Airbus Operations Patente

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Disclosed is a valve comprising a valve housing (210) defining a valve chamber (220). A valve member (250) is rotatably mounted in the valve chamber. The valve comprises a drive member (340) in the valve housing, the drive member coupled to the valve member and linearly movable relative to the valve housing to cause rotation of the valve member. The valve comprises a linkage located in the housing for translating a linear motion of the drive member to a rotating motion of the valve member.

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A navigation system (10) for navigating an autonomous mobile robot (100) in an environment (1) is provided. The navigation system (10) comprises at least one optical sensor (110) attached to the autonomous mobile robot (100), a controller (120) in communication with the at least one optical sensor (110), and a plurality of optical identifiers (2) distributed within the environment (1) at fixed locations and detectable by the at least one optical sensor (110). Each of the plurality of optical identifiers (2) encodes a location within the environment (1). The controller (120) is configured to obtain pictures of the environment (1) via the at least one optical sensor (110), detect visible optical identifiers (2) of the plurality of optical identifiers (2), which are within a field of view of the at least one optical sensor (110), decode the visible optical identifiers (2), and navigate the autonomous mobile robot (100) based on real-time localizations of the autonomous mobile robot (100) within the environment (1) using the decoded visible optical identifiers (2).

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The invention relates to a method (100) and system (50) for real-time determining required characteristics for junction of at least two hollow components (10, 12) defining at least one joining area (14) between each of the at least two hollow components (10, 12) during an alignment process, by measuring the at least one joining area (14) in a single measuring step and relative from the inside of a first (12) of the at least two hollow components (10, 12), comprising the following steps:Providing (102) at least two hollow components (10, 12), wherein the at least two hollow components (10, 12) are adapted to be joined and wherein the at least two hollow components (10, 12) are at least partially dimensionally unstable,Providing (104) a scanning device (16), wherein the scanning device (16) is adapted to contactless scan the at least two hollow components (10, 12) in a single measuring step, Arranging (106) the scanning device (16) in a rigid manner inside of the first hollow component (10) of the at least two hollow components (10, 12) in line of sight of the at least one joining area (14),Scanning (108) the at least one joining area (14) in a single measuring step to receive scan data to determine required characteristics for junction of the at least two hollow components (10, 12),Output (110) the scan data and the corresponding required characteristics for junction the at least two hollow components (10, 12).

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A fairing (10), in particular for an aircraft, comprises a wall element (12) comprising an inner surface (16) and an outer surface (14), wherein the outer surface (14) is exposed to a free air flow (F) outside the fairing (10), and at least one stiffener element (18) attached to the inner surface (16) of the wall element (12), to keep the fairing in shape under dynamic pressure loads. The fairing (10) comprises at least one air inlet device (22) comprising an inlet opening (26) to allow a part of the free air flow (F) outside the fairing (10) to pass through the wall element (12) and to enter the interior of the fairing (10). The air inlet device (22) is at least partially integrated into the stiffener element (18), and the inlet opening (26) of the air inlet device (22) is formed in the stiffener element (18) and extends into or through the stiffener element (18). The air inlet device (22) and the stiffener element (18) may be integrally formed as one single part, preferably by 3D printing.

The present disclosure relates to a fuel cell system (100) capable of defreezing a dedicated component (120) by guiding a coolant via a coolant branch line (125, 126) from a fuel cell stack 110 to the dedicated component (120). Further disclosed is a vehicle comprising such fuel cell system.

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The present invention relates to a user interface onboard an aircraft. In order to provide a facilitated way of providing information to a user, a method (100) for generating a spatially selective user interface on surface parts in an aircraft cabin is provided that comprises the following steps: selecting (102) a user perspective for a location in an aircraft cabin interior; determining (104) a graphic appearance as an interface content for the selected user perspective; projecting (106) the determined graphic appearance onto predetermined visible surfaces of the aircraft cabin interior; determining (108) visual appearances for the predetermined visible surfaces, based on the projected determined graphic appearance, to generate the determined graphic appearance for the selected user perspective; and providing (110) the predetermined visible surfaces with the determined visual appearances.

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In order to allow a monument and an overhead storage bin to be mounted on a vehicle the invention proposes a fastening structure (3) which is mountable on an attachment structure (2) of an interior of a vehicle (100) and which comprises at last one first module (10) for the monument, at least one second module (10) for the overhead storage bin and a spacer module (40) arranged between the first module (10) and the second module (10). The first module (10) and the second module (10) each comprise an elongate body (17), a first strut (19) detachably coupled between the elongate body (17) and a first fastening (20) for fastening the module (10) to the attachment structure (2) and a second strut (21) that is detachably coupled between the elongate body (17) and the first fastening (20) and that extends at an inclined angle to the elongate body (17). The spacer module (40) comprises an elongate spacer body (41), a first elongate interface strut (42) having a second fastening for fastening the spacer module (40) to the attachment structure (2) and a second interface strut (43) having a third fastening for fastening the spacer module (40) to the attachment structure (2). The elongate spacer body (41) is detachably coupled by a third strut (52) to the first interface strut (42) at a first joint (53) intermediate the length of the first interface strut (42) and is detachably coupled by a fourth strut (54) to the second interface strut (43) at a second joint (55) intermediate the length of the second interface strut (43).

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An aircraft (101) includes a ground manoeuvre control unit (226) for automatically controlling ground manoeuvres. The aircraft (101) has control mechanisms (230) such as a rudder, nose wheel steering, spoilers, wheel brakes (110a and 110b) and the like for controlling motion of the aircraft (101). The control unit (226) is configured to receive lateral input demands (220) concerning lateral motion of the aircraft (e.g. heading control) and longitudinal input demands (222) concerning longitudinal motion of the aircraft (e.g. deceleration). The control unit (226) passes on the input demands (220, 222) as output demands (228) to the relevant control mechanisms (230) of the aircraft (101) with, if so required, a modification which prioritises one of the lateral input demand (220) and longitudinal input demand (222) based on the risk of a lateral runway excursion and the risk of a longitudinal runway excursion (232).

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