Foldable tilted wingtips with aerodynamic devices

Abstract

This application discloses a foldable, tilted wingtip with an aerodynamic device. The disclosed exemplary wing for use with an aircraft includes a fixed portion and a folding portion proximate a distal end of the wing. The folding portion includes an inclined surface. The wing also includes at least one of a feather or a winglet, and a hinge operably coupled between the fixed portion and the folding portion to enable the folding portion to fold relative to the fixed portion.

Description

Technical Field

[0001] The present disclosure relates generally to aircraft, and more particularly to foldable raked wingtips with aerodynamic devices. Background Art

[0002] In recent years, foldable wings have been implemented on aircraft to allow wings with relatively long wing spans. Specifically, during cruise, relatively long wing spans can result in favorable aerodynamic properties (such as reduced drag) and, therefore, reduced fuel consumption. However, these wing spans can also reduce the aircraft's ability to comply with wingspan requirements of airports, buildings, and / or maintenance areas (e.g., gates, runways, taxiway shoulders, taxiways, maintenance facilities, etc.). To maintain compliance with wingspan requirements, some aircraft employ foldable wings, in which the distal portion of the wing rotates to reduce the aircraft's effective wingspan when the aircraft is on the ground. Thus, aircraft with extended wingspans that employ folding can still comply with wingspan requirements. Summary of the Invention

[0003] An exemplary wing for use with an aircraft includes a fixed portion and a folding portion proximate a distal end of the wing. The folding portion includes an inclined surface. The wing also includes at least one of a feather or a winglet, and a hinge operably coupled between the fixed portion and the folding portion to enable the folding portion to fold relative to the fixed portion.

[0004] An exemplary aerodynamic structure for an aircraft includes a fixed portion including a first inclined portion, and a folding portion including a second inclined portion and at least one of a winglet or a feather. The aerodynamic structure further includes a hinge operatively coupling the fixed portion and the folding portion to enable the folding portion to rotate relative to the fixed portion.

[0005] An exemplary folding wingtip that rotates relative to a fixed portion of a wing includes: a canted portion extending along a lateral length of the folding wingtip; at least one of a winglet or a feather; and a hinge portion coupled to a hinge, wherein the hinge is used to rotationally couple the folding wingtip to the fixed portion.

[0006] An exemplary method includes coupling a folded portion proximate a distal portion of a wing, wherein the folded portion includes an inclined surface, and wherein at least one of the folded portions includes a winglet, or at least one of the wing or the folded portion includes a feather. BRIEF DESCRIPTION OF THE DRAWINGS

[0007] Figure 1 An exemplary aircraft is depicted in which the examples disclosed herein may be implemented.

[0008] Figure 2 yes Figure 1 A top view of the wingtip of an exemplary wingtip region of an aircraft.

[0009] Figures 3A-3C An exemplary wingtip according to the teachings of the present disclosure is depicted.

[0010] Figures 4A-4C Depicted separately Figures 3A-3C An exemplary wingtip folding.

[0011] Figures 5A-5B Additional exemplary wingtips according to the teachings of the present disclosure are depicted.

[0012] Figure 6 is a flowchart representing an exemplary method for implementing the examples disclosed herein.

[0013] The drawings are not drawn to scale. For example, the thickness of the depicted lifting surfaces is not drawn to scale. Instead, the thickness of a layer or region may be exaggerated in the drawings. Generally, the same reference numerals will be used throughout the drawings and accompanying written description to refer to the same or similar parts. As used in this patent, stating that any part is in any way on another part (e.g., positioned on it, located on it, set on it, or formed on it, etc.) indicates that the referenced part is in contact with the other part, or that the referenced part is above the other part with one or more intermediate parts located between them. Stating that any part is in contact with another part means that there are no intermediate parts between the two parts. Although the drawings show layers and regions (e.g., lifting surfaces) with clear lines and boundaries, some or all of these lines and / or boundaries may be ideal. In practice, the boundaries and / or lines may be unobservable, mixed, and / or irregular.

[0014] Descriptors "first," "second," "third," etc., are used herein when identifying multiple elements or components that can be referenced individually. Unless otherwise specified or understood based on the context of use, such descriptors are not intended to infer any meaning of priority, physical order or arrangement in a list, or chronological order, but are intended to facilitate understanding that the disclosed examples are merely used as labels to refer to multiple elements or components, respectively. In some examples, the descriptor "first" may be used to refer to an element in a specific embodiment, while in the claims, the same element may be referred to by different descriptors (such as "second" or "third"). In such cases, it should be understood that such descriptors are used only for the convenience of referencing multiple elements or components. DETAILED DESCRIPTION

[0015] The present invention discloses a foldable, canted wingtip with an aerodynamic device. Some aircraft employ folding portions (e.g., folding wingtips) to achieve favorable aerodynamic characteristics while ensuring compliance with airport infrastructure requirements. For example, a folding portion at the distal end of an aircraft wing folds upward to reduce the aircraft's overall wingspan in order to comply with the aforementioned infrastructure requirements.

[0016] The examples disclosed herein implement a foldable tilted wingtip with an aerodynamic device (e.g., a foldable wingtip having an inclined surface, an inclined portion, an inclined external shape, etc.) to improve the aerodynamic characteristics of an aircraft. Specifically, the foldable tilted wingtip implements at least one of a winglet or a feather, for example, to reduce the overall drag of the aircraft and reduce weight impact, thereby achieving significant fuel savings. In addition, because the aforementioned aerodynamic device can generally be implemented as a fixed, non-movable component, the implementation of the aerodynamic device is relatively cost-effective. In addition, the aforementioned aerodynamic device can be relatively easily produced and / or integrated into the foldable wingtip (e.g., relatively less complex integration).

[0017] In some examples, the angled portion of the foldable wingtip overlaps at least one of a winglet or feather mounted thereon. In other words, in some such examples, the winglet and / or feather are disposed on an angled portion or surface of the foldable wingtip. Additionally or alternatively, a front or rear feather is implemented on the angled foldable wingtip. In some examples, the foldable wingtip includes both the feather and the winglet.

[0018] As used herein, the terms "inclined," "inclined portion," and "inclined surface" refer to geometric shapes, surfaces, component shapes, and / or external shapes that exhibit an inclined curvature or a straight swept planar shape. As used herein, the term "hinge" refers to a component, assembly, and / or device used to enable rotational motion between two components. As used herein, the term "fixed portion" refers to a component, assembly, and / or device that is, for example, substantially fixed (i.e., fixed in translation and rotation) and / or constrained to another component that is movable, such as an aircraft fuselage.

[0019] Figure 1 An example aircraft 100 is depicted in which examples disclosed herein may be implemented. The aircraft 100 of the illustrated example includes a fuselage 102 having a cockpit 104, stabilizers 106, and fins 108. The example aircraft 100 also includes wings 110, both of which include corresponding engines 112 mounted thereon. In this example, the wings 110 also include wingtips 114 located near the distal ends of the wings 110. In this example, the wings 110, stabilizers 106, and fins 108 include corresponding control and high-lift surfaces (e.g., movable control surfaces, etc.) 116.

[0020] In operation, the aircraft 100 is steered in flight by movement of the control surfaces 116 in conjunction with the thrust provided by the engines 112. Specifically, rotational movement of the control surfaces 116 affects the movement and / or orientation of the aircraft 100 during flight by inducing airflow changes or gradients over the aircraft 100. During cruise of the aircraft 100, the control surfaces 116 are appropriately oriented and / or positioned to maintain the heading, trim, and overall aerodynamic performance of the aircraft 100. However, high drag may be encountered. Therefore, to enhance the aerodynamic performance of the aircraft 100, the wings 110 include a relatively long wingspan, which is wider than is typically permitted at some airports. As will be discussed below in conjunction with Figures 3A-5B As discussed in greater detail, the wings 110 also include aerodynamic devices (such as winglets or feathers), for example, located at wingtips 114 of the respective wings 110 for further aerodynamic performance enhancement. Accordingly, the wingtips 114 fold relative to the wings 110 to reduce the wing span (e.g., effective wing span) of the aircraft 100 (e.g., the wingtips 114 are folded when the aircraft 100 is on the ground).

[0021] Figure 2 yes Figure 1 FIG. 1 is a top view of a wingtip 114 of an exemplary aircraft 100. Specifically, the exemplary wingtip 114 exhibits an inclined shape and / or overall geometry. Figure 2 The parameters described may be associated with the exemplary wingtip 114 or other aerodynamic features and / or components described herein. Figure 2 As can be seen in the example shown, the wingtip 114 includes a leading edge sweep 202, represented by "a," and a half span 204, represented by "b." Additionally, the wingtip 114 has a root chord 206, represented by "c," a tip chord 208, represented by "d," and an overall span 210, represented by "e." The leading and trailing edge planforms of the wingtip 114 may be curved or straight.

[0022] For the examples disclosed herein, the parameters described below may be used to characterize the features associated therewith. In this example, the planform area of ​​the two wing tips 114 may be calculated based on the following exemplary equation 1:

[0023] A_Planform=b*(c+d) (1)

[0024] Additionally, the aspect ratio of the wingtip 114 may be calculated by the following exemplary Equation 2:

[0025]

[0026] In addition, the taper ratio (e.g. Figure 2The d / c) in the illustrated example may be used to characterize the examples disclosed herein. However, any suitable equation and / or mathematical relationship may be implemented instead.

[0027] According to the teachings of the present disclosure, an exemplary raked wingtip may exhibit an aspect ratio of approximately 1.4 to 2.5 (e.g., 1.8). In some examples, the taper ratio may be in the range of approximately 0.20 to 0.40 (e.g., 0.28). In some examples, the leading edge sweep may be approximately 40 to 70 degrees (e.g., 55 degrees).

[0028] Figures 3A-3C Depicted are exemplary wingtips (e.g., folding portions, foldable tilted wingtips, etc.) 302, 312, 322 according to the teachings of the present disclosure. The wingtips 302, 312, 322 may be used to implement Figure 1 Wing tip 114. Go to Figure 3A , an exemplary tilted foldable wingtip 302 is shown in a top view and a front view (shown together for clarity). According to the example shown, the wingtip 302 includes a winglet (e.g., an upper winglet) 304, which is implemented to extend upward (at Figure 3A 30). Additionally, wingtip 302 includes a base portion 306 and a hinge (e.g., hinge mounting portion / section, fold axis portion, hinge end, rotation axis, etc.) 308. In this example, wingtip 302 exhibits an inclined shape or curvature extending along its respective lateral and vertical lengths.

[0029] In some examples, a ratio of the height of the wingtip 302 to the half span of the wingtip 302 is between approximately 0.2 and 0.5. Additionally or alternatively, the aspect ratio of the winglet 304 is in the range of approximately 1.0 to 4.0.

[0030] Figure 3B An exemplary tilted foldable wingtip 312 is shown in top and front views. The exemplary wingtip 312 includes a winglet (e.g., an upper and lower winglet) 314, a base portion 316, and a hinge 318. Figure 3A In contrast to the winglet 304, the winglet 314 of the illustrated example extends upwardly and downwardly from the top surface 315 and bottom surface 317 of the wing 110, respectively. Figure 3B Specifically, the winglet 314 includes an upper portion 320 and a lower portion 321.

[0031] In some examples, the ratio of the height of the wingtip 312 to the half span of the wingtip 312 is between approximately 0.3 and 0.7. Additionally or alternatively, the aspect ratio of the winglet 314 is in the range of approximately 1.0 to 6.0.

[0032] Go to Figure 3C, an exemplary tilted foldable wingtip 322 is shown having a winglet 324, a base portion 326, and a hinge 328. In this example, the winglet 324 extends upward and downward from the wing 110, but is not connected to the hinge 328. Figure 3B The winglet 314 is positioned inboard of the distal end 329 of the wingtip 322. Thus, the winglet 324 of the illustrated example includes an upper portion 330 and a lower portion 332.

[0033] In some examples, the semi-spanwise position of the winglet 324 along the wingtip 322 is within a range of between approximately 0.5 and 0.9 of the semi-span of the wingtip 322 .

[0034] Figures 4A to 4C Shown respectively Figures 3A to 3C Folding of exemplary wing tips 302, 312, 322. Figure 4A , shows a front view of a wingtip 302 in a folded state and an unfolded state. In this example, the exemplary wingtip 302 is depicted from Figure 1 The fixed portion (e.g., stationary portion) 401 of the wing 110 rotates about the hinge 308, as generally indicated by arrow 402. In this example, the wing tip 302 rotates with the winglet 304 to within the span limit 404, which represents the span limit. Figure 1 The wingspan limit (eg, width limit) of the aircraft 100 is shown. Specifically, the wing tip 302 is rotated from an unfolded angle (eg, a deployed angle) to an angle of approximately 90 degrees (eg, a horizontal angle) with respect to the ground. Figure 4A shown).

[0035] Go to Figure 4B , an exemplary wing tip 312 is shown in a front view in a folded state and an unfolded state. Figure 4B As can be seen in the example shown, the wingtip 312 rotates about the hinge 318 relative to the fixed portion 401, as generally indicated by arrow 410. Specifically, the wingtip 312 rotates at an angle greater than 90 degrees such that the lower portion 321 of the winglet 314 is positioned within the span limit 404. In this example, the wingtip 312 rotates to a position aligned with the ground (e.g., Figure 4B as shown) and / or the fixing portion 401 is at an angle greater than 90 degrees.

[0036] Figure 4C An exemplary wingtip 322 is shown in a front view in a folded and unfolded state. Figure 4B Similar to the example of , the lower portion 332 of the winglet 324 rotates about the hinge 328 relative to the stationary portion 401 , as generally indicated by arrow 414 , such that the lower portion 332 remains within the span limit 404 .

[0037] Figures 5A to 5BDepicted are exemplary tilt-foldable wingtips 502, 512 according to the teachings of the present disclosure. The exemplary wingtips 502, 512 may be used to implement Figure 1 The wing tip is 114. Combined with Figures 3A-4C Compared to the exemplary wing tips 302 , 312 , 322 shown and described, the exemplary wing tips 502 , 512 instead implement a wingtip feather aerodynamic device that extends in a fore-aft direction of the wing 110 . Figure 5A , an exemplary wingtip 502 is shown in a top view and a front view (shown together for clarity). According to the example shown, the wingtip 502 includes feathers 504 (hereinafter feathers 504a, 504b), a base portion 506, a hinge 508, and a distal end 510. In this particular example, the feathers 504a extend relatively vertically with respect to the ground (e.g., at 90 degrees to the ground) (at Figure 5A ).

[0038] In some examples, the tip feather joint location is within a range of approximately 0.2 to 0.7 of the half-span of the wingtip 502 (e.g., outward from the root of the wingtip 502). In some examples including front and rear feathers, the front feather half-span length divided by the rear feather half-span length is equal to a range between approximately 0.8 and 1.2 (e.g., 1.0). In some examples, at least one of the feathers 504a, 504b has an aspect ratio between approximately 2.0 and 5.0. In some other examples, the feathers 504a, 504b are not positioned on the wingtip 502 (e.g., the wingtips 504a, 504b are located inboard of the wingtip 502).

[0039] Figure 5B An exemplary wingtip 512 is shown in front and top views, and is shown in a folded state and an unfolded state. According to the example shown, the wingtip 512 includes a feather 514 (hereinafter feathers 514a, 514b), a base portion 516, a hinge 518, and a distal end 520. Figure 5A Compared to the exemplary wingtip 502, the feathers 514a are canted (eg, exhibit curvature in multiple planes), as opposed to the relatively vertically aligned feathers 504a.

[0040] In operation, wingtip 512 rotates about hinge 518. To enable distal end 520 and base portion 516 to be within span limit 404, e.g., when aircraft 100 is on the ground, wingtip 512 is fully rotated (e.g., to an angular displacement of at least 90 degrees), as generally indicated by arrow 530.

[0041] In some examples, the angle of inclination of the front and rear feathers ranges from about 25 degrees to about 90 degrees. In some examples, the front feathers are positioned higher (from the ground) than the rear feathers. Additionally or alternatively, the height of the front feathers is higher than the height of the rear feathers. In some examples, the tip fold position coincides with an increase and / or transition in the leading edge sweep (e.g., an inflection, a change in slope, etc.). In some examples, the feather geometry is integrated with the winglet geometry (e.g., the feathers are incorporated into the winglet and / or winglet shape). In some other examples, the feathers 514a, 514b are not positioned on the wingtip 512.

[0042] For example, in this article, Figure 2-5B The above exemplary ranges and other ranges disclosed may be advantageous in terms of aerodynamic efficiency (e.g., drag reduction) in folding wingtip applications. Figure 2-5B A number of example dimensions and parameter values ​​are described, but any suitable dimensions and / or parameter values ​​may alternatively be implemented.

[0043] Figure 6 6 is a flow chart representing an exemplary method 600 for implementing the examples disclosed herein. Exemplary method 600 may be used to install a canted, foldable wingtip or folding portion (e.g., wingtip 302, 312, 322, 502, 512) onto an aircraft being manufactured or in service (e.g., during a modification and / or upgrade process).

[0044] According to the example shown, at least one of a winglet or a feather is attached to a foldable tilted wingtip (block 602). In some examples, the winglet or feather is integrally manufactured (e.g., die-cast, molded, etc.) on the wingtip. In other examples, the winglet or feather is mounted or assembled to the wingtip.

[0045] In this example, the foldable wingtip is coupled to a fixed portion of the wing at block 604. Specifically, the foldable wingtip is assembled to a hinge that defines an interface between the fixed portion and the foldable tilted wingtip.

[0046] At block 606, in some examples, the rotation of the foldable wingtip is verified and the process ends. For example, the rotation range of the foldable wingtip is verified to ensure that aerodynamic performance requirements and / or span requirements are met when the foldable wingtip is folded (e.g., folded upward).

[0047] Example 1 includes a wing for use with an aircraft. The wing includes a fixed portion and a folding portion proximate a distal end of the wing. The folding portion includes an inclined surface. The wing also includes at least one of a feather or a winglet and a hinge operably coupled between the fixed portion and the folding portion to enable the folding portion to fold relative to the fixed portion.

[0048] Example 2 includes the wing of Example 1, wherein the folded portion includes the winglet.

[0049] Example 3 includes the wing of Example 2, wherein the folded portion further includes the feathers.

[0050] Example 4 includes the wing of Example 3, wherein the folding portion is rotated to an angular displacement greater than 90 degrees from the fixed portion.

[0051] Example 5 includes the wing of Example 2, wherein the folded portion further comprises the feathers.

[0052] Example 6 includes the wing of Example 2, wherein the winglet comprises a height between approximately 0.2 and 0.9 of the half-span of the folded portion.

[0053] Example 7 includes the wing of Example 2, wherein the winglet comprises an aspect ratio between approximately 1.0 and 6.0.

[0054] Example 8 includes the wing of Example 1, wherein the folded portion has an aspect ratio between approximately 1.4 and 2.5.

[0055] Example 9 includes an aerodynamic structure for an aircraft. The aerodynamic structure includes a fixed portion including a first inclined portion; and a folding portion having a second inclined portion and at least one of a winglet or a feather. The aerodynamic structure further includes a hinge operably coupling the fixed portion and the folding portion to enable the folding portion to rotate relative to the fixed portion.

[0056] Example 10 includes the aerodynamic structure of Example 9, wherein the folded portion includes the winglet.

[0057] Example 11 includes the aerodynamic structure of Example 10, wherein the winglet extends beyond a bottom surface and a top surface of the wing.

[0058] Example 12 includes the aerodynamic structure of Example 11, wherein the folded portion is rotated to an angular displacement greater than 90 degrees from the fixed portion.

[0059] Example 13 includes the aerodynamic structure of Example 10, wherein the folded portion further comprises the feather.

[0060] Example 14 includes the aerodynamic structure of Example 10, wherein the winglet comprises a height between approximately 0.2 and 0.9 of the half-span of the folded portion.

[0061] Example 15 includes the aerodynamic structure of Example 9, wherein the folded portion includes the feather, and wherein the feather has a joint location between about 0.2 and 0.7 of a half-span of the folded portion.

[0062] Example 16 includes a folding wingtip that rotates relative to a fixed portion of a wing. The folding wingtip includes: a canted portion extending along a lateral length of the folding wingtip; at least one of a winglet or a feather; and a hinge portion coupled to a hinge, wherein the hinge is used to rotationally couple the folding wingtip to the fixed portion.

[0063] Example 17 includes the folding wingtip of Example 16, wherein the inclined portion overlaps at least one of the winglet or the feather.

[0064] Example 18 includes the folding wingtip of Example 16, wherein the folding wingtip includes the winglet having a height between approximately 0.2 and 0.9 of a half-span of the folding wingtip.

[0065] Example 19 includes the folding wingtip of Example 16, wherein the folding wingtip has an aspect ratio of between approximately 1.4 and 2.5.

[0066] Example 20 includes the folding wingtip of Example 16, wherein the folding wingtip comprises the feather, and wherein the feather has a joint location between approximately 0.2 and 0.7 of a half-span of the folding wingtip.

[0067] Example 21 includes an exemplary method comprising coupling a folded portion proximate a distal portion of a wing, wherein the folded portion comprises an inclined surface, and wherein at least one of the folded portions comprises a winglet, or at least one of the wing or the folded portion comprises a feather.

[0068] Example 22 includes the method of Example 21, and further includes constraining at least one of the winglet or the feather to the folded portion.

[0069] Example 23 includes the method of Example 21, wherein coupling the folding portion proximate the distal portion of the wing comprises coupling the folding portion to a hinge.

[0070] From the foregoing, it will be appreciated that exemplary methods, apparatus, and articles of manufacture have been disclosed that improve the aerodynamic efficiency of foldable wingtips without requiring additional complex and expensive moving parts and / or control systems. Thus, the disclosed examples enable increased aerodynamic efficiency in a cost-effective manner. Additionally, some of the examples disclosed herein may enable increased wingspan (e.g., larger span wing designs for greater aerodynamic benefit).

[0071] Although certain exemplary methods, apparatus, and articles have been disclosed herein, the scope of coverage of this patent is not limited thereto. Rather, this patent covers all methods, apparatus, and articles of manufacture fully within the scope of the claims of this patent. Although the examples disclosed herein are shown in relation to folding wingtips for aircraft, the examples disclosed herein can be applied to any suitable vehicle structure and / or application, including but not limited to diving applications, boating applications, automotive applications, and the like.

[0072] This disclosure includes the subject matter described in the following clauses:

[0073] Clause 1. A wing (110) for use with an aircraft (100), the wing (110) comprising:

[0074] Fixed portion (401);

[0075] a folded portion (302, 312, 322, 502, 512) proximate a distal end (329, 510, 520) of the wing (110), the folded portion (302, 312, 322, 502, 512) comprising an inclined surface;

[0076] at least one of a feather (504a, 504b, 514a, 514b) or a winglet (304, 314, 324); and

[0077] A hinge (308, 318, 328, 508, 518) is operably coupled between the fixed portion (401) and the folding portion (302, 312, 322, 502, 512) to enable the folding portion (302, 312, 322, 502, 512) to be folded relative to the fixed portion (401).

[0078] Clause 2. The wing (110) of clause 1, wherein the folded portion (302, 312, 322, 502, 512) comprises the winglet (304, 314, 324).

[0079] Clause 3. The wing (110) of clause 2, wherein the winglet (304, 314, 324) extends beyond a bottom surface (317) and a top surface (315) of the wing (110).

[0080] Clause 4. The wing (110) of clause 3, wherein the folding portion (302, 312, 322, 502, 512) is rotated to an angular displacement greater than 90 degrees from the fixed portion.

[0081] Clause 5. The wing (110) of clause 2 or clause 3, wherein the folded portion (302, 312, 322, 502, 512) further comprises the feathers (504a, 504b, 514a, 514b).

[0082] Clause 6. The wing (110) of any one of clauses 2 to 5, wherein the winglet (304, 314, 324) comprises a height between approximately 0.2 and 0.9 of the half span of the folded portion (302, 312, 322, 502, 512).

[0083] Clause 7. The wing (110) of any one of clauses 2 to 6, wherein the winglet (304, 314, 324) comprises an aspect ratio between approximately 1.0 and 6.0.

[0084] Clause 8. The wing (110) of any preceding clause, wherein the folded portion (302, 312, 322, 502, 512) has an aspect ratio of between about 1.4 and 2.5.

[0085] Clause 9: An aerodynamic structure (110) for an aircraft (100), the aerodynamic structure (110) comprising:

[0086] a fixing portion (401), the fixing portion comprising a first inclined portion;

[0087] A folding portion (302, 312, 322, 502, 512), the folding portion comprising:

[0088] a second inclined portion, and

[0089] The winglets (304, 314, 324) or feathers (504a, 504b, 514a, 514b)

[0090] at least one; and

[0091] A hinge (308, 318, 328, 508, 518) operably connects the fixed portion (401) and the folding portion (302, 312, 322, 502, 512) to enable the folding portion (302, 312, 322, 502, 512) to rotate relative to the fixed portion (401).

[0092] Clause 10. The aerodynamic structure (110) of clause 9, wherein the folded portion (302, 312, 322, 502, 512) comprises the winglet (304, 314, 324).

[0093] Clause 11. The aerodynamic structure (110) of clause 10, wherein the winglet (304, 314, 324) extends beyond a bottom surface (317) and a top surface (315) of the wing (110).

[0094] Clause 12. The aerodynamic structure (110) of clause 11, wherein the folded portion (302, 312, 322, 502, 512) is rotated to an angular displacement greater than 90 degrees relative to the fixed portion (401).

[0095] Clause 13. The aerodynamic structure (110) of clause 10 or clause 11, wherein the folded portion (302, 312, 322, 502, 512) further comprises the feather (504a, 504b, 514a, 514b).

[0096] Clause 14. The aerodynamic structure (110) of any one of clauses 10 to 13, wherein the winglet (304, 314, 324) comprises a height between approximately 0.2 and 0.9 of the half span of the folded portion (302, 312, 322, 502, 512).

[0097] Clause 15. An aerodynamic structure (110) according to any one of clauses 9 to 14, wherein the folded portion (302, 312, 322, 502, 512) includes the feathers (504a, 504b, 514a, 514b), and wherein the feathers (504a, 504b, 514a, 514b) have a joint position between approximately 0.2 and 0.7 of the half span of the folded portion (302, 312, 322, 502, 512).

[0098] Clause 16: A folding wingtip (302, 312, 322, 502, 512) that rotates relative to a fixed portion (401) of a wing (110), the folding wingtip (302, 312, 322, 502, 512) comprising:

[0099] an inclined portion extending along a lateral length of the folding wingtip (302, 312, 322, 502, 512);

[0100] at least one of a winglet (304, 314, 324) or a feather (504a, 504b, 514a, 514b); and

[0101] A hinge portion coupled to a hinge (308, 318, 328, 508, 518) for rotationally coupling the folding wing tip (302, 312, 322, 502, 512) to the fixed portion (401).

[0102] Clause 17. The folding wingtip (302, 312, 322, 502, 512) of clause 16, wherein the inclined portion overlaps at least one of the winglet (304, 314, 324) or the feather (504a, 504b, 514a, 514b).

[0103] Clause 18. A folding wingtip according to clause 16 or clause 17, wherein the folding wingtip (302, 312, 322, 502, 512) comprises the winglet (304, 314, 324) having a height between approximately 0.2 and 0.9 of the half span of the folding wingtip (302, 312, 322, 502, 512).

[0104] Clause 19. The folding wingtip (302, 312, 322, 502, 512) of any one of clauses 16 to 18, wherein the folding wingtip (302, 312, 322, 502, 512) has an aspect ratio of between approximately 1.4 and 2.5.

[0105] Clause 20. A folding wingtip (302, 312, 322, 502, 512) according to any one of clauses 16 to 19, wherein the folding wingtip (302, 312, 322, 502, 512) comprises the feathers (504a, 504b, 514a, 514b), and wherein the feathers (504a, 504b, 514a, 514b) have a joint position between approximately 0.2 and 0.7 of the half span of the folding wingtip (302, 312, 322, 502, 512).

[0106] Clause 21 A method comprising:

[0107] A folded portion (302, 312, 322, 502, 512) is coupled proximate a distal portion of a wing (110), wherein the folded portion (302, 312, 322, 502, 512) includes an inclined surface, and wherein at least one of:

[0108] The folded portion (302, 312, 322, 502, 512) includes a winglet (304, 314,

[0109] 324), or

[0110] The wing (110) or the folded portion (302, 312, 322, 502, 512)

[0111] At least one of includes a feather (504a, 504b, 514a, 514b).

[0112] Clause 22. The method of clause 21, further comprising confining at least one of the winglet (304, 314, 324) or the feather (504a, 504b, 514a, 514b) to the folded portion (302, 312, 322, 502, 512).

[0113] Clause 23 The method of clause 21 or clause 22, wherein coupling the folding portion (302, 312, 322, 502, 512) proximate the distal portion of the wing (110) comprises coupling the folding portion (302, 312, 322, 502, 512) to a hinge (308, 318, 328, 508, 518).

Claims

1. A wing for use with an aircraft, the wing comprising: Fixed part a folded portion proximate a distal end of the wing, the folded portion comprising: inclined surfaces; and Winglet; The wing further includes a hinge operably coupled between the fixed portion and the folding portion to enable the folding portion to be folded relative to the fixed portion; wherein the wing comprises a bottom surface and a top surface; and wherein the winglet extends through a bottom surface of the wing and a top surface of the wing; wherein the folding portion is rotated to an angular displacement greater than 90 degrees relative to the fixed portion so that the portion of the winglet extending beyond the bottom surface remains within span limits.

2. The wing of claim 1, wherein the folded portion further comprises feathers.

3. The wing of claim 1 , wherein the winglet comprises a height between 0.2 and 0.9 of the half span of the folded portion.

4. The wing of claim 1 , wherein the winglet comprises an aspect ratio between 1.0 and 6.

0.

5. The wing of claim 1 , wherein the folded portion has an aspect ratio between 1.4 and 2.

5.

6. An aerodynamic structure for an aircraft, the aerodynamic structure comprising: a fixing portion, the fixing portion comprising a first inclined portion; A folding portion, the folding portion comprising: a second inclined portion, and winglets; and The aerodynamic structure further includes a hinge operably coupling the fixed portion and the folding portion to enable the folding portion to rotate relative to the fixed portion between a folded position and a deployed position, wherein the aerodynamic structure comprises a bottom surface and a top surface, and wherein the winglet extends across a bottom surface of the aerodynamic structure and a top surface of the aerodynamic structure; wherein the folding portion is rotated to an angular displacement greater than 90 degrees relative to the fixed portion so that the portion of the winglet extending beyond the bottom surface remains within span limits.

7. The aerodynamic structure of claim 6, wherein the folded portion further comprises feathers.

8. The aerodynamic structure of claim 6, wherein the winglet comprises a height between 0.2 and 0.9 of the half span of the folded portion.

9. The aerodynamic structure of claim 7, wherein the feathers have a joint location between 0.2 and 0.7 of the half span of the folded portion.

10. A folding wingtip that rotates relative to a fixed portion of a wing, the folding wingtip comprising: an inclined portion extending along a lateral length of the folding wingtip; Winglet; as well as a hinge portion coupled to a hinge for rotationally coupling the folding wingtip to the fixed portion, the folding wingtip moving between a folded position and a deployed position at the hinge portion; wherein the wing comprises a bottom surface and a top surface, and wherein the winglet extends through a bottom surface of the wing and a top surface of the wing; wherein the folding wingtip is rotated to an angular displacement greater than 90 degrees relative to the fixed portion such that the portion of the winglet extending beyond the bottom surface remains within span limits. The folding wingtip according to claim 10 , wherein the inclined portion overlaps the winglet.

12. A folding wingtip according to claim 10 or claim 11, wherein the folding wingtip comprises the winglet, the winglet having a height of between 0.2 and 0.9 of the half span of the folding wingtip.

13. A folding wingtip according to claim 10 or claim 11, wherein the folding wingtip has an aspect ratio of between 1.4 and 2.

5.

14. The folding wingtip according to claim 10 or 11, wherein the folding wingtip comprises feathers, and wherein the feathers have a joint position between 0.2 and 0.7 of the half span of the folding wingtip.

15. A method for providing a wing with a folding portion, comprising: a folded portion coupled proximate a distal portion of the wing, wherein the folded portion includes an inclined surface, wherein the folded portion includes a winglet, wherein the wing comprises a bottom surface and a top surface, and wherein the folding portion moves between a folded position and a deployed position; the winglet extends across a bottom surface of the wing and a top surface of the wing; The folded portion is rotated to an angular displacement greater than 90 degrees relative to the wing so that the portion of the winglet extending beyond the bottom surface remains within span limits.

16. The method of claim 15, further comprising securing the winglet to the folded portion.

17. The method of claim 15 or claim 16, wherein coupling the folded portion proximate the distal portion of the wing comprises coupling the folded portion to a hinge.

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