AIRBUS FRANCE Patent applications |
Patent application number | Title | Published |
20120328385 | MACHINING MEANS FOR CEILING FIXED PARTS - A machining device has a machine head capable of displacement along at least three translation axes X, Y, Z for machining an immobile part fixed above the machining head. The machining head is maintained in a constant orientation by at least three articulated connecting rods. Two connecting rods define together with the machining head and with a first Y carriage, on which they are articulated, an deformable articulated parallelogram in the XZ plane. Another connecting rod is articulated on the machining head and on a second Y carriage and the second Y carriage is capable of displacement along Y on a second X carriage capable of displacement along X. The relative movement along X of the Y carriages results in a displacement in the Z direction. Several devices can be positioned in a plurality of tunnels, these tunnels being arranged so as to share several means. | 12-27-2012 |
20120325958 | AIRCRAFT WITH REAR ANNULAR TAIL - A rear tail assembly for an aircraft, including a fuselage, a wing and at least one propulsion engine attached in the rear portion of the fuselage located behind the wing along the X longitudinal axis of the aircraft, wherein the aforementioned assembly includes aerodynamic surfaces connected in the rear portion of the fuselage. The tail assembly essentially includes horizontal aerodynamic surfaces and essentially vertical aerodynamic surface arranged so as to form an annular structure including at least one ring attached to the fuselage. At lease one engine is held in the ring formed by the tail assembly. In one embodiment, a central fin is used for defining two rings in the annular structure. In particular embodiments of an aircraft including such a tail assembly, one or two engines can be fitted in the ring area. | 12-27-2012 |
20120284006 | METHOD OF DETERMINING THE PARTICLE SENSITIVITY OF ELECTRONIC COMPONENTS - To analyze an electronic component, this component is exposed to a focused laser beam. The information provided by the laser mapping relating to the position and to the depth of the sensitivity zones of the component is used as input parameter in prediction codes for quantifying the sensitivity of the mapped component to ionizing particles in the natural radioactive environment. The prediction codes are used to determine the occurrence of malfunctions in the electronic component. Determination of the risks associated with the radiative environment imposes two aspects: one, probabilistic, takes into account the particle/matter interaction and the other, electrical, takes into account the charge collection inside the electronic component. | 11-08-2012 |
20120141066 | OPTICAL COMMUNICATION BUS NETWORK FOR AVIONIC EQUIPMENT - An avionic system for an aircraft including at least two pieces of equipment ( | 06-07-2012 |
20110226899 | Autonomous plane architecture for the transport and the replacement of propulsion engines - To be able to transport and replace in an autonomous manner one of its failing propulsion engines, a plane includes: a fuselage; propulsion engines maintained above the fuselage; maintenance wells traversing the fuselage substantially vertically with respect to the engines in which the engines can be lifted or lowered; a cargo compartment including a floor arranged in the fuselage, where the height, length and width dimensions of the cargo compartment are compatible with the transport of an engine; the cargo compartment and the wells have a common separation wall including an exit whose dimensions allow the passage of an engine; and a lower hatch or ramp for closing the lower opening of the well includes a position in which the upper surface of the ramp is substantially horizontal and substantially in the extension of the floor of the cargo compartment. According to this arrangement, a propulsion engine can be replaced by an engine which is transported in the cargo compartment in the autonomous manner for the plane. | 09-22-2011 |
20110220758 | ARCHITECTURE D'AVION A FUSELAGE LARGE - A large-capacity airplane principally includes a fuselage which has no region of constant width between the front and the rear and a wing fixed to the fuselage. As a preference, the engines are fixed at the rear under a horizontal tail held above the fuselage by vertical stabilizers and maintenance wells are formed in the fuselage in vertical alignment with each engine to allow the engines to be fitted and removed using conventional means. The width of the fuselage is determined, on the one hand, so that the airplane landing gear is fixed to the fuselage and in the up position is included within the interior volume of the fuselage and, on the other hand, so that the rear engines are above the fuselage in order to make use of the beneficial effects of this position. | 09-15-2011 |
20110198918 | DEVICE AND METHOD FOR STANDBY POWER SUPPLY ON BOARD AN AIRCRAFT - A device and a method for emergency electricity supply on board an aircraft, able to supply a part of the aircraft's electrical power circuit. The device includes a synchronous machine with separate excitation, associated with a flywheel, and an auxiliary device to set the flywheel in rotation and to maintain rotation of the flywheel. | 08-18-2011 |
20110017870 | SECTION OF AIRCRAFT FUSELAGE AND AIRCRAFT INCLUDING ONE SUCH SECTION - The invention relates to a section of fuselage for an aircraft, including frames and bays for receiving cabin windows. According the the disclosed embodiments, at least some of the frames include at least one frame segment that surrounds at least one bay, the frame segment having two branches that are disposed to the side of the bay. The ends of the branches are attached to each of the ends of the frame segment such as to form a Y. | 01-27-2011 |
20110004361 | METHOD AND DEVICE FOR ESTIMATING THE FORCES EXERTED ON A CONTROL SURFACE OF AN AIRCRAFT - The device ( | 01-06-2011 |
20100332111 | DEVICE FOR GUIDING AN AIRCRAFT ALONG A FLIGHT TRAJECTORY - The guidance device ( | 12-30-2010 |
20100319801 | SYSTEM FOR WEAVING A CONTINUOUS ANGLE - A weaving loom including a mechanism drawing-in threads, for insertion of picks, and for formation of a weaving shed, so as to render possible formation of a continuous angle or corner by a thread during weaving. The loom preferably also includes a vertical offset system, so that it is possible to weave a three-dimensional surfacic structure, the threads of which are continuous between the faces and at the level of the edges. The loom can be configured particularly for manufacture of continuous tridedral corners that are used as reinforcements for composite structures. | 12-23-2010 |
20100312835 | METHOD FOR COMMUNICATING DATA BETWEEN LOCALLY NETWORKED HETEROGENEOUS PROCESSING SYSTEMS AND COMMUNICATION SYSTEM USING SAID METHOD - A method for communicating data in an aircraft between at least a first data processing system and a second data processing system locally networked, each processing system being capable of executing at least one application, wherein the data to be exchanged are organized in messages, the aforementioned messages as well as the processing systems and the applications being defined in files stored in a backup unit connected to the network and accessible by the data processing systems. | 12-09-2010 |
20100301161 | ACOUSTIC COATING FOR AN AIRCRAFT INCORPORATING A FROST TREATMENT SYSTEM BY JOULE EFFECT - The invention relates to acoustic lining for an aircraft, which can cover a leading edge, such as an air inlet in the nacelle of a propulsion unit, said lining comprising: (i) from the inside outwards, a reflective layer ( | 12-02-2010 |
20100297390 | SELF-STABILISED STIFFENER ENABLING ELEMENT RECOVERY - A stiffener for a structure submitted to tensile and/or compression and/or shear stresses, that includes a shaped section including: a contact area with an element to be stiffened having a closed cross-section and providing stability, the aforementioned area including first and second legs; and a core normal to the element to be stiffened that provides a support surface capable of element recovery, the aforementioned core being formed by one of the two legs. Application in aircraft structures. | 11-25-2010 |
20100294882 | AIRCRAFT LEADING EDGE - An aircraft leading edge, such as, for example, an air intake ( | 11-25-2010 |
20100289671 | AIRCRAFT VIEWING SYSTEM - This invention relates to an aircraft viewing system comprising:
| 11-18-2010 |
20100288883 | Method for detecting a fuel leakage in an aircraft engine and system for carrying out said method - A method for detecting and localizing a fuel leakage in the engine of a multi-engine aircraft consisting in determining a fuel consumption for each aircraft engine, in comparing the consumption of each engine with the other aircraft engines, in determining the engine exhibiting the greater fuel consumption ratio, in determining the excess consumption ratio of the aforementioned engine with respect to the other engines, in checking whether the excessive consumption is caused by a leakage and in triggering an alarm if the step is checked. A system for detecting and localizing a fuel leakage in the engine of a multi-engine aircraft including an airborne computer for carrying out the aforementioned method is also disclosed. | 11-18-2010 |
20100288516 | FLUID EJECTION DEVICE - The disclosed embodiments relate to a pressurised fluid ejection device. More especially, the disclosed embodiments relate to such a device especially intended for fire fighting with improved reliability and efficiency, especially concerning the device placing the tank in communication with the fluid distribution circuit, including: a tank containing fluid, a fluid ejection port, ejection port closing means, a device capable of opening the said closing means including a breakable seal and means capable of retaining the seal after breakage comprising a pivot with an axis perpendicular to the ejected fluid flow. | 11-18-2010 |
20100282903 | AIRCRAFT PRESSURIZED FLOOR - The invention concerns a pressurized flooring for aircraft, provided with beams ( | 11-11-2010 |
20100270858 | DEVICE AND METHOD FOR GENERATING A BACK-UP ELECTRICITY SUPPLY ON BOARD AN AIRCRAFT - A device and a method to generate electricity on board an aircraft, including plural generators and plural air-conditioning units having an outside air intake. This device includes a control to command air-conditioning units as emergency generators and a storage device. | 10-28-2010 |
20100269948 | THREE-DIMENSIONAL SURFACE WEAVING - A weaving method that makes it possible to directly produce three-dimensional structures having two-dimensional walls with corners, without requiring sewing or other joining between two edges. The weave is created by turning weft threads ( | 10-28-2010 |
20100268373 | METHOD FOR CUTTING OUT A PANOPLY OF PARTS - A method for cutting out a panoply of parts. This cutting-out method includes producing data relating to points defining the contour of each part and to the position of each part in a Cartesian frame of reference of the panoply, grouping the parts together into at least one subset, each subset embodied by a box being considered as a single part; grouping the subsets into at least one set, each set embodied by a box being considered as a single part; establishing an order in which to cut out the parts from the subsets and sets defined respectively a cutting-out step in which the cutting-out tool moves from part to part in the cutting-out order. | 10-21-2010 |
20100264264 | METHOD FOR PRODUCING AN AIRCRAFT WITH REDUCED ENVRIONMENTAL IMPACT AND THE AIRCRAFT THUS OBTAINED - A method for producing an aircraft with reduced environmental impact and the aircraft thus obtained. | 10-21-2010 |
20100238642 | SUPPORT TO FIX ELECTRICAL CABLES ON A STRUCTURE - A support for holding a cable harness capable of being attached to a structure to hold the aforementioned harness in position and orientation with respect to the aforementioned structure. The aforementioned support comprises means of positioning and holding the harness close to means of connecting the support to the structure and rails that extend on either side of the means, substantially in the direction in which the harness must be held. Each rail is attached to the aforementioned first means at one end and free at the other end. | 09-23-2010 |
20100237189 | LANDING GEAR CASING PROVIDED WITH A BOX STRUCTURE - A reduced-volume landing gear casing for the landing gear of an aircraft including a box structure to which the landing gear is fixed and which takes up the toads acting thereon. The box structure can include, in particular, means for receiving the fixing bearings of the landing gear. | 09-23-2010 |
20100224729 | Device for installing windshield panes - A fastening device for at least one pair of window panes, especially aircraft windshield window panes, each having a window pane retainer equipped with a frame that is applied to the borders of receptacle openings for the window panes, wherein the frames have a pair of posts facing one another provided with matching profiles that can mate the aforementioned posts, one inside the other, in a fastening line of the window pane retainer on the common border to the openings that receive the pair of panes. | 09-09-2010 |
20100219289 | PURGE DEVICE AND HYDRAULIC SYSTEM COMPRISING SUCH A PURGE DEVICE - Purge device and hydraulic system comprising such a purge device. The purge device ( | 09-02-2010 |
20100200701 | FLY-BY-WIRE CONTROL SYSTEM FOR AN AIRCRAFT COMPRISING DETECTION OF PILOT INDUCED OSCILLATIONS AND A CONTROL FOR SUCH A SYSTEM - A fly-by-wire control system for an aircraft including detection of pilot induced oscillations and a mobile control unit for such a system, According to the invention, provision is made for the pivotings of the mobile control unit to be damped by a controllable damper controlled by a detector that detects oscillations corresponding to pilot induced oscillations. | 08-12-2010 |
20100200699 | SYSTEM FOR DEFROSTING THE LEADING EDGE SHEATH OF AN AIR INLET HOOD FOR A TURBOENGINE - The system for defrosting the leading edge sheath of an air intake hood for a turboengine comprises a hot pressure air supply duct ( | 08-12-2010 |
20100200691 | DEVICE FOR ATTACHING A LIFT MEMBER TO THE FUSELAGE OF AN AIRCRAFT - The disclosed embodiments relate to an aircraft equipped with at least one device for attaching a lift member to the fuselage which includes elastic articulations whose rigidity in translation and in rotation can be adjusted axially, vertically, and transversely. An airfoil may be connected to the body of the fuselage by these elastic articulations. | 08-12-2010 |
20100199629 | SYSTEME D'ANTI GIVRAGE ET DE DEGIVRAGE DE NACELLE DE MOTEUR D'AERONEF A TAPIS RESISTIF - A deicing and anti-icing system for an aircraft engine pod, including an air intake provided with a lip followed by an air intake tubular part, equipped with a first sound attenuating panel, including deicing means having at least one array of resistive heating elements embedded in an insulating material, the deicing means being in the form of a mat incorporating the resistive element in the thickness of the air intake lip. | 08-12-2010 |
20100195531 | METHOD OF ROUTING VIRTUAL LINKS IN A FRAME-SWITCHING NETWORK WITH GUARANTEED DETERMINISM - A method for routing virtual links in a frame switching network including a plurality of source terminals and/or destination of the frames, frame switches being connected together through physical connections, each virtual link being defined, for a point-to-point type, by a path through the network between a source terminal and a destination terminal and, for a multipoint type, by a plurality of paths through the network between a source terminal and a plurality of destination terminals. The method carries out routing of the links while observing a segregation constraint with regard to triplets of consecutive switches belonging to the oriented loops, so as to allow verification of determinism of the network. | 08-05-2010 |
20100193630 | SYSTEM FOR ELECTRICAL GENERATION, CONVERSION, DISTRIBUTION, AND STARTING ON BOARD AN AIRCRAFT - A system for electrical generation, conversion, distribution and starting on board an aircraft, of “bleedless” type, that is, with an electrical power architecture with no pneumatic circuits. The electrical distribution channels for high power loads specific to aircraft of “bleedless” type, and the electrical distribution channels for conventional loads, including technical loads, such as avionics, lighting, fuel pumps and commercial loads are separated, and are supplied with power by separate generators driven by the aircraft's engines. | 08-05-2010 |
20100193627 | ASSEMBLY FOR AN AIRCRAFT INCLUDING A WING ELEMENT AND A SUSPENSION PYLON - The invention relates to an assembly for an aircraft comprising a wing element ( | 08-05-2010 |
20100176250 | FAIRING FOR A PYLON VIA WHICH A TURBINE ENGINE IS SUSPENDED FROM A WING OF AN AIRCRAFT - Fairing for a pylon via which a turbine engine is suspended from a wing of an aircraft. According to the invention, the forward attachment ( | 07-15-2010 |
20100174425 | METHOD AND DEVICE TO ASSIST IN THE DRIVING OF A VEHICLE, IN PARTICULAR OF AN AIRCRAFT, FOR THE AVOIDANCE OF OBSTACLES - A method and a device to assist in the driving of a vehicle, in particular of an aircraft, for the avoidance of obstacles. | 07-08-2010 |
20100155603 | SYSTEM FOR DETECTING AND LOCATING WATER IN A SANDWICH-TYPE STUCTURE FOR AIRCRAFTS - A system for detecting and locating water in a sandwich-type structure for aircrafts, the system including means for heating the water contained in an intermediate layer of the sandwich-type structure, and means for recording at least one image of a surface of the sandwich-type structure, the image showing particular regions of the surface, corresponding to the presence of water in the intermediate layer. The means for heating the water include a device for emitting microwaves inside the sandwich-type structure, at a frequency essentially equal to the resonance frequency of the water molecules. The invention also relates to a method implemented by the system. | 06-24-2010 |
20100152925 | METHOD AND DEVICE FOR DETECTING OSCILLATORY FAILURES IN A POSITION SERVOCONTROL SUBSYSTEM OF AN AIRCRAFT CONTROL SURFACE - The detection device ( | 06-17-2010 |
20100140407 | LOCKING AND UNLOCKING SYSTEM FOR THE COCKPIT DOOR OF AN AIRCRAFT AND DOOR WITH SUCH A SYSTEM - Embodiments relate to a locking and unlocking system of a separation door separating a cockpit from a cabin of an aircraft. In one embodiment, a system comprises a set of electrically controlled bolts configured to lock the door, a control unit configured to electrically control the set of bolts, a first manual control connected to the control unit, installed in the cockpit and configured to unlock the door, a second manual control connected to the control unit, installed in the cabin and configured to unlock the door, an accelerometer to detect a crash, and a switching relay to control automatic unlocking of the door when a crash of the aircraft is detected, the relay connected to the accelerometer, the control unit and the set of bolts. | 06-10-2010 |
20100140397 | ARRANGEMENT FOR A PILOT AREA OF AN AIRCRAFT - An aircraft flight deck includes: first and second seats disposed side-by-side longitudinally in a flying direction of an aircraft, and separated by a central pedestal; control or display elements distributed ergonomically in the flight deck; and a third seat disposed longitudinally in the flying direction, located behind the first and second seats, and at a rear of the central pedestal. The central pedestal includes: a connecting device for the display elements, a control device dedicated to a third crew member and disposed at a side of the third seat; and display or control elements dedicated to tasks other than piloting, and visible and accessible from the three seats. | 06-10-2010 |
20100136309 | METHOD FOR MAKING A STRUCTURAL PART OF A COMPOSITE MATERIAL HAVING A CALIBRATED THICKNESS AND STRUCTURAL PART THUS OBTAINED - The disclosed embodiments offer a solution for controlling the thickness of a finished structural composite part when precise tolerances must be complied with for the quality of the assembly and in order to ease the assembly operations of this part. In order to implement the method according to the disclosed embodiments, an additional layer of plies made out of a non-structural composite material, called calibrating plies, is applied onto the structural plies of the structural part, at least in an area where the thickness must be maintained within close tolerances and, after the composite material has been cured, the calibrating plies are machined in order to obtain the thickness required for the finished part. The thickness of the calibrating plies applied is determined according to the possible thicknesses of structural plies, taking into account the manufacturing spreads so that the machining operation for the calibrating plies does not affect the structural plies. | 06-03-2010 |
20100133378 | ACOUSTIC PANEL HAVING A VARIABLE ACOUSTIC CHARACTERISTIC - An acoustic panel includes a reflective layer, at least one alveolar structure, and an acoustically resistive structure forming an aerodynamic surface of an aircraft on the surface of which at least one acoustic wave propagates along an axis of propagation ( | 06-03-2010 |
20100126798 | PROCESS FOR THE PRODUCTION OF AN ACOUSTICALLY RESISTIVE STRUCTURE, THE ACOUSTICALLY RESISTIVE STRUCTURE THUS OBTAINED, AND COATING USING SUCH A STRUCTURE - A process for the production of an acoustically resistive structure that can be inserted in an alveolar structure so as to obtain a coating for the acoustic treatment, whereby the acoustically resistive structure includes at least one porous layer ( | 05-27-2010 |
20100124875 | MOVABLE AIR EXHAUST DEVICE FOR AN AIRCRAFT - An air exhaust device is equipped with a grid ( | 05-20-2010 |
20100121568 | DEVICE FOR ASSISTING GROUND NAVIGATION OF AN AIRCRAFT ON AN AIRPORT - The invention concerns a device ( | 05-13-2010 |
20100116587 | ACOUSTIC PANEL - The invention relates to a panel for an acoustic treatment at the surface of an aircraft, that comprises from the outside to the inside an acoustically resistive porous layer, at least one cellular structure and a reflective or non-permissive layer, wherein the acoustically resistive porous layer includes, at the outer surface that may contact the aerodynamic flows of a sheet or foil, open areas ( | 05-13-2010 |
20100103174 | METHOD AND DEVICES FOR PROJECTING TWO-DIMENSIONAL PATTERNS ONTO COMPLEX SURFACES OF THREE-DIMENSIONAL OBJECTS - A method and device optimizing projection of a two-dimensional pattern onto a three-dimensional object surface. After defining an original curve on the two-dimensional pattern and a projection curve on the three-dimensional object surface, a point of the pattern is selected. The abscissa and ordinate of the projection of the selected point are determined according to the abscissa and ordinate of the selected point and first and second projection ratios, respectively. A projection plane, including the point of the projection curve determined by the abscissa of the projection of the selected point, is then determined. The projection of the selected point onto the three-dimensional object surface is determined according to the ordinate of the projection of the selected point, the intersection of the surface of the three-dimensional object with the plane of projection, and the projection curve. | 04-29-2010 |
20100101205 | DEVICE FOR DEFLECTION AND RETENTION OF AIRCRAFT ENGINE DEBRIS - A protective device for treating at least one piece of debris that comes from a source of an aircraft, in particular a compressor stage or a turbine stage of an aircraft power plant, and to prevent it from reaching a target of the aircraft, characterized in that it has a geometry and a position relative to the source and to the target that make it possible to deflect the debris with the most energy so as to protect the target that is placed in a predefined protected zone. | 04-29-2010 |
20100096213 | COATING FOR ACOUSTIC TREATMENT HAVING A HOT AIR ICING PROCESSING FUNCTION OF FROST TREATMENT WITH HOT AIR - A coating for acoustic treatment relative to an aircraft's surface, in particular a leading edge such as an air intake of an aircraft nacelle, includes an acoustically resistive layer, at least one alveolar structure ( | 04-22-2010 |
20100090829 | METHOD FOR MONITORING AUTHORIZED AND UNAUTHORIZED PERSONS WITHIN A SECURITY PERIMETER AROUND AN APPARATUS - The invention relates to the automatic detection of the presence of non-authorized persons in the vicinity of an apparatus of the aircraft type. To this end, the invention comprises equipping persons with radio transmitters for identifying them as authorized personnel. The aircraft are also fitted, such as at the existing PODs, with a transceiver device of a radio identification system of the RFID type for recognition of the persons wearing the radio transmitters. Only the persons who are not authorized in the vicinity of the aircraft initiate an alarm procedure. | 04-15-2010 |
20100089690 | METHOD FOR MAKING AN ACOUSTIC TREATMENT COATING AND COATING THUS OBTAINED - A process for the producing a coating for acoustic treatment relative to a leading edge such as an air intake of an aircraft nacelle, the coating including a reflective layer, an alveolar structure, and an acoustically resistive layer, includes: | 04-15-2010 |
20100089145 | DEVICE AND METHOD FOR MEASURING THE FLOW SPEED AND DIRECTION OF A GASEOUS FLUID - A device for measuring the flow speed of a fluid as well as its direction and its orientation, based on a thermal-sensor measurement principle, that comprises at least three flow measurement probes each having a sensitive member and an obstacle masking a predetermined measurement area of the sensor, characterized in that the flow measurement probes are attached on carrier posts, the carrier posts defining the obstacles that form masking members for an angular sector of the flow measurement probes facing the sensitive member of the probes. | 04-15-2010 |
20100078521 | DEVICE FOR DETECTING AND ELIMINATING THE PRESENCE OF A LAYER OF ICE OR LIQUID - The invention concerns a device for detecting and eliminating a layer of ice formed on the surface of an aircraft structure ( | 04-01-2010 |
20100077695 | PANEL ASSEMBLY AND MANUFACTURING METHOD - A panel assembly, in which the liaison between two adjacent panels is sealed by a sealing joint, where the sealing joint comprises a central part, housed in an interstice between the two panels, and an external part, facing the exterior of the panel assembly, and capable of covering at least partially the external face of the two longitudinal edges of the panels surrounding the interstice. Also, a method for mounting a panel assembly, in which two adjacent panels are fixed to one another. | 04-01-2010 |
20100077690 | PANEL ASSEMBLY AND METHOD FOR MOUNTING A PANEL ASSEMBLY - A panel assembly and therefor in which two panels are connected to one another, where one surface of each of the panels includes a joggle, so as to include an upper plateau and a lower plateau, the two panels being connected to each other at their lower plateaus. The sum of the joggle heights of the two panels is for example equal to the sum of the accepted gap tolerances in the joint zone between the two panels. | 04-01-2010 |
20100076623 | BRAKING PROCESS FOR AN AIRPLANE - An aircraft braking adaptation process is used to prevent rapid derotation of an aircraft causing damage to the front landing gear by formulating a braking command, applying the command to at least one brake, adapting the braking command by acquiring the aircraft trim and modifying the braking commands as a function of the aircraft trim. | 03-25-2010 |
20100072319 | LANDING GEAR CASING PROVIDED WITH A BOX STRUCTURE - A reduced-volume landing gear casing for the landing gear of an aircraft including a box structure to which the landing gear is fixed and which takes up the toads acting thereon. The box structure can include, in particular, means for receiving the fixing bearings of the landing gear. | 03-25-2010 |
20100070114 | METHOD AND DEVICE FOR REDUCING ON AN AIRCRAFT LATERAL EFFECTS OF A TURBULENCE - A method and device for attenuating on an aircraft lateral effects engendered by a turbulence. | 03-18-2010 |
20100067999 | FASTENER ASSEMBLY FOR TRANSPORT VEHICLE - This invention relates to a fastener assembly that has a rail ( | 03-18-2010 |
20100066386 | SYSTEM FOR DETECTING, QUANTIFYING AND/OR LOCATING WATER IN AIRCRAFT SANDWICH STRUCTURES AND METHODS FOR USING THIS SYSTEM - A system for the detection of water in a sandwich structure for aircraft including: a microwave generator, at least two microwaves emitters/sensors mounted in the structure, and a microwave detector capable of detecting the microwaves after propagation in the structure; a data-processing unit associated with a library containing at least one model of the structure when empty. Also methods for implementing this system as well as an aircraft including such a system. | 03-18-2010 |
20100065680 | DEVICE WITH PLANE JETS FOR REDUCING THE NOISE GENERATED BY A JET AIRCRAFT - The invention relates to an aircraft engine having a longitudinal axis (XX′), comprising a wall ( | 03-18-2010 |
20100059626 | FUSELAGE ARRANGEMENT FOR AIRPLANE - An aircraft fuselage with a shape elongated along a longitudinal axis X along a longitudinal axis of the aircraft that determines a direction toward the front along a direction of motion of the aircraft in flight. A front section with straight cross sections widening relative to the X axis, located at the front of the fuselage and ending in the front of the fuselage in a fuselage nose, and delimited at the rear by a cross section for joining to a rear part of the fuselage behind the front section. The front section includes a cockpit located above a floorboard between a cockpit bulkhead to the rear and a front base to the front. | 03-11-2010 |
20100059624 | AIRCRAFT COMPRISING A DEVICE FOR REDUCING THE INDUCED DRAG - An aircraft including a longitudinal fuselage, at least two lateral wings connected symmetrically one on each side of the fuselage and at least one engine pod fixed to each lateral wing via an engine support pylon. At least one profiled bearing rod is positioned on each of the engine support pylons so as to generate a propulsive resultant force under action of an oblique air flow. | 03-11-2010 |
20100052705 | DEVICE FOR DETECTING THE STATE OF A SWITCH - A device for detecting the state of a switch. The device includes a detection circuit which delivers a signal of specified value (V | 03-04-2010 |
20100052699 | METHOD FOR INSTANTANEOUSLY DETERMINING RATES OF DISTORTION OF SIGNALS ON AN AC ELECTRICAL NETWORK, AND ASSOCIATED DEVICE - A method for instantaneously determining rates of distortion on variable frequency signals, and an associated device, in which a harmonic distortion rate is calculated across the shortest possible temporal window, corresponding to the duration of a period of a given signal's fundamental. Hence, the aim being to precisely determine the signal frequency value, whose HDR is to be calculated, an iteration of certain measurements, achieved at the time of a given calculation, is embodied in order to calculate the HDR on subsequent signals. | 03-04-2010 |
20100049475 | METHOD AND AIDS FOR RELATIVE POSITIONING OF OBJECTS DURING A DESIGN PHASE - A method aiding in relative positioning of | 02-25-2010 |
20100045486 | METHOD AND DEVICE FOR AUDIBLE WARNING WHEN AN AIRCRAFT AUTOPILOT IS DEACTIVATED - The invention relates to a method for producing an audible warning when an aircraft autopilot ( | 02-25-2010 |
20100044941 | FIXED SUPPORT FOR PARTS IN MACHINE TOOLS - A fixed carrier for machine tool parts includes a table frame and a table having a first face That can hold a first part to be machined, the first face being fixed above a machining device and the first part being stationary during the machining process. The table also has a second face for holding steady a second part to be machined. | 02-25-2010 |
20100044519 | METHOD OF REDUCING THE COMPRESSIBILITY DRAG OF A WING, AND CONTAINER INPLEMENTING THE METHOD - The present invention provides a method of reducing the compressibility drag of wing, and it also provides a container implementing the method. The container ( | 02-25-2010 |
20100044513 | AIRCRAFT CABIN WINDOW ASSEMBLY METHOD - A method for assembling a cabin window to a bay in a side wall of an aircraft fuselage, the cabin window including an outer transparent element and at least one inner transparent element. A non-through hole is made in a portion of the side wall along the edge of the bay. Subsequently, the outer transparent element is positioned in the bay from the exterior of the fuselage. The element includes a first part which has a diameter greater than that of the bay and which is shaped to co-operate with the above mentioned portion such as to block the outer transparent element in the bay both laterally and longitudinally. A second part of the outer transparent element has a groover that projects into the fuselage. The outer transparent element and the at least one inner transparent element are welded to the fuselage using a strap which presses a seal against at least the fuselage and the inner wall of the groove. | 02-25-2010 |
20100044504 | REAR PROPULSION SYSTEM WITH LATERAL AIR INLETS FOR AN AIRCRAFT WITH SUCH SYSTEM - A propulsive system for an aircraft including an auxiliary jet engine is integrated within a tail cone of a fuselage. Lateral air intakes include each one a scoop movable between a closed position and an opened position are associated with aerodynamic channels to supply with air the auxiliary jet engine. The aerodynamic channels meet at a common channel including a movable flap to balance air flows coming from the air intakes when the operation is not symmetrical. | 02-25-2010 |
20100044503 | JET ENGINE NACELLE FOR AN AIRCRAFT AND AIRCRAFT COMPRISING SUCH A NACELLE - A nacelle for an aircraft high-bypass jet engine, in which a jet engine having a longitudinal axis is mounted, the nacelle including a wall concentrically and at least partially surrounding the jet engine and defining with the latter an annular duct for fluid inner flow, including at the downstream end of the nacelle wall a passage section of a flow outlet. The nacelle includes a displacement mechanism displacing on request a portion of the nacelle wall to modify the passage section of the flow outlet through which a major portion of the flow escapes, the displacement forming in the nacelle wall at least one opening through which a small portion of a leak flow, naturally escapes. The nacelle further includes a fluid device that uses a fluid for compelling the leak flow to flow along the outer face of the portion of the nacelle wall located downstream relative to the at least one opening. | 02-25-2010 |
20100044502 | BEAM MOUNTED REAR PROPULSION SYSTEM FOR AN AIRCRAFT AND AIRCRAFT WITH SUCH SYSTEM - A propulsive system for an aircraft including an auxiliary jet engine is integrated into a tail cone of a fuselage. A carrying structure of the jet engine is primarily formed with beams and frames or half-frames to which the auxiliary jet engine is fixed by lateral beams. The beams are interdependent of the frames and half-frames, and the beams are overhanging behind a frame behind which is fixed the engine. Each beam includes a lower half-beam and a higher half-beam, separated on at least a part of its length ahead from attachments of the jet engine to determine a space free of structure impediment for lateral air intakes. | 02-25-2010 |
20100042873 | METHOD AND DEVICE FOR FAULT AUTO-DETECTION IN AN ON-BOARD SYSTEM - The method includes:
| 02-18-2010 |
20100042270 | ACTIVE PITCH CONTROL METHOD AND DEVICE FOR AN AIRCRAFT - The device ( | 02-18-2010 |
20100038476 | DEVICE THAT MAKES IT POSSIBLE TO IMPROVE THE EFFECTIVENESS OF THE ACOUSTIC TREATMENTS IN A PIPE OF AN AIRCRAFT POWER PLANT - A device for improving the effectiveness of the acoustic treatment(s) in an aircraft propulsion unit that includes a pipe ( | 02-18-2010 |
20100038474 | AIRCRAFT HORIZONTAL STABILIZER - According to the invention, the horizontal stabilizer comprises a fixed intermediate part secured to the structure of said aircraft and at least one mobile edge part able to slide with respect to said fixed intermediate part, transversely to the length thereof. Mobile flaps are able to provide the aerodynamic continuity of the suction face and of the pressure face of said stabilizer when said mobile edge part is deployed. | 02-18-2010 |
20100038472 | AIRPLANE WITH REAR ENGINES - An aircraft has at least two jet-propulsion engines mounted laterally on the fuselage in a symmetrical design in the aft part of the fuselage. Each jet engine is mounted on the fuselage some distance from the vertical plane of symmetry of the aircraft, so that the jet engine, in a so-called half-buried configuration, is partly inside an envelope surface of a theoretical fuselage. The half-buried, jet engines are mounted on a main boom fitted on the vertical plane of symmetry of the aircraft, inside the fuselage in back, of a forward main frame. The tail sections are mounted on the main boom and the boom is integral with structures for transmitting forces into the forward part of the fuselage. The structure is advantageously made of fiber-reinforced composite materials. | 02-18-2010 |
20100036551 | METHOD AND DEVICE FOR ASSISTING AN AIRCRAFT FLIGHT CONTROL DURING LANDING APPROACH - The inventive flight control assisting device comprises first means ( | 02-11-2010 |
20100032523 | AIRCRAFT FUSELAGE MADE FROM LONGITUDINAL PANELS AND METHOD OF PRODUCING SUCH A FUSELAGE - The invention relates to an aircraft fuselage comprising a nose cone, a tail section and a central section, the central section comprising longitudinal panels assembled directly with one another, at least one of these longitudinal panels having a length corresponding to the distance between the nose cone and the tail section in order to connect said nose cone with said tail section. | 02-11-2010 |
20100032521 | LANDING GEAR CASING PROVIDED WITH A DISSOCIATED STRUCTURE - A reduced-volume casing for a landing gear including a chassis for fixing and taking up loads, to which the landing gear is exposed and an envelope-type structure arranged on the chassis for taking up pressurization forces. The chassis can include, in particular, a frame which is even to the output opening of the landing gear and is provided with beams used for receiving means for maintaining the fastening bearings of the gear and also including polygons which are used for receiving the fastening bearings of the gear manoeuvring strut and are fixed to the beams, wherein the beams and polygons form a lattice structure. | 02-11-2010 |
20100032519 | AIRPLANE WITH A MODIFIABLE SURFACE OF VERTICAL EMPANNAGE - An aircraft has a vertical fin fastened to the rear and above a fuselage of elongated form, essentially in a vertical plane of symmetry of the aircraft. The vertical fin has at least two stable positions, an extended position and a returned position, such that a surface of the vertical fin, subjected to an aerodynamic flow when the aircraft is in flight, is modified in position or in surface between the returned position and the extended position, so that the aerodynamic drag of the vertical fin is reduced in the returned position under given flight conditions compared to the extended position. The change from one surface to another of the vertical fin is accomplished by modifying the geometry of the vertical fin or by displacing the vertical fin relative to the fuselage so that the vertical fin, for example, is more or less inside the fuselage, or more or less immersed in the wake zone of the fuselage in which the local dynamic pressure Pd is reduced relative to the infinitely upstream dynamic pressure Pd0. | 02-11-2010 |
20100032518 | AIRCRAFT FUSELAGE - An aircraft fuselage including a front part including a cockpit, a central part, and a rear part. The central part of the fuselage includes a first zone located at the front part and that increases in width to a maximum width towards the rear of the aircraft, a second zone that decreases in width, and a third zone that has an essentially constant width and is located behind the second zone, width begin measured along the pitch axis. | 02-11-2010 |
20100031630 | AIRCRAFT NACELLE THAT INCORPORATES A DEVICE FOR REVERSING THRUST - An aircraft nacelle in which a power plant is arranged and delimits a duct for a flow which assists the thrust. The nacelle includes a device for reducing, canceling, or reversing the thrust that includes at least one flap that can an active position in which it deflects—in the direction of a radial opening—at least a portion of the flow and an at-rest position in which the flap does not interfere with the flow, whereby the wall of the nacelle delimiting the duct includes at least one moving part that can occupy a first position in which it is interposed between the flow to be deflected and the flap and another position in which it releases the flap so as to allow the flap to change position and to move from the at-rest position to the active position. Each flap includes articulation elements with a first pivoting axis and a second pivoting axis, whereby the pivoting axes are essentially parallel to the vertical median axis of the nacelle. | 02-11-2010 |
20100030538 | METHOD AND AIDS FOR MODELLING 3D OBJECTS - A method for aiding modelling 3D objects permits production of a parameterizable instantiate model of a 3D object from a generic model of the object and a specific model of a second object including at least a part of first object. Certain characteristic data are extracted from the specific model of the second 3D object according to the parameters of the generic model of the first 3D object. A parameterizable instantiate model is produced fro the generic model of the first 3D model by matching this model to the extracted data. | 02-04-2010 |
20100030406 | DEVICE FOR REST MANAGMENT FOR AIRCRAFT PILOT - A device for managing a rest period, in flight, of a pilot in a cockpit of an airplane including parameter acquisition means, for acquiring one input parameter characteristic of a desired rest period by the pilot who wishes to have a rest, calculations means intended for calculating, from the current position of the airplane given by the airplane parameters, a future position of the airplane at the end of the desired rest period along a trajectory programmed from the input parameters and airplane parameters, means for displaying information on the rest period and or on the position of the airplane. | 02-04-2010 |
20100030404 | METHOD AND DEVICE FOR AIDING THE MANAGEMENT OF SUCCESSIVE FLIGHTS OF AN AIRCRAFT - Method and device for aiding the management of successive flights of an aircraft. | 02-04-2010 |
20100028139 | TURBOJET FOR AIRCRAFT - A turbojet for an aircraft includes an engine housed in a nacelle and a thermal exchanger that can be traversed by a hot fluid designed to be cooled by thermal exchange with a cold fluid external to the thermal exchanger. The thermal exchanger is disposed in an internal volume of the nacelle, between an internal wall of the nacelle and an external wall of the engine, in such a way as to present two thermal exchange surfaces in the flow of the air stream from the turbojet. The disclosed embodiments also relate to an aircraft equipped with such a jet turbine engine. | 02-04-2010 |
20100027006 | DEVICE AND METHOD FOR MONITORING THE PARTICLE CONTAMINATION IN FLOWING HYDRAULIC FLUIDS - A device for monitoring particle contamination in flowing hydraulic fluids includes a mechanism for particle counting and particle sizing. Further, a method for monitoring particle contamination in flowing hydraulic fluids: determines fluid flow velocity; counts particles in the hydraulic fluid passing the light barrier for a fixed period of time; and obtains particle size distribution by using a range of different trigger levels. The monitoring device is insertable into an A/C hydraulic system to enable an online-monitoring of degradation of fluid quality during normal flight operations or on the ground. The device and method help lower costs for A/C maintenance and increase A/C availability since necessary service actions can be scheduled strategically. | 02-04-2010 |
20100026524 | PROCESS AND APPARATUS FOR AIDING IN THE CONCEPTION OF TEXTS FOR A PILOT OR A CONDUCTOR - The method for aiding in the design of a text to be displayed to a user is provided with: | 02-04-2010 |
20100024387 | AIRCRAFT NACELLE WHICH INCLUDES THRUST REVERSER SYSTEM AND AIRCRAFT INCORPORATING AT LEAST ONE SUCH NACELLE - Aircraft nacelle which includes a cowl with a longitudinal axis, an engine housed in the cowl, an annular channel surrounding the engine and designed to receive a secondary flow, wherein the cowl includes a fixed part and a moving part which slides along the longitudinal axis to define a radial opening between the moving and fixed parts, a thrust reverser system which includes internal flaps mounted so that they rotate and which are designed to block the annular channel, at least partially, in the deployed position, where the moving part of the cowl includes a radial housing to receive the internal flaps in the at-rest position and where a system of applying an elastic force on each flap towards deployment is provided. Thus control over the position of the internal flaps is obtained directly by sliding the moving part. | 02-04-2010 |
20100023848 | METHOD AND DEVICE FOR INPUTTING DIGITAL VALUES - The invention concerns a device ( | 01-28-2010 |
20100023258 | DISPLAYING METHOD AND DEVICE FOR AN AIRCRAFT FOLLOWING A FLIGHT PLAN - A device comprises means for computing the air-craft (A) current position means for determining at least one maximum permitted deviation (E | 01-28-2010 |
20100019939 | DISPLAY SYSTEM FOR AIRCRAFT - The display system ( | 01-28-2010 |
20100019081 | AIRPLANE WITH PITCH AND YAW COMMAND BY PROPULSION SYSTEM - Swiveling engines | 01-28-2010 |
20100017241 | METHOD, SYSTEM, AND COMPUTER PROGRAM PRODUCT FOR A MAINTENANCE OPTIMIZATION MODEL - A method of developing maintenance optimization model includes finding relevant criteria to drive the design towards operational performances at minimal cost for the end user, selecting inputs necessary to assess criteria selected, defining mathematical models to jointly drive the equipment/sub-system/system design and its support towards better supportability, and presenting the maintenance optimization model results to enable the exploration of the cause and effect relationships between design decisions and their operational and support impacts. The selected inputs may cover all the potential factors influencing the criteria values. The mathematical modeling can facilitate leveraging the intuitive “cause and effect” relationship between design and support, and affordability. The maintenance optimization model method, system, and computer program product provides a solid basis for the supportability evaluation of equipment/system/sub-system choices, particularly when integrated in a systematic way into the design process and used from the beginning of the development cycle. | 01-21-2010 |
20100017113 | Method and device for constructing a low altitude flight trajectory intended to be followed by an aircraft - Method and device for constructing a low altitude flight trajectory intended to be followed by an aircraft. | 01-21-2010 |
20100013300 | DEVICE AND METHOD FOR SUPPLYING ELECTRICAL POWER TO AT LEAST ONE INDUCTION MACHINE ON BOARD AN AIRCRAFT - A device and a method for supplying electrical power to at least one induction machine on board an aircraft. This device includes at least one CVFR type source, in which the voltage and frequency are both variable but in a constant ratio, that supplies power to at least one induction machine. | 01-21-2010 |
20100012781 | Aircraft with retracted front landing gear - An aircraft has a fuselage | 01-21-2010 |
20100012423 | ACOUSTIC TREATMENT DEVICE FOR TURBINE AND COMBUSTION NOISES - An acoustic treatment device for an internal primary ejection duct from a turbojet pod, including an upstream zone and a downstream zone relative to an airflow direction in the primary ejection duct, the upstream and downstream zones being located on each side of a separating wall with a first face on the side of the upstream side and a second face on the side of the downstream side. The separating wall is a micro-porous wall and the face of the separating wall located on the side of the downstream side is covered by a honeycomb structure to attenuate high frequency acoustic waves. Such a device may find application to treatment of combustion and turbine noises. | 01-21-2010 |
20100012311 | HEAT FLOW DEVICE - A device comprises equipment ( | 01-21-2010 |
20100011861 | DEVICE FOR NON DESTRUCTIVE TESTING OF A COMPONENT BY ANALYZING RADIATION DISSIPATION - A device for non-destructive testing of a component by analyzing radiation dissipation when the component is stressed by mechanical stresses. The device includes measuring means for determining a surface radiation field of the component. The measuring means are integrated in a flexible housing for covering a region of the surface of the component to be tested. The device enables an initial crack upon stress concentration on a surface of the component and the presence of a crack upon propagation of the crack to be detected. The disclosed embodiments are useful for non-destructive testing of aircraft components, but may be used in all industrial sectors where testing the integrity of components is important, such as the automotive, railway, marine and nuclear industries. | 01-21-2010 |
20100001132 | Device for interaction with a display system, in particular for an avionics display system - A display system in a flight deck comprises at least one screen (CDS, EFB) adapted for displaying several different applications and at least one cursor associated with the applications. | 01-07-2010 |
20100001129 | STORAGE COMPARTMENT FOR THE NOSE GEAR OF AN AIRCRAFT - A front landing gear storage compartment configured for an airplane including a set of retractable landing gears including a front gear centered on a longitudinal median plane of the fuselage. The storage compartment forms an impervious partition between a pressurized zone and the housing for the front gear in its retracted position, and includes a reinforced upper face including a more or less flat zone, more or less horizontal when the airplane is on the ground, so as to form a floor of a pressurized area of the airplane. | 01-07-2010 |
20100000227 | AIR INTAKE FOR AN AIRCRAFT TURBINE ENGINE - According to the invention, the air intake ( | 01-07-2010 |
20090326739 | METHOD AND DEVICE FOR DETECTING OSCILLATORY FAILURES RELATED TO A SERVOCONTROL SUBSYSTEM OF AN AIRCRAFT CONTROL SURFACE - Method and device for detecting oscillatory faults relating to an aircraft airfoil slaving chain. | 12-31-2009 |
20090326738 | DEVICE FOR AIDING TO TAKE A DECISION CONCERNING THE ABILITY OF AN AIRCRAFT TO START A FLIGHT - The device ( | 12-31-2009 |
20090321978 | PROCESS FOR MANUFACTURING A PANEL MADE OF A THERMOPLASTIC COMPOSITE - A method of manufacturing a panel made of a composite material using a tool having a support on which a lay-up is performed, the lay-up producing a stack of plies of fiber prepregs, followed by consolidating the stack aiming to obtain the panel using a compacting plate arranged above the stack. The method is implemented such that a first set of polyimide films partially covering each other is located in contact with the stack of plies, between the latter and the compacting plate. | 12-31-2009 |
20090321561 | NACELLE FOR AIRCRAFT COMPRISING MEANS OF REVERSING THRUST AND AIRCRAFT COMPRISING AT LEAST ONE SUCH NACELLE - Aircraft nacelle comprising a cowling and an engine, the cowling comprising a fixed portion and a mobile portion able to slide in order to define a radial opening with the mobile portion, a thrust reverser system comprising a plurality of flaps intended to be deployed in order to seal at least partially an annular channel surrounding the engine, the mobile portion of the cowling comprising an annular housing extending longitudinally in order to receive the flaps in rest position. Each flap is linked to the fixed portion by a pivot joint and is linked to the mobile portion by a sliding-pivot joint, in such a way that a sliding of the mobile portion in separating from the fixed portion provokes a rotation of each flap around the axis of rotation of the joint with the fixed portion. | 12-31-2009 |
20090320445 | METHOD AND DEVICE FOR THE DETECTION OF A THRUST DISSYMMETRY OF AN AIRCRAFT DURING A BRAKING - According to the invention, under braking of an aircraft (AC) with reverse thrust, that (those) engine(s) (Mc) of said aircraft (AC) the associated control lever ( | 12-31-2009 |
20090319122 | DETECTION OF ERRORS IN DATA RELATING TO THE ACTUATION OF A VEHICLE MEMBER - The invention relates to a method for the transmission of data relating to the actuation of a member used to operate a vehicle, in which code words are transmitted along the length of a given channel, each of said code words resulting from the channel coding of a block of information symbols that is representative of the aforementioned data. According to the invention, at least two such successive blocks of information symbols are coded using two different codes. The invention also relates to a data transmission system that is used to implement said method. | 12-24-2009 |
20090319104 | SYSTEM FOR GUIDING AND PILOTING AN AIRCRAFT IN CASE OF INABILITY OF THE PILOTS - The system ( | 12-24-2009 |
20090319099 | COMPUTER MAINTENANCE SYSTEM FOR AN AIRCRAFT WITH REMOTE TERMINAL - The present invention relates to a computer maintenance system for an aircraft comprising a server hosting maintenance software and at least one access terminal. The system comprises a KVM switch over IP linked to said server. The terminal is adapted to connect to said switch by means of a TCP/IP connection and hosts a client application. Symmetrically, the switch hosts a server application, said applications being suitable for implementing a protocol for remotely accessing a video frame buffer. Each video frame is transmitted from the server application to the client application in the form of bitmap image data, uncompressed or else compressed by a lossless compression algorithm. | 12-24-2009 |
20090314900 | METHOD AND DEVICE FOR REDUCING ON AN AIRCRAFT THE EFFECTS OF A VERTICAL TURBULENCE - The device ( | 12-24-2009 |
20090314897 | PROCEDURE AND DEVICE FOR IMPROVING THE MANEUVERABILITY OF AN AIRCRAFT DURING THE APPROACH TO LANDING AND FLARE-OUT PHASES - The process improves the maneuverability of an aircraft during the approach to landing and then flare-out phases, the aircraft being equipped with air brakes. According to the process, the air brakes are put in a first deployed position during the approach phase, and as a function of a representative parameter of a given altitude and in case of a steep angle approach, they are actuated to transition to a second more retracted position than the first position so as to achieve a flare-out allowing to essentially maintain the same angle of incidence, corresponding in case of a steep angle approach to achieve a flare-out with habitual exterior piloting references during the flare-out phase. | 12-24-2009 |
20090314896 | AIRCRAFT PILOTING METHOD AND DEVICE FOR PICKING UP A VERTICAL PROFILE OF A FLIGHT PLAN - An aircraft piloting method and device for picking up a vertical profile of a flight plan. | 12-24-2009 |
20090314076 | HYBRID METHOD FOR ESTIMATING THE GROUND EFFECT ON AN AIRCRAFT - A method for assessing the aerodynamic ground effects on an aircraft. The method includes determining the variation of at least one aerodynamic coefficient of the aircraft as a function of the height for a range of heights extending from an aerodynamically infinite height to a zero height. In the method, (i) the range of heights is subdivided into at least two consecutive sets of heights; (ii) for one of the sets of heights, the variation of said aerodynamic coefficient is determined by wind tunnel tests using a model of the aircraft; and (iii) for the other of the sets of heights, the variation of said aerodynamic coefficient is determined by digital simulation reproducing by computation the physical reality of the air flow around said aircraft. | 12-24-2009 |
20090311059 | BORING DEVICE - The invention concerns a perforating device comprising a cutting tool ( | 12-17-2009 |
20090310085 | IMAGE VIEWING SYSTEM FOR PASSENGERS OF AN AIRCRAFT AND AIRCRAFT COMPRISING SUCH A SYSTEM - The invention relates to an image viewing system for aircraft passengers, characterized in that it is embodied in the form of a module ( | 12-17-2009 |
20090309574 | DEVICE FOR COUNTING OSCILLATIONS OF AN OSCILLATING TEMPORAL SIGNAL - A device for counting oscillations of an oscillating temporal signal. The device comprises means for counting all the alternate crossings of a positive threshold value and of a negative threshold value by a monitored time signal. | 12-17-2009 |
20090308977 | AIRCRAFT DOORWAY - The invention concerns a doorway in an aircraft fuselage comprising a door frame in which a door is mounted, this frame comprising an outer framework, an inner framework and a core placed between the inner framework and the outer framework, capable of absorbing energy from an impact, the core being a stiffener made of composite material having an accordion shape. | 12-17-2009 |
20090308973 | AIRCRAFT TAIL CONE - In a rear cone of a fuselage of an airplane a pressurized space is arranged in the rear cone and extends up to an impervious strong wall, placed on a rear portion of the length covered by a fin. The pressurized space constitutes an area accessible to individuals and is able to constitute, in particular, a rest and service area for the crew. | 12-17-2009 |
20090306927 | METHOD FOR DETERMINING THE TOTAL TEMPERATURE OF AN AIRFLOW SURROUNDING AN AIRCRAFT - A method for determining the total temperature of the air stream surrounding an aircraft, including the following operations; measuring a parameter of static temperature, measuring a parameter of total temperature, determining a value of speed of the air stream, determining a total temperature computed from the parameters of measured static temperature and measured total temperature as a function of the speed of the air stream. | 12-10-2009 |
20090303083 | METHOD AND DEVICE FOR DETECTING ATTEMPTS AT INTRUDING ON A COMMUNICATION LINK BETWEEN AN AIRCRAFT AND A GROUND STATION - The invention concerns a method and device for detecting attempts at intruding on a communication link between an aircraft and a ground station, the communication being capable of being configured according to multiple security levels, comprising the following steps: a) analyzing a message received to determine a security level corresponding to said message; b) comparing said security level with a security level associated with the communication; c) if the security levels compared at step b) are different, performing an action concerning the rejection of the received message and the signalling of an attempt at intrusion. The invention also concerns a device for implementing said method. | 12-10-2009 |
20090302836 | DEVICE FOR NON-DESTRUCTIVE TESTING OF A COMPONENT BY ANALYZING DISTIBUTION OF A LEAKAGE MAGNETIC FIELD - A device for non-destructive control of a component analyzes distribution of a leakage magnetic field emitted by the component when it is subjected to an exciting magnetic field, includes means for generating an exciting magnetic field inside the component to be tested, and means for detecting and measuring the distribution of the magnetic field. The set of means is integrated in a flexible housing to form a device in the form of a flexible coating for being fixed on a region of the surface of the component to be tested. The disclosed embodiments are useful for non-destructive testing of aircraft components, but may also be used in all industrial sectors where testing the integrity of components is important, such as the automotive, railway, marine or nuclear industry. | 12-10-2009 |
20090302157 | Device for fixing a seat rail on a floor, and aircraft equipped with such a fixing device - A device for fixing a seat rail, designed to maintain passenger seats on a floor, wherein it includes a connecting bracket, secured to the floor and to the seat rail, the bracket being adapted to support the stresses perpendicular to the plane of the floor, and the stresses parallel to the plane of the floor. The bracket extends obliquely between the floor and the rail seat, a lower end of the bracket being secured to the floor and an upper end of the bracket being secured to the seat rail. | 12-10-2009 |
20090301197 | DEVICE FOR NON-DESTRUCTIVE TESTING OF A STRUCTURE BY VIBRATORY ANALYSIS - A device for non-destructive testing of a structure likely to contain a defect, including means for measuring vibratory waves emitted by the structure at different points of a surface of the structure, the measuring means being integrated in a flexible housing capable of adhering on the surface of the structure to be tested. The disclosed embodiments are applicable to all industrial sectors where testing of the integrity of structures is important, in particular in areonautics. | 12-10-2009 |
20090301101 | Heat exchanger, propulsion unit and aircraft provided therewith - A heat exchanger provided with a heat exchanger housing for circulating a cooling air flow and a hot air flow therein including a hot air input channel placed on the housing rear side for supplying the hot air flow to the heat exchanger housing and a cooling air discharge channel arranged on the rear side of said heat exchanger housing for exhausting the cooling air flow therefrom, wherein the channels are concentrically shaped. The disclosed embodiments also relate to a propulsion unit provided with the inventive heat exchanger, wherein the cooling air discharge channel arranged in the rear part of the housing crosses the strut in such a way that the cooling air flow is exhausted behind a jet engine. An aircraft provided with at least one inventive propulsion unit is also disclosed. | 12-10-2009 |
20090301057 | TURBOREACTOR FOR AIRCRAFT - The invention concerns a turbojet for aircraft including engine located in nacelle, and thermal exchanger intended to cool a fluid participating in the engine propulsive system, characterized in that said thermal exchanger is located on engine external wall, an interstitial space within which air can circulate being arranged between the engine external wall and a lower wall of said thermal exchanger. The invention also concerns an aircraft provided with at least one such turbojet. | 12-10-2009 |
20090299552 | METHOD AND SYSTEM FOR AUTOMATICALLY MANAGING A CONVOY OF AIRCRAFT DURING A TAXIING - The system ( | 12-03-2009 |
20090296430 | PRE-CHARGING DEVICE FOR A CHOPPING CONVERTER, AND AN ASSEMBLY AND AIRCRAFT COMPRISING IT - The device for precharging a voltage converter ( | 12-03-2009 |
20090295601 | METHOD AND DEVICE FOR GENERATING A TAXIING SPEED FOR AN AIRCRAFT OF A CONVOY - The device ( | 12-03-2009 |
20090294587 | AIRCRAFT FLOOR, USE OF SAID FLOOR AND AIRCRAFT SECTION FITTED WITH SAID FLOOR - An aircraft floor, and aircraft section provided with such a floor, and the utilization of such a floor in an aircraft section. The aircraft floor generally includes at least one central rail firmly mounted on a rigid structure of the aircraft, at least two lateral rails positioned on both sides of the central rail, and floor panels. Each lateral rail is connected vertically to the structure of the aircraft through a vertical connecting rod, each lateral rail being transversely free. Each floor panel is positioned between two adjacent rails, so that the transverse forces to which the lateral rails are subjected pass through the floor panels to the central rail. | 12-03-2009 |
20090294580 | THRUST FORCE TAKE-UP DEVICE FOR AN AIRCRAFT ENGINE PYLON ENGINE MOUNTING STRUCTURE, COMPRISING LATERAL LINK RODS WITH INTEGRAL SPREADER BAR STOPS - The invention relates to a device ( | 12-03-2009 |
20090294579 | PRIMARY ENGINE STRUT STRUCTURE OF AN AIRCRAFT - The disclosed embodiments relate to a primary engine strut structure of an aircraft characterized in that it includes single-piece composite panels while replacing the metallic spars and metal panels, the composite panels having a lay-up of fibers oriented along crosswise directions whereby integrating, in the width of the skin of the panles, a lattice structure that replaces longitudinal and transversal stiffeners of the spars and metal panels. | 12-03-2009 |
20090294577 | DEVICE FOR AUTONOMOUS MOVEMENT OF AN AIRCRAFT ON THE GROUND - In order to allow an aircraft to move around autonomously on the ground, a system turns at least one wheel of the aircraft. The wheel is coupled to rotational drive means ( | 12-03-2009 |
20090292483 | DEVICE AND METHOD FOR DETERMINING A RUNWAY STATE, AIRCRAFT COMPRISING SUCH A DEVICE AND PILOTING ASSISTANCE SYSTEM USING THAT RUNWAY STATE - This invention relates to a device and a method for determining an airport runway state, as well as to the use of such a datum. | 11-26-2009 |
20090292410 | PILOTING METHOD AND DEVICE AVOIDING THE PILOT INDUCED OSCILLATIONS - A piloting method and device avoiding the Pilot Induced Oscillations. | 11-26-2009 |
20090287787 | Process for transmitting data between at least one cockpit display screen and at least one remote client system - A process for transmitting data between at least one display screen in a cockpit and at least one remote client system includes at least one computer, in which the display screen displays a first request to send a message in a first communication protocol; this message is sent to the remote client system over a first link using a second communication protocol. A request to confirm a message is generated and displayed on the display screen via a communication interface designed to receive and generate messages in this first communication protocol, and to receive and generate messages that can be received by the remote client system. The request to confirm the message from the first request is validated by activating a confirmation device separate from the at least one display screen; activating this confirmation device sends a confirmation message via a router system to the remote system awaiting confirmation; this confirmation message, not generated in the first protocol, can be received by the remote client system awaiting confirmation; the router system includes at least one second link separate from the first link. | 11-19-2009 |
20090287336 | METHOD OF ANALYZING AN ASSEMBLY OF PARTS WITH RESPECT TO A PREDETERMINED DESIGN CRITERION - The invention relates to a method of analyzing an assembly of parts with respect to at least one predetermined design criterion, characterized in that it comprises the following steps performed on the basis of the design data represented by digital mock-ups each reliably representing a part in three dimensions, the assembly of mock-ups together defining the assembly of parts in three dimensions: —identifying the parts of the assembly, —determining, among the parts thus identified of the assembly, several first pairs of parts which each define two parts in mechanical contact with one another, —determining, among the first pairs of parts, several second pairs of parts which each define two parts which conform to said at least one predetermined criterion, —identifying a set of second pairs of parts, —as a function of the set thus identified, determining the result of the analysis of the assembly of parts with respect to said at least one predetermined design criterion. | 11-19-2009 |
20090284427 | Unit comprised of a glidepath aerial and a support organ - The invention concerns a unit having a glidepath aerial ( | 11-19-2009 |
20090283637 | Aircraft floor and fuselage supplied with said floor - The invention refers to an aircraft floor ( | 11-19-2009 |
20090283251 | HEAT FLOW DEVICE - A device comprises equipment ( | 11-19-2009 |
20090282889 | Advanced feed device for a superplastic press forming system - A feed device for a superplastic press-forming press has a slide that moves vertically and a base between which is held a tool having a cover and a bottom die enclosing a forming tool, which includes at least one heating shuttle to transport the bottom die, equipped with the forming tool and a cover, with the heating shuttle adapted to complete the press and constitute the base of the press during a hot-press forming operation. | 11-19-2009 |
20090277155 | NACELLE FOR AIRCRAFT JET ENGINE AND AIRCRAFT INCLUDING SUCH NACELLE - The invention relates to a nacelle, for an aircraft jet engine ( | 11-12-2009 |
20090273487 | APPARATUS FOR INTERCONNECTING A PILOT STATION TO AT LEAST ONE OTHER AIRCRAFT ZONE, COCKPIT AND AIRCRAFT EQUIPPED WITH SUCH AN APPARATUS - An interconnecting apparatus for interconnecting a pilot station of an aircraft to at least one aircraft zone includes a device for communicating between the pilot station and the aircraft zone. The aircraft zone includes a device permitting a person present in the aircraft zone to identify themselves and a display device indicating a functional status of the aircraft. The pilot station includes a display device indicating a location of each person being identified in the aircraft zone. | 11-05-2009 |
20090272851 | METHOD AND DEVICE FOR CORRECTING THE LATERAL DISSYMMETRY OF AN AIRCRAFT - Method and device for correcting the lateral dissymmetry of an aircraft. | 11-05-2009 |
20090272842 | DEVICE TO HANDLE AND LOCK A COVER OF AN AIRCRAFT NACELLE - The object of the invention is an aircraft nacelle that comprises, on the inside, an inside pipe ( | 11-05-2009 |
20090266938 | METHOD AND DEVICE FOR AN AIRCRAFT BUFFET REDUCTION - The device ( | 10-29-2009 |
20090266932 | ENGINE ASSEMBLY FOR AN AIRCRAFT COMPRISING A SUPPORT CRADLE FOR A FAN SHROUD MOUNTED ON TWO SEPARATE ELEMENTS - The present invention relates to an aircraft engine assembly comprising an engine, an engine mounting structure ( | 10-29-2009 |
20090265153 | SENSOR SIMULATION SYSTEM - The invention concerns a sensor simulation system. The simulation system ( | 10-22-2009 |
20090265089 | METHOD AND DEVICE FOR AIDING THE AIRPORT NAVIGATION - The device ( | 10-22-2009 |
20090261198 | PYLON FOR SUSPENDING A TURBOENGINE - Suspension mast for a turbine engine. | 10-22-2009 |
20090261079 | PROCESS FOR HIGH-ENERGY DENSITY BEAM WELDING - A high-energy density beam welding process for two panels includes a step that include placing a metal band on the upper face of at least one panel, in the axis of the desired welded joint before welding the panels, so that the metal band is inserted between the panels and the high-energy density beam during the welding step, and so that the thickness of this metal band integrates all of the geometric faults present on the surface of the welded joint. | 10-22-2009 |
20090259392 | METHOD AND DEVICE FOR GUIDING AN AIRCRAFT - The device ( | 10-15-2009 |
20090259351 | METHOD AND DEVICE FOR GUIDING AN AIRCRAFT - The device ( | 10-15-2009 |
20090255589 | TURBINE ENGINE FOR AIRCRAFT - According to the invention, the internal wall of the air intake ( | 10-15-2009 |
20090253361 | VENTILATING AIR INTAKE ARRANGEMENT - The invention concerns an arrangement comprising at least one air passage channel ( | 10-08-2009 |
20090251838 | SAFETY DEVICE FOR A SEMICONDUCTOR SWITCH - A safety device for a semiconductor switch controlling a secondary line provided with a fuse on the input side of the switch device that includes component to create a short circuit in the secondary line, so as to cut off the fuse, and means of activating this component following detection of an overcurrent in the secondary line. | 10-08-2009 |
20090251322 | FIRE DETECTION SYSTEM AND AIRCRAFT EQUIPPED WITH SUCH A SYSTEM - A fire detection system comprises a detection unit ( | 10-08-2009 |
20090250558 | AERODYNAMIC SURFACE ASSEMBLY FOR AIRCRAFT - Set of aerodynamic surfaces for an aircraft. | 10-08-2009 |
20090250551 | METHOD FOR IMPROVING ROLL STEERING OF AN AIRCRAFT AND AIRCRAFT USING SAME - The invention concerns a method which consists in subdividing the direction of the control surface into at least two elements ( | 10-08-2009 |
20090246531 | PROCESS FOR THE PRODUCTION OF A STIFFENER THAT IS SCOOPED OUT IN THE SHAPE OF AN OMEGA AND CORE FOR THE PRODUCTION OF A STIFFENER THAT IS SCOOPED OUT IN THE SHAPE OF AN OMEGA - A process for obtaining a core for the production of a stiffener ( | 10-01-2009 |
20090245968 | NUT ATTACHING AN AIRCRAFT WINDSHIELD AND DEVICE FOR ATTACHING AN AIRCRAFT WINDSHIELD INCORPORATING SAID NUT - A nut for the attachment of an aircraft windshield interposed between two elements kept assembled by at least one connecting element that includes a screw and the nut includes two parts, a first part called a body that has a threaded bore for the threaded stem of the screw, and a second part called a base that can be integrated with one of the windshield holding elements. The body and the base have cooperating shapes to prevent the body from rotating relative to the base along the axis of the bore of the body. The body, at one of its ends, includes a surface that can be in contact with the base, whereby the surface has at least one protuberance that projects relative to the surface in the direction of the axis of the bore that can work with a pattern that is provided at the base. | 10-01-2009 |
20090242705 | HYDRAULIC SYSTEM PROTECTED FROM EXTERNAL IMPACTS - A hydraulic system includes at least one hydraulic circuit with at least one pump, one or more consumer equipment units, at least one HP discharge line comprising at least one bypass, the bypass being located between the pump and the units, at least one return line including at least one bypass, the bypass being located between a tank and the units. The hydraulic system further includes at least one closure element on the at least one HP line between the bypass and the units, and at least one nonreturn valve on the at least one return line between the bypass and the units. The closure element is placed automatically in the closed position when a break of the HP line is detected downstream of the closure element of the HP line. | 10-01-2009 |
20090240386 | DEVICE FOR ISSUING AUTHORIZATION TO ACT ON THE OPERATING CONDITIONS OF AN AIRCRAFT ENGINE AND ENGINE CONTROL SYSTEM COMPRISING SAME - The invention concerns a device ( | 09-24-2009 |
20090230253 | METHOD AND DEVICE FOR PILOTING AN AIRCRAFT OPTIMIZING THE CONTROL OF THE AILERONS IN AN ENHANCED-LIFT CONFIGURATION - In conformance with the invention, based on the incident conditions and velocity, the steering of the ailerons is weakly negative (b | 09-17-2009 |
20090230251 | AIRPLANE ENGINE PYLON COMPRISING AT LEAST ONE PROTRUDING ELEMENT TO GENERATE A VORTEX OF THE AIRFLOW - A wing arrangement of an aircraft has a wing and at least one pylon for suspending an engine below the wing. The wing has a leading edge with a high-lift device, which is able to move between a deployed position in which the high-lift device projects forward of the leading edge, and which is interrupted in a forward intermediate region of the wing located at the leading edge, the pylon having a forward edge extending forward of the leading edge of the wing between a forward upper portion connected to the wing in the forward intermediate region and a forward lower portion connected to a nacelle of the engine. An element of narrow elongate shape protrudes longitudinally from the forward edge and, during flight at a high angle of attack of the aircraft, generates a vortex of aerodynamic flow that is propagated toward the forward intermediate region above the wing. | 09-17-2009 |
20090230246 | WINDOW PANEL AND METHOD OF MANUFACTURING SUCH A WINDOW, AIRCRAFT COMPRISING A WINDOW PANEL - This invention relates to the design of aircraft ( | 09-17-2009 |
20090222151 | METHOD AND SYSTEM FOR LIMITING AN AIRCRAFT CONTROL SURFACE STEERING ANGLE - The disclosed embodiments concern a process for limiting the control surface steering angle of an aircraft, including operations to:
| 09-03-2009 |
20090222150 | System for monitoring anemobaroclinometric parameters for aircraft - The disclosed embodiments concern a system for monitoring anemobaroclinometric parameters in an aircraft, including a primary detection circuit having at least one measurement channel. The measurement channel includes
| 09-03-2009 |
20090221218 | TOOL FOR MACHINING COMPOSITE MATERIAL PARTS - A tool for machining composite material parts and a machining machine including such a tool. The tool has a substantially cylindrical main body. The main body includes a polishing part with a diameter D | 09-03-2009 |
20090220143 | Method for measuring a shape anomaly on an aircraft structural panel and system therefor - The disclosed embodiments concern a method for measuring a shape anomaly on an aircraft structural panel, including the following operations: projecting a target pattern at the site of the anomaly on the panel; producing at least two images of the projected pattern; processing the two images by stereocorrelation to obtain measurements of the anomaly. The disclosed embodiments also concern a system for implementing the method, including: a projected device for projecting a target pattern at the site of the anomaly on the panel; at least two imaging devices for producing each an image of the target pattern; and means for processing the target pattern images. | 09-03-2009 |
20090212992 | METHOD AND DEVICE FOR DETECTING AN ENVIRONNING AIRCRAFT - The device ( | 08-27-2009 |
20090211780 | Electrical Cable Provided With External Marking And Method Of Crimping The Barrel Of A Contact Onto An Electrical Cable Provided With External Marking - An electrical cable ( | 08-27-2009 |
20090210104 | PROCESS AND DEVICE FOR DIAGNOSTIC AND MAINTENANCE OPERATIONS OF AIRCRAFT - The object of the invention is a method and a device for filtering diagnostic messages obtained from a plurality of elements of a system, each of these elements comprising diagnostic means capable of detecting a failure and of transmitting a message comprising at least one failure indication. The state of at least certain elements of the said plurality of elements is represented by a model of state. After at least one failure message has been received, this message is filtered according to the failure indication that it contains and according to the model of state. In response to the filtering step, the model of state is updated according to the failure indication or the message is rejected. The filtering step is advantageously based on a propositional logic mechanism. | 08-20-2009 |
20090200419 | AIRCRAFT ENGINE ATTACHMENT DEVICE COMPRISING TWO THRUST-REACHING LINK RODS THAT FIT TOGETHER TRANSVERSELY - A mounting structure for an aircraft engine including a rigid structure and a mechanism to mount the engine on the rigid structure. The mounting mechanism includes a thrust load device including two side thrust links each including an aft end mounted on an evener bar of the device, via a mechanical connection. Each connection is formed by a lug provided on the evener bar and passing through an orifice made in the aft end, the lug being arranged so as to extend substantially laterally relative to the mounting structure. | 08-13-2009 |
20090200418 | DEVICE FOR ATTACHING AN AIRCRAFT ENGINE - A device for attaching an aircraft engine including a rigid structure forming a structure box, and a device for absorbing thrust loads including a main fitting fixedly mounted on one of the spars forming the structure box, by a fixing mechanism. The fixing mechanism includes a fixing peg mounted on the spar and including a main portion located on the outside relatively to the box, the fitting being crossed by the portion of the peg and pressed against the spar by a bell-shaped supporting washer surrounding the main portion and stressed by a screw crossing it, the latter being screwed into a barrel nut housed in a bore made within the main portion. | 08-13-2009 |
20090199536 | PROCESS FOR REVERSING THE THRUST PRODUCED BY A PROPULSION UNIT OF AN AIRCRAFT, DEVICE FOR ITS IMPLEMENTATION, NACELLE EQUIPPED WITH SAID DEVICE - The object of the invention is a process whose purpose is to reduce, cancel or reverse the thrust generated by at least one air flow exiting from a propulsion unit of an aircraft by deflecting at least a portion of the flow that is able to assist the thrust, characterized in that it consists in injecting at the level of the propulsion unit a fluid called a thrust reversal fluid to deflect by an entrainment effect, from the inside of the nacelle toward the outside of the nacelle, at least a portion of the flow that is able to assist the thrust. | 08-13-2009 |
20090198390 | SECURE COMMAND METHOD AND DEVICE FOR REMOTE MAINTENANCE TERMINAL - The object of the invention is a secure command method and device for controlling an on-board maintenance device, such as a maintenance device installed on board an aircraft, from a remote maintenance terminal. The maintenance device is connected to the remote maintenance terminal by a communication network. After at least one datum representative of at least one command associated with at least one instruction has been received, the received datum is filtered to determine the validity of the command. If the received datum is valid, an instruction or a set of instructions associated with the command represented by this datum is identified in order to be executed. The filtering step is preferably iterative and based on the transmission protocol as well as on the encoding of the datum. | 08-06-2009 |
20090196201 | SWITCHING DEVICE ADAPTED TO SWITCH AN AIRCRAFT WIRELESS NETWORK FROM A MAINTENANCE CONFIGURATION TO A COMMERCIAL CONFIGURATION AND VICE-VERSA - The object of the invention is a switching device in an aircraft wireless network for configuring the network from a maintenance configuration to a commercial use wherein the passengers have access to the network. The aircraft comprises a maintenance server and a cabin server as well as a cabin access point connected to an internal antenna and an outside access point connected preferably to two external antennas. The network infrastructure additionally comprises a network switch, a radio switch and a maintenance access point. In a first configuration, the cabin server is connected to the cabin access point and the outside access point is connected to the two external antennas. In a second configuration, the maintenance server is connected to the cabin access point and the maintenance access point is connected to one of the two external antennas. | 08-06-2009 |
20090195413 | LANDING ASSISTANCE DEVICE AND METHOD FOR AIRCRAFT - A landing assistance device and method for an aircraft. According to the invention, based on the landing procedure rules attached to the runway ( | 08-06-2009 |
20090193371 | METHOD AND DEVICES TO ASSIST IN DETERMINING THE FEASIBILITY OF A COMPUTER SYSTEM - The invention concerns a method and devices for analyzing the feasibility of a computer system composed of subsystems, each having functions. After having determined the functional architecture of the computer system comprising at least one subsystem and at least one function, the characteristics of the functions implemented are imported from a database. The user determines the number of subsystems and the number of connectors per subsystem. He then distributes the functions to the subsystems and enters the characteristics of the connectors and the characteristics of the subsystems. The computer system is analyzed in light of the information provided by the user and the characteristics of the functions implemented in order to determine the feasibility of the computer system. | 07-30-2009 |
20090189786 | Method and device for modifying the sound volume of an audio alarm signal onboard an aircraft - A method for modifying a current sound-volume value assigned by an on-board system to an acoustic alert signal emitted on board an aircraft is provided. The method includes furnishing, on board the aircraft, the on-board system with at least one information item defining a modification of the current sound-volume value to a new sound-volume value in accordance with a predetermined rule. | 07-30-2009 |
20090187976 | METHODS AND DEVICES FOR IMPROVING THE RELIABILITY OF COMMUNICATION BETWEEN AN AIRCRAFT AND A REMOTE SYSTEM - The object of the invention is methods and devices for improving the reliability of communication between an aircraft and a remote system. According to the invention, the aircraft transmits a request for verification of security to a remote system. Upon reception of the response to this request, comprising at least one indication pertaining to the security of the remote system, the aircraft analyzes this indication and decides to establish or not to establish data communication between the aircraft and the remote system. When a verification request is received, the remote system is verified and a response to the request is transmitted to the aircraft. | 07-23-2009 |
20090177400 | METHOD AND SYSTEM FOR PILOTING AN AIRCRAFT - The invention concerns a system ( | 07-09-2009 |
20090171519 | METHOD AND DEVICE FOR AUTOMATICALLY GUIDING AN AIRCRAFT DURING A SPACING FLIGHT WITH A LANDING - The device ( | 07-02-2009 |
20090167076 | ELECTRICITY DISTRIBUTION SYSTEM AND METHOD INSIDE AN AIRCRAFT - A system and a method for distribution of electric power inside an aircraft. The system includes at least two systems distributing electric power from at least one power source to electric loads of the aircraft via electric and/or electronic protection/switching components, the components being configurable and commandable by dedicated electronics. Each electric distribution system includes command electronics in which a configuration file is downloaded allocating an installation status to each of the protection/switching components. | 07-02-2009 |
20090159743 | CASING AND FRONT LANDING GEAR ASSEMBLY FOR AN AIRCRAFT - The casing comprises a wall defining an internal housing open on the bottom in order to allow the retraction of a corresponding front landing gear into the interior of the housing. The said wall separates the said non-pressurized internal housing from a surrounding pressurized zone of the aircraft. A reinforcement structure is provided around the wall on the side of the surrounding pressurized zone. The separation wall is a shell coming to envelop the shape of the front landing gear, on the side opposite the opening of the internal housing, and the reinforcement structure comprises on the one hand longitudinal reinforcement elements extending on both sides of the shell and on the other hand transverse reinforcement elements connecting the longitudinal reinforcement elements. The shell has a first zone of considerable width accommodating the wheels of the landing gear, a second zone of lesser width accommodating the rod of the landing gear, and a third zone running from the second zone of lesser width, becoming wider and accommodating a portion of the mechanism for deployment/retraction of the landing gear. As a variant or in combination, the shell has on the one hand a front area of considerable height accommodating the wheels of the landing gear and on the other hand a rear area of lesser height accommodating the rod and a portion of the mechanism for deployment/retraction of the said landing gear and above which there extends at least one transverse reinforcement element making it possible to provide support for an equipment item of the aircraft. | 06-25-2009 |
20090159306 | Lightning protection system and an aircraft having such a system - A lightning protection system for a composite structure has an outer surface designed to be subject to an air flow. This system has an electrically conductive strip and fasteners from the strip to the structure. | 06-25-2009 |
20090159300 | DEVICE FOR INCREASING THE EFFECTIVENESS OF THE PRESSURIZING GAS IN AN EXTINGUISHER BOTTLE - A fire extinction device comprises a reservoir ( | 06-25-2009 |
20090152403 | METHOD FOR PILOTING AN AIRCRAFT IN APPROACH PHASE - According to the invention, high lift Leading-edge slats ( | 06-18-2009 |
20090150068 | METHOD AND DEVICE FOR GENERATING A TAXIING TRAJECTORY FOR AN AIRCRAFT - The device ( | 06-11-2009 |
20090150011 | METHOD AND DEVICE FOR GENERATING A SPEED PROFILE FOR AN AIRCRAFT DURING A TAXIING - A method and device for generating a speed profile for an aircraft rolling on the ground. | 06-11-2009 |
20090150010 | METHOD AND DEVICE FOR GENERATING A YAW SPEED ORDER FOR AN AIRCRAFT DURING A TAXIING - The device ( | 06-11-2009 |
20090150009 | METHOD AND DEVICE CONCERNING THE TAXIING OF AN AIRCRAFT, WHICH IS AUTOMATIC AT LEAST IN PART - Method and device for the at least partially automatic driving of an aircraft rolling on the ground. | 06-11-2009 |
20090150008 | METHOD AND DEVICE FOR GENERATING A SPEED FOR AN AIRCRAFT DURING A TAXIING - Method and device for generating a controlled speed for an aircraft rolling on the ground. | 06-11-2009 |
20090149122 | AIRCRAFT AIR CONDITIONING SYSTEM - According to the invention, in addition to a main air conditioning device ( | 06-11-2009 |
20090140104 | TURBOJET NACELLE AND METHOD FOR CONTROLLING SEPARATION IN A TURBOJET NACELLE - An aircraft turbojet nacelle comprising blowing means intended to inject a tangential airflow (F | 06-04-2009 |
20090133101 | SECURE FILE TRANSFER METHOD - An on-board telecommunication system, partitioned into a secure area and a non secure area, including at least a first telecommunication equipment unit in the secure area, a second telecommunication equipment unit in the non secure area, and a first one-way link from the first to the second equipment. The first equipment unit is configured to transmit data on the first link according to a first protocol. The system further includes a second link from the second to the first equipment unit, in accordance with a second protocol, the first two layers of which are distinct of those of the first protocol, the second equipment configured to transmit data on the second link as messages in accordance with the first protocol and encapsulated in frames in accordance with the second protocol. | 05-21-2009 |