Folding type folding flexible solar wing module and solar wing

Abstract

The invention provides a folding type folding flexible solar wing module and a solar wing, the folding type folding flexible solar wing module 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 oppositely arranged in parallel, and the first folding arm assembly and the second folding arm assembly are both 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, and the two ends of the second folding arm assembly are hinged to the first frame and the second frame on the other 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 arranged to be perpendicular to each other, so that the overall degree of freedom of the solar wing module is reduced to one, and in the unfolding process, the first frame and the second frame are kept parallel all the time, so that unfolding synchronization control does not need to be applied in the unfolding process of the solar wing module; the method is simple and reliable.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of space spacecraft solar sail, in particular to a folding and folding flexible solar wing module and a solar wing. BACKGROUND

[0002] The solar wing provides power for the on-orbit operation of the spacecraft such as satellite, and is the core component of the satellite. The construction of large satellite constellation requires the satellite to realize one rocket multi-satellite launch, and further puts forward higher requirements on the storage ratio of the solar wing. The area in the unfolded state and the volume in the folded state of the solar wing reach 1:100 m2 / m3. 3 The above.

[0003] To realize high storage ratio, flexible solar wing with flexible substrate has become the development trend of future spacecraft solar wing. At present, there are two kinds of folding modes for flexible solar wing. The first is the winding folding mode, but under the limitation of the minimum bending curvature of the solar cell, the curvature radius of the winding type flexible solar wing after folding is difficult to reduce, which leads to the difficulty in improving the storage ratio. The second is the fan-shaped folding mode. The fan-shaped folding scheme connects multiple flexible solar wing substrates into a whole through a piano hinge and then folds. The whole is unfolded in orbit by tensioning at both ends of the flexible substrate, but the attitude and unfolding timing of multiple flexible substrates cannot be controlled during unfolding, which has high collision and hooking risk.

[0004] The existing patent document with publication number CN118220539A discloses an unfolding and folding solar wing based on shape memory material, a working method thereof and a spacecraft. The unfolding and folding solar wing based on shape memory material is based on the characteristics of shape memory polymers and shape memory alloys. The shape memory characteristics of the shape memory material are used to realize self-deformation driving. The winding driving element made of shape memory material is used to realize the winding and stretching of the substrate, and then the flexible winding and unfolding of the flexible solar cell are realized.

[0005] The existing patent document with publication number CN113401368A discloses a secondary unfolding fan-shaped solar wing, which comprises: a disc hinge provided with two rotatable rotating discs; a driving mechanism connected to the disc hinge and used to drive one rotating disc to rotate around the other rotating disc; two unfolding mechanisms, the first ends of the two unfolding mechanisms are respectively connected to the two rotating discs; two cover plates, which are parallel and opposite to each other, the second ends of the two unfolding mechanisms are respectively connected to one cover plate; a flexible solar wing, which is fan-shaped and arranged between the two cover plates, the two sides of the flexible solar wing away from the disc hinge are respectively fixed to the two cover plates, and the two sides of the flexible solar wing close to the disc hinge are respectively fixed to the first ends of the two unfolding mechanisms; and a plurality of telescopic struts arranged on the flexible solar wing and arranged in a circular manner around the disc hinge, the two ends of the telescopic struts are respectively connected to the two ends of the flexible solar wing close to and away from the disc hinge.

[0006] The existing flexible solar wing of the roll type and the fan-shaped folding type needs to realize the deployment driving of the flexible substrate through a space mechanism such as a roll rod or a scissors difference, but the high-reliable deployment of the large space deployment mechanism has always been a difficulty in the development of a spacecraft. With the continuous increase of the power of the spacecraft such as a satellite, the area of the solar wing required is continuously increased. When the area of the solar wing is increased to more than 30 m2, the existing flexible solar wing of the roll type and the fan-shaped folding type will face the problem of too low in-orbit fundamental frequency, which will generate ultra-low frequency flexible vibration in orbit, and further affect the attitude control accuracy of the spacecraft. Meanwhile, the existing flexible solar wing scheme does not adopt a modular design, and once the area of the solar wing is changed, the corresponding deployment mechanism, compression release device and other components will need a large amount of changes, and it is difficult to realize rapid design iteration and batch production.

[0007] Therefore, the traditional flexible solar wing does not adopt a modular design, has a difficult to improve storage ratio, a low in-orbit fundamental frequency, and cannot realize modular expansion. At present, the modular design of the large flexible solar wing with a high storage ratio is a difficulty in the rapid development and deployment of a spacecraft. SUMMARY

[0008] In view of the defects in the prior art, the purpose of the present application is to provide a folding and folding flexible solar wing module and a solar wing.

[0009] According to the folding and folding flexible solar wing module provided by the present application, 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, and the two ends of the second folding arm assembly are hinged to the first frame and the second frame on the same 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 connected by a hinge, and a first torsional spring is arranged at the hinge of 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 connected by a hinge, and a second torsional spring is arranged at the hinge of the third folding arm and the fourth folding arm.

[0014] Preferably, a flexible substrate is arranged on the first folding arm assembly, and the end of the flexible substrate is fixedly connected with the first folding arm assembly.

[0015] Preferably, the flexible substrate comprises a first flexible substrate and a second flexible substrate, the end of the first flexible substrate is fixed on the first folding arm, and the second flexible substrate is fixed on the second folding arm.

[0016] Preferably, the first folding arm assembly comprises two groups, one group of the first folding arm assembly is arranged at one end of the same side first frame and second frame, and the other group of the first folding arm assembly is arranged at the other end of the same side first frame and second frame.

[0017] Preferably, the second folding arm assembly comprises two groups, one group of the second folding arm assembly is arranged at one end of the same side first frame and second frame, and the other group of the second folding arm assembly is arranged at the other end of the same side first frame and second frame.

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

[0019] In the folded state, the pressing points arranged on the first folding arm assembly, the first frame and the second frame are aligned, and the pressing points arranged on the second folding arm assembly, the first frame and the second frame are aligned.

[0020] The application provides a folding and folding flexible solar wing, which comprises at least two serially connected folding and folding flexible solar wing modules.

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

[0022] 1、The folding direction of the first folding arm assembly and the second folding arm assembly is perpendicular to each other, so that the overall degree of freedom of the solar wing module is reduced to 1, so that the first frame and the second frame are always parallel during the unfolding process, and the two frames can only move horizontally relative to each other and cannot rotate relative to each other, thereby the solar wing module of the application does not need to apply an unfolding synchronization control during the unfolding process, and has the characteristics of simplicity and reliability.

[0023] 2、The first folding arm assembly and the second folding arm assembly are arranged to realize folding and folding, and passive unfolding, and have the technical characteristics of small volume after folding, no need for electric driving to unfold, simple mechanism and high reliability.

[0024] 3、The two frames and the two folding arm assemblies with different folding directions form a space truss structure, and have the technical characteristic of high overall stiffness after unfolding.

[0025] 4、The solar wing module designed in the application is a single modular design, by increasing or reducing the number of the folded and retracted flexible solar wing modules, different area spacecraft flexible solar wings can be realized, and batch production preparation can be realized at the same time;

[0026] 5、The solar wing of the application contains a plurality of folded and retracted flexible solar wing modules, the unfolding process of each folded and retracted flexible solar wing module is independent of each other, the failure of a single solar wing module cannot spread, and the reliability of the whole solar wing is greatly improved. BRIEF DESCRIPTION OF DRAWINGS

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

[0028] Figure 1 The main embodiment of the application is a solar wing module unfolded state schematic diagram;

[0029] Figure 2 The main embodiment of the application is a solar wing module unfolded state schematic diagram;

[0030] Figure 3 The main embodiment of the application is a solar wing module folded state schematic diagram;

[0031] Figure 4 The main embodiment of the application is a solar wing module half-unfolded state schematic diagram;

[0032] Figure 5 The main embodiment of the application is a first folded arm assembly half-unfolded state schematic diagram;

[0033] Figure 6 The main embodiment of the application is a second folded arm assembly half-unfolded state schematic diagram;

[0034] Figure 7 The main embodiment of the application is a plurality of solar wing modules connected in series to form a solar wing structure schematic diagram.

[0035] Shown in the figure:

[0036] Flexible substrate 1 second folded arm 32

[0037] First flexible substrate 11 first torsional spring 33

[0038] Second flexible substrate 12 second folded arm assembly 40

[0039] First frame 21 third folded arm 41

[0040] Second frame 22 fourth folded arm 42

[0041] First folded arm assembly 30 second torsional spring 43

[0042] first folding arm 31 DETAILED DESCRIPTION

[0043] The application will be described in detail below with specific examples. The following examples will help those skilled in the art to further understand the application, but do not limit the application in any form. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the application. These are within the scope of protection of the application.

[0044] As shown in Figures 1 to 4 According to the folding type folding flexible solar wing module provided by the application, the first folding arm assembly 30 and the second folding arm assembly 40 are arranged between the first frame 21 and the second frame 22, the folding direction of the first folding arm assembly 30 is perpendicular to the folding direction of the second folding arm assembly 40, and the solar wing module includes a folded state and an unfolded state. In the folded state, the perpendicular distance between the first frame 21 and the second frame 22 is the shortest, and the unfolding angles of the first folding arm assembly 30 and the second folding arm assembly 40 are both 0°. In the unfolded state, the perpendicular distance between the first frame 21 and the second frame 22 is the longest, and the unfolding angles of the first folding arm assembly 30 and the second folding arm 32 are both 180°.

[0045] As shown in Figure 4 The folding direction of the first folding arm assembly 30 can be horizontal, and the folding direction of the second folding arm assembly 40 can be vertical. During the unfolding process of the solar wing module, since the unfolding 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 produce relative rotation, but can only produce relative translation. By arranging the folding directions of the first folding arm assembly 30 and the second folding arm assembly 40 to be perpendicular to each other, the overall degree of freedom of the solar wing module is reduced to 1, so that the first frame 21 and the second frame 22 can always remain parallel during the unfolding process of the solar wing module, and the two frames can only produce relative translation and cannot produce relative rotation, thereby eliminating the need for the solar wing module of the application to exert an unfolding synchronization control during the unfolding process, and the solar wing module has the characteristics of simplicity and reliability.

[0046] As shown in Figures 1 to 4As shown, the flexible substrate 1 is arranged on the first folding arm assembly 30, and the surface of the flexible substrate 1 is used to attach solar cell pieces. The end of the flexible substrate 1 is fixedly connected with 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 be set to include a group. One group of the first folding arm assembly 30 is arranged at the top end or the bottom end of the first frame 21 and the second frame 22, and one group of the second folding arm assembly 40 is arranged at the top end or the bottom end of the first frame 21 and the second frame 22. The top end or the bottom end of the flexible substrate 1 is fixedly connected with the first folding arm assembly 30, and the two ends of the first folding arm assembly 30 and the two ends of the second folding arm assembly 40 are respectively hingedly connected with the first frame 21 and the second frame 22, so that the folding or unfolding of the solar wing module can be realized.

[0048] The preferred design scheme is that the first folding arm assembly 30 and the second folding arm assembly 40 each include two groups. The two ends of the flexible substrate 1 are respectively fixedly connected with the two groups of the first folding arm assembly 30. The two ends of one group of the first folding arm assembly 30 are respectively hingedly connected with the top end of the first frame 21 and the top end of the second frame 22. The two ends of one group of the second folding arm assembly 40 are respectively hingedly connected with the top end of the first frame 21 and the top end of the second frame 22. The two ends of the other group of the first folding arm assembly 30 are respectively hingedly connected with the bottom end of the first frame 21 and the bottom end of the second frame 22. The two ends of the other group of the second folding arm assembly 40 are respectively hingedly connected with the bottom end of the first frame 21 and the bottom end of the second frame 22. After the two groups of the first folding arm assembly 30 and the two groups of the second folding arm assembly 40 are respectively hingedly connected with the two frames, the folding direction of the first folding arm assembly 30 is perpendicular to the folding direction of the second folding arm assembly 40, and a single-degree-of-freedom spatial foldable and unfoldable space truss is formed. The two groups of the first folding arm assembly 30 and the two groups of the second folding arm assembly 40 are synchronously folded or unfolded, and the two frames are always kept parallel. The flexible substrate 1 is installed on the spatial space truss structure, and the flexible solar wing module with overall high rigidity is realized.

[0049] As shown in Figure 5 The first folding arm assembly 30 includes a first folding arm 31, a second folding arm 32, and a first torsional spring 33. The first folding arm 31 is hingedly connected with the second folding arm 32. The first torsional spring 33 serves as a power source and is used to drive the first folding arm assembly 30 to unfold by storing elastic potential energy. The first folding arm assembly 30 is driven 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 is unfolded to 180°, the first folding arm 31 and the second folding arm 32 are locked.

[0050] As shown in 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).

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 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 point between the first folding arm (31) and the second folding arm (32).

4. The foldable, retractable flexible solar panel module as described in claim 1, characterized in that, 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 point between the third folding arm (41) and the fourth folding arm (42).

5. The foldable, retractable flexible solar panel module as described in claim 3, characterized in that, 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.

6. The foldable, retractable flexible solar panel module as described in claim 5, characterized in that, 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).

7. 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.

8. 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.

9. 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.

10. 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 9, wherein the direction of the series connection includes the deployment direction of the solar array modules.

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