Patent application number | Description | Published |
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 |
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 |
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 |
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 |
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 |
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 |
20130103233 | AUTOMATIC LANDING METHOD AND DEVICE FOR AN AIRCRAFT ON A STRONG SLOPE RUNWAY - The device ( | 04-25-2013 |
20130126671 | Unknown - There is provided an aircraft folding seat ( | 05-23-2013 |
20130134259 | FRONT STRUCTURE OF AN AIRCRAFT FUSELAGE COMPRISING LANDING GEAR - A front structure of an aircraft fuselage comprising landing gear pivoting about a main shaft and a stay shaft. The front structure also comprises a first reinforcing frame and a second reinforcing frame, the main shaft and the stay shaft being respectively connected to the first and second frames, and a device for the mechanical connection and transfer of forces connecting the stay shaft and the main shaft and transferring to the main shaft a portion of the forces induced by the wheels of the landing gear onto the stay shaft, the second frame and said device being perpendicular to one another. | 05-30-2013 |
20130135202 | INTERACTIVE DIALOG DEVICE BETWEEN AN OPERATOR OF AN AIRCRAFT AND A GUIDANCE SYSTEM OF SAID AIRCRAFT - Interactive dialog device between an operator of an aircraft and a guidance system of the aircraft. The dialog device includes an interaction on a screen which represents, on the one hand, a playback element indicating the value of a guidance setpoint of the guidance system of the aircraft, and on the other hand, a control element which can be grasped and moved along a curve by an operator to modify the value of the guidance setpoint. | 05-30-2013 |
20130135779 | CABLING OF AN AIRCRAFT CIRCUIT BREAKER PANEL - A distribution panel aboard an aircraft includes sites intended for the installation of functional electrical circuit breakers of which at least one of the sites is not occupied by a functional circuit breaker. The functional circuit breakers are wired up to a monitoring system via monitoring cabling so as to monitor a state of the circuit breakers. The at least one site not occupied by a functional circuit breaker is occupied by a nonfunctional circuit breaker, termed a false circuit breaker. The false circuit breaker is able to deliver a state signal and is wired up to the monitoring system by the monitoring cabling in a manner identical to that of a functional circuit breaker. | 05-30-2013 |
20130138272 | INTERACTIVE DIALOG DEVICE BETWEEN AN OPERATOR OF AN AIRCRAFT AND A GUIDANCE SYSTEM OF SAID AIRCRAFT - The dialog device includes a display screen, on which are displayed three graphic representations, which are respectively associated with the three control axes of the aircraft, each of said graphic representations comprising a plurality of portions, each of which is associated with a guidance mode of the associated control axis, so that all the possible guidance modes of the guidance system are thus represented, this representation highlighting the fact that the guidance modes are active exclusively on a given guidance axis. | 05-30-2013 |
20130142565 | DEVICE AND METHOD FOR ASSEMBLING TWO SHELL ELEMENTS MADE FROM A COMPOSITE MATERIAL - A device and method for assembling two structural elements made from a composite material is provided. The device includes two cylindrical flanged receptacles, each pierced by an aperture perpendicular to the axis of the cylinder, and a shaft that can be introduced into said apertures. The device also includes bearing means, which bear on the interior surfaces of the cylindrical receptacles and can maintain tension in the shaft when the shaft extends through the apertures in the two receptacles. The device includes means of placing the shaft under tension. | 06-06-2013 |
20130145770 | SUBSTITUTION DEVICE FOR AIRCRAFT ENGINE - A substitution device for replacing a turbojet type of aircraft engine, with a nacelle comprising protective covers, and a support mast having two engine mounts, each of said protective covers being mounted to pivot between an open position and a closed position, said substitution device comprising a body, two anchors attaching to the engine mounts of the engine support mast, and bearing portions adapted to receive support portions belonging to the protective covers. A method for installing such a substitution device in a nacelle, which makes it possible to close the engine covers and authorize the movement of the aircraft. | 06-13-2013 |
20130146393 | METHOD FOR PRODUCING AN ACOUSTIC TREATMENT PANEL - A method for producing an acoustic treatment panel, including:
| 06-13-2013 |
20130151147 | METHOD AND DEVICE FOR AUTOMATICALLY MONITORING ON AN AIRCRAFT AN IDENTIFICATION CODE OF A GROUND STATION OF A NAVIGATION SYSTEM - A monitoring device is provided. The monitoring device includes means for verifying whether an identifier received from a ground station of a radionavigation system is among the identifiers of the ground stations situated in a monitoring zone around the current horizontal position of the aircraft. | 06-13-2013 |
20130156427 | AFDX NETWORK WITH A PASSIVE OPTICAL NETWORK - The present invention concerns an AFDX network which is extended by a passive optical network or PON. The AFDX network comprises an AFDX switch to which are connected a plurality of equipments. The AFDX switch constitutes the optical line termination and said equipments constitute the optical network terminations of the PON. The PON broadcasts over the downlink, to all said equipments, every AFDX frame output by said AFDX switch. It also multiplexes over the uplink the AFDX frames transmitted by the same equipments. The invention also concerns an μAFDX network using a PON. | 06-20-2013 |
20130157017 | SECURE BEAM, IN PARTICULAR STRONG FRAME OF FUSELAGE, AND AIRCRAFT FUSELAGE PROVIDED WITH SUCH FRAMES - An arrangement for freeing the structures of fail-safe type from the damage tolerance criterion and to allow a significantly improved fatigue resistance, while producing a weight saving. This is provided by forming a composite hybrid structure in a configuration that makes it possible to combine the advantages of metal and of composite material. In a secure hybrid structure, at least two longitudinal structural spars are joined back to back by fastening means. One of the spars is metal and equipped with stability partitions, whereas another spar is made of a composite material with carbon fibers oriented in the direction of the forces to be predicted such that this spar exhibits a rigidity equivalent to that of the metal spar. | 06-20-2013 |
20130161123 | Standardised insulation device for an aircraft and processes of making and using thereof - An insulation device for an aircraft, comprising a blanket comprising a layer of insulation filling enclosed in a cover and having provision areas for the passage of aircraft components, these areas being devoid of insulation filling and being formed by a surface junction of two opposite faces of the cover inducing a recess in at least one face. The insulation device comprises an associated detachable complementary assembly to cover at least one of the provision areas, the assembly comprising a portion of insulation filling shaped to fit into the corresponding recess, and a retention arrangement for retaining this portion of filling. The retention arrangement is provided with a detachable arrangement for fixing the detachable complementary assembly on at least one face of the cover. | 06-27-2013 |
20130174918 | Bleeding System - A bleeding system includes an open conduit and, upstream, a control controlling the hydraulic fluid flow, toward the open conduit. The bleeding system includes a dismountable connection device including connection means adapted to be connected to the bleeding system; an outlet adapted to be connected to a pipe; a first central portion including the connection means, a cylindrical bearing, and a conduit extending from the connection means up to the surface of the cylindrical bearing; and an annular second portion including a bore adapted to pivot on the cylindrical bearing, at least one conduit connecting the outlet and the surface of the bore. The first portion and/or the annular portion include a groove ensuring the hydraulic fluid flows between the conduits. The central portion includes a section arranged between the connection means and the cylindrical bearing to ensure the connection of the connection device to the bleeding system. | 07-11-2013 |
20130179842 | METHOD AND SYSTEM FOR MONITORING A GRAPHICAL INTERFACE IN AN AIRCRAFT COCKPIT - The invention relates in particular to a method and a system for monitoring a graphical interface in a computer system of an aircraft cockpit. The method comprises, in addition to the display of a graphical interface of a client application based on a tree structure of graphical interaction objects composing said graphical interface, the following steps: obtaining a plurality of graphical interaction objects having a tree-structure organization; creating and adding, to said obtained tree structure, at least one new graphical interaction object defining a critical graphical display zone; modifying the tree-structure dependency of at least one critical graphical interaction object, of the obtained tree structure to make it dependent from the new graphical interaction object defining the critical zone; and performing critical monitoring only of the critical graphical objects attached to the critical zone. | 07-11-2013 |
20130181509 | Interface device between an electrical network and consumer systems - An interface device between an electrical network and energy consumer systems, including an input converter with a first winding connected on one side with a reverse blocking module and on the other with a first semiconductor chopper device, second and third windings having an end connected to output converters via first and second reverse blocking modules, and another end connected to the output converters, via a switching cell, a fourth winding having an end to be connected to the network, via a second semiconductor chopper device; and a control module for the semiconductor chopper devices. The interface device also includes a buffer capacitor having a first end connected to the output converters, and another end, to which a reference voltage is applied, isolated from the network; and a power reserve having an end to be connected to the network and another end connected to the fourth winding. | 07-18-2013 |
20130183513 | WALL MADE FROM A COMPOSITE MATERIAL REINFORCED SO AS TO LIMIT THE SPREAD OF A CRACK IN A DIRECTION - The invention relates to a wall made from a composite material comprising at least two layers of fibers ( | 07-18-2013 |
20130184899 | METHOD FOR THE AUTOMATIC MONITORING OF AIR OPERATIONS NECESSITATING GUARANTEED NAVIGATION AND GUIDANCE PERFORMANCE - A method is disclosed for automatic monitoring of a flight management assembly of an aircraft implementing air operations necessitating guaranteed navigation and guidance performance, wherein flight path data generated by first and second flight management systems respectively, are compared in order to check their consistency; first and second flight management systems transmit their flight path data to a third flight management system; the third flight management system receives a current position of the aircraft, calculates deviations between this current position and a flight path depending on the flight path data received from the first and second flight management systems, which it utilizes only if they are identical, and calculates, according to these deviations, guidance commands for slaving onto this flight path. Monitoring can compare deviations and guidance commands received from the first second and third flight management systems in order to be able to detect an inconsistency between them. | 07-18-2013 |
20130184900 | VEHICLE ENERGY CONTROL SYSTEM WITH A SINGLE INTERFACE - A system for controlling energy of a vehicle, for example an aircraft, characterized in that it comprises:
| 07-18-2013 |
20130190949 | VEHICLE ENERGY CONTROL SYSTEM - A system for controlling energy of a vehicle, for example an aircraft, comprising a control interface able to be in at least one first and one second state, the first state being an instruction state in which the interface generates at least a first instruction for speed of variation of a current energy of the vehicle and the second state being a resting state in which it gives no instruction, the interface furthermore being configured to return into the second state after having been brought into the first state. | 07-25-2013 |
20130191087 | METHOD OF CALCULATING DYNAMIC PRESSURE AT THE LEVEL OF AN AIRCRAFT SURFACE - The invention is aimed at a method simulating the aerodynamic flow around an aircraft, so as to detect the aerodynamic loads exerted on a predetermined surface of the aircraft. The method includes a phase of determining a value denoted QA of global dynamic pressure at the level of the predetermined surface of the aircraft. The method includes steps of carrying out simulations of aerodynamic flow around the predetermined surface of the aircraft for given environmental conditions, on the basis of a mesh produced around the shape of the aircraft, determining a local dynamic pressure qA around the predetermined surface of the aircraft, and then calculating the global dynamic pressure QA. | 07-25-2013 |
20130192045 | DEVICE AND METHOD FOR ASSEMBLING BRACKETS IN AN AIRCRAFT STRUCTURE - The invention relates to a positioning device for assembling parts on a structure. More specifically, the invention relates to a positioning device designed for assembling fixed brackets to an aircraft structure. A laser projector is fastened directly on the rigid aircraft structure; its position is therefore stable in relation to the latter, even if said structure undergoes slight deformations. The position of the projector is determined accurately by utilizing targets, which are also fastened to the primary structure. The invention also relates to a method for implementing this device. | 08-01-2013 |
20130192345 | DEVICE FOR CARRYING OUT TESTS ON AT LEAST ONE FLUID CIRCUIT OF AN AIRCRAFT - A device for carrying out a test on a fluid circuit of an aircraft including a test unit which includes, at the inlet, at least one means of connection to a pressurized gas supply connected to means for regulating the pressure of the gas provided by the supply as a function of the test to be carried out and, at the outlet, at least two connection means connected to the means for regulating the pressure of the gas, wherein at least two connection means have different dimensions tailored to a range of pressures or a given pressure. | 08-01-2013 |
20130192433 | Method for disassembly of two elements welded by ultrasound and element able to be welded by ultrasound to another element to the implementation of said method - A method for disassembling two ultrasonically welded elements, one of the elements comprising, at a surface opposite the other element, an energy director that concentrates the heating during ultrasonic welding and forms a material junction between the two assembled elements after the ultrasonic welding. The method includes the steps of positioning a wire between the two assembled elements, so as to be secant to the energy director, said wire having suitable mechanical characteristics allowing it to cut the junction formed by the energy director and moving the wire between the two assembled elements so as to cut said junction. | 08-01-2013 |
20130197726 | METHOD AND DEVICE FOR DISPLAYING TRIM INFORMATION ON AN AIRPLANE DURING A TAKE-OFF - A method and device for displaying trim information on an airplane during a take-off, for determining and displaying a precise trim setpoint which enables the pilot, by following the displayed information, to carry out a manual take-off which is optimized from the performance point of view. | 08-01-2013 |
20130197727 | METHOD AND DEVICE FOR AIDING THE PILOTING OF AN AIRCRAFT DURING A LANDING PHASE - Method and device for aiding the piloting of an airplane during a landing phase for ensuring, during rollout on a landing runway, that in the nominal case the airplane will stop level with a selected exit, while guaranteeing that in the case of a fault the airplane will stop before the end of the runway. | 08-01-2013 |
20130200904 | METHOD AND ARCHITECTURE FOR DETECTING INACCESSIBLE ELECTRICAL ANOMALIES BY MEANS OF REFLECTOMETRY - Detection and location of electrical faults in a network of metal structures which can receive electric cables and allow return of current by the cables. The reflectometry-based method involves injecting a probe signal into a cable coupled to the structures and analyzing the signal reflected by the anomalies. A conductive element is provided for carrying the probe signal at a constant distance from each structure. In one aspect, an insulated conductive element is arranged inside the metal structure and is built into a longitudinal groove in a surface for receiving a longitudinal plastic holder wedged into the structure. The reflected signal from the conductive element is compared to a threshold above which an anomaly is detected, and the anomaly is located by topological correlation. The invention is useful for airplane raceways having a composite skin. | 08-08-2013 |