초록 ▼

An aircraft comprises a wing tip device, for example a winglet, a raked-tip device, a wing tip fence or a planar wing extension, mounted in the region of the tip of a wing on the aircraft. The wing tip device is rotatably moveable between a first position and a second position, in which the upward l

An aircraft comprises a wing tip device, for example a winglet, a raked-tip device, a wing tip fence or a planar wing extension, mounted in the region of the tip of a wing on the aircraft. The wing tip device is rotatably moveable between a first position and a second position, in which the upward lift produced by the wing or the wing tip device is reduced. During flight, the bending moment at the root of the aircraft wing therefore changes in dependence on the position of the wing tip device. The maximum bending moment in the aircraft wing sustained during high-load conditions is thereby reduced, allowing the structural mass of the aircraft to be reduced.

대표청구항 ▼

The invention claimed is: 1. An aircraft comprising a wing, the wing comprising a root, a tip, and a wingtip device mounted in the region of the tip, there being a first plane with which the wing is generally aligned, and a second plane which is vertical and includes the longitudinal axis of the ai

The invention claimed is: 1. An aircraft comprising a wing, the wing comprising a root, a tip, and a wingtip device mounted in the region of the tip, there being a first plane with which the wing is generally aligned, and a second plane which is vertical and includes the longitudinal axis of the aircraft, the wingtip device being rotatably moveable between a first position and a second position, and being so arranged that, during flight of the aircraft, the bending moment at the root changes in dependence on the position of the wingtip device so that the maximum bending moment at the root of the wing sustained during high-load flight conditions may be reduced, wherein the axis of rotation of the wingtip device is so positioned that: (a) the acute angle between the axis of rotation and the first plane is less than 45 degrees, and (b) the acute angle between the axis of rotation and the second plane is between 5 and 30 degrees, and wherein the axis of rotation of the wingtip device is so positioned and the wing and wingtip device are so arranged that: (c) the mean incidence of the wingtip device, when the wingtip device is in the second position, is less than the mean incidence of the wingtip device were the wingtip device in the first position. 2. An aircraft according to claim 1, wherein the axis of rotation of the wingtip device is substantially parallel to the first plane. 3. An aircraft according to claim 1, wherein the wingtip device is mounted about a hinge joint for rotational movement. 4. An aircraft according to claim 1, wherein the shape of the wingtip device is arranged to be changeable during use. 5. An aircraft according to claim 1, wherein the wingtip device is mounted about an elastically deformable portion for rotational movement of the wingtip device between the first position and the second position. 6. An aircraft according to claim 1, wherein the aircraft includes a load sensing device arranged to sense a load on the wing and a control system arranged such that in use the control system receives signals from the load sensing device and sends signals to an actuator to move the wingtip device in dependence on the signals received from the load sensing device. 7. An aircraft according to claim 1, wherein the wing includes a linear actuator for causing movement of the wingtip device between the first position and the second position. 8. An aircraft according to claim 3, wherein the hinge joint is so arranged that movement of the wingtip device between the first and second positions is able to be caused during flight of the aircraft as a result of the interaction between the wingtip device and the air moving past the wingtip device. 9. A wing for an aircraft, the wing including a root, a tip, and a wingtip device mounted in the region of the tip, there being a first plane with which the wing is generally aligned, and a second plane which is vertical and includes the longitudinal axis of the aircraft, the wingtip device being rotatably moveable between a first position and a second position, and being so arranged that, during flight of an aircraft to which the wing is attached, the bending moment at the root changes in dependence on the position of the wingtip device so that the maximum bending moment at the root of the wing sustained during high-load flight conditions may be reduced, wherein (a) the axis of rotation of the wingtip device is so positioned that the acute angle between the axis of rotation and the first plane is less than 45 degrees, (b) the axis of rotation of the wingtip device is so positioned that, when the wing is attached to an aircraft, the acute angle between the axis of rotation and the second plane is between 5 and 30 degrees, and (c) the axis of rotation of the wingtip device is so positioned and the wing and wingtip device are so arranged that the mean incidence of the wingtip device, when the wingtip device is in the second position, is less than the mean incidence of the wingtip device were the wingtip device in the first position. 10. A wingtip device for a wing on an aircraft, there being a first plane with which the wins is generally aligned, and a second plane which is vertical and includes the longitudinal axis of the aircraft, the wingtip device including a mounting portion for facilitating attachment of the wingtip device to the wing in the region of the wingtip, the wingtip device being rotatably moveable relative to the mounting portion between a first position and a second position, and being so arranged that, during flight of an aircraft to which the wingtip device is attached, the bending moment at the root changes in dependence on the position of the wingtip device so that the maximum bending moment sustained during high-load flight conditions at the root of the wing, to which the wingtip device is attached, may be reduced, wherein (a) the axis of rotation of the wingtip device is so positioned that, when the wingtip is attached to an aircraft wing, the acute angle between the axis of rotation and the first plane is less than 45 degrees, (b) the axis of rotation of the wingtip device is so positioned that, when the wingtip is attached to an aircraft, the acute angle between the axis of rotation and the second plane is between 5 and 30 degrees, and (c) the wingtip device is so arranged and configured that, when attached to a wing by means of the mounting portion, the mean incidence of the wingtip device, when the wingtip device is in the second position, is less than the mean incidence of the wingtip device were the wingtip device in the first position.