Flexible assembly fixture for solar unmanned aerial vehicle wings

Abstract

The invention relates to the technical field of aerospace engineering, and discloses a flexible assembly fixture for solar unmanned aerial vehicle wings, which comprises a support plate and a rotating rod arranged on the outer side of the support plate; the regulation and control mechanism comprises a lifting assembly arranged under the supporting plate and used for controlling the height of the supporting plate, a rotating assembly arranged on the outer surface of the lifting assembly and used for cooperatively controlling the supporting plate to rotate, and an overturning assembly located at the top of the rotating assembly and used for controlling the angle of the supporting plate. Through cooperation of all parts in the lifting assembly, the rotating assembly and the overturning assembly, the height, the rotating angle and the overturning angle of the assembly fixture body and the wings can be flexibly adjusted, the universality and the flexibility of the assembly fixture body are greatly improved, and meanwhile, the assembly fixture body can be used for simulating the flying state of the unmanned aerial vehicle. And the wing is inclined or overturned at a specific angle to verify the performance of the wing, so that the effect that the assembly fixture body and the wing are allowed to be subjected to more diversified posture adjustment in a three-dimensional space is achieved.

Description

Technical Field

[0001] The present invention relates to the technical field of aerospace engineering, and in particular to a flexible assembly jig for solar-powered unmanned aerial vehicle wings. Background Art

[0002] Indeed, in recent years, advances in solar cells and energy storage technology have greatly promoted the development of solar drones. By adopting advanced energy storage solutions such as lithium-ion batteries and solid-state batteries, the endurance of solar drones has been significantly improved. The flexible assembly jigs used for solar drone wings play a vital role in ensuring that the design of the drone is accurately implemented. By flexibly clamping the wing surface, it can effectively avoid the damage that traditional rigid fixtures may cause to the sensitive material wing surface, so that each wing can be docked with the fuselage in a complete state, thereby ensuring the structural integrity of the wing.

[0003] Some flexible assembly jigs for solar drone wings in the existing technology often have the defect of poor flexibility in adjusting the position of the flexible vise and the wing during use. When assembling wings of different sizes and shapes, if the position of the flexible vise and the wing is difficult to flexibly adjust, it may be difficult to accurately position the wing to the appropriate position on the fuselage surface, thereby affecting the assembly accuracy of the product and further affecting the flight performance. Summary of the Invention

[0004] In view of the above-mentioned problems existing in the existing flexible assembly frame for solar-powered UAV wings, the present invention is proposed.

[0005] Therefore, the object of the present invention is to provide a flexible assembly frame for the wings of solar-powered UAVs.

[0006] In order to solve the above technical problems, the present invention provides the following technical solutions: comprising: The assembly jig body includes a support plate, a rotating rod arranged on the outside of the support plate, a first threaded rod fixedly mounted on the inner surface of the rotating rod, an internally threaded plate threadedly connected to the outer surface of the first threaded rod, a first flexible vise fixedly mounted on the top of the internally threaded plate, a linear guide fixedly connected to the top of the support plate and used in conjunction with the internally threaded plate, and a second flexible vise fixedly mounted on the top of the other side of the support plate and used in conjunction with the linear guide; The regulating mechanism includes a lifting assembly provided directly below the support plate for controlling the height of the support plate, a rotating assembly provided on the outer surface of the lifting assembly for controlling the rotation of the support plate, and a flip assembly located on top of the rotating assembly for controlling the angle of the support plate; The lifting assembly includes a plurality of fixing frames distributed in a circumferential array below the support plate, a first servo motor adapted to be mounted on the outer surface of the fixing frame, a second threaded rod fixedly mounted to the output end of the first servo motor via a coupling, an internal threaded block threadedly connected to the outer surface of the second threaded rod, and a connecting rod fixedly connected to the outer surface of the internal threaded block; The rotating assembly includes a second servo motor adapted to be mounted on the outer surface of the connecting rod, and a gear fixedly mounted on the output end of the second servo motor via a coupling.

[0007] As a preferred solution of the flexible assembly frame for solar drone wings described in the present invention, a bearing sleeve that rotates in conjunction is installed at the connection between the first threaded rod and the support plate, and the bottom of the internal threaded plate is in sliding contact with the outer surface of the linear guide rail.

[0008] As a preferred solution of the flexible assembly frame for solar drone wings described in the present invention, the through end of the second threaded rod is fixedly mounted on the inner wall of the fixing frame through a bearing, a bearing sleeve for matching rotation is installed at the connection between the second threaded rod and the fixing frame, and the outer surface of the internal thread block is in sliding contact with the inner wall of the fixing frame.

[0009] As a preferred solution of the flexible assembly frame for solar drone wings described in the present invention, the lifting assembly also includes a support wheel fixedly mounted on the outer surface of the connecting rod, a turntable arranged on the top of the support wheel, and a limiting ring fixedly connected to the bottom of the turntable and used in conjunction with the support wheel.

[0010] As a preferred solution of the flexible assembly frame for solar drone wings described in the present invention, the bottom of the turntable is in sliding contact with the outer surface of the support wheel, and the outer end surface of the support wheel is in sliding contact with the inner side of the turntable.

[0011] As a preferred embodiment of the flexible assembly frame for solar-powered drone wings of the present invention, the rotating assembly further comprises a gear wheel fixedly sleeved on the outer surface of the rotating disk and used in conjunction with the gear, wherein the outer surface of the gear meshes with the outer surface of the gear wheel; When the gear rotates, it can drive the gear plate and the rotating disk to rotate synchronously.

[0012] As a preferred solution of the flexible assembly frame for solar drone wings described in the present invention, the flip assembly includes push-in cylinders respectively adapted to be installed on both sides of the top of the turntable, a circular guide rail fixedly connected to the output end of the push-in cylinder, and a ball movably connected to the inner wall of the circular guide rail.

[0013] As a preferred solution of the flexible assembly frame for solar drone wings described in the present invention, the flip assembly also includes a shaped rod fixedly connected to the inner surface of the ball bearing, a connecting column fixedly installed at the other end of the shaped rod, and a mounting plate fixedly connected to the outer end surface of the connecting column and used in conjunction with the support plate.

[0014] As a preferred solution of the flexible assembly frame for solar drone wings described in the present invention, the flip assembly also includes a positioning rod fixedly connected to the center position of the top of the turntable, and a sleeve fixedly connected to the other end of the positioning rod and used in conjunction with the connecting column.

[0015] As a preferred solution of the flexible assembly frame for solar drone wings described in the present invention, the support plate is fixedly installed on the top of the mounting plate, and a bearing sleeve for cooperation and rotation is installed at the connection between the connecting column and the sleeve.

[0016] The beneficial effects of the present invention are as follows: through the coordination of the various components in the lifting assembly, the rotating assembly and the flipping assembly, not only can the height, rotation angle and flipping angle of the assembly jig body and the wing be flexibly adjusted, thereby greatly improving the versatility and flexibility of the assembly jig body, but also when simulating the flight state of the drone, the wing can be tilted or flipped at a specific angle to verify its performance, thereby achieving the effect of allowing the assembly jig body and the wing to perform more diversified posture adjustments in three-dimensional space. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] To more clearly illustrate the technical solutions of the embodiments of the present invention, the following briefly introduces the drawings required for describing the embodiments. Obviously, the drawings described below are only some embodiments of the present invention. Those skilled in the art can also derive other drawings based on these drawings without inventive effort. Among them: Figure 1 It is a schematic diagram of the overall structure of the present invention.

[0018] Figure 2 For the present invention Figure 1 A schematic diagram of the enlarged structure of the local area in the middle.

[0019] Figure 3 For the present invention Figure 1 A schematic diagram of the enlarged structure of the local area B in the middle.

[0020] Figure 4 Schematic diagram of the structure inside the fixing frame of the present invention.

[0021] Figure 5 It is a schematic structural diagram of the entire flip assembly in the present invention.

[0022] Figure 6 For the present invention Figure 5 A schematic diagram of the enlarged structure of the local area C in the middle.

[0023] Figure 7 It is a schematic structural diagram of the entire assembly frame body in the present invention.

[0024] In the figure: 100, assembly frame body; 101, support plate; 102, rotating rod; 103, first threaded rod; 104, internal threaded plate; 105, first flexible vise; 106, linear guide; 107, second flexible vise; 200, regulating mechanism; 201, lifting assembly; 201a, fixed frame; 201b, first servo motor; 201c, second threaded rod; 201d, internal threaded block; 201e, connecting Rod; 201f, support wheel; 201g, turntable; 201h, limit ring; 202, rotating assembly; 202a, second servo motor; 202b, gear; 202c, gear plate; 203, flip assembly; 203a, push cylinder; 203b, circular guide rail; 203c, ball; 203d, L-shaped rod; 203e, connecting column; 203f, mounting plate; 203g, positioning rod; 203h, sleeve. DETAILED DESCRIPTION

[0025] In order to make the above-mentioned objects, features and advantages of the present invention more obvious and easy to understand, the specific embodiments of the present invention are described in detail below with reference to the accompanying drawings.

[0026] In the following description, many specific details are set forth to facilitate a full understanding of the present invention. However, the present invention may also be implemented in other ways different from those described herein. Those skilled in the art may make similar generalizations without violating the connotation of the present invention. Therefore, the present invention is not limited to the specific embodiments disclosed below.

[0027] Secondly, the term "one embodiment" or "embodiment" herein refers to a specific feature, structure, or characteristic that may be included in at least one implementation of the present invention. The phrase "in one embodiment" appearing in various places throughout this specification does not necessarily refer to the same embodiment, nor does it refer to a separate or selective embodiment that is mutually exclusive of other embodiments.

[0028] Furthermore, the present invention is described in detail with reference to schematic diagrams. For ease of illustration, when describing the embodiments of the present invention, cross-sectional views illustrating device structures may be partially enlarged and not to scale. Furthermore, the schematic diagrams are merely illustrative and should not limit the scope of protection of the present invention. Furthermore, in actual production, the three-dimensional dimensions of length, width, and depth should be included.

[0029] Example 1 Reference Figures 1 to 4 and Figure 7, which is the first embodiment of the present invention, provides a flexible assembly frame for the wings of a solar-powered UAV, the device comprising: The assembly jig body 100 includes a support plate 101, a rotating rod 102 disposed on the outside of the support plate 101, a first threaded rod 103 fixedly mounted on the inner surface of the rotating rod 102, an internally threaded plate 104 threadedly connected to the outer surface of the first threaded rod 103, a first flexible vise 105 fixedly mounted on the top of the internally threaded plate 104, a linear guide 106 fixedly connected to the top of the support plate 101 and used in conjunction with the internally threaded plate 104, and a second flexible vise 107 fixedly mounted on the top of the other side of the support plate 101 and used in conjunction with the linear guide 106; It should be noted that the support plate 101 is the basic platform of the entire assembly frame body 100, which is used to carry other components. The rotating rod 102 can facilitate the operator to rotate the first threaded rod 103. When the first threaded rod 103 rotates, it can drive the first flexible vise 105 to move linearly along the linear guide rail 106. The first flexible vise 105 and the second flexible vise 107 are both used to clamp the wings. The first flexible vise 105 and the second flexible vise 107 are each movably connected to a plurality of movable clamping points on one side close to the first flexible vise 105 and the second flexible vise 107. Each clamping point can move independently and freely to adapt to wings of different shapes and sizes, which not only ensures the stability of the clamping, but also reduces any potential damage to the wing structure, thereby effectively protecting the wing surface made of sensitive materials.

[0030] The control mechanism 200 includes a lifting assembly 201 disposed directly below the support plate 101 for controlling the height of the support plate 101, a rotating assembly 202 disposed on the outer surface of the lifting assembly 201 for controlling the rotation of the support plate 101, and a flip assembly 203 located on top of the rotating assembly 202 for controlling the angle of the support plate 101. The lifting assembly 201 includes a plurality of fixing brackets 201a distributed in a circular array below the support plate 101, a first servo motor 201b adapted to be mounted on the outer surface of the fixing bracket 201a, a second threaded rod 201c fixedly mounted to the output end of the first servo motor 201b via a coupling, an internally threaded block 201d threadedly connected to the outer surface of the second threaded rod 201c, and a connecting rod 201e fixedly connected to the outer surface of the internally threaded block 201d. It should be noted that the fixed frame 201a is used to support other components in the lifting assembly 201. The first servo motor 201b can control the rotation of the second threaded rod 201c through the coupling. When the second threaded rod 201c rotates, it can control the internal thread block 201d to drive the connecting rod 201e to move vertically along the inner wall of the fixed frame 201a.

[0031] The rotating assembly 202 includes a second servo motor 202a adapted to be mounted on the outer surface of the connecting rod 201e, and a gear 202b fixedly mounted on the output end of the second servo motor 202a via a coupling.

[0032] Specifically, a bearing sleeve for cooperation and rotation is installed at the connection between the first threaded rod 103 and the support plate 101 , and the bottom of the internal threaded plate 104 is in sliding contact with the outer surface of the linear guide rail 106 .

[0033] Furthermore, the through end of the second threaded rod 201c is fixed to the inner wall of the fixing frame 201a through a bearing, and a bearing sleeve for cooperation and rotation is installed at the connection between the second threaded rod 201c and the fixing frame 201a. The outer surface of the internal thread block 201d is in sliding contact with the inner wall of the fixing frame 201a.

[0034] Among them, the lifting assembly 201 also includes a support wheel 201f fixedly installed on the outer surface of the connecting rod 201e, a turntable 201g arranged on the top of the support wheel 201f, and a limiting ring 201h fixedly connected to the bottom of the turntable 201g and used in conjunction with the support wheel 201f.

[0035] It should be further explained that the cooperation between the connecting rod 201e and the supporting wheel 201f can drive the turntable 201g to move synchronously, and the limiting ring 201h is used to limit the movement range of the turntable 201g, thereby preventing the position of the turntable 201g from shifting.

[0036] Preferably, the bottom of the turntable 201g is in sliding contact with the outer surface of the support wheel 201f, and the outer end surface of the support wheel 201f is in sliding contact with the inner side of the turntable 201g.

[0037] It should be noted that the rotating assembly 202 further includes a toothed disc 202c fixedly mounted on the outer surface of the rotating disc 201g and cooperating with the gear 202b. The outer surface of the gear 202b meshes with the outer surface of the toothed disc 202c. When the gear 202b rotates, it can drive the gear plate 202c and the rotating plate 201g to rotate synchronously.

[0038] It should be explained that the second servo motor 202a can control the rotation of the gear 202b through the coupling. When the gear 202b rotates, it can drive the turntable 201g to rotate synchronously by cooperating with the gear plate 202c.

[0039] When in use, the wing is placed on the top of the support plate 101 between the first flexible vise 105 and the second flexible vise 107, and the rotating rod 102 is rotated to drive the first threaded rod 103 to rotate, and the first threaded rod 103 drives the internal threaded plate 104 to slide along the linear guide 106, and then the internal threaded plate 104 drives the first flexible vise 105 to move toward the second flexible vise 107. The wing is clamped and fixed by each independently movable clamping point of the first flexible vise 105 and the second flexible vise 107 to adapt to wings of different shapes and sizes, so as to ensure that the wing is firmly clamped while reducing potential damage to wings made of sensitive materials. When the height of the first flexible vise 105, the second flexible vise 107 and the wing needs to be adjusted: the first servo motor 201b is turned on to drive the second threaded rod 201c to rotate, and the second threaded rod 201c drives the internal thread block 201d to move vertically, and then the internal thread block 201d drives the connecting rod 201e and the support wheel 201f to move, so that the turntable 201g moves synchronously with the support wheel 201f, and then the turntable 201g cooperates with the flip assembly 203 to drive the support plate 101 to adjust its height; When it is necessary to adjust the direction of the first flexible vise 105, the second flexible vise 107 and the wing: turn on the second servo motor 202a to drive the driving gear 202b to rotate, and the gear 202b rotates and cooperates with the toothed disk 202c to drive the turntable 201g to rotate synchronously, and then the turntable 201g drives the turntable 201g and the flip assembly 203 to rotate, so that the flip assembly 203 controls the support plate 101 to rotate.

[0040] In summary, through the cooperation of the lifting component 201 and the rotating component 202, the height and rotation angle of the assembly frame body 100 and the wing can be flexibly adjusted, which greatly improves the versatility and flexibility of the assembly frame body 100, so as to achieve the effect of enabling the assembly frame body 100 to adapt to the assembly requirements of wings of more different sizes and shapes.

[0041] Example 2 Reference Figure 1 、 Figure 5 and Figure 6 , which is the second embodiment of the present invention. This embodiment is different from the first embodiment in that: this embodiment provides a flip component 203 for controlling the flipping of the assembly jig body 100 and the wing.

[0042] Furthermore, the flip assembly 203 includes a push-in cylinder 203a respectively adapted to be installed on both sides of the top of the turntable 201g, a circular guide rail 203b fixedly connected to the output end of the push-in cylinder 203a, and a ball 203c movably connected to the inner wall of the circular guide rail 203b.

[0043] When the output end of the push cylinder 203a extends, it can drive the circular guide rail 203b to move vertically.

[0044] Furthermore, the flip assembly 203 also includes an L-shaped rod 203d fixedly connected to the inner surface of the ball 203c, a connecting column 203e fixedly installed at the other end of the L-shaped rod 203d, and a mounting plate 203f fixedly connected to the outer end surface of the connecting column 203e and used in conjunction with the support plate 101.

[0045] Specifically, the flip assembly 203 further includes a positioning rod 203g fixedly connected to the center position of the top of the turntable 201g, and a sleeve 203h fixedly connected to the other end of the positioning rod 203g and used in conjunction with the connecting column 203e.

[0046] It should be explained that when the circular guide rail 203b moves vertically, it can drive the connecting column 203e to rotate on the inner wall of the sleeve 203h through cooperation with the ball 203c and the L-shaped rod 203d, thereby causing the mounting plate 203f, the assembly frame body 100 and the wing driven by the connecting column 203e to flip.

[0047] Preferably, the support plate 101 is fixedly mounted on the top of the mounting plate 203f, and a bearing sleeve for cooperation and rotation is installed at the connection between the connecting column 203e and the sleeve 203h.

[0048] When in use, the push-in cylinder 203a is activated to extend its output end and drive the circular guide rail 203b to move vertically; When the circular guide rail 203b moves: as the circular guide rail 203b moves vertically, the ball 203c rolls along the inner wall of the circular guide rail 203b. After the L-shaped rod 203d is pushed by the ball 203c, it drives the connecting column 203e to rotate on the inner wall of the sleeve 203h. Since the connecting column 203e is connected to the mounting plate 203f, the mounting plate 203f will also drive the assembly frame body 100 and the wing to flip and rotate accordingly, thereby achieving the effect of accurately adjusting the flip angle of the wing.

[0049] In summary, through the coordination of the various components in the flip assembly 203, the assembly jig body 100 and the wing can be quickly adjusted to a flip angle suitable for assembly, which not only meets the high-precision requirements of the assembly process, but also can tilt or flip the wing at a specific angle to verify its performance when simulating the flight state of the drone, so as to achieve the effect of allowing the assembly jig body 100 and the wing to perform more diverse posture adjustments in three-dimensional space.

[0050] It is important to note that the construction and arrangement of the present application, as illustrated in various exemplary embodiments, are illustrative only. Although only a few embodiments are described in detail in this disclosure, those reading this disclosure will readily appreciate that numerous modifications are possible (e.g., variations in the size, dimensions, structure, shape, and proportions of various components, as well as parameter values ​​(e.g., temperature, pressure, etc.), mounting arrangements, use of materials, color, orientation, etc.) without materially departing from the novel teachings and advantages of the subject matter described herein. For example, components shown as integrally formed may be constructed from multiple parts or components, the positions of components may be inverted or otherwise altered, and the nature, number, or position of discrete components may be modified or changed. All such modifications are therefore intended to be encompassed within the scope of this invention. The order or sequence of any process or method steps may be altered or resequenced according to alternative embodiments. In the claims, any "means-plus-function" clause is intended to cover structures described herein that perform the recited function, and not only structural equivalents but also equivalent structures. Other substitutions, modifications, changes, and omissions may be made in the design, operating conditions, and arrangement of the exemplary embodiments without departing from the scope of this invention. Therefore, the invention is not limited to the specific embodiments, but extends to various modifications that still fall within the scope of the appended claims.

[0051] Additionally, in order to provide a concise description of exemplary embodiments, all features of an actual embodiment may not be described (ie, those features that are not relevant to the best mode presently contemplated for carrying out the invention or those that are not relevant to implementing the invention).

[0052] It should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention and are not intended to limit the present invention. Although the present invention has been described in detail with reference to the preferred embodiments, those skilled in the art should understand that the technical solutions of the present invention may be modified or replaced by equivalents without departing from the spirit and scope of the technical solutions of the present invention, which should all be included in the scope of the claims of the present invention.

Claims

1. A flexible assembly jig for solar-powered drone wings, characterized by: include, An assembly jig body (100) comprises a support plate (101), a rotating rod (102) arranged on the outside of the support plate (101), a first threaded rod (103) fixedly mounted on the inner surface of the rotating rod (102), an internal threaded plate (104) threadedly connected to the outer surface of the first threaded rod (103), a first flexible vise (105) fixedly mounted on the top of the internal threaded plate (104), a linear guide rail (106) fixedly connected to the top of the support plate (101) and used in conjunction with the internal threaded plate (104), and a second flexible vise (107) fixedly mounted on the top of the other side of the support plate (101) and used in conjunction with the linear guide rail (106); The regulating mechanism (200) comprises a lifting assembly (201) disposed directly below the support plate (101) for controlling the height of the support plate (101), a rotating assembly (202) disposed on the outer surface of the lifting assembly (201) for cooperating with the rotation control of the support plate (101), and a flip assembly (203) located on top of the rotating assembly (202) for controlling the angle of the support plate (101); The lifting assembly (201) comprises a plurality of fixing frames (201a) distributed in a circular array below the support plate (101), a first servo motor (201b) adapted to be mounted on the outer surface of the fixing frame (201a), a second threaded rod (201c) fixedly mounted on the output end of the first servo motor (201b) via a coupling, an internal threaded block (201d) threadedly connected to the outer surface of the second threaded rod (201c), and a connecting rod (201e) fixedly connected to the outer surface of the internal threaded block (201d); The rotating assembly (202) comprises a second servo motor (202a) adapted to be mounted on the outer surface of the connecting rod (201e), and a gear (202b) fixedly mounted on the output end of the second servo motor (202a) via a coupling.

2. The flexible assembly jig for solar-powered UAV wings according to claim 1, characterized in that: A bearing sleeve for cooperative rotation is installed at the connection between the first threaded rod (103) and the support plate (101), and the bottom of the internal threaded plate (104) is in sliding contact with the outer surface of the linear guide rail (106).

3. The flexible assembly jig for solar-powered UAV wings according to claim 2, characterized in that: The through end of the second threaded rod (201c) is fixedly mounted on the inner wall of the fixing frame (201a) via a bearing, a bearing sleeve for matching rotation is mounted at the connection between the second threaded rod (201c) and the fixing frame (201a), and the outer surface of the internal thread block (201d) is in sliding contact with the inner wall of the fixing frame (201a).

4. The flexible assembly jig for solar-powered UAV wings according to claim 3 is characterized in that: The lifting assembly (201) further comprises a support wheel (201f) fixedly mounted on the outer surface of the connecting rod (201e), a turntable (201g) arranged on the top of the support wheel (201f), and a limiting ring (201h) fixedly connected to the bottom of the turntable (201g) and used in conjunction with the support wheel (201f).

5. The flexible assembly jig for solar-powered UAV wings according to claim 4 is characterized in that: The bottom of the turntable (201g) is in sliding contact with the outer surface of the support wheel (201f), and the outer end surface of the support wheel (201f) is in sliding contact with the inner side of the turntable (201g).

6. The flexible assembly jig for solar-powered UAV wings according to claim 5, characterized in that: The rotating assembly (202) further comprises a toothed disc (202c) fixedly sleeved on the outer surface of the rotating disc (201g) and used in conjunction with the gear (202b), the outer surface of the gear (202b) being meshed with the outer surface of the toothed disc (202c); When the gear (202b) rotates, it can drive the toothed disc (202c) and the rotating disc (201g) to rotate synchronously.

7. The flexible assembly jig for solar-powered UAV wings according to claim 6, characterized in that: The turning assembly (203) comprises push-in cylinders (203a) respectively adapted to be mounted on both sides of the top of the turntable (201g), a circular guide rail (203b) fixedly connected to the output end of the push-in cylinder (203a), and a ball (203c) movably connected to the inner wall of the circular guide rail (203b).

8. The flexible assembly jig for solar-powered UAV wings according to claim 7, characterized in that: The flip assembly (203) further comprises an L-shaped rod (203d) fixedly connected to the inner surface of the ball (203c), a connecting column (203e) fixedly mounted on the other end of the L-shaped rod (203d), and a mounting plate (203f) fixedly connected to the outer end surface of the connecting column (203e) and used in conjunction with the support plate (101).

9. The flexible assembly jig for solar-powered UAV wings according to claim 8, characterized in that: The turning assembly (203) further comprises a positioning rod (203g) fixedly connected to the center position of the top of the turntable (201g), and a sleeve (203h) fixedly connected to the other end of the positioning rod (203g) and used in conjunction with the connecting column (203e).

10. The flexible assembly jig for solar-powered UAV wings according to claim 9, characterized in that: The support plate (101) is fixedly mounted on the top of the mounting plate (203f), and a bearing sleeve for cooperative rotation is installed at the connection between the connecting column (203e) and the sleeve (203h).

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