Solar cell arrays, solar array structures, and satellites

Abstract

This invention discloses a solar cell array, a solar fin mechanism, and a satellite, relating to the field of aerospace technology. The solar cell array includes multiple solar cell units connected in sequence, at least one of the solar cell units comprising a main solar cell unit and a first extended solar cell unit. The main solar cell unit and the first extended solar cell unit are connected by a first connector made of shape memory alloy. The first extended solar cell unit, folded onto the main solar cell unit, can unfold to an unfolded state under the deformation of the first connector. This application solves the problem of not being able to sufficiently increase the unfolded area while ensuring the storage volume of the solar fin.

Description

Technical Field

[0001] This invention relates to the field of aerospace technology, and in particular to a solar cell array, solar array mechanism, and satellite. Background Technology

[0002] In the aerospace field, solar panels are the power generation devices of spacecraft, converting solar energy into electrical energy to power various electrical equipment on the spacecraft. In recent years, with the increasing demands for satellite payload power and electric propulsion power, higher requirements have been placed on the power generation capacity of solar panels. Under the constraint that the power generation efficiency of solar cells in solar panels can not be further improved, increasing the area of ​​the solar panels in the deployed state, so that more solar cells can be laid, has become an important means to improve power generation capacity.

[0003] Existing solar array designs are insufficient to meet the demands of efficient space utilization in multi-satellite launches, failing to maximize their deployed area while maintaining a sufficient retractable volume. Therefore, it is imperative to overcome the limitations of current technology to significantly improve the deployed area and retractable ratio of solar arrays, providing strong support for the efficient operation of satellites in multi-satellite launch modes and for broader applications of space technology. Summary of the Invention

[0004] In order to overcome the above-mentioned defects of the prior art, the technical problem to be solved by the embodiments of the present invention is to provide a solar cell array, solar wing mechanism and satellite, which can solve the problem of not being able to fully increase the unfolded area while ensuring the storage volume of the solar wing.

[0005] The specific technical solution of this invention is as follows:

[0006] A solar cell array, the solar cell array comprising:

[0007] Multiple solar cell units connected in sequence, at least one of the solar cell units includes: a main solar cell unit and a first extended solar cell unit, the main solar cell unit and the first extended solar cell unit are connected by a first connector made of shape memory alloy; the first extended solar cell unit folded on the main solar cell unit can be unfolded to an unfolded state under the action of deformation of the first connector.

[0008] Preferably, the main solar cell unit has opposing first and second sides, and the first side of the main solar cell unit is connected to the first extended solar cell unit via the first connector;

[0009] The solar cell unit further includes a second extended solar cell unit, wherein the second side of the main solar cell unit and the second extended solar cell unit are connected by a second connector made of shape memory alloy; the second extended solar cell unit folded on the main solar cell unit can be unfolded to an unfolded state under the deformation of the second connector.

[0010] Preferably, there are multiple first extended solar cell units, which are sequentially connected by a third connector made of shape memory alloy. The multiple first extended solar cell units can be folded and unfolded into an unfolded state under the deformation of the third connector.

[0011] Preferably, the first connector is in the form of a strip, and the first connector is attached to the first extended solar cell unit and the main solar cell unit by means of adhesive.

[0012] Preferably, the first connector is attached to the back of the first extended solar cell unit and the main solar cell unit.

[0013] Preferably, the first connector is strip-shaped, the second connector is strip-shaped, and the first connector and the second connector form an integral structure.

[0014] Preferably, the first connector is strip-shaped, the third connector is strip-shaped, and the first connector and the third connector form an integral structure.

[0015] Preferably, the shape memory alloy is a nickel-titanium alloy.

[0016] Preferably, the shape memory alloy is a shape memory alloy with a one-way memory effect;

[0017] The shape memory alloy deforms when the temperature exceeds a first preset value, reaching a phase transition temperature and recovering from a first form to a second form, so that the first extended solar cell unit folded on the main solar cell unit unfolds to the unfolded state. The first preset value is between 45 degrees Celsius and 70 degrees Celsius.

[0018] Preferably, the shape memory alloy deforms when the temperature exceeds a first preset value, reaching a phase transition temperature and recovering from a first form to a second form. In the second form, the radial cross-section of the first connector is a hollow, flattened oval shape.

[0019] Preferably, adjacent solar cell units are connected by a hinge between the main solar cell units, so that multiple solar cell units can be folded and stored.

[0020] A solar array mechanism, the solar array mechanism comprising:

[0021] Solar cell arrays as described above;

[0022] An unfolding assembly is used to unfold the main solar cell unit of the solar cell array from a retracted state.

[0023] Preferably, the solar array mechanism includes:

[0024] An upper pressure plate and a lower pressure plate are respectively connected to the beginning and end of a plurality of sequentially connected solar cell units. The upper pressure plate and the lower pressure plate can be folded together with the solar cell array for storage. An unfolding assembly is connected to the upper pressure plate and the lower pressure plate respectively. During the unfolding process, the unfolding assembly can drive the main solar cell units of the solar cell array to unfold from the stored state through the upper pressure plate and the lower pressure plate.

[0025] The system includes a lifting assembly and a flipping assembly. The unfolding assembly is connected to the lifting assembly via the flipping assembly. The lifting assembly is used to adjust the height of the solar cell array, and the flipping assembly is used to adjust the orientation of the unfolding assembly and the solar cell array before unfolding.

[0026] The first clamping and releasing assembly is capable of clamping, locking and releasing the upper and lower pressure plates that clamp the solar cell unit.

[0027] The second clamping and releasing assembly is capable of clamping and locking the lifting assembly, the upper pressure plate and the lower pressure plate that clamp the solar cell unit onto the satellite body and releasing them from the satellite body.

[0028] Preferably, the lifting assembly includes: a lower base, an upper base, two sets of lifting structures and driving members respectively connecting the lower base and the upper base. The lifting structure includes a first support member hinged to the lower base and a second support member with both ends hinged to the first support member and the upper base respectively. The lifting assembly has a compressed state and a lifted state. In the compressed state, the first support member and the second support member are bent and folded. In the lifted state, the first support member and the second support member are vertical. The driving member has a tendency to change the lifting assembly from the compressed state to the lifted state. After the second compression release assembly releases the lifting assembly from the star, the driving member changes the lifting assembly from the compressed state to the lifted state.

[0029] A satellite, the satellite comprising:

[0030] Stars;

[0031] A solar array mechanism as described above, mounted on the celestial body.

[0032] The technical solution of the present invention has the following significant beneficial effects:

[0033] After the solar cell array in this application unfolds the sequentially connected solar cell units, the first extended solar cell unit folded on the main solar cell unit can be unfolded to the unfolded state using a first connector made of shape memory alloy. The shape memory alloy can use temperature changes to achieve deformation of the first connector. The whole process not only does not require other power components, but the first connector can also be folded and retracted together with the main solar cell unit and the first extended solar cell unit, and the size of the solar array after unfolding can be further increased. In this way, the solar cell array can have a higher storage ratio and be better suited for spacecraft with high power requirements and compact installation requirements.

[0034] Specific embodiments of the invention are disclosed in detail below with reference to the description and accompanying drawings, indicating how the principles of the invention can be employed. It should be understood that the embodiments of the invention are not therefore limited in scope. Features described and / or shown for one embodiment may be used in the same or similar manner in one or more other embodiments, combined with features in other embodiments, or substituted for features in other embodiments. Attached Figure Description

[0035] The accompanying drawings described herein are for illustrative purposes only and are not intended to limit the scope of the invention in any way. Furthermore, the shapes and proportions of the components in the drawings are merely illustrative to aid in understanding the invention and do not specifically limit the shapes and proportions of the components. Those skilled in the art, guided by the teachings of this invention, can select various possible shapes and proportions to implement the invention according to specific circumstances.

[0036] Figure 1 This is a schematic diagram of the solar array mechanism in its fully deployed state in an embodiment of the present invention;

[0037] Figure 2 This is a schematic diagram of the structure of a solar cell unit in an embodiment of the present invention;

[0038] Figure 3 This is a schematic diagram of the solar panel mechanism when it is fully retracted in an embodiment of the present invention;

[0039] Figure 4 This is a schematic diagram of the lifting assembly of the solar array mechanism after it has been raised in an embodiment of the present invention;

[0040] Figure 5 This is a schematic diagram of the structure of the flipping component of the solar array mechanism after flipping in an embodiment of the present invention;

[0041] Figure 6 This is a partial schematic diagram of the lifting and tilting components of the solar array mechanism in an embodiment of the present invention;

[0042] Figure 7 This is a schematic diagram of the deployment process of the solar array mechanism in an embodiment of the present invention;

[0043] Figure 8 This is a partial schematic diagram of the deployment process of the solar array mechanism in an embodiment of the present invention;

[0044] Figure 9 This is a schematic diagram of the solar array mechanism after deployment in the second stage in an embodiment of the present invention;

[0045] Figure 10 This is a schematic diagram of the solar array mechanism during the third stage of deployment in an embodiment of the present invention.

[0046] The reference numerals in the above figures are as follows:

[0047] 1. Lifting assembly; 11. Lower base; 12. Upper base; 13. First support member; 14. Second support member; 2. Flipping assembly; 3. Deployment assembly; 31. Rod; 33. Connecting intersection structure; 4. Upper pressure plate; 5. Lower pressure plate; 6. Solar cell array; 61. Solar cell unit; 611. Flexible hinge; 612. Main solar cell unit; 613. First extended solar cell unit; 614. Second extended solar cell unit; 615. First connector; 616. Second connector; 617. Third connector; 618. Fourth connector; 7. First clamping release assembly; 8. Second clamping release assembly; 10. Solar wing mechanism; 20. Star body. Detailed Implementation

[0048] The details of the present invention can be more clearly understood by referring to the accompanying drawings and the description of specific embodiments. However, the specific embodiments of the present invention described herein are for illustrative purposes only and should not be construed as limiting the invention in any way. Under the teachings of this invention, those skilled in the art can conceive of any possible modifications based on the invention, all of which should be considered within the scope of the invention. It should be noted that when an element is referred to as being "set on" another element, it can be directly on the other element or there may be an intervening element. When an element is referred to as being "connected" to another element, it can be directly connected to the other element or there may be an intervening element. The terms "mounted," "connected," and "connected" should be interpreted broadly, for example, they can refer to mechanical or electrical connections, or internal communication between two elements, and can be direct or indirect connections through an intermediate medium. Those skilled in the art can understand the specific meaning of the above terms according to the specific circumstances. The terms "vertical," "horizontal," "upper," "lower," "left," "right," and similar expressions used herein are for illustrative purposes only and do not represent the only embodiments.

[0049] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this application belongs. The terminology used herein in the specification of this application is for the purpose of describing particular embodiments only and is not intended to be limiting of the application. The term "and / or" as used herein includes any and all combinations of one or more of the associated listed items.

[0050] To address the issue of not being able to fully increase the deployed area while ensuring the storage volume of the solar array, this application proposes a solar cell array 6. Figure 1 This is a schematic diagram of the solar panel mechanism in its fully deployed state according to an embodiment of the present invention. Figure 2 This is a schematic diagram of the structure of a solar cell unit in an embodiment of the present invention, as shown below. Figure 1 and Figure 2 As shown, the solar cell array 6 may include: a plurality of solar cell units 61 connected in sequence, at least one solar cell unit 61 including: a main solar cell unit 612 and a first extended solar cell unit 613, the main solar cell unit 612 and the first extended solar cell unit 613 being connected by a first connector 615 made of shape memory alloy; the first extended solar cell unit 613 folded on the main solar cell unit 612 can be unfolded to the unfolded state under the action of deformation of the first connector 615.

[0051] After the solar cell array 6 in this application unfolds the sequentially connected solar cell units 61, the first extended solar cell unit 613 folded on the main solar cell unit 612 can be unfolded to the unfolded state using the first connector 615 made of shape memory alloy. The shape memory alloy can use temperature changes to achieve the deformation of the first connector 615. The whole process not only does not require other power components, but the first connector 615 can also be folded and retracted together with the main solar cell unit 612 and the first extended solar cell unit 613, which can further expand the size of the solar array after unfolding. In this way, the solar cell array 6 can have a higher storage ratio and is better suited for spacecraft with high power requirements and compact installation requirements.

[0052] In addition, during the process of unfolding the first extended solar cell unit 613 folded on the main solar cell unit 612 to the unfolded state using the first connector 615 made of shape memory alloy, the shape memory alloy can reduce its own energy requirement for unfolding by utilizing the energy of sunlight.

[0053] Finally, with the same unfolded area of ​​the solar array 6, the above-mentioned unfolding method can increase the unfolded width of the solar array 6 and reduce the unfolded length of the solar array 6, thereby reducing the inertia of the unfolded solar array 6 and thus reducing the difficulty of spacecraft attitude and orbit control.

[0054] like Figure 2 As shown, the solar cell array 6 includes multiple solar cell units 61 connected in sequence. The solar cell units 61 can be folded back and forth in a Z-shape to achieve storage, allowing the entire solar cell array 6 to be stored in a relatively thin cuboid shape. To achieve this Z-shaped folding of the solar cell units 61, as shown... Figure 1 and Figure 2 As shown, adjacent solar cell units 61 are connected by flexible hinges 611. At least one solar cell unit 61 includes a main solar cell unit 612 and a first extended solar cell unit 613. Adjacent main solar cell units 612 are connected by flexible hinges 611 to achieve sequential connection of multiple solar cell units 61; at the same time, so that the solar cell array 6 can be unfolded and folded for storage.

[0055] like Figure 2As shown, the main solar cell unit 612 and the first extended solar cell unit 613 can be connected by a first connector 615 made of shape memory alloy. The first extended solar cell unit 613 can be folded onto the main solar cell unit 612 via the first connector 615. When the first extended solar cell unit 613 is folded onto the main solar cell unit 612 via the first connector 615, the first connector 615 is in a bent state. When the temperature of the first connector 615 made of shape memory alloy is below the austenite transformation temperature, it is in the martensitic state, allowing for large deformation folding and maintaining shape stability. When the temperature of the first connector 615 made of shape memory alloy reaches above the austenite transformation temperature, a phase transition occurs, it becomes austenitic, and recovers its original shape. Throughout the shape recovery process, the shape memory alloy has self-driving capability. When the solar cell array 6 is in a space environment, the first connector 615 made of shape memory alloy heats up under sunlight, gradually reaching the phase transition temperature, and the first connector 615 drives the first extended solar cell unit 613 to unfold. Shape memory alloys have a very high driving stress level, which can reach about 10 times that of hydraulic pressure and 200 to 20,000 times that of human muscle, a significant advantage compared to other driving mechanisms.

[0056] Considering the temperature achievable in the space environment, the shape memory alloy reaches the phase transition temperature and deforms when the temperature exceeds the first preset value, restoring from the first form to the second form, so that the first extended solar cell unit 613 folded on the main solar cell unit 612 can be unfolded into the unfolded state. The first preset value can be controlled between 45 degrees Celsius and 70 degrees Celsius.

[0057] Shape memory alloys can be made of different alloy systems, and this application does not impose any specific limitations. Considering the temperatures achievable in the space environment, nickel-titanium alloys are preferably selected as shape memory alloys. In addition, to avoid reverting to the low-temperature phase shape when the temperature drops too low in the space environment, shape memory alloys with a one-way memory effect are preferred.

[0058] To ensure a more stable connection between the first extended solar cell unit 613 and the main solar cell unit 612 in the deployed state, it is necessary to increase the bending stiffness of the first connector 615. As a feasible approach, in the second configuration, the radial cross-section of the first connector 615 can be a hollow, flattened oval shape. In other feasible embodiments, in the second configuration, the radial cross-section of the first connector 615 can also be wavy, C-shaped, or tubular, etc.

[0059] As a feasible option, in order to achieve a higher storage ratio for the solar cell array 6, in the first configuration, the radial cross-section of the first connector 615 can be flat, and its thickness can be less than or equal to 0.3 mm, or even thinner to about 0.1 mm to 0.2 mm.

[0060] like Figure 2 As shown, the main solar cell unit 612 may have opposing first and second sides. The first side of the main solar cell unit 612 is connected to the first extended solar cell unit 613 via a first connector 615. There may be one or more first extended solar cell units 613. When there are multiple first extended solar cell units 613, they are sequentially connected by a third connector 617 made of shape memory alloy. The multiple first extended solar cell units 613 can be folded and unfolded to an unfolded state under the deformation of the third connector 617. The characteristics of the third connector 617 may be the same as those of the first connector 615, and will not be described further here. The main solar cell unit 612 may also have opposing third and fourth sides. Adjacent main solar cell units 612 are connected via the third and fourth sides and folded along the third and fourth sides.

[0061] As a feasible option, such as Figure 2 As shown, the solar cell unit 61 may further include: a second extended solar cell unit 614, wherein the second side of the main solar cell unit 612 and the second extended solar cell unit 614 are connected by a second connector 616 made of shape memory alloy; the second extended solar cell unit 614, folded on the main solar cell unit 612, can unfold to an unfolded state under the deformation of the second connector 616. The characteristics of the second connector 616 may be the same as those of the first connector 615, and will not be described again here. There may be one or more second extended solar cell units 614. When there are multiple second extended solar cell units 614, the multiple second extended solar cell units 614 are connected sequentially by a fourth connector 618 made of shape memory alloy, and the multiple second extended solar cell units 614 can be folded and unfolded to an unfolded state under the deformation of the fourth connector 618. The characteristics of the fourth connector 618 may be the same as those of the first connector 615, and will not be described again here.

[0062] As a feasible option, such as Figure 2As shown, the first connector 615 can be generally strip-shaped, and it is attached to the first extended solar cell unit 613 and the main solar cell unit 612 by adhesive bonding. This connection method will not damage the first extended solar cell unit 613 or the main solar cell unit 612, thus not affecting their power generation. Furthermore, the first connector 615 is adhesively attached to the back of the first extended solar cell unit 613 and the main solar cell unit 612, so that it will not obstruct the front of the first extended solar cell unit 613 and the main solar cell unit 612, thereby affecting their power generation under sunlight.

[0063] To prevent the first connector 615 and the second connector 616 from easily detaching from the main solar cell unit 612, such as Figure 2 As shown, the first connector 615 can be in the form of a strip, the second connector 616 can be in the form of a strip, and the first connector 615 and the second connector 616 form an integral structure. This arrangement also facilitates the fabrication of the solar cell array 6. Similarly, the first connector 615 can be in the form of a strip, the third connector 617 can be in the form of a strip, and the first connector 615 and the third connector 617 can form an integral structure. Alternatively, the fourth connector 618 can be in the form of a strip, and the second connector 616 and the fourth connector 618 can form an integral structure.

[0064] Furthermore, the first connector 615, the second connector 616, the third connector 617, and the fourth connector 618 can form an integral structure.

[0065] When there are multiple first extended solar cell units 613, in one embodiment, such as Figure 2 As shown, multiple first extended solar cell units 613 can be folded back and forth in a Z-shape. In another embodiment, multiple first extended solar cell units 613 can be continuously folded inward to form a similar rolled structure.

[0066] This application also proposes a solar panel mechanism 10, such as Figure 1 As shown, the solar array mechanism 10 may include: a solar cell array 6 as described above; and a deployment component 3, which is used to deploy the main solar cell units 612 of the solar cell array 6 from their retracted state. The deployment component 3 can adopt various different structures or methods, and no limitation is made thereto in this application. Preferably, Figure 7 This is a schematic diagram illustrating the deployment process of the solar array mechanism's deployment component in an embodiment of the present invention. Figure 8 This is a partial schematic diagram of the deployment process of the solar array mechanism in an embodiment of the present invention, as shown below. Figure 7 and Figure 8As shown, the unfolding component 3 can adopt a scissor-arm structure. The scissor-arm structure includes multiple sets of scissor-arm units connected in sequence by hinges. At least some of the scissor-arm units include a connecting intersection structure 33 and four rods 31 hinged to the connecting intersection structure 33. A driving unit is located at the hinge of the four rods 31, causing the four rods 31 to tend to open, thereby increasing the length of the scissor-arm unit in the solar cell array 6. Two rods 31 in one scissor-arm unit are hinged to two rods 31 in an adjacent scissor-arm unit. The two scissor-arm units at the tail end can consist only of the connecting intersection structure 33 and two rods 31 hinged to the connecting intersection structure 33.

[0067] Figure 3 This is a schematic diagram of the solar panel mechanism when it is fully retracted in an embodiment of the present invention. Figure 9 This is a schematic diagram of the solar array mechanism after deployment in the second stage in an embodiment of the present invention. Figure 10 This is a schematic diagram of the solar array mechanism during the third stage of deployment in an embodiment of the present invention, as shown below. Figure 3 , Figure 9 and Figure 10 As shown, the solar array mechanism 10 may include an upper pressure plate 4 and a lower pressure plate 5. The upper pressure plate 4 and the lower pressure plate 5 are respectively connected to the beginning and end of a plurality of sequentially connected solar cell units 61, that is, connected to the third side of the main solar cell unit 612 of the first solar cell unit 61 and the fourth side of the main solar cell unit 612 of the last solar cell unit 61. The upper pressure plate 4 can be hinged to the third side of the main solar cell unit 612 of the first solar cell unit 61, and the lower pressure plate 5 can be hinged to the fourth side of the main solar cell unit 612 of the last solar cell unit 61. The upper pressure plate 4 and the lower pressure plate 5 can be folded together with the solar array 6 for storage. An unfolding assembly 3 is connected to the upper pressure plate 4 and the lower pressure plate 5 respectively. During unfolding, the unfolding assembly 3 can cause the main solar cell unit 612 of the solar array 6 to unfold from its stored state by increasing the distance between the upper pressure plate 4 and the lower pressure plate 5.

[0068] The scissor-type units at the beginning and end can be connected to the upper pressure plate 4 and the lower pressure plate 5, respectively. The hinge joint of the two rods 31 in the scissor-type unit can be connected to either the upper pressure plate 4 or the lower pressure plate 5. For example... Figure 3 As shown, multiple sets of scissor-type units that are sequentially hinged can be compressed into a generally parallel state. The unfolded component 3 of the scissor-type units in the parallel state is arranged in parallel with the folded upper pressure plate 4, lower pressure plate 5 and solar cell array 6.

[0069] As a feasible option, such as Figure 7 and Figure 9 As shown, the first extended solar cell unit 613 folded onto the main solar cell unit 612 can be located on the side of the main solar cell unit 612 facing the unfolding assembly 3. In another feasible embodiment, it can also be located on the other side of the main solar cell unit 612 away from the unfolding assembly 3. Similarly, the second extended solar cell unit 614 folded onto the main solar cell unit 612 can be located on the side of the main solar cell unit 612 facing the unfolding assembly 3, or it can be located on the other side of the main solar cell unit 612 away from the unfolding assembly 3. Furthermore, when the first extended solar cell unit 613 and the second extended solar cell unit 614 are folded onto the main solar cell unit 612 and located on the side of the main solar cell unit 612 facing the unfolding assembly 3, when the unfolding assembly 3 is not fully unfolded, some components of the unfolding assembly 3 block and limit the first extended solar cell unit 613 and / or the second extended solar cell unit 614, so that the first extended solar cell unit 613 and / or the second extended solar cell unit 614 cannot be unfolded from the folded state to the unfolded state. Only after the unfolding assembly 3 is fully unfolded can the first extended solar cell unit 613 and / or the second extended solar cell unit 614 be unfolded from the folded state to the unfolded state. This ensures the smoothness of the unfolding process of the first extended solar cell unit 613 and / or the second extended solar cell unit 614, preventing interference between completely adjacent extended solar cell units during the unfolding process. For example, when the unfolding assembly 3 is a scissor-type structure, the rods block and limit the first extended solar cell unit 613 and / or the second extended solar cell unit 614 when the unfolding assembly 3 is not fully unfolded.

[0070] Figure 4 This is a schematic diagram of the lifting assembly of the solar array mechanism after it has been raised in an embodiment of the present invention. Figure 5 This is a schematic diagram of the flipping assembly of the solar array mechanism after flipping in an embodiment of the present invention. Figure 6 This is a partial schematic diagram of the lifting and tilting components of the solar array mechanism in an embodiment of the present invention, as shown below. Figures 3 to 6 As shown, the solar array mechanism 10 may include a lifting assembly 1 and a flipping assembly 2. The deployment assembly 3 is connected to the lifting assembly 1 via the flipping assembly 2. The lifting assembly 1 is used to adjust the height of the solar cell array 6, and the flipping assembly 2 is used to adjust the orientation of the deployment assembly 3 and the solar cell array 6 before deployment.

[0071] As a feasible option, such as Figures 3 to 5 As shown, there can be two solar cell arrays 6. Each of the two solar cell arrays 6 has a corresponding unfolding component 3 and a flipping component 2. The two flipping components 2 are connected to each other on both sides of the lifting component 1, and the unfolding component 3 is connected to the flipping component 2.

[0072] like Figure 3 As shown, the solar array mechanism 10 may include a first clamping and releasing assembly 7, which is capable of clamping, locking, and releasing the upper clamping plate 4 and the lower clamping plate 5 that clamp the solar cell unit 61. Multiple first clamping and releasing assemblies 7 may be present, located at the edges of the upper clamping plate 4 and the lower clamping plate 5 respectively. When the first clamping and releasing assembly 7 releases the upper clamping plate 4 and the lower clamping plate 5, the distance between the upper clamping plate 4 and the lower clamping plate 5 increases under the action of the driving unit of the unfolding assembly 3, thereby causing the main solar cell unit 612 of the solar cell array 6 to unfold from its retracted state.

[0073] like Figure 6 As shown, the solar array mechanism 10 may include a second clamping and releasing assembly 8, which is capable of clamping and locking the lifting assembly 1, the upper pressure plate 4 and the lower pressure plate 5 of the clamping solar cell unit 61 onto the satellite body 20 and releasing them from the satellite body 20. During the launch of the satellite equipped with the solar array mechanism 10, the second clamping and releasing assembly 8 clamps and locks the lifting assembly 1, the upper pressure plate 4 and the lower pressure plate 5 of the clamping solar cell unit 61 onto the satellite body 20.

[0074] Alternatively, a portion of the first compression release component 7 and a portion of the second compression release component 8 may be integrated to form a single compression release component.

[0075] The first clamping release component 7 and the second clamping release component 8 can be unlocked in various ways. When an electrical signal is received for unlocking, the unlocking can be performed using a pyrotechnic principle or a mechanical structure.

[0076] like Figure 3 As shown, when a satellite equipped with solar array 10 is launched into space, and it is necessary to deploy the solar array 10, as follows: Figure 4 As shown, first unlock the second clamping release assembly 8, thereby releasing the lifting assembly 1, the upper pressure plate 4 and the lower pressure plate 5 that clamp the solar cell unit 61 from the satellite 20. Then, as... Figure 4 As shown, the lifting assembly 1 is raised, thereby adjusting the height of the solar array 6 to move the celestial body 20 away from the satellite by a certain distance. Then, as... Figure 5 As shown, the flipping component 2 adjusts the orientation of the deployment component 3 and the solar array 6 before deployment. Specifically, before adjustment, the deployment component 3 and the solar array 6 are arranged parallel to the side wall surface of the satellite body 20. During adjustment, the flipping component 2 rotates the deployment component 3 and the solar array 6 by 90 degrees, so that the deployment component 3 and the solar array 6 are perpendicular to the side wall surface of the satellite body 20 before deployment. The first stage of deployment of the solar array mechanism 10 is completed through the above process.

[0077] After that, such as Figure 7As shown, the first pressing and releasing assembly 7 releases the upper pressing plate 4 and the lower pressing plate 5 from their locked positions. Under the action of the driving unit of the unfolding assembly 3, the distance between the upper pressing plate 4 and the lower pressing plate 5 increases, thereby causing the main solar cell unit 612 of the solar cell array 6 to unfold from its retracted state. After unfolding, as shown... Figure 9 As shown, the main solar cell unit 612 of the solar cell array 6 becomes planar. The above process completes the second stage deployment of the solar array mechanism 10.

[0078] After the second stage of the solar array mechanism 10 is deployed, as Figure 10 As shown, the solar cell array 6 is exposed to sunlight, causing its temperature to rise. When the first connector 615, second connector 616, third connector 617, and fourth connector 618, made of shape memory alloy, reach the phase transition temperature when the temperature exceeds a first preset value, they deform and return from the first form to the second form. This causes multiple first extended solar cell units 613 to unfold into the unfolded state, and the first extended solar cell units 613 folded on the main solar cell unit 612 unfold into the unfolded state. After this, as... Figure 1 As shown, the entire solar cell array 6 is planar.

[0079] In order to ensure that the lifting assembly 1 can automatically rise after being released from the star body 20 under the action of the second clamping release assembly 8, such as Figure 6 As shown, the lifting assembly 1 may include: a lower base 11, an upper base 12, two sets of lifting structures and driving components respectively connecting the lower base 11 and the upper base 12. The lifting structure includes a first support member 13 hinged to the lower base 11 and a second support member 14 hinged at both ends to the first support member 13 and the upper base 12 respectively. The lifting assembly 1 has a compressed state and a lifted state. In the compressed state, the first support member 13 and the second support member 14 are bent and folded. In the lifted state, the first support member 13 and the second support member 14 are in a vertical state. The driving component has a tendency to change the lifting assembly 1 from the compressed state to the lifted state. After the second pressing release component 8 releases the lifting assembly 1 from the star 20, the driving component changes the lifting assembly 1 from the compressed state to the lifted state. For example, the driving component can be a torsion spring or a coil spring. The torsion spring or coil spring can be installed at the hinge between the first support member 13 and the lower base 11, or at the hinge between the first support member 13 and the second support member 14, or at the hinge between the second support member 14 and the upper base 12.

[0080] This application also proposes a satellite, which may include: a celestial body 20; and the aforementioned solar array mechanism 10 mounted on the celestial body 20. The celestial body 20 may have a top surface or a bottom surface, and the solar array mechanism 10 is mounted on the top surface or the bottom surface.

[0081] All articles and references disclosed herein, including patent applications and publications, are incorporated herein by reference for various purposes. The term “substantially constitutes…” used to describe a combination should include the identified element, component, part, or step, as well as other elements, components, parts, or steps that do not substantially affect the essential novelty of the combination. The use of the terms “comprising” or “including” to describe combinations of elements, components, parts, or steps herein also contemplates embodiments substantially constituted by such elements, components, parts, or steps. The use of the term “may” herein is intended to indicate that any described attribute “may” include is optional. Multiple elements, components, parts, or steps can be provided by a single integrated element, component, part, or step. Alternatively, a single integrated element, component, part, or step can be divided into multiple separate elements, components, parts, or steps. The disclosure of “a” or “an” used to describe an element, component, part, or step does not imply exclusion of other elements, components, parts, or steps.

[0082] The various embodiments in this specification are described in a progressive manner, with each embodiment focusing on its differences from other embodiments. Similar or identical parts between embodiments can be referred to interchangeably. The above embodiments are only for illustrating the technical concept and features of the present invention, and are intended to enable those skilled in the art to understand the content of the present invention and implement it accordingly. They should not be construed as limiting the scope of protection of the present invention. All equivalent changes or modifications made according to the spirit and essence of the present invention should be covered within the scope of protection of the present invention.

Claims

1. A solar cell array, characterized in that, The solar cell array includes: A plurality of solar cell units are connected in sequence, at least one of the solar cell units comprising: a main solar cell unit and a first extended solar cell unit, the main solar cell unit and the first extended solar cell unit being connected by a first connector made of shape memory alloy; the first extended solar cell unit folded on the main solar cell unit is capable of unfolding to an unfolded state under the action of deformation of the first connector; the main solar cell unit has opposing first and second sides, the first side of the main solar cell unit being connected to the first extended solar cell unit by the first connector; The solar cell unit further includes: a second extended solar cell unit, wherein the second side of the main solar cell unit and the second extended solar cell unit are connected by a second connector made of shape memory alloy; the second extended solar cell unit folded on the main solar cell unit can be unfolded to an unfolded state under the deformation of the second connector; the first connector is strip-shaped, the second connector is strip-shaped, and the first connector and the second connector form an integral structure.

2. The solar cell array according to claim 1, characterized in that, The first extended solar cell unit is multiple, and the multiple first extended solar cell units are connected in sequence by a third connector made of shape memory alloy. The multiple first extended solar cell units can be folded and unfolded into an unfolded state under the deformation of the third connector.

3. The solar cell array according to claim 1, characterized in that, The first connector is strip-shaped and is attached to the first extended solar cell unit and the main solar cell unit by means of adhesive.

4. The solar cell array according to claim 3, characterized in that, The first connector is attached to the back of the first extended solar cell unit and the main solar cell unit.

5. The solar cell array according to claim 2, characterized in that, The third connector is strip-shaped, and the first connector and the third connector form an integral structure.

6. The solar cell array according to claim 1, characterized in that, The shape memory alloy is a nickel-titanium alloy.

7. The solar cell array according to claim 1, characterized in that, The shape memory alloy is a shape memory alloy with a one-way memory effect; The shape memory alloy deforms when the temperature exceeds a first preset value, reaching a phase transition temperature and recovering from a first form to a second form, so that the first extended solar cell unit folded on the main solar cell unit unfolds to the unfolded state. The first preset value is between 45 degrees Celsius and 70 degrees Celsius.

8. The solar cell array according to claim 1, characterized in that, When the temperature exceeds a first preset value, the shape memory alloy reaches the phase transition temperature and undergoes deformation, recovering from the first form to the second form. In the second form, the radial cross-section of the first connector is a hollow flattened circle.

9. The solar cell array according to any one of claims 1 to 8, characterized in that, Adjacent solar cell units are connected by a hinge between the main solar cell units, so that multiple solar cell units can be folded and stored.

10. A solar array mechanism, characterized in that, The solar panel mechanism includes: The solar cell array as described in any one of claims 1 to 9; An unfolding assembly is used to unfold the main solar cell unit of the solar cell array from a retracted state.

11. The solar array mechanism according to claim 10, characterized in that, The solar panel mechanism includes: An upper pressure plate and a lower pressure plate are respectively connected to the beginning and end of a plurality of sequentially connected solar cell units. The upper pressure plate and the lower pressure plate can be folded together with the solar cell array for storage. An unfolding assembly is connected to the upper pressure plate and the lower pressure plate respectively. During the unfolding process, the unfolding assembly can drive the main solar cell units of the solar cell array to unfold from the stored state through the upper pressure plate and the lower pressure plate. The system includes a lifting assembly and a flipping assembly. The unfolding assembly is connected to the lifting assembly via the flipping assembly. The lifting assembly is used to adjust the height of the solar cell array, and the flipping assembly is used to adjust the orientation of the unfolding assembly and the solar cell array before unfolding. The first clamping and releasing assembly is capable of clamping, locking and releasing the upper and lower pressure plates that clamp the solar cell unit. The second clamping and releasing assembly is capable of clamping and locking the lifting assembly, the upper pressure plate and the lower pressure plate that clamp the solar cell unit onto the satellite body and releasing them from the satellite body.

12. The solar array mechanism according to claim 11, characterized in that, The lifting assembly includes: a lower base, an upper base, two sets of lifting structures and a driving member respectively connecting the lower base and the upper base. The lifting structure includes a first support member hinged to the lower base and a second support member with both ends hinged to the first support member and the upper base respectively. The lifting assembly has a compressed state and a lifted state. In the compressed state, the first support member and the second support member are bent and folded. In the lifted state, the first support member and the second support member are vertical. The driving member has a tendency to change the lifting assembly from the compressed state to the lifted state. After the second compression release assembly releases the lifting assembly from the star, the driving member changes the lifting assembly from the compressed state to the lifted state.

13. A satellite, characterized in that, The satellites include: Stars; The solar array mechanism as described in claim 10, mounted on the said celestial body.

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