The invention relates to an aqueous composition for the electrolytic deposition of a chromium coating on the surface of a substrate, which has a pH of between 0 and 1 and which contains a trivalent chromium salt, glycine, an alkali metal salt, an aluminium salt and, optionally, an ammonium salt. The chromium plating process according to the invention comprises the immersion of the substrate to be treated in this composition and the application of a current between this substrate and an anode. This process makes it possible to form a high-quality chromium coating on the entire surface of the substrate.
The invention relates to a device (1) for encoding information between a plurality of normally closed switches (P1 . . . Pn) arranged on an operating lever (2) and a control device (9), said switches being connected in series between a voltage line (3) and a measuring line (5), each switch (Pi) being associated with a single resistor (Ri) connected between the terminal of the switch closest to a voltage source (Vcc) and the measuring line. The encoding device thus allows a hierarchy of the switches to be obtained.
H03M 11/24 - Codage statique utilisant des moyens analogiques
B64C 13/04 - Dispositifs amorçant la mise en œuvre actionnés par l'homme
B64C 27/56 - Mécanismes pour la commande du réglage ou du mouvement de la pale par rapport à la tête du rotor, p. ex. mouvement de traînée caractérisés par les dispositifs de déclenchement de la commande, p. ex. à commande manuelle
G05G 9/047 - Mécanismes de commande manuelle équipés d'un seul organe de commande travaillant avec plusieurs organes commandés, p. ex. en sélection ou simultanément l'organe de commande étant manœuvré de différentes manières indépendantes, chacune de ces manœuvres individuelles entraînant un seul organe commandé dans lesquels la manœuvre de l'organe de commande peut être effectuée de plusieurs manières simultanément l'organe de commande étant manœuvré à la main autour d'axes orthogonaux, p. ex. manches à balai
H03M 1/76 - Conversion simultanée utilisant un arbre de commutation
H03M 1/78 - Conversion simultanée utilisant un réseau en échelle
3.
Process and device for manufacturing a composite part enabling the evacuation of gas from the composite part
Disclosed is a process for manufacturing a part, named composite part, formed from at least one composite material including at least one layer of a reinforcing structure impregnated with a polymer matrix within which the reinforcing structure extends, wherein: a composite blank of the composite part is prepared; and a step of curing the polymer matrix of the composite blank is carried out, exerting a pressure on at least one pressed face of the composite blank. The pressure is exerted in the form of a pressure gradient applied to the pressed face of the composite blank so as to cause the gas present within the composite part to flow from a zone of maximum pressurization to a gas evacuation zone. Also disclosed is a device for manufacturing such a part.
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 33/40 - Matière plastique, p. ex. mousse ou caoutchouc
B29C 43/36 - Moules pour la fabrication d'objets de longueur définie, c.-à-d. d'objets séparés
B29C 37/00 - Éléments constitutifs, détails, accessoires ou opérations auxiliaires non couverts par le groupe ou
4.
DEVICE FOR ENCODING INFORMATION BETWEEN A PLURALITY OF SWITCHES OF AN OPERATING LEVER AND A CONTROL DEVICE
The invention relates to a device (1) for encoding information between a plurality of normally closed switches (P1...Pn) arranged on an operating lever (2) and a control device (9), said switches being connected in series between a voltage line (3) and a measuring line (5), each switch (Pi) being paired with a single resistor (Ri) connected between the switch terminal closest to a voltage source (Vcc) and the measuring line. The encoding device thus makes it possible to obtain a hierarchy of switches.
H03M 11/24 - Codage statique utilisant des moyens analogiques
B64C 13/00 - Systèmes de commande ou systèmes de transmission pour actionner les gouvernes, les volets hypersustentateurs, les aérofreins ou les destructeurs de portance (spoilers)
H03M 1/78 - Conversion simultanée utilisant un réseau en échelle
5.
PROCESS AND DEVICE FOR MANUFACTURING A COMPOSITE PART ENABLING THE EVACUATION OF GAS FROM THE COMPOSITE PART
The invention relates to a process for manufacturing a part, referred to as a composite part, formed from at least one composite material comprising at least one layer of a reinforcing structure impregnated with a polymer matrix within which the reinforcing structure extends, in which: - a composite blank (1) of said composite part is prepared, - a step of curing the polymer matrix of said composite blank is carried out, while exerting pressure on at least one pressed face (2) of said composite blank, characterized in that said pressure is exerted, in the form of a pressure gradient, applied to said pressed face of said composite blank, so as to make the gas present within the composite part flow from a zone of maximum pressurization to a gas evacuation zone (4). The invention also relates to a device for manufacturing such a part.
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 33/40 - Matière plastique, p. ex. mousse ou caoutchouc
6.
Device for de-icing a rotor blade, rotor blade provided with such a device, rotor, turbomachine and aircraft
A de-icing device is provided for at least one surface portion of a rotor blade liable to be covered with a layer of ice. The device includes: at least one first heating device adapted to permit detachment of at least part of the layer of ice, as well as at least one second heating device including heating elements extending facing only part of the surface portion so as to circumscribe at that location closed-contour zones of the surface portion. The heating elements of the second heating device are adapted to cause breaking of the ice through the thickness of the layer of ice, and the first heating device extends at least partly facing the inside of the closed-contour zones.
An actuator of an aircraft includes at least one limit stop in which at least one of the bearing surfaces, named destructible bearing surface (19), has at least one destructible portion which is able to, and is arranged to, be irreversibly deformed under the effect of the co-operation by limit contact between the driving member bearing surface (19) and the driven member bearing surface (20). Each destructible portion of each destructible bearing surface is mounted to be removable with respect to the stop as to be able to be replaced.
B64C 13/00 - Systèmes de commande ou systèmes de transmission pour actionner les gouvernes, les volets hypersustentateurs, les aérofreins ou les destructeurs de portance (spoilers)
A bearing for guiding a first guided piece includes a first bearing surface with respect to a second bearing surface fixedly attached to a second guided piece. At least one first intermediate piece is interposed between the first bearing surface and the first guided piece and at least one first automatic release assembly for i) in a first assembly state, fixedly attaching the at least one first intermediate piece and the first guided piece for guidance forces which are lower than a triggering value, and ii) in a release state, permitting a relative displacement of the first guided piece with respect to the at least one first intermediate piece, at least in one displacement orientation, for guidance forces which are greater than the triggering value of the first assembly.
F16C 29/00 - Paliers pour pièces à déplacement uniquement linéaire
F16F 9/20 - Dispositifs à un ou plusieurs organes, p. ex. des pistons, des aubes, se déplaçant en va-et-vient dans des chambres et utilisant un effet d'étranglement comportant uniquement un déplacement rectiligne des parties travaillant avec un cylindre fermé et un piston déterminant, à l’intérieur de ce cylindre, plusieurs espaces de travail avec tige du piston traversant les deux extrémités du cylindre
A device for supplying electricity to at least one secondary electric load (30) on-board a turbomachine rotor (12) including a main circuit for transmitting main electric power to at least one main on-board electrical load (16), includes a device (15) for rotatably and electrically connecting the stator and the rotor, and at least one secondary circuit for transmitting a secondary electric power including at least one secondary conductor (28) of the stator connected to a secondary electric power source (29) suitable for outputting a secondary power in the form of a power signal with a secondary frequency selected such as to enable selective, interference-free transmission of the secondary power via the rotary electric connection device (15), separately from the main power transmission.
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
F03D 80/40 - Détection de givreMoyens de dégivrage
B64D 15/12 - Dégivrage ou antigivre des surfaces externes des aéronefs par chauffage électrique
10.
Device for emergency actuation especially intended for an aircraft opening
A method and a device for coupling piloting members (20, 50), wherein saturation values (SCpsat−, SCpsat+, SCcopsat−, SCcopsat+) of at least one force saturator (28, 58) are adapted such that a force-feedback is exerted for each of these saturation values at a force-feedback value, taken at the force application centre of the manoeuvring handle (21, 51), of between 4 daN and 40 daN, with the result that a function of disconnecting is at least in part performed by the at least one force saturator.
A device and a control method are described for a swinging aircraft door (3), mobile around a swinging axis (21) substantially parallel to the longitudinal axis of the aircraft via a motorized mechanism and having integrated boarding stairs (31). The method includes the capture of electromagnetic or ultrasonic radiation using at least one sensor (401, 501); the detection of something on the stairs on the basis of captured electromagnetic or ultrasonic radiation, in order to deduce therefrom whether a detection condition is satisfied or not; and, driving of the motorized mechanism in order to control the closure of the door in response to a closure command except in case of detection of something on the stairway.
an accumulator comprising a rigid shell (20) inside of which a separation means (40) is located, defining a compensation chamber (42) that is filled with hydraulic fluid and is in communication with the working chamber, and a chamber (47) filled with pressurized gas, the rigid shell (20) being a metal shell produced by means of welded assembly and the accumulator being made such as to obtain an entirely welded enclosure (47) containing the gas.
B64C 1/14 - FenêtresPortesTrappes d'évacuation ou panneaux de visiteStructures de cadres environnantsVerrièresPare-brise
F16F 9/06 - Ressorts, amortisseurs de vibrations, amortisseurs de chocs ou amortisseurs de mouvement de structure similaire, utilisant un fluide ou moyen équivalent comme agent d'amortissement utilisant à la fois un gaz et un liquide
A blade includes an aerodynamic portion (21) and an assembly of the aerodynamic portion to a blade shank retaining the aerodynamic portion in a radial direction (23). The blade shank includes at least one passage restriction in at least one retention direction orthogonal to the radial direction, having a restricted width allowing the aerodynamic portion (21) to pass through. The base of the aerodynamic portion (21) has an overall dimension which is strictly greater than the restricted width so that, in the event of rupture of the assembly, the base is able to come into abutment against the passage restriction so as to retain the aerodynamic portion (21) in the blade shank (20).
A device for opening and closing according to the invention relates to an aircraft door (2) hinged around an axis (6) substantially parallel to the longitudinal axis the aircraft comprising a motorized mechanism and a driving system combined with a control device comprising a system for acquisition of the angular position of the door (2) relative to the structure (4) the aircraft, where said angular position acquisition system for the door comprises at least one inclinometer (20) combined with the door (2).
G05D 3/00 - Commande de la position ou de la direction
B64C 1/14 - FenêtresPortesTrappes d'évacuation ou panneaux de visiteStructures de cadres environnantsVerrièresPare-brise
E05F 15/603 - Mécanismes pour battants mus par une force motrice utilisant des actionneurs électriques utilisant des électromoteurs rotatifs
E05F 15/611 - Mécanismes pour battants mus par une force motrice utilisant des actionneurs électriques utilisant des électromoteurs rotatifs pour battants pivotants
E05F 15/70 - Mécanismes pour battants mus par une force motrice avec déclenchement automatique
16.
Process and device for controlling an operating lever of a vehicle
a converter feeding each winding of the motor with an alternating-voltage signal (U_alim) worked out on the basis of the limited control voltage as a function of the angular position of the motor.
B64D 31/06 - Dispositifs amorçant la mise en œuvre actionnés automatiquement
H02P 6/00 - Dispositions pour commander les moteurs synchrones ou les autres moteurs dynamo-électriques utilisant des commutateurs électroniques en fonction de la position du rotorCommutateurs électroniques à cet effet
G05B 1/01 - Éléments de comparaison, c.-à-d. éléments pour effectuer la comparaison directement ou indirectement entre une valeur désirée et des valeurs existantes ou prévues électriques
G05B 11/42 - Commandes automatiques électriques avec les dispositions nécessaires pour obtenir des caractéristiques particulières, p. ex. proportionnelles, intégrales, différentielles pour obtenir une caractéristique à la fois proportionnelle et dépendante du temps, p. ex. P.I., P.I.D.
H02P 6/28 - Dispositions pour la commande du courant
17.
Device for combining force among control units, control unit and aircraft
A device for combining force between two control units includes force feedback, each control unit including a control stick (21, 31) and at least one force sensor (24, 34) suitable for providing a value of the control force (Fp, Fcp) exerted by a pilot, the device being suitable for forming a force feedback value from the sum of the values of the control forces of each control unit. A correction device limits the force feedback value (Fcor_p) according to at least one parameter taken from the absolute value of the control force (Fcp) of the second control unit and the difference between the control force values of each control unit. A control unit including such a device for combining forces, and an aircraft provided with such control units are also described.
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
18.
Blade with redundant anchoring in a hub, propeller, turboprop engine and aircraft
A propeller blade includes an aerodynamic portion and a blade shank, a hub assembly (28, 32) which provides anchoring in a hub, a blade shank assembly of the aerodynamic portion, a safety device including a safety element (24) which extends from a distal assembly in the aerodynamic portion to a proximal assembly (26, 27) in the blade shank and which is adapted to be able to anchor the aerodynamic portion in the blade shank, wherein the blade shank assembly is anchored radially outside the hub assembly, the proximal assembly is anchored to the blade shank radially inside the hub assembly, and the distal assembly and/or the proximal assembly has a strictly positive radial clearance (30).
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
F01D 5/30 - Fixation des aubes au rotorPieds de pales
The invention relates to a device for supplying electricity to at least one secondary electric load (30) on-board a turbine engine rotor (12) including a main circuit for transmitting main electric power to at least one main on-board electrical load (16), comprising a device (15) for rotatably and electrically connecting the stator and the rotor, and at least one secondary circuit for transmitting a secondary electric power including at least one secondary conductor (28) of the stator connected to a secondary electric power source (29) suitable for outputting a secondary power in the form of a power signal with a secondary frequency selected such as to enable selective, interference-free transmission of the secondary power via the rotary electric connection device (15), separately from the main power transmission.
H02J 3/34 - Dispositions pour le transfert de puissance électrique entre réseaux de fréquences très différentes
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
20.
Motorized device for opening and/or closing an aircraft door
A device for opening or closing an aircraft door includes an electric motor; a connector to connect the motor, and a driver. The driver includes a screw and nut system having a screw rotationally driven by the motor. The driver is configured to drive continuously and in sequence the connector with the door in a translational movement along one preset direction and then in rotational movement.
E05D 15/58 - Suspensions pour battants à mouvements successifs différents à mouvements aussi bien de "va-et-vient" que coulissant
E05F 15/611 - Mécanismes pour battants mus par une force motrice utilisant des actionneurs électriques utilisant des électromoteurs rotatifs pour battants pivotants
E05F 15/63 - Mécanismes pour battants mus par une force motrice utilisant des actionneurs électriques utilisant des électromoteurs rotatifs pour battants pivotants manœuvrés par bras pivotants
B64C 1/14 - FenêtresPortesTrappes d'évacuation ou panneaux de visiteStructures de cadres environnantsVerrièresPare-brise
Rotary-shaft brake system includes a rotary braking member attached to a rotary shaft, first and second friction members arranged on either side of the rotary braking member, each friction member being moveable between a first braking position when the friction members are in contact with the rotary braking member and a second idle position away from the rotary braking member, a bracket holding the friction members and guiding device and control device controlling movement of the friction members on the bracket. The control device comprises a linear actuator acting on at least a first lever and a solid elastically deformable element.
F16D 55/22 - Freins à surfaces de freinage substantiellement radiales pressées l'une contre l'autre dans une direction axiale, p. ex. freins à disques avec disques ou patins déplaçables selon l'axe pressés contre des organes en rotation situés dans l'axe par serrage entre des organes mobiles de freinage, p. ex. des disques ou des patins de freins mobiles
F16D 55/224 - Freins à surfaces de freinage substantiellement radiales pressées l'une contre l'autre dans une direction axiale, p. ex. freins à disques avec disques ou patins déplaçables selon l'axe pressés contre des organes en rotation situés dans l'axe par serrage entre des organes mobiles de freinage, p. ex. des disques ou des patins de freins mobiles avec un organe d'actionnement commun pour les organes de freinage
F16D 66/00 - Dispositions pour la surveillance des conditions de fonctionnement des freins, p. ex. de l'usure ou de la température
F16D 121/24 - Électrique ou magnétique utilisant des moteurs
The present invention relates to a device which comprises: a tubular body (2) and a first attachment means (6), a piston (30) provided with a rod (12) connected to a second attachment means (10), the piston (30) sliding inside the tubular body (2) and defining inside said body a working chamber filled with hydraulic fluid, an accumulator comprising a rigid shell (20) inside of which a separation means (40) is located, defining a compensation chamber (42) that is filled with hydraulic fluid and is in communication with the working chamber, and a chamber (47) filled with pressurised gas, the rigid shell (20) being a metal shell produced by means of welded assembly and the accumulator being made such as to obtain an entirely welded enclosure (47) containing the gas.
F16F 9/06 - Ressorts, amortisseurs de vibrations, amortisseurs de chocs ou amortisseurs de mouvement de structure similaire, utilisant un fluide ou moyen équivalent comme agent d'amortissement utilisant à la fois un gaz et un liquide
F15B 1/10 - Accumulateurs utilisant un coussin de gazDispositifs de remplissage de gazIndicateurs ou flotteurs à cet effet avec des moyens de séparation flexibles
B64C 1/14 - FenêtresPortesTrappes d'évacuation ou panneaux de visiteStructures de cadres environnantsVerrièresPare-brise
23.
DEVICE FOR COMBINING FORCE AMONG CONTROL UNITS, CONTROL UNIT AND AIRCRAFT
The invention relates to a device for combining force between two control units that comprises force feedback, each control unit comprising a control stick (21, 31) and at least one force sensor (24, 34) suitable for providing a value of the control force (Fp, Fcp) exerted by a pilot, the device being suitable for forming a force feedback value from the sum of the values of the control forces of each control unit. A correction device limits said force feedback value (Fcor_p) according to at least one parameter taken from the absolute value of the control force (Fcp) of said second control unit and the difference between the control force values of each control unit. The invention extends to a control unit comprising such a device for combining forces as well as to an aircraft provided with such control units.
G05G 5/03 - Moyens pour attirer l'attention de l'opérateur sur l'arrivée de l'organe de commande dans une position de commande ou de repèreCréation d'une sensation, p. ex. moyens pour générer une force antagoniste
G05G 11/00 - Mécanismes de commande manuelle équipés de plusieurs organes de commande travaillant avec un seul organe commandé
24.
Piloting device for piloting a vehicle, in particular an aircraft
A piloting device (1) for piloting a vehicle, in particular an aircraft, has a frame (10), a cradle (20) pivoting with respect to the frame on a first pivot axis (R), a piloting member, called a stick (30), pivoting with respect to the cradle (20) on a second axis (T) orthogonal to and intersecting the first axis, first return elements (11,11′,12) for returning the cradle to a predetermined position with respect to the frame, called the neutral position of the cradle, second return elements (21,21′,22) for returning the stick to a predetermined position with respect to the cradle, called the neutral position of the stick, wherein at least one of the second return elements, called a stick jack (22), is arranged between the stick and the frame.
G05G 9/047 - Mécanismes de commande manuelle équipés d'un seul organe de commande travaillant avec plusieurs organes commandés, p. ex. en sélection ou simultanément l'organe de commande étant manœuvré de différentes manières indépendantes, chacune de ces manœuvres individuelles entraînant un seul organe commandé dans lesquels la manœuvre de l'organe de commande peut être effectuée de plusieurs manières simultanément l'organe de commande étant manœuvré à la main autour d'axes orthogonaux, p. ex. manches à balai
B64C 13/04 - Dispositifs amorçant la mise en œuvre actionnés par l'homme
25.
Piloting device for piloting an aircraft having a protected force sensor
A piloting device for piloting an aircraft includes a piloting member (11), a mechanism (13) for mounting and guiding in rotation the piloting member about at least one rotation axis with respect to a frame (12), stops (25, 26, 35) arranged so as to cooperate with bearing surfaces (32) integral with the piloting member upstream of the mechanism in order to limit the rotation amplitude thereof, and at least one force sensor (19), these being arranged with respect to one another so that each contact of a bearing surface (32) with a stop (25, 26, 35) generates an abutment reaction, the orientation of which with respect to each deformable sensing element of each force sensor is such that it stresses this deformable sensing element at least substantially outside its deformation modes.
B64C 13/04 - Dispositifs amorçant la mise en œuvre actionnés par l'homme
G05G 5/04 - Butées pour limiter le mouvement des organes de commande, p. ex. butée réglable
G05G 9/047 - Mécanismes de commande manuelle équipés d'un seul organe de commande travaillant avec plusieurs organes commandés, p. ex. en sélection ou simultanément l'organe de commande étant manœuvré de différentes manières indépendantes, chacune de ces manœuvres individuelles entraînant un seul organe commandé dans lesquels la manœuvre de l'organe de commande peut être effectuée de plusieurs manières simultanément l'organe de commande étant manœuvré à la main autour d'axes orthogonaux, p. ex. manches à balai
26.
Propeller blade with reinforcing spars and boxes, and propeller comprising at least one such blade
b) in surface contact with the hollow casing (1) so as to provide structural support for the hollow casing (1), and at least two cavities (15, 16) which are spaced apart in the direction of the chord (25), wherein the propeller blade further comprises at least two reinforcing spars (6, 7) which extend between the framework and the hollow casing.
means for guiding the opening of the gate-valve via the pressurized fluid located in the chamber when the door is in the opening position, so as to open the exhaust pipe in order to set said chamber of the cylinder to atmospheric pressure in a rapid manner once the door is open.
F15B 11/048 - Systèmes comportant essentiellement des moyens particuliers pour commander la vitesse ou la puissance d'un organe de sortie pour commander la vitesse en fonction de la position de l'élément de travail avec commande de la décélération
28.
Aircraft hatch emergency opening actuator including opening delay means
an active position, in which the fluid means are injected at the point of the fluid circuit, means for delaying the injection of the fluid means into the cylinder including a mobile element in the fluid circuit, delaying opening of the circuit when the injection means are in the active position, the injection delay being determined by a time of movement of the mobile element.
The present invention relates to devices for damping the movement of a body Co between two positions at the end of travel. The device according to the invention is essentially characterized in that it comprises two abutments B1, B2, a cylinder 10, a wall 11 closing off the end 12 of the cylinder 10, a piston 14 delimiting a chamber 16 with variable volume, a cylinder 20 with an external section at most equal to the internal section of the cylinder 10, a mounting unit for mounting the cylinder 20 in cooperation with the piston 14 so that the latter closes off the end 21 of this cylinder 20, a piston 24 delimiting a chamber 26 with variable volume, a first fluid Li filling the two chambers 16, 26, a communicating unit 30 for communication under pressure loss between the chambers 16, 26, an abutment 40 mounted in cooperation with the piston 24 so that this abutment 40 has a movement correlative with that of the piston 24, and a connecting unit 50 for connecting the cylinder 20 to the body Co. Application notably to the control for opening and closing an aircraft door.
Actuator for gas-operated emergency opening of an openable element of an aircraft, having the ability to vent the gas. The actuator for emergency opening of an openable element of an aircraft includes a thrustor, a pressurised-gas reservoir where the gas reservoir having a membrane capable of being perforated in order to actuate said thrustor, a movable perforator arranged to perforate said membrane of said reservoir in order to release the gas into the thrustor via a first fluid circuit, and a venting circuit that vents, away from the thrustor, the gas contained in the reservoir, in the event of accidental rupture of said membrane, via a second fluid circuit which does not actuate said thrustor.
A device for piloting includes a piloting member connected to at least one member for driving the craft, an electromechanical support box including, for each pivot connection, at least one actuating motor of the piloting member constituted of an electromagnetic actuator including a movable armature integrally formed with the piloting member and equipped with at least one permanent magnet having a magnetic moment parallel to the axis of the pivot connection, and an electromagnetic circuit including a fixed armature, arranged to allow the movable armature to move in the air gap zone, the magnetic moment of the movable armature sweeping each radial surface portion, and at least one coil winding which is dependent in position on the fixed armature and is capable of generating electromagnetic torque on the movable armature.
a supply and measuring circuitry which is configured for selecting, for each detecting cell supplied with power, a predetermined value of a compensation coefficient Gk depending on the position in relation to the axis of rotation of this powered detecting cell, and for applying this compensation coefficient value Gk by modifying at least one intensity and/or voltage signal, such that errors caused by the radial offset are corrected.
G01B 7/30 - Dispositions pour la mesure caractérisées par l'utilisation de techniques électriques ou magnétiques pour mesurer des angles ou des cônesDispositions pour la mesure caractérisées par l'utilisation de techniques électriques ou magnétiques pour tester l'alignement des axes
33.
Electronic operational control device for a piloting member with cross-monitoring, piloting device and aircraft
An electronic operational control device for an aircraft piloting device with two connected piloting members, includes electronic circuits for main monitoring from signals delivered by sensors associated with one of the piloting members, and at least one electronic circuit (52 to 55) for cross-monitoring, for digital processing of signals delivered by sensors (83, 93) associated with the other piloting member, adapted to detect any deviation of these signals corresponding to a fault and to generate a signal representing such a fault. A piloting device and an aircraft including such an electronic operational control device with cross-monitoring are also disclosed.
The invention relates to a piloting device comprising a piloting component (10) which is connected to at least one steering component (13), at least one force sensor (17) which measures the forces imparted into the kinematic chain (12) by said piloting component (10), a logic circuit (23) which is adapted to develop a speed reference signal according to a predetermined function of said force signals, and a circuit for controlling at least one parallel actuator (14) as regards speed.
It extends to a method for the motorised assistance and control of a device of this kind and to an aircraft comprising a device of this kind.
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 1/08 - Commande de l'attitude, c. à d. élimination ou réduction des effets du roulis, du tangage ou des embardées
G05D 3/00 - Commande de la position ou de la direction
G06F 7/00 - Procédés ou dispositions pour le traitement de données en agissant sur l'ordre ou le contenu des données maniées
G06F 17/00 - Équipement ou méthodes de traitement de données ou de calcul numérique, spécialement adaptés à des fonctions spécifiques
brevets
