Aircraft fly-by-wire systems and related vehicle electrical systems are provided. A vehicle electrical system includes a bus arrangement having a plurality of buses, a first control module coupled to a first subset of the buses, a second control module coupled to a second subset of the buses, and a third control module coupled to a third subset of the buses. The first subset includes a first bus, a second bus, a third bus, and a fourth bus, the second subset includes the third bus, the fourth bus, a fifth bus, and a sixth bus, and the third subset includes the first bus, the second bus, the fifth bus and the sixth bus.

An avionics mounting unit includes a housing with a first mounting interface to couple the housing to a structure of an aircraft and a second mounting interface to couple an avionics device to the housing. The second mounting interface includes slots oriented orthogonal to each other and extending to sides of the housing such that the avionics device can be installed via the slots from any of four sides of the housing. The avionics mounting unit also includes communication circuitry, power supply circuitry, one or more avionics device interface ports, and one or more aircraft interface ports. The avionics device interface port(s) are configured to provide power to the avionics device and configured to enable data communications with the avionics device. The aircraft interface port(s) are configured to receive power from the aircraft and to enable data communications between other aircraft systems and the avionics device.

A method of communication, within a processing system of a gas turbine engine, between a first electronic component and a second electronic component, comprising: generating by the first electronic component, a request, comprising a digital certificate, intern comprising a first host public key and a first client public key, signed with a first host private key, to initiate a trusted communication session with a second electronic component; encrypting at the first electronic component, at least a portion of the request with a first client private key; transmitting the request to the second electronic component; the first host private key and the first host public key defining a first asymmetric keypair and the first client private key and the first client public key defining a second asymmetric keypair.

An aircraft comprising a first power supply such as a battery, avionics including a plurality of sensors that provide aircraft parameter information, a transceiver and a gateway. The gateway includes a processing system and is coupled to the first power supply, avionics and transceiver. The gateway is configured to operate in a first mode to receive from the transceiver a remote wake request initiated by a user of a remote communication device, power on at least portions of the avionics in response to the received remote wake request by causing the first power supply to be coupled to the at least portions of the avionics, receive aircraft parameter information from the powered on portions of the avionics, and provide the received aircraft parameter information to the transceiver for transmission from the aircraft, optionally to the user of the remote communication device.

A system for time synchronization over redundant switch-based avionics networks is disclosed. The system includes a master or source clock for determining precise UTC timing information from received satellite signals and generating time marks based on the timing information. The source clock generates network-compatible timing messages and forwards the timing messages to network switches within the switch-based avionics networks. The network switches modify the timing information to account for switch-based delays and forward the modified timing messages to destination clocks in aircraft end systems. The end systems relay timing messages back to the source clock via the network switches, the timing information again modified by the network switches according to switch-based delays, and based on the precise timing information exchanged destination clocks in end systems throughout the switched network can precisely synchronize to the source clock.

A system and method for compiling and monitoring a list of operational aircraft components to determine if a threshold is met. Utilizing the list and the threshold can provide for monitoring the network of aircraft components to monitor both health and security of the aircraft network and components thereof. The system can then indicate or alert when a threshold is met or exceeded. Such an alert can be on a display to a pilot, for example, or to a remote monitoring station.

An aircraft comprising a first power supply such as a battery, avionics including a plurality of sensors that provide aircraft parameter information, a transceiver and a gateway. The gateway includes a processing system and is coupled to the first power supply, avionics and transceiver. The gateway is configured to operate in a first mode to receive from the transceiver a remote wake request initiated by a user of a remote communication device, power on at least portions of the avionics in response to the received remote wake request by causing the first power supply to be coupled to the at least portions of the avionics, receive aircraft parameter information from the powered on portions of the avionics, and provide the received aircraft parameter information to the transceiver for transmission from the aircraft, optionally to the user of the remote communication device.

Aircraft fly-by-wire systems and related vehicle electrical systems are provided. In one embodiment, an electrical system suitable for use with a control surface of a vehicle, such as an aircraft, is provided. The electrical system includes a plurality of communications buses and a plurality of control modules, wherein each of the plurality of control modules is connected to a respective subset of the plurality of communications buses that is unique among the plurality of control modules, and a plurality of actuation control modules associated with the control surface, wherein each of the plurality of actuation control modules is connected to a respective subset of the plurality of communications buses that is unique among the plurality of actuation control modules. Thus, each of the control modules is isolated from at least one of the communications buses.

A method that includes operating a bus monitoring system having at least one interface configured to be coupled to at least one communication bus and receive bus traffic transmitted over the communication bus(es). The method also includes, using a device authentication system of the bus monitoring system, analyzing the bus traffic received via the at least one interface. Analyzing the bus traffic includes obtaining a message in the bus traffic (where the message identifies a source), identifying a support vector machine that corresponds to the source of the message, applying a wave transform to a waveform of the received message in order to generate a transformed waveform, inputting the transformed waveform to the identified support vector machine, and taking action in response to the identified support vector machine determining that the transformed waveform or the associated information does not correspond to the source.

A system includes an avionics power bus network, switch, and data concentrator. The avionics power bus network provides power to at least a first endpoint system and second endpoint system coupled via at least one network pathway configured for transmitting a data packet between the first and second endpoint and is operably connected to the switch. The switch is configured to receive a data packet from the first endpoint and transmit the data packet along the network pathway to the second endpoint and is configured to receive power from the avionics power bus network. The data concentrator is operably connected the first endpoint to receive the data packet from the first endpoint and is operably connected to the switch through a wire. The wire is configured to transmit power from the switch to the data concentrator and to transmit the data packet from the data concentrator to the switch.