Space condition monitoring business device, and accelerating / decelerating object tracking device

Abstract

To enable updating of a catalog with reduced errors in public information.SOLUTION: A space condition monitoring business device 47 includes: a first monitoring device 810a flying along a stationary orbit; a second monitoring device 840 located on the ground; a catalog that records orbital information; a measurement error examination device 471; and an accelerating / decelerating object tracking device 472. The catalog stores public orbital information, first orbital information acquired by the first monitoring device 810a, and second orbital information acquired by the second monitoring device 840. The space condition monitoring business device 47 acquires monitoring information of specific space objects including the first monitoring device 810a and the second monitoring device 840 on the basis of the public orbital information of the specific space object. The measurement error examination device 471 selects orbital information on the basis of the public orbital information, the first orbital information and the second orbital information of the specific space objects, and generates third orbital information being update information.SELECTED DRAWING: Figure 29

Description

Technical Field

[0001] The present disclosure relates to a space situation monitoring device, a monitoring device, and an accelerating / decelerating object tracking device.

Background Art

[0002] With the increase in debris, the collision risk of space objects is increasing. If a space object flying in a geostationary orbit can be observed by a satellite flying in the vicinity of the geostationary orbit, such observation is effective for risk countermeasures such as collision avoidance. When observation is performed using an optical observation device, the optical observation device observes the sunlight reflected from the observation target. Therefore, the relative positional relationship among the sun, the observation satellite, and the observation target becomes one of the constraint conditions.

[0003] A satellite called a geostationary satellite orbits the earth in synchronization with the rotation of the earth. Therefore, when viewed from the ground surface, the satellite appears to be stationary. Therefore, the relative positional relationship between the sun and the geostationary satellite is determined depending on time.

[0004] Patent Document 1 discloses a method for observing space debris in a space where sunlight is backlit.

Prior Art Documents

Patent Documents

[0005]

Patent Document 1

Summary of the Invention

Problems to be Solved by the Invention

[0006] In the method of Patent Document 1, in addition to a camera, a laser transmitter for irradiating space debris with a laser beam is required. Further, it is necessary to arrange an optical filter for cutting sunlight in front of the lens of the camera. Therefore, it is difficult to reduce the cost of monitoring by an observation satellite in the method of Patent Document 1.

[0007] In the present disclosure, an object is to enable updating of a catalog with reduced error of public information by acquiring monitoring information of a specific monitoring target based on public orbit information using a first monitoring device and a second monitoring device.

Means for Solving the Problems

[0008] A space situation monitoring business device according to the present disclosure is a space situation monitoring business device that acquires space object information representing the situation of a space object flying in space and manages the space object information, a first monitoring device flying in a geostationary orbit, a second monitoring device installed on the ground, a catalog for recording orbit information of a plurality of space objects, a measurement error inspection device, and an acceleration / deceleration object tracking device and includes The catalog records public orbit information acquired from publicly available information, first orbit information acquired by the first monitoring device, and second orbit information acquired by the second monitoring device and records, The space situation monitoring business device acquires monitoring information of a specific space object by the first monitoring device and the second monitoring device based on public orbit information of the specific space object, and the measurement error inspection device selects orbit information based on the public orbit information, the first orbit information, and the second orbit information of the specific space object, and generates third orbit information as updated information.

Effects of the Invention

[0009] In the space situation monitoring business device according to the present disclosure, by acquiring the monitoring information of a specific monitoring target based on the publicly available orbital information using the first monitoring device and the second monitoring device, it is possible to update the catalog 590 with reduced errors in the publicly available information, and by reducing the inclusion error of the orbital information, there is an effect that the first monitoring device to the second monitoring device can surely capture the field of view.

Brief Description of the Drawings

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Embodiments for Carrying Out the Invention

[0011] Hereinafter, 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. Also, in the following drawings, the size relationships of the respective components may be different from the actual ones. Further, in the description of the embodiments, directions or positions such as "above", "below", "left", "right", "front", "rear", "front side", and "back side" may be indicated. Those notations are merely for convenience of explanation and do not limit the arrangement and orientation of components such as devices, instruments, or parts.

[0012] Embodiment 1. ***Description of Configuration*** FIG. 1 is a configuration example of a space traffic management system 500 according to the present embodiment. The space traffic management system 500 acquires space object information 501 representing the situation of a space object 60 flying in space and manages the space object information 501. The space traffic management system 500 includes a management business device 40. The management business device 40 further includes a space traffic management device 700. The space traffic management system 500 includes a plurality of space traffic management devices 700 each performing flight safety management of space objects. The space traffic management device 700 is installed in a management business device 40 used by each of a plurality of management operators who manage space objects flying in space. The plurality of space traffic management devices 700 are connected to each other by a communication line.

[0013] The space traffic management device 700 communicates with other management business devices 40. The space traffic management device 700 may be mounted on the ground facility 701. For example, the megaconstellation business device 41 includes a space traffic management device 700 that is compatible with the space traffic management devices 700 included in each of the plurality of management business devices. The space traffic management device 700 included in the megaconstellation business device 41 is connected via the space traffic management device 700 to a space traffic management system 500 in which the space traffic management devices 700 included in each of the other plurality of management business devices are connected to each other by a communication line.

[0014] The management business device 40 provides information on space objects 60 such as artificial satellites or debris. The management business device 40 is a computer of an operator that collects information on space objects 60 such as artificial satellites or debris. The management business device 40 includes devices such as a megaconstellation business device 41, a LEO constellation business device 42, a satellite business device 43, an orbit transition business device 44, a debris removal business device 45, a rocket launch business device 46, and an SSA business device 47. SSA is an abbreviation for Space Situational Awareness. LEO is an abbreviation for Low Earth Orbit. Note that the management business device 40 may be configured to include a monitoring device 810 such as an observation satellite and monitor space objects with the monitoring device 810. The configuration including the monitoring device 810 will be described later.

[0015] The megaconstellation business device 41 is a computer of a megaconstellation business operator that conducts a large-scale satellite constellation, that is, a megaconstellation business. The megaconstellation business device 41 is, for example, a business device that manages a satellite constellation composed of 100 or more satellites. The LEO constellation business device 42 is a computer of a LEO constellation business operator that conducts a low-earth orbit constellation, that is, a LEO constellation business. The satellite business device 43 is a computer of a satellite business operator that handles one to several satellites. The orbit transition business device 44 is a computer of an orbit transition business operator that issues an alert for a satellite's intrusion into a space object. The debris removal business device 45 is a computer of a debris removal business operator that conducts a business of collecting debris. The rocket launch business device 46 is a computer of a rocket launch business operator that conducts a rocket launch business. The SSA business device 47 is a computer of an SSA business operator who conducts the SSA business, that is, the space situation monitoring business. The SSA business operator publicly discloses at least a part of the information on space objects collected through the SSA business, for example, on a server. The SSA business device 47 is also called a space situation monitoring business device.

[0016] The management business device 40 may be other devices as long as it can collect information on space objects such as artificial satellites or debris and provide the collected information to the space traffic management system 500.

[0017] The space traffic management device 700 includes a processor 910 and 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 other hardware via signal lines and controls these other hardware.

[0018] As an example of functional elements, the space traffic management device 700 includes a space traffic management unit 710 and a storage unit 720. The space object information 501 is stored in the storage unit 720.

[0019] The functions of the space traffic management unit 710 are realized by software. The storage unit 720 may be provided in the memory 921. Alternatively, the storage unit 720 may be provided in the auxiliary storage device 922. Also, the storage unit 720 may be divided and provided in the memory 921 and the auxiliary storage device 922. For example, the space traffic management device 700 realizes the function of space object intrusion warning. However, as will be described later, the space traffic management device 700 has various functions other than the function of space object intrusion warning.

[0020] The processor 910 is a device that executes a space traffic management program. The space traffic management program is a program that realizes the functions of each component of the space traffic management device 700 and the space traffic management system 500.

[0021] The processor 910 is an IC (Integrated Circuit) that performs arithmetic processing. Specific examples of the processor 910 are a CPU, a DSP (Digital Signal Processor), and a GPU (Graphics Processing Unit).

[0022] The memory 921 is a storage device that temporarily stores data. Specific examples of the memory 921 are SRAM (Static Random Access Memory) or DRAM (Dynamic Random Access Memory). The auxiliary storage device 922 is a storage device that stores data. A specific example of the auxiliary storage device 922 is an HDD. Also, the auxiliary storage device 922 may be a portable storage medium such as an SD (registered trademark) memory card, a CF, a 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.

[0023] 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 USB (Universal Serial Bus) terminal. Note that the input interface 930 may be a port connected to a LAN (Local Area Network). 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).

[0024] The communication device 950 has a receiver and a transmitter. Specifically, the communication device 950 is a communication chip or a NIC (Network Interface Card). The space traffic management device 700 communicates with ground facilities and satellites, or between satellites via the communication device 950.

[0025] The space traffic management program is loaded into the processor 910 and executed by the processor 910. In the memory 921, not only the space traffic management program but also an OS (Operating System) is stored. While executing the OS, the processor 910 executes the space traffic management program. The space traffic management program and the OS may be stored in an auxiliary storage device. The space traffic 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 part or all of the space traffic management program may be incorporated into the OS.

[0026] The space traffic management device 700 may include a plurality of processors that replace the processor 910. These multiple processors share the execution of the space traffic management program. Each processor is a device that executes the space traffic management program in the same way as the processor 910.

[0027] Data, information, signal values, and variable values used, processed, or output by the space traffic management program are stored in the memory 921, the auxiliary storage device 922, or registers or cache memory within the processor 910.

[0028] The "section" of the space traffic management section 710 may be read as "process", "procedure", or "step". Also, the "process" of the space traffic management process may be read as "program", "program product", or "computer-readable storage medium storing a program". The space traffic management program causes a computer to execute each process, each procedure, or each step obtained by replacing the "section" of the above-described space traffic management section with "process", "procedure", or "step". Further, the space traffic management method is a method performed when the space traffic management device 700 executes the space traffic management program. The space traffic management program may be stored and provided in a computer-readable recording medium or storage medium. Further, the space traffic management program may be provided as a program product.

[0029] FIG. 2 is a configuration example of the SSA business device 47 according to the present embodiment. The SSA business device 47 acquires space object information 501 representing the situation of a space object 60 flying in space. Then, the SSA business device 47 manages the acquired space object information 501. The SSA business device 47 communicates with a monitoring device 810 flying in the vicinity of the geostationary orbit. The SSA business device 47 may include the monitoring device 810 flying in the vicinity of the geostationary orbit. At this time, the SSA business device 47 is also referred to as an SSA business system including the monitoring device 810. The SSA business device 47 includes a ground facility 701 that transmits a command 711 to the monitoring device 810 and receives monitoring data 712 acquired by the monitoring device 810. The SSA business device 47 is an example of the management business device 40 described above. The ground facility 701 is an example of the space traffic management device 700 described above.

[0030] In the following embodiments, there may be cases where it is described that the management business device 40, the SSA business device 47, the space traffic management device 700, or the ground facility 701 executes control and data processing functions. In this case, mainly, the space traffic management section 710 realizes the functions.

[0031] FIG. 3 is a configuration example of a satellite 30 which is an example of the space object 60 according to the present embodiment. Satellite 30 includes a satellite control device 310, a satellite communication device 32, a propulsion device 33, an attitude control device 34, and a power supply device 35. In addition, it includes components for realizing various functions. However, in FIG. 3, the satellite control device 310, the satellite communication device 32, the propulsion device 33, the attitude control device 34, and the power supply device 35 will be described. Satellite 30 is an example of a celestial object 60.

[0032] The satellite control device 310 is a computer that controls the propulsion device 33 and the attitude control device 34 and includes a processing circuit. Specifically, the satellite control device 310 controls the propulsion device 33 and the attitude control device 34 according to various commands transmitted from the ground device. The satellite communication device 32 is a device that communicates with the ground device. Specifically, the satellite communication device 32 transmits various data related to the satellite itself to the ground device. Also, the satellite communication device 32 receives various commands transmitted from the ground device. The propulsion device 33 is a device that applies a propulsion force to the satellite 30 and changes the speed of the satellite 30. Specifically, the propulsion device 33 is an apogee kick motor or a chemical propulsion device, or an electric propulsion device. An apogee kick motor (AKM) is the upper-stage propulsion device used for injecting an artificial satellite into orbit and is also called an apogee motor (when using a solid rocket motor) or an apogee engine (when using a liquid engine). The chemical propulsion device is a thruster using a mono-liquid or bi-liquid fuel. As the electric propulsion device, an ion engine or a Hall thruster is used. The apogee kick motor is the name of the device used for orbit transfer and may also be a type of chemical propulsion device. The attitude control device 34 is a device for controlling attitude elements such as the attitude of the satellite 30, the angular velocity of the satellite 30, and the line of sight direction. The attitude control device 34 changes each attitude element in a desired direction. Or, 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 is a device such as a gyroscope, an earth sensor, a sun sensor, a star tracker, a thruster, and a magnetic sensor. The actuator is a device such as 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 device. The power supply device 35 includes devices such as a solar cell, a battery, and a power control device, and supplies power to each device mounted on the satellite 30.

[0033] The processing circuit provided in the satellite control device 310 will be described. The processing circuit may be dedicated hardware or a processor that executes a program stored in a memory. In the processing circuit, some functions may be realized by dedicated hardware and the remaining functions may be realized by software or firmware. That is, the processing circuit can be realized by hardware, software, firmware, or a combination thereof. Specifically, the dedicated hardware is a single circuit, a composite circuit, a programmed processor, a parallel programmed processor, an ASIC, an FPGA, or a combination thereof. ASIC is an abbreviation for Application Specific Integrated Circuit. FPGA is an abbreviation for Field Programmable Gate Array.

[0034] FIG. 4 is a diagram showing a configuration example of the communication satellite 811 according to the present embodiment. FIG. 5 is a diagram showing a configuration example of an observation satellite 812 which is an example of the monitoring device 810 according to the present embodiment. FIG. 6 is a diagram showing a configuration example of an observation satellite 813 which is another example of the monitoring device 810 according to the present embodiment. In FIGS. 3 to 6, components with the same name may have the same functions, and the description thereof may be omitted.

[0035] Based on FIG. 4, the configuration of the communication satellite 811 will be described. The communication satellite 811 includes a communication device 121, a propulsion device 122, a power supply device 123, and a camera 124. For example, the camera 124 is a wide-angle camera that points in the same direction as the pointing direction of the first directional antenna 121E or the second directional antenna 121W.

[0036] The communication satellite 811 can visually capture an observation satellite and other space objects flying in a geostationary orbit or an orbit near the geostationary orbit. Therefore, it is possible to visually confirm that there are no obstacles around the communication satellite 811 that cause interference and noise due to communication. The other space objects are space objects different from the space objects observed by the observation satellite.

[0037] Further, the camera 124 may be a camera having a fish-eye lens. The camera 124 is arranged such that the direction from the communication satellite 811 to the Earth becomes the line-of-sight vector. The camera 124 equipped with a fish-eye lens can obtain elevation direction image information in a 360-degree field-of-view direction around the line-of-sight vector as an axis. By arranging the camera 124 such that the direction from the communication satellite 811 to the Earth becomes the line-of-sight vector, the observation satellite 812 and other space objects flying in a geostationary orbit or an orbit near the geostationary orbit can be visually captured. Furthermore, it becomes possible to estimate the positions of other space objects on the orbit. Therefore, it is possible to visually confirm that there is no interference and noise due to communication around the communication satellite 811.

[0038] Based on FIG. 5, the configuration of the observation satellite 812, which is an example of the monitoring device 810, will be described. The observation satellite 812 includes an observation device 111, a satellite control device 112, a communication device 113, a propulsion device 114, an attitude control device 115, a power supply device 116, and a camera 117. The observation device 111 is a device for observing cosmic objects. The observation device 111 is also referred to as monitoring equipment. The camera 117 is, for example, a wide-angle camera that points at the communication satellite 811.

[0039] The camera 117 can visually capture the communication satellite 811 and other cosmic objects flying in a geostationary orbit or an orbit near the geostationary orbit. Therefore, it is possible to visually confirm that the environment around the observation satellite 812 is free from communication interference and noise.

[0040] Also, the camera 117 may be a camera with a fish-eye lens. The camera 117 is arranged, for example, such that the direction from the observation satellite 812 to the communication satellite 811 becomes the line-of-sight vector.

[0041] With the camera 117 equipped with a fish-eye lens, image information in the elevation direction can be obtained in the 360-degree field-of-view direction around the axis of the line-of-sight vector. By arranging the camera 117 such that the direction from the observation satellite 812 to the communication satellite 811 becomes the line-of-sight vector, the communication satellite 811 and other cosmic objects flying in a geostationary orbit or an orbit near the geostationary orbit can be visually captured. Furthermore, it becomes possible to estimate the positions of other cosmic objects on the orbit. Therefore, it is possible to visually confirm that the environment around the observation satellite 812 is free from communication interference and noise.

[0042] Based on FIG. 6, the configuration of the observation satellite 813, which is another example of the monitoring device 810, will be described. The observation satellite 813 includes an observation device 201, a satellite control device 202, a communication device 203, a propulsion device 204, an attitude control device 205, and a power supply device 206.

[0043] Observation device 201 is a device for observing celestial objects. Observation device 201 optically photographs celestial objects flying at altitudes different from the orbital altitude of the observation satellite. Specifically, observation device 201 is a visible optical sensor. Observation device 201 generates observation data. The observation data is data obtained by the observation performed by observation device 201. For example, the observation data corresponds to data representing an image in which celestial object 110 is reflected.

[0044] Satellite control device 202 is a computer that controls observation satellite 813. Satellite control device 202 controls observation device 201, propulsion device 204, and attitude control device 205 according to a predetermined procedure or various commands transmitted from ground facilities.

[0045] Communication device 203 is a device that communicates with ground facilities. It is also called a satellite communication device. Communication device 203 transmits observation data to ground facilities. Also, communication device 203 receives various commands transmitted from ground facilities.

[0046] Figure 7 is an example of celestial object information 501 according to this embodiment. In celestial object information 501, a celestial object ID for identifying celestial object 60 and orbit information are set. The orbit information includes predicted orbit information and actual orbit information. The predicted orbit information includes an epoch, orbital elements, prediction error, information providing business device ID, and information update date. The actual orbit information includes UTS time, position coordinates, measurement error, information providing business device ID, and information update date.

[0047] Celestial object information 501 includes orbit information of celestial objects collected from other management business devices 40. For example, celestial object information 501 includes a catalog 590 in which orbit information of celestial objects is recorded in advance. Catalog 590 is collected from a management operator who manages celestial objects.

[0048] FIG. 8 is a diagram showing an example of space object information 501 according to the present embodiment. The SSA business device 47 stores, for example, space object information 501 in which predicted values of the orbits of space objects 60 are set, in the storage unit 720. The SSA business device 47 may acquire, for example, predicted values of the orbits of the plurality of space objects 60 from a management business device 40 used by a management business operator that manages the plurality of space objects 60, and store them as catalog 590 in the space object information 501. Alternatively, the SSA business device 47 may acquire space object information 501 in which predicted values of the orbits of the plurality of space objects 60 are set from the management business operator, and store it in the storage unit 720. Alternatively, the SSA business device 47 may store the space object information 501 in the storage unit 720 based on the monitoring data 712 received from the monitoring device 810 included in the SSA business device 47.

[0049] The space object information 501 includes satellite orbit prediction information 52 and debris orbit prediction information 53. Predicted values of the orbits of satellites are set in the satellite orbit prediction information 52. Predicted values of the orbits of debris are set in the debris orbit prediction information 53. In the present embodiment, the satellite orbit prediction information 52 and the debris orbit prediction information 53 are included in the space object information 501, but the satellite orbit prediction information 52 and the debris orbit prediction information 53 may be stored in the storage unit 720 as individual information.

[0050] In the space object information 501, information such as, for example, a space object ID (Identifier) 511, a prediction source period 512, predicted orbit elements 513, and a prediction error 514 is set.

[0051] The space object ID 511 is an identifier for identifying the space object 60. In FIG. 8, a satellite ID and a debris ID are set as the space object ID 511. Specifically, space objects are objects such as rockets launched into space, artificial satellites, space stations, debris removal satellites, planetary exploration spacecraft, satellites or rockets that have become debris after the end of a mission.

[0052] The prediction reference period 512 is the reference period for which the orbits of a plurality of celestial objects are predicted. The predicted orbit elements 513 are the orbit elements that specify the orbits of a plurality of celestial objects. The predicted orbit elements 513 are the orbit elements predicted for the orbits of a plurality of celestial objects. In FIG. 8, six Keplerian orbit elements are set as the predicted orbit elements 513.

[0053] The prediction error 514 is the error predicted in the orbit of each of a plurality of celestial objects. The prediction error 514 is set with a travel direction error, an orthogonal direction error, and the basis of the error. In this way, in the prediction error 514, the error amount included in the actual value is explicitly shown together with the basis. As the basis of the error amount, it includes some or all of the measurement means, the content of data processing performed as a means for improving the accuracy of position coordinate information, and the statistical evaluation results of past data.

[0054] Note that in the celestial object information 501 according to this embodiment, for the celestial object 60, the prediction reference period 512 and the predicted orbit elements 513 are set. With the prediction reference period 512 and the predicted orbit elements 513, the time and position coordinates in the near future of the celestial object 60 can be obtained. For example, the time and position coordinates in the near future for the celestial object 60 may be set in the celestial object information 501. In this way, the celestial object information 501 is provided with orbit information of celestial objects including the reference period and orbit elements, or time and position coordinates, and the predicted values in the near future of the celestial object 60 are explicitly shown.

[0055] ***Explanation of Operations*** Next, an operation example of the SSA business device 47 will be described. The monitoring device 810 flies near a geostationary satellite. The ground facility 701 transmits a command 711 to the monitoring device 810 and receives the monitoring data 712 acquired by the monitoring device 810. In the following description, a specific example of the monitoring device 810 will be described as the observation satellite 812.

[0056] <Operation Example 1 of the Present Embodiment> The ground facility 701 includes a catalog 590 that records the orbital information of a plurality of space objects. Based on the orbital information of the space object 60 selected from the plurality of space objects recorded in the catalog 590, the ground facility 701 transmits a command 711 to the monitoring device 810 to operate the monitoring device 810 by directing it to the position coordinates in the Earth-fixed coordinate system included in the orbital information of the space object 60.

[0057] Specifically, the space traffic management department 710 transmits a command 711 to the monitoring device 810 to operate the monitoring device 810 by directing it to the position coordinates in the Earth-fixed coordinate system included in the orbital information, based on the orbital information of the space object 60 selected from the catalog 590.

[0058] It is necessary to monitor space objects so that space objects such as debris do not approach near a geostationary satellite owned by one's own country and cause problems in service continuity. For this reason, a management business device 40 such as the SSA business device 47 holds a catalog 590 of the orbital information of space objects around the geostationary orbit in advance. The World Geodetic System WGS84 is an Earth-fixed coordinate system also used in the positioning satellite system. In the present embodiment, the orbital information of space objects is recorded in the catalog 590 based on this position coordinate. Further, the ground facility 701 generates the command 711 using the position coordinates in the Earth-fixed coordinate system.

[0059] In operation example 1 of the present embodiment, there is an effect that an SSA operator who monitors the space situation can issue an instruction to acquire monitoring data of a desired space object to a monitoring device flying near the geostationary orbit using the position coordinates of the space object recorded in the catalog.

[0060] <Operation Example 2 of the Present Embodiment> Based on the command 711 received from the ground facility 701, the monitoring device 810 acquires monitoring data by directing it to the position coordinates specified by the command 711.

[0061] The monitoring device 810, such as the observation satellite 812, is directed at the space object 60 flying in space based on the position coordinates in the geocentric coordinate system received from the ground facility 701.

[0062] In operation example 2 of the present embodiment, the SSA operator performing space situation monitoring can monitor the situation of space objects flying near the geostationary orbit with high resolution from the vicinity by using the position coordinates of the space objects recorded in the catalog.

[0063] <Operation Example 3 of the Present Embodiment> FIG. 9 is a diagram showing a configuration example of the satellite control device 112 of the monitoring device 810 according to the present embodiment. The monitoring device 810 includes a data analysis device 821, a data re-acquisition determination device 822, and an automatic monitoring control device 823. The data analysis device 821, the data re-acquisition determination device 822, and the automatic monitoring control device 823 are provided in, for example, the satellite control device 112 of the observation satellite 812 or the satellite control device 202 of the observation satellite 813.

[0064] The data analysis device 821 transmits the luminance data obtained by digitizing the luminance information of the acquired monitoring data to the data re-acquisition determination device 822. When the luminance data meets the determination criteria of a predetermined luminance level or the determination criteria of a luminance histogram, the data re-acquisition determination device 822 transmits a data re-acquisition instruction to re-acquire the monitoring data to the automatic monitoring control device 823. Based on the data re-acquisition instruction, the automatic monitoring control device 823 generates position coordinates obtained by autonomously changing the position coordinates received in advance from the ground facility 701, directs at the generated position coordinates, and acquires monitoring data.

[0065] When the space object 60 moves from the position coordinates recorded in the catalog 590, there is a possibility that it deviates from the monitoring range of the monitoring data instructed by the command 711 from the ground facility 701 and disappears from the monitoring data. The background of the monitoring data is generally space, and the luminance level is generally at the zero level when black is set to zero and white is set to 100. Monitoring data is acquired by a monitoring device 810 with sensitivity set so that the sunlight reflection of a desired celestial object 60 has a significant luminance level of 100 or less. If the celestial object 60 is included in the monitoring data, it shows a significant luminance level. Also, when monitoring data is acquired with high resolution using optical monitoring data such as a two-dimensional area sensor, the reflected light of the celestial object is acquired as a significant luminance level over a large number of pixels. Stars may have a significant luminance level, but their luminance level is sufficiently low compared to celestial objects that reflect sunlight. Also, like point light sources, at most four pixels, including one pixel or adjacent pixels, will have a significant luminance level. Therefore, if the monitoring data acquired by the data analysis device is quantified as a luminance level, the desired celestial object can be automatically identified as existing in orbit as a significant luminance level over a large number of pixels.

[0066] For example, the data re-acquisition determination device 822 sets an example of a criterion for determining that a desired celestial object is not included in monitoring data where there is no data with a luminance level of 5 or more in advance. Alternatively, the data re-acquisition determination device 822 sets an example of a criterion for determining that a desired celestial object is not included in monitoring data where there are less than 10 pixels with a luminance level of 5 or more in the luminance histogram. Then, when this condition is met, the data re-acquisition determination device 822 instructs the automatic monitoring control device 823 to re-acquire data. The automatic monitoring control device 823 generates a position coordinate obtained by autonomously changing the position coordinate received from the ground facility 701 in advance and points to that position coordinate to acquire monitoring data. It is reasonable to set the change of the position coordinate so as to acquire the adjacent range of the acquired monitoring data as the monitoring range of the monitoring device 810. It is desirable to change the position coordinate in consideration of the relative position change between the monitoring device 810 and the celestial object over time.

[0067] In Operation Example 3 of the present embodiment, by re-acquiring data, there is an effect that even if a celestial object moves from the position in the catalog, it can be monitored. Further, since data can be autonomously re-acquired in orbit, there is an effect that monitoring data can be acquired even in a situation where no communication line with ground facilities is established.

[0068] ***Explanation of the Effects of the Present Embodiment*** According to the SSA business apparatus according to the present embodiment, there is an effect that an acquisition instruction for monitoring data of a desired celestial object can be given to a monitoring apparatus flying in the vicinity of the geostationary orbit by using the position coordinates of the celestial object recorded in the catalog.

[0069] Further, according to the SSA business apparatus according to the present embodiment, there is an effect that the situation of a celestial object flying in the vicinity of the geostationary orbit can be monitored with high resolution from the vicinity by using the position coordinates of the celestial object recorded in the catalog.

[0070] Further, according to the SSA business apparatus according to the present embodiment, by re-acquiring data, there is an effect that even if a celestial object moves, it can be monitored. Further, since data can be autonomously re-acquired in orbit, there is an effect that monitoring data can be acquired even in a situation where no communication line with ground facilities is established.

[0071] Embodiment 2. In the present embodiment, mainly, the points added to or different from Embodiment 1 will be described. Note that the same components as those in Embodiment 1 may be denoted by the same reference numerals, and the description thereof may be omitted.

[0072] FIG. 10 is a diagram showing a configuration example of the SSA business apparatus 47 according to the present embodiment. In the present embodiment, the SSA business apparatus 47 includes a monitoring apparatus 810 flying in the vicinity of the geostationary orbit equipped with a communication device, a geostationary satellite 830 equipped with a communication device, and ground facilities 701 communicating with the geostationary satellite 830. The configuration of the geostationary satellite 830 is the same as, for example, the example of the satellite in FIG. 3.

[0073] The ground facility 701 includes a catalog 590 that records the orbital information of a plurality of celestial objects. Based on the orbital information of the celestial object selected from the catalog 590, the ground facility 701 transmits a command for operating the monitoring device 810 to point to the position coordinates in the Earth-fixed coordinate system included in the orbital information to the monitoring device 810 via the geostationary satellite 830.

[0074] Since the ground facility 701 and the monitoring device 810 can always communicate with each other via the geostationary satellite 830, there is an effect that rapid command transmission and acquisition of monitoring data are possible.

[0075] Based on the command received from the ground facility 701 via the geostationary satellite 830, the monitoring device 810 acquires monitoring data by pointing to the position coordinates specified by the command. Then, the monitoring device 810 transmits the monitoring data to the ground facility 701 via the geostationary satellite 830.

[0076] Since the ground facility 701 and the monitoring device 810 can always communicate with each other via the geostationary satellite 830, there is an effect that rapid command transmission and acquisition of monitoring data are possible. Therefore, even when an emergency such as the approach of a suspicious object such as debris occurs and emergency response such as risk avoidance is required, there is an effect that the space situation can be grasped immediately.

[0077] Based on the monitoring data transmitted from the monitoring device 810, the ground facility 701 sets the position coordinates for re-acquiring data in the command. The ground facility 701 transmits the command to the monitoring device 810 via the geostationary satellite 830. Based on the command received from the ground facility 701 via the geostationary satellite 830, the monitoring device 810 acquires monitoring data by pointing to the position coordinates specified by the command. Then, the monitoring device 810 transmits the acquired monitoring data to the ground facility 701 via the geostationary satellite 830.

[0078] Since the ground facility 701 and the monitoring device 810 can always communicate via the geostationary satellite 830, even if a celestial object moves out of the monitoring range, it is possible to immediately issue an instruction to re-acquire data.

[0079] Embodiment 3. In this embodiment, mainly, the points added to or different from Embodiments 1 and 2 will be described. Note that the same components as those in Embodiments 1 and 2 may be denoted by the same reference numerals, and the description thereof may be omitted.

[0080] FIG. 11 is a diagram showing an example of an observation mode by the observation satellite 812 which is an example of the monitoring device 810 in this embodiment. The observation satellite 812 is an example of the monitoring device 810. Also, the observation devices 111 and 201 of the observation satellites 812 and 813 are examples of the monitoring equipment. In this embodiment, the observation device 111 of the observation satellite 812 will be described.

[0081] The monitoring device 810 includes monitoring equipment. The monitoring device 810 operates the monitoring equipment in the upper air on the back side of the earth where sunlight does not shine between LST 18:00 and LST 06:00 the next morning while moving eastward with respect to the celestial object, and acquires a plurality of pieces of monitoring data. LST is an abbreviation for Local Sun Time. LST is also called a sun-synchronous orbit.

[0082] Specifically, the observation satellite 812 observes a celestial object orbiting the earth and flying near the geostationary orbit. The observation satellite 812 includes an observation device 111 and a propulsion device 114. The observation satellite 812 controls the propulsion device 114 so that the observation satellite 812 decelerates, thereby decreasing the orbital altitude of the observation satellite 812. As the orbital altitude decreases, the orbital velocity of the observation satellite 812 with respect to the earth's rotation velocity increases, so that the observation satellite 812 moves eastward with respect to the celestial object and operates the observation device 111 in the upper air on the back side of the earth where sunlight does not shine between LST 18:00 and LST 06:00 the next morning.

[0083] FIG. 12 is a diagram showing another example of an observation mode by an observation satellite 812 which is an example of the monitoring device 810 of the present embodiment.

[0084] The monitoring device 810 includes monitoring equipment. While moving westward with respect to a space object, the monitoring device 810 operates the monitoring equipment above the upper atmosphere of the front side of the Earth which is the side irradiated with sunlight between LST 06:00 and LST 18:00, and acquires monitoring data a plurality of times.

[0085] Specifically, the observation satellite 812 raises the orbital altitude of the observation satellite 812 by operating the propulsion device 114 so that the observation satellite 812 accelerates. As the orbital altitude rises, the orbital speed of the observation satellite 812 with respect to the rotation speed of the Earth decreases. Thus, while the observation satellite 812 moves westward with respect to the space object, the observation device 111 is operated above the upper atmosphere of the front side of the Earth which is the side irradiated with sunlight between LST 06:00 and LST 18:00.

[0086] According to the SSA business device 47 according to the present embodiment, by reacquiring monitoring data in a reasonable time period for the monitoring device to capture the sunlight reflected by the space object, there is an effect that the monitoring data of the space object can be acquired quickly and reliably. Note that information exchange between the ground facilities and the monitoring device may be performed via a geostationary satellite.

[0087] Embodiment 4. In the present embodiment, mainly, points added or different from Embodiments 1 to 3 will be described. Note that the same reference numerals are given to the same configurations as those in Embodiments 1 to 3, and the description thereof may be omitted.

[0088] The monitoring device 810 includes a camera with a fish-eye lens having a line-of-sight vector parallel to the orbital radius direction. Specifically, the camera 117 of the observation satellite 812 described in FIG. 5 is a camera with a fish-eye lens having a line-of-sight vector parallel to the orbital radius direction.

[0089] Alternatively, the monitoring device 810 includes a wide-angle camera having a line-of-sight vector parallel to the orbital radius direction, or a plurality of wide-angle cameras having line-of-sight vectors that point in the east-west direction with respect to the orbital radius direction. Specifically, the camera 117 of the observation satellite 812 described in FIG. 5 may be a wide-angle camera having a line-of-sight vector parallel to the orbital radius direction, or a plurality of wide-angle cameras having line-of-sight vectors that point in the east-west direction with respect to the orbital radius direction.

[0090] The operation of an observation satellite equipped with a camera having a fish-eye lens or a camera having a wide-angle camera will be described below.

[0091] FIG. 13 is a diagram showing an example of a fish-eye view by a camera equipped with a fish-eye lens according to the present embodiment. When all cosmic objects are flying in a geostationary orbit with an orbital inclination angle of 0 degrees using a camera with a fish-eye lens equipped on an observation satellite that monitors cosmic objects near the geostationary orbit while flying at an orbital altitude lower than the geostationary orbit and moving relatively eastward, the imaged objects are aligned in a row within the field of view of the fish-eye lens as shown in FIG. 13.

[0092] FIG. 14 is a diagram showing an example of a fish-eye view by a camera equipped with a fish-eye lens according to the present embodiment. When the cosmic object has an orbital inclination angle other than 0 degrees, in the acquired image of the camera with a fish-eye camera, the cosmic objects are not aligned in a row and are scattered as shown in FIG. 14. If the center of the field of view of the image of the camera with a fish-eye lens is taken as the origin and the horizontal axis is the geostationary orbit plane with an orbital inclination angle of 0 degrees, the angle from the horizontal axis is the azimuth angle of the cosmic object, and the distance from the center corresponds to the distance between the observation satellite and the cosmic object.

[0093] FIG. 15 is a diagram in which information on cosmic objects is plotted on a graph with the distance on the horizontal axis and the azimuth angle on the vertical axis. FIG. 16 is a diagram analyzing FIG. 15. When information on cosmic objects is plotted on a graph with the distance on the horizontal axis and the azimuth angle on the vertical axis, as shown in FIG. 15, the information is concentrated near azimuth angle 0 degrees and near azimuth angle 180 degrees. Analyzing this graph, as shown in Fig. 16, the vicinity of azimuth 0 degrees corresponds to cosmic objects in the east, and the vicinity of azimuth 180 degrees corresponds to cosmic objects in the west. It can be seen that the deviation of the azimuth varies due to the orbital inclination angle not being 0 degrees.

[0094] Fig. 17 is an example of a fisheye view by a camera equipped with the fisheye lens according to this embodiment. Fig. 18 is a graph corresponding to Fig. 17. When the observation satellite moves eastward and performs multiple imaging with a time delay, the cosmic objects in the west move away while generally maintaining a relative distribution, and the cosmic objects in the east approach while generally maintaining a relative distribution. After the observation satellite overtakes them, they will move westward. Strictly speaking, a cosmic object flying in an orbit with an orbital inclination angle of θ degrees will have its azimuth vary by ±θ degrees in one year. However, the variation during multiple imaging in a short period is a minute quantity.

[0095] Fig. 19 is a graph corresponding to the fisheye view of the camera equipped with the fisheye lens according to this embodiment. Next, the case where the cosmic object is moving will be described. In the images taken multiple times with a time difference, as described above, the cosmic objects in the east should generally maintain a relative distribution and approach in distance. However, if the orbital altitude of the cosmic object is different from the geostationary orbit, or if the cosmic object operates its propulsion device to move, it will deviate from the relative distribution.

[0096] Fig. 20 is a graph corresponding to the fisheye view of the camera equipped with the fisheye lens according to this embodiment. When the relative relationship is maintained, the position of the cosmic object can be predicted in advance. If the measured value deviates from this, it can be determined that the cosmic object is a moving object. When the approaching speed in the east is slower than predicted, that is, when the distance is farther than predicted, it is estimated that the orbital altitude of the cosmic object is lower than the geostationary orbit and is at an altitude between the orbital altitude of the observation satellite and the altitude of the geostationary orbit. Also, it can be understood that when there is a deviation in the azimuth direction, it involves movement in the out-of-plane direction. However, it is difficult to realize a large out-of-plane movement in a short time in a normal artificial satellite. Therefore, in this case, it is presumed that the debris is near the geostationary orbit and has an out-of-plane velocity component and crosses it.

[0097] Note that the same analysis is possible even with a wide-angle camera without a fish-eye lens. Also, if the wide-angle cameras are arranged linearly symmetrically with respect to the orbital radius direction, the same analysis is possible even if the line-of-sight vectors of the individual cameras are not parallel to the orbital radius direction.

[0098] According to the data processing according to this embodiment, when other space objects are concentrated near the monitoring target, the monitoring target can be identified in advance, so that there is an effect that data of the monitoring target can be surely obtained by the monitoring device. Also, when there is a moving object with suspicious movement near the monitoring target, there is an effect that it can be identified in advance and monitoring data can be acquired by the monitoring device. Also, there is an effect that an alarm can be issued to cause the monitoring target to take an avoidance action.

[0099] Embodiment 5. In this embodiment, mainly, the points added or different from Embodiments 1 to 4 will be described. Note that the same components as those in Embodiments 1 to 4 may be denoted by the same reference numerals, and the description thereof may be omitted.

[0100] In this embodiment, the monitoring device 810 includes a camera with a fish-eye lens or a wide-angle camera and controls the orientation of the monitoring target.

[0101] According to the imaging information obtained by a camera equipped with a fish-eye lens, image information in the elevation direction can be obtained for a 360° field of view around the line of sight vector. Therefore, if imaging is performed in an arrangement that results in a line of sight vector from the observation satellite 810, which is the monitoring device 810, toward the communication satellite 811, the communication satellite 811 and other celestial objects flying in the geostationary orbit vicinity can be visually captured, and there is an effect that the position in orbit can be estimated. In addition, there is an effect that it is possible to visually confirm that the surrounding area is an environment where communication is occurring and there is no interference noise.

[0102] FIG. 21 is a diagram showing an example of a fish-eye view in a fish-eye camera according to the present embodiment. Using FIG. 21, the data processing of the fish-eye lens-equipped camera will be described. When the observation satellite is directed at a communication satellite on the geostationary orbit, since other satellites are arranged on the geostationary orbit, if all the satellites were aligned on the geostationary orbit with an orbital inclination angle of 0 degrees, the fish-eye view, which is the acquired image of the fish-eye lens-equipped camera, would be as shown in FIG. 21.

[0103] FIG. 22 is a diagram in which contour lines are plotted in the fish-eye view of FIG. 21. If the orbital altitude of the observation satellite and the pointing direction toward the communication satellite are known in advance, the contour lines from the observation satellite can be plotted within the fish-eye view as shown in FIG. 22.

[0104] FIG. 23 is a diagram in which the fish-eye view of FIG. 22 is plotted on a graph. When plotting each geostationary satellite on a graph with the communication satellite at the center of the fish-eye view, the horizontal axis arranged such that the east direction of the geostationary orbit plane is the horizontal axis, this is set as azimuth angle 0 degrees, the azimuth angle of each geostationary satellite as the vertical axis, and the distance from the observation satellite as the horizontal axis, it will be as shown in FIG. 23. When the communication satellite is the pointing center, the geostationary satellites east of the communication satellite will be aligned at an azimuth angle of 0 degrees, and the satellites west of the communication satellite will be aligned at an azimuth angle of 180 degrees.

[0105] FIG. 24 is a diagram showing another example of a fish-eye view in a fish-eye camera according to the present embodiment. In fact, for satellites near the geostationary orbit, the orbital inclination angle may be other than 0 degrees, and this example is shown in FIG. 24. When a satellite east of the communication satellite has an orbital inclination angle other than 0 degrees, on the graph with the vertical axis being the azimuth angle and the horizontal axis being the distance, it appears as the variation of the vertical axis near the azimuth angle of 0 degrees, and for the satellite on the west side, it appears as the variation of the vertical axis near the azimuth angle of 180 degrees.

[0106] FIG. 25 is a diagram showing an example of a fisheye view when it is acquired again after a time delay while maintaining the pointing direction of the observation satellite in FIG. 24. FIG. 26 is a diagram showing an example of a fisheye view in which a position deviating from the relative position relationship is detected. If the fisheye view is acquired again after a time delay while maintaining the pointing direction of the observation satellite, as shown in FIG. 25, the group of satellites on the east side of the geostationary orbit will generally approach while maintaining the relative relationship. Therefore, for the geostationary satellite group, on the premise of generally maintaining the relative relationship, the position on the fisheye view acquired after a time delay is predictable. On the contrary, if there is an object that deviates from the relative position relationship and is at a position different from the prediction, it can be estimated that it is a moving satellite. In general, it is difficult to change the out-of-plane position of a satellite in a short time. Therefore, when there is a large variation in the azimuth angle, it is highly likely that it is a cosmic object that has just crossed near the geostationary orbit.

[0107] FIG. 27 is a diagram showing an example of a fisheye view when the line-of-sight direction is moved toward the monitoring target. So far, the comparison with the monitoring data acquired after the passage of time while maintaining the line-of-sight direction has been shown. Here, a supplementary explanation will be given for the case when the line-of-sight direction is moved toward the monitoring target. Since the distance to the object in the orbit near the geostationary orbit changes with the change of the angle of the monitoring device, the fisheye view will change as shown in FIG. 27. This example shows the case where the cosmic objects are aligned with an orbital inclination angle of 0 degrees. Since the change in the relative relationship between the monitoring target and the object on the orbit due to the difference in the line-of-sight direction can be analyzed geometrically, even if the appearance in the fisheye view changes, it has no adverse effect on data analysis. Even when using a wide-angle camera without a fish-eye lens, similar data processing is possible.

[0108] According to the data processing according to this embodiment, when other celestial objects are concentrated near the monitoring target, the monitoring target can be identified in advance, so that there is an effect that data of the monitoring target can be surely obtained by the monitoring device. Also, when there is a moving object with suspicious movement near the monitoring target, there is an effect that it can be identified in advance and monitoring data can be acquired by the monitoring device. Also, there is an effect that an alarm can be issued to cause the monitoring target to take an evasive action.

[0109] Embodiment 6. In this embodiment, mainly, the points added or different from Embodiments 1 to 5 will be described. Note that the same components as those in Embodiments 1 to 5 may be denoted by the same reference numerals, and the description thereof may be omitted.

[0110] FIG. 28 is a diagram showing a configuration example of a satellite control device 112 of a monitoring device 810 according to this embodiment. The monitoring device 810 according to this embodiment flies near the geostationary orbit. The monitoring device 810 includes a camera with a fish-eye lens or a wide-angle camera, a data analysis device 821, a monitoring target identification device 824, and an automatic monitoring control device 823. As shown in FIG. 28, the data analysis device 821, the monitoring target identification device 824, and the automatic monitoring control device 823 are provided in, for example, the satellite control device 112.

[0111] The data analysis device 821 digitizes the luminance information of the monitoring data acquired by the camera with a fish-eye lens or a wide-angle camera into luminance data, and transmits map information obtained by converting the luminance distribution of the luminance data into distance and azimuth angle information to the monitoring target identification device 824. The monitoring target identification device 824 performs matching analysis on the map information and the foresight map information, which is the map information of celestial objects transmitted in advance from ground facilities, identifies the monitoring target, and extracts the identified monitoring target.

[0112] By including a data analysis device 821, a monitoring target identification device 824, and an automatic monitoring control device 823, the monitoring device 810 can automatically perform the data processing described in Embodiments 4 and 5 in orbit.

[0113] The monitoring data may include background celestial bodies in addition to cosmic objects near the geostationary orbit, or cosmic objects farther away from the geostationary orbit, called graveyard orbits. However, during monitoring from 18:00 to 06:00 in westward movement or from 06:00 to 18:00 in eastward movement, the positional relationship between the monitoring target and the sun is favorable. Therefore, since the brightness of objects near the geostationary orbit is high and that of distant celestial bodies is low, it is easy to remove celestial bodies. Also, bright celestial bodies can be identified because their position coordinates or azimuth angles are already known in advance from the star catalog of the star sensor.

[0114] Regarding cosmic objects flying near the geostationary orbit, it is possible to identify cosmic objects that enter the field of view at specific monitoring timings and in specific pointing directions based on the orbit information catalog data of cosmic objects pre - equipped on the ground. Therefore, if the look - ahead map information of distance and azimuth angle is transmitted from the ground to the monitoring device in advance and compared with the map information acquired in orbit, it is possible to match a group of cosmic objects whose orbital arrangement is as per the catalog information. Note that regarding cosmic objects in graveyard orbits, since the targets can be identified based on the orbit information of cosmic objects pre - equipped on the ground, they can be excluded. The processing content in which the data analysis device 821 digitizes data and identifies objects in orbit is the same as that described in Embodiments 4 and 5.

[0115] <Operation Example 1 of the Present Embodiment> In addition, the monitoring target identification device 824 analyzes the in - orbit position coordinates of the extracted monitoring target from the image information, and if there is a difference from the look - ahead position coordinates transmitted from the ground facility in advance, it transmits the position coordinates after correcting the difference to the automatic monitoring control device 823. The automatic monitoring control device 823 acquires monitoring data by directing the line-of-sight vector of the monitoring device 810 toward the position coordinates obtained from the monitoring target identification device 824.

[0116] As a method for extracting a monitoring target from among a plurality of orbital objects, a method of extracting the monitoring target using the orbital object information obtained in advance from an SSA operator as foresight information is effective. However, due to the error information included in the orbital object information, there may be a deviation from the predicted position. In that case, by matching the relative positional relationship with the space objects flying around, the monitoring target is identified, and further, by analyzing the difference from the predicted orbit, the orbit information is corrected and then transmitted to the automatic monitoring control device 823. The automatic monitoring control device 823 can surely acquire high-resolution monitoring data by directing the line-of-sight vector of the monitoring device 810 toward the position coordinates of the monitoring target corrected by the monitoring target identification device 824, using a monitoring device main body with excellent narrow-area monitoring performance at high resolution.

[0117] <Operation Example 2 of the Present Embodiment> As a result of performing matching analysis on the map information and the foresight map information, the monitoring target identification device 824 identifies a space object with a significant movement and extracts it as a monitoring target. The monitoring target identification device 824 analyzes the on-orbit position coordinates of the extracted monitoring target from the image information and transmits the position coordinates to the automatic monitoring control device 823. The automatic monitoring control device 823 acquires monitoring data by directing the line-of-sight vector of the monitoring device 810 toward the position coordinates obtained from the monitoring target identification device 824.

[0118] As an object that makes a significant movement, the passage of debris or the approach of a space object that has lost its control ability and is floating can be considered. When it is necessary to quickly perform an avoidance action to avoid a collision, according to the monitoring device 810 of Operation Example 2 of the present embodiment, there is an effect that monitoring data of a moving object can be quickly acquired on the orbit.

[0119] Embodiment 7. In this embodiment, mainly, the points added to or different from Embodiments 1 to 6 will be described. Note that the same reference numerals will be given to the same configurations as those in Embodiments 1 to 6, and the description thereof may be omitted.

[0120] FIG. 29 is a configuration example of the SSA business apparatus 47 according to this embodiment.

[0121] The SSA business apparatus 47 includes a first monitoring device 810a flying near the geostationary orbit, a second monitoring device 840 installed on the ground, and a catalog 590 that records orbit information of a plurality of space objects. Further, the SSA business apparatus 47 includes a measurement error inspection device 471 and an acceleration / deceleration object tracking device 472. A specific example of the first monitoring device 810a is the observation satellite 812. Also, a specific example of the second monitoring device 840 is the observation device included in the ground facility 701 of the SSA business apparatus 47.

[0122] <Operation Example 1 of this Embodiment> The catalog 590 records the public orbit information acquired from the publicly available information, the first orbit information acquired by the first monitoring device 810a, and the second orbit information acquired by the second monitoring device 840. Based on the public orbit information of a specific space object, the SSA business apparatus 47 acquires the monitoring information of the specific space object by the first monitoring device 810a and the second monitoring device 840. The SSA business apparatus 47 acquires the first monitoring information by the first monitoring device 810a and the second monitoring information by the second monitoring device 840. The monitoring information includes the first monitoring information and the second monitoring information. The measurement error inspection device 471 selects highly reliable orbit information based on the public orbit information, the first orbit information, and the second orbit information of a specific space object, and generates third orbit information as updated information.

[0123] The orbital information based on public information has a problem that the accuracy of the position information is poor. Also, in the first monitoring device and the second monitoring device, the object information obtained by the optical monitoring means has a problem that the measurement accuracy of the azimuth angle as seen from the monitoring device is high, but the distance direction error is large. Further, the object information obtained by the monitoring means using radar or laser has a problem that the accuracy in the distance direction as seen from the monitoring device is high, but the azimuth angle error is large.

[0124] Therefore, by acquiring the monitoring information of the specific monitoring target based on the public orbital information with the first monitoring device and the second monitoring device, it becomes possible to update the catalog 590 with reduced errors in the public information. Also, by selecting highly reliable information as the position information constituting the orbital information according to the position of the monitoring device and the monitoring means, it becomes possible to improve the accuracy of the orbital information. Stars in the inertial space or space objects flying near the geostationary orbit, which do not involve the operation of artificial propulsion devices and rely only on natural phenomena for flying, it is easy to estimate their positions after a specific time has passed. However, when the error in the public orbital information is large, there is a risk that they cannot be monitored outside the field of view of the first monitoring device to the second monitoring device.

[0125] According to the operation example 1 of the present embodiment, by reducing the inclusion error of the orbital information, there is an effect that it can surely be captured within the field of view by the first monitoring device to the second monitoring device.

[0126] <Operation Example 2 of the Present Embodiment> The SSA business device 47 re-acquires the monitoring information of a specific space object based on the third orbital information with both or one of the first monitoring device 810 and the second monitoring device 840. The measurement error inspection device 471 updates the third orbit information based on the third orbit information, the updated first orbit information, and the updated second orbit information. The measurement error inspection device 471 compares and evaluates the third orbit information before and after the update to identify the presence or absence of artificial acceleration and deceleration motion of a specific space object. Then, the measurement error inspection device 471 records the information of the space object with artificial acceleration and deceleration motion in the acceleration and deceleration object tracking device 472 as the initial value of the tracking information.

[0127] Space objects flying near the geostationary orbit may involve the operation of an artificial propulsion device. Compared with space objects flying depending only on natural phenomena, in the case of a space object where there is a significant difference between the position after acceleration and deceleration over time and the estimated position, it can be identified as a space object with artificial acceleration and deceleration motion. In operation example 2 of the present embodiment, a space object that performs artificial acceleration and deceleration motion on the geostationary orbit is identified. For space objects for which an unsteady movement plan has been publicly disclosed in advance for orbit injection, orbit departure, or orbit transition, even if artificial acceleration and deceleration motion is identified, precautions have been taken in advance so as not to have an adverse effect or danger on other satellites. However, space objects for which an unsteady movement plan has not been publicly disclosed need to be tracked as suspicious objects.

[0128] <Operation Example 3 of the Present Embodiment> Based on the updated third orbit information, the acceleration and deceleration object tracking device 472 reacquires the monitoring information of a specific space object by both or one of the first monitoring device 810 and the second monitoring device 840. The measurement error inspection device 471 re-updates the third orbit information based on the updated third orbit information, the re-updated first orbit information, and the re-updated second orbit information. Then, the measurement error inspection device 471 compares and evaluates the third orbit information before the update, after the update, and after the re-update to obtain the acceleration and deceleration information of a specific space object, and records the updated value of the orbit information of the specific space object as the tracking information.

[0129] According to operation example 3 of the present embodiment, by tracking the passage of time with respect to the third orbit information, it is possible to eliminate the offset error included in the position measurement error and grasp the intentional movement direction of the space object.

[0130] <Operation Example 4 of the Present Embodiment> The acceleration / deceleration object tracking device 472 repeatedly updates the monitoring information by either or both of the first monitoring device 810 and the second monitoring device 840 based on the third orbit information, and records the updated value of the orbit information of the specific space object as tracking information.

[0131] By tracking the passage of time with respect to the third orbit information, it becomes possible to grasp the intentional moving direction of the space object, and it becomes possible to predict the approach to other space objects on the geostationary orbit. In particular, when the direction and magnitude of the acceleration / deceleration change with the passage of time, there is an effect that the movement history of the specific space object serves as a clue for inferring the artificial intention.

[0132] <Operation Example 5 of the Present Embodiment> The SSA business device 47 provides the tracking information recorded by the acceleration / deceleration object tracking device 472 to the space object operator affected by the artificial movement of the specific space object.

[0133] There may be a case where a suspicious space object approaches a critical infrastructure essential as a social infrastructure such as a communication satellite and a meteorological satellite. At this time, in order to avoid risks such as collisions, countermeasures such as implementing a satellite evacuation operation are required. Therefore, the tracking information recorded by the acceleration / deceleration object tracking device 472 is provided to the relevant space object operators. As a result, there is an effect that the risk avoidance actions of the space object operators can be implemented.

[0134] In the above-described Embodiments 1 to 7, each part of each system and each device such as the space traffic management system, the SSA business system, and the SSA business device has been described as an independent functional block. However, the configuration of each system and each device does not have to be the configuration as in the above-described embodiments. As long as the functional blocks of each system and each device can realize the functions described in the above-described embodiments, any configuration may be used. Also, each system and each device may be a single device or a system composed of a plurality of devices. Also, among Embodiments 1 to 7, a plurality of parts may be combined and implemented. Alternatively, one part among these embodiments may be implemented. In addition, these embodiments may be combined and implemented in any way, either as a whole or partially. That is, in Embodiments 1 to 7, free combinations of each embodiment, or modifications of any constituent elements of each embodiment, or omissions of any constituent elements in each embodiment are possible.

[0135] Note that the above-described embodiments are essentially preferred examples and are not intended to limit the scope of the present disclosure, the scope of the applications of the present disclosure, and the scope of the uses of the present disclosure. The above-described embodiments can be variously modified as necessary.

Description of Reference Numerals

[0136] 30 satellites, 310,112,202 satellite control devices, 32 satellite communication devices, 33,122,114,204 propulsion devices, 34,115,205 attitude control devices, 35,123,116,206 power supply devices, 111,201 observation devices, 121,113,203 communication devices, 124,117 cameras, 40 management business devices, 41 megaconstellation business devices, 42 LEO constellation business devices, 43 satellite business devices, 44 orbit transfer business devices, 45 debris removal business devices, 46 rocket launch business devices, 47 SSA business devices, 500 space traffic management system, 501 space object information, 590 catalog, 471 measurement error inspection device, 472 acceleration / deceleration object tracking device, 52 satellite orbit forecast information, 53 debris orbit forecast information, 511 space object ID, 512 forecast reference period, 513 forecast orbit elements, 514 forecast error, 60 space object, 700 space traffic management device, 701 ground equipment, 710 space traffic management department, 711 command, 712 monitoring data, 720 memory unit, 810 monitoring device, 810a first monitoring device, 811 communication satellite, 812,813 observation satellites, 821 data analysis device, 822 data re-acquisition judgment device, 823 automatic monitoring control device, 824 monitoring target identification device, 830 geostationary satellite, 840 second monitoring device, 910 processor, 921 memory, 922 auxiliary storage device, 930 input interface, 940 output interface, 941 display device, 950 communication device.

Claims

1. A space situation monitoring business device that acquires space object information representing the status of a space object flying in space and manages the space object information, a first monitoring device flying in a geostationary orbit; a second monitoring device located on the ground; a catalogue recording orbital information of a plurality of space objects; A measurement error inspection device; Acceleration / deceleration object tracking device and Equipped with The catalogue includes: Public orbit information obtained from publicly available information; First trajectory information acquired by the first monitoring device; Second trajectory information acquired by the second monitoring device; Record the The space situation monitoring business device includes: Obtaining monitoring information of a specific space object by the first monitoring device and the second monitoring device based on public orbit information of the specific space object; A space situation monitoring business device in which the measurement error examination device selects orbit information based on the public orbit information, first orbit information, and second orbit information for the specific space object, and generates third orbit information, which is updated information.

2. The space situation monitoring business device includes: Based on the third orbit information, reacquire monitoring information of the specific space object by both or one of the first monitoring device and the second monitoring device; the measurement error examining device updates the third orbit information based on the third orbit information, the updated first orbit information, and the updated second orbit information; The third orbit information before and after the update is compared and evaluated to identify whether or not the specific space object has an artificial acceleration / deceleration motion, and information on the space object having an artificial acceleration / deceleration motion is recorded as an initial value of tracking information in the acceleration / deceleration object tracking device.

2. The space situational awareness business device of claim 1.

3. The accelerating / decelerating object tracking device comprises: Based on the updated third orbit information, reacquire monitoring information of the specific space object by both or one of the first monitoring device and the second monitoring device; The measurement error inspection device, re-updating the third orbit information after the update based on the third orbit information after the update, the re-updated first orbit information, and the re-updated second orbit information; The third orbit information before the update, after the update, and after the re-update is compared and evaluated to obtain acceleration / deceleration information of the specific space object, and the updated value of the orbit information of the specific space object is recorded as tracking information.

3. A space situational awareness business device as claimed in claim 2.

4. The accelerating / decelerating object tracking device comprises: Repeatedly updating the monitoring information by both or one of the first monitoring device and the second monitoring device based on the third orbit information, and recording the updated value of the orbit information of the specific space object as tracking information.

4. A space situational awareness business device as claimed in claim 3.

5. Providing tracking information recorded by the acceleration / deceleration object tracking device to space object operators who are affected by the artificial movement of the specific space object 5. A space situational awareness business device as claimed in claim 4.

6. An accelerating / decelerating object tracking device provided in the space situation monitoring business device according to any one of claims 1 to 5.

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