Patents by Inventor Nicholas CRANE
Nicholas CRANE has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).
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Patent number: 11919626Abstract: 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.Type: GrantFiled: May 6, 2022Date of Patent: March 5, 2024Assignee: AIRBUS OPERATIONS LIMITEDInventors: Nicholas Crane, Adrian Harrison
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Patent number: 11514728Abstract: 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.Type: GrantFiled: February 26, 2019Date of Patent: November 29, 2022Assignee: AIRBUS OPERATIONS LIMITEDInventors: Nicholas Crane, Arnaud Didey
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Publication number: 20220266991Abstract: 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.Type: ApplicationFiled: May 6, 2022Publication date: August 25, 2022Inventors: Nicholas CRANE, Adrian HARRISON
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Patent number: 11345466Abstract: 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.Type: GrantFiled: February 14, 2019Date of Patent: May 31, 2022Assignee: AIRBUS OPERATIONS LIMITEDInventors: Nicholas Crane, Adrian Harrison
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Patent number: 11260961Abstract: 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.Type: GrantFiled: June 21, 2018Date of Patent: March 1, 2022Assignee: Airbus Operations LimitedInventors: George Howell, Nicholas Crane
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Patent number: 10569864Abstract: 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.Type: GrantFiled: June 25, 2018Date of Patent: February 25, 2020Assignee: Airbus Operations LimitedInventors: Robert Tangye, Cecile Lea Lourdes Garaygay, Nicholas Crane
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Publication number: 20190263508Abstract: 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.Type: ApplicationFiled: February 26, 2019Publication date: August 29, 2019Inventors: Nicholas CRANE, Arnaud DIDEY
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Publication number: 20190248478Abstract: 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.Type: ApplicationFiled: February 14, 2019Publication date: August 15, 2019Inventors: Nicholas CRANE, Adrian HARRISON
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Publication number: 20190002091Abstract: 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.Type: ApplicationFiled: June 25, 2018Publication date: January 3, 2019Inventors: Robert TANGYE, Cecile Lea Lourdes GARAYGAY, Nicholas CRANE
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Publication number: 20180370616Abstract: 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.Type: ApplicationFiled: June 21, 2018Publication date: December 27, 2018Inventors: George HOWELL, Nicholas CRANE
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Publication number: 20150360524Abstract: A tire assembly includes a tire having a pneumatic cavity, first and second sidewalls extending respectively from first and second tire bead regions to a tire tread region, the first sidewall having at least one bending region operatively bending when radially within a rolling tire footprint, and a chafer component with an air passageway defined by an air tube resiliently deforming segment by segment between an expanded condition and an at least partially collapsed condition in response to respective segment by segment deformation of the sidewall when radially within the rolling tire footprint. The tire assembly pumps a constant volume of air for every revolution of the tire thus providing a linear pumping rate regardless of dead volumes in the tire.Type: ApplicationFiled: June 16, 2014Publication date: December 17, 2015Inventors: Thulasiram Gobinath, Robert Leon Benedict, Richard Nicholas Crane