Ultra-large flexible solar cell array wound and unfolded step by step and unfolding method

Abstract

The invention relates to a step-by-step winding and unfolding ultra-large flexible solar cell array and an unfolding method, and belongs to the technical field of space solar cell arrays. The battery array comprises a battery array body structure, a pressing and releasing mechanism, an unfolding and locking mechanism and an extension arm mechanism, the cell array body structure has a folded state and an unfolded state; under folding, pressing force is provided through the pressing and releasing mechanism, so that the device is folded on the side walls of the two sides of the satellite body and can bear the mechanical load of the launching section; during unfolding, under the action of the unfolding locking mechanism, the folding mechanism and the stretching arm mechanism, the folding mechanism is unfolded in a distributed manner according to a time sequence; and after being unfolded, the antenna can rotate by 360 degrees to provide energy for satellites. The invention has the advantages of small folding volume, large unfolding area and light weight, and solves the contradiction that the power demand of a spacecraft power supply is large and the envelope size of a launching section is small.

Description

Technical Field

[0001] This invention belongs to the field of space solar cell array technology, and relates to an ultra-large flexible solar cell array and its deployment method that uses a step-by-step winding and unfolding process. Background Technology

[0002] Space solar arrays are the core power supply equipment for spacecraft. With the rapid development of aerospace science and technology, the functionality and performance of aerospace satellite equipment are continuously improving, placing increasingly higher demands on power supply systems. This means that while meeting the power requirements of spacecraft, high standards are also being set for advanced indicators such as ultra-high power, storage ratio, and power-to-weight ratio. The roll-up flexible solar array solution has the significant advantages of small size and light weight, and once the technology matures, it can completely replace the solar array designs for large, medium, and small spacecraft. Through the modular combination of multiple high-power, high-storage-ratio flexible solar arrays, the technical bottleneck of nearly 100kW requirements can also be solved. If such spacecraft continue to use traditional rigid or semi-rigid substrate solar array technology, its large folded volume would result in a launch section envelope size exceeding the launch fairing size, and it also suffers from complex deployment processes, low reliability, low stiffness, and heavy weight, making it impractical in engineering. Therefore, high-power, high-storage-ratio roll-up flexible solar arrays are the best choice for satellite power supply system power and the platform's core competitiveness. Summary of the Invention

[0003] The technical problem solved by this invention is to overcome the shortcomings of the prior art. This invention provides a step-by-step winding and unfolding ultra-large flexible solar cell array and an unfolding method.

[0004] The solution of the present invention is: a step-by-step winding and unfolding ultra-large flexible solar cell array, including a cell array body structure, a pressing and releasing mechanism, an unfolding and locking mechanism, a folding mechanism, and an extension arm mechanism;

[0005] The battery array structure has two states: folded and unfolded. When folded, a clamping and releasing mechanism provides clamping force to make it folded against the two side walls of the satellite body and withstand the mechanical load of the launch phase. When unfolded, it unfolds in sequence under the action of the unfolding locking mechanism, folding mechanism, and extension arm mechanism. After unfolding, it can rotate 360° to provide energy for the satellite.

[0006] The compression and release mechanism has compression and release functions, and can complete the compression and release of the battery array body structure itself, as well as the compression and release between the battery array body structure and the satellite body.

[0007] The locking mechanism is used to connect the solar array drive mechanism on the satellite body to the solar array body structure. The solar array body structure is deployed for the first time under its passive drive.

[0008] The folding mechanism has unfolding and locking functions, and under its active drive, the battery array body structure is unfolded and locked a second time.

[0009] The extension arm mechanism has the functions of retracting and unfolding, and under its action, the battery array body structure is unfolded for the third time.

[0010] Furthermore, the battery array body structure includes: a connecting rod, battery array body structure A, and battery array body structure B; battery array body structure A and battery array body structure B are connected to the satellite body via the connecting rod.

[0011] Battery array body structure A includes battery array body structure AI and battery array body structure AII, which have the same composition and structure.

[0012] The battery array body structure B includes battery array body structure BI and battery array body structure BII, which have the same composition and structure.

[0013] Connecting rods, including connecting rod I and connecting rod II;

[0014] In the folded state, the battery array body structure AI and battery array body structure BI are pressed side by side against one side of the satellite body and connected to the satellite body through connecting rod I; the battery array body structure AII and battery array body structure BII are pressed side by side against the other side of the satellite body and connected to the satellite body through connecting rod II; when deployed for the first time, the positions of battery array body structure AI and battery array body structure AII are centrally symmetrical with respect to the center of the satellite body, and the positions of battery array body structure BI and battery array body structure BII are centrally symmetrical with respect to the center of the satellite body.

[0015] Furthermore, when the battery array body structure is deployed for the second time, the battery array body structure AI rotates to be above the battery array body structure BI and is placed coaxially and perpendicularly with it, and the battery array body structure AII rotates to be above the battery array body structure BII and is placed coaxially and perpendicularly with it; the positions of the battery array body structures AI and AII are axially symmetrical with respect to the center of the satellite, and the positions of the battery array body structures BI and BII are axially symmetrical with respect to the center of the satellite.

[0016] Furthermore, the battery array body structure AI includes a crossbeam A, a sun blanket A, and a roller A; the sun blanket A is connected to the roller A at one end and to the crossbeam A at the other end through a constant torque spring structure A; the crossbeam A is connected to the connecting rod I.

[0017] The battery array body structure BI includes a crossbeam B, a sun blanket B, and a roller B; one end of the sun blanket B is connected to the roller B, and the other end is connected to the crossbeam B through a constant torque spring structure B; the crossbeam B is connected to the connecting rod II.

[0018] Furthermore, the constant torque spring structure A is connected to the sun blanket A at its top and to the crossbeam A at its bottom; the constant torque spring structure B is connected to the sun blanket B at its top and to the crossbeam B at its bottom. The constant torque spring structures A and B can provide a controllable constant torque, and when the sun blanket A and sun blanket B are displaced due to temperature changes or mechanical vibration, they continuously maintain the tension between the sun blanket A and the crossbeam A, and between the sun blanket B and the crossbeam B, ensuring structural stability and functional reliability.

[0019] Furthermore, the aforementioned clamping and releasing mechanism includes a clamping and releasing device between the reel and the crossbeam, and a clamping and releasing device between the crossbeam and the celestial body;

[0020] The device for releasing the clamping force between the reel and the crossbeam includes a release nut assembly A and a release nut assembly B. One end of the release nut assembly A is connected to the reel A, and the other end is connected to the crossbeam A. When retracted, the release nut assembly A is locked, pressing the reel A against the crossbeam A. When unfolded, an external excitation drives the release nut assembly A to unlock, releasing the clamping force between the reel A and the crossbeam A. Similarly, the release nut assembly B enables the clamping and release between the reel B and the crossbeam B.

[0021] The beam-to-satellite clamping release device includes a separation nut assembly AI and a separation nut assembly BI. The separation nut assembly AI is connected to the beam A at one end and to the satellite body at the other end. When retracted, the separation nut assembly AI is in a locked state, clamping the beam A and fixing it to the side wall of the satellite body. When extended, the separation nut assembly AI is unlocked by external excitation, releasing the clamping between the beam A and the satellite body. Similarly, the separation nut assembly BI is used to clamp the beam B and the satellite body, thus releasing the beam.

[0022] Furthermore, the aforementioned deployment and locking mechanism includes a root hinge and a hinge between the connecting rod and the crossbeam; the root hinge has a first spiral spring inside, one end of which is connected to the satellite body and the other end to the connecting rod; the hinge between the connecting rod and the crossbeam has a second spiral spring inside, one end of which is connected to the connecting rod and the other end is connected to both crossbeam A and crossbeam B; the battery array body structure is deployed for the first time under the sequential passive drive of the first spiral spring and the second spiral spring.

[0023] Furthermore, the folding mechanism includes an inter-beam unfolding and locking mechanism and an inter-roll unfolding and locking mechanism;

[0024] The beam-to-beam unfolding and locking mechanism is equipped with a drive device and a pin assembly. The drive device is connected to both the beam-to-beam unfolding and locking mechanism and the scroll-to-scroll unfolding and locking mechanism, providing driving force to drive them to rotate and unfold 180° from the folded state, completing the second unfolding of the battery array body structure. The pin assembly is connected to beam A at one end and beam B at the other end, and is used to lock the two.

[0025] The roll-to-roll locking mechanism includes a locking hook and locking post assembly and a roll-to-roll interlocking device. The locking hook and locking post assembly is connected to roll A at one end and roll B at the other end to lock the two. The roll-to-roll interlocking device is connected to roll A at one end and roll B at the other end to further lock the two.

[0026] Furthermore, the aforementioned extension arm mechanism includes extension arm A, extension arm B, extension arm end shaping mechanism, and extension arm surface shaping mechanism.

[0027] Extending arm A, one end is connected to crossbeam A, and the other end is connected to reel A;

[0028] Extending arm B, one end is connected to crossbeam B, and the other end is connected to reel B;

[0029] The extension arm shape control mechanism includes extension arm shape control mechanism A and extension arm shape control mechanism B; extension arm shape control mechanism A has one end always pressed against the surface of the reel A, and the other end in contact with the extension arm A, for realizing the tangential extension of the extension arm A; extension arm shape control mechanism B has one end always pressed against the surface of the reel B, and the other end in contact with the extension arm B, for realizing the tangential extension of the extension arm B.

[0030] The extension arm end control mechanism includes extension arm end control mechanism A and extension arm end control mechanism B; extension arm end control mechanism A is located at the root of extension arm A and controls and locks extension arm A; extension arm end control mechanism B is located at the root of extension arm B and controls and locks extension arm B.

[0031] A method for deploying an ultra-large flexible solar cell array using a step-by-step winding and unfolding process includes:

[0032] In the folded state, the battery array body structure is divided into two symmetrical parts, which are pressed against the two sides of the satellite body and are distributed axially symmetrically.

[0033] The clamping and releasing mechanism releases the constraints between the battery array structure and the satellite, as well as the clamping constraints on the battery array structure itself, thus completing the clamping release action.

[0034] The battery array body structure is deployed for the first time under the passive drive of the deployment locking mechanism. After deployment, the components of the battery array body structure located on both sides of the satellite body are centrally symmetrically distributed.

[0035] Under the active drive of the folding mechanism, the battery array body structure is unfolded and locked for the second time. The folding mechanism first rotates and unfolds 180° from the folded state, and then locks the crossbeam end of the battery array body structure by means of the pin assembly, and double locks the roll end of the battery array body structure (2) by means of the locking hook and locking post assembly and the roll interlocking device.

[0036] Driven by the extension arm mechanism, the battery array body structure is wound and unfolded for the third time. Through shape control and end shape control, after the third unfolding, the battery array body structure and the connecting rod form a plane.

[0037] Once the battery array is fully deployed, it rotates 360° under the continuous rotation axis of the satellite, enabling single-axis solar orientation.

[0038] The advantages of this invention compared to the prior art are:

[0039] (1) The step-by-step winding and unfolding ultra-large flexible solar cell array proposed in this invention unlocks different pressing and releasing mechanisms in sequence and combines them with the active driving mechanism between the crossbeams to realize the distributed unfolding of the ultra-large flexible solar cell array, making the unfolding process simpler.

[0040] (2) In the third winding and unfolding process of the solar cell array proposed in this invention, the elastic strain energy stored in the extension arm itself is used to provide the unfolding driving force. Combined with the function of the extension arm shape control mechanism, reliable tangential unfolding is achieved. After unfolding, it becomes an open extension arm shape, which ensures the stiffness requirements of the solar cell array after unfolding.

[0041] (3) The ultra-large flexible solar cell array proposed in this invention has the triple advantages of small folding volume, large unfolding area and light weight. The weight of the flexible solar cell array can be reduced to about 70% of that of the rigid solar cell array, and the volume can be reduced to about 25% of that of the rigid solar cell array, thus solving the contradiction of large power demand of spacecraft and small envelope size of launch section. Attached Figure Description

[0042] Figure 1 This is a closed-up view of the overall structure of the present invention;

[0043] Figure 2 This is a first unfolded schematic diagram of the overall structure of the present invention;

[0044] Figure 3 This is a second unfolded schematic diagram of the overall structure of the present invention;

[0045] Figure 4 This is a third unfolded schematic diagram of the overall structure of the present invention;

[0046] Figure 5 This is a schematic diagram of the solar cell array on one side of the satellite body of the present invention in a retracted state.

[0047] Figure 6 This is a schematic diagram of the deployed state of the solar cell array on one side of the satellite body of the present invention. Detailed Implementation

[0048] The present invention will be further explained and described below with reference to the accompanying drawings and specific embodiments.

[0049] like Figure 1 , Figure 5 As shown, a step-by-step, roll-up, unfolding ultra-large flexible solar cell array includes:

[0050] The components include an unfolding locking mechanism, a folding mechanism, an extension arm mechanism, a battery array body structure 2, and a pressing and releasing mechanism; among which,

[0051] The locking mechanism is deployed, including the root hinge 23 and the hinge 22 between the connecting rod and the crossbeam;

[0052] The folding mechanism includes a crossbeam unfolding and locking mechanism 11 and a scroll unfolding and locking mechanism 12.

[0053] The extension arm mechanism includes extension arm A7, extension arm B9, extension arm end shape control mechanism, and extension arm surface control mechanism.

[0054] The battery array body structure 2 includes a connecting rod 3, a crossbeam A16, a crossbeam B17, a solar blanket A19, a solar blanket B21, a scroll A14, and a scroll B15;

[0055] The clamping release mechanism includes a clamping release device 10 between the reel and the crossbeam, and a clamping release device 13 between the crossbeam and the satellite. Both are unlocked via a release nut assembly. The release nut assembly is driven by an external excitation condition to unlock, thereby releasing the clamping state between the reel and the crossbeam or between the crossbeam and the satellite.

[0056] The separating nut assembly includes a housing assembly, a split nut assembly, a bearing force transmission assembly, a shape memory alloy drive assembly, and a nut release assembly. The split nut assembly is located at the top inside the housing. The shape memory alloy drive assembly is installed at the bottom inside the housing. The nut release assembly is installed on the shape memory alloy drive assembly and is in contact with the split nut assembly. The bearing force transmission assembly is located between the split nut assembly and the shape memory alloy drive assembly and is connected to both. It rotates under the drive of the shape memory alloy drive assembly, releasing the constraint on the split nut assembly, and opens the split nut assembly under the action of the nut release assembly, ultimately completing the unlocking of the separating nut mechanism.

[0057] After the battery array structure 2 is folded up, it is pressed firmly against the side wall of the satellite body 1, as shown below. Figure 1 As shown, at this time, the battery array body structure 2 is in a coiled-up state. The solar cell array drive mechanism on the satellite body 1 is connected to the connecting rod 3, the crossbeam A16, and the crossbeam B17 in sequence through the root hinge 23, the hinge 22 between the connecting rod and the crossbeam, and the unfolding locking mechanism 11 between the crossbeams. The connecting rod 3, the crossbeam A16, and the crossbeam B17 are pressed and fixed to the side wall of the satellite body 1 by six sets of crossbeams and satellite body pressing and releasing devices 13. The six sets of crossbeams and satellite body pressing and releasing devices 13 provide a certain preload to ensure that the battery array body structure 2 can withstand the mechanical load of the launch segment. In the retracted state 7 of the extension arm A, the solar blanket A19 is wound on the reel A14. In the retracted state 9 of the extension arm B, the solar blanket B21 is wound on the reel B15. The reel A14 and the reel B15 are connected by the reel-to-reel unfolding locking mechanism 12. The retracted states 7 of the extension arm A and 9 of the extension arm B are respectively connected to the crossbeams A16 and B17 through the extension arm end control mechanism. The solar blankets A19 and B21 are connected to the crossbeams A16 and B17 through multiple sets of solar blanket tensioning devices. The reel A14 and the reel B15 are respectively pressed onto the crossbeams A16 and B17 by two sets of reel-to-crossbeam pressing and releasing devices 10, ensuring that the solar cell array reel-solar blanket assembly can withstand the mechanical load of the launch section.

[0058] After the spacecraft enters orbit and separates from the launch vehicle, the six sets of crossbeams and the spacecraft's clamping release device 13 release the constraints of connecting rod 3, crossbeam A16, and crossbeam B17. The battery array main body structure 2 then undergoes its first deployment under the passive drive of the spiral springs of the root hinge 23 and the hinge 22 between the connecting rod and the crossbeam. Figure 2 As shown. In the second step, the crossbeams A16 and B17, and the reels A14 and B15 are actively driven by the drive components of the crossbeam-to-beam and reel-to-reel unfolding and locking mechanisms 11 and 12, respectively, to achieve a second unfolding and locking, as shown. Figure 3 As shown.

[0059] When unfolded, the drive device of the crossbeam unfolding locking mechanism 11 provides driving force, and the roll unfolding locking mechanism 12 moves accordingly under the driving force. The two rotate and unfold 180° from the folded state. The crossbeam unfolding locking mechanism 11 locks by means of the crossbeam pin, so that the crossbeam A16 and the crossbeam B17 form a whole. The roll unfolding locking mechanism 12 locks the roll A14 and the roll B15 by means of the locking hook-locking pin, and at the same time, it further locks the roll A14 and the roll B15 by means of the roll interlocking device, so that the sun blanket A19, the roll A14, the sun blanket B21, and the roll B15 form a whole.

[0060] Thirdly, the clamping release device 10 between the four sets of reels and the crossbeam releases the constraints on the reel-sun blanket assembly A6 and the reel-sun blanket assembly B8. Under the combined action of the two unfolding mechanisms, reel-sun blanket assembly A6 and reel-sun blanket assembly B8 achieve a third winding unfolding, and the unfolded configuration is as follows. Figure 4 , Figure 6 As shown. During the third deployment, scrolls A14 and B15 move away from crossbeams A16 and B17. To ensure that the extended arms A in deployment state 18 and B in deployment state 20 form a complete tubular high-rigidity support structure, their roots are supported by the extension arm end-shaping mechanism to form a C-shaped port. The extension arm end-shaping mechanism is located at the root of the extended arms A and B, and controls the shape of the extended arms A and B based on the four-bar linkage principle.

[0061] Extending arms A and B retract or unfold synchronously; when retracted, sun blanket A19 is wound on roller A14 and sun blanket B21 is wound on roller B15; when unfolded, extending arm A is above sun blanket A19 and extending arm B is below sun blanket B21, and all four are coplanar and parallel.

[0062] like Figure 6 As shown, in order to ensure the orderly unfolding of the extension arm A in state 18 and the extension arm B in state 20, the outer ring of the extension arm is tangentially extended relative to the secondary ring by the extension arm shape control mechanism.

[0063] The extension arm shape control mechanism includes extension arm shape control mechanism A and extension arm shape control mechanism B; extension arm shape control mechanism A has one end always pressed against the surface of the reel A14, and the other end in contact with the extension arm A, for realizing the tangential extension of the extension arm A; extension arm shape control mechanism B has one end always pressed against the surface of the reel B15, and the other end in contact with the extension arm B, for realizing the tangential extension of the extension arm B.

[0064] During and after the third deployment of the battery array structure 2, a solar blanket tensioning device is used to ensure that the solar blankets A19 and B21 maintain a certain tension relative to the crossbeams A16 and B17. This device ensures that the solar blankets remain taut during deployment and can be deployed simultaneously with the extension arms, while also adapting to the high and low temperature environment in orbit after deployment. The solar blanket tensioning device is equipped with constant torque springs. A controllable constant torque is provided between solar blankets A19 and A16, and between solar blankets B21 and B17, by these springs. This maintains the tension between solar blankets A19 and A16, and between solar blankets B21 and B17, even when solar blankets A19 and B21 shift due to temperature changes or mechanical vibrations, ensuring structural stability and functional reliability.

[0065] In the compressed state, the solar array is folded up against the side wall of satellite body 1. In the folded state, the connecting rod 3, the crossbeam assembly, and the roll-sun blanket assembly rely on the compression and release device to provide a certain amount of compression force, so that the folded solar array can withstand the vibration, impact and noise environment generated by the launch vehicle in the launch section.

[0066] A step-by-step unfolding process for an ultra-large flexible solar cell array includes:

[0067] After the spacecraft is launched into orbit, the first step is for the solar array to begin its deployment. The crossbeam and the satellite body clamping release device 13 releases the constraint from the satellite body 1, and the solar array is deployed once under the combined action of the root hinge 23 and the hinge 22 between the connecting rod and the crossbeam.

[0068] In the second step, solar cell arrays A and B are deployed a second time under the active drive of the inter-beam deployment locking mechanism 11. The crossbeam components in the main body structure A4 and main body structure B5 are locked in place by the inter-beam deployment locking mechanism 11, and the roll-solar blanket components in the main body structure A4 and main body structure B5 are locked in place by the roll-roll deployment locking mechanism 12.

[0069] In the third step, the clamping release device 10 between the roll and the crossbeam releases the constraint between the roll and the crossbeam. The battery array body structures A4 and B5, driven by the extension arms A and B mechanisms, undergo three winding and unfolding processes. The roll assembly moves away from the crossbeam assembly, and the sun blanket unfolds synchronously around the roll and with the extension arms. During the third unfolding process, the extension arms A and B mechanisms unwind from a planar, closed state to an open extension arm. The connection between the extension arm and the crossbeam is achieved using the extension arm end shape control mechanism to create a C-shaped port. During unfolding, to prevent the outer ring of the extension arm from becoming uncontrollable, the extension arm shape control mechanism ensures that the extension arm always unfolds tangentially. A sun blanket tensioning device provides a certain tension between the sun blanket and the crossbeam.

[0070] After the solar cell array is deployed, as shown Figure 4 As shown. At this time, the main body structure A4 and the main body structure B5 of the solar array, together with the connecting rod 3, form a plane. The solar array can then rotate 360° via the 360° continuous rotation axis tracking mechanism, achieving single-axis solar orientation.

[0071] Although the present invention has been disclosed above with reference to preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art can make possible changes and modifications to the technical solutions of the present invention by utilizing the methods and techniques disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and alterations made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solutions of the present invention shall fall within the protection scope of the technical solutions of the present invention.

Claims

1. A step-and-roll, unroll-and-fly, very large flexible solar cell array, characterized by: The battery array body structure, the compression release mechanism, the unfolding locking mechanism, the folding mechanism and the stretching arm mechanism are provided. The battery array body structure (2) has two states of folding and unfolding. The compression release mechanism has compression and release functions and is used for compression and release of the battery array body structure (2) and the satellite body (1). The unfolding locking mechanism is used for connecting the solar cell array driving mechanism on the satellite body (1) and the battery array body structure (2). The folding mechanism has unfolding and locking functions and is used for second unfolding and locking of the battery array body structure (2). The stretching arm mechanism has folding and unfolding functions and is used for third unfolding of the battery array body structure (2).

2. A step-and-shoot wrap-and-unwrap very large flexible solar cell array according to claim 1, wherein, The battery array body structure (2) comprises a connecting rod (3), a battery array body structure A (4) and a battery array body structure B (5). The battery array body structure A (4) comprises a battery array body structure AI and a battery array body structure AII. The battery array body structure B (5) comprises a battery array body structure BI and a battery array body structure BII. The connecting rod (3) comprises a connecting rod I and a connecting rod II. In the folding state, the battery array body structure AI and the battery array body structure BI are arranged in parallel and compressed on one side of the satellite body (1) and connected to the satellite body (1) through the connecting rod I.

3. A step-and-shoot wrap-and-unwrap very large flexible solar cell array according to claim 2, wherein, In the second unfolding, the battery array body structure AI is rotated to above the battery array body structure BI and arranged in parallel with the battery array body structure BI, the battery array body structure AII is rotated to above the battery array body structure BII and arranged in parallel with the battery array body structure BII. In the second unfolding, the battery array body structure AI is rotated to above the battery array body structure BI and arranged in parallel with the battery array body structure BI, the battery array body structure AII is rotated to above the battery array body structure BII and arranged in parallel with the battery array body structure BII.

4. A step and roll out super flexible solar cell array as claimed in claim 2, wherein, The battery array body structure AI includes a crossbeam A (16), a solar blanket A (19), and a reel A (14); the solar blanket A (19) is connected to the reel A (14) at one end and is connected to the crossbeam A (16) at the other end through a constant torque spring structure A; the crossbeam A (16) is connected to a connecting rod I; The battery array body structure BI includes a crossbeam B (17), a solar blanket B (21), and a reel B (15); the solar blanket B (21) is connected to the reel B (15) at one end and is connected to the crossbeam B (17) at the other end through a constant torque spring structure B; the crossbeam B (17) is connected to a connecting rod II.

5. A step-and-shoot wrap-and-unwrap very large flexible solar cell array according to claim 4, wherein: The constant torque spring structure A is connected to the solar blanket A (19) at the top end and is connected to the crossbeam A (16) at the bottom end; the constant torque spring structure B is connected to the solar blanket B (21) at the top end and is connected to the crossbeam B (17) at the bottom end; The constant torque spring structure A and the constant torque spring structure B can provide a controllable constant torque, and when the solar blanket A (19) and the solar blanket B (21) are displaced due to temperature changes or mechanical vibrations, the constant torque spring structure A and the constant torque spring structure B can continuously maintain the tension state between the solar blanket A (19) and the crossbeam A (16) and between the solar blanket B (21) and the crossbeam B (17), thereby ensuring the structural stability and functional reliability.

6. A step-and-shoot wrap-and-unwrap very large flexible solar cell array according to claim 4, wherein, The compact release mechanism includes a reel and crossbeam compact release device (10) and a crossbeam and satellite compact release device (13); The reel and crossbeam compact release device (10) includes a separation nut assembly A and a separation nut assembly B; The separation nut assembly A is connected to the reel A (14) at one end and is connected to the crossbeam A (16) at the other end; when the separation nut assembly A is in a locked state, the reel A (14) is compacted on the crossbeam A (16); when the separation nut assembly A is unlocked through external excitation, the compacted state between the reel A (14) and the crossbeam A (16) is released, and the release is completed; similarly, through the separation nut assembly B, the compacting and releasing between the reel B (15) and the crossbeam B (17) are achieved; The crossbeam and satellite compact release device (13) includes a separation nut assembly AI and a separation nut assembly BI; the separation nut assembly AI is connected to the crossbeam A (16) at one end and is connected to the satellite body (1) at the other end; when the separation nut assembly AI is in a locked state, the crossbeam A (16) is compacted and fixed on the side wall of the satellite body (1); when the separation nut assembly AI is unlocked through external excitation, the compacted state between the crossbeam A (16) and the satellite body (1) is released, and the release is completed; similarly, through the separation nut assembly BI, the compacting between the crossbeam B (17) and the satellite body (1) is achieved, and the release is completed.

7. A step-and-shoot wrap-and-unwrap very large flexible solar cell array as defined in claim 4, wherein: The unfolding locking mechanism comprises a root hinge (23) and a connecting rod and cross beam hinge (22); the root hinge (23) is internally provided with a first spiral spring, one end of the first spiral spring is connected with the satellite star body (1), and the other end is connected with the connecting rod (3); the connecting rod and cross beam hinge (22) is internally provided with a second spiral spring, one end of the second spiral spring is connected with the connecting rod (3), and the other end is connected with the cross beam A (16) and the cross beam B (17) simultaneously; the first spiral spring and the second spiral spring are sequentially driven passively to realize the first unfolding of the battery array body structure (2).

8. A step and roll, unroll, super flexible solar cell array as described in claim 4 wherein: The folding mechanism comprises a cross beam unfolding locking mechanism (11) and a reel unfolding locking mechanism (12); The cross beam unfolding locking mechanism (11) is internally provided with a driving device and a bolt assembly; the driving device is connected with the cross beam unfolding locking mechanism (11) and the reel unfolding locking mechanism (12) simultaneously, provides driving force for the two, and drives the two to rotate and unfold 180° from the folded state, thereby completing the second unfolding of the battery array body structure (2); one end of the bolt assembly is connected with the cross beam A (16), and the other end is connected with the cross beam B (17), which is used for locking the two; The reel unfolding locking mechanism (12) is internally provided with a lock hook and locking column assembly and a reel mutual embedding device; the lock hook and locking column assembly is connected with the reel A (14) at one end and connected with the reel B (15) at the other end, which is used for locking the two; the reel mutual embedding device is connected with the reel A (14) at one end and connected with the reel B (15) at the other end, which is used for further locking the two.

9. A step-and-shoot wrap-and-unwrap very large flexible solar cell array according to claim 4, wherein, The stretching arm mechanism comprises a stretching arm A, a stretching arm B, a stretching arm end shape control mechanism and a stretching arm surface control mechanism; The stretching arm A is connected with the cross beam A (16) at one end and connected with the reel A (14) at the other end; The stretching arm B is connected with the cross beam B (17) at one end and connected with the reel B (15) at the other end; The stretching arm surface control mechanism comprises a stretching arm surface control mechanism A and a stretching arm surface control mechanism B; the stretching arm surface control mechanism A is always pressed on the surface of the reel A (14) at one end and in contact with the stretching arm A at the other end, which is used for realizing the tangential unfolding of the stretching arm A; The stretching arm surface control mechanism B is always pressed on the surface of the reel B (15) at one end and in contact with the stretching arm B at the other end, which is used for realizing the tangential unfolding of the stretching arm B; The stretching arm end shape control mechanism comprises a stretching arm end shape control mechanism A and a stretching arm end shape control mechanism B; the stretching arm end shape control mechanism A is located at the root of the stretching arm A and controls and locks the stretching arm A; the stretching arm end shape control mechanism B is located at the root of the stretching arm B and controls and locks the stretching arm B.

10. A method of stepwise roll-out deployment of a very large flexible solar cell array, characterized in that, Comprise: In the folded state, the battery array body structure (2) is divided into two symmetrical parts and is pressed on both sides of the side wall of the satellite star body (1) in an axial symmetrical manner; The battery array body structure (2) and the satellite star body (1) are released from the constraint by the pressing and releasing mechanism, and the battery array body structure (2) is also constrained by the pressing and releasing mechanism, thereby completing the pressing and releasing action, The first time the battery array body structure (2) is unfolded under the passive drive of the unfolding locking mechanism. After unfolding, the components of the battery array body structure (2) on both sides of the satellite body (1) are centrally symmetrically distributed; The second time the battery array body structure (2) is unfolded and locked under the active drive of the folding mechanism. The folding mechanism first rotates 180° from the folded state, and then locks the beam end of the battery array body structure (2) by means of the latch assembly, and double-locks the reel end of the battery array body structure (2) by means of the lock hook and locking column assembly, and the reel interfitting device; The third time the battery array body structure (2) is unfolded under the drive of the stretching arm mechanism. Through shape control and end control, after the third time of unfolding, the battery array body structure (2) and the connecting rod (3) form a plane. After the battery array body structure (2) is fully unfolded, it can be rotated 360° under the action of the continuous rotation shaft of the satellite body (1), and can be oriented to the sun by a single shaft.

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