Solar wing mechanism, solar wing satellite, and solar wing mechanism deployment method

Abstract

The application relates to a solar wing mechanism, a solar wing satellite and a solar wing mechanism unfolding method, wherein the solar wing mechanism comprises a base assembly, a connecting assembly comprising a first elastic member and a connecting structure, the connecting structure being rotatably connected with the base assembly, the first elastic member exerting elastic force on the base assembly and the connecting structure, a solar wing assembly, the solar wing assembly comprising a second elastic member and a solar wing structure, the solar wing structure being rotatably connected with the connecting structure on a side away from the connecting assembly, the second elastic member exerting elastic force on the connecting structure and the solar wing structure, and a timing assembly, the timing assembly comprising a first timing structure and a second timing structure, the first timing structure being arranged on the base assembly, the second timing structure being arranged on the solar wing structure, and the first timing structure and the second timing structure being movably matched. The technical scheme of the application solves the problem that the solar wing mechanism in the prior art has a relatively large risk of vibration interference on a satellite during unfolding.

Description

Technical Field

[0001] This application relates to the technical field of solar array mechanisms, and more specifically, to a solar array mechanism, a solar array satellite, and a method for deploying the solar array mechanism. Background Technology

[0002] Satellite solar panels are the core energy supply device for spacecraft in orbit, and their deployment reliability directly affects the success or failure of space missions. During launch, the solar panels must remain folded and compressed to withstand the harsh mechanical environment; after entering orbit, they must reliably deploy and lock. Existing satellite solar panels typically employ a structure where multiple panels are connected sequentially by hinges. A connecting frame between the panels and the satellite body enables the hinge connection, and torsion springs are installed at each hinge as the deployment power source. After entering orbit, a compression release device releases the constraints, allowing the panels to deploy under the drive of the torsion springs. However, because multiple panels have multiple degrees of freedom at their hinges, if the torsion springs at all hinges are driven simultaneously, the panels are prone to uncontrolled swaying during deployment, potentially colliding with the satellite body, causing structural damage or deployment failure.

[0003] To address the aforementioned issues, some existing devices (e.g., application number 202011418621.3, entitled "Satellite Solar Panel Deployment Device") employ a locking pin and channel structure, causing the support closest to the satellite to deploy first, followed by the wing panels furthest from the satellite. The wing panels furthest from the satellite exert a significant torque on the satellite. Even minor impacts, vibrations, or imbalances in force on the satellite's sides during deployment can cause serious damage, requiring lengthy adjustments and sometimes even rendering the satellite malfunction. Summary of the Invention

[0004] This application provides a solar array mechanism, a solar array satellite, and a method for deploying the solar array mechanism to solve the problem that the deployment of the solar array mechanism in the prior art causes significant vibration interference to the satellite, or even collisions with the satellite.

[0005] A solar array mechanism according to this application includes: a base assembly; a connecting assembly, the connecting assembly including a first elastic element and a connecting structure, the connecting structure being rotatably connected to the base assembly, the first elastic element applying an elastic force to the base assembly and the connecting structure; a solar array assembly, the solar array assembly including a second elastic element and a solar array structure, the solar array structure being rotatably connected to the side of the connecting structure away from the base assembly, the second elastic element applying an elastic force to the connecting structure and the solar array structure; and a timing assembly, the timing assembly including a first timing structure and a second timing structure, the first timing structure being disposed on the base assembly, the second timing structure being disposed on the solar array structure, the first timing structure and the second timing structure being movablely engaged.

[0006] Furthermore, the first time-series structure and the second time-series structure counteract each other.

[0007] Furthermore, the first timing structure includes a vertical rod and a horizontal rod. The first end of the vertical rod is connected to the base assembly, the second end of the vertical rod is connected to the first end of the horizontal rod, the second end of the horizontal rod extends away from the satellite, and the inner wall of the horizontal rod abuts against the outer wall of the second timing structure.

[0008] Furthermore, the second timing structure includes a linear plate segment and an arc plate segment of integrated structure, with the linear plate segment connected to the solar array assembly.

[0009] Furthermore, the solar array structure includes a first wing plate, which is connected to the connecting structure via a first rotating shaft. The arc plate segment is an arc with the first rotating shaft as the center and the radius from the first rotating shaft to the arc plate segment. The central angle of the arc plate segment is between 15° and 55°.

[0010] Furthermore, the solar array structure also includes a second wing plate, which is rotatably connected to the first wing plate.

[0011] Furthermore, the connecting structure includes a first horizontal plate, a second horizontal plate, and multiple connecting plates, which are connected between the first and second horizontal plates at intervals. When the solar array mechanism is in a folded state, the timing component passes through the connecting structure.

[0012] Furthermore, both the first and second elastic elements are torsion springs, and the first and second elastic elements are located on both sides of the connecting frame, respectively.

[0013] According to another aspect of this application, a solar-wing satellite is also provided. The solar-wing satellite includes a satellite, a solar-wing constraint structure, and multiple sets of solar-wing mechanisms. The solar-wing constraint structure and the multiple sets of solar-wing mechanisms are both disposed on the satellite. The solar-wing constraint structure is connected to the multiple sets of solar-wing mechanisms so that the multiple sets of solar-wing mechanisms are in a folded state. Each solar-wing mechanism is the aforementioned solar-wing mechanism.

[0014] According to another aspect of this application, a method for deploying a solar wing mechanism is also provided. The method includes: S10 the solar wing constraint structure stops constraining; S20 the solar wing mechanism deploys in an orderly manner under its own mechanical force; S21 the solar wing assembly deploys; S22 the first timing structure and the second timing structure move in coordination, at which time the connecting structure is in a folded state; S23 when the solar wing assembly deploys to a predetermined angle, the first timing structure and the second timing structure stop coordinating, and the connecting structure deploys; S30 the solar wing mechanism is fully deployed.

[0015] Applying the technical solution of this application, during the deployment of the solar array mechanism, the second elastic element applies an elastic force to the connecting structure and the solar array structure, causing the solar array structure to rotate and deploy. During the deployment process, the first and second timing structures move relative to each other. The second elastic element overcomes the interaction force between the first and second timing structures. Simultaneously, the second elastic element applies a force to the connecting structure while simultaneously applying a force to the solar array structure. The first elastic element applies an elastic force to the connecting structure, and the torque exerted by the first elastic element on the connecting structure is balanced by the torque exerted by the second elastic element on the connecting structure. At this time, the connecting structure does not rotate or rotates only slightly. This significantly reduces the torque on the satellite during the solar array deployment process, thereby reducing vibration interference to the satellite. Only after the first and second timing structures disengage, the second elastic element reduces the force generated by overcoming the interaction between the first and second timing structures. That is, the torque exerted by the first elastic element on the connecting structure is greater than the torque exerted by the second elastic element on the connecting structure. The connecting structure gradually deploys, thus avoiding collisions with the satellite. Furthermore, the solar array structure and the connecting structure open simultaneously, improving deployment efficiency. The technical solution of this application effectively solves the problem that the deployment of the solar array mechanism in the prior art poses a significant risk of vibration interference to the satellite. Attached Figure Description

[0016] The accompanying drawings, which are incorporated in and form part of this specification, illustrate embodiments consistent with this application and, together with the description, serve to explain the principles of this application.

[0017] To more clearly illustrate the technical solutions in the embodiments of this application or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, for those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0018] Figure 1 A three-dimensional structural schematic diagram of the solar panel mechanism in the retracted state according to Embodiment 1 of this application is shown; Figure 2 It shows Figure 1 A three-dimensional structural diagram of the solar array mechanism in its partially deployed state; Figure 3 It shows Figure 2 Enlarged schematic diagram of point A of the solar array mechanism; Figure 4 It shows Figure 1 A three-dimensional schematic diagram of the fully deployed solar array mechanism; Figure 5 It shows Figure 1 A front view schematic diagram of the solar array mechanism in its retracted state; Figure 6 It shows Figure 5 A front view schematic diagram of the solar array mechanism when the timing components of the solar array mechanism are in sync; Figure 7 It shows Figure 5 A front view of the solar array mechanism when the timing components of the solar array mechanism are disengaged; Figure 8 It shows Figure 5 A front view schematic diagram of the solar array mechanism in its fully deployed state; Figure 9 It shows Figure 1 A schematic diagram of the torque analysis of the solar panel mechanism; Figure 10 It shows Figure 1 A partially enlarged schematic diagram of the junction between the first and second time-series structures of the solar energy mechanism; Figure 11 It shows Figure 1 A three-dimensional structural diagram of the hinge structure of the solar energy mechanism; Figure 12 It shows Figure 11 A front view schematic diagram of the hinge structure; Figure 13 It shows Figure 12 A schematic diagram of the hinge structure viewed along the AA direction; Figure 14 It shows Figure 13 A rear view diagram of the hinge structure; Figure 15 A schematic diagram of the deployment process of the solar array mechanism of this application is shown.

[0019] The above figures include the following reference numerals: 10. Base assembly; 20. Connecting assembly; 21. Connecting structure; 30. Solar fin assembly; 31. Solar fin structure; 311. First fin plate; 312. Second fin plate; 40. Timing assembly; 41. First timing structure; 411. Vertical rod; 412. Horizontal rod; 413. Protrusion; 42. Second timing structure; 421. Straight plate segment; 422. Curved plate segment; 4221. Curved vertical plate; 4222. Curved baffle; 50. Hinge structure; 51. First torsion spring; 52. First pivot; 53. First hinge plate; 54. Second hinge plate; 55. Pin seat; 56. Fixed pin; 57. Spring; 58. Curved fixing seat; 59. Fixed pin hole; 100. Satellite; 200. Solar fin constraint structure. Detailed Implementation

[0020] It should be noted that, unless otherwise specified, the embodiments and features described in this application can be combined with each other. This application will now be described in detail with reference to the accompanying drawings and embodiments.

[0021] It should be noted that the following detailed descriptions are illustrative and intended to provide further explanation of this application. Unless otherwise specified, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this application pertains.

[0022] For ease of description, spatial relative terms such as "above," "on top of," "on the upper surface of," "above," etc., are used herein to describe the spatial positional relationship of a device or feature as shown in the figures to other devices or features. It should be understood that spatial relative terms are intended to encompass different orientations in use or operation beyond the orientation of the device as described in the figures. For example, if the device in the figures were inverted, a device described as "above" or "on top of" other devices or structures would subsequently be positioned as "below" or "under" other devices or structures. Thus, the exemplary term "above" can include both "above" and "below." The device may also be positioned in other different ways, rotated 90 degrees, or in other orientations, and the spatial relative descriptions used herein will be interpreted accordingly.

[0023] like Figures 1 to 14 As shown, in Embodiment 1, the solar array mechanism includes: a base assembly 10, a connecting assembly 20, a solar array assembly 30, and a timing assembly 40. The connecting assembly 20 includes a first elastic element and a connecting structure 21, the connecting structure 21 being rotatably connected to the base assembly 10. The first elastic element applies an elastic force to the base assembly 10 and the connecting structure 21. The solar array assembly 30 includes a second elastic element and a solar array structure 31, the solar array structure 31 being rotatably connected to the side of the connecting structure away from the base assembly 10. The second elastic element applies an elastic force to the connecting structure 21 and the solar array structure 31. The timing assembly 40 includes a first timing structure 41 and a second timing structure 42. The first timing structure 41 is disposed on the base assembly 10, and the second timing structure 42 is disposed on the solar array structure 31. The first timing structure 41 and the second timing structure 42 are movable and engaged.

[0024] Applying the technical solution of this embodiment, when the solar array mechanism deploys, the second elastic element applies an elastic force to the connecting structure 21 and the solar array structure 31, causing the solar array structure 31 to rotate and deploy. During the deployment of the solar array structure 31, the first timing structure 41 and the second timing structure 42 move relative to each other. The second elastic element overcomes the combined force of the first timing structure 41 and the second timing structure 42. While applying a force to the solar array structure 31, the second elastic element also applies a reverse force to the connecting structure 21. The first elastic element applies an elastic force to the connecting structure 21, and the torque of the first elastic element on the connecting structure 21 is balanced by the torque of the second elastic element on the connecting structure 21. At this time, the connecting structure 21 does not rotate or rotates only slightly. In this way, the torque on the satellite during the deployment of the solar array structure is greatly reduced, thereby reducing vibration interference to the satellite. Until the first timing structure 41 and the second timing structure 42 disengage, the second elastic element reduces the force generated by overcoming the engagement between the first and second timing structures 41 and 42. That is, the torque of the first elastic element on the connecting structure 21 is greater than the torque of the second elastic element on the connecting structure 21. The connecting structure 21 gradually unfolds, thus avoiding collision with the satellite. Furthermore, the solar array structure 31 and the connecting structure 21 open simultaneously, improving deployment efficiency. The technical solution of this embodiment effectively solves the problem of significant vibration interference to the satellite during the deployment of the solar array mechanism in the prior art.

[0025] It should be noted that the technical solution implemented in this way can also effectively avoid the risk of the solar array structure 31 colliding with the satellite 100. For example, see... Figure 2 If the connecting structure 21 rotates at a large angle, the upper part of the solar array structure 31 will collide with the satellite 100. The technical solution of this embodiment effectively eliminates the risk of the solar array structure 31 colliding with the satellite 100; that is, the upper part of the solar array structure 31 will not rotate towards the satellite 100. The height of the connecting structure 21 is less than the height of the first wing plate 311. Figure 5 (The vertical direction in the figure is the height). In this embodiment, the height of the connecting structure 21 is between 1 / 6 and 1 / 2 of the height of the first wing plate 311.

[0026] In the technical solution of Embodiment 1, the first timing structure 41 and the second timing structure 42 abut against each other. The above structure is compact and achieves good results. Figure 9As shown, for ease of force and torque analysis, the following definitions are made: the base assembly 10 and the connecting structure 21 are fitted by a first rotating shaft and a first torsion spring; the connecting structure 21 and the first wing plate 311 are fitted by a second rotating shaft and a second torsion spring; and the first wing plate 311 and the second wing plate 312 are fitted by a third rotating shaft and a third torsion spring. The first torsion spring drives the connecting structure 21, the second torsion spring, the inner and outer wing plates (the first wing plate 311 and the second wing plate 312), and the third torsion spring between the inner and outer wing plates. The connecting structure 21, the second torsion spring, the inner and outer wing plates (the first wing plate 311 and the second wing plate 312), and the third torsion spring between the inner and outer wing plates, as a whole M, are subjected to the following external forces: the elastic force F1 of the first torsion spring and the abutting force F between the first timing structure 41 and the second timing structure 42. When this whole M swings or has a tendency to swing, the interaction force F between the first timing structure 41 and the second timing structure 42 will interfere, that is, the driving force F1 of the first torsion spring will be restricted by the timing assembly 40. The forces acting within the overall M are: the second torsion spring between the connecting structure 21 and the first wing plate 311, and the third torsion spring between the first wing plate 311 and the second wing plate 312. These forces are essentially internal forces, and their effects need not be considered in the force analysis here.

[0027] The first torsion spring applies a torque to the connecting structure 21 (which is also equivalent to applying a torque to the whole M), denoted as M1. The distance from the center of the first torsion spring to the contact position of the first timing structure 41 and the second timing structure 42 is denoted as L1. The force exerted by the first torsion spring on the entire system a should be F1 = M1 / L1. The force exerted by the contact between the two components of the timing control mechanism is denoted as F. If F1 ≤ F, rotation is not possible.

[0028] Force analysis is performed on the second torsion spring: When analyzing the force of the second torsion spring, the first wing plate 311, the second wing plate 312, and the third torsion spring between the first wing plate 311 and the second wing plate 312 are considered as a whole N, and the influence of the third torsion spring between the first wing plate 311 and the second wing plate 312 need not be considered.

[0029] The torque exerted by the second torsion spring on the first wing plate (inner wing plate) is denoted as M2. The distance from the second torsion spring to the contact point between the first timing structure 41 and the second timing structure 42 is denoted as L2. The force exerted by the second torsion spring on the first wing plate 311 is: F2 = M2 / L2. The second torsion spring drives the first wing plate 311 to swing. At this time, the second timing structure 42 moves relative to the first timing structure 41. Since the first timing structure 41 and the second timing structure 42 are in contact, there is also a frictional force between the first timing structure 41 and the second timing structure 42, denoted as Ff. F2 > Ff, so the first wing 311 can be deployed.

[0030] like Figure 3 As shown, in the technical solution of Embodiment 1, the first timing structure 41 includes a vertical rod 411 and a horizontal rod 412. The first end of the vertical rod 411 is connected to the base assembly 10, and the second end of the vertical rod 411 is connected to the first end of the horizontal rod 412. The second end of the horizontal rod 412 extends away from the satellite, and the inner wall of the horizontal rod 412 abuts against the outer wall of the second timing structure 42. The above structure is compact and easy to operate. The vertical rod 411 and the horizontal rod 412 form an L-shape, a cantilever beam structure, which provides stable abutment and good vibration resistance. The cantilever beam structure can resist a certain impact force.

[0031] like Figure 3 As shown, in the technical solution of Embodiment 1, the second timing structure 42 includes a straight plate segment 421 and an arc plate segment 422 of integral structure. The straight plate segment 421 is connected to the solar panel assembly 30. The straight plate segment 421 facilitates finding a reference point for installation. In addition, the straight plate segment 421 facilitates structural transition, reduces processing difficulty, reduces stress concentration in the second timing structure 42, and can also serve as an auxiliary limiting element. It should be noted that the curved plate segment 422 includes a curved vertical plate 4221 and a curved baffle 4222. The curved baffle 4222 is located at the upper edge of the curved vertical plate 4221 and protrudes from the surfaces on both sides of the curved vertical plate 4221. The aforementioned force F is the normal force exerted by the curved baffle 4222 on the protrusion 413 of the transverse rod 412. There are two vertical rods 411 and transverse rods 412, located on opposite sides of the second time sequence structure 42. In this way, the force distribution between the first time sequence structure 41 and the second time sequence structure 42 is more stable, uniform, and controllable.

[0032] like Figure 3As shown, in the technical solution of Embodiment 1, the solar panel structure 31 includes a first wing plate 311, which is connected to the connecting structure 21 via a first rotating shaft. The arc plate segment 422 is an arc with the first rotating shaft as its center and the radius from the first rotating shaft to the arc plate segment 422. The central angle of the arc plate segment 422 is between 15° and 55°. When the transverse rod 412 (or transverse plate) presses against the outer wall of the arc plate segment 422 with the first rotating shaft as its center, the gap and pressure between the two do not change significantly with the rotation of the first wing plate 311. The arc plate segment 422 has a certain width, which allows for movement deviation between the transverse rod 412 and the arc plate segment 422. The central angle of the arc plate segment 422 is limited to 15° to 55°. This satisfies the requirement that after the first stage of motion is completed, the transverse rod 412 and the arc plate segment 422 disengage, and the connecting structure 21 and the first wing plate 311 simultaneously perform the second stage of motion. The unlocking of the connecting structure 21 is limited by the range of the central angle of the arc plate segment 422. If the angle is too small, the first wing plate 311 is prone to interference or collision with the satellite 100; if the angle is too large, the deployment efficiency of the solar panel mechanism is low. It should be noted that the first wing plate 311 is connected perpendicularly to the straight plate segment 421. The inner wall surface of the transverse rod 412 has a protrusion 413. The protrusion contacts the inner wall surface of the arc baffle 4222 of the second timing structure 42, generating frictional and normal forces. This improves the stability of the pressure positioning and reduces the uncontrollability of large-area contact between the transverse rod 412 and the arc plate segment 422. To ensure smooth relative movement, prevent jamming, and improve centering adaptability, protrusion 413 is cylindrical.

[0033] In the technical solution of Embodiment 1, the solar panel structure 31 further includes a second wing plate 312, which is rotatably connected to the first wing plate 311. This reduces the volume of the collapsed envelope, increases the power generation area, and facilitates the layout of battery cells and wiring; from a stress perspective, it can disperse the impact of deployment and reduce the load.

[0034] like Figure 2 and Figure 3 As shown, in the technical solution of Embodiment 1, the connecting structure 21 includes a first horizontal plate, a second horizontal plate, and multiple connecting plates. The multiple connecting plates are connected between the first and second horizontal plates at intervals. When the solar panel mechanism is in the folded state, the timing component 40 passes through the connecting structure 21. The above structure can reduce the weight of the connecting structure 21, reduce vibration response, reduce resonance risk, and facilitate circuit layout while ensuring rigidity. More importantly, the above structure facilitates the avoidance of the timing component 40, and the timing component 40 is less likely to interfere with the connecting structure 21 when it moves.

[0035] It should be noted that the length of the second horizontal plate is greater than that of the first horizontal plate, and the two pivots of the first wing plate 311 are connected to the two ends of the second horizontal plate. The above structure can enhance resistance to torque and uneven force generated during vibration.

[0036] In the technical solution of Embodiment 1, both the first and second elastic elements are torsion springs, and the first and second elastic elements are located on both sides of the connecting frame, respectively. The above structure is compact, facilitating spatial layout, and ensuring stable deployment torque output and uniform force distribution. It should be noted that the first wing plate 311 and the second wing plate 312 are also connected via a rotating shaft and a torsion spring structure.

[0037] like Figures 11 to 14 As shown below, the hinge structure 50 is described. The hinge structures 50 used for the relatively rotating parts in this article are all similar. Taking the structure of the first torsion spring 51 (the first torsion spring 51 is the specific structural form of the first elastic element mentioned above) and the first rotating shaft 52 as an example, one end of the elastic wire at both ends of the first torsion spring 51 presses against the first hinge plate 53, and the other end presses against the second hinge plate 54. The first hinge plate 53 and the second hinge plate 54 are connected by the first rotating shaft 52. The first torsion spring 51 is sleeved on the first rotating shaft 52. There are two first torsion springs 51 and two first rotating shafts 52. The first hinge plate 53 is provided with a pin seat 55, and a fixing pin 56 is disposed in the pin seat 55. A compressed spring 57 is disposed between the first end of the fixing pin 56 and the inner wall of the pin seat 55. The second hinge plate 54 has an arc-shaped fixing seat 58 in the middle. One end of the arc-shaped fixing seat 58 is fixed with a pin hole 59, and the second end of the fixing pin 56 abuts against the arc-shaped fixing seat 58. When the first hinge plate 53 and the second hinge plate 54 are in the unfolded state, the second end of the fixing pin 56 enters the pin hole 59. Two first torsion springs 51 are respectively sleeved on two first rotating shafts 52, and the two first rotating shafts 52 are symmetrically arranged on both sides of the arc-shaped fixing seat 58. The first hinge plate 53 and the second hinge plate 54 are respectively connected to the base assembly 10 and the connecting structure 21. The connection method between the connecting structure 21 and the first wing plate 311, and the connection method between the first wing plate 311 and the second wing plate 312 are similar.

[0038] The difference between the technical solution of Embodiment 2 and Embodiment 1 is that both the first timing structure 41 and the second timing structure 42 are magnetic components; both permanent magnet and electromagnet structures are acceptable. For example, the first timing structure 41 can be a permanent magnet, and the second timing structure 42 can be a metallic material that can be attracted by the permanent magnet. Alternatively, both the first timing structure 41 and the second timing structure 42 can be electromagnets, and the interaction force between the first timing structure 41 and the second timing structure 42 can be achieved through electronic control.

[0039] The difference between the technical solution of Embodiment 3 and Embodiment 1 is that a friction groove is provided on the outer wall surface of the second timing structure 42. The friction groove cooperates with the protrusion to realize the timing control of the timing component 40. This makes the cooperation between the first timing structure 41 and the second timing structure 42 more stable and the force more uniform. It should be noted that, to avoid jamming of the first timing structure 41 and the second timing structure 42, both the protrusion and the groove have arc-shaped contours. Alternatively, the protrusion can be located on the second timing structure 42, and the groove can be located on the first timing structure 41.

[0040] According to another aspect of this application, a solar-wing satellite is also provided. The solar-wing satellite includes a satellite 100, a solar-wing constraint structure 200, and multiple sets of solar-wing mechanisms. The solar-wing constraint structure 200 and the multiple sets of solar-wing mechanisms are all disposed on the satellite 100. The solar-wing constraint structure 200 is connected to the multiple sets of solar-wing mechanisms to allow the multiple sets of solar-wing mechanisms to be in a folded state. Each solar-wing mechanism is the aforementioned type. A connecting structure 21 and a base assembly 10 are connected via a second pivot. The angular limits of the connecting structure 21, the first wing plate 311, and the second wing plate 312 are all achieved through their own structures. For example, when the connecting structure 21 unfolds 90° from a vertical state to a horizontal state, the base assembly 10 forms a blocking limit on the connecting structure 21. Some embodiments involve two sets of solar-wing mechanisms symmetrically arranged on both sides of the satellite 100. This structure makes the force on the satellite 100 more balanced.

[0041] like Figure 15 As shown, according to another aspect of this application, a method for deploying a solar wing mechanism is also provided. The method includes: S10, the solar wing constraint structure stops constraining; S20, the solar wing mechanism deploys in an orderly manner under its own mechanical force; S21, the solar wing assembly 30 deploys; S22, the first timing structure 41 and the second timing structure 42 move in relative coordination, at which time the connecting structure 21 is in a folded state; S23, when the solar wing assembly 30 deploys to a predetermined angle, the first timing structure 41 and the second timing structure 42 stop coordinating, and the connecting structure 21 deploys; S30, the solar wing mechanism is fully deployed. The first side of the connecting structure 21 is rotatably connected to the base assembly 10, the second side of the connecting structure 21 is rotatably connected to the first wing plate 311, the second side of the first wing plate 311 is rotatably connected to the first side of the second wing plate, and the second side of the second wing plate is a free end. When the solar array mechanism is in the folded state, the connecting structure 21, the first wing plate 311, and the second wing plate 312 are all folded vertically, parallel to the side wall connected to the satellite 100; Figure 3 or Figure 4Taking the right-side solar wing mechanism as an example, after the solar wing constraint structure 200 is released from constraint, the second wing plate 312 rotates counterclockwise under the force of the torsion spring, and the first wing plate 311 rotates clockwise under the force of the torsion spring. During the initial time period after the solar wing constraint structure 200 is released from constraint, under the combined force of the first timing structure 41, the second timing structure 42, the first elastic element, and the second elastic element, the connecting structure 21 is in a balanced state (i.e., the connecting structure 21 hardly rotates in the vertical state). After the first timing structure 41 and the second timing structure 42 disengage, the connecting structure 21 rotates counterclockwise until the first wing plate 311 and the second wing plate 312 are on the same plane, at which point the first wing plate 311 and the second wing plate 312 stop rotating. In some embodiments, the connecting structure 21, the first wing plate 311, and the second wing plate 312 are perpendicular to the corresponding ground plane of the satellite 100.

[0042] In summary, the solar array mechanism of this application solves the problems of existing solar array deployment components that rely on active control elements, have complex structures, insufficient reliability, and suffer from low deployment efficiency and easy collisions between the wingplates and the satellite due to the step-by-step activation of the torsion springs. This application achieves control over the deployment sequence of the satellite's solar array mechanism through the timing component 40, thus avoiding collisions between the satellite's solar array mechanism and the satellite body during deployment.

[0043] It should be noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to limit the exemplary embodiments according to this application. As used herein, the singular form is intended to include the plural form as well, unless the context clearly indicates otherwise. Furthermore, it should be understood that when the terms "comprising" and / or "including" are used in this specification, they indicate the presence of features, steps, operations, devices, components, and / or combinations thereof.

[0044] It should be noted that the terms "first," "second," etc., in the specification, claims, and accompanying drawings of this application are used to distinguish similar objects and are not necessarily used to describe a specific order or sequence. It should be understood that such data can be interchanged where appropriate so that the embodiments of this application described herein can be implemented, for example, in orders other than those illustrated or described herein. Furthermore, the terms "comprising" and "having," and any variations thereof, are intended to cover non-exclusive inclusion; for example, a process, method, system, product, or apparatus that comprises a series of steps or units is not necessarily limited to those steps or units explicitly listed, but may include other steps or units not explicitly listed or inherent to such processes, methods, products, or apparatus.

[0045] The above are merely preferred embodiments of this application and are not intended to limit this application. Various modifications and variations can be made to this application by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of this application should be included within the protection scope of this application.

Claims

1. A solar array mechanism, characterized in that, include: Base assembly (10); A connecting component (20) includes a first elastic element and a connecting structure (21), the connecting structure (21) being rotatably connected to the base assembly (10), the first elastic element applying an elastic force to the base assembly (10) and the connecting structure (21); A solar array assembly (30) includes a second elastic element and a solar array structure (31), the solar array structure (31) being rotatably connected to the side of the connecting structure (21) away from the base assembly (10), the second elastic element applying an elastic force to the connecting structure (21) and the solar array structure (31); The timing component (40) includes a first timing structure (41) and a second timing structure (42). The first timing structure (41) is disposed on the base component (10), and the second timing structure (42) is disposed on the solar array structure (31). The first timing structure (41) and the second timing structure (42) are movable in cooperation.

2. The solar array mechanism according to claim 1, characterized in that, The first timing structure (41) and the second timing structure (42) are mutually opposed.

3. The solar array mechanism according to claim 2, characterized in that, The first timing structure (41) includes a vertical rod (411) and a horizontal rod (412). The first end of the vertical rod (411) is connected to the base assembly (10), and the second end of the vertical rod (411) is connected to the first end of the horizontal rod (412). The second end of the horizontal rod (412) extends away from the satellite, and the inner wall of the horizontal rod (412) abuts against the outer wall of the second timing structure (42).

4. The solar array mechanism according to claim 3, characterized in that, The second timing structure (42) includes a straight plate segment (421) and an arc plate segment (422) of an integral structure, wherein the straight plate segment (421) is connected to the solar array assembly (30).

5. The solar array mechanism according to claim 4, characterized in that, The solar array structure (31) includes a first wing plate (311), which is connected to the connecting structure (21) via a first rotating shaft. The arc plate segment (422) is an arc with the first rotating shaft as the center and the radius from the first rotating shaft to the arc plate segment (422). The central angle of the arc plate segment (422) is between 15° and 55°.

6. The solar array mechanism according to claim 5, characterized in that, The solar array structure (31) further includes a second wing plate (312), which is rotatably connected to the first wing plate (311).

7. The solar array mechanism according to any one of claims 1 to 6, characterized in that, The connecting structure (21) includes a first horizontal plate, a second horizontal plate and a plurality of connecting plates, which are connected at intervals between the first horizontal plate and the second horizontal plate. When the solar wing mechanism is in a folded state, the timing component (40) passes through the connecting structure (21).

8. The solar array mechanism according to any one of claims 1 to 6, characterized in that, Both the first elastic element and the second elastic element are torsion springs, and the first elastic element and the second elastic element are located on both sides of the connecting frame, respectively.

9. A solar-powered satellite, characterized in that, The solar array satellite includes a satellite (100), a solar array constraint structure (200), and multiple sets of solar array mechanisms. The solar array constraint structure (200) and the multiple sets of solar array mechanisms are both disposed on the satellite (100). The solar array constraint structure (200) is connected to the multiple sets of solar array mechanisms so that the multiple sets of solar array mechanisms are in a folded state. Each of the solar array mechanisms is the solar array mechanism according to any one of claims 1 to 8.

10. A method for deploying a solar array mechanism, characterized in that, The deployment method of the solar array mechanism includes: S10 solar panel restraint structure stop restraint; S20 The solar panel mechanism unfolds in an orderly manner under its own mechanical force; S21 Solar fin assembly (30) deploys; S22 The first timing structure (41) and the second timing structure (42) move in coordination with each other, at which time the connecting structure (21) is in a folded state; S23 When the solar array assembly (30) unfolds to a predetermined angle, the first timing structure (41) and the second timing structure (42) stop cooperating, and the connecting structure (21) unfolds; The S30 solar array mechanism has been fully deployed.

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