Flexible solar wing

Abstract

The invention relates to a flexible solar wing which comprises a lifting mechanism, a pressing and releasing mechanism, a shear fork type unfolding mechanism, a flexible substrate, a top rigid plate, a bottom rigid plate, a bottom support and a top support. The bottom support and the top support are connected to the two ends of the shear fork type unfolding mechanism respectively, and the lifting mechanism is installed on the bottom support. The top rigid plate and the bottom rigid plate are connected to the two ends of the front face of the shear fork type unfolding mechanism respectively, the multiple flexible substrates are connected to the portion, between the top rigid plate and the bottom rigid plate, of the shear fork type unfolding mechanism, and the adjacent flexible substrates are connected through hinges. The bottom rigid plate and the flexible substrate are connected through a hinge; the pressing and releasing mechanisms are installed on the top rigid plate and the bottom rigid plate respectively. The flexible solar wing has the advantages that the flexible solar wing is large in surface area when unfolded and small in size when folded and compressed.

Description

Technical Field

[0001] The present invention relates to the technical field of solar cell arrays, and more specifically, to a flexible solar wing. Background Art

[0002] From the perspective of the structural design of the solar array, the "organ-like" (multiple solar panels are folded and compacted, and then unfolded to generate electricity after launch) foldable space solar arrays are commonly used in my country's low-orbit satellite industry. They mainly include rigid, semi-rigid and flexible solar arrays. The different structural forms of solar panels (solar panels) determine the launch weight and launch and folded volume of the solar array.

[0003] From the perspective of commercial low-cost applications, under the same conditions, minimizing the launch weight and minimizing the folded volume is the optimal economic design. Under the same conditions, flexible solar panels have obvious design advantages of light weight and small folded volume compared to rigid and semi-rigid solar panels.

[0004] With the advancement of design and manufacturing technologies related to flexible solar arrays, under the conditions of the same launch weight and collapsed volume, the power generation area of ​​flexible solar arrays can be increased several times or even 10 times compared to traditional rigid solar arrays (the greater the power, the more obvious the advantage), and there is a new solution to the problem of power generation area limiting power generation capacity.

[0005] The preceding description is intended to provide general background information and does not necessarily constitute prior art. Summary of the invention

[0006] The object of the present invention is to provide a flexible solar wing, which fully embodies the advantages of the flexible solar wing having a large surface area when unfolded and a small volume when folded and compressed.

[0007] The present invention provides a flexible solar wing, comprising a lifting mechanism, a pressing and releasing mechanism, a scissor-type unfolding mechanism, a flexible substrate, a top rigid plate, a bottom rigid plate, a bottom bracket and a top bracket; the bottom bracket and the top bracket are respectively connected at both ends of the scissor-type unfolding mechanism, and the lifting mechanism is installed on the bottom bracket; the top rigid plate and the bottom rigid plate are respectively connected at the two ends in front of the scissor-type unfolding mechanism, a plurality of the flexible substrates are connected between the top rigid plate and the bottom rigid plate on the scissor-type unfolding mechanism, and the adjacent flexible substrates are connected to each other. The top rigid plate and the bottom rigid plate are connected by a hinge, and the bottom rigid plate and the flexible substrate are connected by a hinge; the compression and release mechanisms are respectively installed on the top rigid plate and the bottom rigid plate; when the scissors-type deployment mechanism is in a folded state, it will drive multiple flexible substrates to be stacked between the top rigid plate and the bottom rigid plate, and locked by the compression and release mechanism; at the same time, the lifting mechanism is folded on the bottom bracket; when the lifting mechanism is deployed, the flexible solar wing pressed against the surface of the star will be lifted as a whole, and the scissors-type deployment mechanism will be deployed, which will drive the flexible substrate and the rigid plate to be deployed.

[0008] Furthermore, eight flexible substrates are connected between the top rigid plate and the bottom rigid plate on the scissor-type deployment mechanism.

[0009] Furthermore, the lifting mechanism includes a base, a lower lifting plate, an upper lifting plate, a 90-degree hinge, a 180-degree hinge, a first torsion spring and a lock; the base is square, and the lower lifting plate is connected to the two side edges of the base through the 90-degree hinges, the other end of the lower lifting plate is connected to the upper lifting plate through the 180-degree hinge, and the other end of the upper lifting plate is connected to the bottom bracket through the 90-degree hinge; the first torsion spring for controlling the expansion of the hinge is connected to the 90-degree hinge and the 180-degree hinge; a lock hole is provided in the middle of the base, and the lock head is connected to the bottom bracket; when the lower lifting plate is in a folded state, the lock hole is clamped on the lock head.

[0010] Furthermore, the locking head is connected to the middle part of the bottom bracket, and the two upper lifting plates are symmetrically arranged with respect to the locking head.

[0011] Furthermore, the scissors-type deployment mechanism includes a first bottom short rod, a second bottom short rod, a first top short rod, a second top short rod, a scissors rod group, a middle rotating shaft, a bent hinge and a second torsion spring; the first bottom short rod and the second bottom short rod are respectively connected to the side of the bottom bracket away from the lifting mechanism, and the first top short rod and the second top short rod are respectively connected to the side of the top bracket close to the bottom bracket; the scissors rod group is hinged between the first bottom short rod and the second top short rod and between the second bottom short rod and the first top short rod through the bent hinge; the scissors rod group is formed by the ends of a plurality of the scissors rods being hinged through the bent hinge, and the middle parts of the two matching scissors rods on the two scissors rod groups are rotatably connected through the middle rotating shaft; the second torsion spring is installed on the bent hinge.

[0012] Furthermore, the scissor rod group is formed by the tail ends of five scissor rods being hinged by the bending hinges.

[0013] Furthermore, the scissors-type deployment mechanism also includes a deployment guide rope and a constant force spring. The constant force spring is connected to the bottom bracket above the first bottom short rod and below the second bottom short rod. The constant force spring is connected to the deployment guide rope, and the other end of the deployment guide rope is connected to the top bracket.

[0014] Furthermore, a plurality of tension springs are connected between the top rigid plate and the adjacent flexible substrate.

[0015] Furthermore, the compression release mechanism includes a compression rod and a memory alloy unlocking device; the memory alloy unlocking device is connected to the edge of the bottom rigid plate, and the compression rod cooperating with the memory alloy unlocking device is connected to the edge of the top rigid plate; when the flexible solar wing is in a folded state, the compression rod is connected to the memory alloy unlocking device through threads.

[0016] Furthermore, two of the memory alloy unlocking devices are connected to the two long sides of the bottom rigid plate, and one of the memory alloy unlocking devices is connected to the two short sides of the bottom rigid plate.

[0017] The flexible solar wing provided by the present invention fully demonstrates the advantages of the flexible solar wing, which is large in surface area when unfolded and small in volume when folded and compressed, through the scissor-type unfolding mechanism; the entire solar wing is lifted a certain distance from the satellite body through the lifting mechanism to prevent structural interference during the subsequent movement of the solar wing; during the overall unfolding of the solar wing, in order to avoid the shaking of the wing surface causing collision between the substrate and other components or hooking to cause damage to the battery cells, etc., an unfolding guide rope and a constant force spring are designed to assist the wing surface in completing the unfolding action, and the traction of the unfolding guide rope is used to ensure smooth and orderly unfolding. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 A plan view schematically showing the unfolded state of a flexible solar wing provided in an embodiment of the present invention.

[0019] Figure 2 for Figure 1 A plan view schematic diagram of the flexible solar wing in the unfolded state from another perspective.

[0020] Figure 3 for Figure 1 Schematic diagram of the structure of the flexible solar wing in the folded state.

[0021] Figure 4 for Figure 1 Schematic diagram of the structure of the lifting mechanism of the medium-flexible solar wing.

[0022] Figure 5 for Figure 1 Schematic diagram of the structure of the lifting mechanism and bottom bracket of the medium-flexible solar wing.

[0023] Figure 6 for Figure 1 A plan view schematic diagram of the folded state of the lifting mechanism of the flexible solar wing.

[0024] Figure 7 for Figure 1 Schematic plan view of the scissor-type deployment mechanism of the medium-flexible solar wing.

[0025] Figure 8 for Figure 1 Schematic diagram of the structure of the bottom bracket of the medium-flexible solar wing.

[0026] Fig. 9 for Figure 1 Schematic diagram of the structure of the top support of the medium-flexible solar wing.

[0027] Fig.10 for Figure 1 Schematic diagram of the structure of the compression and release mechanism of the medium-flexible solar wing.

[0028] The reference numerals and components involved in the drawings are as follows:

[0029] 1. Lifting mechanism 11, base 12, lower lifting plate

[0030] 13. Upper lifting plate 14. 90 degree hinge 15. 180 degree hinge

[0031] 16. first torsion spring 17. lock head 18. lock hole

[0032] 2. Compression release mechanism 21, compression rod 22, memory alloy unlocking device

[0033] 3. Scissor-type deployment mechanism 31, first bottom short rod 32, second bottom short rod

[0034] 33. First top short rod 34. Second top short rod 35. Scissor rod assembly

[0035] 351, scissor rod 36, middle shaft 37, bending hinge

[0036] 38. Second torsion spring 39. Unfolding guide rope 391. Constant force spring

[0037] 4. Flexible substrate 5. Top rigid board 6. Bottom rigid board

[0038] 7. Bottom bracket 8. Top bracket 9. Extension spring DETAILED DESCRIPTION

[0039] The specific implementation of the present invention is further described in detail below in conjunction with the accompanying drawings and examples. The following examples are used to illustrate the present invention, but are not intended to limit the scope of the present invention.

[0040] The terms "first", "second", "third", "fourth" and the like in the description and claims of the present invention are used to distinguish similar objects and are not necessarily used to describe a particular order or sequence.

[0041] Example 1

[0042] Figure 1 A schematic plan view of the unfolded state of a flexible solar wing provided by an embodiment of the present invention, Figure 2 for Figure 1 A schematic plan view of the flexible solar wing in the unfolded state from another perspective. Figure 3 for Figure 1 Schematic diagram of the structure of the flexible solar wing in the folded state. Please refer to Figure 1 , Figure 2 , Figure 3 The flexible solar wing provided by the embodiment of the present invention comprises a lifting mechanism 1, a pressing and releasing mechanism 2, a scissor-type unfolding mechanism 3, a flexible substrate 4, a top rigid plate 5, a bottom rigid plate 6, a bottom bracket 7 and a top bracket 8; the bottom bracket 7 and the top bracket 8 are respectively connected to the two ends of the scissor-type unfolding mechanism 3, and the lifting mechanism 1 is installed on the bottom bracket 7; the two ends in front of the scissor-type unfolding mechanism 3 are respectively connected to the top rigid plate 5 and the bottom rigid plate 6, and a plurality of flexible substrates 4 are connected between the top rigid plate 5 and the bottom rigid plate 6 on the scissor-type unfolding mechanism 3, and adjacent flexible substrates 4 are connected by hinges, and the bottom rigid plate 6 and the flexible substrate 4 are connected by hinges; the pressing and releasing mechanism 2 is respectively installed on the top rigid plate 5 and the bottom rigid plate 6;

[0043] It should be noted that when the scissors-type deployment mechanism 3 is in a folded state, it will drive the multiple flexible substrates 4 to be stacked between the top rigid plate 5 and the bottom rigid plate 6, and locked by the clamping release mechanism 2; at the same time, the lifting mechanism 1 is folded on the bottom bracket 7; when the lifting mechanism 1 is deployed, the flexible solar wing pressed against the surface of the star will be lifted as a whole in a linear motion, and the scissors-type deployment mechanism 3 will be deployed, which will drive the flexible substrate 4 and the rigid plate to be deployed.

[0044] The flexible solar wing provided by the present invention fully demonstrates the advantages of the flexible solar wing having a large surface area when unfolded and a small volume when folded and compressed through the scissor-type unfolding mechanism 3; the entire solar wing is lifted a certain distance from the satellite body through the lifting mechanism 1 to prevent structural interference during the subsequent movement of the solar wing.

[0045] Further references Figure 1 , Figure 2 In the present invention, eight flexible substrates 4 are connected between the top rigid plate 5 and the bottom rigid plate 6 on the scissor-type unfolding mechanism 3 .

[0046] It should be noted that during the use of the flexible solar wing of the present invention, thin triple-junction gallium arsenide solar cells are attached to the surfaces of eight flexible substrates 4 and a top rigid board 5; at the same time, flexible foam boards are directly arranged between the top rigid board 5 and the flexible substrate 4, and the bottom rigid board 6 and the star structure.

[0047] Figure 4 for Figure 1 Schematic diagram of the lifting mechanism of the medium-flexible solar wing. Figure 5 for Figure 1 Schematic diagram of the structure of the lifting mechanism and bottom bracket of the medium-flexible solar wing. Figure 6 for Figure 1 A schematic diagram of the folded state of the lifting mechanism of the flexible solar wing. Figure 4 , Figure 5 , Figure 6The lifting mechanism 1 of the present invention comprises a base 11, a lower lifting plate 12, an upper lifting plate 13, a 90-degree hinge 14, a 180-degree hinge 15, a first torsion spring 16 and a lock 17; the base 11 is square, and the lower lifting plate 12 is connected to the two side edges of the base 11 through the 90-degree hinge 14, the other end of the lower lifting plate 12 is connected to the upper lifting plate 13 through the 180-degree hinge 15, and the other end of the upper lifting plate 13 is connected to the bottom bracket 7 through the 90-degree hinge 14; the first torsion spring 16 for controlling the unfolding of the hinge is connected to the 90-degree hinge 14 and the 180-degree hinge 15; a lock hole 18 is provided in the middle of the base 11, and the lock head 17 is connected to the bottom bracket 7; when the lower lifting plate 12 is in a retracted state, the lock hole 18 is stuck on the lock head 17.

[0048] It should be noted that, in the folded state, the lower lifting plate 12, the upper lifting plate 13 and the base 11 are in a parallel state; the deployment process of the lifting mechanism 1 requires that the solar wing, which is initially pressed against the surface of the star, be lifted as a whole in a linear motion, and deployed in a single degree of freedom in space, and locked after being deployed into place to ensure that the overall structure is in a stable system state.

[0049] Specifically, driven by the first torsion spring 16, the lower lifting plate 12 rotates 90 degrees around the base 11, and the lower lifting plate 12 and the base 11 change from a parallel state to a vertical state, and the angle between the lower lifting plate 12 and the upper lifting plate 13 changes from 0 degrees to 180 degrees. At the same time, the upper lifting plate 13 rotates 90 degrees around the bottom bracket 7, and the upper lifting plate 13 and the bottom bracket 7 change from a parallel state to a vertical state; thereby realizing the translational lifting of the solar wing as a whole;

[0050] With the lifting mechanism 1 of the present invention, after the satellite enters orbit, the lock 17 is unlocked under the satellite remote control or program control command; the lifting mechanism 1 lifts the entire solar wing to a certain distance from the satellite body to prevent structural interference during the subsequent movement of the solar wing.

[0051] Furthermore, the lock head 17 of the present invention is connected to the middle part of the bottom bracket 7, and the two upper lifting plates 13 are symmetrically arranged with respect to the lock head 17, thereby improving the stability during the lifting process.

[0052] Figure 7 for Figure 1 A schematic diagram of the scissor-type deployment mechanism of the flexible solar wing. Figure 8 for Figure 1 Schematic diagram of the structure of the bottom bracket of the medium-flexible solar wing. Fig. 9 for Figure 1 Schematic diagram of the structure of the top bracket of the medium flexible solar wing. Please refer to Figure 7 , Figure 8 , Fig. 9 The scissor-type deployment mechanism 3 of the present invention comprises a first bottom short rod 31, a second bottom short rod 32, a first top short rod 33, a second top short rod 34, a scissor-type rod group 35, a middle rotating shaft 36, a bending hinge 37 and a second torsion spring 38; the first bottom short rod 31 and the second bottom short rod 32 are respectively connected to the side of the bottom bracket 7 away from the lifting mechanism 1, and the first top short rod 33 and the second top short rod 34 are respectively connected to the side of the top bracket 8 close to the bottom bracket 7; the scissor-type rod group 35 is hinged between the first bottom short rod 31 and the second top short rod 34 and between the second bottom short rod 32 and the first top short rod 33 through the bending hinge 37; the scissor-type rod group 35 is formed by the tail ends of a plurality of scissor-type rods 351 being hinged through the bending hinge 37, and the middle parts of the two matching scissor-type rods 351 on the two scissor-type rod groups 35 are rotatably connected through the middle rotating shaft 36; the second torsion spring 38 is installed on the bending hinge 37.

[0053] It should be noted that, under the push of the second torsion spring 38, the adjacent scissor rods 351 will extend and open, and the scissor-type deployment mechanism 3 will unfold in one direction; thereby, the flexible substrate 4, the top rigid plate 5 and the bottom rigid plate 6 will be synchronously unfolded with the scissor-type deployment mechanism 3; in addition, the overall unfolded length of the solar wing can be calculated based on the solar wing surface area and wing surface size, and the requirements of indicators such as the solar array stiffness can be guaranteed.

[0054] Furthermore, the scissor rod group 35 is formed by the five scissor rods 351 being hinged at their ends by the bending hinge 37 .

[0055] Further references Figure 1 , Figure 8 The scissors-type unfolding mechanism 3 of the present invention also includes an unfolding guide rope 39 and a constant force spring 391. The constant force spring 391 is connected to the bottom bracket 7 above the first bottom short rod 31 and below the second bottom short rod 32. The unfolding guide rope 39 is connected to the constant force spring 391, and the other end of the unfolding guide rope 39 is connected to the top bracket 8.

[0056] It should be noted that during the overall deployment of the solar wing, in order to avoid the shaking of the wing surface, which may cause the substrate to collide with other components or hook and cause damage to the battery cells, a deployment guide rope 39 and a constant force spring 391 are designed to assist the wing surface in completing the deployment action. A deployment limit device is set at the hinge of the flexible substrate 4, which is pulled by the deployment guide rope 39 to ensure smooth and orderly deployment.

[0057] Specifically, the deployment guide rope 39 is in a tension-free state when the solar wing is in a compressed state. After deployment, the deployment guide rope 39 between the bottom bracket 7 and the top bracket 8 is always in a tensioned state through the constant force spring 391; the wing surface is deployed along the deployment guide rope 39 path. In order to ensure that the deployment guide rope 39 does not generate additional disturbance force in the compressed state and prevent interference with the positioning of the wing surface when it is compressed, the position of the guide rope limit structure is adjusted during the assembly of the entire satellite to achieve the control of the deployment guide rope 39 in the compressed state. During the deployment process, the deployment guide rope 39 drives the constant force spring 391 to deploy and generate a constant tensioning force, and finally eliminates the overall mechanism gap of the deployment mechanism.

[0058] Further references Figure 1 , Figure 2 In the present invention, a plurality of tension springs 9 are connected between the top rigid plate 5 and the adjacent flexible substrate 4 .

[0059] It should be noted that when the solar wing surface is in a locked state after the scissor-type deployment mechanism 3 is deployed in place, in order to ensure that the entire substrate maintains a certain rigidity and meet the satellite's requirements for the fundamental frequency of the battery array, the entire wing surface needs to be tensioned, that is, after the wing surface is fully deployed, a tensioning force in the deployment direction still needs to be applied to the wing surface structure. This function can be ensured by connecting multiple tension springs 9 between the top rigid plate 5 and the adjacent flexible substrate 4; the top compression plate of the wing surface is structurally fixedly connected to the top fixed structure of the deployment mechanism, and a group of tension springs 9 is added between the top rigid plate 5 and the adjacent flexible substrate 4; the deployment length of the deployment mechanism matches the length of the solar wing surface to ensure sufficient stretching distance of each tension spring 9, and finally ensure the pre-tension of the substrate, and keep all structures and wing surfaces stable.

[0060] Fig.10 for Figure 1 Schematic diagram of the compression and release mechanism of the flexible solar wing. Fig.10 The clamping release mechanism 2 of the present invention comprises a clamping rod 21 and a memory alloy unlocking device 22; the memory alloy unlocking device 22 is connected to the edge of the bottom rigid plate 6, and the clamping rod 21 cooperating with the memory alloy unlocking device 22 is connected to the edge of the top rigid plate 5;

[0061] When the flexible solar wing is in the folded state, the pressing rod 21 is threadedly connected to the memory alloy unlocking device 22. Specifically, two memory alloy unlocking devices 22 are connected to the two long sides of the bottom rigid plate 6, and one memory alloy unlocking device 22 is connected to the two short sides of the bottom rigid plate 6.

[0062] It should be noted that the memory alloy unlocking device 22 is a memory-closed breaker of the prior art. When the solar wing is folded, the compression release mechanism 2 compresses and folds the solar wing deployment mechanism, the rigid and flexible substrate 4, etc. on the surface of the star.

[0063] When the memory alloy unlocking device 22 is powered on and unlocked, the clamping rod 21 will be pulled out a certain distance by the clamping rod 21 pulling spring, thereby increasing the safety space between the clamping rod 21 and the lower plate during the unfolding process, and then the entire unfolding mechanism is unfolded into place and locked under the drive of the hinge.

[0064] Based on the above description, it can be seen that the advantages of the present invention are:

[0065] The flexible solar wing provided by the present invention fully demonstrates the advantages of the flexible solar wing, which is large in surface area when unfolded and small in volume when folded and compressed, through the scissor-type unfolding mechanism; the entire solar wing is lifted a certain distance from the satellite body through the lifting mechanism to prevent structural interference during the subsequent movement of the solar wing; during the overall unfolding of the solar wing, in order to avoid the shaking of the wing surface causing collision between the substrate and other components or hooking to cause damage to the battery cells, etc., an unfolding guide rope and a constant force spring are designed to assist the wing surface in completing the unfolding action, and the traction of the unfolding guide rope is used to ensure smooth and orderly unfolding.

[0066] The above is only a specific embodiment of the present invention, but the protection scope of the present invention is not limited thereto. Any person skilled in the art can easily think of changes or substitutions within the technical scope disclosed by the present invention, which should be included in the protection scope of the present invention. Therefore, the protection scope of the present invention should be based on the protection scope of the claims.

Claims

1. A flexible solar wing, characterized in that: It comprises a lifting mechanism (1), a pressing and releasing mechanism (2), a scissor-type unfolding mechanism (3), a flexible substrate (4), a top rigid plate (5), a bottom rigid plate (6), a bottom bracket (7) and a top bracket (8); The bottom bracket (7) and the top bracket (8) are respectively connected to the two ends of the scissor-type deployment mechanism (3), and the lifting mechanism (1) is installed on the bottom bracket (7); The top rigid plate (5) and the bottom rigid plate (6) are respectively connected to the two ends in front of the scissor-type unfolding mechanism (3); a plurality of the flexible substrates (4) are connected between the top rigid plate (5) and the bottom rigid plate (6) on the scissor-type unfolding mechanism (3); adjacent flexible substrates (4) are connected by hinges; and the bottom rigid plate (6) and the flexible substrates (4) are connected by hinges; the pressing and releasing mechanism (2) is respectively mounted on the top rigid plate (5) and the bottom rigid plate (6); When the scissor-type deployment mechanism (3) is in a folded state, it drives the plurality of flexible substrates (4) to be stacked between the top rigid plate (5) and the bottom rigid plate (6), and locked by the clamping release mechanism (2); at the same time, the lifting mechanism (1) is folded onto the bottom bracket (7); When the lifting mechanism (1) is deployed, the flexible solar wing pressed against the surface of the star is lifted in translation as a whole, and the scissor-type deployment mechanism (3) is deployed, which drives the flexible substrate (4) and the rigid plate to be deployed.

2. The flexible solar wing according to claim 1, characterized in that: Eight flexible substrates (4) are connected between the top rigid plate (5) and the bottom rigid plate (6) on the scissor-type unfolding mechanism (3).

3. The flexible solar wing according to claim 1, characterized in that: The lifting mechanism (1) comprises a base (11), a lower lifting plate (12), an upper lifting plate (13), a 90-degree hinge (14), a 180-degree hinge (15), a first torsion spring (16) and a lock (17); The base (11) is square in shape, and the lower lifting plate (12) is connected to both side edges of the base (11) via the 90-degree hinges (14), the other end of the lower lifting plate (12) is connected to the upper lifting plate (13) via the 180-degree hinge (15), and the other end of the upper lifting plate (13) is connected to the bottom bracket (7) via the 90-degree hinge (14); The first torsion spring (16) for controlling the unfolding of the hinge is connected to the 90-degree hinge (14) and the 180-degree hinge (15); a lock hole (18) is provided in the middle of the base (11), and the lock head (17) is connected to the bottom bracket (7); When the lower end lifting plate (12) is in a retracted state, the locking hole (18) is locked on the locking head (17).

4. The flexible solar wing according to claim 3, characterized in that: The locking head (17) is connected to the middle part of the bottom bracket (7), and the two upper lifting plates (13) are symmetrically arranged with respect to the locking head (17).

5. The flexible solar wing according to claim 1, characterized in that: The scissor-type deployment mechanism (3) comprises a first bottom short rod (31), a second bottom short rod (32), a first top short rod (33), a second top short rod (34), a scissor-type rod group (35), a middle rotating shaft (36), a bending hinge (37) and a second torsion spring (38); The first bottom short rod (31) and the second bottom short rod (32) are respectively connected to the side of the bottom bracket (7) away from the lifting mechanism (1), and the first top short rod (33) and the second top short rod (34) are respectively connected to the side of the top bracket (8) close to the bottom bracket (7); The scissor rod assembly (35) is hingedly connected between the first bottom short rod (31) and the second top short rod (34) and between the second bottom short rod (32) and the first top short rod (33) via the bending hinge (37); The scissor rod group (35) is formed by a plurality of scissor rods (351) whose ends are hinged by the bending hinge (37); the middle parts of two matching scissor rods (351) on the two scissor rod groups (35) are rotatably connected by the middle rotating shaft (36); and the second torsion spring (38) is installed on the bending hinge (37).

6. The flexible solar wing according to claim 5, characterized in that: The scissor rod group (35) is formed by the five scissor rods (351) being hinged at their ends through the bending hinges (37).

7. The flexible solar wing according to claim 5, characterized in that: The scissor-type unfolding mechanism (3) also includes an unfolding guide rope (39) and a constant force spring (391), and the constant force spring (391) is connected to the bottom bracket (7) above the first bottom short rod (31) and below the second bottom short rod (32), and the unfolding guide rope (39) is connected to the constant force spring (391), and the other end of the unfolding guide rope (39) is connected to the top bracket (8).

8. The flexible solar wing according to claim 1, characterized in that: A plurality of tension springs (9) are connected between the top rigid plate (5) and the adjacent flexible substrate (4).

9. The flexible solar wing according to claim 1, characterized in that: The pressing and releasing mechanism (2) comprises a pressing rod (21) and a memory alloy unlocking device (22); The memory alloy unlocking device (22) is connected to the edge of the bottom rigid plate (6), and the pressing rod (21) cooperating with the memory alloy unlocking device (22) is connected to the edge of the top rigid plate (5); When the flexible solar wing is in a folded state, the pressing rod (21) is connected to the memory alloy unlocking device (22) via threads.

10. The flexible solar wing according to claim 9, characterized in that: Two memory alloy unlocking devices (22) are connected to the two long sides of the bottom rigid plate (6), and one memory alloy unlocking device (22) is connected to the two short sides of the bottom rigid plate (6).

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