Twilight orbit computing satellite and its super large deployable concentrating solar wing structure

Abstract

A dawn-dusk orbit computing satellite and its ultra-large deployable concentrating solar array structure belong to the field of spacecraft power system technology. It includes: a clamping and releasing assembly and a first solar array and a second solar array respectively disposed on both sides of the satellite body; both the first and second solar arrays include concentrating solar panels; the concentrating solar panels include a frame structure and multiple sets of concentrating solar cell arrays disposed on the frame structure, each set of concentrating solar cell arrays including multiple concentrating solar cell units; the second solar array is folded onto the satellite body via a deployment hinge, and the first solar array is folded onto the second solar array via a deployment hinge; the clamping and releasing assembly locks the first solar array, the second solar array, and the satellite body together, and after unlocking, allows the first and second solar arrays to deploy automatically via the deployment hinges. This utility model's solar array structure can meet the power supply requirements of computing satellites.

Description

Technical Field

[0001] This utility model relates to the field of spacecraft power system technology, specifically to a dawn-dusk orbit computing satellite and its ultra-large deployable concentrating solar array structure. Background Technology

[0002] The dawn-dusk orbit computing satellite is an ultra-high-performance integrated computing platform deployed in outer space. It can provide services such as data storage and computation, AI inference and decision-making. Its ability to perform complex calculations in orbit effectively reduces latency and potential data loss caused by space-to-ground communication bandwidth bottlenecks, greatly improving computing efficiency and quality.

[0003] Furthermore, dawn-dusk orbit computing satellites offer advantages in energy, environmental protection, and operational environment stability. The space environment provides uninterrupted solar energy resources, and satellites operating in dawn-dusk orbits can obtain a continuous and inexhaustible supply of clean energy. Compared to traditional ground-based data centers, dawn-dusk orbit computing satellites have higher energy efficiency and lower operating costs. In addition, the extremely cold environment in space facilitates efficient heat dissipation for the satellites, not only contributing to energy conservation and consumption reduction but also effectively reducing the Earth's heat load, fully leveraging their environmental advantages. Finally, the absence of weather variations, humidity fluctuations, and dust in space provides a stable operating environment for computing equipment.

[0004] Currently, research on computing satellites in dawn-dusk orbits is in its early stages, with many countries still in the design phase. Existing designs typically employ traditional non-concentrating triple-junction gallium arsenide solar arrays, requiring large solar panels to meet power demands, resulting in high material costs. Furthermore, the large solar panel area leads to excessive structural weight and low energy density in the solar arrays, significantly increasing rocket launch costs. These issues make conventional designs insufficient to meet the requirements of low cost and high energy-to-mass ratio (W / kg) for dawn-dusk orbit computing satellites. Utility Model Content

[0005] This invention provides a computing satellite in a dawn-dusk orbit that can meet power supply requirements and its ultra-large deployable concentrating solar array structure.

[0006] As a first aspect of this utility model, an ultra-large deployable concentrating solar array structure for a dawn-dusk orbit computing satellite is provided, comprising: a clamping and releasing assembly and a first solar array and a second solar array respectively disposed on both sides of the satellite body; the first solar array and the second solar array each include two or more concentrating solar panels connected by a deploying hinge; the concentrating solar panel includes a frame structure and multiple sets of concentrating solar cell arrays disposed on the frame structure, each set of concentrating solar cell arrays including multiple concentrating solar cell units; the second solar array is folded onto the satellite body by a deploying hinge, and the first solar array is folded onto the second solar array by a deploying hinge; the clamping and releasing assembly locks the first solar array, the second solar array, and the satellite body together as one unit, and after unlocking, the first solar array and the second solar array deploy automatically by the deploying hinge.

[0007] The clamping release assembly includes a fixed cylinder, a positioning cylinder, a spring, a long screw, and a release nut. The fixed cylinder is fixedly mounted on the outermost concentrating solar panel of the first solar wing, and the positioning cylinders are mounted on the other concentrating solar panels. After the first and second solar wings are folded, the fixed cylinder and the positioning cylinder are connected in sequence to form a cylindrical structure. The long screw passes through the cylindrical structure and is connected to a puller to lock the first and second solar wings. The spring is mounted on the fixed cylinder and provides elastic force to the long screw away from the release nut. After the long screw separates from the release nut, it disengages from each positioning cylinder under the elastic force of the spring to unlock.

[0008] The separating nut includes a shape memory alloy puller connected to a long screw.

[0009] The positioning cylinder has a conical recess and a truncated cone at both ends, and the conical recess and truncated cone of the adjacent positioning cylinder cooperate with each other.

[0010] The long screw has a plug at its end, the spring is fitted on the long screw and located inside the fixed cylinder, and the fixed cylinder has a truncated cone at its end that engages with the conical recess of the positioning cylinder.

[0011] The concentrating solar panel has dimensions of 2.048m × 2.048m and a tolerance of ±2mm.

[0012] The first solar array and the second solar array each include two concentrating solar panels.

[0013] The concentrating solar panel is equipped with 4×4 groups of concentrating solar cell arrays, and each group of concentrating solar cell arrays includes 5×5 concentrating solar cell units.

[0014] The frame structure includes multiple thin-walled carbon fiber tubes arranged longitudinally and laterally.

[0015] As a second aspect of this utility model, a dawn-dusk orbit computing satellite is also provided, including the satellite body and the ultra-large deployable concentrating solar array structure as described above.

[0016] Based on the above scheme, it can be seen that the dawn-dusk orbit computing satellite and its ultra-large deployable concentrating solar array structure of this utility model have at least one of the following beneficial effects compared with the prior art: This invention relates to an ultra-large deployable concentrating solar array structure for a dawn-dusk orbit computing satellite. By installing multiple concentrating solar panels on both sides of the satellite body and effectively folding them onto the satellite body, the overall space occupied can be greatly saved. Furthermore, after deployment, the concentrating solar panels can generate electricity efficiently. This ultra-large deployable concentrating solar array structure can support continuous high-power power supply for dawn-dusk orbit computing satellites, providing a basic energy architecture for computing satellites and meeting their power supply requirements. Attached Figure Description

[0017] To more clearly illustrate the technical solution of this utility model, the accompanying drawings used in the embodiments will be briefly introduced below.

[0018] Figure 1 This is a schematic diagram of the ultra-large deployable concentrating solar wing structure of this utility model; Figure 2 This is a schematic diagram of the folded state of an ultra-large deployable concentrating solar array structure. Figure 3 A schematic diagram of a single solar panel; Figure 4 This is a schematic diagram of a concentrating solar cell array; Figure 5 This is a schematic diagram of the compression release assembly; Figure 6 A partial view of the compress-release component; Figure 7 A schematic diagram for unfolding the hinge; Figure 8 A schematic diagram of the clamping rod after the solar panel is deployed; Figure 9 A schematic diagram showing the installation position of the unfolding hinge.

[0019] In the above figures, the meanings of the reference numerals are as follows: In the diagram: 1. First solar panel; 2. Second solar panel; 3. Concentrating solar panel; 31. Concentrating solar cell array; 32. Concentrating solar cell unit; 321. Primary mirror; 322. Secondary mirror; 323. Secondary mirror support; 324. Light funnel; 33. Frame structure; 4. Deployment hinge; 51. Fixing cylinder; 52. Positioning cylinder; 53. Spring; 54. Long screw; 55. Separation nut; 56. Positioning point; 10. Satellite body. Detailed Implementation

[0020] To better understand the technical solutions of the embodiments of this utility model, the embodiments of this utility model will be described in detail below with reference to the accompanying drawings.

[0021] It should be understood that the described embodiments are merely some embodiments of this utility model, and not all embodiments. All other embodiments obtained by those skilled in the art based on the embodiments of this utility model without creative effort are within the protection scope of this utility model.

[0022] like Figures 1 to 9 As shown in the figure, this utility model embodiment discloses an ultra-large deployable concentrating solar array structure for a dawn-dusk orbit computing satellite, including a compression release assembly and a first solar array 1 and a second solar array 2 respectively disposed on both sides of the satellite body 10.

[0023] like Figure 1 As shown, the extension directions of the first solar wing 1 and the second solar wing 2 are referred to as the +X axis direction and the -X axis direction, respectively.

[0024] The first solar panel 1 and the second solar panel 2 each include two or more concentrating solar panels 3 connected by deployment hinges 4.

[0025] The concentrating solar panel 3 includes a frame structure 33 and multiple concentrating solar cell arrays 31 disposed on the frame structure 33. Each concentrating solar cell array 31 includes multiple concentrating solar cell units 32. When folded, the second solar wing 2 is folded onto the satellite body 10 via the deployment hinge 4, and the first solar wing 1 is folded onto the second solar wing 2 via the deployment hinge 4.

[0026] In other words, the two concentrating solar panels 3 or the concentrating solar panel 3 and the satellite body 10 are connected by a deployable hinge 4, the structure of which is as follows: Figure 7 As shown, this is an existing technology applied to satellites. The unfolding hinge 4 has an unfolding angle of 180° and an unfolding accuracy of ≤±0.1°.

[0027] The compression release assembly locks the first solar array 1, the second solar array 2, and the satellite body 10 together as one unit, and after unlocking, the first solar array 1 and the second solar array 2 are automatically deployed by the deployment hinge 4.

[0028] The ultra-large deployable concentrating solar array structure for a dawn-dusk orbit computing satellite of this utility model can install multiple concentrating solar panels 3 on both sides of the satellite body 10 and effectively fold them onto the satellite body 10. This can greatly save the overall space occupied, and after deployment, it can generate electricity efficiently through the concentrating solar panels 3. The overall structure is simple and compact. This ultra-large deployable concentrating solar array structure can provide a basic energy architecture for computing satellites and meet the power supply requirements of computing satellites.

[0029] In this embodiment, the frame structure 33 includes multiple thin-walled carbon fiber tubes arranged longitudinally and laterally. These thin-walled carbon fiber tubes are lightweight, high-strength, and have a long service life, which can meet the weight reduction requirements of the concentrating solar panel 3.

[0030] The first solar wing 1 and the second solar wing 2 of this invention both include two concentrating solar panels 3. In other embodiments, the number of concentrating solar panels 3 may also be three or other numbers, and the number of concentrating solar panels 3 in the first solar wing 1 and the second solar wing 2 may also be different.

[0031] In this embodiment, the first solar panel 1 and the second solar panel 2 have identical structures. The concentrating solar panel 3 has dimensions of 2.048m × 2.048m, with a tolerance of ±2mm. Figure 3 and Figure 4 As shown, the concentrating solar panel 3 is provided with 4×4 groups of concentrating solar cell arrays 31, and each group of concentrating solar cell arrays 31 includes 5×5 concentrating solar cell units 32. Each concentrating solar cell unit 32 includes a primary mirror 321, a secondary mirror 322, a secondary mirror support 323, and a light funnel 324.

[0032] like Figure 5 and Figure 6 As shown, the clamping release assembly includes a fixed cylinder 51, a positioning cylinder 52, a spring 53, a long screw 54, and a release nut 55. The fixed cylinder 51 is fixedly mounted on the outermost concentrating solar panel 3 of the first solar wing 1. Positioning cylinders 52 are mounted on the other concentrating solar panels 3. After the first solar wing 1 and the second solar wing 2 are folded, the fixed cylinder 51 and the positioning cylinders 52 are sequentially connected to form a cylindrical structure. The long screw 54 passes through the cylindrical structure and connects to a puller to lock the first solar wing 1 and the second solar wing 2. The spring 53 is located in the fixed cylinder 51 and provides a spring force to the long screw 54 away from the release nut 55. After the long screw 54 separates from the release nut 55, it disengages from each positioning cylinder 52 under the spring force of the spring 53 to achieve unlocking. Figure 8 As shown, after the long screw 54 separates from the positioning cylinder 52, the long screw 54 remaining on the outermost side of the first solar wing 1 will be limited by the fixing cylinder 51 and stay on the fixing cylinder 51, and will not detach from the fixing cylinder 51.

[0033] In this embodiment, the release nut 55 includes a shape memory alloy puller connected to the long screw 54, which enables unlocking without fire and is safer to use.

[0034] The two ends of the positioning cylinder 52 are respectively provided with a conical recess and a truncated cone. The conical recess and the truncated cone of the adjacent positioning cylinder cooperate to achieve a more stable positioning connection and prevent misalignment.

[0035] The end of the long screw 54 is provided with a plug, and the spring 53 is fitted onto the long screw 54 and located inside the fixed cylinder 51. The end of the fixed cylinder 51 is provided with a truncated cone that mates with the conical recess of the positioning cylinder 52. This allows for a compact connection between the spring 53, the long screw 54, and the fixed cylinder 51, saving space.

[0036] Depend on Figure 1 It is known that a radial cooling plate 11 is also connected to the satellite body 10. The radial cooling plate 11 can be folded onto the satellite body 10 together with the first solar array 1 and the second solar array 2, and locked together as one unit by the clamping and releasing assembly. After the clamping and releasing assembly is unlocked, the first solar array 1, the second solar array 2 and the radial cooling plate 11 unfold to perform their functions.

[0037] This embodiment also discloses a dawn-dusk orbit computing satellite, including the satellite body and the aforementioned ultra-large deployable solar array structure.

[0038] The computing satellite in the dawn-dusk orbit of this invention can ensure sufficient power through an ultra-large deployable concentrating solar array structure.

[0039] The above description is only a preferred embodiment of the present utility model and is not intended to limit the present utility model. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present utility model should be included within the protection scope of the present utility model.

Claims

1. A super-large deployable concentrating solar array structure for a dawn-dusk orbit computing satellite, characterized in that, include: The system includes a clamping and releasing assembly and a first solar panel and a second solar panel respectively disposed on both sides of the satellite body. Each of the first and second solar panels includes two or more concentrating solar panels connected by a deployable hinge. Each concentrating solar panel includes a frame structure and multiple sets of concentrating solar cell arrays disposed on the frame structure, each set of concentrating solar cell arrays including multiple concentrating solar cell units. The second solar panel is folded onto the satellite body via the deployable hinge, and the first solar panel is folded onto the second solar panel via the deployable hinge. The clamping and releasing assembly locks the first solar panel, the second solar panel, and the satellite body together as a single unit, and upon unlocking, allows the first and second solar panels to deploy automatically via the deployable hinge.

2. The ultra-large deployable concentrating solar array structure for a dawn-dusk orbit computing satellite according to claim 1, characterized in that, The clamping release assembly includes a fixed cylinder, a positioning cylinder, a spring, a long screw, and a release nut. The fixed cylinder is fixedly mounted on the outermost concentrating solar panel of the first solar wing, and the positioning cylinders are mounted on the other concentrating solar panels. After the first and second solar wings are folded, the fixed cylinder and the positioning cylinder are connected in sequence to form a cylindrical structure. The long screw passes through the cylindrical structure and is connected to a puller to lock the first and second solar wings. The spring is mounted on the fixed cylinder and provides elastic force to the long screw away from the release nut. After the long screw separates from the release nut, it disengages from each positioning cylinder under the elastic force of the spring to unlock.

3. The ultra-large deployable concentrating solar array structure for a dawn-dusk orbit computing satellite according to claim 2, characterized in that, The release nut includes a shape memory alloy puller connected to a long screw.

4. The ultra-large deployable concentrating solar array structure for a dawn-dusk orbit computing satellite according to claim 2, characterized in that, The positioning cylinder has a conical recess and a truncated cone at both ends, and the conical recess and truncated cone of the adjacent positioning cylinder cooperate with each other.

5. The ultra-large deployable concentrating solar array structure for a dawn-dusk orbit computing satellite according to claim 4, characterized in that, The end of the long screw is provided with a plug, the spring is fitted on the long screw and located inside the fixed cylinder, and the end of the fixed cylinder is provided with a truncated cone that mates with the conical recess of the positioning cylinder.

6. The ultra-large deployable concentrating solar array structure for a dawn-dusk orbit computing satellite according to claim 1, characterized in that, The concentrating solar panel has dimensions of 2.048m × 2.048m and a tolerance of ±2mm.

7. The ultra-large deployable concentrating solar array structure for a dawn-dusk orbit computing satellite according to claim 1, characterized in that, Both the first and second solar panels include two concentrating solar panels.

8. The ultra-large deployable concentrating solar array structure for a dawn-dusk orbit computing satellite according to claim 1, characterized in that, The concentrating solar panel is equipped with 4×4 groups of concentrating solar cell arrays, and each group of concentrating solar cell arrays includes 5×5 concentrating solar cell units.

9. The ultra-large deployable concentrating solar array structure for a dawn-dusk orbit computing satellite according to claim 1, characterized in that, The frame structure comprises multiple thin-walled carbon fiber tubes arranged longitudinally and laterally.

10. A computing satellite in a dawn-dusk orbit, comprising a satellite body, characterized in that, It also includes an ultra-large deployable concentrating solar array structure as described in any one of claims 1 to 9.

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