Solar wing damage replacement apparatus

Abstract

This invention discloses a solar array damage replacement device, relating to the field of satellite solar array deployment technology. The device includes a satellite body, a flipping frame, a storage frame, a deployment frame, a reinforcement frame, a clamping component, a working solar array, and a spare solar array. The flipping frame is located on both sides of the satellite body and is used to drive the deployment of the storage frame. The storage frame contains a slidable deployment frame and an extendable reinforcement frame. The deployment frame has a working solar array, and the reinforcement frame has a fixing block and rotating wheels for guiding and driving the movement of the spare solar array. The clamping component is used to clamp and flip the spare solar array. This invention can supplement the solar array area and improve charging efficiency when energy is insufficient by flipping and deploying the spare solar array; it can also accurately transport and replace the damaged part of the spare solar array through the cooperation of the reinforcement frame and the clamping component when the working solar array is damaged, achieving rapid on-orbit replacement and improving the satellite's on-orbit survivability and mission reliability.

Description

Technical Field

[0001] This invention relates to the field of satellite solar panel deployment technology, and in particular to a solar panel damage replacement device. Background Technology

[0002] Solar arrays are the core components of a satellite's on-orbit operation. Their performance directly determines the satellite's mission cycle and payload capacity. Solar arrays have flexible oscillation and sun-tracking capabilities, which can maximize the capture of solar energy, improve photoelectric conversion efficiency, and adapt to the high-power energy needs of satellites.

[0003] However, in orbital environments with high density of space debris, such as low Earth orbit, although the solar array has improved its impact resistance through its independent deployment structure, it still cannot completely avoid collision damage from space debris, and there are still significant shortcomings in the current replacement technology for damaged solar arrays in orbit.

[0004] Therefore, there is an urgent need to develop a device that can be stored in orbit, deployed quickly, and used to replace damaged solar panels in order to improve the satellite's on-orbit survivability and mission reliability. Summary of the Invention

[0005] To address the aforementioned technical problems, the present invention aims to provide a solar array damage replacement device. This device integrates working and spare solar arrays by incorporating foldable deployment mechanisms on both sides of the satellite body, along with a transport and connection system consisting of a reinforcement frame, clamping components, and a drive assembly. This enables on-orbit deployment of the solar arrays, energy replenishment, and rapid replacement of damaged sections.

[0006] A solar panel damage replacement device includes: a satellite body, a flipping frame, a storage frame, a deployment frame, a reinforcement frame, a clamping component, a solar panel one, and a solar panel two.

[0007] The flipping frame is located on both sides of the satellite body, and has a rotating shaft and a flipping rod connected to the storage rack inside.

[0008] The storage rack is connected and folded to both sides of the satellite body via a hinge, and a solar panel is laid on it. The storage rack has a sliding unfolding frame inside.

[0009] The deployment frame is equipped with a solar panel, and a connector is located on the back of the solar panel.

[0010] The reinforcement frame is located inside both sides of the storage rack and can extend outward. It is equipped with a fixing block, a telescopic rod and a telescopic limiter.

[0011] The second solar wing is a spare solar wing. It has a connector on the back and control slots on both sides, with a rotating pad attached inside the control slots.

[0012] The clamping component is located below the unfolding frame and the storage frame, and is connected by a hinge pin 5. It is used to clamp and rotate the second solar panel.

[0013] Furthermore, the flipping rod is a telescopic structure, and the driving device is located inside the rotating shaft to drive the storage rack to unfold.

[0014] Furthermore, the deployment frame is equipped with a drive unit for rotating the solar array to adjust its angle to the sun.

[0015] Furthermore, the reinforcing frame is stacked and connected by hinge three and hinge four, and has a telescopic component at the end. The telescopic component is connected to the inside of the storage rack and is used to control the extension and retraction of the reinforcing frame.

[0016] Furthermore, the fixed block is provided with a positioning block and a rotating wheel. The rotating wheel is driven to rotate by a drive device located inside the fixed block, which is used to drive the solar panel along the reinforcement frame.

[0017] Furthermore, the second solar panel is connected to the first solar panel via the second connecting block on the clamping member, thereby achieving clamping and flipping.

[0018] Furthermore, the first connector and the second connector are mechanically locked by a snap-fit ​​or magnetic attraction, and are equipped with a hot-swappable electrical connector for power transmission.

[0019] Furthermore, each hinge shaft is equipped with a pre-compressed torsion spring and an explosive bolt for locking the launch section. After the satellite enters orbit, the explosive bolt is unlocked, and the torsion spring releases energy to drive the assembly to automatically deploy.

[0020] Furthermore, the second solar panel can be flipped to a position parallel to the first solar panel in the energy replenishment mode to increase the total area of ​​the solar panels and improve charging efficiency.

[0021] Furthermore, when solar panel one is damaged, solar panel two can move along the reinforcement frame to the damaged location, connect to solar panel one via a connector, and replace its function.

[0022] Beneficial technical effects of the present invention: 1. When the satellite's energy supply is insufficient, the present invention can flip the spare solar array to a position parallel to the working solar array, increasing the overall deployment area of ​​the solar array, thereby enhancing the satellite's energy charging effect and improving energy collection efficiency; 2. The device of the present invention is equipped with a spare solar array. When the working solar array is damaged, the spare solar array can be accurately transported to the damaged location through the cooperation of the reinforcement frame, clamping parts and other structures, and then connected and replaced through the connector, so as to realize the rapid replacement of the damaged solar array and solve the problem of difficult follow-up treatment of damaged solar arrays in orbit. Attached Figure Description

[0023] 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...

[0024] Figure 1 This is a schematic diagram of the overall invention.

[0025] Figure 2 This is a schematic diagram of the assembly of the storage rack of the present invention.

[0026] Figure 3 This is a schematic diagram of the storage rack of the present invention.

[0027] Figure 4 This is a schematic diagram of the assembly of the unfolding frame of the present invention.

[0028] Figure 5 This is a schematic diagram of the mounting bracket assembly of the present invention.

[0029] Figure 6 This is a schematic diagram of the two-position structure of the solar array of the present invention.

[0030] Figure 7 This is a schematic diagram of the unfolding mechanism of the present invention in its unfolded state.

[0031] Figure 8 This is a schematic diagram of the orbital deployment of the present invention.

[0032] In the image, 1. The satellite itself; 2. Tilting frame; 21. Rotating shaft; 22. Tilting rod; 3. Storage rack; 31. Solar panel; 32. Hinge pin one; 4. Deployment frame; 41. Drive unit; 42. Hinge shaft II; 43. Limiting block; 44. Movable locking block; 5. Solar panel one; 51. Connector one; 6. Reinforcing frame; 61. Fixing block; 611. Positioning block; 612. Rotating wheel; 62. Telescopic rod; 63. Telescopic limiting component; 631. Limiting groove; 64. Telescopic component; 65. Hinge shaft three; 66. Hinge shaft four; 7. Solar fin II; 71. Connector II; 72. Connector I; 73. Control slot; 731. Rotating pad; 8. Clamping component one; 81. Hinge shaft five; 82. Connecting block three. Detailed Implementation

[0033] 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.

[0034] like Figure 1 As shown, a solar panel damage replacement device has a flip frame 2 on both sides of the satellite body 1. The flip frame 2 has a rotatable rotating shaft 21 inside. One end of the rotating shaft 21 is connected to a storage frame 3 through a flip rod 22. The flip rod 22 is a telescopic rod structure. The driving device is set inside the rotating shaft 21. Multiple sets of the storage frames 3 are folded and stored on both sides of the satellite body 1.

[0035] like Figure 2 As shown, adjacent storage racks 3 are connected by hinge shaft 32, and the two sets of fan blades of hinge shaft 32 are connected to the two sets of storage racks 3 respectively.

[0036] Each of the storage racks 3 is provided with multiple sets of unfolding racks 4 that are folded, and each unfolding rack 4 is provided with a solar panel 5.

[0037] like Figure 3 As shown, the upper surface of the storage rack 3 is covered with a solar panel 31, and the folded unfolding rack 4 can slide on both sides of the storage rack 3. The inner walls on both sides of the storage rack 3 are provided with grooves for sliding and limiting the movement. The first driving device for controlling the movement of the unfolding rack 4 is provided in the inner walls on both sides of the storage rack 3.

[0038] The storage rack 3 has reinforcing frames 6 inside on both sides, and the reinforcing frames 6 can extend outwards from the storage rack 3.

[0039] The unfolding frame 4 is equipped with a solar panel 5, and a block-shaped connector 51 is provided on the back of the solar panel 5.

[0040] like Figure 4 As shown, movable locking blocks 44 are provided on both sides of the unfolding frame 4 at the connected end. The movable locking blocks 44 can slide and be limited inside the reserved groove on the inner wall of the storage rack 3. At the same time, a second driving device is provided inside the reserved groove to push the unfolding frame 4 to move. A solar wing 5 is provided in the middle of the unfolding frame 4. The two sides of the solar wing 5 are connected to the driving component 41 on the unfolding frame 4. The driving component 41 can drive the solar wing 5 to perform a certain degree of rotation movement, thereby adjusting the solar angle of the solar wing 5.

[0041] A clamping member 8 is provided on the other end of the unfolding frame 4 in the connected state. The clamping member 8 is connected by a hinge shaft 81. The clamping member 8 can rotate on the unfolding frame 4. A connecting block 82 is provided on the other end of the clamping member 8.

[0042] like Figure 5As shown, the reinforcing frame 6 is stacked and connected by hinge shaft three 65 and hinge shaft four 66. One end of the last reinforcing frame 6 is provided with a telescopic component 64. The other end of the telescopic component 64 is connected to the inside of the storage rack 3 through a preset telescopic shaft. The extension and retraction of the telescopic component 64 can cause the reinforcing frame 6 to extend or retract as a whole.

[0043] The reinforcement frame 6 is provided with a fixing block 61. A rectangular protruding positioning block 611 is provided on one side of the fixing block 61. A rotating wheel 612 is provided between the two positioning blocks 611. The third driving device of the rotating wheel 612 is provided inside the fixing block 61, which can drive the rotating wheel 612 to rotate. The other side of the fixing block 61 is connected to the reinforcement frame 6 through a telescopic rod 62. The fourth driving mechanism that controls the extension and retraction of the telescopic rod 62 is provided inside the reinforcement frame 6.

[0044] The reinforcing frame 6 is provided with a telescopic limiting member 63, and a spring is provided at the bottom of the telescopic limiting member 63. When the reinforcing frame 6 is stacked, the telescopic limiting rods 63 are pressed against each other and are in a contracted state, and the spring is compressed. When the reinforcing frame 6 is unfolded, the telescopic limiting rods 63 are extended under the action of the spring. The telescopic limiting member 63 is provided with a groove-shaped limiting groove 631.

[0045] In the unfolded state, the last set of reinforcing frames 6 and its adjacent reinforcing frames 6 are unfolded laterally, while the remaining sets are unfolded longitudinally.

[0046] like Figure 6 As shown, clamping parts 8 are also installed on both sides of the lower part of the storage rack 3. The clamping parts 8 are connected by hinge pin 81. The other end of the clamping parts 8 is connected to the second solar wing 7. The second solar wing 7 is a spare solar wing. The back of the second solar wing 7 is provided with a connector 71. The connector 71 can be connected to the connector 51 on the first solar wing 5.

[0047] A connecting block 72 is provided on one side of the second solar wing 7. The connecting block 72 can be connected to the connecting block 82 on the clamping member 8, so that the two sets of clamping members 8 can clamp the second solar wing 7 respectively.

[0048] On the other two sides of the second solar panel 7, there are rectangular groove-shaped control slots 73, which can cooperate with the positioning block 611 of the fixing block 61 for guidance. A rotating pad 731 is attached inside the control slot 73 to increase the friction between it and the rotating wheel 612. When the rotating wheel 612 rotates, it can drive the second solar panel 7 to move along the reinforcing frame 6 through friction.

[0049] Each hinge (32, 42, 65, 66, 81) is equipped with a pre-compressed torsion spring and an explosive bolt for locking the launch phase. After the satellite enters orbit, the explosive bolt is unlocked according to the command, the torsion spring releases energy, and drives the corresponding component to automatically deploy.

[0050] Working principle of the invention: 1. Orbital deployment process: like Figure 8 As shown, when the satellite body 1 enters the orbit, the rotating shaft 21 inside the flipping frame 2 rotates 90 degrees, thereby causing the folded storage frame 3 to unfold outward, and the flipping rod 22 extends, driving the storage frame 3 to extend outward, providing space for subsequent unfolding; The hinge 32 drives the folded storage rack 3 to unfold; The telescopic shaft at the end of the telescopic component 64 extends, thereby causing the reinforcing frame 6 to extend out of the storage frame 3. The hinge shaft three 65 and the hinge shaft four 66 drive the reinforcing frame 6 to fully unfold, and the telescopic limiting component 63 on the reinforcing frame 6 loses its restriction and extends. The folded unfolding frame 4 moves toward both sides of the storage rack 3, exposing the sun panel 31 on the storage rack 3, and the limiting block 43 at the bottom of the unfolding frame 4 enters the limiting groove 631 of the telescopic limiting member 63. The folded unfolding frame 4 unfolds under the control of the hinge shaft 42. After unfolding, the limiting blocks 43 of each set of unfolding frames 4 enter the limiting grooves 631 of the telescopic limiting member 63, thereby limiting and reinforcing the unfolding frame 4 and enhancing its impact resistance. 2. Energy Supplementation Mode: like Figure 7 As shown, the telescopic rod 62 of the end reinforcement frame 6 retracts, the fixing block 61 retracts into the reinforcement frame 6, the hinge shaft 81 drives the clamping part 8 at the bottom of the storage frame 3 to flip, and drives the second solar wing 7 to flip to the bottom of the unfolding frame 4. Then the telescopic rod 62 extends, the fixing block 61 returns to its original position, the positioning block 611 of the fixing block 61 and the rotating wheel 612 enter the control groove 73 of the second solar wing 7. The rotating wheel 612 rotates and rubs against the rotating pad 731 to drive the second solar wing 7 to move outward until the second solar wing 7 contacts the clamping part 8 at the end of the unfolding frame 4. The connecting block 82 of the clamping part 8 is combined with the connecting block 72 on the second solar wing 7. The hinge shaft 81 drives the clamping part 8 at the end of the unfolding frame 4 to flip, so that the second solar wing 7 flips to be parallel to the first solar wing 5, increasing the light absorption area of ​​the solar wing and strengthening the charging. The connection between the solar wing 2 7 and the clamping part 8, the connecting block 1 72 and the connecting block 2 82, are provided with corresponding interfaces, which can transfer the electrical energy absorbed by the solar wing 2 7 to the device body. 3. Damage Replacement Mode: When the deployed solar panel 5 is damaged, the fixing block 61 of the deployed reinforcement frame 6 closest to the storage frame 3 retracts inward, and the telescopic rod 62 retracts. The clamping parts 8 on both sides below the storage rack 3 carry the second solar wing 7 to fold, so that the second solar wing 7 is parallel to the fixed frame 6. The retracted fixed block 61 returns to its original position. The positioning block 611 of the fixed block engages with the control groove 73 of the second solar wing 7 to limit the second solar wing 7. The rotating wheel 612 rotates and, through friction with the rotating pad 731, carries the second solar wing 7 along the fixed frame 6 until the second solar wing 7 moves to the bottom of the damaged first solar wing 5. The second connecting part 71 of the second solar wing 7 connects with the first connecting part 51 of the first solar wing 5. Drive frame 41 drives the damaged solar panel 1 5 to rotate 180 degrees, so that solar panel 2 7 can rotate to the front and replace solar panel 1 5 to work. Connector 1 51 and connector 2 71 are mechanically locked together by snap-fit ​​or magnetic attraction and are equipped with a hot-swappable electrical connector, so that the electrical energy converted by solar panel 2 7 can be transmitted to the inside of the equipment.

Claims

1. A solar panel damage replacement device, characterized in that, include: Satellite body (1), flip frame (2), storage frame (3), unfolding frame (4), reinforcement frame (6), clamping parts (8), solar wing one (5) and solar wing two (7); The flipping frame (2) is located on both sides of the satellite body (1), and has a rotating shaft (21) and a flipping rod (22) connected to the storage rack (3) inside. The storage rack (3) is connected and folded on both sides of the satellite body (1) via a hinge (32), and a solar panel (31) is laid on it. The storage rack (3) has a sliding unfolding rack (4) inside. The unfolding frame (4) is provided with a solar wing (5), and a connector (51) is provided on the back of the solar wing (5). The reinforcing frame (6) is located inside both sides of the storage rack (3) and can extend outward. It is equipped with a fixing block (61), a telescopic rod (62) and a telescopic limiting member (63). The second solar wing (7) is a spare solar wing. It has a connector (71) on the back and control slots (73) on both sides. A rotating pad (731) is attached inside the control slot (73). The clamping member (8) is located below the unfolding frame (4) and the storage frame (3) and is connected by the hinge five (81) for clamping and flipping the second solar wing (7).

2. The solar panel damage replacement device according to claim 1, characterized in that, The flipping rod (22) is a telescopic structure, and the driving device is located inside the rotating shaft (21) to drive the storage rack (3) to unfold.

3. The solar panel damage replacement device according to claim 1, characterized in that, The unfolding frame (4) is equipped with a drive unit (41) for driving the solar wing (5) to rotate to adjust the angle to the sun.

4. The solar panel damage replacement device according to claim 1, characterized in that, The reinforcing frame (6) is stacked and connected by hinge three (65) and hinge four (66), and a telescopic component (64) is provided at the end. The telescopic component (64) is connected to the inside of the storage rack (3) and is used to control the extension and retraction of the reinforcing frame (6).

5. The solar panel damage replacement device according to claim 1, characterized in that, The fixed block (61) is provided with a positioning block (611) and a rotating wheel (612). The rotating wheel (612) is driven to rotate by a driving device located inside the fixed block (61) to drive the second solar panel (7) to move along the reinforcing frame (6).

6. The solar panel damage replacement device according to claim 1, characterized in that, The second solar wing (7) is connected to the first solar wing (7) via the second connecting block (82) on the clamping member (8) to achieve clamping and flipping.

7. The solar panel damage replacement device according to claim 1, characterized in that, The first connector (51) and the second connector (71) are mechanically locked by snap-fit ​​or magnetic attraction, and are equipped with hot-swappable electrical connectors for power transmission.

8. The solar panel damage replacement device according to claim 1, characterized in that, Each hinge shaft (32, 42, 65, 66, 81) is equipped with a pre-compressed torsion spring and an explosive bolt for locking the launch section. After the satellite enters orbit, the explosive bolt is unlocked, and the torsion spring releases energy to drive the assembly to automatically deploy.

9. The solar panel damage replacement device according to claim 1, characterized in that, The second solar panel (7) can be flipped to a position parallel to the first solar panel (5) in the energy replenishment mode to increase the total area of ​​the solar panel and improve the charging efficiency.

10. The solar panel damage replacement device according to claim 1, characterized in that, When solar wing one (5) is damaged, solar wing two (7) can move along the reinforcement frame (6) to the damaged position, connect with solar wing one (5) through the connector and replace its function.

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