Aircraft attitude controller and wing system
An aircraft attitude controller configured to obtain information representative of an attitude of an aircraft is disclosed. On the basis of the information, the attitude controller is configured to control the attitude of the aircraft by actively controlling a position of a winglet at a distal end of a wing portion of a wing of the aircraft, relative to the wing portion, thereby to control an angle of incidence of the winglet.
1 . An aircraft attitude controller configured to:
obtain information on any one or more of the following properties:
a mass of the aircraft,
a distribution of mass of the aircraft,
a centre of gravity of the aircraft,
an amount of fuel in the aircraft, and
a fuel consumption of the aircraft; and,
on the basis of the information, control an attitude of the aircraft by actively controlling a position of a winglet at a distal end of a wing portion of a wing of the aircraft, relative to the wing portion, thereby to control an angle of incidence of the winglet;
wherein the aircraft attitude controller is configured to determine a target attitude of the aircraft; and,
wherein the controlling the attitude of the aircraft comprises controlling the attitude of the aircraft to bring the attitude of the aircraft towards the target attitude of the aircraft.
2 . The aircraft attitude controller of claim 1 , wherein the attitude of the aircraft comprises a pitch of the aircraft and/or an angle of attack of the aircraft.
3 . The aircraft attitude controller of claim 1 , wherein the information comprises information on any one or more of the following properties:
a pitch of the aircraft;
an angle of attack of the aircraft;
a speed of the aircraft;
a drag of the aircraft;
and
an efficiency of the aircraft.
4 . A wing system for an aircraft, the wing system comprising at least a wing portion of a wing, a winglet at a distal end of the wing portion, and a controller, wherein a position of the winglet relative to the wing portion is variable to change an angle of incidence of the winglet, and
wherein the controller is configured to:
obtain information on any one or more of the following properties:
a mass of the aircraft,
a distribution of mass of the aircraft,
a centre of gravity of the aircraft,
an amount of fuel in the aircraft, and
a fuel consumption of the aircraft, and,
on the basis of the information,
control the attitude of the aircraft by actively controlling the position of the winglet relative to the wing portion;
wherein the controller is configured to determine a target attitude of the aircraft, and
wherein the controlling the attitude of the aircraft comprises controlling the attitude of the aircraft to bring the attitude of the aircraft towards the target attitude of the aircraft.
5 . The wing system of claim 4 , wherein the winglet is rotatably movable relative to the wing portion.
6 . The wing system of claim 5 , wherein an axis of rotation of the winglet relative to the wing portion is orientated at a non-zero toe angle to a vertical plane that includes a longitudinal axis of the aircraft.
7 . The wing system of claim 4 , comprising a restrictor operable to restrict a range of movement of the winglet.
8 . The wing system of claim 4 , wherein the winglet is movable to an extended position, in which a proximal end of the winglet is substantially aligned with the distal end of the wing portion, and
wherein a span of the winglet, when the winglet is in the extended position, constitutes from 10% to 50% of the total span of the wing comprising the wing portion.
9 . The wing system of claim 4 , comprising an actuator for varying the position of the winglet relative to the wing portion.
10 . The wing system of claim 4 , wherein the attitude controller is configured to:
obtain information representative of an attitude of an aircraft; and,
on the basis of the information, control the attitude of the aircraft by actively controlling a position of a winglet at a distal end of a wing portion of a wing of the aircraft, relative to the wing portion, thereby to control an angle of incidence of the winglet.
11 . A method of controlling an attitude of an aircraft, the method comprising:
obtaining information on any one or more of the following properties:
a mass of the aircraft,
a distribution of mass of the aircraft,
a centre of gravity of the aircraft,
an amount of fuel in the aircraft, and
a fuel consumption of the aircraft; and,
on the basis of the information, controlling the attitude of the aircraft by controlling a position of a winglet at a distal end of a wing portion of a wing of the aircraft, relative to the wing portion, thereby to control an angle of incidence of the winglet;
wherein the method comprises determining a target attitude of the aircraft, and
wherein the controlling the attitude of the aircraft comprises controlling the attitude of the aircraft to bring the attitude of the aircraft towards the target attitude of the aircraft.
12 . The method of claim 11 , comprising determining a target attitude of the aircraft, wherein the controlling the attitude of the aircraft comprises controlling the attitude of the aircraft to bring the attitude of the aircraft towards the target attitude of the aircraft.
13 . A non-transitory computer-readable storage medium storing instructions that, when executed by a processor, cause the processor to perform the method of claim 11 .
14 . An aircraft comprising the aircraft altitude controller of claim 1 .
15 . An aircraft comprising the wing system of claim 4 .
16 . An aircraft comprising the non-transitory computer-readable storage medium of claim 13 .