Aerodynamic structure and method of forming an aerodynamic structure

Abstract

This document discloses an aerodynamic structure and a method for forming the aerodynamic structure. The aerodynamic structure includes: a first skin region including a first skin edge; and a second skin region including a second skin edge. The first and second skin regions are angled relative to each other and define a gap between the first and second skin edges. The aerodynamic structure also includes a trailing edge structure extending within the gap and between the first and second skin edges. The aerodynamic structure further includes a plurality of one-sided fasteners. A first subgroup of the plurality of one-sided fasteners operatively interconnects the first skin region and the trailing edge structure. A second subgroup of the plurality of one-sided fasteners operatively interconnects the second skin region and the trailing edge structure. The method includes a method for forming the aerodynamic structure.

Description

Technical Field

[0001] This disclosure generally relates to aerodynamic structures and methods for forming aerodynamic structures. Background Technology

[0002] Aerodynamic structures can be used in a variety of vehicles, such as aircraft, helicopters, spacecraft, and / or ships. In this context, aerodynamic structures can be used to reduce and / or adjust drag on fluids flowing through the vehicle. Many aerodynamic structures consist of two surfaces that converge or terminate in a trailing edge region. Economically manufacturing this trailing edge region and / or saving weight within it can often be challenging. Furthermore, creating an efficient, durable, robust, and easily accessible arrangement of structures within a limited dimensional space is challenging. Therefore, there is a need for improved aerodynamic structures and / or improved methods for forming aerodynamic structures. Summary of the Invention

[0003] This document discloses an aerodynamic structure and a method for forming the aerodynamic structure. The aerodynamic structure includes a first skin region including a first skin edge; and a second skin region including a second skin edge. The first skin region and the second skin region are angled relative to each other and define a gap between the first skin edge and the second skin edge. The aerodynamic structure also includes a trailing edge structure within the gap and extending between the first skin edge and the second skin edge. The aerodynamic structure further includes a plurality of one-sided fasteners. A first subgroup of the plurality of one-sided fasteners operatively interconnects the first skin region and the trailing edge structure. A second subgroup of the plurality of one-sided fasteners operatively interconnects the second skin region and the trailing edge structure.

[0004] The method includes positioning a trailing edge structure within a gap between a first skin edge of a first skin region and a second skin edge of a second skin region. The method also includes operatively attaching the first and second skin regions to the trailing edge structure using a plurality of one-sided fasteners. The operative attachment includes operatively attaching such that a first subgroup of the plurality of one-sided fasteners operatively interconnects the first skin region and the trailing edge structure, and further operatively interconnecting the second skin region and the trailing edge structure with a second subgroup of the plurality of one-sided fasteners. Attached Figure Description

[0005] Figure 1 This is a schematic diagram of a vehicle in the form of an aircraft that may include and / or utilize aerodynamic structures, according to this disclosure.

[0006] Figure 2This is a more detailed view of the aerodynamic surface according to this disclosure.

[0007] Figure 3 This is a schematic cross-sectional view of an aerodynamic surface according to the present disclosure.

[0008] Figure 4 yes Figure 3 A more detailed view of the aerodynamic surface area.

[0009] Figure 5 This is a schematic cross-sectional view of another aerodynamic surface according to the present disclosure.

[0010] Figure 6 It is along Figure 5 The line BB cut Figure 5 A cross-sectional view of the aerodynamic surface.

[0011] Figure 7 This is a schematic cross-sectional view of another aerodynamic surface according to the present disclosure.

[0012] Figure 8 This is a schematic cross-sectional view of another aerodynamic surface according to the present disclosure.

[0013] Figure 9 This is a schematic cross-sectional view of another aerodynamic surface according to the present disclosure. Detailed Implementation

[0014] Figures 1 to 9 Illustrative, non-exclusive examples of aerodynamic structures 30 and / or vehicles 10 including aerodynamic structures 30 are provided. Elements serving similar or at least substantially similar purposes are also included. Figures 1 to 9 Each of the accompanying figures is labeled with the same numbers, and references are made to... Figures 1 to 9 These components will not be discussed in detail here. Similarly, those not mentioned... Figures 1 to 9 All elements are labeled in each of the accompanying drawings, but reference numerals may be used herein for consistency. Without departing from the scope of this disclosure, references are made to... Figures 1 to 9 The elements, components, and / or features discussed in one or more of the accompanying drawings may include, and / or be related to, the elements, components, and / or features discussed in the drawings. Figures 1 to 9 Any one of them can be used together.

[0015] Generally, elements that may be included in a given (i.e., a particular) embodiment are illustrated with solid lines, while elements that are optional for a given embodiment are illustrated with dashed lines. However, elements shown in solid lines are not essential to all embodiments, and elements shown in solid lines may be omitted from a particular embodiment without departing from the scope of this disclosure.

[0016] Figure 1 This is a schematic diagram of a vehicle 10 in the form of an aircraft 12 that may include and / or utilize aerodynamic structures 30 according to the present disclosure. As shown, the aircraft 12 may include multiple components, including a wing 14, a fuselage 16, and / or a tail 18. One or more of these components may include aerodynamic surfaces 19, such as control surfaces 20 and / or fixed surfaces 26. Examples of control surfaces 20 include a rudder 21, an elevator 22, an aileron 23, flaps 24, and / or a spoiler 25. Examples of fixed surfaces 26 include winglets 27 of the wing 14 and / or fixed regions 28. Control surfaces 20 and / or fixed surfaces 26 may include and / or may define a trailing edge 138, and aerodynamic structures 30 may form and / or define at least a portion and / or at least a region of the trailing edge 138. Although Figure 1 Vehicle 10 in the form of aircraft 12 is shown, but aerodynamic structure 30 may be included and / or formed as part of any suitable vehicle 10 and is also within the scope of this disclosure. Additional examples of vehicle 10 include helicopters, spacecraft and / or ships.

[0017] Figure 2 This is a more detailed view of the aerodynamic surface 19 in the form of a rudder 21 according to this disclosure. Figure 3 This is a schematic cross-sectional view of the aerodynamic surface 19 according to the present disclosure, and Figure 4 yes Figure 3 A more detailed view of the aerodynamic surface 19 region. Figure 5 This is a schematic cross-sectional view of another aerodynamic surface 19 according to this disclosure, and Figure 6 It is along Figure 5 The line BB cut Figure 5 A cross-sectional view of the aerodynamic surface 19. Figure 7 This is a schematic cross-sectional view of another aerodynamic surface 19 according to this disclosure; Figure 8 This is a schematic cross-sectional view of another aerodynamic surface 19 according to the present disclosure; and Figure 9 This is a schematic cross-sectional view of another aerodynamic surface 19 according to this disclosure. While not strictly necessary, however... Figures 3 to 5 and Figures 7 to 9 This may include and / or along Figure 2 The line AA is intercepted Figure 2 A cross-sectional view of the aerodynamic surface 19.

[0018] like Figures 2 to 9As jointly illustrated, according to this disclosure, the aerodynamic surface 19 includes an aerodynamic structure 30. The aerodynamic structure 30 includes a first skin region 40 and a second skin region 60, the first skin region including and / or defining a first skin edge 42, and the second skin region including and / or defining a second skin edge 62. Figures 3 to 9 As shown, the first skin region 40 and the second skin region 60 may be angled relative to each other to define a gap 80 between the first skin edge 42 and the second skin edge 62. In some examples, and also as illustrated, the first skin region 40 and the second skin region 60 may be angled relative to each other and / or may be oriented at an angle relative to each other. In other words, and in some such examples, the first skin region 40 and the second skin region 60 may not be parallel to each other and / or may taper towards each other. This taper can cause the distance between the first skin region 40 and the second skin region 60 to decrease towards the first skin edge 42, towards the second skin edge 62, and / or towards the gap 80.

[0019] For example Figures 2 to 9 As shown herein, the aerodynamic structure 30 includes a trailing edge structure 100. The trailing edge structure 100 extends and / or is positioned within a gap 80. Alternatively or additionally, the trailing edge structure 100 extends and / or is positioned therein between the first skin region 40 and the second skin region 60 and / or between the first skin edge 42 and the second skin edge 62. The trailing edge structure 100 may define, or may be referred to herein as defining, the trailing edge 138 of the aerodynamic surface 19 and / or the aerodynamic structure 30.

[0020] like Figures 2 to 9 Further demonstrated, the aerodynamic structure 30 includes a plurality of one-sided fasteners 150. A first subgroup 152 of the one-sided fasteners 150 is operatively interconnected or attached to a first skin region 40 and a trailing edge structure 100. A second subgroup 154 ​​of the one-sided fasteners 150 is operatively interconnected or attached to a second skin region 60 and a trailing edge structure 100.

[0021] The first skin region 40 may include and / or one and / or more of any suitable structures. As an example, the first skin region 40 may include and / or a first composite skin, a first fiber-reinforced composite skin, a first multilayer composite material layer, and / or a first cured or pre-cured composite skin. Similarly, the second skin region 60 may include and / or a second composite skin, a second fiber-reinforced composite skin, a second multilayer composite material layer, and / or a second cured or pre-cured composite skin.

[0022] The first skin region 40 may have and / or define a first skin inner surface 44 and / or a first skin outer surface 46. The first skin inner surface 44 may face the second skin region 60, may face the trailing edge structure 100, may contact the trailing edge structure 100, and / or may have direct physical contact with the trailing edge structure 100. The first skin outer surface 46 may be away from the second skin region 60 and / or may be away from the trailing edge structure 100. In other words, the first skin region 40 may define a first interface 50 with the trailing edge structure 100. In some examples, the first skin outer surface 46 may include and / or be a smooth first aerodynamic skin outer surface, for example, it may define at least one region of the aerodynamic surface 19.

[0023] Similarly, the second skin region 60 may have and / or define a second skin inner surface 64 and / or a second skin outer surface 66. The second skin inner surface 64 may face the first skin region 40, may face the trailing edge structure 100, may contact the trailing edge structure 100, and / or may be in direct physical contact with the trailing edge structure 100. The second skin outer surface 66 may be opposite to the first skin region 40 and / or may be opposite to the trailing edge structure 100. In other words, the second skin region 60 may define a second interface 70 together with the trailing edge structure 100. In some examples, the second skin outer surface 66 may include and / or be a smooth second aerodynamic skin outer surface, for example, defining at least one region of the aerodynamic surface 19.

[0024] The trailing edge structure 100 may include and / or may be positioned within the gap 80, operably attachable to the first skin region 40 and / or the second skin region 60 via a one-sided fastener 150, and / or may define the trailing edge 138. In some examples, the trailing edge structure 100 may include, is, is composed of, and / or substantially comprises the following structures: a monolithic trailing edge structure, an integral trailing edge structure, a one-piece trailing edge structure, a continuously formed trailing edge structure, and / or an integrally formed trailing edge structure. Figure 5 and Figure 7 The configuration shown can reduce the overall weight of the aerodynamic structure 30, increase its strength, and / or facilitate improved, faster, and / or more efficient assembly of the aerodynamic structure 30. However, this is not necessary, and as... Figures 8 to 9 As shown, the trailing edge structure 100 may include and / or a multi-part trailing edge structure or a multi-piece trailing edge structure, which is also within the scope of this disclosure.

[0025] Similar to the first skin region 40 and / or the second skin region 60, the trailing edge structure 100 may include and / or a composite trailing edge structure, a fiber-reinforced composite trailing edge structure, and / or a cured or pre-cured composite trailing edge structure. In some such examples, the trailing edge structure 100 may be formed of a trailing edge multilayer composite material. Examples of trailing edge multilayer composite materials include at least 2 layers, at least 3 layers, at least 4 layers, at least 5 layers, at least 6 layers, at least 7 layers, up to 20 layers, up to 18 layers, up to 16 layers, up to 14 layers, up to 12 layers, up to 10 layers, up to 9 layers, up to 8 layers, up to 7 layers, up to 6 layers, up to 5 layers, and / or up to 4 composite material layers.

[0026] In some examples, such as Figures 4 to 5 and Figures 7 to 9 As shown, the trailing edge structure 100 may have and / or define an outer trailing edge structure surface 102. The outer trailing edge structure surface 102 may contact or be in direct physical contact with the first skin region 40 and / or the second skin region 60. Similar to the first skin outer surface 46 and / or the second skin outer surface 66, the outer trailing edge structure surface 102 may be a smooth aerodynamic outer trailing edge structure surface, for example, it may define at least one region of the aerodynamic surface 19.

[0027] like Figures 4 to 5 and Figures 7 to 9 As shown, the trailing edge structure 100 may have, include, and / or define a front region 110, a rear region 130, and a transition region 140. The front region 110 may be positioned within, or at least partially positioned within, the gap 80. The rear region 130 may define a trailing edge 138. The transition region 140 may extend from the front region 110 to the rear region 130 and / or may extend between the front region 110 and the rear region 130.

[0028] like Figures 4 to 9 As shown, the front region 110 may have and / or define a first front region surface 112 and a second front region surface 116. The first front region surface 112 may face the first skin region 40, may contact the first skin region 40, and / or may have direct physical contact with the first skin region 40. Similarly, the second front region surface 116 may face the second skin region 60, may contact the second skin region 60, and / or may have direct physical contact with the second skin region 60.

[0029] The first skin region 40 may have and / or define a plurality of first skin holes 48, and the second skin region 60 may have and / or define a plurality of second skin holes 68. Similarly, the first front region surface 112 may have and / or define a plurality of first structural holes 114, and the second front region surface 116 may have and / or define a plurality of second structural holes 118. Each single-sided fastener of the first subgroup 152 of the plurality of single-sided fasteners 150 may extend through the first skin holes corresponding to the plurality of first skin holes 48 and may also extend through the first structural holes corresponding to the plurality of first structural holes 114. Similarly, each single-sided fastener of the second subgroup 154 ​​of the plurality of single-sided fasteners 150 may extend through the second skin holes corresponding to the plurality of second skin holes 68 and may also extend through the second structural holes corresponding to the plurality of second structural holes 118.

[0030] In some examples, the front region 110 may have, define, delineate, and / or at least partially define a front region void space 120. When the front region void space 120 is present, it may extend at least partially between the first front region surface 112 and the second front region surface 116. Furthermore, each of the plurality of one-sided fasteners 150 may include and / or define a corresponding exposed end 156 and a corresponding unexposed end 158. The corresponding exposed end 156 may form and / or define at least one region of the outer surface of the aerodynamic structure 30. Conversely, the corresponding unexposed end 158 may be inside the aerodynamic structure 30, possibly inaccessible from the outside of the aerodynamic structure 30, and / or may be positioned within the front region void space 120. In other words, the single-sided fastener 150 may not extend through or not fully extend through the aerodynamic structure 30, the single-sided fastener 150 may extend only through one of the first skin region 40 and the second skin region 60, and / or each single-sided fastener 150 may extend through a single, or only a single, corresponding hole within the front region 110.

[0031] In some examples, and such as Figure 4 dotted lines and Figure 5 and Figures 7 to 9 As shown by the solid lines, the front region 110 may include and / or define a front spar 122. When present, the front spar 122 may extend at least partially, or even entirely, between the first skin region 40 and the second skin region 60, for example, to support normal forces oriented between the first skin region 40 and the second skin region 60. Additionally or alternatively, the front spar 122 may extend along, at least partially, or entirely along, the longitudinal length of the trailing edge structure 100, such as... Figure 2 As shown in 104. In some examples, the front spar 122 may include and / or a front C-shaped spar. In some such examples, and as... Figure 5As shown, the front C-shaped spar can be recessed towards the rear region 130 and / or open towards the rear region 130. In some examples, and as... Figures 7 to 9 As shown, the front C-shaped spar can face the rear 130° protrusion and / or can be open away from the rear region. (As shown) Figure 4 and Figures 7 to 9 In the example shown, where the front region 110 includes a front spar 122, the front region 110 may include an inspection opening 124. When present, the inspection opening 124 allows and / or facilitates observation of the area of ​​the one-sided fastener 150 positioned within the front region clearance space 120. This configuration allows for visual determination and / or verification of the actuation state of the one-sided fastener 150.

[0032] The rear region 130 can have and / or define any suitable shape. As an example, and as... Figures 3 to 4 As shown, the rear region 130 may have and / or be defined by a duckbill-shaped cross-sectional shape, or at least partially a triangular cross-sectional shape. As another example, and as... Figure 5 and Figures 7 to 9 As shown, the rear region 130 may have and / or be defined by a wedge-shaped cross-section.

[0033] In some examples, the rear region 130 may be without a joint, for example, within the material defining the rear region 130. Additionally or alternatively, the rear region 130 may be without a joint at and / or within the trailing edge 138. As an example, and as... Figure 4 As shown, the rear region 130 may be defined by a plurality of rear region layers of composite material 132. In this configuration, at least one of the plurality of rear region layers of composite material 132 may surround a trailing edge 138, may extend around the trailing edge, and / or may not terminate within the trailing edge. This configuration may increase the structural stiffness of the rear region 130 and / or may reduce the likelihood of the trailing edge structure 100 separating at and / or along the trailing edge 138.

[0034] In some examples, the rear region 130 may have and / or define a first rear region outer surface 134 and a second rear region outer surface 136. In some such examples, the first rear region outer surface 134 and the second rear region outer surface 136 may be angled relative to each other, may be oriented at an angle relative to each other, may not be parallel to each other, may taper toward a trailing edge 138, and / or may converge at the trailing edge 138.

[0035] The transition region 140 may have and / or define any suitable structure and / or shape. In some examples, the transition region 140 may taper from the front region 110 to the rear region 130 and / or may taper monotonically from the front region 110 to the rear region 130. In some examples, the transition region 140 may define a first exposed transition region surface 142 and a second exposed transition region surface 144. In some such examples, the first exposed transition region surface 142 and the second exposed transition region surface 144 may be angled relative to each other, may be oriented at an angle relative to each other, may not be parallel to each other, may taper towards the rear region 130, and / or may taper monotonically towards the rear region 130.

[0036] In some examples, and such as Figure 4 As shown, the transition region 140 may include a transition region spar 146. The transition region spar 146, when present, may increase the stiffness of the trailing edge structure 100 and / or may increase the stiffness of its transition region 140. Additionally or alternatively, the transition region spar 146 may increase resistance to deflection of the first exposed transition region surface 142 and / or the second exposed transition region surface 144, which may be caused, for example, by loads, normal loads, and / or aerodynamic loads applied to the trailing edge structure 100 during operational use.

[0037] The single-sided fastener 150 may include and / or any suitable fastener that can be used to operatively interconnect the first skin region 40 and / or the second skin region 60 with the trailing edge structure 100 and may also be actuated only from the exposed end 156. In other words, and as used herein, the phrase "single-sided fastener" or "multiple single-sided fasteners" refers to a fastener that can be used to operatively attach two or more components together by means of operative engagement only with one side or end (e.g., exposed end 156) of the single-sided fastener and / or not with the opposite side or end (e.g., unexposed end 158) of the single-sided fastener.

[0038] Considering the above, each single-sided fastener 150 can be configured to operatively attach a corresponding skin region of the first skin region 40 or the second skin region 60 to the trailing edge structure 100. In other words, each single-sided fastener 150 does not operatively attach the corresponding skin regions of both the first skin region 40 and the second skin region 60 to the trailing edge structure 100. Examples of single-sided fasteners 150 include countersunk rivets, baffle rivets, poppet hollow rivets, self-retaining fasteners, and / or self-tapping fasteners.

[0039] As discussed, the one-sided fastener 150 can be configured to be actuated only from one side, or from an end (e.g., exposed end 156). This actuation can keep the one-sided fastener 150 in an unacted state 160 (e.g., ...). Figure 5 and Figures 7 to 9 center solid line and Figure 6 The best way to show the transition from the dashed line to the actuation state is 162 (e.g., the middle dashed line). Figure 6 (The solid line is best shown). In the example of single-sided fasteners 150, including countersunk rivets, baffle rivets, and / or hollow rivets, and as... Figure 6 The single-sided fastener 150 shown may include a fastener body 164 and a shank 166. During the operative attachment of the first skin region 40 or the second skin region 60 to the trailing edge structure 100 using this single-sided fastener 150, the single-sided fastener 150 is initially inserted into the corresponding hole in the trailing edge structure 100 and into the first skin region 40 or the second skin region 60, in an unactuated state 160. Subsequently, the shank 166 can be pulled away from or withdrawn from the exposed end 156, thus pulling the unexposed end 158 toward the exposed end 156 to transition the single-sided fastener 150 to an actuated state 162. This actuation compresses the trailing edge structure 100 and the first skin region 40 or the second skin region 60 between the exposed end 156 and the unexposed end 158, thereby completing the operative attachment.

[0040] Considering the above, the single-sided fastener 150 is not, or may be referred to herein as, a double-sided rivet and / or a compression rivet. In other words, the single-sided fastener 150 does not need to be brought close to its two opposite ends to be actuated from the unacted state 160 to the actuated state 162, and / or the single-sided fastener is not compressed between the two surfaces of the corresponding tool during such actuation.

[0041] In some examples of the aerodynamic structure 30, a single one-sided fastener 150 may be sufficient to operatively attach the first skin region 40 and / or the second skin region 60 to the trailing edge structure 100. In some such examples, the aerodynamic structure 30 may be, or may be, referred herein to as having no adhesive between the first skin region 40 and the trailing edge structure 100, which adhesive directly or indirectly adheres the first skin region 40 to the trailing edge structure 100; and no adhesive between the second skin region 60 and the trailing edge structure 100, which adhesive directly or indirectly adheres the second skin region 60 to the trailing edge structure 100.

[0042] In some examples of the aerodynamic structure 30, and as discussed, the first skin region 40, the second skin region 60, and / or the trailing edge structure 100 may be formed of composite materials. In some such examples, the first skin region 40, the second skin region 60, and / or the trailing edge structure 100 may be cured, pre-cured, and / or fully cured prior to the assembly of the aerodynamic structure 30. In other words, the aerodynamic structure 30 may not require a composite curing adhesive between the first skin region 40 and the trailing edge structure 100 and / or between the second skin region 60 and the trailing edge structure.

[0043] As discussed, the aerodynamic structure 30 can form and / or define the vehicle 10 (e.g., Figure 1 At least one region of the aerodynamic surface 19 of the aircraft 12). The aerodynamic structure 30 may have and / or define any suitable size, for example, suitable for a given vehicle 10. In some examples, the aerodynamic structure 30 and / or its trailing edge structure 100 may define a longitudinal length, or maximum range, of at least 0.25 meters (m), at least 0.5m, at least 1m, at least 2m, at least 3m, at least 4m, at least 5m, at least 10m, up to 50m, up to 40m, up to 30m, up to 20m, up to 10m, and / or up to 5m. Examples of longitudinal lengths are as follows: Figure 2 As shown and indicated by 104. In some examples, the aerodynamic structure 30 and / or its trailing edge structure 100 may be defined with an aspect ratio of at least 10, at least 25, at least 50, at least 100, at least 200, at least 300, at least 400, at least 500, up to 1000, up to 900, up to 800, up to 700, up to 600, up to 500, up to 400, up to 300, up to 200, and / or up to 100. The aspect ratio may be defined as... Figure 2 The longitudinal length 104 and Figures 3 to 9 The ratio of the length of the gap to 80.

[0044] Methods of constructing and / or assembling aerodynamic structures 30 and / or aerodynamic surfaces 19 and / or a vehicle 10 including aerodynamic structures 30 may include positioning a trailing edge structure 100 and / or a gap 80 between a first skin edge 42 and a second skin edge 62. The method may then include operatively attaching the first skin region 40 and the second skin region 60 to the trailing edge structure 100 using a one-sided fastener 150. After this operative attachment, a first subgroup 152 of the one-sided fastener 150 may operatively interconnect the first skin region 40 with the trailing edge structure 100, while a second subgroup 154 ​​of the one-sided fastener 150 may operatively interconnect the second skin region 60 with the trailing edge structure 100.

[0045] In some examples, the aerodynamic structure 30 may define an exposed outer surface that defines an enclosed volume, which may include a front region void space 120. In some such examples, operably attaching may include operably attaching such that the unexposed end 158 of each one-sided fastener 150 is positioned within the enclosed volume. In some examples, and as discussed, operably attaching may include actuating each one-sided fastener 150 from or only from its exposed end 156.

[0046] In some examples, operably attaching may include operably attaching such that a first interface 50 between the first skin region 40 and the trailing edge structure 100 has no corresponding adhesive between the first skin region 40 and the trailing edge structure 100. Additionally or alternatively, operably attaching may include operably attaching such that a second interface 70 between the second skin region 60 and the trailing edge structure 100 has no corresponding adhesive between the second skin region 60 and the trailing edge structure 100.

[0047] In some examples, the method may further include providing, forming, and / or defining a first skin region 40, a second skin region 60, and / or a trailing edge structure 100. In some such examples, this may include providing, forming, and / or defining a pre-cured first skin region, a pre-cured second skin region, and / or a pre-cured trailing edge structure.

[0048] In some examples, operably attaching may include positioning each of a first single-sided fastener of a first subgroup 152 of a plurality of single-sided fasteners 150 within a corresponding first hole extending through both the first skin region 40 and the trailing edge structure 100, and subsequently actuating each first single-sided fastener from a corresponding first exposed end 156 to operably attach the first skin region 40 to the trailing edge structure 100. Similarly, operably attaching may also include positioning each of a second single-sided fastener of a second subgroup 154 ​​of a plurality of single-sided fasteners 150 within a corresponding second hole extending through both the second skin region 60 and the trailing edge structure 100, and subsequently actuating each second single-sided fastener from a corresponding second exposed end 156 to operably attach the second skin region 60 to the trailing edge structure 100.

[0049] The following paragraphs describe illustrative, non-exclusive examples of the inventive subject matter according to this disclosure:

[0050] A1. An aerodynamic structure (30), comprising:

[0051] A first skin region (40) includes a first skin edge (42);

[0052] A second skin region (60) includes a second skin edge (62), wherein the first skin region (40) and the second skin region (60) are angled relative to each other and define a gap (80) between the first skin edge (42) and the second skin edge (62);

[0053] A trailing edge structure (100) extending within the gap (80) and between the first skin edge (42) and the second skin edge (62); and

[0054] Multiple single-sided fasteners (150), of which:

[0055] (i) A first subgroup (152) of the plurality of single-sided fasteners (150) operatively interconnects the first skin region (40) with the trailing edge structure (100); and

[0056] (ii) The second subgroup (154) of the plurality of single-sided fasteners (150) is operatively interconnected with the second skin region (60) and the trailing edge structure (100).

[0057] A2. The aerodynamic structure (30) as described in paragraph A1, wherein the first skin region (40) includes or includes at least one of the following:

[0058] (i) First composite skin;

[0059] (ii) First fiber reinforced composite skin;

[0060] (iii) the first multilayer composite material layer; and

[0061] (iv) First-cured or pre-cured composite skin.

[0062] A3. The aerodynamic structure (30) as described in any one of paragraphs A1-A2, wherein the first skin region (40) defines a first skin inner surface (44), optionally wherein the first skin inner surface (44) is at least one of the following:

[0063] (i) Facing the second skin region (60);

[0064] (ii) Facing the trailing edge structure (100);

[0065] (iii) in contact with the trailing edge structure (100); and

[0066] (iv) in direct physical contact with the trailing edge structure (100).

[0067] A4. The aerodynamic structure (30) as described in any one of paragraphs A1-A3, wherein the first skin region (40) defines a first skin outer surface (46), optionally wherein the first skin outer surface (46) is at least one of the following:

[0068] (i) deviating from the second skin region (60);

[0069] (ii) deviating from the trailing edge structure (100); and

[0070] (iii) is the smooth aerodynamic outer surface of the first skin.

[0071] A5. The aerodynamic structure (30) as described in any one of paragraphs A1-A4, wherein the second skin region (60) comprises or includes at least one of the following:

[0072] (i) Second composite skin;

[0073] (ii) Second fiber reinforced composite skin;

[0074] (iii) a second multilayer composite material layer; and

[0075] (iv) Second-cured or pre-cured composite skin.

[0076] A6. The aerodynamic structure (30) as described in any one of paragraphs A1-A5, wherein the second skin region (60) defines a second skin inner surface (64), optionally wherein the second skin inner surface (64) is at least one of the following:

[0077] (i) Facing the first skin region (40);

[0078] (ii) Facing the trailing edge structure (100);

[0079] (iii) in contact with the trailing edge structure (100); and

[0080] (iv) in direct physical contact with the trailing edge structure (100).

[0081] A7. The aerodynamic structure (30) as described in any one of paragraphs A1-A6, wherein the second skin region (60) defines a second skin outer surface (66), optionally wherein the second skin outer surface (66) is at least one of the following:

[0082] (i) deviating from the first skin region (40);

[0083] (ii) deviating from the trailing edge structure (100); and

[0084] (iii) is a smooth aerodynamic second skin outer surface.

[0085] A8. The aerodynamic structure (30) as described in any one of paragraphs A1-A7, wherein the trailing edge structure (100) comprises at least one of the following, is at least one of the following, consists of at least one of the following, or is substantially composed of at least one of the following:

[0086] (i) Monolithic trailing edge structure;

[0087] (ii) Integral trailing edge structure;

[0088] (iii) One-piece rear edge structure;

[0089] (iv) continuously formed trailing edge structures; and

[0090] (v) The trailing edge structure formed as a single unit.

[0091] A9. The aerodynamic structure (30) as described in any one of paragraphs A1-A8, wherein the trailing edge structure (100) is a multi-component trailing edge structure.

[0092] A10. The aerodynamic structure (30) as described in any one of paragraphs A1-A9, wherein the trailing edge structure (100) comprises, is, or is only at least one of the following:

[0093] (i) Composite trailing edge structure;

[0094] (ii) Fiber-reinforced composite trailing edge structure;

[0095] (iii) trailing edge multilayer composite material layer; and

[0096] (iv) Cured or pre-cured composite trailing edge structure.

[0097] A11. The aerodynamic structure (30) as described in paragraph A10, wherein the trailing edge multilayer composite material layer comprises at least one of the following:

[0098] (i) at least two, at least three, at least four, at least five, at least six, or at least seven composite material layers; and

[0099] (ii) Up to 20 layers, up to 18 layers, up to 16 layers, up to 14 layers, up to 12 layers, up to 10 layers, up to 9 layers, up to 8 layers, up to 7 layers, up to 6 layers, up to 5 layers, or up to 4 composite material layers.

[0100] A12. The aerodynamic structure (30) as described in any one of paragraphs A1-A11, wherein the trailing edge structure (100) defines an outer trailing edge structure surface (102), and further comprising at least one of the following:

[0101] (i) The outer trailing edge structure surface (102) contacts the first skin region (40);

[0102] (ii) The outer trailing edge structure surface (102) is in direct physical contact with the first skin region (40);

[0103] (iii) The outer trailing edge structure surface (102) contacts the second skin region (60);

[0104] (iv) The outer trailing edge structural surface (102) is in direct physical contact with the second skin region (60); and

[0105] (v) The outer trailing edge structure surface (102) is a smooth aerodynamic outer trailing edge structure surface.

[0106] A13. The aerodynamic structure (30) as described in any one of paragraphs A1-A12, wherein the trailing edge structure (100) comprises:

[0107] (i) a front region (110) that is at least partially located within the gap (80);

[0108] (ii) a rear region (130) defining the rear edge (138) of the rear edge structure (100); and

[0109] (iii) A transition region (140) that extends from the front region (110) to the rear region (130).

[0110] A14. The aerodynamic structure (30) as described in paragraph A13, wherein the front region (110) defines a first front region surface (112) and a second front region surface (116), and further, at least one of the following:

[0111] (i) The first front region surface (112) faces the first skin region (40);

[0112] (ii) The surface (112) of the first front region is in contact with the first skin region (40);

[0113] (iii) The surface (112) of the first front region is in direct physical contact with the first skin region (40);

[0114] (iv) The second front region surface (116) faces the second skin region (60);

[0115] (v) The surface (116) of the second front region contacts the second skin region (60); and

[0116] (vi) The surface (116) of the second front region is in direct physical contact with the second skin region (60).

[0117] A15. The aerodynamic structure (30) as described in paragraph A14, wherein the first skin region (40) defines a plurality of first skin holes (48), wherein the first front region surface (112) defines a plurality of first structural holes (114), and further wherein each of the first subgroups (152) of the plurality of one-sided fasteners (150) extends through a corresponding first skin hole in the plurality of first skin holes (48) and also through a corresponding first structural hole in the plurality of first structural holes (114).

[0118] A16. An aerodynamic structure (30) as described in any one of paragraphs A14-A15, wherein the second skin region (60) defines a plurality of second skin holes (68), wherein the second front region surface (116) defines a plurality of second structural holes (118), and further wherein each of the second subgroups (154) of the plurality of one-sided fasteners (150) extends through a corresponding second skin hole in the plurality of second skin holes (68) and also through a corresponding second structural hole in the plurality of second structural holes (118).

[0119] A17. An aerodynamic structure (30) as described in any one of paragraphs A13-A16, wherein the front region (110) at least partially defines a front region void space (120) extending between a first front region surface (112) and a second front region surface (116), wherein each of the plurality of single-sided fasteners (150) includes a corresponding exposed end (156) and a corresponding unexposed end (158), and further wherein the corresponding unexposed end (158) is positioned within the front region void space (120).

[0120] A18. An aerodynamic structure (30) as described in any one of paragraphs A13-A17, wherein a given single-sided fastener or each single-sided fastener among a plurality of single-sided fasteners (150) extends through a corresponding hole in the front region (110) of a single, or only single, trailing edge structure (100).

[0121] A19. The aerodynamic structure (30) as described in any one of paragraphs A13-A18, wherein the front region (110) includes a front spar (122), the front spar being at least one of the following:

[0122] (i) extending at least partially or completely between the first skin region (40) and the second skin region (60); and

[0123] (ii) along the longitudinal length (104) of the trailing edge structure (100), or along the entire longitudinal length.

[0124] A20. The aerodynamic structure (30) as described in paragraph A19, wherein the front spar (122) comprises a front C-shaped spar.

[0125] A21. The aerodynamic structure (30) as described in paragraph A20, wherein the front C-shaped spar is at least one of the following:

[0126] (i) protrudes toward the rear region (130); and

[0127] (ii) Recessed toward the rear region (130).

[0128] A22. The aerodynamic structure (30) as described in any one of paragraphs A13-A21, wherein the rear region (130) defines at least one of the following:

[0129] (i) the duckbill-shaped cross-sectional shape; and

[0130] (ii) Wedge-shaped cross-section shape.

[0131] A23. The aerodynamic structure (30) as described in any one of paragraphs A13-A22, wherein the rear region (130) is at least one of the following:

[0132] (i) lacks a connector; and

[0133] (ii) There is no joint at the trailing edge (138).

[0134] A24. An aerodynamic structure (30) as described in any one of paragraphs A13-A23, wherein the rear region (130) is defined by one or more rear region layers of composite material (132), and further wherein at least one of the plurality of rear region layers surrounds the rear edge (138) of the rear edge structure (100).

[0135] A25. The aerodynamic structure (30) as described in any one of paragraphs A13-A24, wherein the rear region (130) defines a first rear region outer surface (134) and a second rear region outer surface (136), optionally wherein the first rear region outer surface (134) and the second rear region outer surface (136) are at least one of the following:

[0136] (i) tapering toward the trailing edge (138); and

[0137] (ii) They meet at the trailing edge (138).

[0138] A26. The aerodynamic structure (30) as described in any one of paragraphs A13-A25, wherein the rear region (130) is at least one of the following:

[0139] (i) Gradually narrowing from the front region (110) to the rear region (130); and

[0140] (ii) It monotonically shrinks from the front region (110) to the rear region (130).

[0141] A27. The aerodynamic structure (30) as described in any one of paragraphs A13-A26, wherein the transition region (140) defines a first exposed transition region surface (142) and a second exposed transition region surface (144), and further wherein the first exposed transition region surface (142) and the second exposed transition region surface (144) are at least one of the following:

[0142] (i) Gradually narrowing from the front region (110) to the rear region (130); and

[0143] (ii) It monotonically shrinks from the front region (110) to the rear region (130).

[0144] A28. The aerodynamic structure (30) as described in any one of paragraphs A13-A27, wherein the transition region (140) includes a transition region spars (146) located within the transition region (140).

[0145] A29. An aerodynamic structure (30) as described in any one of paragraphs A1-A28, wherein each of the plurality of single-sided fasteners (150) is configured to operatively attach a corresponding skin region of one or only of the first skin region (40) and the second skin region (60) to the trailing edge structure (100).

[0146] A30. The aerodynamic structure (30) as described in any one of paragraphs A1-A29, wherein the plurality of single-sided fasteners (150) comprises at least one of the following:

[0147] (i) Countersunk rivet;

[0148] (ii) Rivets;

[0149] (iii) Poppy hollow rivets;

[0150] (iv) Self-holding fasteners; and

[0151] (v) Self-tapping fasteners.

[0152] A31. The aerodynamic structure (30) as described in any one of paragraphs A1-A30, wherein the plurality of single-sided fasteners (150) are at least one of the following:

[0153] (i) It is not a double-sided rivet; and

[0154] (ii) Not a squeeze rivet.

[0155] A32. The aerodynamic structure (30) as described in any one of paragraphs A1-A31, wherein the aerodynamic structure (30) is at least one of the following:

[0156] (i) There is no adhesive between the first skin region (40) and the trailing edge structure (100);

[0157] (ii) It does not have an adhesive that can directly adhere the first skin region (40) to the trailing edge structure (100);

[0158] (iii) It does not have an adhesive that indirectly adheres the first skin region (40) to the trailing edge structure (100);

[0159] (iv) There is no adhesive between the second skin region (60) and the trailing edge structure (100);

[0160] (v) It does not have an adhesive that allows the second skin region (60) to be directly adhered to the trailing edge structure (100); and

[0161] (vi) It does not have an adhesive that indirectly adheres the second skin region (60) to the trailing edge structure (100).

[0162] A33. The aerodynamic structure (30) as described in any one of paragraphs A1-A32, wherein the aerodynamic structure (30) is at least one of the following:

[0163] (i) There is no composite curing adhesive between the first skin region (40) and the trailing edge structure (100); and

[0164] (ii) There is no composite curing adhesive between the second skin region (60) and the trailing edge structure (100).

[0165] A34. The aerodynamic structure (30) as described in any one of paragraphs A1-A33, wherein the longitudinal length (104) of the trailing edge structure (100) is at least one of the following:

[0166] (i) at least 0.25 meters (m), at least 0.5 meters, at least 1 meter, at least 2 meters, at least 3 meters, at least 4 meters, at least 5 meters, or at least 10 meters; and

[0167] (ii) Maximum 50m, maximum 40m, maximum 30m, maximum 20m, maximum 10m, or maximum 5m.

[0168] A35. The aerodynamic structure (30) as described in any one of paragraphs A1-A34, wherein the aspect ratio of the trailing edge structure (100) is at least one of the following:

[0169] (i) at least 10, at least 25, at least 50, at least 100, at least 200, at least 300, at least 400, or at least 500; and

[0170] (ii) Maximum 1000, maximum 900, maximum 800, maximum 700, maximum 600, maximum 500, maximum 400, maximum 300, maximum 200, or maximum 100.

[0171] A36. An aerodynamic surface (19) at least partially defined by an aerodynamic structure (30) as described in any one of paragraphs A1-A35.

[0172] A37. An aerodynamic surface (19) as described in paragraph A36, wherein the aerodynamic surface (19) includes a control surface (20), optionally wherein the control surface (20) includes at least one of the following:

[0173] (i) Rudder (21);

[0174] (ii) Elevator (22);

[0175] (iii) Aileron (23);

[0176] (iv) flaps (24); and

[0177] (v) spoiler (25).

[0178] A38. An aerodynamic surface (19) as described in paragraph A36, wherein the aerodynamic surface (19) includes a fixed surface (26), optionally wherein the fixed surface (26) includes at least one of the following:

[0179] (i) winglets (27); and

[0180] (ii) Fixed area (28) of wing (14).

[0181] A39. A means of transport (10) comprising an aerodynamic structure (30) as described in any one of paragraphs A1-A36 or an aerodynamic surface (19) as described in any one of paragraphs A37-A38, optionally wherein the means of transport (10) comprises at least one of the following:

[0182] (i) Aircraft;

[0183] (ii) Helicopter;

[0184] (iii) Spacecraft; and

[0185] (iv) Ships.

[0186] B1. A method for forming an aerodynamic structure (30), the method comprising:

[0187] The trailing edge structure (100) is positioned within the gap (80) between the first skin edge (42) of the first skin region (40) and the second skin edge (62) of the second skin region (60); and

[0188] The first skin region (40) and the second skin region (60) are operatively attached to the trailing edge structure (100) using multiple single-sided fasteners (150), wherein, after the operative attachment step:

[0189] (i) The first subgroup (152) of the plurality of single-sided fasteners (150) operatively interconnects the first skin region (40) with the trailing edge structure (100); and

[0190] (ii) The second subgroup (154) of the plurality of single-sided fasteners (150) is operatively interconnected with the second skin region (60) and the trailing edge structure (100).

[0191] B2. The method as described in paragraph B1, wherein the aerodynamic structure (30) defines an exposed outer surface that defines an enclosed volume, and further wherein the operative attachment step includes operatively attaching such that the unexposed end (158) of each of the plurality of one-sided fasteners (150) is positioned within the enclosed volume.

[0192] B3. The method as described in any one of paragraphs B1-B2, wherein, during operative attachment, each of the plurality of one-sided fasteners (150) is actuated only from its corresponding exposed end (156).

[0193] B4. The method as described in any one of paragraphs B1-B3, wherein the operative attachment step comprises operatively attaching such that at least one of the following is performed:

[0194] (i) The first interface (50) located between the first skin region (40) and the trailing edge structure (100) does not have a corresponding adhesive between the first skin region (40) and the trailing edge structure (100); and

[0195] (ii) The second interface (70) located between the second skin region (60) and the trailing edge structure (100) does not have a corresponding adhesive between the second skin region (60) and the trailing edge structure (100).

[0196] B5. The method as described in any one of paragraphs B1-B4, wherein the method further comprises providing the first skin region (40), the second skin region (60), and the trailing edge structure (100), wherein the providing step comprises providing the previously cured first skin region, the previously cured second skin region, and the previously cured trailing edge structure.

[0197] B6. The method as described in any one of paragraphs B1-B5, wherein the operative attachment step comprises positioning each first single-sided fastener of a first subgroup (152) of the plurality of single-sided fasteners (150) in a corresponding first hole extending through both the first skin region (40) and the trailing edge structure (100), and subsequently actuating each first single-sided fastener from a corresponding exposed first end of each first single-sided fastener of the first subgroup (152) of the plurality of single-sided fasteners (150) to operatively attach the first skin region (40) to the trailing edge structure (100).

[0198] B7. The method as described in any one of paragraphs B1-B6, wherein the operative attachment step comprises positioning each second single-sided fastener of the second subgroup (154) of the plurality of single-sided fasteners (150) in a corresponding second hole extending through both the second skin region (60) and the trailing edge structure (100), and subsequently actuating each second single-sided fastener from the corresponding exposed second end of each second single-sided fastener of the second subgroup (154) of the plurality of single-sided fasteners (150) to operatively attach the second skin region (60) to the trailing edge structure (100).

[0199] B8. The method as described in any one of paragraphs B1-B7, wherein the operative attachment step comprises operatively attaching such that the unexposed end (158) of each of the plurality of one-sided fasteners (150) is positioned within a void space, the void space being at least partially or even completely defined within the trailing edge structure (100).

[0200] B9. The method as described in any one of paragraphs B1-B8, wherein the aerodynamic structure (30) comprises any suitable structure of any aerodynamic structure (30) as described in any one of paragraphs A1-A36 or any aerodynamic surface (19) as described in any one of paragraphs A37-A38.

[0201] C1. The use of multiple single-sided fasteners (150) to operatively attach the first skin region (40) and the second skin region (60) to the trailing edge structure (100), thereby at least partially defining the aerodynamic structure (30).

[0202] C2. For the purpose of any of the aerodynamic structures (30) according to any one of paragraphs A1-A36, any one of the methods according to any one of paragraphs B1-B9.

[0203] C3. Use of any one of the methods described in any one of paragraphs B1-B9 to form any one of the aerodynamic structures (30) described in any one of paragraphs A1-A36.

[0204] As used herein, the terms “selective” and “selectively” mean, when modifying the action, movement, configuration or other activity of one or more components or characteristics of a device, that a particular action, movement, configuration or other activity is a direct or indirect result of the user’s manipulation of one aspect or one or more components of the device.

[0205] As used herein, the terms “adaptive” and “configurable” mean that an element, component, or other subject is designed and / or intended to perform a given function. Therefore, the use of the terms “adaptive” and “configurable” should not be construed as meaning that a given element, component, or other subject is merely “capable” of performing a given function, but rather that the element, component, and / or other subject is specifically selected, created, implemented, utilized, programmed, and / or designed to perform that function. Also within the scope of this disclosure, elements, components, and / or other listed subjects listed as adapted to perform a particular function may additionally or alternatively be described as being configured to perform that function, and vice versa. Similarly, subjects listed as configured to perform a particular function may additionally or alternatively be described as being operationally capable of performing that function.

[0206] As used herein, the phrase “at least one” in relation to a list of one or more entities should be understood to mean at least one entity selected from any one or more entities in the entity list, but not necessarily including at least one of each entity specifically listed in the entity list, and does not exclude any combination of entities in the entity list. This definition also allows for entities other than those explicitly identified in the entity list referred to by the phrase “at least one”, which may optionally exist, whether related to or unrelated to those explicitly identified entities. Thus, as a non-limiting example, “at least one of A and B” (or equivalently, “at least one of A or B”, or equivalently, “at least one of A and / or B”) may mean, in one embodiment, at least one optionally includes more than one A, B is absent (and optionally includes entities other than B); in another embodiment, at least one optionally includes more than one B, A is absent (and optionally includes entities other than A); in yet another embodiment, for at least one, optionally includes more than one A, and at least one optionally includes more than one B (and optionally includes other entities). In other words, the phrases “at least one,” “one or more,” and “and / or” are open-ended expressions that are both connected and separate in operation. For example, each of the expressions “at least one of A, B, and C,” “at least one of A, B, or C,” “one or more of A, B, and C,” “one or more of A, B, or C,” and “A, B, and / or C” can refer to a single A, a single B, a single C, A and B together, A and C together, B and C together, A, B, and C together, and any of the above, optionally combined with at least one other entity.

[0207] The steps of the various disclosed apparatus elements and methods herein are not necessary for all apparatuses and methods according to this disclosure, and this disclosure includes all novel and non-obvious combinations and sub-combinations of the various elements and steps disclosed herein. Furthermore, one or more of the various elements and steps disclosed herein may define an independent inventive subject matter that is separate and independent from the overall disclosed apparatus or method. Therefore, such inventive subject matter does not need to be associated with a specific apparatus or method explicitly disclosed herein, and such inventive subject matter can find utility in apparatuses and / or methods not explicitly disclosed herein.

[0208] As used herein, the phrases “for example,” “as an example,” and / or simply “example” when referring to one or more components, features, details, structures, embodiments, and methods according to this disclosure are intended to convey illustrative, non-exclusive examples of the components, features, details, structures, embodiments, and / or methods according to this disclosure. Therefore, the described components, features, details, structures, embodiments, and / or methods are not intended to be limiting, claiming, or exclusive / exhaustive; and other components, features, details, structures, embodiments, and / or methods that are structurally and / or functionally similar and / or equivalent are also within the scope of this disclosure.

[0209] As used herein, "at least substantially" can include not only the listed "substantial" degree or relationship, but also the entire range of the listed degree or relationship, when the degree or relationship is modified. A large number of the listed degree or relationship can include at least 75% of the listed degree or relationship. For example, an object at least substantially formed of a material includes an object in which at least 75% of the object is formed of that material, and also includes an object formed entirely of that material. As another example, a first length at least substantially as long as the second length includes a first length within 75% of the second length and also includes a first length as long as the second length.

Claims

1. An aerodynamic structure (30), comprising: The first skin region (40) includes the first skin edge (42). The second skin region (60) includes a second skin edge (62), wherein the first skin region (40) and the second skin region (60) are angled relative to each other and define a gap (80) between the first skin edge (42) and the second skin edge (62). A trailing edge structure (100) extends within the gap (80) and between the first skin edge (42) and the second skin edge (62), wherein the trailing edge structure (100) comprises: (i) A front region (110) is at least partially located within the gap (80) and includes a front spar defining a leading edge of the trailing edge structure and extending along the longitudinal length of the trailing edge structure, wherein the front spar is a front C-shaped spar recessed toward the trailing edge of the trailing edge structure, and a central bend of the front C-shaped spar defines the leading edge; (ii) The rear region (130) defines the rear edge (138) of the rear edge structure (100); and (iii) A transition region (140) extending from the front region (110) to the rear region (130); and Multiple single-sided fasteners (150), of which: (i) The first subgroup (152) of the plurality of single-sided fasteners (150) operatively interconnects the first skin region (40) with the trailing edge structure (100); and (ii) The second subgroup (154) of the plurality of single-sided fasteners (150) operatively interconnects the second skin region (60) with the trailing edge structure (100), and The first subgroup and the second subgroup of the plurality of single-sided fasteners both extend through the region of the rear edge structure located behind the central bend of the front C-shaped spar; and The trailing edge structure is a single-piece trailing edge structure, which defines the entirety of the front region, the rear region, and the transition region.

2. Aerodynamic structure (30) according to claim 1, wherein The front region (110) defines a first front region surface (112) and a second front region surface (116), and further, at least one of the following: (i) The first front region surface (112) faces the first skin region (40). (ii) The surface (112) of the first front region is in contact with the first skin region (40); (iii) The surface (112) of the first front region is in direct physical contact with the first skin region (40); (iv) The second front region surface (116) faces the second skin region (60); (v) The surface (116) of the second front region contacts the second skin region (60); as well as (vi) The surface (116) of the second front region is in direct physical contact with the second skin region (60).

3. The aerodynamic structure (30) according to claim 2, wherein, The first skin region (40) defines a plurality of first skin holes (48), wherein the first front region surface (112) defines a plurality of first structural holes (114), wherein each of the first subgroup (152) of the plurality of single-sided fasteners (150) extends through a corresponding first skin hole in the plurality of first skin holes (48) and also through a corresponding first structural hole in the plurality of first structural holes (114), wherein the second skin region (60) defines a plurality of second skin holes (68), wherein the second front region surface (116) defines a plurality of second structural holes (118), and further, wherein each of the second subgroup (154) of the plurality of single-sided fasteners (150) extends through a corresponding second skin hole in the plurality of second skin holes (68) and also through a corresponding second structural hole in the plurality of second structural holes (118).

4. The aerodynamic structure (30) according to claim 2 or 3, wherein, The front region (110) at least partially defines a front region void space (120) extending between the first front region surface (112) and the second front region surface (116), wherein each of the plurality of single-sided fasteners (150) includes a corresponding exposed end (156) and a corresponding unexposed end (158), and further, wherein the corresponding unexposed end (158) is positioned within the front region void space (120).

5. The aerodynamic structure (30) according to claim 1 or 2, wherein, The rear region (130) is at least one of the following: (i) The rear region does not have a joint; and (ii) The rear region does not have a joint at the rear edge (138).

6. The aerodynamic structure (30) according to claim 1 or 2, wherein, The transition region (140) is at least one of the following: (i) The transition region gradually narrows from the front region (110) to the rear region (130); and (ii) The transition region monotonically shrinks from the front region (110) to the rear region (130).

7. The aerodynamic structure (30) according to claim 1, wherein, Each of the plurality of single-sided fasteners (150) is configured to operatively attach the corresponding skin area of ​​only one of the first skin area (40) and the second skin area (60) to the trailing edge structure (100).

8. The aerodynamic structure (30) according to claim 1, wherein, The plurality of single-sided fasteners (150) include at least one of the following: (i) Countersunk rivets; (ii) Rivets; (iii) Poppy hollow rivets; (iv) Self-holding fasteners; and (v) Self-tapping fasteners.

9. The aerodynamic structure (30) according to claim 1, wherein, The aerodynamic structure (30) is at least one of the following: (i) There is no adhesive between the first skin region (40) and the trailing edge structure (100); (ii) It does not have an adhesive that allows the first skin region (40) to be directly adhered to the trailing edge structure (100); (iii) It does not have an adhesive that indirectly adheres the first skin region (40) to the trailing edge structure (100); (iv) There is no adhesive between the second skin region and the trailing edge structure (100); (v) It does not have an adhesive that allows the second skin region to be directly adhered to the trailing edge structure (100); as well as (vi) It does not have an adhesive that indirectly adheres the second skin region to the trailing edge structure (100).

10. The aerodynamic structure (30) according to claim 1, wherein, The transition region includes a transition region spar, which is disposed within the transition region and configured to increase the stiffness of the trailing edge structure when the trailing edge structure is subjected to external loads, and to increase the resistance to deflection of the first exposed transition region surface and the second exposed transition region surface.

11. The aerodynamic structure (30) according to claim 1, wherein, The trailing edge structure is a one-piece trailing edge structure.

12. A vehicle (10) comprising an aerodynamic structure (30) according to claim 1 or 2, wherein the vehicle (10) comprises at least one of the following: (i) Aircraft; (ii) Helicopter; (iii) Spacecraft; and (iv) Ships.

13. A method for forming an aerodynamic structure (30), the method comprising: The trailing edge structure (100) is positioned within the gap (80) between the first skin edge (42) of the first skin region (40) and the second skin edge (62) of the second skin region (60); as well as The first skin region (40) and the second skin region (60) are operatively attached to the trailing edge structure (100) using multiple single-sided fasteners (150), wherein, after the operative attachment step: (i) The first subgroup (152) of the plurality of single-sided fasteners (150) operatively interconnects the first skin region (40) with the trailing edge structure (100); and (ii) The second subgroup (154) of the plurality of single-sided fasteners (150) operatively interconnects the second skin region (60) with the trailing edge structure (100). The trailing edge structure (100) includes: (i) A front region (110) is at least partially located within the gap (80) and includes a front spar extending between the first skin region (40) and the second skin region (60), defining the leading edge of the trailing edge structure, and the front spar extending along the longitudinal length of the trailing edge structure; (ii) The rear region (130) defines the rear edge (138) of the rear edge structure (100); and (iii) A transition region (140) extending from the front region (110) to the rear region (130). Wherein, the front wing spar is a front C-shaped wing spar, the front C-shaped wing spar is recessed toward the rear edge of the rear edge structure, wherein the central curved portion of the front C-shaped wing spar defines the front edge; The first subgroup and the second subgroup of the plurality of single-sided fasteners both extend through the region of the rear edge structure located behind the central bend of the front C-shaped spar; and The trailing edge structure is a single-piece trailing edge structure, which defines the entirety of the front region, the rear region, and the transition region.

14. The method according to claim 13, wherein, The aerodynamic structure (30) defines an exposed outer surface that defines an enclosed volume, and further wherein the operative attachment step includes operatively attaching such that the unexposed end (158) of each of the plurality of one-sided fasteners (150) is positioned within the enclosed volume.

15. The method according to claim 13 or 14, wherein, During operative attachment, each of the plurality of single-sided fasteners (150) is actuated only from the corresponding exposed end (156).

16. The method according to claim 13 or 14, wherein, The steps of operative attachment include operative attachment such that at least one of the following is achieved: (i) The first interface (50) located between the first skin region (40) and the trailing edge structure (100) does not have a corresponding adhesive between the first skin region (40) and the trailing edge structure (100); as well as (ii) The second interface (70) located between the second skin region (60) and the trailing edge structure (100) does not have a corresponding adhesive between the second skin region (60) and the trailing edge structure (100).

17. The method according to claim 13 or 14, wherein, The transition region includes a transition region spar, which is disposed within the transition region and configured to increase the stiffness of the trailing edge structure when the trailing edge structure is subjected to external loads, and to increase the resistance to deflection of the first exposed transition region surface and the second exposed transition region surface.

18. The method according to claim 13 or 14, wherein, The operative attachment step includes positioning each first single-sided fastener of the first subgroup (152) of the plurality of single-sided fasteners (150) in a corresponding first hole extending through both the first skin region (40) and the trailing edge structure (100), and subsequently actuating each first single-sided fastener from the corresponding exposed first end of each first single-sided fastener of the first subgroup (152) of the plurality of single-sided fasteners (150) to operatively attach the first skin region (40) to the trailing edge structure (100).

19. The method according to claim 13 or 14, wherein, The operative attachment step includes positioning each of the second subgroup (154) of the plurality of one-sided fasteners (150) in a corresponding second hole extending through both the second skin region (60) and the trailing edge structure (100), and subsequently actuating each of the second one-sided fasteners from the corresponding exposed second end of each of the second subgroup (154) of the plurality of one-sided fasteners (150) to operatively attach the second skin region (60) to the trailing edge structure (100).

20. The method according to claim 13 or 14, wherein, The operative attachment step includes operatively attaching such that the unexposed end (158) of each of the plurality of one-sided fasteners (150) is positioned within a gap space, the gap space being at least partially defined within the trailing edge structure (100).

Images