, whereas it is engaged when the pendulum element is in the neutral position. This pendulum assembly faces a cog wheel that is capable of driving the hub of the said wheel. | 12-13-2012 |
| 20120304433 | METHOD FOR REPAIRING AN AIRCRAFT FUSELAGE - The invention relates to a method for repairing aircraft primary structures. More specifically, the invention relates to a method for repairing damage to the coating of an aircraft fuselage, which coating is made of fiber-reinforced composite material. This method comprises a step consisting of making a cut-out in the fuselage with a substantially parallelepipedal outline around the damages and of drilling a circular hole substantially centered on the intersection of the sides of the outline of the parallelepiped of the cut-out at each of the corners of said outline before the cutting out operation. | 12-06-2012 |
| 20120303186 | Method And System For Aiding The Piloting Of An Airplane During An Approach - The system ( | 11-29-2012 |
| 20120300093 | Method For Pointing A Plurality Of Predetermined Locations Inside A Structure And Corresponding Pointing System - According to the invention, the system ( | 11-29-2012 |
| 20120298795 | AIRCRAFT WITH A PIVOTABLE REAR PORTION - The invention relates to an aircraft the fuselage ( | 11-29-2012 |
| 20120296498 | METHOD FOR CONTROLLING THE DECELERATION ON THE GROUND OF A VEHICLE - The invention relates to a method for controlling the deceleration on the ground of a vehicle. The method obtains, from the crew of the vehicle or from an outside operator, parameters relating to its current position and its current speed. Then it determines a reference position and speed of the vehicle, the reference position being a theoretical position to be reached by the vehicle. Finally it determines, from indicated parameters and from reference parameters, a deceleration command with a view to ending up at a target position at a preselected speed. | 11-22-2012 |
| 20120292461 | MOUNTING FOR HOLDING ELONGATE OBJECTS IN POSITION RELATIVE TO A STRUCTURE - The invention relates to a mounting ( | 11-22-2012 |
| 20120290155 | Method And Device For Aiding The Piloting Of An Aircraft During An Intermediate Approach Phase Of A Descent - Method and device for aiding the piloting of an aircraft during an intermediate approach phase of a descent. | 11-15-2012 |
| 20120289109 | Method For Manufacturing A Part Of A Composite Material And Part Thus Obtained - The manufacturing method includes a step of resin transfer moulding, wherein resin is injected (E) in a preform ( | 11-15-2012 |
| 20120286505 | CONNECTION DEVICE FOR FUEL TUBING OF AN AIRCRAFT - A device for connecting aircraft fuel piping that includes male/female end fittings made of highly resistive material, designed to be bonded at the extremities of tubes in the piping and/or of piping connectors. | 11-15-2012 |
| 20120285950 | ELECTRICAL POWER DISTRIBUTION UNIT AND A VEHICLE HAVING SUCH A UNIT - In an electrical cabinet ( | 11-15-2012 |
| 20120285665 | Method for distribution of cooling air for electrical equipment installed in an avionic bay and aircraft equipped with such a bay - This invention relates to a method for distribution of cooling air for cooling an electrical equipment item installed in an avionic bay. | 11-15-2012 |
| 20120285132 | AVIONIC BAY COMPRISING A DEVICE FOR FILTERING COOLING AIR FOR ELECTRICAL EQUIPMENT INSTALLED IN SUCH A BAY AND AIRCRAFT EQUIPPED WITH SUCH A BAY - This invention relates to an avionic bay comprising a device for filtering cooling air for aircraft electrical equipment. | 11-15-2012 |
| 20120282052 | DEVICE FOR DRILLING A COMPLEX PANEL - The invention relates to a device for drilling and/or boring large complex panels. Said device comprises:
| 11-08-2012 |
| 20120280092 | FIXTURE DEVICE FOR AN AIRCRAFT TUBING - A device to attach an aircraft's piping that includes a clamping ring made up of two jaws shaped into a gliding arc breaker separator and including at least one transverse support cut-out for at least one tube. | 11-08-2012 |
| 20120280090 | CONNECTING DEVICE PARTICULARLY ADAPTED FOR THE CONNECTION BETWEEN AN AIR INTAKE AND AN ENGINE OF AN AIRCRAFT NACELLE - A connecting device between two cylindrical parts that are connected at a junction plane, more particularly suited for connecting an air intake and a power plant of an aircraft nacelle, includes—at the parts to be connected—a large number of through holes that are perpendicular to the junction plane and that empty out at the junction plane, arranged facing one another and connecting elements housed in the through holes, each including a rod with supports at each end that make it possible to keep the parts to be connected flattened. The through holes include—for each—at least one small cross-section that is adjusted to the rod of the connecting element close to the corresponding support and a cross-section with significant play at the junction plane so that the rod only undergoes very weak shear forces at the junction plane during the relative deformation of the assembled parts. | 11-08-2012 |
| 20120280083 | METHOD OF MAKING A SEALED JUNCTION BETWEEN AIRCRAFT PARTS - In the method of making a sealed junction between elongate aircraft parts that extend locally in main directions that are not mutually parallel, the following steps are performed: assembling a plurality of portions of a mold on the parts; and injecting a sealing material into the mold. | 11-08-2012 |
| 20120279729 | FLUID EJECTION DEVICE - A fluid ejection device for example used as a fire extinguisher in which ejected fluid is an extinguishing agent in liquid or powdery form. The device includes: a cylinder shaped tank, split hermetically, perpendicular to its axis, into two chambers by a piston, slidable axially inside the tank; a first chamber, including a non-gaseous fluid, which communicates with an ejection port closed by a cap, which can open for a pressure greater than or equal to a defined pressure in the first chamber; a second pressurization chamber to be connected to a mechanism increasing pressure in the chamber; and a mechanism to link the piston to the tank in full fixity at a storage position, which mechanism can break and release the piston for axial translation at a pressure higher than or equal to a given pressure in the pressurization chamber, to cause the fluid to be ejected. | 11-08-2012 |
| 20120273610 | ENGINE PYLON COMPRISING A VORTEX GENERATOR, AND METHOD FOR THE PRODUCTION THEREOF - The invention relates to a method for manufacturing an engine pylon ( | 11-01-2012 |
| 20120273609 | STREAMLINED PROFILE REDUCING THE SPEED DEFICIT IN ITS WAKE - The invention relates to a streamlined profile reducing the speed deficit in its wake, a pylon comprising such a profile, a propulsion assembly including such a pylon and an aircraft including this assembly. The profile comprises a device ( | 11-01-2012 |
| 20120268866 | Method Of Equipments Integration For A Complex Electrical Heart And Module Of Implementation - The invention aims at simplifying the electrical connections between equipment and an electrical power centre to be supplied in electricity, while enabling a good accessibility of each piece of equipment and an easier maintenance. To do so, a particular integration of this equipment is carried out so as to be able to assemble them together and connect them in a direct extension of the electrical power centre. According to one embodiment, an integration module consists in a frame and a cover, the frame having a substantially parallelepipedic shape adapted to be able to extend longitudinally along a main axis in parallel with a longitudinal main side of the electrical power centre of the structure to be supplied. Cells of constant section and a width being adjustable by movable intermediary walls, extend perpendicularly to the main axis. Such cells are adapted to receive formatted electrical equipment. | 10-25-2012 |
| 20120267478 | AIRCRAFT INCLUDING AN INTERNAL PARTITION - The aircraft includes a structural portion such as a fuselage, a wing, or a tail, the structural portion including a wall separating the inside from the outside of the portion and including fractions defining between them an inside volume of the portion and at least one structural partition separating zones of the volume, e.g. a front zone and a rear zone, from each other, the partition including at least one flexible diaphragm suitable for deforming and at least two preferably rigid supports supporting the diaphragm in discontinuous manner. | 10-25-2012 |
| 20120261521 | NACELLE INCORPORATING AN ELEMENT FOR CONNECTING A LIP AND AN ACOUSTIC ATTENUATION PANEL TOGETHER - An aircraft nacelle includes a first subassembly consisting of a pipe ( | 10-18-2012 |
| 20120261069 | AUTOMATED DRAPE-FORMING DEVICE - The invention relates to an automated device for implementing a drape-forming step to form a laminated fibrous preform, which is then impregnated with resin to produce a part made of composite material. The invention relates more particularly to the production of preforms for manufacturing parts such as panels, in particular very thick panels, that extend basically in two dimensions. The device of the invention comprises a manipulator ( | 10-18-2012 |
| 20120256047 | Method For Improving The Aerodynamic Efficiency Of The Vertical Tail Of An Aircraft - According to the invention, the thickness (EP | 10-11-2012 |
| 20120255258 | Method Of Slowing The Propagation Of Cracks In A Fail Safe Structure And Fail Safe Frame, Especially For Fuselage - The invention seeks to improve the integrity in respect of tolerance to damage following the spread of cracks in failure-mitigating structures of the failsafe type. To do this, the invention proposes to form a composite hybrid structure within the failure-mitigating structure. A failure-mitigating mainframe, particularly of an aircraft fuselage, equipped with a structural element made of composite according to the invention, has profiled longitudinal structural components assembled back to back by fasteners. First sides are longitudinally aligned and bonded to the fuselage skin, and the other sides are longitudinally aligned some distance away from the first sides. Fasteners couple the composite structural element to the external face of the sides of the metal components that are longitudinally aligned some distance away from the first sides. | 10-11-2012 |
| 20120253650 | Method And Device For Checking That An Aircraft Fulfils Successive Time Constraints - Method and device for checking that an aircraft fulfils successive time constraints. | 10-04-2012 |
| 20120253562 | Method And Device For Automatically Managing The Vertical Profile Of The Flight Plan Of An Aircraft - The device includes means for determining a plurality of successive standard flight sections (S | 10-04-2012 |
| 20120253559 | Method And Device For Automatically Detecting Erroneous Air Data On An Aircraft - The device ( | 10-04-2012 |
| 20120248250 | AIRCRAFT NACELLE AIR INTAKE INCORPORATING OPTIMIZED ICE-TREATMENT HOT AIR INJECTION MEANS - An aircraft nacelle air intake includes a duct extending around the circumference of the air intake and elements ( | 10-04-2012 |
| 20120248249 | AIR INLET OF AN AIRCRAFT NACELLE INCLUDING OPTIMIZED FROST TREATMENT - An air inlet of an aircraft nacelle includes a pipe, extending over the circumference of the air inlet and defined in the back by a front frame, and an element for the localized injection of hot air into the pipe, thus ensuring the flow of hot air into the pipe in one direction along the circumference of the nacelle. The inlet includes at least one vortex generator ( | 10-04-2012 |
| 20120247597 | DEVICE FOR CONNECTING AN AIR LEAK DETECTION SYSTEM TO A SLEEVE THAT ENVELOPS A PRESSURIZED AIR HOSE OF AN AIRCRAFT - An aircraft includes a hose that makes it possible to channel the pressurized air that is used in a sleeve ( | 10-04-2012 |
| 20120246522 | METHOD AND DEVICE FOR DETECTING LOGIC INTERFACE INCOMPATIBILITIES OF EQUIPMENT ITEMS OF ON-BOARD SYSTEMS - The invention in particular has as an object detecting incompatibility between equipment items of a on-board system. A logic interface associated with one equipment item comprises at least one input while a logic interface associated with another equipment item comprises at least one output. The input and the output are connected. After a minimal data definition level associated with the input and a data definition level associated with the output have been obtained ( | 09-27-2012 |
| 20120245862 | METHOD FOR THE STRUCTURAL ANALYSIS OF PANELS CONSISTING OF AN ISOTROPIC MATERIAL AND STIFFENED BY TRIANGULAR POCKETS - The invention relates to a method for dimensioning, by an analytical method, of an essentially plane panel consisting of a homogenous and isotropic material, said panel consisting of a skin reinforced by a set of three parallel bundles of stiffeners built into the panel. The pockets determined on the skin by said groups of stiffeners are triangular, the stiffeners are blade shaped and the stiffened panel must comply with specifications for mechanical resistance to predetermined external loads, the angles between bundles of stiffeners being such that the triangular pockets have any kind of isosceles form. | 09-27-2012 |
| 20120241249 | PANEL FOR THE ACOUSTIC TREATMENT WITH A PROGRESSIVE THICKNESS - An aircraft nacelle includes an air inlet ( | 09-27-2012 |
| 20120240108 | METHOD AND DEVICE FOR INSTALLING/UNINSTALLING SOFTWARE MODULES, WITH CENTRALIZED RESOLUTION OF CONSTRAINTS, IN AIRCRAFT APPARATUSES - The invention in particular has as an object the installation and/or deinstallation of at least one software module, with centralized resolution of constraints, in aircraft equipment items. After having received a list of software module references, the said list comprising at least one reference to the said at least one software module, and at least one command, linked to the said at least one reference, for installation of deinstallation of the said at least one software module, the constraints are accessed. This access is independent of the access to the said at least one module. A sequence of basic operations resolving the said constraints then is evaluated for applying the said at least one command to the said at least one reference. | 09-20-2012 |
| 20120239244 | MONITORING OF A FLIGHT CONTROL ACTUATOR OF AN AIRCRAFT - The invention concerns a system for monitoring a flight control actuator of an aircraft, including:
| 09-20-2012 |
| 20120237736 | PROCESS FOR THE PRODUCTION OF A PROFILE MADE OF COMPOSITE MATERIAL FIBERS THAT HAS A HALF-NAIL-HEAD OR NAIL-HEAD CROSS-SECTION - A process for the production of a fiber profile ( | 09-20-2012 |
| 20120237332 | FLUID-COOLING DEVICE FOR A TURBINE ENGINE PROPULSIVE UNIT - The invention relates to a fluid cooling device ( | 09-20-2012 |
| 20120235620 | Electrical Actuator And Method For Controlling Such An Actuator - The actuator ( | 09-20-2012 |
| 20120234489 | PROCESS FOR MANUFACTURING A PART MADE OF COMPOSITE MATERIAL THAT COMPRISES AT LEAST ONE RADIUS OF CURVATURE - A process for the production of a part made of composite material including at least one radius of curvature, includes a stage for deposition of pre-impregnated fiber layers ( | 09-20-2012 |
| 20120234110 | DEVICE FOR DETECTING SHOCKS ON A STRUCTURE - A detection device ( | 09-20-2012 |
| 20120232725 | Method For Optimizing Aircraft Landing On A Runway - According to the invention, a target vertical speed (Vzo), defined in relation to the ground, is determined and an optimized ground slope (γ | 09-13-2012 |
| 20120223720 | Method And System For Detecting And Locating By Reflectometry Electrical Faults In Metal Structures - The invention aims to provide for detecting and locating by reflectometry electrical faults in a network of metal structures able to receive electrical cables and perform the return-current function of these cables. The invention consists in injecting a probe signal into a conductor, associated with the structures, then in analyzing the reflected signal by comparison with a reference signal. | 09-06-2012 |
| 20120215386 | Method And Device For Aiding The Flight Management Of An Aircraft - Method and device for aiding the flight management of an aircraft.
| 08-23-2012 |
| 20120212391 | RADOME AND DEVICE FOR ATTACHING SAID RADOME TO AN AIRCRAFT - The invention relates to a radome ( | 08-23-2012 |
| 20120211602 | FRAME FOR AN OPENING PROVIDED IN AN AIRCRAFT FUSELAGE - A frame of a door that is provided at an opening made in a fuselage of an aircraft that is delimited by a skin, whereby the frame that includes an upper longitudinal stiffener and a lower longitudinal stiffener provides the connection between two vertical substructures ( | 08-23-2012 |
| 20120211597 | SYSTEM FOR ATTACHING AN IMPELLER ENGINE - The invention relates to a system for attaching an element ( | 08-23-2012 |
| 20120205991 | DEVICE FOR SIMULATING AN ALTERNATOR, METHOD OF CONTROLLING SUCH A DEVICE AND SIMULATION SYSTEM COMPRISING SUCH A DEVICE | 08-16-2012 |
| 20120205495 | Method And Device For Yaw Controlling Of An Aircraft - According to the invention, the pilot having beforehand moved a commanding system in such a manner that the movement of said system ( | 08-16-2012 |
| 20120205490 | AIRCRAFT HORIZONTAL STABILISER FITTED WITH LEADING-EDGE STRAKE - An adjustable, or all-moving, horizontal stabiliser for an aircraft, the stabiliser having a leading edge, a trailing edge, a root and a tip, and a strake fixed with respect to the stabiliser and attached to, or integrally formed with, the stabiliser leading edge adjacent the root. | 08-16-2012 |
| 20120205192 | PANEL FOR ACOUSTIC TREATMENT COMPRISING A JUNCTION BETWEEN TWO PARTS AND PROCESS FOR THE REPARATION OF A PANEL FOR ACOUSTIC TREATMENT - An acoustic treatment panel includes two portions with edges spaced in one direction, and from the outside to the inside, a first acoustically resistive layer, a first alveolar structure, and a reflective layer, and a block inserted between the two edges which includes, from the outside to the inside, a second acoustically resistive layer arranged at the first acoustically resistive layer and a second alveolar structure. The block includes at least one sector of alveolar structures with sloped pipes whose height is less than that of the first alveolar structure, whereby the pipes are sloped in a direction such that the ends of the pipes are close to one of the edges of the portions at the first acoustically resistive layer, and the opposite ends of the pipes are moved away from the edge and the reflective layer so as to house connecting elements between the block and the panel. | 08-16-2012 |
| 20120204967 | Device For Ventilating A Compartment - A ventilation device for a compartment, preferably a compartment of an aircraft engine, the device including an air intake adapted to capture a flow of air outside the compartment, an air diffuser adapted to guide the air flow into the compartment, and an air distributor adapted to distribute the air flow within the compartment, the air distributor in this device being separated from the air diffuser, and being placed inside the compartment at a distance from the air diffuser | 08-16-2012 |
| 20120201391 | DEVICE FOR LOCALIZING ACOUSTIC SOURCES AND/OR MEASURING THEIR INTENSITIES - Device for localizing acoustic sources and/or measuring their intensities, intended in particular to be used in confined spaces, the device including at least one acoustic antenna having a first series of microphones delimiting a first volume, and a second series of microphones delimiting a volume containing at least substantially the first series of microphones. | 08-09-2012 |
| 20120196080 | STIFFENED STRUCTURE INTEGRATING AN OPENING - A stiffened structure includes stiffeners ( | 08-02-2012 |
| 20120193475 | CONNECTOR FOR STIFFENING FRAMES BETWEEN AN AIRCRAFT FUSELAGE AND A WING BOX - The stiffening frames ( | 08-02-2012 |
| 20120186224 | AIRCRAFT JET ENGINE COMPRISING A SYSTEM FOR REDUCING THE NOISE GENERATED BY THE EJECTION OF THE GASES - The invention relates to an aircraft jet engine comprising a nozzle ( | 07-26-2012 |
| 20120183296 | MULTIPORT PASSIVE DEVICE FOR SHARING OPTICAL SIGNALS - A multiport passive optical signal sharing device enabling optical signals received by each of a first plurality of ports of the device to be transmitted to all of the ports of a second plurality of ports of the device. The device includes a first coupling mechanism adapted to combine signals received by each port of the first plurality of ports of said device into a first optical signal, the first optical signal being transmitted over a bi-directional optical link. The device further includes a second coupling mechanism and guide for redirecting the first optical signal in a form of a second optical signal into the bi-directional optical link, in the opposite direction from that of the first optical signal, the first coupling mechanism being adapted to duplicate the second optical signal on each port of the second plurality of ports of the device. | 07-19-2012 |
| 20120181384 | DEVICE FOR PROTECTING PIPING FROM LIGHTNING - A device for protecting piping from lightning. The piping includes tubular metal sections connected to each other by connection parts, a first portion of the connection parts being plastic material parts and a second portion of the connection parts being metal parts. | 07-19-2012 |
| 20120180718 | DEVICE FOR APPLYING A PROTECTIVE MATERIAL ON THE EDGE OF AN ELEMENT - Device for applying a protective material on one edge of a part, includes a body equipped with elements for applying the protective material on the edge, elements for calibrating the protective material in terms of height after application, at least one stop to position the body relative to the edge and elements for calibrating the edges of the protective material including two smoothing plates that rest respectively against the right and the left surfaces of the part adjacent to the edge, at least one of the two smoothing plates being movable relative to the other smoothing plate. The body includes at least one arm that supports a smoothing plate and pivots relative to the body around an axis of rotation so as to regulate the spacing between the two smoothing plates and return elements that tend to make the arm pivot so as to bring the smoothing plates close together. | 07-19-2012 |
| 20120180279 | BLIND FASTENER EQUIPPED WITH A SELF-BREAKING HOLDING SYSTEM - A blind attachment that includes a body ( | 07-19-2012 |
| 20120177878 | Part For And Method Of Repairing A Damaged Structure, In Particular An Airframe Skin, And A Repair Kit For Implementing It - The invention aims to enable rapid and efficient repair of damaged metal structures, in particular airframe fuselage skins, without necessitating any additional thickness compromising the transmission of waves. To this end it proposes a double internal/external plate constituted by a particular material. In one embodiment, the damaged structure having an external face and an internal face, the part features a substantially plane double internal/external plate adapted to be fastened to the internal face and the external face of the metal structure, respectively, and a central hub connecting the internal plate and the external plate. A groove is thus formed between these plates. The part is constituted of a single composite material block, and a glass ply, lining the groove, may be positioned between the plates and the structure. The hub may have passing through it at least one orifice adapted to allow connections to pass through the structure. | 07-12-2012 |
| 20120175462 | AIRCRAFT ENGINE MOUNTING STRUCTURE, ASSEMBLY COMPRISING THIS STRUCTURE AND ASSOCIATED AIRCRAFT - An engine is suspended from a main linear portion of a structure mounted on a fuselage or a wing surface of an aircraft. A connection includes flat symmetrical wings at an angle to one another, to support an attaching flange on which the engine is mounted, directly or through a mounting element. The flat shape of the wings makes them easy to manufacture, and enables them to resist the forces satisfactorily. The intermediate element resists overhang forces of the mounting satisfactorily. Flexible connections filter the engine's vibrations and prevent irregular forces being transmitted. | 07-12-2012 |
| 20120173052 | Method And Device For Automatically Monitoring Air Operations Requiring Navigation And Guidance Performance - The monitoring device ( | 07-05-2012 |
| 20120168558 | AIRCRAFT ASSEMBLY INCLUDING AN ELEMENT FOR MOUNTING AN ENGINE AND ASSOCIATED AIRCRAFT - An engine is mounted on a structure by an intermediate structure assembled by flanges, to the structure and to the engine, where a rigid structure connects the flanges. This arrangement enables design of the structure to be simplified while allowing a substantial overhang when it is sought to mount the engine by the plane of its center of gravity, while being obliged to move the mounting structure away from it. The intermediate structure is resistant to forces resulting from the overhang, and also allows assemblies that are favorable to a balanced transmission of forces to the structure and a satisfactory ability to filter vibrations. | 07-05-2012 |
| 20120160962 | INSTALLATION ASSEMBLY INCLUDING A FIXATION RAIL FOR ATTACHING DEVICES IN AN AIRCRAFT - The invention relates to a fastening assembly for the fastening of systems in an aircraft comprising frames ( | 06-28-2012 |
| 20120153078 | FRONT PART OF AN AIRCRAFT FUSELAGE INCORPORATING A BAY FOR STOWING LANDING GEAR - A front part of an aircraft fuselage according to this invention comprises:
| 06-21-2012 |
| 20120152443 | METHOD FOR MAKING A NETWORK OF DRAINAGE PIPES AND ACOUSTIC PROCESSING PANEL INCLUDING SUCH A NETWORK OF DRAINAGE PIPES - A process for producing a panel for acoustic treatment including an acoustically resistive porous layer, at least one alveolar structure, a reflective layer with openings, and a drainage plate having at least one furrow for delimiting at least one evacuation pipe when the drainage plate is flattened against the free surface of the reflective layer, includes: shaping, if necessary, the reflective layer according to its final geometry, affixing a demolding film on at least one portion of the free surface of the reflective layer, positioning on the demolding film at least one core whose cross-section is adapted to that of the evacuation pipe so that the at least one core covers the openings of the reflective layer, molding the drainage plate on the demolding film and the at least one core, demolding the drainage plate and removing the at least one core and the demolding film, and making the drainage plate integral with the free surface of the reflective layer. | 06-21-2012 |
| 20120151733 | TAPPED INSERT FOR CYLINDRICAL BORE AND INSTALLATION EQUIPMENT FOR SUCH INSERT - The present invention relates to a tapped insert for cylindrical plain bore ( | 06-21-2012 |
| 20120150369 | Method And Device For Aiding The Approach Of An Aircraft During An Approach Phase For The Purpose Of Landing - The device ( | 06-14-2012 |
| 20120150368 | Method And Device For Automatically Monitoring Lateral Guidance Orders Of An Aircraft - Method and device for automatically monitoring lateral guidance orders of an aircraft. | 06-14-2012 |
| 20120150367 | Method And Device For Automatically Monitoring The Ability Of An Aircraft To Follow A Flight Trajectory With At Least One Turn - Method and device for automatically monitoring the ability of an aircraft to follow a flight trajectory with at least one turn. | 06-14-2012 |
| 20120150366 | Method And Device For The Passivation Of Guidance Orders Of An Aircraft - The device ( | 06-14-2012 |
| 20120146816 | Automatic Method And Device For Aiding The Piloting Of An Airplane - The device ( | 06-14-2012 |
| 20120146403 | AIRCRAFT COMPRISING A REVERSIBLE ROTARY ELECTRICAL MACHINE - The invention concerns an aircraft comprising a reversible rotary electrical machine | 06-14-2012 |
| 20120145254 | AIR INLET FOR AIRCRAFT PROPULSION UNIT HAVING A STRUCTURE RESISTANT TO EXCESS PRESSURE AND A PROCESS FOR REPAIRING AN AIR INLET OF AN AIRCRAFT PROPULSION UNIT - An air inlet for nacelle of an aircraft propulsion unit comprising an inner envelope provided with a plurality of orifices for passage of fluid passing through said envelope, and a lip connected to the upstream edge of said inner envelope, and having a portion devoid of orifices for passage of fluid with an axial span of between 20% and 90% of the span of said inner envelope, and a circumferential span α of between 60° and 150° about a longitudinal axis of said air inlet. | 06-14-2012 |
| 20120143505 | Method And Device For Determining An Optimal Flight Trajectory Followed By An Aircraft - Method and device for determining an optimal flight trajectory followed by an aircraft. | 06-07-2012 |
| 20120143487 | Method And Device For Aiding The Evaluation Of A Flight Trajectory Intended To Be Followed By An Aircraft In A Constrained Environment - Method and device for aiding the evaluation of a flight trajectory intended to be followed by an aircraft in a constrained environment. | 06-07-2012 |
| 20120140041 | METHOD AND SYSTEM FOR THE REMOTE INSPECTION OF A STRUCTURE - The invention relates to a method for the remote inspection of a structure, comprising the following operations:
| 06-07-2012 |
| 20120138746 | OBLIQUE PANEL AT THE REAR OF A CENTRAL BOX OF AN AIRCRAFT FUSELAGE - An aircraft structure includes a wing spar ( | 06-07-2012 |
| 20120138741 | Method And Device For Aiding The Localization Of An Aircraft Wreck Submerged In A Sea - Method and device for aiding the localization of an aircraft wreck submerged in a sea. | 06-07-2012 |
| 20120138736 | AIRPLANE WITH A TAILCOAT TAIL ASSEMBLY AND REAR ENGINE - An airplane, including a fuselage having an elongate shape along a longitudinal axis of the airplane, and at least one wing attached to the fuselage between front and back ends of the fuselage and a substantially cylindrical central portion and a rear scaleable portion on which a vertical tail assembly and a rear propulsion assembly are attached. Between a section for connecting the rear portion to the central portion of the fuselage and the back end: the maximum width of each fuselage section is constant or increases towards the rear up to a maximum fuselage width L; the height of each fuselage section decreases towards the rear, such that the back end of the fuselage forms a thin trailing edge substantially horizontal in the indicating line of the airplane and substantially rectilinear; a reactor for the propulsion assembly is provided in a so-called semi-buried configuration in the fuselage. | 06-07-2012 |
| 20120137798 | PROTECTING DEVICE FOR AN AIRCRAFT EXTERIOR PROBE | 06-07-2012 |
| 20120136562 | Method And System For Aiding The Taxiing Of An Aircraft On An Airport Domain - Method and system for aiding the taxiing of an aircraft on an airport domain. | 05-31-2012 |
| 20120132747 | UNDER-FLAP STIFFENER FOR AIRCRAFT - An assembly of longitudinal structural stiffeners for an aircraft including, in a front portion of the fuselage, a windscreen that is slightly recessed relative to the airplane nose, and a fuselage portion extending in alignment with the airplane nose up to the base of the windscreen. The stiffeners include a bending-resistance main plane and are arranged under the flap and connected to the fuselage along a force transfer line. For one or more of the stiffeners, the bending resistance main plane substantially coincides, at least a certain number of points of the fuselage force transfer line, with the plane predetermined by the local normal to the fuselage surface and the longitudinal axis of the airplane. A method is also provided for calculating the shape of the stiffeners. | 05-31-2012 |
| 20120132493 | SAFETY LINK DEVICE AND AIRCRAFT EQUIPPED WITH SUCH A SAFETY LINK DEVICE - The present invention relates to a device for safety linking of a first member ( | 05-31-2012 |
| 20120128443 | DEVICE FOR MECHANICALLY LINKING AT LEAST TWO PARTS HAVING COAXIAL BORES - A device for mechanically linking with a rotating axis at least two parts, which is configured to extend in a longitudinal direction in coaxial bores formed respectively in the at least two parts hinged in relation to each other around the axis. The device includes: a cylindrical body including at least one end portion including at least one longitudinal slot, the cylindrical body including in the longitudinal direction a cylindrical bore extended by a frusto-conical bore extending in the at least one end portion configured to be located in another bore; an insert of frusto-conical shape substantially complementary to the frusto-conical bore, the insert including a tapped aperture extending in the longitudinal direction when the insert is accommodated in the frusto-conical bore, and a screw with a threaded end configured to cooperate by screwing with the tapped aperture of the insert allowing to lock the cylindrical body in the another bore and making a rotoide joint around axis. | 05-24-2012 |
| 20120126060 | METHOD OF FABRICATING AN AIRCRAFT PART BY INFUSING RESIN - The method of fabricating an aircraft part comprises the steps of placing in a stack comprising a preform at least one layer of a material that presents permeability to a predetermined resin that is less than the permeability of a portion of the preform that is the closest to the layer; and placing a resin presence sensor on a side of the layer that is remote from the preform. | 05-24-2012 |
| 20120126059 | SEALING DEVICE BETWEEN A CROSS MEMBER AND INSULATION BLANKET PROVIDED AT AN AIRCRAFT FUSELAGE - An insulation blanket to be connected at the inside surface ( | 05-24-2012 |
| 20120119761 | METHOD OF ELECTRICALLY CHARACTERIZING A COMPOSITE MATERIAL FOR MANUFACTURING AN AIRCRAFT - In the method of electrically characterizing a composite material for manufacturing an aircraft, the following steps are performed: compressing two spacers against at least one test piece made of a composite material; determining an electrical resistance value for the assembly formed by the spacers and the test piece; and deducing from said value a value for the electrical resistance of the composite material. | 05-17-2012 |
| 20120119572 | AIRCRAFT INCLUDING PIECES OF ELECTRICAL EQUIPMENT AND PARTS MADE OF COMPOSITE MATERIAL - The aircraft includes at least one piece of equipment and a composite material part to which the equipment is connected. It is arranged in such a manner that a fault current circuit of the equipment passes via the part. | 05-17-2012 |
| 20120106114 | BACKPLANE ELECTRONIC CIRCUIT BOARD OF AN ELECTRONIC APPARATUS, IN PARTICULAR FOR AN AIRCRAFT - A backplane electronic circuit board of an electronic apparatus ( | 05-03-2012 |
| 20120104184 | AIRCRAFT COMPRISING A DEVICE FOR INFLUENCING THE DIRECTIONAL STABILITY OF THE AIRCRAFT, AND A METHOD FOR INFLUENCING THE DIRECTIONAL STABILITY OF THE AIRCRAFT - An aircraft including a device for influencing the directional stability of the aircraft is provided. The device includes a control-input device; a flight control device; a sensor device for acquiring the rotation rates, including the yaw rates, of the aircraft; and at least one actuator, which is coupled with ailerons, spoilers, an elevator and a rudder. The flight control device includes a control function generating adjusting commands for the actuators for controlling the aircraft according to control commands. The aircraft includes two tail-mounted flaps, each including an actuator connected with the flight control device, situated symmetrically to each other and on opposite sides of the fuselage, and movable between retracted and extended positions. The control function is designed such that the adjusting commands that are generated on the basis of the control commands depending on the acquired rotation rates include adjusting commands to the actuators of the tail-mounted flaps. | 05-03-2012 |
| 20120104173 | DEVICE FOR SHUTTING A JETTISONING CIRCUIT OF AN AIRCRAFT - A device for shutting an aircraft jettisoning circuit includes a coupling endpiece. The endpiece carries a sealing gasket and means suitable for modifying a dimension of the gasket. | 05-03-2012 |
| 20120104170 | FUSELAGE ELEMENT COMPRISING A FUSELAGE SEGMENT AND JOINING MEANS - The invention relates to a fuselage element comprising a fuselage segment ( | 05-03-2012 |
| 20120104167 | FUSELAGE ELEMENT COMPRISING A FUSELAGE SEGMENT AND JUNCTION MEANS, FUSELAGE PORTION, FUSELAGE AND AIRCRAFT - The invention relates to a fuselage element ( | 05-03-2012 |
| 20120104160 | AERODYNE INCLUDING MOTORIZED UNDERCARRIAGES - The aerodyne, e.g. an airplane, includes: an auxiliary power unit suitable for producing electricity; a first electricity distributor connected to the unit; at least one flight propulsion engine including an electricity generator; at least one undercarriage motor, the motor enabling the aerodyne to taxi; and a second electricity distributor connected to the generator and to the undercarriage motor in order to transmit electricity from the generator to the motor independently of the first distributor. | 05-03-2012 |
| 20120102842 | AIRCRAFT LATCH COMPRISING A HOOK AND A HANDLE - An aircraft latch including an operating lever; and adjustable means for adjusting an angle of inclination of the lever in a closed position of the latch, the means being controllable on the lever. | 05-03-2012 |
| 20120102719 | ATTACHMENT INTERFACE DEVICE FOR ATTACHING MOBILE EQUIPMENT TO AN AIRCRAFT STRUCTURE - An interface device for attaching mobile equipment ( | 05-03-2012 |
| 20120101793 | METHOD, DEVICES AND COMPUTER PROGRAM FOR ASSISTING IN THE DIAGNOSTIC OF AN AIRCRAFT SYSTEM, USING FAILURE CONDITION GRAPHS - The invention in particular has as an object aid in diagnosis of a system of an aircraft, comprising a plurality of sub-systems at least one of which comprises means for monitoring and notification of at least one detected event, using graphs of feared events. After a message of notification of occurrence of the said detected event has been received ( | 04-26-2012 |
| 20120098155 | CURVED STRUCTURAL PART MADE OF COMPOSITE MATERIAL AND A PROCESS FOR MANUFACTURING SUCH A PART - A process for manufacturing a curved structural part includes fabricating a mold of the curved structural part having at least two faces that form a male mold section between a minimum radius of curvature of the curved structural part and another radius of curvature belonging to one of the two faces, preparing a stack of multidirectional fibers of one or more fiber plies oriented ±α or 90° in relation to a longitudinal direction of the curved structural part, cutting a first multidirectional strip in the stack extending longitudinally and having a width at least equal to a maximum width of the curved structural part, applying the first multidirectional strip over the mold to gradually conform the first multidirectional strip to the mold, applying the first multidirectional strip on the face having the minimum radius of curvature, and pressing and tightening the first multidirectional strip over the other faces. | 04-26-2012 |
| 20120097794 | AIRCRAFT PANEL COMPRISING AN OPENING EQUIPPED WITH A SURROUND - The subject of the invention is an aircraft panel, notably a fuselage panel of the aircraft, comprising at least one opening equipped with a surround intended to accept a closing-off device that closes off the opening, the panel comprising at least one exterior surface, the surround surrounding the opening being fixed to the panel, forming an interface for fitting the closing-off device, and comprising at least one lip extending towards the centre of the opening, the lip supporting the closing-off device, and the surround having an external face interposed between the exterior surface of the panel and the closing-off device; the panel is characterized in that the surround comprises fixing means which work by gripping the edge of the opening of the panel. | 04-26-2012 |
| 20120097793 | SURROUND FOR AN OPENING MADE IN AN AIRCRAFT PANEL, AND METHOD OF FITTING IT - The subject of the invention is a surround for an opening made in a panel of an aircraft, notably a fuselage panel of the aircraft. The panel comprises at least one exterior surface, the surround is fixed to the panel, forming an interface for fitting a closing-off device, and comprises at least one lip extending towards the centre of the opening. The lip supports the closing-off device and has at least one external face interposed between the external surface of the panel and the closing-off device. The surround is characterized in that it is made of at least two independent components joined together, a first component comprising the lip and a second component being fixed to the panel. | 04-26-2012 |
| 20120097261 | AIRCRAFT COVER INCLUDING MEANS FOR LIMITING THE SCOOP PHENOMENA OF PNEUMATIC TYPE - An aircraft nacelle includes at its outside wall a cowl moveable relative to the nacelle so as to block or unblock an opening. The cowl includes an articulation and locking/unlocking elements distant from the upstream edge of the cowl that include elements for limiting the appearance of scooping phenomena. The limiting elements include at least one lock integral with the rest of the nacelle or respectively the cowl that can occupy a locked state in which part of the lock interferes with the cowl or respectively the rest of the nacelle and prevents a deformation that includes a radial component of the cowl, and another free state in which the part no longer interferes with the cowl or respectively the rest of the nacelle and allows the opening movement of the cowl, with the switch from one state to the next being generated by a gas pressure variation. | 04-26-2012 |
| 20120097260 | AIRCRAFT COVER INCLUDING MEANS FOR LIMITING THE SCOOP PHENOMENA OF ELECTROMAGNETIC TYPE - An aircraft nacelle includes at its outside wall a cowl that can move relative to the rest of the nacelle so as to block or unblock an opening. The cowl includes an articulation relative to the rest of the nacelle and locking/unlocking elements distant from the upstream edge of the cowl that includes elements for limiting the appearance of scooping phenomena. The limiting elements include at least one electromagnetic torque, having one element integral with the rest of the nacelle and the other element integral with the cowl, with at least one of these two elements emitting a magnetic field that generates a force of attraction on the other element, and the surfaces of the two elements of the electromagnetic torque that are flattened against one another are arranged in planes having at least one component in the radial direction. | 04-26-2012 |
| 20120092193 | Method And Device For Aiding The Managing Of Air Operations With Required Navigation And Guidance Performance - The device ( | 04-19-2012 |
| 20120091285 | AIRCRAFT NACELLE INCLUDING A CONTINUE JOINT AREA BETWEEN AN OUTER WALL AND A FRONT FRAME - An aircraft nacelle includes a lip that is extended inside the nacelle by an inside wall that delimits a pipe that empties at a power plant and outside of the nacelle by an outside wall, a first frame called a front frame that connects the inside wall and the outside wall, delimiting an annular pipe with the lip, and a second frame called a rear frame that connects the inside wall and the outside wall close to the power plant, characterized in that it includes at least one junction zone—at at least one cross-section of the nacelle along a plane that contains the longitudinal axis of the nacelle—an element that constitutes at least one part of the outside wall and at least one part of the front frame and that includes an offset whose shapes are suitable for accommodating a panel that forms the lip. | 04-19-2012 |
| 20120090695 | AIRCRAFT NACELLE INCLUDING AT LEAST ONE RADIAL PARTITION BETWEEN TWO CONDUCTS - An aircraft nacelle that makes it possible to channel a stream of air in a longitudinal direction and that includes at least two panels ( | 04-19-2012 |
| 20120090694 | AIRCRAFT NACELLE INCLUDING A REAR FRAME INCLINED TO THE REAR - An aircraft nacelle includes a lip whose surface contacts with the aerodynamic streams extends inside the nacelle by an inside wall that delimits a layer that empties at a power plant and outside of the nacelle by an outside wall, a first front frame connects the inside and outside walls, delimiting an annular pipe with the lip, and a rear frame connects the inside and outside walls at a junction zone between the inside pipe and power plant pipe, for a given cross-section of the nacelle along a plane that contains the longitudinal axis of the nacelle, a point A at the intersection between the rear frame and the inside wall, and a point B at the intersection between the rear frame and the outside wall, with B being offset toward the rear of the nacelle relative to A over more than 50% of the rear frame's periphery. | 04-19-2012 |
| 20120090693 | ACOUSTIC PROCESSING PANEL, MORE PARTICULARLY ADAPTED FOR AN AIR INTAKE IN AN AIRCRAFT NACELLE - An acoustic treatment panel that is connected to an air intake of an aircraft nacelle, includes at least one acoustically resistive structure ( | 04-19-2012 |
| 20120080582 | SPIGOT-TYPE FASTENER PROVIDED WITH AT LEAST ONE MEANS FOR MEASURING THE FORCE GENERATED BY AN AIRCRAFT ENGINE - The invention relates to a spigot-type fastener ( | 04-05-2012 |
| 20120080566 | CABLE SECURING DEVICE - The subject of the invention is a cable securing device comprising a base, a housing having an interior and an exterior surface and two spaced-apart edges allowing a plurality of cables to be inserted into the said housing, and a tongue connecting the two edges so as to hold the cables in the housing. The said tongue is connected removably at one end, known as the free end, to the first edge. The tongue comprises at least one orifice capable of engaging with a pin provided on the exterior surface of the housing. The interior surface of the tongue comprises a touch-and-close structure capable of engaging with a touch-and-close structure provided on the exterior surface of the housing. | 04-05-2012 |
| 20120080555 | TAKE-UP DEVICE FOR THRUST FORCES WITH CONNECTING RODS FOR AIRCRAFT ENGINE ATTACHMENT PYLON, INTEGRATING THREE ALIGNED BALL JOINTS - The present invention relates to a take-up device for thrust forces ( | 04-05-2012 |
| 20120080554 | AIRCRAFT ENGINE ATTACHMENT PYLON COMPRISING TWO FRONT WING SYSTEM ATTACHMENTS WITH ORTHOGONAL SHEARING PINS - The present invention relates to an aircraft assembly ( | 04-05-2012 |
| 20120078596 | METHOD FOR VERIFYING THE VALIDITY OF THE SIMULATION OF A SYSTEM AND CORRESPONDING DEVICE - In order to verify, using a processor, the validity of a simulation of a system, a method includes providing first data representative, in a computer language, of at least one expected property of the simulation, providing second data representative, in the computer language, of the at least one property obtained by the simulation, and determining an item of information representative of the validity of the simulation on the basis of the first data and the second data. | 03-29-2012 |
| 20120074932 | NONDESTRUCTIVE INSPECTION OF A STRUCTURE IN AN AIRCRAFT - The invention relates to a non-destructive inspection method using eddy currents for detecting flaws in a metal structure ( | 03-29-2012 |
| 20120073262 | AIR DISCHARGING DEVICE FOR AN AIRCRAFT DOUBLE-FLOW TURBINE ENGINE - An air discharging device ( | 03-29-2012 |
| 20120069519 | FLUID-COOLED ELECTRICAL EQUIPMENT, AVIONIC RACK TO RECEIVE SUCH EQUIPMENT AND AIRCRAFT EQUIPPED WITH SUCH RACKS - This invention relates to a fluid-cooled electronic equipment item, an avionic rack to receive such an equipment item and an aircraft equipped with such racks. | 03-22-2012 |
| 20120066907 | INSTALLATION FOR MAKING A FUSELAGE PORTION OF AN AIRCRAFT - In the method of making an aircraft a mandrel is caused to pass through frames carried by a magazine; and as it passes through, the frames are transferred onto the mandrel. | 03-22-2012 |
| 20120065921 | METHOD AND DEVICE FOR TESTING INPUT/OUTPUT INTERFACES OF AVIONIC MODULES OF IMA TYPE - Input/output interfaces of avionic modules of IMA type in a device including several modules is tested. A system includes at least one application employed by a set of computer modules. This set includes the computer module (a first module), and at least one other computer modul (at least one second module). A system test is associated with the at least one system for functionally testing the set of computer modules according to the system. The system test includes at least one elementary system test for functionally testing at least one input/output interface of the first module. The execution of the at least one elementary system test is independent of the at least one second module. At least one result of execution of the at least one elementary system test is transmitted to a maintenance computer distinct from the computer modules of the plurality of computer modules. | 03-15-2012 |
| 20120061513 | AIRCRAFT INCLUDING FLOOR SUPPORT CROSS-MEMBERS WITH BEARINGS INCLUDING A FLEXIBLE MATERIAL CONNECTING THE CROSS-MEMBER TO THE SUPPORT - An aircraft including: at least one floor cross-member; at least one support carrying the cross-member; and at least one bearing including at least one flexible material and connecting the cross-member to the support. | 03-15-2012 |
| 20120060938 | AIRCRAFT NACELLE COMPRISING A REINFORCED OUTER WALL - An aircraft nacelle includes a wall that delimits an inside pipe ( | 03-15-2012 |
| 20120060755 | DEVICE FOR DEPOSITION OF FIBERS UPON A FRAME WITH CONCAVE CIRCULAR SECTIONS - A device for deposition of fibers on a support ( | 03-15-2012 |
| 20120056760 | Method And Device For Automatically Determining An Erroneous Height Value Of A Radioaltimeter Mounted On An Aircraft - Method and device for automatically determining an erroneous height value of a radio altimeter mounted on an aircraft. The device ( | 03-08-2012 |
| 20120056033 | PYLON FOR ATTACHING AN AIRCRAFT TURBINE ENGINE COMPRISING ALIGNED FRONT WING TIES - The invention relates to a pylon for attaching a turbine engine for an aircraft, having a rigid structure ( | 03-08-2012 |
| 20120055008 | METHOD FOR JOINING TOGETHER AIRCRAFT PARTS - In the method of fastening aircraft parts together, the following steps are performed:
| 03-08-2012 |
| 20120041951 | METHOD AND DEVICE FOR TRANSMITTING GEOGRAPHICAL DATA ON AN AIRCRAFT - The invention relates to a device ( | 02-16-2012 |
| 20120040159 | STRUCTURAL COMPOSITE PANEL FOR AN AIRCRAFT INCLUDING A PROTECTION AGAINST HIGH ENERGY IMPACTS - A structural panel consisting of a stratified composite material includes one face exposed to impacts and further includes a layer consisting of a hyper-elastic material bonded adhesively to its other face. According to this embodiment, debris striking the exposed face of this composite panel will have some of its energy dissipated by the local rupture of the composite skin, while the rest of the energy is absorbed by the deformation of the layer of hyper-elastic material that captures the debris and expels it again. | 02-16-2012 |
| 20120025604 | ELECTRICAL POWER SUPPLY SYSTEM FOR AN AIRCRAFT - The invention relates to an electrical power supply system for an aircraft comprising at least one main generator ( | 02-02-2012 |
| 20120024468 | METHOD FOR MANUFACTURING A STIFFENED PANEL OF COMPOSITE MATERIAL - A process for the production of a stiffened panel made of composite material, includes the stages of depositing the fibers that constitute the panel on a rigid device ( | 02-02-2012 |
| 20120024455 | METHOD FOR MANUFACTURING A STIFFENED PANEL OF COMPOSITE MATERIAL - A process for the production of a stiffened panel made of composite material includes the stages of depositing the fibers that constitute the panel on a rigid device, depositing at least one stiffener, covering the unit with a sealed wall, and then polymerizing, and providing—for each stiffener—a rigid counter-mold in contact with the convex surface of the stiffener, covering the zone(s) of the panel that is/are not covered by the stiffener with at least one band sufficiently rigid to transmit compression forces by allowing play between the band and the stiffener, and then depositing a seal such that the seal, the band, and the rigid counter-mold form the sealed wall, whereby the seal is able to have two states, a first malleable state during application so that it adapts to the profile of the lateral edges of the stiffeners, and a hardened state to ensure transmission of compression forces in a manner essentially identical to the rigid counter-molds or to the bands arranged on either side of the seal so as not to generate a pressure gradient. | 02-02-2012 |
| 20120023900 | AIRCRAFT NACELLE - The invention relates to an aircraft nacelle comprising a cowling, an engine housed in an internal volume of the cowling and at least one thrust reverser, an air passage duct ( | 02-02-2012 |
| 20120023727 | Tools For Manufacturing A Composite Panel, In Particular Of An Aircraft Fuselage - A tool equipment for manufacturing a panel in a composite material, in particular for an aircraft fuselage. | 02-02-2012 |
| 20120022725 | Method And Device For Updating A Target Altitude For An Emergency Descent Of An Aircraft - Method and device for updating a target altitude for an emergency descent of an aircraft. | 01-26-2012 |
| 20120022724 | Automatic Management Method And Device Of A Lateral Trajectory For An Emergency Descent Of An Aircraft - Automatic management method and device of a lateral trajectory for an emergency descent of an aircraft. | 01-26-2012 |
| 20120022723 | Method And Device For Determining And Updating A Target Altitude For An Emergency Descent Of An Aircraft - Method and device for determining and updating a target altitude for an emergency descent of an aircraft | 01-26-2012 |
| 20120022720 | METHOD AND DEVICE FOR PROTECTING SOFTWARE COMMANDS IN AN AIRCRAFT COCKPIT - The invention in particular has as an object the control of execution of software commands of a data-processing system in an aircraft cockpit comprising means for allowing a user to call up these commands. For these purposes, the means making it possible to call up these commands initially are locked ( | 01-26-2012 |
| 20120018580 | Insulating blanket for an aircraft and assembly integrating such a blanket - This invention proposes an insulation blanket for an aircraft, the said blanket coming in the form of a strip of insulation material of elongated shape having two more or less parallel longitudinal edges ( | 01-26-2012 |
| 20120018577 | ENGINE MOUNTING WITH AN ADAPTED LOAD/DEFORMATION CURVE - The invention relates to a mounting for attaching an engine to an aircraft structure, said mounting including a metal spring and being adapted for fulfilling the following conditions: the stiffness of the mounting for load values falling within a predetermined range ([CA, CB]) is less than the stiffness of the mounting for load values that fall below or above the predetermined range; considering a first load value (CS | 01-26-2012 |
| 20120018576 | LINKING DEVICE FOR LINKING A FIRST BODY TO A SECOND BODY, IN PARTICULAR FOR AN AIRCRAFT ENGINE ASSEMBLY | 01-26-2012 |
| 20120017514 | Aircraft opening window and aircraft equipped with at least one such window - The invention relates to an aircraft opening window comprising at least one pane ( | 01-26-2012 |
| 20120016540 | Method And Device For Aiding The Control Of Guiding Modes Transitions Of An Aircraft - The device includes means ( | 01-19-2012 |
| 20120015595 | AIRCRAFT VENTILATION SYSTEM - This ventilation system is intended for an aircraft comprising a structure bearing an exterior wall and an interior covering. | 01-19-2012 |
| 20120015213 | Fabrication Method Of Composite Components And Thus Obtained Components - During the cooking of a composite component ( | 01-19-2012 |
| 20120012218 | INTERIOR COVERING DEVICE FOR AN AIRCRAFT CABIN INCORPORATING AT LEAST ONE SYSTEM - The invention relates to a device for interior covering ( | 01-19-2012 |
