Airbus Operations

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)

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.

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.

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 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.

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).

An aircraft (1) with a first tank (20) suitable for containing fuel, a second tank (30) suitable for containing a second, different fuel or fuel additive, a first fuel line (22) configured to transport the fuel from the first tank to a mixer (50), a pump (62) arrangement configured to drive a flow of fuel from the first tank along the first fuel line and a second fuel line (32) configured to transport the second, different fuel or fuel additive from the second tank to the mixer. The mixer is configured to mix the fuel and second, different fuel or fuel additive to form a blended fuel. The aircraft also includes a mixer line (52) configured to transport the blended fuel from the mixer to a combustor (40).

A high lift arrangement for an aircraft wing comprises a high lift element arranged to have a deployed position wherein the high lift element extends in front of at least an inboard portion of a leading edge of the wing tip. The high lift element has a sweep angle which is less than the sweep angle of the wing tip, such that a gap is formed between the element and the wing tip. A vortex is generated at the tip of the high lift element to energise the wing tip upper surface boundary layer. The gap accelerates the flow, improving low speed performance of the wing.