Foldable stowed flexible solar wing module and solar wing

Abstract

The application provides a folding and retracting flexible solar wing module and a solar wing, which comprises a first frame, a second frame, a first folding arm assembly and a second folding arm assembly. The first frame and the second frame are arranged in parallel. The first folding arm assembly and the second folding arm assembly are arranged between the first frame and the second frame. The two ends of the first folding arm assembly are hinged to the first frame and the second frame on the same side respectively. The two ends of the second folding arm assembly are hinged to the first frame and the second frame on the same side respectively. The folding direction of the first folding arm assembly is perpendicular to the folding direction of the second folding arm assembly. The folding directions of the first folding arm assembly and the second folding arm assembly are perpendicular to each other, so that the overall degree of freedom of the solar wing module is reduced to one. During the unfolding process, the first frame and the second frame are always kept parallel, so that the solar wing module of the application does not need to exert an unfolding synchronization control during the unfolding process, and has the characteristics of simplicity and reliability.

Description

Technical Field

[0001] This invention relates to the field of solar panels for spacecraft, specifically to a foldable, retractable flexible solar panel module and solar panel. Background Technology

[0002] Solar panels provide power for satellites and other spacecraft to operate in orbit and are a core component of satellites. The construction of large satellite constellations requires the ability to launch multiple satellites with a single rocket, which places higher demands on the solar panel's retractable ratio—that is, the ratio of the solar panel's area in its deployed state to its volume in its retracted state must reach 1:100 m² / m². 3 above.

[0003] To achieve a high storage ratio, flexible solar panels using flexible substrates have become a development trend for future spacecraft solar panels. Currently, flexible solar panels mainly employ two folding methods. The first is the roll-up folding method, but due to the limitation of the minimum bending curvature of the solar cells, the radius of curvature of the roll-up flexible solar panel after folding is difficult to reduce, making it difficult to improve its storage ratio. The second is the fan-shaped folding folding method, which connects multiple flexible solar panel substrates into a whole through piano hinges and then folds them. In orbit, the entire panel is unfolded by tensioning at both ends of the flexible substrates. However, during the unfolding process, the attitude and unfolding sequence of the multiple flexible substrates cannot be controlled, resulting in a higher risk of collision and snagging.

[0004] The existing patent document with publication number CN118220539A discloses a retractable solar array based on shape memory materials, its working method, and a spacecraft. The retractable solar array based on shape memory materials utilizes the characteristics of shape memory materials such as shape memory polymers and shape memory alloys to achieve self-deformation drive. The substrate is rolled up and extended by a roll-up drive component made of shape memory materials, thereby realizing the flexible roll-up and retractable of flexible solar cells.

[0005] Existing patent document CN113401368A discloses a secondary unfolding fan-shaped solar array, comprising: a disc hinge with two relatively rotatable discs; a drive mechanism connected to the disc hinge and used to drive one disc to rotate around the other; two unfolding mechanisms, the first ends of which are respectively connected to the two discs; two cover plates, parallel and oppositely arranged, the second ends of which are respectively connected to one cover plate; a flexible solar array, fan-shaped and located between the two cover plates, with the two sides of the flexible solar array away from the disc hinge fixed to the two cover plates, and the two sides of the flexible solar array near the disc hinge fixed to the first ends of the two unfolding mechanisms; and a plurality of telescopic struts, arranged on the flexible solar array and circumferentially around the disc hinge, with the two ends of the telescopic struts respectively connected to the ends of the flexible solar array near and away from the disc hinge.

[0006] Existing rollable and fan-shaped folding flexible solar panels require space mechanisms such as roll-up rods or scissor differentials to drive the deployment of the flexible substrate. However, the highly reliable deployment of large space deployment mechanisms has always been a challenge in spacecraft development. As the power of satellites and other spacecraft continues to increase, the required solar panel area is constantly growing. When the solar panel area exceeds 30㎡, existing rollable and fan-shaped folding flexible solar panel technologies will face the problem of excessively low on-orbit fundamental frequency, resulting in ultra-low frequency flexural vibrations that will affect the attitude control accuracy of the spacecraft. Furthermore, existing flexible solar panel solutions do not employ modular design; any change in the solar panel area requires significant modifications to the corresponding deployment mechanism, clamping and release device, and other components, hindering rapid design iteration and mass production.

[0007] Therefore, traditional flexible solar arrays, due to their lack of modular design, suffer from limitations in improving their retractability, resulting in lower on-orbit fundamental frequencies and an inability to achieve modular expansion. Currently, the modular design of large flexible solar arrays with high retractability remains a challenge for the rapid development and deployment of spacecraft. Summary of the Invention

[0008] To address the shortcomings of existing technologies, the purpose of this invention is to provide a foldable, retractable flexible solar panel module and solar panel.

[0009] According to the present invention, a foldable flexible solar panel module includes a first frame, a second frame, a first folding arm assembly, and a second folding arm assembly. The first frame and the second frame are arranged in parallel with each other. The first folding arm assembly and the second folding arm assembly are both disposed between the first frame and the second frame. The two ends of the first folding arm assembly are respectively hinged to the first frame and the second frame on the same side. The two ends of the second folding arm assembly are respectively hinged to the first frame and the second frame on the other side.

[0010] The folding direction of the first folding arm assembly is perpendicular to the folding direction of the second folding arm assembly.

[0011] Preferably, the folding direction of the first folding arm assembly includes a horizontal direction, and the folding direction of the second folding arm assembly includes a vertical direction.

[0012] Preferably, the first folding arm assembly includes a first folding arm and a second folding arm that are hinged together, and a first torsion spring is disposed at the hinge point between the first folding arm and the second folding arm.

[0013] Preferably, the second folding arm assembly includes a third folding arm and a fourth folding arm that are hinged together, and a second torsion spring is disposed at the hinge point between the third folding arm and the fourth folding arm.

[0014] Preferably, the first folding arm assembly is provided with a flexible substrate, the end of which is fixedly connected to the first folding arm assembly, and the first folding arm assembly drives the flexible substrate to fold or unfold.

[0015] Preferably, the flexible substrate includes a first flexible substrate and a second flexible substrate, with the end of the first flexible substrate fixed to a first folding arm and the second flexible substrate fixed to a second folding arm.

[0016] Preferably, the first folding arm assembly includes two sets, one set of the first folding arm assembly is disposed at one end of the first frame and the second frame on the same side, and the other set of the first folding arm assembly is disposed at the other end of the first frame and the second frame on the same side.

[0017] Preferably, the second folding arm assembly includes two sets, one set of the second folding arm assembly is disposed at one end of the first frame and the second frame on the same side, and the other set of the second folding arm assembly is disposed at the other end of the first frame and the second frame on the same side.

[0018] Preferably, the first folding arm assembly, the second folding arm assembly, the first frame, and the second frame are all provided with clamping points;

[0019] In the folded state, the clamping points of the first folding arm assembly, the first frame, and the second frame are aligned, and the clamping points of the second folding arm assembly, the first frame, and the second frame are also aligned.

[0020] The present invention provides a foldable flexible solar panel, comprising at least two foldable flexible solar panel modules connected in series, wherein the direction of the series connection includes the unfolding direction of the solar panel modules.

[0021] Compared with the prior art, the present invention has the following beneficial effects:

[0022] 1. By setting the folding directions of the first folding arm assembly and the second folding arm assembly to be perpendicular to each other, the overall degree of freedom of the solar wing module is reduced to 1. This ensures that the first frame and the second frame remain parallel during the deployment process. The two frames can only undergo relative translation and cannot rotate relative to each other. As a result, the solar wing module of the present invention does not require deployment synchronization control during the deployment process, and has the characteristics of simplicity and reliability.

[0023] 2. The present invention achieves folding and retraction by setting a first folding arm assembly and a second folding arm assembly, and realizes passive unfolding. It has the technical characteristics of small volume after folding, no need for electric drive to unfold, simple mechanism and high reliability.

[0024] 3. This invention utilizes two frames and two folding arm assemblies with different folding directions to form a space truss structure, which has the technical feature of high overall rigidity after unfolding.

[0025] 4. The solar wing module designed in this invention is a single modular design. By increasing or decreasing the number of foldable flexible solar wing modules, flexible solar wing modules of different areas for spacecraft can be realized, and mass production can be achieved at the same time.

[0026] 5. The solar array of the present invention includes multiple foldable flexible solar array modules. The deployment process of each foldable flexible solar array module is independent of each other, and the failure of a single solar array module will not spread, which greatly improves the overall reliability of the solar array. Attached Figure Description

[0027] Other features, objects, and advantages of the present invention will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings:

[0028] Figure 1 This mainly illustrates the schematic diagram of the solar panel module in the deployed state of the present invention;

[0029] Figure 2 This mainly illustrates the exploded view of the solar panel module in the deployed state of this invention;

[0030] Figure 3 This mainly illustrates the schematic diagram of the retracted state of the solar panel module of this invention;

[0031] Figure 4 This mainly illustrates the schematic diagram of the solar panel module in a semi-deployed state.

[0032] Figure 5 This mainly illustrates the schematic diagram of the first folding arm assembly in a semi-expanded state.

[0033] Figure 6 This mainly illustrates the schematic diagram of the second folding arm assembly in a semi-deployed state.

[0034] Figure 7 The main illustration is a schematic diagram of the structure of multiple solar array modules connected in series to form a solar array.

[0035] As shown in the figure:

[0036] Flexible substrate 1 Second folding arm 32

[0037] First flexible substrate 11 First torsion spring 33

[0038] Second flexible substrate 12 Second folding arm assembly 40

[0039] First frame 21, third folding arm 41

[0040] Second frame 22 Fourth folding arm 42

[0041] First folding arm assembly 30 Second torsion spring 43

[0042] First folding arm 31 Detailed Implementation

[0043] The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the protection scope of the present invention.

[0044] like Figures 1 to 4 As shown, a foldable flexible solar panel module according to the present invention is mainly used for spacecraft solar panels. It includes a first frame 21, a second frame 22, a first folding arm assembly 30, and a second folding arm assembly 40. The first frame 21 and the second frame 22 are arranged parallel to each other. The first folding arm assembly 30 and the second folding arm assembly 40 are both disposed between the first frame 21 and the second frame 22. The two ends of the first folding arm assembly 30 are hinged to the first frame 21 and the second frame 22 on the same side, respectively. The two ends of the second folding arm assembly 40 are hinged to the first frame 21 and the second frame 22 on the other side, respectively. The folding direction of the first folding arm assembly 30 and the folding direction of the second folding arm assembly 40 are perpendicular to each other. The solar panel module includes a folded state and an unfolded state. In the folded state, the vertical distance between the first frame 21 and the second frame 22 is the shortest, and the unfolding angle of both the first folding arm assembly 30 and the second folding arm assembly 40 is 0°. In the unfolded state, the vertical distance between the first frame 21 and the second frame 22 is the longest, and the unfolding angle of both the first folding arm assembly 30 and the second folding arm assembly 40 is 180°.

[0045] like Figure 4 As shown, the folding direction of the first folding arm assembly 30 can be set to the horizontal direction, and the folding direction of the second folding arm assembly 40 can be set to the vertical direction. During the deployment of the solar wing module, since the deployment directions of the first folding arm assembly 30 and the second folding arm assembly 40 are perpendicular to each other, the first frame 21 and the second frame 22 cannot rotate relative to each other, but can only translate relative to each other. By setting the folding directions of the first folding arm assembly 30 and the second folding arm assembly 40 to be perpendicular to each other, the present invention reduces the overall degree of freedom of the solar wing module to 1. This ensures that during the deployment of the solar wing module, the first frame 21 and the second frame 22 remain parallel at all times, and the two frames can only translate relative to each other, without relative rotation. Consequently, the solar wing module of the present invention does not require deployment synchronization control during deployment, and has the characteristics of simplicity and reliability.

[0046] like Figures 1 to 4As shown, a flexible substrate 1 is disposed on the first folding arm assembly 30, and the surface of the flexible substrate 1 is used to attach solar cells. The end of the flexible substrate 1 is fixedly connected to the first folding arm assembly 30, and the first folding arm assembly 30 drives the flexible substrate 1 to fold or unfold.

[0047] The first folding arm assembly 30 and the second folding arm assembly 40 can each be configured to include a set. The first folding arm assembly 30 is disposed at the top or bottom of the first frame 21 and the second frame 22, and the second folding arm assembly 40 is disposed at the top or bottom of the first frame 21 and the second frame 22. The top or bottom of the flexible substrate 1 is fixedly connected to the first folding arm assembly 30. The two ends of the first folding arm assembly 30 and the two ends of the second folding arm assembly 40 are respectively hinged to the first frame 21 and the second frame 22, which can realize the folding or unfolding of the solar panel module.

[0048] A preferred design comprises two sets of both the first folding arm assembly 30 and the second folding arm assembly 40. The two ends of the flexible substrate 1 are fixedly connected to the two sets of the first folding arm assemblies 30. One set of the first folding arm assemblies 30 is hinged at both ends to the top of the first frame 21 and the top of the second frame 22, respectively; the other set of the first folding arm assemblies 30 is hinged at both ends to the bottom of the first frame 21 and the bottom of the second frame 22, respectively; the other set of the second folding arm assemblies 40 is also hinged at both ends to the bottom of the first frame 21 and the bottom of the second frame 22, respectively. After the two sets of the first folding arm assemblies 30 and the two sets of the second folding arm assemblies 40 are hinged to the two frames, the folding directions of the first folding arm assemblies 30 and the second folding arm assemblies 40 are perpendicular to each other, forming a single-degree-of-freedom spatially foldable and deployable three-dimensional truss. Two sets of first folding arm assemblies 30 and two sets of second folding arm assemblies 40 are folded or unfolded synchronously, the two frames remain parallel at all times, and the flexible substrate 1 is installed on the spatial three-dimensional truss structure, realizing a flexible solar panel module with high overall rigidity.

[0049] like Figure 5 As shown, the first folding arm assembly 30 includes a first folding arm 31, a second folding arm 32, and a first torsion spring 33. The first folding arm 31 and the second folding arm 32 are hinged together. The first torsion spring 33 serves as a power source and stores elastic potential energy to drive the first folding arm assembly 30 to unfold, thereby driving the first folding arm assembly 30 to unfold from 0° in the folded state to 180° in the unfolded state. The maximum unfolding angle of the first folding arm assembly 30 is 180°. After the first folding arm assembly 30 unfolds to 180°, the first folding arm 31 and the second folding arm 32 will lock together.

[0050] like Figure 6As shown, the second folding arm assembly 40 includes a third folding arm 41, a fourth folding arm 42, and a second torsion spring 43. The third folding arm 41 and the fourth folding arm 42 are hinged together. The second torsion spring 43 serves as a power source, storing elastic potential energy to drive the second folding arm assembly 40 to unfold, thereby driving the second folding arm assembly 40 to unfold from 0° in the folded state to 180° in the unfolded state. The maximum unfolding angle of the second folding arm assembly 40 is 180°. After the second folding arm assembly 40 unfolds to 180°, the third folding arm 41 and the fourth folding arm 42 will lock together.

[0051] When the solar array module is fully deployed, the first folding arm assembly 30 and the second folding arm assembly 40 both have an deployment angle of 180°, and the solar array module is in the deployed state, as shown below. Figure 1 As shown; when the solar array module is fully retracted, the deployment angle of both the first folding arm assembly 30 and the second folding arm assembly 40 is 0°, and the solar array module is in a folded state, as... Figure 3 As shown. Specifically, the flexible substrate 1 can be mechanically connected to the first folding arm 31 and the second folding arm 32 via screws. The first folding arm 31 and the second folding arm 32 are hinged together by a first pin and a first torsion spring 33. The first pin is preferably a cylindrical pin, which passes through corresponding through holes on the first folding arm 31 and the second folding arm 32, connecting the first folding arm 31 and the second folding arm 32 together, allowing the first folding arm 31 and the second folding arm 32 to rotate freely around the axis of the first pin. The first torsion spring 33 is preferably a helical spring, which is sleeved on the first pin, with its two ends connected to the first folding arm 31 and the second folding arm 32 respectively. When the first folding arm 31 and the second folding arm 32 rotate around the first pin, the first torsion spring 33 deforms. When the first folding arm 31 and the second folding arm 32 are released from their folded state, the first torsion spring 33 generates an elastic force, thereby unfolding the first folding arm 31 and the second folding arm 32. Similarly, the third folding arm 41 and the fourth folding arm 42 are connected by the second pin and the second torsion spring 43, and have the same unfolding principle.

[0052] Specifically, the flexible substrate 1 can be configured to include a first flexible substrate 11 and a second flexible substrate 12. The end of the first flexible substrate 11 is fixed to a first folding arm 31, and the second flexible substrate 12 is fixed to a second folding arm 32. Both ends of the first flexible substrate 11 are fixedly connected to the two first folding arms 31, and both ends of the second flexible substrate 12 are fixedly connected to the two second folding arms 32. When the first folding arm assembly 30 folds, it drives the first flexible substrate 11 and the second flexible substrate 12 to fold simultaneously. When the first folding arm assembly 30 unfolds, it drives the first flexible substrate 11 and the second flexible substrate 12 to unfold simultaneously. The area of ​​the first flexible substrate 11 and the second flexible substrate 12 can be set according to the required area of ​​the solar cell. For example, the areas of the first flexible substrate 11 and the second flexible substrate 12 can be set to be equal, and the first flexible substrate 11 and the second flexible substrate 12 can be symmetrically arranged about the axis of the first pin to achieve a good folding effect.

[0053] The first folding arm assembly 30, the second folding arm assembly 40, the first frame 21, and the second frame 22 are all provided with pressing points. In the folded state, the pressing points of the first folding arm assembly 30, the first frame 21, and the second frame 22 are aligned, and the pressing points of the second folding arm assembly 40, the first frame 21, and the second frame 22 are also aligned. The pressing points are preferably circular pressing points. Specifically, taking two sets of first folding arm assemblies 30 and two sets of second folding arm assemblies 40 as examples, in the first folding arm assembly 30, circular pressing points are provided on the two first folding arms 31 and the two second folding arms 32. In the second folding arm assembly 40, circular pressing points are provided on the two third folding arms 41 and the two fourth folding arms 42. At the same time, circular pressing points are provided at four positions on the first frame 21 and four positions on the second frame 22. Preferably, two positions on the first frame 21 are respectively located at the center of the top rod and the bottom rod of the first frame 21, and two positions on the second frame 22 are respectively located at the center of the top rod and the bottom rod of the second frame 22. The other two positions on the first frame 21 are respectively located on one side rod of the first frame 21, and the other two positions on the second frame 22 are respectively located on one side rod of the second frame 22. These two side rods are used to connect the second folding arm assembly 40.

[0054] When the solar array module is fully retracted (folded state), the circular clamping points of one of the first folding arms 31 and one of the second folding arms 32 are aligned with the circular clamping points at the center of the top rod of the first frame 21 and the center of the top rod of the second frame 22, respectively. Similarly, the circular clamping points of the other two first folding arms 31 and second folding arms 32 are aligned with the circular clamping points at the center of the bottom rod of the first frame 21 and the center of the bottom rod of the second frame 22. One of the third folding arms 41 and one of the fourth folding arms 42 are aligned with the circular clamping points on the upper part of the side rods of the first frame 21 and the second frame 22, respectively. The other three third folding arms 41 and the other four fourth folding arms 42 are aligned with the circular clamping points on the lower part of the side rods of the first frame 21 and the second frame 22. This allows the first folding arm assembly 30, the second folding arm assembly 40, the first frame 21, and the second frame 22 to be retracted and pressed firmly onto the spacecraft.

[0055] In a preferred embodiment, the flexible substrate 1 is made of a composite material of polyimide and glass fiber, and has a thickness of 0.5 mm. The first frame 21 and the second frame 22 are both made of carbon fiber composite square rods bonded to aluminum alloy joints. The first folding arm 31, the second folding arm 32, the third folding arm 41, and the fourth folding arm 42 are all made of aluminum alloy. The first torsion spring 33 and the second torsion spring 43 are both made of 65Mn spring steel. The flexible substrate 1 has a width of 500 mm and a length of 2000 mm, allowing for the placement of solar cells on an area of ​​0.9 m². With the first frame 21 and the second frame 22 both having a thickness of 5 mm, the total thickness of the solar panel module after folding is 10 mm, and the unfolded length is 1100 mm. The unfolded direction has a folding ratio of 110, achieving a high folding ratio characteristic.

[0056] like Figure 7 As shown, the present invention also provides a foldable flexible solar array, comprising at least two foldable flexible solar array modules connected in series, the series direction including the deployment direction of the solar array modules. To meet the spacecraft's requirements for solar arrays of different areas, the total area of ​​the spacecraft's solar array can be adjusted by configuring the number of foldable flexible solar array modules.

[0057] When the solar array is in the folded state, the first folding arm assembly 30 of the multiple solar array modules is pressed together by a pressing device through its own pressing points, the second folding arm assembly 40 is pressed together by a pressing device through its own pressing points, and the first frame 21 and the second frame 22 are pressed together by a pressing device through their own pressing points. The pressing device can be a pyrotechnic nut.

[0058] In one specific embodiment, a solar array is composed of ten foldable flexible solar array modules connected in series, with the series connection direction being the deployment direction of the foldable flexible solar array modules. In the launch state, each solar array module is in a folded state, with the first folding arm assembly 30 and the second folding arm assembly 40 both having a deployment angle of 0°. The solar array is in a folded state. After the solar array enters orbit, according to satellite commands, the clamping device unlocks, and the first folding arm assembly 30 unfolds to 180° under the drive of the first torsion spring 33. The second folding arm assembly 40 automatically unfolds to 180° under the drive of the second torsion spring 43. When all ten solar array modules provided by this invention are in the unfolded state, the entire solar array reaches the unfolded state.

[0059] The solar array of the present invention includes multiple foldable flexible solar array modules. The deployment process of each foldable flexible solar array module is independent of each other, and the failure of a single solar array module will not spread, which greatly improves the overall reliability of the solar array.

[0060] In the description of this application, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application.

[0061] Specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

Claims

1. A foldable, retractable flexible solar panel module, characterized in that, The assembly includes a first frame (21), a second frame (22), a first folding arm assembly (30), and a second folding arm assembly (40). The first frame (21) and the second frame (22) are arranged in parallel relative to each other. The first folding arm assembly (30) and the second folding arm assembly (40) are both arranged between the first frame (21) and the second frame (22). The two ends of the first folding arm assembly (30) are respectively hinged to the first frame (21) and the second frame (22) on the same side. The two ends of the second folding arm assembly (40) are respectively hinged to the first frame (21) and the second frame (22) on the other side. The folding direction of the first folding arm assembly (30) is perpendicular to the folding direction of the second folding arm assembly (40); The first folding arm assembly (30) includes a first folding arm (31) and a second folding arm (32) that are hinged together, and a first torsion spring (33) is provided at the hinge joint between the first folding arm (31) and the second folding arm (32). The second folding arm assembly (40) includes a third folding arm (41) and a fourth folding arm (42) that are hinged together, and a second torsion spring (43) is provided at the hinge of the third folding arm (41) and the fourth folding arm (42). The first folding arm assembly (30) is provided with a flexible substrate (1), the end of the flexible substrate (1) is fixedly connected to the first folding arm assembly (30), and the first folding arm assembly (30) drives the flexible substrate (1) to fold or unfold. The flexible substrate (1) includes a first flexible substrate (11) and a second flexible substrate (12). The end of the first flexible substrate (11) is fixed on the first folding arm (31), and the second flexible substrate (12) is fixed on the second folding arm (32).

2. The foldable, retractable flexible solar panel module as described in claim 1, characterized in that, The folding direction of the first folding arm assembly (30) includes the horizontal direction, and the folding direction of the second folding arm assembly (40) includes the vertical direction.

3. The foldable, retractable flexible solar panel module as described in claim 1, characterized in that, The first folding arm assembly (30) includes two sets, one set of the first folding arm assembly (30) is disposed at one end of the first frame (21) and the second frame (22) on the same side, and the other set of the first folding arm assembly (30) is disposed at the other end of the first frame (21) and the second frame (22) on the same side.

4. The foldable, retractable flexible solar panel module as described in claim 1, characterized in that, The second folding arm assembly (40) includes two sets, one set of the second folding arm assembly (40) is disposed at one end of the first frame (21) and the second frame (22) on the same side, and the other set of the second folding arm assembly (40) is disposed at the other end of the first frame (21) and the second frame (22) on the same side.

5. The foldable, retractable flexible solar panel module as described in claim 1, characterized in that, The first folding arm assembly (30), the second folding arm assembly (40), the first frame (21) and the second frame (22) are all provided with pressing points; In the folded state, the pressing points of the first folding arm assembly (30), the first frame (21) and the second frame (22) are aligned, and the pressing points of the second folding arm assembly (40), the first frame (21) and the second frame (22) are aligned.

6. A foldable, retractable flexible solar panel, characterized in that, It includes at least two foldable, collapsible flexible solar array modules connected in series as described in any one of claims 1 to 5, wherein the direction of the series connection includes the deployment direction of the solar array modules.

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