公开(公告)号：US20240025563A1

公开(公告)日：2024-01-25

申请号：US18347336

申请日：2023-07-05

Applicant: Airbus Operations Limited ,  Airbus Operations (S.A.S)

Inventor： George HOWELL ,  Ting Yu AU ,  Jonathan COOPER ,  Asier PEREZ ,  Laura CAPELLERAS MAGANA ,  David James SCOTT ,  Sushmita GUDIMELLA

IPC: B64F5/60 ,  B64C25/42 ,  G06N20/00

CPC classification number: B64F5/60 ,  B64C25/42 ,  G06N20/00

Abstract: A test apparatus and method for testing a trained classifier configured to control an aircraft system. Scenario data includes operating inputs representing an operational state of an aircraft and classifier outputs for controlling the aircraft system, is obtained. Model data representing a model of the at aircraft system is obtained. Error categorisation data for each aircraft operating scenario is generated based on respective classifier outputs applied to the model.

公开(公告)号：US20220358849A1

公开(公告)日：2022-11-10

申请号：US17732019

申请日：2022-04-28

Applicant: AIRBUS OPERATIONS LIMITED ,  Airbus SAS

Inventor： George HOWELL ,  Andrew HEBBORN ,  James BULLEN ,  Andrea LARUELO-FERNANDEZ

IPC: G08G5/06 ,  G08G5/00 ,  G08G5/02 ,  B64D45/04

Abstract: 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.

公开(公告)号：US20220245063A1

公开(公告)日：2022-08-04

申请号：US17586913

申请日：2022-01-28

Applicant: AIRBUS OPERATIONS LIMITED ,  AIRBUS OPERATIONS (S.A.S.)

Inventor： Louis-Emmanuel ROMANA ,  George HOWELL

IPC: G06F11/36

Abstract: 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.

公开(公告)号：US20240037290A1

公开(公告)日：2024-02-01

申请号：US18359473

申请日：2023-07-26

Applicant: AIRBUS OPERATIONS LIMITED

Inventor： George HOWELL ,  Jonathan COOPER

IPC: G06F30/15

CPC classification number: G06F30/15 ,  G06F2111/06

Abstract: Computer-implemented methods and systems for selecting components to be used in an aircraft system including: a reliability evaluation function, to produce a reliability score, and a complexity evaluation function, to produce a complexity score, are provided; and a multi-objective optimisation function is performed to determine at least one set of candidate components for the aircraft system that satisfy one or more conditions. The multi-objective optimisation function includes selecting a new set of candidate components, performing at least one of the reliability evaluation function and the complexity evaluation function, and evaluating at least one of the reliability score and the complexity score according to the conditions. The new set of candidate components are stored in associated with an indication of the outcome of the evaluation. An aircraft comprising a set of components that have been selected from one or more of the stored sets of components is also provided.

公开(公告)号：US20220324423A1

公开(公告)日：2022-10-13

申请号：US17764841

申请日：2020-09-25

Applicant: AIRBUS OPERATIONS LIMITED

Inventor： George HOWELL

IPC: B60T8/17 ,  B64C25/42 ,  B64F5/60

Abstract: An aircraft controller 5, aircraft braking system 13 and method for determining braking parameters. The aircraft controller 5 is configured to determine information associated with an aircraft taxiing route associated with an aircraft 1. On the basis of the information, the aircraft controller 5 determines a first braking parameter for a first main landing gear 8 of the aircraft 1 and a second braking parameter for a second main landing gear 9 of the aircraft 1 during a landing event. The first and second braking parameters are determined to result in asymmetrical braking between the first 8 and second 9 main landing gears during the landing event.

公开(公告)号：US20160016576A1

公开(公告)日：2016-01-21

申请号：US14802776

申请日：2015-07-17

Applicant: AIRBUS OPERATIONS LIMITED

Inventor： George HOWELL ,  Matthieu Della NAVE

IPC: B60T17/22

CPC classification number: B60T17/221 ,  B60T8/1703 ,  B60T8/325

Abstract: A method of determining the integrity of an electric or hydraulic braking control system. A reduction rate of a voltage or hydraulic pressure in the braking control system is determined, and the integrity of the braking control system is determined by comparing the reduction rate with a threshold. The braking control system may be an aircraft braking control system, and the method may be performed during flight of the aircraft—typically during cruise.

Abstract translation: 一种确定电动或液压制动控制系统的完整性的方法。 确定制动控制系统中的电压或液压的减小率，并且通过将减速率与阈值进行比较来确定制动控制系统的完整性。 制动控制系统可以是飞行器制动控制系统，并且该方法可以在飞机飞行期间执行 - 通常在巡航期间。

公开(公告)号：US20220363406A1

公开(公告)日：2022-11-17

申请号：US17702187

申请日：2022-03-23

Applicant: Airbus Operations Limited

Inventor： George HOWELL ,  Andrew HEBBORN

IPC: B64D45/00

Abstract: A monitoring system 300 for an aircraft 100 including a controller 301 to 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 system 3000 comprising the monitoring system, an aircraft comprising the monitoring system or the avionics system, and a method 600 of monitoring an aircraft.

公开(公告)号：US20220332408A1

公开(公告)日：2022-10-20

申请号：US17720893

申请日：2022-04-14

Applicant: Airbus Operations Limited

Inventor： George HOWELL ,  Ashley BIDMEAD

IPC: B64C25/42

Abstract: 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.

公开(公告)号：US20220250769A1

公开(公告)日：2022-08-11

申请号：US17669011

申请日：2022-02-10

Applicant: AIRBUS OPERATIONS LIMITED ,  AIRBUS OPERATIONS (S.A.S.)

Inventor： George HOWELL ,  Louis Emmanuel ROMANA

IPC: B64F5/60 ,  B64D43/00 ,  B64D45/04 ,  G06N20/00

Abstract: An aircraft control system (100) including an aircraft control module (110) and a test module (120). The aircraft control module includes a memory storing a machine learning model (130) adapted, based on received live aircraft operating inputs (102a-102f), to generate live aircraft control outputs (104a-104b). The test module (120) includes a memory storing input data representing test aircraft operating inputs (102a′-102f′) and respective output data representing expected aircraft control outputs (114a, 114b) that are expected to be generated by the aircraft control module in response to an input of the respective test aircraft operating inputs (102a′-102f′). The test module (120) is adapted to write test aircraft operating inputs (102a′-102f′) to the aircraft control module, read test aircraft control outputs (104a′-104b′) of the aircraft control module (110), and remove the authority of the aircraft control module (110) to perform aircraft control.

公开(公告)号：US20180370616A1

公开(公告)日：2018-12-27

申请号：US16014298

申请日：2018-06-21

Applicant: Airbus Operations Limited

Inventor： George HOWELL ,  Nicholas CRANE

IPC: B64C13/42 ,  B64C25/22 ,  B64C25/60

Abstract: A hydraulic system 300 for an aircraft including a backup hydraulic pressure source 216 to provide hydraulic pressure to a brake 222 in the event of a failure condition of a primary hydraulic brake pressure source. The hydraulic system 300 also includes a landing gear backup system to provide hydraulic pressure to enable extension and/or retraction of landing gear 100. The backup hydraulic pressure source 216 is 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.