Opening and closing mechanism of solar wing plate and satellite

Abstract

The utility model provides an opening and closing mechanism of a solar wing plate and a satellite, the solar wing plate rotates on a satellite body in a first direction through the opening and closing mechanism and is locked at an unfolding position, the opening and closing mechanism comprises a seat body, an elastic piece and a locking piece, the solar wing plate is hinged to the satellite body through the seat body, the locking piece is movably arranged on the seat body, and the elastic piece is arranged on the locking piece. The elastic piece is connected with the locking piece and used for driving the locking piece to move to the reverse side of the first direction of the solar wing plate after the solar wing plate is located at the unfolding position so as to limit the solar wing plate. Through the arrangement of the seat body, the elastic piece and the locking piece, the elastic piece can drive the locking piece to move to the reverse side of the first direction of the solar wing plate, limiting is formed in the reverse direction of the first direction, and the solar wing plate can be automatically locked to the unfolding position. The opening and closing mechanism is simple in structure, use of electronic devices is reduced, the risk that locking cannot be achieved due to faults of the electronic devices is reduced, and the reliability is higher in the severe space environment.

Description

Technical Field

[0001] The present application belongs to the field of aerospace equipment technology, and specifically relates to an opening and closing mechanism of a solar wing panel and a satellite. Background Art

[0002] Satellites usually obtain electricity through solar panels. During the satellite launch process, the solar panels are usually in a folded state to save space. After the satellite enters the predetermined orbit, the solar panels are usually unfolded and locked in the unfolded position through an opening and closing mechanism. Therefore, the reliability of the opening and closing mechanism of the solar panels is crucial.

[0003] In existing opening and closing mechanisms, after the solar panels are deployed, a small motor typically drives a latch to lock the panels. Specifically, when the solar panels are fully deployed, a position switch is triggered. A control chip, based on the signal from the position switch, activates the small motor, which in turn drives the latch into the corresponding socket on the solar panel, locking the panels in the deployed position. However, this opening and closing mechanism is complex, and the electronic components are susceptible to damage in the harsh space environment, making it difficult to lock the panels. Utility Model Content

[0004] Therefore, the technical problem to be solved by the present application is to provide an opening and closing mechanism and satellite of a solar wing panel, which can stably and reliably rotate and lock the solar wing panel in the unfolded position.

[0005] In order to solve the above problems, the first aspect of the present application provides an opening and closing mechanism for a solar wing panel, wherein the solar wing panel is rotated along a first direction on the satellite body through the opening and closing mechanism and locked in the expanded position, the opening and closing mechanism includes a seat body, an elastic member and a locking member, the solar wing panel is hinged to the satellite body through the seat body, the locking member is movably arranged on the seat body, the elastic member is connected to the locking member, and is used to drive the locking member to move to the opposite side of the first direction of the solar wing panel after the solar wing panel is in the expanded position, so as to limit the solar wing panel.

[0006] The opening and closing mechanism of the present invention has good rigidity and strength. Moreover, while maintaining good rigidity and strength, the volume of the opening and closing mechanism is reduced, the space occupied is reduced, and less material is used, thereby reducing the overall weight.

[0007] The opening and closing mechanism in the present application has a simple structure, reduces the use of electronic devices, reduces the risk of locking failure due to electronic device failure, and has higher reliability in harsh space environments.

[0008] Optionally, the opening and closing mechanism is made of AL6061.

[0009] AL6061 is 6061 aluminum alloy. The opening and closing mechanism is made of AL6061, which can make the opening and closing mechanism lighter and reduce launch costs.

[0010] The seat body includes a first mounting seat, which is connected to the satellite body. The elastic member is arranged on the first mounting seat. The opening and closing mechanism also includes a connecting rod, which is respectively connected to the elastic member and the locking member. The elastic member drives the locking member to move through the connecting rod.

[0011] Optionally, a mounting hole is provided on the first mounting seat, the elastic member is provided in the mounting hole, the first end of the elastic member is fixed to the first mounting seat, the second end is sleeved on the connecting rod and abuts against the abutment boss on the connecting rod, and the end of the connecting rod away from the elastic member extends out of the mounting hole and is connected to the locking member.

[0012] Optionally, a locking member is inserted into the end of the mounting hole away from the locking member, and the locking member is connected to the end of the elastic member away from the connecting rod, so that the elastic member is in a compressed state before the opening and closing mechanism locks the solar wing panel in the expanded position, and the locking member is threadedly connected to the hole wall of the mounting hole.

[0013] Optionally, the locking member is hinged on the first mounting seat, and the connecting rod is hinged to the locking member to drive the connecting rod to rotate on the first mounting seat.

[0014] Optionally, the opening and closing mechanism further includes a first rotating shaft and a connecting plate, the first rotating shaft is connected to the first mounting seat via the connecting plate, and the locking member is rotatably disposed on the first rotating shaft.

[0015] Optionally, the locking member is eccentrically arranged on the first rotating shaft, and the protrusion of the locking member is hinged to the connecting rod.

[0016] Optionally, the seat body includes a second mounting seat, the second mounting seat is connected to the solar wing panel, a mounting groove is provided on the first mounting seat, a second rotating shaft is provided in the mounting groove, and the second mounting seat is rotatably connected to the second rotating shaft; before the solar wing panel rotates to the unfolded position, the elastic member abuts the locking member on the second mounting seat through the connecting rod, and after the solar wing panel is in the unfolded position, the elastic member drives the locking member to move to the opposite side of the first direction of the second mounting seat through the connecting rod, and abuts against the second mounting seat.

[0017] Optionally, the second mounting seat includes a sleeve and a connecting member, the sleeve is rotatably sleeved on the second rotating shaft, and the connecting member is connected to the solar wing panel.

[0018] In a second aspect of the present application, a satellite is provided, comprising the above-mentioned opening and closing mechanism of the solar wing panel.

[0019] Beneficial effects

[0020] The embodiments of the present invention provide a solar wing panel opening and closing mechanism and satellite. By providing a bracket, an elastic member, and a locking member, when the solar wing panel is rotated to the deployed position by the opening and closing mechanism, the elastic member drives the locking member to the side opposite the first direction of the solar wing panel, thereby limiting the solar wing panel in the direction opposite to the first direction and automatically locking the solar wing panel in the deployed position. The opening and closing mechanism has a simple structure, reduces the use of electronic components, and reduces the risk of locking failure due to electronic component failure, thereby enhancing reliability in the harsh space environment. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 This is a first structural schematic diagram of the opening and closing mechanism of an embodiment of the present application;

[0022] Figure 2 This is a second structural schematic diagram of the opening and closing mechanism of an embodiment of the present application;

[0023] Figure 3 This is a third structural schematic diagram of the opening and closing mechanism of an embodiment of the present application;

[0024] Figure 4 This is a schematic structural diagram of the opening and closing mechanism of the embodiment of the present application excluding the first rotating shaft and the connecting plate;

[0025] Figure 5 This is a schematic structural diagram of a locking member according to an embodiment of the present application;

[0026] Figure 6 This is a schematic structural diagram of a first mounting base according to an embodiment of the present application;

[0027] Figure 7 This is a schematic structural diagram of the second mounting base of an embodiment of the present application.

[0028] The reference numerals indicate:

[0029] 1. First mounting seat; 11. Second rotating shaft;

[0030] 2. Second mounting seat; 21. Socket; 22. Connector;

[0031] 31. Elastic member; 32. Locking member; 33. Connecting rod; 331. Abutting boss; 34. Locking member; 35. First rotating shaft; 36. Connecting plate. DETAILED DESCRIPTION

[0032] In the description of this application, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise" and the like to indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as a limitation on the present invention.

[0033] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of the technical features being referred to. Thus, a feature specified as "first" or "second" may explicitly or implicitly include one or more of such features. In the description of this utility model, "plurality" means two or more, unless otherwise specifically defined.

[0034] In this application, unless otherwise specified or limited, the terms "installed," "connected," "connect," "fixed," etc. should be understood in a broad sense. For example, they can refer to fixed connection, detachable connection, or integral connection; mechanical connection or electrical connection; direct connection or indirect connection through an intermediate medium; or internal communication between two components. Those skilled in the art will understand the specific meanings of the above terms in this utility model based on specific circumstances.

[0035] The preferred embodiments of the present invention are described below in conjunction with the accompanying drawings. It should be understood that the preferred embodiments described herein are only used to illustrate and explain the present invention and are not used to limit the present invention.

[0036] See also Figures 1 to 7 As shown, according to the first aspect of the embodiment of the present application, an opening and closing mechanism of a solar wing panel is provided, and the solar wing panel is rotated along a first direction on the satellite body through the opening and closing mechanism and locked in the expanded position, the opening and closing mechanism includes a seat body, an elastic member 31 and a locking member 32, the solar wing panel is hinged to the satellite body through the seat body, the locking member 32 is movably arranged on the seat body, and the elastic member 31 is connected to the locking member 32, and is used to drive the locking member 32 to move to the opposite side of the first direction of the solar wing panel after the solar wing panel is in the expanded position, so as to limit the solar wing panel.

[0037] By providing a bracket, elastic member 31, and locking member 32, when the solar wing panel is rotated to the deployed position via the opening and closing mechanism, the elastic member 31 drives the locking member 32 to the side opposite the first direction of the solar wing panel, thereby limiting the solar wing panel in the direction opposite to the first direction and automatically locking the solar wing panel in the deployed position. The simple opening and closing mechanism reduces the use of electronic components and the risk of locking failure due to electronic failure, providing higher reliability in the harsh space environment.

[0038] The opening and closing mechanism in this embodiment has good rigidity and strength. Moreover, while maintaining good rigidity and strength, the volume of the opening and closing mechanism is reduced, which reduces the space occupied, and the material used is also less, which reduces the overall weight.

[0039] The solar panels are folded during satellite launch. After the satellite enters orbit, they unfold in a first direction. Specifically, the first direction is the direction in which the solar panels rotate and unfold on the satellite body, and the direction opposite to the first direction is the direction of rotation from the unfolded position back to the folded position. Once the solar panels are in the unfolded position, the elastic member 31 drives the locking member 32 to move to the side opposite to the first direction, thereby limiting the solar panels on the side opposite to the first direction and locking them in the unfolded position.

[0040] Among them, after the solar wing panel is in the unfolded position, the locking member 32 is driven to move to the opposite side of the first direction of the solar wing panel, so that the locking member 32 can abut against the solar wing panel or the part of the seat body that is hinged to the solar wing panel, thereby locking the solar wing panel in the unfolded position.

[0041] Specifically, in this embodiment, after the solar wing panel is in the unfolded position, the locking member 32 abuts against the portion of the seat body hinged to the solar wing panel, thereby locking the solar wing panel in the unfolded position.

[0042] More specifically, in this embodiment, the seat body includes a first mounting seat 1 and a second mounting seat 2, the first mounting seat 1 is connected to the satellite body, the solar wing panel is connected to the second mounting seat 2, the first mounting seat 1 and the second mounting seat 2 are hinged, so that the solar wing panel can be rotated and unfolded on the satellite body, after the solar wing panel is in the unfolded position, the locking member 32 is on the opposite side of the first direction of the second mounting seat 2, and the locking member 32 is in contact with the second mounting seat 2, thereby locking the solar wing panel in the unfolded position.

[0043] The deployed position is the extreme position of the solar wing panel rotating along the first direction on the satellite body.

[0044] The opening and closing mechanism is made of AL6061, which can make the opening and closing mechanism lighter and reduce launch costs.

[0045] Among them, AL6061 is 6061 aluminum alloy.

[0046] The elastic member 31 is arranged on the first mounting seat 1 . The opening and closing mechanism further includes a connecting rod 33 . The connecting rod 33 is connected to the elastic member 31 and the locking member 32 respectively. The elastic member 31 drives the locking member 32 to move through the connecting rod 33 .

[0047] By connecting the connecting rod 33 to the elastic member 31 and the locking member 32, the elastic member 31 drives the locking member 32 more directly and stably. The elastic force of the elastic member 31 can be more effectively transmitted to the locking member 32, ensuring the accurate movement of the locking member 32 during the deployment of the solar wing panels and improving the reliability of the locking action.

[0048] The first mounting seat 1 is fixedly connected to the outer wall of the satellite body.

[0049] Specifically, a plurality of through holes are provided on the first mounting seat 1 , and the first mounting seat 1 is fixedly connected to the threaded holes on the outer wall of the satellite body by bolts.

[0050] The connecting rod 33 is a long straight rod, thereby stably transmitting the elastic force.

[0051] Specifically, the direction of the elastic force is the same as the extending direction of the connecting rod 33 .

[0052] A mounting hole is provided on the first mounting seat 1, and the elastic member 31 is provided in the mounting hole. The first end of the elastic member 31 is fixed to the first mounting seat 1, and the second end is sleeved on the connecting rod 33 and abuts against the abutting boss 331 on the connecting rod 33. The end of the connecting rod 33 away from the elastic member 31 extends out of the mounting hole and is connected to the locking member 32.

[0053] By arranging the elastic member 31 in the mounting hole of the first mounting seat 1 and fixing its first end to the first mounting seat 1, a stable mounting base is provided for the elastic member 31, so that the second end of the elastic member 31 is sleeved on the connecting rod 33, so that it is not easy to be displaced or shaken during operation. The second end of the elastic member 31 abuts against the abutting boss 331, ensuring that the elastic member 31 can accurately transmit force to the connecting rod 33 during the extension and retraction process, thereby ensuring the accuracy and reliability of the locking action.

[0054] The mounting hole is a straight hole, the elastic member 31 is a spring, and the diameter of the mounting hole is slightly larger than the outer diameter of the elastic member 31 .

[0055] The elastic member 31 and the connecting rod 33 are both arranged along the axial direction of the mounting hole.

[0056] The middle portion of the connecting rod 33 protrudes radially outward to form a platform, forming an abutment boss 331. The second end is sleeved on the connecting rod 33 and abuts against the wall surface of the abutment boss 331 on the side close to the elastic member 31. Since the first end of the elastic member 31 is fixed to the first mounting seat 1 and the second end abuts against the abutment boss 331, the elastic member 31 can apply an elastic force on the abutment boss 331 toward the locking member 32, and also apply an elastic force on the connecting rod 33 toward the locking member 32, thereby pushing a portion of the locking member 32 to the side opposite to the first direction of the second mounting seat 2, thereby achieving locking.

[0057] The outer diameter of the contact boss 331 is larger than the inner diameter of the elastic member 31 .

[0058] A locking piece 34 is inserted into the end of the mounting hole away from the locking piece 32, and the locking piece 34 is connected to the end of the elastic piece 31 away from the connecting rod 33, so that the elastic piece 31 is in a compressed state before the opening and closing mechanism locks the solar wing panel in the unfolded position, and the locking piece 34 is threadedly connected to the hole wall of the mounting hole.

[0059] The locking member 34 provides support for the first end of the elastic member 31, enabling it to exert an elastic force on the connecting rod 33. By threading the locking member 34 into the wall of the mounting hole, not only does it seal the opening at one end of the mounting hole, but the degree of compression of the elastic member 31 can also be precisely adjusted through the threads, thereby controlling the preload force applied by the elastic member 31 to the locking member 32. Before the solar wing panel is deployed, an appropriate preload ensures that the locking member 32 is tightly abutted against the panel, preventing it from accidentally moving due to vibrations during launch and ensuring the reliability of the initial opening and closing mechanism. Once the solar wing panel is fully deployed, the elastic member 31 releases its stored elastic potential energy, driving the locking member 32 to move to the opposite side for locking. This precise preload ensures a stable and reliable locking action, ensuring that the solar wing panel is securely locked in the deployed position.

[0060] The locking member 34 may be a bolt.

[0061] The outer diameter of the portion of the locking member 34 that extends into the mounting hole is larger than the inner diameter of the elastic member 31 .

[0062] The locking member 32 is hinged on the first mounting seat 1 , and the connecting rod 33 is hinged to the locking member 32 to drive the connecting rod 33 to rotate on the first mounting seat 1 .

[0063] By hingedly connecting the locking member 32 to the first mounting base 1 and also hingedly connecting the connecting rod 33 to the locking member 32, the dual-hinged structure enables the locking member 32 to flexibly rotate relative to the first mounting base 1. During the deployment of the solar wing panel, when the elastic member 31 transmits force through the connecting rod 33, the locking member 32 can smoothly rotate about the hinge point, accurately adapting to changes in the position of the solar wing panel. This ensures that when the solar wing panel reaches the deployed position, the locking member 32 accurately moves to the predetermined reverse position and tightly abuts the solar wing panel, achieving reliable locking.

[0064] A connecting shaft is provided on the locking member 32 , the connecting rod 33 is hinged to the connecting shaft, and the connecting shaft is parallel to the central axis of rotation of the locking member 32 on the first mounting seat 1 .

[0065] The opening and closing mechanism further includes a first rotating shaft 35 and a connecting plate 36 . The first rotating shaft 35 is connected to the first mounting seat 1 via the connecting plate 36 , and the locking member 32 is rotatably disposed on the first rotating shaft 35 .

[0066] The first rotating shaft 35 is connected to the first mounting base 1 via the connecting plate 36, providing a stable rotation axis for the locking member 32. The locking member 32 is rotatably mounted on the first rotating shaft 35, effectively limiting its degrees of freedom in other directions and ensuring smoother and more accurate rotation. During the deployment and locking of the solar wing panels, the locking member 32 can precisely rotate along the first rotating shaft 35, effectively improving the reliability and consistency of the locking action and ensuring that the solar wing panels are securely locked in the deployed position.

[0067] One end of the first rotating shaft 35 is fixed on the first mounting seat 1 , and the other end is fixed on the connecting plate 36 . The connecting plate 36 is fixed on the first mounting seat 1 by bolts.

[0068] A space is reserved between the side of the connecting plate 36 where the first rotating shaft 35 is located and the first mounting seat 1 to accommodate the locking member 32 .

[0069] The locking member 32 is eccentrically disposed on the first rotating shaft 35 , and the protrusion of the locking member 32 is hinged to the connecting rod 33 .

[0070] By eccentrically positioning the locking member 32 on the first rotating shaft 35, when the elastic member 31 applies a force to the locking member 32 via the connecting rod 33, the eccentric structure generates a torque about the first rotating shaft 35. This effectively converts the linear expansion and contraction force of the elastic member 31 into rotational force for the locking member 32, achieving a force amplification effect to a certain extent. This allows the locking member 32 to generate a greater rotational torque with a smaller force from the elastic member 31 during rotation, thereby more effectively pushing the locking member 32 to the opposite side of the solar wing panel for locking. This enhances the locking force and ensures that the solar wing panel is securely locked in the deployed position.

[0071] Among them, the elastic member 31 applies elastic force to the connecting rod 33, so that the connecting rod 33 pushes the protrusion of the locking member 32 to move in the direction away from the elastic member 31, that is, to the opposite side of the first direction of the second mounting seat 2, and then reaches the opposite side of the first direction of the second mounting seat 2, thereby realizing limited locking.

[0072] The locking member 32 may be a cam, and the connecting rod 33 is hinged on the convex portion of the cam.

[0073] The seat body includes a second mounting seat 2, which is connected to the solar wing panel. The first mounting seat 1 is provided with a mounting groove, in which a second rotating shaft 11 is provided. The second mounting seat 2 is rotatably connected to the second rotating shaft 11.

[0074] By connecting the second mounting bracket 2 to the solar wing panel and rotating it with the first mounting bracket 1 via the second rotating shaft 11, a stable rotating auxiliary structure is formed. During the rotation of the solar wing panel, the second mounting bracket 2 can rotate smoothly around the second rotating shaft 11, ensuring smooth deployment of the solar wing panel. It also provides a reliable support point for the solar wing panel, preventing it from shifting or shaking during rotation, ensuring that the solar wing panel accurately reaches the deployed position and paving the way for subsequent locking operations.

[0075] The second mounting seat 2 is connected to the solar wing panel by bolts.

[0076] The mounting groove is roughly U-shaped, making way for the rotation of the second mounting seat 2.

[0077] Specifically, one end of the second rotating shaft 11 is fixed to a groove wall at one end in the width direction of the installation groove, and the other end of the second rotating shaft 11 is fixed to a groove wall at the other end in the width direction of the installation groove.

[0078] The second rotating shaft 11 is arranged parallel to the connecting rod 33 , and an extending direction of the second rotating shaft 11 is perpendicular to an extending direction of the first rotating shaft 35 .

[0079] Before the solar wing panel rotates to the unfolded position, the elastic member 31 abuts the locking member 32 against the second mounting seat 2 through the connecting rod 33. After the solar wing panel is in the unfolded position, the elastic member 31 drives the locking member 32 to move to the opposite side of the first direction of the second mounting seat 2 through the connecting rod 33, and abuts against the second mounting seat 2.

[0080] Before the solar wing panel rotates to the deployed position, the elastic member 31, via the connecting rod 33, abuts the locking member 32 against the second mounting base 2. This prevents the locking member 32 from shaking and striking the second mounting base 2 or other parts, potentially causing instability. Once the solar wing panel reaches the deployed position, the elastic member 31, via the connecting rod 33, drives the locking member 32 to the opposite side of the second mounting base 2, where it abuts against it, achieving precise locking and improving both reliability and effectiveness.

[0081] Before the solar wing panel rotates to the deployed position, the elastic member 31 applies elastic force to the connecting rod 33 , so that the outer wall surface of the protrusion of the locking member 32 abuts against the second mounting seat 2 .

[0082] When the solar wing panel reaches the unfolded position, the elastic member 31 applies elastic force to the connecting rod 33, so that the protrusion of the locking member 32 moves to the opposite side of the second mounting seat 2 and abuts against the second mounting seat 2, achieving precise locking.

[0083] The second mounting seat 2 includes a sleeve member 21 and a connecting member 22 . The sleeve member 21 is rotatably sleeved on the second rotating shaft 11 , and the connecting member 22 is connected to the solar wing panel.

[0084] The sleeve 21 rotatably fits over the second rotating shaft 11, enabling the second mounting base 2 to rotate flexibly about the second rotating shaft 11, ensuring smooth deployment of the solar wing panel. Simultaneously, the connector 22 connects to the solar wing panel, tightly integrating it with the second mounting base 2. This ensures that the panel's rotational motion is accurately transmitted to the second mounting base 2. Once the solar wing panel is fully deployed, the second mounting base 2 cooperates with the opening and closing mechanism to achieve stable locking. This structure achieves both rotational functionality and connection reliability, effectively improving the overall performance of the solar wing panel's deployment and locking.

[0085] The sleeve 21 and the connector 22 are connected, and may be integrally formed.

[0086] The sleeve 21 is annular in shape, and its inner diameter matches the outer diameter of the second rotating shaft 11 , thereby rotating on the second rotating shaft 11 .

[0087] The connecting member 22 may be a flat plate structure and may be fixed to the solar wing panel by bolts.

[0088] A second aspect of this embodiment provides a satellite comprising the above-mentioned opening and closing mechanism of the solar wing panel.

[0089] It is easy for those skilled in the art to understand that, under the premise of no conflict, the above-mentioned advantageous methods can be freely combined and superimposed.

[0090] The above are merely preferred embodiments of the present application and are not intended to limit the present application. Any modifications, equivalent replacements, and improvements made within the spirit and principles of the present application shall be included within the scope of protection of the present application. The above are merely preferred embodiments of the present application. It should be noted that those skilled in the art may make various improvements and variations without departing from the technical principles of the present application, and such improvements and variations shall also be considered within the scope of protection of the present application.

Claims

1. A solar wing panel opening and closing mechanism, characterized in that: The solar wing panel is rotated along a first direction on the satellite body through an opening and closing mechanism and locked in an unfolded position. The opening and closing mechanism includes a seat, an elastic member (31) and a locking member (32). The solar wing panel is hinged to the satellite body through the seat. The locking member (32) is movably arranged on the seat. The elastic member (31) is connected to the locking member (32) to drive the locking member (32) to move to the opposite side of the first direction of the solar wing panel after the solar wing panel is in the unfolded position, so as to limit the solar wing panel.

2. The opening and closing mechanism of the solar wing panel according to claim 1, characterized in that: The opening and closing mechanism is made of AL6061; The seat body comprises a first mounting seat (1), the first mounting seat (1) is connected to the satellite body, the elastic member (31) is arranged on the first mounting seat (1), and the opening and closing mechanism further comprises a connecting rod (33), the connecting rod (33) is respectively connected to the elastic member (31) and the locking member (32), and the elastic member (31) drives the locking member (32) to move through the connecting rod (33).

3. The opening and closing mechanism of the solar wing panel according to claim 2, characterized in that: A mounting hole is provided on the first mounting seat (1), and the elastic member (31) is provided in the mounting hole. A first end of the elastic member (31) is fixed to the first mounting seat (1), and a second end is sleeved on the connecting rod (33) and abuts against an abutting boss (331) on the connecting rod (33). An end of the connecting rod (33) away from the elastic member (31) extends out of the mounting hole and is connected to the locking member (32).

4. The opening and closing mechanism of the solar wing panel according to claim 3, characterized in that: A locking member (34) is inserted into one end of the mounting hole away from the locking member (32), and the locking member (34) is connected to one end of the elastic member (31) away from the connecting rod (33), so that the elastic member (31) is in a compressed state before the opening and closing mechanism locks the solar wing panel in the unfolded position, and the locking member (34) is threadedly connected to the hole wall of the mounting hole.

5. The solar wing panel opening and closing mechanism according to claim 3, characterized in that: The locking member (32) is hinged on the first mounting seat (1), and the connecting rod (33) is hinged to the locking member (32) to drive the connecting rod (33) to rotate on the first mounting seat (1).

6. The solar wing panel opening and closing mechanism according to claim 2, characterized in that: The opening and closing mechanism further comprises a first rotating shaft (35) and a connecting plate (36); the first rotating shaft (35) is connected to the first mounting seat (1) via the connecting plate (36); and the locking member (32) is rotatably arranged on the first rotating shaft (35).

7. The solar wing panel opening and closing mechanism according to claim 6, characterized in that: The locking member (32) is eccentrically arranged on the first rotating shaft (35), and the protrusion of the locking member (32) is hinged to the connecting rod (33).

8. The solar wing panel opening and closing mechanism according to claim 2, characterized in that: The seat body comprises a second mounting seat (2), the second mounting seat (2) is connected to the solar wing panel, the first mounting seat (1) is provided with a mounting groove, a second rotating shaft (11) is provided in the mounting groove, and the second mounting seat (2) is rotatably connected to the second rotating shaft (11); Before the solar wing panel is rotated to the unfolded position, the elastic member (31) abuts the locking member (32) against the second mounting seat (2) through the connecting rod (33); after the solar wing panel is in the unfolded position, the elastic member (31) drives the locking member (32) to move to the opposite side of the first direction of the second mounting seat (2) through the connecting rod (33) and abuts against the second mounting seat (2).

9. The solar wing panel opening and closing mechanism according to claim 8, characterized in that: The second mounting seat (2) comprises a sleeve member (21) and a connecting member (22), wherein the sleeve member (21) is rotatably sleeved on the second rotating shaft (11), and the connecting member (22) is connected to the solar wing panel.

10. A satellite, characterized in that: The invention comprises an opening and closing mechanism of a solar wing panel as described in any one of claims 1 to 9.

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