GB2573282A - Actuator locking mechanism - Google Patents

Actuator locking mechanism Download PDF

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Publication number
GB2573282A
GB2573282A GB1806836.1A GB201806836A GB2573282A GB 2573282 A GB2573282 A GB 2573282A GB 201806836 A GB201806836 A GB 201806836A GB 2573282 A GB2573282 A GB 2573282A
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GB
United Kingdom
Prior art keywords
wing
aircraft
actuator
configuration
tip device
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.)
Withdrawn
Application number
GB1806836.1A
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GB201806836D0 (en
Inventor
Harding Matt
Horwood Jack
Morrell Paul
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 GB1806836.1A priority Critical patent/GB2573282A/en
Publication of GB201806836D0 publication Critical patent/GB201806836D0/en
Publication of GB2573282A publication Critical patent/GB2573282A/en
Withdrawn legal-status Critical Current

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C23/00—Influencing air flow over aircraft surfaces, not otherwise provided for
    • B64C23/06—Influencing air flow over aircraft surfaces, not otherwise provided for by generating vortices
    • B64C23/065—Influencing air flow over aircraft surfaces, not otherwise provided for by generating vortices at the wing tips
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C23/00—Influencing air flow over aircraft surfaces, not otherwise provided for
    • B64C23/06—Influencing air flow over aircraft surfaces, not otherwise provided for by generating vortices
    • B64C23/065—Influencing air flow over aircraft surfaces, not otherwise provided for by generating vortices at the wing tips
    • B64C23/069—Influencing 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
    • B64C23/072—Influencing 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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/38—Adjustment of complete wings or parts thereof
    • B64C3/54—Varying in area
    • B64C3/546—Varying in area by foldable elements
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/38—Adjustment of complete wings or parts thereof
    • B64C3/56—Folding or collapsing to reduce overall dimensions of aircraft
    • Y—GENERAL 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
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/10—Drag reduction

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Actuator (AREA)

Abstract

An aircraft comprising an aircraft wing, the aircraft wing comprises a fixed wing 14 and wing tip device 12, wherein the wing tip device is movable between a flight configuration and a ground configuration wherein 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, the wing further comprising an actuator 18, 20, 22 to move the wing tip between configurations, and a locking device 26 that locks the actuator when the wing tip is in the ground configuration. Additionally, an aircraft wing comprises a fixed wing 14 and foldable wing tip device 12, the wing tip device is configurable via extension of an actuator18, 20, 22, between a flight configuration and a ground configuration in which the wing span is reduced below an airport gate limit, wherein the wing comprises a shot bolt assembly (30, fig 3) for selectively extending a shot bolt through an aperture associated with the actuator that locks the actuator in an extended configuration, such that the wing tip device is held in the ground or folded configuration.

Description

ACTUATOR LOCKING MECHANISM
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).
[0002] Therefore, folding 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] Typically, an actuator is used to move the wing tip device from the flight configuration to the ground configuration, and the actuator holds the wing tip device in the ground configuration during ground based manoeuvres. Stresses and strains during ground based manoeuvres will be passed from the wing tip device through the actuator, thereby potentially damaging the actuator, and/or requiring significant reinforcement of the actuator.
[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 and actuation system.
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, the aircraft wing further comprising an actuator to move the wing tip device between the flight configuration and the ground configuration, and a locking device configured to lock the actuator when the wing tip device is in the ground configuration.
[0006] The actuator may comprise a movable element, the movable element arranged to drive the wing tip device between the flight configuration and ground configuration. The locking device may be configured to mechanically engage the movable element when the wing tip device is in the ground configuration. The locking device may isolate loads on the movable element exerted by the wing tip device from the rest of the actuator. Such an arrangement may allow for an actuator with a lower load rating to be used. The movable element may comprise an aperture, and the locking device may comprise a locking pin which may be extended into the aperture when the wing tip device is in the ground configuration. The aperture may be in the form of a recess or a through-hole. The movable element may comprise a lug and the aperture may be provided in the lug.
[0007] The actuator may be a piston. The piston may comprise a movable element in the form of a piston rod connected to the wing tip device, and the locking device may be configured to mechanically engage with the piston rod when the wing tip device is in the ground configuration. The locking device may isolate loads on the piston rod exerted by the wing tip device from the rest of the actuator. The piston rod may comprise an aperture, and the locking device may comprise a locking pin which may be extended into the aperture when the wing tip device is in the ground configuration. The aperture may be in the form of a recess or a through-hole. The piston rod may comprise a lug and the aperture may be provided in the lug. The piston may be pneumatically or hydraulically driven.
[0008] The actuator may be electrically driven and the movable element may be a drive arm extending from the electrically driven actuator. For example, the actuator may be any suitable rotary to linear actuator, such as a roller screw arrangement.
[0009] The actuator may be substantially housed within the fixed wing. The fixed wing may comprise a wing box, and the actuator may be substantially housed within the wing box. The actuator may at least partially extend beyond the wing box when the wing tip device is in the ground configuration.
[0010] According to a second aspect, the invention provides 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, the aircraft wing further comprising an actuator to move the wing tip device between the flight configuration and the ground configuration, and a locking device configured to lock the actuator when the wing tip device is in the ground configuration.
[0011] According to a third aspect, the invention provides a method of moving a wing tip device of an aircraft according to the first aspect of the invention from the flight configuration to the ground configuration, the method comprising the steps of: activating the actuator to drive the wing tip device from the flight configuration to the ground configuration, and activing the locking device to lock the actuator in position.
[0012] The actuator may comprise a movable element with an aperture, the locking device may comprise a locking pin, and the step of activating the locking device to lock the actuator comprises driving the locking pin into the aperture, thereby preventing movement of the movable element. The movable member may comprise a lug and the aperture may be provided in the lug.
[0013] According to a fourth aspect, the invention provides a method of moving a wing tip device of an aircraft according to the first aspect from the ground configuration to the flight configuration, the method comprising the steps of: activating the locking device to unlock the actuator, and activating the actuator to drive the wing tip device from the ground configuration to the flight configuration.
[0014] The actuator may comprise a movable element including an aperture, the locking device may comprise a locking pin, and the step of activating the locking device to unlock the actuator comprises withdrawing the locking pin from the aperture, thereby allowing movement of the movable element. The movable member may comprise a lug and the aperture may be provided in the lug.
[0015] In embodiments of the present invention, the wing tip device is configurable between: (a) a flight configuration for use during flight and (b) 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. In the flight configuration, the span may exceed an airport compatibility 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 limit. The airport compatibility limit is a span limit (for example relating to clearance restrictions for buildings, signs, other aircraft). The compatibility limit is preferably a gate limit.
[0016] 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.
[0017] In the flight configuration the trailing edge of the wing tip device is preferably a continuation of the trailing edge of the 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. The span ratio of the fixed wing relative to the wing tip device may be such that the fixed wing comprises at least 70%, 80%, 90%, or more, of the overall span of the aircraft wing.
[0018] When the wing tip device is in the ground configuration, the aircraft incorporating the wing, 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.
[0019] 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.
[0020] According to yet another aspect, there is provided, an aircraft wing comprising a fixed wing and a foldable wing tip device at the tip thereof, the wing tip device being configurable via extension of an actuator, between a flight configuration and a ground configuration in which the span is reduced below an airport gate limit, wherein the wing comprises a shot bolt assembly for selectively extending a shot bolt through an aperture associated with the actuator, to lock the actuator in an extended configuration, such that the wing tip device can be held in the ground configuration.
[0021] 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.
[0022] The term ‘or’ shall be interpreted as ‘and/or’ unless the context requires otherwise.
DESCRIPTION OF THE DRAWINGS [0023] Embodiments of the present invention will now be described by way of example only with reference to the accompanying schematic drawings of which:
[0024] Figure 1A shows a schematic view of an aircraft wing according to a first embodiment of the invention;
[0025] Figure IB shows a schematic view of an aircraft according to a second embodiment of the invention;
[0026] Figure 2 shows a cross-sectional view of an aircraft wing including an actuator and locking arrangement in a ground configuration according to a third embodiment of the invention; and [0027] Figure 3 shows a plan view of the arrangement shown in figure 2;
DETAILED DESCRIPTION [0028] Figure 1A shows a wing 10 comprising a wing tip device 12 and a fixed wing 14. Figure IB shows an aircraft 100 comprising the wing 10. The wing tip device 12 is configurable between: (i) a flight configuration for use during flight, as shown in figure IB and (ii) a ground configuration for use during ground-based operations, as shown in figure 1A, in which ground configuration the wing tip device 12 is moved away from the flight configuration such that the span of the aircraft wing 10 is reduced.
[0029] Figures 2 and 3 show an actuator arrangement according to the invention. Figure 2 shows a cross-sectional view of the fixed wing 14 and the wing tip device 12. Figure 3 shows the same arrangement as in figure 2, in a plan view with the details of the wing tip device 12 removed for clarity. The wing tip device 12 is in the ground configuration, where it has been rotated around a hinge line 16 such that the span of the wing to which the wing tip device 12 is fixed is reduced. A piston 18 comprising a piston body 20 and a piston rod 22 is located within the fixed wing 14. The piston may be hydraulically or pneumatically driven. The piston rod 22 is connected to a driving arm 24 of the wing tip device 12, whereby the piston rod 22 being driven away from the piston body 20 causes the wing tip device 12 to move into the ground configuration. The piston rod 22 comprises a lug 28 extending away from the rod, in this case approximately half way along the piston rod 22. However, the skilled person will appreciate the lug 28 could be located in any suitable position on the piston rod 22. When the piston rod 22 has been extended and the wing tip device 12 is in the ground configuration, the lug 28 is located such that a locking unit 26 may extend a locking pin 30 into an aperture in the lug 28. The locking unit 26 is mounted to the fixed wing structure. Once the locking pin 30 has been inserted into the lug 28, the piston body 20 is isolated from the wing tip device 12, such that forces exerted on the piston rod 22 by the wing tip device 12 are reacted through the piston rod, into the locking unit 26, and thereby into the structure of the fixed wing 14. In order to move the wing tip device back into the flight configuration, the locking pin 30 is retracted from the lug 26, such that the piston 18 may then be contracted and the piston rod 22 brings the driving arm 24 of the wing tip device 12 back into the fixed wing 14. When the wing tip device 12 has been returned to the flight configuration it will be locked in position, most likely using a locking system independent of the locking unit 26. However, the skilled person will appreciate that the locking unit 26 may be used to lock the piston rod in position in the flight configuration, for example by engagement with a suitably located second lug.
[0030] 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. For example, the piston could be replaced by an electric actuator, for example a rotary to linear actuator. The embodiment has been described with relation to a simple folding wing tip mechanism, but could be equally applicable to rotary wing tip mechanisms, for example where a wing tip device is rotated in an oblique plane around a slew ring.
[0031] 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, the aircraft wing further comprising an actuator to move the wing tip device between the flight configuration and the ground configuration, and a locking device configured to lock the actuator when the wing tip device is in the ground configuration.
2. An aircraft as claimed in claim 1, wherein the actuator comprises a moveable element, the moveable element arranged to drive the wing tip device between the flight configuration and ground configuration.
3. An aircraft as claimed in claim 2, wherein the locking device is configured to mechanically engage with the movable element when the wing tip device is in the ground configuration.
4. An aircraft as claimed in claim 3, wherein the locking device isolates loads on the movable element exerted by the wing tip device from the rest of the actuator.
5. An aircraft as claimed in any of claims 2 to 4, wherein the movable element comprises an aperture, and the locking device comprises a locking pin configured to be extended into the aperture when the wing tip device is in the ground configuration
6. An aircraft as claimed in any of claims 2 to 5, wherein the actuator is a piston, and the moveable element is a piston rod connected to the wing tip device.
7. An aircraft as claimed in claim 6, wherein the piston is hydraulically driven.
8.
An aircraft as claimed in claim 6, wherein the piston is pneumatically driven.
9. An aircraft as claimed in any of claims 2 to 5, where the actuator is electrically driven and the movable element is a drive arm extending from the actuator.
10. An aircraft as claimed in any preceding claim, wherein the actuator is substantially housed within the fixed wing.
11. An aircraft as claimed in claim 10, wherein the fixed wing comprises a wing box, and the actuator is substantially housed within the wing box.
12. An aircraft as claimed in claim 11, wherein the actuator at least partially extends beyond the wing box when the wing tip device is in the ground configuration.
13. 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, the aircraft wing further comprising an actuator to move the wing tip device between the flight configuration and the ground configuration, and a locking device configured to lock the actuator when the wing tip device is in the ground configuration.
14. A method of moving a wing tip device of an aircraft according to claim 1 from the flight configuration to the ground configuration, the method comprising the steps of:
activating the actuator to drive the wing tip device from the flight configuration to the ground configuration, and activing the locking device to lock the actuator in position.
15. A method as claimed in claim 14, wherein the actuator comprises a movable element with an aperture, the locking device comprises a locking pin, and the step of activating the locking device to lock the actuator comprises driving the locking pin into the aperture, thereby preventing movement of the movable element.
16. A method of moving a wing tip device of an aircraft according to claim 1 from the ground configuration to the flight configuration, the method comprising the steps of:
activating the locking device to unlock the actuator, and activating the actuator to drive the wing tip device from the ground configuration to the flight configuration.
17. An aircraft wing comprising a fixed wing and a foldable wing tip device at the tip thereof, the wing tip device being configurable via extension of an actuator, between a flight configuration and a ground configuration in which the span is reduced below an airport gate limit, wherein the wing comprises a shot bolt assembly for selectively extending a shot bolt through an aperture associated with the actuator, to lock the actuator in an extended configuration, such that the wing tip device can be held in the ground configuration.
GB1806836.1A 2018-04-26 2018-04-26 Actuator locking mechanism Withdrawn GB2573282A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB1806836.1A GB2573282A (en) 2018-04-26 2018-04-26 Actuator locking mechanism

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB1806836.1A GB2573282A (en) 2018-04-26 2018-04-26 Actuator locking mechanism

Publications (2)

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GB201806836D0 GB201806836D0 (en) 2018-06-13
GB2573282A true GB2573282A (en) 2019-11-06

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GB1806836.1A Withdrawn GB2573282A (en) 2018-04-26 2018-04-26 Actuator locking mechanism

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Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2533429A (en) * 1949-12-09 1950-12-12 Joseph D Carpenter Wing fold mechanism
US5988563A (en) * 1997-12-30 1999-11-23 Mcdonnell Douglas Corporation Articulating winglets
US20140061371A1 (en) * 2011-10-01 2014-03-06 The Boeing Company Wing fold system with latch pins through multiple mating lugs
EP3357808A1 (en) * 2017-02-03 2018-08-08 Airbus Operations Limited A rotational joint for an aircraft folding wing tip

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2533429A (en) * 1949-12-09 1950-12-12 Joseph D Carpenter Wing fold mechanism
US5988563A (en) * 1997-12-30 1999-11-23 Mcdonnell Douglas Corporation Articulating winglets
US20140061371A1 (en) * 2011-10-01 2014-03-06 The Boeing Company Wing fold system with latch pins through multiple mating lugs
EP3357808A1 (en) * 2017-02-03 2018-08-08 Airbus Operations Limited A rotational joint for an aircraft folding wing tip

Also Published As

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