Deformable wing and aircraft

Abstract

The present application discloses a deformable wing and an aircraft, which relates to the field of wing technology and solves the technical problem in the prior art that the size and shape of the aircraft wing cannot be adjusted according to actual needs. The deformable wing includes a skin and a deformation mechanism installed in the skin; the deformation mechanism includes a guide rail, at least one tie rod and a plurality of shape memory alloy wires; one end of the tie rod is slidably arranged in the guide rail, and the other end of the tie rod is connected to the skin; one end of the shape memory alloy wire is connected to the guide rail and is configured to drive the guide rail to rotate when powered on, so that the tie rod moves in its own length direction. The aircraft includes at least one deformable wing as described above. The wing can change size and shape according to the flight state of the aircraft, and can reduce the area occupied by the aircraft by reducing the size of the wing when it is parked.

Description

Technical Field

[0001] The present application relates to the technical field of wings, and in particular to a deformable wing and an aircraft. Background Art

[0002] The wing is the main component of an aircraft that generates lift. The size and shape of the wing have an important impact on the lift and control of the aircraft.

[0003] During the flight of existing aircraft, the size and shape of the wings remain basically unchanged regardless of how the flight speed, altitude and load change, and the size and shape of the wings cannot be adjusted according to actual control and lift requirements. Summary of the invention

[0004] The embodiments of the present application provide a deformable wing and an aircraft, thereby solving the technical problem in the prior art that the size and shape of the aircraft wing cannot be adjusted according to actual needs.

[0005] In a first aspect, an embodiment of the present application provides a deformable wing, which comprises a skin and a deformation mechanism installed in the skin; the deformation mechanism comprises a guide rail, at least one tie rod and a plurality of shape memory alloy wires; one end of the tie rod is slidably disposed in the guide rail, and the other end of the tie rod is connected to the skin; one end of the shape memory alloy wire is connected to the guide rail, and is configured to drive the guide rail to rotate when power is supplied, so that the tie rod moves in its own length direction.

[0006] In combination with the first aspect, in a possible implementation, the guide rail includes at least one rotating part, and the rotating part includes a first guide segment, a second guide segment and a third guide segment connected in sequence; the second guide segment is bent at an obtuse angle in a first direction relative to the first guide segment, and the third guide segment is bent at an acute angle in the first direction relative to the second guide segment.

[0007] In combination with the first aspect, in a possible implementation, the deformable wing includes two shape memory alloy wires respectively located on both sides of the rotating part; one of the shape memory alloy wires is connected to the first guide segment of the rotating part, and the other shape memory alloy wire is connected to the second guide segment of the same rotating part.

[0008] In combination with the first aspect, in a possible implementation, the deformation mechanism includes two pull rods, and the guide rail includes two coaxially arranged rotating parts; the third guide sections of the two rotating parts are connected, and the two rotating parts are connected to the shape memory alloy wire and are configured to rotate simultaneously under the drive of the shape memory alloy wire; one end of the two pull rods is respectively slidably arranged on the two rotating parts.

[0009] In combination with the first aspect, in a possible implementation, the pull rod includes a first connecting section, a second connecting section and a third connecting section connected in sequence; the first connecting section is arranged in parallel with the third connecting section; the free end of the first connecting section is slidably arranged in the rotating part, and the free end of the third connecting section is connected to the skin.

[0010] In combination with the first aspect, in a possible implementation, the skin includes a plurality of skin connection segments arranged along the length direction of the wing, and two adjacent skin connection segments are slidingly connected; and the pull rod is arranged along the length direction of the wing.

[0011] In combination with the first aspect, in a possible implementation manner, the pull rod is arranged along the width direction of the wing.

[0012] In combination with the first aspect, in a possible implementation, the deformation mechanism also includes a shell, and the guide rail and the multiple shape memory alloy wires are located in the shell; the guide rail is rotatably connected to the inner wall of the shell, and the ends of the multiple shape memory alloy wires away from the guide rail are connected to the inner wall of the shell.

[0013] In combination with the first aspect, in a possible implementation, the deformation mechanism further includes a sleeve, one end of which is connected to the shell; and the pull rod passes through the sleeve.

[0014] In a second aspect, an embodiment of the present application provides an aircraft, comprising at least one deformable wing as described in the first aspect or any possible implementation of the first aspect.

[0015] The technical solution provided in the embodiments of the present application has at least the following technical effects:

[0016] An embodiment of the present application provides a deformable wing. When the size or shape needs to be changed, the shape memory alloy wire is energized to cause the shape memory alloy to heat up and deform. The shape memory alloy wire drives the guide rail to rotate, and the pull rod connected to the guide rail moves in its own length direction, thereby driving the skin to move or deform, so that the wing can change its size and shape according to the flight state of the aircraft, and when the aircraft is parked, the area occupied by the aircraft can be reduced by reducing the size of the wing. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings required for use in the embodiments of the present application will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0018] Figure 1A schematic diagram of the structure of a deformable wing provided in an embodiment of the present application;

[0019] Figure 2 for Figure 1 The schematic diagram of the structure of the deformable wing after shortening is shown;

[0020] Figure 3 A schematic diagram of the connection of two skin connection sections provided in an embodiment of the present application;

[0021] Figure 4 A schematic diagram of the structure of the deformation mechanism provided in the embodiment of the present application;

[0022] Figure 5 for Figure 4 The structural schematic diagram of the deformation mechanism after the operation is shown;

[0023] Figure 6 A schematic diagram of the structure of the guide rail provided in the embodiment of the present application;

[0024] Figure 7 A schematic diagram of the structure of the pull rod provided in an embodiment of the present application.

[0025] Figure markings: 1-skin; 11-first skin connecting section; 12-second skin connecting section; 13-third skin connecting section; 2-deformation mechanism; 21-guide rail; 211-rotating part; 2111-first guide section; 2112-second guide section; 2113-third guide section; 22-pull rod; 221-first connecting section; 2211-sliding shaft; 222-second connecting section; 223-third connecting section; 23a, 23b, 23c, 23d-shape memory alloy wire; 24-shell; 25-sleeve; 26-rotating shaft. DETAILED DESCRIPTION

[0026] The following will be combined with the drawings in the embodiments of the present application to clearly and completely describe the technical solutions in the embodiments of the present application. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0027] In the description of the embodiments of the present application, it should be noted that the terms "upper", "lower", "left", "right", "vertical", "horizontal", "inside", "outside" and the like indicate positions or positional relationships based on the positions or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the embodiments of the present application and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present invention. The terms "first", "second", and "third" are used for descriptive purposes only and cannot be understood as indicating or implying relative importance. In addition, the terms "installation" and "connection" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be directly connected, or indirectly connected through an intermediate medium, or it can be a connection between the two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the embodiments of the present application can be understood according to the specific circumstances.

[0028] The present application embodiment provides a deformable wing. Please refer to Figures 1 to 7 As shown. Among them, Figures 1 to 5 The coordinate system of the embodiment of the present application is shown in the figure; the X direction is perpendicular to the fuselage and points from the fuselage to the left, the Y direction is from the nose to the tail, and the Z direction is the height direction of the aircraft.

[0029] The deformable wing provided in the embodiment of the present application includes a skin 1 and a deformation mechanism 2 installed in the skin 1. Figure 4 and Figure 5 The specific structure of the deformation mechanism 2 is shown. The deformation mechanism 2 includes a guide rail 21, at least one pull rod 22 and a plurality of shape memory alloy wires 23.

[0030] One end of the tie rod 22 is slidably disposed in the guide rail 21. Specifically, one end of the tie rod 22 is provided with a sliding shaft 2211 extending into the guide rail 21, and the guide rail 21 drives the tie rod 22 to move through the sliding shaft 2211 when it rotates. The other end of the tie rod 22 is connected to the skin 1. Specifically, the other end of the tie rod 22 can be directly connected to the skin 1, or it can be indirectly connected to the skin 1 through components such as wing beams or wing ribs. If the tie rod 22 is directly connected to the skin 1, a connection method such as welding or riveting can be used; if the tie rod 22 is indirectly connected to the skin 1 through components such as wing beams or wing ribs, a connection method such as welding, riveting or bolting can be used.

[0031] One end of the shape memory alloy wire 23a, 23b, 23c, 23d is connected to the guide rail 21, and is configured to drive the guide rail 21 to rotate when powered on, so that the pull rod 22 moves in its own length direction. Specifically, the shape memory alloy wire 23a, 23b, 23c, 23d generates heat when powered on. According to the thermal-mechanical coupling cyclic deformation law, the current passed through the shape memory alloy wire 23a, 23b, 23c, 23d is controlled to achieve precise control of the heating amount thereof, so that the shape memory alloy wire 23a, 23b, 23c, 23d reaches the austenite phase end temperature, at which time, the shape memory alloy wire 23a, 23b, 23c, 23d is transformed into a pure austenite phase, and the overall length is shortened to the pure austenite phase. The deformable wing has multiple shape memory alloy wires 23a, 23b, 23c, and 23d. By energizing different shape memory alloy wires 23a, 23b, 23c, and 23d, the guide rail 21 rotates in different directions, thereby enabling the pull rod 22 slidably connected to the guide rail 21 to achieve reciprocating movement in its own length direction.

[0032] For example, Figure 4 and Figure 5 The deformation mechanism 2 shown has two tie rods 22. When the guide rail 21 rotates under the drive of the shape memory alloy wire 23, the two tie rods 22 move closer to or farther from each other, and the two tie rods 22 simultaneously drive the skin 1, so that the size and shape of the wing change. Of course, the deformation mechanism 2 may also have only one tie rod 22. When the guide rail 21 rotates under the drive of the shape memory alloy wire 23, the one tie rod 22 drives the skin 1, so that the size and shape of the wing change.

[0033] The shape memory alloy wire 23 in the embodiment of the present application can drive the guide rail 21 to rotate, and the pull rod 22 connected to the guide rail 21 moves in its own length direction, thereby driving the skin 1 to move or deform, so that the wing can change size and shape according to the flight state of the aircraft. In addition, when the aircraft is parked, the aircraft occupation area can be reduced by reducing the size of the wing.

[0034] For example, Figure 6 A specific structural form of a guide rail 21 is provided. The guide rail 21 includes at least one rotating portion 211, and the rotating portion 211 includes a first guide segment 2111, a second guide segment 2112, and a third guide segment 2113 connected in sequence. Specifically, the second guide segment 2112 is bent at an obtuse angle in a first direction relative to the first guide segment 2111, and the third guide segment 2113 is bent at an acute angle in the first direction relative to the second guide segment 2112.

[0035] The above-mentioned specific structure enables the rotating part 211 to occupy less space when rotating, and enables the rotating part 211 to rotate at a smaller angle to drive the pull rod 22 to generate a larger displacement.

[0036] Specifically, the rotating portion 211 provided in the embodiment of the present application is an integrated structure, that is, the first guide segment 2111 is integrally connected with the second guide segment 2112, and the second guide segment 2112 is integrally connected with the third guide segment 2113. The rotating portion 211 of the integrated structure enables the end of the pull rod 22 to smoothly pass through the connection between the first guide segment 2111 and the second guide segment 2112, and the connection between the second guide segment 2112 and the third guide segment 2113.

[0037] When the deformation mechanism 2 includes two pull rods 22, the guide rail 21 includes two coaxially arranged rotating parts 211. The third guide sections 2113 of the two rotating parts 211 are connected, and the guide rail 21 is Z-shaped as a whole. The two rotating parts 211 are connected to the shape memory alloy wires 23a, 23b, 23c, and 23d, and the two rotating parts 211 are configured to rotate simultaneously under the drive of the shape memory alloy wires 23a, 23b, 23c, and 23d. The ends of the two pull rods 22 are respectively slidably arranged in the two rotating parts 211. When the deformation mechanism 2 has only one pull rod 22, the guide rail 21 only includes one rotating part 211.

[0038] The deformable wing provided in the embodiment of the present application includes two shape memory alloy wires 23a, 23b, 23c, 23d respectively located on both sides of the rotating part 211. One of the shape memory alloy wires 23a, 23c is connected to the first guide section 2111 of the rotating part 211, and the other shape memory alloy wires 23b, 23d are connected to the second guide section 2112 of the same rotating part 211. Figure 4 and Figure 5 Taking the direction shown in as an example, when the shape memory alloy wires 23a and 23c connected to the first guide segment 2111 of the rotating part 211 are powered on and heated, the rotating part 211 rotates counterclockwise; when the shape memory alloy wires 23b and 23d connected to the second guide segment 2112 of the rotating part 211 are powered on and heated, the rotating part 211 rotates clockwise.

[0039] When the guide rail 21 includes two rotating parts 211 , shape memory alloy wires 23a , 23b , 23c , 23d may be provided on both sides of each rotating part 211 , or may be provided on both sides of only one of the rotating parts 211 .

[0040] Figure 4 and Figure 5 The figure shows that the deformation mechanism 2 includes two pull rods 22, the guide rail 21 includes two rotating parts 211, and shape memory alloy wires 23a, 23b, 23c, and 23d are arranged on both sides of each rotating part 211. Figure 4When the two shape memory alloy wires 23a and 23c connected to the first guide section 2111 are energized, the two shape memory alloy wires 23a and 23c are shortened, driving the two rotating parts 211 to rotate counterclockwise, the left pull rod 22 moves to the right, and the right pull rod 22 moves to the left, and the two pull rods 22 move away from each other until they reach Figure 5 Status shown. Figure 5 When the two shape memory alloy wires 23b and 23d connected to the second guide section 2112 are energized, the two shape memory alloy wires 2323b and 23d shorten, driving the two rotating parts 211 to rotate clockwise, the left pull rod 22 moves to the right, and the right pull rod 22 moves to the left, and the two pull rods 22 approach each other until they reach Figure 4 Status shown.

[0041] Of course, the guide rail 21 is not Figures 4 to 6 The specific structure shown is a limitation, and the guide rail 21 can also adopt other structural forms. For example, the guide rail 21 includes at least one rotating portion 211, the rotating portion 211 is in an arc shape, and the rotating shaft 26 of the rotating portion 211 is located at the end of the arc.

[0042] Figure 7 A specific structure of the tie rod 22 is shown, and the tie rod 22 includes a first connecting section 221, a second connecting section 222 and a third connecting section 223 which are connected in sequence. The first connecting section 221 and the third connecting section 223 are arranged in parallel. The free end of the first connecting section 221 is slidably arranged in the rotating part 211, and the free end of the third connecting section 223 is connected to the skin 1. Specifically, the tie rod 22 is an integral structure, that is, the first connecting section 221 and the second connecting section 222 are integrally connected, and the second connecting section 222 and the third connecting section 223 are integrally connected. Other connection methods can also be used between the parts of the tie rod 22, such as welding the first connecting section 221 and the second connecting section 222, and welding the second connecting section 222 and the third connecting section 223.

[0043] When the deformation mechanism 2 includes two tie rods 22, the first connection sections of the two tie rods 22 are parallel, and the displacement paths of the third connection sections 223 of the two tie rods 22 overlap. When the two tie rods 22 are close to each other, the first connection sections 221 of the two tie rods 22 do not interfere with each other, so that each tie rod 22 can have a larger displacement stroke, and can drive the skin 1 to produce a larger size and shape change.

[0044] The pull rod 22 may also be Figure 7 For example, the pull rod 22 is a straight rod; to avoid mutual interference between the two pull rods 22 during displacement, the two pull rods 22 are arranged in parallel so that the displacement paths of the two pull rods 22 do not overlap.

[0045] like Figures 1 to 3As shown, the skin 1 includes a plurality of skin 1 connecting sections arranged along the length direction of the wing, two adjacent skin 1 connecting sections are slidably connected, and the tie rod 22 is arranged along the length direction of the wing. For example, Figure 1 and Figure 2 The wing middle skin 1 shown includes three skin connection segments, that is, the skin 1 includes a first skin connection segment 11, a second skin connection segment 12 and a third skin connection segment 13, the first skin connection segment 11 and the second skin connection segment 12 are slidingly connected, and the second skin connection segment 12 and the third skin connection segment 13 are slidingly connected.

[0046] When the pull rod 22 of the deformation mechanism 2 pulls the two skin connection sections closer to each other, the length of the wing decreases, and the wing is Figure 1 The status shown changes to Figure 2 When the pull rod 22 of the deformation mechanism 2 pushes the two skin 1 connecting sections away from each other, the length of the wing increases, and the wing is Figure 2 The status shown changes to Figure 1 Status shown.

[0047] Specifically, Figure 4 and Figure 5 The specific structure of the deformation mechanism 2 shown is used to illustrate the working process of the deformation mechanism 2 changing the wing length. When the length of the wing needs to be increased, the two shape memory alloy wires 23a and 23c connected to the first guide section 2111 are energized, the two shape memory alloy wires 23a and 23c are shortened, driving the guide rail 21 to rotate counterclockwise, and the two pull rods 22 move away from each other, thereby pushing the two adjacent skin 1 connection sections away from each other, so that the length of the wing increases. When the length of the wing needs to be reduced, the two shape memory alloy wires 23b and 23d connected to the second guide section 2112 are energized, the two shape memory alloy wires 23b and 23d are shortened, driving the guide rail 21 to rotate clockwise, and the two pull rods 22 move closer to each other, thereby pulling the two adjacent skin connection sections closer to each other, so that the length of the wing decreases.

[0048] For example, Figure 3 The specific structure for realizing sliding connection between the first skin connection section 11 and the second skin connection section 12 is provided in the figure. The first skin connection section 11 is arranged as a double-layer structure near the second skin connection section 12, and the second skin connection section 12 is partially inserted between the double-layer structures. When the tie rod 22 moves in its own length direction, the tie rod 22 drives the first skin connection section 11 and the second skin connection section 12 to move, and the length of the double-layer structure of the second skin connection section 12 inserted into the first skin connection section 11 changes, thereby changing the overall length of the wing.

[0049] In addition, the rod 22 can also be arranged along the width direction of the wing. When the rod 22 moves in its own length direction, the cross-sectional shape of the wing is driven to change, thereby affecting the lift of the aircraft.

[0050] like Figure 4 and Figure 5 As shown, the deformation mechanism 2 in the embodiment of the present application further includes a housing 24, a guide rail 21 and a plurality of shape memory alloy wires 23a, 23b, 23c, 23d are located in the housing 24, and the guide rail 21 is rotatably connected to the inner wall of the housing 24, and the ends of the plurality of shape memory alloy wires 23a, 23b, 23c, 23d away from the guide rail 21 are connected to the inner wall of the housing 24. Specifically, the shape memory alloy wires 23a, 23b, 23c, 23d are connected to the inner wall of the housing 24 by welding, riveting, etc., and the guide rail 21 is connected to the inner wall of the housing 24 through a rotating shaft 26.

[0051] The housing 24 protects the guide rail 21 and the plurality of shape memory alloy wires 23a, 23b, 23c, 23d therein. When the deformation mechanism 2 is installed in the wing, only the housing 24 needs to be fixed, and there is no need to set installation positions for the guide rail 21 and the shape memory alloy wires 23a, 23b, 23c, 23d.

[0052] Continue to refer to Figure 4 and Figure 5 As shown, the deformation mechanism 2 further includes a sleeve 25, one end of which is connected to the housing 24. The pull rod 22 passes through the sleeve 25. The sleeve 25 protects the portion of the pull rod 22 outside the housing 24. Figure 4 and Figure 5 In the sleeve 25 shown, a roller is arranged inside, and the roller contacts the pull rod 22 to support and guide the pull rod 22 .

[0053] The present application also provides an aircraft, which includes at least one deformable wing according to the present application. The aircraft can adjust the size and shape of the wing according to the flight speed, altitude and load during flight, so that the aircraft has better control performance.

[0054] The various embodiments in this specification are described in a progressive manner, and the same or similar parts between the various embodiments can be referenced to each other. Each embodiment focuses on the differences from other embodiments.

[0055] The above embodiments are only used to illustrate the technical solutions of the present application, rather than to limit the present application. Although the present application has been described in detail with reference to the aforementioned embodiments, a person of ordinary skill in the art should understand that the technical solutions described in the aforementioned embodiments may still be modified, or some or all of the technical features thereof may be replaced by equivalents. However, these modifications or replacements do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the present application.

Claims

1. A deformable wing, characterized in that: It comprises a skin, and a deformation mechanism installed in the skin; the deformation mechanism comprises a guide rail, at least one pull rod and a plurality of shape memory alloy wires; One end of the pull rod is slidably disposed in the guide rail, and the other end of the pull rod is connected to the skin; One end of the shape memory alloy wire is connected to the guide rail, and is configured to drive the guide rail to rotate when powered on, so that the pull rod moves in its own length direction; Wherein, the guide rail includes at least one rotating portion, and the rotating portion includes a first guide segment, a second guide segment and a third guide segment connected in sequence; the second guide segment is bent at an obtuse angle in the first direction relative to the first guide segment, and the third guide segment is bent at an acute angle in the first direction relative to the second guide segment; The guide rail further comprises two shape memory alloy wires respectively located on both sides of the rotating part; one of the shape memory alloy wires is connected to the first guide section of the rotating part, and the other shape memory alloy wire is connected to the second guide section of the same rotating part; The deformation mechanism comprises two pull rods, and the guide rail comprises two coaxially arranged rotating parts; the third guide sections of the two rotating parts are connected, and the two rotating parts are both connected to the shape memory alloy wire and are configured to rotate simultaneously under the drive of the shape memory alloy wire; one end of the two pull rods is respectively slidably arranged on the two rotating parts; The pull rod includes a first connecting section, a second connecting section and a third connecting section which are connected in sequence; the first connecting section is arranged in parallel with the third connecting section; the free end of the first connecting section is slidably arranged in the rotating part, and the free end of the third connecting section is connected to the skin.

2. The deformable wing according to claim 1, characterized in that: The skin comprises a plurality of skin connection segments arranged along the length direction of the wing, and two adjacent skin connection segments are slidably connected to each other; The pull rod is arranged along the length direction of the wing.

3. The deformable wing according to claim 1 or 2, characterized in that: The tie rod is arranged along the width direction of the wing.

4. The deformable wing according to claim 1, characterized in that: The deformation mechanism further comprises a housing, wherein the guide rail and the plurality of shape memory alloy wires are located in the housing; The guide rail is rotatably connected to the inner wall of the shell, and ends of the plurality of shape memory alloy wires away from the guide rail are connected to the inner wall of the shell.

5. The deformable wing according to claim 4, characterized in that: The deformation mechanism further includes a sleeve, one end of which is connected to the housing; The pull rod passes through the sleeve.

6. An aircraft, characterized in that: Comprising at least one deformable wing according to any one of claims 1-5.

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