Abstract: An avionics network comprises at least one data bus system, a multiplicity of network subscribers connected to one or more of the data bus systems via network interfaces, a central configuration server configured to configure each of the multiplicity of network subscribers individually according to a predefined functionality, and a synchronization note configured to stipulate a work-cycle for the multiplicity of network subscribers via the at least one data bus system according to a stipulated synchronization protocol.

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: 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: An access system for a vehicle is provided. The access system includes a central rights management unit, an access control device, and a portable identification medium. The access control device makes it possible to run verification mechanisms on the identification medium with the use of input means for interacting with a user. To this effect the identification medium includes an authentication unit and also a data part that depends on it which for viral epidemic propagation of privilege data may forward this data to access control devices without its own data connection. Even in the case of an incomplete infrastructure, extensive vehicle movements and very substantial fluctuations in personnel it is nevertheless possible to achieve very high security and reliability of enabling access and vehicle functions.

Abstract: An access system for a vehicle is provided. The access system includes a central rights management unit, an access control device, and a portable identification medium. The access control device makes it possible to run verification mechanisms on the identification medium with the use of input means for interacting with a user. To this effect the identification medium includes an authentication unit and also a data part that depends on it which for viral epidemic propagation of privilege data may forward this data to access control devices without its own data connection. Even in the case of an incomplete infrastructure, extensive vehicle movements and very substantial fluctuations in personnel it is nevertheless possible to achieve very high security and reliability of enabling access and vehicle functions.

Abstract: The control system of an aircraft including at least two communication networks and a controlled device control unit connected to one of them. The system determines control commands for the device with a DAL-A quality assurance level requirement and includes a set of at least three physical units each including at least two computers, an electrical power supply and a network interface device. The electrical power supplies, and the network interface devices, are of at least three different types, the computers are of at least two different types and include operating systems of at least two different types; the computers each have a DAL-C, DAL-D or DAL-E hardware and/or software quality assurance level and at least six of the computers are configured to independently determine control commands for the device. A DAL-A hardware and software quality assurance level selection logic unit is configured to select valid control commands used by the control unit to control the device.

Abstract: The control system of an aircraft including at least two communication networks and a controlled device control unit connected to one of them. The system determines control commands for the device with a DAL-A quality assurance level requirement and includes a set of at least three physical units each including at least two computers, an electrical power supply and a network interface device. The electrical power supplies, and the network interface devices, are of at least three different types, the computers are of at least two different types and include operating systems of at least two different types; the computers each have a DAL-C, DAL-D or DAL-E hardware and/or software quality assurance level and at least six of the computers are configured to independently determine control commands for the device. A DAL-A hardware and software quality assurance level selection logic unit is configured to select valid control commands used by the control unit to control the device.

Abstract: A flight attendant panel, in which a plurality of computer units can be coupled to a common input/output device by a circuitry. One of the computer units is designated as the master computer unit and controls the circuitry in order to specify which of the computer units should be coupled to the input/output device. The actuation of a switch makes it possible to once again return the flight attendant panel into an original state, in which the master computer unit is coupled to the input/output device by the circuitry.

Abstract: A flight attendant panel, in which a plurality of computer units can be coupled to a common input/output device by a circuitry. One of the computer units is designated as the master computer unit and controls the circuitry in order to specify which of the computer units should be coupled to the input/output device. The actuation of a switch makes it possible to once again return the flight attendant panel into an original state, in which the master computer unit is coupled to the input/output device by the circuitry.

Abstract: The rails (10) or switch components are scanned with one or more eddy-current inspection probe(s) (20) and the measured signal of the probe(s) is plotted as a function of position. The probe(s) (20) is/are seated on a measuring head, which is guided along the rail (10). A GPS unit (26) equipped with a gyro module (32) is used as the position-signal generator.