Airbus Operations Patente

Disclosed is a rib for an aircraft aerodynamic structure. The rib comprises a monolithic frame (30) that forms at least a majority of a perimeter of a space, and comprises first and second frame connectors. The space is between the first and second frame connectors. The rib comprises a replaceable strut (121, 122, 123, 124, 125, 126) having first (401, 403, 406, 408, 409, 412) and second (402, 404, 405, 407, 410, 411) ends that are releasably connected to the first and second frame connectors, respectively, so that the replaceable strut extends across the space.

Disclosed is an aircraft refuelling system, the aircraft refuelling system comprising: a fuel tank; a refuel connector; and a conduit extending between the refuel connector and the fuel tank configured to carry a fluid; wherein the aircraft refuelling system further comprises a flame arrester removably mounted to the refuel connector.

This cavity filling device (26) for a track (24) of a high lift system (16) is configured for being installed in a cavity (33, 36, 40) of the track (24) for obstructing said cavity (33, 36, 40), the cavity filling device (26) comprising an obstructing portion defining an obstruction face, the obstruction face being configured to be flush with a border (B) of the cavity (33, 36, 40) when the cavity filling device (26) is installed in said cavity (33, 36, 40).

A trolley arrangement (10, 10'), in particular for use in an aircraft cabin, comprises a trolley body (12) defining an interior space, a plurality of carriers (26) removably accommodated in the interior space of the trolley body (12), a plurality of heating devices (32, 32'), each heating device (32, 32') being associated with at least one of the plurality of carriers (26) and being configured to heat an item (28) arranged in at least a partial region (34a-c) of the carrier (26), a power distribution network (38) connectable to each of the heating devices (32, 32'), and a control unit (54) configured to receive an individual heating command for each of the heating devices (32, 32') and to control the power distribution network (38) so as to individually provide power to a selected one of the plurality of heating devices (32, 32') in response to a respective individual heating command.

The present invention relates to a computer system (100) and a computer-implemented method (300) for providing assistance data for at least one passenger-owned device (200) in an aircraft (10). The method (300) comprises providing (310), via an in-aircraft first data interface (112), real-time data indicative for at least one of an aircraft context and a cabin context of the aircraft (10). Alternatively or additionally, the method (300) comprises providing (320), via the first data interface (112) or via a ground-bound second data interface (120), static data descriptive for at least one of cabin characteristics of the aircraft (10) and in-flight service offerings. Further, the method (300) comprises processing (330), by at least one accessibility application (202) running on the at least one passenger-owned device (200), at least one of the real-time data and the static data to generate the assistance data.

A pipe assembly (100) comprising: a first rigid pipe section (110) having a first longitudinal axis (A1); a second rigid pipe section (120) having a second longitudinal axis (A2); and a flexible pipe section (130) attached to the first and second rigid pipe sections and configured to allow relative movement between the first rigid pipe section and the second rigid pipe section. The pipe assembly comprises a first sliding support (140) comprising a first joint section (142) fixed with respect to the first rigid pipe section and a second joint section (144) fixed with respect to the second rigid pipe section. The first joint section is configured to be in sliding contact with the second joint section during relative movement between the first rigid pipe section and the second rigid pipe section so as to limit axial misalignment between the first and second longitudinal axes. The pipe assembly comprises a second sliding support (150) comprising a third joint section (152) fixed with respect to the first rigid pipe section and a fourth joint section (154) fixed with respect to the second rigid pipe section. The third joint section is spaced apart from the fourth joint section in a first state. The third joint section is in sliding contact with the fourth joint section and maintains said sliding contact during relative movement between the first rigid pipe section and the second rigid pipe section so as to limit axial misalignment between the first and second longitudinal axes in a second state in which the first sliding support has failed.

A system for servicing a vacuum space in a hydrogen storage and distribution system of an aircraft is provided, the vacuum space being an interspace between a vessel and an insulated jacket, and having a vacuum valve communicating with the space. The system controls a vacuum pump arrangement using a sensor such as a microphone for sensing the pressure in the interspace, to equalise the pressure on the pump side of the valve with the vacuum space before opening the valve. This mitigates any damage to internal equipment which can result from high flow rates in the interspace.

L'invention a pour objet un procédé de détermination du niveau de contamination d'une surface (11) comprenant un recouvrement (E1) de tout ou partie d'une surface (11) par des gouttes de fluide incolore (12) ayant toutes sensiblement le même volume, lesdites gouttes (12) étant déposées sur ladite surface (11), selon un schéma de dépose défini en fonction des contraintes suivantes : la distance entre deux gouttes de fluide incolore (16) déposées successivement est sensiblement constante et chaque goutte de fluide incolore (16) est espacée d'une distance non nulle des autres gouttes de fluide incolores (16) l'entourant. Le procédé comprend également les étapes successives : acquisition (E2) d'une image de la surface (11) à analyser, une étape de calcul (E3), une étape de comparaison (E4) et une étape de décompte (E5) afin d'obtenir la position des gouttes (16) pour lesquelles la surface (11) sous lesdites gouttes (16) est dite contaminée.

Set (1) for a modular antenna arrangement (2) for an aircraft (50), comprising a base module (10) for connecting at least one plate shaped antenna element (20a, 20b) with a fuselage (51) of the aircraft (50), wherein the base module (10) has a bottom surface (11) mechanically connectable with the fuselage (51) of the aircraft (50) and a top surface (12) comprising at least one accommodation recess (13a, 13b) for accommodating, at least partially, the at least one plate shaped antenna element (20a, 20b); at least one interchangeable antenna adapter module (30a, 30b) connectable to the base module (10) and the at least one plate shaped antenna element (20a, 20b), wherein the interchangeable antenna adapter module (30a, 30b) is configured to be arranged in the accommodation recess (13a, 13b) between a bottom (14a, 14b) of the accommodation recess (13a, 13b) and the plate shaped antenna element (20a, 20b); and a cover module (40) configured for at least partially covering the base module (10), wherein the cover module (40) comprises at least one opening (41a, 41b), wherein an opening cross-section of the at least one opening (41a, 41b) is adapted to a cross-section of the at least one plate shaped antenna element (20a, 20b).

The present invention provides an actuation unit (1) in an aircraft wing (201a, b) comprising two actuators (2a, b) driving a hinged lever (3) rotatably mounted in an attachment structure (4) with the attachment structure (2) having a base plate (16) and a first and a second flange (12a, b) each including a through hole (11a, b) and extend-ing vertically with respect to the base plate (16), with a receiving space (15) for receiving an end portion of the lever (3) formed between the flanges (12a, b) , wherein a tube (5) rotatably supported in the through holes (11a, b) extends through the flanges (12a, b) and the lever end and projects on both sides of the flanges (12a, b), wherein the tube (5) comprises on its outer circumferential surface (18) an outer structure (8a) engaged with the lever end for transmitting torque and on its inner circumferential surface an inner spline structure (7) engaged with an outer spline structure (14) of output shafts (6a, b) of the actuators (2a, b) attached on the outer surfaces (17, 19) of the flanges (12a, b), a method of assembling an actuation unit (1), an aircraft wing and an aircraft having such wing.

The present invention provides an actuation and latching system (100) in an aircraft wing (201a, b) having a fixed wing part (12) and a wing tip (11) part foldable relative to the fixed wing part (12) about a hinge axis (30) aligned perpendicular to an aircraft wing (201a, b) longitudinal axis, comprising at least one tip actuation unit (9) providing an interface between the fixed wing part (12) and the foldable wing tip (11) having hinge levers (5); at least one latching unit (7) arranged in the fixed wing part (12), wherein the at least one latching unit (7) comprises two latching bolts (8a, b) displaceable in opposite directions parallel to the hinge axis (30), wherein said latching bolts (8a, b) can be brought into engagement with the hinge levers (5) extending into the latching unit (7); a drive unit (101) arranged in the fixed wing part (12) and axially down-stream of the latching unit (7) with the drive unit (101) having at least a first drive shaft (3) coupled to the latching unit (7) and a second drive shaft (4) passing through the latching unit (7) and coupled to the tip actuation unit (9); and a control unit (13) for controlling the drive unit (101), a method for extending the foldable wing tip (11) part of an aircraft wing (201a, b), an aircraft wing (201a, b) and an aircraft (200) having such wing (201a, b) .

The present invention provides a latching unit (1) in an aircraft wing (201a, b) having a fixed wing part (202a, b) and a hinged wing tip (204a, b) foldable about a hinge axis, comprising a first latching actuator (3a) driven by a drive unit arranged within the fixed wing part (202a, b) and coupled to a first latching bolt (7a) and a second latching actuator (3b) coupled to a second latching bolt (7b) with both latching bolts (7a, b) configured for locking or unlocking hinge levers (10) extending into the latching unit (1),wherein the latching actuators (3a, b) comprise hollow screw shafts (6a, b) having threaded rods (8a, b) extending in opposite directions from adjacent ends (15a, b) of the hollow screw shafts (6a, b) and engaging with threaded elements (24a, b) provided in end portions (25a, b) of the respective latching bolts (7a, b), and wherein the latching bolts (7a, b) are movable in opposite axial directions into a locking or unlocking position by rotation of the threaded rods (8a, b), an aircraft wing (201a, b) and an aircraft (200) having such wing (201a, b) .

An aircraft wing, comprising: a fixed wing 12 an outboard wing section 14; and a hinge assembly 52 connecting the outboard wing section to the fixed wing. The wing is configurable between a flight configuration and a ground configuration. The hinge assembly 52 comprises: a fore set of interleaving lugs 58 and an aft set of interleaving lugs 58; an actuator, such as a Geared Rotary Actuator (GRA) 66, located between the fore set of lugs and the aft set of lugs. The wing also comprises: a latch assembly 68, located in the fixed wing and inboard of the actuator 66; a fore latching arm 74 and an aft latching arm 76. The latch assembly 68 comprises an aft latch pin 72, deployable in the aft direction to latch the aft latching arm 76, and a fore latch pin 74, deployable in a forward direction, to latch the fore latching arm 74.

The invention relates to a protection device, comprising:- at least one head protection cover (18) configured to cover at least one printhead (12.1) of a printing device (12),- at least one frame (24),- at least one flexible connection system (26) connecting the head protection cover (18) and the frame (24),- at least one automatic fastening system (28) configured to connect the frame (24) and the printing device (12).This solution allows automatic mounting of the protective cover on the corresponding printhead.The invention also relates to an item of printing equipment including at least one protection device.

The present invention relates to an aircraft fuselage construction (14) featuring a detachable fuselage part (32) designed to facilitate access to an accommodation space (34) for installing and removing liquid hydrogen (LH2) tanks (36) or other equipment. The fuselage construction (14) includes a fuselage section (27). A fuselage opening (38) is provided in the fuselage section (27), enabling the installation of the detachable fuselage part (32) via a mounting arrangement (40). The mounting arrangement (40) includes a bearing support system (44) allowing linear movement along the longitudinal axis of the aircraft (10) and a locking system (48) securing the detachable fuselage part (32) in place. The detachable fuselage part (32) is designed to maintain structural integrity and aerodynamic continuity when installed while providing easy removal for maintenance or equipment replacement. The invention ensures efficient handling of large tanks or equipment, optimizing operational efficiency and reducing aircraft modification complexity.

A method of configuring a collision avoidance system (3) for a vehicle (1), such as an aircraft, for warning an operating person (P) of the vehicle (1), such as a pilot, of a collision potential (U) with an object (O), such as another aircraft, a corresponding computer program (11), computer-readable data carrier (12), control module (6), collision avoidance system (3), and vehicle, in particular an aircraft, provided, wherein the method comprises the steps of detecting the object (O) with the collision avoidance system (3), determining the collision potential (U), and issuing a warning signal (I) to the operating person (P) if the collision potential (U) exceeds a predetermined potential threshold (T).

A method of configuring a collision avoidance system (3) for a vehicle (1), such as an aircraft, for warning an operating person (P) of the vehicle (1), such as a pilot, of a collision potential (U) with an object (O), such as another aircraft, a corresponding computer program (11), computer-readable data carrier (12), control module (6), collision avoidance system (3), and vehicle, in particular an aircraft, provided, wherein the method comprises the steps of detecting the object (O) with the collision avoidance system (3), determining the distance value (D), and issuing the distance value (D) to the operating person (P) if the collision potential (U) exceeds a predetermined potential threshold (T).

The present invention relates to an electrode device.In order to provide an improved thermal management of a battery system, the electrode device (10), comprises a support structure (12), an electroactive structure (14) and a heat transfer structure (16). The support structure is configured for carrying the electroactive structure and the heat transfer structure. The electroactive structure is configured for storing and releasing of charge carriers (18). The heat conductivity of the heat transfer structure is higher than the heat conductivity of any of the support structure or the electroactive structure. The electroactive structure is arranged at the support structure. The heat transfer structure is arranged at the electroactive structure. The heat transfer structure is oriented to guide heat (20) away from a surface (22) of the electroactive structure to prevent thermal tensions (24) in its vicinity while providing diffusivity of the charge carriers to the surface

Disclosed is a hydrogen tank 100, 100a, 100b, 100c, 100d of or for an aircraft, the hydrogen tank comprising an inner hull 30 bordering a tank space I to be filled with liquid hydrogen, an outer hull 10, 10a, 10b, 10c, 10d encasing the inner hull 30 with an insulation layer 20 in-between, and a tank reinforcement structure 40, 40a, 40b, 40c, 40d. The tank reinforcement structure 40, 40a, 40b, 40c, 40d comprises one or various rib/s 41₁, 41₂, 41₃, 41'₃, 41a₁, 41a₂, 41a₃, 41b₁, 41b₂, 41c₁, 41c₂, 41d₁ which is/are attached to the outer hull 10, 10a, 10b, 10c, 10d and/or to the inner hull 30, and which include/s a lattice configuration forming an energy absorbing structure.Further disclosed are a method of producing such hydrogen tank, and a fuselage comprising such hydrogen tank.

Die vorliegende Offenbarung betrifft ein Leitungssystem für ein luftförderndes System in einem Flugzeug, wobei das Leitungssystem eine Mehrzahl von Leitungen (110) und eine Stirnplatte (120) umfasst. die Stirnplatte verbindet die Mehrzahl von Leitungen so, dass sie mindestens paarweise aneinander anliegend angeordnet sind und miteinander verbunden sind. Die Mehrzahl von Leitungen sind zu dem aus einem biegesteifen und isolierenden Material hergestellt. Ferner betrifft die vorliegende Offenbarung ein luftförderndes System mit solch einem Leitungssystem sowie ein Flugzeug mit solch einem luftfördernden System.

Disclosed is an aircraft tyre comprising a circumferential surface, wherein the circumferential surface is centred on a rotation axis, is configured to roll along the ground in use about the rotation axis, and comprises at least one first area and at least one second area circumferentially offset from the at least one first area, the at least one first area and the at least one second area having different respective friction coefficients, measured in respective parallel directions that each have at least a component parallel to the rotation axis, with respect to a material of the ground.

Method and device for repairing an element (100) of composite material, the method comprising infusing a resin (300) into the internal damaged area (101) of the element (100) of composite material, wherein the method further comprises: drilling on the element (100) of composite material at least one first non-through hole (200a) and at least one second non-through hole (200b), each of the non-through holes (200) running from one face of the element (100) of composite material up to the internal damaged area (101), and infusing the resin (300) from the at least one first non-through hole (200a) until the resin (300) fills at least the internal damaged area (101) of the element (100) of composite material. The method comprises applying vibrations at a given frequency to the element (100) of composite material.

- Procédé et système pour augmenter la précision du suivi d'une trajectoire par un outil d'un robot.- Le procédé comprend notamment une étape d'acquisition de données, au cours de laquelle le robot (2) exécute la trajectoire souhaitée sans que l'outil (3) réalise la tâche qui lui est assignée et un dispositif de mesure inertielle (10) effectue des mesures inertielles représentatives de petites imprécisions répétables de la trajectoire, ainsi qu'une étape d'opération au cours de laquelle le robot (2) exécute de nouveau la même trajectoire, l'outil (3) réalise la tâche qui lui est assignée, et on commande des actionneurs (9) pour compenser des imprécisions de l'outil (3), en tenant compte du traitement desdites mesures inertielles, réalisé par un dispositif informatique (13), ce qui permet de minimiser de petites imprécisions de trajectoire de faibles amplitudes de l'outil (3), sans avoir à agir sur la trajectoire du robot (2), et ainsi d'augmenter la précision du suivi d'une trajectoire lisse.

The present disclosure relates to an unpressurised bay compartment (10) in an aircraft, comprising a ventilation system (100). The ventilation system includes a single air inlet (110) in an outer skin (2) of the aircraft, two ducts (131, 132), a conveying device (50) arranged in the first duct (131), a duct furcation (134), where the first duct and the second duct (132) branch off from one another upstream of the conveying device (50), a duct junction (135), where the first duct (131) and the second duct (132) join one another downstream of the conveying device, and a valve (150) arranged in the first duct (131) between the duct furcation (134) and the conveying device (50).

The present disclosure relates to a water supply unit (100) for an aircraft, and an aircraft comprising the same. Particularly, the water supply unit (100) combines a heating device (120) with means (130, 140) to provide water of a controlled temperature.

An aircraft pylon mounting fitting (10a; 10b) comprising a connecting portion (12a; 12b) and a clevis portion (14a; 14b), the clevis portion (14a; 14b) being integrally formed with the connecting portion (12a; 12b), wherein the connecting portion (12a; 12b) comprises a plurality of holes (13) for attaching the connecting portion (12a; 12b) to an aircraft wing structure, tail structure or fuselage structure, and wherein the clevis portion (14a; 14b) comprises mutually-opposing first and second fork parts (16a, 17a; 16b, 17b) arranged to receive a lug (32a; 32b) of a pylon (30) therebetween, the first fork part (16a; 16b) incorporating a first bore (18a; 18b) and the second fork part (17a; 17b) incorporating a second bore, the first and second bores being configured to receive a pin or bolt for attaching the clevis portion (14a; 14b) to the lug (32a; 32b) of the pylon (30); wherein at least the first bore (18a; 18b) incorporates an eccentric bush (20a; 20b).Also provided is an aircraft wing-to-pylon subassembly comprising: a wing structure; a pylon (30); and a pylon mounting fitting (10a; 10b) as outlined above, wherein the connecting portion (12a; 12b) is attached to the wing structure and the clevis portion (14a; 14b) is attached to a lug (32a; 32b) of the pylon (30) by a pin or bolt passing through the first and second bores and the lug (32a; 32b) of the pylon (30). Aircraft tail-to-pylon and fuselage-to-pylon subassemblies are similarly provided.An aircraft (40) comprising one or more such subassemblies is also provided, as is a method of constructing such a subassembly.

The present disclosure relates to an unpressurised bay compartment (10) in an aircraft, comprising a ventilation system (100). The ventilation system includes a single air inlet (110) in an outer skin (2) of the aircraft, two ducts (131, 132), a conveying device (50) arranged in the first duct (131), a duct furcation (134), where the first duct and the second duct (132) branch off from one another upstream of the conveying device (50), a duct junction (135), where the first duct (131) and the second duct (132) join one another downstream of the conveying device, and a valve (150) arranged in the first duct (131) between the duct furcation (134) and the conveying device (50).

The present invention relates to an aircraft fuel delivery system having a first tank for storing a first fluid, second tank for storing a second fluid and a shut-off valve. The shut-off valve comprises a first inlet port for introducing the first fluid into an internal valve chamber and a second inlet port for introducing the second fluid into the internal valve chamber such that the second fluid can be combined with the first fluid to create a fluid mixture. The shut-off valve also comprises a valve member the position of which can be adjusted for controlling the delivery of the first fluid and/or the fluid mixture to the aircraft power plant.

An aircraft wing arrangement (1, 101, 201, 302) is provided. The aircraft wing arrangement comprises a wing skin (2), a first set (8) of stringer(s) (8A-E) for providing support to the wing skin, and extending from a first region (5) of the wing skin to a second region (6) of the wing skin; and a second set (9) of stringer(s) (9A-E) for providing support to the wing skin, and extending from a third region (7) of the wing skin to the second region of the wing skin. The second region of the wing skin is between the first and third regions of the wing skin. At least one stringer of the first set of stringers overlaps with at least one adjacent stringer of the second set of stringers in the second region of the wing skin. An aircraft wing (20, 20') and an aircraft (25) are also provided.

The present invention provides a flat tubular solid oxide fuel cell unit (10), comprising: a porous metal support structure (11) having at least one fuel channel (12) that extends through the porous metal support structure (11) in a longitudinal direction (X) of the porous metal support structure (11); an anode layer (13) that covers the porous metal support structure (11); an electrolyte layer (15) applied on a shell surface of the porous metal support structure (11) covered by the anode layer (13); and a cathode layer (17) applied on the electrolyte layer (15). Further the present invention provides a solid oxide fuel cell stack module (1) for an aircraft comprising such a flat tubular solid oxide fuel cell unit (10).

In order to reduce environmental impact, the invention provides, in an embodiment, landing gear (6) for an aircraft (1), the landing gear (6) comprising a strut (8), a wheel axle (9) coupled to the strut (8), and at least one wheel (11) connected to the wheel axle (9) and a torque converter (10) coupled to the wheel axle (9) so as to drive the wheel axle (9).

This high lift system architecture (22), comprises: - a first rotational sensor (46), configured to be installed on a torque transmission arrangement (24) and to measure a first angular position (A1) of the torque transmission arrangement (24), at a first measurement point (M1); - a second rotational sensor (48), configured to be installed on the torque transmission arrangement (24) and to measure a second angular position (A2) of the torque transmission arrangement (24), at a second measurement point (M2); and - an actuation control device (50), comprising: + an acquisition module (56), configured for acquiring the first angular position (A1) from the first rotational sensor (46) and the second angular position (A2) from the second rotational sensor (48), and + a determination module (58), configured for determining a torque (T) applied to the torque transmission arrangement (24) as a function of said acquired first (A1) and second (A2) angular positions.

This actuation control device (30) for a high lift system (16), comprises: - an acquisition module (46), configured for acquiring a first output torque (OT1), of a first high lift system actuator (24A); - a comparison module (48), configured for comparing the acquired first output torque (OT1) to at least one predetermined first threshold torque (TT1); and - a determination module (50), configured for determining a monitoring signal (M) depending on the comparison of the acquired first output torque (OT1) to the at least one predetermined first threshold torque (TT1).

The present disclosure relates to a potable water connection (100) for a water consumer in an aircraft and comprises a main body (110) having an outer thread (112), a male fitting (120) configured to be coupled to the water consumer, a connector (130) configured to be coupled to a potable water supply means (190), and a nut plate (180) threaded onto the outer thread (112). The present disclosure further relates to an aircraft monument and an aircraft having such potable water connection.

This High lift system monitoring arrangement (24) comprises: - at least one sensor (32), - a monitoring unit (34), connected to the at least one sensor (32), the monitoring unit (34) comprising: + an acquisition module (46), configured for acquiring an analogous sensed information (Al) from the at least one sensor (32), + a processing module (48), comprising a first processing circuitry (48A) and a second processing circuitry (48B), different from the first circuitry, wherein the first processing circuitry (48A) is configured to process the analogous sensed information (Al) into a first digital sensor data (DD1), the second processing circuitry (48B) being configured to process the analogous sensed information (Al) into a second digital sensor data (DD2).

Proposed is a method for providing connectivity between a personal electronic device (110), PED, and a networked output device in an aircraft. The method comprises providing an encapsulated subnetwork within a wireless network of the aircraft. The subnetwork is dedicated to the networked output device (120). The method further comprises providing, via the networked output device (120), configuration information configured to provide access to the subnetwork for the PED (110). The subnetwork is configured to provide connectivity between the networked output device (120) and the PED (110) when the subnetwork is accessed by the PED (110) using the configuration information.

Provided is a cabin management device (10) for an aircraft cabin space. The device comprises a sensor (12); a microcontroller (14), data-connected with the sensor (12); and an output (16), data-connected with the microcontroller (14). The sensor (12) is configured to collect a plurality of distance data across a predetermined part of the cabin space (30) at a plurality of points in time and to transmit the distance data to the microcontroller (14). The microcontroller (14) is configured to evaluate the distance data by a comparison of the distance data collected at one point in time with distance data collected at another point in time and to generate space-related data based on the comparison, and to transmit the space-related data to the output (16). And the output (16) is configured to provide information about a current spatial situation based on the transmitted space-related data.

This high lift system architecture (22) comprises: - an actuation arrangement (24), configured to move at least one moveable surface (20); - a sensor (26), configured to generate an analog sensed signal representative of a configuration of the moveable surface (20); - a flight control computer (28); and - an actuation control device (30) comprising: + an acquisition module (42) for acquiring the analog sensed signal, + a processing module (44) for processing the analog sensed signal and for generating an analog controlling signal based on the processed analog sensed signal, + a conversion module (46) for converting the analog sensed signal into a digitalized monitoring signal, + a control module (48) for controlling the actuation arrangement (24) based on the generated analog controlling signal, and + a communication module (50) for communicating the digitalized monitoring signal to the flight control computer (28)

An actuation assembly (10) is provided, The actuation assembly (10) comprises a control unit (40), a monitoring unit (50), at least one high voltage power supply (32), at least one low voltage power supply (34) and at least two power bridges (60a, 60b). The at least one low voltage power supply (34) is configured to be connected to a source to provide power to the control unit (40) and to the monitoring unit (50), wherein the control unit (40) and the monitoring unit (50) are configured to monitor elements of a sub-system comprising at least one of an electric motor, a brake or a sensor. The at least one high voltage power supply (32) is configured to be connected to a source to provide power to each of the at least two power bridges (60a, 60b). And the at least two power bridges (60a, 60b) are each configured to be coupled with an electric motor.

- Method and system for determining an optimized set of ink colours used to print a pattern on an object - The method comprises in particular steps implemented by a computer device for defining a plurality of sets of different colours in a colour space (19), each of which consists, on the one hand, of spot colours that make it possible to reproduce one or more sensitive colours (C6, C7) of the reference pattern to be printed continuously and exactly and, on the other hand, of process colours intended to be used to produce colour combinations, so as to be able to obtain all of the colours (C1, C2, C3, C4, C5) of the reference pattern to be printed, other than the one or more sensitive colours (C6, C7), in the livery, and for selecting one of these sets of colours taking into account at least one selection criterion, in order to obtain a set of colours that is optimized in particular in terms of precision and/or ink consumption.