Space situation monitoring equipment and acceleration / deceleration object tracking equipment

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 near 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 earth's 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 backlight.

Prior Art Documents

Patent Documents

[0005]

Patent Document 1

Summary of the Invention

Problems to be Solved by the Invention

[0006] The method described in Patent Document 1 requires a laser transmitter to irradiate space debris with laser light, in addition to the camera. Furthermore, an optical filter must be placed in front of the camera lens to block sunlight. Therefore, the method described in Patent Document 1 makes it difficult to reduce the cost of monitoring by observation satellites.

[0007] This disclosure aims to enable updating of catalogs with reduced errors in publicly available information by acquiring monitoring information of specific monitored targets based on publicly available orbital information using a first monitoring device and a second monitoring device. [Means for solving the problem]

[0008] The space situation monitoring system relating to this disclosure is a space situation monitoring system that acquires space object information representing the status of space objects flying in space and manages said space object information, The first monitoring device flying in geostationary orbit, A second monitoring device installed on the ground, A catalog that records the orbital information of multiple space objects, Measurement error scrutiny device, Acceleration / deceleration object tracking device and It is equipped with, The aforementioned catalog is Publicly available orbital information obtained from publicly available information, The first orbital information acquired by the first monitoring device, The second orbital information acquired by the second monitoring device and Record it, The aforementioned space situation monitoring equipment is Based on the publicly available orbital information of a specific space object, the first monitoring device and the second monitoring device acquire monitoring information of the specific space object. The measurement error scrutiny device selects orbital information based on the publicly available orbital information of the specific space object, the first orbital information, and the second orbital information, and generates updated third orbital 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 public orbit information using the first monitoring device and the second monitoring device, it becomes possible to update the catalog 590 with reduced errors in public information, and by reducing the inclusion error of the orbit information, there is an effect that it can be surely captured within the visual field range by the first monitoring device to the second monitoring device.

Brief Description of the Drawings

[0010] [Figure 1] Configuration example of the space traffic management system according to Embodiment 1. [Figure 2] Configuration example of the space situation monitoring business device according to Embodiment 1. [Figure 3] Configuration example of a satellite, which is an example of a space object according to Embodiment 1. [Figure 4] Configuration example of a communication satellite according to Embodiment 1. [Figure 5] Configuration example of an observation satellite, which is an example of a monitoring device according to Embodiment 1. [Figure 6] Configuration example of an observation satellite, which is another example of a monitoring device according to Embodiment 1. [Figure 7] Example of space object information according to Embodiment 1. [Figure 8] Example of space object information according to Embodiment 1. [Figure 9] Configuration example of the satellite control device of the monitoring device according to Embodiment 1. [Figure 10] Configuration example of the space situation monitoring business device according to Embodiment 2. [Figure 11] An example of an observation mode by an observation satellite, which is an example of a monitoring device according to Embodiment 3. [Figure 12] Another example of an observation mode by an observation satellite, which is an example of a monitoring device according to Embodiment 3. [Figure 13] An example of a fisheye view by a camera equipped with a fisheye lens according to Embodiment 4. [Figure 14] An example of a fisheye view by a camera equipped with a fisheye lens according to Embodiment 4. [Figure 15]A diagram in which information on celestial objects is plotted on a graph with the distance on the horizontal axis and the azimuth angle on the vertical axis, according to Embodiment 4. [Figure 16] A diagram analyzing FIG. 15, according to Embodiment 4. [Figure 17] An example of a fisheye view by a camera equipped with a fisheye lens according to Embodiment 4. [Figure 18] A graph corresponding to FIG. 17, according to Embodiment 4. [Figure 19] A graph corresponding to the fisheye view of a camera equipped with a fisheye lens according to Embodiment 4. [Figure 20] A graph corresponding to the fisheye view of a camera equipped with a fisheye lens according to Embodiment 4. [Figure 21] An example of a fisheye view in a fisheye camera according to Embodiment 5. [Figure 22] A diagram in which contour lines are plotted in the fisheye view of FIG. 21, according to Embodiment 5. [Figure 23] A diagram in which the fisheye view of FIG. 22 is plotted on a graph, according to Embodiment 5. [Figure 24] Another example of a fisheye view in a fisheye camera according to Embodiment 5. [Figure 25] An example of a fisheye view when obtained again after a time delay while maintaining the pointing direction of the observation satellite in FIG. 24, according to Embodiment 5. [Figure 26] An example of a fisheye view in which a position deviating from the relative positional relationship is detected, according to Embodiment 5.​​​​​​​​​​​​​​​​The embodiments of this disclosure will be described below 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, the size relationships of the components in the following drawings may differ from those of the actual components. In addition, in the description of the embodiments, directions or positions such as "top," "bottom," "left," "right," "front," "back," "front," and "back" may be indicated. These notations are used for the convenience of explanation only and do not limit the arrangement and orientation of components such as devices, equipment, or parts.

[0012] Embodiment 1. ***Explanation of the structure*** Figure 1 shows an example configuration of the space traffic management system 500 according to this embodiment. The space traffic management system 500 acquires space object information 501 representing the status of space objects 60 flying through space, and manages the space object information 501. The space traffic management system 500 is equipped with a management unit 40. The management unit 40 is equipped with a space traffic management unit 700. The space traffic management system 500 comprises multiple space traffic management devices 700, each responsible for the safe flight management of space objects. The space traffic management devices 700 are implemented in management devices 40 used by each of the multiple management operators that manage space objects flying in space. The multiple space traffic management devices 700 are connected to each other by communication lines.

[0013] The space traffic management device 700 communicates with other management devices 40. The space traffic management device 700 may also be mounted on ground equipment 701. For example, the mega-constellation business unit 41 is equipped with a space traffic management device 700 that is compatible with the space traffic management devices 700 equipped in each of the multiple management business units. The space traffic management device 700 equipped in the mega-constellation business unit 41 is connected via the space traffic management device 700 to a space traffic management system 500, which is formed by connecting the space traffic management devices 700 equipped in each of the other multiple management business units via communication lines.

[0014] The management equipment 40 provides information about space objects 60, such as artificial satellites or space debris. The management equipment 40 is a computer of the operator that collects information about space objects 60, such as artificial satellites or space debris. The management equipment 40 includes equipment such as the mega-constellation equipment 41, the LEO constellation equipment 42, the satellite equipment 43, the orbital transfer equipment 44, the debris removal equipment 45, the rocket launch equipment 46, and the SSA equipment 47. SSA is an abbreviation for Space Situational Awareness. LEO is an abbreviation for Low Earth Orbit. Furthermore, the management equipment 40 may also be configured to include a monitoring device 810, such as an observation satellite, which monitors space objects. The configuration including the monitoring device 810 will be described later.

[0015] The megaconstellation business equipment 41 is a computer for a megaconstellation operator that conducts large-scale satellite constellations, i.e., megaconstellation operations. The megaconstellation business equipment 41 is, for example, a business unit that manages a satellite constellation consisting of 100 or more satellites. The LEO constellation business equipment 42 is the computer of the LEO constellation business operator that conducts low orbit constellation, i.e., LEO constellation business. The satellite operation equipment 43 is a computer used by satellite operators that manage one to several satellites. The orbital transfer operation device 44 is the computer of the orbital transfer operator that issues warnings about intrusions of space objects into the satellite. The debris removal equipment 45 is a computer for a debris removal business that carries out the business of recovering debris. The rocket launch operation device 46 is a computer for a rocket launch operator that conducts rocket launch operations. The SSA (Space Situational Awareness) equipment 47 is the computer of an SSA operator that conducts SSA operations, i.e., space situational awareness operations. The SSA operator, for example, makes at least a portion of the information on space objects collected through SSA operations publicly available on the server. The SSA equipment 47 is also called the space situational awareness equipment.

[0016] The management device 40 may be any device other than those described above, as long as it collects information about space objects such as artificial satellites or space debris and provides the collected information to the space traffic management system 500.

[0017] The space traffic management device 700 includes a processor 910, as well as other hardware such as memory 921, auxiliary storage device 922, input interface 930, output interface 940, and communication device 950. The processor 910 is connected to the other hardware via signal lines and controls this other hardware.

[0018] The space traffic management device 700 includes, as an example of its functional elements, a space traffic management unit 710 and a memory unit 720. The memory unit 720 stores space object information 501.

[0019] The functions of the space traffic management unit 710 are implemented by software. The storage unit 720 is provided in memory 921. Alternatively, the storage unit 720 may be provided in auxiliary storage device 922. Furthermore, the storage unit 720 may be divided and provided in memory 921 and auxiliary storage device 922. For example, the space traffic management device 700 implements the function of alerting for intrusions of space objects. However, as will be described later, the space traffic management device 700 has various functions other than alerting for intrusions of space objects.

[0020] The processor 910 is a device that executes the space traffic management program. The space traffic management program is a program that implements 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 integrated circuit (IC) that performs arithmetic processing. Specific examples of the processor 910 include the CPU, DSP (Digital Signal Processor), and GPU (Graphics Processing Unit).

[0022] Memory 921 is a storage device that temporarily stores data. Specific examples of memory 921 include SRAM (Static Random Access Memory) or DRAM (Dynamic Random Access Memory). The auxiliary storage device 922 is a storage device for storing data. A specific example of the auxiliary storage device 922 is an HDD. Alternatively, the auxiliary storage device 922 may be a portable storage medium such as an SD® memory card, CF, NAND flash, flexible disk, optical disk, compact disk, Blu-ray® disc, or DVD. HDD is an abbreviation for Hard Disk Drive. SD® is an abbreviation for Secure Digital. CF is an abbreviation for CompactFlash®. DVD is an abbreviation for Digital Versatile Disk.

[0023] The input interface 930 is a port to which input devices such as a mouse, keyboard, or touch panel are connected. Specifically, the input interface 930 is a USB (Universal Serial Bus) terminal. Alternatively, the input interface 930 may be a port connected to a LAN (Local Area Network). The output interface 940 is a port to which the cable of a display device 941, such as a display, is connected. Specifically, the output interface 940 is a USB terminal or an HDMI® (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 NIC (Network Interface Card). The space traffic management device 700 communicates between ground equipment and satellites, or between satellites themselves, via the communication device 950.

[0025] The space traffic management program is loaded into processor 910 and executed by processor 910. Memory 921 stores not only the space traffic management program but also the OS (Operating System). Processor 910 executes the space traffic management program while executing the OS. The space traffic management program and OS may also be stored in auxiliary storage. The space traffic management program and OS stored in auxiliary storage are loaded into memory 921 and executed by 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 have multiple processors that replace the processor 910. These multiple processors share the task of executing the space traffic management program. Each processor is a device that executes the space traffic management program, just like the processor 910.

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

[0028] The word "department" in "Space Traffic Management Department 710" may be replaced with "processing," "procedure," or "process." Similarly, the word "processing" in "Space Traffic Management Processing" may be replaced with "program," "program product," or "computer-readable storage medium on which a program is recorded." The space traffic management program causes a computer to execute each process, procedure, or process, replacing "department" in the above-mentioned space traffic management department with "process," "procedure," or "process." The space traffic management method is carried out by the space traffic management device 700 executing the space traffic management program. The space traffic management program may be provided on a computer-readable recording medium or storage medium. Alternatively, the space traffic management program may be provided as a program product.

[0029] Figure 2 shows an example of the configuration of the SSA business equipment 47 according to this embodiment. The SSA (Space Service Area) equipment 47 acquires space object information 501, which represents the status of a space object 60 flying through space. The SSA equipment 47 then manages the acquired space object information 501. The SSA (Space Service Area) operation device 47 communicates with a monitoring device 810 flying near geostationary orbit. The SSA operation device 47 may include the monitoring device 810 flying near geostationary orbit. In this case, the SSA operation device 47 is also called the SSA operation system including the monitoring device 810. The SSA operation device 47 includes ground equipment 701 that transmits commands 711 to the monitoring device 810 and receives monitoring data 712 acquired by the monitoring device 810. The SSA operation device 47 is an example of the management operation device 40 described above. The ground equipment 701 is an example of the space traffic management device 700 described above.

[0030] In the following embodiments, the management equipment 40, SSA equipment 47, space traffic management equipment 700, or ground equipment 701 may be described as performing control and data processing functions. In this case, the space traffic management unit 710 primarily performs these functions.

[0031] Figure 3 shows an example configuration of a satellite 30, which is an example of a space object 60 according to this embodiment. Satellite 30 comprises 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. While it also includes other components for various functions, Figure 3 illustrates the satellite control device 310, satellite communication device 32, propulsion device 33, attitude control device 34, and power supply device 35. Satellite 30 is an example of a space object 60.

[0032] The satellite control device 310 is a computer that controls the propulsion system 33 and the attitude control device 34, and is equipped with processing circuits. Specifically, the satellite control device 310 controls the propulsion system 33 and the attitude control device 34 according to various commands transmitted from the ground equipment. The satellite communication device 32 is a device that communicates with ground equipment. Specifically, the satellite communication device 32 transmits various data related to its own satellite to ground equipment. In addition, the satellite communication device 32 receives various commands transmitted from ground equipment. The propulsion system 33 is a device that provides thrust to the satellite 30 and changes the speed of the satellite 30. Specifically, the propulsion system 33 is an apogee kick motor, a chemical propulsion system, or an electric propulsion system. An apogee kick motor (AKM) is an upper-stage propulsion system used to insert 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). Chemical propulsion systems are thrusters that use mono-liquid or di-liquid fuels. Electric propulsion systems include ion engines or Hall thrusters. An apogee kick motor is a device used for orbital transitions and is sometimes a type of chemical propulsion system. The attitude control device 34 is a device for controlling attitude elements such as the attitude of the satellite 30, its angular velocity, and its line of sight. The attitude control device 34 changes each attitude element in a desired direction, or maintains each attitude element in a desired direction. The attitude control device 34 comprises attitude sensors, actuators, and a controller. The attitude sensors include devices such as gyroscopes, Earth sensors, solar sensors, star trackers, thrusters, and magnetic sensors. The actuators include devices such as attitude control thrusters, momentum wheels, reaction wheels, and control moment gyros. The controller controls the actuators according to the data measured by the attitude sensors or various commands from ground equipment. The power supply unit 35 is equipped with devices such as solar cells, batteries, and a power control device, and supplies power to each device mounted on the satellite 30.

[0033] The processing circuits provided in the satellite control device 310 will now be described. The processing circuit may be dedicated hardware, or it may be a processor that executes a program stored in memory. In a processing circuit, some functions may be implemented by dedicated hardware, while the remaining functions are implemented by software or firmware. In other words, a processing circuit can be implemented using hardware, software, firmware, or a combination thereof. The dedicated hardware specifically includes single circuits, complex circuits, programmed processors, parallel programmed processors, ASICs, FPGAs, or combinations thereof. ASIC is an abbreviation for Application Specific Integrated Circuit. FPGA is an abbreviation for Field Programmable Gate Array.

[0034] Figure 4 shows an example of the configuration of the communications satellite 811 according to this embodiment. Figure 5 shows an example of the configuration of an observation satellite 812, which is an example of a monitoring device 810 according to this embodiment. Figure 6 shows an example configuration of an observation satellite 813, which is another example of the monitoring device 810 according to this embodiment. Note that in Figures 3 to 6, components with the same name have similar functions, and their explanations may be omitted.

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

[0036] The communications satellite 811 allows for the visual observation of observation satellites and other space objects orbiting in geostationary or near-geostationary orbit. This enables visual confirmation that the environment around communications satellite 811 is free from obstacles that could cause interference and noise in communications. Other cosmic objects are different from the cosmic objects observed by observation satellites.

[0037] Furthermore, camera 124 may be a camera with a fisheye lens. Camera 124 is positioned so that the line of sight vector is the direction from the communication satellite 811 to the Earth. A camera 124 equipped with a fisheye lens provides image information in the elevation direction within a 360-degree field of view around the line of sight vector. By positioning camera 124 so that the line of sight vector is from communications satellite 811 to Earth, observation satellite 812 and other space objects flying in geostationary or near-geostationary orbit can be visually captured. Furthermore, it becomes possible to estimate the positions of other space objects in orbit. Therefore, it is possible to visually confirm that the environment around communications satellite 811 is free from communication interference and noise.

[0038] Based on Figure 5, the configuration of an observation satellite 812, which is an example of a monitoring device 810, will be explained. The observation satellite 812 is equipped with an observation instrument 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. Observation device 111 is a device for observing objects in space. Observation device 111 is also called a monitoring device. Camera 117 is, for example, a wide-angle camera pointed towards the communications satellite 811.

[0039] Camera 117 allows for the visual capture of communication satellite 811 and other space objects flying in geostationary or near-geostationary orbit. This allows for visual confirmation that the environment around observation satellite 812 is free from interference and noise for communications.

[0040] Furthermore, camera 117 may be a camera having a fisheye lens. Camera 117 is positioned such that, for example, the direction from observation satellite 812 to communication satellite 811 becomes the line of sight vector.

[0041] A camera 117 equipped with a fisheye lens provides image information in the elevation direction within a 360-degree field of view around the line of sight vector. By positioning camera 117 so that the line of sight vector is from observation satellite 812 to communications satellite 811, it is possible to visually capture communications satellite 811 and other space objects flying in geostationary or near-geostationary orbit. Furthermore, it becomes possible to estimate the positions of other space objects in orbit. Therefore, it is possible to visually confirm that the environment around observation satellite 812 is free from communication interference and noise.

[0042] Based on Figure 6, the configuration of observation satellite 813, which is another example of the monitoring device 810, will be explained. Observation satellite 813 is equipped with an observation instrument 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 objects in space. Observation device 201 optically photographs space objects flying at altitudes different from the observation satellite's orbital altitude. Specifically, observation device 201 is a visible optical sensor. The observation device 201 generates observational data. Observational data is data obtained through observations performed by the observation device 201. For example, the observational data corresponds to data representing an image of the space object 110.

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

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

[0046] Figure 7 shows an example of space object information 501 according to this embodiment. Space object information 501 is set to include a space object ID that identifies space object 60, and orbital information. Orbital information includes predicted orbital information and actual orbital information. The forecast orbital information includes the epoch, orbital elements, prediction error, information provider equipment ID, and information update date. The actual orbital information includes UTS time, position coordinates, measurement error, information provider equipment ID, and information update date.

[0047] Space object information 501 includes orbital information of space objects collected from other management equipment 40. For example, space object information 501 includes a catalog 590 in which orbital information of space objects is pre-recorded. The catalog 590 is collected from management companies that manage space objects.

[0048] Figure 8 shows an example of space object information 501 according to this embodiment. The SSA business device 47 stores, for example, space object information 501 in the storage unit 720, which contains predicted values ​​for the orbits of space objects 60. The SSA business device 47 may, for example, obtain predicted values ​​for the orbits of each of the multiple space objects 60 from a management business device 40 used by a management company that manages multiple space objects 60, and store them in the space object information 501 as a catalog 590. Alternatively, the SSA business device 47 may obtain space object information 501 containing predicted values ​​for the orbits of each of the multiple space objects 60 from a management company 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 monitoring data 712 received from a monitoring device 810 provided by the SSA business device 47.

[0049] The space object information 501 includes satellite orbit forecast information 52 and debris orbit forecast information 53. The satellite orbit forecast information 52 contains the forecast value of the satellite's orbit. The debris orbit forecast information 53 contains the forecast value of the debris's orbit. In this embodiment, the satellite orbit forecast information 52 and the debris orbit forecast information 53 are included in the space object information 501, but the satellite orbit forecast information 52 and the debris orbit forecast information 53 may also be stored as individual pieces of information in the storage unit 720.

[0050] The space object information 501 includes information such as the space object ID (Identifier) ​​511, the forecast epoch 512, the forecast orbital elements 513, and the forecast error 514.

[0051] Space object ID 511 is an identifier that identifies space object 60. In Figure 8, the satellite ID and debris ID are set as space object ID 511. Specifically, space objects include rockets launched into space, artificial satellites, space bases, debris removal satellites, planetary exploration spacecraft, and satellites or rockets that have become debris after the completion of their missions.

[0052] Forecast epoch 512 is the epoch predicted for the individual orbits of multiple cosmic objects. The predicted orbital elements 513 are orbital elements that specify the individual orbits of multiple cosmic objects. The predicted orbital elements 513 are the orbital elements predicted for each of the orbits of multiple cosmic objects. In Figure 8, the six Kepler orbital elements are set as the predicted orbital elements 513.

[0053] The forecast error 514 is the error predicted for each orbit of multiple space objects. The forecast error 514 includes a forward error, a perpendicular error, and the basis for the error. Thus, the forecast error 514 explicitly shows the amount of error inherent in the actual value, along with its basis. The basis for the amount of error includes the measurement means, the data processing performed as a means of improving the accuracy of position coordinate information, and some or all of the results of statistical evaluation of past data.

[0054] In this embodiment, the space object information 501 includes a forecast epoch 512 and a forecast orbital element 513 for the space object 60. The forecast epoch 512 and forecast orbital element 513 allow us to determine the time and position coordinates of the space object 60 in the near future. For example, the time and position coordinates of the space object 60 in the near future may be set in the space object information 501. Thus, the space object information 501 contains orbital information of the space object, including its epoch and orbital elements, or time and position coordinates, and explicitly shows the predicted values ​​for the near future of the space object 60.

[0055] ***Explanation of operation*** Next, we will explain an example of the operation of the SSA business equipment 47. The monitoring device 810 flies in the vicinity of the geostationary satellite. Ground equipment 701 sends command 711 to monitoring device 810 and receives monitoring data 712 acquired by monitoring device 810. In the following explanation, the specific example of the monitoring device 810 will be assumed to be the observation satellite 812.

[0056] <Example of operation of this embodiment 1> Ground equipment 701 is equipped with a catalog 590 that records the orbital information of multiple space objects. Based on the orbital information of space object 60 selected from the multiple space objects recorded in catalog 590, ground equipment 701 transmits a command 711 to the monitoring device 810 to operate the monitoring device 810, directing it to the Earth-fixed coordinate system position coordinates included in the orbital information of space object 60.

[0057] Specifically, the space traffic management unit 710 transmits a command 711 to the monitoring device 810, which directs the monitoring device to the Earth-fixed coordinate system position coordinates included in the orbital information of the space object 60 selected from catalog 590.

[0058] To prevent space objects such as debris from approaching the vicinity of a country's geostationary satellites and disrupting service continuity, it is necessary to monitor space objects. For this reason, management equipment 40, such as SSA (Service Space Administration) equipment 47, has a catalog 590 of orbital information on space objects around geostationary orbit in advance. The World Geodetic System (WGS84) is a fixed Earth coordinate system also used by positioning satellite systems. In this embodiment, orbital information of space objects is recorded in catalog 590 based on these position coordinates. The ground equipment 701 generates command 711 using the position coordinates of the fixed Earth coordinate system.

[0059] In Operation Example 1 of this embodiment, an SSA operator performing space situation monitoring can use the position coordinates of space objects recorded in the catalog to instruct monitoring devices flying near geostationary orbit to acquire monitoring data for desired space objects.

[0060] <Example of operation of this embodiment 2> Based on the command 711 received from the ground equipment 701, the monitoring device 810 directs itself to the position coordinates specified by the command 711 and acquires monitoring data.

[0061] Monitoring devices 810, such as the observation satellite 812, aim at the space object 60 flying through space using the Earth-fixed coordinate system position coordinates received from the ground equipment 701.

[0062] In the operation example 2 of this embodiment, the SSA operator performing space situation monitoring has the effect of being able to monitor the status of space objects flying near geostationary orbit from nearby with high resolution using the position coordinates of space objects recorded in the catalog.

[0063] <Example of operation of this embodiment 3> Figure 9 shows an example of the configuration of the satellite control device 112 of the monitoring device 810 according to this embodiment. The monitoring device 810 comprises a data analysis device 821, a data reacquisition decision device 822, and an automatic monitoring and control device 823. The data analysis device 821, the data reacquisition decision device 822, and the automatic monitoring and control device 823 are installed, for example, in 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, which is a numerical representation of the luminance information from the acquired monitoring data, to the data reacquisition decision device 822. The data reacquisition decision device 822 transmits a data reacquisition instruction to the automatic monitoring control device 823 to reacquire the monitoring data when the luminance data matches a predetermined luminance level judgment criterion or luminance histogram judgment criterion. Based on the data reacquisition instruction, the automatic monitoring and control device 823 autonomously generates position coordinates by modifying the position coordinates previously received from the ground equipment 701, points to the generated position coordinates, and acquires monitoring data.

[0065] If the space object 60 moves from the position coordinates recorded in catalog 590, it may deviate from the monitoring range of the monitoring data instructed by command 711 from the ground equipment 701 and cease to exist in the monitoring data. The background of the monitoring data is generally outer space, and the brightness level is generally at the zero level when black is set to zero and white to 100. By acquiring monitoring data with a monitoring device 810 whose sensitivity is set so that the sunlight reflection of the desired space object 60 is at a significant brightness level of 100 or less, if the space object 60 is included in the monitoring data, it will indicate a significant brightness level. Furthermore, when monitoring data is acquired with high resolution using optical monitoring data such as a 2D area sensor, the reflected light from space objects is acquired as a significant brightness level across a large number of pixels. While stars may have a significant brightness level, their brightness level is significantly lower compared to space objects that reflect sunlight. Also, similar to point light sources, only one pixel, or at most four pixels including adjacent pixels, will have a significant brightness level. Therefore, by quantifying the monitoring data acquired by the data analysis device as brightness levels, the presence of a desired space object in orbit can be automatically identified as a significant brightness level across multiple pixels.

[0066] For example, the data reacquisition decision device 822 may pre-set an example of a criterion for determining that the desired space object is not included in monitoring data where no data with a brightness level of 5 or higher exists. Alternatively, the data reacquisition decision device 822 may pre-set an example of a criterion for determining that the desired space object is not included in monitoring data where the brightness histogram contains fewer than 10 pixels with a brightness level of 5 or higher. Then, if the data reacquisition decision device 822 meets this condition, it instructs the automatic monitoring control device 823 to reacquire the data. The automatic monitoring and control device 823 generates position coordinates by autonomously modifying the position coordinates previously received from the ground equipment 701, points to these position coordinates, and acquires monitoring data. It is reasonable to set the monitoring device 810 to acquire the adjacent range of already acquired monitoring data as the monitoring range when changing the position coordinates. Furthermore, it is desirable to change the position coordinates while taking into account the change in the relative position between the monitoring device 810 and the space object as time progresses.

[0067] In operation example 3 of this embodiment, data reacquisition has the effect of enabling monitoring even if the space object moves from its cataloged location. Furthermore, since data reacquisition can be performed autonomously in orbit, monitoring data can be obtained even when a communication line with ground facilities has not been established.

[0068] ***Description of the effects of this embodiment*** The SSA business device according to this embodiment has the effect of being able to use the position coordinates of space objects recorded in the catalog to instruct a monitoring device flying near geostationary orbit to acquire monitoring data of a desired space object.

[0069] Furthermore, the SSA business device according to this embodiment has the effect of being able to monitor the status of space objects flying near geostationary orbit from nearby with high resolution using the position coordinates of space objects recorded in the catalog.

[0070] Furthermore, the SSA (Sky Space Aid) device according to this embodiment has the effect of enabling monitoring even when space objects are moving by reacquiring data. In addition, since data can be autonomously reacquired in orbit, it has the effect of being able to acquire monitoring data even when a communication line with ground facilities has not been established.

[0071] Embodiment 2. This embodiment mainly describes the points that are added to or differ from Embodiment 1. Note that components similar to those in Embodiment 1 are denoted by the same reference numerals, and their descriptions may be omitted.

[0072] Figure 10 shows an example of the configuration of the SSA business equipment 47 according to this embodiment. In this embodiment, the SSA (Service Space Administration) operation equipment 47 comprises a monitoring device 810 equipped with a communication device that flies near geostationary orbit, a geostationary satellite 830 equipped with a communication device, and ground equipment 701 that communicates with the geostationary satellite 830. The configuration of the geostationary satellite 830 is, for example, the same as the example of the satellite in Figure 3.

[0073] Ground equipment 701 is equipped with catalog 590, which contains orbital information of multiple space objects. Based on the orbital information of a space object selected from catalog 590, the ground equipment 701 transmits a command to the monitoring device 810 via the geostationary satellite 830 to operate the monitoring device 810, directing it to the Earth-fixed coordinate system position coordinates included in the orbital information.

[0074] Since the ground equipment 701 and the monitoring device 810 can communicate at all times via the geostationary satellite 830, this has the effect of enabling rapid command transmission and acquisition of monitoring data.

[0075] The monitoring device 810 acquires monitoring data by pointing to the position coordinates specified by the command, based on a command received from the ground equipment 701 via the geostationary satellite 830. The monitoring device 810 then transmits the monitoring data to the ground equipment 701 via the geostationary satellite 830.

[0076] Because the ground equipment 701 and the monitoring device 810 can communicate at all times via the geostationary satellite 830, it has the effect of enabling rapid command transmission and acquisition of monitoring data. Therefore, even in the event of an emergency such as the approach of a suspicious object like space debris, which requires emergency response such as risk avoidance, the situation in space can be grasped immediately.

[0077] Based on the monitoring data transmitted from the monitoring device 810, the ground equipment 701 sets the position coordinates for data reacquisition as a command. The ground equipment 701 transmits the command to the monitoring device 810 via the geostationary satellite 830. Based on a command received from the ground equipment 701 via the geostationary satellite 830, the monitoring device 810 directs itself to the position coordinates specified by the command and acquires monitoring data. The monitoring device 810 then transmits the acquired monitoring data to the ground equipment 701 via the geostationary satellite 830.

[0078] Since the ground equipment 701 and the monitoring device 810 can communicate at all times via the geostationary satellite 830, even if a space object moves and goes outside the monitoring range, it is possible to immediately instruct the system to reacquire data.

[0079] Embodiment 3. This embodiment mainly describes the additions or differences between Embodiments 1 and 2. Note that components similar to those in Embodiments 1 and 2 are denoted by the same reference numerals, and their descriptions may be omitted.

[0080] Figure 11 shows an example of an observation mode using the observation satellite 812, which is an example of the monitoring device 810 of this embodiment. Observation satellite 812 is an example of monitoring device 810. Also, observation devices 111 and 201 on observation satellites 812 and 813 are examples of monitoring equipment. In this embodiment, the observation device 111 on observation satellite 812 will be used for explanation.

[0081] The monitoring device 810 includes monitoring equipment. The monitoring device 810 moves eastward relative to the space object, operating its monitoring equipment above the opposite side of the Earth (the side not exposed to sunlight) between LST 18:00 and LST 06:00 the following morning, to acquire monitoring data multiple times. LST is an abbreviation for Local Sun Time. LST is also called a sun-synchronous orbit.

[0082] Specifically, observation satellite 812 will orbit the Earth and observe space objects flying near geostationary orbit. Observation satellite 812 is equipped with observation instruments 111 and propulsion devices 114. Observation satellite 812 lowers its orbital altitude by controlling its propulsion system 114 to decelerate. As the orbital altitude decreases, the orbital speed of observation satellite 812 relative to the Earth's rotation speed increases, causing observation satellite 812 to move eastward relative to the space object. Between LST 18:00 and LST 06:00 the following morning, it operates its observation instrument 111 above the far side of the Earth, the side that does not receive sunlight.

[0083] Figure 12 shows another example of an observation mode using the observation satellite 812, which is an example of the monitoring device 810 of this embodiment.

[0084] The monitoring device 810 includes monitoring equipment. The monitoring device 810 moves westward relative to the space object, and between LST06:00 and LST18:00, it operates its monitoring equipment above the Earth's near side, which is the side exposed to sunlight, to acquire monitoring data multiple times.

[0085] Specifically, the observation satellite 812 increases its orbital altitude by operating the propulsion system 114 to increase its speed. As the orbital altitude increases, the orbital speed of the observation satellite 812 relative to the Earth's rotation speed decreases, causing the observation satellite 812 to move westward relative to the space object. Between LST 06:00 and LST 18:00, the observation instrument 111 is operated above the Earth's near side, which is the side exposed to sunlight.

[0086] According to the SSA business device 47 of this embodiment, by reacquiring monitoring data at a reasonable time period for the monitoring device to capture solar reflected light from space objects, it is possible to quickly and reliably acquire monitoring data for space objects. Furthermore, information exchange between ground equipment and monitoring devices may be carried out via geostationary satellites.

[0087] Embodiment 4. This embodiment mainly describes the additions or differences between this embodiment and embodiments 1 to 3. Note that components similar to those in embodiments 1 to 3 are denoted by the same reference numerals, and their descriptions may be omitted.

[0088] The monitoring device 810 is equipped with a fisheye lens camera that has a line-of-sight vector parallel to the orbital radial direction. Specifically, the camera 117 of the observation satellite 812, as described in Figure 5, is a fisheye lens camera that has a line-of-sight vector parallel to the orbital radial direction.

[0089] Alternatively, the monitoring device 810 may comprise a wide-angle camera having a line-of-sight vector parallel to the orbital radial direction, or a plurality of wide-angle cameras having line-of-sight vectors pointed in the east-west direction relative to the orbital radial direction. Specifically, the camera 117 of the observation satellite 812 described in Figure 5 may be a wide-angle camera having a line-of-sight vector parallel to the orbital radial direction, or a plurality of wide-angle cameras having line-of-sight vectors pointed in the east-west direction relative to the orbital radial direction.

[0090] The operation of observation satellites equipped with a fisheye lens or a wide-angle camera is described below.

[0091] Figure 13 shows an example of a fisheye view taken with a camera equipped with a fisheye lens according to this embodiment. If all space objects were flying in a geostationary orbit with an orbital inclination of 0 degrees, and the observation satellite, which is flying at an orbital altitude lower than geostationary orbit and moving relatively eastward while monitoring space objects near geostationary orbit, were captured by a fisheye lens camera, the space objects would be aligned in a single line within the field of view of the fisheye lens, as shown in Figure 13.

[0092] Figure 14 shows an example of a fisheye view obtained using a camera equipped with a fisheye lens according to this embodiment. If a space object has an orbital inclination angle other than 0 degrees, the space object will not be aligned in a line in the image acquired by the fisheye camera, but will be scattered as shown in Figure 14. If the origin is the center of the field of view of the image from the fisheye lens camera, and the horizontal axis represents the geostationary orbit plane with an orbital inclination of 0 degrees, then the angle from the horizontal axis corresponds to the azimuth angle of the space object, and the distance from the center corresponds to the distance between the observation satellite and the space object.

[0093] Figure 15 is a graph plotting information about a space object with distance on the horizontal axis and azimuth on the vertical axis. Figure 16 is an analysis of Figure 15. When information about a space object is plotted on a graph with distance on the horizontal axis and azimuth on the vertical axis, the information is concentrated around 0 degrees and 180 degrees of azimuth, as shown in Figure 15. Analyzing this graph, as shown in Figure 16, we can see that objects near an azimuth of 0 degrees are located in the east, and objects near an azimuth of 180 degrees are located in the west. The deviation in azimuth angles is due to the fact that the orbital inclination is not 0 degrees.

[0094] Figure 17 is an example of a fisheye view taken with a camera equipped with a fisheye lens according to this embodiment. Figure 18 is a graph corresponding to Figure 17. When an observation satellite moves eastward and takes multiple images after a time delay, the western space objects will move further away while maintaining roughly the same relative distribution, while the eastern space objects will move closer while maintaining roughly the same relative distribution, and then move westward after the observation satellite overtakes them. Strictly speaking, a space object flying in an orbit with an orbital inclination of θ degrees will experience an azimuth angle fluctuation of ±θ degrees over a year, but the fluctuation during multiple imaging sessions in a short period of time is negligible.

[0095] Figure 19 shows a fisheye view of a camera equipped with a fisheye lens according to this embodiment, and a corresponding graph. Next, we will consider the case where the space object is in motion. As mentioned above, in images taken multiple times with a time difference, the eastern space object should generally maintain a relative distribution and its distance should decrease. However, if the space object's orbital altitude is different from a geostationary orbit, or if the space object is moving by activating its propulsion system, it will deviate from the relative distribution.

[0096] Figure 20 shows a fisheye view of a camera equipped with a fisheye lens according to this embodiment, and a corresponding graph. If relative relationships are maintained, the position of a space object can be predicted in advance, and if the measured value deviates from this prediction, it indicates that the space object is a moving object. If the approach speed is slower than predicted in the east, meaning the distance is greater than predicted, the orbital altitude of the object is estimated to be lower than that of a geostationary orbit, and is estimated to be between the orbital altitude of the observation satellite and the geostationary orbit. Furthermore, a deviation in the azimuth direction indicates movement in the out-of-plane direction. However, it is generally difficult for artificial satellites to achieve large out-of-plane movements in a short period of time. Therefore, in this case, it is presumed that the debris crossed the orbit near geostationary orbit and possessed an out-of-plane velocity component.

[0097] Furthermore, the same analysis can be performed even with a wide-angle camera that does not have a fisheye lens. Furthermore, if the wide-angle cameras are positioned symmetrically with respect to the orbital radius, similar analysis is possible even if the line-of-sight vectors of the individual cameras are not parallel to the orbital radius.

[0098] According to the data processing of this embodiment, if other space objects are densely clustered near the monitored object, the monitored object can be identified in advance, thus ensuring that data of the monitored object can be reliably obtained by the monitoring device. Furthermore, if there is a moving object exhibiting suspicious behavior near the target of surveillance, it can be identified in advance, and the surveillance device can acquire the monitoring data. Furthermore, it has the effect of issuing an alarm to prompt the monitored target to take evasive action.

[0099] Embodiment 5. This embodiment mainly describes the points that are added to or differ from Embodiments 1 to 4. Note that components similar to those in Embodiments 1 to 4 are denoted by the same reference numerals, and their descriptions may be omitted.

[0100] In this embodiment, the monitoring device 810 is equipped with a fisheye lens camera or a wide-angle camera and controls the direction of the monitoring target.

[0101] Image information from a camera equipped with a fisheye lens provides image information in the elevation direction relative to the line-of-sight vector and the surrounding 360° field of view. Therefore, by imaging in a configuration where the line-of-sight vector from the observation satellite 812 (which is the monitoring device 810) is directed toward the communication satellite 811, it is possible to visually capture the communication satellite 811 and other space objects flying in near-geostationary orbit, and to estimate their positions in orbit. Furthermore, it has the effect of visually confirming that the surrounding environment is free from interference noise due to ongoing communications.

[0102] Figure 21 is a diagram showing an example of a fisheye view in a camera with a fisheye lens according to this embodiment. Using Figure 21, we will explain the data processing of a camera equipped with a fisheye lens. When an observation satellite points at a communications satellite in geostationary orbit, other satellites in geostationary orbit are also aligned. If all satellites were aligned in geostationary orbit with an orbital inclination of 0 degrees, the fisheye view obtained by a camera with a fisheye lens would look like Figure 21.

[0103] Figure 22 shows the contour lines plotted in the fisheye view of Figure 21. If the orbital altitude of the observation satellite and the direction of orientation toward the communications satellite are known in advance, contour lines from the observation satellite can be plotted within the fisheye view as shown in Figure 22.

[0104] Figure 23 is a graph plotting the fisheye view from Figure 22. If we place a communications satellite at the center of the fisheye diagram, position it so that the horizontal axis is eastward in the geostationary orbit plane, set the azimuth of this satellite to 0 degrees, use the azimuth of each geostationary satellite as the vertical axis, and plot each geostationary satellite on a graph with the distance from the observation satellite as the horizontal axis, we get Figure 23. If a communications satellite is used as the pointing center, geostationary satellites to the east of the communications satellite will be aligned at an azimuth angle of 0 degrees, while satellites to the west will be aligned at an azimuth angle of 180 degrees.

[0105] Figure 24 is a diagram showing another example of a fisheye view in a camera with a fisheye lens according to this embodiment. In reality, satellites near geostationary orbit may have orbital inclination angles other than 0 degrees, as shown in Figure 24. When satellites to the east of a communications satellite have orbital inclination angles other than 0 degrees, this appears as a variation on the vertical axis near 0 degrees azimuth on a graph with azimuth on the vertical axis and distance on the horizontal axis, and as a variation on the vertical axis near 180 degrees azimuth for satellites to the west.

[0106] Figure 25 shows an example of a fisheye view acquired again after a time delay, while maintaining the observation satellite's pointing direction as in Figure 24. Figure 26 shows an example of a fisheye view in which a position deviating from the relative positional relationship was detected. If we were to acquire a fisheye image again after a time delay while maintaining the direction of the observation satellite, the satellites on the eastern side of the geostationary orbit would approach each other while generally maintaining their relative relationship, as shown in Figure 25. Therefore, assuming that the relative relationships of geostationary satellites are generally maintained, the positions on the fisheye map acquired after a time delay can be predicted. If, in contrast, an object deviates from the relative positional relationship and is located in a different position than predicted, it can be estimated to be a moving satellite. Furthermore, since it is generally difficult to change the out-of-plane position of a satellite in a short period of time, if there is a large fluctuation in the azimuth angle, it is highly likely that it is a space object that happened to cross near geostationary orbit.

[0107] Figure 27 shows an example of a fisheye view when the line of sight is moved toward the object being monitored. Up to this point, we have shown how to compare monitoring data acquired over time while maintaining the direction of gaze. Now, we will provide supplementary explanation regarding the case where the direction of gaze is shifted toward the monitored object. As the angle of the monitoring device changes, the distance to objects in orbits near geostationary orbit changes, causing the fisheye view to change as shown in Figure 27. This example shows a case where space objects are aligned with an orbital inclination of 0 degrees. Since changes in the relative relationship between the monitored object and orbital objects due to differences in line of sight can be analyzed geometrically, changes in the appearance in the fisheye view do not negatively affect data analysis. Even when using a wide-angle camera without a fisheye lens, the same data processing is possible.

[0108] According to the data processing of this embodiment, if other space objects are densely clustered near the monitored object, the monitored object can be identified in advance, thus ensuring that data of the monitored object can be reliably obtained by the monitoring device. Furthermore, if there is a moving object exhibiting suspicious behavior near the target of surveillance, it can be identified in advance, and surveillance data can be acquired by the monitoring device. It also has the effect of issuing an alarm to the monitored target, prompting them to take evasive action.

[0109] Embodiment 6. This embodiment mainly describes the points that are added to or different from Embodiments 1 to 5. Note that components similar to those in Embodiments 1 to 5 are denoted by the same reference numerals, and their descriptions may be omitted.

[0110] Figure 28 shows an example of the configuration of the satellite control device 112 of the monitoring device 810 according to this embodiment. The monitoring device 810 according to this embodiment flies near a geostationary orbit. The monitoring device 810 comprises a camera with a fisheye 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 Figure 28, the data analysis device 821, the monitoring target identification device 824, and the automatic monitoring control device 823 are provided, for example, in the satellite control device 112.

[0111] The data analysis device 821 digitizes the brightness information of the monitoring data acquired by the fisheye lens camera or wide-angle camera to obtain brightness data, and transmits map information obtained by converting the brightness distribution of the brightness data into distance and azimuth angle information to the monitoring target identification device 824. The monitoring target identification device 824 matches and analyzes map information with foresight map information, which is map information of space objects transmitted in advance from ground equipment, to identify the monitoring target and extract 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 in the monitoring device 810, the data processing described in Embodiments 4 and 5 can be automatically performed by the monitoring device 810 in orbit.

[0113] The monitoring data may include not only celestial objects near geostationary orbit but also background objects, as well as objects further away than geostationary orbit, sometimes referred to as "graveyard orbits." However, during monitoring from 18:00 to 06:00 the following day in the westward movement, or from 06:00 to 18:00 in the eastward movement, the relative positions of the monitored object and the sun are favorable. Therefore, since objects near geostationary orbit have high brightness and distant celestial objects have low brightness, it is easy to remove celestial objects. In addition, bright celestial objects can be identified because their position coordinates or azimuth angles are known in advance from the star catalog equipped with the star sensor.

[0114] For space objects flying near geostationary orbit, it is possible to identify space objects that come into view at specific monitoring timings and directions using orbital information catalog data of space objects that are prepared in advance on the ground. Therefore, by transmitting distance and azimuth map information from the ground to the monitoring device in advance and comparing it with map information acquired in orbit, it is possible to match groups of space objects whose orbital arrangement matches the catalog information. Furthermore, space objects in graveyard orbits can be excluded because they can be identified in advance using orbital information of space objects available on Earth. The process by which the data analysis device 821 digitizes the data and identifies objects in orbit is the same as described in Embodiments 4 and 5.

[0115] <Example of operation of this embodiment 1> Furthermore, the monitoring target identification device 824 analyzes the extracted orbital position coordinates of the monitoring target from the image information, and if there is a difference from the foreseeable position coordinates transmitted in advance from the ground equipment, it transmits the position coordinates after correcting the difference to the automatic monitoring control device 823. The automatic monitoring and control device 823 directs the line-of-sight vector of the monitoring device 810 towards the position coordinates obtained from the monitoring target identification device 824 to acquire monitoring data.

[0116] One effective method for extracting targets for monitoring from among multiple orbiting objects is to use orbital object information obtained in advance from the SSA operator as foresight information to extract targets for monitoring. However, due to error information contained in the orbital object information, there may be cases where the position deviates from the predicted position. In such cases, the relative positional relationship with surrounding space objects is matched to identify the target for monitoring, and the orbital information is corrected by analyzing the difference from the predicted orbit before being transmitted to the automatic monitoring control device 823. The automatic monitoring and control device 823 directs the monitoring target's position coordinates, which have been corrected by the monitoring target identification device 824, thereby ensuring that high-resolution monitoring data is reliably acquired by the monitoring device itself, which has high resolution and excellent narrow-area monitoring performance.

[0117] <Example of operation of this embodiment 2> The monitoring target identification device 824 identifies space objects showing significant movement based on the matching analysis of map information and foresight map information, and extracts them as monitoring targets. The monitoring target identification device 824 analyzes the orbital position coordinates of the extracted monitoring targets from the image information and transmits the position coordinates to the automatic monitoring control device 823. The automatic monitoring and control device 823 directs the line-of-sight vector of the monitoring device 810 towards the position coordinates obtained from the monitoring target identification device 824 to acquire monitoring data.

[0118] Objects undergoing significant movement include the passage of debris or the approach of space objects that have lost control and are floating. When it is necessary to take evasive action quickly to avoid a collision, the monitoring device 810 in operation example 2 of this embodiment has the effect of being able to quickly acquire monitoring data of moving objects in orbit.

[0119] Embodiment 7. This embodiment mainly describes the points that are added to or different from Embodiments 1 to 6. Note that components similar to those in Embodiments 1 to 6 are denoted by the same reference numerals, and their descriptions may be omitted.

[0120] Figure 29 shows an example of the configuration of the SSA business equipment 47 according to this embodiment.

[0121] The SSA project equipment 47 comprises a first monitoring device 810a that flies near geostationary orbit, a second monitoring device 840 installed on the ground, and a catalog 590 that records orbital information of multiple space objects. The SSA project equipment 47 also includes a measurement error correction device 471 and an acceleration / deceleration object tracking device 472. A specific example of the first monitoring device 810a is the observation satellite 812. A specific example of the second monitoring device 840 is the observation device installed in the ground equipment 701 of the SSA project equipment 47.

[0122] <Example of operation of this embodiment 1> Catalog 590 records publicly available orbital information obtained from publicly available information, first orbital information obtained by the first monitoring device 810a, and second orbital information obtained by the second monitoring device 840. The SSA (Space Surveillance) device 47 acquires monitoring information of a specific space object based on the publicly available orbital information of the specific space object using the first monitoring device 810a and the second monitoring device 840. The SSA device 47 acquires first monitoring information using the first monitoring device 810a and second monitoring information using the second monitoring device 840. The monitoring information includes both the first and second monitoring information. The measurement error scrutinization device 471 selects highly reliable orbital information based on the publicly available orbital information of a specific space object, the first orbital information, and the second orbital information, and generates updated third orbital information.

[0123] Publicly available orbital information suffers from poor accuracy in positional data. Furthermore, object information acquired by optical monitoring means in the first and second monitoring devices has high accuracy in measuring azimuth angles as viewed from the monitoring device, but suffers from large errors in distance. Similarly, object information acquired by radar or laser monitoring means has high accuracy in distance as viewed from the monitoring device, but suffers from large errors in azimuth angles.

[0124] Therefore, by acquiring monitoring information for specific monitoring targets based on publicly available orbital information using the first and second monitoring devices, it becomes possible to update Catalog 590 with reduced errors in the publicly available information. Furthermore, by selecting highly reliable information as positional information that constitutes the trajectory information according to the location of the monitoring device and the monitoring means, it becomes possible to improve the accuracy of the trajectory information. For stars in inertial space, or space objects flying near geostationary orbit, that do not involve the operation of artificial propulsion systems and rely solely on natural phenomena, it is easy to estimate their position after a specific period of time. However, if the publicly available orbital information has a large margin of error, there is a risk that the object may fall outside the field of view of the first or second monitoring device and become unmonitored.

[0125] According to Operation Example 1 of this embodiment, by reducing the inclusion error in the trajectory information, it is possible to reliably capture the object within the field of view of the first or second monitoring device.

[0126] <Example of operation of this embodiment 2> Based on the third orbital information, the SSA operation device 47 reacquires monitoring information of the specific space object using either or both of the first monitoring device 810 and the second monitoring device 840. The measurement error scrutinizing 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 scrutinizing device 471 compares and evaluates the third orbit information before and after the update to identify whether or not there is artificial acceleration or deceleration motion of a specific space object. The measurement error scrutinizing device 471 then records the information of the space object with artificial acceleration or deceleration motion as the initial value of the tracking information in the acceleration / deceleration object tracking device 472.

[0127] Space objects flying near geostationary orbit may involve the operation of artificial propulsion systems. Compared to space objects that rely solely on natural phenomena for flight, space objects whose position after acceleration and deceleration over time differs significantly from their estimated position can be identified as space objects undergoing artificial acceleration and deceleration. In Operation Example 2 of this embodiment, a space object undergoing artificial acceleration and deceleration motion in geostationary orbit is identified. For space objects for which an unsteady movement plan for orbit insertion, or orbital transition has been publicly released in advance, precautions have been taken to ensure that even if artificial acceleration and deceleration motion is identified, there will be no adverse effects or dangers to other satellites. However, space objects for which an unsteady movement plan has not been publicly released need to be tracked as suspicious objects.

[0128] <Example of operation of this embodiment 3> Based on the updated third orbital information, the acceleration / deceleration object tracking device 472 reacquires monitoring information of the specific space object using either or both of the first monitoring device 810 and the second monitoring device 840. The measurement error scrutinizing device 471 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. The measurement error scrutinizing device 471 then compares and evaluates the third orbit information before, after, and after the re-updating, obtains acceleration and deceleration information for the specific space object, and records the updated orbit information value for the specific space object as tracking information.

[0129] According to Operation Example 3 of this embodiment, by tracking the time progression of the third orbital information, the offset error inherent in the position measurement error can be eliminated, making it possible to determine the intended direction of movement of a space object.

[0130] <Example of operation of this embodiment 4> The acceleration / deceleration object tracking device 472 repeatedly updates the monitoring information from both or either the first monitoring device 810 and the second monitoring device 840 based on the third orbital information, and records the updated orbital information values ​​of the specific space object as tracking information.

[0131] By tracking the third type of orbital information over time, it becomes possible to determine the intended direction of movement of a space object and predict its approach to other space objects in geostationary orbit. In particular, when the direction and magnitude of acceleration and deceleration change over time, the movement history of a specific space object can provide clues to infer human intent.

[0132] <Example of operation of this embodiment 5> The SSA business device 47 provides tracking information recorded by the acceleration / deceleration object tracking device 472 to space object operators affected by the artificial movement of specific space objects.

[0133] In some cases, suspicious space objects may approach critical infrastructure essential to society, such as communication satellites and weather satellites. In such situations, countermeasures, such as evacuating the satellites, become necessary to avoid risks like collisions. Therefore, tracking information recorded by the acceleration / deceleration object tracking device 472 is provided to the relevant space object operators. This has the effect of enabling space object operators to take risk avoidance actions.

[0134] In embodiments 1 to 7 described above, each part of each system and each device, such as the space traffic management system, the SSA business system, and the SSA business equipment, was described as an independent functional block. However, the configuration of each system and each device does not have to be as described in the embodiments above. The functional blocks of each system and each device can have any configuration as long as they can realize the functions described in the embodiments above. Furthermore, each system and each device may be a single device or a system composed of multiple devices. Furthermore, multiple parts of Embodiments 1 to 7 may be combined and implemented. Alternatively, only one part of these embodiments may be implemented. In addition, these embodiments may be combined and implemented in any way, either as a whole or in part. In other words, in embodiments 1 to 7, it is possible to freely combine each embodiment, modify any component of each embodiment, or omit any component in each embodiment.

[0135] The embodiments described above are essentially preferred examples and are not intended to limit the scope of the Disclosure, the scope of the Applications of the Disclosure, or the scope of Uses of the Disclosure. The embodiments described above can be modified in various ways as needed. [Explanation of symbols]

[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 devices, 41 Mega Constellation devices, 42 LEO Constellation devices, 43 Satellite devices, 44 Orbital transfer devices, 45 Debris removal devices, 46 Rocket launch devices, 47 SSA devices, 500 Space traffic management systems, 501 Space object information, 590 Catalogs, 471 Measurement error analysis devices, 472 Acceleration / deceleration object tracking devices, 52 Satellite orbit forecast information, 53 Debris orbit forecast information, 511 Space object ID, 512 Forecast epoch, 513 Forecast orbital elements, 514 Forecast error, 60 Space object, 700 Space traffic management device, 701 Ground equipment, 710 Space traffic management unit, 711 Command, 712 Monitoring data, 720 Memory unit, 810 Monitoring device, 810a First monitoring device, 811 Communication satellite, 812,813 Observation satellite, 821 Data analysis device, 822 Data reacquisition decision 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 system that acquires space object information representing the status of space objects flying in space and manages said space object information, The first monitoring device flying in geostationary orbit, A second monitoring device installed on the ground, A catalog that records the orbital information of multiple space objects, Measurement error scrutiny device, Acceleration / deceleration object tracking device and It is equipped with, The aforementioned catalog is Publicly available orbital information obtained from publicly available information, The first orbital information acquired by the first monitoring device, The second orbital information acquired by the second monitoring device and Record it, The aforementioned space situation monitoring equipment is Based on the publicly available orbital information of a specific space object, the first monitoring device and the second monitoring device acquire monitoring information of the specific space object. The aforementioned measurement error scrutiny device selects orbital information based on the publicly available orbital information, first orbital information, and second orbital information of the specified space object, and generates third orbital information which is updated information.

2. The aforementioned space situation monitoring equipment is Based on the third orbital information, monitoring information of the specific space object is acquired again from both or one of the first and second monitoring devices. The measurement error scrutinization device updates the third orbital information based on the third orbital information, the updated first orbital information, and the updated second orbital information. The third orbital information before and after the update is compared and evaluated to identify whether or not the specific space object is undergoing artificial acceleration or deceleration motion, and the information of the space object undergoing artificial acceleration or deceleration motion is recorded in the acceleration / deceleration object tracking device as the initial value of the tracking information. The space situation monitoring device according to claim 1.

3. The aforementioned acceleration / deceleration object tracking device, Based on the updated third orbital information, the monitoring information of the specific space object is acquired again from both or one of the first and second monitoring devices. The aforementioned measurement error verification device, Based on the updated third orbital information, the re-updated first orbital information, and the re-updated second orbital information, the updated third orbital information is updated again. The third orbital information is compared and evaluated before, after, and again after the update to obtain acceleration and deceleration information of the specific space object, and the updated value of the orbital information of the specific space object is recorded as tracking information. The space situation monitoring device according to claim 2.

4. The aforementioned acceleration / deceleration object tracking device, The monitoring information is repeatedly updated by both or either the first monitoring device and the second monitoring device based on the third orbital information, and the updated value of the orbital information of the specific space object is recorded as tracking information. The space situation monitoring device according to claim 3.

5. To space object operators affected by the artificial movement of the aforementioned specific space object, the tracking information recorded by the acceleration / deceleration object tracking device will be provided. The space situation monitoring device according to claim 4.

6. An acceleration / deceleration object tracking device provided in a space situation monitoring system according to any one of claims 1 to 5.

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