The invention relates to a lightning protection arrangement for dissipating a current due to a lightning strike from an electronic unit (5) that is attached to an aerodynamic fairing of an aircraft. The device comprises an electrically conductive mounting plate (9A), which is arranged on an outer face of a CFRP sandwich panel (1) of the aerodynamic fairing. The device further comprises an electrically conductive rear plate (9B), which is arranged on an inner face of the CFRP sandwich panel (1) of the aerodynamic fairing and is electrically connected to the mounting plate (9A). A first group of fastening means provided for the electronic unit (5) electrically connects the electrical unit (5) to the rear plate (9B). An electric current arising in the event of a lightning strike is dissipated at low resistance from the electrical unit (5) to the fuselage of the aircraft by means of the rear plate (9B) and the mounting plate (9A).
H02G 13/00 - Installations de paratonnerresFixation de ceux-ci à leur structure de support
B65D 45/02 - Dispositifs de serrage ou autres dispositifs presseurs pour fixer ou retenir les éléments de fermeture exerçant une pression axiale serrant la fermeture contre la surface d'étanchéité
2.
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.
G01F 1/68 - Mesure du débit volumétrique ou du débit massique d'un fluide ou d'un matériau solide fluent, dans laquelle le fluide passe à travers un compteur par un écoulement continu en utilisant des effets thermiques
3.
SYSTEM FOR OPENING AND CLOSING THE LANDING GEAR DOOR OF AN AIRCRAFT
The invention relates to a system for opening and closing a door (50) to the bay (20) of the landing gear (30) of an aircraft (10) with extensive freedom in positioning. According to the invention, the means of connection (60, 70, 81, 82) between the landing gear (30) and the door (50) comprise a first system forming a cylinder actuator (60) mounted on the gear (30) and a second system forming a cylinder actuator (70) mounted on the door (50), the two actuator-forming systems (60, 70) being linked together by at least one fluidic communication means (81, 82) so that actuation of the first actuator-forming system (60) causes actuation of the second actuator-forming system (70).
The invention relates to a monitoring system (22) characterized in that it comprises – detectors (30) for detecting the state of a turbojet thrust reverser, – a monitoring computer (24), - a device (26) for controlling the reverser monitored by the computer as a function of the information from the detectors provided to the computer by way of the control device, - a device (28) for regulating the turbojet monitored by the computer as a function of the information from the detectors provided to the computer by way of the control device. The invention also relates to a monitoring method applied to this monitoring system.
EUROPEAN AERONAUTIC DEFENCE AND SPACE COMPANY EADS FRANCE (France)
AIRBUS FRANCE (France)
ASTRIUM SAS (France)
Inventeur(s)
Miller, Florent
Buard, Nadine
Weulersse, Cécile
Carriere, Thierry
Heins, Patrick
Abrégé
To analyse 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 radiative 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.
The invention relates to an acoustic panel comprising a reflecting layer, at least one cellular structure and an acoustically resistive structure forming an aerodynamic surface of an aircraft at the surface of which at least one acoustic wave is propagated along an axis of propagation (24), at least one of the characteristics of the acoustic panel influencing the impedance of said panel, which varies along the axis of propagation (24) of said at least one acoustic wave, characterized in that it comprises at least a first region A with a constant acoustic impedance juxtaposed, along the axis of propagation (24) of said at least one acoustic wave, with a region C at which at least one characteristic of the acoustic panel that influences the impedance varies progressively along the axis of propagation of said at least one acoustic wave, said characteristic having a value without sudden variations from one region to the other.
F02C 7/045 - Entrées d'air pour ensembles fonctionnels de turbines à gaz ou de propulsion par réaction comportant des dispositifs destinés à supprimer le bruit
F02K 1/82 - Parois des tubulures de jet, p. ex. chemises
G10K 11/172 - Procédés ou dispositifs de protection contre le bruit ou les autres ondes acoustiques ou pour amortir ceux-ci, en général utilisant des effets de résonance
The subject of the invention is an air outlet device fitted with a grid (10) fitted to an aerodynamic surface of an aircraft, wherein said grid comprises a plurality of openings defined by intermediate zones extending away from the aerodynamic surface of the aircraft, said device and the grid are characterized by an area known as the flow area through which air can flow, characterized in that it comprises at least one movable portion in order to increase the flow area of said device, particularly in the event of failure, and in that the grid (10) has a flow area determined according to the flow rate of air to be discharged in the most extreme normal flight conditions, in the absence of a failure.
B64D 13/00 - Aménagements ou adaptations des appareils de conditionnement d'air pour équipages d'aéronefs, passagers ou pour emplacements réservés au fret
8.
METHOD FOR ASSEMBLING A PART OF A METAL MATERIAL AND A PART OF A COMPOSITE MATERIAL USING A FASTENER
The invention relates to a method for assembling a part of a metal material (1) and a part of a composite material (2), the junction of the two parts being achieved through a fastener having a substantially constant section and received in a first hole (11) formed in the part of a metal material and a second hole (3) formed in the part of a composite material. According to the invention and before assembling said parts, the method comprises: an expansion step for generating a field of compression stresses at the periphery of said first hole (11) and locally in the material constituting the part of a metal material using an expansion tool; a single boring step for making said first hole (11) and said second hole (3) with a diameter Ofinal substantially larger than the diameter of the fastener (9) in order to leave a gap between the inner walls of said holes (3, 11) and the outer surface of the fastener (9); and an assembling step for placing the fastener (9) inside said holes (3, 11) for maintaining together the metal part and the composite part.
B23P 9/00 - Traitement ou finition mécanique des surfaces, avec ou sans calibrage, dans le but primordial de mieux résister à l'usure ou aux chocs, p. ex. traitement des aubes de turbines ou des paliers pour les rendre lisses ou rugueuxCaractéristiques, non prévues ailleurs, de telles surfaces lorsque leur traitement n'est pas précisé
C21D 7/02 - Modification des propriétés physiques du fer ou de l'acier par déformation par travail à froid
9.
DEVICE FOR ATTACHING A LIFT MEMBER TO THE FUSELAGE OF AN AIRCRAFT
The invention relates to an aircraft furnished with at least one device for attaching a lift member (9) to the fuselage (8) which comprises elastic articulations (1) whose rigidity in translation and in rotation can be programmed axially (X), vertically (Z) and transversely (Y). In particular the air foil can be connected to the body of the fuselage by means of these elastic articulations.
System for managing rights of access to avionic applications and data and method implemented by this system. The invention relates to a system for managing a user's rights of access to avionic information, which system is on board an aircraft, comprising - at least one identification device (10) able to read user identity information contained in a personal card, and - an avionics computer (1) comprising means (11) for managing access rights, able to authenticate the user and to determine, as a function of the identity of the user, rights of access to the avionics information.
G06F 21/34 - Authentification de l’utilisateur impliquant l’utilisation de dispositifs externes supplémentaires, p. ex. clés électroniques ou cartes à puce intelligentes
11.
METHOD FOR SIMULATING A SYSTEM ON BOARD AN AIRCRAFT FOR TESTING AN OPERATING SOFTWARE PROGRAM AND DEVICE FOR IMPLEMENTING SAID METHOD
The invention relates to a method for simulating a real on-board system for testing an operating software program (11). The invention comprises the following steps: preparation of a test to be carried out on the operating software program (11), by adding and/or removing control functions to/from a library (12); execution of the operating software program of the real on-board system in a simulated environment (3); simulation of a dedicated peripheral (5) by activating functions from the library (12); transmission of the test results from the dedicated peripheral (5) to the results folders stored on the host platform (2) and recording of said results.
The invention relates to a solution for controlling the thickness of a finished structural composite part (1) when precise tolerances must be respected for the quality of the assembly and in order to facilitate the assembling operations of said part. In order to implement the method of the present invention, an additional layer of plies of a non structural composite material, or calibrating plies (105), is applied on the structural plies (2) of the structural part at least in an area where the thickness must be maintained within narrow tolerances and, after curing the composite material, the calibrating plies (105) are machined in order to obtain a finished part having the desired thickness. The thickness of the applied calibrating plies is determined based on the possible thickness of the structural plies (2) while taking into account the manufacturing dispersion, so that the machining operation of the calibrating plies does not affect the structural plies.
The invention relates to a method and a device for managing communication channels for data exchange from an aircraft (105) comprising means (115) for establishing at least one connection path between the aircraft and at least one ground entity (120) with a plurality of communication channels of at least two different types. After detecting an event such as the modification of a communication channel condition or a modification of the aircraft position, a communication configuration enabling the aircraft to receive or transmit data from or to the ground entity via at least one of said communication channels is determined. The means for establishing at least one connection path are then adapted based on the communication configuration. Advantageously, the transmission of at least one datum comprises determining the priority level of said datum and determining the type of communication channel of the connection path, the datum being transmitted if the determined type of communication channel is compatible with the priority level.
The invention relates to a protective device (40) for treating at least one piece of debris (54) originating from an aircraft source (56), such as a turbine or compressor stage of an aircraft power system, and for preventing same from reaching a target of the aircraft. The invention is characterised in that the geometry and position of the device in relation to the source and the target enable the most energetic debris to be diverted in order to protect the target located in a pre-defined protected area.
F01D 21/04 - Arrêt des "machines" ou machines motrices, p. ex. dispositifs d'urgenceDispositifs de régulation, de commande ou de sécurité non prévus ailleurs sensibles à une position incorrecte du rotor par rapport au stator, p. ex. indiquant cette position
15.
METHOD FOR PRODUCING AN ACOUSTICALLY RESISTIVE STRUCTURE, RESULTING ACOUSTICALLY RESISTIVE STRUCTURE AND SKIN USING ONE SUCH STRUCTURE
The invention relates to a method for producing an acoustically resistive structure which can be mounted on a honeycomb structure such as to produce a skin for acoustical treatment, said acoustically resistive structure including at least one porous layer (34) and at least one reinforcing structure (36) which are glued together. The invention is characterised in that the method comprises the following steps in which: an amorphous adhesive is applied to the at least one reinforcing structure (36), the reinforcing structure (36) is subsequently perforated or micro-perforated, and the at least one porous layer is applied against the surface of the reinforcing structure (36) that was coated with amorphous adhesive.
G10K 11/168 - Sélection de matériaux de plusieurs couches de matériaux différents, p. ex. sandwiches
F02C 7/045 - Entrées d'air pour ensembles fonctionnels de turbines à gaz ou de propulsion par réaction comportant des dispositifs destinés à supprimer le bruit
16.
DEVICE FOR BALANCING THE POWER SUPPLIED BY POWER GENERATORS
The invention relates to a device for balancing power generators, comprising a plurality of converters each including an elementary conversion cell with a switch (2) driven by a comparator (3) that receives a ramp on one input thereof and, on another input, a voltage from a driving amplifier (5a, 5b, 5c, 5d), wherein the driving amplifiers receive on their negative input an image of the cell current and have their positive input connected to an adjustment loop including a common path CS_Bus, and wherein the CS_Bus path directly connects the positive inputs of the driving amplifiers (5a, 5b, 5c, 5d) to the outputs of transconductance amplifiers (71a, 71b, 71c, 71d) associated with the elementary conversion cells.
H02J 1/10 - Fonctionnement de sources à courant continu en parallèle
H02M 3/158 - Transformation d'une puissance d'entrée en courant continu en une puissance de sortie en courant continu sans transformation intermédiaire en courant alternatif par convertisseurs statiques utilisant des tubes à décharge avec électrode de commande ou des dispositifs à semi-conducteurs avec électrode de commande utilisant des dispositifs du type triode ou transistor exigeant l'application continue d'un signal de commande utilisant uniquement des dispositifs à semi-conducteurs avec commande automatique de la tension ou du courant de sortie, p. ex. régulateurs à commutation comprenant plusieurs dispositifs à semi-conducteurs comme dispositifs de commande finale pour une charge unique
The invention relates to an electronic card that comprises at least two superimposed conducting layers (2') with an insulation layer (3') between said two conducting layers (2'), said two conducting layers each having a utility conducting portion (7') and a conducting portion (6') at the periphery of said utility conducting portion (7') with an insulating portion (8') between said conducting portions (6', 7'), said insulating portion (8') of a first of said two layers (2') being offset relative to the insulating portion (8') of the second of said layers (2'). The aircraft includes a housing (10') in which at least one such card is provided.
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 (14) permissive to sound waves and solid area (6) not permissive to sound waves, characterised in that the sheet or foil of the acoustically resistive layer includes sets of microperforations (18), each set of microperforations defining an open area (14), the set of microperforations being separated by at least one series of spaced bands of solid areas (16).
G10K 11/172 - Procédés ou dispositifs de protection contre le bruit ou les autres ondes acoustiques ou pour amortir ceux-ci, en général utilisant des effets de résonance
F02C 7/045 - Entrées d'air pour ensembles fonctionnels de turbines à gaz ou de propulsion par réaction comportant des dispositifs destinés à supprimer le bruit
19.
REAR LOWER AERODYNAMIC FAIRING FOR THE ATTACHMENT DEVICE OF AN AIRCRAFT ENGINE
The invention relates to a rear lower aerodynamic fairing for the attachment device of an aircraft engine (30) that comprises side panels (44) assembled together by inner transverse stiffening rib (46) from each other in the longitudinal direction (X) of the fairing, and that further comprises a thermal protection floor (32) closely followed by the engine primary flow. According to the invention, the floor (32) is made of a plurality of floor segments (56) distributed in the (X) direction and non rigidly connected to each other, and the fairing further includes assembling means (76) for the floor segments (56) that offset the latter from the ribs (46) to which the assembling means (76) area attached.
The invention essentially relates to the automatic detection of the presence of non-authorised persons (602B) in the vicinity of an apparatus of the aircraft type. To this end, the invention comprises equipping persons (602B) with radio transmitters (603) for identifying them as authorised personnel. The aircraft are also fitted, advantageously at the existing pods (500), with a transceiver device (503) of a radio identification system of the RFID type for recognition of the persons wearing the radio transmitters. Only the persons who are not authorised in the vicinity of the aircraft initiate an alarm procedure (405).
The subject of the invention is an aircraft nacelle in which an engine is placed, and which delimits a conduit (16) through which a flow capable of contributing to the thrust can pass, said nacelle comprising a device for reducing, canceling out or reversing the thrust comprising at least one flap (34) capable of occupying at least one so-called active position in which it diverts, in the direction of a radial opening, at least part of the flow capable of contributing to the thrust and another so-called rest position in which said flap (34) does not interfere with the flow capable of contributing to the thrust, the wall of the nacelle delimiting the conduit through which the flow to be diverted passes comprising at least one moving part capable of occupying two positions, a first position in which it is interposed between the flow to be diverted and the flap (34) and another position in which it releases the flap (34) so as to allow said flap to change position and move from the rest position to the active position, characterized in that each flap (34) includes pivoting means (40) with a first pivot pin (42) placed at the level of a first so-called upper end of the flap (34) in the upper part of the nacelle and a second pivot pin (44) placed at the level of a second so-called lower end of the flap (34) in the lower part of the nacelle, said pivot pins (42, 44) being substantially parallel to the median vertical axis (26) of the nacelle.
F02K 1/72 - Inversion du flux de la soufflante utilisant des volets inverseurs de poussée ou des portes montées sur le carter de la soufflante la partie arrière du carter de la soufflante étant mobile pour découvrir des ouvertures d'inversion de poussée dans le carter de la soufflante
22.
COATING FOR ACOUSTIC TREATMENT HAVING A HOT AIR ICING PROCESSING FUNCTION
The invention relates to a coating for the acoustic treatment of the surface of an aircraft, especially at the level of a leading edge such as the air intake of an aircraft nacelle, said coating including an acoustically resistive layer, at least one cellular structure (30) and a reflective layer, said cellular layer (30) including a plurality of ducts giving, on the one hand, onto a first imaginary surface (34) and, on the other hand, onto a second imaginary surface (36), characterised in that the cellular structure (30) includes cut-outs or openings (38) formed at the side walls of some ducts for establishing a communication between adjacent ducts in order to create a network of communicating ducts that isolate at least one non communicating duct or group of ducts, one at least of said communicating ducts being connected to at least one hot-air inlet (40).
F02C 7/045 - Entrées d'air pour ensembles fonctionnels de turbines à gaz ou de propulsion par réaction comportant des dispositifs destinés à supprimer le bruit
The invention relates to a method for making an acoustic treatment coating particularly applied at a leading edge, such as the air intake of an aircraft nacelle, said acoustic treatment coating including a reflective layer, a cellular structure (30) and an acoustically-resistive structure. The invention comprises the following steps: digitising the shape that the cellular structure (30) will assume once it is applied on the surface to be treated; virtually positioning, in order to define their geometries, two series of strips (38, 40) in order to define a duct between two adjacent strips (38) of the first series on the one hand, and two adjacent strips (40) of the second series on the other hand; cutting each of the strips (38, 40) according to their previously defined geometries; forming in each of the strips (38, 40) cut-outs for assembling said strips (38, 40); assembling said strips (38, 40) in order to obtain a cellular structure having shapes conforming to the surface to be treated.
F02C 7/045 - Entrées d'air pour ensembles fonctionnels de turbines à gaz ou de propulsion par réaction comportant des dispositifs destinés à supprimer le bruit
B64D 33/02 - Aménagement sur les aéronefs des éléments ou des auxiliaires des ensembles fonctionnels de propulsion, non prévu ailleurs des entrées d'air de combustion
G10K 11/172 - Procédés ou dispositifs de protection contre le bruit ou les autres ondes acoustiques ou pour amortir ceux-ci, en général utilisant des effets de résonance
24.
DEVICE AND METHOD FOR MEASURING THE FLOW SPEED AND DIRECTION OF A GASEOUS FLUID
The invention relates to 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 (1, 1a,..., 1f) each having a sensitive member (2) and an obstacle (3) masking a predetermined measurement area of the sensor, characterised in that the flow measurement probes are attached on carrier posts (7), said carrier posts (7) defining said obstacles (2) that form masking members (4) for an angular sector of the flow measurement probes facing the sensitive member of said probes.
G01P 5/10 - Mesure de la vitesse des fluides, p. ex. d'un courant atmosphériqueMesure de la vitesse de corps, p. ex. navires, aéronefs, par rapport à des fluides en mesurant des variables thermiques
G01P 5/12 - Mesure de la vitesse des fluides, p. ex. d'un courant atmosphériqueMesure de la vitesse de corps, p. ex. navires, aéronefs, par rapport à des fluides en mesurant des variables thermiques en utilisant la variation de la résistance d'un conducteur chauffé
G01P 13/00 - Indication ou enregistrement de l'existence ou de l'absence d'un mouvementIndication ou enregistrement de la direction d'un mouvement
G01P 13/04 - Indication du sens positif ou négatif d'un mouvement linéaire ou du sens horaire ou anti-horaire d'un mouvement de rotation
25.
NACELLE FOR AIRCRAFT JET ENGINE AND AIRCRAFT INCLUDING SUCH NACELLE
The invention relates to a nacelle, for an aircraft jet engine (10) having a high bypass ratio, in which a jet engine having a longitudinal axis (X) is mounted, the nacelle (12) including a wall (24) concentrically and at least partially surrounding the jet engine and defining with the latter an annular duct (26) for a fluid internal flow having, at the downstream end of the nacelle wall, a flow outlet passage section, characterised in that the nacelle includes displacement means (40) for controllably displacing a portion (24b) of the nacelle wall in order to modify the section of the flow outlet passage, wherein said displacement generates in the nacelle wall at least one longitudinally extending opening (28), the nacelle including a device (30) for forming a fluid barrier (fi) extending along a portion at least of the longitudinal extent of said at least one opening (28) in order to counteract the natural exhaust through said at least one opening of a portion of the so-called trailing flow.
F02K 1/28 - Ensembles fonctionnels caractérisés par la forme ou la disposition de la tubulure de jet ou de la tuyèreTubulures de jet ou tuyères particulières à cet effet utilisant des jets de fluide pour influencer l'écoulement du jet
F02K 1/72 - Inversion du flux de la soufflante utilisant des volets inverseurs de poussée ou des portes montées sur le carter de la soufflante la partie arrière du carter de la soufflante étant mobile pour découvrir des ouvertures d'inversion de poussée dans le carter de la soufflante
B64D 33/04 - Aménagement sur les aéronefs des éléments ou des auxiliaires des ensembles fonctionnels de propulsion, non prévu ailleurs des sorties d'échappement ou des tuyères
26.
SECTION OF AIRCRAFT FUSELAGE AND AIRCRAFT INCLUDING ONE SUCH SECTION
The invention relates to a section of fuselage for an aircraft, comprising frames and bays for receiving cabin windows (11). According to the invention, at least some of the frames include at least one frame segment that surrounds at least one bay, said frame segment comprising two branches (15, 16) that are disposed to the side of the bay. The ends of the branches are attached to each of the ends (17, 18) of the frame segment such as to form a Y.
The invention relates to a method for assembling a cabin window to a bay in a side wall (12) of an aircraft fuselage, said cabin window comprising an outer transparent element (10) and at least one inner transparent element (11). According to the invention, a non-through hole is made in a portion of the side wall (12) along the edge of the bay. Subsequently, the outer transparent element (10) is positioned in the bay from the exterior of the fuselage, said element including a first part (13) 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 (10) in the bay both laterally and longitudinally. The outer transparent element (10) also includes a second part (16) having a groove (17) that projects into the fuselage. The outer transparent element (10) and the at least one inner transparent element (11) are welded to the fuselage using a strap (22) which presses a seal (21) against at least the fuselage and the inner wall of the groove (17).
A device for acoustically treating the internal structure of a turbojet nacelle primary jet pipe, the structure comprising an upstream region (Z1) and a downstream region (Z2) with respect to the direction in which air flows through the primary jet pipe, the upstream and downstream regions being positioned one on each side of a dividing wall (3) a first face of which faces the upstream direction and a second face of which faces the downstream direction, characterized in that the dividing wall (3) is a microporous wall and in that the downstream face of the dividing wall (3) is covered with a honeycomb structure (6) to attenuate high-frequency sound waves. Application to the treatment of combustion and turbine noise.
F02K 1/82 - Parois des tubulures de jet, p. ex. chemises
F02K 1/00 - Ensembles fonctionnels caractérisés par la forme ou la disposition de la tubulure de jet ou de la tuyèreTubulures de jet ou tuyères particulières à cet effet
The invention relates to an aircraft fuselage comprising a front part (2) with a cockpit, a central part (4) and a rear part (6). The central part of the fuselage includes a first zone (10) which is located at the front part and which increases in width to a maximum width towards the rear of the aircraft, a second zone (12) that decreases in width, and a third zone (14) which has an essentially constant width and which is located behind the second zone (12), width being measured along the pitch axis.
The invention relates to a rear tail assembly (1) for an aircraft, including a fuselage (3), a wing (2) and at least one propulsion engine (5, 5a, 5b) attached in the rear portion of the fuselage located behind the wing (2) along the X longitudinal axis of the aircraft, wherein said assembly comprises aerodynamic surfaces connected in the rear portion of the fuselage. The tail assembly essentially comprises essentially horizontal aerodynamic surfaces (41a, 41b, 43) and essentially vertical aerodynamic surfaces (42a, 42b) arranged so as to form an annular structure including at least one ring attached to the fuselage. At least 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.
A device for monitoring particle contamination in flowing hydraulic fluids comprises means for particle counting and particle sizing. Further a method for monitoring particle contamination in flowing hydraulic fluids comprises the steps of determining (A, B) fluid flow velocity; counting of particles in the hydraulic fluid passing the light barrier (4) for a fixed period of time; obtaining particle size distribution by using a range of different trigger levels. The monitoring device is insertable into the A/C hydraulic system to enable an online-monitoring of the degradation of the fluid quality during normal flight operations or on the ground using the method according to the present invention. Further the inventive solution helps lowering the costs for A/C maintenance and increase the A/C availability since necessary service actions can be scheduled strategically.
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 (28), at least one cellular structure (30) and an acoustically resistive structure (32) having a pre-determined proportion of open surface; and (ii) at least one frost treatment system in the form of at least one heating layer (46) comprising open zones through which acoustic waves can pass, which co-operate at least partially with the open zones in the acoustically resistive structure. The invention is characterised in that the acoustically resistive structure (32) includes at least one structural layer (36) with openings (38) and in that said at least one heating layer (46) is disposed under the structural layer (36).
B64D 33/02 - Aménagement sur les aéronefs des éléments ou des auxiliaires des ensembles fonctionnels de propulsion, non prévu ailleurs des entrées d'air de combustion
B64D 15/12 - Dégivrage ou antigivre des surfaces externes des aéronefs par chauffage électrique
B64D 15/16 - Dégivrage ou antigivre des surfaces externes des aéronefs par dispositifs mécaniques, p. ex. des gaines ou des bourrelets fixés ou incorporés à la surface et soumis à des pulsations
F02C 7/045 - Entrées d'air pour ensembles fonctionnels de turbines à gaz ou de propulsion par réaction comportant des dispositifs destinés à supprimer le bruit
G10K 11/172 - Procédés ou dispositifs de protection contre le bruit ou les autres ondes acoustiques ou pour amortir ceux-ci, en général utilisant des effets de résonance
B64C 1/40 - Insonorisation ou isolation calorifique
The subject of the invention is an aircraft leading edge such as, for example, an air intake (22) of a nacelle (14) of a propulsion unit, comprising a covering (26) for acoustic treatment comprising, from the outside inwards, an acoustically resistive porous layer having a given proportion of open surface, at least one cellular structure and a reflective layer, said covering (26) incorporating a frost treatment system, characterized in that a frost treatment system comprises at least one vibration emitter (36).
B64D 15/16 - Dégivrage ou antigivre des surfaces externes des aéronefs par dispositifs mécaniques, p. ex. des gaines ou des bourrelets fixés ou incorporés à la surface et soumis à des pulsations
B64D 33/02 - Aménagement sur les aéronefs des éléments ou des auxiliaires des ensembles fonctionnels de propulsion, non prévu ailleurs des entrées d'air de combustion
F02C 7/045 - Entrées d'air pour ensembles fonctionnels de turbines à gaz ou de propulsion par réaction comportant des dispositifs destinés à supprimer le bruit
G10K 11/172 - Procédés ou dispositifs de protection contre le bruit ou les autres ondes acoustiques ou pour amortir ceux-ci, en général utilisant des effets de résonance
A method and aids for modelling 3D objects permit the production of a parameterisable instantiate model (220) of a 3D object from a generic model (210) of said object and a specific model (200) of a second object comprisign at least a part of said first object are disclosed. According to the invention, 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 parameterisable instantiate model is produced fro the generic model of the first 3D model by matching this model to the extracted data.
A method and aids for the relative positioning of 3D objects, in a complex environment involving several involving several techniques, according to a set of geometrical and/or mathematical constraints are disclosed. According to the invention, a parametric model is selected for each of the objects (1000), parametric models comprising models of the constraints are also selected (1025). A representation of one of the objects is displayed (1010), permitting positioning of the other (1015) and the display of a representation of the latter (1020). A piece of data relating to the position of one of the objects is accessed for each parametric model comprising a constraint modelling and a piece of data relating to the position of one of the objects is accessed to permit an evaluation of the corresponding constraint (1035). When an object is added or displaced the relative positions of the objects and the constraints are reevaluated (1065).
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 (24) into warp threads to create at least one face. The method is particularly suitable for weaving reinforcing pieces for composite structures such as three-dimensional corner reinforcements.
A weaving loom (20) comprises means suitable for heddling the threads (26B), pick insertion (64), and shed formation, so as to make it possible to form a continuous angle (30) by a thread (34) during weaving. The loom preferably also comprises a vertical offsetting system (66) so that it is possible to weave a three-dimensional surface structure in which the threads are continuous between the faces and along the edges. This loom is particularly suitable for producing continuous trihedral angles for use as reinforcements in composite structures.
The invention relates to a system for generating, converting, distributing and electrically starting on board an aircraft of the 旜bleedless” type, that is to say with an electrical power architecture and no pneumatic network, characterized in that the electrical distribution channels for high power loads specific to aircraft of the 旜bleedless” type and the electrical distribution channels for conventional loads including technical loads, such as the avionics, the lighting and the fuel pumps and payloads are separate and are powered by separate generators (SG-B, SG-Y; SG-G1, SG-G2) driven by the jet engines (Eng1, Eng2) of the aircraft.
H02J 3/02 - Circuits pour réseaux principaux ou de distribution, à courant alternatif utilisant un réseau unique pour distribution simultanée de puissance à différentes fréquencesCircuits pour réseaux principaux ou de distribution, à courant alternatif utilisant un réseau unique pour distribution simultanée de puissance à courant alternatif et à courant continu
H02J 4/00 - Circuits pour réseaux principaux ou de distribution, la nature alternative ou continue du courant n'étant pas précisée
B64D 41/00 - Installations génératrices de puissance pour servitudes auxiliaires
39.
METHOD AND DEVICE FOR ELECTRICALLY POWERING AT LEAST ONE INDUCTION MACHINE ON BOARD AN AIRCRAFT
The present invention relates to a method and a device for electrically powering at least one induction machine (M1, M2, M3) on board an aircraft. This device comprises at least one CVFR-type source (40) in which the voltage and the frequency are both variable but in a constant ratio, that powers this at least one induction machine (M1, M2, M3).
H02P 27/04 - Dispositions ou procédés pour la commande de moteurs à courant alternatif caractérisés par le type de tension d'alimentation utilisant une tension d’alimentation à fréquence variable, p. ex. tension d’alimentation d’onduleurs ou de convertisseurs
40.
METHOD AND DEVICES FOR PROJECTING TWO-DIMENSIONAL PATTERNS ONTO COMPLEX SURFACES OF THREE-DIMENSIONAL OBJECTS
The method and the devices according to the invention are aimed at optimizing the projection of a two-dimensional pattern onto the surface of a three-dimensional object. After having defined an original curve on the two-dimensional pattern and a projection curve (600, 800) on the surface of the three-dimensional object, a point of the pattern is selected (610, 810). The abscissa of the projection of the selected point is determined according to the abscissa of the selected point and according to a first projection ratio (615, 815). Likewise, the ordinate of the projection of the selected point is determined according to the ordinate of the selected point and according to a second projection ratio (620, 820). A projection plane is then determined. This projection plane comprises the point of the projection curve that is determined by the abscissa of the projection of the selected point. The projection of the selected point onto the surface of the three-dimensional object 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 (625, 825).
The invention relates to an aircraft fuselage comprising a nose cone (2), a tail section (2) and a central section (3), the central section comprising longitudinal panels (31 - 39) 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.
The invention relates to a nacelle (12) for an aircraft high-bypass jet engine, in which a jet engine having a longitudinal axis (X) is mounted, the nacelle including a wall (24) concentrically and at least partially surrounding the jet engine and defining with the latter an annular duct (26) for the fluid inner flow, comprising at the downstream end (26a) of said nacelle wall a passage section of the flow outlet, characterised in that the nacelle includes displacement means (42) for displacing on request a portion (24b) of the nacelle wall in order to modify the passage section of the flow outlet through which a major portion of the flow (Fi') escapes, said displacement forming in the nacelle wall at least one opening (28; 53) through which a small portion of the flow, called the leak flow (Fi '), naturally escapes, the nacelle further comprising a fluid device (30; 54) that uses a fluid for compelling the leak flow to flow along the outer face (24e) of the portion of the nacelle wall located downstream relative to said at least one opening.
The invention relates to a machining device comprising a machining head (10) capable of displacement along at least three translation axes X, Y, Z for machining an immobile part fixed above the machining head (10), said machining head being maintained in a constant orientation by at least three articulated connecting rods (31a, 32a, 31b, 32b). Two connecting rods (31a, 32a) define together with the machining head and with a first Y carriage (33a), on which they are articulated, an deformable articulated parallelogram in the XZ plane. Another connecting rod (31b) is articulated on the machining head (10) and on a second Y carriage (33b). The first Y carriage (33a) is capable of displacement along Y on a first X carriage (20a) capable of displacement along X, and the second Y carriage (33b) is capable of displacement along Y on a second X carriage (20b) capable of displacement along X. The relative movement along X of the X carriages results in a displacement in the Z direction. Several devices can be positioned in a plurality of tunnels (40), said tunnels being arranged so as to share several means (107, 108, 109).
The invention relates to a method for locking and unlocking a separation door (5) that separates the cockpit (2) from the cabin (5) of an aircraft (1), comprising : a lock system (12) electrically controlled for locking the door; a control unit (10) ensuring an electric control of said lock system; a first manual control (8) for unlocking the door, connected to the control unit (10) and arranged in the cockpit; a second manual control (9) for unlocking the door, connected to the control unit (10) and arranged in a cabin; and means (14, 14) for automatically controlling the unlocking of the door when a crash of the aircraft is detected.
The invention relates to a fixed carrier (1) for machine-tool parts. Said carrier comprises a table frame (3) and a table (2) comprising a first face (21) that can hold a first part (211) to be machined, the first face being fixed above a machining device and the first part being stationary during the machining process. The table (2) also comprises a second face (22) for holding steady a second part (221) to be machined.
B23Q 1/52 - Supports mobiles ou réglables d'outils ou de pièces utilisant des mécanismes particuliers avec des guidages en rotation uniquement avec un seul guidage en rotation
The present invention relates to a stiffener for a structure submitted to tensile and/or compression and/or shear stresses, that comprises a shaped section comprising: a contact area with an element to be stiffened (9) having a closed cross-section and providing stability, said area comprising first (6) and second (7) legs; and a core (12) normal to the element to be stiffened that provides a support surface (61) capable of element recovery, said core being formed by one of the two legs. Application in aircraft structures.
The present invention relates to a process for manufacturing a panel made of a composite with the aid of tooling having a support (1) on which a lay-up step is carried out, said step consisting in producing a stack (18) of plies of fibre prepregs (20) followed by a step of consolidating the stack with the aim of obtaining the panel by means of a compacting plate (36) placed on top of this stack. According to the invention, the process is implemented in such a way that a first set (26) of polyimide films (28) partly overlapping one another is placed in contact with the stack of plies (18), between said stack and the compacting plate.
B29C 70/44 - Façonnage ou imprégnation par compression pour la fabrication d'objets de longueur définie, c.-à-d. d'objets distincts utilisant une pression isostatique, p. ex. moulage par différence de pression, avec un sac à vide, dans un autoclave ou avec un caoutchouc expansible
B29C 70/54 - Parties constitutives, détails ou accessoiresOpérations auxiliaires
The invention relates to a panel assembly in which the joint between two adjacent panels is closed by a seal (20), said assembly being characterized in that the seal comprises a central part (21) housed in a gap (19) formed between the two panels, and an outer part (22) located towards the outside of the panel assembly, and capable of at least partly covering the outer face of the two longitudinal lips (16, 17) of the panels (13, 14) bordering the gap. The invention also relates to a method of producing a panel assembly during which two adjacent panels (13, 14) are fixed together.
F16S 1/02 - Feuilles, panneaux ou autres éléments de proportions semblablesStructures comportant des assemblages de ces éléments conçus pour être ajustés bout à bout, p. ex. en formant un angleAssemblages à cet effet
B64C 7/00 - Structures ou carénages non prévus ailleurs
E04B 1/61 - Assemblages pour les constructions du bâtiment en général d'éléments de construction en forme de plaques en contact mutuel
B64C 3/26 - Construction, forme ou fixation des revêtements distincts, p. ex. panneaux
49.
PANEL ASSEMBLY AND METHOD OF ERECTING A PANEL ASSEMBLY
The invention relates to a panel assembly (100) in which two panels (101, 102) are connected together, in which assembly a surface of each of the two panels comprises a step (105, 106), in such a way as to form an upper level (112, 114) and a lower level (113, 115), the two panels being connected together along their lower levels. The sum of the heights of the steps of the two panels may be equal for example to the sum of the tolerance intervals accepted in the region of the joint between the two panels. The invention also relates to a method of making such a panel assembly.
B64C 1/12 - Structure ou fixation de panneaux de revêtement
B64C 3/26 - Construction, forme ou fixation des revêtements distincts, p. ex. panneaux
B64C 21/00 - Moyens permettant d'influencer l'écoulement d'air sur les surfaces des aéronefs en agissant sur la couche limite
F16B 5/00 - Jonction de feuilles ou de plaques soit entre elles soit à des bandes ou barres parallèles à elles
F16B 5/02 - Jonction de feuilles ou de plaques soit entre elles soit à des bandes ou barres parallèles à elles par organes de fixation utilisant un filetage
50.
DEVICE FOR IMPROVING THE EFFECTIVENESS OF ACOUSTIC TREATMENTS IN AN AIRCRAFT DRIVE DUCT
The subject of the invention is an aircraft nacelle comprising a duct (36) through which a stream of gas flows, said duct (36) being delimited by two substantially concentric walls, an internal one (40) and an external one (42), coated at least partly by a coating designed to absorb a part of the acoustic energy and at least one partition (38, 38') extending over at least part of the length of the duct (36) between said internal and external walls (40, 42) where the profile of at least one wall (44, 46) of said at least one partition (38, 38') is defined in such a way as to increase the number of times that an acoustic beam is reflected onto the coating designed to absorb a part of the acoustic energy.
F02K 3/04 - Ensembles fonctionnels comportant une turbine à gaz entraînant un compresseur ou un ventilateur soufflant dans lesquels une partie du fluide énergétique passe en dehors de la turbine et de la chambre de combustion l'ensemble fonctionnel comprenant des soufflantes carénées, c.-à-d. des soufflantes à fort débit volumétrique sous basse pression pour augmenter la poussée, p. ex. du type à double flux
51.
SUPPORT FOR ATTACHING ELECTRIC CABLES TO A STRUCTURE
The invention relates to a support (1) for holding a cable harness capable of being attached to a structure to hold said harness in position and orientation with respect to said structure. Said support comprises means (2) of positioning and holding the harness close to means (3) of connecting the support to the structure and rails (4a, 4b) that extend on either side of the means (2), substantially in the direction in which the harness must be held. Each rail is attached to said first means at one end and free at the other end.
The invention concerns a sensor simulation system. The simulation system (1) comprises a generator (3) that generates a digital signal by direct digital frequency synthesis, based on the following parameters: a frequency, an amplitude, a phase and amplitude shift; a digital/analog converter (4), and a means (6) that modulates the signal received from said converter (4).
The invention concerns a doorway (1) in an aircraft fuselage (2) comprising a door frame in which a door is mounted, this frame comprising an outer framework (60), an inner framework (50) and a core (40) placed between the inner framework and the outer framework, capable of absorbing energy from an impact, the core (40) being a stiffener made of composite material having an accordion shape.
The invention concerns a rear frame of an air intake of a nacelle of an aircraft, characterized in that it is partly made of fiber-reinforced geopolymer resin-based composite material and comprises at least one part (56) that surrounds an opening provided for the passage of a de-icing system made of fiber-reinforced geopolymer-resin based composite material and at least one other part (58) made of metal.
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.
The invention concerns a device for detecting and eliminating a layer of ice formed on the surface of an aircraft structure (6) or a liquid that has infiltrated inside of a structure and/or into the material of the structure. According to the invention, the device comprises at least one pair of subnetworks of conductive elements (2a, 2b), each subnetwork comprising at least one series of conductive elements (3), said subnetworks being arranged in such a way that the interfitting between the conductive elements (3) of the first subnetwork and the conductive elements (3) of the second subnetwork forms a network of capacitive sensors (1), said conductive elements being embedded in an insulating material (4), each subnetwork of conductive elements being incorporated into a flexible substrate (5, 5a, 5b) so that the entire assembly forms a flexible covering.
The invention concerns a conduit incorporated into the tubing of an aircraft characterized in that it is made from a composite material comprising a fiber-reinforced geopolymer resin matrix.
F16L 9/14 - Tubes en matériaux composites, c.-à-d. faits de matériaux non complètement couverts dans un seul des groupes précédents
F16L 9/18 - Tuyaux à double paroiTuyaux à canaux multiples ou assemblages de tuyaux
C04B 28/00 - Compositions pour mortiers, béton ou pierre artificielle, contenant des liants inorganiques ou contenant le produit de réaction d'un liant inorganique et d'un liant organique, p. ex. contenant des ciments de polycarboxylates
A device comprises equipment (101) with a heat source, a cold part (102) relative to the equipment, and a thermal conductor element (103) capable of conducting the heat from the equipment to the cold part. The element (103) is such that, under certain thermal conditions above a given thermal condition, the equipment and the cold part are essentially thermally isolated.
A device comprises equipment (501) with a heat source having a maximum thermal operation condition, a cold part (502) relative to the equipment and an element (503) capable of transmitting the heat from the equipment to the cold part. The element (503) is capable of causing the transmitted heat to be limited for thermal conditions above a specified threshold below said maximum condition.
The subject of the invention is a special layout of the tail cone (4) of the fuselage (1) of an aeroplane. This aeroplane has a fuselage (1) with a nose cone, a main section and a tail cone (4) bearing a vertical stabilizer (14) and an empennage (15). The fuselage (1) is divided into two superimposed regions by a floor (10) forming a main deck, these being respectively a pressurized and air-conditioned upper region (11) in which a passenger cabin (2) is formed, and a pressurized lower region (12) that forms a cargo hold (3). The pressurized upper region (11) is extended into the tail cone (4) by a pressurized space (40) which extends as far as a leaktight and strong transverse bulkhead (41) positioned in the rear part of that portion (13) of the fuselage that is covered by the vertical stabilizer (14), said pressurized space (40) constituting an area accessible to individuals and extending over the majority of that portion (13) of the fuselage that is covered by the vertical stabilizer (14).
This storage compartment for the front landing gear is intended for an aircraft having a set of collapsible landing gears having a nose gear (4) centered on a longitudinal median plane of the fuselage (1). This storage compartment forms a sealed partition between a pressurized area and the housing of the nose gear in its collapsed position. It has a reinforced upper face having an area that is appreciably flat and appreciably horizontal when the aircraft is on the ground, so as to form a floor of a pressurized compartment of the aircraft.
According to the invention, the internal wall (5.1) of the air intake (2) and the housing (12.1) for the fan (3) are pieces of composite fibre/resin material, overlap-jointed at the ends thereof (5.1 R) and (12.1A).
F02C 7/04 - Entrées d'air pour ensembles fonctionnels de turbines à gaz ou de propulsion par réaction
F01D 25/24 - Carcasses d'enveloppeÉléments de la carcasse, p. ex. diaphragmes, fixations
F16B 5/02 - Jonction de feuilles ou de plaques soit entre elles soit à des bandes ou barres parallèles à elles par organes de fixation utilisant un filetage
According to the invention, the internal wall of the air intake (2) and the housing of the fan (3) form a single tubular piece (30) made from a fibre/resin composite material.
F02C 7/04 - Entrées d'air pour ensembles fonctionnels de turbines à gaz ou de propulsion par réaction
F02K 3/06 - Ensembles fonctionnels comportant une turbine à gaz entraînant un compresseur ou un ventilateur soufflant dans lesquels une partie du fluide énergétique passe en dehors de la turbine et de la chambre de combustion l'ensemble fonctionnel comprenant des soufflantes carénées, c.-à-d. des soufflantes à fort débit volumétrique sous basse pression pour augmenter la poussée, p. ex. du type à double flux comprenant une soufflante avant
64.
AIRCRAFT ENGINE ATTACHMENT DEVICE COMPRISING TWO THRUST-REACTING LINK RODS THAT FIT TOGETHER TRANSVERSELY
The present invention relates to an aircraft engine attachment device comprising a rigid structure and means for attaching the engine to the rigid structure, the attachment means comprising a thrust-reacting device (14) comprising two lateral thrust-reacting link rods (26) each having a rear end (26b) mounted on a balance beam (28) of the device (14) via a mechanical link (44). According to the invention, each link (44) is made using a peg (48) provided on the balance beam and passing through a hole (50) made in the rear end (26b), the peg (48) being arranged in such a way as to run substantially transversely with respect to the attachment device.
B64C 27/26 - Giravions complexes, c.-à-d. aéronefs utilisant en vol à la fois les caractéristiques de l'avion et celles du giravion caractérisé par le fait qu'il est doté d'ailes fixes
65.
ENGINE ASSEMBLY FOR AIRCRAFT COMPRISING AN AERODYNAMIC COUPLING FAIRING MOUNTED ON TWO SEPARATE ELEMENTS
The invention relates to an engine unit for aircraft, comprising an engine, an engine mounting device (4), a cowling enclosing the engine, provided with an air intake (32) and fan shrouds, the unit comprising a support cradle (40) for the fan shrouds fixed to the mounting device or to an assembly comprising a fan housing and the air intake, fixed to said housing. According to the invention, the engine unit has more than one aerodynamic coupling fairing (33) with first mounting means fixed to the cradle (40) and second mounting means fixed to other of the elements on the mounting device (4) and said unit.
The invention relates to an engine assembly for an aircraft, comprising an engine, an engine mounting device (4) and a cowling enclosing the engine provided with fan shrouds (34), the mounting device (4) having a rigid structure (8) and a forward aerodynamic structure (24) on which the fan shrouds have an articulated mounting, said forward aerodynamic structure (24) being provided with a cradle (40) having rear mounting means (44a, 44b) fixed to the rigid structure (8). According to the invention, the cradle is also provided with forward mounting means (42) fixed to an engine fan housing (18).
According to the invention, the air intake (2) is made of a piece (23) of fibre/resin composite material, reinforced on the side of the flange (24) by a reinforcing ring (26).
The subject of the invention is a method aimed at reducing, cancelling or reversing the thrust generated by at least one air stream leaving a power plant of an aircraft by deflecting at least some of the stream liable to contribute to the thrust, characterized in that it consists in injecting a fluid termed the thrust-reversal fluid into the power plant in such a way as, through an entrainment effect, to deflect at least some of the stream liable to contribute to the thrust from inside the nacelle toward the outside of the nacelle.
F02K 3/06 - Ensembles fonctionnels comportant une turbine à gaz entraînant un compresseur ou un ventilateur soufflant dans lesquels une partie du fluide énergétique passe en dehors de la turbine et de la chambre de combustion l'ensemble fonctionnel comprenant des soufflantes carénées, c.-à-d. des soufflantes à fort débit volumétrique sous basse pression pour augmenter la poussée, p. ex. du type à double flux comprenant une soufflante avant
F02K 1/09 - Variation de la section utile de la tubulure de jet ou de la tuyère par déplacement axial d'un organe externe, p. ex. d'un carénage
F02K 1/34 - Ensembles fonctionnels caractérisés par la forme ou la disposition de la tubulure de jet ou de la tuyèreTubulures de jet ou tuyères particulières à cet effet utilisant des jets de fluide pour influencer l'écoulement du jet pour atténuer le bruit
F02K 1/32 - Ensembles fonctionnels caractérisés par la forme ou la disposition de la tubulure de jet ou de la tuyèreTubulures de jet ou tuyères particulières à cet effet utilisant des jets de fluide pour influencer l'écoulement du jet pour inverser la poussée
F02K 1/30 - Ensembles fonctionnels caractérisés par la forme ou la disposition de la tubulure de jet ou de la tuyèreTubulures de jet ou tuyères particulières à cet effet utilisant des jets de fluide pour influencer l'écoulement du jet pour faire varier la section utile de la tubulure de jet, ou de la tuyère
F02K 1/28 - Ensembles fonctionnels caractérisés par la forme ou la disposition de la tubulure de jet ou de la tuyèreTubulures de jet ou tuyères particulières à cet effet utilisant des jets de fluide pour influencer l'écoulement du jet
F02K 1/72 - Inversion du flux de la soufflante utilisant des volets inverseurs de poussée ou des portes montées sur le carter de la soufflante la partie arrière du carter de la soufflante étant mobile pour découvrir des ouvertures d'inversion de poussée dans le carter de la soufflante
F02K 1/70 - Inversion du flux de la soufflante utilisant des volets inverseurs de poussée ou des portes montées sur le carter de la soufflante
69.
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.
Method for instantaneously determining rates of distortion of signals on an ac electrical network, and associated device. The present invention addresses the need for real-time calculation of an instantaneous value of discrete harmonic rate, adapted in particular for an electrical network producing a variable-frequency signal. In a general manner, the invention proposes a method for instantaneously determining rates of distortion on variable-frequency signals, and an associated device, in which a rate of harmonic distortion is calculated over a time window that is as short as possible, corresponding to the duration of a period of the fundamental of a relevant signal. Advantageously, one seeks to precisely determine the value of the frequency of the signal whose DHT is to be calculated, and an iteration is carried out for certain measurements made during a given calculation for the calculation of the DHT on subsequent signals.
The invention relates to a turboreactor (100) for an aircraft comprising an engine (103) housed in a nacelle (101) and a heat exchanger (107) intended for cooling a fluid contributing to the propellant system of the engine. The heat exchanger is placed at the level of the outer wall (105) of the engine, an interstitial space wherein the air may circulate being arranged between the outer wall of the engine and an inner wall (112) of the heat exchanger. The invention also relates to an aircraft provided with at least one such turboreactor.
F02C 7/14 - Refroidissement des ensembles fonctionnels des fluides dans l'ensemble fonctionnel
F02K 3/04 - Ensembles fonctionnels comportant une turbine à gaz entraînant un compresseur ou un ventilateur soufflant dans lesquels une partie du fluide énergétique passe en dehors de la turbine et de la chambre de combustion l'ensemble fonctionnel comprenant des soufflantes carénées, c.-à-d. des soufflantes à fort débit volumétrique sous basse pression pour augmenter la poussée, p. ex. du type à double flux
72.
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 (4) comprising at least one motor coupled to said wheel by a mechanical transmission assembly (42) comprising a mechanical gearbox (6) the reduction ratio of which is continuously variable, for a limited angle of rotation of the wheel (10) of the aircraft, by means of spiral gears (61, 62) the radii of which vary continuously over practically a full revolution of said spiral gears and the reduction ratio of which is constant without limitation of the angle of rotation of the wheel (10) of the aircraft outside of said limited angle of rotation. The continuously variable reduction ratio is used to increase the torque supplied at start-up by the drive means without increasing the capability of the motor in order to be able to obtain the initial torque needed to set the wheels of the aircraft in rotation upon startup.
B64C 25/36 - Aménagements ou adaptations des roues, des pneumatiques ou des essieux
F16H 35/00 - Transmissions ou mécanismes ayant d'autres caractéristiques de fonctionnement particulières
B64C 25/40 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue un mouvement rotatif étant communiqué aux éléments avant l'impact
73.
AIRCRAFT PROPULSION ASSEMBLY COMPRISING A JET PIPE WITH A NOTCHED TRAILING EDGE
The subject of the invention is a propulsion assembly comprising at least one jet pipe (62, 76) comprising an air outlet delimited by a trailing edge (78, 82), characterized in that the end portion of the jet pipe (62, 76) has two notches (84) each corresponding to one favoured direction of acoustic radiation, these being separated by protruding portions (86) capable of limiting the acoustic radiation, and the said notches being offset upwards relative to the horizontal midplane.
Fairing for a pylon via which a turbine engine is suspended from a wing of an aircraft. According to the invention, the forward attachment (15) of the anterior part (14) of the fairing (7) for the suspension pylon (6) is radially flexible.
The invention relates to a method of routing virtual links in a frame-switching network comprising a plurality of source and/or destination terminals of said frames, frame switches being connected together by physical connections, each virtual link being defined, for a point-to-point type, by a path through said network between a source terminal and a destination terminal and, for a multipoint type, by a plurality of paths through said network between a source terminal on the one hand and a plurality of destination terminals, on the other hand. The method performs the routing of the links by complying with a segregation constraint in relation to triplets of consecutive switches belonging to said oriented loops, in such a way as to allow verification of the determinism of the network.
According to the invention, high lift leading-edge slats (13) and high lift flaps (14) are simultaneously deployed, when the speed of the aircraft is equal to and less than an AES threshold.
G05D 1/06 - Régime de modification de l'altitude ou de la profondeur
B64C 13/18 - Dispositifs amorçant la mise en œuvre actionnés automatiquement, p. ex. répondant aux détecteurs de rafales utilisant un pilote automatique
A landing assistance device and method for an aircraft. According to the invention, based on the landing procedure rules attached to the runway (2), a lower threshold and an upper threshold of total energy acceptable for the aircraft (1) are determined and the current total energy of the latter is compared with said thresholds.
B64D 45/04 - Aides à l'atterrissageDispositifs de sécurité pour éviter la prise de sol brutale
G05D 1/00 - Commande de la position, du cap, de l'altitude ou de l'attitude des véhicules terrestres, aquatiques, aériens ou spatiaux, p. ex. utilisant des pilotes automatiques
G05D 1/06 - Régime de modification de l'altitude ou de la profondeur
78.
METHOD OF ROUTING VIRTUAL LINKS IN A FRAME-SWITCHING NETWORK
The invention relates to a method of routing virtual links in a frame-switching network comprising a plurality of source and/or destination terminals of said frames, frame switches being connected together by physical connections, each virtual link being defined, for a point-to-point type, by a path through said network between a source terminal and a destination terminal and, for a multipoint type, by a plurality of paths through said network between a source terminal on the one hand and a plurality of destination terminals on the other hand. The method performs the routing of the links by minimizing at least one cost function over a set of solutions satisfying at least one predetermined topological constraint.
In conformance with the invention, based on the incident conditions and velocity, the steering of the ailerons is weakly negative (b0) or corresponds either to the maximum sharpness of the aircraft (b1), or the optimal lift of the latter (b2).
The invention relates to an aircraft comprising 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 (18), characterized in that at least one profiled bearing rod (20; 30) is positioned on each of the engine support pylons so as to generate a propulsive resultant force under the action of an oblique air flow.
A device for receiving messages each having a serial number comprises means for storing a plurality of prior-reception statuses (SR(n)), means (E308) for modifying the status (SR(n)) associated with a serial number (n) on receipt of a message (M) having said serial number (n) and means (E310) for processing the message as a function of the status (SR(n)) associated with its serial number (n). An aircraft equipped with such a device and an associated method are also proposed.
The invention concerns a device for non-destructive control (1) of a component (4) by analyzing distribution of a leakage magnetic field emitted by the component when it is subjected to an exciting magnetic field, comprising 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 (2) 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 (4). The invention is 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.
G01N 27/87 - Recherche ou analyse des matériaux par l'emploi de moyens électriques, électrochimiques ou magnétiques en recherchant des variables magnétiques pour rechercher la présence des criques en étudiant des champs magnétiques de dispersion en utilisant des sondes
83.
DEVICE FOR NON-DESTRUCTIVE TESTING OF A COMPONENT BY ANALYZING RADIATION DISSIPATION
The invention concerns a device for non-destructive testing of a component (4) by analyzing radiation dissipation when the component is stressed by mechanical stresses. Said device comprises measuring means for determining a surface radiation field of the component. The measuring means are integrated in a flexible housing (2) for covering a region of the surface of the component (4) to be tested. Said device enable an initial crack upon stress concentration on a surface of the component and the presence of a crack (5) upon propagation of said crack to be detected. The invention is 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.
This invention relates to a pressure-sealed floor for aircraft, provided with girders (1) comprising a top flange (2), a vertical web (3) and a bottom flange (4), wherein the top flange is provided with two angled legs (7, 8) arranged on either side of the vertical web and having a supporting surface (14, 15) for supporting curved pressurized diaphragms (9), characterized in that the bottom flange includes a connecting element (10) joining the two angled legs in such a way that said bottom flange has a closed cross-section. A structure such as this can advantageously be made of a composite material.
The invention concerns a device (1) for non-destructive testing of a structure (4) likely to contain a defect (5), comprising means for measuring (3) vibratory waves emitted by said structure at different points of a surface of said structure, said measuring means (3) being integrated in a flexible housing (2) capable of adhering on the surface of said structure to be tested. The invention is applicable to all industrial sectors where testing of the integrity of structures is important, in particular in aeronautics.
G01N 29/14 - Recherche ou analyse des matériaux par l'emploi d'ondes ultrasonores, sonores ou infrasonoresVisualisation de l'intérieur d'objets par transmission d'ondes ultrasonores ou sonores à travers l'objet utilisant des techniques d'émission acoustique
G01H 11/00 - Mesure des vibrations mécaniques ou des ondes ultrasonores, sonores ou infrasonores par détection des changements dans les propriétés électriques ou magnétiques
H01L 41/053 - Montures, supports, enveloppes ou boîtiers
86.
METHOD OF REPAIRING A DAMAGED AREA OF AN AIRCRAFT FUSELAGE
The object of the invention is method of cutting out a damaged area from an aircraft fuselage, in particular in order to repair said damaged area, consisting in making at least one cut-out in the fuselage (20) in order to delimit a cut-out area (24) encompassing the damaged area and comprising at least one rounded section, characterized in that it consists in making an opening (34) near said rounded section of the cut-out area (24) with a tool the diameter of which corresponds to that of the desired rounded section.
B64F 5/00 - Tracé, fabrication, assemblage, nettoyage, entretien ou réparation des aéronefs, non prévus ailleursManipulation, transport, test ou inspection de composants d’aéronefs, non prévus ailleurs
B23P 6/00 - Remise en état ou réparation des objets
The present invention relates to an onboard telecommunication system, partitioned into a secure zone and a non-secure zone, comprising at least a first item of telecommunication equipment in the secure zone, a second item of telecommunication equipment in the non-secure zone, and a first one-way link from the first to the second item of equipment, said first item of equipment being suitable for transmitting data on said first link according to a first protocol. The system also comprises a second link from the second to the first item of equipment, according to a second protocol wherein the first two layers are separate from the those of the first protocol, said second item of equipment being suitable for transmitting the data on the second link in the form of messages according to the first protocol and encapsulated in frames according to the second protocol.
The present invention relates to a device for attaching an aircraft engine comprising a rigid structure forming a box, and a device for taking up the thrust forces having a main brace (34) mounted fixedly on one of the longerons (17) forming the box, by fixing means (40). According to the invention, the means (40) comprise a fixing pin (50) mounted on the longeron (17) and having a main portion (54) situated externally with respect to the box, this brace (34) having the portion (54) of the pin (50) passing through it and being pressed against the longeron (17) by a bell-shaped support washer (68) surrounding the main portion (54) and stressed by a screw (72) passing through it, the latter being screwed into a barrel nut (78) housed in a bore (74) formed within the main portion (54).
The invention relates to an electricity distribution system and method inside an aircraft. This system comprises at least two electrical electricity distribution systems (10, 11) from at least one power source (14-16) to current loads (18, 19) of said aircraft via electrical and/or electronic protection/switching components, said components being configurable and controllable by dedicated electronics, wherein each electrical distribution system (10, 11) comprises control electronics wherein a configuration file (FC1, FC2) attributing an installation status to each of the protection/switching components is downloaded.
The purpose of the invention is a communication method on a communication link between an aircraft and a ground station, the communication possibly being configured according to a plurality of safety levels in which, when the aircraft sends a request to a ground station in order to modify the safety level of said communication from a previous safety level to a new safety level and that it does not receive an acknowledgement of said request by the ground station, this aircraft still accepts messages from the ground station according to said new security level. The invention also relates to a device to implement this method.
The purpose of the invention is a safety device for a semiconductor switch controlling a secondary line (2) provided with a fuse (3) on the input side of the switch device that comprises component (4) to create a short circuit in the secondary line, so as to cut off the fuse (3), and means (5, 6, 7) of activating this component (4) following detection of an overcurrent in the secondary line.
H03K 17/082 - Modifications pour protéger le circuit de commutation contre la surintensité ou la surtension par réaction du circuit de sortie vers le circuit de commande
H02H 9/00 - Circuits de protection de sécurité pour limiter l'excès de courant ou de tension sans déconnexion
A tool (10) for cold expansion of holes comprises a body (14) which has at least a cylindrically shaped part (16) having an inner hole (24) in axial direction of the body (14). The body (14) comprises along the circumferential direction a plurality of members (18, 18a, 18b, 18c) which are movable in radial direction of the body (14), such that the outer diameter of the cylindrically shaped part (16) of the body (14) can be changed. Furthermore a core (26, 26c) is provided which is insertable into the inner hole (24), wherein at least one of the core (26, 26c) and the inner hole (24) comprises a portion (28) of changing diameter and the inner hole (24) and the core (26, 26c) get into contact with each other upon insertion of the core, such that in dependency of the depth of the insertion of the core (26, 26c) into the inner hole (24) in axial direction the members (18, 18a, 18b, 18c) move radially outwardly and the outer diameter of the cylindrically shaped part (16) of the body (14) increases.
The invention relates to an aircraft floor (2) comprising at least one central rail (8) mounted secured to a rigid aircraft structure, at least two lateral rails (5), placed on either side of the central rail, each lateral rail being connected vertically to the aircraft structure by a vertical connecting rod (15) and being free transversely, and floor panels (18), each floor panel being placed between two adjacent rails, in such a way that the transverse stresses to which the lateral rails are subject pass through the floor panels as far as the central rail. The invention also relates to an aircraft section (1) fitted with said floor and the use of said floor in an aircraft section.
Radiocommunication system for aircraft. The radiocommunication system (S1) comprises a single box and, integrated into this single box, at least one single main interface module (7), which is formed in such a way as to carry out the processing of the interfaces of all the radiocommunication means (3 to 6) of said radiocommunication system (S1).
The invention concerns a device and a method for standby power supply on board an aircraft, capable of powering the aircraft 'essential' electrical system. Said device comprises a separately energized synchronous machine (MSI) associated with a flywheel (RI) and an auxiliary device (30) for rotating the flywheel and maintaining its rotation.
The flight-control device (1) makes it possible, by offsetting part of a flight command according to a particular flight path, to obtain the same control as is obtained with usual flight control, but without flexible excitation that generates discomfort in the aircraft.
The subject of the invention is a nut for securing an aircraft windscreen (40) inserted between two elements (42, 44) which are held together by at least one connecting element (46) comprising a bolt (48) and the said nut (50), the said nut (50) comprising two parts, a first part (60) called the body comprising a tapped bore (62) able to collaborate with the threaded shank of the bolt (48) and a second part (64) termed the base which can be secured to one of the windscreen securing elements (42, 44), the body (60) and the base (64) having collaborating shapes to prevent the body (60) from rotating with respect to the base (64) about the axis (66) of the bore (62) of the body, characterized in that the body (60) at one of its ends has a surface able to be brought into contact with the base (64), the said surface comprising at least one protrusion projecting from the said surface in the direction of the axis (66) of the bore (62) and able to collaborate with an indentation formed in the base (64).
The present invention relates to a device and a method for generating electricity on board an aircraft, comprising several generators (GEN1-GEN4) and several environmental control systems (ECS1, ECS2, ECS3, ECS4) with an external air inlet. The device comprises means for operating the environmental control systems as back-up generators and a storage device (30).
B64D 13/06 - Aménagements ou adaptations des appareils de conditionnement d'air pour équipages d'aéronefs, passagers ou pour emplacements réservés au fret l'air étant climatisé
99.
AIRCRAFT WING ARRANGEMENT COMPRISING AN ENGINE ATTACHMENT PYLON DEFINING, IN THE FORWARD REGION, A LATERAL AIRFLOW CHANNEL
The invention relates to an aircraft wing arrangement (1) comprising a wing (2) and at least one aircraft engine attachment pylon (4) for attaching an engine suspended under the wing and comprising a forward region (8) protruding forward from an leading edge (10) of the wing. According to the invention, the forward region (8) comprises a lateral projection (12) delimiting a lateral airflow channel (14) extending towards a proximal end of the wing.
The method according to the present invention relates to a device for detecting the state of a switch (1). The device comprises a detection circuit (4) delivering a signal of determined value (VpullUp) when the value of an electric quantity (Rint) characterising the state of the switch is less than a threshold called the lower threshold (Rclosed) and/or a signal of different value when the value of said electric quantity is greater than a threshold different from the lower threshold, called the upper threshold (Ropen). The present invention also relates to flight control systems in which said device is implemented and the aircraft comprising said systems.
H01H 9/16 - Indicateurs de position, p. ex. "marche" ou "arrêt"
H01H 1/60 - Moyens auxiliaires associés constructivement avec l'interrupteur pour nettoyer ou lubrifier les surfaces de contact
H02H 3/04 - Circuits de protection de sécurité pour déconnexion automatique due directement à un changement indésirable des conditions électriques normales de travail avec ou sans reconnexion Détails avec signalisation ou supervision additionnée à la déconnexion, p. ex. pour indiquer que l'appareil de protection a fonctionné
H01H 71/04 - Moyens pour indiquer l'état du dispositif de commutation
brevets
