Airbus Operations Gmbh

Alex Robert Piddock

Andreas Yiasoumi

Fernando Izquierdo Civera

Mark Andrew Johnson

Andrew David Sadler

Terry George Read

David George Stinchcombe

An aircraft control systemincluding a control assemblyhaving control units, including a first control unitfor controlling actuation of the aircraft component during a first time period, using electrical resourcefrom a first electrical resource device, and a second control unitfor controlling actuation of the aircraft component during a second time period, and a switch mechanismfor 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 inputfor indicating the status of the first electrical resource deviceand wherein, the switch mechanism is configured to switch control between the firstand secondcontrol units based on the first electrical resource device status input

Aircraft control system

A steering angle warning system comprising a rotation-measuring unit located on an aircraft, and an alarm unit. The rotation-measuring unit is arranged to output a first signal dependent on the steering angle between a nose landing gear of the aircraft and the longitudinal axis of the aircraft fuselage. The alarm unit is arranged to generate an alarm, in dependence on the first signal, when the steering angle is greater than a predetermined value, for example, 60 degrees. The rotation-measuring unit may also be arranged to perform a function in relation to an aircraft steering system, for example to indicate the steering angle to the pilot during ground manoeuvres.

Aircraft steering angle warning system

Growing community of inventors

Bristol, United Kingdom

Alex Robert Piddock