A flexible circular solar wing deployment mechanism

Abstract

This invention discloses a flexible circular solar array deployment mechanism, belonging to the field of satellite flexible solar array technology. The mechanism includes a flipping component, multiple deployment mechanisms and deployment bays, and a flexible solar array. The deployment bays are connected by an elastic rod and are initially limited by a telescopic plate; each deployment bay contains an extension block hinged by a torsion spring. This invention achieves large-area, efficient deployment and rapid retraction of the solar array for protection, significantly improving its resistance to space debris impacts and its flexibility in tracking the sun.

Description

Technical Field

[0001] This invention relates to the field of flexible solar array technology for satellites, and particularly to a flexible circular solar array deployment mechanism. Background Technology

[0002] As the "energy heart" of a satellite in orbit, the solar array's photoelectric conversion efficiency, structural adaptability, and deployment reliability directly determine the satellite's mission cycle, payload capacity, and environmental adaptability. Traditional rigid solar arrays, due to their inherent defects such as large weight and high volume ratio, can no longer meet the core requirements of the new generation of space missions. Flexible solar arrays, with their dual innovation in materials and structure, have become the core technology direction for promoting the upgrade of satellite energy systems.

[0003] However, when flexible solar arrays operate in low Earth orbit, space debris is dense and the risk of collision is high. The large-area deployment structure of flexible solar arrays is easy to become a collision target, and their lack of rigid protection makes it difficult to continue working after damage, resulting in an increased rate of interruption of satellite energy supply. Therefore, the problem of low impact resistance of flexible solar arrays is particularly prominent.

[0004] Therefore, there is an urgent need for a flexible solar array deployment mechanism that is shock-resistant, retractable for protection, and capable of efficient solar tracking. Summary of the Invention

[0005] The present invention aims to provide a flexible circular solar array deployment mechanism to solve the problems of poor impact resistance and inability to effectively protect against space debris impacts in existing flexible solar arrays.

[0006] A flexible circular solar array deployment mechanism, installed inside a satellite's storage compartment, includes: a flipping component located on one side inside the storage compartment; multiple deployment mechanisms, each connected at one end to the flipping component, each deployment mechanism including: a first fixed frame and a second fixed frame; a second telescopic rod connected between the first and second fixed frames; a first telescopic plate and a first telescopic component driving its extension and retraction, located on the first fixed frame; a second telescopic plate and a second telescopic component driving its extension and retraction, located on the second fixed frame; a first driving component located inside the first fixed frame; and a deployment component connected to the output end of the first driving component.

[0007] Multiple sets of unfolding compartments are interconnected by an elastic rod, and the elastic rod is connected to the unfolding component.

[0008] The unfolding chamber includes: a base and a chamber body; a lifting component, which is vertically and vertically disposed inside the chamber body; and a second driving component, which is connected to the lifting component via a driving rod.

[0009] Multiple extension blocks are circumferentially hinged to the lifting component, and adjacent extension blocks are connected by elastic rods; a control ring is located above the chamber body.

[0010] The flexible solar panels are stacked in an arc shape and stored between adjacent deployment compartments, with their bottoms connected to the lifting components.

[0011] The flipping component drives the unfolding mechanism to flip via the telescopic rod and the rotating component. The driving component can drive multiple sets of unfolding chambers to flip outward and separate via the unfolding component. The driving component can drive the lifting component to rise and fall, so that the extension block can unfold or be restricted by the control ring to retract, thereby causing the flexible solar array to unfold or retract in a circular shape.

[0012] Furthermore, the multiple sets of the deployment mechanisms are interconnected by hinges, which enable the interconnected deployment mechanisms to undergo relative flipping motion.

[0013] Furthermore, a torsion spring is provided at the hinge between the extension block and the lifting member. When the lifting member rises to its limit position, the extension block can flip outward and unfold under the action of the torsion spring. When the lifting member descends, the side of the extension block is restricted by the control ring, compressing the torsion spring and flipping and retracting towards the center.

[0014] Furthermore, the side wall of the farthest unfolding compartment is provided with a rolling wheel, which rolls along the inner wall of the second fixing frame during the outward flipping of the unfolding compartment.

[0015] Furthermore, after the unfolding compartment separates from the first and second fixed frames, the second telescopic rod retracts, causing the first and second fixed frames to move towards each other.

[0016] Furthermore, multiple sets of flexible solar panels are attached to the surface of the flexible solar wing.

[0017] Furthermore, the drive component can drive the deployable component to swing, thereby enabling the deployed flexible solar array to track the sun.

[0018] Furthermore, the end of the extension block is provided with a clamping surface for clamping and fixing the flexible solar panel.

[0019] Beneficial technical effects of the present invention: 1. This invention adopts a multi-group flexible solar array circular independent deployment structure, which avoids the defects of a single large-area structure being susceptible to collisions with space debris. Even if some components are damaged, the remaining components can still work normally, significantly reducing the risk of satellite power supply interruption. At the same time, the lifting components can be driven to descend through the drive components, and the extension blocks can be restricted by the control ring to achieve rapid retraction and protection of the solar array, further avoiding damage from space debris impacts. 2. The flexible solar array of the present invention can perform a certain degree of oscillation, so that the deployed flexible solar array can flexibly track the sun, maximize the capture of solar energy, and further improve the photoelectric conversion efficiency. Attached Figure Description

[0020] The accompanying drawings, which are included to provide a further understanding of this application and form part of this application, illustrate exemplary embodiments of this application and are used to explain this application, but do not constitute an undue limitation of this application. In the drawings...

[0021] Figure 1 This is a schematic diagram of the overall invention.

[0022] Figure 2 This is a schematic diagram of the deployment mechanism assembly of the present invention.

[0023] Figure 3 This is a schematic diagram of the unfolding mechanism of the present invention.

[0024] Figure 4 This is a schematic diagram of the unfolding compartment of the present invention. Figure 1 .

[0025] Figure 5 This is a schematic diagram of the unfolding compartment of the present invention. Figure 2 .

[0026] Figure 6 This is a schematic diagram of the flexible solar array of the present invention.

[0027] Figure 7 This is a schematic diagram of the unfolding mechanism of the present invention in its unfolded state.

[0028] Figure 8 This is a schematic diagram of the orbital deployment of the present invention.

[0029] In the diagram, 1 is the satellite; 11 is the flipping component; 111 is the telescopic rod one; and 112 is the rotating component. 2. Deployment mechanism; 21. Fixed frame one; 211. Telescopic plate one; 212. Telescopic component one; 213. Deployment component; 214. Drive component one; 215. Elastic rod one; 22. Fixed frame two; 221. Telescopic plate two; 222. Telescopic component two; 23. Telescopic rod two; 24. Hinge component; 3. Deployment compartment; 31. Base; 32. Compartment body; 33. Lifting component; 331. Drive rod; 332. Drive component two; 34. Control ring; 35. Extension block; 351. Clamping surface; 352. Elastic rod two; 36. Rolling wheel; 4. Flexible solar panels. Detailed Implementation

[0030] To make the above-mentioned objects, features, and advantages of the present invention more apparent and understandable, the present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments. This will allow for a full understanding of how the present application uses technical means to solve technical problems and achieve technical effects, and to facilitate its implementation.

[0031] like Figure 1 As shown, a flexible circular solar array deployment mechanism is provided. Storage compartments are provided on both sides of the satellite 1. A flipping component 11 is provided on one side of the storage compartment. The flipping component 11 is connected to the deployment mechanism 2 and can drive the deployment mechanism 2 to perform a flipping motion.

[0032] like Figure 2 As shown, the unfolding mechanism 2 is provided with multiple sets. One end of the unfolding mechanism 2 is connected to the flipping member 11. The flipping member 11 is provided with a telescopic rod 111. The telescopic rod 111 can perform telescopic movement. One end of the telescopic rod 111 is connected to the rotating member 112. The rotating member 112 is located inside the unfolding mechanism 2. The rotating member 112 can drive the unfolding mechanism 2 to flip around the circumference of the rotating member 112.

[0033] The unfolding mechanism 2 is composed of a fixed frame 21 and a fixed frame 22 connected by a telescopic rod 23. The fixed frame 21 is provided with a telescopic component 212 and a telescopic plate 211. The telescopic plate 211 can move in and out of the telescopic component 212. The fixed frame 22 is provided with a telescopic plate 221 and a telescopic component 222 with the same principle and structure.

[0034] The first set of fixed frames 21 and the second set of fixed frames 22 on the multiple sets of unfolding mechanisms 2 are provided with hinges 24 to facilitate the connection of the multiple sets of unfolding mechanisms 2. The hinges 24 can drive the interconnected unfolding mechanisms 2 to rotate.

[0035] like Figure 3 As shown, the fixed frame 21 is equipped with a drive component 214, and the drive component 214 is connected to the unfolding component 213. The other end of the unfolding component 213 is connected to the unfolding chamber 3 through an elastic rod 215. Multiple sets of unfolding chambers 3 are connected through the elastic rod 215. At this time, the elastic rod 215 is in a contracted state. When it is not subjected to external force, the elastic rod 215 will extend, driving the multiple sets of unfolding chambers 3 to separate.

[0036] like Figure 4 As shown, the bases 31 of the multiple sets of unfolding chambers 3 are connected by elastic rods 215, and a control ring 34 is provided above the chamber body 32. Rolling wheels 36 are provided on the side wall of the last unfolding chamber 3.

[0037] like Figure 5As shown, a lifting component 33 is provided on the bottom surface inside the compartment 32. The bottom of the lifting component 33 is connected to a second driving component 332 via a driving rod 331. The second driving component 332 drives the driving rod 331 to extend and retract, thereby causing the lifting component 33 to move up and down inside the compartment 32. An extension block 35 is provided around the lifting component 33. The end of the extension block 35 is hinged to the lifting component 33. The extension block 35 can rotate on the lifting component 33. Adjacent extension blocks 35 are connected by an elastic rod 352. When no external force is applied, the elastic rod 352 generates a pulling force between the extension blocks 35, causing them to separate in all directions. A clamping surface 351 is provided on the extension block 35, which can clamp and fix the flexible solar panel 4.

[0038] A torsion spring is provided at the connection between the extension block 35 and the lifting member 33. When not restricted by external force, the extension block 35 can rotate in all directions around the lifting member 33. When the lifting member 33 moves to its limit, the lateral direction of the extension block 35 is unrestricted, and the extension block 35 will rotate under the action of the internal torsion spring. When the extended block 35 moves downward with the lifting member 33, the lateral extension block 35 is restricted by the control ring 34, thereby compressing the torsion spring and causing the extension block 35 to rotate towards the center, so that multiple sets of extension blocks 35 converge, causing the flexible solar wing 4 to retract and preventing the impact of space debris from damaging the flexible solar wing 4.

[0039] like Figure 6 As shown, the flexible solar wing 4 is stacked in an arc shape between the unfolding chambers 3, and the bottom of the flexible solar wing 4 is connected to the lifting component 33; multiple sets of flexible solar panels are attached to the flexible solar wing 4, and the flexible solar wing 4 can be folded to a certain extent. When the extension block 35 unfolds in all directions, it drives the flexible solar wing 4 to unfold in a circle.

[0040] like Figure 7 As shown, the unfolding component 213 drives multiple sets of unfolding chambers 3 to flip outward. The rolling wheel 36 of the last unfolding chamber 3 slides along the inner wall of the second fixed frame 22. When the unfolding chamber 3 separates from the second fixed frame 22, the end of the unfolding chamber 3 is unrestricted, and the elastic rod 352 between the unfolding chambers 3 extends, driving multiple sets of unfolding chambers 3 to separate.

[0041] When the unfolding chamber 3 separates from the first fixed frame 21 and the second fixed frame 22, the upper part of the extension block 35 inside the unfolding chamber 3 is no longer restricted by the first telescopic plate 211 and the second telescopic plate 221. The second elastic rod 352 extends, and multiple sets of extension blocks 35 perform separation movements, thereby driving the flexible solar wing 4 to extend longitudinally.

[0042] When the unfolding chamber 3 separates from the first fixed frame 21 and the second fixed frame 22, the second telescopic rod 23 of the first fixed frame 21 retracts, causing the first fixed frame 21 and the second fixed frame 22 to move towards each other.

[0043] The basic principle of this invention: like Figure 8 As shown, after satellite 1 enters orbit, the flipping component 11 drives the unfolding mechanism 2 to flip outwards from satellite 1; The driving component 214 drives the unfolding component 213 to rotate, causing the unfolding chamber 3 to flip outward. The end of the unfolding chamber 3 is no longer restricted, the elastic rod 215 extends, and multiple sets of unfolding chambers 3 separate. The top of the extension block 35 is no longer restricted, the elastic rod 352 extends, and multiple sets of extension blocks 35 separate, driving the flexible solar wing 4 to extend longitudinally. Drive component 332 drives lifting component 33 to move upward through drive rod 331. When lifting component 33 moves to its limit, the side of extension block 35 is unrestricted. Extension block 35 will flip under the action of torsion spring, thereby driving flexible solar wing 4 to unfold in a planar circular shape. The telescopic rod 23 of the first fixed frame 21 retracts, causing the first fixed frame 21 and the second fixed frame 22 to move towards each other; Among them, the driving component 214 can drive the unfolding component 213 to swing to a certain extent, so that the unfolded flexible solar wing 4 can better track the sun, thereby improving energy conversion efficiency. Among them, the second driving component 332 can drive the lifting component 33 to move downward. By controlling the side of the extension block 35 through the control ring 34, the torsion spring is compressed, causing the deployed flexible solar wing 4 to retract, effectively preventing the impact of space debris and preventing damage to the solar wing.

Claims

1. A flexible circular solar array deployment mechanism, installed in the storage compartment of a satellite (1), characterized in that, include: A flip-up component (11) is located on one side inside the storage compartment; Multiple sets of unfolding mechanisms (2), one end of which is connected to a flipping component (11). Each set of unfolding mechanisms (2) includes: a first fixed frame (21) and a second fixed frame (22); a second telescopic rod (23) connected between the first fixed frame (21) and the second fixed frame (22); a first telescopic plate (211) and a first telescopic component (212) for driving its extension and retraction, which are disposed on the first fixed frame (21); a second telescopic plate (221) and a second telescopic component (222) for driving its extension and retraction, which are disposed on the second fixed frame (22); a first driving component (214) disposed inside the first fixed frame (21); and an unfolding component (213) connected to the output end of the first driving component (214). Multiple sets of unfolding compartments (3) are interconnected by an elastic rod (215), and the elastic rod (215) is connected to the unfolding component (213); The unfolding compartment (3) includes: a base (31) and a compartment body (32); a lifting component (33) which is vertically and vertically disposed inside the compartment body (32); and a second driving component (332) which is connected to the lifting component (33) via a driving rod (331). Multiple extension blocks (35) are circumferentially hinged to the lifting component (33), and adjacent extension blocks (35) are connected by elastic rods (352); a control ring (34) is located above the chamber body (32); The flexible solar panel (4) is stacked in an arc shape between adjacent deployment compartments (3), and its bottom is connected to the lifting component (33); The flipping component (11) drives the unfolding mechanism (2) to flip through the telescopic rod (111) and the rotating component (112). The driving component (214) can drive multiple sets of unfolding chambers (3) to flip outward and separate through the unfolding component (213). The driving component (332) can drive the lifting component (33) to rise and fall, so that the extension block (35) unfolds or is restricted by the control ring (34) to retract, thereby driving the flexible solar wing (4) to unfold or retract in a circular shape.

2. The flexible circular solar array deployment mechanism according to claim 1, characterized in that, Multiple sets of the deployment mechanisms (2) are interconnected by hinges (24), which enable the interconnected deployment mechanisms (2) to generate relative flipping motion.

3. The flexible circular solar array deployment mechanism according to claim 1, characterized in that, The extension block (35) and the lifting member (33) are connected by a torsion spring. When the lifting member (33) rises to its limit position, the extension block (35) can flip outward and unfold under the action of the torsion spring. When the lifting member (33) descends, the side of the extension block (35) is restricted by the control ring (34), compresses the torsion spring, and flips and retracts towards the center.

4. The flexible circular solar array deployment mechanism according to claim 1, characterized in that, The last unfolding chamber (3) is provided with a rolling wheel (36) on its side wall. During the process of the unfolding chamber (3) being flipped outward, the rolling wheel (36) rolls along the inner wall of the second fixing frame (22).

5. The flexible circular solar array deployment mechanism according to claim 1, characterized in that, After the unfolding compartment (3) separates from the first fixed frame (21) and the second fixed frame (22), the second telescopic rod (23) retracts, causing the first fixed frame (21) and the second fixed frame (22) to move towards each other.

6. The flexible circular solar array deployment mechanism according to claim 1, characterized in that, The flexible solar wing (4) has multiple sets of flexible solar panels attached to its surface.

7. The flexible circular solar array deployment mechanism according to claim 1, characterized in that, The drive unit (214) can drive the unfolding unit (213) to swing, thereby enabling the unfolded flexible solar array (4) to track the sun.

8. The flexible circular solar array deployment mechanism according to claim 1, characterized in that, The end of the extension block (35) is provided with a clamping surface (351) for clamping and fixing the flexible solar panel (4).

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