Solar wing unfolding and folding device and spacecraft

Abstract

The invention belongs to the technical field of spacecrafts, and discloses a solar wing unfolding and folding device and a spacecraft. The solar wing unfolding and folding device comprises a folding mechanism, the folding mechanism is provided with two parallel platforms at intervals in the first direction, each platform extends in the second direction, and the first direction is perpendicular to the second direction; the folding mechanisms are arranged on the platform in a one-to-one correspondence mode, each folding mechanism comprises a support, an air floating piece and a rolling driving piece, the supports are in sliding fit with the platform in the second direction, the rolling driving pieces are installed on the supports, the output ends of the rolling driving pieces are coaxially fixed to the ends of rolling shafts of the solar wings in a one-to-one correspondence mode, and the rolling driving pieces can drive the rolling shafts to rotate; the air floating piece is installed on the lower side of the support, and the air floating piece and the platform are arranged in a spaced mode. According to the solar wing unfolding and folding device and the spacecraft, the friction force between the solar wing and the platform can be reduced in the unfolding or folding process of the solar wing, and the solar wing is closer to the zero-gravity state of the space when being unfolded or folded.

Description

Technical Field

[0001] This invention relates to the field of spacecraft technology, and in particular to a solar wing deployment and retraction device and a spacecraft. Background Technology

[0002] Solar panels are the primary power and energy providers for spacecraft. With the rapid development of internet satellite construction and applications, stacked and mass-produced satellite designs have become an important development direction. Flexible solar panels have advantages such as small folded volume, light weight, on-orbit deployment, and strong scalability of output power, enabling ultra-high power characteristics. The flexible solar panel deployment mechanism should possess characteristics such as lightweight and large aspect ratio.

[0003] During the retraction process of the solar array, due to its large weight, the solar array exerts significant pressure on the platform, resulting in friction that causes considerable resistance to the retraction and affects the retraction effect.

[0004] Therefore, there is an urgent need to design a solar wing deployment and retraction device and spacecraft to solve the above problems. Summary of the Invention

[0005] One object of the present invention is to provide a solar wing deployment and retraction device that can reduce the friction between the solar wing and the platform during the deployment or retraction of the solar wing, so that the solar wing is closer to the weightless state of space when it is deployed or retracted.

[0006] Another objective of this invention is to provide a spacecraft that can reduce friction between the solar array and the platform during the deployment or retraction of the solar array, making the solar array closer to the weightless state of space when deployed or retracted, thereby reducing the energy loss of the spacecraft.

[0007] To achieve this objective, the present invention adopts the following technical solution: A solar wing deployment and retraction device, comprising: Two platforms are spaced apart and parallel in a first direction, each extending along a second direction, wherein the first direction is perpendicular to the second direction. A retraction mechanism is provided on the platform in a corresponding manner. The retraction mechanism includes a bracket, an air flotation component, and a winding drive component. The bracket and the platform slide in the second direction. The winding drive component is installed on the bracket. The output end of the winding drive component is coaxially fixed to the end of the solar array's reel in a corresponding manner. The winding drive component can drive the reel to rotate so that the solar array is wound up in the positive direction of the second direction. The air flotation component is installed on the lower side of the bracket and is spaced apart from the platform.

[0008] As an alternative, the aforementioned air-bearing component is an air-bearing bearing.

[0009] As an optional solution, the aforementioned solar wing deployment and retraction device also includes a tension supply mechanism, which comprises: A sliding component, wherein the sliding component and the corresponding platform slide in the second direction, and the bracket is connected to the sliding component; The tension assembly includes a tension drive, which is mounted on the platform. The output end of the tension drive is connected to the sliding assembly. When the winding drive is working, the tension drive can drive the sliding assembly to move in the opposite direction to the second direction.

[0010] As an optional solution, the tension assembly further includes a transmission assembly, which includes a conveyor belt and several tensioning rollers. The tensioning rollers are rotatably connected to the platform. One of the tensioning rollers is coaxially fixed to the output end of the tensioning drive. The conveyor belt passes through the tensioning rollers in sequence and is tensioned by the tensioning rollers together. The sliding assembly is connected to the conveyor belt.

[0011] As an optional solution, the aforementioned sliding component includes: A sliding plate extends along the first direction and is located on the upper side of the platform, and the bracket is connected to the sliding plate. The first pulley is rotatably connected to the lower side of the sliding plate, and its periphery abuts against the first side of the platform, which is perpendicular to the upper side. At least three second pulleys are provided, each of which is rotatably connected to the sliding plate and its periphery abuts against the upper side. The transmission assembly is disposed on the second side of the platform and connected to the corresponding end of the sliding plate. The second side is parallel to the first side and perpendicular to the upper side. The end of the sliding plate opposite to the first pulley is connected to the conveyor belt.

[0012] As an optional solution, the sliding assembly further includes a connector, a floating member, a limiting member, and an elastic member. The connector is connected to the sliding plate and extends along a third direction. The floating member and the connector slide in the first direction. The limiting member is connected to the connector, and a portion of the limiting member and the connector form an installation gap in the first direction. At least a portion of the elastic member is located within the installation gap. One end of the elastic member is connected to the limiting member, and the other end abuts against or connects to the floating member. The first pulley is rotatably connected to the end of the floating member away from the elastic member. The third direction is perpendicular to the first direction and the second direction, respectively.

[0013] As an optional solution, the sliding assembly further includes a detection element, which is connected to the sliding plate and located beside the second side. The solar wing deployment and retraction device also includes a sensor connected to the second side. The detection element passes through the sensor to trigger the sensor to indicate that the winding is in place. The sensor is communicatively connected to the tension drive and the winding drive.

[0014] As an optional solution, the aforementioned support includes: A horizontal frame extends horizontally and is connected to the sliding assembly, and the air flotation component is connected to the horizontal frame. A vertical frame is connected to the upper side of the aforementioned horizontal frame, and the top of the aforementioned vertical frame is provided with a through hole for the aforementioned winding drive component to pass through. A support frame is vertically connected to the aforementioned vertical frame; The slide member and two guide members are provided. The slide member is placed on the support frame. The winding drive member is installed on the slide member. The two guide members are symmetrically arranged on opposite sides of the slide member along the second direction and connected to the support frame. The guide members form a groove on the side facing the slide member. The slide member and the groove slide in a sliding engagement in the first direction. Two locking members are provided in correspondence with the two guide members mentioned above. The locking members are threadedly connected to the guide members and can abut against the surface of the sliding member.

[0015] As an alternative, the vertical frame includes a first frame and a second frame that can be detachably connected. The first frame is vertically connected to the horizontal frame. A first semi-circular groove is formed at the upper end of the first frame. The second frame is fastened to the top of the first frame and a second semi-circular groove is formed on the lower side of the second frame. The first semi-circular groove and the second semi-circular groove together form the through hole.

[0016] A spacecraft comprising the aforementioned solar wing deployment and retraction device.

[0017] The beneficial effects of this invention are: This invention provides a solar wing deployment and retraction device. When the solar wing needs to be retracted, a retraction drive drives the roller to rotate, causing the solar wing to roll up. Simultaneously, the frame and platform slide in a second direction. As the solar wing retracts in the positive direction of the second direction, the support moves in the positive direction of the second direction under the action of the retraction force. During this process, because an air buoyancy component is provided between the support and the platform, the air buoyancy component applies an upward buoyancy force to the support, which assists in lifting the entire solar wing, reducing the friction generated by the sliding contact with the platform. When the solar wing is retracted, it is closer to the weightless state of space, and the simulation on the ground is closer to the state of space. At the same time, when the solar wing is deployed, the air buoyancy component also reduces friction, making the deployment of the solar wing smoother.

[0018] The present invention also provides a spacecraft including the aforementioned solar array deployment and retraction device. This spacecraft can reduce friction between the solar array and the platform during deployment or retraction, and the solar array, when deployed or retracted, more closely approximates the weightless state of space, thus reducing the spacecraft's energy consumption. Attached Figure Description

[0019] Figure 1 This is a schematic diagram of the structure of the solar wing deployment and retraction device provided by the present invention; Figure 2 yes Figure 1 Enlarged view of point A in the middle; Figure 3 yes Figure 2 Enlarged view of point B in the middle; Figure 4 yes Figure 1 Enlarged view of point C in the middle; Figure 5 yes Figure 1 Enlarged view of point D in the middle.

[0020] In the picture: 10. Platform; 11. Upper side; 12. First side; 13. Second side; 20. Retracting mechanism; 21. Bracket; 211. Horizontal frame; 212. Vertical frame; 2121. First frame; 2122. Second frame; 2123. Through hole; 213. Support frame; 214. Sliding component; 215. Guide component; 2151. Slide groove; 216. Locking component; 22. Air flotation component; 23. Winding drive component; 30. Tension supply mechanism; 31. Sliding assembly; 311. Sliding plate; 312. First pulley; 313. Second pulley; 314. Connecting component; 315. Floating component; 316. Limiting component; 317. Elastic component; 318. Installation interval; 319. Detection component; 32. Tension assembly; 321. Tension drive component; 322. Transmission assembly; 3221. Conveyor belt; 3222. Tensioning pulley; 40. Sensor; 200. Solar panel; 210. Reel. Detailed Implementation

[0021] The present invention will now be described in further detail with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and not intended to limit it. Furthermore, it should be noted that, for ease of description, the accompanying drawings show only the parts relevant to the present invention, and not all of the structures.

[0022] In the description of this invention, unless otherwise explicitly specified and limited, the terms "connected," "linked," and "fixed" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0023] In this invention, unless otherwise explicitly specified and limited, "above" or "below" the second feature can include direct contact between the first and second features, or contact between the first and second features through another feature between them. Furthermore, "above," "over," and "on top" of the second feature includes the first feature directly above or diagonally above the second feature, or simply indicates that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature includes the first feature directly below or diagonally below the second feature, or simply indicates that the first feature is at a lower horizontal level than the second feature.

[0024] In the description of this embodiment, the terms "upper," "lower," "left," and "right," etc., refer to the orientation or positional relationship shown in the accompanying drawings. They are used only for ease of description and simplification of operation, 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 the present invention. In addition, the terms "first" and "second" are used only for distinction in description and have no special meaning.

[0025] This embodiment provides a solar wing deployment and retraction device that reduces friction between the solar wing 200 and the platform 10 during deployment or retraction, making the solar wing 200 more closely resemble the weightless state of space when deployed or retracted. Figure 1 and Figure 2 As shown, the solar wing retraction device includes a retraction mechanism 20 and a first direction ( Figure 1 Two parallel platforms 10 are spaced apart in the X direction, and each platform 10 extends along the second direction. Figure 1The first direction is perpendicular to the second direction (Y direction); the retraction mechanism 20 is correspondingly arranged on the platform 10. The retraction mechanism 20 includes a bracket 21, an air flotation component 22 and a winding drive component 23. The bracket 21 is slidably engaged with the platform 10 in the second direction. The winding drive component 23 is installed on the bracket 21. The output end of the winding drive component 23 is coaxially fixed with the end of the reel 210 of the solar array 200. The winding drive component 23 can drive the reel 210 to rotate so that the solar array 200 is wound in the positive direction of the second direction. The air flotation component 22 is installed on the lower side of the bracket 21 and spaced apart from the platform 10.

[0026] In the aforementioned solar wing deployment and retraction device, when the solar wing 200 needs to be rolled up, the roll-up drive 23 drives the roll 210 to rotate, causing the solar wing 200 to roll up. At the same time, the support 21 and the platform 10 slide in a second direction. As the solar wing 200 rolls up in the second direction, the support 21 moves in the second direction under the action of the roll-up force. During this process, since the air buoyancy component 22 is provided between the support 21 and the platform 10, the air buoyancy component 22 applies an upward buoyancy force to the support 21, which assists in lifting the solar wing 200 as a whole, reducing the friction generated by the sliding contact with the platform 10. When the solar wing 200 is retracted, it is closer to the weightless state of space, which is closer to the state of space when simulated on the ground. At the same time, when the solar wing 200 is deployed, the air buoyancy component 22 can also reduce the friction and make the deployment of the solar wing 200 smoother.

[0027] The deployment of the roll-up flexible solar array involves the elastic release of stored strain energy from the carbon fiber elastic struts at both ends, thus extending the central solar cell array in a roll-up manner. This solution primarily optimizes the folding structure; the specific deployment structure is existing technology and will not be elaborated upon here.

[0028] Optionally, the air buoy 22 is an air bearing. The structure of air bearings is common in the prior art and will not be described in detail here. Preferably, four air buoys 22 are provided on the lower side of a bracket 21, corresponding to the four corners of the bracket 21, to ensure that the force on the bracket 21 is relatively uniform.

[0029] During the retraction of the solar array 200, the force that causes the support 21 to move in the second direction is mainly due to the winding force of the winding drive 23. While the solar array 200 is wound onto the reel 210, the shortening of the remaining amount of the solar array 200 forces the support 21 to move in the second direction. However, due to the instability of the winding force of the winding drive 23, the winding of the solar array 200 is irregular.

[0030] To solve the above problems, such as Figures 3-5As shown, the solar wing deployment and retraction device provided in this embodiment also includes a tension supply mechanism 30. The tension supply mechanism 30 includes a sliding component 31 and a tension component 32. The sliding component 31 is slidably engaged with the corresponding platform 10 in the second direction, and the bracket 21 is connected to the sliding component 31. The tension component 32 includes a tensioning drive 321, which is mounted on the platform 10. The output end of the tensioning drive 321 is connected to the sliding component 31 in a transmission manner. When the winding drive 23 is working, the tensioning drive 321 can drive the sliding component 31 to move in the opposite direction of the second direction. With the above configuration, when the winding drive 23 drives the reel 210 to rotate, the tensioning drive 321 applies a force in the opposite direction of the second direction to the sliding component 31, so that while the solar wing 200 is winding up, the reel 210 is pulled forward in the opposite direction. The solar wing 200 is in a tightened state throughout the winding process, and is more regular and compact after being wound onto the reel 210.

[0031] Optionally, continue to refer to Figures 3-5 The tension assembly 32 also includes a transmission assembly 322, which includes a conveyor belt 3221 and several tensioning rollers 3222. All tensioning rollers 3222 are rotatably connected to the platform 10. One tensioning roller 3222 is coaxially fixed to the output end of the tensioning drive 321. The conveyor belt 3221 passes sequentially through and is tensioned by the tensioning rollers 3222. The sliding assembly 31 is connected to the conveyor belt 3221. With this configuration, after the annular conveyor belt 3221 is tensioned, the tensioning drive 321 drives one tensioning roller 3222 to rotate, thereby driving the conveyor belt 3221 to move along the second direction. This, in turn, applies a force in the opposite direction to the second direction to the sliding assembly 31 and the support 21. It should be noted that although the force exerted by the conveyor belt 3221 on the sliding assembly 31 is in the opposite direction to the second direction, the winding drive 23 exerts a greater winding force, resulting in the final trajectory of the sliding assembly 31 being in the positive direction of the second direction.

[0032] Optionally, see Figure 4 and Figure 5 Tensioning rollers 3222 are respectively installed at the four corners of the conveyor belt 3221 to further improve the tension of the conveyor belt 3221. Figure 5 In this process, several tensioning rollers 3222 are added to the middle of the conveyor belt 3221, and the conveyor belt 3221 passes around the tensioning rollers 3222 in a serpentine manner to increase the tension of the conveyor belt 3221.

[0033] Optionally, such as Figure 3 and Figure 4As shown, the sliding assembly 31 includes a sliding plate 311, a first pulley 312, and at least three second pulleys 313. The sliding plate 311 extends along a first direction and is located on the upper side 11 of the platform 10. The bracket 21 is connected to the sliding plate 311. The first pulley 312 is rotatably connected to the lower side of the sliding plate 311, and its circumference abuts against the first side 12 of the platform 10. The first side 12 is perpendicular to the upper side 11 (e.g., ...). Figure 2 (As shown); each second pulley 313 is rotatably connected to the sliding plate 311, and its circumference abuts against the upper side 11. The transmission assembly 322 is disposed on the second side 13 of the platform 10 and connected to the corresponding end of the sliding plate 311. The second side 13 is parallel to the first side 12 and perpendicular to the upper side 11. The end of the sliding plate 311 opposite to the first pulley 312 is connected to the conveyor belt 3221. Figure 3 and Figure 4 The two sides of the platform 10 are shown respectively. The two ends of the sliding plate 311 cross the first side 12 and the second side 13 respectively to ensure the balance of the sliding plate 311 at the two ends opposite each other in the first direction. In addition, at least three second pulleys 313 are arranged non-linearly to ensure more stable support for the sliding plate 311 in the plane. In this embodiment, four second pulleys 313 are provided, and the four second pulleys 313 are arranged in a matrix on the sliding plate 311. In other embodiments, the number of second pulleys 313 can be three, five or more, which is not limited here.

[0034] Optionally, at least two first pulleys 312 are provided in the Y direction to prevent the sliding plate 311 from easily rotating when only one first pulley 312 is provided, which would cause the movement of the sliding plate 311 in the second direction to be unstable.

[0035] In addition, the sliding plate 311 and the platform 10 are connected by a pulley. Compared with the sliding rail type, this type is a point contact and forms rolling friction, which further reduces the contact area between the sliding component 31 and the platform 10, reduces friction, and improves the smoothness of the solar panel 200 unwinding and rewinding.

[0036] Optionally, such as Figure 3 As shown, the sliding assembly 31 also includes a connector 314, a floating member 315, a limiting member 316, and an elastic member 317. The connector 314 is connected to the sliding plate 311 and extends in a third direction (see also...). Figure 1In the Z direction, the floating member 315 and the connecting member 314 slide in the first direction. The limiting member 316 is connected to the connecting member 314, and a portion of the limiting member 316 and the connecting member 314 form an installation gap 318 in the first direction. At least a portion of the elastic member 317 is located within the installation gap 318. One end of the elastic member 317 is connected to the limiting member 316, and the other end of the elastic member 317 abuts against or connects to the floating member 315. The first pulley 312 is rotatably connected to the end of the floating member 315 away from the elastic member 317. The third direction is perpendicular to both the first and second directions. Through the above arrangement, the second pulley 313 can float in the first direction to adapt to the conveyor belt 3221 on the other side. When the conveyor belt 3221 moves slightly in the first direction, the second pulley 313 floats appropriately, preventing excessive contact force between the second pulley 313 and the first side 12, thus avoiding excessive friction.

[0037] Optionally, such as Figure 4 As shown, the sliding assembly 31 also includes a detection element 319, which is connected to the sliding plate 311 and located beside the second side 13. The solar wing deployment and retraction device also includes a sensor 40, which is connected to the second side 13. The detection element 319 triggers the sensor 40 to indicate that the retraction is complete. The sensor 40 is communicatively connected to the tension drive 321 and the retraction drive 23. With the above configuration, when the solar wing 200 finishes retraction, the detection element 319 triggers the sensor 40, and the tension drive 321 and the retraction drive 23 simultaneously stop working, preventing over-retraction and damage to the solar wing 200.

[0038] It should be noted that, Figure 1 To better show the other side of platform 10 (to facilitate magnifying positions C and D), an additional platform 10 is shown. This can be used as a backup platform. In practical applications, one solar panel can be used with two platforms 10.

[0039] Optionally, such as Figure 2 and Figure 3As shown, the bracket 21 includes a horizontal frame 211, a vertical frame 212, a support frame 213, a sliding member 214, and two guide members 215. The horizontal frame 211 extends horizontally and is connected to the sliding assembly 31. The air flotation member 22 is connected to the horizontal frame 211, and the sliding plate 311 is connected to the horizontal frame 211. The vertical frame 212 is connected to the upper side 11 of the horizontal frame 211, and the top of the vertical frame 212 is provided with a through hole 2123 for the winding drive member 23 to pass through. The support frame 213 is vertically connected to the vertical frame 212. The sliding member 214 is placed on the support frame 213, and the winding drive member 23 is installed on the sliding member 214. Two guide members 215 are symmetrically arranged on opposite sides of the slider 214 along the second direction and connected to the support frame 213. The guide member 215 forms a groove 2151 on the side facing the slider 214, and the slider 214 slides in cooperation with the groove 2151 in the first direction. Two locking members 216 are arranged one-to-one with the two guide members 215. The locking member 216 is threadedly connected to the guide member 215 and can abut against the surface of the slider 214. With the above arrangement, when the locking member 216 is released, the slider 214 can slide back and forth (i.e., in the first direction) under the guidance of the groove 2151, thereby changing the position of the winding drive member 23, which facilitates the position adjustment before installation with the reel 210 and the vertical frame 212.

[0040] Optionally, such as Figure 3 As shown, the vertical frame 212 includes a first frame 2121 and a second frame 2122 that are detachably connected. The first frame 2121 is vertically connected to the horizontal frame 211. A first semi-circular groove is formed at the upper end of the first frame 2121. The second frame 2122 is fastened to the top of the first frame 2121, and a second semi-circular groove is formed on the lower side of the second frame 2122. The first and second semi-circular grooves together form a through hole 2123. With the above arrangement, the output end of the winding drive 23 can be well fixed, and the first frame 2121 and the second frame 2122 are easy to disassemble. During installation, the second frame 2122 can be removed to install the winding drive 23. After the position is fixed, the second frame 2122 can be reinstalled.

[0041] Optionally, the platform 10 in this embodiment is a marble platform, which has a smooth surface, low coefficient of friction, and low manufacturing cost.

[0042] Optionally, in this embodiment, three platforms 10 are provided, with a solar panel 200 provided between each pair of adjacent platforms 10. In other embodiments, the number of platforms 10 can be flexibly set according to the total size of the solar panels 200, and is not limited here.

[0043] This embodiment also provides a spacecraft including the aforementioned solar array deployment and retraction device. This spacecraft can reduce friction between the solar array 200 and the platform 10 during deployment or retraction, making the solar array 200 closer to the weightless state of space, thus reducing the spacecraft's energy consumption.

[0044] Obviously, the above embodiments of the present invention are merely examples for clearly illustrating the present invention, and are not intended to limit the implementation of the present invention. Those skilled in the art will be able to make various obvious changes, readjustments, and substitutions without departing from the scope of protection of the present invention. It is neither necessary nor possible to exhaustively describe all embodiments here. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present invention should be included within the scope of protection of the claims of the present invention.

Claims

1. A solar wing deployment and retraction device, characterized in that, include: Two platforms (10) are spaced apart and parallel to each other in a first direction, each of which extends along a second direction, the first direction being perpendicular to the second direction; A retraction mechanism (20) is provided on the platform (10) in a corresponding manner. The retraction mechanism (20) includes a bracket (21), an air flotation component (22), and a winding drive component (23). The bracket (21) slides with the platform (10) in the second direction. The winding drive component (23) is installed on the bracket (21). The output end of the winding drive component (23) is coaxially fixed with the end of the reel (210) of the solar wing (200) in a corresponding manner. The winding drive component (23) can drive the reel (210) to rotate so that the solar wing (200) is wound up in the positive direction of the second direction. The air flotation component (22) is installed on the lower side of the bracket (21) and is spaced apart from the platform (10).

2. The solar wing deployment and retraction device according to claim 1, characterized in that, The air-bearing component (22) is an air-bearing bearing.

3. The solar wing deployment and retraction device according to claim 1, characterized in that, The solar array deployment and retraction device further includes a tension supply mechanism (30), which comprises: A sliding component (31) is slidably engaged with the corresponding platform (10) in the second direction, and the bracket (21) is connected to the sliding component (31). The tension assembly (32) includes a tension drive (321) mounted on the platform (10). The output end of the tension drive (321) is connected to the sliding assembly (31) in a transmission manner. When the winding drive (23) is working, the tension drive (321) can drive the sliding assembly (31) to move in the opposite direction of the second direction.

4. The solar wing deployment and retraction device according to claim 3, characterized in that, The tension assembly (32) further includes a transmission assembly (322), which includes a conveyor belt (3221) and a plurality of tensioning rollers (3222). The plurality of tensioning rollers (3222) are rotatably connected to the platform (10). One of the tensioning rollers (3222) is coaxially fixed with the output end of the tensioning drive (321). The conveyor belt (3221) passes through the plurality of tensioning rollers (3222) in sequence and is tensioned by the plurality of tensioning rollers (3222). The sliding assembly (31) is connected to the conveyor belt (3221).

5. The solar wing deployment and retraction device according to claim 4, characterized in that, The sliding component (31) includes: A sliding plate (311) extends along the first direction and is located on the upper side (11) of the platform (10), and the bracket (21) is connected to the sliding plate (311); The first pulley (312) is rotatably connected to the lower side of the sliding plate (311), and its periphery abuts against the first side (12) of the platform (10). The first side (12) is perpendicular to the upper side (11). At least three second pulleys (313) are rotatably connected to the sliding plate (311) and their circumference abuts against the upper side (11). The transmission assembly (322) is disposed on the second side (13) of the platform (10) and connected to the corresponding end of the sliding plate (311). The second side (13) is parallel to the first side (12) and perpendicular to the upper side (11). The end of the sliding plate (311) opposite to the first pulley (312) is connected to the conveyor belt (3221).

6. The solar wing deployment and retraction device according to claim 5, characterized in that, The sliding assembly (31) further includes a connector (314), a floating member (315), a limiting member (316), and an elastic member (317). The connector (314) is connected to the sliding plate (311) and extends along a third direction. The floating member (315) and the connector (314) are slidably engaged in the first direction. The limiting member (316) is connected to the connector (314), and a portion of the limiting member (316) and the connector (314) are in the first direction. An installation interval (318) is formed in the direction, at least a portion of the elastic member (317) is located within the installation interval (318), one end of the elastic member (317) is connected to the limiting member (316), and the other end of the elastic member (317) abuts or connects to the floating member (315). The first pulley (312) is rotatably connected to the end of the floating member (315) away from the elastic member (317), and the third direction is perpendicular to the first direction and the second direction, respectively.

7. The solar wing deployment and retraction device according to claim 5, characterized in that, The sliding assembly (31) further includes a detection element (319), which is connected to the sliding plate (311) and located on the side of the second side (13). The solar wing deployment and retraction device further includes a sensor (40), which is connected to the second side (13). The detection element (319) triggers the sensor (40) to indicate that the winding is in place. The sensor (40) is communicatively connected to the tension drive (321) and the winding drive (23).

8. The solar wing deployment and retraction device according to any one of claims 3-7, characterized in that, The support (21) includes: A horizontal frame (211) extends horizontally and is connected to the sliding assembly (31), and the air flotation element (22) is connected to the horizontal frame (211); A vertical frame (212) is connected to the upper side (11) of the horizontal frame (211), and the top of the vertical frame (212) is provided with a through hole (2123) for the winding drive (23) to pass through; The support frame (213) is vertically connected to the vertical frame (212); A slider (214) and two guides (215) are provided. The slider (214) is placed on the support frame (213). The winding drive (23) is installed on the slider (214). The two guides (215) are symmetrically arranged on opposite sides of the slider (214) along the second direction and connected to the support frame (213). The guides (215) form a groove (2151) on the side facing the slider (214). The slider (214) and the groove (2151) slide in the first direction. Two locking members (216) are provided in a one-to-one correspondence with the two guide members (215). The locking members (216) are threadedly connected to the guide members (215) and can abut against the surface of the sliding member (214).

9. The solar wing deployment and retraction device according to claim 8, characterized in that, The vertical frame (212) includes a first frame (2121) and a second frame (2122) that can be detachably connected. The first frame (2121) is vertically connected to the horizontal frame (211). A first semi-circular groove is formed at the upper end of the first frame (2121). The second frame (2122) is fastened to the top of the first frame (2121), and a second semi-circular groove is formed on the lower side of the second frame (2122). The first semi-circular groove and the second semi-circular groove together form the through hole (2123).

10. A spacecraft, characterized in that, Includes the solar array deployment and retraction device as described in any one of claims 1-9.

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