The invention relates to a communication system for an air control centre, comprising a first public communication channel, a second secure communication channel, at least one voice communication device for exchanging voice data on each of the two communication channels, at least one management station comprising a control interface and a display interface and designed to manage the voice data exchanges and to control the branching of the voice data into each of the two communication channels, a first stand-alone processing module and a second stand-alone processing module for generating a display in a secure manner on said display interface.

An aircraft data interface function (ADIF) server system comprises a processing module that hosts an aircraft condition monitoring function, comprising an airline modifiable information database including a history buffer and one or more logic units; a management information base (MIB) database; a parameter snapshot database; and a simple network management protocol (SNMP) agent in communication with the MIB database and parameter snapshot database. A core network unit communicates with the SNMP agent and an SNMP manager in an ADIF client. The SNMP agent sends messages to and receives messages from the SNMP manager through the core network unit. The ADIF server system interfaces with one or more avionics systems through a common data network to obtain and store aircraft parameter information. The ADIF client is configured via the core network unit to interact with the ADIF server system to request and receive the aircraft parameter information.

A control system for an engine includes a distributed control module configured to be associated with a sensor of the engine, a digital link, and a communication control. The distributed control module is connected to the communication control via the digital link. The communication control includes a bus communication engine configured to communicate with the engine control via a bus, and a memory. The memory includes a first buffer that is associated with the distributed control module and a second buffer that is associated with the bus communication engine.

An onboard communication network of an aircraft and communication system. The onboard communication network of an aircraft is a deterministic switched Ethernet network including a set of subscribers and at least one switch. It uses virtual links, each defined between a transmitting subscriber and one or more receiving subscribers. The at least one switch includes a communication port configured for communicating with at least one equipment external to the aircraft; and the communication network is configured such that at least one of the virtual links is transmitted though this communication port so as to transmit the information exchanged between subscribers to the network to the equipment external to the aircraft by the virtual link

A pin-configurable bus termination system may includes a bus connector attached to an end of a bus. The bus connector may be configured for electrically connecting the bus to an input connector of a node. The node may include a bus termination resistance. The bus connector may include a first bus output pin, a second bus output pin and configurable first and second termination resistor pins. The configurable first and second termination resistor pins may be configurable to provide a first termination configuration and a second termination configuration. The first termination configuration may electrically interconnect the first and second bus output pins arid the configurable first and second termination resistor pins to electrically connect the bus termination resistance for terminating the bus. The second termination configuration may include an open electrical circuit between the first and second bus output pins and the configurable first and second termination resistor pins.

An avionics network including a plurality of avionics components and a configuration monitoring device, which is connected by wire or wirelessly to the plurality of avionics components. The configuration monitoring device has at least one configuration data interface configured to receive a plurality of configuration parameters characterizing the operating status of the avionics components. The configuration monitoring device further includes a parameter filtering device connected to the configuration data interface and configured to filter a subset of the configuration parameters received. The configuration monitoring device additionally includes reference parameter storage, configured to store sets of reference values for configuration parameters, and a parameter comparison device, coupled to the reference parameter storage and the parameter filtering device, and configured to compare the subset of configuration parameters received and filtered by the parameter filtering device with a set of reference values for the configuration parameters stored in the reference parameter storage.

A flight control system for an aircraft comprises a flight control computer system connected via a bus system with a plurality of bus nodes, which each are configured to at least one of controlling an associated aircraft device based on command messages received from the flight control computer system via the bus system and sending information messages to the flight control computer system via the bus system. The bus system is a redundant bus system comprising plural independent bus sub-systems, wherein each bus node is configured to communicate with the flight control computer system via two different bus sub-systems, wherein each bus node further is configured to communicate with the flight control computer system on basis of an associated predetermined bus communication protocol via a first bus sub-system and on basis of an associated predetermined bus communication protocol via a second bus sub-system.

An example embodiment includes a plurality of flight modules including a primary flight module and a secondary flight module. The embodiment includes a CAN controller, a second CAN controller, a first CAN bus configured to transmit primary control signals from the first CAN controller to the primary flight module and to the secondary flight module, and a second CAN bus configured to transmit secondary control signals from the second CAN controller to the primary flight module and the secondary flight module. The primary flight module is configured to perform functions responsive to receiving the primary control signals, and not in response to receiving the secondary control signals and the secondary flight module is configured to perform functions responsive to receiving the secondary control signals, and not in response to receiving the primary control signals.

Control systems and methods for securely authenticating and validating a control system. The control system may include a plurality of dependent control nodes and master control nodes. Each dependent control node is communicatively coupled to one or more peripheral devices. Each control node maintains a unit level distributed ledger, where each unit level distributed ledger includes information from corresponding peripheral devices. Each control node may transmit a portion of the unit level distributed ledger to a master control node. Each master control node may maintain a system level distributed ledger that includes information from the corresponding unit level distributed ledgers. Each master node may transmit a portion of the system level distributed ledger to a central node that maintains a separate secure distributed ledger. The master node may authenticate the control system based on the received portion of the system level distributed ledgers and the secure distributed ledgers.

The present invention relates to a method for verifying the integrity of data transmission between a main upstream unit (10a) and a main downstream unit (20a), the method being characterised in that it includes the implementation of the following steps: a data-processing module (11a) of the main upstream unit (10a) generates a first frame (T1) including a packet (P1) of data to be transmitted and a cyclic redundancy code (E1) of said packet (P1); encapsulating the first frame (T1) in a second frame (T2) which also includes a cyclic redundancy code (C1) of the first frame (T1); encapsulating the cyclic redundancy code (E1) of the packet (P1) in a third frame (T3); the data-processing module (11b) of the at least one auxiliary upstream unit (10b) compares each of the cyclic redundancy codes (E1) extracted from the first frame (T1) with those extracted from the third frame (T3); and confirming the integrity of data transmission to the main downstream unit (20a) only if the comparison is positive.