Abstract: The modular element for a hybrid electrical power distribution and data communication network of an aircraft comprises a section of a bus and a set of data links extending substantially parallel along a length of the modular element. The bus section comprises connection points at different locations distributed along its length. The set of data links comprises connection points at different locations distributed along its length, each arranged in proximity to a connection point of the bus section. It also comprises a data link between each of the connection points and a cross-connect point. The bus section and the set of data links comprise interconnection points making it possible to link the modular element to first and second, other, modular elements arranged longitudinally in series with the modular element.

Abstract: An aircraft comprises a fuselage, a set of electrical equipment items distributed in the fuselage, and a hybrid electrical power distribution and data communication network. The latter comprises a set of buses comprising at least one electrical power distribution bus extending, at least partly, in a longitudinal direction of the fuselage. A set of data links is associated with each bus of the set of buses. The bus and the associated set of data links each comprise connection points at different locations distributed along their length, forming pairs of connection points. Each of the electrical equipment items of the set of electrical equipment items is linked to a pair of connection points via a local electrical power supply link and/or via a local data link.

Abstract: A base module and an aviation computer system having the base module includes a printed circuit board, an integrated power supply and communication connector, a SMARC connector, and an FMC connector. A power supply circuit supplies the SMARC connector and the FMC connector with power from dedicated power supply contacts of the integrated power supply and communication connector, and a communication circuit connects the SMARC connector to dedicated communication contacts of the integrated power supply and communication connector. In addition, signal lines are provided on the printed circuit board in order to connect dedicated input/output contacts of the SMARC connector to corresponding dedicated input/output contacts of the FMC connector.

Abstract: The modular element for a hybrid electrical power distribution and data communication network of an aircraft comprises a section of a bus and a set of data links extending substantially parallel along a length of the modular element. The bus section comprises connection points at different locations distributed along its length. The set of data links comprises connection points at different locations distributed along its length, each arranged in proximity to a connection point of the bus section. It also comprises a data link between each of the connection points and a cross-connect point. The bus section and the set of data links comprise interconnection points making it possible to link the modular element to first and second, other, modular elements arranged longitudinally in series with the modular element.

Abstract: An aircraft comprises a fuselage, a set of electrical equipment items distributed in the fuselage, and a hybrid electrical power distribution and data communication network. The latter comprises a set of buses comprising at least one electrical power distribution bus extending, at least partly, in a longitudinal direction of the fuselage. A set of data links is associated with each bus of the set of buses. The bus and the associated set of data links each comprise connection points at different locations distributed along their length, forming pairs of connection points. Each of the electrical equipment items of the set of electrical equipment items is linked to a pair of connection points via a local electrical power supply link and/or via a local data link.

Abstract: A base module and an aviation computer system having the base module includes a printed circuit board, an integrated power supply and communication connector, a SMARC connector, and an FMC connector. A power supply circuit supplies the SMARC connector and the FMC connector with power from dedicated power supply contacts of the integrated power supply and communication connector, and a communication circuit connects the SMARC connector to dedicated communication contacts of the integrated power supply and communication connector. In addition, signal lines are provided on the printed circuit board in order to connect dedicated input/output contacts of the SMARC connector to corresponding dedicated input/output contacts of the FMC connector.

Abstract: A passenger seat device for a vehicle cabin comprises a front end and a rear end, a backrest arranged at the rear end, a plurality of seat surface segments extending from the rear end to the front end and a seat frame for carrying the seat surface segments and the backrest. The seat surface segments are arranged in a side-by-side relationship and constitute a seat surface and the seat surface segments are individually adjustable between at least two different vertical positions relative to the seat frame. The passenger seat device may flexibly seat passengers with different constitutions.

Abstract: A data network, especially a data network for an aircraft or spacecraft, includes a primary data grid, and at least one secondary data grid, the primary data grid including 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.

Abstract: A passenger seat device for a vehicle cabin comprises a front end and a rear end, a backrest arranged at the rear end, a plurality of seat surface segments extending from the rear end to the front end and a seat frame for carrying the seat surface segments and the backrest. The seat surface segments are arranged in a side-by-side relationship and constitute a seat surface and the seat surface segments are individually adjustable between at least two different vertical positions relative to the seat frame. The passenger seat device may flexibly seat passengers with different constitutions.

Abstract: A data network, especially a data network for an aircraft or spacecraft, includes a primary data grid, and at least one secondary data grid, the primary data grid including 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.

Abstract: An aircraft structure is provided with load-bearing hollow structural elements that form an aircraft fuselage. The cavities in the structural elements are designed as air ducts for an air conditioning system of the aircraft. An aircraft is also provided with such an aircraft structure.

Abstract: An aircraft structure is provided that includes, but is not limited to structural elements, a first multitude of lines that are in a fixed manner connected to structural elements, a second multitude of lines that are in a fixed manner connected to structural elements and whose longitudinal direction intersects the longitudinal direction of the first multitude of lines so that the longitudinal directions of the lines form a network that covers the aircraft structure at least in some sections, and connecting elements in order to, in the state of the structural elements installed in the aircraft structure, connect selected lines of the first multitude to selected lines of the second multitude of selected points of intersection of the network in order to in this way form transmission lines, such as lines for electricity transmission and/or data transmission. Furthermore, a method is provided for manufacturing such an aircraft structure.

Abstract: An aircraft structure is provided with load-bearing hollow structural elements that form an aircraft fuselage. The cavities in the structural elements are designed as air ducts for an air conditioning system of the aircraft. An aircraft is also provided with such an aircraft structure.

Abstract: An aircraft structure is provided that includes, but is not limited to structural elements, a first multitude of lines that are in a fixed manner connected to structural elements, a second multitude of lines that are in a fixed manner connected to structural elements and whose longitudinal direction intersects the longitudinal direction of the first multitude of lines so that the longitudinal directions of the lines form a network that covers the aircraft structure at least in some sections, and connecting elements in order to, in the state of the structural elements installed in the aircraft structure, connect selected lines of the first multitude to selected lines of the second multitude of selected points of intersection of the network in order to in this way form transmission lines, such as lines for electricity transmission and/or data transmission. Furthermore, a method is provided for manufacturing such an aircraft structure.

Abstract: A window arrangement is provided for enlarging a window area in an aircraft. The window arrangement includes, but is not limited to at least one first installation element. The at least one first installation element is designed to convey fluids, and furthermore includes, but is not limited to a transparent region which covers a first window region such that light waves in the visible spectrum can be let through.

Abstract: The present invention relates to a window arrangement for enlarging a window area in an aircraft, wherein said window arrangement comprises at least one first installation element. The at least one first installation element is designed to convey fluids, and furthermore comprises a transparent region which covers a first window region such that light waves in the visible spectrum can be let through.

Abstract: A fibre optic connector assembly includes first and second parts (1, 2) that can be physically connected together and separated from one another. Each connector part (1, 2) including a plurality of fibres (3, 4), each for optical connection to a respective fibre of the other part. A housing (8) is provided within the assembly, the housing defining a plurality of passageways for housing respective optical connections of the fibres (3, 4) of the first and second connector parts (1, 2) and for maintaining the fibres of each each optical connection in alignment. The housing (8) is tethered to the first connector part (1) by an elongate flexible member (15).

Abstract: A fibre optic connector assembly includes first and second parts (1, 2) that can be physically connected together and separated from one another. Each connector part (1, 2) including a plurality of fibres (3, 4), each for optical connection to a respective fibre of the other part. A housing (8) is provided within the assembly, the housing defining a plurality of passageways for housing respective optical connections of the fibres (3, 4) of the first and second connector parts (1, 2) and for maintaining the fibres of each optical connection in alignment. The housing (8) is tethered to the first connector part (1) by an elongate flexible member (15).