阅读说明：本技术 飞行器、可折叠飞行器机翼及相关方法 (Aircraft, foldable aircraft wing and related methods ) 是由 保罗·W·迪斯 埃里克·格鲁纳 迈克尔·阿丁顿 戴维·道格拉斯·伯斯 埃里克·德怀特·布洛姆 于 2020-01-31 设计创作，主要内容包括：本发明公开了可折叠飞行器机翼。示例飞行器包括具有固定机翼部分、可折叠机翼部分和铰链的可折叠机翼,该铰链用于相对于固定机翼部分枢转地联接可折叠机翼部分。铰链包括机翼过渡部分,机翼过渡部分包括机翼铰链肋和机翼柱肋,机翼铰链肋中的相应一些联接至机翼柱肋中的相应一些。铰链还包括翼尖过渡部分,翼尖过渡部分包括翼尖铰链肋,其中翼尖铰链肋的相应端定位在对应机翼铰链肋与机翼柱肋的相应一些之间。(The invention discloses a foldable aircraft wing. An example aircraft includes a foldable wing having a fixed wing portion, a foldable wing portion, and a hinge for pivotally coupling the foldable wing portion relative to the fixed wing portion. The hinge includes a wing transition portion including wing hinge ribs and wing column ribs, respective ones of the wing hinge ribs being coupled to respective ones of the wing column ribs. The hinge further includes a tip transition portion including tip hinge ribs, wherein respective ends of the tip hinge ribs are positioned between respective ones of the corresponding wing hinge ribs and wing post ribs.)

1. An aircraft (100) comprising:

a foldable wing (104, 204) comprising a fixed wing portion (202), a foldable wing portion, and a hinge (400) for pivotally coupling the foldable wing portion relative to the fixed wing portion (202), the hinge (400) comprising:

a wing transition portion (402) including wing hinge and wing post ribs (610, 612, 614, 616, 1216), respective ones of the wing hinge ribs being coupled to respective ones of the wing post ribs (610, 612, 614, 616, 1216); and

a wing tip transition portion (404) comprising wing tip hinge ribs, respective ends of the wing tip hinge ribs being positioned between respective ones of the wing hinge ribs and the wing post ribs (610, 612, 614, 616, 1216).

2. The aircraft (100) of claim 1, wherein at least a portion of the hinge (400) provides a double shear reaction.

3. The aircraft (100) of claim 2, wherein the portion of the hinge (400) to provide the double shear reaction comprises a latching interface (412).

4. The aircraft (100) of any preceding claim, wherein the hinge (400) provides a primary load path to transfer loads from the foldable wing section to the fixed wing section (202).

5. The aircraft (100) of claim 4, wherein the hinge (400) provides a main wing camber/spanwise load path and a flow/chord-wise stiffening load path.

6. The aircraft (100) of any preceding claim, wherein respective ones of the wing hinge ribs are coupled to respective ones of the tip hinge ribs to define hinge interfaces (212).

7. The aircraft (100) of claim 6, wherein the wing hinge rib and the tip hinge rib provide a single shear reaction at the hinge interface (212) when the hinge interface (212) is subjected to a single shear load.

8. The aircraft (100) of claim 7, further comprising a hinge pin assembly having a first hinge pin supported by the first wing hinge rib (602) and the first wing tip hinge rib (620, 1220), a second hinge pin supported by the second wing hinge rib (622, 1222) and the second wing tip hinge rib (222), and a third hinge pin having a first end supported by the third wing hinge rib (606) and the third wing tip hinge rib (624, 1224) and having a second end opposite the first end supported by the fourth wing hinge rib (608) and the fourth wing tip hinge rib (626).

9. The aircraft (100) of any preceding claim, wherein respective ones of the wing hinge ribs and the wing post ribs (610, 612, 614, 616, 1216) are coupled to respective ones of the wing tip hinge ribs along a latch interface (412).

10. The aircraft (100) of claim 9, wherein the wing hinge ribs and the wing post ribs (610, 612, 614, 616, 1216) provide a double shear reaction at the latch interface (412) when the latch interface (412) is subjected to a single shear load.

11. The aircraft (100) of claim 10, wherein at least one of the wing hinge rib, the wing post ribs (610, 612, 614, 616, 1216), and the wing tip hinge rib includes a latch pin hole.

12. The aircraft (100) of claim 11, wherein at least one of the wing hinge rib and the wing tip hinge rib includes a latch-pin aperture for receiving a latch pin.

13. A foldable aircraft wing comprising: a foldable wing tip; a fixed wing portion (202); and a hinge (400) for rotatably coupling the foldable wing tip to the fixed wing portion (202), the hinge (400) comprising:

a wing transition portion (402) including a first wing hinge rib, a second wing hinge rib, a third wing hinge rib, and a fourth wing hinge rib, the wing transition portion (402) further including a first wing column rib (610, 612, 614, 616, 1216) coupled to the first wing hinge rib (602), a second wing column rib (610, 612, 614, 616, 1216) coupled to the second wing hinge rib (604), a third wing column rib (610, 612, 614, 616, 1216) coupled to the third wing hinge rib (606), and a fourth wing column rib coupled to the fourth wing hinge rib (608); and

a tip transition portion (404) including a first tip hinge rib (220), a second tip hinge rib (222), a third tip hinge rib (224), and a fourth tip hinge rib (226), the first tip hinge rib (620, 1220) coupled to the first wing hinge rib (602) and the first wing column rib, the second tip hinge rib (622, 1222) coupled to the second wing hinge rib (604) and the second wing column rib, the third tip hinge rib (624, 1224) coupled to the third wing hinge rib (606) and the third wing column rib, and the fourth tip hinge rib (626, 1226) coupled to the fourth wing hinge rib (608) and the fourth wing column rib.

14. The foldable aircraft wing of claim 13, wherein at least one of the first wing hinge rib (602), the second wing hinge rib (604), the third wing hinge rib (606), the fourth wing hinge rib (608), the first wing tip hinge rib (620, 1220), the second wing tip hinge rib (622, 1222), the third wing tip hinge rib (624, 1224), and the fourth wing tip hinge rib (626, 1226) includes hinge pin holes aligned to receive a hinge pin assembly at a hinge interface (212).

15. The foldable aircraft wing of claim 14, wherein the hinge interface (212) provides a single shear reaction when the hinge interface (212) is subjected to a single shear load.

16. The foldable aircraft wing of claim 13 or 14, wherein at least one of the first, second, third, fourth, first, second, third, and fourth wing column ribs includes a latch pin hole aligned to receive a latch pin at a latch interface (412).

17. The foldable aircraft wing of claim 16, wherein the latch interface (412) provides a double shear reaction when the latch interface (412) is subjected to a single shear load.

18. The foldable aircraft wing of any of claims 13 to 17, wherein the wing transition portion (402) supports a first stop pad and the wing tip transition portion (404) supports a second stop pad.

19. The foldable aircraft wing of claim 18, wherein the first stop pad engages the second stop pad when the foldable aircraft wing is in an unfolded position, the engagement between the first and second stop pads providing a load path between the foldable wing tip and the fixed wing portion (202).

20. A method of enhancing the structural integrity of a fixed wing portion (202) and a foldable wing tip at a wing joint, the method comprising:

coupling a portion of one end of a tip hinge rib of a foldable wing tip between a wing hinge rib and a post hinge rib of a fixed wing portion (202), the wing hinge rib and the post hinge rib providing a double shear reaction to reduce or limit the transfer of pry forces into a latch-pin actuator positioned adjacent at least the portion of the end of the tip hinge rib when the portion of the end is subjected to a single shear load.

21. The method of claim 20, further comprising pivotally coupling the foldable wing tip and the fixed wing portion (202) via a hinge pin assembly passing through holes of the wing hinge rib and the tip hinge rib.

Technical Field

The present invention relates generally to aircraft wings, and more particularly to foldable aircraft wings.

Background

Long span wings are desirable for commercial aircraft because such wings are more aerodynamically efficient than wings having shorter spans. Higher aerodynamic efficiency reduces fuel consumption, thereby reducing operating costs. The wingspan of an aircraft may be constrained based on dimensional limitations and/or regulations imposed by the International Civil Aviation Organization (ICAO), and/or based on physical infrastructure limitations of the airport (e.g., relative sizes of runways, taxiways, gates, hangars, etc.).

Disclosure of Invention

The present disclosure relates to an aircraft comprising: a foldable wing including a fixed wing portion, a foldable wing portion, and a hinge for pivotally coupling the foldable wing portion relative to the fixed wing portion, the hinge comprising: a wing transition portion including wing hinge ribs and wing column ribs, respective ones of the wing hinge ribs being coupled to respective ones of the wing column ribs; and a tip transition portion comprising tip hinge ribs, respective ends of the tip hinge ribs being positioned between respective ones of the wing hinge ribs and the wing post rib.

The present disclosure also relates to a foldable aircraft wing comprising: a foldable wing tip; a fixed wing portion; and a hinge for rotatably coupling the foldable wing tip to the fixed wing portion, the hinge comprising: a wing transition portion including a first wing hinge rib, a second wing hinge rib, a third wing hinge rib, and a fourth wing hinge rib, the wing transition portion further including a first wing column rib coupled to the first wing hinge rib, a second wing column rib coupled to the second wing hinge rib, a third wing column rib coupled to the third wing hinge rib, and a fourth wing column rib coupled to the fourth wing hinge rib; and a tip transition portion including a first tip hinge rib, a second tip hinge rib, a third tip hinge rib, and a fourth tip hinge rib, the first tip hinge rib coupled to the first wing hinge rib and the first wing column rib, the second tip hinge rib coupled to the second wing hinge rib and the second wing column rib, the third tip hinge rib coupled to the third wing hinge rib and the third wing column rib, and the fourth tip hinge rib coupled to the fourth wing hinge rib and the fourth wing column rib.

The present disclosure also relates to a method of enhancing the structural integrity of a fixed wing portion and a foldable wing tip at a wing joint, the method comprising: coupling a portion of one end of a tip hinge rib of a foldable wing tip between a wing hinge rib and a post hinge rib of a fixed wing section, the wing hinge rib and the post hinge rib providing a double shear reaction to reduce or limit the transfer of a pry force into a latch-pin actuator positioned adjacent at least the portion of the end of the tip hinge rib when the portion of the end is subjected to a single shear load.

Drawings

FIG. 1 is a perspective view of an example aircraft having an example foldable wing constructed in accordance with the teachings of the present invention.

FIG. 2 is a perspective view of the example foldable wing of FIG. 1, shown in an example deployed position.

Fig. 3 is a perspective view of the example foldable wing of fig. 1 and 2, shown in an example folded position.

Fig. 4 is a perspective view of the example foldable wing of fig. 1-3, shown in an example deployed position and without a skin.

Fig. 5 is a top view of an example hinge of the example foldable wing of fig. 1-4.

Fig. 6 is a partial perspective view of the example structure of fig. 1-5.

Fig. 7 is a cross-sectional view of an example hinge taken along hinge axis 210 of fig. 4.

Fig. 8 is a cross-sectional view of the example hinge taken along the latch axis 410 of fig. 4.

Fig. 9 is a schematic overlay of the example load path of fig. 1-5.

Fig. 10 is a partial cross-sectional view of the example foldable wing of fig. 1-9.

FIG. 11 is a perspective view of another example foldable wing disclosed herein.

Fig. 12 is a partial perspective view of the example hinge of fig. 11.

Certain examples are shown in the above-identified figures and described in detail below. In describing these examples, like or identical reference numbers are used to identify the same or similar elements.

Detailed Description

The foldable wing design may be used to reduce the wingspan of an aircraft when the aircraft is not in flight (e.g., when the aircraft is taxiing, parked, and/or stowed). Such designs typically include a foldable outboard portion (e.g., a foldable wing tip) of the wing hinged and/or rotatably coupled to a fixed inboard portion (e.g., a fixed structure or frame) of the wing. The hinged and/or rotatable coupling enables the foldable side portion to move relative to the fixed side portion between a deployed position (e.g., a deployed or flight position) and a folded position (e.g., a stowed position). The foldable outboard portion may be moved from the folded position to the unfolded position prior to takeoff of the aircraft to increase the span of the aircraft. After the aircraft lands, the foldable outboard portion may be conversely moved from the unfolded position to the folded position to reduce the wingspan of the aircraft.

In some examples, a foldable wing for an aircraft includes a fixed wing portion having wing hinge ribs (wing hinge ribs) and wing post ribs (wing post ribs), wherein respective ones of the wing hinge ribs are coupled to respective ones of the corresponding wing post ribs. In some such examples, the foldable wing includes a foldable wing portion having a tip hinge rib, wherein respective ends of the tip hinge rib are positioned between respective ones of the wing hinge ribs and the wing post rib. A hinge pivotably couples the foldable wing section relative to the fixed wing section. In some examples, at least a portion of the hinge provides a double shear reaction. In some examples, the hinge portion providing the double shear reaction includes a latch interface. In some examples, the hinge includes one or more hinge pins to pass through openings formed in respective ones of the wing hinge rib and the wing tip hinge rib. In some examples, the foldable wing includes a latch. In some such examples, the latch is movable between a locked position that prevents pivotal movement of the foldable wing portion and the fixed wing portion about the hinge, and an unlocked position that enables pivotal movement of the foldable wing portion relative to the fixed wing portion about the hinge.

FIG. 1 is a perspective view of an aircraft 100 having foldable wings 102, 104 constructed in accordance with the teachings of the present invention. The foldable wings 102, 104 extend from a fuselage 106. The foldable wing 102 is identical in structure and function to the foldable wing 104. Therefore, for simplicity and brevity, only the foldable wing 102 will be discussed in detail. The aircraft 100 of the illustrated example is a commercial aircraft. In some examples, the foldable wings 102, 104 disclosed herein may be implemented with any other example aircraft, such as military aircraft, transport aircraft, and/or any other suitable aircraft.

Fig. 2 is a perspective view illustrating the foldable wing 102 of fig. 1 in an example deployed position 200 (e.g., a deployed position, an extended position, or a flight position). The foldable wing 102 includes a fixed wing portion 202 and a foldable wing tip 204. The foldable wing tip 204 is a foldable outboard portion of the foldable wing 102. The fixed wing portion 202 is a fixed inboard portion of the foldable wing 102. The fixed wing portion 202 of the foldable wing 102 is fixedly and/or rigidly coupled (e.g., directly or indirectly) to the fuselage 106 of the aircraft 100. In some examples, when the foldable wing tip 204 is in the deployed position 200 of fig. 2, the foldable wing tip 204 is parallel relative to the fixed wing portion 202. For example, when the foldable wing tip 204 is in the deployed position 200, the foldable wing tip 204 is an extension of the fixed wing portion 202. In some examples, the upper surface 206 of the fixed wing portion 202 forms a continuous surface with respect to the upper surface 208 of the foldable wing tip 204. In the deployed position 200, the foldable wing tip 204 is a portion of the aerodynamic surface of the fixed wing section 202 that generates lift during flight. The foldable wing tip 204 of the foldable wing 102 may rotate and/or fold relative to the fixed wing portion 202 of the foldable wing 102. Rotation and/or folding of the foldable wing tip 204 relative to the fixed wing portion 202 occurs about an example hinge line or hinge axis 210 defined by a hinge interface 212.

Fig. 3 is a perspective view illustrating the foldable wing 102 of fig. 1 and 2 in an example folded position 300. In some examples, the foldable wing tip 204 is positioned at an angle relative to the fixed wing portion 202 when the foldable wing tip 204 is in the folded position 300 of fig. 3. In the example shown in fig. 3, the foldable wing tip 204 is positioned at an angle of approximately 85 degrees relative to the position of the fixed wing portion 202. In other examples, the angle between the foldable wing tip 204 and the fixed wing portion 202 may be less than or greater than 85 degrees (e.g., 90 degrees, 45 degrees, 135 degrees, etc.) when the foldable wing tip 204 is in the folded position 300.

Fig. 4 is a perspective view illustrating the foldable wing 102 of fig. 1-3 in the deployed position 200. To define the hinge interface 212, the foldable wing 102 of the illustrated example includes a hinge 400. Specifically, the hinge 400 of the illustrated example defines a hinge interface 212, the hinge interface 212 enabling the foldable wing tip 204 to be pivotally attached relative to the fixed wing portion 202. The hinge 400 of the illustrated example includes a first (e.g., wing) transition portion 402 and a second (e.g., wing tip) transition portion 404. The wing transition portion 402 of the illustrated example is attached (e.g., extends) to a wing box 406 of the fixed wing portion 202, and the wing tip transition portion 404 of the illustrated example is attached (e.g., extends) to a wing tip box 408 of the foldable wing tip 204. In addition, the hinge 400 of the illustrated example locks or prevents pivotal movement of the foldable wing tip 204 relative to the fixed wing portion 202 along a latch axis 410 of the latch interface 412. The latch axis 410 of the illustrated example is offset (e.g., laterally offset) relative to the hinge axis 210. For example, the hinge axis 210 is outboard with respect to the latch axis 410. For example, the latch axis 410 is located closer to the wing box 406 than the hinge axis 210. For example, the hinge axis 210 is located between the wing tip box 408 and the latch axis 410, and the latch axis 410 is located between the wing box 406 and the hinge axis 210. In some examples, the hinge axis 210 is parallel relative to the latch axis 410. In some examples, the hinge axis 210 and/or the latch axis 410 are parallel with respect to the laterally outboard edges of the wing transition portion 402 and/or the wing tip transition portion 404. In some examples, the hinge axis 210 and the latch axis 410 are parallel relative to a fore-aft direction (e.g., a flight direction) of the aircraft 100. In some examples, the hinge axis 210 and the latch axis 410 are parallel relative to an edge 414 (e.g., inboard edge or rib) of the wing transition portion 402 or an edge 416 (e.g., outboard edge or rib) of the wing tip transition portion 404. In some examples, the hinge axis 210 and/or the latch axis 410 may have any other angle and/or orientation relative to the fore-aft direction. In some examples, the hinge axis 210 is not parallel to the latch axis 410.

As described in more detail below, the hinge 400 transfers or distributes loads from the foldable wing tip 204 (e.g., the tip box 408) to the fixed wing portion 202 (e.g., the wing box 406). Additionally, at least a portion of the hinge 400 of the illustrated example provides a double shear reaction. For example, the hinge 400 of the illustrated example provides a single shear reaction load along the hinge interface 212 and a double shear reaction load along the latch interface 412. Thus, the portion of hinge 400 that provides the double shear reaction includes latch interface 412.

Fig. 5 is a top view of a hinge 400 of the example foldable wing of fig. 1-4. As described above, the hinge 400 of the illustrated example couples the foldable wing tip 204 (FIG. 2) and the fixed wing portion 202 (FIG. 2). The wing transition portion 402 of the illustrated example defines a first wing hinge portion 502 and a second wing hinge portion 504 of the hinge interface 212. The wing tip transition portion 404 defines a first wing tip hinge portion 506, a second wing tip hinge portion 508, and a third wing tip hinge portion 510 of the hinge interface 212. The third wing tip hinge portion 510 of the illustrated example is located between the first wing tip hinge portion 506 and the second wing tip hinge portion 508.

The first and second wing hinge portions 502, 504 are interleaved with the wing tip hinge portion 506 and 510 when the wing tip transition portion 404 is coupled to the wing transition portion 402. For example, at least a portion of the first wing hinge portion 502 and/or at least a portion of the second wing hinge portion 504 of the fixed wing portion 202 extend into the foldable wing tip 204, and at least a portion of the wing tip hinge portion 506 and 510 extend into the fixed wing portion 202. To this end, the staggered configuration does not add an Outer Mold Line (OML) to the foldable wing 102. For example, the foldable wing 102 of the illustrated example has a relatively smooth transition between the fixed wing portion 202 and the foldable wing tip 204. In other words, the hinge 400 of the illustrated example does not interfere with or affect the aerodynamic properties or performance of the foldable wing 102. In some examples, between about 10% and 100% of the first and second wing hinge portions 502, 504 extend in the foldable wing tip 204. In some examples, between about 10% and 100% of the wing tip hinge portion 506 and 510 extend within the fixed wing portion 202. In some examples, each of the first and second wing hinge portions 502, 504 includes a width (e.g., in the fore-aft direction) and/or a length (e.g., in the inboard-outboard direction) that is different than a width (e.g., in the fore-aft direction) and/or a length (e.g., in the inboard-outboard direction) of a respective wing tip hinge portion of the wing tip hinge portions 506 and 510. In some examples, each of the first and second wing hinge portions 502, 504 includes a width (e.g., in the fore-aft direction) and/or a length (e.g., in the inboard-outboard direction) that is the same as the width (e.g., in the fore-aft direction) and/or the length (e.g., in the inboard-outboard direction) of the respective wing tip hinge portion of the wing tip hinge portions 506 and 510.

The first wing hinge portion 502 is spaced from the second wing hinge portion 504 to define a space or first opening 512 therebetween to receive the third wing tip hinge portion 510. The first wing tip hinge portion 506 is spaced from the third wing tip hinge portion 510 to define a space or first opening 514 therebetween to receive the first wing hinge portion 502. The second wing tip hinge portion 508 is spaced from the third wing tip hinge portion 510 to define a space or second opening 516 therebetween to receive the second wing hinge portion 504. Thus, the first wing tip hinge portion 502 is located between the first wing tip hinge portion 506 and the third wing tip hinge portion 510, and the second wing tip hinge portion 504 is located between the second wing tip hinge portion 508 and the third wing tip hinge portion 510. As described above and in more detail below, the hinge interface 212 of the illustrated example transfers loads from the foldable wing tip 204 to the fixed wing portion 202 when the foldable wing tip 204 is in the deployed position 200, the folded position 300, during flight, and the like. In some examples, the wing transition portion 402 may include any number of wing hinge portions (e.g., more or less than the first and second wing hinge portions 502, 504), and/or the wing tip transition portion 404 may include any number of wing tip hinge portions (e.g., more or less than the wing tip hinge portion 506 and 510). In some examples, the hinge interface 212 configuration may be mirrored such that the wing transition portion 402 includes three wing hinge portions and the wing tip transition portion 404 includes two wing tip hinge portions. In some examples, the wing transition portion 402 includes only the first wing hinge portion 502 and the wing tip transition portion includes only the first wing tip hinge portion 506 and the third wing tip hinge portion 510. In some examples, the wing transition portion 402 includes a first wing hinge portion 502 and a second wing hinge portion 504, and the wing tip transition portion 404 includes only a third wing tip hinge portion 510. In some examples, the wing transition portion includes any number of wing hinge portions and the wing tip transition portion includes any number of wing tip hinge portions.

Fig. 6 is a partial perspective view of the hinge 400 of fig. 1-5 looking outboard toward the wing tip. The wing transition portion 402 of the illustrated example includes a first wing hinge rib 602, a second wing hinge rib 604, a third wing hinge rib 606, a fourth wing hinge rib 608, a first post rib 610, a second post rib 612, a third post rib 614, and a fourth post rib 616. For example, the first wing hinge portion 502 (fig. 5) of the illustrated example includes a first wing hinge rib 602 and a second wing hinge rib 604. The first wing hinge rib 602 is spaced apart from the second wing hinge rib 604. The second wing hinge portion 504 (fig. 5) of the illustrated example includes a third wing hinge rib 606 and a fourth wing hinge rib 608. The third wing hinge rib 606 is spaced apart from the fourth wing hinge rib 608. As described above, the wing transition section 402 is connected to the fixed wing box 406 (fig. 4). To couple to the fixed wing box 406, the first wing hinge rib 602 is attached to (e.g., abuts) the front spar of the wing box 406, and the fourth wing hinge rib 608 is attached to (e.g., abuts) the rear spar of the wing box 406.

The tip transition portion 404 of the illustrated example includes a first tip hinge rib 620, a second tip hinge rib 622, a third tip hinge rib 624, and a fourth tip hinge rib 626. Additionally, the tip transition portion 404 of the illustrated example includes a fifth tip hinge rib 628 adjacent the first tip hinge rib 620 and a sixth tip hinge rib 630 adjacent the fourth tip hinge rib 626. The first tip hinge portion 506 (FIG. 5) includes a first tip hinge rib 620 and a fifth tip hinge rib 628. The second tip hinge portion 508 (FIG. 5) includes a fourth tip hinge rib 626 and a sixth tip hinge rib 630. The third tip hinge portion 510 (fig. 5) includes second and third tip hinge ribs 622, 624. To couple the tip transition portion 404 and the tip box 408 (fig. 4), the first tip hinge rib 620 is attached to (e.g., abuts) the front spar of the tip box 408, and the fourth tip hinge rib 626 is attached to (e.g., abuts) the rear spar of the tip box 408.

FIG. 6 shows wing hinge ribs 602 and 608 and wing post ribs 610 and 616 relative to wing tip hinge ribs 620 and 630. For example, along the latch axis 410, at least a portion 632 (e.g., an end) of the first tip hinge rib 620 is located between the first wing hinge rib 602 and the first post rib 610, at least a portion 634 (e.g., an end) of the second tip hinge rib 622 is located between the second wing hinge rib 604 and the second post rib 612, at least a portion 636 (e.g., an end) of the third tip hinge rib 624 is located between the third wing hinge rib 606 and the third post rib 614, and at least a portion 638 (e.g., an end) of the fourth tip hinge rib 626 is located between the fourth wing hinge rib 608 and the fourth post rib 616.

Fig. 6 also includes a schematic of shear load 640 along hinge interface 212 and shear load 642 along latch interface 412. Specifically, the hinge interface 212 and the latch interface 412 are subjected to a single shear load. The wing hinge ribs 602-608 and the wing tip hinge ribs 620-626 provide hinge pin reaction loads 644 along the hinge interface 212 to react to the shear loads 640. Hinge pin reaction loads 644 (e.g., load vectors) are represented in fig. 6 by dashed arrowed lines. Wing hinge ribs 602 and 608 and wing post ribs 610 and 616 provide latch pin reaction loads 646 along latch interface 412. The latch-pin reaction load 646 (e.g., load vector) is represented in fig. 6 by the solid arrowed line. Based on the configuration of the wing hinge ribs 602 and 608, the wing post ribs 610 and 616, and the wing tip hinge ribs 620 and 630, the hinge pin reaction load 644 at the hinge interface 212 is a single shear reaction load and the latch pin reaction load 646 at the latch interface 412 is a double shear reaction load. For example, the wing hinge ribs 602 and 608 along with the corresponding wing column ribs 610 and 616 provide a double shear load path for the latch pin 802 (FIG. 8).

Fig. 7 is a cross-sectional view of the hinge 400 taken along line 7-7 of fig. 4 looking inboard toward the root of the fixed wing portion 202. Specifically, the cross-section of fig. 7 is taken along the hinge axis 210 of the hinge 400. As described above, when the wing transition portion 402 is coupled to the wing tip transition portion 404, the first wing hinge portion 502 is located or positioned between the first wing tip hinge portion 506 and the third wing tip hinge portion 510, and the second wing hinge portion 504 is located between the second wing tip hinge portion 508 and the third wing tip hinge portion 510. The wing hinge ribs 602 and 608 and the wing tip hinge rib 620 and 630 support and/or receive the hinge pin assembly 702. The hinge pin assembly 702 of the illustrated example includes a first hinge pin 704, a second hinge pin 706, and a third hinge pin 708. For example, each of the wing hinge ribs 602 and 608 and the wing tip hinge ribs 620 and 630 includes a hinge aperture 712 to receive the hinge pin assembly 702. For example, the hinge holes 712 of the first wing hinge rib 602, the first tip hinge rib 620, and the fifth tip hinge rib 628 receive or support the first hinge pin 704. The hinge holes 712 of the second wing hinge rib 604 and the second wing tip hinge rib 622 receive or support the second hinge pin 706. The hinge holes 712 of the third wing hinge rib 606, the fourth wing hinge rib 608, the third tip hinge rib 624, and the fourth tip hinge rib 626 receive the third hinge pin 708. The third hinge pin 708 extends between the third and fourth wing hinge ribs 606, 608 and the third and fourth tip hinge ribs 624, 626. In some examples, the hinge pin assembly 702 may include a hinge hole 712 extending through the wing hinge ribs 602 and 608 and the wing tip hinge ribs 620 and 630 or an integral hinge pin otherwise supported by the hinge holes 712 of the wing hinge ribs 602 and 608 and the wing tip hinge ribs 620 and 630. In some examples, the hinge pin assembly 702 includes two hinge pins or any other number of hinge pins (e.g., 3, 4, 5, 6, etc.).

Fig. 8 is a cross-sectional view of the hinge 400 taken along line 8-8 of fig. 4 looking inboard toward the root of the fixed wing portion 202. Specifically, the cross-section of fig. 8 is taken along the latch axis 410 of the hinge 400. To prevent the foldable wing tip 204 from rotating (e.g., locking rotation) relative to the fixed wing portion 202, the wing transition portion 402 of the illustrated example includes a latching system 800. Specifically, the latch system 800 of the illustrated example includes a plurality of latch pins 802. Each of the wing hinge ribs 602 and 608, wing post ribs 610 and 616, and wing tip hinge ribs 620 and 626 includes a latch pin hole 804, the latch pin holes 804 being aligned along the latch axis 410 to receive the respective latch pins 802. In some examples, the latching system 800 may include a latch pin bore 804 extending through the wing hinge ribs 602 and 608, the wing column ribs 610 and 616, and the tip hinge ribs 620 and 626 or an integral hinge pin otherwise supported by the wing hinge ribs 602 and 608, the wing column ribs 610 and 616, and the tip hinge ribs 620 and 626. In some examples, the latch system 800 includes two latch pins or any other number of hinge pins (e.g., 3, 4, 5, 6, etc.). In some examples, the latching system 800 includes a latching pin that interfaces with a latching pin hole formed on one of the wing hinge ribs 602-608 or the wing post ribs 610-616 and a latching pin hole formed on one of the wing tip hinge ribs 620-626.

Fig. 8 shows the latching system 800 in an unlatched or unlocked position 806. In the unlocked position 806, the latch pin 802 is removed from the latch pin bore 804 of the respective wing tip hinge rib 620 and 626 to enable the foldable wing tip 204 to rotate about the hinge axis 210 relative to the fixed wing portion 202.

To prevent the foldable wing tip 204 from rotating relative to the fixed wing portion 202, the latching system 800 moves to a locked or latched position. For example, in the locked position, the latch pins 802 are moved or positioned (e.g., by a latch-pin actuator) in the respective latch-pin holes 804. Specifically, in the locked position, the latch pin 802 is positioned within the latch pin bore 804 of the respective wing tip hinge rib 620 and 626. In the locked position, the foldable wing tip 204 is fixed (e.g., cannot rotate) relative to the fixed wing portion 202 about the hinge axis 210.

Fig. 9 is a schematic illustration of the hinge 400 of fig. 5 including an exemplary covering 900 of the load path of the hinge 400. Fig. 9 schematically illustrates hinge pins 704, 706, 708 and latch pin 802. The foldable wing 102 of fig. 9 is in the deployed position 200 and the latching system 800 is in the latched position 806. The wing tip transition portion 404 and the wing transition portion 402 are coupled together to define a hinge interface 212 and a latch interface 412. The hinge 400 provides a primary load path to transfer loads from the foldable wing tip 204 to the fixed wing portion 202. For example, the hinge 400 of the illustrated example utilizes the wing hinge rib 602 and 608 and the tip hinge rib 620 and 626 to transfer loads across the hinge interface 212. For example, the hinge 400 provides a load path from the wing tip box 408 to the wing box 406. In some examples, each of the wing hinge ribs 602-608 and the tip hinge ribs 620-626 can transfer loads across the hinge 400, thereby providing a failsafe system. In this way, if one of the wing hinge ribs 602-608 and the tip hinge rib 620-626 is damaged (e.g., the first wing hinge rib 602 is damaged) and unable to transfer loads, the other of the wing hinge ribs 602-608 and the tip hinge rib 620-626 distribute and transfer the loads to the fixed wing box 406.

Additionally, the hinge 400 of the illustrated example utilizes the hinge pin assembly 702 and the latch system 800 to react loads on the hinge interface 212 and the latch interface 412. For example, the mounting orientation (e.g., horizontal orientation) of the hinge pin assembly 702 enables the hinge pin assembly 702 to react loads across the hinge interface 212. Specifically, the first hinge pin 704 provides a single shear load path when the first hinge pin 704 is supported by the first wing hinge rib 602 and the first tip hinge rib 620 (e.g., the first rib interface). The second hinge pin 706 provides a single shear load path when the hinge pin assembly 702 is supported by the second wing hinge rib 604 and the second wing tip hinge rib 622 (e.g., the second rib interface). The second hinge pin 706 also reacts to axial loads (e.g., in the direction of the hinge axis 210). The third hinge pin 708 provides a double shear load path because the third hinge pin 708 has a first end (e.g., a third hinge rib interface) supported by the third wing hinge rib 606 and the third tip hinge rib 624, and has a second end (e.g., a fourth hinge rib interface) opposite the first end supported by the fourth wing hinge rib 608 and the fourth tip hinge rib 626.

To this end, the hinge 400 of the illustrated example provides a main wing camber/spanwise load path and a flow/chordwise stiffening load path. In FIG. 9, the line identified by reference numeral 902 represents the main wing bending or spanwise load path generally provided by the ribs or spars of the hinge 400 (e.g., tip hinge rib 620, 630, wing hinge rib 602, 608, wing post rib 610, 616, etc.). The line designated by reference numeral 904 represents the flow/chordwise reinforcing load path generally provided by one or more closed ribs or beams of the hinge 400. The direction of the shear load is from the foldable wing tip 204 through the hinge 400 to the fixed wing portion 202. In addition, wing hinge ribs 602 and 608 and corresponding wing post ribs 610 and 616 provide a double shear load path for the latch pin and reduce (e.g., minimize) transferring or prying loads into the latch-pin actuator that actuates the latch pin 802. In some examples, the latch-pin actuator may be positioned adjacent the end 634 of the wing tip hinge rib 620 and 626 and 638.

Fig. 10 is a partial cross-sectional view of the example foldable wing of fig. 1-9 looking forward from behind the wing 102. To react the preload during latching and/or to react flight loads during flight, the wing transition portion 402 of the illustrated example includes a stop pad 1002 (e.g., shoulder, strut, brace, etc.). The stop pad 1002 of the illustrated example is integral with and supported by one of the wing post ribs 612 and 616 (e.g., the third post rib 614). To react the preload during latching and/or react the load during flight, the wing tip transition portion 404 of the illustrated example includes a stop pad 1004 (e.g., shoulder, post, bracket, etc.). The stop pad 1004 is integral with and supported by one of the tip hinge ribs 620 and 630 (e.g., the third tip hinge portion 510). As described above, the first opening 512 of the wing transition portion 402 (FIG. 5) receives the third tip hinge portion 510. When the foldable wing tip 204 is in the deployed position 200, the stop pad 1002 interacts with (e.g., directly engages) the stop pad 1004. When the foldable wing tip 204 is in the folded position 300, the stop pad 1004 moves away (e.g., untwists or disengages) from the stop pad 1002. Specifically, when the foldable wing tip 204 is in the deployed position 200, the engagement between the stop pads 1002 and 1004 provides a load path 1006 to enable load transfer from the foldable wing tip 204 to the fixed wing portion 202. In some examples, the wing transition portion 402 may include a plurality of stops that interact with a plurality of stops of the wing tip transition portion 404.

Fig. 11 is a perspective view of another example foldable wing 1100 disclosed herein. Many of the components of the foldable wing 1100 of fig. 11 are substantially similar or identical to the components of the foldable wing 102 described above in connection with fig. 1-10. Therefore, these components will not be described in detail below. Rather, the interested reader is referred to the corresponding descriptions above to fully describe the structure and operation of such components. To facilitate this process, structures in fig. 11 that correspond to structures in fig. 1-10 will use the same reference numerals.

The foldable wing 1100 includes a fixed wing portion 1102 and a foldable wing tip 1104. The fixed wing portion 1102 of the foldable wing 1100 is a wing box 1106 fixedly and/or rigidly coupled (e.g., directly or indirectly) to a fuselage (e.g., fuselage 106) of an aircraft (e.g., aircraft 100). The foldable wing tip 1104 is a tip box 1108 and is the foldable outboard portion of the foldable wing 1100. Unlike the foldable wing 102 of fig. 1-10, the foldable wing 1100 does not include the wing transition section 402 and the wing tip transition section 404. Instead, the wing box 1106 and the wing tip box 1108 define a hinge interface 1110 to enable the foldable wing tip 1104 to rotate and/or fold relative to the fixed wing portion 1102 about an example hinge line or hinge axis 1112. For example, the hinge interface 1110 of the foldable wing 1100 is located between the wing box 1106 (e.g., at its outboard end) and the wing tip box 1108 (e.g., at its inboard end).

To define the hinge interface 1110, the foldable wing 1100 includes a hinge 1114. Specifically, the hinges 1114 enable the foldable wing tips 1104 to be pivotally attached relative to the fixed wing portions 1102. In addition, the hinge 1114 of the illustrated example locks or prevents pivotal movement of the foldable wing tip 1104 relative to the fixed wing portion 1102 along a latch axis 1116 of the latch interface 1118. The latch axis 1116 of the illustrated example is offset (e.g., laterally offset) relative to the hinge axis 1112. Specifically, the hinge axis 1112 is located outside of the latch axis 1116.

To define the hinge interface 1110, the fixed wing portion 1102 (e.g., wing box 1106) defines a first wing hinge portion 1122 and a second wing hinge portion 1124 of the hinge interface 1110, and the foldable wing tip 1104 (e.g., wing tip box 1108) defines a first wing tip hinge portion 1126, a second wing tip hinge portion 1128, and a third wing tip hinge portion 1130 of the hinge interface 1110. The third tip hinge portion 1130 of the illustrated example is positioned between the first tip hinge portion 1126 and the second tip hinge portion 1128. When the foldable wing tip 1104 is coupled to the fixed wing portion 1102, the first and second wing hinge portions 1122, 1124 are interleaved with the wing tip hinge portion 1126 and 1130. For example, at least a portion of the first wing hinge portion 1122 and/or at least a portion of the second wing hinge portion 1124 of the fixed wing portion 1102 extend into the foldable wing tip 1104, and at least a portion of the wing tip hinge portions 1126 and 1130 extend into the fixed wing portion 1102. Specifically, the first wing hinge portion 1122 is spaced from the second wing hinge portion 1124 to define a space or first opening 1132 therebetween to receive the third tip hinge portion 1130. The first wing tip hinge portion 1126 is spaced apart from the third wing tip hinge portion 1130 to define a space or first opening 1134 therebetween to receive the first wing hinge portion 1122. The second wing tip hinge portion 1128 is spaced apart from the third wing tip hinge portion 1130 to define a space or second opening 1136 therebetween to receive the second wing hinge portion 1124. Thus, the first wing hinge portion 1122 is located between the first wing tip hinge portion 1126 and the third wing tip hinge portion 1130, and the second wing hinge portion 1124 is located between the second wing tip hinge portion 1128 and the third wing tip hinge portion 1130. In some examples, the fixed wing portion 1102 only includes a first wing hinge portion 1122 and the foldable wing tip 1104 only includes a first wing tip hinge portion 1126 and a third wing tip hinge portion 1130. In some examples, the fixed wing portion 1102 includes a first wing hinge portion 1122 and a second wing hinge portion 1124, and the foldable wing tip 1104 includes only a third wing tip hinge portion 1130. In some examples, the fixed wing portion 1102 includes any number of wing hinge portions and the foldable wing tip 1104 includes any number of wing tip hinge portions.

The staggered configuration does not increase the Outer Mold Line (OML) of the foldable wing 1100. For example, the foldable wing 1100 of the illustrated example has a relatively smooth transition between the fixed wing portion 1102 and the foldable wing tip 1104. In other words, the hinge 1114 of the illustrated example does not interfere with or affect the aerodynamic properties or performance of the foldable wing 1100. For example, when the foldable wing tip 1104 is in the deployed position, the foldable wing tip 1104 is an extension of the fixed wing portion 1102. In some examples, the upper surface 1138 of the fixed wing portion 1102 forms a continuous surface with respect to the upper surface 1140 of the foldable wing tip 1104. In the deployed position, the foldable wing tip 1104 is part of the lift-producing aerodynamic surface of the fixed wing section 1102 during flight. In some examples, between about 10% and 100% of the first and second wing hinge portions 1122, 1124 extend in the foldable wing tip 1104. In some examples, between about 10% and 100% of the tip hinge portion 1126 and 1130 extend in the fixed wing portion 1102. In some examples, the first and second wing hinge portions 1122, 1124 each include a width (e.g., in the fore-aft direction) and/or a length (e.g., in the inboard-outboard direction) that is different than the width (e.g., in the fore-aft direction) and/or the length (e.g., in the inboard-outboard direction) of the respective wing tip hinge portions 1126 and 1130. In some examples, the first and second wing hinge portions 1122, 1124 each include a width (e.g., in the fore-aft direction) and/or a length (e.g., in the inboard-outboard direction) that is the same as the width (e.g., in the fore-aft direction) and/or length (e.g., in the inboard-outboard direction) of the corresponding tip hinge portion 1126 and 1130. In some examples, the hinge axis 1112 and the latch axis 1116 are parallel relative to a fore-aft direction (e.g., a flight direction) of the aircraft 100. In some examples, the hinge axis 1112 and the latch axis 1116 are parallel with respect to an edge 1107 (e.g., a rib) of the wing box 1106 or an edge (e.g., a rib) of the wing tip box 1108. In some examples, the hinge axis 1112 and/or the latch axis 1116 may have any other angle and/or orientation relative to the fore-aft direction. In some examples, the hinge axis 1112 is not parallel to the latch axis 1116.

Fig. 12 is a partial perspective view of the hinge interface 1110 of fig. 11 looking outboard toward the foldable wing tip 1104. The fixed wing portion 1102 (e.g., wing box 1106) includes a first wing hinge rib 1202, a second wing hinge rib 1204, a third wing hinge rib 1206, a fourth wing hinge rib 1208, a first column rib 1210, a second column rib 1212, a third column rib 1214, and a fourth column rib 1216. For example, the first wing hinge portion 1122 (fig. 11) includes a first wing hinge rib 1202 spaced apart from a second wing hinge rib 1204. The second wing hinge portion 1124 (fig. 11) includes a third wing hinge rib 1206 spaced apart from a fourth wing hinge rib 1208. In some examples, a first wing hinge rib 1202 is attached to (e.g., abuts) or formed with a front spar of the wing box 1106 and a fourth wing hinge rib 1208 is attached to (e.g., abuts) or formed with a rear spar of the wing box 1106.

The foldable wing tip 1104 (e.g., the wing tip box 1108) includes a first wing tip hinge rib 1220, a second wing tip hinge rib 1222, a third wing tip hinge rib 1224, and a fourth wing tip hinge rib 1226. The first tip hinge portion 1126 (FIG. 11) includes a first tip hinge rib 1220 and the second tip hinge portion 1128 (FIG. 11) includes a fourth tip hinge rib 1226. In some examples, the first wing tip hinge rib 1220 is attached to (e.g., abuts) or formed with the front spar of the wing tip box 1108, and the fourth wing tip hinge rib 1226 is attached to (e.g., abuts) or formed with the back spar of the wing tip box 1108. The third wing tip hinge portion 1130 (fig. 11) includes second and third wing tip hinge ribs 1222, 1224. The hinge interface 1110 receives a hinge pin assembly (e.g., hinge pin assembly 702) and the latch interface 1118 receives a latch system (e.g., latch system 800 and/or latch pin 802).

FIG. 12 shows wing hinge ribs 1202-1208 and wing post ribs 1210-1216 relative to wing tip hinge ribs 1220-1226. For example, along the latch axis 1116, at least a portion 1232 (e.g., an end) of the first wing tip hinge rib 1220 is positioned between the first wing hinge rib 1202 and the first column rib 1210; at least a portion 1234 (e.g., an end) of the second wing tip hinge rib 1222 is positioned between the second wing hinge rib 1204 and the second post rib 1212; at least a portion 1236 (e.g., an end) of the third tip hinge rib 1224 is positioned between the third wing hinge rib 1206 and the third post rib 1214, and at least a portion 1238 (e.g., an end) of the fourth tip hinge rib 1226 is positioned between the fourth wing hinge rib 1208 and the fourth post rib 1216.

Fig. 12 also includes a schematic of shear load 1240 along hinge interface 1110 and shear load 1242 along latch interface 1118. Specifically, the hinge interface 1110 and the latch interface 1118 are subjected to a single shear load. Wing hinge ribs 1202-1208 and wing tip hinge ribs 1220-1226 provide hinge pin reaction loads 1244 along hinge interface 1110 to react shear loads 1240. Hinge pin reaction loads 1244 (e.g., load vectors) are represented in fig. 12 by dashed arrow lines. Wing hinge ribs 1202-1208 and wing post ribs 1210-1216 provide latch pin reaction loads 1246 along the latch interface 1118. The latch-pin reaction load 1246 (e.g., load vector) is represented in fig. 12 by the solid arrowed line. Based on the configuration of the wing hinge ribs 1202-1208, wing column ribs 1210-1216, and wing tip hinge ribs 1220-1226, the hinge pin reaction load 1244 at the hinge interface 1110 is a single shear reaction load and the latch pin reaction load 1246 at the latch interface 1118 is a double shear reaction load. For example, wing hinge ribs 1202-1208 along with corresponding wing column ribs 1210-1216 provide a double shear load path for latch pin 802 (FIG. 8). Additionally, the hinge interface 1110 transfers loads from the foldable wing tip 1104 to the fixed wing portion 1102 when the foldable wing tip 1104 is in the deployed position, the folded position, etc. during flight. For example, the hinges 1114 transfer or distribute loads from the foldable wing tips 1104 (e.g., the tip box 1108) to the fixed wing portions 1102 (e.g., the wing box 1106).

In some examples, the fixed wing portion 1102 may include any number of wing hinge portions (e.g., more or less than the first and second wing hinge portions 1122, 1124) and/or the foldable tip 1104 may include any number of tip hinge portions (e.g., more or less than the tip hinge portion 1126 and 1130). In some examples, the hinge interface 1110 configuration may be mirrored such that the fixed wing portion 1102 includes three wing hinge portions and the foldable wing tip 1104 includes two wing tip hinge portions. In some examples, foldable wing 1100 may include any number of latching pins (e.g., 1, 2, 3, 4, 5, etc.) and/or any number of hinge pins (e.g., 1, 2, 3, 4, 5, etc.) to implement hinge 1114.

As can be appreciated from the foregoing, the disclosed hinge for a foldable aircraft wing advantageously provides a load path that transfers loads from a foldable wing tip to a fixed wing portion. In some examples, the hinge includes a hinge interface that experiences a single shear load. In some examples, the hinge includes a latch-pin interface that experiences double shear loading. In some examples, the hinge includes a wing tip transition portion and a wing transition portion coupled together to define a hinge interface and a latch-pin interface. In some examples, the wing tip transition portion and the wing transition portion of the hinge include a plurality of rib interfaces to provide a load path from the foldable wing tip to the fixed wing portion. In some examples, each rib interface is capable of transferring loads across the hinge to provide fail-safety. In some disclosed examples, the hinge pin interface enables the foldable wing tip to fold relative to the fixed wing or structure when the aircraft wing is not subjected to flight loads.

In some examples, an aircraft includes a foldable wing having a fixed wing portion, a foldable wing portion, and a hinge pivotally coupling the foldable wing portion relative to the fixed wing portion. The hinge includes a wing transition portion including wing hinge ribs and wing column ribs, respective ones of the wing hinge ribs being coupled to respective ones of the wing column ribs. The hinge further includes a tip transition portion including tip hinge ribs, wherein respective ends of the tip hinge ribs are positioned between respective ones of the wing hinge ribs and the wing post rib.

In some examples, at least a portion of the hinge provides a double shear reaction.

In some examples, the hinge portion providing the double shear reaction includes a latch interface.

In some examples, the hinge provides a primary load path to transfer loads from the foldable wing portion to the fixed wing portion.

In some examples, the hinges provide main wing camber/spanwise load paths and flow/chordwise stiffening load paths.

In some examples, respective ones of the wing hinge ribs are coupled to respective ones of the tip hinge ribs to define hinge interfaces.

In some examples, the wing hinge rib and the wing tip hinge rib provide a single shear reaction at the hinge interface when the hinge interface is subjected to a single shear load.

In some examples, the hinge pin assembly has a first hinge pin, a second hinge pin, and a third hinge pin, wherein the first hinge pin is supported by the first wing hinge rib and the first wing tip hinge rib, the second hinge pin is supported by the second wing hinge rib and the second wing tip hinge rib, and the third hinge pin has a first end supported by the third wing hinge rib and the third wing tip hinge rib and a second end opposite the first end supported by the fourth wing hinge rib and the fourth wing tip hinge rib.

In some examples, respective ones of the wing hinge ribs and wing column ribs are coupled to respective ones of the wing tip hinge ribs along the latch interface.

In some examples, the wing hinge rib and the wing post rib provide a double shear reaction at the latch interface when the latch interface is subjected to a single shear load.

In some examples, at least one of the wing hinge rib, wing post rib, and wing tip hinge rib includes a latch pin hole.

In some examples, at least one of the wing hinge rib and the wing tip hinge rib includes a latch-pin aperture for receiving the latch pin.

In some examples, a foldable aircraft wing includes a foldable wing tip, a fixed wing portion, and a hinge rotatably coupling the foldable wing tip to the fixed wing portion. The hinge comprises a wing transition portion comprising a first wing hinge rib, a second wing hinge rib, a third wing hinge rib, and a fourth wing hinge rib, the wing transition portion further comprising a first wing column rib coupled to the first wing hinge rib; a second wing column rib coupled to the second wing hinge rib; a third wing column rib coupled to the third wing hinge rib; and a fourth pillar hinge rib coupled to the fourth wing hinge rib. The hinge includes a tip transition portion including a first tip hinge rib, a second tip hinge rib, a third tip hinge rib, and a fourth tip hinge rib, the first tip hinge rib coupled to the first wing hinge rib and the first hinge column rib, the second tip hinge rib coupled to the second wing hinge rib and the second hinge column rib, the third tip hinge rib coupled to the third wing hinge rib and the third hinge column rib, and the fourth tip hinge rib coupled to the fourth wing hinge rib and the fourth hinge column rib.

In some examples, at least one of the first wing hinge rib, the second wing hinge rib, the third wing hinge rib, the fourth wing hinge rib, the first wing tip hinge rib, the second wing tip hinge rib, the third wing tip hinge rib, and the fourth wing tip hinge rib includes hinge pin holes aligned to receive a hinge pin assembly at a hinge interface.

In some examples, the hinge interface provides a single shear reaction when the hinge interface is subjected to a single shear load.

In some examples, at least one of the first wing column rib, the second wing column rib, the third wing column rib, the fourth wing column rib, the first wing tip hinge rib, the second wing tip hinge rib, the third wing tip hinge rib, and the fourth wing tip hinge rib includes a latch pin hole aligned to receive a latch pin at a latch interface.

In some examples, the latch interface provides a double shear reaction when the latch interface is subjected to a single shear load.

In some examples, the second post rib supports the first stop pad and the third post rib supports the second stop pad.

In some examples, the second wingtip hinge rib supports a third stop pad and the third wingtip hinge rib supports a fourth stop pad.

In some examples, the first stop pad is to engage the third stop pad and the second stop pad is to engage the fourth stop pad when the foldable aircraft wing is in the deployed position, the engagement between the first stop pad and the third stop pad and between the second stop pad and the fourth stop pad providing a load path between the foldable wing tip and the fixed wing portion.

In some examples, a method of enhancing structural integrity of a fixed wing portion and a foldable wing tip at a wing joint comprises: coupling a portion of one end of a tip hinge rib of a foldable wing tip between a wing hinge rib and a post hinge rib of a fixed wing section, the wing hinge rib and post hinge rib providing a double shear reaction when the portion of one end of the tip hinge rib is subjected to a single shear load to reduce or limit the transfer of prying forces into a latch-pin actuator positioned adjacent the portion of one end of the tip hinge rib.

In some examples, the method includes pivotally coupling the foldable wing tip and the fixed wing portion via a hinge pin assembly that passes through hinge holes of the wing hinge rib and the wing tip hinge rib.

In some examples, a foldable wing for an aircraft includes a fixed wing portion including wing hinge ribs and wing column ribs, wherein respective ones of the wing hinge ribs are coupled to respective ones of the wing column ribs. The foldable wing includes a foldable wing portion including wing tip hinge ribs, wherein respective ends of the wing tip hinge ribs are positioned between respective ones of the wing hinge ribs and the wing post ribs. A hinge pivotably couples the foldable wing section relative to the fixed wing section.

In some examples, the hinge portion providing the double shear reaction includes a latch interface.

In some examples, the hinge includes one or more hinge pins to pass through openings formed in respective ones of the wing hinge rib and the wing tip hinge rib.

In some examples, the foldable wing includes a latch that is movable between a latched position that prevents pivotal movement of the foldable wing portion and the fixed wing portion about the hinge and an unlatched position that enables pivotal movement of the foldable wing portion about the hinge relative to the fixed wing portion.

Although certain example methods, apparatus, and articles of manufacture have been disclosed herein, the scope of coverage of this patent is not limited thereto. On the contrary, this patent covers all methods, apparatus, and articles of manufacture fairly falling within the scope of the appended claims either literally or under the doctrine of equivalents.

The invention includes the subject matter described in the clauses below:

clause 1. an aircraft (100) comprising:

a foldable wing (104, 204) comprising a fixed wing portion (202), a foldable wing (104, 204) portion, and a hinge (400) for pivotally coupling a portion of the foldable wing (104, 204) with respect to the fixed wing portion (202), the hinge (400) comprising:

a wing transition portion (402) including wing hinge (400) and wing post ribs (610, 612, 614, 616, 1216), respective ones of the wing hinge (400) ribs being coupled to respective ones of the wing post ribs (610, 612, 614, 616, 1216); and

a wing tip transition portion (404) comprising wing tip hinge (400) ribs, respective ends of the tip hinge (400) ribs being positioned between respective ones of the wing hinge (400) ribs and the wing post ribs (610, 612, 614, 616, 1216).

Clause 2. the aircraft (100) of clause 1, wherein at least a portion of the hinge (400) provides a double shear reaction.

Clause 3. the aircraft (100) of clause 2, wherein the portion of the hinge (400) for providing the double shear reaction comprises a latching interface (412).

Clause 4. the aircraft (100) according to any one of the preceding clauses, wherein the hinge (400) provides a primary load path to transfer loads from the portion of the foldable wing (104, 204) to the fixed wing portion (202).

Clause 5. the aircraft (100) of clause 4, wherein the hinge (400) provides a main wing buckling/spanwise load path and a flow/chordwise stiffening load path.

Clause 6. the aircraft (100) according to any one of the preceding clauses, wherein respective ones of the wing hinge (400) ribs are coupled to respective ones of the wing tip hinge (400) ribs to define the hinge interface (212).

Clause 7. the aircraft (100) according to clause 6, wherein the wing hinge (400) rib and the tip hinge (400) rib provide a single shear reaction at the hinge interface (212) when the hinge interface (212) is subjected to a single shear load.

Clause 8. the aircraft (100) of clause 7, further comprising a hinge (400) pin assembly having a first hinge (400) pin, a second hinge (400) pin, and a third hinge (400) pin, the first hinge (400) pin supported by the first wing hinge (400) rib (602) and the first tip hinge (400) rib (620, 1220); the second hinge (400) pin is supported by the second wing hinge (400) rib (622, 1222) and the second wing tip hinge (400) rib (222), and the third hinge (400) pin has a first end supported by the third wing hinge (400) rib (606) and the third wing tip hinge (400) rib (624, 1224) and a second end opposite the first end supported by the fourth wing hinge (400) rib (608) and the fourth wing tip hinge (400) rib (626).

Clause 9. the aircraft (100) according to any one of the preceding clauses, wherein respective ones of the wing hinge (400) and wing post ribs (610, 612, 614, 616, 1216) are coupled to respective ones of the wing tip hinge (400) ribs along the latch interface (412).

Clause 10. the aircraft (100) according to clause 9, wherein the wing hinge (400) and wing post ribs (610, 612, 614, 616, 1216) provide a double shear reaction at the latch interface (412) when the latch interface (412) is subjected to a single shear load.

Clause 11 the aircraft (100) according to clause 10, wherein at least one of the wing hinge (400) rib, wing post ribs (610, 612, 614, 616, 1216), and wing tip hinge (400) rib includes a latch pin hole.

Clause 12 the aircraft (100) according to clause 11, wherein at least one of the wing hinge (400) rib and the wing tip hinge (400) rib includes a latch-pin aperture for receiving the latch pin.

Clause 13. a foldable aircraft (100) wing, comprising:

a foldable wing (104, 204) tip;

a fixed wing portion (202); and

a hinge (400) for rotatably coupling a tip of a foldable wing (104, 204) to a fixed wing portion (202), the hinge (400) comprising:

a wing transition section (402) including a first wing hinge (400) rib, a second wing hinge (400) rib, a third wing hinge (400) rib, and a fourth wing hinge (400) rib, the wing transition section (402) further including a first wing post rib (610, 612, 614, 616, 1216) coupled to the first wing hinge (400) rib (602); a second wing post rib (610, 612, 614, 616, 1216) coupled to the second wing hinge (400) rib (604); a third wing post rib (610, 612, 614, 616, 1216) coupled to the third wing hinge (400) rib (606); and a fourth pillar hinge (400) rib coupled to the fourth wing hinge (400) rib (608); and

a tip transition portion (404) comprising a first tip hinge (400) rib (220), a second tip hinge (400) rib (222), a third tip hinge (400) rib (224), and a fourth tip hinge (400) rib (226), the first tip hinge (400) rib (620, 1220) coupled to a first wing hinge (400) rib (602) and a first hinge (400) column rib; a second wing tip hinge (400) rib (222, 1222) coupled to the second wing hinge (400) rib (604) and the second hinge (400) post rib; the third wing tip hinge (400) rib (624, 1224) is coupled to the third wing hinge (400) rib (606) and the third hinge (400) column rib, and the fourth wing tip hinge (400) rib (626, 1216) is coupled to the fourth wing hinge (400) rib (608) and the fourth hinge (400) column rib.

Clause 14. the foldable aircraft (100) wing of clause 13, wherein at least one of the first wing hinge (400) rib (602), the second wing hinge (400) rib (604), the third wing hinge (400) rib (606), the fourth wing hinge (400) rib (608), the first tip hinge (400) rib (620, 1220), the second tip hinge (400) rib (620, 1220), the third tip hinge (400) rib (624, 1224), and the fourth tip hinge (400) rib (626, 1226) includes a hinge (400) pin hole aligned to receive a hinge (400) pin assembly at the hinge interface (212).

Clause 15. the wing of the foldable aircraft (100) according to clause 14, wherein the hinge interface (212) provides a single shear reaction when the hinge interface (212) is subjected to a single shear load.

Clause 16. the foldable aircraft (100) wing of clause 13 or clause 14, wherein at least one of the first, second, third, fourth, first, second, third, and fourth wing tip hinge (400) ribs includes a latch pin hole aligned to receive a latch pin at a latch interface (412).

Clause 17. the wing of the foldable aircraft (100) according to clause 16, wherein the latch interface (412) provides a double shear reaction when the latch interface (412) is subjected to a single shear load.

Clause 18. the foldable aircraft (100) wing of any of clauses 13-17, wherein the wing transition portion (402) supports a first stop pad and the wing tip transition portion (404) supports a second stop pad.

Clause 19. the foldable aircraft (100) wing of clause 18, wherein the first stop pad engages the second stop pad when the foldable aircraft (100) wing is in the deployed position, the engagement between the first stop pad and the second stop pad providing a load path between the tip of the foldable wing (104, 204) and the fixed wing portion (202).

Clause 20. a method of enhancing the structural integrity of a fixed wing portion (202) and a tip of a foldable wing (104, 204) at a wing joint, the method comprising:

coupling a portion of one end of a tip hinge (400) rib of a tip of a foldable wing (104, 204) between a wing hinge (400) rib and a post hinge (400) rib of a fixed wing portion (202), the wing hinge (400) rib and the post hinge (400) rib providing a double shear reaction to reduce or limit the transfer of pry forces into an at least partially positioned latch-pin actuator adjacent the one end of the tip hinge (400) rib when the portion of the one end is subjected to a single shear load.

Clause 21. the method of clause 20, further comprising pivotally coupling the tip of the foldable wing (104, 204) and the fixed wing portion (202) via a hinge (400) pin assembly passing through holes of the wing hinge (400) rib and the tip hinge (400) rib.