GB2550409A - Wing tip device - Google Patents

Wing tip device Download PDF

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Publication number
GB2550409A
GB2550409A GB1608864.3A GB201608864A GB2550409A GB 2550409 A GB2550409 A GB 2550409A GB 201608864 A GB201608864 A GB 201608864A GB 2550409 A GB2550409 A GB 2550409A
Authority
GB
United Kingdom
Prior art keywords
wing
tip device
wing tip
aircraft
inner section
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Pending
Application number
GB1608864.3A
Other versions
GB201608864D0 (en
Inventor
Thompson Bob
Mann Alan
Wood Norman
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Airbus Operations Ltd
Original Assignee
Airbus Operations Ltd
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Airbus Operations Ltd filed Critical Airbus Operations Ltd
Priority to GB1608864.3A priority Critical patent/GB2550409A/en
Publication of GB201608864D0 publication Critical patent/GB201608864D0/en
Publication of GB2550409A publication Critical patent/GB2550409A/en
Application status is Pending legal-status Critical

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Classifications

    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C3/00Wings
    • B64C3/38Adjustment of complete wings or parts thereof
    • B64C3/56Folding or collapsing to reduce overall dimensions of aircraft
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C23/00Influencing air-flow over aircraft surfaces, not otherwise provided for
    • B64C23/06Influencing air-flow over aircraft surfaces, not otherwise provided for by generating vortices
    • B64C23/065Influencing air-flow over aircraft surfaces, not otherwise provided for by generating vortices at the wing tips
    • B64C23/069Influencing air-flow over aircraft surfaces, not otherwise provided for by generating vortices at the wing tips using one or more wing tip airfoil devices, e.g. winglets, splines, wing tip fences or raked wingtips
    • B64C23/072Influencing air-flow over aircraft surfaces, not otherwise provided for by generating vortices at the wing tips using one or more wing tip airfoil devices, e.g. winglets, splines, wing tip fences or raked wingtips the wing tip airfoil devices being moveable in their entirety
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C3/00Wings
    • B64C3/38Adjustment of complete wings or parts thereof
    • B64C3/40Varying angle of sweep
    • YGENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02TCLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00Aeronautics or air transport
    • Y02T50/10Drag reduction
    • Y02T50/16Drag reduction by influencing airflow
    • Y02T50/162Drag reduction by influencing airflow by generating or controlling vortexes
    • Y02T50/164Drag reduction by influencing airflow by generating or controlling vortexes at the wing tip, e.g. winglets

Abstract

The wing of an aircraft 10 comprises a fixed wing 12 and a wing tip device 14 movable between a flight position and a ground position reducing the wingspan; the wing tip device 14 has an inner section 16 with a dynamic interface 20 connecting it to the fixed wing 12, and an outer section 18 connected to the inner section by a static interface 22. The dynamic interface 20 may allow rotation or folding movement of the wing tip device 14 relative to the fixed wing 12 about a hinge pivot point or slew ring using an actuator, and have a locking mechanism and seals. Elements of the dynamic interface 20 may be located on both the fixed wing 12 and the inner section 16. Preferably the sacrificial outer section 18 has crumple zones to absorb impacts, or have frangible break lines designed to fail if impacted during ground maneuvers, lightning strikes or hail, for example; it may be fastened to the inner section 16 so it can be removed, without affecting the dynamic interface 20 or inner section 16, for repair or replaced with modules to optimize performance. A method of assembling an aircraft is also claimed.

Description

WING ΊΊΡ DEVICE BACKGROUND OF THE INVENTION

[0001] There is a trend towards increasingly large passenger aircraft, for which it is desirable to have correspondingly large wing spans. However, the maximum aircraft span is effectively limited by airport operating rules which govern various clearances required when manoeuvring around the airport (such as the span and/or ground clearance required for gate entry and safe taxiway usage, and aircraft hangar dimensions and deicing pans).

[0002] Therefore, moveable wing tip devices have been introduced into passenger aircraft, where a wing tip device is movable between a flight configuration for use during flight, and a ground configuration for use during ground-based operations. In the ground configuration, the wing tip device is moved away from the flight configuration such that the span of the aircraft wing is reduced, thereby allowing use of existing gates and safe taxiway usage.

[0003] In order to securely fasten the moveable wing tip device in the flight configuration, one or more locking mechanisms are typically used. In addition to a locking mechanism, there tends to also be some actuation mechanism which creates a dynamic interface between the fixed wing and moveable wing tip device to facilitate the movement between the flight configuration, and the ground configuration. Therefore, the end of the wing can be a relatively complex arrangement. The end of the wing is also vulnerable to damage, particularly when an aircraft is on the ground, with the wing tip device still in the flight configuration because the extended wingspan of the aircraft may be larger than the pilot is typically used to handling. The aircraft wing span in the flight configuration may be larger than the maximum wing span for which an airport has been designed, again making the wing tip device vulnerable to damage during ground manoeuvres. The end of the wing may also be vulnerable to environmental damage, such as lightning strike or hail impacts. Damage to this part of the wing may result in an expensive and time consuming repair job.

[0004] The present invention seeks to mitigate the above-mentioned problems. Alternatively or additionally, the present invention seeks to provide an improved wing tip device.

SUMMARY OF THE INVENTION

[0005] The present invention provides an aircraft comprising an aircraft wing, the aircraft wing comprising a fixed wing and a wing tip device at the tip thereof, wherein the wing tip device is configurable between: (i) a flight configuration for use during flight and (ii) a ground configuration for use during ground-based operations, in which ground configuration the wing tip device is moved away from the flight configuration such that the span of the aircraft wing is reduced, wherein the wing tip device comprises an inner section and an outer section, wherein there is a dynamic interface between the inner section and the fixed wing, the dynamic interface configured to allow the wing tip device to move between the flight configuration and ground configuration, and a static interface between the inner section and the outer section.

[0006] The dynamic interface is located at the in-board end of the inner section and the static interface is located at the out-board end of the inner section. The dynamic interface may be arranged to facilitate folding and/or rotational movement of the wing tip device relative to the fixed wing, and various dynamic interfaces will be known to the person skilled in the art. The dynamic interface may include a hinge mechanism, a pivot point, and/or a slew ring. The dynamic interface may comprise one or more actuators. The one or more actuators may be arranged to drive the wing tip device between the flight configuration and the ground configuration. The dynamic interface may comprise a locking mechanism, or a plurality of locking mechanism. The locking mechanism may be configured to lock the wing tip device in a locked flight configuration. The dynamic interface may comprise one or more seals or sealing surfaces. The one or more seals or sealing surfaces may provide a smooth interface between the fixed wing and the wing tip device when in the flight configuration.

[0007] The dynamic interface may comprise one or more elements located on or within the fixed wing and one or more elements located on or within the inner section of the wing tip device.

[0008] The static interface is configured to prevent relative movement between the inner section and outer section of the wing tip device. The static interface may comprise one or more fasteners joining the inner section and outer section of the wing tip device. Such fasteners may include nut and bolt arrangements, and other fasteners as will be recognised by the person skilled in the art. The static interface may be arranged such that the outer section of the wing tip device is removable from the inner section of the wing tip device without requiring any adjustment or interaction with the dynamic interface. The static interface may be arranged such that the outer section of the wing tip device is removable from the inner section of the wing tip device without damage to the inner section of the wing tip device. Such an arrangement may allow for outer wing tips to be changed in order to meet changing mission parameters for an aircraft. For example, different outer wing tips could be provided directed to improved standard performance, cruise being optimised for long flights, improved take-off performance, or improved short range performance.

[0009] The outer section of the wing tip device may be supplied in a modular manner, such that the outer section may be attached, or detached, from the inner section of the wing tip device as a single unit. Such attachment or detachment is may be via the static interface.

[0010] By providing an outer section of the wing tip device with a static interface with the inner section of the wing tip, the job of removing and replacing the outer section of the wing tip device is much more straightforward than replacing a whole wing tip device, including a dynamic interface with the fixed wing. By dividing the wing tip device into an inner section connected to the fixed wing with a dynamic interface, and an outer section connected to the inner section with a static interface, the task of repairing a damaged wing tip device may be simplified. More specifically, the present invention recognises that on a moveable wing tip device, the dynamic interface may be difficult and/or costly to replace, whereas a static interface may be simpler and/or less expensive to replace. Moveable wing tip devices may be especially prone to damage due to the ensuing large span of the aircraft when the wing tip devices are in the flight configuration. The invention recognises that in these circumstances it is especially desirable to provide these two different interfaces because the outer region (which is most likely to be damaged) can be readily repaired or replaced rather than having the whole wing tip device as a replacement element.

[0011] The invention may also be advantageous when building the aircraft. For example, a fixed wing may be provided with the inner section and associated dynamic interface. The fixed wing may be joined to the aircraft body, and the outer section of the wing tip device may be attached via the static interface to the inner section of the wing tip device in the final assembly line. In such an arrangement, the decision on the shape and design of the outer section of the wing tip device may be delayed until the aircraft is on the final assembly line.

[0012] The outer section of the wing tip device may be arranged to be sacrificed in the event of an impact on the outer section. The outer section of the wing tip device may comprise one or more crumple zones to absorb impacts. The outer section of the wing tip device may comprise one or more break lines arranged to fail, or break, in the event of an impact on the outer section. The outer section of the wing tip device may be arranged to be frangible. Providing such an outer section may prevent impacts on the outer section of the wing tip device being transmitted to, and potentially damaging, the inner section of the wing tip device, and/or the fixed wing. For example, a significant load applied at the outer section of the wing tip device may otherwise cause damage to the wing root of the fixed wing, or other element of the fixed wing. In particular, the dynamic interface between the inner section of the wing tip device and the fixed wing may be protected. The outer wing tip device, if damaged, may be more easily repaired or replaced, with only a static interface with the inner section of the wing tip device, than if the dynamic interface of the inner section needs repair or replacement.

[0013] The wing tip device may be a wing tip extension; for example the wing tip device may be a planar tip extension. In other embodiments, the wing tip device may comprise, or consist of, a non-planar device, such as a winglet.

[0014] In the flight configuration the trailing edge of the wing tip device is preferably a continuation of the trailing edge of a fixed wing. The leading edge of the wing tip device is preferably a continuation of the leading edge of the fixed wing. There is preferably a smooth transition from the fixed wing to the wing tip device. It will be appreciated that there may be a smooth transition, even where there are changes in sweep or twist at the junction between the fixed wing and wing tip device. However, there are preferably no discontinuities at the junction between the fixed wing and wing tip device. The upper and the lower surfaces of the wing tip device may be continuations of the upper and lower surfaces of the fixed wing.

[0015] When the wing tip device is in the ground configuration, the aircraft may be unsuitable for flight. For example, the wing tip device may be aerodynamically and/or structurally unsuitable for flight in the ground configuration. The aircraft is preferably configured such that, during flight, the wing tip device is not moveable to the ground configuration. The aircraft may comprise a sensor for sensing when the aircraft is in flight. When the sensor senses that the aircraft is in flight, a control system is preferably arranged to disable the possibility of moving the wing tip device to the ground configuration.

[0016] In the flight configuration, the span may exceed an airport compatibility gate limit. In the ground configuration the span may be reduced such that the span (with the wing tip device in the ground configuration) is less than, or substantially equal to, the airport compatibility gate limit.

[0017] The aircraft is preferably a passenger aircraft. The passenger aircraft preferably comprises a passenger cabin comprising a plurality of rows and columns of seat units for accommodating a multiplicity of passengers. The aircraft may have a capacity of at least 20, more preferably at least 50 passengers, and more preferably more than 50 passengers. The aircraft is preferably a powered aircraft. The aircraft preferably comprises an engine for propelling the aircraft. The aircraft may comprise wing-mounted, and preferably underwing, engines [0018] According to a second aspect of the invention there is also provided an aircraft wing comprising a fixed wing and a wing tip device at the tip thereof, wherein the wing tip device is configurable between: (i) a flight configuration for use during flight and (ii) a ground configuration for use during ground-based operations, in which ground configuration the wing tip device is moved away from the flight configuration such that the span of the aircraft wing is reduced, wherein the wing tip device comprises an inner section and an outer section, wherein there is a dynamic interface between the inner section and the fixed wing, the dynamic interface configured to allow the wing tip device to move between the flight configuration and ground configuration, and a static interface between the inner section and the outer section. According to a third aspect of the invention, there is provided a wing tip device for an aircraft wing, the wing tip device comprising an inner section and an outer section, wherein there is one or more elements of a dynamic interface associated with the inner section, wherein the one or more elements of the dynamic interface are configured to allow the wing tip device to move between a flight configuration and a ground configuration when attached to a fixed wing, wherein in the ground configuration the wing span of the fixed wing and wing tip device is reduced, and a static interface between the inner section and the outer section. According to a fourth aspect, there is provided a method of assembling an aircraft, the method comprising the steps of providing an aircraft fuselage with an aircraft wing, the aircraft wing comprising a fixed wing and an inner section of a wing tip device, wherein there is a dynamic interface between the fixed wing and the inner section of the wing tip device, the method comprising the step of, in the final assembly line, attaching an outer section of a wing tip device to the inner section of the wing tip device via a static interface. The method provides an aircraft as described with relation to the first aspect of the invention.

[0019] It will of course be appreciated that features described in relation to one aspect of the present invention may be incorporated into other aspects of the present invention. For example, the method of the invention may incorporate any of the features described with reference to the apparatus of the invention and vice versa.

DESCRIPTION OF THE DRAWINGS

[0020] Embodiments of the present invention will now be described by way of example only with reference to the accompanying schematic drawings of which: [0021] Figure 1 shows a schematic view of a wing according to a first embodiment of the invention; and [0022] Figure 2 shows a schematic view of an aircraft according to a second embodiment of the invention,

DETAILED DESCRIPTION

[0023] Figure 1 shows a wing 10 comprising a fixed wing 12 and a wing tip device 14 The wing tip device 14 is movable between a flight configuration and a ground configuration with a reduced wing span. The wing tip device 14 is in the ground configuration in figure 1. The wing tip device 14 comprises an inner section 16 and outer section 18. The inner section 16 is joined to the fixed wing 12 by a dynamic interface 20. The inner section 16 and outer section 18 are joined by a static interface 22.

[0024] The dynamic interface comprises a hinge mechanism, an actuator, and a locking mechanism. The dynamic interface 20 is arranged to facilitate the movement of the wing tip device 14, relative to the fixed wing 12, from a locked flight configuration to a ground configuration with a reduced wing span. One or more seals may be associated with the dynamic interface, the seals arranged to provide an aerodynamic interface between the fixed wing 12 and the wing tip device 14, when the wing tip device 14 is in the locked flight configuration. The dynamic interface may also be associated with systems that serve other components outboard of the dynamic interface, for example wing tip lights and/or anti-icing systems.

[0025] The static interface 22 is arranged to secure the inner section 16 to the outer section 18 such that no relative movement between the two parts is allowed. One or more seals may be associated with the static interface 22, the seals arranged to provide an aerodynamic interface between the inner section 16 and outer section 18. The static interface may be associated with interfaces or disconnects serving systems outboard of the static interface, for example, wing tip lights and/or anti-icing systems.

[0026] The static interface 22 may comprise a relatively simple arrangement of bolts between the inner section 16 and outer section 18. This may allow easy replacement of the outer section 18 in the event of damage to the outer section 18, without having to change or adjust the dynamic interface 20. Additionally, there may not be a need to adjust other aircraft systems, such as hydraulics or electrical power, which could require extensive testing on reassembly to verify that the system integrity is maintained. This is potentially a significant time saving. The outer section 18 may be arranged to be frangible, or sacrificial in the event of damage, such that any impact to the outer section 18 is reduced or not transferred to the inner section 16. Such an arrangement will protect the dynamic interface 22 from impacts and damage to the outer section 18 of the wing tip device 14.

[0027] By providing a static interface 22 which allows the outer section 18 to be easily detached from the inner section 16, an operator may change the outer section 18 to an alternative outer section if the aircraft mission parameters change. For example, the outer section 18 of the wing tip device 14 may be optimised for a long flight, or short take off. Also, by housing the complicated mechanical arrangements which at least partially make up the dynamic interface 20 in the inner section 16 of the wing tip 14, the cost of producing different outer wing tips 18 for different mission parameters is reduced.

[0028] Figure 2 shows an aircraft 200 comprising a wing 10 as described with reference to figure 1. The wing tip device 14 is in the locked flight configuration in figure 2.

[0029] Whilst the present invention has been described and illustrated with reference to particular embodiments, it will be appreciated by those of ordinary skill in the art that the invention lends itself to many different variations not specifically illustrated herein.

[0030] Where in the foregoing description, integers or elements are mentioned which have known, obvious or foreseeable equivalents, then such equivalents are herein incorporated as if individually set forth. Reference should be made to the claims for determining the true scope of the present invention, which should be construed so as to encompass any such equivalents. It will also be appreciated by the reader that integers or features of the invention that are described as preferable, advantageous, convenient or the like are optional and do not limit the scope of the independent claims. Moreover, it is to be understood that such optional integers or features, whilst of possible benefit in some embodiments of the invention, may not be desirable, and may therefore be absent, in other embodiments.

Claims (17)

1. An aircraft comprising an aircraft wing, the aircraft wing comprising a fixed wing and a wing tip device at the tip thereof, wherein the wing tip device is configurable between: (i) a flight configuration for use during flight and (ii) a ground configuration for use during ground-based operations, in which ground configuration the wing tip device is moved away from the flight configuration such that the span of the aircraft wing is reduced, wherein the wing tip device comprises an inner section and an outer section, wherein there is a dynamic interface between the inner section and the fixed wing, the dynamic interface configured to allow the wing tip device to move between the flight configuration and ground configuration, and a static interface between the inner section and the outer section.
2. An aircraft as claimed in claim 1, wherein the dynamic interface is arranged to facilitate folding and/or rotational movement of the wing tip device relative to the fixed wing.
3. An aircraft as claimed in claim 1 or claim 2, wherein the dynamic interface includes a hinge mechanism, a pivot point, and/or a slew ring.
4. An aircraft as claimed in any preceding claim, wherein the dynamic interface comprises one or more actuators.
5. An aircraft as claimed in any preceding claim, wherein the dynamic interface comprises a locking mechanism.
6. An aircraft as claimed in any preceding claim, wherein the dynamic interface may comprise one or more seals or sealing surfaces.
7. An aircraft as claimed in any preceding claim, wherein the dynamic interface comprises one or more elements located on or within the fixed wing and one or more elements located on or within the inner section of the wing tip device.
8. An aircraft as claimed in any preceding claim, wherein the static interface comprises one or more fasteners joining the inner section and outer section of the wing tip device.
9. An aircraft as claimed in any preceding claim, wherein the static interface is arranged such that the outer section of the wing tip device is removable from the inner section of the wing tip device without requiring any adjustment or interaction with the dynamic interface.
10. An aircraft as claimed in any preceding claim, wherein the outer section of the wing tip device is removable from the inner section of the wing tip device without damage to the inner section of the wing tip device.
11 An aircraft as claimed in any preceding claim, wherein the outer section of the wing tip device is arranged to be sacrificed in the event of an impact on the outer section.
12. An aircraft as claimed in any preceding claim, wherein the outer section of the wing tip device comprises one or more crumple zones to absorb impacts.
13. An aircraft as claimed in any preceding claim, wherein the outer section of the wing tip device comprises one or more break lines arranged to fail, or break, in the event of an impact on the outer section.
14. An aircraft as claimed in any preceding claim, wherein the outer section of the wing tip device is arranged to be frangible.
15. An aircraft wing comprising a fixed wing and a wing tip device at the tip thereof, wherein the wing tip device is configurable between: (i) a flight configuration for use during flight and (ii) a ground configuration for use during ground-based operations, in which ground configuration the wing tip device is moved away from the flight configuration such that the span of the aircraft wing is reduced, wherein the wing tip device comprises a inner section and an outer section, wherein there is a dynamic interface between the inner section and the fixed wing, the dynamic interface configured to allow the wing tip device to move between the flight configuration and ground configuration, and a static interface between the inner section and the outer section.
16. A wing tip device for an aircraft wing, the wing tip device comprising an inner section and an outer section, wherein there is one or more elements of a dynamic interface associated with the inner section, wherein the one or more elements of the dynamic interface are configured to allow the wing tip device to move between a flight configuration and a ground configuration when attached to a fixed wing, wherein in the ground configuration the wing span of the fixed wing and wing tip device is reduced, and a static interface between the inner section and the outer section.
17. A method of assembling an aircraft, the method comprising the steps of providing an aircraft fuselage with an aircraft wing, the aircraft wing comprising a fixed wing and an inner section of a wing tip device, wherein there is a dynamic interface between the fixed wing and the inner section of the wing tip device, the method comprising the step of, in the final assembly line, attaching an outer section of a wing tip device to the inner section of the wing tip device via a static interface.
GB1608864.3A 2016-05-20 2016-05-20 Wing tip device Pending GB2550409A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB1608864.3A GB2550409A (en) 2016-05-20 2016-05-20 Wing tip device

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB1608864.3A GB2550409A (en) 2016-05-20 2016-05-20 Wing tip device

Publications (2)

Publication Number Publication Date
GB201608864D0 GB201608864D0 (en) 2016-07-06
GB2550409A true GB2550409A (en) 2017-11-22

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Family Applications (1)

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GB1608864.3A Pending GB2550409A (en) 2016-05-20 2016-05-20 Wing tip device

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Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5201479A (en) * 1992-01-30 1993-04-13 The Boeing Company Self-monitoring latch pin lock for folding wing aircraft
US6260799B1 (en) * 2000-04-24 2001-07-17 Hamilton Sunstrand Corporation Aircraft wing fold actuation system
US20080149758A1 (en) * 2006-04-21 2008-06-26 Colgren Richard D Modular unmanned air-vehicle
US20120292436A1 (en) * 2010-08-12 2012-11-22 Abe Karem Compact aircraft wing folding systems and methods
US20140014768A1 (en) * 2011-10-01 2014-01-16 The Boeing Company Wing fold controller
US20150203190A1 (en) * 2013-04-19 2015-07-23 The Boeing Company Winglet attach fitting and method for attaching a split winglet to a wing

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5201479A (en) * 1992-01-30 1993-04-13 The Boeing Company Self-monitoring latch pin lock for folding wing aircraft
US6260799B1 (en) * 2000-04-24 2001-07-17 Hamilton Sunstrand Corporation Aircraft wing fold actuation system
US20080149758A1 (en) * 2006-04-21 2008-06-26 Colgren Richard D Modular unmanned air-vehicle
US20120292436A1 (en) * 2010-08-12 2012-11-22 Abe Karem Compact aircraft wing folding systems and methods
US20140014768A1 (en) * 2011-10-01 2014-01-16 The Boeing Company Wing fold controller
US20150203190A1 (en) * 2013-04-19 2015-07-23 The Boeing Company Winglet attach fitting and method for attaching a split winglet to a wing

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