Airbus Operations Patente

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The invention provides an aircraft wing, comprising a fixed wing (14) and a wing tip device (12) at the tip. The wing tip device (12) is configurable between: (i) a locked flight configuration for use during flight and (ii) a ground configuration for use during ground-based operations. The wing further comprises a locking mechanism for locking the folding wing tip device (12) in the locked flight configuration. A rotatable locking member (22, 22') is associated with one of the folding wing tip device (12) and the fixed wing (14), and a locking pin (32) associated with the other. The rotatable locking member (22, 22') comprises a guide surface to guide the locking pin to a locked configuration, in which the guide surface is shaped such that the locking pin (32) is urged toward the rotation axis of the rotatable locking member (22, 22') by a camming action of the guide surface on the locking pin (32), thereby preloading the locking mechanism.

The present invention provides a data network, especially a data network for an aircraft or spacecraft, comprising a primary data grid, and at least one secondary data grid, the primary data grid comprising primary data nodes, wherein the primary data nodes are directly or indirectly coupled in data communication with each other, and the at least one secondary data grid comprising secondary data nodes, wherein the at least one secondary data grid is configured to connect the secondary data nodes in a data communication chain and to connect the first secondary data node of the data communication chain to a first respective primary data node and/or the last secondary data node of the data communication chain to a second respective primary data node. Furthermore, the present invention provides an aircraft or spacecraft and a corresponding method.

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A pressure bulkhead system (10) comprises a pressure bulkhead (1) which is adapted to be connected to a fuselage (2) of a vehicle order to separate a pressurized cabin space (12) of the vehicle from an unpressurized cabin space (14) of the vehicle, and a peripheral pressure frame (3) for sealingly connecting the pressure bulkhead (1) to the fuselage (2) of the vehicle. The peripheral pressure frame (3) comprises an attachment section (31) which is sealingly attached to an outer rim portion of a first surface (18) of the pressure bulkhead (1), wherein the first surface (18), when the pressure bulkhead system (10) is installed in the vehicle, faces the unpressurized cabin space (14) of the vehicle, a flange section (33) which is adapted to be sealingly attached to an inner surface of the vehicle fuselage (2) and which extends in a direction facing away from the first surface (18) of the pressure bulkhead (1), and a flexible section (34, 32, 35; 39) which interconnects the attachment section (31) and the flange section (33) and which is flexible to accommodate cabin pressure acting on the pressure bulkhead (1).

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Described and claimed is a method for transmitting continuously created data items from an aircraft to a receiver. The data items are of a plurality of data types and each have a different priority. For each data type a live LIFO buffer and a main LIFO buffer are provided. In a regular operation mode continuously created data items are continuously stored in the main buffers. In a transmission operation mode continuously created data items are continuously stored in the live buffers, consecutive data packets are transmitted and for each data packet the data is selected from the buffers, wherein data items stored in live buffers are transmitted before data items stored in main buffers and data items of higher priorities are transmitted before data items of lower priorities. Further, a transmitter and an aircraft are described and claimed.

The present invention relates to a network for an aircraft (1), comprising a data line (3), and at least two network access devices (4), comprising a first interface (9) and at least one second interface (10) and being connected to the data line (3) via the first interface (9). Identifiers are assigned to the second interfaces (10) in pairs. The network access devices (4) are adapted to receive and/or transmit data via the first interface (9) in first data frames (5) having a fixed format and comprising a first portion (17) and second portions (18) following the first portion (17), the first and second portions (17, 18) having predefined lengths and locations within the first data frame (5). The network access devices (4) are to transmit in the first data frames (5) a sequence of second data frames (12) and, for each second interface (10), a sequence of third data frames (13a, 13b) received on the second interfaces (10), wherein the network access device (4) includes a first processing unit (7) adapted to insert the second data frames (12) in the first portion (17) of the first data frames (5), split each third data frame (13a, 13b) into a plurality of fragment frames (20a, 20b), including a part (19a, 19b) of the respective third data frame (13a, 13b) and reassembly information allowing regeneration of the third data frame (13a, 13b) from the fragment frames (20a, 20b), and insert the fragment frames (20a, 20b) into the second portions (18). The network access devices (4) are also adapted to process received first data frames (5) by extracting the second data frame (12) and the fragment frames (20a, 20b), to regenerate the corresponding third data frames (13a, 13b), and to output the regenerated third data frames (13a, 13b) on corresponding second interface (10).

The present invention relates to a network for an aircraft, comprising a master device and a plurality of slave devices (3a, 3b, 3c) connected in series in a daisy-chain arrangement. Each of the slave devices (3a, 3b, 3c) has an associated unique identifier taken from a predetermined ordered sequence of identifiers. The master device (2) is adapted to transmit polling data packets (8) along the series of slave devices (3a, 3b, 3c), each including one and only one identifier, and the polling data packets (8) are transmitted in successive sequences, each including for each of the slave devices (3a, 3b, 3c) one and only one polling data packet (8) and including the polling data packets (8) in the order defined by the predetermined sequence of identifiers. Each of the slave devices (3a, 3b, 3c) comprises a first data interface (4) for connection in an upstream direction, a second data interface (5) for connection in the downstream direction, and a processing unit (6) adapted to compare for each received polling data packet (8) the identifier thereof with the identifier of the respective slave device (3a, 3b, 3c), and output a response data packet (9) to the master device (2) if the two identifiers match, and forward the polling data packet (8) to the second interface (5) at least if the two identifiers do not match. Each processing unit (6) comprises an adjustable time delay element (7) adapted to delay the output of the response data packets (9) by an adjustable delay period (19). For each of the slave devices (3a, 3b, 3c) the delay period (19) is set to a value depending on the relative position of the respective slave device (3a, 3b, 3c) in the daisy-chain arrangement, such that it continuously decreases from slave device (3a, 3b, 3c) to slave device (3a, 3b, 3c).

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Air supply system (10) comprising at least two bleed sources (12) configured to provide bleed air (14), wherein each bleed source comprises an engine (12a) or an auxiliary power unit (12b) and an oil as lubricant for the engine or the auxiliary power unit; at least one air conditioning pack (16) for cooling the bleed air from the bleed sources; and a plurality of bleed ducts (18), wherein each bleed duct connects one of the bleed sources to the at least one air conditioning pack, characterized in that the system further comprises a plurality of detectors (20), wherein each detector is associated with a bleed source and the plurality of detectors are configured for detecting substances specific for the oil.

The invention is an inlet system (300) for an Auxiliary Power Systems ("APS") (200), the said inlet system (300) comprising: - an inlet (310) having an entrance aperture (313) able to receive a flow (F) from an airstream, - at least an APU air intake duct connection (318, 418a, 418b) able to drive the flow (F) directly to client functions of the APS (200), - a divider (215) positioned inside the inlet (310), able to divide the flow (F) to feed in air each client function of the APS (200), the divider (215) being a deflector able to move inside the inlet (310) defining variable geometry channels (316a, 316b), in order to guide, optimize and regulate dynamically the flow (F) according to the volume and/or rate of flow (F) required by each active client function of the APS (200).

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The present invention provides to a system (1) for producing components of composite material, and especially elongate or continuous components of fibre-reinforced polymer. In this regard, the system (1) comprises: a winding mechanism (4) for winding an elongate sheet (3) of composite material about a winding axis (X) that is at an angle (²) to a perpendicular to a longitudinal axis (L) of the elongate sheet (3) so as to form a helical coil (5) of wound sheet (3); a mechanism for drawing or conveying the helical coil (5) of wound sheet (3) along a process path (P), wherein the process path (P) is preferably substantially parallel to the winding axis (X); and a shaping mechanism (10) for forming or shaping the coil (5) of wound sheet (3) as it is drawn or conveyed along the process path (P). In addition, the present invention provides a corresponding method of producing a composite component.

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