Airbus Operations Gmbh

Airbus Operations (s.a.s.)

Airbus (sas)

Airbus Operationa (sas)

George Howell

Stephen Bernard Pollard

Louis-Emmanuel Romana

Ashley Bidmead

Andrew Hebborn

Florian Becher

Matthieu Della Nave

Nicholas Crane

Andrea Laruelo-fernandez

Benjamin Kerr

Joy Au

Steve David

Laia Navarro

Louis Emmanuel Romana

James Bullen

Livier Ben

Florian F Becher

Andrea Laurelo-Fernandez

An aircraft control system () including an aircraft control module () and a test module (). The aircraft control module includes a memory storing a machine learning model () adapted, based on received live aircraft operating inputs (-), to generate live aircraft control outputs (-). The test module () includes a memory storing input data representing test aircraft operating inputs ('-′) and respective output data representing expected aircraft control outputs () that are expected to be generated by the aircraft control module in response to an input of the respective test aircraft operating inputs (′-′). The test module () is adapted to write test aircraft operating inputs (′-′) to the aircraft control module, read test aircraft control outputs (′-′) of the aircraft control module (), and remove the authority of the aircraft control module () to perform aircraft control.

Aircraft control system

An aircraft landing event system including a processor communicatively coupled with memory storing aircraft landing event data. The processor is configured to receive environment information representative of an environmental condition of a runway approached by an aircraft and receive retardation information representative of a retardation demand of the aircraft during an anticipated landing event of the aircraft on the runway. The processor is further configured to select aircraft landing event data from the memory based on the environment information and the retardation information and determine a performance indicator for the landing event based on the aircraft landing event data selected by the processor. The processor is further configured to communicate the performance indicator to a landing system of the aircraft.

Aircraft landing event system and method

An aircraft landing event system is disclosed including a processor, the processor being configured to receive aircraft braking performance information from a plurality of aircraft that have performed a landing event on a particular runway. The processor is configured to determine an aircraft braking performance indicator on the basis of the aircraft braking performance information of the plurality of aircraft, and communicate the aircraft braking performance indicator to an aircraft landing system of an approaching aircraft that is about to perform a landing event on the particular runway.

A monitoring systemfor an aircraftincluding a controllerto determine, based on one or more conditions, one or more expected operating characteristics of a steering system of the aircraft. The one or more conditions include one or more aircraft conditions indicative of an internal condition of the aircraft and/or one or more external conditions indicative of an external influence on the aircraft. The controller compares the one or more expected operating characteristics with the one or more actual operating characteristics. The controller is configured to determine, based on the compare, whether to issue a signal indicating a condition of the aircraft. An avionics systemcomprising the monitoring system, an aircraft comprising the monitoring system or the avionics system, and a methodof monitoring an aircraft.

Monitoring system for an aircraft

An aircraft control system () including an aircraft control module (), a trained classifier module (), and an aircraft control processing engine (). The aircraft control module () generates first control outputs (to) based on received aircraft operating inputs (to). The trained classifier module receives the aircraft operating inputs (to) and generates second control outputs (to). The aircraft control processing engine () receives the first control outputs (to) and the second control outputs (to) and generates operating control outputs (to), based on the received first control outputs and second control outputs. The aircraft control processing engine () then controls the aircraft using the operating control outputs (to).

Control system

A method of landing an aircraft in which the aircraft receives information from a second aircraft via a direct aircraft-to-aircraft communication from the second aircraft to the aircraft; determines a landing plan of the aircraft based on the information; and lands the aircraft based on the landing plan. The use of a direct aircraft-to-aircraft communication (i.e. a communication from the second aircraft to the first aircraft which does not travel via an intermediary such as a land station, air traffic controller or satellite) makes the method reliable because such a communication is inherently secure and difficult to hack.

Method of landing an aircraft

An aircraft control system () including an input interface (), an output interface () and a processing engine () having a classifier () that applies input data () generated by the input interface () to generate output control data (). The classifier () has a plurality of parameters which represent a control policy for operating the aircraft (). The output interface () generates control outputs to control the aircraft () based on the output control data (). A machine learning system () for training the classifier () including an environment (), a pathway evaluation engine (), storage (), and a training engine (). The machine learning system () generates training data () by selecting a pathway representing an operating procedure using the pathway evaluation engine (). The training engine () trains the classifier () using the training data ().

Scenario-based control system

An aircraft controller, aircraft braking systemand method for determining braking parameters. The aircraft controlleris configured to determine information associated with an aircraft taxiing route associated with an aircraft. On the basis of the information, the aircraft controllerdetermines a first braking parameter for a first main landing gearof the aircraftand a second braking parameter for a second main landing gearof the aircraftduring a landing event. The first and second braking parameters are determined to result in asymmetrical braking between the firstand secondmain landing gears during the landing event.

Aircraft braking system

An aircraft braking system for an aircraft, the aircraft including first and second brakes, and first and second energy distribution systems for delivering energy to the first and second brakes to operate the respective first and second brakes. The aircraft braking system is switchable between: a first configuration, in which the first energy distribution system is coupled to the first brake and is isolated from the second brake, and the second energy distribution system is coupled to the second brake and is isolated from the first brake; and a second configuration, in which the first energy distribution system is coupled to both the first and second brakes.

Braking system

A speed determination system for an aircraft including one or more interfaces arranged to receive first speed data from a first speed measurement system and second speed data from a second speed measurement system. The first speed measurement system provides the first speed data using global positioning system data. The second speed measurement system provides the second speed data based on a second speed measurement. The speed determination system includes a processor arranged to determine whether the data received from the first speed measurement system is reliable. If global positioning data is determined to be reliable, the speed determination system determines a speed from the first speed data and determines correction values for the second speed measurement system. If global positioning data is determined to be unreliable, the speed determination system determines a speed from the second speed data and the correction values.

Speed determination system

An aircraft braking controller for an aircraft, the aircraft braking controller configured to determine a position of at least a part of a landing gear of the aircraft during retraction of the landing gear into the aircraft, and control braking of a wheel of the landing gear based on the position determined.

Aircraft braking controller and system

An aircraft system having a first set of components for performing a function of the aircraft system, and a second, alternative, set of components for performing the function of the aircraft system. The aircraft system has and a controller configured to receive scenario data indicative of a scenario during which the function of the aircraft system is to be performed, and, where each of the first and second sets of components are operational, the controller is configured to select between the first or the second set of components to perform the aircraft system function during the scenario based on the received scenario data. The controller is configured to control the selected set of components to perform the function during the scenario.

Aircraft system

A method of testing a system model is disclosed. The system model includes a system parameter and three or more equipment models, each equipment model includes an equipment parameter which models a parameter of a respective equipment. The method includes (a) making a series of changes of the equipment parameter of one of the equipment models so that the equipment parameter of the one of the equipment models adopts a series of test values of the equipment parameter; (b) operating the system model to determine a series of test values of the system parameter, each test value of the system parameter is determined in accordance with a respective one of the test values of the equipment parameter; (c) determining a weight of the selected one of the equipment models, the weight of the one of the equipment models indicates a sensitivity of the system parameter to the series of changes in the equipment parameter of the one of the equipment models; and (d) outputting the weight of the one of the equipment models.

Method of testing a system model

A hydraulic systemfor an aircraft including a backup hydraulic pressure sourceto provide hydraulic pressure to a brakein the event of a failure condition of a primary hydraulic brake pressure source. The hydraulic systemalso includes a landing gear backup system to provide hydraulic pressure to enable extension and/or retraction of landing gear. The backup hydraulic pressure sourceis arranged to provide hydraulic pressure to the landing gear backup system in the event of a failure condition of a primary landing gear hydraulic pressure source.

Aircraft hydraulics

A method of controlling the motion of a turning aircraft during taxiing on the ground, the aircraft having a steerable landing gear, for example a nose landing gear, operating in a free-to-caster mode, includes (a) ascertaining the rotational position (&#x398;) of the steerable landing gear relative to the longitudinal axis (L) of the aircraft (b) receiving a control instruction that would, if effected, continue turning of the aircraft in the same direction away from the longitudinal axis, and (c) modifying the control instruction so that the angle between the rotational position of the steerable landing gear and the longitudinal axis will be lower than the angle that would otherwise be observed had the control instruction been effected and not so modified. The risk of damage to the steerable landing gear through over-steering may thus be reduced.

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Bristol, United Kingdom

George Howell