Hinge device for aircraft wings

Abstract

To provide a hinge device for aircraft wings. [Solution] A hinge device for an aircraft wing is provided to provide a folding wingtip. The hinge device comprises a first mounting portion for fixing to a first wing section and a second mounting portion for fixing to a second relatively foldable wing section, each having a plurality of hinge elements arranged along a hinge axis. The device comprises a latching device for securing the mounting portion to the folding movement, the latching device having a latching axis positioned substantially in the wing-length direction from the hinge axis so as to extend into, for example, the wing box. This can provide an efficient device that can be housed within the outer mold line of the wing and can reduce the need for fairing.

Description

Technical Field

[0005]

[0001] The present invention relates to a hinge device for an aircraft wing, for example, for folding the wing tip of an aircraft wing to reduce the width of the aircraft on the ground. Such a hinge device may also be used for other movable surfaces or structures of an aircraft that can be moved relative to a fixed part of the aircraft, such as a flight control surface.

Background Art

[0002] To increase aerodynamic efficiency, aircraft wings tend to have an increased wingspan. However, ground structures that need to accommodate aircraft, such as terminal gates, are limited in size. Therefore, it can be beneficial to provide a folding wing tip or outer wing structure on an aircraft wing such that the wing tip is folded upward to reduce the wingspan of the aircraft on the ground. Such folding wing tips are generally required to be latchable and lockable in a predetermined position, especially to be fixed in a deployed or in-line state, particularly during flight.

[0003] Some current aircraft, including military and commercial aircraft, have folding wing sections with a joining mechanism positioned between a fixed part of the wing, also known as the wing box, and a movable or folding part, also known as the wing tip. The joint is generally arranged along a hinge line extending in the chord direction between the generally fixed wing part and the movable wing part.

Summary of the Invention

Problems to be Solved by the Invention

[0004] When the wing has a relatively long chord and / or when the wing loading is relatively low, as in many military aircraft, a suitable hinge mechanism can generally be accommodated within the airfoil. However, in some commercial aircraft, particularly single-aisle or long-range aircraft, where the wing loading is relatively high compared to the size of the airfoil, it can be difficult to accommodate the hinge mechanism within the airfoil.

[0005] Such hinge mechanisms generally feature hinge elements having connecting lugs with integrated latches for securing the folding mechanism. These may protrude from the lower airfoil or the outer mold line (OML) of the cover.

[0006] This protrusion necessitates an aerodynamic fairing to accommodate the structure, increasing drag, number of parts, weight, and cost. In such cases, the pitch between the hinge axis and the latch centerline tends to be reduced to minimize the protrusion (e.g., less than 125 mm). However, reducing the hinge / latch pitch increases the flight load across the joint, thereby increasing stress and the resulting size and weight of the structure.

[0007] The present invention aims to mitigate this problem. [Means for solving the problem]

[0008] The present invention provides a hinge device for an aircraft wing, comprising: a first mounting portion for fixing to a first wing section, the mounting portion having a plurality of first hinge elements; and a second mounting portion for fixing to a second wing section, the second mounting portion having a plurality of second hinge elements, wherein the first and second hinge elements are arranged along a hinge axis such that the first mounting portion is foldable around the hinge axis relative to the second mounting portion between an extended state and a folded state; and the first and second mounting portions are arranged to be fixed against relative folding movement by a latch device having a latch axis when in the extended state, the latch axis being positioned substantially in the wing-length direction from the hinge axis.

[0009] This device enables a beneficial packaging of the folding mechanism, latch mechanism, and locking mechanism, eliminating the need for fairings. By shaping the hinges and latches in the wing's longitudinal direction, housing the hinge and latch devices within the upper and lower wing covers eliminates or significantly reduces the need for aerodynamic fairings and the resulting mounting elements such as nuts and bolts. The reduction in the number of parts simplifies the industrial process and reduces the complexity and subsequent work required to assemble the structure in the manufacturing environment. This can also increase aerodynamic efficiency by reducing drag.

[0010] In addition, increasing the pitch between the hinge and latch centerlines can reduce the flight load across the joint. This reduces the need for additional structures to support these flight loads, which is beneficial in terms of overall wing weight, cost, and simplicity. For example, the distance between the hinge axis and the latch axis may be greater than 200 mm, preferably up to 270 mm.

[0011] Preferably, at least a portion of the first mounting portion overlaps with at least a portion of the second mounting portion, and the latching device is provided in the overlapping area. For example, when 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 generating relative folding movements of the first and second mounting portions, the actuator being a linear actuator having, for example, a first end attached to the first mounting portion adjacent to the latch axis and a second end positioned to be fixed to the second mounting portion when in use. For example, the second end may be positioned to be fixed to the main spar or other fixed part of the wing box structure. Alternatively, the actuator may be a geared rotary actuator.

[0013] The latching device may comprise a plurality of first latching elements provided on a first mounting portion and a plurality of second latching elements provided on a second mounting portion, wherein the first latching elements extend from the first mounting portion beyond the first hinge element. The second latching elements may be recessed behind the second hinge element in the second mounting portion. In addition, the latching axis may be positioned below the hinge axis with respect to the upward folding of the hinge device.

[0014] Conveniently, at least some of the first latch elements are integrated with at least some of the first hinge elements. For example, there may be fewer latch elements than hinge elements, such that only some of the hinge elements form an integrated hinge / latch element. Alternatively, all of the latch elements may be integrated with the hinge elements. Conveniently, the first and second hinge elements may be arranged alternately along the hinge axis, for example, staggered, and the first and second latch elements may also be arranged alternately and / or staggered along the latch axis. The latch elements may be arranged in groups, and the actuator may be conveniently located in a first space between the first and second groups of latch elements.

[0015] For example, the first latch element may extend toward the latch axis, preferably beyond the latch axis, from the first mounting portion and be fixed to integrate with a panel positioned to cover the underside of the hinge device. This allows the underside of the wing to be sealed without requiring additional parts or seals.

[0016] Preferably, the first and second latch elements are provided with latch holes arranged to be aligned in the deployed state, and the device is provided with at least one latch pin arranged to be deployable in the latch holes along the latch axis to secure the first and second latch elements against relative folding movements when the device is in the deployed state.

[0017] Conveniently, two latch pins may be provided, for example, one at each end of the latch shaft, and the latch pins may be deployable inward toward the center of the latch shaft, or they may be deployable outward even if mounted toward the center of the latch shaft. For example, the latch pins may be provided in a second space between a first group and a second group of latch elements. To provide access for maintenance or repair, there may be a removable cover on the panel, which is aligned with the second space.

[0018] The first wing section may be a movable wingtip element, and the second wing section may be a fixed wing element or a wing box. Accordingly, the latching device may be housed within the wing box.

[0019] Furthermore, the present invention comprises a hinge mounting portion for the hinge coupling portion defined above, which is a first mounting portion or a second mounting portion, and an aircraft wing equipped with the hinge device defined above, wherein the first mounting portion is fixed to a first wing portion, and the second mounting portion is fixed to a second relatively foldable wing portion. Preferably, the hinge device does not extend outside the wingtip and the outer surface of the wing box, respectively. [Brief explanation of the drawing]

[0020] To make the present invention easier to understand, the accompanying drawings are referenced here as an example. [Figure 1] This is a lower perspective view of a conventional wing having a fairing that houses hinge and latching devices. [Figure 2] Figure 1 is a perspective view of a prior art hinge and latch coupling, which may be used in the wing shown in Figure 1. [Figure 3] This is a schematic plan view of a hinge and latching device. [Figure 4] Figure 3 is a perspective view of the apparatus. [Figure 5] Figure 4 is a perspective view of the wingtip joint. [Figure 6A] Figure 3 shows a lower perspective view of the device at various positions. [Figure 6B]It is a bottom perspective view of the device in FIG. 3 at various positions. [Figure 6C] It is a bottom perspective view of the device in FIG. 3 at various positions. [Figure 6D] It is a bottom perspective view of the device in FIG. 3 at various positions. [Figure 7A] It is an end view of the device in FIG. 3 at a certain position. [Figure 7B] It is an end view of the device in FIG. 3 at a position different from FIG. 7A. [Figure 8] It is a schematic plan view of another hinge and latch device. [Figure 9] It is a perspective view of the device in FIG. 8. [Figure 10] It is a perspective view of the wing tip joint of FIG. 8. [Figure 11A] It is a bottom perspective view of the device in FIG. 8 at various positions. [Figure 11B] It is a bottom perspective view of the device in FIG. 8 at various positions. [Figure 11C] It is a bottom perspective view of the device in FIG. 8 at various positions. [Figure 11D] It is a bottom perspective view of the device in FIG. 8 at various positions. [Figure 12A] It is an end view of the device in FIG. 8. [Figure 12B] It is an end view of the device in FIG. 8.

Embodiments for Carrying Out the Invention

[0021] Referring to FIGS. 1 and 2, in an example of a hinge and latch device according to the prior art, the wing box joint 2 includes a bracket or attachment portion 4 for attaching to the fixed wing portion. The attachment portion 4 has a plurality of hinge lugs 6 extending from the hinge end 8 and arranged along the hinge axis 10. The attachment portion 4 also includes a plurality of latch lugs 12 for receiving one or more latch pins (not shown) along the latch axis 13. The hinge and latch device also includes a wing tip joint (not shown) having corresponding alternately positioned hinge lugs and latch lugs.

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

[0023] The present invention aims to provide a device having a hinge axis around which the wingtip can rotate and fold, and a location for a latch pin that extends into the wing and locks the wing in flight (deployed) state, thereby eliminating the need for an aerodynamic fairing. This is achieved by providing an integrated hinge / latch lug that extends in the wing-length direction within the wing box.

[0024] Referring to Figures 3, 4, and 5, the hinge and latch device comprises first and second mounting sections, each including a wingtip connector 20 and a wing box connector 22. The wingtip connector 20 includes flanges 24, 26 for mounting to the upper and lower surfaces of the wingtip airfoil, but the connector 20 can be secured to the inner end of the wingtip, which is a separate or integrated part, using flanges or brackets of any suitable size or shape. Similarly, the wing box connector 22 includes upper and lower flanges 30, 32 for mounting to the upper and lower surfaces of the wing box airfoil.

[0025] The joints 20 and 22 are relatively foldable by a hinge comprising a first set of hinge elements in the form of a first hinge lug 34 extending from the wingtip joint 20 and a second set of hinge elements in the form of a second hinge lug 36 extending from the wing box joint 22. The hinge lugs 34 and 36 are positioned alternately, preferably staggered, and joined together with hinge pins (not shown) extending along a hinge axis 38 through hinge openings 39 provided in each of the hinge lugs 34 and 36 to form a hinge that extends substantially in the chord direction. This allows the wingtip joint 20 to be folded between a folded position and an unfolded or in-line position, as will be described in more detail below.

[0026] At least some of the first hinge lugs are extended in length and extend into the wing box joint 22 and overlap with the wing box joint 22. The extended first hinge lugs 341 include a latch opening 40 at the distal end of each extended lug 341, forming a substantially longitudinally extending integrated hinge / latch lug. In this example, there are four integrated longitudinally extending hinge / latch lugs 341 provided at the wingtip joint 20 and two first hinge lugs 34 that are not extended in length.

[0027] At least some of the second hinge lugs 36 are also extended in length and extend rearward so as to be recessed into the wing box joint 22. This allows the integrated first lugs 341 to be alternately, preferably staggered, with the second extended lugs 361. The second extended lugs 361 also have latch openings 42 that are positioned to align with the opening 40 of the first extended lug 341 along the latch axis or latch line 44 when the joint is in the deployed (or in-line) position. The latch openings 40, 42 are positioned to receive at least one latch pin, in this example a left latch pin 46 and a right latch pin 48. The latch pins are deployed from each latch unit 54, 56 into the latch openings 40, 42 from positions adjacent to the right and left edges 50, 52 of the wing box joint 22, respectively, so as to lock the hinge device in the deployed position.

[0028] This device provides a relatively large pitch between the hinge wire or hinge axis and the latch wire or latch axis, for example, at least 200 mm, preferably at least about 270 mm, and thus provides the aforementioned benefits. In addition, to eliminate the need for fairings, the structure can be completely housed within the outer mold lines (OML) of the wingtip and the upper and lower covers of the wing box, as shown in Figure 4.

[0029] Referring to Figure 5, a panel 70 is provided on the underside of the wingtip joint 20, which extends across the joint and is attached to an extended hinge lug 341. The panel 70 is positioned to extend just beyond the latch line 44. The panel 70 may be machined as part of the wingtip joint 22 to cover and seal the underside of the hinge device when in the deployed position.

[0030] This hinge device may be used in conjunction with various methods for driving the folding wings. For example, the integrated hinge / latch lug may be used in a hinge device that uses a GRA (geared rotary actuator) or a linear hydraulic actuator to drive the folding of the wings.

[0031] Referring also to Figures 6A-6D, and Figures 7A and 7B, in this example, the hinge device is configured to be used in conjunction with a folding wingtip driven by a linear hydraulic actuator 60. The first end 61 of the actuator 60 is positioned to be fixed to the wingbox coupling 22 on the fixed wing side via a wingbox bracket 62. In this example, the bracket 62 is attached to the wing sparra 64, which is positioned behind the wingbox coupling 22 when the coupling 22 is attached to the wingbox, but it is understood that any suitable fixing structure may be used. The second end 63 of the actuator 60 is the end of an extendable actuator rod, which is attached to a wingtip bracket 66, which is fixed to the wingtip coupling 20 on the wingtip side. This may be mounted at any convenient position spaced away from the hinge axis to provide a suitable lever.

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

[0033] Figures 6A and 7A show the hinge mechanism in flight. The actuator 60 is not extended, and the hinge mechanism, and therefore the wing, is deployed or flattened. To lock the wing in this state, the latch housing or units 54, 65 deploy the latch pins 46, 48 housed within the latch housing to the lugs 36 on the wing box and the integrated hinge / latch lugs 34 at the wingtips, respectively. This locks the wing as the latch pins 46, 48 prevent relative movement of the integrated hinge / latch lugs. This normally remains in place during flight.

[0034] Panel 70 is found to form a "clamshell" structure, capable of sealing the underside of the wing in the deployed position. Since the integrated hinge / latch lug 341 already requires considerable machining, it is economical to incorporate the large panel 70 under the wingtip 20. When the wingtip is deployed in flight, this large material section can simply cover and seal any gaps under the wing. Once the wingtip is deployed, sealing is completed almost entirely autonomously without the need for any additional parts or seals.

[0035] The wing folding process is illustrated with particular reference to Figures 6A to 6D. Figure 6B shows the hinge mechanism folded to approximately 22 degrees. The latch pins 46, 48 retract from the opening 42 of the latch lug and return to the latch housings 54, 56, unlocking the hinge mechanism and thus allowing the integrated hinge / latch lug 341 to move. The linear hydraulic actuator 60 operates so that the rod 63 is extended. This pushes the bracket 66, and therefore the panel 70 attached to the wingtip mounting section 20, away from the wing box, and rotates the wingtip mounting section 20 around the hinge axis 38 to fold the wingtip upward. Figure 6C shows the hinge folded to approximately 86 degrees after the actuator rod 63 has been further extended. This process can be performed after landing, while taxiing to the airport gate.

[0036] As shown in Figures 6D and 7B, when the linear hydraulic actuator 60 is further extended, the panel 70 is pushed and driven into the hinge device, and thus the wingtip is folded to the ground. In this state, the wingtip joint is folded upward, and the panel 70 and the connected extended lug 342 protrude below the wing box joint. When in use, the wingtip joint is folded, causing the wingtip to fold upward relative to the wing box, thereby reducing the effective wing length.

[0037] Referring to Figures 8, 9, and 10, another hinge and latch device also includes first and second mounting sections comprising a wingtip coupling section 80 and a wing box coupling section 82. The device is similar to those in Figures 3 to 7, except that the arrangement of the lugs is different.

[0038] The joints 80, 82 include upper and lower flanges 84, 86, 88, 90 for attachment to the upper and lower surfaces of the airfoil, as described above. The hinge comprises a first hinge lug 92 extending from the wingtip joint 80. In this example, the first hinge lug 92 is an extended lug, each including a hinge opening 96 for a hinge pin and a latch opening 98 for a latch pin, so as to have an integrated hinge / latch lug, respectively. The lugs 92 are positioned in groups toward each edge of the joint, leaving a central first space 100 between them. In this example, there are two pairs of lugs 92. The first space 100 may house an actuator mechanism for operating the hinge, such as a geared rotary actuator (GRA).

[0039] The first lugs 92 are arranged alternately with the second lugs 94 extending from the wing box joint 82, and each of the second lugs 94 is extended in length to provide an integrated hinge / latch lug and has a hinge opening 106 and a latch opening 108. The second lugs 94 are also arranged to be positioned in groups toward each edge of the joint so that space exists between the groups, and in this example there are three lugs 94 in each group. Each group of lugs 92,93 is joined with a hinge pin which is the right hinge pin 102 and a hinge pin which is the left hinge pin 104, allowing the wingtip joint 80 to be folded between the folded position and the deployed or inline position.

[0040] The latch openings 98,108 in each group of lugs are positioned to receive the latch pins when aligned in the deployed position of the coupling, and in this example, they receive the left latch pin 110 and the right latch pin 112. Due to the positioning of the two alternately arranged groups of lugs, an actuator or a pair of actuators (not shown) for the latch pins 110,112 may be positioned in the second space 114 between the groups of lugs toward the center of the coupling, such that the latch pins 110,112 move outward from a central position between the deployed position in the latch lugs 98,108 and the retracted position in the second space 114.

[0041] Referring to Figure 10, a panel 116 is provided on the underside of the wingtip joint 80, extending across the joint and attached to the base of each of the extended lugs 92. The panel 70 is positioned to extend just beyond the axis of the latch opening 98 and the ends of each lug 92 so as to cover and seal the underside of the wing joint when deployed. In this example, the panel 116 has a cutout 118 which can be covered by a removable cover 120, as shown in Figure 11. The removable cover 120 can allow access to internal components such as the actuator mechanism for maintenance or repair.

[0042] The folding process is illustrated in Figures 11A-11C, and Figures 12A and 12B. Figures 11A and 12A show the hinge mechanism in flight, where the joint, and therefore the wing, is deployed or flattened. To lock the wing in this state, the latch actuator deploys the latch pins 110, 112 outward from the second space 114 so as to extend through aligned latch openings 98, 108 in the first and second lugs 92, 94 of the wing box 82 and wingtip 80. This locks the wing by preventing relative movement of the integrated hinge / latch lugs 92, 94, which normally remain in place during flight.

[0043] As shown in Figures 11C and 12B, the operation of the GRA drives the hinge device, and thus the wingtip to a folded ground position. In this position, the wingtip joint 80 is folded upward, and the panel 116 and the connected extended lug 92 protrude below the wing box joint 82. When in use, the wingtip is folded upward relative to the wing box, thereby reducing the effective wingspan.

Claims

1. A hinge device for an aircraft wing, A first mounting portion for fixing to a first wing portion, comprising a first mounting portion having a plurality of first hinge elements, A second mounting portion for fixing to a second wing portion, comprising a second mounting portion having 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 portion is foldable around the hinge axis relative to the second mounting portion between an unfolded state and a folded state. A hinge device wherein the first and second mounting portions are arranged to be fixed against relative folding movement by a latch device having a latch shaft when in the deployed state, the latch shaft being positioned substantially in the wing-length direction from the hinge shaft.

2. The hinge device according to claim 1, wherein at least a portion of the first mounting portion overlaps with at least a portion of the second mounting portion, and the latch device is provided in the overlapping region.

3. The hinge device according to claim 1 or 2, wherein the distance between the hinge shaft and the latch shaft is greater than 200 mm, preferably between 200 mm and 270 mm.

4. A hinge device according to any one of claims 1 to 3, comprising an actuator for generating relative folding movement of the first mounting portion and the second mounting portion, wherein the actuator is at least one of a geared rotary actuator and a linear actuator having a first end attached to the first mounting portion adjacent to the latch axis and a second end positioned to be fixed to the second mounting portion when in use.

5. The latching device comprises a plurality of first latch elements provided on the first mounting portion and a plurality of second latch elements provided on the second mounting portion, wherein the first latch elements extend from the first mounting portion beyond each of the hinge elements, and the second latch elements are recessed behind the second hinge elements, and optionally at least some or all of the first latch elements are integrated with the first hinge elements, according to any one of claims 1 to 4.

6. The hinge device according to claim 5, wherein the actuator is provided in a first space between a first group and a second group of latch elements.

7. The hinge device according to claim 5 or 6, wherein the first latch element and the second latch element each have latch holes arranged to be aligned in the deployed state, and each has at least one latch pin arranged to be deployable along the latch axis for securing the first latch element and the second latch element against relative folding movement when the device is deployed.

8. The hinge device according to claim 7, comprising two latch pins positioned between opposing ends of the latch shaft and the center of the latch shaft, wherein the latch pins are optionally each deployable outward from a second space between a first group and a second group of the latch elements.

9. The hinge device according to any one of claims 5 to 8, wherein at least some of the first latch elements extend from the first mounting portion beyond the latch axis and are fixed to and optionally integrated with a panel positioned to cover the lower surface of the hinge device, the panel optionally comprising 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 located below the hinge axis.

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

12. The hinge device according to any one of claims 1 to 11, wherein the first hinge element is arranged alternately with the second hinge element.

13. The hinge device according to any one of claims 1 to 12, wherein the first wing portion is a movable wingtip element and the second wing portion is a fixed wing element.

14. A hinge mounting portion for a hinge joint according to any one of claims 1 to 13, wherein the hinge mounting portion is one of a first mounting portion and a second mounting portion.

15. An aircraft comprising a hinge device according to any one of claims 1 to 14, wherein the first mounting portion and the second mounting portion are fixed to the first wing portion and the second wing portion, respectively, and optionally the hinge device does not extend outside the wingtip and the outer surface of the wing box, respectively.

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