Satellite watching system, watching satellite, watching center, infrastructure satellite, and satellite information transmission method

Abstract

To provide a satellite watching system which suppresses rotation after capture, and enables attitude change or rotation operation after capture.SOLUTION: A watching satellite group is composed of a watching satellite 521 which flies in a universal space, monitors a critical infrastructure, and performs on-orbit service. The watching satellite 521 captures an infrastructure satellite 511, and performs on-orbit service of executing, all or a part of inspection, repair, fuel supply, movement, deorbit (ADR), and laser irradiation. The watching satellite 521 includes a watching satellite performing on-orbit service which irradiates the infrastructure satellite 511 with a laser beam, and performs range finding and imparts external stimulation thereto. The watching satellite 521 performs on-orbit service which irradiates a space object as a risk factor of the infrastructure satellite 511 with a laser beam, and performs range finding and imparts external stimulation thereto.SELECTED DRAWING: Figure 4

Description

[Technical field]

[0001] The present disclosure relates to a satellite monitoring system, a monitoring satellite, a monitoring center, an infrastructure satellite, and a satellite information transmission method. [Background technology]

[0002] Social infrastructure using satellites has become a part of our daily lives, such as sending and receiving information to remote or distant areas via communication satellites, weather forecasting using images from the Himawari meteorological satellite, and utilizing geospatial information from quasi-zenith positioning satellites. These practical satellite constellations have become critical infrastructures that are indispensable to our daily lives. It is expected that the satellite will monitor infrastructure satellites that make up critical infrastructure, and if necessary, capture the infrastructure satellites and perform in-orbit servicing.

[0003] The on-orbit services that will be performed after capturing the infrastructure satellite 511 include inspection or repair services in case of breakdown. In addition, there are refueling or transfer services when orbit control is impossible due to fuel depletion but other functions are intact. There is also active orbital deorbiting (ADR) services when it is unable to deorbit on its own. ADR is an abbreviation for Active Debris Removal.

[0004] Patent Document 1 discloses a technology for capturing tumbling or rotating space debris. [Prior art documents] [Patent documents]

[0005] [Patent Document 1] JP 2012-236591 A Summary of the Invention [Problem to be solved by the invention]

[0006] If the infrastructure satellite to be captured is rotating due to a malfunction or other reason, it is necessary to capture it and stop it from rotating. In addition, in space, there is a risk that the temperature on the side receiving sunlight will rise too high, while the temperature on the side not receiving sunlight will fall too low. For this reason, it is necessary to change the attitude or rotate the satellite so that sunlight can enter from the appropriate direction. Patent Document 1 discloses a towing satellite that captures debris with a rope-like object and tows the captured debris. However, there are problems in that it is not possible to prevent the debris from rotating after capture, or to change the attitude or rotate the debris to allow sunlight to enter from an appropriate direction after capture.

[0007] The present disclosure primarily aims to provide a satellite monitoring system that prevents rotation after capture and enables attitude change or rotation after capture. [Means for solving the problem]

[0008] The satellite monitoring system according to the present disclosure includes an infrastructure satellite that constitutes a critical infrastructure, which is an infrastructure in outer space; A constellation of monitoring satellites including monitoring satellites that fly in outer space to monitor the critical infrastructure and perform on-orbit services; a monitoring center that is installed on the ground and transmits and receives information to and from each of the monitoring satellites of the monitoring satellite group; In a satellite monitoring system having The monitoring satellite group includes: The infrastructure satellite includes a monitoring satellite that performs on-orbit services such as distance measurement or external stimuli by irradiating the infrastructure satellite with a laser. Effect of the Invention

[0009] In the satellite monitoring system according to the present disclosure, the group of monitoring satellites includes a monitoring satellite that performs on-orbit service of irradiating a laser to an infrastructure satellite to measure distance or provide an external stimulus, so that the monitoring satellite can identify the infrastructure satellite and measure distance by irradiating a laser to the infrastructure satellite when approaching. Furthermore, since the external stimulus by laser irradiation has the effect of applying an external force, it has the effect of enabling control such as movement of a lightweight object, movement of a minute amount, or suppression of rotation. [Brief description of the drawings]

[0010] [Figure 1] FIG. 1 is a diagram showing an example of the overall configuration of a satellite monitoring system according to a first embodiment. [Diagram 2] FIG. 2 is a diagram showing a configuration example of a watching center according to the first embodiment. [Diagram 3] FIG. 2 is a diagram showing a configuration example of a satellite, which is an example of a space object, according to the first embodiment. [Figure 4] 4 is a diagram showing a first example of a state after an infrastructure satellite is captured by a monitoring satellite according to the first embodiment. FIG. [Diagram 5] 10A and 10B are schematic three-sided diagrams of Example 2 after an infrastructure satellite has been captured by a monitoring satellite in accordance with the first embodiment; [Figure 6] 13A and 13B are schematic two-sided diagrams of Example 2 after an infrastructure satellite has been captured by a monitoring satellite in accordance with the first embodiment. [Figure 7] FIG. 13 is a diagram showing example 3 of a state after a space object is captured by a monitoring satellite in accordance with embodiment 1. [Figure 8] FIG. 13 is a diagram showing Example 4 of the state after a space object is captured by a monitoring satellite in accordance with embodiment 1. [Figure 9] FIG. 5 is a diagram showing Example 5 of a state after the capture of a space object or resource by the exploration satellite or transport vehicle of the first embodiment. [Figure 10] FIG. 6 is a diagram showing a sixth example of a state after the capture of a space object or resource by the exploration satellite or transport vehicle according to the first embodiment. DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

[0011] Hereinafter, the embodiments of the present disclosure will be described with reference to the drawings. In each drawing, the same or corresponding parts are denoted by the same reference numerals. In the description of the embodiments, the description of the same or corresponding parts will be omitted or simplified as appropriate. In addition, the relationship between the sizes of the components in the following drawings may differ from the actual relationship. In addition, in the description of the embodiments, directions or positions such as "upper", "lower", "left", "right", "front", "rear", "front" and "back" may be indicated. These notations are written in this way only for the convenience of explanation, and do not limit the arrangement and orientation of the components such as devices, instruments, or parts.

[0012] Embodiment 1 ***Configuration Description*** FIG. 1 is a diagram showing an example of the overall configuration of a satellite monitoring system 500 according to this embodiment. The satellite monitoring system 500 includes a monitoring satellite group 52 that monitors a critical infrastructure 51, and a monitoring center 53. The satellite monitoring system 500 may include a critical infrastructure 51 in addition to the monitoring satellite group 52 and the monitoring center 53. The monitoring satellite 521 is also called a monitoring satellite or a monitoring device.

[0013] Critical infrastructure 51 is infrastructure in outer space. Critical infrastructure 51 is composed of satellites that form social infrastructure and operate services. Specifically, critical infrastructure 51 is composed of satellites that form social infrastructure such as information exchange with distant or remote areas via communication satellites, weather forecasts using images from the Himawari meteorological satellite, or utilization of geospatial information by quasi-zenith positioning satellites. Moreover, the satellites that constitute the critical infrastructure 51 are called infrastructure satellites 511. Moreover, the infrastructure satellites 511 are also called critical infrastructure constituent satellites.

[0014] The monitoring satellite group 52 is composed of monitoring satellites 521 that fly in space, monitor infrastructure satellites 511 that constitute the critical infrastructure 51, and perform on-orbit services. The monitoring center 53 is installed on the ground, and transmits and receives information to and from the monitoring satellites 521 of the monitoring satellite group 52. For example, the monitoring center 53 transmits commands to the monitoring satellites 521. The monitoring satellites 521 of the monitoring satellite group 52 and the monitoring center 53 may exchange information via a communication device provided in the infrastructure satellite 511 .

[0015] The group of satellites constituting the critical infrastructure 51 includes satellites equipped with communication devices for communicating with the monitoring center 53 as infrastructure satellites 511 . The infrastructure satellite 511 includes all or some of the communication satellite 401, data relay satellite 402, weather satellite 403, observation satellite 404, first observation and monitoring satellite 405, positioning satellite 406, second observation and monitoring satellite 407, space station 408, lunar planetary exploration satellite 409, exploration satellite 410, and transport vehicle 411. The exploration satellite 410 is an exploration satellite that explores planets or resources other than the moon. The transport vehicle 411 transports fuel or materials required for the infrastructure satellite 511. The first observation and monitoring satellite 405 is a satellite that is deployed in a high orbit, such as a geostationary orbit or a Molniya orbit, and performs wide-area observation or monitoring of the earth. The second observation and monitoring satellite 407 is, for example, an observation or monitoring satellite for collecting various types of image information on large-scale disasters and other important matters. Moreover, infrastructure-specific ground facilities 54 corresponding to the critical infrastructure 51 are installed on the ground.

[0016] The on-orbit services performed after capturing the infrastructure satellite 511 include inspection or repair services in case of breakdown, refueling or transfer services when orbit control is impossible due to fuel exhaustion but other functions are intact, and active orbit deorbiting (ADR) services when it is unable to deorbit on its own.

[0017] If the infrastructure satellite 511 to be captured is rotating due to a malfunction or other reason, it is necessary to capture it and stop the rotation. Also, in outer space, there is a risk that the temperature will rise too much on the side receiving sunlight, and there is a risk that the temperature will drop too much on the side not receiving sunlight. For this reason, after capturing the infrastructure satellite 511, the monitoring satellite 521 needs to change its attitude or rotate in order to allow sunlight to enter from an appropriate direction.

[0018] The monitoring satellites 521 include all or some of the optical monitoring satellites 421, the radio wave monitoring satellites 423, the infrared monitoring satellites 422, the service satellites 424, and the debris removal satellites 425. The optical monitoring satellite 421 monitors the infrastructure satellite 511 using an optical system. The radio wave monitoring satellite 423 monitors the infrastructure satellite 511 using radio waves. Infrared watch satellites 422 monitor infrastructure satellites 511 using infrared detection. Servicing satellite 424 provides on-orbit servicing for infrastructure satellite 511 . The debris removal satellite 425 removes the debris.

[0019] In this embodiment, the watchdog satellite 521 captures the infrastructure satellite 511 and performs on-orbit servicing to perform all or part of inspection, repair, refueling, transfer, and ADR. In addition, in this embodiment, the monitoring satellite 521 performs on-orbit services to capture space objects that are a hazard to the infrastructure satellite 511 and to perform all or part of the movement and ADR.

[0020] On-orbit servicing may include any or all of the following: capture, inspection, repair, refueling, transfer, advanced de-orbit (ADR), and laser illumination. For example, the monitoring satellite 521 performs on-orbit services such as irradiating the infrastructure satellite 511 with a laser to measure distance or provide an external stimulus. In addition, the monitoring satellite 521 performs on-orbit services such as irradiating space objects that pose a risk to infrastructure satellites with a laser to measure distances or impart external stimuli.

[0021] The monitoring service provided by the monitoring satellite group 52 can be easily understood by analogy with the roles of eyes, ears, hands, and mouth. In order to achieve the objective of visually monitoring the critical infrastructure 51 using satellites, it is effective to visually monitor suspicious objects such as debris using optical telescopes or radar images. Another effective method is to monitor abnormal temperature environments using infrared detection.

[0022] Additionally, a monitoring service that monitors audibly using the ears has the objective of monitoring radio waves in outer space, where sound waves do not propagate. In order to achieve the objective of monitoring critical infrastructure51 audibly using satellites, it is effective to receive radio waves flying around in the vicinity and monitor the radio wave conditions that may cause malfunctions.

[0023] In addition, as an extension of the monitoring service, there is the on-orbit service, which is an analogy to the role of manual operation. On-orbit services include the capture, inspection, and repair of malfunctioning satellites. Also included are refueling satellites that are running low on fuel, mobile services that move the service location, and active de-orbiting of satellites that cannot de-orbit on their own after the end of their life. Another service includes the use of lasers to monitor the distance to suspicious objects such as debris.

[0024] In this way, it is expected that the monitoring satellite 521 will fulfill the role of eyes, ears, and hands. However, the role of the mouth, i.e., the means of communication to transmit monitoring information 590, is limited, and some ingenuity is required.

[0025] In this embodiment, an infrastructure satellite 511 is used as a monitoring satellite 521 that serves as a port, that is, a monitoring satellite 521 that transmits monitoring information 590. The monitoring satellites 521 include infrastructure satellites 511 as monitoring satellites 521 that play the role of the mouth. The infrastructure satellites 511 also include monitoring satellites 521 that play the role of the mouth. That is, in the satellite monitoring system 500, there are satellites that are monitoring satellites 521 and infrastructure satellites 511. Here, such satellites have been described as infrastructure satellites 511 that mainly play the role of the mouth, but they may also be satellites that play the roles of eyes, ears, and hands.

[0026] 1, the monitoring satellites 521 that perform long-distance communication include a communication satellite 401 and a data relay satellite 402 in a first satellite group 601. Also, the communication satellite 401 is included in a second satellite group 602. Also, a lunar and planetary exploration satellite 409 is included in a third satellite group 603. The monitoring satellites 521 that perform short-distance communication include the meteorological satellites 403 , the positioning satellites 406 , and the observation satellites 404 in the first satellite group 601 .

[0027] As shown in FIG. 1, the satellite monitoring system 500 includes a first satellite group 601, a second satellite group 602, a third satellite group 603, and a monitoring center 53.

[0028] The first satellite group 601 is made up of satellites flying near a geostationary Earth orbit (GEO) or a quasi-zenith orbit (QZO). The first satellite group 601 includes, as infrastructure satellites 511, a communication satellite 401, a data relay satellite 402, a meteorological satellite 403, an observation satellite 404, a first observation and monitoring satellite 405, and a positioning satellite 406. The first satellite group 601 also includes, as monitoring satellites 521, a communication satellite 401, a data relay satellite 402, a meteorological satellite 403, an observation satellite 404, and a positioning satellite 406. The first satellite group 601 also includes, as monitoring satellites 521, all or some of an optical monitoring satellite 421, a radio wave monitoring satellite 423, an infrared monitoring satellite 422, a service satellite 424, and a debris removal satellite 425.

[0029] The second satellite group 602 is made up of satellites flying near a medium earth orbit (MEO: Medium Earth Orbit) or near a low earth orbit (LEO: Low Earth Orbit). The second satellite group 602 includes, as infrastructure satellites 511, an observation satellite 404, a first observation and monitoring satellite 405, a positioning satellite 406, a second observation and monitoring satellite 407, and a space station 408. The second satellite group 602 also includes the communication satellite 401 as a monitoring satellite 521. The second satellite group 602 also includes all or some of the following as the monitoring satellites 521: an optical monitoring satellite 421, a radio wave monitoring satellite 423, an infrared monitoring satellite 422, a service satellite 424, and a debris removal satellite 425.

[0030] The third satellite group 603 is made up of satellites flying in cislunar space, the space between the moon and the earth, or beyond the moon. The third satellite group 603 includes, as infrastructure satellites 511, all or some of the lunar and planetary exploration satellites 409, the exploration satellites 410, and the transport vehicle 411. The transport vehicle 411 may be included in the first satellite group 601 or the second satellite group 602. The third satellite group 603 includes the lunar planetary exploration satellite 409 and the Gateway 419 as monitoring satellites 521. The Gateway 419 is a satellite in the vicinity of the moon. The Gateway 419 is a satellite planned to be constructed through international cooperation. The third satellite group 603 includes, as monitoring satellites 521, all or some of the optical monitoring satellites 421, the radio wave monitoring satellites 423, the service satellites 424, and the debris removal satellites 425.

[0031] FIG. 2 shows an example of the configuration of the monitoring center 53 according to this embodiment. The watching center 53 is also referred to as ground equipment 701 installed on the ground. Here, the explanation will be given as ground equipment 701.

[0032] The ground equipment 701 includes a computer. The ground equipment 701 includes a processor 910, as well as other hardware such as a memory 921, an auxiliary storage device 922, an input interface 930, an output interface 940, and a communication device 950. The processor 910 is connected to the other hardware via signal lines and controls the other hardware.

[0033] The ground equipment 701 includes, as examples of functional elements, a monitoring management unit 710 and a memory unit 720. The memory unit 720 stores the monitoring information 590.

[0034] The functions of the watching management unit 710 are realized by software. The storage unit 720 is provided in the memory 921. Alternatively, the storage unit 720 may be provided in the auxiliary storage device 922. Moreover, the storage unit 720 may be provided separately in the memory 921 and the auxiliary storage device 922.

[0035] The ground equipment 701 transmits and receives monitoring information 590 to and from the monitoring satellite 521 via the infrastructure satellite 511. The monitoring management unit 710 uses the monitoring information 590 transmitted and received from the monitoring satellite 521 to realize a function of dealing with the risk of failure or loss of the critical infrastructure 51. For example, the monitoring management unit 710 realizes a function of warning of danger, preventing danger, or avoiding danger in the critical infrastructure 51.

[0036] The processor 910 is a device that executes a monitoring management program. The monitoring management program is a program that realizes the functions of each component of the ground equipment 701 and the satellite monitoring system 500.

[0037] The processor 910 is an integrated circuit (IC) that performs arithmetic processing. Specific examples of the processor 910 include a CPU, a digital signal processor (DSP), and a graphics processing unit (GPU).

[0038] The memory 921 is a storage device that temporarily stores data. Specific examples of the memory 921 include a static random access memory (SRAM) and a dynamic random access memory (DRAM). The auxiliary storage device 922 is a storage device that stores data. A specific example of the auxiliary storage device 922 is a HDD. The auxiliary storage device 922 may also be a portable storage medium such as an SD (registered trademark) memory card, CF, NAND flash, a flexible disk, an optical disk, a compact disk, a Blu-ray (registered trademark) disk, or a DVD. Note that HDD is an abbreviation for Hard Disk Drive. SD (registered trademark) is an abbreviation for Secure Digital. CF is an abbreviation for CompactFlash (registered trademark). DVD is an abbreviation for Digital Versatile Disk.

[0039] The input interface 930 is a port connected to an input device such as a mouse, a keyboard, or a touch panel. Specifically, the input interface 930 is a Universal Serial Bus (USB) terminal. The input interface 930 may be a port connected to a Local Area Network (LAN). The output interface 940 is a port to which a cable of a display device 941 such as a display is connected. Specifically, the output interface 940 is a USB terminal or an HDMI (registered trademark) (High Definition Multimedia Interface) terminal. Specifically, the display is an LCD (Liquid Crystal Display).

[0040] The communication device 950 includes a receiver and a transmitter, and is specifically a communication chip or a network interface card (NIC).

[0041] The watching management program is read into the processor 910 and executed by the processor 910. The memory 921 stores not only the watching management program but also an OS (Operating System). The processor 910 executes the watching management program while executing the OS. The watching management program and the OS may be stored in an auxiliary storage device. The watching management program and the OS stored in the auxiliary storage device are loaded into the memory 921 and executed by the processor 910. Note that a part or all of the watching management program may be incorporated into the OS.

[0042] The ground equipment 701 may include multiple processors that replace the processor 910. These multiple processors share the execution of the monitoring management program. Each processor is a device that executes the monitoring management program, just like the processor 910.

[0043] Data, information, signal values ​​and variable values ​​used, processed or output by the monitoring management program are stored in memory 921, auxiliary storage device 922, or a register or cache memory within processor 910.

[0044] The "unit" in the monitoring management unit 710 may be read as a "process," a "procedure," or a "step." Also, the "process" in the monitoring management process may be read as a "program," a "program product," or a "computer-readable storage medium on which a program is recorded." The monitoring management program causes a computer to execute each process, procedure, or step of the monitoring management unit, where the "unit" is replaced with a "process," "procedure," or "step." The monitoring management method is a method performed by the ground equipment 701 executing the monitoring management program. The monitoring management program may be provided by being stored in a computer-readable recording medium or a storage medium. The monitoring management program may also be provided as a program product.

[0045] The processor may be replaced by an electronic circuit. Each of the processor and the electronic circuit is also called a processing circuit. In other words, the functions of each device of the satellite monitoring system 500 are realized by the processing circuitry.

[0046] The configuration of the ground facility 54 for each infrastructure is also similar to that of the ground facility 701 .

[0047] FIG. 3 shows an example of the configuration of a satellite 300, which is an example of a space object according to this embodiment. The satellites 300 include an infrastructure satellite 511, a monitoring satellite 521, and other satellites that make up the satellite monitoring system 500. Here, a basic configuration example of the satellite 300 will be described. Depending on the mission or function of the satellite 300, the equipment mounted on the satellite 300 is appropriately selected.

[0048] The satellite 300 includes, for example, a satellite communication device 31, a monitoring device 32, a propulsion device 33, an attitude control device , a satellite control device 35, and a power supply device .

[0049] The satellite communication device 31 is a communication device for communicating with ground facilities. For example, the satellite communication device 31 receives various commands from the ground facilities. Also, for example, the satellite communication device 31 transmits monitoring data obtained by the monitoring device 32 to the ground facilities.

[0050] The monitoring device 32 is a device for monitoring a monitoring target such as the Earth or a space object, and generates monitoring data. The monitoring device 32 is a device such as an infrared monitoring device that uses infrared rays, or a camera.

[0051] The propulsion device 33 is a device that provides propulsive force to the satellite 300 and changes the speed of the satellite 300. Specifically, the propulsion device 33 is an electric propulsion device. For example, the propulsion device 33 is an ion engine or a Hall thruster.

[0052] The attitude control device 34 is a device for controlling attitude elements such as the attitude of the satellite 300 and the angular velocity of the satellite 300 . The attitude control device 34 changes each attitude element to a desired direction. Alternatively, the attitude control device 34 maintains each attitude element in a desired direction. The attitude control device 34 includes an attitude sensor, an actuator, and a controller. The attitude sensor includes a gyroscope, an earth sensor, a sun sensor, a star tracker, a thruster, and a magnetic sensor. The actuator includes an attitude control thruster, a momentum wheel, a reaction wheel, and a control moment gyro. The controller controls the actuator according to the measurement data of the attitude sensor or various commands from the ground equipment.

[0053] The satellite control device 35 is a computer and includes a processing circuit that controls each device of the satellite 300. For example, the satellite control device 35 controls each device according to various commands transmitted from the ground equipment.

[0054] The power supply unit 36 ​​includes a solar paddle, solar cells, a battery, a power control device, and the like, and supplies power to each device of the satellite 300 .

[0055] <Example 1 of the state after the infrastructure satellite 511 is captured by the monitoring satellite 521> FIG. 4 is a diagram showing a first example of the state after the infrastructure satellite 511 is captured by the monitoring satellite 521 according to the present embodiment.

[0056] The monitoring satellite 521 includes a capture device 37 in addition to the configuration shown in FIG. The monitoring satellite 521 captures the infrastructure satellite 511 using the capture device 37 and performs on-orbit servicing, including all or part of inspection, repair, refueling, movement, and ADR. The monitoring satellite 521 that performs on-orbit servicing is equipped with a capture device 37 that captures the infrastructure satellite 511 by constraining it in six degrees of freedom, and a propulsion device 33. After capture, the monitoring satellite 521 can rotate in any direction around the center of gravity of the flying body 600 in which the infrastructure satellite 511 and the monitoring satellite 521 are combined.

[0057] FIG. 4 shows an example of a procedure for turning around the center of gravity C with respect to the traveling direction (+Z) in the flying object 600 in a state where the infrastructure satellite 511 has been captured. In the first example of this embodiment, the capture device 37 of the monitoring satellite 521 is disposed in the opposite direction to the nozzle of the thruster 33a having the maximum jet power among the multiple thrusters. The capture device 37 also includes thrusters 33b and 33c having nozzles in the positive and negative directions of an axis perpendicular to the jet direction of the thruster 33a having the maximum jet power. A torque is applied around the center of gravity of the monitoring satellite 521 in the satellite capture state by the thrust of the thrusters 33b and 33c arranged in the orthogonal direction. In addition, the thrust vector of the thruster 33a having the maximum thrust capacity passes through the center of gravity of the monitoring satellite 521 in the satellite capture state and is in the opposite direction to the flight direction.

[0058] For example, the monitoring satellite 521 uses the thruster 33a with the maximum thrust capacity to decelerate the monitoring satellite 521 in the satellite capture state and make it enter the atmosphere. For this atmospheric entry, the monitoring satellite 521 needs to fly in an attitude such that the thrust vector of the thruster 33a passes through the center of gravity C of the monitoring satellite 521 in the satellite capture state and the direction of the thrust vector is opposite to the flight direction.

[0059] However, the attitude and motion state of the monitoring satellite 521 after the satellite capture is determined depending on the initial attitude and motion state of the satellite, and the accessible position of the capture device. Therefore, it is necessary to change the attitude of the monitoring satellite 521 in the satellite capture state until it attains the desired attitude. Also, depending on the position of the center of gravity when a large satellite is captured, it may be difficult to change the attitude using the attitude control method for the monitoring satellite 521 alone. In the first example of this embodiment, the translational force of a thruster away from the center of gravity is utilized as a torque about the center of gravity to change the attitude of the watching satellite 521 in the satellite capture state.

[0060] In the monitoring satellite 521, the capture device 37 and the thruster 33a with the maximum jet power are placed on the opposite side on the Z axis. A rotational torque about the center of gravity is applied to the monitoring satellite 521 in the satellite capture state by the +X direction thruster 33b perpendicular to the Z axis. Next, a rotational torque in the opposite direction is applied to the monitoring satellite 521 in the satellite capture state by the -X direction thruster 33c so that the monitoring satellite 521 stops at a desired position. The rotational torque in the opposite direction acts as a brake, and the monitoring satellite 521 in the satellite capture state stops.

[0061] Note that the "thruster with the maximum thrust capacity" is used as a general term for deceleration means for lowering the orbital altitude, and may be configured with multiple thrusters. When multiple thrusters are used, the resultant vector of simultaneous thrusts passes through the center of gravity of the monitoring satellite 521 in the satellite capture state, and is in the opposite direction of flight. In this case, the balance between the placement and thrust amount is adjusted so that multiple vectors do not generate a rotational torque around the center of gravity.

[0062] According to the first aspect of the present embodiment, when an infrastructure satellite to be captured is rotating due to a malfunction or the like, it can be captured and prevented from rotating. In space, there is a risk that the temperature on the side where sunlight is incident will rise too high. Also, there is a risk that the temperature on the side where sunlight is not incident will fall too low. According to the first aspect of the present embodiment, it is possible to change the attitude or rotate the device so that sunlight is incident from an appropriate direction.

[0063] <Example 2 of the state after the monitoring satellite captures the infrastructure satellite> FIG. 5 is a schematic three-plane diagram of the second embodiment after the infrastructure satellite 511 is captured by the monitoring satellite 521 according to the present embodiment. FIG. 6 is a diagram showing two schematic views of the second embodiment after the infrastructure satellite 511 is captured by the monitoring satellite 521 according to the present embodiment.

[0064] The watchdog satellite 521 captures the infrastructure satellite 511 and provides on-orbit servicing to perform all or part of inspection, repair, refueling, transfer, and deorbit (ADR). The monitoring satellite 521, which performs on-orbit servicing, is equipped with a capture device 37 that captures the infrastructure satellite 511 by constraining it in six degrees of freedom, and a propulsion device 33. After capture, the monitoring satellite 521 ensures that the center of gravity C of the flying object 600 formed by combining the infrastructure satellite 511 and the monitoring satellite 521 is on a straight line of the flying object 600's travel direction vector.

[0065] 5 and 6, the flying object 600 is in a state where the monitoring satellite 521 and the infrastructure satellite 511 are combined after the infrastructure satellite 511 is captured by the monitoring satellite 521. In this embodiment, the center of gravity C of the flying object 600 is on a straight line of the flying object 600's traveling direction vector.

[0066] When the flying body 600 moves, the propulsion device 33 must be operated in the direction of travel and controlled so that the propulsion vector of the propulsion device 33 passes through the center of gravity C in the captured state and coincides with the desired direction of travel. For example, the monitoring center 53 transmits a control command to the monitoring satellite 521 to control the propulsion device 33 so that the center of gravity C of the flying object 600 is on the straight line of the propulsion vector of the propulsion device 33.

[0067] In reality, the center of gravity of a non-cooperative target after capture is not necessarily conveniently located on the extension of the thrust vector of the fixed thrusters. Therefore, it is practical for the monitoring satellite 521 to control the thrust vector toward the center of gravity by controlling the multiple thrusters 33.

[0068] Normally, it is assumed that after capturing a satellite, the center of gravity of the flying object becomes far away, making it difficult to control the propulsion device. According to the second aspect of the present embodiment, even if the center of gravity of the flying object becomes far away after capturing a satellite, it becomes easier to control the propulsion device and to move the flying object.

[0069] <Example 3 of the situation after a space object is captured by a monitoring satellite> FIG. 7 is a diagram showing a third example of the state after the space object 400 is captured by the monitoring satellite 521 according to the present embodiment.

[0070] The monitoring satellite 521 performs on-orbit servicing to capture, relocate, and perform all or part of the ADR (Advanced Displacement Removal) of space objects 400 that pose a danger to the infrastructure satellite 511. The monitoring satellite 521 that performs on-orbit servicing is equipped with a capture device 37 that captures the space object 400 by constraining it in six degrees of freedom, and a propulsion device 33. After capture, the monitoring satellite 521 can rotate in any direction around the center of gravity of the flying body 600 in which the space object 400 and the monitoring satellite 521 are combined.

[0071] The third aspect is similar to the first aspect except that the infrastructure satellite 511 is replaced with a space object 400. The effects are also similar to those of the first aspect.

[0072] According to the third aspect of the present embodiment, a risk factor such as approaching debris may be discovered for an infrastructure satellite. According to the third aspect of the present embodiment, when capturing and moving or removing the risk factor, the rotation or thrust direction can be controlled in the same manner as in the first aspect.

[0073] <Example 4 of the state after a space object is captured by a monitoring satellite> FIG. 8 is a diagram showing a fourth example of the state after the space object 400 is captured by the monitoring satellite 521 according to the present embodiment.

[0074] The monitoring satellite 521 performs on-orbit servicing to capture, relocate, and perform all or part of the ADR (Advanced Displacement Removal) of space objects 400 that pose a danger to the infrastructure satellite 511. The monitoring satellite 521 that performs on-orbit servicing includes a capture device 37 that captures the space object 400 by constraining it in six degrees of freedom, and a propulsion device 33. The monitoring satellite 521 is a monitoring satellite 521 in which the center of gravity position C of the flying object 600 formed by combining the space object 400 and the monitoring satellite 521 after capture is on a straight line of the traveling direction vector of the flying object 600.

[0075] Incidentally, the fourth embodiment is similar to the second embodiment in that the infrastructure satellite 511 is replaced with a space object 400.

[0076] According to the fourth aspect of the present embodiment, similarly to the second aspect, even if the center of gravity of the flying body becomes far away after capturing the satellite, it becomes easier to control the propulsion device and facilitate movement.

[0077] <Example 5 of the capture of a space object or resource by the exploration satellite 410 or the transport vehicle 411> FIG. 9 is a diagram showing a fifth example of the state after the space object or resource has been captured by the exploration satellite 410 or the transport vehicle 411 according to the present embodiment.

[0078] The infrastructure satellites 511 included in the third satellite group 603 include the exploration satellite 410. The infrastructure satellites 511 included in the third satellite group 603 may also include a transport aircraft 411. The exploration satellite 410 or the transport vehicle 411 is included in the third satellite group 603 and performs on-orbit servicing involving the capture of space objects or resources. The exploration satellite 410 or the transport vehicle 411 is equipped with a capture device 37 that captures the space object or resource by constraining it in six degrees of freedom, and a propulsion device 33. After capture, the exploration satellite 410 or the transport vehicle 411 can rotate in any direction around the center of gravity of the flying body 600 to which the exploration satellite 410 or the transport vehicle 411 is coupled with the space object or resource.

[0079] At this time, satellite information is exchanged between the exploration satellite 410 or the transport vehicle 411 and the infrastructure ground facility 54 (an example of the ground facility) by a satellite information transmission method. In this satellite information transmission method, information is exchanged between the exploration satellite 410 or the transport vehicle 411 and the infrastructure ground facility 54 via the lunar / planetary exploration satellite 409 or the gateway 419.

[0080] The fifth embodiment is similar to the third embodiment in that the monitoring satellite 521 is replaced with an exploration satellite 410 or a transport vehicle 411, and the space object 400 that is a risk factor for the infrastructure satellite 511 is replaced with a space object or resource.

[0081] <Example 6 of the capture of a space object or resource by the exploration satellite 410 or the transport vehicle 411> FIG. 10 is a diagram showing a sixth embodiment after the space object or resource is captured by the exploration satellite 410 or the transport vehicle 411 according to the present embodiment.

[0082] The infrastructure satellites 511 included in the third satellite group 603 include the exploration satellite 410. The infrastructure satellites 511 included in the third satellite group 603 may also include a transport aircraft 411. The exploration satellite 410 or the transport vehicle 411 is included in the third satellite group 603 and performs on-orbit servicing involving the capture of space objects or resources. The exploration satellite 410 or the transport vehicle 411 is equipped with a capture device 37 that captures the space object or resource by constraining it in six degrees of freedom, and a propulsion device 33. After capture, the exploration satellite 410 or the transport vehicle 411 and the space object or resource are combined, and the center of gravity position C of the flying body 600 in which the exploration satellite 410 or the transport vehicle 411 is combined is on a straight line of the traveling direction vector of the flying body 600.

[0083] At this time, satellite information is exchanged between the exploration satellite 410 or the transport vehicle 411 and the infrastructure ground facility 54 (an example of the ground facility) by a satellite information transmission method. In this satellite information transmission method, information is exchanged between the exploration satellite 410 or the transport vehicle 411 and the infrastructure ground facility 54 via the lunar / planetary exploration satellite 409 or the gateway 419.

[0084] The sixth embodiment is similar to the fourth embodiment in that the monitoring satellite 521 is replaced with an exploration satellite 410 or a transport vehicle 411, and the space object 400 that is a risk factor for the infrastructure satellite 511 is replaced with a space object or resource.

[0085] For exploration satellites, there are orbital servicing concepts such as capturing or manipulating planets to move, or mining and transporting space resources, as in the ARM concept. ARM is an abbreviation for Asteroid Return Missionn. According to the fifth and sixth aspects of this embodiment, the above orbital servicing concepts can be reliably implemented, similar to the orbital servicing of monitoring satellites.

[0086] ***supplementary explanation*** Before the monitoring satellite captures the infrastructure satellite, there is a stage where the monitoring satellite identifies the infrastructure satellite and approaches it. At this stage, it is effective for the monitoring satellite to measure the distance by irradiating the infrastructure satellite with a laser. Furthermore, since the external stimulus by the laser irradiation has the effect of applying an external force, it has the effect of controlling the movement of a lightweight object, the movement of a small amount, or the suppression of rotation.

[0087] In-orbit servicing requires monitoring satellites to monitor the status of infrastructure satellites and respond flexibly, making it essential to send commands from ground facilities. The communication lines for sending and receiving information between the monitoring satellites and ground equipment must be available at all times. When implementing on-orbit services in places where there is no permission to communicate in orbit, it is possible to establish a constant communication environment by sending and receiving information between the monitoring satellites and ground equipment via infrastructure satellites that have permission to communicate.

[0088] In the above-mentioned first embodiment, each system and each device, such as the satellite monitoring system, infrastructure satellite, monitoring satellite, ground equipment, and monitoring center, has been described as an independent functional block. However, the configuration of each system and each device does not have to be as in the above-mentioned embodiment. The functional blocks of each system and each device may have any configuration as long as they can realize the functions described in the above-mentioned embodiment. Furthermore, each system and each device may be a single device or a system composed of multiple devices. Furthermore, it is possible to combine multiple parts or examples of the first embodiment. Alternatively, it is possible to implement only one part or example of this embodiment. In addition, it is possible to implement any combination of these embodiments, either as a whole or in part. That is, in the first embodiment, the embodiments can be freely combined, or any of the components in each embodiment can be modified, or any of the components in each embodiment can be omitted.

[0089] It should be noted that the above-described embodiment is essentially a preferred example, and is not intended to limit the scope of the present disclosure, the scope of application of the present disclosure, and the scope of use of the present disclosure. The above-described embodiment can be modified in various ways as necessary. [Explanation of symbols]

[0090] 300 satellite, 31 satellite communication equipment, 32 monitoring equipment, 33 propulsion equipment, 33a, 33b, 33c thrusters, 34 attitude control equipment, 35 satellite control equipment, 36 power supply equipment, 37 capture equipment, 371 solar paddle, 400 space object, 401 communication satellite, 402 data relay satellite, 403 weather satellite, 404 observation satellite, 405 first observation and monitoring satellite, 406 positioning satellite, 407 second observation and monitoring satellite, 408 space station, 409 lunar planetary exploration satellite, 410 exploration satellite, 411 transport aircraft, 419 gateway, 421 optical monitoring satellite, 422 infrared monitoring satellite, 423 radio monitoring satellite, 424 service satellite, 425 debris removal satellite, 51 critical infrastructure, 511 infrastructure satellite, 52 Monitoring satellite group, 521, 521a, 521b, 521c monitoring satellite, 53 monitoring center, 54 infrastructure ground equipment, 55 gateway ground equipment, 590 monitoring information, 600 flying object, 601 first satellite group, 602 second satellite group, 603 third satellite group, 500 satellite monitoring system, 701 ground equipment, 710 monitoring management unit, 720 memory unit, 910 processor, 921 memory, 922 auxiliary storage device, 930 input interface, 940 output interface, 941 display device, 950 communication device.

Claims

1. An infrastructure satellite that constitutes a critical infrastructure, which is an infrastructure in outer space; A constellation of monitoring satellites including monitoring satellites that fly in outer space to monitor the critical infrastructure and perform on-orbit services; a monitoring center that is installed on the ground and transmits and receives information to and from each of the monitoring satellites of the monitoring satellite group; In a satellite monitoring system having The monitoring satellite group includes: A satellite monitoring system comprising a monitoring satellite that performs on-orbit services such as measuring distances or providing external stimuli by irradiating the infrastructure satellite with a laser.

2. An infrastructure satellite that constitutes a critical infrastructure, which is infrastructure in outer space; A constellation of monitoring satellites including monitoring satellites that fly in outer space to monitor the critical infrastructure and perform on-orbit services; a monitoring center that is installed on the ground and transmits and receives information to and from each of the monitoring satellites of the monitoring satellite group; In a satellite monitoring system having The monitoring satellite group includes: A satellite monitoring system comprising a monitoring satellite that performs on-orbit services by irradiating a laser to space objects that are a hazard to the infrastructure satellite, thereby measuring distances or providing external stimuli.

3. An infrastructure satellite that constitutes a critical infrastructure, which is an infrastructure in outer space; A constellation of monitoring satellites including monitoring satellites that fly in outer space to monitor the critical infrastructure and perform on-orbit services; a monitoring center that is installed on the ground and transmits and receives information to and from each of the monitoring satellites of the monitoring satellite group; In a satellite monitoring system having 3. The satellite monitoring system according to claim 1, wherein information is exchanged between the monitoring satellites and the monitoring center via a communication device provided in the infrastructure satellite.

4. a first satellite group consisting of satellites flying in a geostationary earth orbit (GEO) or a quasi-zenith orbit (QZO); a second satellite constellation consisting of satellites flying in a medium earth orbit (MEO: Medium Earth Orbit) or a low earth orbit (LEO: Low Earth Orbit); a third constellation of satellites that fly in cislunar space, which is the space between the moon and the earth, or beyond the moon; The aforementioned monitoring center and The satellite monitoring system according to any one of claims 1 to 3, comprising:

5. A monitoring satellite included in the satellite monitoring system according to any one of claims 1 to 4, The monitoring satellite is characterized by providing the on-orbit service to the infrastructure satellite or a space object that poses a risk to the infrastructure satellite.

6. A monitoring center that transmits commands to the monitoring satellite according to claim 5.

7. An infrastructure satellite included in a third satellite group included in the satellite monitoring system according to claim 4, The infrastructure satellite includes: An infrastructure satellite, which is included in the third satellite group and is an exploration satellite or transport vehicle that performs on-orbit services involving the capture of space objects or resources, and is characterized in that it is equipped with a capture device that captures the space object or resource by constraining it in six degrees of freedom, and a propulsion device, and that after capture, it can rotate in any direction around the center of gravity of the flying body in which the space object or resource and the exploration satellite or transport vehicle are combined.

8. An infrastructure satellite included in a third satellite group included in the satellite monitoring system according to claim 4, The infrastructure satellite includes: An infrastructure satellite, which is included in the third satellite group and performs on-orbit servicing involving the capture of space objects or resources, characterized in that it is equipped with a capture device that captures the space object or resource by constraining it in six degrees of freedom, and a propulsion device, and that after capture, the center of gravity of the flying body formed by combining the space object or resource with the infrastructure satellite is on a straight line with the flying body's direction of travel vector.

9. A method for transmitting and receiving satellite information between a survey satellite or a transport vehicle which is an infrastructure satellite according to claim 7 or 8 and a ground facility, comprising: A satellite information transmission method, comprising: exchanging information between a lunar / planetary exploration satellite or a transport vehicle and the ground facility via a gateway.

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