Airbus

In order to provide a power supply circuit which reliably functions in a cryogenic environment, the invention provides a power supply (10) for producing electrically isolated auxiliary supply voltages at cryogenic temperatures. The power supply (10) comprising an input power supply (11) supplying electric power to a power stage (14), an oscillation circuit (19) coupled to the power stage (14) and a transformer (20) comprising at least one primary winding (21) and at least one secondary winding (22). The primary winding (21) is coupled to a capacitive half bridge (23) and the secondary winding (22) is coupled to a plurality of outputs, each output comprising a rectifier (27) and an auxiliary supply terminal (28).

The present invention relates to method (M) for operating an autonomous certificate management system for technical devices placed in a vehicle, particularly in an aircraft (100), comprising: providing in a vehicle an onboard certificate management system (OCMS) (1) which is designed to be coupled with at least one technical device (4) to be placed within the vehicle, providing to the OCMS (1) a respective list of information from respective technical devices (4) to be placed in the vehicle, qualifying respective technical devices (4) to be placed within the vehicle with a certificate signing request method (5) which is designed to determine at least one unique information about the respective technical device (4) and to transmit a created certificate signing request (CSR) comprising the at least one unique information to the OCMS (1), creation and transmission of a digital certificate by the OCMS (1) to the respective technical device (4) depending on a comparison of stored and received information about the respective technical device (4) in the OCMS (1) carried out by the OCMS (1). In addition, a system (2) for vehicles and an aircraft (100) according to the invention are presented.

The present invention provides an optical terminal (1) for lidar and optical communication, comprising a transmitter section (2), including a first transmitter unit (21) configured to emit a first communication signal (211) at a first wavelength, a second transmitter unit (22) configured to emit a first quantum signal (221) at a second wavelength; and a receiver section (3), including a first receiver unit (31) configured to receive a second communication signal (311) at a third wavelength, a second receiver unit (32) configured to receive a lidar signal (321) at the first wavelength, and a controller (4) configured to control an emission of the first transmitter unit (21) and the second transmitter unit (22), extract data from the received communication signal (311), and determine a time-of-flight of the lidar signal (321) based on the emission of the first communication signal (211). Further, the present invention provides a corresponding method for operating an optical terminal (1).

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.

In order to provide a compact lightweight transformer for use at cryogenic temperatures, the transformer comprises a ferrite core with an air gap and comprising a relative permeability at 77K, µ_r(77K), wherein 50 ≤ µ_r (77K) ≤ 1000, at least one primary winding and at least one secondary winding.

There is disclosed an apparatus for monitoring electrical aircraft components, the apparatus comprising: a pulse generator configured to transmit an electrical pulse to an electrical bus, the electrical bus being electrically connected to a plurality of loads; a pulse receiver configured to receive a reflection of the transmitted electrical pulse from the electrical bus; and a processor configured to: perform a wavelet transformation on the received reflected pulse to identify a plurality of component signals of the reflected pulse; identify an electrical condition associated with the plurality of loads based on the transformed reflection of the electrical pulse, and identify a load associated with the identified electrical condition based on a component signal associated with said load.

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).

L'invention concerne un moteur supraconducteur (100) comportant un rotor (102) portant des aimants permanents (110) et mobiles en rotation autour d'un axe longitudinal (X), un stator (103) traversé par des orifices (116) répartis autour du rotor (102), et pour chaque orifice (116), deux bobines (150) constituées d'un matériau supraconducteur et alimentées électriquement pour générer un champ magnétique, où chaque bobine (150) comporte une première section rectiligne (152a) traversant ledit orifice (116), une deuxième section rectiligne (152b) traversant un autre orifice (116), et deux sections courbes (154a-b) où chacune relie entre elles une extrémité de la première section rectiligne (152a) et une extrémité de la deuxième section rectiligne (152b), où les sections rectilignes (152a) des deux bobines (150) traversant ledit orifice (116) sont empilées radialement. La disposition particulière des bobines permet de limiter les pertes.

- 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.