Hinge device, hinge mount and aircraft wing for an aircraft wing

Abstract

A hinge assembly, a hinge mount, and an aircraft wing are provided. The hinge assembly is used to provide a folding wingtip. The hinge assembly includes a first mount for securing to a first wing section and a second mount for securing to a relatively foldable second wing section. Each of the first and second mounts has a plurality of hinge elements arranged along a hinge axis. The assembly includes a latching device for securing the mount to prevent folding movement. The latching device has a latching axis, spaced apart from the hinge axis, for example, in a generally spanwise direction, to extend into the wing box. This provides an effective device that can be contained within the outer mold line of the wing, reducing the need for a fairing.

Description

Technical Field

[0001] This invention relates to a hinge mechanism for aircraft wings, for example, used to fold the wingtip of an aircraft wing to reduce the width of the aircraft on the ground. Such a hinge mechanism can also be used on other movable surfaces or structures of an aircraft that can move relative to fixed parts of the aircraft, such as flight control surfaces. Background Technology

[0002] Aircraft wings tend to have larger wingspans to improve aerodynamic efficiency. However, the ground structures that need to accommodate aircraft, such as airport gates, are limited in size. Therefore, it can be beneficial for aircraft wings to have folding wingtips or outer wing structures, allowing the wingtips to fold upwards to reduce the aircraft's wingspan on the ground. These folding wingtips typically need to be latchable and lockable in place, particularly to secure them during flight in either an deployed or inline configuration.

[0003] Some current aircraft, including military and commercial aircraft, feature folding wing sections with a joining mechanism between a fixed portion of the wing, also known as the wing box, and a movable or folding portion, also known as the wingtip. The joining is typically arranged along a hinge line that extends generally along the chord direction between the fixed wing portion and the movable wing portion.

[0004] When the wing has a relatively long chord and / or a relatively low wing loading, such as for many military aircraft, a suitable articulation mechanism can usually be accommodated within the wing profile. However, when the wing loading is relatively high compared to the dimensions of the wing profile, such as for some commercial aircraft, especially single-aisle or long-range aircraft, it may be difficult to accommodate an articulation mechanism within the wing profile.

[0005] Such hinge mechanisms typically have hinge elements with connecting lugs that have an integral latch for securing the folding mechanism. These components may protrude beyond the outer mold line (OML) of the lower wing profile or cover.

[0006] This protrusion necessitates the use of an aerodynamic fairing to house the structure, thereby increasing drag, component count, weight, and cost. In such cases, the pitch between the hinge axis and the latch centerline tends to be small in order to reduce the protrusion (e.g., less than 125 mm). However, reducing the hinge / latch pitch increases flight loads at the joint, and thus increases stress and the size and weight of the subsequent structure.

[0007] This invention aims to alleviate this problem. Summary of the Invention

[0008] According to the present invention, a hinge device for an aircraft wing is provided, the hinge device comprising: a first mounting member for fixing to a first wing segment, the first mounting member having a plurality of first hinge elements; and a second mounting member for fixing to a second wing segment, the second mounting member having a plurality of second hinge elements, the first hinge elements and the second hinge elements being arranged along a hinge axis such that the first mounting member is foldable relative to the second mounting member about the hinge axis between an deployed state and a folded state, wherein the first mounting member and the second mounting member are arranged to be fixed in the deployed state by a latching device having a latching axis spaced apart from the hinge axis in a substantially spanwise direction to prevent relative folding movement.

[0009] This device allows for the beneficial encapsulation of folding actuation, latching, and locking mechanisms, eliminating the need for a fairing. By housing the hinge and latching mechanism within the upper and lower wing covers by shaping the hinges and latches along the spanwise direction, the need for aerodynamic fairings and subsequent attachment elements such as nuts and bolts can be eliminated or significantly reduced. This reduction in the number of parts simplifies industrial processes and reduces the complexity and subsequent work required to assemble the structure in a production environment. It also improves aerodynamic efficiency by reducing drag.

[0010] Additionally, the pitch between the hinge centerline and the latch centerline can be increased, thereby reducing the flight load on the joint. This reduces the need for additional structures to support these flight loads, thus benefiting the overall weight, cost, and simplicity of the wing. For example, the distance between the hinge axis and the latch axis can exceed 200 mm, and preferably reach 270 mm.

[0011] Preferably, at least a portion of the first mounting member overlaps with at least a portion of the second mounting member, and the latching device is disposed in the overlapping area. For example, in use, the latching device may extend into the wing box such that the latching axis extends across the wing box.

[0012] The device may include an actuator for causing relative folding movement between a first mount and a second mount. The actuator may be a linear actuator having, for example, a first end attached to the first mount adjacent to a latch axis and a second end arranged to be fixed relative to the second mount in use. For example, the second end may be arranged to be fixed to a main wing spars or other fixed portion of a wing box structure. Alternatively, the actuator may be a gear-type rotary actuator.

[0013] The latching device may include a plurality of first latching elements disposed on a first mounting member and a plurality of second latching elements disposed on a second mounting member, wherein the first latching elements extend beyond the first hinge element from the first mounting member. The second latching elements may be recessed into the second mounting member behind the second hinge element. Additionally, the latching axis may be folded upward relative to the hinge device and disposed below the hinge axis.

[0014] Conveniently, at least some of the first latching elements are integral with at least some of the first hinge elements. For example, the number of latching elements may be less than the number of hinge elements, such that only some of the hinge elements are integral hinge / latch elements. Alternatively, all the latching elements in the latching elements may be integral with the hinge elements. Conveniently, the first and second hinge elements may be staggered, for example, alternating, along the hinge axis, and the first and second latching elements may also be staggered and / or alternating along the latching axis. The latching elements may be arranged in groups, and the actuator may be conveniently disposed in a first space between the first group of latching elements and the second group of latching elements.

[0015] The first latching element can be fixed to a panel, for example, integral with the panel, which extends from the first mounting member toward the latching axis, and preferably extends beyond the latching axis, and is arranged to cover the lower surface of the hinge. This can seal the lower portion of the wing without requiring additional components or seals.

[0016] Preferably, the first latching element and the second latching element include latch holes arranged to be aligned in the unfolded state, and the device includes at least one latching pin arranged to be deployed in the latch holes along the latching axis for securing the first latching element and the second latching element in the unfolded state to prevent them from undergoing relative folding movements.

[0017] Two latching pins are conveniently provided, for example, one latching pin at each end of the latching axis. The latching pins can be deployed inward toward the center of the latching axis, but they can also be installed toward the middle of the latching axis and deployed outward. For example, the latching pins can be located in a second space between the first set of latching elements and the second set of latching elements. A removable cover can be present in the panel, aligned with the second space to provide access for maintenance or repair.

[0018] The first wing section can be a movable wingtip element, and the second wing section can be a fixed wing element or wing box. Therefore, the latching device can be contained within the wing box.

[0019] The invention also includes a hinge mount for the articulated fitting as defined above, the hinge mount being a first mount or a second mount, and the invention includes an aircraft wing having the articulation device as defined above, the first mount being fixed to a first wing segment, and the second mount being fixed to a relatively foldable second wing segment. Preferably, the articulation device does not extend beyond the outer surfaces of the wingtip and the wing box, respectively. Attached Figure Description

[0020] To facilitate a clearer understanding of the invention, reference will now be made to the accompanying drawings by way of example, in which: Figure 1 It is a perspective view of the lower part of a prior art wing with a fairing that includes hinges and latching devices; Figure 2 These are existing articulated and latching fittings, such as those that can be used in... Figure 1 A perspective view of the hinge and latch fittings used in the wing; Figure 3 It is a schematic plan view of the hinge and latching mechanism; Figure 4 yes Figure 3 A three-dimensional view of the device; Figure 5 yes Figure 4 A three-dimensional view of the wingtip components; Figures 6A to 6D yes Figure 3 A three-dimensional view of the device from below, showing its various positions; Figure 7A and Figure 7B yes Figure 3 End views of the device in different positions; Figure 8 This is a schematic plan view of another hinge and latching device; Figure 9 yes Figure 8 A three-dimensional view of the device; Figure 10 yes Figure 8 A three-dimensional view of the wingtip components; Figures 11A to 11C yes Figure 8 A three-dimensional view of the device from below, showing it in various positions; and Figure 12A and Figure 12B yes Figure 8 End view of the device. Detailed Implementation

[0021] Reference Figure 1 and Figure 2In an exemplary articulation and latching device according to the prior art, the wing box mount 2 includes a bracket or mounting member 4 for attachment to a fixed wing segment. The mounting member 4 has a plurality of articulation lugs 6 extending from the articulation end 8 of the mounting member 4 and arranged along the articulation axis 10. The mounting member 4 also includes a plurality of latching lugs 12 for receiving one or more latching pins (not shown) along the latching axis 13. The articulation and latching device also includes a wingtip mount (not shown) having staggered articulation lugs and latching lugs corresponding to the articulation lugs and latching lugs.

[0022] The latch lug 12 also extends from the hinged end 8 of the bracket 4 below the hinge lug 6. It can be seen that the latch lug 12 extends below the lower edge 14 of the bracket 4, which is attached to the lower surface 16 of the wing profile, also known as the outer mold line. Therefore, a fairing 18 must be provided to accommodate the latching mechanism.

[0023] The present invention aims to provide a device having a hinge axis around which the wingtip can rotate and fold, and a latching pin extending into the wing in flight (deployed) and locking the wing in a flight position, which can completely contain the structure within the wing, thus eliminating the need for an aerodynamic fairing. This is achieved by providing an integrated hinge lug / latch lug extending along the wingspan into the wing box.

[0024] Reference Figure 3 , Figure 4 and Figure 5 The hinge and latching device includes a first mounting member and a second mounting member, which include a wingtip mount 20 and a wing box mount 22. The wingtip mount 20 includes flanges 24 and 26 for attachment to the upper and lower surfaces of the wingtip profile; however, flanges or brackets of any suitable size or shape can also be used to secure the mount 20 to the inner end of the wingtip. The wingtip mount 20 can be a separate component or an integral component. Similarly, the wing box mount 22 includes an upper flange 30 and a lower flange 32 for attachment to the upper and lower surfaces of the wing box profile.

[0025] Mounts 20 and 22 are foldable relative to each other by means of a hinge comprising a first set of hinge elements extending from wingtip mount 20 in the form of a first hinge lug 34 and a second set of hinge elements extending from wing box mount 22 in the form of a second hinge lug 36. The hinge lugs 34 and 36 are staggered, preferably alternately positioned, and connected together by a hinge pin (not shown) extending along a hinge axis 38 through a hinge opening 39 provided in each of the hinge lugs 34 and 36 to form a hinge that extends substantially along the chord direction. This allows wingtip mount 20 to fold between a folded position and an extended or in-line position, as explained in more detail below.

[0026] At least some of the first hinge lugs have an extension length that extends into and overlaps with the wing box mount 22. The extended first hinge lugs 341 include a latching opening 40 located at the distal end of each of the extended lugs 341, thereby forming a generally spanwise extending integral hinge lug / latch lug. In this example, there are four integral spanwise extending hinge lugs / latch lugs 341 disposed on the wingtip mount 20, and two non-extending first hinge lugs 34.

[0027] At least some of the second hinge lugs 36 also have an extension length that extends rearward to recess into the wing box mount 22. This allows the integral first lug 341 and the second extension lugs 361 to stagger, preferably alternate, each other. The second extension lug 361 also has a latch opening 42, which is arranged to align with the opening 40 in the first extension lug 341 along the latch axis or latch line 44 when the mount is in the deployed (or in-line) position. The latch openings 40, 42 are arranged to receive at least one latch pin, in this example a left latch pin 46 and a right latch pin 48. The latch pins can each be deployed from the respective latch units 54, 56 into the latch openings 40, 42 from a position adjacent to the right edge 50 and left edge 52 of the wing box mount 22 to lock the hinge in the deployed position.

[0028] As can be seen, this arrangement provides a relatively large spacing, for example, at least 200 mm and preferably at least about 270 mm, between the hinge line or hinge axis and the latch line or latch axis, thus providing the benefits described above. Additionally, this structure can be as follows: Figure 4 As shown, it is completely contained within the outer mold lines of the upper and lower covers (OML) of the wingtip and wing box, so as to eliminate the need for a fairing.

[0029] Reference Figure 5 A panel 70 is provided on the lower surface of the wingtip fitting 20, extending over the fitting and attached to an extended hinge lug 341. The panel 70 is arranged to extend just beyond the latch line 44. The panel 70 can be machined as part of the wingtip fitting 22 to cover and seal the lower portion of the hinge when in the deployed position.

[0030] This articulation device can be used with various methods of driving folding wings. For example, an integrated articulated lug / latch lug can be used in articulation devices that use GRA (gear rotary actuator) to drive wing folding or that use linear hydraulic actuators.

[0031] Also refer to Figures 6A to 6Das well as Figure 7A and Figure 7B In this example, the hinge is configured for use with a folding wingtip driven by a linear hydraulic actuator 60. A first end 61 of the actuator 60 is arranged to be fixed relative to the wing box mount 22 on the fixed wing side via a wing box bracket 62. In this example, when the mount 22 is attached to the wing box, the bracket 62 is attached to a wing spars 64 positioned at the rear of the wing box mount 22; however, it will be understood that any suitable fixing structure can be used. A second end 63 of the actuator 60 is the end of an extendable actuator rod, attached to a wingtip bracket 66, which is fixed to the wingtip mount 20 on the wingtip side. This can be attached at any convenient location spaced apart from the hinge axis, providing sufficient leverage.

[0032] The actuator rod 63 can be extended to drive the folding wing tip, while the adjacent first end 61 of the wing box bracket 22 and the actuator 60 remain in a fixed position, as described in more detail below.

[0033] Figure 6A and Figure 7A The articulated assembly in flight is shown. The actuator 60 is not extended, and the articulated assembly, and therefore the wing, is deployed or flat. To lock the wing in this state, latch housings or latch units 54, 65 each deploy latch pins 46, 48, contained within the latch housing, into both the wing box lug 36 and the integral articulated lug / latch lug 34 at the wingtip. This locks the wing because the latch pins 46, 48 prevent relative movement of the integral articulated lug / latch lug. The integral articulated lug / latch lug will typically remain in place during flight.

[0034] As can be seen, panel 70 has a "flip-top" design, which allows it to seal the underside of the wing when deployed. Since the one-piece hinged lug / latch lug 341 already requires significant machining, it is economical to integrate a large panel 70 onto the lower section of the wingtip portion 20. When the wingtip is deployed in flight, a large portion of this material can simply cover and seal any gaps in the underside of the wing. The sealing is almost entirely autonomous when the wingtip is deployed, requiring no additional components or seals.

[0035] Specific reference Figures 6A to 6D This illustrates the wing folding process. Figure 6BThe hinge is shown folded to approximately 22 degrees. Latch pins 46, 48 retract from openings 42 in the latch lugs into latch housings 54, 56, thereby unlocking the hinge and thus allowing movement of the integral hinge lug / latch lug 341. A linear hydraulic actuator 60 operates to extend rod 63. This causes bracket 66, and thus panel 70 attached to wingtip mount 20, to be pushed away from the wing box, causing wingtip mount 20 to rotate about hinge axis 38 to fold the wingtip upwards. Figure 6C The hinge is shown folding to approximately 86 degrees after the actuator rod 63 extends further. This process can occur after landing and simultaneously while taxiing to the airport gate.

[0036] like Figure 6D and Figure 7B As shown, a further extension of the linear hydraulic actuator 60 pushes the panel 70 and drives the hinge, thus driving the wingtip into a folded ground position. In this position, the wingtip mount folds upward, with the panel 70 and associated extended lugs 342 protruding below the wing box mount. In use, the folding of the wingtip mount causes the wingtip to fold upward relative to the wing box, resulting in a reduction in effective wing span.

[0037] Reference Figure 8 , Figure 9 and Figure 10 Another hinge and latching device also includes a first mounting member and a second mounting member, which include a wingtip mounting member 80 and a wing box mounting member 82. This device is similar to... Figure 3 The device shown in Figure 7 is different, however, in the arrangement of the lugs.

[0038] Mounts 80 and 82 include upper flanges 84 and 88 and lower flanges 86 and 90 for attachment to the upper and lower surfaces of the wing profile as described above. The hinge includes first hinge lugs 92 extending from the wingtip mount 80. In this example, each of the first hinge lugs 92 is an extending lug including a hinge opening 96 for a hinge pin and a latching opening 98 for a latching pin, such that each of the first hinge lugs 92 includes an integral hinge lug / latch lug. The lugs 92 are positioned in groups near each edge of the mount to leave a central first space 100 between the edges. In this example, there are two pairs of lugs 92. The first space 100 can accommodate an actuator mechanism for operating the hinge, such as a geared rotary actuator (GRA).

[0039] The first lug 92 intersects with a second lug 94 extending from the wing box mount 82. Each of the second lugs 94 also extends in length and has both a hinge opening 106 and a latching opening 108 to provide an integrated hinged lug / latch lug. The second lugs 94 are also arranged in groups near each edge of the mount; in this example, each group has three lugs, leaving space between the groups. Each group of lugs 92, 93 is connected together by hinge pins, namely the right hinge pin 102 and the left hinge pin 104, to allow the wingtip mount 80 to fold between a folded position and an extended or in-line position.

[0040] The latching openings 98, 108 of each set of lugs are arranged to receive latching pins when aligned in the deployed position of the fitting, the latching pins in this example being the left latching pin 110 and the right latching pin 112. Due to the positioning of the two sets of staggered lugs, actuators or a pair of actuators (not shown) for the latching pins 110, 112 can be positioned near the center of the fitting in the second space 114 between the sets of lugs, such that the latching pins 110, 112 can move outward from the central position between the deployed position in the latching lugs 98, 108 and the retracted position in the second space 114.

[0041] Reference Figure 10 A panel 116 is provided on the lower surface of the wingtip mount 80, extending over the mount and attached to the base of each extension lug 92. The panel 70 is arranged to extend just beyond the axis of the latch opening 98 and the end of each lug 92 to cover and seal the lower surface of the wing mount when deployed. In this example, the panel 116 has a cutout 118 that can be covered by a removable cover 120, as shown in FIG. 11. The removable cover 120 allows access to internal components such as actuator mechanisms for maintenance or repair.

[0042] The folding process is in Figures 11A to 11C as well as Figure 12A and Figure 12B The diagram in the middle is shown. Figure 11A and Figure 12A The articulated assembly in flight is shown, with the fittings and therefore the wing either deployed or flat. To lock the wing in this state, a latch actuator deploys latch pins 110, 112 outside the second space 114 such that the latch pins 110, 112 extend through aligned latch openings 98, 108 in the first lug 92 and the second lug 94 of the wing box 82 and wingtip 80. This locks the wing by preventing relative movement of the integral articulated lugs / latch lugs 92, 94. The integral articulated lugs / latch lugs 92, 94 will typically remain in place during flight.

[0043] like Figure 11C and Figure 12B As shown in the diagram, the operation of the GRA drives the articulation device and thus drives the wingtip into a folded ground position. In this state, the wingtip mount 80 folds upward, with the panel 116 and associated extension lug 92 protruding below the wing box mount 82. This causes the wingtip to fold upward relative to the wing box during use, resulting in a reduction in the effective wing span.

Claims

1. A hinge device for an aircraft wing, the hinge device comprising: A first mounting member, used for securing itself in a first wing section, the first mounting member having a plurality of first hinge elements, and A second mounting component, used for securing itself in a second wing section, has a plurality of second hinge elements. The first hinge element and the second hinge element are arranged along the hinge axis such that the first mounting member can fold about the hinge axis relative to the second mounting member between an unfolded state and a folded state. The first and second mounting members are arranged to be secured by a latching device having a latching axis when in the unfolded state to prevent relative folding movements, the latching axis being spaced apart from the hinge axis in a substantially spanning direction.

2. The hinge device according to claim 1, wherein, At least a portion of the first mounting member overlaps with at least a portion of the second mounting member, and the latching device is disposed in the overlapping area.

3. The hinge device according to any of the preceding claims, wherein, The distance between the hinge axis and the latch axis is greater than 200 mm, and preferably between 200 mm and 270 mm.

4. The hinge device according to any preceding claim, the hinge device comprising an actuator for causing a relative folding movement between the first mounting member and the second mounting member, wherein, The actuator is at least one of the following: a gear-type rotary actuator and a linear actuator, the gear-type rotary actuator and the linear actuator having a first end attached to the first mounting member adjacent to the latch axis and a second end arranged to be fixed relative to the second mounting member in use.

5. The hinge device according to any of the preceding claims, wherein, The latching device includes a plurality of first latching elements disposed on the first mounting member and a plurality of second latching elements disposed on the second mounting member, wherein the first latching elements extend beyond the corresponding hinge elements from the first mounting member, and wherein the second latching elements are recessed behind the second hinge elements, optionally wherein at least some or all of the first latching elements are engaged with the first hinge elements.

6. The hinge device according to claim 5, wherein, The actuator is disposed in a first space between the first set of latching elements and the second set of latching elements.

7. The hinge device according to claim 5 or 6, wherein, The first latching element and the second latching element each include latching holes arranged to be aligned in the unfolded state, and include at least one latching pin arranged to be deployed along the latching axis to secure the first latching element and the second latching element to prevent relative folding movement when the device is in the unfolded state.

8. The hinge device according to claim 7, wherein the hinge device comprises two latch pins disposed between opposite ends of the latch axis and the center of the latch axis, optionally wherein, Each of the latching pins can be deployed outward from the second space between the first set of latching elements and the second set of latching elements.

9. The hinge device according to any one of claims 5 to 8, wherein, At least some of the first latching elements are secured to a panel, optionally coupled to the panel, which extends beyond the latching axis from the first mounting member and is arranged to cover the lower surface of the hinge, optionally wherein the panel includes a removable cover aligned with the second space.

10. The hinge device according to any one of claims 5 to 9, wherein, The latch hole is arranged below the hinge axis.

11. The hinge device according to any one of claims 5 to 10, wherein, The number of the first latching element and the second latching element is less than that of the first hinge element and the second hinge element, respectively.

12. The hinge device according to any of the preceding claims, wherein, The first hinge element and the second hinge element are interleaved.

13. The hinge device according to any of the preceding claims, wherein, The first wing section is a movable wingtip element, and the second wing section is a fixed wing element.

14. A hinged mounting member for use in a hinge fitting according to any of the preceding claims, wherein the hinged mounting member is one of a first mounting member and a second mounting member.

15. An aircraft wing, said aircraft wing comprising a hinge device according to any of the preceding claims, wherein, The first mounting member and the second mounting member are respectively fixed to the first wing section and the second wing section. Optionally, the hinge device does not extend beyond the outer surface of the wing tip and the wing box, respectively.

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