GB2568743A - System for an aircraft wing - Google Patents
System for an aircraft wing Download PDFInfo
- Publication number
- GB2568743A GB2568743A GB1719681.7A GB201719681A GB2568743A GB 2568743 A GB2568743 A GB 2568743A GB 201719681 A GB201719681 A GB 201719681A GB 2568743 A GB2568743 A GB 2568743A
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- flap
- deployment
- deployment path
- track
- path
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- 238000000034 method Methods 0.000 claims abstract description 30
- 230000001419 dependent effect Effects 0.000 claims 1
- 230000008878 coupling Effects 0.000 abstract 1
- 238000010168 coupling process Methods 0.000 abstract 1
- 238000005859 coupling reaction Methods 0.000 abstract 1
- 238000010586 diagram Methods 0.000 description 3
- 230000007935 neutral effect Effects 0.000 description 3
- 230000000694 effects Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C9/06—Adjustable control surfaces or members, e.g. rudders with two or more independent movements
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C9/14—Adjustable control surfaces or members, e.g. rudders forming slots
- B64C9/16—Adjustable control surfaces or members, e.g. rudders forming slots at the rear of the wing
- B64C9/18—Adjustable control surfaces or members, e.g. rudders forming slots at the rear of the wing by single flaps
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Tires In General (AREA)
- Transmission Devices (AREA)
Abstract
Deployment system and method for an aircraft wing 1 comprising a flap 20 movable along a deployment path 26 between a retracted position and a deployed position, and an actuating system 100 to selectively vary the deployment path of at least part of the flap. This may be achieved by selectively varying the track 110 upon which the flap is mounted, for example by moving the trailing end of the track 112 using an actuator. Alternatively it can be achieved by causing the flap 220 to rotate relative to the deployment path 226 or by moving the flap relative to the deployment path using an actuator 200. This may be achieved by coupling a trailing link 230 to a trailing end of the flap 222 at a first pivot 202 and to the support structure 240 with the actuating system 200 comprising a mechanism for varying the length of the trailing link.
Description
TECHNICAL FIELD [0001] The present invention relates to systems and methods for moving an aircraft wing flap between a retracted position and a deployed position.
BACKGROUND [0002] Aircraft wings may comprise components such as spoilers and flaps, designed to change the shape of the aircraft wing and thus alter the performance characteristics of the aircraft wing. A flap normally forms part of a trailing edge of an aircraft wing and can be movable relative to a main fixed wing portion.
SUMMARY [0003] A first aspect of the present invention provides a deployment system for an aircraft wing, the system comprising a flap moveable between a retracted position and a deployed position, and an actuating system to selectively vary a deployment path followed by at least part of the flap during movement of the flap between the retracted position and the deployed position.
[0004] Optionally, the deployment system comprises a track that defines the deployment path followed by at least part of the flap, wherein the actuating system comprises means to selectively vary a direction of the track, thereby selectively varying the deployment path followed by at least part of the flap.
[0005] Optionally, a trailing end of the track is moved by the actuating system in a direction having a component perpendicular to the chord to the aircraft wing.
[0006] Optionally, a trailing end of the track is pivotable relative to a leading end of the track about an axis substantially parallel to the longitudinal axis of the flap.
[0007] Optionally, at least a portion of a trailing end of the track is flexible.
[0008] Optionally, the deployment system comprises a beam to support the track, wherein the beam extends in a direction parallel to the chord of the aircraft wing, and wherein a trailing end of the beam is moved by the actuating system to move the trailing end of the track.
[0009] Optionally, the deployment system comprises comprising a trailing link, wherein a first end of the trailing link is pivotably coupled to a trailing end of the flap at a first pivot, and wherein a second end of the trailing link is pivotably coupled to a support structure at a second pivot, and wherein the actuating system comprises a mechanism for varying the length of the trailing link, thereby varying the orientation of the flap relative to the deployment path followed by at least part of the flap.
[0010] Optionally, the trailing link is an actuator.
[0011] Optionally, the support structure is a trailing end of the beam.
[0012] Optionally, the deployment system comprises a controller configured to move the flap along a deployment path between a retracted position and a deployed position and selectively vary the deployment path and/or the orientation of the flap relative to the deployment path.
[0013] Optionally, the deployment path defines a fowler motion.
[0014] A second aspect of the present invention provides an aircraft wing comprising a main fixed wing portion, a flap movable along a deployment path relative to the main fixed wing portion, and a mechanism to selectively vary the orientation and/or position of the flap relative to the deployment path.
[0015] Optionally, the mechanism is an actuating mechanism according to the first aspect of the present invention.
[0016] Optionally, the deployment path defines a fowler motion.
[0017] A third aspect of the present invention provides a method of deploying a flap on an aircraft wing, the method comprising moving a flap along a deployment path between a retracted position and a deployed position, and selectively varying the position and/or orientation of the flap relative to the deployment path.
[0018] Optionally, the method comprises selectively changing the orientation of the flap relative to the deployment path during said moving.
[0019] Optionally, the method comprises selectively varying the deployment path.
[0020] Optionally, the deployment path defines a fowler motion.
[0021] A fourth aspect of the present invention provides a method of deploying a flap on an aircraft wing, the method comprising selecting, based on a predetermined criterion, a deployment path to deploy the flap, using an actuating mechanism to control the deployment path; and moving the flap along the selected deployment path.
[0022] Optionally, the deployment path defines a fowler motion.
[0023] A fifth aspect of the present invention provides an aircraft comprising a deployment system according to the first aspect of the present invention or an aircraft wing according to the second aspect of the present invention.
[0024] A sixth aspect of the present invention provides an aircraft configured to perform a method according to the third or fourth aspect of the present invention.
BRIEF DESCRIPTION OF THE DRAWINGS [0025] Embodiments of the invention will now be described, by way of example only, with reference to the accompanying drawings, in which:
[0026] Figures la and lb show schematic cross-sectional side-views of an aircraft wing comprising a flap;
[0027] Figures 2a and 2b show schematic cross-sectional side-views of an aircraft wing according to an embodiment of the present invention;
[0028] Figures 3a - 3d show schematic cross-sectional side-views of an aircraft wing according to embodiments of the present invention;
[0029] Figure 4 shows a schematic diagram of a system according to an embodiment of the present invention;
[0030] Figure 5 is a flow diagram showing an example of a method according an embodiment of the present invention; and [0031] Figure 6 is a schematic front view of an example of an aircraft according to an embodiment of the present invention.
DETAILED DESCRIPTION [0032] One type of flap motion, known as fowler motion, includes aft translation accompanied with downward rotation of a flap relative to a main fixed wing portion. A slot effect is observed when a gap is formed between the wing and the flap. The gap forces high pressure air from below the wing over the flap, to help airflow over the wing remain attached to the flap, thus increasing lift.
[0033] Figures la and lb show schematic cross-sectional side-views of a prior art aircraft wing 1 comprising a flap 20. The wing 1 comprises a main fixed wing portion 2 and a flap 20. The flap 20 is movable in a fowler motion. The flap 20 is positioned aft of the main fixed wing portion 2 relative to a direction of travel X. The flap 20 may extend across a portion of the span of the wing 1 or across substantially all of the span of the wing 1. The flap 20 may comprise a plurality of flap elements positioned longitudinally adjacent to one another along the span of the wing 1.
[0034] Figure la shows the flap 20 in a retracted position. The flap 20 is oriented relative to the main fixed wing portion 2 such that the wing 1 has a substantially aerofoil crosssection.
[0035] Figure lb shows the wing 1 in a configuration in which the flap 20 has been moved from the retracted position to a deployed position relative to the main fixed wing portion
2. In the deployed position, the flap 20 is further aft of the main fixed wing portion 2 and rotated relative to the main fixed wing portion 2 than in the retracted position. In the deployed position, a gap 3 is formed between a trailing edge of the main fixed wing portion 4 and a leading edge 22 of the flap 20, causing the slot effect aforementioned.
[0036] In some embodiments of the present invention, an aircraft wing comprises a main fixed wing portion, a flap movable along a deployment path relative to the main fixed wing portion, and a mechanism to selectively vary the orientation and/or position of the flap relative to the deployment path. The mechanism allows the flap to be configurable in a plurality of positions relative to the main fixed wing portion. In some embodiments, the deployment path defines a fowler motion.
[0037] Figures 2a and 2b show schematic cross-sectional side-views of the aircraft wing 1 according to some embodiments of the present invention. The aircraft wing 1 comprises a deployment system 10. Embodiments of the present invention relate to a deployment system 10 comprising a flap 20 and an actuating system 100. The flap 20 is movable between a retracted position and a deployed position. The actuating system 100 is to selectively vary a deployment path 26 followed by at least part of the flap 20 during movement of the flap between the retracted position and the deployed position. In other words, the actuating system 100 enables different deployment paths to be used in different instances of deployment of the flap 20. In some embodiments, the deployment path 26 defines a fowler motion.
[0038] The actuating system 100 may selectively vary the deployment path 26 of at least part of the flap 20 by causing the flap 20 to rotate relative to the deployment path 26 or by moving the flap 20 relative to the deployment path 26. The actuating system 100 may be, for example, a hydraulic system, an electrical system or an electro-mechanical system. The actuating system 100 may be an actuating mechanism.
[0039] In the embodiment shown in Figures 2a and 2b, the actuating system 100 comprises a track 110 that defines the deployment path 26 of the flap 20. In some embodiments, the deployment system 10 comprises a plurality of tracks 110 along the span of the wing 1. The tracks 110 extend in a direction X parallel to the chord of the wing 1. In other embodiments, the actuating system 100 may comprise a multi-link system configured to move the flap 20 along the deployment path.
[0040] In the embodiment shown in Figures 2a and 2b, the flap 20 is moved along the deployment path 26 by means of a carriage 115 that travels along the length of the track 110. The flap 20 may be fixedly or pivotally connected to the carriage 115 the leading end 24 of the flap 20. Other means of moving the flap 20 along the deployment path 26 are envisaged, for example by an actuator or a rack and pinion.
[0041] The actuating system 100 comprises means to selectively vary a direction of the track 110, thereby selectively varying the deployment path of the flap 20. In some embodiments, a trailing end 112 of the track 110 is moved by the actuating system 100 in a direction Y. Direction Y has a component perpendicular to the chord to the aircraft wing 1.
[0042] In the embodiment shown in Figures 2a and 2b, at least a portion of the trailing end 112 of the track 110 is flexible to allow the trailing end 112 of the track 110 to move in the direction Y relative to the main fixed wing portion 1 and the leading end 114 of the track 110, thereby selectively varying the deployment path of the flap 20 to a new deployment path 28. Figure 2a shows the trailing end 112 of the track 110 in a first position relative to the leading end 114 of the track 110. Figure 2b shows the trailing end 112 of the track 110 in a second position relative to the leading end 114 of the track 110. In the second position, the trailing end 112 of the track 114 has been moved in the direction Y relative to the first position, to selectively vary the deployment path of the flap 20. In other embodiments, the trailing end 112 of the track 110 is pivotable relative to a leading end 114 of the track 110 about an axis substantially parallel to a longitudinal axis of the flap 20. Pivoting of the trailing end 112 of the track 110 about the axis causes the trailing end 112 of the track 110 to move in the direction Y relative to the main fixed wing portion 1 and the leading end 114 of the track 110.
[0043] In the embodiment shown in Figures 2a and 2b, the deployment system 10 comprises a beam 120 to support the track 110. The beam extends in a direction X parallel to the chord of the aircraft wing 1 and the track 110. In embodiments in which the deployment system 10 comprises a plurality of tracks 110, the deployment system comprises a plurality of corresponding beams 120.
[0044] In these embodiments, a trailing end 122 of the beam 120 is moved by the actuating system 100 to move the trailing end 112 of the track 100 in the direction Y. The trailing end 122 of the beam 120 is rotated about the pivot 126 by the actuating mechanism 100 to selectively vary the deployment path of the flap 20 to the new deployment path 28. In some embodiments, the trailing end 122 of the beam 120 is rotated upwards about the pivot 126 by up to 5°. In some embodiments, the trailing end 122 of the beam 120 is rotated downwards about the pivot 126 by up to 20°.
[0045] By moving the trailing end of the track 110 relative to the main fixed wing portion 2, the deployed position of the flap 20 is varied relative to the main fixed wing portion 2, thereby helping to increase the number of operational configurations of the wing 1. For example, the size of the gap 3 (shown in Figure lb) can be varied to change the lift forces on the wing 1.
[0046] Figures 3a - 3c show schematic cross-sectional side-views of an aircraft wing 1 according to an embodiment of the present invention. The wing 1 comprises a deployment system 30 comprising an actuating system 200 and a flap 220 movable along a deployment path 226. In some embodiments, the deployment path 226 defines a fowler motion. The deployment system 30 comprises a trailing link 230. A first end 232 of the trailing link 230 is pivotably coupled to a trailing end 222 of the flap 220 at a first pivot 202. A second end 234 of the trailing link 230 is pivotably coupled to a support structure 240 at a second pivot 204. In the embodiments shown in Figures 3a-3c, the second pivot 204 is mounted on a trailing carriage 215 that is slidable along a track, the track as described with reference to Figures 2a and 2b. A leading end of the flap 220 is pivotally mounted on a leading carriage 217 that is slidable along the track. In some embodiments, the leading carriage 217 and the trailing carriage 215 are configured to remain at a fixed distance from one another, independent of their position along the track. For example, the leading carriage 217 and the trailing carriage 215 may be connected by a rigid link (not shown).
[0047] The actuating system 200 comprises a mechanism for varying the length of the trailing link 230. Varying the length of the trailing link 230 may be done selectively. In some embodiments, the trailing link 230 is an actuator, for example a hydraulic actuator. In some embodiments, the trailing link 230 comprises a linear actuator. In some embodiments, the trailing link 230 comprises a rotary actuator, for example a rotary actuator with an offset pivot connected to a fixed length member. Varying the length of the trailing link 230 causes the flap 220 to rotate about the first pivot 202, thereby varying the orientation of the flap 220 relative to the deployment path 226, and varying the deployment path of part of the flap 220. Figure 3 a shows the trailing link 230 in a neutral position in which the flap 220 is substantially parallel to the deployment path 226. Figure 3b shows the trailing link 230 in a lengthened position relative to the neutral position. In this configuration, the trailing end of the flap 220 is rotated upwards relative to the deployment path 226. Figure 3c shows the trailing link 230 in a shortened position relative to the neutral position. In this configuration, the trailing end of the flap 220 is rotated downwards relative to the deployment path 226.
[0048] Figure 3d shows a schematic cross-sectional side-view of an aircraft wing 1 according to an embodiment of the present invention. The wing 1 is similar to that shown in Figures 3a-3c, except that the first end 232 of the trailing link 230 is pivotably coupled to a leading end 224 of the flap 220 at the first pivot 202. The second end 234 of the trailing link 230 is pivotably coupled to the support structure 240 at a second pivot 204. The second pivot 204 may be a sliding pivot that is slidable along the support structure 240 to move the second pivot 204 towards or away from the main fixed wing portion 2.
[0049] It is to be understood that Figures 3a-3d are schematic drawings only, and that the position of the first pivot 202 may be at any other suitable location on the flap 220. For example, in the embodiments shown in Figures 3a-3c, the first pivot 202 may be located such that, when the flap 220 is in the retracted position, the first pivot 202 is vertically above the second pivot 204.
[0050] Accordingly, the embodiments shown in Figures 3a-3d allow the camber of the wing 1 to be modified to increase the operational capabilities of the wing 1. In some embodiments, the length of trailing link 230 may be varied as the flap 220 is moved between the retracted position and the deployed position, to maintain the pitch of the flap 220 relative to the main fixed wing portion 2. In some embodiments, varying the length of the trailing link 230 may change the angle of the flap 220 relative to the main fixed wing portion 2 by up to 20° in either direction.
[0051] In some embodiments, the actuating system 200 is used together with the track described above with reference to Figures 2a and 2b, and the support structure 240 is a trailing end of a beam such as the beam 120 described with reference to Figures 2a and 2b. In these embodiments, the actuating system 200 may be configured to vary the length of the trailing link 230 and to selectively vary a direction of the track, thereby to selectively vary the position and the orientation of the flap 220 relative to the deployment path 226.
[0052] Figure 4 shows a schematic diagram of a deployment system 40 according to embodiments of the present invention. In the embodiment shown in Figure 4, the system 40 comprises a flap 320, an actuating system 300, and a controller 310. The flap 320 and the actuating system 300 may be as described herein with reference to Figures 2a-3c. The controller 310 is configured to cause the flap 320 to move along a deployment path between a retracted position and a deployed position, and to selectively vary the deployment path and/or the orientation of the flap 320 relative to the deployment path. That is, the controller 310 is configured to control the actuating system 300.
[0053] In some embodiments, the controller 310 is comprised in the wing 1. For example, the controller 310 is positioned within the main fixed wing portion 2. In other embodiments, the controller 310 is comprised in the fuselage of the aircraft. The controller 310 is connected to a central aircraft control system, and may send commands to the actuating system 300 automatically, in response inputs from other systems in the aircraft, and/or the controller 310 may send commands to the actuating system 300 in response to commands received from the cockpit of the aircraft.
[0054] The deployment system 10, 30, 40 comprises a mechanism for moving the flap 20, 220, 320 between the retracted position and the deployed position. In some embodiments, the actuating system 100, 200, 300 comprises the mechanism.
[0055] In some embodiments (not shown), the deployment system 10, 30, 40 comprises a mechanism to translate the flap 20, 220, 320 in a direction substantially parallel to the chord of the wing 1 from a retracted position to a translated position. The translation may be enabled by a track 110, 220 comprising a leading end that is substantially parallel to the chord of the wing and a trailing link 230 having a variable length. The aircraft wing 1 is configured to remain in a substantially sealed aerofoil configuration when the flap 20, 220, 320 is translated by the mechanism. For example, the deployment system 10, 30, 40 may comprise an upper shroud configured to form a substantially continuous surface between an upper surface of the wing 1 and an upper surface of the flap 20, 220, 320 when the flap 20, 220, 320 is in the retracted position and in the translated position, and a lower shroud configured to form a substantially continuous surface between a lower surface of the wing 1 and a lower surface of the flap 20, 220, 320 when the flap 20, 220, 320 is in the first position and in the second position. The lower shroud and upper shroud may be biased toward respective positions in which the lower shroud and upper shroud contact the flap 20, 220, 320. When the flap 20, 220, 320 is in the deployed position, the lower shroud may be configurable between a slotted position, whereby the lower shroud is positioned to create a slot between a trailing edge of the main fixed wing portion and a leading edge of the flap 20, 220, 320, and a contact position, whereby the lower shroud is in contact with the lower surface of the flap 20, 220, 320.
[0056] Embodiments of the present invention comprise a method 400 of deploying a flap on an aircraft wing, as depicted in Figure 5. The method comprises moving 410 a flap along a deployment path between a retracted position and a deployed position, and selectively varying 420 the position and/or orientation of the flap relative to the deployment path. The method may be performed a deployment system 10, 30, 40 according to the present invention. The method may be controlled by the controller 310. In some embodiments, the deployment path defines a fowler motion. In such embodiment, the moving 410 comprises moving the flap in a fowler motion.
[0057] In some embodiments, the method 400 comprises selectively changing 430 the orientation of the flap relative to the deployment path during said moving. For example, the orientation may be changed by selectively changing the length of a trailing link as described with reference to Figures 3a - 3c.
[0058] In some embodiments, the method 400 comprises selectively varying 440 the deployment path. For example, the deployment path may be varied by moving a trailing end of a track along which the flap is moved, relative to a main fixed wing portion.
[0059] Embodiments of the present invention provide a method of deploying a flap on an aircraft wing. The method comprises selecting, based on a predetermined criterion, a deployment path to deploy the flap. The predetermined criteria may, for example, be a required amount of lift, an optimum wave drag, a particular aircraft manoeuvre or a required load alleviation on the wing. The method further comprises using an actuating mechanism to control the deployment path, and moving the flap along the selected deployment path. Controlling the deployment path with the actuating mechanism may comprise moving a trailing end of the deployment path relative to a main fixed wing portion. In some embodiments, the selected deployment path defines a fowler motion. In such embodiment, the moving comprises moving the flap in a fowler motion.
[0060] Embodiments of the present invention provide an aircraft 500, as shown in Figure
6. In some embodiments, the aircraft comprises one or more main landing gears 510 and a nose landing gear 520. In some embodiments, the aircraft 500 comprises a deployment system 100, 200, 300 according to any of the embodiments described herein. Embodiments of the invention provide an aircraft 500 comprise a wing 1 according to any of the embodiments described herein, as shown in Figure 6. Embodiments of the invention provide an aircraft 500 configured to perform a method 400 according to any of the embodiments described herein.
[0061] The present invention provides systems and methods to provide a larger range of wing configurations of an aircraft wing, thereby to help increase the operational capabilities of the aircraft. Embodiments of the present invention are concerned with providing a flap configurable in a plurality of deployed positions. Embodiments of the present invention provide methods and systems of modifying the orientation and/or position of a flap relative to a deployment path. Embodiments of the present invention may help to tailor an aircraft wing to particular operational requirements, rather than needing a different aircraft.
[0062] It is to noted that the term “or” as used herein is to be interpreted to mean “and/or”, unless expressly stated otherwise.
[0063] The above embodiments are to be understood as non-limiting illustrative examples of how the present invention, and aspects of the present invention, may be implemented. Further examples of the present invention are envisaged. It is to be understood that any feature described in relation to any one embodiment may be used alone, or in combination with other features described, and may also be used in combination with one or more features of any other of the embodiments, or any combination of any other of the embodiments. Furthermore, equivalents and modifications not described above may also be employed without departing from the scope of the present invention, which is defined in the accompanying claims.
Claims (19)
1. A deployment system for an aircraft wing, the system comprising:
a flap movable between a retracted position and a deployed position; and an actuating system to selectively vary a deployment path followed by at least part of the flap during movement of the flap between the retracted position and the deployed position.
2. A deployment system according to any one of the preceding claims, comprising: a track that defines the deployment path followed by at least part of the flap, wherein the actuating system comprises means to selectively vary a direction of the track, thereby selectively varying the deployment path followed by at least part of the flap.
3. A deployment system according to claim 2, wherein a trailing end of the track is moved by the actuating system in a direction having a component perpendicular to the chord to the aircraft wing.
4. A deployment system according to claim 2 or claim 3, wherein a trailing end of the track is pivotable relative to a leading end of the track about an axis substantially parallel to the longitudinal axis of the flap.
5. A deployment system according to any one of claims 2 to 4, wherein at least a portion of a trailing end of the track is flexible.
6. A deployment system according to any one of claims 2 to 5, comprising a beam to support the track, wherein the beam extends in a direction parallel to the chord of the aircraft wing, and wherein a trailing end of the beam is moved by the actuating system to move the trailing end of the track.
7. A deployment system according to any one of the preceding claims, comprising a trailing link, wherein a first end of the trailing link is pivotably coupled to a trailing end of the flap at a first pivot, and wherein a second end of the trailing link is pivotably coupled to a support structure at a second pivot, and wherein the actuating system comprises a mechanism for varying the length of the trailing link, thereby varying the orientation of the flap relative to the deployment path followed by at least part of the flap.
8. A deployment system according to claim 2, wherein the trailing link is an actuator.
9. A deployment system according to claim 7 or claim 8, when dependent on claim 6, wherein the support structure is the trailing end of the beam.
10. A deployment system according to any one of the preceding claims, comprising a controller configured to:
cause the flap to move along the deployment path between a retracted position and a deployed position; and selectively vary the deployment path and/or the orientation of the flap relative to the deployment path.
11. An aircraft wing comprising;
a main fixed wing portion;
a flap movable along a deployment path relative to the main fixed wing portion; and a mechanism to selectively vary the orientation and/or position of the flap relative to the deployment path.
12. A deployment system according to any one of claims 1 to 10 or an aircraft wing according to claim 11, wherein the deployment path defines a fowler motion.
13. A method of deploying a flap on an aircraft wing, the method comprising:
moving a flap along a deployment path between a retracted position and a deployed position; and selectively varying the position and/or orientation of the flap relative to the deployment path.
14. A method according to claim 13, comprising selectively changing the orientation of the flap relative to the deployment path during said moving.
15. A method according to claim 13 or claim 14, comprising selectively varying the deployment path.
16. A method of deploying a flap on an aircraft wing, the method comprising: selecting, based on a predetermined criterion, a deployment path to deploy the flap;
using an actuating mechanism to control the deployment path; and moving the flap along the selected deployment path.
17. A method according to any one of claims 13-16, wherein the deployment path defines a fowler motion.
18. An aircraft comprising a deployment system according to any one of claims 1 to 10 or an aircraft wing according to claim 11 or claim 12.
19. An aircraft configured to perform the method of any one of claims 13 to 16.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB1719681.7A GB2568743B (en) | 2017-11-27 | 2017-11-27 | Variable deployable wing flap |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB1719681.7A GB2568743B (en) | 2017-11-27 | 2017-11-27 | Variable deployable wing flap |
Publications (3)
| Publication Number | Publication Date |
|---|---|
| GB201719681D0 GB201719681D0 (en) | 2018-01-10 |
| GB2568743A true GB2568743A (en) | 2019-05-29 |
| GB2568743B GB2568743B (en) | 2020-06-17 |
Family
ID=60950619
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB1719681.7A Active GB2568743B (en) | 2017-11-27 | 2017-11-27 | Variable deployable wing flap |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB2568743B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP4286271A1 (en) * | 2022-06-01 | 2023-12-06 | Asco Industries NV | Trailing edge flap assembly |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112498661B (en) * | 2020-12-04 | 2024-01-30 | 中国航空工业集团公司沈阳飞机设计研究所 | Multifunctional control surface structure |
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| NL49597C (en) * | ||||
| GB2038737A (en) * | 1979-01-02 | 1980-07-30 | Boeing Co | Mechanization of expanding radius of usb flap |
| EP0017756A1 (en) * | 1979-04-12 | 1980-10-29 | Dornier Gmbh | Lifting flap on an aircraft wing |
| US4763862A (en) * | 1985-06-22 | 1988-08-16 | Mbb Gmbh | Flap drive system for air foils |
| US20150090843A1 (en) * | 2013-09-30 | 2015-04-02 | Airbus Operations S.A.S. | High-lift trailing edge flap system for an aircraft wing unit |
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2017
- 2017-11-27 GB GB1719681.7A patent/GB2568743B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| NL49597C (en) * | ||||
| GB2038737A (en) * | 1979-01-02 | 1980-07-30 | Boeing Co | Mechanization of expanding radius of usb flap |
| EP0017756A1 (en) * | 1979-04-12 | 1980-10-29 | Dornier Gmbh | Lifting flap on an aircraft wing |
| US4763862A (en) * | 1985-06-22 | 1988-08-16 | Mbb Gmbh | Flap drive system for air foils |
| US20150090843A1 (en) * | 2013-09-30 | 2015-04-02 | Airbus Operations S.A.S. | High-lift trailing edge flap system for an aircraft wing unit |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP4286271A1 (en) * | 2022-06-01 | 2023-12-06 | Asco Industries NV | Trailing edge flap assembly |
| US12391360B2 (en) | 2022-06-01 | 2025-08-19 | Asco Industries NV | Actuation assembly, trailing edge flap assembly, actuation system, aircraft wing, and method of operating an aircraft |
Also Published As
| Publication number | Publication date |
|---|---|
| GB201719681D0 (en) | 2018-01-10 |
| GB2568743B (en) | 2020-06-17 |
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