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公开(公告)号：US11514728B2
公开(公告)日：2022-11-29
申请号：US16285668
申请日：2019-02-26
发明人： Nicholas Crane , Arnaud Didey
IPC分类号： B64C25/40 , G07C5/00 , F16D3/06 , F16H1/24 , F16H57/01 , F16H1/00 , G07C5/08 , G07C5/02 , G01M13/02 , F16D3/18 , B64D45/00
摘要： A drive system 20, 20′ for rotating a wheel 11, 11′ of an aircraft landing gear 10, 10′, is disclosed having a drive element 24, 24′, a motor 21, 21′ operable to rotate the drive element, and a driven gear 25, 25′ adapted to be attached to the wheel. The drive system has a drive configuration in which the drive element is capable of meshing with the driven gear to drive the driven gear, wherein the drive system further comprises a transmission error measurement apparatus 30, 40, the apparatus configured to obtain, over time, measurement data of one or more characteristics of the drive system when in the drive configuration, the measurement data providing an indication of a transmission error between a torque commanded by the motor and a resulting torque at the driven gear. An aircraft 100 and a method of providing an indication of a transmission error in a drive system is disclosed.
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公开(公告)号：US11345466B2
公开(公告)日：2022-05-31
申请号：US16275682
申请日：2019-02-14
发明人： Nicholas Crane , Adrian Harrison
摘要： A controller for a hydraulic braking system for an aircraft is disclosed. The hydraulic braking system includes a first accumulator and a second accumulator, the controller configured to: receive first signals including first pressure data from a first pressure transducer associated with the first accumulator, receive second signals including second pressure data from a second pressure transducer associated with the second accumulator, monitor the received first and second signals to determine whether a predetermined condition has been met, and issue a warning indicating a loss of integrity of the hydraulic braking system in response to a determination that one or more predetermined conditions has been met. A hydraulic braking system for an aircraft and method to determine the integrity of a hydraulic braking system are also disclosed.
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公开(公告)号：US11260961B2
公开(公告)日：2022-03-01
申请号：US16014298
申请日：2018-06-21
发明人： George Howell , Nicholas Crane
摘要： 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.
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公开(公告)号：US11919626B2
公开(公告)日：2024-03-05
申请号：US17662401
申请日：2022-05-06
发明人： Nicholas Crane , Adrian Harrison
CPC分类号： B64C25/44 , B60T8/325 , B60T17/22 , B64D45/00 , B64F5/60 , B60T8/1703 , B60T13/14 , B60T13/662 , B64D2045/0085
摘要： A controller for a hydraulic braking system for an aircraft is disclosed. The hydraulic braking system includes a first accumulator and a second accumulator, the controller configured to: receive first signals including first pressure data from a first pressure transducer associated with the first accumulator, receive second signals including second pressure data from a second pressure transducer associated with the second accumulator, monitor the received first and second signals to determine whether a predetermined condition has been met, and issue a warning indicating a loss of integrity of the hydraulic braking system in response to a determination that one or more predetermined conditions has been met. A hydraulic braking system for an aircraft and method to determine the integrity of a hydraulic braking system are also disclosed.
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公开(公告)号：US10569864B2
公开(公告)日：2020-02-25
申请号：US16017018
申请日：2018-06-25
摘要： A control apparatus 300 for controlling a steering system 301 of an aircraft landing gear, the aircraft landing gear being configurable in a stowed configuration and a deployed configuration. The steering system 301 includes a wheel arrangement 202 including one or more wheels. The control apparatus 300 is arranged to perform a control process which includes: receiving one or more signals from one or more sensors 302a, 302b indicating a position of the wheel arrangement 202 when the landing gear is in the stowed configuration; determining whether a predetermined condition is satisfied in relation to the position of the wheel arrangement 202; and, in response to determining that the predetermined condition is satisfied, performing an adjustment process to control the steering system 301 to adjust the position of the wheel arrangement 202.
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