Airbus Germany

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).

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.

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.

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).

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.

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 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)

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).

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.

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.