Acceleration and deceleration analysis device, space situation monitoring business device, and satellite watching system

Abstract

To enhance versatility in analysis of acceleration and deceleration of a space object.SOLUTION: The acceleration / deceleration analyzing device 700 is included in a space situation monitoring business device that monitors a space object with a monitoring device, analyzes the orbit of the space object 60 to determine whether the space object 60 is accelerating or decelerating, and, when the monitoring device finds a space object A whose orbit information is unknown and is composed of elements of the orbit 6 based on the original t0 and Kepler's law, sets the following parameters as a parameter set 0 indicating an estimated orbit information initial value that is an estimated value of the orbit information of the space object A in the original t0: Monitoring information of a monitoring device about a space object A is acquired three times or more to derive orbit 6 elements in an original period t0. The acceleration and deceleration analyzer 700 also derives the acceleration of the space object A in the out-of-plane direction at the ascending node and the acceleration of the space object A in the out-of-plane direction at the descending node from the difference between the orbit inclination derived from the monitoring information about the space object A and the orbit inclination of the parameter set 0.SELECTED DRAWING: Figure 1

Description

[Technical Field]

[0001] The present disclosure relates to an acceleration / deceleration analysis device, a space situation monitoring business device, and a satellite monitoring system. [Background technology]

[0002] In recent years, the construction of large-scale satellite constellations consisting of hundreds or even thousands of satellites has begun, increasing the risk of satellites colliding with each other in orbit. One method for avoiding the risk of a satellite colliding with another space object is to use the results of analyzing the acceleration and deceleration of the other space object. Patent Document 1 discloses a space situation monitoring business device equipped with an accelerating and decelerating object tracking device. [Prior art documents] [Patent documents]

[0003] [Patent Document 1] International Publication No. 2021 / 060492 Brochure Summary of the Invention [Problem to be solved by the invention]

[0004] The method of analyzing the acceleration and deceleration of a space object using the accelerating / decelerating object tracking device disclosed in Patent Document 1 has a problem of low versatility.

[0005] The present disclosure aims to increase versatility in analyzing the acceleration and deceleration of space objects. [Means for solving the problem]

[0006] The acceleration / deceleration analyzer according to the present disclosure comprises: An acceleration / deceleration analysis device is provided in a space situation monitoring business device that monitors a space object using a monitoring device, and analyzes the orbit of the space object to analyze whether or not the space object is accelerating or decelerating, When the monitoring device discovers a space object A whose orbital information consisting of an epoch t0 and six orbital elements based on Kepler's laws is unknown, the acceleration / deceleration analysis device acquires monitoring information of the monitoring device about the space object A three or more times as a parameter set 0 indicating an estimated orbital information initial value, which is an estimated value of the orbital information of the space object A at the epoch t0, and derives the six orbital elements at the epoch t0, The direction of travel of the space object A is defined as the X axis, and the normal direction of the orbital plane of the space object A is defined as the Y axis. The difference between the orbital inclination angle derived from monitoring information about the space object A at time t1, which is a time after the epoch t0, and the orbital inclination angle of the parameter set 0 is calculated as follows: deriving a parameter set 1 indicating an estimated orbit information update value, which is an estimate of orbit information of the space object A at the time t1; The acceleration in the out-of-plane direction at the ascending node of the space object A and the acceleration in the out-of-plane direction at the descending node of the space object A between the epoch t0 and the time t1 are derived. [Effects of the Invention]

[0007] According to the present disclosure, by analyzing the acceleration / deceleration of a space object using the results derived from the six orbital elements at epoch t0, the versatility of analyzing the acceleration / deceleration of a space object can be increased. [Brief explanation of the drawings]

[0008] [Figure 1] FIG. 2 is a diagram showing an example of the configuration of a space situation monitoring business device 47 according to the first embodiment. [Figure 2] FIG. 5 is a diagram showing a specific example of a catalog 590 according to the first embodiment. [Figure 3] FIG. 3 is a diagram showing a specific example of orbit forecast information according to the first embodiment. [Figure 4] FIG. 2 is a diagram showing a configuration example of a space object 60 according to the first embodiment. [Figure 5] FIG. 8 is a diagram showing an example of the configuration of a communication satellite 811 according to the first embodiment. [Figure 6]FIG. 8 is a diagram showing an example of the configuration of an observation satellite 812 according to the first embodiment. [Figure 7] FIG. 8 is a diagram showing an example of the configuration of an observation satellite 813 according to the first embodiment. [Figure 8] FIG. 2 is a diagram for explaining adjustment of the orbital inclination angle according to the first embodiment. [Figure 9] FIG. 10 is a diagram showing an example of the configuration of a space situation monitoring business device 47 according to a modified example of the first embodiment. [Figure 10] FIG. 10 is a diagram showing an example of the configuration of a satellite monitoring system 500 according to a second embodiment. [Figure 11] FIG. 10 is a diagram showing an example of the configuration of a monitoring center 57 according to a second embodiment. [Figure 12] FIG. 10 is a diagram showing a first communication method in a first satellite group according to a second embodiment. [Figure 13] FIG. 10 is a diagram showing a second communication method in a first satellite group according to a second embodiment. [Figure 14] FIG. 10 is a diagram showing a first communication method in a second satellite group according to the second embodiment. [Figure 15] FIG. 10 is a diagram showing a second communication method in a second satellite group according to the second embodiment. [Figure 16] FIG. 10 is a diagram showing a first communication method in a third satellite group according to the second embodiment. [Figure 17] FIG. 10 is a diagram showing a second communication method in a third satellite group according to the second embodiment. [Figure 18] FIG. 10 is a diagram showing a third communication method in a third satellite group according to the second embodiment. [Figure 19] FIG. 10 is a diagram showing an example of the configuration of a collision avoidance support system 510 according to a third embodiment. DETAILED DESCRIPTION OF THE INVENTION

[0009] Hereinafter, embodiments of the present disclosure will be described with reference to the drawings. In each drawing, identical or corresponding parts are designated by the same reference numerals. In the description of the embodiments, the description of identical or corresponding parts will be omitted or simplified as appropriate. Arrows in the drawings primarily indicate the flow of data or the flow of processing. Furthermore, the size relationships of the components in the drawings may differ from the actual relationships. Furthermore, in the description of the embodiments, directions or positions such as "up," "down," "left," "right," "front," "rear," "front," and "back" may be indicated. These notations are used merely for the sake of convenience and do not limit the arrangement or orientation of components such as devices, instruments, or parts. Furthermore, "part" may be appropriately interpreted as "circuit," "process," "procedure," "process," "stage," or "circuitry."

[0010] Embodiment 1 Hereinafter, this embodiment will be described in detail with reference to the drawings.

[0011] ***Configuration Description*** 1 shows an example of the configuration of a space situation monitoring business apparatus 47 according to this embodiment. The space situation monitoring business apparatus 47 includes an acceleration / deceleration analyzer 700, a first monitoring device 810, and a second monitoring device 840, and is also called a space situation monitoring management business apparatus or an SSA (Space Situational Awareness) business system. Each of the devices included in the space situation monitoring business apparatus 47 may be composed of multiple devices, or may be appropriately configured integrally. The space situational awareness business device 47 is composed of a computer of an SSA business, i.e., an SSA business operator that conducts a space situational awareness business. The SSA business operator, also called a space situational awareness business operator, for example, publishes at least a portion of the information about space objects collected by the SSA business on a server. The space situation monitoring business device 47 acquires space object information 501 that indicates the status of a space object 60 flying in space. The space situation monitoring business device 47 then manages the acquired space object information 501. Specific examples of the space object 60 include a rocket launched into space, an artificial satellite, a space station, a debris removal satellite, a planetary exploration spacecraft, or a satellite that has become debris after completing its mission. In this specification, an artificial satellite is also simply referred to as a satellite. The space situation monitoring business device 47 appropriately has the function of the collision avoidance support device disclosed in [Patent Document 1].

[0012] The acceleration / deceleration analyzer 700 is a computer that analyzes the trajectory of the space object 60 to determine whether the space object is accelerating or decelerating, and includes a processor 910, a memory 921, an auxiliary storage device 922, an input interface 930, an output interface 940, a display device 941, and a communication device 950. The acceleration / deceleration analyzer 700 may be installed in either the ground facility 701 or the artificial satellite. However, this specification will primarily describe the acceleration / deceleration analyzer 700 as installed in the ground facility 701. The acceleration / deceleration analyzer 700 communicates with each of the first monitoring device 810 and the second monitoring device 840, sends commands 711 to each monitoring device, and receives monitoring data 712 acquired by each monitoring device. The term "monitoring device" is a collective term for the first monitoring device 810 and the second monitoring device 840. A specific example of the first monitoring device 810 is an observation satellite 812. The first monitoring device 810 may fly in the vicinity of a geostationary orbit. A specific example of the second monitoring device 840 is an observation device provided in the ground facility 701 of the space situation monitoring business equipment 47.

[0013] The processor 910 is a device that executes each program that realizes the function of each component of the acceleration / deceleration analyzer 700 . The processor 910 is an integrated circuit (IC) that performs arithmetic processing. A specific example of the processor 910 is a central processing unit (CPU). Unit), DSP (Digital Signal Processor), or GPU (Graphics Processing Unit).

[0014] The memory 921 is a storage device that temporarily stores data. Specific examples of the memory 921 include a static random access memory (SRAM) and a dynamic random access memory (DRAM).

[0015] The auxiliary storage device 922 is a storage device that stores data. A specific example of the auxiliary storage device 922 is a hard disk drive (HDD). The auxiliary storage device 922 may also be a portable storage medium such as a Secure Digital (SD) (registered trademark) memory card, a CompactFlash (CF) (registered trademark), a NAND flash, a flexible disk, an optical disk, a compact disk, a Blu-ray (registered trademark) disk, or a Digital Versatile Disk (DVD).

[0016] 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 also be a port connected to a LAN (Local Area Network).

[0017] 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).

[0018] The communication device 950 has a receiver and a transmitter. Specifically, the communication device 950 is a communication chip or a network interface card (NIC). The acceleration / deceleration analyzer 700 communicates between ground facilities and satellites, or between satellites, via the communication device 950.

[0019] The analysis control unit 911 uses the processor 910 to realize the functions of each component of the acceleration / deceleration analyzer 700 .

[0020] The storage unit 720 is realized by the memory 921. The storage unit 720 records the catalog 590.

[0021] Catalog 590 records orbital information for multiple space objects. Catalog 590 records all or some of the following: free public orbital information obtained from public information; paid orbital information purchased by SSA operators; orbital information including non-public information obtained through agreement between operators; first orbital information obtained by first monitoring device 810; and second orbital information obtained by second monitoring device 840. Catalog 590 includes space object information 501. FIG. 2 shows a specific example of a catalog 590 according to this embodiment.

[0022] The space object information 501 may include orbital information of the space object 60 collected from the management business device 40. For example, the orbital information of the space object 60 is pre-recorded in the catalog 590. The catalog 590 may be collected from a management business that manages the space object 60. The management business device 40 provides information about the space object 60, such as an artificial satellite or debris. The management business device 40 is a computer of a business that collects information about the space object 60, such as an artificial satellite or debris. 2, a space object ID (Identification) for identifying the space object 60 and orbit information are set in the space object information 501. The orbit information includes predicted orbit information and actual orbit information. The forecast orbit information includes the epoch, orbital elements, prediction error, information provider device ID, and information update date. The actual orbit information includes UTC (Universal Time Coordinated) time, position coordinates, measurement error, information provider device ID, and information update date.

[0023] FIG. 3 shows an example of space object information 501 according to this embodiment. The space situation monitoring business device 47 stores, for example, space object information 501 in which forecast values ​​for the orbit of a space object 60 are set in the memory unit 720. The space situation monitoring business device 47 may, for example, acquire forecast values ​​for the orbit 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 the forecast values ​​in the space object information 501 as a catalog 590. Alternatively, the space situation monitoring business device 47 may acquire, from the management company, space object information 501 in which forecast values ​​for the orbit of each of the multiple space objects 60 are set, and store the space object information 501 in the memory unit 720. Alternatively, the space situation monitoring business device 47 may store the space object information 501 in the memory unit 720 based on monitoring data 712 received from a first monitoring device 810 provided in the space situation monitoring business device 47.

[0024] Space object information 501 includes satellite orbit forecast information 52 and debris orbit forecast information 53. Satellite orbit forecast information 52 includes forecast values ​​for satellite orbits. Debris orbit forecast information 53 includes forecast values ​​for debris orbits. In this embodiment, satellite orbit forecast information 52 and debris orbit forecast information 53 are included in space object information 501, but satellite orbit forecast information 52 and debris orbit forecast information 53 may also be stored in memory unit 720 as individual pieces of information.

[0025] In the space object information 501, information such as a space object ID (Identifier) ​​511, a forecast origin 512, forecast orbital elements 513, and a forecast error 514 is set, for example.

[0026] The space object ID 511 is an identifier that identifies the space object 60. In Fig. 3, a satellite ID and a debris ID are set as the space object ID 511.

[0027] The predicted epoch 512 is the predicted epoch for the orbit of each of the plurality of space objects 60 . The predicted orbital elements 513 are orbital elements that specify the orbit of each of the multiple space objects 60. The predicted orbital elements 513 are orbital elements that are predicted for the orbit of each of the multiple space objects 60. In Figure 3, six Keplerian orbital elements are set as the predicted orbital elements 513.

[0028] The forecast error 514 is an error predicted for each orbit of a plurality of space objects. The forecast error 514 includes a heading error, a cross-directional error, and the basis for the error. In this way, the forecast error 514 explicitly indicates the amount of error contained in the actual value along with the basis. The basis for the amount of error includes some or all of the measurement means, the details of data processing performed as a means for improving the accuracy of position coordinate information, and the results of statistical evaluation of past data.

[0029] In the space object information 501 according to this embodiment, a forecast origin 512 and forecast orbital elements 513 are set for the space object 60. The forecast origin 512 and forecast orbital elements 513 can be used to determine the time and position coordinates in the near future of the space object 60. For example, the time and position coordinates in the near future for the space object 60 may be set in the space object information 501. In this way, the space object information 501 includes the orbital information of the space object, including the epoch and orbital elements, or the time and position coordinates, and the predicted values ​​of the space object 60 in the near future are explicitly shown.

[0030] In the following embodiments, it may be described that the space situation monitoring business equipment 47 or the ground equipment executes the control and data processing functions. In this case, the processor 910 mainly realizes the functions.

[0031] FIG. 4 shows an example of the configuration of a satellite 30, which is an example of a space object 60 according to this embodiment. The 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. It also comprises other components that realize various functions, but Fig. 4 will explain 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. The satellite 30 is an example of a space 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 in accordance with various commands transmitted from ground devices. The satellite communication device 32 is a device that communicates with ground equipment. Specifically, the satellite communication device 32 transmits various data related to the satellite 30 to the ground equipment. The satellite communication device 32 also receives various commands transmitted from the ground equipment. The propulsion device 33 is a device that provides thrust to the satellite 30 and changes the speed of the satellite 30. Specifically, the propulsion device 33 is an apogee kick motor, a chemical propulsion device, or an electric propulsion device. The apogee kick motor (AKM) is an upper stage propulsion device used to put a satellite into orbit, and is also called an apogee motor (when a solid rocket motor is used) or an apogee engine (when a liquid engine is used). Chemical propulsion systems are thrusters that use monopropellant or bipropellant fuels. Electric propulsion systems include ion engines and Hall thrusters. An apogee kick motor is a device used for orbital transfer and can also be a type of chemical propulsion system. The attitude control device 34 controls the attitude of the satellite 30, the angular velocity of the satellite 30, and the line of sight (Line Of Sight) direction. The attitude control system 34 is a device for controlling attitude elements such as the attitude sensor, the sun sensor, the star tracker, the thruster, and the control moment gyro. The attitude control system 34 changes each attitude element to a desired direction. Alternatively, the attitude control system 34 maintains each attitude element in a desired direction. The attitude control system 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 ground equipment. The power supply unit 35 includes 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 circuitry provided in the satellite control device 310 will now be described. The processing circuitry may be dedicated hardware or may be 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, i.e., the processing circuit may be realized by hardware, software, firmware, or a combination thereof. The dedicated hardware may be, for example, a single circuit, a composite circuit, a programmed processor, a parallel programmed processor, an ASIC (Application Specific Integrated Circuit), an FPGA (Field Programmable Gate Array), or a combination thereof.

[0034] FIG. 5 shows an example of the configuration of a communications satellite 811 according to this embodiment. FIG. 6 shows an example of the configuration of an observation satellite 812, which is an example of the first monitoring device 810 according to this embodiment. FIG. 7 shows an example of the configuration of an observation satellite 813, which is another example of the first monitoring device 810 according to this embodiment.

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

[0036] The communications satellite 811 can visually capture observation satellites and other space objects flying in geostationary orbit or orbits close to geostationary orbit, making it possible to visually confirm that the environment around the communications satellite 811 is free from obstacles that could cause interference and noise in communications. The other space object 60 is a space object other than the space object observed by the observation satellite. The observation satellite is a specific example of the first monitoring device 810.

[0037] The camera 124 may also be a camera with a fisheye lens. The camera 124 is positioned so that the direction from the communication satellite 811 to the Earth is the line of sight vector. The 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 the camera 124 so that the line of sight vector is the direction from the communication satellite 811 to the Earth, it is possible to visually capture the observation satellite 812 and other space objects flying in geostationary orbit or orbits close to the geostationary orbit. Furthermore, it becomes possible to estimate the positions of other space objects in orbit. This makes it possible to visually confirm that the area around the communication satellite 811 is an environment free of communication interference and noise.

[0038] The configuration of an observation satellite 812, which is an example of the first monitoring device 810, will be described with reference to FIG. 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 equipment 111 is a device for observing the space object 60. The observation equipment 111 is also called a monitoring device. The camera 117 is, for example, a wide-angle camera directed toward the communications satellite 811 .

[0039] The camera 117 can visually capture the communication satellite 811 and other space objects flying in geostationary orbit or orbits close to geostationary orbit, making it possible to visually confirm that the environment around the observation satellite 812 is free from interference and noise due to communications.

[0040] The camera 117 may also be a camera with a fisheye lens. The camera 117 is disposed such that the direction from the observation satellite 812 to the communication satellite 811 is the line of sight vector, for example.

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

[0042] The configuration of an observation satellite 813, which is another example of the first monitoring device 810, will be described with reference to FIG. 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] The observation device 201 is a device for observing the space object 60 . The observation device 201 optically photographs the space object 60 flying at an altitude different from the orbital altitude of the observation satellite 813. Specifically, the observation device 201 is a visible optical sensor. The observation device 201 generates observation data. The observation data is data obtained by observations performed by the observation device 201. For example, the observation data corresponds to data representing an image of the space object 60.

[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 a predetermined procedure or in accordance with various commands transmitted from ground facilities.

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

[0046] ***Explanation of Operation*** The operation procedure of the acceleration / deceleration analyzer 700 corresponds to an acceleration / deceleration analysis method, and the program that realizes the operation of the acceleration / deceleration analyzer 700 corresponds to an acceleration / deceleration analysis program. Any of the programs described herein may be recorded on a computer-readable non-volatile recording medium. Specific examples of the non-volatile recording medium include an optical disk and a flash memory. Any of the programs described herein may be provided as a program product.

[0047] <Operation Example 1 of this Embodiment> The acceleration / deceleration analyzer 700 uses Keplerian elements based on Kepler's laws in the satellite orbital information that is made up of an epoch and six orbital elements. The epochs are as follows: Epoch (year and day) Kepler's orbital elements consist of the following parameters: Mean Motion (m): Mean Motion (orbits / day) or Semi-major Axis (km) Eccentricity (e): Eccentricity (unitless) ·Orbital inclination angle (i): Inclination (degrees) Right Ascension of Ascending Node (Ω): RAAN (Right Ascension of Ascending Node) (degrees) Argument of Perigee (ω): Argument of Perigee (degrees) ·Mean Anomaly (degrees)

[0048] In order to determine the orbital information of space object A, which has no prior information and whose orbital information is unknown, acceleration / deceleration analyzer 700 needs to determine the six orbital elements of space object A, which are unknown quantities. The orbit of a space object 60 orbiting the Earth describes a quadratic curve with the Earth as one focus. Two parameters are required to specify the shape of this quadratic curve. Additionally, two parameters are required to specify the plane in which the orbit of space object 60 lies, and one parameter is required to specify the direction in which the orbit is pointing on that plane. In order to determine five independent parameters that determine the shape of the orbit of the space object 60, the plane in which the orbit exists, and the orientation of the orbit, five independent measurement data, namely, measurement data of the space object 60, are required. Here, measuring the space object 60 once will obtain two independent sets of measurement data, namely, right ascension and declination. Therefore, at least three measurements are required to determine the orbit of the space object 60. However, since the monitoring information obtained by measuring the space object 60 three times in a short period of time has a large measurement error, it is considered appropriate to improve the measurement accuracy by measuring the space object 60 several more times.

[0049] In order to understand the orbital elements of space object A, it is essential to measure space object A multiple times using monitoring equipment owned by the SSA operator. However, it is considered more reasonable to obtain high-precision orbit information with few measurement errors by using a large number of first monitoring devices 810 distributed over a wide area to collect monitoring information using various monitoring methods, such as optical monitoring and radar monitoring, and to calculate initial estimates of the orbital elements. Note that if a single operator does not own monitoring devices using various monitoring methods deployed over a wide area, the acceleration / deceleration analyzer 700 may obtain orbit information obtained using monitoring equipment owned by another operator and use the obtained orbit information. If public orbit information such as TLE (Two Line Element) already exists, acceleration / deceleration analyzer 700 may use the public orbit information as parameter set 0 indicating the initial value of estimated orbit information.

[0050] Therefore, when a monitoring device discovers space object A whose orbital information consisting of epoch t0 and six orbital elements based on Kepler's laws is unknown, acceleration / deceleration analysis device 700 acquires monitoring information about space object A from the monitoring device three or more times as parameter set 0 indicating an estimated orbital information initial value, which is an estimate of the orbital information of space object A at epoch t0, and derives the six orbital elements at epoch t0. Epoch t0 is sometimes referred to as time t0.

[0051] <Operation Example 2 of this Embodiment> The purpose of space situational awareness is to predict the risk of debris or suspicious space objects approaching or colliding with critical infrastructure 55, such as communication satellites, weather satellites, and positioning satellites that function as social infrastructure, and to provide information that contributes to countermeasures. Here, critical infrastructure 55 is composed of satellites that form social infrastructure and operate services. Therefore, when space object A is discovered near space object B, which is space object 60 and critical infrastructure 55, it is considered reasonable from the perspective of assuming the worst case scenario to use the orbital information of space object B as an approximation of the orbital information of space object A and to use the orbital information of space object B as the initial value in the estimated orbit of space object A as a means of quickly grasping the orbital information of space object A. However, if it is assumed that the differential information for monitoring space object A and space object B as different objects is the difference in the argument of perigee, this is considered reasonable because it is equivalent to modeling space object A and space object B as flying in the same orbital plane with a phase difference.

[0052] Therefore, first, when a monitoring device discovers space object A and there is space object B flying around space object A and whose orbital information is known, acceleration / deceleration analysis device 700 uses the five elements other than the argument of perigee from the six orbital elements of the orbital information of space object B as the five elements other than the argument of perigee from the six orbital elements of the orbital information of space object A, and also derives the argument of perigee from the orbital information of space object A using the monitoring information of the monitoring device regarding space object A. The surroundings of space object A correspond to the vicinity of space object A. Next, the acceleration / deceleration analyzer 700 uses the five cited elements and the derived argument of perigee as parameter set 0, which indicates the estimated orbit information initial value, which is an estimate of the orbit information of space object A at epoch t0. Operation examples 3 to 8 of this embodiment are based on operation example 1 or 2 of this embodiment.

[0053] <Operation Example 3 of this Embodiment> When space object A intentionally attempts to approach space object B, it is assumed that space object A will accelerate or decelerate in its direction of travel. If space object A and space object B are flying in the same orbital plane, if space object A increases its speed, the orbital altitude of space object A will increase and its ground speed will decrease. Therefore, space object A can approach space object B when space object B is flying behind space object A. Similarly, if space object A decelerates, the orbital altitude of space object A will decrease and its ground speed will increase. Therefore, space object A can approach space object B when space object B is flying ahead of space object A. If space object A accelerates or decelerates in the direction of its movement, the orbital period of space object A will change. Since the measurement accuracy of the orbital period is high, it is considered reasonable to observe the orbital period of space object A from the perspective of quantitatively evaluating the acceleration and deceleration of space object A.

[0054] Therefore, first, the acceleration / deceleration analysis device 700 derives parameter set 1 from the difference between the orbital period derived from monitoring information about space object A at time t1 and the orbital period of parameter set 0, with the direction of travel of space object A as the X-axis. Time t1 is a time after epoch t0. Parameter set 1 indicates an estimated orbit information update value, which is an estimated value of the orbit information of space object A at time t1. Next, the acceleration / deceleration analyzer 700 derives ΔV and acceleration in the direction of travel of the space object A between the epoch t0 and the time t1 from the monitoring information.

[0055] <Operation Example 4 of this Embodiment> First, acceleration / deceleration analyzer 700 determines the difference between the orbital period derived from monitoring information about space object A at time t1, the orbital period derived from monitoring information about space object A at time t2, and the orbital period of parameter set 0, with the direction of travel of space object A as the X-axis. Time t2 is a time after time t1. Next, the acceleration / deceleration analyzer 700 derives parameter set 1 and parameter set 2 from the calculated difference, deriving ΔV and acceleration in the direction of travel of space object A between epoch t0 and time t1, and deriving ΔV and acceleration in the direction of travel of space object A between time t1 and time t2. Parameter set 2 indicates an estimated orbit information update value, which is an estimated value of the orbit information of space object A at time t2.

[0056] Furthermore, if the interval between epoch t0 and time t1 is short, or if the acceleration / deceleration of space object A is minute, there is a risk of measurement error leading to an incorrect analysis. In these cases, monitoring space object A multiple times has the effect of improving the accuracy of the analysis. Furthermore, according to this operation example, when the acceleration / deceleration amount of the space object A significantly changes from the epoch t0 to the time t2, the changing acceleration / deceleration amount can be detected.

[0057] <Operation Example 5 of this Embodiment> Increasing the number of measurements of space object A reduces measurement errors and enables analysis of space object A with high accuracy. It is also considered reasonable to measure space object A from multiple geometrically dispersed positions. For example, by gathering measurement information from both the perigee and apogee regions of an elliptical orbit, it becomes possible to rationally reduce measurement errors by ground-based monitoring equipment. Furthermore, the characteristics of measurement errors differ: optical monitoring methods have high angle measurement accuracy but large distance measurement errors, while radar monitoring methods have high distance measurement accuracy but large angle measurement errors. Therefore, it is considered reasonable to collect information based on multiple monitoring methods and combine the collected information to improve measurement accuracy. It goes without saying that measurement information from a monitoring device of another business may also be used.

[0058] Therefore, first, the acceleration / deceleration analysis device 700 calculates the difference between the orbital period i derived from the monitoring information of space object A at time ti (i is a natural number greater than or equal to 1 and less than or equal to n, n is a natural number greater than or equal to 3) and the orbital period of parameter set 0, with the direction of travel of space object A as the X-axis. Next, the acceleration / deceleration analyzer 700 derives parameter set i from the calculated difference, and derives ΔV and acceleration in the direction of travel of space object A between time t(i-1) and time ti. Here, parameter set i indicates an estimated orbit information update value, which is an estimated value of the orbit information of space object A at time ti, time t0 is the same as epoch t0, and the larger the value of i, the later the time ti indicates.

[0059] <Operation Example 6 of this Embodiment> When space object A intentionally attempts to approach space object B, it is assumed that it will adjust its orbital inclination to move to a relative position where it can look up or down on space object B from outside the orbital plane. In order to adjust the orbital inclination, it is reasonable to fire the thruster in the direction normal to the orbital plane near the ascending node and descending node, and it is also assumed that the firing direction will be reversed at the ascending node and the descending node. Therefore, in the orbital analysis model of space object A contained within the acceleration / deceleration analysis device 700, a typical analysis parameter setting is input in which Aya1 at the ascending node and Ayd1 at the descending node have equal absolute values ​​and reverse positive and negative signs in the out-of-plane direction, and conditions that fit the difference in orbital inclination angle indicated by parameter set 0 and parameter set 1 are derived. Strictly speaking, the thrust of the propulsion device affects orbital elements other than the orbital inclination, but it is considered reasonable to focus on the orbital inclination as an indicator for determining whether space object A is intentionally performing out-of-plane control.

[0060] Figure 8 is a diagram for explaining the adjustment of the orbital inclination angle, showing a specific example of the orbital inclination change behavior of a low-earth orbit satellite. As shown in Figure 8, if the propulsion device equipped on satellite 30 generates thrust in a direction perpendicular to the orbital plane of satellite 30 at the point (equinox) where satellite 30 crosses the equator of Earth 70, the orbital inclination angle can be effectively fine-tuned.

[0061] Therefore, first, the acceleration / deceleration analysis device 700 calculates the difference between the orbital inclination angle derived from the monitoring information about space object A at time t1 and the orbital inclination angle of parameter set 0, with the direction of travel of space object A as the X-axis and the normal direction of the orbital plane of space object A as the Y-axis. Next, the acceleration / deceleration analysis device 700 derives parameter set 1 from the difference, and derives the acceleration in the out-of-plane direction at the ascending node of space object A and the acceleration in the out-of-plane direction at the descending node of space object A between epoch t0 and time t1.

[0062] <Operation Example 7 of this Embodiment> First, the acceleration / deceleration analysis device 700 calculates the difference between the orbital inclination angle derived from the monitoring information about space object A at time t1, the orbital inclination angle derived from the monitoring information about space object A at time t2, and the orbital inclination angle of parameter set 0, with the direction of travel of space object A as the X-axis and the normal direction of the orbital plane as the Y-axis. Next, the acceleration / deceleration analysis device 700 derives parameter set 1 and parameter set 2 from the calculated difference, derives the out-of-plane acceleration at the ascending node of space object A between epoch t0 and time t1, and the out-of-plane acceleration at the descending node of space object A between time t1 and time t2, and derives the out-of-plane acceleration at the ascending node of space object A between time t1 and time t2. This operation example has the same effect as the operation example 4 of this embodiment.

[0063] <Operation Example 8 of this Embodiment> First, the acceleration / deceleration analysis device 700 calculates the difference between the orbital inclination angle i derived from the monitoring information about space object A at time ti (i is a natural number greater than or equal to 1 and less than or equal to n, n is a natural number greater than or equal to 3) and the orbital inclination angle 0 of parameter set 0, with the direction of travel of space object A as the X-axis and the normal direction of the orbital plane of space object A as the Y-axis. Next, the acceleration / deceleration analysis device 700 derives parameter set i from the calculated difference, and derives the acceleration in the out-of-plane direction at the ascending node of space object A and the acceleration in the out-of-plane direction at the descending node of space object A between time t(i-1) and time ti. This operation example is the same as operation example 5 of this embodiment.

[0064] <Operation Example 9 of this Embodiment> Furthermore, although changes in right ascension of the ascending node were not taken into consideration in operation examples 3 to 8 of this embodiment, the effect of changing the orbital period of the orbital plane of space object A in accordance with acceleration / deceleration in the forward direction and acceleration / deceleration in the out-of-plane direction of space object A causes the right ascension of the ascending node to change. Furthermore, since a change in the orbital period also changes the argument of perigee, in order to perform an analysis with a relatively high degree of accuracy, it is considered appropriate to evaluate changes in all six orbital elements using an orbit analysis model of space object A.

[0065] Therefore, the acceleration / deceleration analysis device 700 uses monitoring information about space object A at time t1, monitoring information about space object A at time t2, and monitoring information about space object A at time tn, with the direction of travel of space object A as the X-axis and the normal direction of the orbital plane of space object A as the Y-axis, and derives parameter set n and the acceleration in the direction of travel of space object A so that the difference between the monitoring information and the orbital information about space object A from time t1 to time tn is minimized, assuming that the acceleration in the direction of travel of space object A is constant.

[0066] For simplicity, assuming that the acceleration is constant, as occurs during rocket launch or orbital descent in the de-orbit process, this operation example enables fitting with little discrepancy in orbit information.

[0067] <Operation Example 10 of this Embodiment> If space object A's acceleration changes over time, and the six orbital elements are evaluated under the condition that the acceleration is fixed as an orbital analysis model for space object A, a large discrepancy in the orbital information will remain between time t1 and time tn. Considering the measurement error of the monitoring device and the analysis error that occurs in the analysis process that derives the six orbital elements from the measured orbital information, it is expected that a considerable amount of variation will occur in the measurement results for space object A. However, if a discrepancy that is clearly larger than the measurement error and analysis error remains, it can be determined that space object A is accelerating.

[0068] Therefore, in operation example 5 of this embodiment, the acceleration / deceleration analysis device 700 further determines that there is acceleration in the direction of travel of space object A when the difference between parameter set 0 and parameter set n, excluding the effects of measurement error and analysis error, is significantly large.

[0069] <Operation Example 11 of this Embodiment> In operation example 5 of this embodiment, furthermore, the acceleration / deceleration analysis device 700 determines that there is acceleration or deceleration in the out-of-plane direction of the space object A when the difference between parameter set 0 and parameter set n, excluding the effects of measurement error and analysis error, is significantly large.

[0070] According to this operation example, if there remains a discrepancy in the out-of-plane direction that is clearly larger than the measurement error and analysis error, the acceleration / deceleration analyzer 700 can determine that the space object A is accelerating.

[0071] <Operation Example 12 of this Embodiment> In any of operation examples 5, 8, and 9 of this embodiment, the acceleration / deceleration analysis device 700 further determines that there is an acceleration / deceleration fluctuation in the direction of travel of the space object A when the difference between the parameter set n and the monitoring information about the space object A from time t1 to time tn, excluding the effects of measurement error and analysis error, is significantly large.

[0072] According to this operation example, it can be determined that space object A is accelerating from epoch t0 to time tn, and furthermore, if there remains a large deviation in the orbital information of space object A when assuming a constant acceleration value for space object A, it can be determined that there is a change in the amount or direction of acceleration of space object A, i.e., there is acceleration or deceleration of space object A. As it is possible to measure changes in the orbital period in the direction of travel of space object A with high accuracy, according to this operation example, it is even possible to evaluate the acceleration / deceleration fluctuations of space object A.

[0073] <Operation Example 13 of this Embodiment> In any of operation examples 5, 8, and 9 of this embodiment, the acceleration / deceleration analysis device 700 further derives the flight position (tn+1, rn+1, θn+1, φn+1) in the Earth-fixed coordinate system as the predicted trajectory S(n+1) of the space object A at time t(n+1), which is later than time tn, based on the derived parameter set n, and thereby tracks and monitors the space object A using the monitoring device at time t(n+1). This operation example corresponds to a tracking and monitoring method.

[0074] <Operation Example 14 of this Embodiment> In any of operation examples 10 to 12 of this embodiment, the acceleration / deceleration analysis device 700 further determines whether or not space object A is accelerating or decelerating, and if there is a space object B that is predicted to approach or collide with space object A, issues an alert to the operator of space object B.

[0075] <Operation Example 15 of this Embodiment> The space situation monitoring business device 47 manages space object information 501. The acceleration / deceleration analysis device 700 includes a first monitoring device 810 flying around a geostationary orbit, a second monitoring device 840 installed on the ground, and a catalog 590 that records orbital information of multiple space objects. The catalog 590 records at least one of the orbital information acquired by the space situation monitoring business device 47, the first orbital information acquired by the first monitoring device, and the second orbital information acquired by the second monitoring device. Specific examples of the orbital information acquired by the space situation monitoring business device 47 include at least one of free public orbital information acquired from public information, paid orbital information purchased by an SSA operator, and orbital information including non-public information obtained through an agreement between operators. In any of operation examples 1 to 9 of this embodiment, the acceleration / deceleration analysis device 700 further derives parameter set n using orbital information acquired by the first monitoring device 810 and the second monitoring device 840 and orbital information acquired by the space situation monitoring business device 47, and registers the derived parameter set n in the catalog 590.

[0076] <Operation Example 16 of this Embodiment> The space situation monitoring business device 47 according to this operation example is the same as the space situation monitoring business device 47 according to the operation example 15 of this embodiment. In any of the operation examples 10 to 12 of this embodiment, the acceleration / deceleration analyzer 700 further derives the parameter set n using the orbit information acquired by the space situation monitoring business device 47. Thereafter, the acceleration / deceleration analysis device 700 performs at least one of the following: suspicious target identification, behavior tracking, behavioral intention analysis, and information transmission to response assets for the space object A using an acceleration / deceleration analysis method shown in any of operation examples 10 to 12 of this embodiment.

[0077] <Operation Example 17 of this Embodiment> The space situation monitoring business device 47 according to this operation example is the same as the space situation monitoring business device 47 according to the operation example 15 of this embodiment. In operation example 13 of this embodiment, the acceleration / deceleration analysis device 700 further generates a parameter set n indicating an estimated orbit information update value, which is an estimated value of the orbit information of space object A at time tn, using the orbit information acquired by the space situation monitoring business device 47. Thereafter, the acceleration / deceleration analyzer 700 tracks and monitors the space object A by the tracking and monitoring method shown in the operation example 13 of this embodiment.

[0078] As described above, according to this embodiment, the versatility of analyzing the acceleration / deceleration of the space object 60 can be improved by using Operation Example 1 or Operation Example 2 or the like.

[0079] ***Other Configurations*** <Variation 1> The functions of the acceleration / deceleration analyzer 700 may be realized by hardware instead of software. FIG. 9 is a diagram showing the configuration of an acceleration / deceleration analyzer 700 according to a modified example of this embodiment. The acceleration / deceleration analyzer 700 includes an electronic circuit 909 in place of a processor 910 , a combination of the processor 910 and a memory 921 , a combination of the processor 910 and an auxiliary storage device 922 , or a combination of the processor 910 , the memory 921 , and the auxiliary storage device 922 . The electronic circuit 909 is a dedicated electronic circuit that realizes the functions of the acceleration / deceleration analyzer 700 . Specifically, the electronic circuit 909 is a single circuit, a composite circuit, a programmed processor, a parallel programmed processor, a logic IC, a GA (Gate Array), an ASIC, or an FPGA. The functions of the acceleration / deceleration analyzer 700 may be realized by one electronic circuit, or may be distributed across multiple electronic circuits. As another modification, some of the functions of the acceleration / deceleration analyzer 700 may be implemented by the electronic circuit 909, and the remaining functions may be implemented by software.

[0080] The processor 910, the electronic circuit 909, the memory 921, and the auxiliary storage device 922 are collectively referred to as a processing circuitry. In other words, the functions of the acceleration / deceleration analyzer 700 are realized by the processing circuitry.

[0081] Embodiment 2 The following mainly describes the differences from the above-described embodiment with reference to the drawings.

[0082] ***Configuration Description*** FIG. 10 is a diagram showing an example of the overall configuration of a satellite monitoring system 500 according to this embodiment. The satellite monitoring system 500 includes a monitoring satellite group 56 that monitors critical infrastructure 55, and a monitoring center 57. The satellite monitoring system 500 may include critical infrastructure 55 in addition to the monitoring satellite group 56 and the monitoring center 57. The monitoring satellite 521 is also called a monitoring satellite or a monitoring device.

[0083] Critical Infrastructure 55 is infrastructure in outer space. Specifically, Critical Infrastructure 55 is formed by a constellation of satellites that make up social infrastructure, such as the exchange of information with distant or remote areas via communication satellites, weather forecasts using images from the Himawari meteorological satellite, or the utilization of geospatial information from quasi-zenith positioning satellites. Furthermore, the satellites that make up the critical infrastructure 55 are called infrastructure satellites 551. Furthermore, infrastructure-specific ground facilities 58 corresponding to the critical infrastructure 55 are installed on the ground.

[0084] The monitoring satellite group 56 is made up of monitoring satellites 521 that monitor infrastructure satellites 551 that make up the critical infrastructure 55 . The monitoring center 57 is installed on the ground and exchanges information with the monitoring satellites 521 of the monitoring satellite group 56 . The monitoring satellite 521 of the monitoring satellite group 56 and the monitoring center 57 exchange information via a communication device provided in the infrastructure satellite 551 .

[0085] The group of satellites that make up the critical infrastructure 55 includes infrastructure satellites 551 that are equipped with communication devices that communicate with the monitoring center 57 . The infrastructure satellites 551 include all or some of the communications satellite 401, data relay satellite 402, meteorological satellite 403, observation satellite 404, first observation and monitoring satellite 405, positioning satellite 406, second observation and monitoring satellite 407, space station 408, lunar and planetary exploration satellite 409, exploration satellite 410, and transport vehicle 411. The exploration satellite 410 is an exploration satellite that explores planets or resources other than the moon. The first observation and monitoring satellite 405 is also called an early warning satellite, and is a satellite that is deployed in a high orbit such as a geostationary orbit or a Molniya orbit, and performs wide-area observation or monitoring of the Earth. The second observation and monitoring satellite 407 is also called an information gathering satellite, and is, for example, an observation or monitoring satellite for collecting various image information of large-scale disasters or other important matters. Furthermore, ground facilities 701 are installed on the ground for each piece of infrastructure corresponding to the critical infrastructure 55 .

[0086] Due to factors such as debris collisions caused by the increasing number of objects in the space environment, hazardous events that carry the risk of failure or loss of critical infrastructure55 are on the rise. Therefore, a system is needed to monitor critical infrastructure55 and take action to avoid danger if necessary.

[0087] The monitoring satellite group 56 includes an infrastructure satellite 551 equipped with a communication device for communicating with a monitoring center 57 as a monitoring satellite 521 . The monitoring satellites 521 include all or some of the optical monitoring satellites 421, radio wave monitoring satellites 423, infrared monitoring satellites 422, servicing satellites 424, and debris removal satellites 425. The optical monitoring satellites 421 monitor the infrastructure satellites 551 using optical systems. The radio wave monitoring satellites 423 monitor the infrastructure satellites 551 using radio waves. The infrared monitoring satellites 422 monitor the infrastructure satellites 551 using infrared detection. The servicing satellites 424 provide on-orbit servicing to the infrastructure satellites 551. The debris removal satellites 425 remove debris.

[0088] On-orbit servicing may include all or some of the following: capture, inspection, repair, refueling, transfer, active debris removal (ADR), and laser illumination.

[0089] The monitoring services provided by a monitoring satellite constellation 56 can be easily understood by analogy with the roles of eyes, ears, hands, and mouths. To achieve the objective of visually monitoring critical infrastructure 55 using satellites, it is effective to visually monitor suspicious objects such as debris using optical telescopes or radar images. Another effective method is to monitor abnormal temperature environments using infrared detection.

[0090] Additionally, a monitoring service that uses ears to monitor the environment has the objective of monitoring radio waves in outer space, where sound waves do not propagate. To achieve the objective of monitoring critical infrastructure55 using ears to monitor the environment, it is effective to receive radio waves flying around the area and monitor the radio wave conditions that could cause malfunctions.

[0091] Additionally, as an extension of the monitoring service, there is on-orbit service, which is analogous to the role of manual operation. On-orbit services include capturing, inspecting, and repairing malfunctioning satellites. Other services include refueling satellites that are running low on fuel, mobile services to move service locations, and active orbit deorbit (ADR) for satellites that cannot deorbit on their own after completing their lifespan. Another service is the use of lasers to monitor the distance to suspicious objects such as debris.

[0092] In this way, it is expected that the monitoring satellite 521 will fulfill the role of eyes, ears, or hands. However, the role of the mouth, that is, the means of communication for transmitting the monitoring information 560, is limited, and some ingenuity is required.

[0093] In this embodiment, an infrastructure satellite 551 is used as the monitoring satellite 521 that serves as the port, that is, the monitoring satellite 521 that transmits the monitoring information 560. The monitoring satellites 521 include infrastructure satellites 551 that act as a mouth. The infrastructure satellites 551 also include a monitoring satellite 521 that acts as a mouth. In other words, the satellite monitoring system 500 includes satellites that are both monitoring satellites 521 and infrastructure satellites 551. Here, such satellites have been described as infrastructure satellites 551 that mainly act as a mouth, but they may also be satellites that act as eyes, ears, and hands.

[0094] 10, the monitoring satellites 521 that perform long-distance communication include a communication satellite 401 and a data relay satellite 402 in a first satellite group 601. Also included are a communication satellite 401 in a second satellite group 602. Also included are a lunar and planetary exploration satellite 409 in a third satellite group 603. The monitoring satellites 521 that perform short-distance communication include the meteorological satellites 403, the positioning satellites 406, and the observation satellites 404 in the first satellite group 601.

[0095] As shown in FIG. 10, the satellite monitoring system 500 includes a first satellite group 601, a second satellite group 602, a third satellite group 603, and a monitoring center 57. The first constellation of satellites 601 is in geostationary Earth orbit (GEO). It consists of a group of satellites flying near the Quasi-Zenith Orbit (QZO) or the equator-zenith orbit (QZN). The second satellite group 602 is made up of satellites flying in the vicinity of a medium earth orbit (MEO) or a low earth orbit (LEO). The third satellite group 603 is made up of satellites flying in cislunar space, which is the space between the moon and the earth, or beyond the moon.

[0096] FIG. 11 shows an example of the configuration of a monitoring center 57 according to this embodiment. The monitoring center 57 is also referred to as ground equipment 701 installed on the ground. Here, the description will be given assuming that the monitoring center 57 is installed in the ground equipment 701.

[0097] The storage unit 720 stores the monitoring information 560.

[0098] The ground equipment 701 exchanges monitoring information 560 with the monitoring satellite 521 via the infrastructure satellite 551. The monitoring management unit 710 uses the monitoring information 560 exchanged with the monitoring satellite 521 to realize a function to deal with the risk of failure or loss of the critical infrastructure 55. For example, the monitoring management unit 710 realizes functions such as warning of danger, preventing danger, or avoiding danger in the critical infrastructure 55.

[0099] ***Explanation of Operation*** The operation procedure of the satellite monitoring system 500 corresponds to a satellite monitoring method, and the program that realizes the operation of the satellite monitoring system 500 corresponds to a satellite monitoring program. First, the communication method of the satellite monitoring system 500 will be explained, and then the characteristic operation of the satellite monitoring system 500 according to this embodiment will be explained.

[0100] <First communication method of first satellite group 601> FIG. 12 is a diagram showing a first communication method in a first satellite group 601 according to this embodiment. The satellite monitoring system 500 includes a first satellite group 601 made up of satellites flying near a geostationary orbit (GEO) or a quasi-zenith orbit (QZO). The first satellite group 601 includes a monitoring satellite 521 and an infrastructure satellite 551, which is a communication satellite 401 or a data relay satellite 402, and which has a communication environment with the ground. The watching satellite 521 exchanges watching information 560 with the communication satellite 401 or the data relay satellite 402 when passing through the communication range of the communication satellite 401 or the data relay satellite 402 . Then, the communication satellite 401 or the data relay satellite 402 exchanges the monitoring information 560 with the monitoring center 57 .

[0101] Figure 12 shows a first communication method, which is a method of exchanging information between a monitoring satellite 521 and a monitoring center 57 in a first satellite group 601 consisting of a group of satellites flying near a geostationary orbit (GEO) or a quasi-zenith orbit (QZO). The communication satellite 401 and the data relay satellite 402 are provided with a communication environment with the ground as critical infrastructure 55 .

[0102] 12, a monitoring satellite 521a acting as eyes and a monitoring satellite 521b acting as ears exchange monitoring information 560 with a communication satellite 401 or a data relay satellite 402 when passing near the satellite. Then, the communication satellite 401 or the data relay satellite 402 exchanges monitoring information 560 with a monitoring center 57.

[0103] <Second communication method of the first satellite group 601> FIG. 13 is a diagram showing the second communication method in the first satellite group 601 according to this embodiment. The first satellite group 601 includes a meteorological satellite 403, a positioning satellite 406, or an observation satellite 404, which are infrastructure satellites 551. A communication environment is established for the meteorological satellite 403, the positioning satellite 406, or the observation satellite 404, which are infrastructure satellites 551, to communicate with the communication satellite 401 or the data relay satellite 402. When passing through the communication range of the meteorological satellite 403 , the positioning satellite 406 , or the observation satellite 404 , the watching satellite 521 exchanges watching information 560 with the meteorological satellite 403 , the positioning satellite 406 , or the observation satellite 404 . The meteorological satellite 403, positioning satellite 406, or observation satellite 404 exchanges the monitoring information 560 with the communication satellite 401 or data relay satellite 402. The communication satellite 401 or data relay satellite 402 exchanges the monitoring information 560 with the monitoring center 57.

[0104] FIG. 13 shows a second communication method, which is a method of exchanging information between the monitoring satellite 521 and the monitoring center 57 in the first satellite group 601. A communication environment for communication with a communication satellite 401 or a data relay satellite 402 is established for a meteorological satellite 403, a positioning satellite 406, or an observation satellite 404 that constitutes the critical infrastructure 55.

[0105] 13, a monitoring satellite 521a that acts as eyes, a monitoring satellite 521b that acts as ears, and a monitoring satellite 521c that acts as hands exchange monitoring information 560 with a meteorological satellite 403, a positioning satellite 406, or an observation satellite 404 as they pass near these satellites. Then, the meteorological satellite 403, the positioning satellite 406, or the observation satellite 404 exchanges monitoring information 560 with a communication satellite 401 or a data relay satellite 402 via a communication environment. Then, the communication satellite 401 or the data relay satellite 402 exchanges monitoring information 560 with a monitoring center 57.

[0106] <First communication method of the second satellite group 602> FIG. 14 is a diagram showing the first communication method in the second satellite group 602 according to this embodiment. The satellite monitoring system 500 is composed of a group of satellites flying near a medium earth orbit (MEO) or a low earth orbit (LEO). The second satellite group 602 includes a monitoring satellite 521 and a communication satellite 401 that is an infrastructure satellite 551 and has a communication environment with the ground. When the watching satellite 521 passes through the communication range of the communication satellite 401, the watching satellite 521 exchanges watching information 560 with the communication satellite 401. Then, the communication satellite 401 exchanges watching information 560 with the watching center 57.

[0107] Figure 14 shows a first communication method for the second satellite group 602, which is a method of exchanging information between a monitoring satellite 521 and a monitoring center 57 in the second satellite group 602, which is composed of a group of satellites flying near the medium Earth orbit (MEO) or the low Earth orbit (LEO). The communications satellite 401, which is an infrastructure satellite 551, has a communications environment with the ground.

[0108] 14, when a monitoring satellite 521b acting as an ear passes near a communication satellite 401, which is a monitoring satellite acting as a mouth and also an infrastructure satellite 551, it exchanges monitoring information 560 with the communication satellite 401. Then, the communication satellite 401 exchanges monitoring information 560 with a monitoring center 57.

[0109] <Second communication method of second satellite group 602> FIG. 15 is a diagram showing a second communication method in the second satellite group 602 according to this embodiment. The second satellite group 602 includes a plurality of communication satellites 401 that are in a communication environment where they can communicate with each other. When the monitoring satellite 521 passes through a range where it can communicate with one of the multiple communication satellites 401, it exchanges monitoring information 560 with that communication satellite 401. The communication satellite 401 that has received the monitoring information 560 then receives and sends the monitoring information 560 to and from other communication satellites among the plurality of communication satellites. Other communication satellites exchange monitoring information 560 with the monitoring center 57 .

[0110] FIG. 15 shows a second communication method of the second satellite group 602, which is a method of exchanging information between the monitoring satellite 521 and the monitoring center 57 in the second satellite group 602. The communications satellite 401, which is an infrastructure satellite 551, has a communications environment established with the ground, and also has a communications environment established for multiple communications satellites to communicate with each other.

[0111] 15, a monitoring satellite 521a that acts as an eye, a monitoring satellite 521b that acts as an ear, and a monitoring satellite 521c that acts as a hand pass near a communication satellite 401 that acts as a monitoring satellite that acts as a mouth and is also an infrastructure satellite 551. At that time, they exchange monitoring information 560 with the communication satellite 401. Then, the communication satellite 401 exchanges the monitoring information 560 with another communication satellite via the communication environment. Then, the communication satellite 401 that has exchanged the monitoring information 560 exchanges the monitoring information 560 with a watching center 57.

[0112] <First communication method of the third satellite group 603> FIG. 16 is a diagram showing the first communication method in the third satellite group 603 according to this embodiment. The satellite monitoring system 500 is configured with a third satellite group 603, which is made up of satellites flying in cislunar space, which is the space between the moon and the earth, or beyond the moon. The third satellite group 603 includes a monitoring satellite 521 and a lunar and planetary exploration satellite 409 which is an infrastructure satellite 551 and has a communication environment with the ground. When the watching satellite 521 passes through the communication range of the lunar and planetary exploration satellite 409, the watching satellite 521 exchanges watching information 560 with the lunar and planetary exploration satellite 409. Then, the lunar and planetary exploration satellite 409 exchanges watching information 560 with the watching center 57.

[0113] FIG. 16 shows a first communication method of the third satellite group 603, which is a method of exchanging information between the monitoring satellite 521 and the monitoring center 57 in the third satellite group 603. The lunar and planetary exploration satellite 409 is an infrastructure satellite 551, and has a communication environment with the ground. The lunar and planetary exploration satellite 409 is an infrastructure satellite 551, and also a monitoring satellite that plays the role of a mouth.

[0114] 16, when a watching satellite 521a, which acts as an eye, passes near the lunar and planetary exploration satellite 409, it exchanges watching information 560 with the lunar and planetary exploration satellite 409. Then, the lunar and planetary exploration satellite 409 exchanges watching information 560 with the watching center 57.

[0115] <Second communication method of the third satellite group 603> FIG. 17 is a diagram showing the second communication method in the third satellite group 603 according to this embodiment. The satellite monitoring system 500 is configured with a third satellite group 603, which is made up of satellites flying in cislunar space, which is the space between the moon and the earth, or beyond the moon. The third satellite group 603 includes a monitoring satellite 521 and a lunar and planetary exploration satellite 409 which is an infrastructure satellite 551 and has a communication environment with the ground. When the monitoring satellite 521 passes through the communication range of the lunar and planetary exploration satellite 409, it exchanges monitoring information 560 with the gateway 412 operating in cislunar space. The gateway 412 exchanges monitoring information 560 with the monitoring center 57 .

[0116] Specifically, the gateway 412 is a gateway constructed through international cooperation, such as a space station near the moon, and has communication links for communicating with ground facilities. The gateway 412 is an infrastructure satellite 551 and also one of the monitoring satellites that plays the role of a mouth.

[0117] FIG. 17 shows a second communication method of the third satellite group 603, which is a method of exchanging information between the monitoring satellite 521 and the monitoring center 57 in the third satellite group 603. When a watching satellite 521a, which acts as an eye, passes near the lunar and planetary exploration satellite 409, it exchanges watching information 560 with the gateway 412. Then, the gateway 412 exchanges watching information 560 with the watching center 57.

[0118] <Third communication method of the third satellite group 603> FIG. 18 is a diagram showing a third communication method in a third satellite group 603 according to this embodiment. The satellite monitoring system 500 is configured with a third satellite group 603, which is made up of satellites flying in cislunar space, which is the space between the moon and the earth, or beyond the moon. The third satellite group 603 includes a monitoring satellite 521 and a lunar and planetary exploration satellite 409 which is an infrastructure satellite 551 and has a communication environment with the ground. When the monitoring satellite 521 passes through the communication range of the lunar and planetary exploration satellite 409, it exchanges monitoring information 560 with a gateway operating in cislunar space. The gateway 412 exchanges monitoring information 560 with the monitoring center 57 via the gateway ground equipment 59 installed on the ground.

[0119] FIG. 18 shows a third communication method of the third satellite group 603, which is a method of exchanging information between the monitoring satellite 521 and the monitoring center 57 in the third satellite group 603. When a monitoring satellite 521a, which acts as an eye, passes near the lunar and planetary exploration satellite 409, it exchanges monitoring information 560 with a gateway 412. Then, the gateway 412 exchanges the monitoring information 560 with a monitoring center 57 via a gateway ground facility 59 installed on the ground. The gateway ground facility 59 is an example of the infrastructure ground facility 58.

[0120] <Operation Example 1 of this Embodiment> The satellite monitoring system 500 determines whether or not the space object A is accelerating or decelerating using the acceleration / deceleration analysis method shown in any of operation examples 10 to 12 of embodiment 1, and if an impact on the critical infrastructure 55 is predicted, issues an alert to the operator of the critical infrastructure 55.

[0121] <Operation Example 2 of this Embodiment> The satellite monitoring system 500 tracks and monitors the space object A by the tracking and monitoring method described in the seventeenth operational example of the first embodiment.

[0122] Embodiment 3 The following mainly describes the differences from the above-described embodiment with reference to the drawings.

[0123] ***Configuration Description*** 19 shows an example of the configuration of a collision avoidance support system 510 according to this embodiment. The space situation monitoring business device 47 includes a collision avoidance support device 100 instead of an acceleration / deceleration analyzer 700. However, the collision avoidance support device 100 analyzes the acceleration / deceleration of the space object A in the same way as the acceleration / deceleration analyzer 700. The collision avoidance assistance system 510 is basically the same as the collision avoidance assistance system disclosed in Patent Document 1. In other words, this embodiment corresponds to a technology that appropriately extends the technology disclosed in Patent Document 1. The collision avoidance assistance system 510 acquires space object information from a space information recorder 50 that records space object information acquired from a management business device used by a management business operator that manages multiple space objects, and assists in avoiding collisions between the multiple space objects. The collision avoidance assistance device 100 assists in avoiding collisions between multiple space objects flying in space.

[0124] The functions of the recorder processing unit 110, the warning control unit 120, the performance presentation unit 130, the avoidance determination unit 150, and the machine learning unit 160 are each realized by software.

[0125] The recorder processing unit 110 acquires the flight performance information 492 and, based on the acquired flight performance information 492, sets the actual epoch 522 of the orbit of each of the multiple space objects, actual orbital elements 523 that identify the orbit, and actual position coordinates 242 of each of the multiple space objects as orbit performance information 54. The recorder processing unit 110 then includes the set orbit performance information 54 in the space information recorder 50. The flight performance information 492 represents the flight performance of each of the multiple space objects. The actual epoch 522 is the actual epoch of the orbit of each of the multiple space objects. The actual orbital elements 523 are orbital elements that identify the orbit of each of the multiple space objects. The actual orbital elements 523 are the actual orbital elements of the orbit of each of the multiple space objects.

[0126] The alarm control unit 120 controls the alarm when an object predicted to collide or approach is present. Based on the orbit forecast information, the alarm control unit 120 determines whether or not multiple space objects that are in a dangerous positional relationship at the same time exist as predicted hazardous objects 65 among the multiple space objects, and if it determines that the predicted hazardous objects 65 exist, it outputs a danger alarm 25 indicating the presence of the predicted hazardous objects 65. The predicted hazardous objects 65 are multiple space objects that are in a dangerous positional relationship at the same time among the multiple space objects.

[0127] When any of the multiple space objects collide with each other, the performance presentation unit 130 extracts the orbit performance information 54 at the time the space objects collided from the orbit performance information 54 as the collision performance 131, and presents the extracted collision performance 131 on an output device.

[0128] When the danger alert 25 is output, the avoidance determination unit 150 determines an avoidable space object 69, which is a space object for which avoidance operations are to be performed, from among the space objects included in the predicted hazard objects 65. The avoidance determination unit 150 may determine the avoidable space object 69 based on whether each space object included in the predicted hazard objects 65 is a rocket at launch. The avoidance determination unit 150 may determine the avoidable space object 69 based on whether each space object included in the predicted hazard objects 65 belongs to a megaconstellation. The avoidance determination unit 150 may determine the avoidable space object 69 based on whether each space object included in the predicted hazard objects 65 is in a steady operation state or an unsteady operation state. The avoidance determination unit 150 may determine the avoidable space object 69 based on whether each space object included in the predicted hazard objects 65 is an orbital transfer satellite currently undergoing orbital transfer. The avoidance determination unit 150 may determine the avoidable space object 69 based on whether each space object included in the predicted hazard objects 65 has a collision avoidance function. The avoidance determination unit 150 may determine the avoided space object 69 based on whether each space object included in the anticipated danger object 65 is located in a dense orbit. The avoidance determination unit 150 may output an avoided object notification 151 notifying the avoided space object 69.

[0129] The machine learning unit 160 updates the algorithm of the avoidance determination process that determines the space object 69 to be avoided by machine learning using the result of determining the space object 69 to be avoided, i.e., the result of determining the space object 69 to be avoided by the avoidance determination unit 150. The space object 69 to be avoided is a space object that is included in the predicted danger objects 65 and that is to undergo avoidance operations.

[0130] The space information recorder 50 includes orbit forecast information 51 and orbit performance information 54 in which orbit performance values ​​are set. The memory unit 720 stores the space information recorder 50. The collision avoidance assistance device 100 acquires flight forecast information 491 from a management business device 40 used by a management business that manages space objects, and based on the acquired flight forecast information 491, sets the forecast origin of the orbit of each of multiple space objects, the forecast orbit elements that specify the orbit, and the forecast error predicted in the orbit as orbit forecast information, and is equipped with a space information recorder 50 that includes the orbit forecast information. The flight forecast information 491 represents a forecast of the flight of each of the multiple space objects. Orbit forecast information 51 is a forecast value of the time and orbit of a plurality of space objects.

[0131] The collision avoidance assistance system 510 may include a database that stores space object information, and a server that includes an avoidance operator determination means that determines a collision avoidance operator that will carry out collision avoidance. The server implements the following steps: receiving notification from the space information recorder that a collision between space object A and space object B, which are included in multiple space objects, has been predicted; acquiring from the space information recorder 50 the estimated time or time period when the collision is predicted, orbital forecast information for space object A, and orbital forecast information for space object B; issuing a danger alert, such as a collision alert or proximity alert, for the estimated time or time period to all or some of the operators of space object A, the operators of space object B, and the debris removal operator; selecting a collision avoidance operator; and requesting collision avoidance action from the selected collision avoidance operator. The server may also implement the step of issuing a danger alert, such as a collision alert or proximity alert, to a space insurance operator that applies an insurance payment system that assesses accident liability and insurance claims based on the difference between the orbital forecast information and the orbital performance information. Note that having each step in the server is equivalent to the server implementing each step. The collision avoidance support system 510 issues an alert to the management company of space object B when it predicts a risk of approach or collision between space object A and space object B, taking into account the future acceleration / deceleration of space object A. The space object information may include information indicating whether or not the space object has a collision avoidance function. The space object information may also include a history of past space collision accidents. The avoidance operator determination means may select a management operator that manages the space object that has the collision avoidance function as the collision avoidance operator when either space object A or space object B has the collision avoidance function. When both space object A and space object B have the collision avoidance function, the avoidance operator determination means may select a collision avoidance operator using an evaluation index of whether the space object is a routinely operated object or a non-routine space object. When both space object A and space object B have the collision avoidance function, the avoidance operator determination means may select a collision avoidance operator using an evaluation index of whether the space object is a megaconstellation satellite. When neither space object A nor space object B has the collision avoidance function, the avoidance operator determination means may select a debris removal operator as the collision avoidance operator. The avoidance operator determination means may select a collision avoidance operator by adding an evaluation index in the process of determining collision avoidance operators in past space collision accidents to the evaluation index for selection.

[0132] The management business equipment 40 includes a megaconstellation business equipment 41, a LEO constellation business equipment 42, a satellite business equipment 43, an orbital transfer business equipment 44, a debris collection business equipment 45, and a rocket launch business equipment 46. The management business equipment 40 may also include a space situation monitoring business equipment 47.

[0133] The database may acquire from the space information recorder the scheduled launch time and launch forecast information of the space object C acquired from the rocket launch operator by the space information recorder. The server may implement a step of reporting launch forecast information for the scheduled launch time information to a mega-constellation operator that manages a mega-constellation satellite with which space object C is at risk of collision, a step in which the avoidance operator determination means requests the mega-constellation operator to take collision avoidance action or request the provision of information necessary for collision avoidance during a rocket launch, and a step of reporting space object information of the mega-constellation satellite with which space object C is at risk of collision to the rocket launch operator.The server may also implement a step of reporting the launch forecast information to a space insurance operator that operates an insurance payment system that can be contracted when a collision risk during a rocket launch is predicted.The server may also implement a step of providing launch time information that can ensure flight safety during a rocket launch. The collision avoidance assistance system 510 may issue an alert to the management company of space object B when it predicts a risk of approach or collision between space object A and space object B, taking into account the future acceleration / deceleration of space object A.

[0134] The database acquires from the space information recorder 50 the scheduled time of orbital transfer of the space object D and transfer forecast information, which are acquired by the space information recorder 50 from the orbital transfer satellite operator. The server implements a step of reporting transfer forecast information at the scheduled time of orbital transfer to a mega constellation operator that manages a mega constellation satellite with which space object D is at risk of collision, a step in which the avoidance operator determination means requests the mega constellation operator to take collision avoidance action or to provide information necessary for collision avoidance during orbital transfer, and a step of reporting space object information of the mega constellation satellite with which space object D is at risk of collision to the orbital transfer satellite operator.The server may also have a step of reporting the transfer forecast information to a space insurance operator that operates an insurance payment system that can be contracted when a collision risk during orbital transfer is predicted.The server may also implement a step of providing transfer forecast information that can ensure flight safety during orbital transfer. The collision avoidance assistance system 510 may issue an alert to the management company of space object B when it predicts a risk of approach or collision between space object A and space object B, taking into account the future acceleration / deceleration of space object A.

[0135] The database may obtain from the space information recorder the scheduled de-orbit time and de-orbit forecast information for space object E obtained from the satellite operator performing the de-orbit using the space information recorder or the debris collection operator. The server may implement a step of reporting deorbit forecast information at the scheduled deorbit time to a mega constellation operator that manages a mega constellation satellite with which space object E is at risk of collision, a step in which the avoidance operator determination means requests the mega constellation operator to take collision avoidance action or request the provision of information necessary for collision avoidance during deorbit, and a step of reporting space object information of the mega constellation satellite with which space object E is at risk of collision to the deorbiting satellite operator or a debris collection operator.The server may also implement a step of reporting the deorbit forecast information to a space insurance operator that operates an insurance payment system that can be contracted when a collision risk during space object deorbit is predicted.The server may also implement a step of providing deorbit forecast information that can ensure flight safety during deorbit. The collision avoidance assistance system 510 may issue an alert to the management company of space object B when it predicts a risk of approach or collision between space object A and space object B, taking into account the future acceleration / deceleration of space object A.

[0136] ***Explanation of Operation*** The operation procedure of the collision avoidance assistance device 100 corresponds to a collision avoidance assistance method, and the program that realizes the operation of the collision avoidance assistance device 100 corresponds to a collision avoidance assistance program. <Operation Example 1 of this Embodiment> First, the space situation monitoring business device 47 measures space object A, whose orbital elements are unknown and consist of an epoch and six orbital elements based on Kepler's laws, multiple times using a monitoring device to calculate initial estimates of the orbital elements of space object A. Next, the space situation monitoring business equipment 47 acquires orbital information of space object A four or more times and calculates updated estimates of the orbital elements of space object A. Next, the space situation monitoring business device 47 determines that there is an acceleration or deceleration effect of space object A when there is a significant variation in the updated estimated value that exceeds the effects of measurement error and estimation error and that varies from the initial estimated value.

[0137] <Operation Example 2 of this Embodiment> In operation example 1 of this embodiment, the space situation monitoring business device 47 further generates orbit prediction information for the space object A after accelerating or decelerating after determining that the space object A is accelerating or decelerating, points the monitoring device using the generated orbit prediction information to measure the space object A, and tracks and monitors the space object A using the results of measuring the space object A.

[0138] <Operation Example 3 of this Embodiment> In operation example 1 or 2 of this embodiment, the space situation monitoring business device 47 further issues an alert to the management company of space object B when it predicts a risk of approach or collision between space object A and space object B, taking into account the future acceleration and deceleration of space object A.

[0139] <Operation Example 4 of this Embodiment> The collision avoidance assistance device 100 issues an alert to the management company of space object B when it predicts a risk of approach or collision between space object A and space object B, taking into account the future acceleration / deceleration of space object A.

[0140] <Operation Example 5 of this Embodiment> The collision avoidance assistance device 100 executes a danger warning output process that outputs a danger warning 25 to an insurance company of a space insurance program that pays insurance money from insurance premiums collected in advance in the event of a collision between space objects A and B among multiple space objects, and to a space object management company that manages at least one of the multiple space objects.

[0141] <Operation Example 6 of this Embodiment> In operation example 4 of this embodiment, the collision avoidance assistance device 100 further executes a danger warning output process for identifying the presence of a potential hazardous object 65 based on the orbit forecast information and outputting a danger warning 25 before a collision occurs between the multiple space objects. In the danger warning output process, the collision avoidance assistance device 100 determines whether or not the potential hazardous object 65 exists based on the orbit forecast information 51 provided by the space information recorder 50, and outputs a danger warning if it is determined that the potential hazardous object 65 exists.

[0142] <Operation Example 7 of this Embodiment> In operation example 4 of this embodiment, when a danger alarm 25 is output, the collision avoidance assistance device 100 further executes a space object to be avoided determination process to determine a space object to be avoided 69. In the space object to be avoided determination process, the collision avoidance assistance device 100 determines a space object to be avoided from among the space objects included in the predicted danger objects 65, for which avoidance operations should be performed, based on the orbit forecast information 51 provided by the space information recorder 50.

[0143] ***Other embodiments*** The above-described embodiments may be freely combined, or any of the components in each embodiment may be modified, or any of the components in each embodiment may be omitted. Furthermore, the embodiments are not limited to those described in the first to third embodiments, and various modifications are possible as necessary. The procedures described in the operation examples and the like may be modified as appropriate. [Explanation of symbols]

[0144] 25 Danger warning, 30 Satellite, 32 Satellite communication equipment, 33, 122, 114, 204 Propulsion equipment, 34, 115, 205 Attitude control device, 35, 123, 116, 206 Power supply unit, 121, 113, 203 Communication equipment, 100 Collision avoidance support device, 110 Recorder processing unit, 111, 201 Observation equipment, 112, 202, 310 Satellite control device, 117, 124 Camera, 120 Alarm control unit, 121E First directional antenna, 121N Omnidirectional antenna, 121W Second directional antenna, 130 Performance presentation unit, 131 Collision performance, 150 Avoidance decision unit, 151 Avoided object notification, 160 Machine learning unit, 242 Actual position coordinates, 40 Management business equipment, 41 Megaconstellation business equipment, 42 LEO constellation business equipment, 43 Satellite business equipment, 44 Orbital transfer business equipment, 45 Debris collection business equipment, 46 Rocket launch business equipment, 47 Space situation monitoring business equipment, 401 Communications satellite, 402 Data relay satellite, 403 Meteorological satellite, 404 Observation satellite, 405 First observation and monitoring satellite, 406 Positioning satellite, 407 Second observation and monitoring satellite, 408 Space station, 409 Lunar and planetary exploration satellite, 410 Exploration satellite, 411 Transport vehicle, 412 Gateway, 421 Optical monitoring satellite, 422 Infrared monitoring satellite, 423 Radio wave monitoring satellite, 424 Service satellite, 425 Debris removal satellite, 491 Flight forecast information, 492 Flight performance information, 50 Space information recorder, 51 Orbit forecast information, 52 Satellite orbit forecast information, 53 Debris orbit forecast information, 54 Orbit performance information, 55 Critical infrastructure, 56 Monitoring satellite constellation, 57 Monitoring center, 58 Ground equipment per infrastructure, 59 Gateway ground equipment, 500 Satellite monitoring system, 501 Space object information, 510 Collision avoidance support system, 511 Space object ID, 512 Forecast origin, 513 Forecast orbital elements, 514 Forecast error, 521, 521a, 521b,521c Monitoring satellite, 522 Actual epoch, 523 Actual orbital elements, 551 Infrastructure satellite, 560 Monitoring information, 590 Catalog, 60 Space object, 65 Predicted danger object, 69 Avoided space object, 601 First satellite group, 602 Second satellite group, 603 Third satellite group, 70 Earth, 700 Acceleration / deceleration analysis device, 701 Ground equipment, 710 Monitoring management unit, 711 Command, 712 Monitoring data, 720 Memory unit, 810 First monitoring device, 811 Communication satellite, 812, 813 Observation satellite, 840 Second monitoring device, 909 Electronic circuit, 910 Processor, 911 Analysis control unit, 921 Memory, 922 Auxiliary storage device, 930 Input interface, 940 Output interface, 941 Display device, 950 Communication device.

Claims

1. An acceleration / deceleration analysis device is provided in a space situation monitoring business device that monitors a space object using a monitoring device, and analyzes the orbit of the space object to analyze whether or not the space object is accelerating or decelerating, When the monitoring device discovers a space object A whose orbital information is unknown and is composed of an epoch t0 and six orbital elements based on Kepler's laws, the acceleration / deceleration analysis device acquires monitoring information of the monitoring device about the space object A three or more times as a parameter set 0 indicating an estimated orbital information initial value, which is an estimated value of the orbital information of the space object A at the epoch t0, and derives the six orbital elements at the epoch t0, The direction of travel of the space object A is defined as the X axis, and the normal direction of the orbital plane of the space object A is defined as the Y axis. From the difference between the orbital inclination angle derived from monitoring information about the space object A at time t1, which is a time after the epoch t0, and the orbital inclination angle of the parameter set 0, deriving a parameter set 1 indicating an estimated orbit information update value, which is an estimate of orbit information of the space object A at the time t1; An acceleration / deceleration analysis device that derives the acceleration in the out-of-plane direction at the ascending node of the space object A and the acceleration in the out-of-plane direction at the descending node of the space object A between the epoch t0 and the time t1.

2. An acceleration / deceleration analysis device is provided in a space situation monitoring business device that monitors a space object using a monitoring device, and analyzes the orbit of the space object to analyze whether or not the space object is accelerating or decelerating, When the monitoring device discovers a space object A whose orbital information is unknown and is composed of an epoch t0 and six orbital elements based on Kepler's laws, the acceleration / deceleration analysis device acquires monitoring information of the monitoring device about the space object A three or more times as a parameter set 0 indicating an estimated orbital information initial value, which is an estimated value of the orbital information of the space object A at the epoch t0, and derives the six orbital elements at the epoch t0, The direction of travel of the space object A is defined as the X axis, and the normal direction of the orbital plane is defined as the Y axis. From the difference between the orbital inclination angle derived from the monitoring information about the space object A at time t1, which is a time after the epoch t0, the orbital inclination angle derived from the monitoring information about the space object A at time t2, which is a time after the time t1, and the orbital inclination angle of the parameter set 0, deriving a parameter set 1 indicating an estimated orbit information update value, which is an estimate of the orbit information of the space object A at the time t1, and a parameter set 2 indicating an estimated orbit information update value, which is an estimate of the orbit information of the space object A at the time t2; Deriving an out-of-plane acceleration at the ascending node of the space object A and an out-of-plane acceleration at the descending node of the space object A between the epoch t0 and the time t1; An acceleration / deceleration analysis device that derives the acceleration in the out-of-plane direction at the ascending node of the space object A and the acceleration in the out-of-plane direction at the descending node of the space object A between the time t1 and the time t2.

3. An acceleration / deceleration analysis device is provided in a space situation monitoring business device that monitors a space object using a monitoring device, and analyzes the orbit of the space object to analyze whether or not the space object is accelerating or decelerating, When the monitoring device discovers a space object A whose orbital information is unknown and is composed of an epoch t0 and six orbital elements based on Kepler's laws, the acceleration / deceleration analysis device acquires monitoring information of the monitoring device about the space object A three or more times as a parameter set 0 indicating an estimated orbital information initial value, which is an estimated value of the orbital information of the space object A at the epoch t0, and derives the six orbital elements at the epoch t0, The direction of travel of the space object A is defined as the X axis, and the normal direction of the orbital plane of the space object A is defined as the Y axis. From the difference between the orbital inclination angle i derived from the monitoring information about the space object A at time ti (i is a natural number between 1 and n, and n is a natural number greater than or equal to 3) and the orbital inclination angle 0 of the parameter set 0, deriving a parameter set i indicating an estimated orbit information update value, which is an estimate of orbit information of the space object A at time ti; Derive the acceleration of the space object A in the out-of-plane direction at the ascending node and the acceleration of the space object A in the out-of-plane direction at the descending node between time t(i-1) and time ti; The time t0 is the same as the epoch t0, The larger the value of i, the later the time ti.

4. The space situation monitoring business device according to any one of claims 1 to 3, The space situation monitoring business apparatus is a space situation monitoring business apparatus including the acceleration / deceleration analysis device.

5. The space situation monitoring business device according to any one of claims 1 to 3, A space situation monitoring business device that determines whether or not the space object A is accelerating or decelerating based on the execution results of the acceleration / deceleration analysis device equipped in the space situation monitoring business device, and issues an alert to the operator of the space object B if there is a space object B that is predicted to approach or collide with the space object A.

6. Critical infrastructure consisting of a constellation of satellites that form social infrastructure and operate services; A group of monitoring satellites that fly in space and monitor the critical infrastructure and provide on-orbit services; A monitoring center is installed on the ground and transmits and receives information to and from the monitoring satellites. In a satellite monitoring system configured as follows: The monitoring center comprises a space situation monitoring business device according to any one of claims 1 to 3, The space situation monitoring business device is a satellite monitoring system equipped with the acceleration / deceleration analysis device.

7. Critical infrastructure consisting of a constellation of satellites that form social infrastructure and operate services; A group of monitoring satellites that fly in space and monitor the critical infrastructure and provide on-orbit services; A monitoring center is installed on the ground and transmits and receives information to and from the monitoring satellites. In a satellite monitoring system configured as follows: The monitoring center comprises a space situation monitoring business device according to any one of claims 1 to 3, A satellite monitoring system that determines whether or not the space object A is accelerating or decelerating based on the execution results of the acceleration / deceleration analysis device equipped in the space situation monitoring business device, and issues an alert to the operator of the critical infrastructure if an impact on the critical infrastructure is predicted.

8. Critical infrastructure consisting of a constellation of satellites that form social infrastructure and operate services; A group of monitoring satellites that fly in space and monitor the critical infrastructure and provide on-orbit services; a monitoring center installed on the ground that transmits and receives information between the monitoring satellites; In a satellite monitoring system configured as follows: The monitoring center comprises the space situation monitoring business device according to claim 3, A satellite monitoring system that tracks and monitors a space object A using a tracking and monitoring method in which the monitoring device tracks and monitors the space object A at time t(n+1) by deriving the flight position (tn+1, rn+1, θn+1, φn+1) in an Earth-fixed coordinate system as the predicted trajectory S(n+1) of the space object A at time t(n+1), which is later than time tn, based on the parameter set n derived by the acceleration / deceleration analysis device equipped in the space situation monitoring business device.

9. The space situation monitoring business device according to any one of claims 1 to 3, the acceleration / deceleration analyzer included in the space situation monitoring business device; a first monitoring device flying near a geostationary orbit; a second monitoring device located on the ground; a catalogue recording orbital information for a plurality of space objects; Equipped with A space situation monitoring business device that manages space object information, the catalog records at least one of orbital information acquired by the space situation monitoring business device, first orbital information acquired by the first monitoring device, and second orbital information acquired by the second monitoring device; The acceleration / deceleration analysis device uses the orbit information acquired by the first monitoring device and the second monitoring device and the orbit information acquired by the space situation monitoring business device to derive a parameter set n indicating an estimated orbit information update value, which is an estimated value of the orbit information of the space object A at a time tn that is later than the epoch t0, and registers the derived parameter set n in the catalog.

10. The space situation monitoring business device according to any one of claims 1 to 3, the acceleration / deceleration analyzer included in the space situation monitoring business device; a first monitoring device flying near a geostationary orbit; a second monitoring device located on the ground; A catalogue recording the orbital information of multiple space objects and Equipped with A space situation monitoring business device that manages space object information, the catalog records at least one of orbital information acquired by the space situation monitoring business device, first orbital information acquired by the first monitoring device, and second orbital information acquired by the second monitoring device; The acceleration / deceleration analysis device uses the orbit information acquired by the space situation monitoring business device to derive a parameter set n indicating an estimated orbit information update value, which is an estimated value of the orbit information of the space object A at a time tn that is a time after the epoch t0; A space situation monitoring business device that performs at least one of suspicious target identification, behavior tracking, behavioral intention analysis, and information transmission to response assets of the space object A using an acceleration / deceleration analysis method using the acceleration / deceleration analysis device.

11. The space situation monitoring business device according to any one of claims 1 to 3, the acceleration / deceleration analyzer included in the space situation monitoring business device; a first monitoring device flying near a geostationary orbit; a second monitoring device located on the ground; A catalogue recording the orbital information of multiple space objects and Equipped with A space situation monitoring business device that manages space object information, the catalog records at least one of orbital information acquired by the space situation monitoring business device, first orbital information acquired by the first monitoring device, and second orbital information acquired by the second monitoring device; The acceleration / deceleration analysis device generates a parameter set n indicating an estimated orbit information update value, which is an estimated value of the orbit information of the space object A at a time tn that is a time later than the epoch t0, using the orbit information acquired by the space situation monitoring business device; A space situation monitoring business device that tracks and monitors the space object A using the tracking and monitoring method using the acceleration / deceleration analysis device.

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