Airbus Operations Gmbh

Nicholas Crane

Adrian Harrison

Arnaud Didey

George Howell

Robert Tangye

Cecile Lea Lourdes Garaygay

Cecile Garaygay

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.

Controller for an aircraft braking system

A drive systemfor rotating a wheelof an aircraft landing gear', is disclosed having a drive element&#x2032;, a motoroperable to rotate the drive element, and a driven gearadapted 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, 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 aircraftand a method of providing an indication of a transmission error in a drive system is disclosed.

Drive system for rotating a wheel of a landing gear having a transmission error measurement apparatus

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 control apparatusfor controlling a steering systemof an aircraft landing gear, the aircraft landing gear being configurable in a stowed configuration and a deployed configuration. The steering systemincludes a wheel arrangementincluding one or more wheels. The control apparatusis arranged to perform a control process which includes: receiving one or more signals from one or more sensorsindicating a position of the wheel arrangementwhen the landing gear is in the stowed configuration; determining whether a predetermined condition is satisfied in relation to the position of the wheel arrangement; and, in response to determining that the predetermined condition is satisfied, performing an adjustment process to control the steering systemto adjust the position of the wheel arrangement

Growing community of inventors

Bristol, United Kingdom

Nicholas Crane