Communication system

Abstract

To provide a communication system that enables stable communication between the lunar surface and Earth. [Solution] The communication system comprises a lunar orbiting satellite constellation composed of multiple lunar orbiting satellites, an Earth orbiting satellite constellation composed of multiple Earth orbiting satellites, and an Earth station. Each lunar orbiting satellite is equipped with an antenna for the probe to communicate with a probe on the lunar surface, an antenna for other lunar orbiting satellites to communicate with other lunar orbiting satellites, and an antenna for Earth orbiting satellites to communicate with Earth orbiting satellites. Each Earth orbiting satellite is equipped with an antenna for lunar orbiting satellites to communicate with lunar orbiting satellites, an antenna for other Earth orbiting satellites to communicate with other Earth orbiting satellites, and an Earth station antenna to communicate with the Earth station. Information from the probe is transmitted from the lunar orbiting satellite constellation to the Earth orbiting satellite constellation, and from the Earth orbiting satellite constellation to the Earth station.

Description

Technical Field

[0001] The present invention relates to a communication system, and particularly to a communication system that realizes communication between the lunar surface and the Earth.

Background Art

[0002] Conventionally, position measurement support for mobile probes that move on celestial bodies such as the Moon has been disclosed (for example, Patent Document 1).

Prior Art Documents

Patent Documents

[0003]

Patent Document 1

Summary of Invention

Means for Solving the Problems

[0004] A communication system according to an embodiment of the present invention is a communication system comprising: a lunar orbiting satellite constellation composed of a plurality of lunar orbiting satellites that orbit the Moon; an Earth orbiting satellite constellation composed of a plurality of Earth orbiting satellites that orbit the Earth; and an Earth station arranged on the Earth, wherein the lunar orbiting satellite includes a probe antenna that performs communication with a probe on the lunar surface, another lunar orbiting satellite antenna that performs communication with another lunar orbiting satellite, and an Earth orbiting satellite antenna that performs communication with an Earth orbiting satellite, the Earth orbiting satellite includes a lunar orbiting satellite antenna that performs communication with a lunar orbiting satellite, another Earth orbiting satellite antenna that performs communication with another Earth orbiting satellite, and an Earth station antenna that performs communication with an Earth station, and information from the probe is transmitted from the lunar orbiting satellite constellation to the Earth orbiting satellite constellation, and is transmitted from the Earth orbiting satellite constellation to the Earth station.

[0005] In a communication system according to one embodiment of the present invention, information from a probe may be received by at least one lunar orbiting satellite constellation, transmitted between the multiple lunar orbiting satellites according to the relative position between the lunar orbiting satellite that received the information from the probe and the multiple Earth orbiting satellites, transmitted from at least one lunar orbiting satellite constellation to at least one Earth orbiting satellite constellation, and transmitted from said Earth orbiting satellite to an Earth station.

[0006] In a communication system according to one embodiment of the present invention, the lunar orbiting satellite constellation may consist of a group of satellites orbiting in low Earth orbit (LEO) orbit and a group of satellites orbiting in high Earth orbit orbit at an altitude higher than that of the low Earth orbit group.

[0007] In a communication system according to one embodiment of the present invention, a lunar orbiting satellite may communicate with other lunar orbiting satellites using at least one of light or radio waves.

[0008] In a communication system according to one embodiment of the present invention, a lunar orbiting satellite and an Earth orbiting satellite may communicate using at least one of light or radio waves.

[0009] In a communication system according to one embodiment of the present invention, the antenna for the lunar orbiting satellite that communicates with the lunar orbiting satellite and the antenna for the earth station that communicates with the earth station may be the same for an Earth orbiting satellite.

[0010] In a communication system according to one embodiment of the present invention, the antenna for other lunar orbiting satellites that communicates with other lunar orbiting satellites and the antenna for Earth orbiting satellites that communicates with Earth orbiting satellites may be the same.

[0011] In a communication system according to one embodiment of the present invention, information from the probe may be transmitted between M of the multiple lunar orbiting satellites constituting a lunar orbiting satellite constellation and N of the multiple Earth orbiting satellites constituting an Earth orbiting satellite constellation (where M and N are integers of 1 or more, including M=N).

[0012] A communication system according to one embodiment of the present invention may provide a packet communication network using an Earth-orbiting satellite constellation and a lunar-orbiting satellite constellation. [Brief explanation of the drawing]

[0013] [Figure 1] Figure 1 is a schematic diagram of a communication system configuration according to one embodiment of the present invention, and is a schematic diagram illustrating one embodiment of the present invention. [Figure 2] Figure 2 is an example of a block diagram of an Earth-orbiting satellite according to one embodiment of the present invention. [Figure 3] Figure 3 is an example of a block diagram of a lunar orbiting satellite according to one embodiment of the present invention. [Figure 4] Figure 4 shows an example of a sequence between a probe, a lunar orbiting satellite constellation, an Earth orbiting satellite constellation, and a ground station according to one embodiment of the present invention. [Modes for carrying out the invention]

[0014] Hereinafter, an embodiment of the invention described herein (also referred to as the present invention) will be explained using the figures. Note that the figures are examples only, and the present invention is not limited to what is shown in the figures. For example, the number and shape of the Earth-orbiting satellites, lunar-orbiting satellites, ground stations (earth stations), and probes that constitute each illustrated satellite constellation, the sequence diagrams, the Earth and the Moon, and the arrangement of the Earth-orbiting satellites, lunar-orbiting satellites, ground stations, and probes relative to them are examples only, and the present invention is not limited to these.

[0015] In recent years, with the progress of lunar base plans, there is a need to establish a stable communication system between the lunar surface and Earth. This communication system will be used not only for the lunar base after its completion, but also for collecting data from probes operating on the lunar surface during the construction of the lunar base. Conventionally, communication between such facilities on the lunar surface and facilities on Earth has been carried out via lunar orbiting satellites. However, lunar orbiting satellites have the problem that they cannot communicate directly with Earth in areas invisible from Earth, such as the far side of the Moon and the polar regions. In contrast, according to one embodiment of the present invention, a satellite constellation of multiple lunar orbiting satellites may be deployed and communicate with an existing satellite constellation consisting of Earth orbiting satellites. The satellite constellation of lunar orbiting satellites may be arranged so that multiple lunar orbiting satellites cover the entire lunar surface, providing means of communication in all areas of the lunar surface. Furthermore, by having the satellite constellations communicate with each other in the lunar orbit and the Earth's orbit, it may be possible to establish constant communication between the lunar surface and Earth.

[0016] <System Configuration> Figure 1 shows an example configuration of a communication system according to one embodiment of the present invention. The communication system 600 may include an Earth orbiting satellite constellation 10 consisting of multiple Earth orbiting satellites 100 (100a, 100b, ...) orbiting in a low-altitude orbit of the Earth's ERT, a ground station (earth station) ES on the Earth's ERT, and a lunar orbiting satellite constellation 30 consisting of multiple lunar orbiting satellites 300 (300a, 300b, ...) orbiting in a low-altitude orbit of the Moon's MO. A satellite constellation is a system in which a large number (tens to tens of thousands) of small satellites are launched into orbit and made to function as a single unit. Because a satellite constellation can cover the entire Earth, it can efficiently provide communication services and Earth observation services. As will be described in detail later, in one embodiment of the present invention, the Earth orbiting satellite constellation 10 may include at least one Earth orbiting satellite 11 orbiting in a high-altitude orbit (altitude approximately 36,000 km) of the Earth's ERT. Furthermore, Lunar Orbiter Constellation 30 may include at least one Lunar Orbiter 31 orbiting in a high-altitude orbit (approximately 8,700 km above the Moon). Low-altitude orbit (LEO) refers to an orbit at an altitude of approximately 200-2000 km for Earth, and an orbit at an altitude of approximately 50-100 km for the Moon. Hereafter, low-altitude orbit and high-altitude orbit will also be referred to as "low orbit" and "high orbit (geostationary orbit)," respectively.

[0017] The communication system 600 may further include a management device (server), not shown in the diagram, installed on the Earth's ERT. The management device may issue commands to correct the orbits of each satellite included in the Earth orbiting satellite constellation 10 and the lunar orbiting satellite constellation 30, respectively, and perform processes related to establishing communication links between the satellites, as described later.

[0018] An overview of a communication system according to one embodiment of the present invention will be described. Data (information) collected by a rover (RV) exploring the lunar surface while moving is transmitted from the rover and received by at least one of the multiple lunar orbiting satellites 300 that make up the lunar orbiting satellite constellation 30 (in the example in Figure 1, lunar orbiting satellite 300a). Here, let's assume that lunar orbiting satellite 300a is located in a region not visible from Earth. In this case, the data may be routed among the multiple lunar orbiting satellites 300 and transmitted to lunar orbiting satellite 300b located in a region visible from Earth. That is, the data may be transmitted among the multiple lunar orbiting satellites 300 depending on their relative positions with respect to the multiple Earth orbiting satellites 100. Furthermore, data may be transmitted from the lunar orbiting satellite constellation 30 to the Earth orbiting satellite constellation 10 via a communication link DAT between the lunar orbiting satellite 300b and at least one of the multiple Earth orbiting satellites 100 that make up the Earth orbiting satellite constellation 10 (in the example in Figure 1, Earth orbiting satellite 100a). In the Earth orbiting satellite constellation 10, data may also be routed among the multiple Earth orbiting satellites 100, and in the example in Figure 1, data may be transmitted from Earth orbiting satellite 100b to the ground station ES. Note that the transmission of data from the ground station ES to the probe RV and lunar bases (not shown) via the Earth orbiting satellite constellation 10 and the lunar orbiting satellite constellation 30 may be achieved by the reverse flow described above.

[0019] Figure 1 shows an example where data from the lunar orbiting satellite 300b is received by a single Earth orbiting satellite 100a. However, data from the lunar orbiting satellite 300 may be received by two or more Earth orbiting satellites 100. In other words, the lunar orbiting satellite 300 and the Earth orbiting satellites 100 may transmit and receive information in a one-to-many relationship. This increases the probability that data will be transmitted to Earth even when affected by attenuation due to electromagnetic waves in space, thereby improving reception quality.

[0020] Further, in FIG. 1, an example is shown in which data from the probe RV is received by a single lunar orbiting satellite 300a. However, the data from the probe RV may be received by two or more lunar orbiting satellites 300. Furthermore, the data may be transmitted to the constellation of Earth-orbiting satellites 10 via separate routes. That is, the lunar orbiting satellites 300 and the Earth-orbiting satellites 100 may transmit and receive information in an M-to-N relationship (where M may be equal to N). With this configuration as well, even in the case of being affected by attenuation caused by electromagnetic waves or the like in outer space, it is possible to increase the probability that data is transmitted to the Earth side, and to improve reception quality.

[0021] Note that communication between the respective satellites constituting each satellite constellation, and communication between the Earth-orbiting satellites 100 and the lunar orbiting satellites 300 may be performed via Inter Satellite Link (ISL). As communication means for the Inter Satellite Link, radio waves (microwaves), light (lasers) or the like may be used. This enables high-speed data transmission. In the case of using light, long-distance communication can be efficiently achieved with a smaller apparatus compared to the case of using radio waves.

[0022] Further, existing technologies may be used for data routing between satellites. For example, a multi-hop routing protocol for mobile objects may be used for data routing between satellites. Alternatively, routing paths between satellites may be set in advance. Alternatively, each satellite may be capable of autonomously selecting an optimal communication link with another satellite on the basis of its own position and communication state. Note that a management apparatus on the Earth may instruct each satellite on the routing paths, without relying on autonomous routing by each of these satellites or program-based routing, or in cooperation with each satellite.

[0023] Note, in setting the route, each satellite may be able to grasp its own position. For acquisition of position information by each satellite, existing technologies such as, for example, an Inertial Navigation System (INS), tracking by a ground station ES, celestial navigation, Global Positioning System (GPS) signals, and the like may be used. Further, each satellite may be able to acquire its own position by exchanging position information with each other through inter-satellite communication.

[0024] Note, regarding the earth-orbiting satellite constellation 10, many satellite constellations for communication and positioning already exist in the sky above the Earth, and these provide communication and positioning services that cover the entire Earth (for example, OneWeb (registered trademark) and the like). For the earth-orbiting satellite constellation 10 in one embodiment of the present invention, these existing ones may be utilized. However, as described above, the earth-orbiting satellites 100 may be equipped with communication devices (antennas and the like) for lunar-orbiting satellites, for establishing communication links with the lunar-orbiting satellites 300.

[0025] Further, data from the lunar-orbiting satellite constellation 30 may be received by the earth-orbiting satellites 11 orbiting in a high orbit (geostationary orbit). The high-orbit earth-orbiting satellites 11 have a wide coverage area and stable communication, so it is possible to increase the possibility that data from the lunar-orbiting satellites 300 is transmitted to the ground station.

[0026] Regarding the lunar-orbiting satellite constellation 30, similar to the Global Navigation Satellite System (GNSS) of the Earth, in order to accurately provide position information, at least 4 lunar-orbiting satellites 300 may be constantly required within the field of view. To cover the entire lunar surface and ensure 4 or more satellites are within the visible range in real time, a plurality of orbital planes and appropriate satellite arrangement are required, which will be described below.

[0027] <In the case of 3-orbit configuration> When using three orbits (e.g., two halo orbits + one distant retrograde orbit (DRO)), five satellites can be placed in each orbit, for a total of 15 satellites, which is expected to improve the overall coverage of the lunar surface. However, with a three-orbit configuration, there is a possibility of insufficient coverage in some areas (especially near the equator), making complete real-time coverage difficult.

[0028] <In the case of a 4-orbit configuration> In the combination of two halo orbits (near the L1 and L2 points of the Lagrange) and two DROs, four satellites can be placed in each orbit, for a total of 16 satellites, which is expected to provide 100% coverage of the entire lunar surface. In this configuration, the position dilution of precision (PDOP) is stable, and at least four satellites remain within the visible range in real time.

[0029] <If there are 5 or more orbitals> While increasing the number of orbits can improve redundancy and accuracy, around 16 satellites are considered sufficient, and increasing them further would decrease cost efficiency.

[0030] Furthermore, redundancy must be considered to maintain service even in the event of a satellite failure. The number of satellites to account for redundancy can typically be designed as an increase of 20-30% of the total number of satellites. For example, in a 4-orbit configuration (16 satellites), 4-6 additional satellites can be added for redundancy, resulting in a total of 20-22 satellites. This ensures that at least 4 satellites remain within constant visibility even if some fail. Additionally, placing backup satellites in standby orbits allows for rapid service continuation in the event of a satellite failure. Backup satellites may be launched from the ground when necessary.

[0031] Furthermore, data transmission and reception between the Earth-orbiting satellite constellation 10 and the lunar orbiting satellite 31, which orbits in high orbit (geostationary orbit), may be performed by the lunar orbiting satellite 31. Because the lunar orbiting satellite 31 in high orbit has a wide coverage area and stable communication, it can increase the likelihood of successful data transmission and reception between it and the Earth-orbiting satellite 100.

[0032] <Earth orbiting satellite> The configuration of Earth-orbiting satellite 100 will be explained using Figure 2.

[0033] The Earth-orbiting satellite 100 may be equipped with a control device 110, a communication device 120, a propulsion device 130, a power supply device 140, an operation control device 150, and a memory device 170.

[0034] The control device 110 may be a computer equipped with processing circuits for controlling each device. The processing circuits may be a processor that executes programs stored in memory. The processor may include, for example, a central processing unit (CPU), an MPU (Micro Processing Unit), a GPU (Graphics Processing Unit), a multiprocessor, an ASIC (Application-Specific Integrated Circuit), an FPGA (Field Programmable Gate Array), etc., and each process disclosed in each embodiment may be realized by logic circuits (hardware) or dedicated circuits formed on an integrated circuit (IC (Integrated Circuit) chip, LSI (Large Scale Integration)), etc. Furthermore, these circuits may be realized by one or more integrated circuits, and the multiple processes shown in each embodiment may be realized by a single integrated circuit.

[0035] Furthermore, the control device 110 may perform the routing control and self-position estimation described above. The processing performed by the control device 110 may, to the extent feasible, be implemented using machine learning or AI (Artificial Intelligence).

[0036] The communication device 120 may include a lunar orbiting satellite antenna 122, a ground station antenna 124, and another Earth orbiting satellite antenna 126. The communication device 120 may control communication with the lunar orbiting satellite 300 constituting the lunar orbiting satellite constellation 30 using the lunar orbiting satellite antenna 122. The communication device 120 may also control communication with the ground station ES using the ground station antenna 124. Furthermore, the communication device 120 may control communication with another Earth orbiting satellite 100 using the other Earth orbiting satellite antenna 126. These communications may be conducted using radio waves (microwaves) or light (lasers). As mentioned above, the Earth orbiting satellite 100 may be an existing one, in which case the ground station antenna 124 or another Earth orbiting satellite antenna 126 may also function as the lunar orbiting satellite antenna 122, and the antenna's directivity may be changed under the control of the control device 110. This will reduce the weight of the satellite and allow for maximum utilization of existing satellites.

[0037] The propulsion system 130 may be a device that provides thrust to the Earth-orbiting satellite 100. The propulsion system 130 may be a chemical propulsion system, an electric propulsion system, etc.

[0038] The power supply unit 140 may be a solar cell or a storage battery, and may be controlled by the control device 110 and supply power to each device of the Earth-orbiting satellite 100.

[0039] The motion control device 150 may be a device for controlling the attitude of the Earth-orbiting satellite 100. The motion control device 150 may include attitude sensors such as a gyroscope and an Earth sensor, actuators, etc., and the controller may change or maintain the angular velocity and line of sight of the Earth-orbiting satellite 100 in a desired direction.

[0040] The storage device 170 may be a memory (for example, ROM (Read Only Memory)) that stores various programs and data necessary for the operation of the control device 110 of the Earth orbiting satellite 100. The storage device 170 may include, for example, an HDD (Hard Disk Drive), an SSD (Solid State Drive), flash memory, etc. The storage device 170 may also include a memory (for example, RAM (Random Access Memory)) that provides a working area for the control device 110. In one embodiment of the present invention, the storage device 170 may include programs necessary for routing the above-mentioned data, identification information of the Earth orbiting satellite 100, etc.

[0041] <Lunar orbiting satellite> Figure 3 will be used to explain the configuration of Lunar Orbiter 300.

[0042] The lunar orbiting satellite 300 may be equipped with a control device 310, a communication device 320, a propulsion device 330, a power supply device 340, an operation control device 350, and a memory device 370.

[0043] The control device 310 may be a computer equipped with processing circuits for controlling each device. The processing circuits may be a processor that executes programs stored in memory. The processor may include, for example, a central processing unit (CPU), MPU, GPU, multiprocessor, ASIC, FPGA, etc., and each process disclosed in each embodiment may be realized by logic circuits (hardware) or dedicated circuits formed on an integrated circuit (IC chip, LSI), etc. Furthermore, these circuits may be realized by one or more integrated circuits, and the multiple processes shown in each embodiment may be realized by a single integrated circuit.

[0044] Furthermore, the control device 310 may perform the routing control and self-position estimation described above. The processing performed by the control device 110 may be implemented using machine learning or AI to the extent feasible.

[0045] The communication device 320 may include an antenna 322 for other lunar orbiting satellites, an antenna 324 for Earth orbiting satellites, and an antenna 326 for probes. The communication device 320 may control communication with other lunar orbiting satellites 300 that constitute the lunar orbiting satellite constellation 30 using the antenna 322 for other lunar orbiting satellites. The communication device 320 may also control communication with Earth orbiting satellites 100 that constitute the Earth orbiting satellite constellation 10 using the antenna 324 for Earth orbiting satellites. These communications may be conducted using microwaves or light (lasers). In the lunar orbiting satellite 300, at least one of the antennas 322 for other lunar orbiting satellites, the antenna 324 for Earth orbiting satellites, and the antenna 326 for probes may be common to all of them, and the directivity of the antennas may be changeable under the control of the control device 310. This reduces the weight of the satellite and allows for maximum utilization of existing satellites.

[0046] The propulsion system 330 may be a device that provides thrust to the lunar orbiting satellite 300. The propulsion system 330 may be a chemical propulsion system, an electric propulsion system, etc.

[0047] The power supply unit 340 may be a solar cell or a storage battery, and may be controlled by the control device 310 to supply power to each device of the lunar orbiting satellite 300.

[0048] The motion control device 350 may be a device for controlling the attitude of the lunar orbiting satellite 300. The motion control device 350 may be equipped with attitude sensors such as a gyroscope and an Earth sensor, actuators, etc., and the controller may change or maintain the angular velocity and line of sight of the lunar orbiting satellite 300 in a desired direction.

[0049] The storage device 370 may be a memory (e.g., ROM) that stores various programs and data necessary for the operation of the control device 310 of the lunar orbiting satellite 300. The storage device 170 may include, for example, an HDD, SSD, flash memory, etc. The storage device 370 may also include a memory (e.g., RAM) that provides a working area for the control device 310. In one embodiment of the present invention, the storage device 370 may include programs necessary for routing the above-mentioned data, identification information of the lunar orbiting satellite 300, etc.

[0050] In this way, when operating the lunar orbiting satellite constellation 30, Earth's communication systems can be roamed to the moon without modification.

[0051] <Sequence> Using Figure 4, the control sequence between the RV spacecraft, the lunar orbiting satellite constellation 30, the Earth orbiting satellite constellation 10, and the ground station ES will be explained.

[0052] The RV probe may transmit the acquired data to at least one lunar orbiter 300 of the lunar orbiter constellation 30 (step S11). The lunar orbiter 300 of the lunar orbiter constellation 30 may acquire data from the RV probe (step S12). Depending on the relative position of the lunar orbiter 300 that has received data from the RV probe with respect to the Earth ERT, data routing may be performed among multiple lunar orbiter 300 in the lunar orbiter constellation 30 (step S13). Then, the lunar orbiter 300 that has established a communication link with the Earth orbiter 100 may transmit the data to at least one Earth orbiter 100 of the Earth orbiter constellation 10 (step S14). The Earth orbiter 100 of the Earth orbiter constellation 10 may acquire data from the lunar orbiter 300 (step S15). In the Earth-orbiting satellite constellation 10, data routing may occur between multiple Earth-orbiting satellites 100 (step S16). Then, an Earth-orbiting satellite 100 that has established a communication link with a ground station ES may transmit data to the ground station ES (step S17). The ground station ES may acquire data from the Earth-orbiting satellites 100 (step S18).

[0053] Thus, according to one embodiment of the present invention, a satellite constellation of lunar orbiting satellites orbiting in low Earth orbit above the Moon can enable communication at any location on the lunar surface. This allows information on the lunar surface to be transmitted to Earth in real time.

[0054] The present invention has been described based on various drawings and embodiments, but it should be noted that those skilled in the art will find it easy to make various modifications and alterations based on this disclosure. Therefore, it should be noted that these modifications and alterations are within the scope of the present invention. For example, the functions included in each component, step, etc., can be rearranged in a logically consistent manner, and multiple components or steps, etc., can be combined into one or divided. Furthermore, the configurations shown in the above embodiments may be combined as appropriate.

[0055] For example, the structure of each satellite constellation may differ. Specifically, in a lunar orbiting satellite constellation 30, the lunar orbiting satellite 300 does not need to have both the Earth orbiting satellite antenna 324 and the probe antenna 326; it may have at least one of them. Depending on the type of antenna provided, the constellation may be appropriately formed, and the operation may be limited to the communication targets of the satellites. Therefore, in a lunar orbiting satellite 300, there may be some that communicate only with the probe RV and not with the Earth orbiting satellite 100, and others that communicate only with the Earth orbiting satellite 100 and not with the probe RV. This can reduce the manufacturing cost of the satellites.

[0056] Furthermore, the communication system 600 may be a system that provides a packet communication network between the Earth-orbiting satellite constellation 10 and the lunar-orbiting satellite constellation 30. More specifically, the communication system 600 may be a system in which, in communication between the Earth-orbiting satellite constellation 10 and the lunar-orbiting satellite constellation, the transmitting side divides the information into packets, adds destination information, and transmits them to the lunar or Earth-orbiting satellite constellation (M), and the receiving side receives packets from the Earth or lunar-orbiting satellite constellation (N) and reconstructs the divided information. This makes it possible to establish a stable communication environment on the lunar surface.

[0057] The programs of each embodiment of this disclosure may be provided stored in a storage medium readable by the information processing device. The storage medium is a “non-temporary tangible medium” capable of storing programs. The programs include, for example, software programs and information processing device programs.

[0058] The storage medium may, where appropriate, include one or more semiconductor-based or other integrated circuits (ICs) (e.g., field-programmable gate arrays (FPGAs), application-specific integrated circuits (ASICs), hard disk drives (HDDs), hybrid hard drives (HHDs), optical disks, optical disk drives (ODDs), magneto-optical disks, magneto-optical drives, floppy diskettes, floppy disk drives (FDDs), magnetic tape, solid-state drives (SSDs), RAM drives, secure digital cards or drives, any other suitable storage medium, or two or more suitable combinations thereof. The storage medium may, where appropriate, be volatile, non-volatile, or a combination of volatile and non-volatile.

[0059] Furthermore, each embodiment of this disclosure can also be realized in the form of a data signal embedded in a carrier wave, where the program is embodied by electronic transmission. The programs of this disclosure may be implemented using, for example, scripting languages ​​such as JavaScript® and Python®, or languages ​​such as C, Go, Swift®, Koltin®, and Java®.

[0060] Each aspect of this disclosure described above can contribute to achieving Sustainable Development Goal (SDG) 9, "Build resilient infrastructure, promote inclusive and sustainable industrialization and foster innovation." [Explanation of Symbols]

[0061] 10 Earth-orbiting satellite constellations 11 High Earth orbit satellites 30 Lunar orbiting satellite constellation 31 High-Earth Lunar Orbit Satellites 100 Earth-orbiting satellites (low Earth orbit) 110 Control device 120 Communication equipment 122 Antenna for lunar orbiting satellite 124 Ground station antenna 126 Other Earth-orbiting satellite antennas 130 Propulsion device 140 Power supply 150 Operation control device 170 Storage device 300 Lunar orbit satellite (low Earth orbit) 310 Control device 320 Communication equipment 322 Antennas for other lunar orbiting satellites 324 Antenna for Earth-orbiting satellites 326 Antenna for probe 330 Propulsion device 340 Power Supply 350 Operation control device 370 Storage device 600 Communication Systems ERT Earth MO Month ES ground station RV probe DAT communication link

Claims

1. A lunar orbiting satellite constellation consists of multiple lunar orbiting satellites that orbit the Moon, A constellation of Earth-orbiting satellites consists of multiple Earth-orbiting satellites that orbit the Earth, Earth stations located on the Earth, A communication system comprising, The aforementioned lunar orbiting satellite, An antenna for the probe that communicates with the probe on the lunar surface, An antenna for another lunar orbiting satellite that communicates with other lunar orbiting satellites, An antenna for an Earth-orbiting satellite that communicates with the aforementioned Earth-orbiting satellite, Equipped with, The aforementioned Earth-orbiting satellite is An antenna for a lunar orbiting satellite that communicates with the aforementioned lunar orbiting satellite, An antenna for another Earth-orbiting satellite that communicates with other Earth-orbiting satellites, An antenna for earth station that communicates with the aforementioned earth station, Equipped with, Information from the probe is transmitted from the lunar orbiting satellite constellation to the Earth orbiting satellite constellation, and from the Earth orbiting satellite constellation to the Earth station. Communication system.

2. The information from the probe is received by at least one of the lunar orbiting satellites constituting the lunar orbiting satellite constellation, transmitted between the lunar orbiting satellites according to the relative position between the lunar orbiting satellite that received the information from the probe and the plurality of Earth orbiting satellites, transmitted from at least one of the lunar orbiting satellites constituting the lunar orbiting satellite constellation to at least one of the Earth orbiting satellites constituting the Earth orbiting satellite constellation, and transmitted from the Earth orbiting satellite to the Earth station. The communication system according to claim 1.

3. The aforementioned lunar orbiting satellite constellation consists of a group of satellites orbiting in low Earth orbit (LEO) and a group of satellites orbiting in high Earth orbit at an altitude higher than that of the low Earth orbit group. The communication system according to claim 1.

4. The aforementioned lunar orbiting satellite communicates with other lunar orbiting satellites using at least one of light or radio waves. The communication system according to claim 1.

5. The lunar orbiting satellite and the Earth orbiting satellite communicate using at least one of light or radio waves. The communication system according to claim 1.

6. In the Earth-orbiting satellite, the antenna for the lunar-orbiting satellite that communicates with the lunar-orbiting satellite and the antenna for the earth station that communicates with the earth station are common to each other. The communication system according to claim 1.

7. In the aforementioned lunar orbiting satellite, the antenna for communicating with other lunar orbiting satellites and the antenna for communicating with the Earth orbiting satellite are common to each other. The communication system according to claim 1.

8. The communication system according to claim 1, wherein the information from the probe is transmitted between M of the lunar orbiting satellites constituting the lunar orbiting satellite constellation and N of the Earth orbiting satellites constituting the Earth orbiting satellite constellation (where M and N are integers of 1 or more, including M=N).

9. The present invention provides a packet communication network using the Earth-orbiting satellite constellation and the lunar-orbiting satellite constellation. The communication system according to claim 1.

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