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公开(公告)号：EP4325316A2
公开(公告)日：2024-02-21
申请号：EP23189837.0
申请日：2023-08-04
发明人： BIDMEAD, Ashley , JOHNSON, Mark
摘要： An aircraft (101) includes a ground manoeuvre control unit (226) for automatically controlling ground manoeuvres. The aircraft (101) has control mechanisms (230) such as a rudder, nose wheel steering, spoilers, wheel brakes (110a and 110b) and the like for controlling motion of the aircraft (101). The control unit (226) is configured to receive lateral input demands (220) concerning lateral motion of the aircraft (e.g. heading control) and longitudinal input demands (222) concerning longitudinal motion of the aircraft (e.g. deceleration). The control unit (226) passes on the input demands (220, 222) as output demands (228) to the relevant control mechanisms (230) of the aircraft (101) with, if so required, a modification which prioritises one of the lateral input demand (220) and longitudinal input demand (222) based on the risk of a lateral runway excursion and the risk of a longitudinal runway excursion (232).
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公开(公告)号：EP4043303A1
公开(公告)日：2022-08-17
申请号：EP22156313.3
申请日：2022-02-11
发明人： HAYES, Alexander , BIDMEAD, Ashley , STORME, Thierry , COOMBE, Robert , JOHNSON, Mark , HEBBORN, Andrew
摘要： The present invention provides an aircraft brake control system 60 for controlling antiskid braking of at least first 11 and second 12 wheels in a wheel set of an aircraft 100, the system comprising a control assembly 60 having wheel speed inputs including an input of an indication of the wheel speed 13 of the first wheel 11, and an input of an indication 14 of the wheel speed of the second wheel 12, a wheel speed comparator 62 for determining which of the wheel speeds indicated is a lowest wheel speed 63, and an output 66 for indicating a wheel speed 64 other than the lowest wheel speed 63. The invention also provides an aircraft landing gear 10, an aircraft 100 and methods of braking an aircraft 100.
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公开(公告)号：EP4403466A1
公开(公告)日：2024-07-24
申请号：EP24151250.8
申请日：2024-01-10
发明人： BIDMEAD, Ashley , JOHNSON, Mark
IPC分类号： B64C25/42 , B60T8/17 , B60T8/1755 , B64C25/50
CPC分类号： B64C25/50 , B64C25/48 , B64C25/42 , B60T8/1703 , B60T8/1755 , B60T8/885
摘要： An aircraft (101) includes a ground manoeuvre control system (120) that automatically steers a nose landing gear wheel (112) to compensate for asymmetrical braking of the wheels (104) of the aircraft resulting from a failure on one side in comparison to the other. A control system (control unit 130) detects such a failure in order to be able to effect such automatic steering. The system (120) may be retrofitted by the installation of software (132) on an existing aircraft, having a braking and steering computer system (138) with a pre-existing steering control functional block (134) and a pre-existing braking control functional block (136).
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公开(公告)号：EP4325316A3
公开(公告)日：2024-03-27
申请号：EP23189837.0
申请日：2023-08-04
发明人： BIDMEAD, Ashley , JOHNSON, Mark
摘要： An aircraft (101) includes a ground manoeuvre control unit (226) for automatically controlling ground manoeuvres. The aircraft (101) has control mechanisms (230) such as a rudder, nose wheel steering, spoilers, wheel brakes (110a and 110b) and the like for controlling motion of the aircraft (101). The control unit (226) is configured to receive lateral input demands (220) concerning lateral motion of the aircraft (e.g. heading control) and longitudinal input demands (222) concerning longitudinal motion of the aircraft (e.g. deceleration). The control unit (226) passes on the input demands (220, 222) as output demands (228) to the relevant control mechanisms (230) of the aircraft (101) with, if so required, a modification which prioritises one of the lateral input demand (220) and longitudinal input demand (222) based on the risk of a lateral runway excursion and the risk of a longitudinal runway excursion (232).
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公开(公告)号：EP3921185A1
公开(公告)日：2021-12-15
申请号：EP20753679.8
申请日：2020-07-16
发明人： ROBERTSON, Michael , JOHNSON, Mark
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公开(公告)号：EP4397550A1
公开(公告)日：2024-07-10
申请号：EP23218869.8
申请日：2023-12-20
发明人： BIDMEAD, Ashley , JOHNSON, Mark
CPC分类号： B60T8/1703 , B60T8/325 , B60T13/66 , B64C25/00
摘要： A control device (462) for an aircraft (100) comprises a push-button switch (412) that is configured to be held in a depressed position (412b) by a pilot during taxiing of the aircraft (100). The push-button switch (412) is configured to return automatically to a released position (412a) if it is not held in the depressed position (412b) by the pilot. The control device (462) is configured to output a command for braking to a braking system (464) of the aircraft, if the push-button switch (412) moves to the released position (412a) during taxiing of the aircraft and does not return to the depressed position (412b) within a set time. The button may be provided on a tiller (301). A method (505) of detecting on-board pilot incapacitation during an aircraft taxi phase is also disclosed.
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公开(公告)号：EP4215437A1
公开(公告)日：2023-07-26
申请号：EP23152827.4
申请日：2023-01-23
摘要： Disclosed is an aircraft control system 100 for controlling actuation of an aircraft component 700, the system comprising a control assembly 110 having control units, including a first control unit 130 for controlling actuation of the aircraft component during a first time period, using electrical resource 512 from a first electrical resource device 510, and a second control unit 140 for controlling actuation of the aircraft component during a second time period, and a switch mechanism 120 for switching control of the actuation of the aircraft component between the first and second control units, wherein the switch mechanism has a first electrical resource device status input 513 for indicating the status of the first electrical resource device 510 and wherein, the switch mechanism is configured to switch control between the first 130 and second 140 control units based on the first electrical resource device status input 513. Also disclosed is an aircraft 1000, aircraft assembly and a method of controlling an aircraft component of an aircraft.
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