Device for a wing, method for moving a wing blade, method for moving a panel

Abstract

The present application relates to an apparatus for a wing, a method for moving a flap, and a method for moving a panel. An airflow-dependent deployable flap for an aircraft wing is described. An example apparatus includes a flap, which is coupled to the wing of the aircraft. The flap is movable between a stowed position and a deployed position relative to the wing, in which the panel of the flap extends along the skin of the wing, and in the deployed position, the panel extends away from the skin at an upward angle. The panel is configured to obstruct airflow along the span of the wing when the flap is in the deployed position. The flap is configured to move from the deployed position to the stowed position in response to an aerodynamic force applied to the panel.

Description

Technical Field

[0001] The present disclosure relates generally to fences for aircraft wings and, more particularly, to airflow-dependent deployable fences for aircraft wings. Background Art

[0002] Wing blades may be implemented on a wing of an aircraft (e.g., a swept wing aircraft) to impede (e.g., block) spanwise airflow along the wing to improve handling of the aircraft at reduced speeds (e.g., lower speeds during takeoff and / or landing operations of the aircraft relative to higher speeds during cruise operations of the aircraft). Conventional wing blades are positioned and / or arranged in a generally chordwise direction along the top side of an aircraft wing.

[0003] Some conventional wing blades are fixed in position on the aircraft wing and / or are immovably coupled to the aircraft wing, such that such conventional wing blades generate and / or produce drag throughout the flight of the aircraft (e.g., during takeoff operations, during cruise operations, and during landing operations). Other conventional wing blades can be deployed and / or retracted between a vertically deployed position extending upward from the aircraft wing and a vertically stowed position within the airfoil of the aircraft wing, but space-consuming mechanical linkages are typically required to actuate such movement of the wing blade, which is under the control of the aircraft pilot.

[0004] It is with respect to these and other considerations that the present disclosure made herein is presented. Summary of the invention

[0005] Disclosed herein are example airflow-dependent deployable winglets for aircraft wings. In some examples, a device is disclosed. In some disclosed examples, the device includes a winglet connected to the aircraft wing. In some disclosed examples, the winglet can be moved relative to the wing between a stowed position and a deployed position, in which the panel of the winglet extends along the skin of the wing, and in the deployed position, the panel extends away from the skin at an upward angle. In some disclosed examples, the panel is configured to hinder the airflow along the span of the wing when the winglet is in the deployed position. In some disclosed examples, the winglet is configured to move from the deployed position to the stowed position in response to an aerodynamic force applied to the panel.

[0006] In some examples, a method for moving a wing blade connected to an aircraft wing is disclosed. In some disclosed examples, the method includes the following steps: moving the wing blade between a stowed position and a deployed position, in which a panel of the wing blade extends along the skin of the wing, and in the deployed position, the panel extends away from the skin at an upward angle. In some disclosed examples, the panel obstructs airflow along the span direction of the wing when the wing blade is in the deployed position. In some disclosed examples, the movement includes moving the wing blade from the deployed position to the stowed position in response to an aerodynamic force applied to the panel. BRIEF DESCRIPTION OF THE DRAWINGS

[0007] Figure 1 An example aircraft is illustrated that may implement an example airflow-dependent deployable wing blade in accordance with the teachings of the present disclosure.

[0008] Figure 2 Illustrated Figure 1 Examples of deployable blades that rely on airflow to deploy, Figure 1 Example aircraft.

[0009] Figure 3 is taken inboard and across the example center axis of the example axle, Figure 1 and Figure 2 A cross-sectional view of a first example wing blade, wherein the first wing blade is Figure 1 Example of a collapsed position.

[0010] Figure 4 Looking backward along the example center axis of the example axle Figures 1 to 3 A front view of a first example wing knife, wherein the first wing knife is in Figure 1 and Figure 3 Example of a collapsed position.

[0011] Figure 5 Looking backward along the example chordwise direction of the first example wing Figures 1 to 4 A front view of a first example wing knife, wherein the first wing knife is in Figure 1 , Figure 3 as well as Figure 4 Example of a collapsed position.

[0012] Figure 6 is in Figure 1 as well as Figures 3 to 5 Example of collapsed position Figures 1 to 5 A plan view of a first example wing blade.

[0013] Figure 7 is taken inboard and across the example center axis of the example axle, Figures 1 to 6 A cross-sectional view of a first example wing blade, wherein the first wing blade is Figure 2 Example of expanded location.

[0014] Figure 8 Looking backward along the example center axis of the example axle Figures 1 to 7 A front view of a first example wing knife, wherein the first wing knife is in Figure 2 and Figure 7 Example of expanded location.

[0015] Fig. 9 Looking backward along the example chordwise direction of the first example wing Figures 1 to 8 A front view of a first example wing knife, wherein the first wing knife is in Figure 2 , Figure 7 as well as Figure 8 Example of expanded location.

[0016] Fig.10 is in Figure 2 as well as Figures 7 to 9 Example of expanded position in Figures 1 to 9 A plan view of a first example wing blade.

[0017] Fig.11 Another example aircraft that may implement an example airflow-dependent deployable wing blade in accordance with the teachings of the present disclosure is illustrated.

[0018] Fig.12 Illustrated Fig.11 Examples of deployable blades that rely on airflow to deploy, Fig.11 Example aircraft.

[0019] Fig.13 is taken inboard and across the example center axis of the example axle, Fig.11 and Fig.12 A cross-sectional view of a first example wing blade, wherein the first wing blade is Fig.11 Example of a collapsed position.

[0020] Fig.14 Looking backward along the example center axis of the example axle Figures 11 to 13 A front view of a first example wing knife, wherein the first wing knife is in Fig.11 and Fig.13 Example of a collapsed position.

[0021] Fig.15 Looking backward along the example chordwise direction of the first example wing Figures 11 to 14 A front view of a first example wing knife, wherein the first wing knife is in Fig.11 , Fig.13 as well as Fig.14 Example of a collapsed position.

[0022] Fig.16 is in Fig.11 as well as Figures 13 to 15 Example of collapsed position Figures 11 to 15 A plan view of a first example wing blade.

[0023] Fig.17 is taken inboard and across the example center axis of the example axle, Figures 11 to 16 A cross-sectional view of a first example wing blade, wherein the first wing blade is Fig.12 Example of expanded location.

[0024] Fig.18 Looking backward along the example center axis of the example axle Figures 11 to 17 A front view of a first example wing knife, wherein the first wing knife is in Fig.12 and Fig.17 Example of expanded location.

[0025] Fig.19 Looking backward along the example chordwise direction of the first example wing Figures 11 to 18 A front view of a first example wing knife, wherein the first wing knife is in Fig.12 , Fig.17 as well as Fig.18 Example of expanded location.

[0026] Fig. 20 is in Fig.12 as well as Figures 17 to 19 Example of expanded position in Figures 11 to 19 A plan view of a first example wing blade.

[0027] Fig.21 Another example aircraft that may implement an example airflow-dependent deployable wing blade in accordance with the teachings of the present disclosure is illustrated.

[0028] Fig. 22 Illustrated Fig.21 Examples of deployable blades that rely on airflow to deploy, Fig.21 Example aircraft.

[0029] Fig.23 is taken inboard and across the example center axis of the example axle, Fig.21 and Fig. 22 A cross-sectional view of a first example wing blade, wherein the first wing blade is Fig.21 Example of a collapsed position.

[0030] Fig.24 Looking backward along the example center axis of the example axle Figure 21 to Figure 23 A front view of a first example wing knife, wherein the first wing knife is in Fig.21 and Fig.23 Example of a collapsed position.

[0031] Fig.25 is in Fig.21 , Fig.23 as well as Fig.24 Example of collapsed position Figure 21 to Figure 24 A plan view of a first example wing blade.

[0032] Fig.26 is taken looking inboard and across the example center axis of the example axle, Figure 21 to Figure 25 A cross-sectional view of a first example wing blade, wherein the first wing blade is Fig. 22 Example of expanded location.

[0033] Fig. 27 Looking backward along the example center axis of the example axle Figure 21 to Figure 26 A front view of a first example wing knife, wherein the first wing knife is in Fig. 22 and Fig.26 Example of expanded location.

[0034] Fig.28 is in Fig. 22 , Fig.26 as well as Fig. 27 Example of expanded position in Figure 21 to Figure 27 A plan view of a first example wing blade.

[0035] Fig.29 Another example aircraft that may implement an example airflow-dependent deployable wing blade in accordance with the teachings of the present disclosure is illustrated.

[0036] Fig.30 Illustrated Fig.29 Examples of deployable blades that rely on airflow to deploy, Fig.29 Example aircraft.

[0037] Fig.31 is taken from the inside and across the example center axis of the example base, Fig.29 and Fig.30 A cross-sectional view of a first example wing blade, wherein the first wing blade is Fig.29 Example of a collapsed position.

[0038] Fig.32 Looking backward along the example center axis of the example base Figure 29 to Figure 31 A front view of a first example wing knife, wherein the first wing knife is in Fig.29 and Fig.31 Example of a collapsed position.

[0039] Fig.33 is in Fig.29 , Fig.31 as well as Fig.32 Example of collapsed position Figure 29 to Figure 32 A plan view of a first example wing blade.

[0040] Fig.34is taken from the inside and across the example center axis of the example base, Figure 29 to Figure 33 A cross-sectional view of a first example wing blade, wherein the first wing blade is Fig.30 Example of expanded location.

[0041] Fig.35 Looking backward along the example center axis of the example base Figures 29 to 34 A front view of a first example wing knife, wherein the first wing knife is in Fig.30 and Fig.34 Example of expanded location.

[0042] Fig.36 is in Fig.30 , Fig.34 as well as Fig.35 Example of expanded position in Figure 29 to Figure 35 A plan view of a first example wing blade.

[0043] Fig.37 is a cross-sectional view of an example wing blade having a single example planar panel positioned in an example stowed position relative to an example curved wing.

[0044] Fig.38 is a cross-sectional view of an example wing blade having a plurality of example planar panels respectively positioned in corresponding example stowed positions relative to an example curved wing.

[0045] Fig.39 yes Fig.38 A cross-sectional view of an example wing blade having a Fig.38 An example curved wing is shown with multiple example planar panels respectively positioned in corresponding example deployed positions.

[0046] Fig.40 is a cross-sectional view of an example wing blade having a plurality of example panels respectively positioned in corresponding example recessed stowed positions relative to an example curved wing.

[0047] Fig.41 yes Fig.40 A cross-sectional view of an example wing blade having a Fig.40 An example curved wing is shown with multiple example panels respectively positioned in corresponding example deployed positions.

[0048] Specific examples are shown in the drawings identified above and described in detail below. In describing these examples, similar or identical reference numerals are used to identify the same or similar elements. The drawings are not necessarily to scale, and certain features and certain views of the drawings may be exaggerated in scale or shown in schematic form for the sake of clarity and / or brevity. DETAILED DESCRIPTION

[0049] Wing blades may be implemented on the wings of an aircraft (e.g., a swept wing aircraft) to impede (e.g., block) spanwise airflow along the wing to improve aircraft handling at reduced speeds (e.g., lower speeds during takeoff and / or landing operations of the aircraft relative to higher speeds during cruise operations of the aircraft). Conventional wing blades implemented on aircraft wings typically have relatively large wetted areas that generate and / or produce drag while the aircraft is in flight.

[0050] Some conventional winglets are fixed in position on an aircraft wing and / or are immovably coupled to the wing of the aircraft such that such conventional winglets generate and / or produce drag throughout the flight of the aircraft (e.g., during takeoff operations, during cruise operations, and during landing operations). While implementing such conventional winglets on an aircraft wing to obstruct spanwise airflow along the wing can advantageously improve the handling of the aircraft during low-speed operations (e.g., during takeoff and / or landing), this advantage is not without disadvantages. For example, the presence of such conventional winglets may cause an undesirable loss of aerodynamic performance (e.g., drag) during high-speed operations of the aircraft (e.g., during cruise).

[0051] Other conventional wing blades are movable (e.g., deployable and / or retractable) between a vertically deployed position extending upward from an aircraft wing and a vertically stowed position within the aerofoil of the aircraft wing. While implementing such movable conventional wing blades on an aircraft wing to impede spanwise airflow along the wing can advantageously improve the handling of the aircraft during low-speed operations (e.g., during takeoff and / or landing), this advantage is again not without disadvantages. For example, such movable conventional wing blades typically require space-consuming in-wing mechanical linkages to actuate and / or move the wing blades between their respective deployed and stowed positions, such mechanical linkages being under the control of the aircraft pilot.

[0052] In the absence of the implementation of conventional wing blades as described above, an aircraft is typically required to implement one or more other countermeasures to mitigate spanwise airflow along the aircraft wing during low-speed operation. Known countermeasures undesirably increase the costs associated with designing, testing, installing and / or otherwise implementing the wing and / or, more generally, the aircraft.

[0053] Different from the above-mentioned traditional wing blade and / or other countermeasures, the example deployable wing blade disclosed herein is aerodynamically initiated and / or airflow-dependent. In some disclosed examples, the deployable wing blade is connected (e.g., rotatably connected) to the aircraft wing so that the wing blade can be advantageously moved relative to the wing between the stowed position and the deployed position, in which the panel of the wing blade extends along the skin of the wing, and in the deployed position, the panel extends away from the skin at an upward angle. The panel is configured to hinder the airflow around the aircraft when the wing blade is in the deployed position. For example, the panel can hinder the airflow along the spanwise direction of the wing when the wing blade is in the deployed position. As another example, the panel can initiate and / or generate a vortex along the wing when the wing blade is in the deployed position. The wing blade is advantageously configured to move between the stowed position and the deployed position in response to the aerodynamic force applied to the wing blade. In some disclosed examples, the wing blade is configured to move from the deployed position to the stowed position in response to the aerodynamic force applied to the panel. In other disclosed examples, the flapper is configured to move from a stowed position to a deployed position in response to aerodynamic forces applied to deployed blades of the flapper.

[0054] The deployable wing blades of the example disclosed herein that rely on airflow provide a large number of advantages that exceed the above-mentioned traditional wing blades. For example, the mobility (e.g., movement from the deployed position to the stowed position) of the deployable wing blades that rely on airflow disclosed herein advantageously reduces the loss (e.g., drag) of undesirable aerodynamic performance during the high-speed operation of the aircraft (e.g., during cruising). As another example, the deployable wing blades that rely on airflow disclosed herein provide a stowed position for the wing blade, whereby the wing blade extends along the skin of the wing (contrary to the vertical in the wing), thereby advantageously increasing the amount of unused space in the wing relative to the amount of space that can be consumed by the mechanical linkage in the wing in other ways, and these linkages are associated with the above-mentioned number of vertically deployable traditional wing blades. As another example, the deployable wing blades that rely on airflow disclosed herein promote the non-pilot operation (e.g., deployment and retraction) of the wing blade, which advantageously ensures that the wing blade is deployed and / or retracted at the appropriate time and / or under appropriate flight conditions.

[0055] Figure 1 An example aircraft 100 is illustrated that may implement an example airflow-dependent deployable wing blade in accordance with the teachings of the present disclosure. Figure 1 Illustrated Figure 1 Examples of airflow-dependent deployable blades that are retracted, Figure 1 An example aircraft 100 is shown. Figure 2 Illustrated Figure 1 Examples of deployable blades that rely on airflow to deploy, Figure 1The example aircraft 100 is shown in FIG. 1 . The aircraft 100 may be any form and / or type of aircraft, including, for example, a civilian (e.g., commercial or business) aircraft, a military aircraft, a manned aircraft, an unmanned aircraft (e.g., a drone), etc. Figure 1 and 2 In the illustrated example of FIG. 1 , the aircraft 100 includes an example fuselage 102 , a first example wing 104 (e.g., a left wing), a second example wing 106 (e.g., a right wing), a first example wing blade 108 (e.g., a left wing blade), and a second example wing blade 110 (e.g., a right wing blade). Figure 1 and Figure 2 The illustrated example depicts only a single wing blade located on each wing of the aircraft 100 (e.g., first wing blade 108 located on first wing 104 and second wing blade 110 located on second wing 106), but other example implementations may include multiple (e.g., 2, 3, 4, etc.) wing blades located on each wing of the aircraft 100. In some examples, the position, size, and / or shape of each wing blade of the aircraft 100 (e.g., first wing blade 108 and second wing blade 110) may be relative to each other. Figure 1 and Figure 2 The blades shown are in different locations, sizes and / or shapes.

[0056] Figure 1 and Figure 2 The fuselage 102 has a generally cylindrical shape that defines an example longitudinal axis 112 of the aircraft 100 . Figure 1 and Figure 2 The first wing 104 and the second wing 106 are respectively coupled to the fuselage 102 and swept in a rearward direction of the aircraft 100. The first wing 104 includes an example skin 114 that forms an outer surface of the first wing 104 (e.g., forms all or part thereof), and the second wing 106 includes an example skin 116 that forms an outer surface of the second wing 106 (e.g., forms all or part thereof).

[0057] Figure 1 and Figure 2The first airfoil 104 of the embodiment of the present invention defines an example spanwise direction 118 moving from an example inboard portion 120 of the first airfoil 104 (e.g., inboard relative to the spanwise position of the first airfoil 108) toward an example outboard portion 122 of the first airfoil 104 (e.g., outboard relative to the spanwise position of the first airfoil 108). The spanwise direction 118 defined by the first airfoil 104 represents a direction of spanwise airflow that may occur along the first airfoil 104. The first airfoil 104 also defines an example chordwise direction 124 moving from an example leading edge 126 of the first airfoil 104 toward an example trailing edge 128 of the first airfoil 104. The chordwise direction 124 defined by the first airfoil 104 represents a direction of chordwise airflow (e.g., cruising airflow) that may occur along the first airfoil 104.

[0058] Figure 1 and Figure 2 The second airfoil 106 of the embodiment of the present invention defines an example spanwise direction 130 moving from an example inboard portion 132 of the second airfoil 106 (e.g., inboard relative to the spanwise position of the second airfoil 110) toward an example outboard portion 134 of the second airfoil 106 (e.g., outboard relative to the spanwise position of the second airfoil 110). The spanwise direction 130 defined by the second airfoil 106 represents a direction of spanwise airflow that may occur along the second airfoil 106. The second airfoil 106 also defines an example chordwise direction 136 moving from an example leading edge 138 of the second airfoil 106 toward an example trailing edge 140 of the second airfoil 106. The chordwise direction 136 defined by the second airfoil 106 represents a direction of chordwise airflow (e.g., cruising airflow) that may occur along the second airfoil 106.

[0059] Figure 1 and Figure 2 The first wing blade 108 is rotatably coupled to the first wing 104 so that the first wing blade 108 can be rotated Figure 1 Stowed position shown Figure 2 The first flap 108 includes an exemplary panel 142. The panel 142 of the first flap 108 is movable (e.g., rotatable) between the deployed positions shown. Figure 1 When in the stowed position shown, the first wing blade 108 extends along the skin 114 of the first wing 104 (e.g., in an inboard direction toward the longitudinal axis 112). In some examples, when the first wing blade 108 is in the stowed position, the first wing blade 108 extends along the skin 114 of the first wing 104 (e.g., in an inboard direction toward the longitudinal axis 112). Figure 1 When in the stowed position shown, the panel 142 of the first wing blade 108 extends along the skin 114 of the first wing 104 and is positioned above and / or on top of the skin. Figure 1When in the stowed position shown, the panel 142 of the first wing blade 108 extends along the skin 114 of the first wing 104 and is recessed (e.g., fully or partially recessed) relative to the skin. Figure 2 When in the deployed position shown, the panel 142 of the first wing blade 108 extends away from the skin 114 of the first wing 104 at an upward angle (e.g., vertically). Figure 2 When in the deployed position shown, the panel 142 of the first wing blade 108 is configured to impact the airflow around the aircraft 100. For example, when the first wing blade 108 is in Figure 2 When in the deployed position shown, the panel 142 can block the spanwise airflow occurring along the spanwise direction 118 of the first wing 104. As another example, when the first wing blade 108 is in the Figure 2 When in the deployed position as shown, the panels 142 may initiate and / or generate vortices along the first wing 104 .

[0060] Panel 142 and / or more generally, Figure 1 and Figure 2 The first wing blade 108 is rotatably coupled to the Figure 1 and Figure 2 The first wing 104. Figure 1 and Figure 2 In the illustrated example, the central axis 146 of the axle 144 is inclined (eg, oriented at an angle) relative to the chordwise direction 124 of the first wing 104. Figure 1 and Figure 2 As shown, the central axis 146 of the axle 144 is tilted at an example toe-in angle 148 relative to the chordwise direction 124 of the first wing 104, such that a first end of the axle 144 positioned toward the leading edge 126 of the first wing 104 is positioned closer to the longitudinal axis 112 of the aircraft 100 than a second end of the axle 144 positioned toward the trailing edge 128 of the first wing 104. For clarity, the axle 144 is exaggerated. Figure 1 and Figure 2 An example toe angle 148 is shown. When implemented, the toe angle 148 preferably has a value within a range from one to fifteen degrees.

[0061] Figure 1 and Figure 2 The first wing blade 108 is configured to move from the panel 142 of the first wing blade 108 in response to the aerodynamic force applied to the panel 142 of the first wing blade 108. Figure 2 The expanded position shown moves to Figure 1In some examples, the aerodynamic force may be generated via chord-wise airflow (e.g., cruising airflow) occurring along the chord-wise direction 124 of the first wing 104. In some examples, in response to the aerodynamic force exerted on the panel 142 of the first flap 108 being less than a threshold force value (e.g., less than a biasing force generated by the actuator), an actuator operatively coupled to the first flap 108 biases and / or maintains the first flap 108 in the stowed position. Figure 2 In the expanded position shown in . Figures 3 to 10 Example devices for implementing the actuator are discussed. In some disclosed examples, in response to an aerodynamic force applied to the panel 142 of the first flap 108 being greater than a threshold force value (e.g., greater than a biasing force generated by the actuator), the first flap 108 is moved from Figure 2 The expanded position shown moves to Figure 1 In some disclosed examples, the first wing blade 108 is configured to move from a first position to a second position during a cruise operation of the aircraft 100 having a first speed. Figure 2 The expanded position shown moves to Figure 1 The first wing blade 108 is also configured to be stowed from the first wing blade 108 during a slow speed operation (e.g., takeoff or landing operation) of the aircraft 100 having a second speed that is less than the first speed. Figure 1 The stowed position shown moves to Figure 2 Expanded position shown.

[0062] Figure 1 and Figure 2 The second wing blade 110 is rotatably connected to the second wing 106 so that the second wing blade 110 can be rotated at Figure 1 Stowed position shown Figure 2 The second flap 110 includes an exemplary panel 150. The panel 150 of the second flap 110 is movable (e.g., rotatable) between the deployed positions shown. Figure 1 When in the stowed position shown, the second wing blade 110 extends along the skin 116 of the second wing 106 (e.g., in an inboard direction toward the longitudinal axis 112). In some examples, when the second wing blade 110 is in the stowed position, the second wing blade 110 extends along the skin 116 of the second wing 106 (e.g., in an inboard direction toward the longitudinal axis 112). Figure 1 When in the stowed position shown, the panel 150 of the second wing blade 110 extends along the skin 116 of the second wing 106 and is positioned above and / or on top of the skin. Figure 1 When in the stowed position shown, the panel 150 of the second wing blade 110 extends along the skin 116 of the second wing 106 and is recessed (e.g., fully or partially recessed) relative to the skin. Figure 2In the deployed position shown, the panel 150 of the second wing blade 110 extends away from the skin 116 of the second wing 106 at an upward angle (e.g., vertically). Figure 2 When in the deployed position shown, the panel 150 of the second wing blade 110 is configured to impact the airflow around the aircraft 100. For example, when the second wing blade 110 is in Figure 2 When in the deployed position shown, the panel 150 can block the spanwise airflow occurring along the spanwise direction 130 of the second wing 106. As another example, when the second wing blade 110 is in the Figure 2 When in the deployed position as shown, the panels 150 may initiate and / or generate vortices along the second wing 106 .

[0063] Panel 150 and / or more generally Figure 1 and Figure 2 The second wing blade 110 is rotatably coupled to the Figure 1 and Figure 2 The second wing 106. Figure 1 and Figure 2 In the illustrated example, the central axis 154 of the axle 152 is inclined (e.g., oriented at an angle) relative to the chordwise direction 136 of the second wing 106. For example, Figure 1 and Figure 2 As shown, the central axis 154 of the axle 152 is tilted relative to the chordwise direction 136 of the second wing 106 at an example toe angle 156 such that a first end of the axle 152 positioned toward the leading edge 138 of the second wing 106 is positioned closer to the longitudinal axis 112 of the aircraft 100 than a second end of the axle 152 positioned toward the trailing edge 140 of the second wing 106. For clarity, the axle 152 is exaggerated. Figure 1 and Figure 2 An example toe angle 156 is shown. When implemented, the toe angle 156 preferably has a value within a range from one to fifteen degrees.

[0064] Figure 1 and Figure 2 The second wing blade 110 is configured to respond to the aerodynamic force applied to the panel 150 of the second wing blade 110 from Figure 2 The expanded position shown moves to Figure 1 In some examples, the aerodynamic force may be generated via chord-wise airflow (e.g., cruising airflow) occurring along the chord-wise direction 136 of the second wing 106. In some examples, in response to the aerodynamic force exerted on the panel 150 of the second flap 110 being less than a threshold force value (e.g., less than a biasing force generated by the actuator), an actuator operatively coupled to the second flap 110 biases and / or maintains the second flap 110 in the stowed position. Figure 2 In the expanded position shown in . Figures 3 to 10 Example devices for implementing the actuator are discussed. In some disclosed examples, in response to an aerodynamic force applied to the panel 150 of the second winglet 110 being greater than a threshold force value (e.g., greater than a biasing force generated by the actuator), the second winglet 110 is moved from Figure 2 The expanded position shown moves to Figure 1 In some disclosed examples, the second wing blade 110 is configured to move from a stowed position to a retracted position during a cruise operation of the aircraft 100 having a first speed. Figure 2 The expanded position shown moves to Figure 1 The second wing blade 110 is also configured to be stowed from the first wing blade 110 during a slow operation of the aircraft 100 (e.g., a takeoff or landing operation) having a second speed that is less than the first speed. Figure 1 The stowed position shown moves to Figure 2 Expanded position shown.

[0065] Figures 3 to 10 Provided to be rotatably coupled to Figure 1 and Figure 2 A first example of a wing 104 Figure 1 and Figure 2 Additional views of the first example wing blade 108. More specifically, Figure 3 is taken inboard and across the example center axis 146 of the example axle 144, Figure 1 and Figure 2 A cross-sectional view of a first example wing blade 108, wherein the first wing blade 108 is in Figure 1 Example of a collapsed position. Figure 4 Looking rearward along the example center axis 146 of the example axle 144 Figures 1 to 3 A front view of a first example wing blade 108, wherein the first wing blade 108 is in Figure 1 and Figure 3 Example of a collapsed position. Figure 5 Looking backward along the example chordwise direction 124 of the first example wing 104 Figures 1 to 4 A front view of a first example wing blade 108, wherein the first wing blade 108 is in Figure 1 , Figure 3 as well as Figure 4 Example of a collapsed position. Figure 6 is in Figure 1 as well as Figures 3 to 5 Example of collapsed position Figures 1 to 5 FIG. 1 is a plan view of a first example wing blade 108 . Figure 7 is taken inboard and across the example center axis 146 of the example axle 144, Figures 1 to 6 A cross-sectional view of a first example wing blade 108, wherein the first wing blade 108 is in Figure 2 Example of expanded location. Figure 8 Looking rearward along the example center axis 146 of the example axle 144 Figures 1 to 7 A front view of a first example wing blade 108, wherein the first wing blade 108 is in Figure 2 and Figure 7 Example of expanded location. Fig. 9 Looking backward along the example chordwise direction 124 of the first example wing 104 Figures 1 to 8 A front view of a first example wing blade 108, wherein the first wing blade 108 is in Figure 2 , Figure 7 as well as Figure 8 Example of expanded location. Fig.10 is in Figure 2 as well as Figures 7 to 9 Example of expanded position in Figures 1 to 9 FIG. 1 is a plan view of a first example wing blade 108 .

[0066] exist Figures 3 to 10 In the illustrated example of FIG. 1 , the first wing blade 108 is rotatably coupled to the first wing 104 via an axle 144. The axle 144 includes a first example end 302 coupled to the first wing 104 via a first example axle mount 304, and further includes a second example end 306 that is positioned opposite the first end 302 and is coupled to the first wing 104 via a second example axle mount 308. The first end 302 of the axle 144 is positioned toward the leading edge 126 of the first wing 104 and / or toward the first axle mount 304, and the second end 306 of the axle 144 is positioned toward the trailing edge 128 of the first wing 104 and / or toward the second axle mount 308.

[0067] The first flap 108 includes a first exemplary end 310, a second exemplary end 312 positioned opposite the first end 310, and an exemplary through hole 314 extending between the first end 310 and the second end 312 of the first flap 108. The first end 310 of the first flap 108 is positioned toward the leading edge 126 of the first wing 104 and / or toward the first axle seat 304, and the second end 312 of the first flap 108 is positioned toward the trailing edge 128 of the first wing 104 and / or the second axle seat 308. The axle 144 passes through and / or extends through the through hole 314 of the first flap 108, such that the axle 144 and the through hole 314 are positioned parallel and / or coaxially, and such that the first flap 108 is fixed to the axle 144 via the first axle seat 304 and the second axle seat 308. Thus, the first axle mount 304 and the second axle mount 308 secure both the axle 144 and the first wing blade 108 to the first wing 104. The first wing blade 108 can rotate about the axle 144 and can also rotate relative to the first wing 104. For example, the first wing blade 108 can rotate in a Figure 1 as well as Figures 3 to 6 Stowed position shown Figure 2 as well as Figures 7 to 10 The deployed positions are shown with respect to the first wing 104 rotated about the axle 144 .

[0068] exist Figures 3 to 10 In the illustrated example, the panel 142 of the first wing blade 108 is in the first position of the wing blade 108 Figures 3 to 6 In the stowed position shown, the skin 114 along the first wing 104 extends in an inboard direction (eg, toward the longitudinal axis 112 of the aircraft 100). Figures 3 to 6 As shown, when the first wing blade 108 is in the stowed position, the panel 142 of the first wing blade 108 extends along the skin 114 of the first wing 104 and is positioned above and / or on top of the skin. In other examples, when the first wing blade 108 is in the stowed position, the panel 142 of the first wing blade 108 may extend along the skin 114 of the first wing 104 and be recessed (e.g., fully or partially recessed) relative to the skin. Figures 7 to 10 As shown, when the first wing blade 108 is in the deployed position, the panel 142 of the first wing blade 108 extends away from the skin 114 of the first wing 104 at an upward angle (e.g., vertically). Figures 7 to 10 When in the deployed position shown, the panel 142 of the first wing blade 108 is configured to impact the airflow around the aircraft 100. For example, when the first wing blade 108 is in Figures 7 to 10 When in the deployed position shown, the panel 142 can block the spanwise airflow occurring along the spanwise direction 118 of the first wing 104. As another example, when the first wing blade 108 is in the Figures 7 to 10 When in the deployed position as shown, the panels 142 may initiate and / or generate vortices along the first wing 104 .

[0069] exist Figures 3 to 10 In the illustrated example, the panel 142 of the first wing blade 108 is planar. In other examples, the panel 142 of the first wing blade 108 can be non-planar. For example, the panel 142 of the first wing blade 108 can have a non-planar (e.g., curved) aerodynamic shape. In some examples, the non-planar aerodynamic shape can be configured to match and / or mimic the non-planar (e.g., curved) aerodynamic shape of the first wing 104. Figures 3 to 10In the illustrated example, the panel 142 of the first flap 108 has a trapezoidal shape between the first end 310 of the first flap 108 and the second end 312 of the first flap 108. In other examples, the panel 142 of the first flap 108 may have a different (e.g., non-trapezoidal) shape between the first end 310 of the first flap 108 and the second end 312 of the first flap 108. For example, the panel 142 of the first flap 108 may have a rectangular, square, triangular, semicircular, circular, or oval shape between the first end 310 of the first flap 108 and the second end 312 of the first flap 108, as well as any one of others.

[0070] exist Figures 3 to 10 In the illustrated example, an example spring-loaded axle 316 is formed via the axle 144 and an example spring 318 coiled around a portion of the axle 144. As further described below, the spring 318 and / or more generally the spring-loaded axle 316 functions as and / or operates as an actuator that is configured to cause the first wing blade 108 to move in a direction and / or intensity of airflow captured by and / or received at the panel 142 of the first wing blade 108. Figures 3 to 6 Stowed position shown Figures 7 to 10 to move between the expanded positions shown. Figures 3 to 10 In the illustrated example of FIG. 1 , the spring 318 of the spring-loaded axle 316 is located between the second end 312 of the first wing blade 108 and the second axle seat 308. The spring 318 and / or more generally the spring-loaded axle 316 is operatively coupled to the first wing blade 108 such that the spring 318 and / or the spring-loaded axle 316 biases the first wing blade 108 to the position of the second wing blade 108. Figures 7 to 10 For example, the spring 318 of the spring-loaded axle 316 generates a restoring force (e.g., a biasing force) having a restoring force value. In the absence of a deflection force (e.g., a counter-biasing force that may be generated via chord-wise and / or cruising airflow) that is opposite to the restoring force and has a deflection force value greater than the restoring force value, the restoring force generated by the spring 318 causes the first blade 108 to move (e.g., rotate) to Figures 7 to 10 The deployed position is shown and / or the first winglet 108 is maintained in this position.

[0071] exist Figures 3 to 10 In the illustrated example, the first wing blade 108 is Figures 7 to 10 Compared to the deployed position shown, when the first wing blade 108 is in Figures 3 to 6 In the stowed position shown, the spring 318 is in a relatively more wound state. Figures 3 to 6 Compared to the stowed position shown, when the first wing blade 108 is in Figures 7 to 10In the deployed position shown, the spring 318 is in a relatively more unwound state. In other words, as the first wing blade 108 is moved from Figures 7 to 10 The expanded position shown moves to Figures 3 to 6 In the stowed position shown, the spring 318 is wound around the spring loaded axle 316 and as the first wing blade 108 is moved from Figure 3 Of Figure 6 The stowed position shown moves to Figures 7 to 10 In the deployed position shown, the spring 318 is unwound in the opposite direction about the spring loaded axle 316. Figures 3 to 10 In the illustrated example, the spring 318 is implemented via one or more torsion springs. In other examples, the spring 318 can be implemented additionally or alternatively via one or more (e.g., alone or in combination) appropriately arranged leaf springs, compression springs and / or tension springs.

[0072] The movement (e.g., rotation) of the first wing blade 108 relative to the first wing 104 is dependent on airflow. Figure 1 and Figure 2 Describe and Figures 3 to 10 As further shown in FIG. 1 , the central axis 146 of the axle 144 is tilted at a toe angle 148 relative to the chordwise direction 124 of the first wing 104. Positioning and / or orienting the central axis 146 of the axle 144 at the toe angle 148 causes the panel 142 of the first wing blade 108 to be positioned and / or oriented in a similar manner. Figures 7 to 10 In the deployed position shown (e.g., as may be caused by the restoring force generated by the spring 318 of the spring-loaded axle 316), the panel 142 of the first wing 108 is positioned to capture, receive, and / or react to chord-wise airflow (e.g., cruising airflow) occurring along the chord-wise direction 124 of the first wing 104. As a result of the toe angle 148 at which the central axis 146 of the axle 144 is tilted, the chord-wise airflow occurring along the chord-wise direction 124 of the first wing 104 carries a deflection force component that counteracts (e.g., opposes) the restoring force generated by the spring 318 of the spring-loaded axle 316.

[0073] If the deflection force component of the chord-wise airflow received at, applied to, and / or exerted on the panel 142 of the first blade 108 is greater than the restoring force generated by the spring 318 of the spring-loaded axle 316, the chord-wise airflow causes the first blade 108 to move from Figures 7 to 10 The expanded position shown moves to Figures 3 to 6 Conversely, if the deflection force component of the chord-wise airflow received at, applied to, and / or exerted on the panel 142 of the first flap 108 is less than the restoring force generated by the spring 318 of the spring-loaded axle 316, the spring 318 maintains the first flap 108 in the stowed position. Figures 7 to 10In the deployed position shown, and / or the first wing blade 108 is moved from Figures 3 to 6 The stowed position shown moves to Figures 7 to 10 Thus, the movement of the first wing blade 108 relative to the first wing 104 depends on the presence or absence of chord-wise airflow, and the relative strength (eg, force) of such airflow.

[0074] In some examples, first wing blade 108 is configured to move from Figures 7 to 10 The expanded position shown moves to Figures 3 to 6 The first wing blade 108 is also configured to be stowed from the first wing blade 108 during a slow speed operation (e.g., takeoff or landing operation) of the aircraft 100 having a second speed that is less than the first speed. Figures 3 to 6 Move the stowed position to Figures 7 to 10 For example, the spring 318 of the spring-loaded axle 316 may be configured and / or implemented to have a spring constant that generates a spring force sufficient to move the first wing blade 108 to the deployed position when the aircraft 100 is traveling at a speed less than a speed threshold (e.g., less than a cruising speed). Figures 7 to 10 When the aircraft 100 is traveling at a speed greater than or equal to the speed threshold, the restoring force generated by the spring 318 of the spring-loaded axle 316 is overcome via the deflection force, and thus, the first wing blade 108 is moved from Figures 7 to 10 The expanded position shown moves to Figures 3 to 6 Shown in stowed position.

[0075] Although the above Figures 3 to 10 The description thereof is directed to the actuator of the first wing blade 108 being implemented as a spring-loaded axle (e.g., spring-loaded axle 316) configured to cause the first wing blade 108 to move from Figures 3 to 6 The stowed position shown is offset and / or moved to Figures 7 to 10 The deployed position shown in the figure, but the actuator of the first wing blade 108 can be implemented in other forms, including, for example, electric, hydraulic, pneumatic, motor-driven and / or shape memory alloy actuators. In addition, although the above provided Figures 3 to 10 and its description is devoted to being rotatably connected to Figure 1 and Figure 2 The first wing 104 Figure 1 and Figure 2 The first wing blade 108, but the reader with knowledge of the situation will recognize that the rotatable connection to the Figure 1 and Figure 2 The second wing 106 Figure 1 and Figure 2The second wing blade 110 (e.g., in a mirrored manner about the longitudinal axis 112 of the aircraft 100). Moreover, although the above Figures 3 to 10 and its description is devoted to being rotatably coupled to Figure 1 and Figure 2 The first wing 104 Figure 1 and 2 1 , but the knowledgeable reader will recognize that any number of additional wing blades may be similarly implemented on the first wing 104 .

[0076] Fig.11 Another example aircraft 1100 is illustrated that may implement an example airflow-dependent deployable wing blade in accordance with the teachings of the present disclosure. Fig.11 Illustrated Fig.11 Examples of airflow-dependent deployable blades that are retracted, Fig.11 Example aircraft 1100 . Fig.12 Illustrated Fig.11 Examples of deployable blades that rely on airflow to deploy, Fig.11 The example aircraft 1100 is shown. The aircraft 1100 may be any form and / or type of aircraft, including, for example, a civilian (e.g., commercial or business) aircraft, a military aircraft, a manned aircraft, an unmanned aircraft (e.g., a drone), etc. Fig.11 and 12 In the illustrated example of FIG. 1 , the aircraft 1100 includes an example fuselage 1102 , a first example wing 1104 (e.g., a left wing), a second example wing 1106 (e.g., a right wing), a first example wing blade 1108 (e.g., a left wing blade), and a second example wing blade 1110 (e.g., a right wing blade). Fig.11 and Fig.12 The illustrated example depicts only a single wing blade located on each wing of aircraft 1100 (e.g., first wing blade 1108 located on first wing 1104 and second wing blade 1110 located on second wing 1106), but other example implementations may include multiple (e.g., 2, 3, 4, etc.) wing blades located on each wing of aircraft 1100. In some examples, the position, size, and / or shape of each wing blade of aircraft 1100 (e.g., first wing blade 1108 and second wing blade 1110) may be relative to each other. Fig.11 and Fig.12 The blades shown are in different locations, sizes and / or shapes.

[0077] Fig.11 and Fig.12 Fuselage 1102 of vehicle 1100 has a generally cylindrical shape that defines an example longitudinal axis 1112 of vehicle 1100 . Fig.11 and Fig.12First wing 1104 and second wing 1106 are respectively coupled to fuselage 1102 and are swept in a rearward direction of aircraft 1100. First wing 1104 includes an example skin 1114 that forms an outer surface of first wing 1104 (e.g., forms all or part thereof), and second wing 1106 includes an example skin 1116 that forms an outer surface of second wing 1106 (e.g., forms all or part thereof).

[0078] Fig.11 and Fig.12 The first airfoil 1104 defines an example spanwise direction 1118 moving from an example inboard portion 1120 of the first airfoil 1104 (e.g., inboard relative to the spanwise position of the first airfoil 1108) toward an example outboard portion 1122 of the first airfoil 1104 (e.g., outboard relative to the spanwise position of the first airfoil 1108). The spanwise direction 1118 defined by the first airfoil 1104 represents a direction of spanwise airflow that may occur along the first airfoil 1104. The first airfoil 1104 also defines an example chordwise direction 1124 moving from an example leading edge 1126 of the first airfoil 1104 toward an example trailing edge 1128 of the first airfoil 1104. The chordwise direction 1124 defined by the first airfoil 1104 represents a direction of chordwise airflow (e.g., cruising airflow) that may occur along the first airfoil 1104.

[0079] Fig.11 and Fig.12 The second airfoil 1106 of the embodiment of the present invention defines an example spanwise direction 1130 moving from an example inboard portion 1132 of the second airfoil 1106 (e.g., inboard relative to the spanwise position of the second airfoil 1110) toward an example outboard portion 1134 of the second airfoil 1106 (e.g., outboard relative to the spanwise position of the second airfoil 1110). The spanwise direction 1130 defined by the second airfoil 1106 represents a direction of spanwise airflow that may occur along the second airfoil 1106. The second airfoil 1106 also defines an example chordwise direction 1136 moving from an example leading edge 1138 of the second airfoil 1106 toward an example trailing edge 1140 of the second airfoil 1106. The chordwise direction 1136 defined by the second airfoil 1106 represents a direction of chordwise airflow (e.g., cruising airflow) that may occur along the second airfoil 1106.

[0080] Fig.11 and Fig.12 The first wing blade 1108 is rotatably connected to the first wing 1104 so that the first wing blade 1108 can be rotated. Fig.11 Stowed position shown Fig.12 The first wing blade 1108 includes an exemplary panel 1142. The panel 1142 of the first wing blade 1108 is movable (e.g., rotatable) between the deployed positions shown. Fig.11 The first wing blade 1108 extends along the skin 1114 of the first wing 1104 (e.g., in an outboard direction away from the longitudinal axis 112) when in the stowed position shown. Fig.11 When in the stowed position shown, the panel 1142 of the first wing blade 1108 extends along the skin 1114 of the first wing 1104 and is positioned above and / or on top of the skin. Fig.11 When in the stowed position shown, the panel 1142 of the first wing blade 1108 extends along the skin 1114 of the first wing 1104 and is recessed (e.g., fully or partially recessed) relative to the skin. Fig.12 When in the deployed position shown, the panel 1142 of the first wing blade 1108 extends away from the skin 1114 of the first wing 1104 at an upward angle (e.g., vertically). Fig.12 When in the deployed position shown, the panel 1142 of the first wing blade 1108 is configured to impact the airflow around the aircraft 1100. For example, when the first wing blade 1108 is in Fig.12 When in the deployed position shown, the panel 1142 can block the spanwise airflow occurring along the spanwise direction 1118 of the first wing 1104. As another example, when the first wing blade 1108 is in the Fig.12 When in the deployed position as shown, panels 1142 may initiate and / or generate vortices along first wing 1104 .

[0081] Panel 1142 and / or more generally, Fig.11 and Fig.12 The first wing blade 1108 is rotatably coupled to the Fig.11 and Fig.12 The first wing 1104. Fig.11 and Fig.12 In the illustrated example of FIG. 1 , the central axis 1146 of the axle 1144 is tilted (e.g., oriented at an angle) relative to the chordwise direction 1124 of the first wing 1104. For example, Fig.11 and Fig.12 As shown, the central axis 1146 of the axle 1144 is inclined relative to the chordwise direction 1124 of the first wing 1104 at an example toe angle 1148, so that the first end of the axle 1144 located toward the leading edge 1126 of the first wing 1104 is located further away from the longitudinal axis 1112 of the aircraft 1100 than the second end of the axle 1144 located toward the trailing edge 1128 of the first wing 1104. For clarity, the axle 1144 is exaggerated. Fig.11 and Fig.12An example rear toe angle 1148 is shown. When implemented, rear toe angle 1148 preferably has a value within a range from one to fifteen degrees.

[0082] Fig.11 and Fig.12 The first wing blade 1108 is configured to move from the panel 1142 of the first wing blade 1108 in response to the aerodynamic force applied to the panel 1142 of the first wing blade 1108. Fig.12 The expanded position shown moves to Fig.11 In some examples, the aerodynamic force can be generated via chord-wise airflow (e.g., cruising airflow) occurring along the chord-wise direction 1124 of the first wing 1104. In some examples, in response to the aerodynamic force exerted on the panel 1142 of the first flap 1108 being less than a threshold force value (e.g., less than a biasing force generated by the actuator), an actuator operatively coupled to the first flap 1108 biases and / or maintains the first flap 1108 in a stowed position. Fig.12 In the expanded position shown in . Figures 13 to 20 Example devices for implementing the actuator are discussed. In some disclosed examples, in response to an aerodynamic force applied to the panel 1142 of the first wing blade 1108 being greater than a threshold force value (e.g., greater than a biasing force generated by the actuator), the first wing blade 1108 is moved from Fig.12 The expanded position shown moves to Fig.11 In some disclosed examples, the first wing blade 1108 is configured to move from a first position to a second position during a cruise operation of the aircraft 1100 having a first speed. Fig.12 The expanded position shown moves to Fig.11 The first wing blade 1108 is further configured to be stowed from the first wing blade 1108 during a slow operation (e.g., takeoff or landing operation) of the aircraft 1100 having a second speed that is less than the first speed. Fig.11 The stowed position shown moves to Fig.12 Expanded position shown.

[0083] Fig.11 and Fig.12 The second wing blade 1110 is rotatably connected to the second wing 1106 so that the second wing blade 1110 can be rotated. Fig.11 Stowed position shown Fig.12 The second wing blade 1110 includes an exemplary panel 1150. The panel 1150 of the second wing blade 1110 is movable (e.g., rotatable) between the deployed positions shown. Fig.11 The second wing blade 1110 extends along the skin 1116 of the second wing 1106 (e.g., in an outboard direction away from the longitudinal axis 1112) when in the stowed position shown. Fig.11When in the stowed position shown, the panel 1150 of the second wing blade 1110 extends along the skin 1116 of the second wing 1106 and is positioned above and / or on top of the skin. Fig.11 When in the stowed position shown, the panel 1150 of the second wing blade 1110 extends along the skin 1116 of the second wing 1106 and is recessed (e.g., fully or partially recessed) relative to the skin. Fig.12 When in the deployed position shown, the panel 1150 of the second wing blade 1110 extends away from the skin 1116 of the second wing 1106 at an upward angle (e.g., vertically). Fig.12 When in the deployed position shown, the panel 1150 of the second wing blade 1110 is configured to impact the airflow around the aircraft 1100. For example, when the second wing blade 1110 is in Fig.12 When in the deployed position shown, the panel 1150 can block the spanwise airflow occurring along the spanwise direction 1130 of the second wing 1106. As another example, when the second wing blade 1110 is in the Fig.12 When in the deployed position shown, panel 1150 may initiate and / or generate a vortex along second wing 1106 .

[0084] Panel 1150 and / or more generally Fig.11 and Fig.12 The second wing blade 1110 is rotatably coupled to the Fig.11 and Fig.12 The second wing 1106. Fig.11 and Fig.12 In the illustrated example of FIG. 1 , the central axis 1154 of the axle 1152 is tilted (e.g., oriented at an angle) relative to the chordwise direction 1136 of the second wing 1106. For example, Fig.11 and Fig.12 As shown, the central axis 1154 of the axle 1152 is tilted at an example toe-out angle 1156 relative to the chordwise direction 1136 of the second wing 1106, such that a first end of the axle 1152 positioned toward the leading edge 1138 of the second wing 1106 is positioned further away from the longitudinal axis 1112 of the aircraft 1100 than a second end of the axle 1152 positioned toward the trailing edge 1140 of the second wing 1106. For clarity, the axle 1152 is exaggerated. Fig.11 and Fig.12 An example rear toe angle 1156 is shown. When implemented, rear toe angle 1156 preferably has a value within a range from one to fifteen degrees.

[0085] Fig.11 and Fig.12The second wing blade 1110 is configured to respond to the aerodynamic force applied to the panel 1150 of the second wing blade 1110 from Fig.12 The expanded position shown moves to Fig.11 In some examples, the aerodynamic force can be generated via chord-wise airflow (e.g., cruising airflow) occurring along the chord-wise direction 1136 of the second wing 1106. In some examples, in response to the aerodynamic force exerted on the panel 1150 of the second flap 1110 being less than a threshold force value (e.g., less than a biasing force generated by the actuator), an actuator operatively coupled to the second flap 1110 biases and / or maintains the second flap 1110 in a stowed position. Fig.12 In the expanded position shown in . Figures 13 to 20 Example devices for implementing the actuator are discussed. In some disclosed examples, in response to an aerodynamic force applied to the panel 1150 of the second winglet 1110 being greater than a threshold force value (e.g., greater than a biasing force generated by the actuator), the second winglet 1110 is moved from Fig.12 The expanded position shown moves to Fig.11 In some disclosed examples, the second wing blade 1110 is configured to move from a stowed position to a retracted position during a cruise operation of the aircraft 1100 having a first speed. Fig.12 The expanded position shown moves to Fig.11 The second wing blade 1110 is further configured to be stowed from the first wing blade 1110 during a slow operation (e.g., takeoff or landing operation) of the aircraft 1100 having a second speed that is less than the first speed. Fig.11 The stowed position shown moves to Fig.12 Expanded position shown.

[0086] Figures 13 to 20 Provided to be rotatably coupled to Fig.11 and Fig.12 The first example of wing 1104 Fig.11 and Fig.12 Additional views of the first example wing blade 1108. More specifically, Fig.13 is taken inboard and across the example center axis 1146 of the example axle 1144, Fig.11 and Fig.12 A cross-sectional view of a first example wing blade 1108, wherein the first wing blade 1108 is Fig.11 Example of a collapsed position. Fig.14 Looking backward along the example center axis 1146 of the example axle 1144 Figures 11 to 13 A front view of a first example wing blade 1108, wherein the first wing blade 1108 is in Fig.11 and Fig.13 Example of a collapsed position. Fig.15Looking backward along the example chordwise direction 1124 of the first example wing 1104 Figures 11 to 14 A front view of a first example wing blade 1108, wherein the first wing blade 1108 is in Fig.11 , Fig.13 as well as Fig.14 Example of a collapsed position. Fig.16 is in Fig.11 as well as Figures 13 to 15 Example of collapsed position Figures 11 to 15 A plan view of a first example wing blade 1108 is shown. Fig.17 is taken inboard and across the example center axis 1146 of the example axle 1144, Figures 11 to 16 A cross-sectional view of a first example wing blade 1108, wherein the first wing blade 1108 is Fig.12 Example of expanded location. Fig.18 Looking backward along the example center axis 1146 of the example axle 1144 Figures 11 to 17 A front view of a first example wing blade 1108, wherein the first wing blade 1108 is in Fig.12 and Fig.17 Example of expanded location. Fig.19 Looking backward along the example chordwise direction 1124 of the first example wing 1104 Figures 11 to 18 A front view of a first example wing blade 1108, wherein the first wing blade 1108 is in Fig.12 , Fig.17 as well as Fig.18 Example of expanded location. Fig. 20 is in Fig.12 as well as Figures 17 to 19 Example of expanded position in Figures 11 to 19 A plan view of a first example wing blade 1108 is shown.

[0087] exist Figures 13 to 20 In the illustrated example, the first wing blade 1108 is rotatably coupled to the first wing 1104 via an axle 1144. The axle 1144 includes a first example end 1302 coupled to the first wing 1104 via a first example axle mount 1304, and further includes a second example end 1306 that is positioned opposite the first end 1302 and coupled to the first wing 1104 via a second example axle mount 1308. The first end 1302 of the axle 1144 is positioned toward the leading edge 1126 of the first wing 1104 and / or toward the first axle mount 1304, and the second end 1306 of the axle 1144 is positioned toward the trailing edge 1128 of the first wing 1104 and / or the second axle mount 1308.

[0088] The first flap 1108 includes a first exemplary end 1310, a second exemplary end 1312 positioned opposite the first end 1310, and an exemplary through hole 1314 extending between the first end 1310 and the second end 1312 of the first flap 1108. The first end 1310 of the first flap 1108 is positioned toward the leading edge 1126 of the first wing 1104 and / or toward the first axle seat 1304, and the second end 1312 of the first flap 1108 is positioned toward the trailing edge 1128 of the first wing 1104 and / or the second axle seat 1308. The axle 1144 passes through and / or extends through the through hole 1314 of the first flap 1108, such that the axle 1144 and the through hole 1314 are positioned parallel and / or coaxially, and such that the first flap 1108 is fixed to the axle 1144 via the first axle seat 1304 and the second axle seat 1308. Thus, first axle mount 1304 and second axle mount 1308 secure both axle 1144 and first wing blade 1108 to first wing 1104. First wing blade 1108 can rotate about axle 1144 and can also rotate relative to first wing 1104. For example, first wing blade 1108 can rotate about axle 1144 and can rotate relative to first wing 1104. Fig.11 as well as Figures 13 to 16 Stowed position shown Fig.12 as well as Figures 17 to 20 The deployed positions are shown with respect to the first wing 1104 rotated about the axle 1144 .

[0089] exist Figures 13 to 20 In the illustrated example, the panel 1142 of the first wing blade 1108 is in the first position of the wing blade 1108 Figures 13 to 16 In the stowed position shown, the first wing 1104 extends along the skin 1114 in an outboard direction (eg, away from the longitudinal axis 1112 of the aircraft 1100). Figures 13 to 16 As shown, when the first wing blade 1108 is in the stowed position, the panel 1142 of the first wing blade 1108 extends along the skin 1114 of the first wing 1104 and is positioned above and / or on top of the skin. In other examples, when the first wing blade 1108 is in the stowed position, the panel 1142 of the first wing blade 1108 can extend along the skin 1114 of the first wing 1104 and be recessed (e.g., fully or partially recessed) relative to the skin. Figures 17 to 20 As shown, when the first wing blade 1108 is in the deployed position, the panel 1142 of the first wing blade 1108 extends away from the skin 1114 of the first wing 1104 at an upward angle (e.g., vertically). Figures 17 to 20 When in the deployed position shown, the panel 1142 of the first wing blade 1108 is configured to impact the airflow around the aircraft 1100. For example, when the first wing blade 1108 is in Figures 17 to 20When in the deployed position shown, the panel 1142 can block the spanwise airflow occurring along the spanwise direction 1118 of the first wing 1104. As another example, when the first wing blade 1108 is in the Figures 17 to 20 When in the deployed position as shown, panels 1142 may initiate and / or generate vortices along first wing 1104 .

[0090] exist Figures 13 to 20 In the illustrated example, the panel 1142 of the first wing blade 1108 is planar. In other examples, the panel 1142 of the first wing blade 1108 can be non-planar. For example, the panel 1142 of the first wing blade 1108 can have a non-planar (e.g., curved) aerodynamic shape. In some examples, the non-planar aerodynamic shape can be configured to match and / or mimic the non-planar (e.g., curved) aerodynamic shape of the first wing 1104. Figures 13 to 20 In the illustrated example, the panel 1142 of the first flap 1108 has a trapezoidal shape between the first end 1310 of the first flap 1108 and the second end 1312 of the first flap 1108. In other examples, the panel 1142 of the first flap 1108 can have a different (e.g., non-trapezoidal) shape between the first end 1310 of the first flap 1108 and the second end 1312 of the first flap 1108. For example, the panel 1142 of the first flap 1108 can have a rectangular, square, triangular, semicircular, circular, or oval shape between the first end 1310 of the first flap 1108 and the second end 1312 of the first flap 1108, as well as any one of others.

[0091] exist Figures 13 to 20 In the illustrated example, an example spring-loaded axle 1316 is formed via an axle 1144 and an example spring 1318 coiled around a portion of the axle 1144. As further described below, the spring 1318 and / or more generally the spring-loaded axle 1316 acts as an actuator and / or operates as an actuator that is configured to cause the first wing blade 1108 to move in a direction and / or strength of airflow captured by and / or received at the panel 1142 of the first wing blade 1108. Figures 13 to 16 Stowed position shown Figures 17 to 20 to move between the expanded positions shown. Figures 13 to 20 In the illustrated example of FIG. 1 , the spring 1318 of the spring-loaded axle 1316 is located between the second end 1312 of the first wing blade 1108 and the second axle seat 1308. The spring 1318 and / or more generally the spring-loaded axle 1316 is operatively coupled to the first wing blade 1108 such that the spring 1318 and / or the spring-loaded axle 1316 biases the first wing blade 1108 to the position of the second wing blade 1108. Figures 17 to 20For example, the spring 1318 of the spring-loaded axle 1316 generates a restoring force (e.g., a biasing force) having a restoring force value. In the absence of a deflection force (e.g., a counter-biasing force that may be generated via chord-wise and / or cruising airflow) that is opposite to the restoring force and has a deflection force value greater than the restoring force value, the restoring force generated by the spring 1318 causes the first wing blade 1108 to move (e.g., rotate) to Figures 17 to 20 The deployed position shown and / or maintaining the first winglet 1108 in this position.

[0092] exist Figures 13 to 20 In the illustrated example, the first wing blade 1108 is in Figures 17 to 20 Compared to the deployed position shown, when the first wing blade 1108 is in Figures 13 to 16 In the stowed position shown, the spring 1318 is in a relatively more wound state. Figures 13 to 16 Compared to the stowed position shown, when the first wing blade 1108 is in Figures 17 to 20 In the deployed position shown, the spring 1318 is in a relatively more unwound state. In other words, as the first wing blade 1108 is moved from Figures 17 to 20 The expanded position shown moves to Figures 13 to 16 In the stowed position shown, the spring 1318 is wound around the spring loaded axle 1316 and as the first wing blade 1108 is moved from Figures 13 to 16 The stowed position shown moves to Figures 17 to 20 In the deployed position shown, the spring 1318 is unwound in the opposite direction about the spring loaded axle 1316. Figures 13 to 20 In the illustrated example, the spring 1318 is implemented via one or more torsion springs. In other examples, the spring 1318 can be implemented additionally or alternatively via one or more (e.g., alone or in combination) appropriately arranged leaf springs, compression springs and / or tension springs.

[0093] The movement (e.g., rotation) of the first wing blade 1108 relative to the first wing 1104 is dependent on airflow. Fig.11 and Fig.12 Describe and Figures 13 to 20 As further shown in FIG. 1 , the central axis 1146 of the axle 1144 is tilted at a toe angle 1148 relative to the chordwise direction 1124 of the first wing 1104. Positioning and / or orienting the central axis 1146 of the axle 1144 at the toe angle 1148 causes the panel 1142 of the first wing blade 1108 to be positioned and / or oriented in a similar manner. Figures 17 to 20In the deployed position shown (e.g., as may be caused by the restoring force generated by the spring 1318 of the spring-loaded axle 1316), the panel 1142 of the first wing 1108 is positioned to capture, receive and / or react to chord-wise airflow (e.g., cruising airflow) occurring along the chord-wise direction 1124 of the first wing 1104. As a result of the inclined toe angle 1148 of the central axis 1146 of the axle 1144, the chord-wise airflow occurring along the chord-wise direction 1124 of the first wing 1104 carries a deflection force component that counteracts (e.g., resists) the restoring force generated by the spring 1318 of the spring-loaded axle 1316.

[0094] If the deflection force component of the chord-wise airflow received at, applied to and / or exerted on the panel 1142 of the first blade 1108 is greater than the restoring force generated by the spring 1318 of the spring-loaded axle 1316, the chord-wise airflow causes the first blade 1108 to move from Figures 17 to 20 The expanded position shown moves to Figures 13 to 16 Conversely, if the deflection force component of the chord-wise airflow received at, applied to, and / or exerted on the panel 1142 of the first wing blade 1108 is less than the restoring force generated by the spring 1318 of the spring-loaded axle 1316, the spring 1318 maintains the first wing blade 1108 in the stowed position. Figures 17 to 20 In the deployed position shown, and / or the first wing blade 1108 is moved from Figures 13 to 16 The stowed position shown moves to Figures 17 to 20 Thus, the movement of the first wing blade 1108 relative to the first wing 1104 depends on the presence or absence of chord-wise airflow, and the relative strength (eg, force) of such airflow.

[0095] In some examples, first wing blade 1108 is configured to move from Figures 17 to 20 The expanded position shown moves to Figures 13 to 16 The first wing blade 1108 is further configured to be stowed from the first wing blade 1108 during a slow operation (e.g., takeoff or landing operation) of the aircraft 1100 having a second speed that is less than the first speed. Figures 13 to 16 Move the stowed position to Figures 17 to 20 For example, the spring 1318 of the spring-loaded axle 1316 can be configured and / or implemented to have a spring constant that generates a spring constant sufficient to move the first wing blade 1108 to the deployed position when the aircraft 1100 is traveling at a speed less than a speed threshold (e.g., less than a cruising speed). Figures 17 to 20When the aircraft 1100 is traveling at a speed greater than or equal to the speed threshold, the restoring force generated by the spring 1318 of the spring-loaded axle 1316 is overcome by the deflection force, so that the first wing blade 1108 is moved from Figures 17 to 20 The expanded position shown moves to Figures 13 to 16 Shown in stowed position.

[0096] Although the above Figures 13 to 20 The description thereof is directed to an actuator of the first wing blade 1108 being implemented as being configured to cause the first wing blade 1108 to move from Figures 13 to 16 The stowed position shown is offset and / or moved to Figures 17 to 20 The spring-loaded axle (e.g., spring-loaded axle 1316) in the deployed position is shown, but the actuator of the first wing blade 1108 can be implemented in other forms, including, for example, electric, hydraulic, pneumatic, motor-driven and / or shape memory alloy actuators. In addition, although the above-mentioned Figures 13 to 20 and its description is devoted to being rotatably connected to Fig.11 and Fig.12 The first wing of 1104 Fig.11 and Fig.12 The first wing blade 1108 of the embodiment of the present invention, but the reader with knowledge of the situation will recognize that the rotatable connection to the Fig.11 and Fig.12 The second wing 1106 Fig.11 and Fig.12 The second wing blade 1110 (e.g., in a mirrored manner around the longitudinal axis 1112 of the aircraft 1100). Moreover, although the above Figures 13 to 20 and its description is devoted to being rotatably coupled to Fig.11 and Fig.12 The first wing of 1104 Fig.11 and 12 1108 , but the knowledgeable reader will recognize that any number of additional wing blades may be similarly implemented on first wing 1104 .

[0097] Fig.21 Another example aircraft 2100 is illustrated that may implement an example airflow-dependent deployable wing blade in accordance with the teachings of the present disclosure. Fig.21 Illustrated Fig.21 Examples of airflow-dependent deployable blades that are retracted, Fig.21 Example aircraft 2100 . Fig. 22 Illustrated Fig.21 Examples of deployable blades that rely on airflow to deploy, Fig.212100. Aircraft 2200 may be any form and / or type of aircraft, including, for example, a civilian (e.g., commercial or business) aircraft, a military aircraft, a manned aircraft, an unmanned aircraft (e.g., a drone), etc. Fig.21 and 22 In the illustrated example of FIG. 2 , aircraft 2100 includes an example fuselage 2102 , a first example wing 2104 (e.g., a left wing), a second example wing 2106 (e.g., a right wing), a first example wing blade 2108 (e.g., a left wing blade), and a second example wing blade 2110 (e.g., a right wing blade). Fig.21 and Fig. 22 The illustrated example depicts only a single wing blade located on each wing of aircraft 2100 (e.g., first wing blade 2108 located on first wing 2104 and second wing blade 2110 located on second wing 2106), but other example implementations may include multiple (e.g., 2, 3, 4, etc.) wing blades located on each wing of aircraft 2100. In some examples, the position, size, and / or shape of each wing blade of aircraft 2100 (e.g., first wing blade 2108 and second wing blade 2110) may be relative to the position, size, and / or shape of each wing blade of aircraft 2100. Fig.21 and Fig. 22 The blades shown are in different locations, sizes and / or shapes.

[0098] Fig.21 and Fig. 22 The fuselage 2102 has a generally cylindrical shape that defines an example longitudinal axis 2112 of the aircraft 2100 . Fig.21 and Fig. 22 The first wing 2104 and the second wing 2106 are respectively coupled to the fuselage 2102 and swept in a rearward direction of the aircraft 2100. The first wing 2104 includes an example skin 2114 that forms an outer surface of the first wing 2104 (e.g., forming all or part thereof), and the second wing 2106 includes an example skin 2116 that forms an outer surface of the second wing 2106 (e.g., forming all or part thereof).

[0099] Fig.21 and Fig. 22The first airfoil 2104 of the embodiment of the present invention defines an example spanwise direction 2118 moving from an example inboard portion 2120 of the first airfoil 2104 (e.g., inboard relative to the spanwise position of the first airfoil 2108) toward an example outboard portion 2122 of the first airfoil 2104 (e.g., outboard relative to the spanwise position of the first airfoil 2108). The spanwise direction 2118 defined by the first airfoil 2104 represents a direction of spanwise airflow that may occur along the first airfoil 2104. The first airfoil 2104 also defines an example chordwise direction 2124 moving from an example leading edge 2126 of the first airfoil 2104 toward an example trailing edge 2128 of the first airfoil 2104. The chordwise direction 2124 defined by the first airfoil 2104 represents a direction of cruising airflow that may occur along the first airfoil 2104.

[0100] Fig.21 and Fig. 22 The second airfoil 2106 of the embodiment of the present invention defines an example spanwise direction 2130 moving from an example inboard portion 2132 of the second airfoil 2106 (e.g., inboard relative to the spanwise position of the second airfoil 2110) toward an example outboard portion 2134 of the second airfoil 2106 (e.g., outboard relative to the spanwise position of the second airfoil 2110). The spanwise direction 2130 defined by the second airfoil 2106 represents a direction of spanwise airflow that may occur along the second airfoil 2106. The second airfoil 2106 also defines an example chordwise direction 2136 moving from an example leading edge 2138 of the second airfoil 2106 toward an example trailing edge 2140 of the second airfoil 2106. The chordwise direction 2136 defined by the second airfoil 2106 represents a direction of cruising airflow that may occur along the second airfoil 2106.

[0101] Fig.21 and Fig. 22 The first wing blade 2108 is rotatably connected to the first wing 2104 so that the first wing blade 2108 can be rotated. Fig.21 Stowed position shown Fig. 22 The first wing blade 2108 includes an exemplary panel 2142. The panel 2142 of the first wing blade 2108 is movable (e.g., rotatable) between the deployed positions shown. Fig.21 When in the stowed position shown, the first wing blade 2108 extends along the skin 2114 of the first wing 2104 (e.g., in an inboard direction toward the longitudinal axis 2112). In some examples, when the first wing blade 2108 is in the stowed position, the first wing blade 2108 extends along the skin 2114 of the first wing 2104 (e.g., in an inboard direction toward the longitudinal axis Fig.21 When in the stowed position shown, the panel 2142 of the first wing blade 2108 extends along the skin 2114 of the first wing 2104 and is positioned above and / or on top of the skin. Fig.21When in the stowed position shown, the panel 2142 of the first wing blade 2108 extends along the skin 2114 of the first wing 2104 and is recessed (e.g., fully or partially recessed) relative to the skin. Fig. 22 When in the deployed position shown, the panel 2142 of the first wing blade 2108 extends away from the skin 2114 of the first wing 2104 at an upward angle (e.g., vertically). Fig. 22 When in the deployed position shown, the panel 2142 of the first wing blade 2108 is configured to impact the airflow around the aircraft 2100. For example, when the first wing blade 2108 is in Fig. 22 When in the deployed position shown, the panel 2142 can block the spanwise airflow occurring along the spanwise direction 2118 of the first wing 2104. As another example, when the first wing blade 2108 is in the Fig. 22 When in the deployed position as shown, panels 2142 may initiate and / or generate vortices along first wing 2104 .

[0102] The first wing blade 2108 also includes an example deployable blade 2144. Fig.21 and Fig. 22 In the illustrated example, the deployed blade 2144 of the first winglet 2108 is orthogonal to the panel 2142 of the first winglet 2108. In other examples, the deployed blade 2144 of the first winglet 2108 can be oriented at a non-orthogonal angle relative to the panel 2142 of the first winglet 2108. For example, the deployed blade 2144 of the first winglet 2108 can be oriented at an angle between forty-five degrees and one hundred and thirty-five degrees relative to the panel 2142 of the first winglet 2108. The deployed blade 2144 of the first winglet 2108 is orthogonal to the panel 2142 of the first winglet 2108 when the winglet 2108 is in the Fig. 22 When in the deployed position shown, the first wing blade 2108 extends along the skin 2114 of the first wing 2104 (e.g., in an outboard direction away from the longitudinal axis 2112). In some examples, when the first wing blade 2108 is in Fig. 22 When in the deployed position shown, the deployed blade 2144 of the first wing blade 2108 extends along the skin 2114 of the first wing 2104 and is positioned above and / or on top of the skin. Fig. 22 When in the deployed position shown, the deployed blade 2144 of the first wing blade 2108 extends along the skin 2114 of the first wing 2104 and is recessed (e.g., fully or partially recessed) relative to the skin. Fig.21 When in the stowed position shown, the deployed blades 2144 of the first wing blade 2108 extend at an upward angle (e.g., vertically) away from the skin 2114 of the first wing 2104. The deployed blades 2144 of the first wing blade 2108 are configured to be in the stowed position when the first wing blade 2108 is in the stowed position. Fig.21 In the stowed position shown, the first wing 2104 is configured to capture, receive, and / or react to spanwise airflow occurring along the spanwise direction 2118 of the first wing 2104 .

[0103] Panel 2144 and unfolded leaves 2144 and / or more generally, for Fig.21 and Fig. 22 The first wing blade 2108 is rotatably coupled to the Fig.21 and Fig. 22 The first wing of 2104. Fig.21 and Fig. 22 In the illustrated example, the central axis 2148 of the axle 2146 is parallel to the chordwise direction 2124 of the first wing 2104. In other examples, the central axis 2148 of the axle 2146 can be tilted relative to the chordwise direction 2124 of the first wing 2104 (e.g., at a toe angle or a toe angle). Fig.21 and Fig. 22 The first wing blade 2108 is configured to respond to the aerodynamic force applied to the deployed blade 2144 of the first wing blade 2108 from Fig.21 The stowed position shown moves to Fig. 22 In some examples, the aerodynamic force can be generated via a spanwise airflow occurring along the spanwise direction 2118 of the first wing 2104. In some disclosed examples, in response to the aerodynamic force exerted on the deployed blade 2144 of the first flap 2108 being less than a threshold force value (e.g., less than a biasing force generated by the actuator), an actuator operatively coupled to the first flap 2108 biases and / or maintains the first flap 2108 in the deployed position. Fig.21 In the stowed position shown in . Figure 23 to Figure 28 Example devices for implementing the actuator are discussed. In some disclosed examples, in response to an aerodynamic force applied to the deployed blade 2144 of the first winglet 2108 being greater than a threshold force value (e.g., greater than a bias force generated by the actuator), the first winglet 2108 is moved from Fig.21 The stowed position shown moves to Fig. 22 Expanded position shown.

[0104] Fig.21 and Fig. 22 The second wing blade 2110 is rotatably connected to the second wing 2106 so that the second wing blade 2110 can be rotated. Fig.21 Stowed position shown Fig. 22 The second wing blade 2110 includes an example panel 2150. The panel 2150 of the second wing blade 2110 is movable (e.g., rotatable) between the deployed positions shown. Fig.21When in the stowed position shown, the second wing blade 2110 extends along the skin 2116 of the second wing 2106 (e.g., in an inboard direction toward the longitudinal axis 2112). In some examples, when the second wing blade 2110 is in the stowed position, the second wing blade 2110 extends along the skin 2116 of the second wing 2106 (e.g., in an inboard direction toward the longitudinal axis Fig.21 When in the stowed position shown, the panel 2150 of the second wing blade 2110 extends along the skin 2116 of the second wing 2106 and is positioned above and / or on top of the skin. In other examples, when the second wing blade 2110 is in Fig.21 When in the stowed position shown, the panel 2150 of the second wing blade 2110 extends along the skin 2116 of the second wing 2106 and is recessed (e.g., fully or partially recessed) relative to the skin. Fig. 22 When in the deployed position shown, the panel 2150 of the second wing blade 2110 extends away from the skin 2116 of the second wing 2106 at an upward angle (e.g., vertically). Fig. 22 When in the deployed position shown, the panel 2150 of the second wing blade 2110 is configured to impact the airflow around the aircraft 2100. For example, when the second wing blade 2110 is in Fig. 22 When in the deployed position shown, the panel 2150 can block the spanwise airflow occurring along the spanwise direction 2130 of the second wing 2106. As another example, when the second wing blade 2110 is in Fig. 22 When in the deployed position shown, panel 2150 may initiate and / or generate vortices along second wing 2106 .

[0105] The second wing blade 2110 also includes an example deployable blade 2152. Fig.21 and Fig. 22 In the illustrated example, the deployed blade 2152 of the second winglet 2110 is orthogonal to the panel 2150 of the second winglet 2110. In other examples, the deployed blade 2152 of the second winglet 2110 can be oriented at a non-orthogonal angle relative to the panel 2150 of the second winglet 2110. For example, the deployed blade 2152 of the second winglet 2110 can be oriented at an angle between forty-five degrees and one hundred and thirty-five degrees relative to the panel 2150 of the second winglet 2110. The deployed blade 2152 of the second winglet 2110 is orthogonal to the panel 2150 of the second winglet 2110 when the winglet 2110 is in the Fig. 22 The second wing blade 2106 extends along the skin 2116 of the second wing 2106 (e.g., in an outboard direction away from the longitudinal axis 2112) when in the deployed position shown. In some examples, when the second wing blade 2110 is in Fig. 22 When in the deployed position shown, the deployed blade 2152 of the second wing blade 2110 extends along the skin 2116 of the second wing 2106 and is positioned above and / or on top of the skin. In other examples, when the second wing blade 2110 is in Fig. 22When in the deployed position shown, the deployed blade 2152 of the second wing blade 2110 extends along the skin 2116 of the second wing 2106 and is recessed (e.g., fully or partially recessed) relative to the skin. Fig.21 When in the stowed position shown, the deployed blades 2152 of the second wing blade 2110 extend at an upward angle (e.g., vertically) away from the skin 2116 of the second wing 2106. The deployed blades 2152 of the second wing blade 2110 are configured to be in the stowed position when the second wing blade 2110 is in the stowed position. Fig.21 In the stowed position shown, the second wing 2106 is configured to capture, receive and / or react to spanwise airflow occurring along the spanwise direction 2130 of the second wing 2106 .

[0106] Panel 2150 and unfolded leaves 2152 and / or more generally, Fig.21 and Fig. 22 The second wing blade 2110 is rotatably coupled to the Fig.21 and Fig. 22 The second wing 2106. Fig.21 and Fig. 22 In the illustrated example, the central axis 2156 of the axle 2154 is parallel to the chordwise direction 2136 of the second wing 2106. In other examples, the central axis 2156 of the axle 2154 can be tilted relative to the chordwise direction 2136 of the second wing 2106 (e.g., at a toe angle or a toe angle). Fig.21 and Fig. 22 The second wing blade 2110 is configured to respond to the aerodynamic force applied to the deployed blade 2152 of the second wing blade 2110 from Fig.21 The stowed position shown moves to Fig. 22 In some examples, the aerodynamic force can be generated via a spanwise airflow occurring along the spanwise direction 2130 of the second wing 2106. In some disclosed examples, in response to the aerodynamic force exerted on the deployed blade 2152 of the second flap 2110 being less than a threshold force value (e.g., less than a biasing force generated by the actuator), an actuator operatively coupled to the second flap 2110 biases and / or maintains the second flap 2110 in a spanwise direction 2130. Fig.21 In the stowed position shown in . Figure 23 to Figure 28 Example devices for implementing the actuator are discussed. In some disclosed examples, in response to an aerodynamic force applied to the deployed blade 2152 of the second winglet 2110 being greater than a threshold force value (e.g., greater than a bias force generated by the actuator), the second winglet 2110 is moved from Fig.11 The stowed position shown moves to Fig. 22 Expanded position shown.

[0107] Figure 23 to Figure 28 Provided to be rotatably coupled to Fig.21 and Fig. 22 The first example of wing 2104 Fig.21 and Fig. 22 Additional views of the first example wing blade 2108. More specifically, Fig.23 is taken inboard and across the example center axis 2148 of the example axle 2146, Fig.21 and Fig. 22 A cross-sectional view of a first example wing blade 2108, wherein the first wing blade 2108 is in Fig.21 Example of a collapsed position. Fig.14 Looking backward along the example center axis 2148 of the example axle 2146 Figure 21 to Figure 23 A front view of a first example wing blade 2108, wherein the first wing blade 2108 is in Fig.21 and Fig.23 Example of a collapsed position. Fig.25 is in Fig.21 , Fig.23 as well as Fig.24 Example of collapsed position Figure 21 to Figure 24 A plan view of a first example wing blade 2108. Fig.26 is taken inboard and across the example center axis 2148 of the example axle 2146, Figure 21 to Figure 25 A cross-sectional view of a first example wing blade 2108, wherein the first wing blade 2108 is in Fig. 22 Example of expanded location. Fig. 27 Looking backward along the example center axis 2148 of the example axle 2146 Figure 21 to Figure 26 A front view of a first example wing blade 2108, wherein the first wing blade 2108 is in Fig. 22 and Fig.26 Example of expanded location. Fig.28 is in Fig. 22 , Fig.26 as well as Fig. 27 Example of expanded position in Figure 21 to Figure 27 A plan view of a first example wing blade 2108.

[0108] exist Figure 23 to Figure 28In the illustrated example of FIG. 2 , the first wing blade 2108 is rotatably coupled to the first wing 2104 via an axle 2146. The axle 2146 includes a first example end 2302 coupled to the first wing 2104 via a first example axle mount 2304, and further includes a second example end 2306 that is positioned opposite the first end 2302 and is coupled to the first wing 2104 via a second example axle mount 2308. The first end 2302 of the axle 2146 is positioned toward the leading edge 2126 of the first wing 2104 and / or toward the first axle mount 2304, and the second end 2306 of the axle 2146 is positioned toward the trailing edge 2128 of the first wing 2104 and / or the second axle mount 2308.

[0109] The first winglet 2108 includes a first exemplary end 2310, a second exemplary end 2312 positioned opposite the first end 2310, and an exemplary through hole 2314 extending between the first end 2310 and the second end 2312 of the first winglet 2108. The first end 2310 of the first winglet 2108 is positioned toward the leading edge 2126 of the first wing 2104 and / or toward the first axle seat 2304, and the second end 2312 of the first winglet 2108 is positioned toward the trailing edge 2128 of the first wing 2104 and / or the second axle seat 2308. The axle 2146 passes through and / or extends through the through hole 2314 of the first winglet 2108, such that the axle 2146 and the through hole 2314 are positioned parallel and / or coaxially, and such that the first winglet 2108 is fixed to the axle 2146 via the first axle seat 2304 and the second axle seat 2308. Thus, first axle mount 2304 and second axle mount 2308 secure both axle 2146 and first wing blade 2108 to first wing 2104. First wing blade 2108 can rotate about axle 2146 and can also rotate relative to first wing 2104. For example, first wing blade 2108 can rotate about axle 2146. Fig.21 as well as Figure 23 to Figure 25 Stowed position shown Fig. 22 as well as Figure 26 to Figure 28 The deployed positions are shown with respect to the first wing 2104 rotated about the axle 2146 .

[0110] exist Figure 23 to Figure 28 In the illustrated example, the panel 2142 of the first wing blade 2108 is in the first position of the wing blade 2108 Figure 23 to Figure 25 In the stowed position shown, the skin 2114 along the first wing 2104 extends in an inboard direction (eg, toward the longitudinal axis 2112 of the aircraft 2100). Figure 23 to Figure 25As shown, when the first wing blade 2108 is in the stowed position, the panel 2142 of the first wing blade 2108 extends along the skin 2114 of the first wing 2104 and is positioned above and / or on top of the skin. In other examples, when the first wing blade 2108 is in the stowed position, the panel 2142 of the first wing blade 2108 can extend along the skin 2114 of the first wing 2104 and be recessed (e.g., fully or partially recessed) relative to the skin. Figure 26 to Figure 28 As shown, when the first wing blade 2108 is in the deployed position, the panel 2142 of the first wing blade 2108 extends away from the skin 2114 of the first wing 2104 at an upward angle (e.g., vertically). Figure 26 to Figure 28 When in the deployed position shown, the panel 2142 of the first wing blade 2108 is configured to impact the airflow around the aircraft 2100. For example, when the first wing blade 2108 is in Figure 26 to Figure 28 When in the deployed position shown, the panel 2142 can block the spanwise airflow occurring along the spanwise direction 2118 of the first wing 2104. As another example, when the first wing blade 2108 is in the Figure 26 to Figure 28 When in the deployed position as shown, panels 2142 may initiate and / or generate vortices along first wing 2104 .

[0111] exist Figure 23 to Figure 28 In the illustrated example, the panel 2142 of the first wing blade 2108 is planar. In other examples, the panel 2142 of the first wing blade 2108 can be non-planar. For example, the panel 2142 of the first wing blade 2108 can have a non-planar (e.g., curved) aerodynamic shape. In some examples, the non-planar aerodynamic shape can be configured to match and / or mimic the non-planar (e.g., curved) aerodynamic shape of the first wing 2104. Figure 23 to Figure 28 In the illustrated example, the panel 2142 of the first flap 2108 has a trapezoidal shape between the first end 2310 of the first flap 2108 and the second end 2312 of the first flap 2108. In other examples, the panel 2142 of the first flap 2108 can have a different (e.g., non-trapezoidal) shape between the first end 2310 of the first flap 2108 and the second end 2312 of the first flap 2108. For example, the panel 2142 of the first flap 2108 can have a rectangular, square, triangular, semicircular, circular, or oval shape between the first end 2310 of the first flap 2108 and the second end 2312 of the first flap 2108, as well as any one of others.

[0112] exist Figure 23 to Figure 28 In the illustrated example, the expanded blade 2144 of the first wing blade 2108 is in the first position of the wing blade 2108. Figure 26 to Figure 28In the deployed position shown, the skin 2114 along the first wing 2104 extends in an outboard direction (eg, away from the longitudinal axis 2112 of the aircraft 2100). Figure 26 to Figure 28 As shown, when the first wing blade 2108 is in the deployed position, the deployed blade 2144 of the first wing blade 2108 extends along the skin 2114 of the first wing 2104 and is positioned above and / or on top of the skin. In other examples, when the first wing blade 2108 is in the deployed position, the deployed blade 2144 of the first wing blade 2108 can extend along the skin 2114 of the first wing 2104 and be recessed (e.g., completely or partially recessed) relative to the skin. Figure 23 to Figure 25 As shown, when the first wing blade 2108 is in the stowed position, the deployed blade 2144 of the first wing blade 2108 extends away from the skin 2114 of the first wing 2104 at an upward angle (e.g., vertically). The deployed blade 2144 of the first wing blade 2108 is configured to be in the first wing blade 2108. Figure 23 to Figure 25 In the stowed position shown, the first wing 2104 is configured to capture, receive, and / or react to spanwise airflow that may occur along the spanwise direction 2118 of the first wing 2104 .

[0113] exist Figure 23 to Figure 28 In the illustrated example, the deployed blades 2144 of the first wing blade 2108 are planar. In other examples, the deployed blades 2144 of the first wing blade 2108 can be non-planar. For example, the deployed blades 2144 of the first wing blade 2108 can have a non-planar (e.g., curved) aerodynamic shape. In some examples, the non-planar aerodynamic shape can be configured to match and / or mimic the non-planar (e.g., curved) aerodynamic shape of the first wing 2104. Figure 23 to Figure 28 In the illustrated example, the deployed blade 2144 of the first wing blade 2108 has a trapezoidal shape between the first end 2310 of the first wing blade 2108 and the second end 2312 of the first wing blade 2108. In other examples, the deployed blade 2144 of the first wing blade 2108 may have a different (e.g., non-trapezoidal) shape between the first end 2310 of the first wing blade 2108 and the second end 2312 of the first wing blade 2108. For example, the deployed blade 2144 of the first wing blade 2108 may have a rectangular, square, triangular, semicircular, circular, or elliptical shape, as well as any one of others, between the first end 2310 of the first wing blade 2108 and the second end 2312 of the first wing blade 2108. Figure 23 to Figure 28 In the illustrated example, the size of the deployed blade 2144 of the first wing blade 2108 is smaller than the size of the panel 2142 of the first wing blade 2108. In other examples, the size of the deployed blade 2144 of the first wing blade 2108 can be smaller than or equal to the size of the panel 2142 of the first wing blade 2108.

[0114] exist Figure 23 to Figure 28 In the illustrated example, the example spring-loaded axle 2316 is formed via the axle 2146 and the example spring 2318 coiled around a portion of the axle 2146. As further described below, the spring 2318 and / or more generally the spring-loaded axle 2316 acts as an actuator and / or operates as an actuator that is configured to move the first wing blade 2108 in a direction and / or strength of airflow captured by and / or received at the deployed blade 2144 of the first wing blade 2108. Figure 23 to Figure 25 Stowed position shown Figure 26 to Figure 28 to move between the expanded positions shown. Figure 23 to Figure 28 In the illustrated example of FIG. 1 , the spring 2318 of the spring-loaded axle 2316 is located between the second end 2312 of the first wing blade 2108 and the second axle seat 2308. The spring 2318 and / or more generally the spring-loaded axle 2316 is operatively coupled to the first wing blade 2108 such that the spring 2318 and / or the spring-loaded axle 2316 biases the first wing blade 2108 to the position of the second wing blade 2108. Figure 23 to Figure 25 For example, the spring 2318 of the spring-loaded axle 2316 generates a restoring force (e.g., a biasing force) having a restoring force value. In the absence of a deflection force (e.g., a counter-biasing force that can be generated by the airflow in the span direction) that is opposite to the restoring force and has a deflection force value greater than the restoring force value, the restoring force generated by the spring 2318 causes the first wing blade 2108 to move (e.g., rotate) to the stowed position. Figure 23 to Figure 25 The stowed position shown and / or the first wing blade 2108 is maintained in this position.

[0115] exist Figure 23 to Figure 28 In the illustrated example, the first wing blade 2108 is in Figure 23 to Figure 25 Compared to the stowed position shown, when the first wing blade 2108 is in Figure 26 to Figure 28 In the extended position shown, the spring 2318 is in a relatively more wound state. Figure 26 to Figure 28 Compared to the deployed position shown, when the first wing blade 2108 is in Figure 23 to Figure 25 In the stowed position shown, the spring 2318 is in a relatively more unwound state. In other words, as the first wing blade 2108 is moved from Figure 23 to Figure 25 The stowed position shown moves to Figure 26 to Figure 28 In the deployed position shown, the spring 2318 is wound around the spring loaded axle 2316 and as the first wing blade 2108 is moved from Figure 26 to Figure 28 The expanded position shown moves to Figure 23 to Figure 25 In the stowed position shown, the spring 2318 is unwound in the opposite direction around the spring loaded axle 2316. Figure 23 to Figure 28In the illustrated example, the spring 2318 is implemented via one or more torsion springs. In other examples, the spring 2318 can be implemented additionally or alternatively via one or more (e.g., alone or in combination) appropriately arranged leaf springs, compression springs and / or tension springs.

[0116] The movement (e.g., rotation) of the first wing blade 2108 relative to the first wing 2104 is dependent on airflow. Fig.21 and Fig. 22 Describe and Figure 23 to Figure 28 As further shown in FIG. 2 , the central axis 2148 of the axle 2146 is parallel to the chordwise direction 2124 of the first wing 2104. The central axis 2148 of the axle 2146 is positioned and / or oriented in this way so that the panel 2142 and the deployed blades 2144 of the first wing blade 2108 are positioned and / or oriented in a similar manner. The deployed blades 2144 of the first wing blade 2108 are orthogonal relative to the panel 2142 of the first wing blade 2108. When the first wing blade 2108 is in Figure 23 to Figure 25 In the stowed position shown (e.g., as may be caused by the restoring force generated by the spring 2318 of the spring-loaded axle 2316), the deployed blades 2144 of the first wing 2108 are positioned to capture, receive and / or react to the spanwise airflow occurring along the spanwise direction 2118 of the first wing 2104. The spanwise airflow occurring along the spanwise direction 2118 of the first wing 2104 carries a deflection force component that counteracts (e.g., resists) the restoring force generated by the spring 2318 of the spring-loaded axle 2316.

[0117] If the deflection force component of the spanwise airflow received at the deployed blade 2144 of the first wing blade 2108, applied to and / or exerted on the deployed blade is greater than the restoring force generated by the spring 2318 of the spring-loaded axle 2316, the spanwise airflow causes the first wing blade 2108 to move from Figure 23 to Figure 25 The stowed position shown moves to Figure 26 to Figure 28 Conversely, if the deflection force component of the spanwise airflow received at the deployed blade 2144 of the first wing blade 2108, applied to and / or exerted on the deployed blade is less than the restoring force generated by the spring 2318 of the spring-loaded axle 2316, the spring 2318 maintains the first wing blade 2108 in the deployed position. Figure 23 to Figure 25 and / or causing the first wing blade 2108 to be moved from the stowed position shown in FIG. Figure 26 to Figure 28 The expanded position shown moves to Figure 23 to Figure 25 Thus, the movement of the first wing blade 2108 relative to the first wing 2104 depends on the presence or absence of airflow in the span direction, and the relative strength (eg, force) of such airflow.

[0118] Although the above Figure 23 to Figure 28The description thereof is devoted to the actuator of the first wing blade 2108 being implemented as: being configured to cause the first wing blade 2108 to move from Figure 26 to Figure 28 The deployed position shown is offset and / or moved to Figure 23 to Figure 25 The spring-loaded axle (e.g., spring-loaded axle 2316) in the stowed position is shown, but the actuator of the first wing blade 2108 can be implemented in other forms, including, for example, electric, hydraulic, pneumatic, motor-driven and / or shape memory alloy actuators. In addition, although the above-mentioned Figure 23 to Figure 28 and its description is devoted to being rotatably connected to Fig.21 and Fig. 22 The first wing of 2104 Fig.21 and Fig. 22 The first wing blade 2108, but the reader with knowledge of the situation will recognize that the rotatable connection to the Fig.21 and Fig. 22 The second wing of 2106 Fig.21 and Fig. 22 The second wing blade 2110 (e.g., in a mirrored manner around the longitudinal axis 2112 of the aircraft 2100). Moreover, although the above Figure 23 to Figure 28 and its description is devoted to being rotatably coupled to Fig.21 and Fig. 22 The first wing of 2104 Fig.21 and 22 2108 , but the knowledgeable reader will recognize that any number of additional wing blades may be similarly implemented on first wing 2104 .

[0119] In some examples, the above components (e.g. Figures 1 to 10 The first wing blade 108, the axle 144, the first axle seat 304, the second axle seat 308 and / or the spring 318, Figures 11 to 20 The first wing blade 1108, the axle 1144, the first axle seat 1304, the second axle seat 1308 and / or the spring 1318, Figures 21 to 28 Two or more of the first wing blade 2108, the axle 2146, the first axle seat 2304, the second axle seat 2308 and / or the spring 2318, etc., can be manufactured as a single piece, formed of an elastic material such as a carbon fiber composite material or a 3D printed plastic, and structured or configured to generate an elastic restoring force. For example, Fig.29 Another example aircraft 2900 is illustrated that may implement an example airflow-dependent deployable wing blade in accordance with the teachings of the present disclosure. Fig.29 Illustrated Fig.29 Examples of airflow-dependent deployable blades that are retracted, Fig.29 Example aircraft 2900 . Fig.30 Illustrated Fig.29 Examples of deployable blades that rely on airflow to deploy, Fig.29 2900. Aircraft 2900 may be any form and / or type of aircraft, including, for example, a civilian (e.g., commercial or business) aircraft, a military aircraft, a manned aircraft, an unmanned aircraft (e.g., a drone), etc. Fig.29 and 30 In the illustrated example of FIG. 2 , aircraft 2900 includes an example fuselage 2902 , a first example wing 2904 (e.g., a left wing), a second example wing 2906 (e.g., a right wing), a first example wing blade 2908 (e.g., a left wing blade), and a second example wing blade 2910 (e.g., a right wing blade). Fig.29 and Fig.30 The illustrated example depicts only a single wing blade located on each wing of aircraft 2900 (e.g., first wing blade 2908 located on first wing 2904 and second wing blade 2910 located on second wing 2906), but other example implementations may include multiple (e.g., 2, 3, 4, etc.) wing blades located on each wing of aircraft 2900. In some examples, the position, size, and / or shape of each wing blade of aircraft 2900 (e.g., first wing blade 2908 and second wing blade 2910) may be relative to the position, size, and / or shape of each wing blade of aircraft 2900. Fig.29 and Fig.30 The blades shown are in different locations, sizes and / or shapes.

[0120] Fig.29 and Fig.30 The fuselage 2902 has a generally cylindrical shape that defines an example longitudinal axis 2912 of the aircraft 2900 . Fig.29 and Fig.30 First wing 2904 and second wing 2906 are respectively coupled to fuselage 2902 and swept in a rearward direction of aircraft 2900. First wing 2904 includes an example skin 2914 that forms an outer surface of first wing 2904 (e.g., forms all or part thereof), and second wing 2906 includes an example skin 2916 that forms an outer surface of second wing 2906 (e.g., forms all or part thereof).

[0121] Fig.29 and Fig.30The first airfoil 2904 of the embodiment defines an example spanwise direction 2918 moving from an example inboard portion 2920 of the first airfoil 2904 (e.g., inboard relative to the spanwise position of the first airfoil 2908) toward an example outboard portion 2922 of the first airfoil 2904 (e.g., outboard relative to the spanwise position of the first airfoil 2908). The spanwise direction 2918 defined by the first airfoil 2904 represents a direction of spanwise airflow that may occur along the first airfoil 2904. The first airfoil 2904 also defines an example chordwise direction 2924 moving from an example leading edge 2926 of the first airfoil 2904 toward an example trailing edge 2928 of the first airfoil 2904. The chordwise direction 2924 defined by the first airfoil 2904 represents a direction of chordwise airflow (e.g., cruising airflow) that may occur along the first airfoil 2904.

[0122] Fig.29 and Fig.30 The second airfoil 2906 of the embodiment of the present invention defines an example spanwise direction 2930 moving from an example inboard portion 2932 of the second airfoil 2906 (e.g., inboard relative to the spanwise position of the second airfoil 2910) toward an example outboard portion 2934 of the second airfoil 2906 (e.g., outboard relative to the spanwise position of the second airfoil 2910). The spanwise direction 2930 defined by the second airfoil 2906 represents the direction of spanwise airflow that may occur along the second airfoil 2906. The second airfoil 2906 also defines an example chordwise direction 2936 moving from an example leading edge 2938 of the second airfoil 2906 toward an example trailing edge 2940 of the second airfoil 2906. The chordwise direction 2936 defined by the second airfoil 2906 represents the direction of chordwise airflow (e.g., cruising airflow) that may occur along the second airfoil 2906.

[0123] Fig.29 and Fig.30 The first wing blade 2908 includes an example base 2942, an example panel 2944, and an example living hinge 2946 extending between the base 2942 and the panel 2944. The base 2942 of the first wing blade 2908 is coupled (e.g., fixedly or non-movably coupled) to the first wing 2904 of the aircraft 2900. The base 2942 has an example central axis 2948. Fig.29 and Fig.30 In the illustrated example, the central axis 2948 of the base 2942 is inclined (e.g., oriented at an angle) relative to the chordwise direction 2924 of the first wing 2904. Fig.29 and Fig.30As shown, the central axis 2948 of the base 2942 is inclined relative to the chord-wise direction 2924 of the first wing 2904 at an example toe angle 2950, ​​so that the first end of the base 2942 positioned toward the leading edge 2926 of the first wing 2904 is positioned closer to the longitudinal axis 2912 of the aircraft 2900 than the second end of the base 2942 positioned toward the trailing edge 2928 of the first wing 2904. For clarity, the center axis 2948 of the base 2942 is exaggerated. Fig.29 and Fig.30 Example toe angle 2950 is shown. When implemented, toe angle 2950 preferably has a value in the range from one to fifteen degrees.

[0124] The panel 2944 of the first wing blade 2908 is connected to the base 2942 of the first wing blade 2908 via the movable hinge 2946 of the first wing blade 2908, so that the panel 2944 can be Fig.29 Stowed position shown Fig.30 The panel 2944 of the first wing blade 2908 is movable (e.g., rotatable) relative to the base 2942 and / or relative to the first wing 2904 between the deployed positions shown. Fig.29 When in the stowed position shown, the first wing blade 2908 extends along the skin 2914 of the first wing 2904 (e.g., in an inboard direction toward the longitudinal axis 2912). In some examples, when the first wing blade 2908 is in the stowed position, the first wing blade 2908 extends along the skin 2914 of the first wing 2904 (e.g., in an inboard direction toward the longitudinal axis Fig.29 When in the stowed position shown, the panel 2944 of the first wing blade 2908 extends along the skin 2914 of the first wing 2904 and is positioned above and / or on top of the skin. Fig.29 When in the stowed position shown, the panel 2944 of the first wing 2908 extends along the skin 2914 of the first wing 2904 and is recessed (eg, fully or partially recessed) relative to the skin.

[0125] When the first wing blade 2908 is in Fig.30 When in the deployed position shown, the panel 2944 of the first wing blade 2908 extends away from the skin 2914 of the first wing 2904 at an upward angle (e.g., vertically). Fig.30 When in the deployed position shown, the panel 2944 of the first wing blade 2908 is configured to impact the airflow around the aircraft 2900. For example, when the first wing blade 2908 is in Fig.30 When in the deployed position shown, the panel 2944 can block the spanwise airflow occurring along the spanwise direction 2918 of the first wing 2904. As another example, when the first wing blade 2908 is in the Fig.30 When in the deployed position shown, panel 2944 may initiate and / or generate vortices along first wing 2904 .

[0126] The living hinge 2946 of the first wing blade 2908 extends between the base 2942 of the first wing blade 2908 and the panel 2944 of the first wing blade 2908. In some examples, the thickness of the living hinge 2946 is less than the thickness of the base 2942 and / or less than the thickness of the panel 2944. The living hinge 2946 of the first wing blade 2908 is flexible and allows Fig.29 and Fig.30 The panel 2944 of the first wing blade 2908 can and / or enable the panel to Fig.29 Stowed position shown Fig.30 to move between the expanded positions shown. Fig.29 and Fig.30 In the illustrated example, the movable hinge 2946 of the first wing blade 2908 biases the panel 2944 of the first wing blade 2908 to Fig.30 Expanded position shown.

[0127] Fig.29 and Fig.30 The panel 2944 of the first wing blade 2908 is configured to move from the panel 2944 of the first wing blade 2908 in response to an aerodynamic force applied to the panel 2944 of the first wing blade 2908. Fig.30 The expanded position shown moves to Fig.29 In some examples, the aerodynamic force can be generated via chord-wise airflow (e.g., cruising airflow) occurring along the chord-wise direction 2924 of the first wing 2904. In some examples, in response to the aerodynamic force applied to the panel 2944 of the first flap 2908 being less than a threshold force value (e.g., less than the biasing force generated by the living hinge 2946), the living hinge 2946 of the first flap 2908 biases and / or maintains the panel 2944 of the first flap 2908 in the stowed position. Fig.30 In some disclosed examples, in response to an aerodynamic force applied to the panel 2944 of the first wing blade 2908 being greater than a threshold force value (e.g., greater than the biasing force generated by the living hinge 2946), the panel 2944 of the first wing blade 2908 is moved from Fig.30 The expanded position shown moves to Fig.29 Shown in stowed position.

[0128] In some disclosed examples, the panel 2944 of the first wing blade 2908 is configured to move from the first wing blade 2908 to the second wing blade 2908 during cruise operation of the aircraft 2900 having a first speed. Fig.30 The expanded position shown moves to Fig.29 The panel 2944 of the first wing blade 2908 is further configured to be stowed from the first wing blade 2908 during a slow operation (e.g., takeoff or landing operation) of the aircraft 2900 having a second speed that is less than the first speed. Fig.29 The stowed position shown moves to Fig.30 Expanded position shown.

[0129] Fig.29 and Fig.30 The second wing blade 2910 includes an example base 2952, an example panel 2954, and an example living hinge 2956 extending between the base 2952 and the panel 2954. The base 2952 of the second wing blade 2910 is coupled (e.g., fixedly or non-movably coupled) to the second wing 2906 of the aircraft 2900. The base 2952 has an example central axis 2958. Fig.29 and Fig.30 In the illustrated example of FIG. 29 , the central axis 2958 of the base 2952 is inclined (e.g., oriented at an angle) relative to the chordwise direction 2936 of the second wing 2906. For example, Fig.29 and Fig.30 As shown, the central axis 2958 of the base 2952 is inclined relative to the chordwise direction 2936 of the second wing 2906 at an example toe angle 2960, so that the first end of the base 2952 positioned toward the leading edge 2938 of the second wing 2906 is positioned closer to the longitudinal axis 2912 of the aircraft 2900 than the second end of the base 2952 positioned toward the trailing edge 2940 of the second wing 2906. For clarity, the center axis 2958 of the base 2952 is exaggerated. Fig.29 and Fig.30 Example toe angle 2960 is shown. When implemented, toe angle 2960 preferably has a value in the range from one to fifteen degrees.

[0130] The panel 2954 of the second wing blade 2910 is connected to the base 2952 of the second wing blade 2910 via the movable hinge 2956 of the second wing blade 2910 so that the panel 2954 can be moved Fig.29 Stowed position shown Fig.30 The panel 2954 of the second wing blade 2910 is movable (e.g., rotatable) relative to the base 2952 and / or relative to the second wing 2906 between the deployed positions shown. Fig.29 When in the stowed position shown, the second wing blade 2910 extends along the skin 2916 of the second wing 2906 (e.g., in an inboard direction toward the longitudinal axis 2912). In some examples, when the second wing blade 2910 is in Fig.29 When in the stowed position shown, the panel 2954 of the second wing blade 2910 extends along the skin 2916 of the second wing 2906 and is positioned above and / or on top of the skin. In other examples, when the second wing blade 2910 is in Fig.29 When in the stowed position shown, the panel 2954 of the second wing blade 2910 extends along the skin 2916 of the second wing 2906 and is recessed (eg, fully or partially recessed) relative to the skin.

[0131] When the second wing blade 2910 is in Fig.30 When in the deployed position shown, the panel 2954 of the second wing blade 2910 extends away from the skin 2916 of the second wing 2906 at an upward angle (e.g., vertically). Fig.30 When in the deployed position shown, the panel 2954 of the second wing blade 2910 is configured to impact the airflow around the aircraft 2900. For example, when the second wing blade 2910 is in Fig.30 When in the deployed position shown, the panel 2954 can block the spanwise airflow occurring along the spanwise direction 2930 of the second wing 2906. As another example, when the second wing blade 2910 is in Fig.30 When in the deployed position shown, panel 2954 may initiate and / or generate vortices along second wing 2906 .

[0132] The living hinge 2956 of the second wing blade 2910 extends between the base 2952 of the second wing blade 2910 and the panel 2954 of the second wing blade 2910. In some examples, the thickness of the living hinge 2956 is less than the thickness of the base 2952 and / or less than the thickness of the panel 2954. The living hinge 2956 of the second wing blade 2910 is flexible and allows Fig.29 and Fig.30 The panel 2954 of the second wing blade 2910 can and / or enable the panel to Fig.29 Stowed position shown Fig.30 to move between the expanded positions shown. Fig.29 and Fig.30 In the illustrated example, the movable hinge 2946 of the second wing blade 2910 biases the panel 2954 of the second wing blade 2910 to Fig.30 Expanded position shown.

[0133] Fig.29 and Fig.30 The panel 2954 of the second wing blade 2910 is configured to respond to the aerodynamic force applied to the panel 2954 of the second wing blade 2910 from Fig.30 The expanded position shown moves to Fig.29 In some examples, the aerodynamic force can be generated via chord-wise airflow (e.g., cruising airflow) occurring along the chord-wise direction 2936 of the second wing 2906. In some examples, in response to the aerodynamic force applied to the panel 2954 of the second flap 2910 being less than a threshold force value (e.g., less than the biasing force generated by the living hinge 2956), the living hinge 2956 of the second flap 2910 biases and / or maintains the panel 2954 of the second flap 2910 in the stowed position. Fig.30In some disclosed examples, in response to an aerodynamic force applied to the panel 2954 of the second wing blade 2910 being greater than a threshold force value (e.g., greater than the biasing force generated by the living hinge 2956), the panel 2954 of the second wing blade 2910 is moved from Fig.30 The expanded position shown moves to Fig.29 Shown in stowed position.

[0134] In some disclosed examples, the panel 2954 of the second wing blade 2910 is configured to move from the first speed to the second speed during cruise operation of the aircraft 2900. Fig.30 The expanded position shown moves to Fig.29 The panel 2954 of the second wing blade 2910 is also configured to be stowed from the first wing blade 2910 during a slow operation (e.g., takeoff or landing operation) of the aircraft 2900 having a second speed that is less than the first speed. Fig.29 The stowed position shown moves to Fig.30 Expanded position shown.

[0135] Figure 31 to Figure 36 Provides connection to Fig.29 and Fig.30 The first example of wing 2904 Fig.29 and Fig.30 Additional views of the first example wing blade 2908. More specifically, Fig.31 is taken inwardly and across the example central axis 2948 of the example base 2942, Fig.29 and Fig.30 A cross-sectional view of a first example wing blade 2908, wherein the first wing blade 2908 is in Fig.29 Example of a collapsed position. Fig.32 Looking backward along the example central axis 2948 of the example base 2942 Figure 29 to Figure 31 A front view of a first example wing blade 2908, wherein the first wing blade 2908 is in Fig.29 and Fig.31 Example of a collapsed position. Fig.33 is in Fig.29 , Fig.31 as well as Fig.32 Example of collapsed position Figure 29 to Figure 32 A plan view of a first example wing blade 2908. Fig.34 is taken inwardly and across the example central axis 2948 of the example base 2942, Figure 29 to Figure 33 A cross-sectional view of a first example wing blade 2908, wherein the first wing blade 2908 is in Fig.30 Example of expanded location. Fig.35 Looking backward along the example central axis 2948 of the example base 2942 Figures 29 to 34A front view of a first example wing blade 2908, wherein the first wing blade 2908 is in Fig.30 and Fig.34 Example of expanded location. Fig.36 is in Fig.30 , Fig.34 as well as Fig.35 Example of expanded position in Figure 29 to Figure 35 A plan view of a first example wing blade 2908.

[0136] exist Figure 31 to Figure 36 In the illustrated example of FIG. 29, the base 2942 of the first wing blade 2908 is coupled (e.g., fixedly or non-movably coupled) to the first wing 2904 of the aircraft 2900. For example, the base 2942 of the first wing blade 2908 can be coupled to the first wing 2904 via one or more fasteners, which can include one or more mechanical fasteners (e.g., rivets, screws, bolts, pins, etc.) and / or one or more chemical fasteners (e.g., glue, epoxy, adhesive, etc.) and / or any combination thereof. The base 2942 of the first wing blade 2908 includes a first example end 3102, and also includes a second example end 3104 positioned opposite the first end 3102. The first end 3102 of the base 2942 is positioned toward the leading edge 2926 of the first wing 2904, and the second end 3104 of the base 2942 is positioned toward the trailing edge 2928 of the first wing 2904.

[0137] exist Figure 31 to Figure 36 In the illustrated example, the panel 2944 of the first wing blade 2908 is in the first position of the wing blade 2908. Figure 31 to Figure 33 In the stowed position shown, the skin 2914 along the first wing 2904 extends in an inboard direction (eg, toward the longitudinal axis 2912 of the aircraft 2900). Figure 31 to Figure 33 As shown, when the first wing blade 2908 is in the stowed position, the panel 2944 of the first wing blade 2908 extends along the skin 2914 of the first wing 2904 and is positioned above and / or on top of the skin. In other examples, when the first wing blade 2908 is in the stowed position, the panel 2944 of the first wing blade 2908 can extend along the skin 2914 of the first wing 2904 and be recessed (e.g., fully or partially recessed) relative to the skin. Figure 34 to Figure 36 As shown, when the first wing blade 2908 is in the deployed position, the panel 2944 of the first wing blade 2908 extends away from the skin 2914 of the first wing 2904 at an upward angle (e.g., vertically). Figure 34 to Figure 36 When in the deployed position shown, the panel 2944 of the first wing blade 2908 is configured to impact the airflow around the aircraft 2900. For example, when the first wing blade 2908 is in Figure 34 to Figure 36When in the deployed position shown, the panel 2944 can block the spanwise airflow occurring along the spanwise direction 2918 of the first wing 2904. As another example, when the first wing blade 2908 is in the Figure 34 to Figure 36 When in the deployed position shown, panel 2944 may initiate and / or generate vortices along first wing 2904 .

[0138] exist Figure 31 to Figure 36 In the illustrated example, the panel 2944 of the first wing blade 2908 is planar. In other examples, the panel 2944 of the first wing blade 2908 can be non-planar. For example, the panel 2944 of the first wing blade 2908 can have a non-planar (e.g., curved) aerodynamic shape. In some examples, the non-planar aerodynamic shape can be configured to match and / or mimic the non-planar (e.g., curved) aerodynamic shape of the first wing 2904. Figure 31 to Figure 36 In the illustrated example, the panel 2944 of the first wing blade 2908 has a trapezoidal shape between the first end 3102 of the base 2942 and the second end 3104 of the base 2942. In other examples, the panel 2944 of the first wing blade 2908 may have a different (e.g., non-trapezoidal) shape between the first end 3102 of the base 2942 and the second end 3104 of the base 2942. For example, the panel 2944 of the first wing blade 2908 may have a rectangular, square, triangular, semicircular, circular, or oval shape between the first end 3102 of the base 2942 and the second end 3104 of the base 2942, as well as any of other shapes.

[0139] exist Figure 31 to Figure 36 In the illustrated example, the movable hinge 2946 of the first wing blade 2908 acts and / or operates as an actuator, which is configured to move the panel 2944 of the first wing blade 2908 in a direction and / or intensity of the airflow captured by the panel 2944 of the first wing blade 2908 and / or received by the panel 2944 thereof. Figure 31 to Figure 33 Stowed position shown Figure 34 to Figure 36 The movable hinge 2946 of the first wing blade 2908 extends between the base 2942 of the first wing blade 2908 and the panel 2944 of the first wing blade 2908. Fig.32 and Fig.35 As shown, the thickness of the active hinge 2946 is less than the thickness of the base 2942 and less than the thickness of the panel 2944. The active hinge 2946 of the first wing blade 2908 is flexible and enables the panel 2944 of the first wing blade 2908 to and / or allows the panel to be moved when Figure 31 to Figure 33 Stowed position shown Figure 34 to Figure 36 between the expanded positions shown.

[0140] exist Figure 31 to Figure 36 In the illustrated example, the movable hinge 2946 of the first wing blade 2908 biases the panel 2944 of the first wing blade 2908 to Figure 34 to Figure 36 For example, the movable hinge 2946 generates a restoring force (e.g., a biasing force) having a restoring force value. In the absence of a deflection force (e.g., a counter-biasing force that may be generated via chord-wise and / or cruising airflow) that is opposite to the restoring force and has a deflection force value greater than the restoring force value, the restoring force generated via the movable hinge 2946 causes the panel 2944 of the first wing blade 2908 to move (e.g., rotate) to Figure 34 to Figure 36 The deployed position shown and / or maintaining the panel 2944 of the first wing 2908 in this position.

[0141] exist Figure 31 to Figure 36 In the illustrated example, the panel 2944 of the first wing blade 2908 is in Figure 34 to Figure 36 Compared to the deployed position shown, when the panel 2944 of the first wing blade 2908 is in Figure 31 to Figure 33 When in the stowed position shown, the movable hinge 2946 is in a relatively less flexed and / or bent state. In contrast, the panel 2944 with the first wing blade 2908 is in a relatively more flexed and / or bent state. Figure 31 to Figure 33 Compared to the stowed position shown, when the panel 2944 of the first wing blade 2908 is in Figure 34 to Figure 36 In the expanded position shown, the active hinge 2946 is in a relatively more flexed and / or bent state. In other words, as the panel 2944 of the first wing blade 2908 is moved from Figure 31 to Figure 33 The stowed position shown moves to Figure 34 to Figure 36 In the deployed position shown, the living hinge 2946 is flexed, bent and / or curled away from the skin 2914 of the first wing 2904 and as the panel 2944 of the first wing blade 2908 is moved from Figure 34 to Figure 36 The expanded position shown moves to Figure 31 to Figure 33 In the stowed position shown, the living hinge 2946 is loosened, straightened, and / or extended toward the skin 2914 of the first wing 2904 .

[0142] The movement (e.g., rotation) of the panel 2944 of the first wing 2908 relative to the base 2942 of the first wing 2908 via the living hinge 2946 of the first wing 2908 (e.g., the movement causes the panel 2944 to move relative to the first wing 2904) is dependent on airflow. Fig.29 and Fig.30 Describe and Figure 31 to Figure 36As further shown in FIG. 2 , the central axis 2948 of the base 2942 of the first wing 2908 is inclined relative to the chordwise direction 2924 of the first wing 2904 at a toe angle 2950. Positioning and / or orienting the central axis 2948 of the base 2942 at the toe angle 2950 causes the panel 2944 of the first wing 2908 to be positioned and / or oriented in a similar manner. Figure 34 to Figure 36 In the deployed position shown (e.g., as may be caused by the restoring force generated by the living hinge 2946 of the first wing 2908), the panel 2944 of the first wing 2908 is positioned to capture, receive and / or react to chord-wise airflow (e.g., cruising airflow) occurring along the chord-wise direction 2924 of the first wing 2904. As a result of the toe angle 2950 at which the central axis 2948 of the base 2942 is inclined, the chord-wise airflow occurring along the chord-wise direction 2924 of the first wing 2904 carries a deflection force component that counteracts (e.g., resists) the restoring force generated by the living hinge 2946 of the first wing 2908.

[0143] If the deflection force component of the chord-wise airflow received at the panel 2944 of the first flap 2908, applied to and / or exerted on the panel 142 is greater than the restoring force generated by the living hinge 2946 of the first flap 2908, the chord-wise airflow causes the panel 2944 of the first flap 2908 to move from Figure 34 to Figure 36 The expanded position shown moves to Figure 31 to Figure 33 Conversely, if the deflection force component of the chord-wise airflow received at the panel 2944 of the first flap 2908 and applied to and / or exerted on the panel 142 is less than the restoring force generated by the active hinge 2946 of the first flap 2908, the active hinge 2946 maintains the panel 2944 of the first flap 2908 in the stowed position. Figure 34 to Figure 36 and / or causing the panel 2944 of the first wing blade 2908 to be moved from the Figure 31 to Figure 33 The stowed position shown moves to Figure 34 to Figure 36 Thus, movement of the panel 2944 of the first winglet 2908 relative to the base 2942 of the first winglet 2908 and / or relative to the first wing 2904 depends on the presence or absence of chord-wise airflow, and the relative strength (eg, force) of such airflow.

[0144] In some examples, the panel 2944 of the first wing blade 2908 is configured to move from Figure 34 to Figure 36 The expanded position shown moves to Figure 31 to Figure 33 The panel 2944 of the first wing blade 2908 is further configured to be stowed from the first wing blade 2908 during a slow operation (e.g., takeoff or landing operation) of the aircraft 2900 having a second speed that is less than the first speed. Figure 31 to Figure 33 Move the stowed position to Figure 34 to Figure 36 For example, the active hinge 2946 of the first wing blade 2908 can be configured and / or implemented to have a flexing, bending, and / or curling moment that causes the active hinge 2946 to generate a sufficient force to move the panel 2944 of the first wing blade 2908 to the deployed position when the aircraft 2900 is traveling at a speed less than a speed threshold (e.g., less than a cruising speed). Figure 34 to Figure 36 When the aircraft 2900 is traveling at a speed greater than or equal to the speed threshold, the restoring force generated by the living hinge 2946 of the first wing blade 2908 is overcome by the deflection force, so that the panel 2944 of the first wing blade 2908 is moved from Figure 34 to Figure 36 The expanded position shown moves to Figure 31 to Figure 33 Shown in stowed position.

[0145] Although the above Figure 31 to Figure 36 The description thereof is directed to an actuator of the first wing blade 2908 being implemented as being configured to cause the panel 2944 of the first wing blade 2908 to move from Figure 31 to Figure 33 The stowed position shown is offset and / or moved to Figure 34 to Figure 36 The active hinge (e.g., active hinge 2946) in the deployed position is shown, but the actuator of the first wing blade 2908 can be implemented in other forms, including, for example, electric, hydraulic, pneumatic, motor-driven and / or shape memory alloy actuators. In addition, although the above-mentioned Figure 31 to Figure 36 and its description is dedicated to connecting to Fig.29 and Fig.30 The first wing of 2904 Fig.29 and Fig.30 The first wing blade 2908 of the embodiment of the present invention, but the reader with knowledge of the situation will recognize that the connection to the Fig.29 and Fig.30 The second wing of 2906 Fig.29 and Fig.30 The second wing blade 2910 (e.g., in a mirrored manner around the longitudinal axis 2912 of the aircraft 2900). Moreover, although the above Figure 31 to Figure 36 and its description is dedicated to connecting to Fig.29 and Fig.30 The first wing of 2904 Fig.29 and 30 The first wing blade 2908 is shown, but the knowledgeable reader will recognize that any number of additional wing blades can be similarly implemented on the first wing 2904. Moreover, although the above provided Figures 29 to 36 and its description is disclosed Figures 29 to 36 The first wing blade 2908 is generally consistent with and / or corresponds to Figures 1 to 10The first wing blade 108 is implemented and / or constructed in a manner associated with the structure and / or orientation, but the informed reader will also recognize that Figures 29 to 36 The first wing blade 2908 may alternatively be arranged to conform to and / or correspond to Figures 11 to 20 The first wing knife 1108 or Figures 21 to 28 The first wing blade 2108 is implemented and / or constructed in an associated structure and / or orientation manner.

[0146] In some examples, any of the above-mentioned wing blades (e.g. Figures 1 to 10 The first wing knife 108, Figures 11 to 20 The first wing knife 1108, Figures 21 to 28 The first wing knife 2108, Figures 29 to 36 The first wing blade 2908, etc.) is implemented as follows: A wing blade having a single flat panel may in some cases become problematic with respect to retracting the wing blade along the skin of the aircraft wing, especially when the wing is a curved wing with considerable curvature. For example, Fig.37 3706. The curved wing 3706 has an example chord 3708 moving from an example leading edge 3710 of the curved wing 3706 toward an example trailing edge 3712 of the curved wing 3706. The planar panel 3704 is oriented at an example angle 3714 relative to the chord 3708. The planar panel 3704 includes a first example end 3716 positioned toward the leading edge 3710 of the curved wing 3706, a second example end 3718 opposite the first end 3716 and positioned toward the trailing edge 3712 of the curved wing 3706, and an example intermediate portion 3720 located between the first and second ends 3716, 3718 of the planar panel 3704.

[0147] like Fig.37 As shown, although the middle portion 3720 of the planar panel 3704 is adjacent to the curved wing 3706 when the wing blade 3702 is in the stowed position, the curvature of the curved wing 3706 prevents the first and second ends 3716, 3718 of the planar panel 3704 from being adjacent to the curved wing 3706. Fig.37 The illustrated spacing and / or spacing between the curved wings 3706 may result in an undesirable loss of aerodynamic performance (e.g., drag) when the wing blades 3702 are in the stowed position. In some examples, this undesirable loss of aerodynamic performance may be achieved by alternatively placing Fig.37 The wing blade 3702 is implemented as a wing blade having multiple planar panels to advantageously reduce.

[0148] For example, Fig.383802 having a plurality of example planar panels 3804 each positioned in a corresponding example stowed position relative to an example curved wing 3806. The curved wing 3806 has an example chord 3808 moving from an example leading edge 3810 of the curved wing 3806 toward an example trailing edge 3812 of the curved wing 3806. Fig.38 In the illustrated example, the planar panels 3804 of the wing blade 3802 include a first example planar panel 3814, a second example planar panel 3816, a third example planar panel 3818, a fourth example planar panel 3820, and a fifth example planar panel 3822. In other examples, the wing blade 3802 may include a different number of planar panels (e.g., 2, 3, 4, 6, 8, 10, etc.).

[0149] Fig.38 The first planar panel 3814 is oriented at a first example angle 3824 relative to the chord 3808. Fig.38 The second planar panel 3816 is located behind the first planar panel 3814 and is oriented at a second example angle 3826 relative to the chord 3808. Fig.38 The third planar panel 3818 is located behind the second planar panel 3816 and is oriented at a third example angle 3828 relative to the chord 3808. Fig.38 The fourth planar panel 3820 is located behind the third planar panel 3818 and is oriented at a fourth example angle 3830 relative to the chord 3808. Fig.38 The fifth planar panel 3822 is located behind the fourth planar panel 3820 and is oriented at a fifth example angle 3832 relative to the chord 3808.

[0150] exist Fig.38 In the illustrated example, some or all of the first, second, third, fourth, and fifth angles 3824, 3826, 3828, 3830, 3832 are different from each other, and the different angles correspond to and / or are determined based on the respective local curvatures of the skin of the curved wing 3806 adjacent to the respective positions of the first, second, third, fourth, and fifth planar panels 3814, 3816, 3818, 3820, 3822. Therefore, when the first, second, third, fourth, and fifth planar panels 3814, 3816, 3818, 3820, 3822 are in their respective stowed positions, the first, second, third, fourth, and fifth planar panels 3814, 3816, 3818, 3820, 3822 collectively match and / or mimic the overall curvature of the curved wing 3806. For example, Fig.38 Each of the first, second, third, fourth and fifth planar panels 3814, 3816, 3818, 3820, 3822 is different from the above-mentioned Fig.37The curved airfoils 3706 exhibit a smaller spacing with the curved airfoils 3806 than the spacing exhibited by the single planar panel 3704. This reduced spacing in turn reduces the undesirable aerodynamic performance loss that may be associated with implementing a wing blade with a single planar panel.

[0151] Fig.39 yes Fig.38 A cross-sectional view of an example wing blade 3802 having a Fig.38 The example curved wing 3806 of the example plane panels 3804 (e.g., first, second, third, fourth, and fifth plane panels 3814, 3816, 3818, 3820, 3822) are respectively positioned in corresponding example deployed positions. The first, second, third, fourth, and fifth plane panels 3814, 3816, 3818, 3820, 3822 of the wing blade 3802 are individually and collectively configured to be in a state where the wing blade 3802 is in a deployed position. Fig.39 When in the deployed position, the airflow is along the span direction of the curved wing 3806. Fig.38 and Fig.39 In the illustrated example, each of the first, second, third, fourth, and fifth planar panels 3814, 3816, 3818, 3820, 3822 of the wing blade 3802 can be individually movable and / or actuatable. For example, each of the first, second, third, fourth, and fifth planar panels 3814, 3816, 3818, 3820, 3822 of the wing blade 3802 can be operatively coupled to a separate corresponding spring-loaded axle. The knowledgeable reader will recognize that each of the corresponding spring-loaded axles can use any of the above-described spring-loaded axles (e.g., Figures 3 to 10 Spring loaded axle 316, Figures 13 to 20 Spring loaded axle 1316, Figure 23 to Figure 28 As another example, each of the first, second, third, fourth, and fifth planar panels 3814, 3816, 3818, 3820, 3822 of the wing blade 3802 may be operatively coupled to a separate corresponding living hinge and / or base. The knowledgeable reader will recognize that the Figures 29 to 36 The above-mentioned movable hinge 2946 and / or base 2942 are used to implement each of the corresponding movable hinges and / or bases.

[0152] In some examples, any of the above panels and / or more generally any of the above blades (e.g. Figures 1 to 10 The first wing knife 108, Figures 11 to 20 The first wing knife 1108, Figures 21 to 28 The first wing knife 2108, Figures 29 to 36 The first wing knife 2908, Fig.38 and Fig.39 The first wing blade 3802, etc.) can be implemented such that when the wing blade is in its stowed position, the panel and / or wing blade extends along the surrounding skin of the wing and is recessed (e.g., completely or partially recessed) relative to the skin. Fig.40 4002 having a plurality of example panels 4004 positioned in corresponding example recessed stowed positions relative to an example wing 4006. The wing 4006 includes an example support structure 4008 (e.g., a spar) located between an example leading edge 4010 and an example trailing edge 4012 of the wing 4006. Fig.40 In the illustrated example of FIG. 4 , the panels 4004 of the wing blade 4002 include a first example panel 4014, a second example panel 4016, a third example panel 4018, and a fourth example panel 4020. The first panel 4014 is located in front of the support structure 4008. The second panel 4016 is located behind the first panel 4014 and in front of the support structure 4008. The third panel 4018 is located behind the second panel 4016 and behind the support structure 4008. The fourth panel 4020 is located behind the third panel 4018 and behind the support structure 4008. In other examples, the wing blade 4002 can include a different number of panels (e.g., 2, 3, 5, 6, 8, 10, etc.), and the panels can be arranged at different positions relative to the support structure 4008.

[0153] like Fig.40 As shown, each of the first, second, third, and fourth panels 4014, 4016, 4018, 4020 has a respective stowed position in which the panel of the flap 4002 is recessed into the wing 4006 (e.g., recessed relative to the skin of the wing 4006). In some examples, each of the first, second, third, and fourth panels 4014, 4016, 4018, 4020 can be recessed into the wing 4006, respectively, so that the panel and any axle, axle seat, spring, living hinge, and / or base coupled to the panel and / or more generally coupled to the flap 4002 are recessed (e.g., fully or partially recessed) relative to the surrounding skin of the wing 4006 when the flap 4002 is in its stowed position. When the flap 4002 is stowed, recessing such components into the wing 4006 can further reduce the drag associated with the flap 4002.

[0154] Fig.41 yes Fig.40 A cross-sectional view of an example wing blade 4002 having a Fig.40 The example wings 4006 are positioned in a plurality of example panels 4004 in corresponding example deployed positions. Fig.41As shown, each of the first, second, third, and fourth panels 4014, 4016, 4018, 4020 has a respective deployed position in which the panel of the wing blade 4002 extends upward from the wing 4006 (e.g., extends upward relative to the skin of the wing 4006). Fig.40 and Fig.41 The wing blade 4002 may also include a non-recessed panel positioned above the support structure 4008 of the wing 4006. In yet another example, Fig.40 and Fig.41 The wing blade 4002 may additionally or alternatively include one or more non-recessed panels located at the leading edge 4010 and / or the trailing edge 4012 of the wing 4006.

[0155] From the foregoing, it will be understood that an example airflow-dependent deployable wing blade for an aircraft wing has been disclosed. Different from the above-mentioned traditional wing blade and / or other countermeasures, the example deployable wing blade disclosed herein is aerodynamically initiated and / or airflow-dependent. In some disclosed examples, the deployable wing blade is connected (e.g., rotatably connected) to the aircraft wing so that the wing blade can be advantageously moved relative to the wing between a stowed position and an extended position, in which the panel of the wing blade extends along the skin of the wing, and in the extended position, the panel extends away from the skin at an upward angle. The panel is configured to hinder the airflow around the aircraft when the wing blade is in the extended position. For example, the panel can hinder the airflow along the spanwise direction of the wing when the wing blade is in the extended position. As another example, the panel can initiate and / or generate vortices along the wing when the wing blade is in the extended position. The wing blade is advantageously configured to move between a stowed position and an extended position in response to the aerodynamic force applied to the wing blade. In some disclosed examples, the wing blade is configured to move from a deployed position to a stowed position in response to an aerodynamic force applied to the panel. In other disclosed examples, the wing blade is configured to move from a stowed position to a deployed position in response to an aerodynamic force applied to a deployed blade of the wing blade.

[0156] The deployable wing blades of the example disclosed herein that rely on airflow provide a large number of advantages that exceed the above-mentioned traditional wing blades. For example, the mobility (e.g., movement from the deployed position to the stowed position) of the deployable wing blades that rely on airflow disclosed herein advantageously reduces the loss (e.g., drag) of undesirable aerodynamic performance during the high-speed operation of the aircraft (e.g., during cruising). As another example, the deployable wing blades that rely on airflow disclosed herein provide a stowed position for the wing blade, whereby the wing blade extends along the skin of the wing (contrary to the vertical in the wing), thereby advantageously increasing the amount of unused space in the wing relative to the amount of space that can be consumed by the mechanical linkage in the wing in other ways, and these linkages are associated with the above-mentioned number of vertically deployable traditional wing blades. As another example, the deployable wing blades that rely on airflow disclosed herein promote the non-pilot operation (e.g., deployment and retraction) of the wing blade, which advantageously ensures that the wing blade is deployed and / or retracted at the appropriate time and / or under appropriate flight conditions.

[0157] In some examples, a device is disclosed. In some disclosed examples, the device includes a wing blade connected to an aircraft wing. In some disclosed examples, the wing blade can be moved relative to the wing between a stowed position and a deployed position, in which the panel of the wing blade extends along the skin of the wing, and in the deployed position, the panel extends away from the skin at an upward angle. In some disclosed examples, the panel is configured to hinder the airflow along the span direction of the wing when the wing blade is in the deployed position. In some disclosed examples, the wing blade is configured to move from the deployed position to the stowed position in response to an aerodynamic force applied to the panel.

[0158] In some disclosed examples, the panels are further configured to generate vortices along the wing when the blades are in the deployed position.

[0159] In some disclosed examples, the apparatus further includes an actuator configured to move the wing from the stowed position to the deployed position.

[0160] In some disclosed examples, the actuator is configured to move the flap from the stowed position to the deployed position in response to an aerodynamic force being less than a threshold force value.

[0161] In some disclosed examples, the wing blade is configured to move from the deployed position to the stowed position during a cruise operation of the aircraft having a first speed. In some disclosed examples, the wing blade is also configured to move from the stowed position to the deployed position during a slow speed operation of the aircraft having a second speed less than the first speed.

[0162] In some disclosed examples, the actuator includes a spring-loaded axle operatively coupled to the wing blade and mounted to the wing. In some disclosed examples, the spring-loaded axle includes an axle and a spring coiled around the axle.

[0163] In some disclosed examples, the spring is configured to wind around the axle in response to the aerodynamic force being greater than a threshold force value. In some disclosed examples, the spring is further configured to unwind around the axle in response to the aerodynamic force being less than the threshold force value.

[0164] In some disclosed examples, the axle has a central axis that is tilted relative to the chord-wise direction of the wing.

[0165] In some disclosed examples, the central axis is inclined at a toe angle relative to a chordwise direction of the wing. In some disclosed examples, when the blade is in the stowed position, the panel extends in an inboard direction away from the central axis.

[0166] In some disclosed examples, the central axis is inclined at a toe angle relative to a chordwise direction of the wing. In some disclosed examples, when the blade is in the stowed position, the panel extends in an outboard direction away from the central axis.

[0167] In some disclosed examples, the panel is recessed within the wing when the blades are in the stowed position.

[0168] In some disclosed examples, the panel includes a first panel positioned adjacent to a first portion of the skin. In some disclosed examples, the first portion of the skin has a first orientation relative to the chord of the wing. In some disclosed examples, the first panel is configured to be oriented along the first portion of the skin when the wing blade is in the stowed position. In some disclosed examples, the panel also includes a second panel, which is located behind the first panel and adjacent to the second portion of the skin located behind the first portion. In some disclosed examples, the second portion of the skin has a second orientation relative to the chord of the wing, and the second orientation is different from the first orientation. In some disclosed examples, the second panel is configured to be oriented along the second portion of the skin when the wing blade is in the stowed position. In some disclosed examples, the first panel and the second panel are configured to hinder the airflow along the span direction of the wing when the wing blade is in the deployed position.

[0169] In some examples, a method for moving a wing blade connected to an aircraft wing is disclosed. In some disclosed examples, the method includes the following steps: moving the wing blade between a stowed position and a deployed position, in which a panel of the wing blade extends along the skin of the wing, and in the deployed position, the panel extends away from the skin at an upward angle. In some disclosed examples, the panel obstructs airflow along the span direction of the wing when the wing blade is in the deployed position. In some disclosed examples, the movement includes moving the wing blade from the deployed position to the stowed position in response to an aerodynamic force applied to the panel.

[0170] In some disclosed examples, the panels generate vortices along the wing when the blades are in the deployed position.

[0171] In some disclosed examples, aerodynamic forces are generated via a substantially chord-wise airflow along a chord-wise direction of the wing.

[0172] In some disclosed examples, the blade is rotatably coupled to the wing via an axle having a central axis that is inclined relative to a chord-wise direction of the wing.

[0173] In some disclosed examples, the central axis is inclined at a toe angle relative to a chordwise direction of the wing. In some disclosed examples, when the blade is in the stowed position, the panel extends in an inboard direction away from the central axis.

[0174] In some disclosed examples, the central axis is inclined at a toe angle relative to a chordwise direction of the wing. In some disclosed examples, when the blade is in the stowed position, the panel extends in an outboard direction away from the central axis.

[0175] In some examples, a device is disclosed. In some disclosed examples, the device includes a wing blade connected to an aircraft wing. In some disclosed examples, the wing blade can be moved relative to the wing between a stowed position and an extended position, in which the panel of the wing blade extends along the skin of the wing, and in the extended position, the panel extends away from the skin at an upward angle. In some disclosed examples, the panel is configured to hinder the airflow along the span direction of the wing when the wing blade is in the extended position. In some disclosed examples, the wing blade is configured to move from the stowed position to the extended position in response to the aerodynamic force applied to the extended blade of the wing blade.

[0176] In some disclosed examples, the deployed blades are generally normal to the panel.

[0177] In some disclosed examples, the panels are further configured to generate vortices along the wing when the blades are in the deployed position.

[0178] In some disclosed examples, the apparatus further includes an actuator configured to move the wing from the deployed position to the stowed position.

[0179] In some disclosed examples, the actuator is configured to move the flap from the deployed position to the stowed position in response to an aerodynamic force being less than a threshold force value.

[0180] In some disclosed examples, the actuator includes a spring-loaded axle operatively coupled to the wing blade and mounted to the wing. In some disclosed examples, the spring-loaded axle includes an axle and a spring coiled around the axle.

[0181] In some disclosed examples, the spring is configured to wind around the axle in response to the aerodynamic force being greater than a threshold force value. In some disclosed examples, the spring is further configured to unwind around the axle in response to the aerodynamic force being less than the threshold force value.

[0182] In some disclosed examples, the axle has a central axis that is generally parallel to the chord-wise direction of the wing.

[0183] In some disclosed examples, the panel extends in an inboard direction away from the central axis when the blade is in the stowed position.

[0184] In some disclosed examples, when the winglet is in the deployed position, the deployed blade extends in an outboard direction away from the central axis.

[0185] In some disclosed examples, the panel is recessed within the wing when the blades are in the stowed position.

[0186] In some disclosed examples, the panel includes a first panel positioned adjacent to a first portion of the skin. In some disclosed examples, the first portion of the skin has a first orientation relative to the chord of the wing. In some disclosed examples, the first panel is configured to be oriented along the first portion of the skin when the wing blade is in the stowed position. In some disclosed examples, the panel also includes a second panel, which is located behind the first panel and adjacent to the second portion of the skin located behind the first portion. In some disclosed examples, the second portion of the skin has a second orientation relative to the chord of the wing, and the second orientation is different from the first orientation. In some disclosed examples, the second panel is configured to be oriented along the second portion of the skin when the wing blade is in the stowed position. In some disclosed examples, the first panel and the second panel are configured to hinder the airflow along the span direction of the wing when the wing blade is in the deployed position.

[0187] In some examples, a method for moving a wing blade connected to an aircraft wing is disclosed. In some disclosed examples, the method includes the following steps: moving the wing blade between a stowed position and a deployed position, in which the panel of the wing blade extends along the skin of the wing, and in the deployed position, the panel extends away from the skin at an upward angle. In some disclosed examples, the panel hinders the airflow along the span direction of the wing when the wing blade is in the deployed position. In some disclosed examples, the movement includes moving the wing blade from the stowed position to the deployed position in response to the aerodynamic force applied to the deployment blade of the wing blade.

[0188] In some disclosed examples, the deployed blades are generally normal to the panel.

[0189] In some disclosed examples, the panels generate vortices along the wing when the blades are in the deployed position.

[0190] In some disclosed examples, aerodynamic forces are generated via a generally spanwise airflow along a spanwise direction of the wing.

[0191] In some disclosed examples, the blade is rotatably coupled to the wing via an axle having a central axis.

[0192] In some disclosed examples, the central axis is generally parallel to the chord-wise direction of the wing.

[0193] In some disclosed examples, the panel extends in an inboard direction away from the central axis when the blade is in the stowed position.

[0194] In some disclosed examples, when the winglet is in the deployed position, the deployed blade extends in an outboard direction away from the central axis.

[0195] In some examples, a device is disclosed. In some disclosed examples, the device includes a wing blade of an aircraft wing. In some disclosed examples, the wing blade includes: a base, the base is connected to the wing; and a panel, the panel can be moved relative to the base and the wing between a stowed position and a deployed position, in which the panel extends along the skin of the wing, and in the deployed position, the panel extends away from the skin at an upward angle. In some disclosed examples, the panel is configured to hinder the airflow along the span of the wing when the panel is in the deployed position. In some disclosed examples, the panel is configured to move from the deployed position to the stowed position in response to an aerodynamic force applied to the panel.

[0196] In some disclosed examples, the panel is further configured to generate vortices along the wing when the panel is in the deployed position.

[0197] In some disclosed examples, the device further comprises a living hinge extending between the panel and the base. In some disclosed examples, the living hinge is configured to move the panel from the stowed position to the deployed position.

[0198] In some disclosed examples, the living hinge is configured to move the panel from the stowed position to the deployed position in response to an aerodynamic force being less than a threshold force value.

[0199] In some disclosed examples, the panel is configured to move from the deployed position to the stowed position during cruising operation of the aircraft at a first speed. In some disclosed examples, the panel is further configured to move from the stowed position to the deployed position during slow speed operation of the aircraft at a second speed less than the first speed.

[0200] In some disclosed examples, the living hinge is configured to bend away from the skin of the wing as the panel moves from the stowed position to the deployed position. In some disclosed examples, the living hinge is also configured to straighten toward the skin of the wing as the panel moves from the deployed position to the stowed position.

[0201] In some disclosed examples, the living hinge is configured to bend away from the skin of the wing in response to the aerodynamic force being less than a threshold force value. In some disclosed examples, the living hinge is further configured to straighten toward the skin of the wing in response to the aerodynamic force being greater than the threshold force value.

[0202] In some disclosed examples, the base has a central axis that is inclined relative to the chord-wise direction of the wing.

[0203] In some disclosed examples, the central axis is inclined at a toe angle relative to a chordwise direction of the wing. In some disclosed examples, when the panel is in the stowed position, the panel extends in an inboard direction away from the central axis.

[0204] In some disclosed examples, the central axis is inclined at a toe angle relative to a chordwise direction of the wing. In some disclosed examples, when the panel is in the stowed position, the panel extends in an outboard direction away from the central axis.

[0205] In some disclosed examples, the panel is recessed within the wing when the panel is in the stowed position.

[0206] In some disclosed examples, the panel includes a first panel positioned adjacent to a first portion of the skin. In some disclosed examples, the first portion of the skin has a first orientation relative to the chord of the wing. In some disclosed examples, the first panel is configured to be oriented along the first portion of the skin when the panel is in a stowed position. In some disclosed examples, the panel also includes a second panel, which is located behind the first panel and adjacent to a second portion of the skin located behind the first portion. In some disclosed examples, the second portion of the skin has a second orientation relative to the chord of the wing, which is different from the first orientation. In some disclosed examples, the second panel is configured to be oriented along the second portion of the skin when the panel is in the stowed position. In some disclosed examples, the first panel and the second panel are configured to hinder the spanwise airflow along the wing when the panel is in the deployed position.

[0207] In some examples, a method for moving a panel of a wing of an aircraft relative to the wing and relative to a base of the wing coupled to the wing is disclosed. In some disclosed examples, the method includes the following steps: moving the panel between a stowed position and a deployed position, in which the panel extends along the skin of the wing, and in which the panel extends away from the skin at an upward angle in the deployed position. In some disclosed examples, the panel obstructs airflow along the span of the wing when the panel is in the deployed position. In some disclosed examples, the movement includes moving the panel from the deployed position to the stowed position in response to an aerodynamic force applied to the panel.

[0208] In some disclosed examples, the panel generates vortices along the wing when the panel is in the deployed position.

[0209] In some disclosed examples, aerodynamic forces are generated via a substantially chord-wise airflow along a chord-wise direction of the wing.

[0210] In some disclosed examples, the blade further comprises a living hinge extending between the base and the panel. In some disclosed examples, the base has a central axis inclined relative to a chordwise direction of the wing.

[0211] In some disclosed examples, the central axis is inclined at a toe angle relative to a chordwise direction of the wing. In some disclosed examples, when the panel is in the stowed position, the panel extends in an inboard direction away from the central axis.

[0212] In some disclosed examples, the central axis is inclined at a toe angle relative to a chordwise direction of the wing. In some disclosed examples, when the panel is in the stowed position, the panel extends in an outboard direction away from the central axis.

[0213] Although certain example methods, apparatus, and articles of manufacture have been disclosed herein, the scope of coverage of this patent is not limited thereto. On the contrary, this patent covers all methods, apparatus, and articles of manufacture fully falling within the scope of the claims of this patent.

Claims

1. A device for a wing of an aircraft, the device comprising: a flapper coupled to the wing of the aircraft, the flapper having a first end positioned toward a leading edge of the wing and a second end positioned toward a trailing edge of the wing, the flapper being movable relative to the wing between a stowed position in which a panel of the flapper extends along a skin of the wing, and a deployed position in which the panel extends away from the skin at an upward angle, the panel being configured to obstruct spanwise airflow along the wing when the flapper is in the deployed position, the flapper being configured to move from the deployed position to the stowed position in response to an aerodynamic force applied to the panel; as well as an actuator configured to move the wing blade from the stowed position to the deployed position, wherein the wing blade is configured to move from the deployed position to the stowed position during cruise operation of the aircraft having a first speed, wherein the wing blade is further configured to move from the stowed position to the deployed position during slow speed operation of the aircraft having a second speed less than the first speed, and wherein the actuator comprises a spring loaded axle operatively coupled to the blade and mounted to the wing via a first axle seat positioned toward the leading edge of the wing and a second axle seat positioned toward the trailing edge of the wing, the spring loaded axle comprising an axle and a spring wound around the axle, the spring being positioned between the second end of the blade and the second axle seat, Wherein, the panel comprises: a first panel positioned adjacent a first portion of the skin, the first portion of the skin having a first orientation relative to a chord of the wing, the first panel being configured to be oriented along the first portion of the skin when the blade is in the stowed position; and a second panel located rearward of the first panel and adjacent a second portion of the skin located rearward of the first portion, the second portion of the skin having a second orientation relative to the chord of the wing, the second orientation different from the first orientation, the second panel being configured to be oriented along the second portion of the skin when the blade is in the stowed position, the first panel and the second panel being configured to obstruct the spanwise airflow along the wing when the blade is in the deployed position.

2. The device according to claim 1, wherein The panel is further configured to generate a vortex along the wing when the blade is in the deployed position, and wherein the panel is recessed within the wing when the blade is in the stowed position.

3. The device according to claim 1, wherein: The actuator is configured to move the flap from the stowed position to the deployed position in response to the aerodynamic force being less than a threshold force value.

4. The device according to claim 3, wherein: The spring is configured to wind around the axle in response to the aerodynamic force being greater than the threshold force value, and the spring is further configured to unwind around the axle in response to the aerodynamic force being less than the threshold force value.

5. The device according to claim 4, wherein: The axle has a central axis that is inclined at a toe angle relative to a chordwise direction of the wing, and wherein the panel extends in an outboard direction away from the central axis when the blade is in the stowed position.

6. The device according to claim 4, wherein: The axle has a central axis that is inclined at a toe angle relative to a chordwise direction of the wing, and wherein the panel extends in an inboard direction away from the central axis when the blade is in the stowed position.

7. A method for moving a wing blade coupled to a wing of an aircraft, the wing blade having a first end positioned toward a leading edge of the wing and a second end positioned toward a trailing edge of the wing, the method comprising the steps of: The flap is moved between a stowed position and a deployed position, wherein a panel of the flap extends along the skin of the wing, and wherein the panel extends away from the skin at an upward angle in the deployed position, wherein the panel obstructs airflow along the span of the wing when the flap is in the deployed position, wherein the movement comprises: moving the flap from the deployed position to the stowed position in response to an aerodynamic force applied to the panel, wherein the movement further comprises: moving the flap from the stowed position to the deployed position by means of an actuator, wherein the actuator comprises a spring loaded axle operatively coupled to the blade and mounted to the wing via a first axle seat positioned toward the leading edge of the wing and a second axle seat positioned toward the trailing edge of the wing, the spring loaded axle comprising an axle and a spring wound around the axle, the spring being positioned between the second end of the blade and the second axle seat, Wherein, the panel comprises: a first panel positioned adjacent a first portion of the skin, the first portion of the skin having a first orientation relative to a chord of the wing, the first panel being configured to be oriented along the first portion of the skin when the blade is in the stowed position; and a second panel located rearward of the first panel and adjacent a second portion of the skin located rearward of the first portion, the second portion of the skin having a second orientation relative to the chord of the wing, the second orientation different from the first orientation, the second panel being configured to be oriented along the second portion of the skin when the blade is in the stowed position, the first panel and the second panel being configured to obstruct the spanwise airflow along the wing when the blade is in the deployed position.

8. The method according to claim 7, wherein: The panel generates a vortex along the wing when the flap is in the deployed position, wherein the aerodynamic force is generated via a chord-wise airflow along a chord-wise direction of the wing, and wherein the flap is rotatably coupled to the wing via an axle having a central axis that is inclined relative to the chord-wise direction of the wing.

9. The method according to claim 8, wherein: The central axis is inclined at a toe-in or toe-out angle relative to the chordwise direction of the wing, and wherein the panel extends in an inboard direction or an outboard direction away from the central axis when the blade is in the stowed position.

10. A device for a wing of an aircraft, the device comprising: a flapper coupled to the wing of the aircraft, the flapper being movable relative to the wing between a stowed position in which a panel of the flapper extends along a skin of the wing, and a deployed position in which the panel extends away from the skin at an upward angle, the panel being configured to obstruct spanwise airflow along the wing when the flapper is in the deployed position, the flapper being configured to move from the stowed position to the deployed position in response to an aerodynamic force applied to a deployed blade of the flapper, wherein the deployable blades of the flap are oriented at a non-orthogonal angle relative to the panel, or the deployable blades are orthogonal to the panel, and when the flap is in the deployed position, the deployable blades of the flap extend along the skin of the wing, and when the flap is in the stowed position, the deployable blades of the flap extend away from the skin of the wing at an upward angle, and the deployable blades of the flap are configured to capture, receive and / or react to spanwise airflow occurring along the spanwise direction of the wing when the flap is in the stowed position.

11. A method for moving a wing blade coupled to a wing of an aircraft, the method comprising the steps of: The flap is moved between a stowed position in which a panel of the flap extends along the skin of the wing and a deployed position in which the panel extends away from the skin at an upward angle, the panel obstructing spanwise airflow along the wing when the flap is in the deployed position, the movement comprising: moving the flap from the stowed position to the deployed position in response to an aerodynamic force applied to a deployed blade of the flap, wherein the deployable blades of the flap are oriented at a non-orthogonal angle relative to the panel, or the deployable blades are orthogonal to the panel, and when the flap is in the deployed position, the deployable blades of the flap extend along the skin of the wing, and when the flap is in the stowed position, the deployable blades of the flap extend away from the skin of the wing at an upward angle, and the deployable blades of the flap are configured to capture, receive and / or react to spanwise airflow occurring along the spanwise direction of the wing when the flap is in the stowed position.

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