Abstract: An aircraft brake control system for controlling antiskid braking of an aircraft wheel is disclosed including a control assembly having a mode controller which sets the mode of operation of an antiskid brake calculator, configured to set a first mode, when an input of the indication of a brake energy supply configuration indicates a first brake energy supply being used, in which the antiskid brake calculator applies a first restriction level on a rise rate of the antiskid brake command, and a second mode, when the input 305 indicates a second brake energy supply being used, in which the antiskid brake calculator applies a second, lower, restriction level on a rise rate of the antiskid brake command.

Abstract: A method of parking an aircraft is disclosed including flight crew pedal braking to cause a brake force to be applied to the aircraft wheel brakes to slow the aircraft to a stationary state in which it is ready to be parked. Flight crew then activate a parking brake device and then release the pedal braking. An electronic control device, forming part of the aircraft’s braking system for example, automatically intervenes, following the manual release of the pedal braking, to cause a brake force to continue to be applied to the wheels. This may be until sufficient brake force is applied, as a result of the activation of the parking brake device, to hold the aircraft in its parked state or may be for a predetermined period of time, say, ten seconds.

Abstract: A heading control system for an aircraft arranged to maintain a heading of an aircraft by controlling a nose wheel angle of the aircraft. The heading control system includes an interface arranged to receive a bias signal indicating a bias towards the port or the starboard of the aircraft and one or more processors. The one or more processors are arranged to determine, based on the bias signal, an offset angle defining an offset from a longitudinal axis of the aircraft and to perform a control process to control the nose wheel angle within an angular range based on the offset angle.

Abstract: A monitoring system 300 for an aircraft 100 including a controller 301 to determine, based on one or more conditions, one or more expected operating characteristics of a steering system of the aircraft. The one or more conditions include one or more aircraft conditions indicative of an internal condition of the aircraft and/or one or more external conditions indicative of an external influence on the aircraft. The controller compares the one or more expected operating characteristics with the one or more actual operating characteristics. The controller is configured to determine, based on the compare, whether to issue a signal indicating a condition of the aircraft. An avionics system 3000 comprising the monitoring system, an aircraft comprising the monitoring system or the avionics system, and a method 600 of monitoring an aircraft.

Abstract: An aircraft landing event system is disclosed including a processor, the processor being configured to receive aircraft braking performance information from a plurality of aircraft that have performed a landing event on a particular runway. The processor is configured to determine an aircraft braking performance indicator on the basis of the aircraft braking performance information of the plurality of aircraft, and communicate the aircraft braking performance indicator to an aircraft landing system of an approaching aircraft that is about to perform a landing event on the particular runway.

Abstract: A brake control system for an aircraft is disclosed having a plurality of brake actuators. Each brake actuator includes a braked state imparting an unknown braking torque, and a parked state imparting a known braking torque. The system includes a controller to control the states of the brake actuators. In response to a parking signal, when at least one of the brake actuators is in the braked or parked state, the controller performs a parking procedure comprising maintaining a first brake actuator in the braked or parked state whilst changing the state of a second brake actuator from the braked state to the parked state. Also disclosed is an aircraft including the brake control system, a method of controlling a brake system for an aircraft, and a non-transitory computer readable storage medium.

Abstract: A brake control system 200 and method 300 for controlling a park brake of an aircraft including a controller 201 configured to cause an increase in a brake torque of the park brake based of an indication to the controller. The indication is generated in response to touchdown of the aircraft.

Abstract: An aircraft brake control system for controlling antiskid braking of an aircraft wheel is disclosed including a control assembly having a mode controller which sets the mode of operation of an antiskid brake calculator, configured to set a first mode, when an input of the indication of a brake energy supply configuration indicates a first brake energy supply being used, in which the antiskid brake calculator applies a first restriction level on a rise rate of the antiskid brake command, and a second mode, when the input 305 indicates a second brake energy supply being used, in which the antiskid brake calculator applies a second, lower, restriction level on a rise rate of the antiskid brake command.

Abstract: An aircraft brake control system for controlling anti-skid braking of at least first and second wheels in a wheel set of an aircraft is disclosed. The system includes a control assembly having wheel speed inputs including an input of an indication of the wheel speed of the first wheel, and an input of an indication of the wheel speed of the second wheel, a wheel speed comparator for determining which of the wheel speeds indicated is a lowest wheel speed, and an output for indicating a wheel speed other than the lowest wheel speed. An aircraft landing gear, an aircraft, and methods of braking an aircraft are also disclosed.

Abstract: An aircraft brake control system for controlling a plurality of brakeable wheels of a landing gear. Each brakeable wheel includes a brake actuator and a wheel speed sensor. The system includes a controller configured to receive aircraft control parameters and provide brake commands to the brake actuator of each wheel. The controller being configured to activate pre-retraction braking in response to an aircraft control parameter indicating that landing gear retraction is required and execute a functional brake test during pre-retraction braking.

Abstract: A method, apparatus and software is disclosed for controlling the heading of an aircraft travelling on the ground in which veering is detected and compensatory steering commands generated so as to automatically maintain a reference heading.

Abstract: A method, apparatus and software is disclosed for controlling the heading of an aircraft travelling on the ground in which veering is detected and compensatory steering commands generated so as to automatically maintain a reference heading.