Satellite solar wing deployment locking mechanism

Abstract

This application relates to a satellite solar panel deployment and locking mechanism, belonging to the field of aircraft technology. The mechanism includes a storage frame, a connecting frame, and multiple solar panels disposed on opposite sides of the satellite body. The two ends of the connecting frame are respectively hinged to the side of the satellite body and the end of the solar panel closest to the satellite body. Adjacent solar panels are hinged to each other. Deployment components for applying rotational thrust to the connecting frame and solar panels are provided between the connecting frame and the satellite body, between the connecting frame and the solar panels, and between adjacent solar panels. A limiting component is provided on the storage frame for restricting solar panels away from the satellite body, allowing the multiple solar panels to be stacked sequentially. This application stacks multiple solar panels against the side of the satellite body, reducing the possibility of damage to the solar panels. The deployment components apply rotational thrust to the connecting frame and solar panels, facilitating the deployment of multiple solar panels on both sides of the satellite body, thus improving the safety of satellite flight.

Description

Technical Field

[0001] This application relates to the field of aircraft technology, and in particular to a satellite solar array deployment and locking mechanism. Background Technology

[0002] In recent years, satellite technology has developed rapidly, and satellites have been widely used in various industries and fields. During the satellite's launch phase, the solar panels are folded and retracted, pressing them firmly against both sides of the satellite body. After the satellite enters orbit and its attitude stabilizes, the panels are unlocked, and the solar panels unfold synchronously under the action of the deployment and locking mechanism, providing an indication signal that the satellite is effectively locked once in place.

[0003] There are various deployment mechanisms for the solar panels of existing satellites, with the most common being a four-point clamping mechanism using pyrotechnics. However, when the solar panels are stacked on both sides of the satellite body, the use of ropes to apply tension to the solar panels results in poor stability, thus affecting the safety of satellite flight. Summary of the Invention

[0004] In order to effectively improve the safety of satellite flight, this application provides a satellite solar array deployment and locking mechanism.

[0005] The purpose of this application is to provide a satellite solar panel deployment and locking mechanism, which adopts the following technical solution:

[0006] A satellite solar panel deployment and locking mechanism includes a storage frame, a connecting frame, and multiple solar panels disposed on opposite sides of a satellite body. The two ends of the connecting frame are respectively hinged to the side of the satellite body and the end of the solar panel closest to the satellite body. Adjacent solar panels are hinged to each other. Deployment components for applying rotational thrust to the connecting frame and solar panels are provided between the connecting frame and the satellite body, between the connecting frame and the solar panels, and between adjacent solar panels. The storage frame is provided with a limiting component for restricting the solar panels away from the satellite body so that the multiple solar panels are stacked sequentially.

[0007] By adopting the above technical solution, the storage frame and the limiting component work together to allow multiple solar panels to be stacked and abutted against the side of the satellite body. When the satellite body is in operation, the damage to the solar panels can be reduced. When the satellite body is in operation, the limiting component releases the restriction on the solar panels, and the deployment component applies rotational thrust to the connecting frame and the solar panels, which facilitates the deployment of multiple solar panels on both sides of the satellite body, improving the safety of satellite flight. The mechanism is simple and reliable.

[0008] Optionally, the deployment assembly includes a first connector, a second connector, a rotating shaft, and an elastic element. The first and second connectors are rotatably connected to the rotating shaft. One side of the first connector is fixedly connected to the satellite body, the connecting frame, or the solar panel, and one side of the second connector is fixedly connected to the connecting frame or the solar panel. The elastic element is sleeved on the rotating shaft, with one end of the elastic element fixedly connected to the first connector and the other end of the elastic element fixedly connected to the second connector.

[0009] By adopting the above technical solution, the first and second joints can rotate on the rotating shaft, so that the connecting frame and the solar panel can rotate and unfold under the action of the elastic element, resulting in a simple structure.

[0010] Optionally, the limiting component includes a limiting block and a limiting groove. The side wall of the storage frame is provided with a sliding groove, and the limiting block is slidably connected in the sliding groove. The limiting groove is located on the side of the solar panel away from the satellite body. The end of the limiting block is inserted into the limiting groove. A limiting spring is provided in the sliding groove. One end of the limiting spring is fixedly connected to the bottom of the sliding groove, and the other end of the limiting spring is fixedly connected to the limiting block. The storage frame is provided with an electromagnet for driving the limiting block to retract into the sliding groove.

[0011] By adopting the above technical solution, when the limiting block is aligned with the limiting groove, the end of the limiting block will be inserted into the limiting groove under the action of the limiting spring, so that multiple solar panels can be stacked and abutted against the side of the satellite body, that is, the solar panels can be stored in the storage frame, which is convenient for protecting the solar panels; by cooperating with the limiting block, the limiting block can be attracted and the end of the limiting block can be retracted into the sliding groove, so that the connecting frame and the solar panels can be rotated and deployed under the action of the deployment assembly.

[0012] Optionally, the solar panel includes a fixed frame and a solar panel, the solar panel being fixed within the fixed frame; a first connecting post is fixedly connected to one end of the fixed frame near the satellite body, and a second connecting post is fixedly connected to the other end of the fixed frame; a connecting sleeve that engages with the first connecting post is sleeved on the second connecting post; a connecting spring is sleeved on the second connecting post, one end of the connecting spring being fixedly connected to the second connecting post, and the other end of the connecting spring being fixedly connected to the connecting sleeve.

[0013] By adopting the above technical solution, after multiple solar panels are rotated and deployed, the connecting sleeve will be inserted into the outside of the first connecting post under the action of the connecting spring; the first connecting post, the second connecting post and the connecting sleeve cooperate to make the connection between the connecting frame and the solar panel and between adjacent solar panels more stable, thereby improving the safety of satellite flight.

[0014] Optionally, a storage assembly is provided on one side of the satellite body. The storage assembly includes a drive unit, a winding reel, and a winding rope. The drive unit is fixed inside the satellite body to drive the winding reel to rotate. One end of the winding rope is wound around the winding reel, and the other end of the winding rope is fixedly connected to the side of the solar panel away from the satellite body.

[0015] By adopting the above technical solution, the driving component drives the winding wheel to rotate, which allows the coiling rope to be wound around the winding wheel. This facilitates pulling the solar panels that are far from the satellite body toward the satellite body, thereby applying a rotational pulling force to the connecting frame and the solar panels. This makes it easier for multiple solar panels to be stacked and abutted on both sides of the satellite body, achieving the effect of coiling the solar panels.

[0016] Optionally, the side of the solar panel is provided with an unlocking groove along the width direction of the solar panel, an unlocking block is slidably connected in the unlocking groove, and the other end of the retracting rope is fixedly connected to the unlocking block; an unlocking spring is provided in the unlocking groove, the unlocking spring is located on the side of the unlocking block closer to the satellite body, and one end of the unlocking spring is fixedly connected to the groove wall of the unlocking groove, and the other end of the unlocking spring is fixedly connected to the unlocking block; the retracting rope is provided with a linkage component for pulling the connecting sleeve and the first connecting post to separate from each other.

[0017] By adopting the above technical solution, the unlocking block and the unlocking slot cooperate to allow the coiling rope to move along the width direction of the solar panel; that is, when the winding wheel winds the coiling rope, it pulls the coiling rope a distance, and then the pulling of the coiling rope causes the connecting frame and the solar panel to rotate. The linkage component allows the movement of the coiling rope to drive the connecting sleeve to move together towards the satellite body, making it easier for the connecting sleeve to separate from the first connecting post, and facilitating the rotation of the connecting frame and the solar panel under the tension of the coiling rope.

[0018] Optionally, the linkage component includes a linkage block and a locking ring. The linkage block is fixedly connected to the retracting rope, and the locking ring is fixedly connected to the outer wall of the connecting sleeve. The linkage block abuts against the side of the locking ring away from the satellite body. The locking ring has an opening for the retracting rope to move out. When multiple solar panels are stacked and abut against each other, the opening of the locking ring faces the retracting rope.

[0019] By adopting the above technical solution, when the solar panel is deployed, the locking ring is sleeved outside the retracting rope. The retracting rope pulls the unlocking block to move, causing the linkage block to move towards the satellite body along with the locking ring, thereby achieving the purpose of separating the connecting sleeve from the first connecting post. When the solar panel and the connecting frame rotate, the connecting sleeve and the locking ring will move away with the rotation of the solar panel and the connecting frame, and the opening facilitates the retracting rope to move out from inside the locking ring. Thus, the presence of the locking ring will not affect the tension applied by the retracting rope to the rotation of the solar panel, making it easier for the solar panel to be stacked and abutted against both sides of the satellite body.

[0020] Optionally, one end of the first connector has a connecting hole, and a positioning rod is slidably connected in the connecting hole. The end face of the second connector facing the first connector has an arc-shaped groove concentric with the rotating shaft. The arc-shaped groove is inserted into the end of the positioning rod, and the depth of the arc-shaped groove gradually decreases. A positioning spring is sleeved on the positioning rod. One end of the positioning spring is fixedly connected to the wall of the connecting hole, and the other end of the positioning spring is fixedly connected to the positioning rod.

[0021] By adopting the above technical solution, the first joint and the second joint rotate relative to each other on the rotating shaft to achieve the purpose of rotating and unfolding the solar panel and the connecting frame. After the solar panel and the connecting frame are unfolded, the end of the positioning rod will be inserted into the bottom of the arc-shaped groove under the action of the positioning spring. The positioning rod and the arc-shaped groove cooperate to facilitate the positioning of the unfolding degree of the solar panel and the connecting frame. When the solar panel and the connecting frame need to be folded up and stacked, the end face of the positioning rod moves along the inclined bottom of the arc-shaped groove, which makes it easy to retract the end of the positioning rod into the connecting hole, thereby making the unfolding and folding effect of the solar panel better.

[0022] Optionally, a recessed groove is provided on the outer wall of the connecting sleeve. When the connecting spring is in a compressed state, the recessed groove is inserted into the end of the positioning rod away from the arc-shaped groove.

[0023] By adopting the above technical solution, the recessed groove cooperates with the other end of the positioning rod to restrict the position of the connecting sleeve, so that the connecting sleeve and the first connecting post are separated from each other. When the solar panel is deployed, the end of the positioning rod away from the connecting sleeve will be inserted into the bottom of the arc-shaped groove under the action of the positioning spring, and at the same time, the other end of the positioning rod will be separated from the connecting sleeve, so that the connecting sleeve can be sleeved on the outside of the first connecting post under the action of the connecting spring, thereby making the entire structure of the solar panel more stable after deployment.

[0024] Optionally, the end face of the limiting block is an inclined surface that faces away from the satellite body.

[0025] By adopting the above technical solution, during the process of folding and stacking the solar panels, the end face of the solar panels will abut against the inclined surface of the limiting block so that the end of the limiting block retracts into the sliding groove; when the limiting block is aligned with the limiting groove, the limiting block will be inserted into the limiting groove under the action of the limiting spring, thus making the operation of folding and stacking the solar panels in the storage frame simpler.

[0026] In summary, this application includes at least the following beneficial technical effects:

[0027] 1. By combining the storage frame and the limiting component, multiple solar panels can be stacked and abutted against the side of the satellite body. This reduces the risk of damage to the solar panels during the satellite's radiation and orbital operation. When the satellite body is in operation, the limiting component releases the restriction on the solar panels, and the deployment component applies rotational thrust to the connecting frame and solar panels, facilitating the deployment of multiple solar panels on both sides of the satellite body. This improves the safety of satellite flight, and the mechanism is simple and reliable.

[0028] 2. When the solar panel is deployed, the locking ring is engaged with the retracting rope. The retracting rope pulls the unlocking block, causing the linkage block to move towards the satellite body along with the locking ring, thereby separating the connecting sleeve from the first connecting post. When the solar panel and connecting frame rotate, the connecting sleeve and locking ring will move away from each other as the solar panel and connecting frame rotate, and the opening facilitates the retracting rope to move out from inside the locking ring. This ensures that the presence of the locking ring does not affect the tension applied by the retracting rope to the rotation of the solar panel, making it easier for the solar panel to be stacked and abutted against both sides of the satellite body. Attached Figure Description

[0029] Figure 1 This is a schematic diagram of the structure of a satellite solar panel deployment and locking mechanism according to an embodiment of this application;

[0030] Figure 2 yes Figure 1 Enlarged view of section A;

[0031] Figure 3 This is a partial connection diagram of an embodiment of this application, mainly used for connecting the connecting frame, the solar panel, and the storage assembly;

[0032] Figure 4 This is a partial structural cross-sectional view of an embodiment of this application, mainly used as a connection diagram of the storage frame and the limiting component;

[0033] Figure 5 yes Figure 3 Enlarged view of section B;

[0034] Figure 6This is a partial connection diagram of an embodiment of this application, mainly used as a connection diagram of the unfolding component, the positioning rod, and the arc-shaped groove;

[0035] Figure 7 This is a partial structural cross-sectional view of an embodiment of this application, mainly used as a connection diagram of the unfolding component, positioning rod, and arc groove.

[0036] Explanation of reference numerals in the attached drawings: 1. Satellite body; 2. Storage frame; 3. Connecting frame; 4. Solar panel; 41. Fixing frame; 42. Solar panel; 5. Deployment assembly; 51. First connector; 52. Second connector; 53. Rotating shaft; 54. Elastic element; 6. Restriction assembly; 61. Restriction block; 62. Restriction groove; 63. Sliding groove; 64. Restriction spring; 7. Electromagnet; 8. First connecting post; 9. Second connecting post; 10. Connecting sleeve; 11. Connecting spring; 12. Storage assembly; 121. Driving element; 122. Winding reel; 123. Retracting rope; 13. Unlocking groove; 14. Unlocking block; 15. Unlocking spring; 16. Linkage assembly; 161. Linkage block; 162. Snap-fit ​​ring; 163. Opening; 17. Connecting hole; 18. Positioning rod; 19. Arc groove; 20. Positioning spring; 21. Recessed groove. Detailed Implementation

[0037] To make the purpose, technical solution, and advantages of this application clearer, the following description is provided in conjunction with the appendix. Figure 1-7 The present application will be further described in detail below with reference to embodiments. It should be understood that the specific embodiments described herein are for illustrative purposes only and are not intended to limit the scope of the application.

[0038] This application discloses a satellite solar panel deployment and locking mechanism. (Refer to...) Figure 1 The mechanism includes a satellite body 1, with connecting frames 3 and multiple solar panels 4 mounted on opposite sides of the satellite body 1. The two ends of the connecting frames 3 are respectively hinged to the side of the satellite body 1 and the end of the solar panel 4. The solar panel 4 is the one closer to the side of the satellite body 1; adjacent solar panels 4 are also hinged to each other.

[0039] In this embodiment, the solar panel 4 on one side of the satellite body 1 consists of three parts: an inner wing panel, a middle wing panel, and an outer wing panel. One end of the connecting frame 3 is hinged to one end of the inner wing panel, the end of the inner wing panel away from the connecting frame 3 is hinged to one end of the middle wing panel, and the end of the middle wing panel away from the inner wing panel is hinged to one end of the outer wing panel. The width of the connecting frame 3 is half the width of the solar panel 4, and the end of the connecting frame 3 away from the inner wing panel is hinged to the middle of the side of the satellite body 1.

[0040] Reference Figure 2 and Figure 3To accommodate and stack the solar panel 4 and connecting frame 3 on both sides of the satellite body 1, a storage assembly 12 is installed on one side of the satellite body 1. The storage assembly 12 includes a drive component 121, a winding reel 122, and a winding rope 123. The drive component 121 is fixed inside the satellite body 1 to drive the winding reel 122 to rotate. One end of the winding rope 123 is wound around the winding reel 122, and the other end of the winding rope 123 is fixedly connected to the side of the outer wing panel. The drive component 121 is a drive motor, which is embedded inside the satellite body 1. The output shaft of the drive motor is keyed to the central shaft of the winding reel 122. In addition, there are two sets of storage assemblies 12 on one side of the satellite body 1, that is, two winding ropes 123 are located on both sides of the solar panel 4.

[0041] In this embodiment, by starting the drive motor to drive the winding wheel 122 to rotate, the coiling rope 123 can be wound around the winding wheel 122, which makes it easier to pull the solar panel 4 away from the satellite body 1 toward the satellite body 1. This applies a rotational pulling force to the connecting frame 3 and the solar panel 4, making it easier for multiple solar panels 4 to be stacked and abutted on both sides of the satellite body 1, thus achieving the effect of coiling the solar panel 4.

[0042] Reference Figure 2 and Figure 3 An unlocking groove 13 is provided on the side of the solar panel 4, and the unlocking groove 13 is set along the width direction of the solar panel 4. An unlocking block 14 is slidably connected in the unlocking groove 13, and the other end of the coiling rope 123 is fixedly connected to the unlocking block 14. An unlocking spring 15 is provided in the unlocking groove 13. The unlocking spring 15 is located on the side of the unlocking block 14 closer to the satellite body 1, and one end of the unlocking spring 15 is fixedly connected to the groove wall of the unlocking groove 13, and the other end of the unlocking spring 15 is fixedly connected to the unlocking block 14. Through the cooperation of the unlocking block 14 and the unlocking groove 13, the coiling rope 123 can move along the width direction of the solar panel 4; that is, when the winding wheel 122 winds the coiling rope 123, it will pull the coiling rope 123 to move a distance, and then the pulling of the coiling rope 123 will cause the connecting frame 3 and the solar panel 4 to rotate.

[0043] Reference Figure 1 and Figure 4To ensure a more stable stacking of the solar panels 4 and connecting frame 3, storage frames 2 are fixed to opposite sides of the satellite body 1. Restriction components 6 are installed on the storage frames 2 to restrict the outer solar panels, allowing multiple solar panels 4 to be stacked sequentially. The storage frame 2 consists of two flat plates, both welded to the sides of the satellite body 1. The distance between the two plates is the same as the width of the solar panels 4. When the solar panels 4 are stacked, the two flat plates rest against the end faces of the solar panels 4. The storage frame 2 and restriction components 6 restrict the horizontal and vertical movement of the solar panels 4, thereby reducing the risk of damage.

[0044] Reference Figure 1 and Figure 4 The limiting component 6 includes a limiting block 61 and a limiting groove 62. A sliding groove 63 is provided on the side wall of the storage frame 2, and the limiting block 61 is slidably connected within the sliding groove 63. The limiting groove 62 is located on the end face of the outer wing plate, and the end of the limiting block 61 is inserted into the limiting groove 62. A limiting spring 64 is installed within the sliding groove 63, with one end fixedly connected to the bottom of the groove and the other end fixedly connected to the limiting block 61. An electromagnet 7 is installed on the storage frame 2. The electromagnet 7 is fixed to the bottom of the sliding groove 63 by welding. The portion of the limiting block 61 located within the sliding groove 63 is made of iron. When the electromagnet 7 is energized, it applies a pulling force to the limiting block 61, causing it to retract into the sliding groove 63.

[0045] In this embodiment, the coiling rope 123 pulls the solar panel 4, causing the connecting frame 3 and the solar panel 4 to rotate and stack on one side of the satellite body 1. When the limiting block 61 is aligned with the limiting groove 62, the end of the limiting block 61 will be inserted into the limiting groove 62 under the action of the limiting spring 64, so that multiple solar panels 4 can be stacked and abutted against the side of the satellite body 1, that is, the solar panels 4 can be stored in the storage frame 2, which is convenient for protecting the solar panels 4. Through the cooperation of the electromagnet 7 with the limiting block 61, the limiting block 61 can be attracted so that the end of the limiting block 61 is retracted into the sliding groove 63, which is convenient for the connecting frame 3 and the solar panel 4 to rotate and unfold.

[0046] Reference Figure 1 and Figure 4 To simplify the stacking operation of the solar panels 4, the end face of the limiting block 61 is an inclined surface facing away from the satellite body 1. During the process of folding and stacking the solar panels 4, the end face of the solar panels 4 will abut against the inclined surface of the limiting block 61 so that the end of the limiting block 61 retracts into the sliding groove 63; when the limiting block 61 is aligned with the limiting groove 62, the limiting block 61 will be inserted into the limiting groove 62 under the action of the limiting spring 64, thereby simplifying the operation of folding and stacking the solar panels 4 in the storage frame 2.

[0047] Reference Figure 3 and Figure 5 Deployment components 5 are installed between the connecting frame 3 and the satellite body 1, between the connecting frame 3 and the solar panels 4, and between adjacent solar panels 4. The deployment components 5 are used to apply rotational thrust to the connecting frame 3 and the solar panels 4. When the satellite body 1 needs to operate, the rotational thrust applied to the connecting frame 3 and the solar panels 4 by the deployment components 5 facilitates the deployment of multiple solar panels 4 on both sides of the satellite body 1, improving the safety of satellite flight.

[0048] Reference Figure 5 and Figure 6 The deployment assembly 5 includes a first connector 51, a second connector 52, a rotating shaft 53, and an elastic element 54. The first connector 51 and the second connector 52 are rotatably connected to the rotating shaft 53. One side of the first connector 51 is fixedly connected to the satellite body 1, the connecting frame 3, or the solar panel 4, and one side of the second connector 52 is fixedly connected to the connecting frame 3 or the solar panel 4. The elastic element 54 is sleeved on the rotating shaft 53, with one end of the elastic element 54 fixedly connected to the first connector 51 and the other end of the elastic element 54 fixedly connected to the second connector 52. The elastic element 54 is a deployment spring, which can rotate on the rotating shaft 53 via the first connector 51 and the second connector 52, causing the connecting frame 3 and the solar panel 4 to rotate and deploy under the action of the deployment spring.

[0049] Reference Figure 5 and Figure 6 The solar panel 4 includes a fixing frame 41 and a solar panel 42, with the solar panel 42 fixed inside the fixing frame 41. A first connecting post 8 is fixedly connected to one end of the fixing frame 41 near the satellite body 1, and a second connecting post 9 is fixedly connected to the other end of the fixing frame 41. A connecting sleeve 10, which is inserted into the first connecting post 8, is sleeved on the second connecting post 9. A connecting spring 11 is fitted onto the second connecting post 9, with one end fixedly connected to the second connecting post 9 and the other end fixedly connected to the connecting sleeve 10. After the multiple solar panels 4 are rotated and deployed, the connecting sleeve 10 will be inserted into the outside of the first connecting post 8 under the action of the connecting spring 11. The cooperation of the first connecting post 8, the second connecting post 9, and the connecting sleeve 10 will make the connection between the connecting frame 3 and the solar panel 4, as well as between adjacent solar panels 4, more stable, thereby improving the safety of satellite flight.

[0050] Reference Figure 5 and Figure 6The retracting rope 123 is equipped with a linkage assembly 16 for pulling the connecting sleeve 10 and the first connecting post 8 apart. The linkage assembly 16 includes a linkage block 161 and a locking ring 162. The linkage block 161 is fixedly connected to the retracting rope 123, and the locking ring 162 is fixedly connected to the outer wall of the connecting sleeve 10. The linkage block 161 abuts against the side of the locking ring 162 away from the satellite body 1. The locking ring 162 has an opening 163 for the retracting rope 123 to move out. When multiple solar panels 4 are stacked and abutted, the opening 163 of the locking ring 162 faces the retracting rope 123.

[0051] In this embodiment, when the solar panel 4 is deployed, the locking ring 162 is sleeved on the outside of the retracting rope 123. The retracting rope 123 pulls the unlocking block 14 to move, causing the linkage block 161 to move towards the satellite body 1 together with the locking ring 162, thereby achieving the purpose of separating the connecting sleeve 10 from the first connecting post 8. When the solar panel 4 and the connecting frame 3 rotate, the connecting sleeve 10 and the locking ring 162 will move away from each other as the solar panel 4 and the connecting frame 3 rotate. The opening 163 facilitates the retracting rope 123 to move out from inside the locking ring 162, so that the presence of the locking ring 162 will not affect the pulling force applied by the retracting rope 123 to the rotation of the solar panel 4, making it easier for the solar panel 4 to be better stacked and abutted against both sides of the satellite body 1.

[0052] Reference Figure 5 and Figure 7 The first connector 51 has a connecting hole 17 at one end, and a positioning rod 18 is slidably connected in the connecting hole 17. The second connector 52 has an arc-shaped groove 19 with the same center as the rotating shaft 53 on the end face facing the first connector 51. The arc-shaped groove 19 is inserted and matched with the end of the positioning rod 18, and the groove depth of the arc-shaped groove 19 gradually decreases. A positioning spring 20 is sleeved on the positioning rod 18. One end of the positioning spring 20 is fixedly connected to the hole wall of the connecting hole 17, and the other end of the positioning spring 20 is fixedly connected to the positioning rod 18.

[0053] In this embodiment, the first connector 51 and the second connector 52 rotate relative to each other on the rotating shaft 53 to achieve the purpose of rotating and unfolding the solar panel 4 and the connecting frame 3. After the solar panel 4 and the connecting frame 3 are unfolded, the end of the positioning rod 18 will be inserted into the bottom of the arc-shaped groove 19 under the action of the positioning spring 20. The positioning rod 18 and the arc-shaped groove 19 cooperate to facilitate the positioning of the unfolding degree of the solar panel 4 and the connecting frame 3. When the solar panel 4 and the connecting frame 3 need to be folded up and stacked, the end face of the positioning rod 18 moves along the inclined bottom of the arc-shaped groove 19 to facilitate the retraction of the end of the positioning rod 18 into the connecting hole 17, thereby making the unfolding and folding effect of the solar panel 4 better.

[0054] Reference Figure 5 and Figure 7A recessed groove 21 is provided on the outer wall of the connecting sleeve 10. When the connecting spring 11 is compressed, the recessed groove 21 engages with the end of the positioning rod 18 away from the arc-shaped groove 19. The recessed groove 21 can be a long groove, arranged along the length of the connecting sleeve 10, to facilitate better insertion of the other end of the positioning rod 18 into the recessed groove 21. The engagement of the recessed groove 21 with the other end of the positioning rod 18 restricts the position of the connecting sleeve 10, separating it from the first connecting post 8. When the solar panel 4 unfolds, the end of the positioning rod 18 away from the connecting sleeve 10 is inserted into the bottom of the arc-shaped groove 19 under the action of the positioning spring 20, simultaneously separating the other end of the positioning rod 18 from the connecting sleeve 10. This allows the connecting sleeve 10 to be fitted onto the first connecting post 8 under the action of the connecting spring 11, thus making the entire structure of the solar panel 4 more stable after unfolding.

[0055] The implementation principle of a satellite solar panel deployment and locking mechanism according to an embodiment of this application is as follows: When the satellite body 1 needs to work, the electromagnet 7 is energized, which facilitates the electromagnet 7 to attract the limiting block 61 so that the end of the limiting block 61 retracts into the sliding groove 63. Under the action of the deployment spring, a rotational thrust is applied to the solar panel 4 and the connecting frame 3 so that the solar panel 4 has a tendency to deploy; with the cooperation of the first joint 51, the second joint 52 and the rotating shaft 53, the deployment of the solar panel 4 is completed. After the multiple solar panels 4 are deployed, the end of the positioning rod 18 will be inserted into the bottom of the arc-shaped groove 19 under the action of the positioning spring 20. The positioning rod 18 and the arc-shaped groove 19 cooperate to facilitate the positioning of the solar panels 4 and the connecting frame 3 at the deployment degree. At the same time, the first connecting post 8 and the second connecting post 9 will be aligned. The connecting sleeve 10 will be sleeved on the outside of the first connecting post 8 under the action of the connecting spring 11. The cooperation of the first connecting post 8, the second connecting post 9 and the connecting sleeve 10 will make the connection between the connecting frame 3 and the solar panels 4 and between adjacent solar panels 4 more stable, thereby improving the safety of satellite flight.

[0056] When the satellite body 1 is in the process of radiation and orbital operation, the drive motor is started to drive the winding wheel 122 to rotate, so that the winding rope 123 can be wound around the winding wheel 122. When the winding wheel 122 winds the winding rope 123, it will pull the winding rope 123 to move one end, which will cause the linkage block 161 to move towards the satellite body 1 together with the locking ring 162, thereby achieving the purpose of separating the connecting sleeve 10 from the first connecting post 8. Then, the pulling of the winding rope 123 will cause the connecting frame 3 and the solar panel 4 to rotate. The connecting sleeve 10 and the locking ring 162 will move away from each other as the solar panel 4 and the connecting frame 3 rotate, and the opening 163 will facilitate the winding rope 123 to move out of the locking ring 162. Simultaneously, the end face of the positioning rod 18 moves along the inclined bottom of the arc-shaped groove 19, so that the end of the positioning rod 18 retracts into the connecting hole 17; while the other end of the positioning rod 18 will be inserted into the recessed groove 21, which will restrict the position of the connecting sleeve 10, so that the connecting sleeve 10 and the first connecting post 8 remain separated. After the retracting rope 123 pulls the solar panel 4 to retract, when the limiting block 61 is aligned with the limiting groove 62, the limiting block 61 will be inserted into the limiting groove 62 under the action of the limiting spring 64, so as to achieve the purpose of retracting and stacking the solar panel 4 in the storage frame 2.

[0057] The above are all preferred embodiments of this application and are not intended to limit the scope of protection of this application. Any feature disclosed in this specification (including the abstract and drawings) may be replaced by other equivalent or similar features unless specifically stated otherwise. Therefore, all equivalent changes made to the structure, shape, and principle of this application should be covered within the scope of protection of this application.

Claims

1. A satellite solar array deployment and locking mechanism, characterized in that, The system includes a storage frame (2), a connecting frame (3), and multiple solar panels (4) located on opposite sides of the satellite body (1). The two ends of the connecting frame (3) are respectively hinged to the side of the satellite body (1) and the end of the solar panel (4) near the satellite body (1). Two adjacent solar panels (4) are hinged to each other. Deployment components (5) for applying rotational thrust to the connecting frame (3) and the solar panel (4) are provided between the connecting frame (3) and the satellite body (1), between the connecting frame (3) and the solar panel (4), and between adjacent solar panels (4). The storage frame (2) is provided with a limiting component (6) for restricting the solar panels (4) away from the satellite body (1) so that multiple solar panels (4) are stacked in sequence. The solar panel (4) includes a fixed frame (41) and a solar panel (42). The solar panel (42) is fixed inside the fixed frame (41). A first connecting post (8) is fixedly connected to one end of the fixed frame (41) near the satellite body (1), and a second connecting post (9) is fixedly connected to the other end of the fixed frame (41). A connecting sleeve (10) that is inserted into the first connecting post (8) is sleeved on the second connecting post (9). A connecting spring (11) is sleeved on the second connecting post (9). One end of the connecting spring (11) is fixedly connected to the second connecting post (9), and the other end of the connecting spring (11) is fixedly connected to the connecting sleeve (10). A storage assembly (12) is provided on one side of the satellite body (1). The storage assembly (12) includes a drive (121), a winding wheel (122), and a winding rope (123). The drive (121) is fixed inside the satellite body (1) to drive the winding wheel (122) to rotate. One end of the winding rope (123) is wound around the winding wheel (122), and the other end of the winding rope (123) is fixedly connected to the side of the solar panel (4) away from the satellite body (1). The side of the solar panel (4) is provided with an unlocking groove (13) along the width direction of the solar panel (4). An unlocking block (14) is slidably connected in the unlocking groove (13). The other end of the coiling rope (123) is fixedly connected to the unlocking block (14). An unlocking spring (15) is provided in the unlocking groove (13). The unlocking spring (15) is located on the side of the unlocking block (14) close to the satellite body (1). One end of the unlocking spring (15) is fixedly connected to the groove wall of the unlocking groove (13), and the other end of the unlocking spring (15) is fixedly connected to the unlocking block (14). A linkage component (16) for pulling the connecting sleeve (10) and the first connecting post (8) to separate from each other is provided on the coiling rope (123).

2. The satellite solar array deployment and locking mechanism according to claim 1, characterized in that, The deployment assembly (5) includes a first connector (51), a second connector (52), a rotating shaft (53), and an elastic element (54). The first connector (51) and the second connector (52) are rotatably connected to the rotating shaft (53). One side of the first connector (51) is fixedly connected to the satellite body (1), the connecting frame (3), or the solar panel (4). One side of the second connector (52) is fixedly connected to the connecting frame (3) or the solar panel (4). The elastic element (54) is sleeved on the rotating shaft (53). One end of the elastic element (54) is fixedly connected to the first connector (51), and the other end of the elastic element (54) is fixedly connected to the second connector (52).

3. The satellite solar array deployment and locking mechanism according to claim 1, characterized in that, The limiting component (6) includes a limiting block (61) and a limiting groove (62). The side wall of the storage frame (2) is provided with a sliding groove (63). The limiting block (61) is slidably connected in the sliding groove (63). The limiting groove (62) is opened on the side of the solar panel (4) away from the satellite body (1). The end of the limiting block (61) is inserted into the limiting groove (62). A limiting spring (64) is provided in the sliding groove (63). One end of the limiting spring (64) is fixedly connected to the bottom of the sliding groove (63). The other end of the limiting spring (64) is fixedly connected to the limiting block (61). An electromagnet (7) is provided on the storage frame (2) to drive the limiting block (61) to retract into the sliding groove (63).

4. A satellite solar panel deployment and locking mechanism according to claim 1, characterized in that, The linkage component (16) includes a linkage block (161) and a snap ring (162). The linkage block (161) is fixedly connected to the coiling rope (123), and the snap ring (162) is fixedly connected to the outer wall of the connecting sleeve (10). The linkage block (161) abuts against the snap ring (162) on the side away from the satellite body (1). The snap ring (162) has an opening (163) for the coiling rope (123) to move out. When multiple solar panels (4) are stacked and abutted, the opening (163) of the snap ring (162) faces the coiling rope (123).

5. A satellite solar array deployment and locking mechanism according to claim 2, characterized in that, One end of the first connector (51) is provided with a connecting hole (17), and a positioning rod (18) is slidably connected in the connecting hole (17). The end face of the second connector (52) facing the first connector (51) is provided with an arc-shaped groove (19) concentric with the rotating shaft (53). The arc-shaped groove (19) is inserted into the end of the positioning rod (18), and the groove depth of the arc-shaped groove (19) gradually decreases. A positioning spring (20) is sleeved on the positioning rod (18). One end of the positioning spring (20) is fixedly connected to the wall of the connecting hole (17), and the other end of the positioning spring (20) is fixedly connected to the positioning rod (18).

6. A satellite solar array deployment and locking mechanism according to claim 5, characterized in that, A recessed groove (21) is provided on the outer wall of the connecting sleeve (10). When the connecting spring (11) is in a compressed state, the recessed groove (21) is inserted into the end of the positioning rod (18) away from the arc groove (19).

7. A satellite solar array deployment and locking mechanism according to claim 3, characterized in that, The end face of the limiting block (61) is an inclined surface that is away from the satellite body (1).

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