Satellite thermal control method and two-dimensional driven solar wing

Abstract

This invention relates to a thermal control method for a flat-panel satellite and a two-dimensional driven solar array, including obtaining the length and width dimensions L0 and B0 of the flat-panel satellite, the height distance H between the solar array and the satellite platform after on-orbit deployment, the length and width dimensions L1 and B1 of the solar array substrate, the number of solar array substrates on one side n, and the horizontal distance d of the solar array substrate on one side from the A-axis; obtaining the orbital inclination angle i of the flat-panel satellite, calculating and analyzing the range of the solar illumination angle β of the flat-panel satellite orbit; and calculating and analyzing the instantaneous temperature T of the solar array at the synoptic point position under different solar illumination angles β. t ; Calculate and analyze the solar array at different instantaneous temperatures T t The infrared radiation intensity Q of the solar panel substrate at different locations on the upward-facing heat dissipation surface of the flat-panel satellite. i Total infrared radiation intensity Q total Apply a low infrared emissivity thermal control coating to the back of the first substrate to the i-th substrate from the middle position on both sides of the solar array; increase the horizontal distance d from the A-axis on both sides of the solar array to d+dΔ.

Description

Technical Field

[0001] This invention relates to the field of spacecraft thermal control technology, and more specifically, to a flat-panel satellite thermal control method and a two-dimensional driven solar array. Background Technology

[0002] Large-scale satellite constellations often employ a flat-panel satellite configuration, which facilitates stacked launch layouts and improves launch efficiency. The flat-panel configuration results in a flat, hexahedral structure for the satellite. As a three-axis stabilized, Earth-oriented flat-panel satellite, its upward-facing surface has the largest area relative to the ground, serving as an effective heat dissipation surface, while the surrounding surfaces are relatively small. When the satellite carries a large external Earth-pointing payload, the payload severely obstructs heat dissipation from the ground. For low-Earth orbit satellites, the Earth's infrared radiation over a long period results in a significant average absorption of external heat flux. Since the upward-facing surface is directly exposed to the cold space and not directly exposed to sunlight for most of the time, the upward-facing surface of a flat-panel satellite becomes the optimal heat dissipation surface.

[0003] To achieve concentrated coverage in low- and mid-latitude regions and enable high-frequency revisits to specific areas, low-Earth orbit (LEO) satellite constellations are often designed in inclined orbits. However, due to the significant annual variation in solar illumination angles in inclined orbits, traditional one-dimensional drive methods cannot guarantee that the effective area of ​​the solar array will meet the satellite's energy requirements throughout its entire lifecycle. A two-dimensional drive method can effectively solve the problem of solar cell orientation in inclined orbits. To minimize the rotational inertia after satellite deployment, the two-dimensional drive solar array is positioned above the upward-facing surface of the flat-panel satellite. Its drive mechanism's A-axis is parallel to the satellite's Z-axis, and its B-axis is perpendicular to the A-axis, ensuring efficient solar array orientation throughout the satellite's entire lifecycle.

[0004] After the solar panels deploy in orbit, they are positioned above the sun-facing surface of the flat-panel satellite. When the satellite is in the sunlit area, the two-dimensional drive mechanism can theoretically ensure that the solar panels are perfectly perpendicular to the sun. At this time, the temperature of the solar cell circuitry rapidly rises to the level of 100°C due to solar radiation and remains high in the sunlit area. This high temperature from the solar panels generates infrared radiation heat flow, which is transferred to the main heat dissipation surface of the flat-panel satellite. The infrared radiation intensity from the high temperature of the solar panels can reach 1000 W / m² when the satellite reaches the synoptic point. 2 This causes serious contamination to the heat dissipation surface of flat-panel satellites.

[0005] The preceding description is intended to provide general background information and does not necessarily constitute prior art. Summary of the Invention

[0006] The purpose of this invention is to provide a thermal control method for flat-panel satellites and a two-dimensional driven solar array. This thermal control method reduces the infrared radiation from the solar array to the main heat dissipation surface of the flat-panel satellite in the illuminated area.

[0007] This invention provides a thermal control method for a flat-panel satellite, the thermal control method comprising the following steps:

[0008] S1: Obtain the length and width dimensions L0 and B0 of the flat-panel satellite, obtain the height distance H between the solar array and the satellite platform after it is deployed in orbit, obtain the length and width dimensions L1 and B1 of the solar array substrate, obtain the number of solar array substrates on one side n, and obtain the horizontal distance d between the solar array substrate on one side and the drive mechanism A-axis. The drive mechanism A-axis is parallel to the satellite +Z direction, where the satellite +Z direction is directly above the plane of the flat-panel satellite.

[0009] S2: Obtain the orbital inclination angle i of the flat-panel satellite and calculate and analyze the range of the solar illumination angle β of the flat-panel satellite orbit;

[0010] S3: Calculate and analyze the instantaneous temperature T of the solar array at the synodic point under different solar illumination angles β. t Alternatively, calculate and analyze the equilibrium temperature T of the solar array at different solar illumination angles β and at the synodic point. s ;

[0011] S4: Calculation and analysis of the solar array at different instantaneous temperatures T t Or equilibrium temperature T s Below, the infrared radiation intensity Q of the solar panel substrate at different locations on the upward-facing heat dissipation surface of the flat-panel satellite is measured. i The total infrared radiation intensity Q of all solar panel substrates on the upward-facing heat dissipation surface of the flat-panel satellite. total ;

[0012] S5: Apply a low infrared emissivity thermal control coating to the back of the first substrate from the middle position to the i-th substrate on both sides of the solar array;

[0013] S6: Repeat steps S1-S4 to calculate the infrared radiation intensity of the solar panel substrate on the upward-facing heat dissipation surface of the flat-panel satellite, and evaluate the degree of reduction in the infrared radiation intensity of the solar panel substrate on the upward-facing heat dissipation surface of the flat-panel satellite.

[0014] S7: Increase the horizontal distance d from the A-axis of the drive mechanism on both sides of the solar panels to d+Δd;

[0015] S8: Continue repeating steps S1-S4 to calculate the infrared radiation intensity of the solar panel substrate on the upward-facing heat dissipation surface of the flat-panel satellite, and evaluate the degree of reduction in infrared radiation intensity of the solar panel substrate on the upward-facing heat dissipation surface of the flat-panel satellite.

[0016] Furthermore, the formula for calculating the range of variation of the solar illumination angle β in step S2 is as follows:

[0017] .

[0018] Furthermore, the solar array equilibrium temperature equation in step S3 is:

[0019] Where σ is the Stefan-Boltzmann constant, ε h1 ε represents the hemispherical infrared emissivity of the solar cell circuit. h2 α represents the hemispherical infrared emissivity of the solar panel substrate. S1 α represents the solar absorptivity of the solar cell circuit. S2 The solar absorptivity of the solar array substrate is given by S, where S is the solar constant and E is the solar absorptivity. p J represents the intensity of Earth's infrared radiation. a This represents the intensity of Earth's albedo radiation.

[0020] Furthermore, in step S4, the total infrared radiation intensity Q total The calculation formula is: .

[0021] This invention also provides a two-dimensional driven solar array, which is applied to the above-mentioned flat-panel satellite thermal control method. The flat-panel satellite operates in a low-Earth orbit inclined orbit, and the two-dimensional driven solar array is used to make the solar cell circuits oriented towards the sun, with the upward-facing surface of the flat-panel satellite serving as the main heat dissipation surface. The two-dimensional driven solar array includes a deployment mechanism, a drive mechanism A-axis, a drive mechanism B-axis, a solar array substrate, and a solar cell circuit. The drive mechanism B-axis is perpendicular to the drive mechanism A-axis, the solar array substrate is arranged on both sides of the drive mechanism A-axis, and the normal of the solar cell circuit is always parallel to the sunlight.

[0022] The thermal control method for flat-panel satellites of the present invention first evaluates the projected (absorbed) heat flux density of different substrates along the length of the solar array on the heat dissipation surface of the satellite at different times under different solar illumination angles. Secondly, it proposes an engineering scheme to reduce the infrared radiation heat flux of the solar array on the heat dissipation surface of the satellite. The present invention can specifically perform quantitative analysis on the infrared radiation intensity of the solar array on the heat dissipation surface of the satellite's upward-facing surface of a flat-panel satellite with two-dimensional driven solar arrays. It can reduce the infrared radiation intensity of the solar array on the heat dissipation surface of the satellite's upward-facing surface of a flat-panel satellite with two-dimensional driven solar arrays operating in inclined orbits to 1 / 10 of the original intensity, thereby improving the heat dissipation efficiency of the heat dissipation surface. Attached Figure Description

[0023] Figure 1 This is a flowchart illustrating the flat-panel satellite thermal control method provided in Embodiment 1 of the present invention.

[0024] Figure 2 This is a schematic diagram showing the orientation of the solar array at different times when the flat-panel satellite is in a 15° solar illumination angle orbit.

[0025] Figure 3 This is a schematic diagram showing the orientation of the solar array at different times when the flat-panel satellite is in a 45° solar illumination angle orbit.

[0026] Figure 4This is a schematic diagram of the structure of a two-dimensional driven solar array provided in an embodiment of the present invention.

[0027] Figure 5 The image shows the infrared radiation intensity curves of the solar panel substrates with different serial numbers at the synoptic point position of the satellite before optimization, as provided in Embodiment 2 of the present invention, on the heat dissipation surface of the flat-panel satellite facing upwards.

[0028] Figure 6 The graph shows the infrared radiation intensity curves of the solar panel substrates of different numbers at different times under different solar illumination angles and orbits provided in Embodiment 2 of the present invention, representing the heat dissipation surface of the flat-panel satellite facing upwards.

[0029] Figure 7 The image shows the infrared radiation intensity curves of the solar panel substrates with different serial numbers at the synoptic point of the satellite, as provided in Embodiment 2 of the present invention, on the heat dissipation surface of the flat-panel satellite facing upwards.

[0030] Figure 8 The image shows the infrared radiation intensity curves of the solar panel substrates of different numbers at different times under different solar illumination angles and orbits provided in Embodiment 2 of the present invention, representing the heat dissipation surface of the flat-panel satellite facing upwards.

[0031] The reference numerals and components involved in the accompanying drawings are shown below:

[0032] 01. Flat Panel Satellite Platform

[0033] 02. Solar Panel Assembly

[0034] 03. Large ground loads

[0035] 11. Solar wing support rod

[0036] 12. Drive mechanism A-axis

[0037] 13. Drive mechanism B-axis Detailed Implementation

[0038] The specific embodiments of the present invention will be described in further detail below with reference to the accompanying drawings and examples. The following examples are for illustrative purposes only and are not intended to limit the scope of the invention.

[0039] The terms "first," "second," "third," "fourth," etc., used in the specification and claims of this invention are used to distinguish similar objects and are not necessarily used to describe a specific order or sequence.

[0040] Example 1

[0041] Figure 2 This is a schematic diagram showing the orientation of the solar panels of a flat-panel satellite at different times while it is in a 15° solar illumination angle orbit. Figure 3This is a schematic diagram showing the orientation of the solar panels at different times for a flat-panel satellite operating in a 45° solar illumination angle orbit. Figure 2 and Figure 3 It can be seen that a two-dimensional drive mechanism can theoretically guarantee that the solar array is vertically oriented toward the sun at any time.

[0042] First, the projected (absorbed) heat flux density of different substrates along the length of the solar array on the sun-facing surface of the flat-panel satellite at different times under different solar illumination angles and orbits is evaluated. The specific method is as follows:

[0043] Figure 1 This is a schematic flowchart of the flat-panel satellite thermal control method provided in Embodiment 1 of the present invention. Figure 4 This is a schematic diagram of the structure of a two-dimensional driven solar array provided in an embodiment of the present invention. Please refer to... Figure 1 , Figure 4 The thermal control method for flat-panel satellites provided in this embodiment of the invention includes the following steps:

[0044] S1: Obtain the length and width dimensions L0 and B0 of the flat-panel satellite; obtain the height distance H between the solar array and the satellite platform after on-orbit deployment; obtain the length and width dimensions L1 and B1 of the solar array substrate; obtain the number of solar array substrates on one side, n; obtain the horizontal distance d of the solar array substrate on one side from the A-axis of the drive mechanism, wherein the A-axis of the drive mechanism is parallel to the +Z direction of the satellite, and the +Z direction of the satellite is directly above the plane of the flat-panel satellite (e.g., ...). Figure 4 (as shown)

[0045] S2: Obtain the orbital inclination angle i of the flat-panel satellite and calculate and analyze the range of the solar illumination angle β of the flat-panel satellite orbit;

[0046] Specifically, the formula for calculating the range of variation of the solar illumination angle β in step S2 is as follows:

[0047] .

[0048] S3: Calculate and analyze the instantaneous temperature T of the solar array at the synodic point under different solar illumination angles β. t Alternatively, calculate and analyze the equilibrium temperature T of the solar array at different solar illumination angles β and at the synodic point. s ;

[0049] Specifically, the solar array equilibrium temperature equation in step S3 is:

[0050] Where σ is the Stefan-Boltzmann constant, ε h1 ε represents the hemispherical infrared emissivity of the solar cell circuit. h2 α represents the hemispherical infrared emissivity of the solar panel substrate. S1 α represents the solar absorptivity of the solar cell circuit.S2 The solar absorptivity of the solar array substrate is given by S, where S is the solar constant and E is the solar absorptivity. p J represents the intensity of Earth's infrared radiation. a This represents the intensity of Earth's albedo radiation.

[0051] S4: Calculation and analysis of the solar array at different instantaneous temperatures T t Or equilibrium temperature T s Below, the infrared radiation intensity Q of the solar panel substrate at different locations on the upward-facing heat dissipation surface of the flat-panel satellite is measured. i (i=1~n), and the total infrared radiation intensity Q of all solar panel substrates on the upward-facing heat dissipation surface of the flat-panel satellite. total ;

[0052] Specifically, in step S4, the total infrared radiation intensity Q total The calculation formula is:

[0053] .

[0054] Secondly, an engineering solution is proposed to reduce the infrared radiation heat flux from the solar array to the satellite's upward-facing heat dissipation surface. The specific methods are as follows:

[0055] S5: Apply a low infrared emissivity thermal control coating to the back of the first substrate from the middle position to the i-th substrate on both sides of the solar array;

[0056] S6: Repeat steps S1-S4 to calculate the infrared radiation intensity of the solar panel substrate on the upward-facing heat dissipation surface of the flat-panel satellite, and evaluate the degree of reduction in the infrared radiation intensity of the solar panel substrate on the upward-facing heat dissipation surface of the flat-panel satellite.

[0057] S7: Increase the horizontal distance d from the A-axis of the drive mechanism on both sides of the solar panels to d+Δd;

[0058] S8: Continue repeating steps S1-S4 to calculate the infrared radiation intensity of the solar panel substrate on the upward-facing heat dissipation surface of the flat-panel satellite, and evaluate the degree of reduction in infrared radiation intensity of the solar panel substrate on the upward-facing heat dissipation surface of the flat-panel satellite.

[0059] It should be noted that the flat-panel satellite thermal control method of the present invention first evaluates the projected (absorbed) heat flux density of different substrates along the length of the solar array on the heat dissipation surface of the satellite at different times under different solar illumination angles. Secondly, it proposes an engineering scheme to reduce the infrared radiation heat flux of the solar array on the heat dissipation surface of the satellite. The present invention can specifically perform quantitative analysis on the infrared radiation intensity of the solar array on the heat dissipation surface of the satellite's upward-facing surface of a flat-panel satellite with two-dimensional driven solar arrays. It can reduce the infrared radiation intensity of the solar array on the heat dissipation surface of the satellite's upward-facing surface of a flat-panel satellite with two-dimensional driven solar arrays operating in inclined orbits to 1 / 10 of the original intensity, thereby improving the heat dissipation efficiency of the heat dissipation surface.

[0060] Figure 4 This is a schematic diagram of the structure of a two-dimensional driven solar array provided in an embodiment of the present invention. Please refer to... Figure 4 The present invention also provides a two-dimensional driven solar array, which is applied to the above-mentioned flat-panel satellite thermal control method; the flat-panel satellite operates in a low-Earth orbit inclined orbit, and the two-dimensional driven solar array is used to make the solar cell circuit point towards the sun, with the upward-facing surface of the flat-panel satellite serving as the main heat dissipation surface.

[0061] It should be noted that the flat-panel satellite and the two-dimensional driven solar array configuration are as follows: Figure 4 As shown, it includes a flat-panel satellite platform (01), solar array assembly (02), large ground payload (03), solar array support rod (11), drive mechanism A axis (12), drive mechanism B axis (13) and solar cell circuit. In addition, 21-2n in the figure are the solar array substrate of a single solar array along the center of the satellite to the outside of the satellite.

[0062] Specifically, the two-dimensional driven solar array of the present invention includes a deployment mechanism, a drive mechanism A-axis (12), a drive mechanism B-axis (13), a solar array substrate, and a solar cell circuit; the drive mechanism B-axis (13) is perpendicular to the drive mechanism A-axis (12), the solar array substrate is arranged on both sides of the drive mechanism A-axis (12), and the normal of the solar cell circuit is always parallel to the sunlight.

[0063] Example 2

[0064] Figure 5 The image shows the infrared radiation intensity curves of the solar panel substrates with different serial numbers at the synoptic point position of the satellite before optimization, as provided in Embodiment 2 of the present invention, on the heat dissipation surface of the flat-panel satellite facing upwards. Figure 6 The graphs shown in Embodiment 2 of the present invention depict the infrared radiation intensity curves of the solar panel substrate on the heat dissipation surface of the flat-panel satellite at different times under different solar illumination angles and orbits, before optimization. Figure 7 This is an infrared radiation intensity curve of the solar panel substrate with different serial numbers at the synoptic point location of the satellite, provided in Embodiment 2 of the present invention, showing the radiation intensity on the heat dissipation surface of the flat-panel satellite facing upwards. Figure 8 The graph shows the infrared radiation intensity curves of the solar panel substrates on the upward-facing heat dissipation surface of the flat-panel satellite at different times under different solar illumination angles and orbits provided in Embodiment 2 of the present invention. Please refer to... Figure 5 , Figure 6 , Figure 7 Figure 8 This embodiment is a flat-panel satellite with two-dimensional driven solar panels. Its orbital parameters are: orbital inclination i = 50°, orbital altitude H = 500km. According to the formula, the range of the solar illumination angle of the satellite orbit is -73.5° ≤ β ≤ 73.5°.

[0065] The flat-panel satellite has dimensions L0 = 2.5m and B0 = 2.5m.

[0066] After the solar panels deploy in orbit, the altitude distance between them and the satellite platform is h = 1.25m.

[0067] The solar panel substrate has dimensions L0 = 2.0m and B0 = 0.4m.

[0068] The number of single-sided solar panel substrates is n=20;

[0069] The horizontal distance d from the edge of the first substrate of the single-sided solar array to the A-axis of the drive mechanism is 0.2m;

[0070] The Stefan-Boltzmann constant σ = 5.67e -8 W / m 2 .K 4 ;

[0071] Hemispherical infrared emissivity ε of solar cell circuit h1 =0.84;

[0072] Hemispherical infrared emissivity ε of solar panel substrate h2 =0.69;

[0073] Solar absorptivity α of solar cell circuit S1 =0.92;

[0074] Solar absorptivity α of solar panel substrate S2 =0.32;

[0075] Solar constant S = 1367 W / m 2 ;

[0076] The intensity of Earth's infrared radiation and the intensity of Earth's albedo are calculated.

[0077] The infrared radiation intensity of the solar panel substrates with different serial numbers on the heat dissipation surface of the flat-panel satellite at different times under different solar illumination angles can be calculated. Figure 5 , Figure 6 As shown.

[0078] Specifically, a low-infrared emissivity thermal control coating is applied to the back of the first to fourth substrates from the middle position on both sides of the solar array. The hemispherical infrared emissivity ε of the low-infrared emissivity thermal control coating is... h2 =0.05;

[0079] Specifically, the horizontal distance between the two solar panels and the drive mechanism A axis is increased from d=0.2m to d+Δd=0.5m;

[0080] The infrared radiation intensity of the solar panel substrates with different serial numbers on the heat dissipation surface of the flat-panel satellite at different times under different solar illumination angles can be calculated. Figure 7 , Figure 8 As shown.

[0081] As can be seen from the above description, the advantages of this invention are:

[0082] The thermal control method for flat-panel satellites of the present invention first evaluates the projected (absorbed) heat flux density of different substrates along the length of the solar array on the heat dissipation surface of the satellite at different times under different solar illumination angles. Secondly, it proposes an engineering scheme to reduce the infrared radiation heat flux of the solar array on the heat dissipation surface of the satellite. The present invention can specifically perform quantitative analysis on the infrared radiation intensity of the solar array on the heat dissipation surface of the satellite's upward-facing surface of a flat-panel satellite with two-dimensional driven solar arrays. It can reduce the infrared radiation intensity of the solar array on the heat dissipation surface of the satellite's upward-facing surface of a flat-panel satellite with two-dimensional driven solar arrays operating in inclined orbits to 1 / 10 of the original intensity, thereby improving the heat dissipation efficiency of the heat dissipation surface.

[0083] The above description is merely a specific embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in the present invention should be included within the scope of protection of the present invention. Therefore, the scope of protection of the present invention should be determined by the scope of the claims.

Claims

1. A method for thermal control of a flat-panel satellite, characterized in that, The thermal control method includes the following steps: S1: Obtain the length and width dimensions L0 and B0 of the flat-panel satellite, obtain the height distance H between the solar array and the satellite platform after it is deployed in orbit, obtain the length and width dimensions L1 and B1 of the solar array substrate, obtain the number of solar array substrates on one side n, and obtain the horizontal distance d between the solar array substrate on one side and the drive mechanism A-axis. The drive mechanism A-axis is parallel to the satellite +Z direction, where the satellite +Z direction is directly above the plane of the flat-panel satellite. S2: Obtain the orbital inclination angle i of the flat-panel satellite and calculate and analyze the range of the solar illumination angle β of the flat-panel satellite orbit; S3: Calculate and analyze the instantaneous temperature T of the solar array at the synodic point under different solar illumination angles β. t Alternatively, calculate and analyze the equilibrium temperature T of the solar array at different solar illumination angles β and at the synodic point. s ; S4: Calculation and analysis of the solar array at different instantaneous temperatures T t Or equilibrium temperature T s Below, the infrared radiation intensity Q of the solar panel substrate at different locations on the upward-facing heat dissipation surface of the flat-panel satellite is measured. i The total infrared radiation intensity Q of all solar panel substrates on the upward-facing heat dissipation surface of the flat-panel satellite. total ; S5: Apply a low infrared emissivity thermal control coating to the back of the first substrate from the middle position to the i-th substrate on both sides of the solar array; S6: Repeat steps S1-S4 to calculate the infrared radiation intensity of the solar panel substrate on the upward-facing heat dissipation surface of the flat-panel satellite, and evaluate the degree of reduction in the infrared radiation intensity of the solar panel substrate on the upward-facing heat dissipation surface of the flat-panel satellite. S7: Increase the horizontal distance d from the A-axis of the drive mechanism on both sides of the solar panels to d+Δd; S8: Continue repeating steps S1-S4 to calculate the infrared radiation intensity of the solar panel substrate on the upward-facing heat dissipation surface of the flat-panel satellite, and evaluate the degree of reduction in infrared radiation intensity of the solar panel substrate on the upward-facing heat dissipation surface of the flat-panel satellite.

2. The flat-panel satellite thermal control method according to claim 1, characterized in that, The formula for calculating the range of variation of the solar illumination angle β in step S2 is as follows: 。 3. The flat-panel satellite thermal control method according to claim 1, characterized in that, The solar array equilibrium temperature equation in step S3 is: Where σ is the Stefan-Boltzmann constant, ε h1 ε represents the hemispherical infrared emissivity of the solar cell circuit. h2 α represents the hemispherical infrared emissivity of the solar panel substrate. S1 α represents the solar absorptivity of the solar cell circuit. S2 The solar absorptivity of the solar array substrate is given by S, where S is the solar constant and E is the solar absorptivity. p J represents the intensity of Earth's infrared radiation. a This represents the intensity of Earth's albedo radiation.

4. The flat-panel satellite thermal control method according to claim 1, characterized in that, The total infrared radiation intensity Q in step S4 total The calculation formula is: .

5. A two-dimensional driven solar array, characterized in that, The two-dimensional driven solar array is applied to the flat-panel satellite thermal control method of claim 1; The flat-panel satellite operates in a low-Earth orbit inclined orbit, and uses the two-dimensional driven solar array to align the solar cell circuits with the sun. The upward-facing surface of the flat-panel satellite serves as the main heat dissipation surface. The two-dimensional driven solar array includes a deployment mechanism, a drive mechanism A-axis, a drive mechanism B-axis, a solar array substrate, and solar cell circuits. The drive mechanism B-axis is perpendicular to the drive mechanism A-axis, the solar array substrates are arranged on both sides of the drive mechanism A-axis, and the normal of the solar cell circuits is always parallel to the sunlight.

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