A deformable wing device, wing and flight equipment

Abstract

The present invention relates to the field of aircraft technology, and in particular, to a deformable wing device, a wing and a flight device. The deformable wing device is used for the wing of an aircraft, and the deformable wing device includes: a power assembly for outputting power; a connecting assembly, movably connected to the output end of the power assembly; a wing assembly, and the wing assembly is movably connected to the connecting assembly; wherein: the connecting assembly includes a connecting body and a sliding limiter, and the sliding limiter movably connects the power assembly and the wing assembly respectively, and is used to control the swing angle of the wing assembly. In an embodiment, the wing assembly is changed to different states by connecting the connecting assembly, that is, by connecting the connecting assembly to the wing assembly, and by external force to achieve the mutual movement between the connecting assembly and the wing assembly, so as to realize the transformation of the wing assembly to a desired state.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft, and in particular to a deformable wing device, a wing and a flight device. Background Art

[0002] With the continuous deepening of research on unmanned aerial vehicles, the scope of application of unmanned aerial vehicles is also expanding. With its advantages of convenient and fast flying and transportation in the air, it is gradually applied to various industries. However, at present, in the actual application of most unmanned aerial vehicles, there is still a certain site environment required for the take-off and landing of unmanned aerial vehicles because the wings are usually designed in a fixed form.

[0003] In the process of realizing the present invention, the inventors of the present invention found that: when the wings of existing UAVs are restricted by the operating environment, that is, when the site cannot provide the UAV with sufficient take-off and landing space, it is impossible to change the wing state to change the take-off and landing site requirements by properly adjusting the forward-swept wing state of the UAV, nor is it possible to shorten the take-off and landing distance while satisfying the disadvantage of being unable to respond quickly due to the slow flight speed. Summary of the invention

[0004] In view of the above-mentioned defects of the prior art, the main purpose of the present invention is to provide a morphing wing device for use in the wing of an aircraft, characterized in that the morphing wing device comprises: a power assembly for outputting power;

[0005] A connecting component, movably connected to the output end of the power component;

[0006] a wing assembly, wherein the wing assembly is movably connected to the connecting assembly;

[0007] Wherein: the connecting assembly includes a connecting body and a sliding limiter, and the sliding limiter is movably connected to the power assembly and the wing assembly respectively, so as to control the swing angle of the wing assembly.

[0008] The embodiment connects the wing assembly through the connecting assembly, and the embodiment realizes the change of different states of the wing assembly through the connection of the connecting assembly, that is, through the connection of the connecting assembly and the wing assembly, and through the external force to realize the mutual movement between the connecting assembly and the wing assembly, so as to realize the transformation of the wing assembly to the desired state. Moreover, the embodiment realizes the automatic transformation of the state of the wing assembly by connecting the power assembly to the connecting assembly through the output power of the power assembly, and driving the connecting assembly through the power assembly.

[0009] In a further embodiment, the sliding limiter comprises:

[0010] a first movable member, which is disposed on the connecting body and is movable on the connecting body; and

[0011] The second movable member is arranged on the connecting body and is movably connected to the connecting body and the wing assembly respectively.

[0012] In a further embodiment, a sliding groove is provided on the connecting body, and the sliding groove is movably connected to the first movable member.

[0013] In a further embodiment, the first sliding groove is an arc-shaped groove.

[0014] In a further embodiment, the wing assembly includes a first spar, which is arranged on one side of the connecting body and is movably connected to the first movable member and the second connecting member respectively;

[0015] a second spar, which is arranged on a side of the connecting body away from the first spar and is movably connected to the first movable member; and

[0016] A wing frame group is connected to the first wing beam and the second wing beam respectively.

[0017] In a further embodiment, the wing frame assembly includes at least two wing ribs, and the wing ribs are spaced apart and respectively connected to the first wing spar and the second wing spar;

[0018] The third wing spar is arranged on the wing rib.

[0019] In a further embodiment, a second sliding groove is provided on the second wing beam, and the second sliding groove is installed in cooperation with the second movable member.

[0020] In a further embodiment, the power assembly includes a driving member, the driving member is connected and installed with the aircraft; and,

[0021] A connecting rod, one end of which is connected to the output end of the driving member, and the other end of which is movably connected to the first movable member.

[0022] In a second aspect, an embodiment provides a wing, comprising any one of the morphing wing devices; and,

[0023] A shell member covers the surface of the deformable wing device.

[0024] A third aspect of the embodiment provides a flying device, comprising the wing.

[0025] The forward-swept wing of the flying device of the embodiment adopts the wing of this scheme. Therefore, in this embodiment, the servo-actuator drives the crank structure to rotate, and the wing is rotated forward and merged with or unfolded on the fuselage through the rotation of the connecting rod, the first movable part and the second movable part, and the cooperation of the first sliding groove and the second sliding groove. In other words, the embodiment realizes the switching of the wing of the aircraft between the forward-swept wing and the delta wing layout, so that it can improve the low-speed maneuverability of the aircraft and realize short-distance takeoff and landing by switching to the forward-swept wing layout; it can fly in the delta wing layout during the high-speed flight stage, thereby solving the problem of large high-speed flight resistance and bending and torsion divergence affecting the strength of the wing structure when the forward-swept wing layout is used. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] In order to more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the following is a brief introduction to the drawings required for the specific embodiments or the description of the prior art. In all the drawings, similar elements or parts are generally identified by similar reference numerals. In the drawings, the elements or parts are not necessarily drawn according to the actual scale.

[0027] Figure 1 is a schematic diagram of a morphing wing device according to an embodiment of the present invention;

[0028] Figure 2 is a schematic diagram of another state of the deformable wing device of the present invention;

[0029] Figure 3 is a schematic diagram of another state of the deformable wing device of the present invention;

[0030] Figure 4 The present invention Figure 3 A schematic diagram from another perspective;

[0031] Figure 5 It is a schematic diagram of the connection body of the present invention;

[0032] Figure 6 is a schematic diagram of a second spar of the present invention;

[0033] Figure 7 is a schematic diagram of a first spar of the present invention;

[0034] Figure 8 is a schematic diagram of a wing rib of the present invention;

[0035] Fig. 9 It is a schematic diagram of the aircraft of the present invention.

[0036] Reference numerals:

[0037] 1. Deformable wing device;

[0038] 10. driving assembly; 101. driving member; 102. connecting rod;

[0039] 20. Connecting assembly; 201. First movable member; 202. Second movable member; 203. First sliding groove; 204. Connecting body;

[0040] 30. Wing assembly; 301. Second wing spar; 302. Third wing spar; 303. First wing spar; 304. Wing rib; 305. Second sliding groove. DETAILED DESCRIPTION

[0041] The following embodiments of the technical solution of the present invention are described in detail in conjunction with the accompanying drawings. The following embodiments are only used to more clearly illustrate the technical solution of the present invention, and are therefore only used as examples, and cannot be used to limit the protection scope of the present invention.

[0042] It should be noted that, unless otherwise specified, the technical terms or scientific terms used in this application should have the common meanings understood by those skilled in the art to which the present invention belongs.

[0043] In the description of the present application, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise", "axial", "radial", "circumferential" and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as limiting the present invention.

[0044] In addition, the terms "first", "second", etc. are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated. In the description of the present invention, the meaning of "plurality" is more than two, unless otherwise clearly and specifically defined.

[0045] In this application, unless otherwise clearly specified and limited, the terms "installed", "connected", "connected", "fixed" and the like 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 a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0046] In the present application, unless otherwise clearly specified and limited, a first feature being “above” or “below” a second feature may mean that the first and second features are in direct contact, or the first and second features are in indirect contact through an intermediate medium. Moreover, a first feature being “above”, “above”, and “above” a second feature may mean that the first feature is directly above or obliquely above the second feature, or simply means that the first feature is higher in level than the second feature. A first feature being “below”, “below”, and “below” a second feature may mean that the first feature is directly below or obliquely below the second feature, or simply means that the first feature is lower in level than the second feature.

[0047] Please refer to the attached Figure 1 , discloses a morphing wing device 1 for use in a wing of an aircraft, the morphing wing device 1 comprising: a power assembly for outputting power;

[0048] A connecting component 20, movably connected to the output end of the power component;

[0049] A wing assembly 30, wherein the wing assembly 30 is movably connected to the connecting assembly 20;

[0050] Wherein: the connecting assembly 20 includes a connecting body 204 and a sliding limiter, and the sliding limiter is movably connected to the power assembly and the wing assembly 30 respectively, and is used to control the swing angle of the wing assembly 30.

[0051] It can be understood that the embodiment connects the wing assembly 30 through the connection assembly 20, and the embodiment realizes the change of different states of the wing assembly 30 through the connection of the connection assembly 20, that is, through the connection of the connection assembly 20 and the wing assembly 30, and through the external force to realize the mutual movement between the connection assembly 20 and the wing assembly 30, so as to realize the transformation of the wing assembly 30 to the desired state. Moreover, the embodiment realizes the automatic transformation of the state of the wing assembly 30 by connecting the power assembly to the connection assembly 20 through the output power, and driving the connection assembly 20 through the power assembly.

[0052] Here, the sliding limiter moves relative to the connecting assembly 20 and / or the wing assembly 30, and the swing of the wing assembly 30 is changed by sliding of the sliding limiter, thereby realizing the change of the state of the wing assembly 30, and meeting the state requirements of the wing of the aircraft under different circumstances.

[0053] In actual use, the power assembly and the connection assembly 20 are respectively installed and connected to the aircraft, the sliding limiter is matched and installed with the connection assembly 20, and it is ensured that the sliding limiter can achieve reciprocating movement on the connection assembly 20. The output end of the power assembly is movably connected with the sliding limiter, so as to achieve driving the sliding limiter to move on the connection assembly 20 by the power assembly. The wing assembly 30 is movably connected with the sliding limiter, that is, when the driving assembly 10 drives the sliding limiter to move on the connection assembly 20, the wing assembly 30 can achieve a relative change state.

[0054] Please refer to the attached Figure 2 and 5 , In a further embodiment, the connection assembly 20 includes a connection body 204, and the connection body 204 is connected and installed with the aircraft;

[0055] Please refer to the attached Figure 4 In a further embodiment, the sliding limiter comprises:

[0056] A first movable member 201 is movably disposed on the connecting body 204, and the first movable member 201 is movably connected to the wing assembly 30 and the power assembly respectively; and,

[0057] The second movable member 202 is disposed on the connecting body 204 and is movably connected to the connecting body 204 and the wing assembly 30 respectively.

[0058] It can be understood that the connection assembly 20 of the embodiment includes a connection body 204 and a sliding limiter, the sliding limiter includes a first movable member 201 and a second movable member 202, and the connection body 204 is installed and connected to the aircraft. In addition, a first movable member 201 capable of relative movement is provided on the connection body 204, the first movable member 201 can move relatively on the connection body 204, and the first movable member 201 is movably connected to the power assembly, that is, under the drive of the power assembly, the first movable member 201 can move relatively on the connection body 204. In addition, the second movable member 202 is also provided on the connection body 204, the second movable member 202 is movably connected to the connection body 204, and at the same time, the second movable member 202 is also movably connected to the wing assembly 30. In the embodiment, driven by the power assembly and through the cooperation of the first movable part 201 and the second movable part 202, the wing assembly 30 can be swung to different angles relative to the connecting body 204, thereby realizing the state requirements of the wing under different flight states of the aircraft.

[0059] For actual use, please refer to the attached Figure 4 , the connecting body 204 can be a plate structure or a connecting rod structure, where the connecting body 204 is a plate member, one side of which is connected and installed with the aircraft. In addition, the embodiment further provides a first movable member 201 and a second movable member 202 on the plate member, wherein both the first movable member 201 and the second movable member 202 have smoothed outer surfaces, which can be understood as cylindrical pins. The first movable member 201 can move back and forth within a certain range on the plate member, and the second movable member 202 is movably connected to the plate member, that is, the second movable member 202 can rotate around the axis on the plate member.

[0060] In the embodiment, the first movable part 201 is connected to the power assembly and the wing assembly 30 respectively, that is, the position where the wing assembly 30 is connected to the first movable part 201 is moved together under the drive of the power assembly. Since the wing assembly 30 is also movably connected to the second movable part 202, when the first movable part 201 moves, the second movable part 202 also moves relatively. Under the action of the power assembly, the first movable part 201 and the second movable part 202, the wing assembly 30 can achieve the required swing angle.

[0061] Please refer to the attached Figure 2 In a further embodiment, a first sliding groove 203 is provided on the connecting body 204 , and the first sliding groove 203 is movably connected to the first movable member 201 .

[0062] It can be understood that in the embodiment, a first sliding groove 203 is provided on the connecting body 204 for cooperating with the installation of the first movable part 201, and the first movable part 201 can move on the first sliding groove 203, and the first sliding groove 203 serves to limit the movement trajectory of the first movable part 201, so that the first movable part 201 can only move on the prescribed trajectory, thereby achieving the purpose of accurately controlling the required swing angle of the wing assembly 30.

[0063] In actual use, the first movable member 201 is movably connected to the power assembly and the wing assembly 30 respectively, and the first movable member 201 is arranged in the first sliding groove 203 on the connecting body 204. When driven by the power assembly, the first movable member 201 can be moved along the first sliding groove 203, thereby driving the wing assembly 30 to follow the movement of the first movable member 201, and the moving trajectory is the first sliding groove 203, so that the swing of the wing assembly 30 is realized. It can also be understood that the first sliding groove 203 serves as a limiting trajectory of the first movable member 201.

[0064] Please refer to the attached Figure 5 In a further embodiment, the first sliding groove 203 is an arc-shaped groove.

[0065] It can be understood that in the embodiment, the first sliding groove 203 is configured as an arc groove, that is, it cooperates with the movement trajectory when the power component drives the sliding limiter, so as to realize the angle trajectory of controlling the swing of the wing assembly 30.

[0066] Please refer to the attached Figure 1 , 6 , 7 and 8, in further embodiments, the wing assembly 30 includes a first wing spar 303, which is arranged on one side of the connecting body 204 and is movably connected to the first movable member 201 respectively;

[0067] The second spar 301 is disposed on a side of the connecting body 204 away from the first spar and is movably connected to the second movable member 202; and,

[0068] A wing frame group, wherein the wing frame group is connected to the first wing beam 303 and the second wing beam 301 respectively.

[0069] It can be understood that the embodiment sets the wing to include a first spar 303 and a second spar 301, and the first spar 303 and the second spar 301 are respectively arranged on two opposite sides of the connecting body 204. The first spar 303 is movably connected to the movable member, so as to follow the movement of the first movable member 201 on the connecting body 204. The second spar 301 is movably connected to the second movable member 202, specifically, the second movable member 202 can move on the second spar 301, and the first spar 303 and the second spar 301 can swing through the movement and coordination of the first movable member 201 and the second movable member 202. At the same time, a wing frame group is also included, and the wing frame group is respectively connected to the first spar 303 and the second spar 301.

[0070] Please refer to the attached Figure 3 and 8 In a further embodiment, the wing frame assembly includes at least two wing ribs 304, and the wing ribs 304 are spaced and respectively connected to the first wing beam 303 and the second wing beam 301; and

[0071] The third spar 302 is arranged on the rib 304 .

[0072] It can be understood that the wing frame assembly of the embodiment includes at least two wing ribs 304, and the first wing beam 303 and the second wing beam 301 are connected to form a desired structure through the wing ribs 304. The wing ribs 304 are arranged at intervals to ensure the strength of the connection at each location, making the wing structure more stable. In the embodiment, the wing ribs 304 are also provided with a third wing beam 302, and the third wing beam 302 is arranged at a position away from the first wing beam 303 or the second wing beam 301, and the third wing beam 302 plays a role in stabilizing the wing ribs 304.

[0073] In some embodiments, there are three wing ribs 304, and the three wing ribs 304 are spaced apart and connected to the first wing spar 303 and the second wing spar 301 respectively; in other embodiments, there are four wing ribs 304, and the four wing ribs 304 are spaced apart and connected to the first wing spar 303 and the second wing spar 301 respectively; in still other embodiments, there are six wing ribs 304, and the six wing ribs 304 are spaced apart and connected to the first wing spar 303 and the second wing spar 301 respectively.

[0074] Please refer to the attached Figure 6 In a further embodiment, a second sliding groove is provided on the second wing beam 301 , and the second sliding groove is installed in cooperation with the second movable member 202 .

[0075] It can be understood that in the embodiment, a second sliding groove is provided on the second wing beam 301, the second sliding groove is installed in cooperation with the second movable member 202, and the second movable member 202 can reciprocate on the second sliding groove. In the embodiment, when the first movable member 201 moves on the second sliding groove, the second sliding groove here ensures that the second movable member 202 can also move relatively, so that the wing assembly 30 can swing relatively on the connecting assembly 20, thereby realizing the change of the state of the wing.

[0076] In actual implementation, the embodiment opens a second sliding groove on the second wing beam 301, and the second movable member 202 installed on the connecting assembly 20 cooperates with the second sliding groove, so that the second movable member 202 can move in the second sliding groove. That is, when the power assembly drives the first movable member 201, the first movable member 201 moves in the first sliding groove 203, and the wing assembly 30 is also connected and installed with the first movable member 201, so the wing assembly 30 also follows and makes the same movement.

[0077] It should be noted here that the second sliding groove can also be set on the connecting component 20, and the second movable part 202 is set on the second wing beam 301, and the second sliding groove and the second movable part 202 are installed in coordination. It can also be considered that the difference from the above scheme is that swapping the setting method of the second sliding groove and the second movable part 202 can also achieve the same effect, which is also included in the protection scope required by the present technical solution.

[0078] Please refer to the attached Figure 2 In a further embodiment, the power assembly includes a driving member 101, and the driving member 101 is connected and installed with the aircraft; and

[0079] A connecting rod 102 , one end of which is connected to the output end of the driving member 101 , and the other end of which is movably connected to the first movable member 201 .

[0080] It can be understood that the power assembly of the embodiment includes a driving member 101 and a connecting rod 102. The driving member 101 here includes a servo steering gear or a motor, and the driving member 101 is installed on the aircraft. One end of the connecting rod 102 here is connected to the output end of the driving member 101, and the other end of the connecting rod 102 is connected to the first movable member 201, that is, the driving member 101 can drive the first movable member 201 to move through the connecting rod 102, so that the wing can be driven by the driving member 101 to automatically change the state.

[0081] In actual implementation, the power assembly includes a connecting rod 102 and a driving member 101, and one end of the connecting rod 102 is movably connected to the first movable member 201, so as to drive the first movable member 201 through the driving member 101. The driving member 101 here is a servo steering engine, and a crank is usually provided on the output shaft of the servo steering engine, and the crank is movably connected to the other end of the connecting rod 102. The embodiment can cause the wing assembly 30 to change state through the connecting rod 102 and the servo steering engine, and realize the function of changing the wing assembly 30 by electric control.

[0082] In actual use, in order to realize the rotation of the wing assembly 30, the embodiment is realized by rotating the first movable member 201 as the axis. For specific implementation, please refer to the attached Figure 1 In the initial state, the wing is swept forward, and the servo drive drives the connecting rod 102 to swing, and the second movable member 202 constrained in the first sliding groove 203 cooperates with the first movable member 201 constrained in the second sliding groove. Figure 2When the connecting rod 102 swings 30° in one direction with the output shaft of the servo motor as the center, the first movable member 201 moves to the middle of the first sliding groove 203 in the first sliding groove 203. At this time, the first movable member 201 and the second sliding groove are on the same straight line. Figure 3 and 4 In the delta wing state, the connecting rod 102 continues to swing 30° around the output shaft of the servo actuator, and the second movable member 202 moves from one end of the second sliding groove to the other end. At the same time, the first movable member 201 also reaches the other end of the first sliding groove 203, and the wing assembly realizes a 40.5° deflection forward, that is, it realizes the switch from the forward swept wing to the delta wing state.

[0083] When the servo actuator rotates in the opposite direction, the connecting rod 102 swings 30° in the opposite direction with the output shaft of the servo actuator as the center. At this time, the first movable part 201 moves in the first sliding groove 203 to the middle of the first sliding groove 203, and the first movable part 201 and the second sliding groove are in the same straight line. At this time, the connecting rod 102 continues to swing 30° with the output shaft of the servo actuator as the center, and the second movable part 202 moves from one end of the second sliding groove to the other end. At the same time, the first movable part 201 also reaches the other end of the first sliding groove 203, and the wing assembly realizes a deflection of 40.5° in the opposite direction. At this time, the wing assembly 30 returns to its original state, that is, the switch from the delta wing to the forward swept wing state is realized.

[0084] A second aspect discloses a wing, comprising any one of the deformable wing devices 1; and,

[0085] A shell member is provided, wherein the shell member covers the surface of the deformable wing device 1 .

[0086] In this embodiment, the servo steering engine is used as the original power to drive the connecting rod 102 to rotate, thereby driving the movement of the first movable part 201 in the first sliding groove 203 and the second movable part 202 in the second sliding groove. At the same time, the first movable part 201 and the second movable part 202 rotate themselves, and the connection method of the first wing beam 303 and the second wing beam 301 realizes the rotation of the wing. In this embodiment, the forward-swept wing is switched to the delta-wing state, that is, the fuselage of the aircraft is combined to form a delta-wing layout. At this time, the forward-swept wing layout aircraft can make up for the bending moment divergence caused by the large flight resistance under high-speed conditions, thereby affecting the strength of the wing structure. In this embodiment, the flight speed of the aircraft can be effectively improved, thereby ensuring the flight safety of the aircraft.

[0087] At the same time, during the low-speed flight stage, the servo steering gear can be reversed to rotate the wings backwards and transform them into a forward-swept wing layout, thereby regaining the advantages of a forward-swept wing layout aircraft, improving the aircraft's low-speed maneuverability and achieving short-distance takeoff and landing.

[0088] The third aspect of the embodiment also discloses a flying device, please refer to the attached Fig. 9 , comprising the wing as claimed in the claims.

[0089] It can be understood that the forward-swept wing of the flying device of the embodiment adopts the wing of this scheme. Therefore, in this embodiment, the crank structure is driven to rotate by the servo servo, and the wing is rotated forward and merged or unfolded with the fuselage through the rotation of the connecting rod 102, the first movable part 201 and the second movable part 202, and through the cooperation of the first sliding groove 203 and the second sliding groove. In other words, the embodiment realizes the switching of the wing of the aircraft between the forward-swept wing and the delta wing layout, so that it can improve the low-speed maneuverability of the aircraft and achieve short-distance takeoff and landing by switching to the forward-swept wing layout; it can fly in the delta wing layout during the high-speed flight stage, thereby solving the problem of large high-speed flight resistance and bending and torsion divergence affecting the strength of the wing structure when the forward-swept wing layout is used.

[0090] Attached Fig. 9 The wings of the aircraft are in a forward-swept state.

[0091] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit them; although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or replace some or all of the technical features therein by equivalents; and these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the scope of the technical solutions of the embodiments of the present invention, and they should all be included in the scope of the claims and specification of the present invention. In particular, as long as there is no structural conflict, the various technical features mentioned in each embodiment can be combined in any way. The present invention is not limited to the specific embodiments disclosed herein, but includes all technical solutions that fall within the scope of the claims.

Claims

1. A morphing wing device, used for the wing of an aircraft, characterized in that: The morphing wing device comprises: a power assembly for outputting power; A connecting component, movably connected to the output end of the power component; a wing assembly, wherein the wing assembly is movably connected to the connecting assembly; Wherein: the connecting assembly comprises a connecting body and a sliding stopper, and the sliding stopper is respectively and movably connected to the power assembly and the wing assembly, and is used to control the swing angle of the wing assembly; The wing assembly includes a first wing spar, which is arranged on one side of the connecting body and is movably connected to the first movable member respectively; a second spar, which is arranged on a side of the connecting body away from the first wing and is movably connected to the second movable member; and a wing frame group, wherein the wing frame group is connected to the first wing spar and the second wing spar respectively; The sliding limiter comprises: a first movable member, which is disposed on the connecting body and is movable on the connecting body; and The second movable member is arranged on the connecting body and is movably connected to the connecting body and the wing assembly respectively.

2. The morphing wing device according to claim 1, characterized in that: The connecting body is provided with a first sliding groove, and the first sliding groove is movably connected to the first movable member.

3. The morphing wing device according to claim 2, characterized in that: The sliding groove is an arc-shaped groove.

4. The morphing wing device according to claim 1, characterized in that: The wing frame group includes at least two wing ribs, and the wing ribs are spaced and respectively connected to the first wing spar and the second wing spar; The third wing spar is arranged on the wing rib.

5. The morphing wing device according to claim 1 or 4, characterized in that: The second wing beam is provided with a second sliding groove, and the second sliding groove is installed in cooperation with the second movable member.

6. The morphing wing device according to claim 1, characterized in that: The power assembly includes a driving member, and the driving member is connected and installed with the aircraft; and, A connecting rod, one end of which is connected to the output end of the driving member, and the other end of which is movably connected to the first movable member.

7. A wing, characterized in that: A morphing wing device comprising any one of claims 1 to 6; and A shell member covers the surface of the deformable wing device.

8. A flying device, characterized in that: Comprising the wing as claimed in claim 7.

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