Flexible solar wing

Abstract

The utility model 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 utility model relates to solar cell array technical field, more specifically, relate to a kind of flexible solar wing. BACKGROUND

[0002] From the mechanism design form of solar cell array, currently in the low-orbit satellite industry of our country, the folding space solar cell array of "organ" (multiple solar panels are folded and folded and compressed, solar panel array is unfolded to generate electricity after launch) is generally used, which mainly includes rigid, semi-rigid, flexible solar cell array, and the different structure of solar cell panel (solar panel) determines the launch weight, launch volume of solar cell array.

[0003] From the perspective of commercial low-cost application, under the same conditions, the minimum launch weight and the minimum volume of the flexible solar panel are the most optimal design, and under the same conditions, the flexible solar panel has obvious advantages of lightweight and small volume compared with rigid and semi-rigid solar panels.

[0004] With the progress of flexible solar cell array related design and manufacturing technology, under the same launch weight and volume conditions, the power generation area of flexible solar cell array can be improved by several times or even 10 times compared with traditional rigid solar cell array (the larger the power, the more obvious the advantage), and the problem of power generation area limiting power generation capacity has a new solution.

[0005] The foregoing narrative is to provide general background information, and does not necessarily constitute prior art. CONTENT OF THE UTILITY MODEL

[0006] The utility model aims at providing a flexible solar wing, which fully embodies the advantages of large surface area when unfolded and small volume when folded and compressed.

[0007] The utility model provides a kind of flexible solar wing, including lifting mechanism, compression release mechanism, scissor type unfolding mechanism, flexible substrate, top rigid plate, bottom rigid plate, bottom support and top support;Two ends of the scissor type unfolding mechanism are connected with the bottom support and the top support respectively, the lifting mechanism is installed on the bottom support;Two ends of the front of the scissor type unfolding mechanism are connected with the top rigid plate and the bottom rigid plate respectively, a plurality of flexible substrates are connected between the top rigid plate and the bottom rigid plate on the scissor type unfolding mechanism, adjacent flexible substrates are connected by hinge, the bottom rigid plate and the flexible substrate are connected by hinge;The compression release mechanism is installed on the top rigid plate and the bottom rigid plate respectively;When the scissor type unfolding mechanism is in the state of being gathered, a plurality of flexible substrates will be stacked between the top rigid plate and the bottom rigid plate, and locked by the compression release mechanism;While the lifting mechanism is gathered on the bottom support;When the lifting mechanism is unfolded, the flexible solar wing pressed on the surface of star body is translational lifted, the scissor type unfolding mechanism is unfolded, and will drive flexible substrate and rigid plate to unfold.

[0008] Further, 8 flexible substrates are connected between the top rigid plate and the bottom rigid plate on the scissor type unfolding mechanism.

[0009] Further, the lifting mechanism includes base, lower end lifting plate, upper end lifting plate, 90 degree hinge, 180 degree hinge, first torsional spring and lock head;The base is square, the lower end lifting plate is connected to both sides of the base through the 90 degree hinge, the upper end lifting plate is connected to the other end of the lower end lifting plate through the 180 degree hinge, and the upper end lifting plate is connected to the bottom support through the 90 degree hinge;The first torsional spring for controlling the unfolding of hinge is connected to the 90 degree hinge and the 180 degree hinge;Lock hole is arranged in the middle of the base, and the lock head is connected to the bottom support;When the lower end lifting plate is in the state of being gathered, the lock hole is clamped on the lock head.

[0010] Further, the lock head is connected to the middle of the bottom support, and the two upper end lifting plates are symmetrically arranged about the lock head.

[0011] Further, the scissor type unfolding mechanism comprises a first bottom short rod, a second bottom short rod, a first top short rod, a second top short rod, a scissor rod group, a middle rotating shaft, a bending hinge and a second torsion spring; the first bottom short rod and the second bottom short rod are connected to the side of the bottom support away from the lifting mechanism; the first top short rod and the second top short rod are connected to the side of the top support close to the bottom support; the first bottom short rod and the second top short rod and the second bottom short rod and the first top short rod are hingedly connected by the bending hinge and the scissor rod group; the scissor rod group is formed by a plurality of scissor rods hingedly connected by the bending hinge; the middle parts of two scissor rods on the two scissor rod groups are rotatably connected by the middle rotating shaft; the second torsion spring is installed on the bending hinge.

[0012] Further, the scissor rod group is formed by five scissor rods hingedly connected by the bending hinge.

[0013] Further, the scissor type unfolding mechanism further comprises an unfolding guide rope and a constant force spring; the constant force spring is connected above the first bottom short rod and below the second bottom short rod of the bottom support; the unfolding guide rope is connected to the constant force spring and the other end of the unfolding guide rope is connected to the top support.

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

[0015] Further, the compression releasing mechanism comprises a compression rod and a memory alloy unlocking device; the memory alloy unlocking device is connected to the edge of the bottom rigid plate; the compression rod matched with the memory alloy unlocking device is connected to the edge of the top rigid plate; when the flexible solar wing is in the folded state, the compression rod is threadedly connected with the memory alloy unlocking device.

[0016] Further, two memory alloy unlocking devices are connected to the two long edges of the bottom rigid plate and one memory alloy unlocking device is connected to each of the two short edges of the bottom rigid plate.

[0017] The flexible solar wing fully embodies the advantages of large surface area in unfolding and small volume in folding and compression through the scissor type unfolding mechanism; the lifting mechanism lifts the whole solar wing to a certain distance away from the satellite body to prevent structural interference in the subsequent movement of the solar wing; in the whole unfolding process of the solar wing, the unfolding guide rope and the constant force spring are designed to assist the wing surface to complete the unfolding action, so as to avoid the wing surface shaking to cause the collision or hooking of the substrate with other components and cause the damage of the battery sheet; the unfolding guide rope is pulled to ensure the stable and orderly unfolding. BRIEF DESCRIPTION OF DRAWINGS

[0018] Figure 1 A planar schematic view of the deployed state of the flexible solar wing is provided for the embodiments of the present application.

[0019] Figure 2 A planar schematic view of the deployed state of the flexible solar wing is provided for the embodiments of the present application. Figure 1

[0020] Figure 3 A planar schematic view of the deployed state of the flexible solar wing is provided for the embodiments of the present application. Figure 1

[0021] Figure 4 A planar schematic view of the deployed state of the flexible solar wing is provided for the embodiments of the present application. Figure 1

[0022] Figure 5 A planar schematic view of the deployed state of the flexible solar wing is provided for the embodiments of the present application. Figure 1

[0023] Figure 6 A planar schematic view of the deployed state of the flexible solar wing is provided for the embodiments of the present application. Figure 1

[0024] Figure 7 A planar schematic view of the deployed state of the flexible solar wing is provided for the embodiments of the present application. Figure 1

[0025] Figure 8 A planar schematic view of the deployed state of the flexible solar wing is provided for the embodiments of the present application. Figure 1

[0026] Figure 9 A planar schematic view of the deployed state of the flexible solar wing is provided for the embodiments of the present application. Figure 1

[0027] Figure 10 A planar schematic view of the deployed state of the flexible solar wing is provided for the embodiments of the present application. Figure 1

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

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

[0030] 13, upper end lifting plate 14, 90-degree hinge 15, 180-degree hinge

[0031] 16, first torsional spring 17, lock head 18, lock hole

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

[0033] ​​​​​​​​​3, scissor unfolding mechanism 31, first bottom short rod 32, second bottom short rod 33, first top short rod 34, second top short rod 35, scissor rod group

[0034] 351, scissor rod 36, middle rotating shaft 37, bending hinge

[0035] 38, second torsion spring 39, unfolding guide rope 391, constant force spring

[0036] 4, flexible substrate 5, top rigid plate 6, bottom rigid plate

[0037] 7, bottom support 8, top support 9, tension spring DETAILED DESCRIPTION

[0038] The specific embodiments of the utility model are described in further detail below in combination with the drawings and examples. The following examples are used to illustrate the utility model, but are not used to limit the scope of the utility model.

[0039] The terms "first", "second", "third", "fourth" and the like in the specification and claims of the utility model are used to distinguish similar objects, and do not have to be used to describe a specific order or sequence.

[0040] Example 1

[0041] Figure 1 The planar schematic view of the unfolding state of the flexible solar wing provided in the embodiments of the utility model, Figure 2 The planar schematic view of the unfolding state of the flexible solar wing provided in the embodiments of the utility model, Figure 1 The planar schematic view of the unfolding state of the flexible solar wing provided in the embodiments of the utility model, Figure 3 The planar schematic view of the unfolding state of the flexible solar wing provided in the embodiments of the utility model, Figure 1 The planar schematic view of the unfolding state of the flexible solar wing provided in the embodiments of the utility model. Please refer to Figure 1 , Figure 2 , Figure 3 The flexible solar wing provided in the embodiments of the utility model comprises a lifting mechanism 1, a compression release mechanism 2, a scissor unfolding mechanism 3, a flexible substrate 4, a top rigid plate 5, a bottom rigid plate 6, a bottom support 7 and a top support 8. The bottom support 7 and the top support 8 are respectively connected to the two ends of the scissor unfolding mechanism 3, and the lifting mechanism 1 is installed on the bottom support 7. The top rigid plate 5 and the bottom rigid plate 6 are respectively connected to the two end parts in front of the scissor unfolding mechanism 3, and a plurality of flexible substrates 4 are connected between the top rigid plate 5 and the bottom rigid plate 6 on the scissor unfolding mechanism 3. Adjacent flexible substrates 4 are connected through hinges, and the bottom rigid plate 6 and the flexible substrate 4 are connected through hinges. The compression release mechanism 2 is respectively installed on the top rigid plate 5 and the bottom rigid plate 6.

[0042] It should be noted that when the scissor type unfolding mechanism 3 is in the folding state, a plurality of flexible substrates 4 are stacked between the top rigid plate 5 and the bottom rigid plate 6 and are locked through the pressing and releasing mechanism 2; at the same time, the lifting mechanism 1 is folded on the bottom support 7; when the lifting mechanism 1 is unfolded, the flexible solar wing pressed on the surface of the star body is lifted as a whole, the scissor type unfolding mechanism 3 is unfolded, and the flexible substrate 4 and the rigid plate are unfolded.

[0043] The flexible solar wing provided by the utility model fully embodies the advantages of large surface area when unfolded and small volume when folded and pressed through the scissor type unfolding mechanism 3; the whole solar wing is lifted a certain distance from the satellite body through the lifting mechanism 1, so that structural interference in the subsequent movement of the solar wing is prevented.

[0044] Further referring to Figure 1 、 Figure 2 , the utility model is connected with 8 flexible substrates 4 between the top rigid plate 5 and the bottom rigid plate 6 on the scissor type unfolding mechanism 3.

[0045] It should be noted that in the use process of the flexible solar wing of the utility model, 8 flexible substrates 4 and a top rigid plate 5 are pasted with thin three-junction gallium arsenide solar cells on the surfaces; at the same time, the top rigid plate 5 and the flexible substrate 4 and the bottom rigid plate 6 and the star body structure are directly arranged with flexible foam plates.

[0046] Figure 4 For Figure 1 the structure diagram of the lifting mechanism of the flexible solar wing, Figure 5 for Figure 1 the structure diagram of the combination of the lifting mechanism and the bottom support of the flexible solar wing, Figure 6 for Figure 1 the plane diagram of the folding state of the lifting mechanism of the flexible solar wing. Please refer to Figure 4 、 Figure 5 、 Figure 6The lifting mechanism 1 of this utility model includes 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 head 17. The base 11 is square. The lower lifting plate 12 is connected to both sides of the base 11 via the 90-degree hinge 14. The upper lifting plate 13 is connected to the other end of the lower lifting plate 12 via the 180-degree hinge 15. The other end of the upper lifting plate 13 is connected to the bottom support 7 via the 90-degree hinge 14. The first torsion spring 16 for controlling the hinge opening 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 support 7. When the lower lifting plate 12 is in the retracted state, the lock hole 18 is engaged with the lock head 17.

[0047] It should be noted that in the retracted state, the lower lifting plate 12, the upper lifting plate 13 and the base 11 are in a parallel state; the unfolding process of the lifting mechanism 1 requires the solar wings, which are initially pressed against the surface of the star, to be translated and lifted as a whole, and unfolded in a single degree of freedom in space. After unfolding into place, they are locked to ensure that the overall structure is in a stable state.

[0048] Specifically, driven by the first torsion spring 16, the lower lifting plate 12 rotates 90 degrees around the base 11, changing from a parallel state to a perpendicular state between the lower lifting plate 12 and the base 11, 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 support 7, changing from a parallel state to a perpendicular state between the upper lifting plate 13 and the bottom support 7; thereby realizing the overall translational lifting of the solar array.

[0049] After the satellite enters orbit, the lifting mechanism 1 of this utility model unlocks the lock 17 under the remote control or program control command of the satellite; the lifting mechanism 1 raises the entire solar array a certain distance away from the satellite body to prevent structural interference during the subsequent movement of the solar array.

[0050] Furthermore, the lock head 17 of this utility model is connected to the middle of the bottom bracket 7, and the two upper lifting plates 13 are symmetrically arranged about the lock head 17; thus improving the stability during the lifting process.

[0051] Figure 7 for Figure 1 A plan view of the scissor-type deployment mechanism of a medium-flexible solar array. Figure 8 for Figure 1 A schematic diagram of the bottom support structure of the medium-flexible solar panel. Figure 9 for Figure 1 A schematic diagram of the top support structure for the flexible solar panel. Please refer to... Figure 7 , Figure 8、 Figure 9 The scissor type unfolding 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 rod group 35, a middle rotating shaft 36, a bending hinge 37 and a second torsional spring 38.

[0052] It should be noted that under the pushing of the second torsional spring 38, the adjacent scissor rods 351 will be extended and opened, and the scissor type unfolding mechanism 3 will be unfolded in one direction; so as to drive the flexible substrate 4, the top rigid plate 5 and the bottom rigid plate 6 to be unfolded synchronously with the scissor type unfolding mechanism 3; in addition, the overall unfolding length of the solar wing can be calculated according to the solar wing area and the wing size, and the solar array stiffness and other index requirements are ensured.

[0053] Further, the scissor rod group 35 is formed by five scissor rods 351 connected through the bending hinge 37.

[0054] Further referring to Figure 1 、 Figure 8 The scissor type unfolding mechanism 3 further comprises an unfolding guide rope 39 and a constant force spring 391, the constant force spring 391 is connected above the first bottom short rod 31 and below the second bottom short rod 32 on the bottom support 7, 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 support 8.

[0055] It should be noted that in the overall unfolding process of the solar wing, in order to avoid the problem that the wing surface shaking causes the collision or hooking of the substrate with other components to cause the damage of the battery piece, the unfolding guide rope 39 and the constant force spring 391 are designed to assist the wing surface to complete the unfolding action. The unfolding limiting device is arranged at the bending hinge of the flexible substrate 4, the unfolding guide rope 39 is pulled, and the stable and orderly unfolding is ensured.

[0056] Specifically, the deployment guide rope 39 is in a tensionless state when the solar wing is in a compact state, and after deployment, the deployment guide rope 39 between the bottom bracket 7 and the top bracket 8 is always in a tension state through the constant force spring 391; the wing surface is deployed along the path of the deployment guide rope 39. In order to ensure that the deployment guide rope 39 does not generate additional disturbance force when in a compact state, prevent interference with the positioning of the wing surface when compact, the position of the guide rope limiting structure is adjusted during the whole satellite assembly process to realize the control of the deployment guide rope 39 in the compact state. The deployment guide rope 39 drives the constant force spring 391 to deploy and generate a constant tension force during the deployment process, and finally the overall mechanism gap of the deployment mechanism can be eliminated.

[0057] Further referring to Figure 1 、 Figure 2 The utility model discloses a plurality of tension springs 9 are connected between the top rigid plate 5 and adjacent flexible base plate 4.

[0058] It should be noted that the solar wing surface is in the state of being locked by the scissor type deployment mechanism 3 after being deployed to the position, in order to ensure that the whole base plate maintains a certain rigidity, and meets the requirement of the satellite on the battery array base frequency, the whole wing surface needs to be tensioned, that is, a tensioning force in the deployment direction still needs to be applied on the wing surface structure after the wing surface is completely deployed. This function can be guaranteed by connecting a plurality of tension springs 9 between the top rigid plate 5 and the adjacent flexible base plate 4; the top compact plate of the wing surface is fixedly connected with the top fixed structure of the deployment mechanism, a plurality of tension springs 9 are added between the top rigid plate 5 and the adjacent flexible base plate 4; the deployment length of the deployment mechanism is matched with the length of the wing surface of the solar wing, so that each tension spring 9 has sufficient stretching distance, and finally the pre-tension of the base plate is ensured, and all structures and the wing surface are kept in a stable state.

[0059] Figure 10 For Figure 1 The structure diagram of the compact release mechanism of the flexible solar wing is shown in FIG. 2. Please refer to Figure 10 The compact release mechanism 2 of the utility model comprises a compact rod 21 and a memory alloy unlocking device 22; the memory alloy unlocking device 22 is connected at the edge opening of the bottom rigid plate 6, and the compact rod 21 matched with the memory alloy unlocking device 22 is connected at the edge opening of the top rigid plate 5.

[0060] When the flexible solar wing is in a folded state, the compact rod 21 is threadedly connected with the memory alloy unlocking device 22. Specifically, two memory alloy unlocking devices 22 are connected on each long side of the bottom rigid plate 6, and one memory alloy unlocking device 22 is connected on each short side of the bottom rigid plate 6.

[0061] It should be noted that the memory alloy unlocking device 22 is a memory alloy disconnecting device of the prior art, and the sun wing unfolding mechanism, the rigid and flexible substrate 4 and the like are pressed and folded on the surface of the star body in the sun wing folding state;

[0062] When the memory alloy unlocking device 22 is unlocked by power supply, the compression rod 21 is pulled out by the compression rod 21 spring to a certain distance, so that the safety space between the compression rod 21 and the lower plate in the unfolding process is increased, and then the whole unfolding mechanism is unfolded to the position under the drive of the hinge and is locked.

[0063] Based on the above description, the utility model has the advantages that:

[0064] The flexible sun wing fully reflects the advantages of large surface area in unfolding and small volume in folding and pressing through the scissor type unfolding mechanism; the whole sun wing is lifted a certain distance from the satellite body through the lifting mechanism, so that structural interference in the subsequent movement of the sun wing is prevented; in the whole unfolding process of the sun wing, in order to avoid the problems of collision or hooking of the substrate and other components caused by wing surface shaking and battery piece damage, the unfolding guide rope and the constant force spring are designed to assist the wing surface to complete the unfolding action, the unfolding guide rope is pulled, and stable and orderly unfolding is ensured.

[0065] The above is only a specific implementation manner of the utility model, but the protection scope of the utility model is not limited to this, any person skilled in the art can easily think of changes or replacements within the technical range disclosed by the utility model, which should be covered in the protection scope of the utility model. Therefore, the protection scope of the utility model should be subject to the protection scope of the claims.

Claims

1. A flexible solar wing, characterized in that, The lifting mechanism (1), the compression release mechanism (2), the scissor unfolding mechanism (3), the flexible base plate (4), the top rigid plate (5), the bottom rigid plate (6), the bottom support (7) and the top support (8) are connected. The bottom support (7) and the top support (8) are respectively connected to the two ends of the scissor unfolding mechanism (3), and the lifting mechanism (1) is installed on the bottom support (7). The top rigid plate (5) and the bottom rigid plate (6) are respectively connected to the two ends of the front of the scissor unfolding mechanism (3), a plurality of flexible base plates (4) are connected between the top rigid plate (5) and the bottom rigid plate (6) on the scissor unfolding mechanism (3), adjacent flexible base plates (4) are connected through hinges, the bottom rigid plate (6) and the flexible base plate (4) are connected through a hinge, and the compression release mechanism (2) is installed on the top rigid plate (5) and the bottom rigid plate (6). When the scissor unfolding mechanism (3) is in a folded state, a plurality of flexible base plates (4) are stacked between the top rigid plate (5) and the bottom rigid plate (6), and are locked through the compression release mechanism (2); at the same time, the lifting mechanism (1) is folded on the bottom support (7). When the lifting mechanism (1) is unfolded, the flexible solar wing pressed on the surface of the star is lifted as a whole, the scissor unfolding mechanism (3) is unfolded, and the flexible base plate (4) and the rigid plate are unfolded.

2. The flexible solar wing of claim 1, wherein, Eight flexible base plates (4) are connected between the top rigid plate (5) and the bottom rigid plate (6) on the scissor unfolding mechanism (3).

3. The flexible solar wing of claim 1, wherein, The lifting mechanism (1) comprises a base (11), a lower end lifting plate (12), an upper end lifting plate (13), a 90-degree hinge (14), a 180-degree hinge (15), a first torsional spring (16) and a lock head (17). The base (11) is square, the lower end lifting plate (12) is connected to the two side edges of the base (11) through the 90-degree hinge (14), the upper end lifting plate (13) is connected to the other end of the lower end lifting plate (12) through the 180-degree hinge (15), and the other end of the upper end lifting plate (13) is connected to the bottom support (7) through the 90-degree hinge (14). The first torsional spring (16) for controlling the unfolding of the hinge is connected to the 90-degree hinge (14) and the 180-degree hinge (15), and the lock hole (18) is arranged in the middle of the base (11), and the lock head (17) is connected to the bottom support (7). When the lower end lifting plate (12) is in a folded state, the lock hole (18) is clamped on the lock head (17).

4. The flexible solar wing of claim 3, wherein, The lock head (17) is connected to the middle of the bottom support (7), and the two upper end lifting plates (13) are symmetrically arranged about the lock head (17).

5. The flexible solar wing of claim 1, wherein, The scissors type unfolding 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 scissors 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 connected to the bottom support (7) away from the lifting mechanism (1), and the first top short rod (33) and the second top short rod (34) are connected to the top support (8) close to the bottom support (7); The scissors 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 scissors rod group (35) is formed by a plurality of scissors rods (351) connected through the bending hinge (37), and the middle parts of two scissors rods (351) matched on the two scissors rod groups (35) are rotatably connected through the middle rotating shaft (36); the second torsion spring (38) is installed on the bending hinge (37).

6. The flexible solar wing of claim 5, wherein, The scissors rod group (35) is formed by five scissors rods (351) connected through the bending hinge (37).

7. The flexible solar wing of claim 5, wherein, The scissors type unfolding mechanism (3) further comprises an unfolding guide rope (39) and a constant force spring (391), and the constant force spring (391) is connected above the first bottom short rod (31) and below the second bottom short rod (32) on the bottom support (7), 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 support (8).

8. The flexible solar wing of claim 1, wherein, 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 of claim 1, wherein, The compression release mechanism (2) comprises a compression 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 compression rod (21) matched 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 the folded state, the compression rod (21) is threadedly connected with the memory alloy unlocking device (22).

10. The flexible solar wing of claim 9, wherein, Two memory alloy unlocking devices (22) are connected to each long edge of the bottom rigid plate (6), and one memory alloy unlocking device (22) is connected to each short edge of the bottom rigid plate (6).

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