Moonlet solar wing capable of rapidly replacing battery piece

Abstract

The invention discloses a moonlet solar wing capable of quickly replacing battery pieces, which comprises a substrate frame and battery piece modules of the solar wing, a plurality of mounting shipping spaces for regularly arranging the battery piece modules are distributed on the substrate frame, and the battery piece modules are positioned between the mounting shipping spaces and the battery piece modules through locking devices. The solar wing veneers which are connected in a hinged mode are unfolded or folded through the wing unfolding mechanism. According to the solar wing veneer capable of replacing the battery pieces in the modularized mode, the locking devices are arranged, the battery pieces and the substrate frame are rapidly fixed and detached through the locking rod pieces, the elastic pieces, the locking bodies and other components, the replacement cost is reduced, and the modularized design is achieved. A telescopic spring is used in the locking device to provide stable locking force, adaptability is high, reliability is improved, cost is reduced, and maintenance and replacement are easy. According to the solar wing unfolding mechanism, overturning is achieved in the unfolding and folding processes at the same time, the deploying and retracting time is saved, and the working efficiency is improved.

Description

Technical Field

[0001] The present invention relates to the technical field of satellite solar wings, and particularly to a small satellite solar wing with replaceable solar cells quickly. Background Art

[0002] Currently, with the continuous increase in the number of satellites in orbit, among which the solar wing, as the energy supply system of the satellite, is the core element of space equipment and directly determines whether the satellite can operate normally in orbit. However, the extreme conditions of the space environment are likely to damage the solar wing, resulting in the actual service life of the satellite being much lower than expected. Therefore, it is crucial to regularly replace and maintain the solar cells on the solar wing. However, there are relatively many solar cells on a single substrate of the solar wing. If a solar cell on a single substrate is damaged, the entire substrate needs to be replaced, and the replacement cost is high and it is not convenient to replace.

[0003] In the prior art, the solar cells are usually fixed on the substrate by adhesives or integrated in a flexible substrate. Once damaged, the entire substrate or the solar wing needs to be replaced.

[0004] The present invention aims to provide a small satellite solar wing with replaceable solar cells quickly, which can realize the quick fixation of the solar cells on the solar wing substrate and can be quickly disassembled. Through the innovative deployment structure design, it ensures precise and reliable movement, high transmission efficiency, and simple and compact structure, thereby reducing the maintenance cost and enhancing the flexibility and reliability of the satellite solar wing. Summary of the Invention

[0005] The purpose of the present invention is to overcome the defects existing in the prior art and provide a small satellite solar wing with replaceable solar cells quickly.

[0006] To achieve the above purpose, the technical solution of the present invention is as follows: A solar wing single board with modular replaceable solar cells, including a substrate frame of the solar wing and a solar cell module. Installation compartments for arranging a number of solar cell modules regularly are distributed on the substrate frame, and a locking device is used to position the solar cell module between the installation compartment and the solar cell module.

[0007] Further, the locking device includes a substrate half-module arranged on the installation compartment and a battery half-module arranged on the solar cell module. When installed, a detachable coupling connection is formed between the battery half-module and the substrate half-module.

[0008] Further, the substrate half-module and the battery half-module are arranged in central symmetry; and both are provided with locking bodies for insertion and cooperation. A locking rod is rotatably arranged in the locking body, and an elastic member for providing a reset force to the locking rod; when the substrate half-module and the battery half-module are buckled, the ends of the two locking rods hold hands to form a splicing shaft, and under the action of the elastic member, the locking rod rotates around the center and is embedded in the locking body of the other party to form an anti-detachment buckle.

[0009] Furthermore, the plug end of the locking body is arranged in a stepped shape, and the plug end has a horizontal step surface perpendicular to the plug-in direction and a vertical step surface parallel to the plug-in direction, and a plug block and a slot are respectively formed on the horizontal step surface where the substrate half module and the battery half module are assembled.

[0010] Furthermore, the locking rod comprises a semi-cylindrical tile-shaped shaft rod, and a driving lever connected to the outer circumferential surface of the tile-shaped shaft rod; A semicircular groove is provided on the locking body, and the tile-shaped shaft is rotatably arranged in the semicircular groove; one end of the elastic member is connected to the driving lever, and the other end is connected to the locking body, and the elastic member is configured to always make the edge of the tile-shaped shaft on the side away from the insertion direction of the locking body have a movement tendency to rotate out to the outside of the locking body.

[0011] A solar wing deployment mechanism comprises at least two hingedly connected solar wing panels and a wing deployment mechanism for driving the solar wing panels to deploy or fold, wherein the wing deployment mechanism comprises a swinging main arm and a side expansion arm, the hinge axes of the two solar wing panels are positioned at the ends of the swinging main arms, a main arm slider is provided on the swinging main arm, and the main arm slider slides along the direction of the swinging main arm; one end of the side expansion arm is hinged to the solar wing panel, and the other end is hinged to the main arm slider.

[0012] Furthermore, the solar wing single panel performs a follow-up expansion movement of unfolding or folding while the swinging main arm rotates. The swinging main arm is rotatably arranged on the main support arm, and the end of the main support arm is located on one side of the swinging main arm and is provided with a curved guide rail. The swinging main arm is provided with a linear guide rail for guiding the main arm slider, and the curved guide rail is at least partially arranged in a fan-shaped area swept by the linear guide rail; the end of the main arm slider is slidably arranged in the curved guide rail, so that the main arm slider is guided by the linear guide rail and the curved guide rail at the same time to perform a compound movement.

[0013] Furthermore, a fixed guide rail is provided on the main support arm, and a sliding block in the groove is slidably arranged in the fixed guide rail; a second connecting rod is fixedly provided on one side of the swing main arm, the end of the second connecting rod is hinged to the first connecting rod, and the other end of the first connecting rod is hinged to the sliding block in the groove.

[0014] Furthermore, a motor body is provided on the main support arm, a cam disc is provided at the driving end of the motor body, a cam track of a predetermined shape is provided on one side of the cam disc, and the end of the slider in the groove is placed in the cam track to form a cam fit.

[0015] A wing-spreading small satellite comprises a solar wing panel with modular replaceable battery cells as described above and a small satellite solar wing with rapidly replaceable battery cells as described above; and also comprises a satellite body, wherein a satellite connecting frame for controlling the rotation of a main support arm is provided on the side of the satellite body.

[0016] The advantages and beneficial effects of the present invention are as follows: 1. In the present invention, the locking device provided on the solar wing single panel with modular battery cell replacement realizes the rapid fixation and disassembly of the battery cell and the substrate frame through components such as locking rods, elastic members, and locking bodies, reduces the replacement cost, and realizes modular design.

[0017] 2. The telescopic spring is used in the locking device to provide a stable locking force, which has strong adaptability, improves reliability, reduces costs, and is easy to maintain and replace.

[0018] 3. In the solar wing deployment mechanism of the present invention, flipping is simultaneously realized during the deployment and retraction processes, saving deployment and recovery time and improving work efficiency.

[0019] 4. The principle of the linkage combined multi-directional sliding slider is used in the solar wing deployment mechanism to realize precise linear or curvilinear motion, and has the advantages of simple structure, high reliability, accurate positioning, and strong load-bearing capacity.

[0020] 5. The solar wing deployment mechanism uses a cam mechanism to achieve precise speed control. By designing the cam contour curve, the driven slider realizes complex motion laws. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 is one of the structural schematic diagrams of a winged small satellite of the present invention; Figure 2 is another structural schematic diagram of the winged small satellite of the present invention; Figure 3 is the third structural schematic diagram of the winged small satellite of the present invention; Figure 4 is the structural schematic diagram of the solar wing single panel of the present invention; Figure 5 is the structural schematic diagram of the battery cell module of the present invention; Figure 6 is the axonometric drawing of the locking device of the present invention; Figure 7 is the schematic diagram of the insertion and locking steps of the locking device of the present invention; Figure 8 is the installation schematic diagram of the locking device of the present invention; Figure 9 is one of the structural schematic diagrams of the wing deployment mechanism of the present invention; Figure 10 is another structural schematic diagram of the wing deployment mechanism of the present invention; Figure 11 is the fourth structural schematic diagram of the winged small satellite of the present invention; In the figure: 1. Single solar wing board; 2. Satellite main body; 3. Substrate frame; 4. Battery cell module; 5. Installation position; 6. Locking device; 7. Substrate half-module; 8. Battery half-module; 9. Locking main body; 10. Locking rod; 11. Elastic member; 12. Fitting shaft; 13. Plug end; 14. Horizontal stepped surface; 15. Vertical stepped surface; 16. Insert block; 17. Slot; 18. Tile-shaped shaft rod; 19. Driving lever; 20. Semi-circular groove; 21. Edge; 22. Wing unfolding mechanism; 23. Swing main arm; 24. Side unfolding support arm; 25. Main arm slider; 26. Main support arm; 27. Curved guide rail; 28. Linear guide rail; 29. Fixed guide rail; 30. Slider in the slot; 31. Second connecting rod; 32. First connecting rod; 33. Motor main body; 34. Cam disc; 35. Satellite connecting frame. Detailed implementation manners

[0022] The following combines the accompanying drawings and embodiments to further describe the detailed implementation manners of the present invention. The following embodiments are only used to more clearly illustrate the technical solutions of the present invention, and cannot be used to limit the protection scope of the present invention.

[0023] A wing-unfolding small satellite, as Figures 1-11 shown, includes a satellite main body 2, and a satellite connecting frame 35 for controlling the rotation of the main support arm 26 is provided on the side of the satellite main body 2. Exemplarily, satellite connecting frames 35 are provided through the side walls on the opposite sides of the satellite main body 2, and a servo motor for driving the satellite connecting frame 35 to rotate at a fixed angle is provided inside the satellite, so as to control the rotation direction of the solar wings on both sides of the satellite to face the sun. It has the characteristic of flexible adjustment, and when in use, any side of the solar wing can be controlled to flip alone or flipped simultaneously.

[0024] In the prior art, the battery cells on the solar wings are usually fixedly arranged. If any battery cell on the single solar board is damaged, the entire board must be replaced, resulting in high maintenance costs and inconvenient replacement.

[0025] As an improvement, in this embodiment, a single solar wing board 1 with modular battery cell replacement is designed, including a substrate frame 3 of the solar wing and a battery cell module 4. Installation positions 5 for regularly arranging a number of battery cell modules 4 are distributed on the substrate frame 3, and a locking device 6 is used to position the battery cell module 4 between the installation position 5 and the battery cell module 4. Thus, rapid fixation and disassembly between the battery cell module 4 and the substrate frame 3 are realized.

[0026] Specifically, as Figure 4 , 5As shown in the figure, in this embodiment, a plurality of installation compartments 5 are arranged in sequence on the substrate frame 3. The installation compartment 5 is a rectangular groove-shaped installation compartment 5 that matches the shape of the battery cell module 4. When the battery cell module 4 is placed in the installation compartment 5, good position positioning can be obtained. The fixation of the battery cell module 4 in the installation compartment 5 can be carried out by means of interference fit between the periphery of the installation compartment 5 and the battery cell supplemented by adhesive bonding; it can also be fixed by means of snap fixation. Snap fasteners are provided around the installation compartment 5. When the battery cell is pressed into the compartment, the snap fasteners pop out and snap onto the edge of the battery cell to form the fixation of the battery cell and the frame; it can also be positioned by using the locking device 6 designed in this embodiment. As Figures 6-8 shown, the two short sides of the battery cell module 4 are respectively provided with the locking device 6. During installation, when the locking devices 6 on both sides are snapped onto the corresponding snap positions on the substrate frame 3, the connection and fixation can be completed.

[0027] Specifically, the locking device 6 includes a substrate half-module 7 provided on the installation compartment 5 and a battery half-module 8 provided on the battery cell module 4. As Figure 6 shown, the shape structures of the two half-modules are generally the same. The two half-modules are respectively arranged on the battery cell and the substrate frame 3. During installation, a detachable coupling connection is formed between the battery half-module 8 and the substrate half-module 7. The solar wing single board 1 of the small satellite solar wing has five battery cells, and each battery cell is connected to a part of the locking device 6 (i.e., the half-module). The other part of the locking device 6 is connected to the substrate frame 3. The two parts of the locking device 6 are used to realize the quick installation or disassembly of the battery cell replacement.

[0028] Specifically, the two generally identical half-modules are as Figures 6-8 shown, that is, the substrate half-module 7 and the battery half-module 8 are centrosymmetrically arranged when they are inserted relatively; and both are provided with locking bodies 9 for insertion and mating. Specifically, the plug end 13 of the locking body 9 is arranged in a stepped shape. The plug end 13 has a horizontal step surface 14 perpendicular to the insertion direction and a vertical step surface 15 parallel to the insertion direction. Exemplarily, the stepped plug end 13 in this embodiment is provided with two levels of steps and forms two horizontal step surfaces 14, and the two horizontal step surfaces 14 are connected by a vertical step surface 15. When the plug ends 13 of the two half-modules are inserted relatively, the horizontal step surface 14 at the high point of one half-module fits with the horizontal step surface 14 at the low point of the other half-module, and the vertical step surfaces 15 on the two half-modules also fit with each other. In this way, a rectangular parallelepiped-shaped combined plug can be formed after the insertion and mating. Its overall shape is regular and it is convenient to be arranged on the solar wing single board 1; as an improvement, in order to prevent the two locking bodies 9 from having relative lateral displacement after insertion, insertion blocks 16 and slots 17 are respectively formed on the horizontal step surfaces 14 where the substrate half-module 7 and the battery half-module 8 are joined. Specifically, exemplarily, asFigures 6-8 As shown, a protruding plug block 16 can be formed on the horizontal stepped surface 14 at the high point end, and a slot 17 can be formed correspondingly on the horizontal stepped surface 14 at the low point end. When the two locking bodies 9 are docked, the plug block 16 cooperates with the slot 17 to avoid lateral sliding. Of course, the number of the plug blocks 16 and the slots 17 is not limited. Figure 8 As shown, two plugs are arranged side by side on the high point horizontal step surface 14. As an improvement, the plug and the plug block 16 can be given the function of electrical connection, which not only realizes the auxiliary fixation of the lateral position, but also enables the corresponding plug and the plug block 16 to connect the circuit between the substrate frame 3 and the battery module 4 after plug connection, thereby achieving not only the fixing effect, but also the electrical connection effect, and also directly connects the circuit during the battery installation process, avoiding the cumbersome operation of secondary circuit connection.

[0029] As an improvement, a locking rod 10 is provided for rotational movement in the locking body 9, and an elastic member 11 is provided for providing a reset force to the locking rod 10; when the substrate half module 7 and the battery half module 8 are buckled together, the ends of the two locking rods 10 shake hands to form a splicing axis 12, and under the action of the elastic member 11, the locking rod 10 rotates around the center and embeds into the other locking body 9 to form an anti-drop buckle. In the aforementioned embodiment, the lateral positioning of the two half modules is achieved by the stepped surface insertion and the plug-in connection of the plug and the plug block 16, but there is still a risk of force disengagement in the length direction. This embodiment further provides a locking rod 10, such as Figure 7 As shown, the locking rod 10 includes a semi-cylindrical tile-shaped shaft rod 18 and a driving lever 19 connected to the outer circumferential surface of the tile-shaped shaft rod 18 .

[0030] The locking body 9 is provided with a semicircular groove 20 on the vertical step surface 15, and the semicircular groove 20 is an open groove. When the two locking bodies 9 are inserted into place, the openings of the two semicircular grooves 20 are relatively spliced ​​to form a cylindrical hole, and the tile-shaped shaft rod 18 is rotatably set in the semicircular groove 20; one end of the elastic member 11 is connected to the driving lever 19, and the other end is connected to the locking body 9. The elastic member 11 is configured to always make the edge 21 of the tile-shaped shaft rod 18 on the side away from the insertion direction of the locking body 9 have a movement tendency to rotate out to the outside of the locking body 9.

[0031] The specific principle is that before locking, the front ends of the locking bodies 9 in the two-part locking device 6 are aligned with each other and press inward. During the initial insertion, the front end of the locking body 9 presses on the tile-shaped shaft rod 18 in another locking body 9, causing the locking rod 10 to rotate by applying pressure, and stretching the elastic member 11. Exemplarily, the elastic member 11 can adopt the following structural form: it includes a first hinge joint, a spring, and a second hinge joint. The two ends of the spring are respectively connected to the two hinge joints. The first hinge joint is hinged to the driving lever 19, and the second hinge joint is hinged to the locking body 9. During the insertion process, the rotation of the tile-shaped shaft rod 18 drives the driving lever 19 to rotate, thereby stretching the telescopic spring. As Figures 6-8 shown, the edge 21 on the protruding side of the semi-cylindrical tile-shaped shaft rod 18 contracts towards the center, so that the planar side of the tile-shaped shaft rod 18 is flush with the vertical stepped surface 15, and then the relative insertion can continue; the locking body 9 can continue to move forward until the insertion block 16 is inserted into the slot 17 of the other part. At this time, the two semi-circular grooves 20 are spliced to form a cylindrical hole. At the same time, the tile-shaped shaft rods 18 on both sides are also spliced into the combined shaft 12. At this time, the combined shaft 12 can rotate in the cylindrical hole. Since there is no external force applied on the flat side of the tile-shaped shaft rod 18 of the locking rod 10 at this time, the telescopic spring contracts back to its original state, and the locking body 9 can no longer apply pressure to the semi-cylindrical surface. The two tile-shaped shaft rods 18 rotate in the opposite direction and are engaged with each other into the semi-circular grooves 20 of each other to form the locked state of the locking device 6, so that the battery cell is fixed on the substrate.

[0032] A solar wing deployment mechanism includes at least two hinged solar wing single plates 1, and a wing deployment mechanism 22 for driving the solar wing single plates 1 to deploy or retract. Exemplarily, as Figure 1 shown, solar wings are respectively arranged on both sides of the satellite body 2. Each side of the solar wing is composed of two identical-sized solar wing single plates 1 hinged together. When the satellite is in orbit, the solar wing single plates 1 on both sides are controlled to deploy to form a larger-area solar wing.

[0033] Specifically, as Figure 9 、 10As shown, the wing unfolding mechanism 22 includes a swinging main arm 23 and side unfolding support arms 24. The hinge axes of the two solar wing single plates 1 are positioned at the end of the swinging main arm 23. A main arm slider 25 is provided on the swinging main arm 23, and the main arm slider 25 slides along the direction of the swinging main arm 23. A linear guide rail 28 for guiding the main arm slider 25 is provided on the swinging main arm 23, and the main arm slider 25 slides on the linear guide rail 28. In this embodiment, two side unfolding support arms 24 are simultaneously hinged to the main arm slider 25. And considering avoiding interference with the solar wing single plates 1 during folding, the side unfolding support arms 24 are designed to be curved, specifically divided into a first curved arm and a second curved arm. One ends of the two curved arms are simultaneously hinged to the main arm slider 25, and the other ends are hinged to the corresponding solar wing single plates 1. Thus, when the main arm slider 25 is pushed forward, the two solar wing single plates 1 can be folded together as Figure 9 and 10 shown. Conversely, when the main arm slider 25 moves backward, the two solar wing single plates 1 are pulled by the side unfolding support arms 24 to be unfolded flatly.

[0034] Furthermore, the solar wing single plate 1 performs a follow-up unfolding movement of unfolding or folding while the swinging main arm 23 rotates. The swinging main arm 23 is rotatably arranged on the main support arm 26. A curved guide rail 27 is provided at one side of the end of the main support arm 26 where the swinging main arm 23 is located. At least part of the curved guide rail 27 is arranged in the fan-shaped area swept by the rotation of the linear guide rail 28. The end of the main arm slider 25 is slidably arranged in the curved guide rail 27, so that the main arm slider 25 is guided by both the linear guide rail 28 and the curved guide rail 27 to perform a compound movement. Thus, the movement of the main arm slider 25 is jointly controlled by the linear guide rail 28 and the curved guide rail 27 to form a compound movement, as Figure 9 and 10 shown. When the swinging main arm 23 is controlled to rotate counterclockwise, under the action of the curved guide rail 27, the main arm slider 25 slides along the linear track to its front end, realizing the function of pushing the main arm slider 25 forward. At this time, the two solar wing single plates 1 are folded and retracted on the one hand, and on the other hand, they are driven by the swinging main arm 23 to flip upward. Thus, the precise unfolding and flipping of the solar wing single plates 1 are realized, and the whole mechanism is designed to be simple, compact and highly reliable.

[0035] Further, a fixed guide rail 29 is provided on the main support arm 26. A slider 30 is slidably arranged in the fixed guide rail 29. In actual use, the rotating shaft end of the swing main arm 23 is rotatably arranged at the front end of the fixed guide rail 29, so that the swing gradually swings on the main support arm 26. A second connecting rod 31 is fixedly arranged on one side of the swing main arm 23. The end of the second connecting rod 31 is hinged to the first connecting rod 32, and the other end of the first connecting rod 32 is hinged to the slider 30 in the groove. When the slider 30 in the groove actually slides, the effect formed is that the swing is driven to gradually rotate around its rotating shaft end through the hinge of the first connecting rod 32 and the second connecting rod 31. And it can be understood that the process of this rotation also forms a driving force for folding or retracting the single panel 1 of the rear-stage solar wing. Further, its front stage drives the slider 30 in the groove to move through a cam structure. The driving force of the front stage includes a motor body 33 arranged on the main support arm 26. A cam disc 34 is arranged at the driving end of the motor body 33. A cam track with a predetermined shape is arranged on one side of the cam disc 34. The end of the slider 30 in the groove is placed in the cam track to form a cam fit. The cam disc 34 is driven by the motor body 33. The surface of the cam disc 34 is provided with a cam track designed according to a preset moving state. Through the rotation of the motor and the transmission of the cam fit, the slider 30 in the groove is controlled to move linearly and stably along the fixed guide rail 29. Generally, it serves as the driving force of the front stage, and then the driving force is transmitted to the swing main arm 23 of the rear stage through the first connecting rod 32 and the second connecting rod 31, so that it rotates clockwise or counterclockwise, forming the flipping control of the solar wing. At the same time, the composite influence of the curved guide rail 27 and the linear guide rail 28 on the movement of the main arm slider 25 is utilized to further control the deployment and retraction of the single panel 1 of the final-stage solar wing.

[0036] The solar wing deployment mechanism uses a cam mechanism to achieve precise speed control. By designing the cam contour curve, the driven slider realizes a complex motion law. The linkage combined multi-directional sliding slider mechanism is used in the solar wing deployment mechanism to achieve precise linear or curved motion, with the advantages of simple structure, accurate positioning, strong load-bearing capacity, etc. During the deployment and retraction process, flipping is achieved simultaneously, saving deployment and recovery time and improving work efficiency.

[0037] The above are only the preferred embodiments of the present invention. It should be noted that for those of ordinary skill in the art in this technical field, without departing from the technical principle of the present invention, several improvements and refinements can still be made, and these improvements and refinements should also be regarded as the protection scope of the present invention.

Claims

1. A solar wing single panel with modular battery cell replacement, characterized in that, The invention comprises a solar wing substrate frame (3) and a battery module (4); a plurality of battery modules (4) are distributed on the substrate frame (3) and are regularly arranged in an installation compartment (5); and a locking device (6) is used between the installation compartment (5) and the battery module (4) to position the battery module (4).

2. The single solar wing board with modular battery chip replacement according to claim 1, characterized in that The locking device (6) comprises a substrate half module (7) arranged on the installation compartment (5) and a battery half module (8) arranged on the battery cell module (4); during installation, a detachable coupling connection is formed between the battery half module (8) and the substrate half module (7).

3. The single solar wing board with modular battery chip replacement according to claim 2, characterized in that The substrate half module (7) and the battery half module (8) are arranged symmetrically with respect to the center; and both are provided with a locking body (9) for mating, a locking rod (10) is provided for rotational movement in the locking body (9), and an elastic member (11) provides a reset force for the locking rod (10); when the substrate half module (7) and the battery half module (8) are buckled together, the ends of the two locking rods (10) shake hands to form a splicing axis (12), and under the action of the elastic member (11), the locking rod (10) rotates around the center and is embedded in the other locking body (9) to form an anti-drop buckle.

4. The single solar wing board with modular battery chip replacement according to claim 3, characterized in that The plug end (13) of the locking body (9) is arranged in a stepped shape, and the plug end (13) has a horizontal step surface (14) perpendicular to the plugging direction and a vertical step surface (15) parallel to the plugging direction. The horizontal step surface (14) where the substrate half module (7) and the battery half module (8) are joined is respectively formed with an insert block (16) and a slot (17).

5. A single solar wing panel with modular battery cell replacement according to claim 3, characterized in that, The locking rod (10) comprises a semi-cylindrical tile-shaped shaft rod (18) and a driving lever (19) connected to the outer circumferential surface of the tile-shaped shaft rod (18); The locking body (9) is provided with a semicircular groove (20), and the tile-shaped shaft rod (18) is rotatably arranged in the semicircular groove (20); one end of the elastic member (11) is connected to the driving lever (19), and the other end is connected to the locking body (9), and the elastic member (11) is configured to always make the edge (21) of the tile-shaped shaft rod (18) on the side away from the insertion direction of the locking body (9) have a movement tendency to rotate out of the locking body (9).

6. A solar panel deployment mechanism, characterized in that, A solar wing panel (1) with modular replaceable battery cells as claimed in any one of claims 1 to 5, comprising at least two hingedly connected solar wing panels (1), and a wing spreading mechanism (22) for driving the solar wing panel (1) to unfold or fold, wherein the wing spreading mechanism (22) comprises a swinging main arm (23) and a side spreading arm (24), the hinge axes of the two solar wing panels (1) are positioned at the ends of the swinging main arms (23), the swinging main arms (23) are provided with a main arm slider (25), and the main arm slider (25) slides in the direction of the swinging main arms (23); one end of the side spreading arm (24) is hinged to the solar wing panel (1), and the other end is hinged to the main arm slider (25).

7. The solar panel deployment mechanism according to claim 6, characterized in that, The single solar panel (1) performs a follow-up deployment motion of unfolding or folding while the swing main arm (23) rotates. The swing main arm (23) is rotatably arranged on the main support arm (26). A curved guide rail (27) is provided at one side of the end of the main support arm (26) where the swing main arm (23) is located. A linear guide rail (28) for guiding the main arm slider (25) is provided on the swing main arm (23). At least part of the curved guide rail (27) is arranged within the fan-shaped area swept by the rotation of the linear guide rail (28). The end of the main arm slider (25) is slidably arranged within the curved guide rail (27), so that the main arm slider (25) is guided by both the linear guide rail (28) and the curved guide rail (27) to perform a compound motion.

8. The solar panel deployment mechanism according to claim 6, characterized in that, A fixed guide rail (29) is provided on the main support arm (26), and a slider in the groove (30) is slidably arranged within the fixed guide rail (29). A second connecting rod (31) is fixedly provided on one side of the swing main arm (23). The end of the second connecting rod (31) is hinged to a first connecting rod (32), and the other end of the first connecting rod (32) is hinged to the slider in the groove (30).

9. The solar panel deployment mechanism according to claim 8, wherein A motor body (33) is provided on the main support arm (26). A cam disk (34) is provided at the driving end of the motor body (33). A cam track with a predetermined shape is provided on one side of the cam disk (34). The end of the slider in the groove (30) is placed within the cam track to form a cam fit.

10. A winged small satellite, characterized in that, It includes the single solar panel (1) for modular replacement of battery cells as described in any one of claims 1-5 and the small satellite solar wing for rapid replacement of battery cells as described in any one of claims 6-9. It further includes a satellite body (2), and a satellite connecting frame (35) for controlling the rotation of the main support arm (26) is provided on the side of the satellite body (2).

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