Control device and method for an aircraft
A control device for an aircraft is disclosed including a push-button switch that is configured to be held in a depressed position by a pilot during taxiing of the aircraft. The push-button switch is configured to return automatically to a released position if it is not held in the depressed position by the pilot. The control device is configured to output a command for braking to a braking system of the aircraft, if the push-button switch moves to the released position during taxiing of the aircraft and does not return to the depressed position within a set time. The button may be provided on a tiller. A method of detecting on-board pilot incapacitation during an aircraft taxi phase is also disclosed.
1. A control device for an aircraft, the aircraft including a braking system, the control device comprising:
a manually operable push-button switch movable from a released position to a depressed position,
the push-button switch being configured to return to the released position if it is not manually held in the depressed position,
the push-button switch being configured to be held by a pilot in the depressed position during a taxi phase of the aircraft,
the control device being arranged, in response to the push-button switch moving to the released position during the taxi phase, to output a signal which causes a braking command to be issued, after a set time has passed without the push-button switch being returned to the depressed position.
2. The control device according to claim 1 , wherein the push-button switch is located on a steering tiller of the aircraft.
3. The control device according to claim 1 , including a control module arranged to detect when the push-button switch has moved from the depressed position to the released position during taxi phase and to output a signal to the braking system in response.
4. The control device according to claim 1 , wherein the control device is configured to have a first function and to have a second function during single pilot operation of the aircraft, the second function being different from the first function.
5. The control device according to claim 4 , wherein the first function is to allow a rudder check to be performed with rudder pedals without causing a nose-wheel to be turned by the pedals.
6. The control device according to claim 5 , wherein the push-button switch is located on a steering tiller of the aircraft.
7. The control device according to claim 1 , wherein the set time is between 1 and 5 seconds.
8. The control device according to claim 1 , wherein the push button switch is spring loaded.
9. An aircraft, comprising:
a control system,
a braking system,
a steering tiller, and
a sensor located on the steering tiller for detecting whether or not the steering tiller is being gripped,
the control system being arranged to receive a signal from the sensor indicating whether the steering tiller is being gripped during an aircraft taxi phase, and to output a command for braking to the braking system in response, in the event that the steering tiller is not being gripped for a set time period.
10. An aircraft according to claim 9 , wherein the sensor located on the steering tiller is configured additionally to perform the function of a rudder pedal disconnect button which is provided to allow for checking of rudder control independently of nose wheel steering.
11. An aircraft including the control device according to claim 1 .
12. A method of modifying an existing aircraft to make it more suited to single-pilot operations, the aircraft having a sensor on a steering tiller with a primary function, the method comprising:
adapting the sensor to have a secondary function specific to single pilot operations;
adding a secondary indicator to the sensor to indicate the functionality of the sensor to flight crew; and
installing software on a system of the aircraft such that when installed the system of the aircraft detects the state of the sensor allowing the sensor to perform the secondary function during taxiing and single pilot operations.
13. A method of detecting on-board pilot incapacitation during an aircraft taxi phase, comprising:
a switch automatically moving to a released position if it is not held in a depressed position by the on-board pilot;
detecting that the switch has moved from the depressed position;
waiting for a specified time period, before one of
(a) the switch returning to the depressed position before the end of the time period; or
(b) as a consequence of the switch not being in the depressed position throughout the time period, the method further comprises outputting a command to a braking system of the aircraft for braking.
14. The method according to claim 13 , the method further comprising:
the aircraft entering taxi phase;
the on-board pilot moving the switch to the depressed position; and
the on-board pilot holding the switch in the depressed position.
15. The method according to claim 13 , wherein the specified time period is between 1 and 5 seconds.
16. The method according to claim 13 , wherein the aircraft comprises a control system, a braking system, a steering tiller, and a sensor located on the steering tiller for detecting whether or not the steering tiller is being gripped, the control system being arranged to receive a signal from the sensor indicating whether the steering tiller is being gripped during an aircraft taxi phase, and to output a command for braking to the braking system in response, in the event that the steering tiller is not being gripped for a set time period.
17. An aircraft arranged to allow for performance of the method of claim 11 .