An aircraft control system 100 including a control assembly 110 having control units, including a first control unit 130 for controlling actuation of the aircraft component during a first time period, using electrical resource 512 from a first electrical resource device 510, and a second control unit 140 for controlling actuation of the aircraft component during a second time period, and a switch mechanism 120 for 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 input 513 for indicating the status of the first electrical resource device 510 and wherein, the switch mechanism is configured to switch control between the first 130 and second 140 control units based on the first electrical resource device status input 513.

A method for controlling an aircraft when taxiing comprising the steps of: measuring an angle of rotation of an active side stick about a first axis and a second axis; receiving an aircraft signal representative of an actual state of the aircraft; generating a control signal based on at least one of: the aircraft signal and the angle of rotation of the active side stick about a first axis and a second axis; transmitting the control signal to the aircraft, whereby the control signal causes an action affecting the actual state of the aircraft; determining a required state of the aircraft; generating a user feedback signal based on at least one difference between the actual state and the required state; and carrying out a user feedback action based on the user feedback signal.

A method for controlling an aircraft when taxiing comprising the steps of: measuring an angle of rotation of an active side stick about a first axis and a second axis; receiving an aircraft signal representative of an actual state of the aircraft; generating a control signal based on at least one of: the aircraft signal and the angle of rotation of the active side stick about a first axis and a second axis; transmitting the control signal to the aircraft, whereby the control signal causes an action affecting the actual state of the aircraft; determining a required state of the aircraft; generating a user feedback signal based on at least one difference between the actual state and the required state; and carrying out a user feedback action based on the user feedback signal.

The invention provides a locking device for preventing movement between two elements (11, 12) that are mounted to move relative to each other, the locking device including a lock (31) mounted to rotate relative to one of the elements in order to present successive angular positions for locking and for release in which the lock alternates between preventing and allowing relative movement between the two elements, the lock being constrained to rotate with a selector (55) of an angular indexing mechanism (50) actuated by a pulse-controlled actuator (70, 71) arranged to push the selector against a spring member (58) in order to cause it to turn on each pulse and thereby cause the lock to pass from one angular position to the other.

A system is described. The system may detect whether a user within a flight deck is authorized to control the aircraft. The user may receive differing levels of authority to control the aircraft depending on whether the user is authorized or unauthorized. The system may also control the aircraft depending on the various phases of the aircraft, including in flight and on the ground. The system may also be used to unlock the controls for the aircraft. The system may unlock the control using biometric information or nonbiometric information. The system may include a camera which is added to a flight deck. The camera may capture images of users within the flight deck. Faces within the images may be detected and compared against authorized users for locking or unlocking the aircraft controls.

A system is described. The system may detect whether a user within a flight deck is authorized to control the aircraft. The user may receive differing levels of authority to control the aircraft depending on whether the user is authorized or unauthorized. The system may also control the aircraft depending on the various phases of the aircraft, including in flight and on the ground. The system may also be used to unlock the controls for the aircraft. The system may unlock the control using biometric information or nonbiometric information. The system may include a camera which is added to a flight deck. The camera may capture images of users within the flight deck. Faces within the images may be detected and compared against authorized users for locking or unlocking the aircraft controls.

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.

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.

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.

A nose-wheel steering system may comprise an actuator and a bevel gear rotationally coupled to a drive shaft of the actuator. The bevel gear may be configured to rotate about a first axis. A collar gear may be intermeshed with the bevel gear. The collar gear may be configured to rotate about a second axis that is generally perpendicular to the first axis.