LIFTING SURFACES AND ASSOCIATED METHOD

Abstract

An arrangement of lifting surfaces including a primary lifting surface having a flexural axis extending in the spanwise direction of the lifting surface, a root, and a tip. A first tip device is attached to the tip and has a first lifting surface. A second tip device is attached to the tip and has a second lifting surface. A control system is coupled to the first and second tip devices for moving the first and second lifting surfaces relative to the tip and/or for actively controlling circulation of the first and second lifting surfaces. The control system is operable to change a value of torque effective at the primary lifting surface about the flexural axis. Also, a method of controlling an arrangement of lifting surfaces.

Claims

1. An aircraft having an arrangement of lifting surfaces comprising: a primary lifting surface having a flexural axis extending in a spanwise direction of the primary lifting surface, a root, and a tip; a first tip device attached to the tip and having a first lifting surface; a second tip device attached to the tip and having a second lifting surface; and a flight control system coupled to the first and second tip devices and configured to move the first and second lifting surfaces relative to the tip by moving at least one of the first and second tip devices relative to the primary lifting surface and/or to actively control circulation of the first and second lifting surfaces; wherein the control system is operable in a first mode of operation in which the first and second lifting surfaces are actively controlled to change a value of torque effective at the primary lifting surface about the flexural axis whilst maintaining a value of lift generated by the first and second tip devices substantially constant, and wherein the flight control system is operable in a second mode of operation in which the first and second lifting surfaces are actively controlled to change a value of lift generated by the first and second tip devices whilst maintaining a value of torque effective at the primary lifting surface about the flexural axis substantially constant.

2. The aircraft according to claim 1, wherein the first lifting surface is moved mechanically independently of the second lifting surface.

3. The aircraft according to claim 1, wherein the first lifting surface is moved relative to the primary lifting surface in a first direction, and the second lifting surface is moved relative to the primary lifting surface in a second direction opposite the first direction.

4. The aircraft according to claim 3, wherein movement of the first lifting surface is mechanically linked to movement of the second lifting surface.

5. The aircraft according to claim 1, wherein the first tip device has a leading edge and a trailing edge, and the first lifting surface extends full chord between the leading edge and the trailing edge of the first tip device.

6. The aircraft according to claim 5, wherein the arrangement further comprises an actuator for rotating the first lifting surface relative to the tip.

7. The aircraft according to claim 5, wherein the arrangement further comprises an actuator for morphing the first lifting surface.

8. The aircraft according to claim 1, wherein the first tip device has a leading edge and a trailing edge, the first lifting surface extends only part chord between the leading and trailing edges, and the first tip device has a third lifting surface fixed with respect to the primary lifting surface.

9. The aircraft according to claim 8, wherein the first lifting surface is hinged with respect to the third lifting surface and the movement of the first lifting surface includes rotating the first lifting surface about the hinge.

10. The aircraft according to claim 1, wherein the second tip device has a leading edge and a trailing edge, and the second lifting surface extends full chord between the leading and trailing edges of the second tip device.

11. The aircraft according to claim 10, wherein the arrangement further comprises an actuator for rotating the second lifting surface relative to the tip.

12. The aircraft according to claim 10, wherein the arrangement further comprises an actuator for morphing the second lifting surface.

13. The aircraft according to claim 1, wherein the second tip device has a leading edge and a trailing edge, the second lifting surface extends only part chord between the leading and trailing edges, and the second tip device has a fourth lifting surface fixed with respect to the primary lifting surface.

14. The aircraft according to claim 13, wherein the second lifting surface is hinged with respect to the fourth lifting surface and the movement of the second lifting surface includes rotating the second lifting surface about the hinge.

15. The aircraft according to claim 1, wherein the first and second lifting surfaces each include at least one aperture, and the control system is configured to control movement of fluid through the at least one aperture of the first and second lifting surfaces to provide active circulation control.

16. The aircraft according to claim 1, wherein the first tip device is swept forwards and the second tip device is swept backwards.

17. The aircraft according to claim 1, wherein the first tip device is swept backwards and the second tip device is swept backwards.

18. The aircraft according to claim 1, wherein the first tip device is swept forwards and the second tip device is swept forwards.

19. The aircraft according to claim 1, wherein the primary lifting surface is swept backwards.

20. The aircraft according to claim 1, wherein the primary lifting surface is swept forwards.

21. The aircraft according to claim 1, wherein the primary lifting surface is unswept.

22. The aircraft according to claim 1, wherein the first tip device is located forward of the flexural axis and the second tip device is located aft of the flexural axis.

23. The aircraft according to claim 1, wherein the primary lifting surface defines a wing plane, and the first and second tip devices are substantially co-planar with the wing plane.

24. The aircraft according to claim 1, wherein the first and second tip devices are located in different planes.

25. The aircraft according to claim 24, wherein the first and second tip devices are located in intersecting planes.

26. The aircraft according to claim 24, wherein the primary lifting surface, the first tip device and the second tip device are each located in different parallel planes.

27. The aircraft according to claim 26, wherein the first tip device is mounted on a first pylon extending from the tip of the primary lifting surface, and the second tip device is mounted on a second pylon extending from the tip of the primary lifting surface.

28. A method of controlling an arrangement of lifting surfaces on an aircraft, the arrangement comprising a primary lifting surface having a flexural axis extending in a spanwise direction of the primary lifting surface, a root, and a tip; a first tip device attached to the tip and having a first lifting surface; and a second tip device attached to the tip and having a second lifting surface, and a flight control system coupled to the first and second tip devices; the method comprising: using the flight control system in: i) a first mode of operation in which the first and second lifting surfaces are actively controlled to change a value of torque effective at the primary lifting surface about the flexural axis whilst maintaining a value of lift generated by the first and second tip devices substantially constant, and ii) a second mode of operation in which the first and second lifting surfaces are actively controlled to change a value of lift generated by the first and second tip devices whilst maintaining a value of torque effective at the primary lifting surface about the flexural axis substantially constant by performing at least one of: a) moving the first and second lifting surfaces relative to the tip, and b) actively controlling circulation of the first and second lifting surfaces.

29. The method according to claim 28, further comprising moving the first lifting surface mechanically independently of the second lifting surface.

30. The method according to claim 28, further comprising moving the first lifting surface relative to the primary lifting surface in a first direction, and moving the second lifting surface relative to the primary lifting surface in a second direction opposite the first direction.

31. The method according to claim 30, wherein the movement of the first lifting surface is mechanically linked to movement of the second lifting surface.

32. The method according to claim 28, further comprising rotating the first lifting surface relative to the tip.

33. The method according to claim 28, further comprising rotating the second lifting surface relative to the tip.

34. The method according to claim 28, further comprising controlling movement of fluid through at least one aperture in each of the first and second lifting surfaces to provide active circulation control.

35. The method according to claim 28, wherein the arrangement of lifting surfaces is provided at each of a port side and a starboard side of the aircraft, and the method comprises changing a value of torque effective at the respective port and starboard primary lifting surfaces about their flexural axes to effect one or more of: i) roll control of the aircraft; ii) yaw control of the aircraft; iii) pitch control of the aircraft; iv) tip vortex control; and v) drag control.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0030] Embodiments of the invention will now be described with reference to the accompanying drawings, in which:

[0031] FIGS. 1a-c illustrate a primary lifting surface with a tip device according to a first embodiment;

[0032] FIG. 2 illustrates a control system for the tip device of FIG. 1;

[0033] FIG. 3 illustrates the movement of the tip device of FIG. 1 under the control system;

[0034] FIGS. 4a-c illustrate a primary lifting surface with a tip device according to a second embodiment;

[0035] FIGS. 5a-c illustrate a primary lifting surface with a tip device according to a third embodiment;

[0036] FIG. 6 illustrates a first alternative actuator for the control system of the first embodiment;

[0037] FIG. 7 illustrates a second alternative actuator for the control system of the first embodiment;

[0038] FIG. 8 illustrates an alternative primary lifting surface for the first embodiment;

[0039] FIGS. 9a-c illustrate a primary lifting surface with a tip device according to a fourth embodiment; and

[0040] FIG. 10 illustrates a primary lifting surface with a tip device according to a fifth embodiment.

DETAILED DESCRIPTION OF EMBODIMENT(S)

[0041] In the first embodiment shown in FIGS. 1a to c, 2 and 3, a lifting surface 1 is arranged as a wing of a fixed wing aircraft, in particular a cranked, aft swept transonic wing, e.g. for a civil airliner. It will be appreciated that the lifting surface 1 may take a variety of different planform shapes and profiles depending on the particular application. In particular, the lifting surface 1 may have a straight trailing edge, may be un-swept or swept forwards (leading edge sweep or quarter chord sweep), and/or may have a curved leading and/or trailing edge.

[0042] The lifting surface 1 has a root 2 at the inboard end of the lifting surface and a tip 3 at the outboard end of the lifting surface. The flexural axis (elastic axis) of the lifting surface is indicated by broken line 4.

[0043] Attached to the tip 3 of the lifting surface is a tip device indicated generally by reference numeral 5. In the first embodiment the tip device 5 comprises a first tip device 6 attached to the tip 3 and having a first lifting surface 7 moveable relative to the primary lifting surface 1. The tip device 5 further comprises a second tip device 8 attached to the tip 3 and having a second lifting surface 9 moveable relative to the primary lifting surface 1. As best shown in FIG. 1b the first tip device 6 is substantially planar and the second tip device 8 is also substantially planar, and the first and second tip devices 6, 8 lie substantially co-planar with the plane of the primary lifting surface 1.

[0044] As best shown in FIGS. 1a and 1c the first tip device 6 is swept forwards and the second tip device 8 is swept backwards. The first tip device 6 has a leading edge which is swept forward with respect to the aft sweep of the leading edge of the primary lifting surface 1. The first tip device leading edge is also swept forward with respect to the spanwise direction (i.e. perpendicular to the chord) at the tip 3. The second tip device 8 has a leading edge swept aft with respect to the leading edge sweep of the primary lifting surface 1 and also swept aft with respect to the spanwise direction.

[0045] In other embodiments it may be desirable that the first tip device 6 is swept forward with respect to the leading edge sweep of the primary lifting surface 1 but is either un-swept or swept aft with respect to the spanwise direction. Also, it may be desirable that the second tip device 8 is swept aft with respect to the spanwise direction but is either un-swept or swept forward with respect to the leading edge of the primary lifting surface 1.

[0046] As shown in FIG. 2 the first tip device 6 is mounted for rotation about axis 10 extending perpendicular to the chordwise direction at the tip 3. Similarly, the second tip device 8 is mounted for rotation about axis 11 extending substantially perpendicular to the chordwise direction at the tip 3. A first actuator 12 mounted in the outboard end of the primary lifting surface 1 adjacent to the tip 3 is coupled to the first tip device 6 for rotating the first tip device 6 about axis 10. A second actuator 13 is mounted in the outboard end of the primary lifting surface 1 adjacent to the tip 3 and is coupled to the second tip device 8 for rotating the second tip device 8 about axis 11. The actuators 12, 13 may be arranged as rotary actuators, for example.

[0047] The actuators 12 and 13 are connected to a control system 14. The control system 14 may either form part of, or be connected to, a flight control system (not shown) of the aircraft. The control system 14 is arranged for moving the first and second lifting surfaces 7, 9 relative to the tip 3. Movement of the first lifting surface is mechanically independent of movement of the second lifting surface, however for simplified versions of the device, a single actuator may be used to control both lifting surfaces.

[0048] The control system 14 is operable to move the first lifting surface 7 relative to the second lifting surface 9 to change a value of torque effective at the primary lifting surface 1 about the flexural axis 4. By changing the torque effective at the primary lifting surface about the flexural axis during flight it becomes possible to control the wing twist and hence the aerodynamic loading distribution across the primary lifting surface in the spanwise direction. The amount of torque generated by the tip device 5 is controlled by the control system 14, e.g. to optimise the twist distribution of the primary lifting surface according to operating and environmental conditions.

[0049] For example, during cruise, the twist of the wing may advantageously be set to provide minimum fuel burn (corresponding to maximum lift/drag ratio) for the instantaneous aircraft gross weight and weight distribution. For manoeuvres and gusts the twist may be set to minimise the loads effective at the wing or improve ride comfort. At high Mach numbers the tip device 5 may be used to counteract or delaying the unstable flutter point. In addition, by having independent control of each of the first and second tip devices 6, 8 it is possible to assist (i.e. make smaller) or even replace the function of flight control surfaces such as ailerons to enhance manoeuvring capabilities or achieve the requisite capabilities with lower complexity and/or weight.

[0050] This wing loading control function of the wing tip device 5 is provided in addition to conventional vortex drag reduction associated with conventional tip devices. Since the torque generated through aerodynamic means by the tip device 5 is dependent on the force and the distance of the centre of pressure of the first and second lifting surfaces from the flexural axis 4, the configuration of the tip device 5 is optimised by arranging the tip device 5 as such that the first lifting surface 7 has a centre of pressure significantly offset from the flexural axis 4 in the forward direction (of the aircraft) and arranging the centre of pressure of the second lifting surface 9 at a significant offset from the flexural axis 4 in the aft direction.

[0051] The torque generated by each of the first and second tip devices 6, 8 is directly dependent on the aerodynamic lift (whether positive or negative lift) developed by their respective lifting surfaces 7, 9. It is to be expected that changing the angle of incidence (angle of attack) of one or both of the first and second lifting surfaces 7, 9 will directly affect the lift generated by the tip device 5 as a whole. The lift generated by the tip device 5 influences the bending of the primary lifting surface 1 as well as the vortex drag developed by the primary lifting surface and the tip device combined. In some circumstances it may be desirable to maintain the lift generated by the tip device 5 unchanged whilst altering the torque generated by the tip device 5 and therefore controlling the twist of the primary lifting surface 1. Similarly, it may be desirable under some circumstances to maintain the value of torque exerted on the primary lifting surface constant whilst changing the value of lift generated by the tip device 5 as a whole.

[0052] To this end, the control system is operable in a first mode in which the first and second lifting surfaces are moved relative to one another to change the value of torque effective at the primary lifting surface about the flexural axis whilst maintaining a value of lift generated by the first and second tip devices substantially constant. The control system may be operable in a second mode in which the first and second lifting surfaces are moved in the same direction to change a value of lift generated by the first and second tip devices whilst maintaining a value of torque effective at the primary lifting surface about the flexural axis substantially constant.

[0053] By operating the control system 14 in this way it becomes possible to, for example, maintain a substantially constant torque effective at the primary lifting surface by the tip device 5 whilst changing the lift generated by the tip device 5 to reduce loads or to perform a manoeuver such as a roll.

[0054] FIG. 3 illustrates a side view of the primary lifting surface 1 having the tip device 5 illustrating how rotation of the first and second tip devices 6, 8 about their axis of rotation 10, 11 respectively varies the angle of incidence (angle of attack) of the respective first and second tip devices 6, 8 with respect to the free stream airflow, S.

[0055] For the tip device 5 to function most effectively the primary lifting surface 1 is required to be relatively flexible about the flexural axis 4. Otherwise, the torque generated by the device 5 will be largely ineffectual in controlling twist of the primary lifting surface from the root to the tip 3. However, it will be appreciated that structural constraints will limit the degree of torsional flexibility achievable for any given primary lifting surface.

[0056] FIGS. 4a to 4c illustrate a second embodiment in which like reference numerals have been used to denote like parts and only those differences over the first embodiment will be described in detail below. In the second embodiment the tip device 5 comprises a first tip device 6 similar to the first embodiment and a second tip device 8 having a second lifting surface 9. The tip device 5 differs from the tip device 5 of the first embodiment only in that the second tip device 8 extends out of the plane of the primary lifting surface 1, whereas the first tip device 6 remains in the plane of the primary lifting surface. This is best shown in FIGS. 4b and 4c. The second tip device 8 is attached to the tip 3 of the lifting surface 1 and extends upwardly and rearwardly from the tip 3. In all other respects the primary lifting surface 1 and the tip device 5 are identical to the primary lifting surface 1 and the tip device 5 of the first embodiment.

[0057] By positioning the second tip device so as to extend out of the plane of the primary lifting surface 1 so as to form an angle of approximately 10-30 with the plane of the primary lifting surface 1 the second tip device 8 avoids potential wake impingement effects from the first tip device 6 positioned forwardly of the second tip device 8.

[0058] The control system and actuators for controlling movement of the first and second tip devices 6, 8, although not shown in FIGS. 4a to 4c, are identical to those shown in FIGS. 2 and 3 for the first embodiment to substantially the same effects.

[0059] FIGS. 5a to 5c illustrate a third embodiment in which the primary lifting surface 1 is identical to that of the first embodiment and like reference numerals have been used to denote like parts with the first embodiment. Attached to the tip 3 of the primary lifting surface 1 is a tip device 5 comprising a first tip device 6 having a first lifting surface 7 moveable relative to the primary lifting surface 1, and a second tip device 8 attached to the tip 3 and having a second lifting surface 9 moveable relative to the primary lifting surface 1. Unlike the tip device 5 of the first embodiment, the tip device 5 of the third embodiment has the first and second tip devices 6 and 8 rotatably mounted on pylons (or tip fence) 15, 16 respectively, as best shown in FIG. 5c. The first pylon 15 is attached to a forward portion of the tip 3. The second pylon 16 is attached to a rear portion of the tip 3. The pylons 15 and 16 extend substantially perpendicular to the plane of the primary lifting surface 1, i.e. in a substantially vertical direction when the aircraft is in steady level flight. The first pylon 15 extends downwardly and forwardly of the tip 3 and the second pylon 16 extends upwardly and rearwardly from the tip 3.

[0060] The first tip device 6 is mounted at the lower edge of the pylon 15 for rotation about a substantially spanwise axis. The second tip device 8 is mounted at the upper edge of the second pylon 16 for rotation about a substantially span wise axis. The first tip device 5 has a first lifting surface 7 with a substantially trapezoidal planform and aft swept leading and trailing edges. The second tip device 8 has a second lifting surface 9 with a substantially trapezoidal planform and aft swept leading and trailing edges.

[0061] Similar to the first embodiment, the first and second tip devices 6 and 8 are moved by actuators under a control system similar to that shown and described with respect to FIG. 2 relating to the first embodiment and to similar effects.

[0062] In each of the first to third embodiments described above, the first and second tip devices have a leading edge and a trailing edge and their respective lifting surfaces extend full chord between the leading and trailing edges. FIG. 6 illustrates an alternative arrangement which may be adopted in any of the first to third embodiments. In the arrangement shown in FIG. 6 the first tip device 17 has a moveable first lifting surface 18 and a fixed third lifting surface 20. The first lifting surface 18 extends only part chord between the leading edge 22 and the trailing edge 23 of the first tip device, and is positioned aft of the fixed lifting surface 20, although it may alternatively be positioned forward of it. An actuator 24 is arranged to move the first lifting surface 18 with respect to the third lifting surface 20. The second tip device (not shown) may be arranged similarly.

[0063] FIG. 7 illustrates a yet further arrangement of the tip device which may be employed in any of the first to third embodiments described above. In the arrangement shown in FIG. 7 the first tip device 19 has an actuator 26 arranged as a torque tube embedded within the aerofoil profile of the first lifting surface 25. The actuator 26 is configured for rotating the tip 27 of the first tip device 19 with respect to the root 28 thereof so as to twist the first lifting surface 25 along its length from the root end 28 to the tip end 27. This has the effect of changing the angle of the incidence (angle of attack) at the tip relative to the angle of the incidence at the root. The actuator for the torque tube may be located in the first tip device and/or the primary lifting surface. The second tip device may be arranged similarly. The torque tube or other actuator may be arranged to more generally morph the shape of the lifting surface to one of a plurality of desired shapes rather than simply twisting the lifting surface from root to tip.

[0064] FIG. 8 illustrates a yet further configuration in which the primary lifting surface 1 is swept forwardly and has straight leading and trailing edges. As shown in FIG. 8 the tip device 5 is identical to that of the first embodiment but it will be appreciated that any of the tip devices described above may be used in combination with the forward swept primary lifting surface 1 shown in FIG. 8. Forward swept wings do not naturally offer load alleviation and so are discounted for many applications. However, the invention provides control to counteract the load increases due to the structural configuration and so applications where forward swept wings would otherwise be beneficial are now realised.

[0065] High aspect ratio wings typically suffer the problem that structural weight becomes a limiting factor with respect to the maximum practical aspect ratio, and also the dynamic behaviour of the wing becomes more challenging to predict and control. The invention described herein has advantages in enabling higher aspect ratio wings than previously achievable in practice due to the active control at the tip.

[0066] The invention also opens up the possibility to create highly flexible (in torsion) wings. Whereas excessive torsion of the wing a static wing tip device would be undesirable, the active wing tip device control of the invention can accommodate and take advantage of highly flexible wing structures to allow large changes in wing shape across the flight envelope.

[0067] FIGS. 9a to 9c illustrate a fourth embodiment in which the primary lifting surface 1 is identical to that of the first embodiment and like reference numerals have been used to denote like parts with the first embodiment. Attached to the tip 3 of the primary lifting surface 1 is a tip device 5 comprising a first tip device 6 having a first lifting surface 7 moveable relative to the primary lifting surface 1, and a second tip device 8 attached to the tip 3 and having a second lifting surface 9 moveable relative to the primary lifting surface 1. Unlike the tip device 5 of the first embodiment, the tip device 5 of the fourth embodiment has the first and second tip devices 6 and 8 formed as curved tip feathers.

[0068] The first lifting surface 7 extends curving forwardly and downwardly from a forward portion of the tip chord. The second lifting surface 9 extends curving rearwardly and upwardly from a rearward portion of the tip chord. In an alternative arrangement, the first lifting surface may curve forwardly and upwardly from the forward portion of the tip chord and the second lifting surface may curve rearwardly and downwardly from a rearward portion of the tip chord. The first and second lifting surfaces 7 and 9 have curved leading and trailing edges. The leading edge of the first lifting surface extends from the leading edge of the primary lifting surface at the tip and curves forwardly in an S curve towards the tip of the first tip device. The trailing edge of the first lifting surface sweeps forwardly in a continuous curve towards the tip of the first tip device. The trailing edge of the second lifting surface extends from the trailing edge of the primary lifting surface at the tip and curves rearwardly in an S curve towards the tip of the second tip device. The leading edge of the second lifting surface sweeps rearwardly in a continuous curve towards the tip of the second tip device.

[0069] The first and second tip devices are each mounted for rotation about a respective hinge line at the tip of the primary lifting surface 1. Unlike the first embodiment, the hinge lines are staggered and are inclined with respect to the free stream flow direction.

[0070] Similar to the first embodiment, the first and second tip devices 6 and 8 are moved by actuators under a control system similar to that shown and described with respect to FIG. 2 relating to the first embodiment and to similar effects. Alternatively, the part chord lifting surface, or the morphing/twisting lifting surfaces, described with respect to with respect to FIG. 7 may be used in combination with the tip feathers of the fourth embodiment.

[0071] FIG. 10 illustrates a fifth embodiment in which the primary lifting surface 1 is identical to that of the first embodiment and like reference numerals have been used to denote like parts with the first embodiment. Attached to the tip 3 of the primary lifting surface 1 is a tip device 50 comprising a first tip device 60 having a first lifting surface 70, and a second tip device 80 attached to the tip 3 and having a second lifting surface 90. The shape of the first and second tip devices is identical to those of the first embodiment.

[0072] Unlike the tip device 5 of the first embodiment, the first and second lifting surfaces 70, 90 each include an aperture 71, 91. In the illustrated example the apertures 71, 91 are each a single straight slit (a narrow slot) in the respective low pressure (upper) surfaces of the first and second lifting surfaces 70, 90. Each aperture is fluidly coupled to an active circulation control device 72, 92 which ejects and/or admits fluid flow through the aperture. The apertures are located adjacent the trailing edge of the respective lifting surfaces in the illustrated example. The active circulation control devices 72, 92 are connected to a control system 140. The control system 140 may either form part of, or be connected to, a flight control system (not shown) of the aircraft.

[0073] Active circulation control devices are known in the art which eject a fluid into the boundary layer/airflow around the lifting surface, or which admit fluid from the boundary layer/airflow around the lifting surface, or which eject and admit fluid alternately. These devices include a fluid pump and a reservoir beneath the lifting surface to provide a suction and/or blown slot in that surface. By controlling the circulation the lift and/or lift distribution of the lifting surface is altered. Since the first and second lifting surfaces have a centre of pressure on either side of the wing flexural axis this change in lift/lift distribution can be altered to change a value of torque effective at the primary lifting surface about the flexural axis.

[0074] As an alternative to the single slit, the apertures may be one or more rows of slots or holes. The active circulation control may be used as an alternative to physically moving the first and second lifting surfaces to alter the lift/lift distribution and thereby change the value of torque effective at the primary lifting surface about the flexural axis, or further alternatively the active circulation control may be combined with the physically movable first and second lifting surfaces to further enhance the active aerodynamic control of the lift/lift distribution. As such the features of the fifth embodiment may be combined with those of any of the other embodiments described above.

[0075] The embodiments described above relate to wings of fixed civil airliners, but the invention has broad application to a variety of flexible lifting surfaces, including rotary wings (helicopter blades, where a tip torque device could assist the manoeuvrability and control of the rotor), wind turbines, compressor blades, propellers, gliders, etc.

[0076] Although the invention has been described above with reference to one or more preferred embodiments, it will be appreciated that various changes or modifications may be made without departing from the scope of the invention as defined in the appended claims.