Solar power generation satellite and control method of solar power generation satellite

Abstract

To provide a solar power generation satellite capable of maintaining a posture of a satellite with less energy and capable of reducing an operation cost of the solar power generation satellite, and to provide a control method of the solar power generation satellite.SOLUTION: Provided is a long solar power generation satellite 1 including: an antenna 110 for power transmission; a plurality of vertical beams 120 arranged having an interval; a transverse beam 130 for connecting the vertical beams 120 with each other; and one or a plurality of solar battery panels 140. The plurality of vertical beams 120 extend in parallel with or inclined to a longer direction of the solar power generation satellite 1, the antenna 110 for power transmission is provided on one end part side in the longer direction of the solar power generation satellite 1, a power transmission direction of the antenna 110 for power transmission faces the direction in parallel with the longer direction of the solar power generation satellite 1, and the solar battery panels 140 are connected in a rotatable manner with respect to the vertical beams 120. Also provided is a control method of the same.SELECTED DRAWING: Figure 2

Description

[Technical field]

[0001] The present invention relates to a solar power satellite and a method for controlling a solar power satellite. [Background technology]

[0002] There is a space solar power satellite system that generates solar power by launching an artificial satellite into an orbit around the Earth. The solar power satellite used in this system needs to be oriented so that its solar panels for generating electricity face the Sun, and its transmission antenna for sending microwave power to the Earth faces the Earth. A solar power satellite is a gigantic structure that is several kilometers in size and weighs tens of thousands of tons. For this reason, a great deal of energy is required to stabilize its attitude.

[0003] For example, in conventional solar power satellites as described in Non-Patent Document 1 or 2, wide and thin solar cell panels are spread out in the orbital plane of the orbit. In such a structure, a large amount of thrust is required to control the attitude of the satellite. In addition, in conventional solar power satellites as described in Non-Patent Document 3, the solar cell panels cannot be oriented toward the sun and the antennas cannot be oriented toward the earth, so the power generation capacity is insufficient. [Prior art documents] [Non-patent literature]

[0004] [Non-Patent Document 1] GM Hanley, “Satellite power systems (SPS) concept definition study I-Executive summary”, NASA, CR- 3317, 1980. [Non-Patent Document 2] DOE and NASA report; “Satellite Power System; Concept Development and Evaluation Program”, Reference System Report, Oct. 1978. [Non-Patent Document 3] S. Sasaki, K. Tanaka, K. Higuchi, N. Okuizumi, S. Kawasaki, N. Shinohara, K. Senda, and K. Ishimura, “A new concept of solar power satellite: Tethered-SPS”, Acta Astronautica, 60, pp.153 - 165, 2006. Summary of the Invention [Problem to be solved by the invention]

[0005] As mentioned above, conventionally, solar power satellites are so large that a huge amount of energy is required to stabilize their attitude. In addition, to generate and transmit electricity efficiently, special structures and devices are required to orient the solar panels toward the sun and the antennas toward the earth.

[0006] The present invention has been made in consideration of the above, and aims to provide a solar power satellite and a control method for a solar power satellite that can maintain the satellite's attitude with less energy and reduce the operating costs of the solar power satellite. [Means for solving the problem]

[0007] (1) A solar power satellite according to one embodiment of the present disclosure, A power transmission antenna; A plurality of spaced longitudinal beams; A horizontal beam connecting the vertical beams to each other; one or more solar panels; A long solar power satellite comprising: The plurality of longitudinal beams extend in a direction parallel to or inclined to a longitudinal direction of the solar power satellite, the power transmission antenna is provided on one end side of the solar power satellite in the longitudinal direction, a power transmission direction of the power transmission antenna is parallel to the longitudinal direction of the solar power satellite; The solar panel is rotatably connected to the longitudinal beam; The rotation axis of the solar cell panel is parallel to the surface of the solar cell panel and perpendicular to the longitudinal direction of the longitudinal beams. It is characterized by: According to the solar power satellite having the above-mentioned configuration, the power transmission antenna pointing to the receiving antenna on the earth is provided at one end of the long solar power satellite in the longitudinal direction, and the power transmission direction is parallel to the longitudinal direction of the solar power satellite, so that the direction of gravity and the longitudinal direction of the solar power satellite are almost the same, and therefore the satellite's attitude can be maintained with less energy. Also, because the solar cell panel is rotatably connected to the longitudinal beam, it is possible to control the surface of the solar cell panel to face the sun on the orbit, and sunlight can be efficiently received. This simplifies the control of the satellite and allows the satellite's attitude to be maintained with less energy, thereby reducing the operating costs of the solar power satellite. (2) In the solar power satellite described in (1) above, A plurality of the solar cell panels may be provided in the longitudinal direction of the vertical beam. (3) In the solar power satellite described in (2) above, A rotary joint and a support portion are further provided to connect the solar cell panel and the vertical beam, The support portion extends in a direction intersecting the longitudinal beam and the rotation axis or in the longitudinal direction of the longitudinal beam, The rotary joint may be movable along the support portion. (4) In the solar power satellite according to any one of (1) to (3) above, A plurality of the solar cell panels may be provided along the rotation axis of the solar cell panel. (5) In the solar power satellite according to any one of (1) to (3) above, The length of the vertical beam in the longitudinal direction may be three or more times the length of the solar cell panel in a direction perpendicular to the rotation axis. (6) A solar power satellite according to one embodiment of the present disclosure, A power transmission antenna; A plurality of panel structures each including a plurality of vertical beams arranged at intervals, a horizontal beam connecting the vertical beams, and a plurality of solar cell panels as a set; A long solar power satellite comprising: The plurality of longitudinal beams extend in a direction parallel to or inclined to a longitudinal direction of the solar power satellite, the power transmission antenna is provided on one end side of the solar power satellite in the longitudinal direction, a power transmission direction of the power transmission antenna is parallel to the longitudinal direction of the solar power satellite; In each of the panel structures, Each of the plurality of solar cell panels is rotatably connected to the longitudinal beam; a rotation axis of the solar cell panel is parallel to a surface of the solar cell panel and perpendicular to a longitudinal direction of the plurality of longitudinal beams; the panel structures are connected to each other at an end portion of the solar power satellite opposite to an end portion at which the power transmission antenna is provided in the longitudinal direction; It is characterized by: According to the solar power satellite having the above-mentioned configuration, the power transmission antenna pointing to the receiving antenna on the earth is provided at the end of the long solar power satellite, and the power transmission direction is parallel to the longitudinal direction of the solar power satellite, so that the direction of gravity and the longitudinal direction of the solar power satellite are almost the same, and therefore the attitude of the satellite can be maintained with less energy. Furthermore, since the solar cell panel is rotatably connected to the longitudinal beam, it is possible to control the surface of the solar cell panel to face the sun on the orbit, and the solar light can be efficiently received. Therefore, the control of the satellite is simplified, and the attitude of the satellite can be maintained with less energy, so that the operating cost of the solar power satellite can be reduced. Furthermore, the rigidity of the solar power satellite itself can be ensured by connecting the panel structures to each other. (7) In the solar power satellite described in (6) above, A rotary joint and a support portion are further provided to connect the solar cell panel and the vertical beam, The support portion extends in a direction intersecting the longitudinal beam and the rotation axis or in the longitudinal direction of the longitudinal beam, The rotary joint may be movable along the support portion. (8) In the solar power satellite described in (6) or (7) above, The length of the vertical beam in the longitudinal direction may be three or more times the length of the solar cell panel in a direction perpendicular to the rotation axis. (9) A method for controlling a solar power satellite according to one aspect of the present disclosure includes: A method for controlling a solar power satellite according to (1), (2), (6) or (7), comprising: Controlling the solar cell panel so as to face the sun and controlling the power transmission antenna so as to face the receiving antenna on the earth on the orbit. It is characterized by: (10) A method for controlling a solar power satellite according to one aspect of the present disclosure includes: A method for controlling a solar power satellite according to (2) or (3) above, When the solar power satellite is located at a phase of 40 to 50 degrees or 220 to 230 degrees from the sun direction on the orbit, the solar power satellite is rotated 180 degrees around a rotation axis parallel to a longitudinal direction of the solar power satellite. It is characterized by: Effect of the Invention

[0008] According to the solar power satellite and the control method for the solar power satellite of the present invention, the attitude of the satellite can be maintained with less energy, and the operating costs of the solar power satellite can be reduced. [Brief description of the drawings]

[0009] [Figure 1] 1 is a schematic diagram for explaining the orbit of a solar power satellite according to the present disclosure. [Diagram 2] 1 is a schematic perspective view for explaining a structure of a solar power satellite according to a first embodiment. FIG. [Diagram 3] 1 is a schematic perspective view for explaining a structure of a solar power satellite according to a first embodiment. FIG. [Figure 4]3A to 3C are schematic diagrams for explaining the orientation of solar cell panels in each phase of the solar power satellite according to the first embodiment. [Diagram 5] FIG. 11 is a schematic perspective view for explaining the structure of a solar power satellite according to a second embodiment. [Figure 6] 11 is a schematic diagram for explaining the orientation of a solar cell panel in each phase of a solar power satellite in a control method 1 according to a second embodiment. FIG. [Figure 7] 13 is a schematic diagram for explaining the orientation of a solar cell panel in each phase of a solar power satellite in a control method 2 according to a second embodiment. FIG. [Figure 8] FIG. 11 is a schematic perspective view for explaining the structure of a solar power satellite according to a third embodiment. [Figure 9] FIG. 9 is a plan view of the solar power satellite in FIG. 8, viewed in a direction parallel to the rotation axis of the solar cell panels. [Figure 10] FIG. 11 is a plan view of a solar power satellite according to a third embodiment, viewed in a direction parallel to the rotation axis of the solar cell panels. [Figure 11] FIG. 11 is a schematic perspective view for explaining the structure of a solar power satellite according to a fourth embodiment. [Figure 12] FIG. 13 is a schematic perspective view for explaining the structure of another solar power satellite according to the fourth embodiment. DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

[0010] Hereinafter, embodiments of the present invention will be described with reference to examples, but it is obvious that the present invention is not limited to the examples described below. In the following description, specific numerical values ​​and materials may be exemplified, but other numerical values ​​and materials may be applied as long as the effects of the present invention are obtained. In addition, the components of the following embodiments may be combined with each other. In this specification, a numerical range expressed using "~" means a range that includes the numerical values ​​before and after "~" as the lower and upper limits.

[0011] [First embodiment] Fig. 1 is a schematic diagram for explaining the orbit of a solar power satellite according to the present disclosure. As shown in Fig. 1, the solar power satellite 1 according to this embodiment revolves around the Earth E along an orbit 0. The solar power satellite 1 transmits microwaves from a power transmission antenna 110, which will be described later, to a receiving antenna (not shown) on the Earth, and therefore revolves around the orbit O along with the rotation of the Earth E. As illustrated in Fig. 1, the power transmission direction of the power transmission antenna 110 is parallel to the longitudinal direction of the solar power satellite 1, and therefore the longitudinal direction of the solar power satellite 1 is approximately parallel to a plane including the orbit O.

[0012] As described above, the solar power satellite 1 revolves on the orbit O together with the rotation of the Earth E, and therefore goes around the Earth E once in about one day. Also, since the power transmission antenna 110 faces the direction of the Earth E, the longitudinal direction of the solar power satellite 1 always faces the direction of the Earth E. Meanwhile, the direction in which sunlight shines on the Earth E does not change during the day. Therefore, the angle between the longitudinal direction of the solar power satellite 1 and the direction in which sunlight shines changes depending on the position of the solar power satellite 1 on the orbit O.

[0013] Therefore, in order to efficiently collect sunlight using the solar cell panel 140 installed on the solar power satellite 1, it is necessary to always maintain the collecting panel surface 140A of the solar cell panel 140 on which the solar cells are mounted perpendicular to the direction of the sun, i.e., the direction in which the sunlight is irradiated. In the solar power satellite 1 according to this embodiment, the solar cell panel 140 is rotatably connected to the vertical beam 120 that constitutes the solar power satellite 1, so that the concentrating panel surface 140A of the solar cell panel 140 can always be maintained perpendicular to the irradiation direction of the sunlight.

[0014] Next, the structure of the solar power satellite 1 according to this embodiment will be described. Figures 2 and 3 are schematic perspective views for explaining the structure of the solar power satellite 1 according to this embodiment. In the following figures, the X coordinate axis, the Y coordinate axis, and the Z coordinate axis are mutually orthogonal.

[0015] The solar power satellite 1 of this embodiment is a long structure that includes a power transmission antenna 110, two vertical beams 120 spaced apart, a horizontal beam 130 connecting the vertical beams 120, and one solar cell panel 140.

[0016] The power transmitting antenna 110 is provided at one end side in the longitudinal direction of the solar power satellite 1 (the negative side of the Z coordinate in the example of FIG. 2). The power transmitting direction of the power transmitting antenna 110 is parallel to the longitudinal direction of the solar power satellite 1. In other words, the antenna surface 110a of the power transmitting antenna 110 is perpendicular to the Z coordinate axis. The power transmitting antenna 110 is a device that pairs with a receiving antenna on the earth and transmits power to the receiving antenna, and may be, for example, an array antenna.

[0017] As illustrated in Fig. 2, the two longitudinal beams 120 are disposed at a distance from each other, and the solar cell panel 140 is located between the longitudinal beams 120. The longitudinal beams 120 extend in a direction parallel to or inclined to the longitudinal direction of the solar power satellite 1. In the example of Fig. 2 or 3, the longitudinal direction of the solar power satellite 1 is parallel to the Z coordinate axis, and the longitudinal beams 120 also extend in a direction parallel to the Z coordinate axis.

[0018] An end of the vertical beam 120 on the power transmission antenna 110 side (negative direction side of the Z coordinate) in the longitudinal direction of the vertical beam 120 is connected to the antenna holding part 111. The antenna holding part 111 is a structure for holding the power transmission antenna 110. Moreover, the vertical beam 120 is connected to the horizontal beam 130 at an end portion of the vertical beam 120 opposite the power transmission antenna 110 side (positive side of the Z coordinate) in the longitudinal direction. By supporting the vertical beam 120 by the antenna holding portion 111 and the horizontal beam 130 at each end portion of the vertical beam 120 in the longitudinal direction, the structure of the solar power satellite 1 can be strengthened and the interval between the vertical beams 120 supporting the solar cell panels 140 can be maintained. In the example of FIG. 2 or FIG. 3, the vertical beam 120, the antenna holding portion 111, and the horizontal beam 130 form an area surrounding the solar cell panels 140.

[0019] From a practical standpoint, the length of the vertical beam 120 according to this embodiment is preferably in the range of 10 to 15 km.

[0020] According to the above configuration, the power transmitting antenna 110 pointing toward the receiving antenna on the Earth is provided at one end of the long solar power satellite 1 in the longitudinal direction, and the power transmitting direction is parallel to the longitudinal direction of the solar power satellite 1, so that the direction of gravity of the Earth relative to the solar power satellite 1 nearly coincides with the longitudinal direction of the solar power satellite 1. By using such a gravity gradient stabilization method (the gravitational force of the Earth changes inversely proportional to the square of the distance, so the satellite naturally stabilizes with its longitudinal direction pointing to the center of the Earth), it becomes easier to maintain and control the attitude of the solar power satellite 1, and the satellite's attitude can be maintained with less energy.

[0021] The solar cell panel 140 is connected to be rotatable relative to the vertical beams 120. A rotation axis C of the solar cell panel 140 is parallel to the surface of the solar cell panel 140 and perpendicular to the longitudinal direction of the two vertical beams 120. The solar cell panel 140 includes a solar cell and a support panel that supports the solar cell. The solar cell includes a solar cell, electrodes, and a sealant and glass that protect these components. The solar cell is provided on one surface of the support panel. In this embodiment, the solar cell is provided on one light collecting panel surface 140A of the solar cell panel 140.

[0022] The solar cell panel 140 is preferably rotatably connected to the vertical beam 120 via a rotation joint 150. As illustrated in Fig. 2 or 3, the rotation axis C of the solar cell panel 140 coincides with the rotation axis of each of the two rotation joints 150 supporting the solar cell panel 140. The rotation axis C is parallel to the Y coordinate axis, parallel to the plane of the solar cell panel 140, and perpendicular to the longitudinal direction of the two vertical beams 120.

[0023] The rotary joint 150 is connected to an end of the solar cell panel 140 along the width direction of the solar cell panel 140 (in the example of FIG. 2, a direction parallel to the Y coordinate axis). The rotary joint 150 is connected to the vertical beam 120 on the side opposite to the side connected to the solar cell panel 140 in the direction along the rotation axis. For example, when a large solar cell panel 140 is adopted, by positioning the rotation axis C of the solar cell panel 140 so that it passes through the center of the longitudinal direction of the solar cell panel 140 (in the example of FIG. 2, the direction parallel to the Z coordinate axis), the solar cell panel 140 can be rotated stably with little driving force.

[0024] The rotary joint 150 is preferably composed of, for example, two elements that fit together and can rotate relatively around the rotation axis. The rotary joint 150 also preferably has a structure for electrically connecting the parts to be connected. As the rotary joint 150, a known part that has both a rotation mechanism and electrical conductivity, such as a slip ring, can be used. By employing such a component, the vertical beam 120 and the solar cell panel 140 can be rotatably connected, and the solar cell of the solar cell panel 140 and the power transmission antenna 110 can be electrically connected.

[0025] Because the solar cell panel 140 is rotatably connected to the vertical beam 120, the power transmission antenna 110 and the solar cell panel 140 can face in different directions around the rotation axis C. Therefore, when the solar power satellite 1 is on its orbit O, it is possible to control the light collecting panel surface 140A of the solar cell panel 140 to always face the sun while keeping the antenna surface 110a of the power transmission antenna 110 facing the Earth E, and sunlight can be efficiently received by the light collecting panel surface 140A.

[0026] From a practical standpoint, the planar size of the solar cell panel 140 according to this embodiment is preferably 5×10 km to 3×15 km.

[0027] According to the solar power satellite 1 of this embodiment, the power transmitting antenna 110 pointing toward the receiving antenna on the earth is provided at one end of the long solar power satellite 1 in the longitudinal direction, and the power transmitting direction is parallel to the longitudinal direction of the solar power satellite 1, so that the direction of gravity and the longitudinal direction of the solar power satellite 1 are almost the same. Therefore, the attitude of the solar power satellite 1 can be maintained with less energy. Also, because the solar cell panel 140 is rotatably connected to the longitudinal beam 120, it is possible to control the surface of the solar cell panel 140 to face the sun on the orbit O, and sunlight can be efficiently received. Therefore, the control of the solar power satellite 1 can be simplified and the attitude of the satellite can be maintained with less energy, thereby reducing the operating costs of the solar power satellite 1.

[0028] In the solar power satellite 1 according to the first embodiment, the strength of the entire satellite can be ensured by the longitudinal beams 120 and the like, so that the solar cell panels 140 are not required to be strong, and there is an advantage that various solar cells or solar cell panels, such as large or thin ones, can be adopted.

[0029] (Control Method) Next, a control method for the solar power satellite 1 according to this embodiment will be described. As described above, the solar power satellite 1 revolves around the Earth E along an orbit O relative to the Earth E. Figure 4 is a schematic diagram for explaining the orientation of the solar cell panel 140 in each phase (position on the orbit O) of the solar power satellite 1. The orbit O and the plane of the paper in Figure 4 are parallel to each other.

[0030] As illustrated in Fig. 4, the solar power satellite 1 periodically orbits the Earth E so as to be in the states of phase P1 to phase P8. When the solar power satellite 1 is on the orbit O, the power transmission antenna 110 is controlled to always face the direction of the Earth E. Meanwhile, as illustrated in Fig. 4, the solar cell panel 140 is controlled so that the angle with respect to the vertical beam 120 changes depending on the phase of the solar power satellite 1.

[0031] In the example of Fig. 4, the power transmission direction of the power transmitting antenna 110 is parallel to the longitudinal direction of the solar power satellite 1. In addition, the rotation axis of the solar cell panel 140 is perpendicular to the plane of Fig. 4. Therefore, the rotation direction of the solar cell panel 140 is parallel to the plane of Fig. 4. The rotation axis of the solar cell panel 140 is perpendicular to . In the example of Fig. 4, the longitudinal direction of the solar power satellite 1 and the longitudinal direction of the vertical beam 120 are parallel to each other.

[0032] In the example of FIG. 4, in phase P1, the irradiation direction of sunlight and the longitudinal direction of the solar power satellite 1 are parallel to each other, so that the light collecting panel surface 140A of the solar cell panel 140 is controlled to be perpendicular to the longitudinal direction of the vertical beam 120. In phase P2, the longitudinal direction of the solar power satellite 1 is tilted relative to the irradiation direction of the sunlight, so the light collecting panel surface 140A of the solar cell panel 140 is controlled to be perpendicular to the irradiation direction of the sun. Therefore, the longitudinal direction of the vertical beam 120 is tilted relative to the light collecting panel surface 140A of the solar cell panel 140. In phase P3, the longitudinal direction of the solar power satellite 1 is perpendicular to the irradiation direction of sunlight, so that the light collecting panel surface 140A of the solar cell panel 140 is controlled to be parallel to the longitudinal direction of the vertical beam 120. In phases P4, P6, and P8, similar to phase P2, the longitudinal direction of the solar power satellite 1 is tilted with respect to the irradiation direction of sunlight, so that the concentrating panel surface 140A of the solar cell panel 140 is controlled to be perpendicular to the irradiation direction of sunlight. In phase P5, similar to phase P1, the concentrating panel surface 140A of the solar cell panel 140 is controlled to be perpendicular to the longitudinal direction of the vertical beam 120. In phase P7, similar to phase P3, the concentrating panel surface 140A of the solar cell panel 140 is controlled to be parallel to the longitudinal direction of the vertical beam 120.

[0033] It is preferable to control the solar power satellite 1 by transmitting a control signal from a control device on Earth E to the solar power satellite 1. In addition, phase data of the solar power satellite 1 may be transmitted to a control device on Earth E, and the solar power satellite 1 may be controlled based on this phase data.

[0034] According to the control method for the solar power satellite of this embodiment, the direction of gravity and the longitudinal direction of the solar power satellite are almost the same, so the attitude of the satellite can be maintained with less energy. Also, by controlling the surface of the solar cell panel to face the sun on the orbit, sunlight can be efficiently received. This simplifies satellite control and enables the satellite's attitude to be maintained with less energy, thereby reducing the operating costs of the solar power satellite.

[0035] [Second embodiment] The solar power satellite 2 according to this embodiment has a similar basic structure to the solar power satellite 1 according to the first embodiment, but is provided with multiple solar cell panels 241 and 242 in the longitudinal direction of the vertical beam 220. The solar power satellite 2 according to this embodiment can employ a similar configuration to the solar power satellite 1 according to the first embodiment, except that multiple solar cell panels are provided, and therefore a detailed description of the similar configuration will be omitted.

[0036] FIG. 5 is a schematic perspective view for explaining the structure of a solar power satellite 2 according to the second embodiment. The solar power satellite 2 in this embodiment is a long structure that includes a power transmission antenna 210, two vertical beams 220 spaced apart, and a horizontal beam 230 connecting the vertical beams 220, as well as two solar cell panels 241 and 242. The configurations of the power transmission antenna 210, the vertical beams 220, and the horizontal beams 230 are similar to those in the first embodiment.

[0037] The two solar cell panels 241 and 242 are each rotatably connected to the vertical beam 220. The rotation axes C1 and C2 of the solar cell panels 241 and 242 are each parallel to the surface of the solar cell panel 240 and perpendicular to the longitudinal direction of the two vertical beams 220. Each of the solar cell panels 241 and 242 includes a solar cell and a solar cell support panel that supports the solar cell. The solar cell includes a solar cell, an electrode, and a sealant and glass that protect these components. The solar cell is provided on one surface of the solar cell support panel. In this embodiment, the solar cell is provided on one light collecting panel surface 241A and 242A of the solar cell panel 241 and the solar cell panel 242, respectively.

[0038] Each of the solar cell panels 241 and 242 is preferably rotatably connected to the vertical beam 220 via a rotation joint 250. As illustrated in Fig. 5, each of the rotation axis C1 of the solar cell panel 241 and the rotation axis C2 of the solar cell panel 242 coincides with the rotation axis of each of the rotation joints 250 connected to the solar cell panels 241 and 242. The rotation axes C1 and C2 are parallel to the Y coordinate axis, parallel to the respective faces of the solar cell panels 241 and 242, and perpendicular to the longitudinal direction of the two vertical beams 220. The configuration of the rotary joint 250 is the same as in the first embodiment. In each of the solar cell panels 241 and 242, the direction along the rotation axis C1 or C2 is the width direction of the solar cell panel, and the direction perpendicular to the width direction and parallel to the panel surface of the solar cell panel is the length direction of the solar cell panel.

[0039] In the example of FIG. 5, the rotation axis C1 and the rotation axis C2 are located on the end sides of the solar cell panels 241 and 242 in the length direction. However, the respective positions of the rotation axis C1 and the rotation axis C2 are not limited to this, and the rotation axis C1 and the rotation axis C2 may be disposed so as to pass through the centers of the solar cell panels 241 and 242, respectively.

[0040] In the solar power satellite 2 according to this embodiment, by providing multiple solar cell panels 241 and 242 in the longitudinal direction of the vertical beam 220, the rigidity of the solar cell panel itself can be designed to be lower than when a single solar cell panel is used, resulting in a lighter solar power satellite.

[0041] Next, a control method for the solar power satellite 2 according to this embodiment will be described. (Control method 1) First, a control method 1 for a solar power satellite 2 in which the longitudinal length of the vertical beam 220 is increased as shown in Fig. 6 will be described. In this example, the longitudinal length of the vertical beam 220 is approximately three times the longitudinal length of the solar cell panels 241 and 242. 6 is a schematic diagram for explaining the orientation of the solar cell panel 240 in each phase (position on the orbit O) of the solar power satellite 2. The orbit O and the plane of the paper in FIG.

[0042] As illustrated in Fig. 6, the solar power satellite 2 periodically orbits the Earth E so as to be in a state of phase P1 to phase P8. When the solar power satellite 2 is on its orbit O, the power transmission antenna 210 is controlled to always face the direction of the Earth E. Meanwhile, as illustrated in Fig. 6, the solar cell panels 241 and 242 are each controlled so that their angle with respect to the vertical beam 220 changes depending on the phase of the solar power satellite 2.

[0043] In the example of Fig. 6, the power transmission direction of the power transmitting antenna 210 is parallel to the longitudinal direction of the solar power satellite 2. In addition, the rotation axes of the solar cell panels 241 and 242 are perpendicular to the plane of Fig. 6. Therefore, the rotation directions of the solar cell panels 241 and 242 are parallel to the plane of Fig. 6. The rotation axes of the solar cell panels 241 and 242 are perpendicular to a plane including the orbit O. In the example of Fig. 6, the longitudinal direction of the solar power satellite 2 and the longitudinal direction of the vertical beam 220 are parallel to each other.

[0044] In the example of Figure 6, in phase P1, the direction of sunlight irradiation and the longitudinal direction of the solar power satellite 2 are parallel, so that the concentrating panel surfaces 241A and 242A of the solar cell panels 241 and 242, respectively, are controlled to be perpendicular to the longitudinal direction of the vertical beam 220. In phase P2, the longitudinal direction of the solar power satellite 2 is tilted relative to the irradiation direction of the sunlight, so that each of the condenser panel surfaces 241A and 242A is controlled to be perpendicular to the irradiation direction of the sun. Therefore, the longitudinal direction of the vertical beam 220 is tilted relative to each of the condenser panel surfaces 241A and 242A. In phase P3, the longitudinal direction of the solar power satellite 2 is perpendicular to the irradiation direction of sunlight, so that the light collecting panel surfaces 241A and 242A are controlled to be parallel to the longitudinal direction of the vertical beams 220. In phases P4, P6, and P8, similar to phase P2, the longitudinal direction of the solar power satellite 2 is tilted with respect to the irradiation direction of sunlight, so that each of the concentrating panel surfaces 241A and 242A is controlled to be perpendicular to the irradiation direction of the sun. In phase P5, similar to phase P1, each of the concentrating panel surfaces 241A and 242A is controlled to be perpendicular to the longitudinal direction of the vertical beam 220. In phase P7, similar to phase P3, each of the concentrating panel surfaces 241A and 242A is controlled to be parallel to the longitudinal direction of the vertical beam 220.

[0045] In the solar power satellite 2 relating to control method 1, the longitudinal length of the vertical beam 220 is approximately three times the longitudinal length of the two solar cell panels 241 and 242, which is preferable because it makes it less likely for the solar cell panels to cast shadows of sunlight on each other.

[0046] (Control method 2) Next, a control method 2 for the solar power satellite 2 in which the length of the longitudinal beam 220 is approximately twice the length of the solar cell panels 241 and 242 in the longitudinal direction as shown in FIG. 7 is a schematic diagram for explaining the orientation of the solar cell panel 240 in each phase (position on the orbit O) of the solar power satellite 2. The orbit O and the plane of the paper in FIG.

[0047] 7, the solar power satellite 2 periodically orbits the Earth E so as to be in a state of phase P1 to phase P8. When the solar power satellite 2 is on the orbit O, the power transmission antenna 210 is controlled to always face the direction of the Earth E. Meanwhile, as illustrated in FIG 7, the solar cell panels 241 and 242 are each controlled so that the angle with respect to the vertical beam 220 changes depending on the phase of the solar power satellite 2.

[0048] In the example of Fig. 7, the power transmission direction of the power transmitting antenna 210 is parallel to the longitudinal direction of the solar power satellite 2. In addition, the rotation axes of the solar cell panels 241 and 242 are perpendicular to the plane of Fig. 7. Therefore, the rotation directions of the solar cell panels 241 and 242 are parallel to the plane of Fig. 7. The rotation axes of the solar cell panels 241 and 242 are perpendicular to a plane including the orbit O. In the example of Fig. 7, the longitudinal direction of the solar power satellite 2 and the longitudinal direction of the vertical beam 220 are parallel to each other.

[0049] In control method 2, when the solar power satellite 2 is located on the orbit O at a phase of 40 to 50 degrees or 220 to 230 degrees from the sun direction, the solar power satellite 2 is rotated 180 degrees around a rotation axis parallel to the longitudinal direction of the solar power satellite 2. A phase of 40 to 50 degrees or 220 to 230 degrees from the direction of the sun is an angle measured based on the direction of the sunlight, and roughly corresponds to 3 a.m. or 3 p.m. on Earth.

[0050] In the example of Figure 7, in phase P1, the direction of sunlight irradiation and the longitudinal direction of the solar power satellite 2 are parallel, so that the concentrating panel surfaces 241A and 242A of the solar cell panels 241 and 242, respectively, are controlled to be perpendicular to the longitudinal direction of the vertical beam 220.

[0051] In phase P2, the longitudinal direction of the solar power satellite 2 is tilted relative to the irradiation direction of the sunlight, so that each of the condenser panel surfaces 241A and 242A is controlled to be perpendicular to the irradiation direction of the sun. Therefore, the longitudinal direction of the vertical beam 220 is tilted relative to each of the condenser panel surfaces 241A and 242A.

[0052] Furthermore, since phase P2 corresponds to a phase of 40 to 50 degrees from the sun direction, the solar power satellite 2 is rotated 180 degrees around a rotation axis parallel to the longitudinal direction of the solar power satellite 2. As a result, as shown in phase P2', the solar cell panels 241 and 242 move to the opposite side with respect to the vertical beam 220 on the plane including the orbit O. Depending on the longitudinal length of the vertical beam 220, a shadow of the solar cell panel located on the sun side (solar cell panel 241 in the example of FIG. 7) may be cast on the surface of the solar cell panel located on the rear side relative to the sun (solar cell panel 242 in the example of FIG. 7). However, by rotating the solar power satellite 2 180 degrees around the rotation axis parallel to the longitudinal direction of the solar power satellite 2 as described above and swapping the positions of the solar cell panel 241 and the solar cell panel 242 around the vertical beam 220, the effect of such a shadow can be suppressed.

[0053] In phase P3, the longitudinal direction of the solar power satellite 2 is perpendicular to the irradiation direction of sunlight, so that the light collecting panel surfaces 241A and 242A are controlled to be parallel to the longitudinal direction of the vertical beams 220.

[0054] In phase P4, the longitudinal direction of the solar power satellite 2 is tilted with respect to the direction of irradiation of the sunlight, so that the light collecting panel surface 241A and the light collecting panel surface 242A are controlled so as to be perpendicular to the direction of irradiation of the sunlight. In this phase, the problem of the shadow of the solar cell panel on the front side as described above does not occur.

[0055] In phase P5, similarly to phase P1, each of light-collecting panel surface 241A and light-collecting panel surface 242A is controlled to be perpendicular to the longitudinal direction of vertical beam 220.

[0056] In phase P6, similarly to phase P2, the longitudinal direction of solar power satellite 2 is tilted with respect to the irradiation direction of sunlight, so that each of condenser panel surface 241A and condenser panel surface 242A is controlled to be perpendicular to the irradiation direction of the sun. Furthermore, since phase P6 corresponds to a phase of 220 to 230 degrees from the sun direction, the solar power satellite 2 is rotated 180 degrees around a rotation axis parallel to the longitudinal direction of the solar power satellite 2. As a result, as shown in phase P6', the solar cell panels 241 and 242 move to the opposite side with respect to the vertical beam 220 on the plane including the revolution orbit O. As in the state of phase P2, the above-mentioned shadow effect can be suppressed by rotating the solar power satellite 2 180 degrees around a rotation axis parallel to the longitudinal direction of the solar power satellite 2 and swapping the positional relationship between the solar cell panels 241 and 242 around the vertical beam 220.

[0057] In phase P7, similar to phase P3, each of the concentrating panel surfaces 241A and 242A is controlled to be parallel to the longitudinal direction of the vertical beam 220. In phase P8, similar to phase P4, the longitudinal direction of the solar power satellite 2 is tilted with respect to the irradiation direction of the sunlight, so each of the concentrating panel surfaces 241A and 242A is controlled to be perpendicular to the irradiation direction of the sun. In this phase, the problem of the shadow of the solar cell panel on the front side as described above does not occur.

[0058] The rotation of the solar power satellite 2 around a rotation axis parallel to the longitudinal direction of the solar power satellite 2 is achieved by a thruster or a reaction wheel.

[0059] [Third embodiment] The solar power satellite of this embodiment has a basic structure similar to that of the solar power satellite of the second embodiment, but a support part is provided that connects the longitudinal beam and the rotary joint, and the rotary joint can move along this support part. The solar power satellite 3 according to this embodiment can adopt a similar configuration to the solar power satellite 2 according to the second embodiment, except that the rotary joint is movable along the support part, and therefore a detailed description of the similar configuration will be omitted.

[0060] FIG. 8 is a schematic perspective view for explaining the structure of a solar power satellite according to the third embodiment. The solar power satellite 3 of this embodiment is a long structure that includes a power transmission antenna 310, two vertical beams 320 spaced apart, and a horizontal beam 330 that connects the vertical beams 320, as well as four solar cell panels 341-344. The configurations of the power transmission antenna 310, the vertical beams 320, and the horizontal beams 330 are similar to those of the first or second embodiment.

[0061] In the solar power satellite 3 according to this embodiment, a support portion 361 and a support portion 362 are further provided, and each of the solar cell panels 341 and 342 and the vertical beam 320 are connected to the vertical beam 320 via a plurality of rotary joints 351, the support portion 361 and the support portion 362. In addition, the solar cell panels 343 and 344 are connected to the vertical beam 320 via a plurality of rotary joints 350.

[0062] The support portion 361 extends in a direction intersecting the rotation axis C1 of the vertical beam 320 and the solar cell panel 341 or in the longitudinal direction of the vertical beam 320. Similarly, the support portion 362 extends in a direction intersecting the rotation axis C2 of the vertical beam 320 and the solar cell panel 342 or in the longitudinal direction of the vertical beam 320. In the example of FIG. 8, the support portion 361 and the support portion 362 extend in a direction perpendicular to the longitudinal beam 320 and the rotation axis C1 of the solar cell panel 341 (or the rotation axis C2 of the solar cell panel 342), respectively.

[0063] 8, the rotation axis C1 of the solar cell panel 341, the rotation axis C2 of the solar cell panel 342, the rotation axis C3 of the solar cell panel 343, and the rotation axis C4 of the solar cell panel 344 each coincide with the rotation axis of the rotation joints 350 and 351 connected to each of the solar cell panels 341 to 344. The rotation axes C1 to C4 are parallel to the Y coordinate axis, parallel to the surfaces of the solar cell panels 341 to 344, and perpendicular to the longitudinal direction of the two vertical beams 320.

[0064] The configuration of the rotary joint 350 or 351 is the same as that of the first or second embodiment. In each of the solar cell panels 341 to 344, the direction along the rotation axes C1 to C4 is the width direction of each solar cell panel, and the direction perpendicular to the width direction and parallel to the panel surface of each solar cell panel is the length direction of each solar cell panel.

[0065] In the example of FIG. 8, the rotation axes C1 to C4 are located on the end sides of the solar cell panels 341 to 344 in the longitudinal direction, respectively. However, the positions of the rotation axes C1 to C4 are not limited to this, and the rotation axes C1 to C4 may be disposed so as to pass through the centers of the solar cell panels 341 to 344.

[0066] In the solar power satellite 3 according to this embodiment, each rotary joint 351 is movable along the support portion 361 or the support portion 362. As a result, for example, even if a shadow of a solar cell panel located on the sun side is cast on the surface of a solar cell panel located on the rear side, the solar cell panel can be moved to reduce the effect of this shadow. Therefore, power loss can be suppressed.

[0067] The pair of support parts 361 and the pair of support parts 362 may be, for example, long members having a rail structure or a groove. The rotary joint 351 may be configured to move along such a rail structure or groove.

[0068] Next, a method for controlling the solar power satellite 3 according to this embodiment will be described. (Control method 3) The basic operation of the solar power satellite 3 according to this embodiment is the same as that of the control method 1 according to the second embodiment. The solar power satellite 3 periodically orbits the Earth, and when the solar power satellite 3 is on an orbit O, the power transmission antenna 310 is controlled to always face the Earth. Also, each of the solar cell panels 341 to 344 is controlled so that the angle with respect to the vertical beam 320 changes depending on the phase of the solar power satellite 3.

[0069] Fig. 9 is a plan view of the solar power satellite 3 in Fig. 8 viewed from a direction parallel to the rotation axes C1 to C4. Therefore, the rotation directions of the solar cell panels 341 to 344 are parallel to the paper surface of Fig. 9. Furthermore, the longitudinal axis L of the vertical beam 320 is parallel to the paper surface of Fig. 9. The rotation axes of the solar cell panels 341 to 344 are perpendicular to a plane including the orbit O.

[0070] In the example of Fig. 9, sunlight is irradiated from the end side of the longitudinal beam 320 of the solar power satellite 3 opposite to the power transmission antenna 310 side in the longitudinal direction. In other words, the solar power satellite 3 is located between the Earth and the Sun. In addition, the longitudinal direction of the longitudinal beam 320 of the solar power satellite 3 is inclined with respect to the irradiation direction of the sunlight. In this state, the condensing panel surfaces 341A to 344A of the solar cell panels 341 to 344 are controlled to be perpendicular to the direction of solar irradiation, respectively. Therefore, the longitudinal direction of the vertical beam 320 is inclined with respect to the condensing panel surfaces 341A to 344A, respectively.

[0071] In addition, the solar cell panel 341 connected to the vertical beam 320 via the support portion 361 and the solar cell panel 342 connected to the vertical beam 320 via the support portion 362 move parallel to the support portion 361 or the support portion 362 in a direction perpendicular to the longitudinal axis L of the vertical beam 320. Depending on the length of the vertical beams 320 in the longitudinal direction and the number of solar cell panels, the shadow of the solar cell panel located on the sun side (solar cell panel 342 in the example of FIG. 9) may be cast on the surface of the solar cell panel located on the rear side relative to the sun (solar cell panel 343 in the example of FIG. 9). However, by translating the solar cell panel connected to the vertical beams via the support parts in a direction perpendicular to the vertical beams as described above, the effect of such a shadow can be suppressed.

[0072] Also, control may be performed as illustrated in Fig. 10. Fig. 10 is a plan view of the solar power satellite 4 as viewed in a direction parallel to the rotation axes of the solar cell panels 441 and 442, similar to Fig. 9. In the example of FIG. 10, the rotary joint 450 holding the solar cell panel 441 can move along the longitudinal direction of the vertical beam 420 by a support portion extending in the longitudinal direction of the vertical beam 420. In this case, the support portion may be, for example, a rail structure or a groove provided in a partial range of the vertical beam 420 along the axis line L of the vertical beam 420. This allows the rotary joint 450 to move in parallel along the longitudinal direction of the vertical beam 420. As illustrated in FIG. 10, it is possible to prevent the solar cell panel 441 from overlapping with the solar cell panel 442 in a specific direction. Therefore, the light collecting panel surface 441A of the solar cell panel 441 and the light collecting panel surface 442A of the solar cell panel 442 can efficiently collect light. As described above, the effect of such shadows can be suppressed by moving the solar cell panel connected to the vertical beam 420 in a direction parallel to the vertical beam via a support portion provided along the longitudinal direction of the vertical beam.

[0073] [Fourth embodiment] The solar power satellite according to this embodiment has a basic structure similar to that of the solar power satellites according to the above-mentioned embodiments, but is provided with a panel structure including a plurality of longitudinal beams arranged at intervals, a cross beam connecting the longitudinal beams, and a plurality of solar cell panels as a set. The solar power satellite according to this embodiment can adopt a similar configuration to the solar power satellites according to the above-mentioned embodiments, except that it is provided with a plurality of solar cell panels each including a plurality of panel structures, and therefore a detailed description of the similar configuration will be omitted.

[0074] FIG. 11 is a schematic perspective view for explaining the structure of a solar power satellite 5 according to the fourth embodiment. The solar power satellite 5 according to this embodiment includes a power transmission antenna 510. The solar power satellite 5 also includes a plurality of vertical beams 520 arranged at intervals, a horizontal beam 530 connecting the vertical beams 520 to each other, and a plurality of solar cell panels 541-544 (or solar cell panels 545-548) as a set of panel structures (panel structure 501 or panel structure 502).

[0075] 11, in the panel structure 501, two vertical beams 520 are disposed with a gap between them, and four solar cell panels 541-544 are located between the vertical beams 520. The vertical beams 520 extend in a direction parallel to the longitudinal direction of the solar power satellite 5. In the example of FIG. 11, the longitudinal direction of the solar power satellite 5 is parallel to the Z coordinate axis, and each vertical beam 520 also extends in a direction parallel to the Z coordinate axis. Panel structure 502 has the same configuration as panel structure 501. In panel structure 502, two vertical beams 520 are disposed with a gap therebetween, and four solar cell panels 545-548 are positioned between vertical beams 520.

[0076] An end of the vertical beam 520 on the power transmission antenna 510 side (negative side of the Z coordinate) in the longitudinal direction of the vertical beam 520 is connected to the antenna holding part 511. In addition, the vertical beam 520 is connected to the horizontal beam 530 at an end of the vertical beam 520 opposite to the power transmission antenna 510 side (positive side of the Z coordinate) in the longitudinal direction of the vertical beam 520. Furthermore, at the end of the vertical beam 520 opposite the power transmission antenna 510 side (positive side of the Z coordinate) in the longitudinal direction, the panel structure 501 and the panel structure 502 are connected via a support beam 560. By supporting the vertical beam 520 by the antenna holding part 511, the cross beam 530, and further the support beam 560 at each end side in the longitudinal direction of the vertical beam 520, the rigidity of the solar power satellite 5 can be further increased.

[0077] The multiple solar cell panels 541-548 are rotatably connected to each vertical beam 520. Rotation axes C1-C8 of the solar cell panels 541-548 are parallel to the plane of the solar cell panels 541-548 and perpendicular to the longitudinal direction of the vertical beam 520. The solar cell panels 541 to 548 are preferably rotatably connected to the vertical beam 520 via a rotary joint 550. As illustrated in Fig. 11, the rotation axes C1 to C8 of the solar cell panels 541 to 548 respectively coincide with the rotation axes of the two rotary joints 550 supporting the solar cell panels 541 to 548. The rotation axes C1 to C8 are parallel to the Y coordinate axis, parallel to the plane of the solar cell panels 541 to 548, and perpendicular to the longitudinal direction of the vertical beam 520.

[0078] In a plan view from a direction parallel to the rotation axes C1 to C8 of the solar cell panels 541 to 548, the solar power satellite 5 appears as a rectangle as a whole. The power transmission antenna 510, the vertical beam 520, the horizontal beam 530, and the solar cell panels 541 to 548 are configured similarly to the above-described embodiments.

[0079] Next, another example of the solar power satellite according to this embodiment will be described with reference to FIG. Fig. 12 is a schematic perspective view for explaining the structure of the solar power satellite 6. The solar power satellite 6 illustrated in Fig. 12 can employ a similar configuration to the solar power satellite 5 illustrated in Fig. 11 except that the vertical beams 620 constituting the panel structures 601 and 602 are connected to each other at the ends of the vertical beams 620 on the opposite side to the power transmission antenna 610 side (the positive side of the Z coordinate) in the longitudinal direction of the vertical beams 620, and therefore a detailed description of the similar configuration will be omitted.

[0080] In the solar power satellite 6, the vertical beams 620 constituting the panel structures 601 and 602 are connected to each other at the end of the vertical beams 620 opposite the power transmission antenna 610 side (the positive side of the Z coordinate) in the longitudinal direction of the vertical beams 620. The panel structures 601 and 602 share a cross beam 630 , and the vertical beams 620 included in each panel structure are connected to each other by the cross beam 630 .

[0081] The solar power satellite 6 comprises a plurality of vertical beams 620 arranged at intervals, a horizontal beam 630 connecting the vertical beams 620, and a plurality of solar cell panels 641 and 642 (solar cell panels 643 and 644) as a set of panel structures (panel structure 601 or panel structure 602).

[0082] 12, in the panel structure 601, two longitudinal beams 620 are disposed at an interval, and two solar cell panels 641 and 642 are located between the longitudinal beams 620. Each of the longitudinal beams 620 extends in a direction inclined with respect to the longitudinal direction of the solar power satellite 6.

[0083] The solar power satellite 6 illustrated in FIG. 12 appears as an isosceles triangle as a whole when viewed from a direction parallel to the rotation axes C1 to C4 of the solar cell panels 641 to 644.

[0084] The structure of the solar power satellite 6 has the advantage of reducing the number of beam structures and making it lighter.

[0085] According to the solar power satellite of this embodiment, the power transmission antenna pointing to the receiving antenna on the earth is provided at the end of the long solar power satellite, and the power transmission direction is parallel to the longitudinal direction of the solar power satellite, so that the direction of gravity and the longitudinal direction of the solar power satellite are almost the same, and therefore the attitude of the solar power satellite can be maintained with less energy. Furthermore, since the solar cell panel is rotatably connected to the longitudinal beam, it is possible to control each surface of the solar cell panel to face the sun on the orbit, and the solar light can be efficiently received. Therefore, the control of the solar power satellite is simplified, and the attitude of the solar power satellite can be maintained with less energy, so that the operating cost of the solar power satellite can be reduced. Furthermore, the panel structure and the panel structures are connected to each other at each end side in the longitudinal direction of the longitudinal beams that constitute each panel structure, so that the rigidity of the solar power satellite itself can be ensured.

[0086] In the solar power satellite according to this embodiment, the support portion that connects the vertical beam and the rotary joint as described in the third embodiment may be adopted, so that the rotary joint can be moved along the support portion. As a result, for example, even if a shadow of a solar cell panel located on the sun side is cast on the surface of a solar cell panel located on the rear side, the solar cell panel can be moved to reduce the effect of this shadow. Therefore, power loss can be suppressed.

[0087] The control method of the solar power satellite according to this embodiment can employ the control methods of the above embodiments.

[0088] [Variations] In the solar power satellite according to each of the above embodiments, it is preferable that a plurality of solar panels are provided along the rotation axis of the solar panel. By arranging the same number of solar panels along the rotation axis of each vertical beam, it is possible to maintain good balance in the direction perpendicular to the longitudinal direction of the vertical beam.

[0089] In the solar power satellite according to each of the above embodiments, it is preferable that the length of the longitudinal beam in the longitudinal direction is three or more times the length in the direction perpendicular to the rotation axis of the solar cell panel. The direction perpendicular to the rotation axis of the solar cell panel is also the length direction of the solar cell panel described in the above embodiments. By making the longitudinal length of the vertical beam more than three times the length of the solar panel, the length in the longitudinal direction of the solar power satellite, i.e., in the direction of gravity, is secured, and the attitude of the solar power satellite can be stabilized with less energy.

[0090] According to the solar power satellite and the control method for the solar power satellite of the present disclosure, the attitude of the satellite can be maintained with less energy, and the operating cost of the solar power satellite can be reduced. Therefore, by using the solar power satellite and the control method for the solar power satellite of the present disclosure, it is possible to supply a large amount of power of several million kW to the earth. Furthermore, by using the solar power satellite and the control method for the solar power satellite of the present disclosure, it is possible to avoid the problems of global warming and resource depletion. [Explanation of symbols]

[0091] 1,2,3,4,5,6 Solar Power Satellite 110,210,310,410,510,610 Power transmission antenna 111,211,311,411,511,611 Antenna holder 120,220,320,420,520,620 Longitudinal beam 130,230,330,430,530,630 Cross beam 140,241,242,341,342,343,344,441,442,541,542,543,544,545,546,547,548,641,642,643,644 Solar Panels 150,250,350,351,450,550,650 Rotational joint 361,362 Support part 501,502,601,602 Panel structure

Claims

1. A power transmission antenna; A plurality of spaced longitudinal beams; A horizontal beam connecting the vertical beams to each other; one or more solar panels; A long solar power satellite comprising: The plurality of longitudinal beams extend in a direction parallel to or inclined to a longitudinal direction of the solar power satellite, the power transmission antenna is provided on one end side of the solar power satellite in the longitudinal direction, a power transmission direction of the power transmission antenna is parallel to the longitudinal direction of the solar power satellite; The solar panel is rotatably connected to the longitudinal beam; The rotation axis of the solar cell panel is parallel to the surface of the solar cell panel and perpendicular to the longitudinal direction of the longitudinal beams. A solar power satellite.

2. A plurality of the solar cell panels are provided in the longitudinal direction of the vertical beam.

2. The solar power satellite according to claim 1 .

3. A rotary joint and a support portion are further provided to connect the solar cell panel and the vertical beam, The support portion extends in a direction intersecting the longitudinal beam and the rotation axis or in the longitudinal direction of the longitudinal beam, The rotary joint is movable along the support.

3. The solar power satellite according to claim 2.

4. A plurality of the solar panels are provided along the rotation axis of the solar panel.

3. The solar power satellite according to claim 1 or 2.

5. The length of the longitudinal beam in the longitudinal direction is three times or more the length of the solar cell panel in a direction perpendicular to the rotation axis.

3. The solar power satellite according to claim 1 or 2.

6. A power transmission antenna; A plurality of panel structures each including a plurality of vertical beams arranged at intervals, a horizontal beam connecting the vertical beams, and a plurality of solar cell panels as a set; A long solar power satellite comprising: The plurality of longitudinal beams extend in a direction parallel to or inclined to a longitudinal direction of the solar power satellite, the power transmission antenna is provided on one end side of the solar power satellite in the longitudinal direction, a power transmission direction of the power transmission antenna is parallel to the longitudinal direction of the solar power satellite; In each of the panel structures, Each of the plurality of solar cell panels is rotatably connected to the longitudinal beam; a rotation axis of the solar cell panel is parallel to a surface of the solar cell panel and perpendicular to a longitudinal direction of the plurality of longitudinal beams; the panel structures are connected to each other at an end portion of the solar power satellite opposite to an end portion at which the power transmission antenna is provided in the longitudinal direction; A solar power satellite.

7. A rotary joint and a support portion are further provided to connect the solar cell panel and the vertical beam, The support portion extends in a direction intersecting the longitudinal beam and the rotation axis or in the longitudinal direction of the longitudinal beam, The rotary joint is movable along the support.

7. The solar power satellite according to claim 6.

8. The length of the longitudinal beam in the longitudinal direction is three times or more the length of the solar cell panel in a direction perpendicular to the rotation axis.

8. A solar power satellite according to claim 6 or 7.

9. A method for controlling a solar power satellite according to claim 1, 2, 6 or 7, comprising the steps of: Controlling the solar cell panel so as to face the sun and the power transmission antenna so as to face the receiving antenna on the earth on the orbit. A method for controlling a solar power satellite.

10. 4. A method for controlling a solar power satellite according to claim 2, further comprising the steps of: When the solar power satellite is located at a phase of 40 to 50 degrees or 220 to 230 degrees from the sun direction on the orbit, the solar power satellite is rotated by 180 degrees around a rotation axis parallel to the longitudinal direction of the solar power satellite. A method for controlling a solar power satellite.

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