Space structure control system and space structure control method

Abstract

To provide a space structure control system which is lighter, in which surface shape control is easy and deployment time is short when increasing a size in a space structure deployed in the space.SOLUTION: A space structure control system includes: a space structure; an artificial satellite which is connected to the space structure; and a propulsion device which is mounted on the artificial satellite to control an orbit and an attitude of the artificial satellite. The space structure includes: a sunlight reflectance control device which has a film-like structure and controls a spatial pattern of sunlight reflectance in a reflector installed on the film-like structure; and a shape maintenance device which is connected to the film-like structure. The propulsion device rotates the film-like structure to generate centrifugal force. The sunlight reflectance control device controls a solar radiation pressure applied to the reflector by controlling the sunlight reflectance in the reflector, controls a three-dimensional shape of the film-like structure by the centrifugal force caused by the rotation of the film-like structure and the solar radiation pressure, and maintains or stabilizes a shape of the film-like structure by the shape maintenance device.SELECTED DRAWING: Figure 5

Description

[Technical Field]

[0001] The present invention relates to a space structure that is deployed in space. [Background technology]

[0002] Space structures that are transported from the ground to outer space and deployed include satellite antennas and sunlight-condensing, reflective surfaces used in solar power generation panels.

[0003] Parabolic antennas, which have a simple structure and can achieve high gain, are often used as satellite antennas, but increasing the gain of such antennas requires a larger reflector. Conventionally, lightweight parabolic antennas mounted on satellites are deployable antennas that form a curved reflector by deploying a thin-film reflecting surface, a frame, and ribs in space, resulting in lightweight, large parabolic antennas of several tens of meters in size. However, to further increase the gain, further enlargement is required. This increases the weight and the cost of launching by rocket, so research is being conducted on new membrane deployment methods and surface shape control aimed at reducing weight.

[0004] A prior art document related to this technical field is Patent Document 1. Patent Document 1 describes a shape forming method for an electromagnetic wave focusing device for space use equipped with a reflector formed from a thin film material, in which the surface distribution of emissivity and reflectivity on the reflector surface is adjusted to approximate the shape of the reflector surface to a specified shape. [Prior art documents] [Patent documents]

[0005] [Patent Document 1] Japanese Patent Application Laid-Open No. 2005-72913 Summary of the Invention [Problem to be solved by the invention]

[0006] Patent Document 1 describes controlling the surface shape using emissivity and reflectivity, but does not take into account the deployment time of the membrane structure or the operation time required to correct the effects of gravity gradient and air disturbances.

[0007] Therefore, an object of the present invention is to provide a space structure control system that is lightweight, has easy surface shape control, and requires a short deployment time when a space structure to be deployed in space is enlarged. [Means for solving the problem]

[0008] One example of the present invention is a space structure control system that controls the shape of a space structure deployed in outer space, comprising a space structure, a satellite connected to the space structure, and a propulsion device mounted on the satellite and controlling the satellite's orbit and attitude, the space structure having a membrane-like structure, a solar reflectance control device that controls the spatial pattern of solar reflectance on a reflector installed on the membrane-like structure, and a shape maintenance device connected to the membrane-like structure, the propulsion device rotates the membrane-like structure to generate centrifugal force, the solar reflectance control device controls the solar reflectance on the reflector to control the solar radiation pressure applied to the reflector, the centrifugal force due to the rotation of the membrane-like structure and the solar radiation pressure control the three-dimensional shape of the membrane-like structure, and the shape maintenance device maintains or stabilizes the shape of the membrane-like structure. [Effects of the Invention]

[0009] According to the present invention, it is possible to provide a space structure control system that is lighter in weight, easier to control the surface shape, and requires less time to deploy, even when the space structure is enlarged and deployed in outer space. [Brief explanation of the drawings]

[0010] [Figure 1] FIG. 1 is a configuration block diagram of a space structure control system according to a first embodiment. [Figure 2] 1 is a perspective view showing the overall configuration of a space structure control system according to a first embodiment. [Figure 3]FIG. 3 is a top view of the space structure control system in FIG. 2 as seen from the sun side. [Figure 4] FIG. 3 is a side view of the space structure control system in FIG. 2. [Figure 5] FIG. 3 is a development view of the membrane structure in FIG. 2 as seen from the sun side. [Figure 6] 1 is a cross-sectional view of a thin film structure of a membrane structure in Example 1. FIG. [Figure 7] 4 is a cross-sectional view of another thin film structure of the membrane structure in Example 1. FIG. [Figure 8] 4 is a process flowchart of the shape control of the membrane structure in the space structure control system according to the first embodiment. [Figure 9] FIG. 10 is a configuration block diagram of a space structure control system according to a second embodiment. [Figure 10] FIG. 10 is a perspective view showing the overall configuration of a space structure control system according to a second embodiment. [Figure 11] FIG. 11 is a development view of the membrane structure in FIG. 10 as seen from the sun side. [Figure 12] FIG. 11 is a perspective view showing the overall configuration of a space structure control system according to a third embodiment. [Figure 13] FIG. 13 is a view of the thin-film satellite module in FIG. 12 as seen from the sun side. DETAILED DESCRIPTION OF THE INVENTION

[0011] DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS Hereinafter, an embodiment of the present invention will be described with reference to the accompanying drawings. In the present embodiment, an antenna mounted on an artificial satellite will be described as an example of a space structure. [Example]

[0012] Figure 1 is a configuration block diagram of a space structure control system in this embodiment. In Figure 1, a space structure control system 100 has a space structure 130, an artificial satellite 102, and a propulsion device 103. The space structure 130 also constitutes an antenna as a space structure, and has a membrane structure 101, an expandable pillar 107, and a transmitter / receiver 108. Furthermore, the membrane structure 101 has a solar reflectance control device 104, a shape maintenance device 105, and a solar panel 106.

[0013] Figure 2 is a perspective view showing the overall configuration of a space structure control system 100 in this embodiment. In Figure 2, the same components as in Figure 1 are assigned the same reference numerals, and their explanation will be omitted. As shown in Figure 2, a satellite 102 is connected to the central axis of a membrane structure 101, and a propulsion device 103 mounted on the satellite 102 rotates the membrane structure 101. Note that 9 schematically represents the sun, and 109 represents a small weight.

[0014] Fig. 3 is a top view of the space structure control system 100 in Fig. 2 as seen from the sun side. Also, Fig. 4 is a side view of the space structure control system 100 in Fig. 2. Furthermore, Fig. 5 is a development view of the membrane structure 101 in Fig. 2 as seen from the sun side.

[0015] As shown in Fig. 5, the membrane structure 101 in this embodiment constitutes a large deployable antenna with an aperture size of 10 to 50 m. The membrane structure 101 is formed of membrane modules 120, which are thin triangular films obtained by radially dividing a three-dimensional parabolic (paraboloidal) thin film that constitutes the antenna. The membrane modules 120 are joined at their centers. Note that each membrane module 120 is not limited to a triangular shape, and may be rectangular or rectangular with the center cut out.

[0016] The film surface module 120 has a thin film structure in which a reflector and a liquid crystal device are attached to a thin film. FIG. 6 is a schematic diagram illustrating the thin film structure of this embodiment, showing a cross-sectional view of the thin film structure. As shown in FIG. 6, the thin film structure 121 is composed of, from the sun 9 side, a liquid crystal device 141, a thin film 142, and a reflector 143. The liquid crystal device 141 can control the spatial pattern of solar reflectance on the reflector 143. Therefore, the liquid crystal device 141 functions as a solar reflectance control device 104. The solar reflectance control device 104 can control the solar radiation pressure applied to the reflector 143 by controlling the solar reflectance on the reflector 143. Note that the solar reflectance control device 104 may be a device other than the liquid crystal device 141 that can control the light transmittance or absorptance using, for example, an electrochromic device or material.

[0017] The thin film structure 121 of the membrane structure 101 may have a reflecting mirror 144 in which the thin film and the reflecting mirror are integrated, as shown in FIG.

[0018] The thin film 142 is preferably made of a material that is highly resistant to the space environment, such as a polyimide film, a GFRP (glass fiber reinforced plastic) fabric, or a CFRP (carbon fiber reinforced plastic) fabric. The reflecting mirror 143 is preferably made of a zirconium alloy fabric, a GFRP fabric, or a CFRP fabric.

[0019] In addition, the film surface module 120 has a solar panel 106 that measures the illuminance on the film surface, i.e., a photodetector that functions as an illuminance meter, and the solar reflectance control device 104 controls the solar reflectance on the reflector 143 or 144 based on information from the solar panel 106.

[0020] 5, the solar radiation pressure distribution on the AA cross section acting on the membrane structure 101 when the solar radiation pressure acting on the reflector is controlled by controlling the solar reflectance of the reflector using the solar reflectance control device 104 is shown at the bottom of the figure. As shown in Fig. 5, by controlling the solar radiation pressure, the membrane structure 101 formed by multiple membrane modules 120 can be controlled to have a parabolic shape that forms an antenna.

[0021] The membrane structure 101 is transported in a folded state due to storage volume restrictions when transporting it from the ground to outer space. After being transported into outer space, the membrane structure 101 is rotated by a propulsion device 103 mounted on an artificial satellite 102, and the membrane structure 101 is deployed by the centrifugal force generated at that time. After that, the membrane structure 101 is controlled to assume a three-dimensional parabolic shape by the balance between the centrifugal force caused by the rotation of the membrane structure 101 and solar radiation pressure. As shown in Figure 5, the multiple membrane modules 120 that make up the membrane structure 101 each have ground sensors 110 on two radial sides, and by detecting that each membrane module 120 has come into contact with an adjacent membrane module 120, it is determined that generation of the three-dimensional shape of the membrane structure 101 has been completed.

[0022] Furthermore, the membrane module 120 has shape maintenance devices 105 on two radial sides, which maintain the shape of the membrane structure 101 after the shape generation is complete. Specifically, the shape maintenance device 105 is composed of a tether connected to the membrane structure 101, a tether expansion / contraction control device, a magnet, a hardening resin, a latch mechanism, or the like. The shape maintenance device 105 may have an infrared sensor or a camera, and may maintain or stabilize the shape of the membrane structure 101 based on information from these.

[0023] The space structure control system 100 in this embodiment maintains the parabolic shape of the membrane structure 101 and has an antenna function using a transmitter / receiver 108 connected to the satellite 102 or the membrane structure 101 via an extendable pillar 107. The transmitter / receiver 108 may be connected via a tether instead of an extendable pillar.

[0024] The artificial satellite 102 may use the propulsion device 103 to control the rotation speed in order to maintain the attitude (pointing direction) of the membrane structure 101.

[0025] Furthermore, the satellite 102 may have a function of separating the satellite itself, which acts as a weight, from the membrane structure 101 in order to maintain the shape of the membrane structure 101 .

[0026] The sunlight reflectance control device 104 may also control the orientation of the three-dimensional shape of the membrane structure 101 by controlling the sunlight reflectance on the reflecting mirror 143 to control the solar radiation pressure acting on the reflecting mirror 143 .

[0027] FIG. 8 is a processing flowchart for controlling the shape of a membrane structure in the space structure control system according to this embodiment. In FIG. 8, first, in step S11, the membrane structure 101 is rotated using the propulsion device 103 to deploy the membrane structure 101. Next, in step S12, the illuminance on the membrane surface is measured using a solar panel. Then, in step S13, the solar reflectance of the liquid crystal device, which is the solar reflectance control device 104, is changed to control solar radiation pressure. Then, in step S14, the membrane shape of the membrane structure 101 is controlled by centrifugal force due to the rotation of the membrane structure and solar radiation pressure control using the change in the solar reflectance of the liquid crystal device. Next, in step S15, it is determined whether signals are present in the ground sensors 110 located on two radial sides of each of the multiple membrane modules 120 that make up the membrane structure 101. If no signals are present, it is determined that control of the membrane shape of the membrane structure 101 is incomplete, and the process returns to step S13. In step S15, if a signal is present, it is determined that the deployment by rotation of the membrane structure 101 and the control of the membrane surface shape are completed, and the process proceeds to step S16.

[0028] Then, in step S16, a shape maintaining device is used to maintain the membrane surface shape of the membrane structure 101. Then, in step S17, the expandable pillars 107 are deployed, and the transmitter / receiver 108 is placed at a desired position.

[0029] As described above, according to this embodiment, the space structure 130 is transported in a folded state due to storage volume restrictions when transported from the ground to outer space. After transport into outer space, the membrane structure 101 is rotated by the propulsion device 103 mounted on the artificial satellite 102, and the membrane structure 101 is deployed by the centrifugal force generated during the rotation. Therefore, a space structure control system with a short deployment time can be provided. Furthermore, since the membrane structure 101 includes the solar reflectance control device 104, the solar reflectance of the reflector 143 can be controlled by the solar reflectance control device 104, thereby controlling the solar radiation pressure applied to the reflector 143. Therefore, the parabolic shape of the membrane structure 101 can be formed by balancing the centrifugal force caused by the rotation of the membrane structure 101 and the solar radiation pressure. Therefore, the orbit and attitude of the space structure can be controlled by the propulsion device 103 and the solar reflectance control device 104, and the effects of gravity gradient, air disturbance, etc. can also be corrected. In other words, it is possible to provide a space structure control system that is lighter in weight, easier to control the surface shape, and requires less time to deploy, even when the space structure is enlarged and deployed in outer space. [Example]

[0030] In the first embodiment, a large deployable antenna of 10 to 50 m class was described as a space structure, but in this embodiment, an even larger space structure, a large deployable antenna of 100 to 500 m class, will be described.

[0031] Figure 9 is a configuration block diagram of a space structure control system in this embodiment. In Figure 9, the same components as in Figure 1 are assigned the same reference numerals, and their explanation will be omitted. In Figure 9, a space structure control system 200 is composed of multiple thin-film satellite modules 230 and a transmitter / receiver module 240. Furthermore, the thin-film satellite module 230 has a membrane structure module 210, an artificial satellite 102, and a propulsion device 103. Furthermore, the membrane structure module 210 has a solar reflectance control device 104, a shape maintenance device 105, and a solar panel 106, similar to the membrane structure 101 in Example 1.

[0032] Figure 10 is a perspective view showing the overall configuration of a space structure control system 200 in this embodiment. In Figure 10, the same components as in Figure 2 are assigned the same reference numerals, and their description will be omitted. Figure 10 differs from Figure 2 in that the membrane structure 220 that constitutes the space structure is made up of multiple thin-film satellite modules 230, and small satellites, or end satellites 209, are connected to the periphery of the thin-film satellite modules 230. In other words, the end satellites 209 refer to artificial satellites installed at the ends of the thin-film satellite modules 230, for example, and may be replaced with small satellites.

[0033] FIG. 11 is a development view of the membrane structure 220 in FIG. 10 as seen from the sun side. As shown in FIG. 11, the membrane structure 220 in this embodiment constitutes a large deployable antenna with an aperture size of 100 to 500 m class. The membrane structure 220 constituting the space structure is formed of thin-film satellite modules 230, which are multiple triangular thin films obtained by radially dividing a parabolic thin film constituting the antenna. Furthermore, the multiple thin-film satellite modules 230 have end satellites 209 connected to their thin-film ends. Note that the multiple thin-film satellite modules 230 are not limited to a triangular shape, and may be rectangular or rectangular with a cutout in the center.

[0034] The thin-film satellite module 230 has a thin-film structure in which a reflector and a liquid crystal device are attached to a thin film, similar to the film module 120 in Example 1. That is, the liquid crystal device functions as a solar reflectance control device 104, and is capable of controlling the solar radiation pressure applied to the reflector by controlling the solar reflectance of the reflector. Also, similar to the film module 120, the thin-film satellite module 230 has a solar panel 106.

[0035] In Figure 11, as in Figure 5, by controlling the solar radiation pressure using the solar reflectance control device 104, it is possible to control the membrane structure 220 formed by multiple thin-film satellite modules 230 to have a parabolic shape that forms an antenna.

[0036] In this embodiment, the space structure is transported in a folded state due to storage volume restrictions when transporting it from the ground to outer space. After the space structure is transported into outer space, the membrane structure 220 of the space structure is rotated by the propulsion device 103 and the end satellite 209 mounted on the artificial satellite 102, and the membrane structure 220 is deployed by the centrifugal force generated at that time. The membrane structure 220 is controlled to assume a three-dimensional parabolic shape by the balance between the centrifugal force caused by the rotation of the membrane structure 220 and solar radiation pressure.

[0037] The thin-film satellite module 230 also has shape maintaining devices 105 on two radial sides to maintain the shape of the thin-film structure after the shape generation is completed. The shape maintaining devices 105 have the same configuration as in Example 1, and the description thereof will be omitted.

[0038] The space structure control system 200 in this embodiment maintains the parabolic shape of the membrane structure 220 of the space structure, and has an antenna function with a transmitter / receiver 108 connected to the satellite 102 or the membrane structure 220 via a retractable pillar 107 in the transmitter / receiver module 240. Note that the transmitter / receiver 108 may be connected via a constellation satellite instead of a retractable pillar.

[0039] Furthermore, the artificial satellite 102 may use the propulsion device 103 to control the rotation speed in order to maintain the attitude of the membrane structure 220 (maintain the pointing direction).

[0040] Furthermore, the satellite 102 may have a function of separating the satellite itself, which acts as a weight, from the membrane structure 220 in order to maintain the shape of the membrane structure 220 .

[0041] Furthermore, the sunlight reflectance control device 104 may control the orientation of the three-dimensional shape of the membrane structure 220 by controlling the solar radiation pressure acting on the reflecting mirror by controlling the sunlight reflectance on the reflecting mirror.

[0042] As described above, according to this embodiment, the space structure is transported in a folded state due to storage volume limitations when transported from the ground to outer space. After transport into outer space, the membrane structure 220 is rotated by the end satellite 209 together with the propulsion device 103 mounted on the artificial satellite 102. This causes the membrane structure 101 to be deployed by centrifugal force generated by the rotation. Therefore, compared to the first embodiment, a space structure control system with a shorter deployment time can be provided, even for larger space structures, because the thrust from the end satellite 209 is also used. Furthermore, as in the first embodiment, the parabolic shape of the membrane structure 220 can be formed by balancing the centrifugal force caused by the rotation of the membrane structure 220 and solar radiation pressure. Therefore, the propulsion device 103 and the solar reflectance control device 104 can control the orbit and attitude of the space structure, and can also correct for the effects of gravity gradient, air disturbance, and the like. That is, for space structures to be deployed in outer space, a space structure control system with a lighter weight, easier surface shape control, and shorter deployment time can be provided, even as the space structures become larger. [Example]

[0043] In the second embodiment, a large deployable antenna of 100 to 500 m class was described as a space structure, but in this embodiment, an even larger space structure, an ultra-large deployable antenna of km class, will be described.

[0044] Figure 12 is a perspective view showing the overall configuration of a space structure control system 300 in this embodiment. In Figure 12, the same components as in Figure 10 are assigned the same reference numerals, and their description will be omitted. Figure 12 differs from Figure 10 in that the parabolic membrane structure 220 that constitutes the antenna constitutes an ultra-large deployable antenna with a diameter of the km class. Also, multiple thin-film satellite modules 230 are connected in a row in the radial and circumferential directions of the parabolic membrane structure 220 that constitutes the antenna.

[0045] 12, the thin-film satellite module 230 is a triangular thin film, as in Example 2, and the end satellite 209 is connected to the vertex of the thin-film satellite module 230. Note that the thin-film satellite module 230 is not limited to a triangular shape, and may be a square or rectangular shape.

[0046] FIG. 13 is a view of the thin-film satellite module 230 in FIG. 12 as seen from the sun side. As shown in FIG. 13, the thin-film satellite module 230 has a liquid crystal device 141 on the thin film facing the sun. That is, like the membrane module 120 in Example 1, the thin-film satellite module 230 has a thin-film structure in which a reflector and a liquid crystal device are attached to a thin film. Therefore, the liquid crystal device 141 functions as a solar reflectance control device 104, and can control the solar radiation pressure applied to the reflector by controlling the solar reflectance of the reflector. Furthermore, like the membrane module 120, the thin-film satellite module 230 has a solar panel 106. Therefore, in this example as well, by controlling the solar radiation pressure using the solar reflectance control device 104, it is possible to control the membrane structure 220 formed by multiple thin-film satellite modules 230 to have a parabolic shape that constitutes an antenna.

[0047] The parabolic membrane structure 220 constituting the antenna in this embodiment is an ultra-large antenna of the km class, so it has high gain and detects electromagnetic waves over a narrow range. Therefore, as shown in Figure 13, by installing an array patch antenna 250 at the end of the thin-film satellite module 230, it becomes possible to detect electromagnetic waves over a wide range despite low gain. Considering time delays, it is preferable to connect the signal line to the array patch antenna 250 via a wire via the thin film or the end satellite.

[0048] In this embodiment, the space structure is transported in a folded state due to storage volume restrictions when transporting it from the ground to outer space. After the space structure is transported into outer space, the thin-film satellite modules 230 are deployed by holding or pulling the thin film using the end satellites 209 connected to the thin-film satellite modules 230. The membrane structure 220 of the space structure is deployed by connecting multiple thin-film satellite modules 230 to each other. The three-dimensional parabolic shape of the membrane structure 220 is maintained and controlled by controlling solar radiation pressure. Note that the entire membrane structure 220 may be rotated by the end satellites 209, and the centrifugal force generated by the rotation may also be used to deploy the membrane structure 220.

[0049] Furthermore, the thin-film satellite module 230 has a shape maintaining device 105 on each of its constituent sides, which maintains the shape of the membrane structure 220 after the shape generation is completed. The shape maintaining device 105 has the same configuration as in the first embodiment, and therefore the description thereof will be omitted.

[0050] The space structure control system 300 in this embodiment maintains the parabolic shape of the membrane structure 220 of the space structure, and has the function of an antenna using the transmitter / receiver 108 connected to the membrane structure 220 via a tether 111. Note that the transmitter / receiver 108 may be connected via a constellation satellite instead of a tether.

[0051] Furthermore, the sunlight reflectance control device 104 may control the orientation of the three-dimensional shape of the membrane structure 220 by controlling the solar radiation pressure acting on the reflecting mirror by controlling the sunlight reflectance on the reflecting mirror.

[0052] As described above, according to this embodiment, the space structure is transported in a folded state due to storage volume limitations when transported from the ground to space. After transport into space, the thin-film satellite module 230 is deployed by holding or pulling the thin film by the end satellite 209 connected to the thin-film satellite module 230. The parabolic membrane structure 220 constituting the antenna is then connected to a plurality of thin-film satellite modules 230 in an array in the radial and circumferential directions of the parabolic membrane structure 220, thereby deploying the membrane structure 220 of the space structure. Therefore, a space structure control system with a shorter deployment time than that of Embodiment 2 can be provided, even for very large space structures. Furthermore, as in Embodiments 1 and 2, the parabolic shape of the membrane structure can be formed by controlling solar radiation pressure. Therefore, the orbit and attitude of the space structure can be controlled by the propulsion device 103 and the solar reflectance control device 104, and the effects of gravity gradient, air disturbance, and the like can be corrected. In other words, a space structure control system with a lighter weight, easier surface shape control, and shorter deployment time can be provided for very large space structures deployed in space.

[0053] The present invention is not limited to the above-described embodiments and includes various modifications. For example, the above-described embodiments have been described in detail to clearly explain the present invention, and the present invention is not necessarily limited to those including all of the described configurations. For example, in the above-described embodiments, an antenna mounted on an artificial satellite was used as an example of a space structure, but an electromagnetic wave focusing device such as a sunlight-collecting reflective surface used in a solar power generation panel may also be used. Furthermore, the three-dimensional shape of the membrane structure does not have to be limited to a parabolic shape. Furthermore, it is possible to replace part of the configuration of one embodiment with the configuration of another embodiment, or to add the configuration of another embodiment to the configuration of one embodiment. Furthermore, it is possible to add, delete, or replace part of the configuration of each embodiment with other configurations. [Explanation of symbols]

[0054] 100, 200, 300: Space structure control system, 101, 220: Membrane structure, 102: Satellite, 103: Propulsion device, 104: Solar reflectance control device, 105: Shape maintenance device, 106: Solar panel, 107: Telescopic pillar, 108: Transmitter / receiver, 109: Small weight, 110: Ground sensor, 111: Tether, 120: Membrane module, 121: Thin film structure, 130: Space structure, 141: Liquid crystal device, 142: Thin film, 143, 144: Reflector, 209: End satellite, 210: Membrane structure module, 230: Thin film satellite module, 240: Transmitter / receiver module, 250: Array patch antenna

Claims

1. A space structure control system for controlling the shape of a space structure deployed in space, comprising: the space structure; a satellite connected to the space structure; a propulsion device mounted on the satellite to control the orbit and attitude of the satellite; the space structure has a membrane-like structure, a solar reflectance control device that controls a spatial pattern of solar reflectance on a reflector installed on the membrane-like structure, and a shape maintenance device connected to the membrane-like structure; the propulsion device rotates the membrane structure to generate centrifugal force; the sunlight reflectance control device controls the sunlight reflectance of the reflector to control the solar radiation pressure applied to the reflector, controlling the three-dimensional shape of the membrane structure by the centrifugal force caused by the rotation of the membrane structure and the solar radiation pressure; A space structure control system characterized in that the shape of the membrane structure is maintained or stabilized by the shape maintenance device.

2. 2. The space structure control system according to claim 1, The satellite is connected to the central axis of the membrane-like structure, and the membrane-like structure is deployed to form the three-dimensional shape by centrifugal force generated by rotating the membrane-like structure using the propulsion device installed on the satellite.

3. 2. The space structure control system according to claim 1, A space structure control system, wherein the solar reflectance control device is a liquid crystal device or an electrochromic device that electrically controls the reflectance of light.

4. 2. The space structure control system according to claim 1, the membrane structure is formed of a plurality of membrane modules obtained by radially dividing the three-dimensional thin film, A space structure control system characterized in that the shape maintenance device is provided on two radial sides of the membrane module and is a tether connected to the membrane structure, a tether extension / contraction control device, a magnet, a hardened resin, or a latch mechanism.

5. 2. The space structure control system according to claim 1, a solar panel that measures the illuminance on the membrane surface of the membrane structure; A space structure control system characterized in that the solar reflectance control device controls the solar reflectance of the reflector based on information from the solar panel.

6. 2. The space structure control system according to claim 1, A space structure control system characterized in that the shape maintenance device has an infrared sensor or a camera, and maintains or stabilizes the shape of the membrane structure based on information from these sensors.

7. 2. The space structure control system according to claim 1, The three-dimensional shape of the membrane structure is a parabolic shape, A space structure control system having a transmitter / receiver connected to the satellite or the membrane structure via an expandable pillar or tether, and having the function of an antenna.

8. 2. The space structure control system according to claim 1, A space structure control system characterized in that the artificial satellite has a function of controlling the rotation speed of the membrane structure using the propulsion device in order to maintain the attitude of the membrane structure.

9. 2. The space structure control system according to claim 1, A space structure control system characterized in that the artificial satellite has a function of separating the artificial satellite from the space structure in order to maintain the shape of the membrane structure.

10. 2. The space structure control system according to claim 1, A space structure control system characterized in that the solar reflectance control device controls the attitude of the three-dimensional shape of the membrane structure by controlling the solar radiation pressure applied to the reflector by controlling the solar reflectance of the reflector.

11. 2. The space structure control system according to claim 1, the membrane structure is formed of a plurality of thin film satellite modules obtained by radially dividing the three-dimensional thin film, and end satellites are connected to the thin film ends of the thin film satellite modules; The satellite is connected to the central axis of the membrane structure, and the membrane structure is deployed to form the three-dimensional shape by centrifugal force generated by rotating the membrane structure using the propulsion device and the end satellite mounted on the satellite.

12. 2. The space structure control system according to claim 1, the membrane structure is formed of a plurality of thin-film satellite modules arranged and connected in the radial and circumferential directions of the three-dimensionally shaped thin film, and end satellites are connected to the vertices of the thin film of the thin-film satellite modules; A space structure control system characterized in that the thin-film satellite module is deployed by holding or pulling the thin film using an end satellite connected to the thin-film satellite module, and the three-dimensional shape is formed by connecting multiple thin-film satellite modules to each other.

13. 13. The space structure control system according to claim 12, A space structure control system characterized in that the thin-film satellite module has an array patch antenna installed at its end.

14. A space structure control method for a space structure control system that controls the shape of a space structure deployed in space, comprising: a space structure control system including the space structure, a satellite connected to the space structure, and a propulsion device mounted on the satellite for controlling the orbit and attitude of the satellite; the space structure has a membrane structure, Rotating the membrane structure using the propulsion device to generate centrifugal force; controlling the solar radiation pressure acting on the reflector by controlling the solar reflectance of the reflector installed on the membrane structure; controlling the three-dimensional shape of the membrane structure by the centrifugal force caused by the rotation of the membrane structure and the solar radiation pressure; A space structure control method characterized by maintaining or stabilizing the shape of the membrane structure.

15. 15. The space structure control method according to claim 14, The satellite is connected to the central axis of the membrane structure, and the propulsion device mounted on the satellite rotates the membrane structure, causing centrifugal force to deploy the membrane structure to form the three-dimensional shape.

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