Acceleration / deceleration analysis device, acceleration / deceleration analysis method, acceleration / deceleration analysis program, space situation monitoring equipment, and satellite monitoring system

Abstract

To enhance versatility in analysis of acceleration / deceleration of a space object.SOLUTION: An acceleration / deceleration analysis device (700) is provided on a space condition monitoring business device for monitoring a space object with a monitoring device, analyzes an orbit of a space object (60) and analyzes presence / absence of acceleration / deceleration of the space object (60), and acquires monitoring information on the monitoring device for a space object A, in which the orbit information composed of the original period t0 and the orbit 6 elements based on Kepler's law is unknown, three times or more, as a parameter set 0 indicating an estimated orbit information initial value that is an estimated value of orbit information of the space object A at the original period t0, when the monitoring device discovers the space object A, and derives orbit six factors at an original period t0.SELECTED DRAWING: Figure 1

Description

Technical Field

[0001] The present disclosure relates to an acceleration / deceleration analysis device, an acceleration / deceleration analysis method, an acceleration / deceleration analysis program, , u a space situation monitoring business device, And, a satellite monitoring system Mu and related matters.

Background Art

[0002] In recent years, the construction of large-scale satellite constellations consisting of hundreds to thousands of satellites has begun, and the risk of satellites colliding with each other in orbit has been increasing. As a method for avoiding the risk of a satellite colliding with other space objects, there is also a method that uses the result of analyzing the acceleration / deceleration of other space objects. Patent Document 1 discloses a space situation monitoring business device including an acceleration / deceleration object tracking device.

Prior Art Documents

Patent Documents

[0003]

Patent Document 1

Summary of the Invention

Problems to be Solved by the Invention

[0004] The method for analyzing the acceleration / deceleration of space objects by the acceleration / deceleration object tracking device disclosed in Patent Document 1 has a problem of low versatility.

[0005] An object of the present disclosure is to enhance the versatility in the analysis of the acceleration / deceleration of space objects.

Means for Solving the Problems

[0006] The acceleration / deceleration analysis device according to the present disclosure is a space situation monitoring business device equipped with a monitoring device for monitoring space objects, and is an acceleration / deceleration analysis device that analyzes the orbit of the space objects to analyze the presence or absence of acceleration / deceleration of the space objects, When the monitoring device detects an object A whose orbital information, composed of epoch t0 and six orbital elements based on Kepler's laws, is unknown, the monitoring device acquires monitoring information for the object A three or more times to derive the six orbital elements in epoch t0, which are then used as parameter set 0, representing the estimated initial orbital information, which is the estimated value of the orbital information of the object A in epoch t0. [Effects of the Invention]

[0007] According to this disclosure, by analyzing the acceleration and deceleration of a space object using the results obtained from deriving the six orbital elements in epoch t0, the versatility of the analysis of the acceleration and deceleration of a space object can be increased. [Brief explanation of the drawing]

[0008] [Figure 1] A diagram showing an example configuration of the space situation monitoring system 47 according to Embodiment 1. [Figure 2] A diagram showing a specific example of catalog 590 according to Embodiment 1. [Figure 3] A diagram showing a specific example of orbital forecast information according to Embodiment 1. [Figure 4] A diagram showing an example of the configuration of the space object 60 according to Embodiment 1. [Figure 5] A diagram showing an example configuration of the communications satellite 811 according to Embodiment 1. [Figure 6] A diagram showing an example configuration of the observation satellite 812 according to Embodiment 1. [Figure 7] A diagram showing an example configuration of the observation satellite 813 according to Embodiment 1. [Figure 8] A diagram illustrating the adjustment of the trajectory inclination angle according to Embodiment 1. [Figure 9] This figure shows an example configuration of a space situation monitoring system 47 according to a modified embodiment of Embodiment 1. [Figure 10] A diagram showing an example configuration of the satellite monitoring system 500 according to Embodiment 2. [Figure 11] A diagram showing an example configuration of the monitoring center 57 according to Embodiment 2. [Figure 12]Figure showing the first communication method in the first satellite group according to Embodiment 2. [Figure 13] Figure showing the second communication method in the first satellite group according to Embodiment 2. [Figure 14] Figure showing the first communication method in the second satellite group according to Embodiment 2. [Figure 15] Figure showing the second communication method in the second satellite group according to Embodiment 2. [Figure 16] Figure showing the first communication method in the third satellite group according to Embodiment 2. [Figure 17] Figure showing the second communication method in the third satellite group according to Embodiment 2. [Figure 18] Figure showing the third communication method in the third satellite group according to Embodiment 2. [Figure 19] Figure showing a configuration example of the collision avoidance support system 510 according to Embodiment 3.

Modes for Carrying Out the Invention

[0009] Hereinafter, embodiments of the present disclosure will be described with reference to the drawings. In each figure, the same or corresponding parts are denoted by the same reference numerals. In the description of the embodiments, the description of the same or corresponding parts will be omitted or simplified as appropriate. The arrows in the figures mainly indicate the flow of data or the flow of processing. Also, in the following drawings, the size relationships of the respective configurations may be different from the actual ones. Further, in the description of the embodiments, directions or positions such as "up", "down", "left", "right", "front", "rear", "front", and "back" may be shown. Those notations are only described as such for the convenience of explanation, and do not limit the arrangement and orientation of the configurations such as devices, instruments, or parts. Also, "part" may be appropriately read as "circuit", "step", "procedure", "process", "stage", or "circuitry".

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

[0011] ***Explanation of the structure*** Figure 1 shows an example configuration of the Space Situational Awareness (SSA) system according to this embodiment. The Space Situational Awareness (SSA) system comprises an acceleration / deceleration analyzer 700, a first monitoring device 810, and a second monitoring device 840, and is also called a Space Situational Awareness (SSA) system. Each device in the Space Situational Awareness (SSA) system may consist of multiple devices, and may be configured integrally as appropriate. The Space Situational Awareness (SSA) system 47 consists of computers belonging to SSA operators, that is, SSA operators that conduct space situational awareness (SSA) operations. SSA operators, also known as space situational awareness businesses, for example, make at least some of the information on space objects collected through SSA operations publicly available on their servers. The space situation monitoring system 47 acquires space object information 501 representing the status of space objects 60 flying in space. The space situation monitoring system 47 then manages the acquired space object information 501. Specific examples of space objects 60 include rockets launched into space, artificial satellites, space bases, debris removal satellites, planetary exploration spacecraft, or satellites that have become debris after the completion of their missions. In this specification, artificial satellites are also simply referred to as satellites. The space situational awareness system 47 appropriately incorporates the functions of a collision avoidance support system disclosed in [Patent Document 1].

[0012] The acceleration / deceleration analyzer 700 analyzes the orbit of the space object 60 to determine whether or not the space object is accelerating or decelerating. It is a computer equipped with a processor 910, memory 921, auxiliary storage device 922, input interface 930, output interface 940, display device 941, and communication device 950. The acceleration / deceleration analyzer 700 may be installed in either the ground equipment 701 or the satellite, but in this specification, the acceleration / deceleration analyzer 700 will be described assuming that it is installed in the ground equipment 701. The acceleration / deceleration analyzer 700 communicates with 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 the observation satellite 812. The first monitoring device 810 may fly in the vicinity of geostationary orbit. A specific example of the second monitoring device 840 is the observation device provided by the ground equipment 701 of the space situation monitoring device 47.

[0013] The processor 910 is a device that executes each program that realizes the function of each component of the acceleration / deceleration analysis device 700. The processor 910 is an IC (Integrated Circuit) that performs arithmetic processing. A specific example of the processor 910 is the CPU (Central Processing Unit). This refers to a DSP (Digital Signal Processor) or a GPU (Graphics Processing Unit).

[0014] Memory 921 is a storage device that temporarily stores data. Specific examples of memory 921 include SRAM (Static Random Access Memory) or DRAM (Dynamic Random Access Memory).

[0015] The auxiliary storage device 922 is a storage device for storing data. A specific example of the auxiliary storage device 922 is an HDD (Hard Disk Drive). Alternatively, the auxiliary storage device 922 may be a portable storage medium such as an SD (Secure Digital) memory card, a CF (CompactFlash) memory card, a NAND flash memory card, a flexible disk, an optical disk, a compact disk, a Blu-ray (Registered Trademark) disc, or a DVD (Digital Versatile Disk).

[0016] The input interface 930 is a port to which input devices such as a mouse, keyboard, or touch panel are connected. Specifically, the input interface 930 is a USB (Universal Serial Bus) terminal. Alternatively, the input interface 930 may be a port connected to a LAN (Local Area Network).

[0017] The output interface 940 is a port to which the cable of a display device 941, such as a display, is connected. Specifically, the output interface 940 is a USB terminal or an HDMI® (High Definition Multimedia Interface) terminal. Specifically, the display is an LCD (Liquid Crystal Display).

[0018] The communication device 950 has a receiver and a transmitter. Specifically, the communication device 950 is a communication chip or NIC (Network Interface Card). The acceleration / deceleration analysis device 700 communicates with ground equipment and satellites, or with satellites themselves, via the communication device 950.

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

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

[0021] Catalog 590 records orbital information for multiple space objects. Catalog 590 records all or part of the orbital information, including publicly available orbital information obtained from publicly accessible sources, paid orbital information purchased by SSA operators, non-public information obtained through inter-operator agreements, first orbital information obtained by the first monitoring device 810, and second orbital information obtained by the second monitoring device 840. Catalog 590 includes space object information 501. Figure 2 shows a specific example of 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 equipment 40. For example, the catalog 590 has the orbital information of the space object 60 pre-recorded. The catalog 590 may be collected from a management company that manages the space object 60. The management equipment 40 provides information about space objects 60, such as artificial satellites or space debris. The management equipment 40 is a computer of a company that collects information about space objects 60, such as artificial satellites or space debris. As shown in Figure 2, the space object information 501 includes a space object ID (Identification) that identifies the space object 60, and orbital information. The orbital information includes predicted orbital information and actual orbital information. The forecast orbital information includes the epoch, orbital elements, prediction error, information provider equipment ID, and information update date. The actual orbital information includes UTC (Universal Time Coordinated) time, position coordinates, measurement error, information provider equipment ID, and information update date.

[0023] Figure 3 shows an example of space object information 501 according to this embodiment. The space situation monitoring system 47 stores, for example, space object information 501 in the storage unit 720, which contains predicted values ​​for the orbits of space objects 60. The space situation monitoring system 47 may, for example, obtain predicted values ​​for the orbits of each of the multiple space objects 60 from a management system 40 used by a management company that manages multiple space objects 60, and store them in the space object information 501 as a catalog 590. Alternatively, the space situation monitoring system 47 may obtain space object information 501 containing predicted values ​​for the orbits of each of the multiple space objects 60 from a management company and store it in the storage unit 720. Alternatively, the space situation monitoring system 47 may store the space object information 501 in the storage unit 720 based on monitoring data 712 received from a first monitoring device 810 provided by the space situation monitoring system 47.

[0024] The space object information 501 includes satellite orbit forecast information 52 and debris orbit forecast information 53. The satellite orbit forecast information 52 contains the forecast value of the satellite's orbit. The debris orbit forecast information 53 contains the forecast value of the debris's orbit. In this embodiment, the satellite orbit forecast information 52 and the debris orbit forecast information 53 are included in the space object information 501, but the satellite orbit forecast information 52 and the debris orbit forecast information 53 may also be stored as individual pieces of information in the storage unit 720.

[0025] The space object information 501 includes information such as the space object ID (Identifier) ​​511, the forecast epoch 512, the forecast orbital elements 513, and the forecast error 514.

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

[0027] The predicted epoch 512 is the predicted epoch for each of the orbits of the multiple cosmic 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 each of the orbits of the multiple space objects 60. In Figure 3, the six Kepler orbital elements are set as the predicted orbital elements 513.

[0028] The forecast error 514 is the error predicted for each orbit of multiple space objects. The forecast error 514 includes a forward error, a perpendicular error, and the basis for the error. Thus, the forecast error 514 explicitly shows the amount of error inherent in the actual value, along with its basis. The basis for the amount of error includes the measurement means, the data processing performed as a means of improving the accuracy of position coordinate information, and some or all of the results of statistical evaluation of past data.

[0029] In this embodiment, the space object information 501 includes a forecast epoch 512 and a forecast orbital element 513 for the space object 60. The forecast epoch 512 and the forecast orbital element 513 allow us to determine the time and position coordinates of the space object 60 in the near future. For example, the time and position coordinates of the space object 60 in the near future may be set in the space object information 501. Thus, the space object information 501 contains orbital information of the space object, including its epoch and orbital elements, or time and position coordinates, and explicitly shows the predicted values ​​for the near future of the space object 60.

[0030] In the following embodiments, the space situational awareness system 47 or ground equipment may be described as performing control and data processing functions. In this case, the processor 910 primarily performs these functions.

[0031] Figure 4 shows an example configuration of a satellite 30, which is an example of a space object 60 according to this embodiment. Satellite 30 comprises a satellite control device 310, a satellite communication device 32, a propulsion device 33, an attitude control device 34, and a power supply device 35. While it also includes other components for various functions, Figure 4 will focus on the satellite control device 310, satellite communication device 32, propulsion device 33, attitude control device 34, and power supply device 35. Satellite 30 is an example of a space object 60.

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

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

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

[0035] Based on Figure 5, the configuration of communications satellite 811 will be explained. The communications satellite 811 includes a communications device 121, a propulsion device 122, a power supply device 123, and a camera 124. The communication device 121 includes a first directional antenna 121E, a second directional antenna 121W with a directional direction, and an omnidirectional antenna 121N. For example, camera 124 is a wide-angle camera that points in the same direction as the first directional antenna 121E or the second directional antenna 121W.

[0036] The communications satellite 811 allows for the visual observation of observation satellites and other space objects orbiting in geostationary or near-geostationary orbit. This enables visual confirmation that the environment around communications satellite 811 is free from obstacles that could cause interference and noise in communications. Other space objects 60 are space objects distinct from those observed by the observation satellite. The observation satellite is a specific example of the first monitoring device 810.

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

[0038] Based on Figure 6, the configuration of an observation satellite 812, which is an example of the first monitoring device 810, will be explained. The observation satellite 812 is equipped with an observation instrument 111, a satellite control device 112, a communication device 113, a propulsion device 114, an attitude control device 115, a power supply device 116, and a camera 117. Observation device 111 is a device for observing space object 60. Observation device 111 is also called a monitoring device. Camera 117 is, for example, a wide-angle camera pointed towards the communications satellite 811.

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

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

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

[0042] Based on Figure 7, the configuration of observation satellite 813, which is another example of the first monitoring device 810, will be explained. Observation satellite 813 is equipped with an observation instrument 201, a satellite control device 202, a communication device 203, a propulsion device 204, an attitude control device 205, and a power supply device 206.

[0043] Observation device 201 is a device for observing space object 60. Observation device 201 optically photographs space object 60 flying at an altitude different from the orbital altitude of observation satellite 813. Specifically, observation device 201 is a visible optical sensor. The observation device 201 generates observational data. This observational data is obtained through observations performed by the observation device 201. For example, the observational 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 predetermined procedures or various commands transmitted from ground equipment.

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

[0046] ***Explanation of operation*** The operating procedure of the acceleration / deceleration analysis device 700 corresponds to the acceleration / deceleration analysis method. Furthermore, the program that enables the operation of the acceleration / deceleration analysis device 700 corresponds to the acceleration / deceleration analysis program. Any program described herein may be recorded on a computer-readable non-volatile recording medium. Specific examples of non-volatile recording media include optical discs or flash memory. Any program described herein may be provided as a program product.

[0047] <Example of operation of this embodiment 1> The acceleration / deceleration analyzer 700 uses Keplerian elements based on Kepler's laws in the orbital information of a satellite, which is composed of the epoch and six orbital elements. The periods are as follows: • Epoch: (Year and day) The orbital elements based on Kepler's laws consist of the following parameters: • Mean motion (m): Mean Motion (laps / day), or Semi-major Axis (km) • Eccentricity (e): Unitless ·Orbital inclination angle (i): Inclination (degrees) • Right Ascension of Ascending Node (Ω): RAAN (degrees) • Argument of Perigee (ω): Argument of Perigee (degrees) ·Mean Anomaly (degrees)

[0048] The acceleration / deceleration analyzer 700 needs to determine the six orbital elements of space object A, which is an unknown entity for which there is no prior information and the orbital information is unknown, in order to understand the orbital information of space object A. The orbit of the space object 60 orbiting the Earth traces a quadratic curve with the Earth as one focus. Two parameters are required to specify the shape of this quadratic curve. Furthermore, two parameters are required to specify the plane on which the orbit of the space object 60 resides, and one parameter is required to specify the direction in which the orbit is pointing on that plane. To determine the shape of the orbit of space object 60, the plane in which the orbit exists, and the orientation of the orbit, five independent measurement data points are needed, specifically measurement data points of space object 60. Here, one measurement of space object 60 yields a pair of two independent measurement data points: right ascension and declination. Therefore, at least three measurements are necessary to determine the orbit of space object 60. However, since the measurement error is large in monitoring information obtained by measuring space object 60 three times in a short period, it is considered appropriate to improve the measurement accuracy by measuring space object 60 several more times.

[0049] To determine the orbital elements of space object A, it is fundamental to measure space object A multiple times using monitoring equipment owned by the SSA operator. However, it is considered reasonable to collect monitoring information using various monitoring methods such as optical monitoring and radar monitoring, using a large number of first monitoring devices 810 distributed over a wide area, in order to calculate initial estimates of orbital elements and obtain highly accurate orbital information with minimal measurement error. If a single operator does not possess monitoring equipment with diverse monitoring methods that can be deployed over a wide area, the acceleration / deceleration analysis device 700 may obtain orbital information acquired using monitoring equipment owned by another operator and use that acquired orbital information. Furthermore, if publicly available orbital information such as TLE (Two Line Element) already exists, the acceleration / deceleration analyzer 700 may use the existing publicly available orbital information as parameter set 0, which indicates the initial values ​​of the estimated orbital information.

[0050] Therefore, when the monitoring device detects an object A in space whose orbital information, composed of the period t0 and the six orbital elements based on Kepler's laws, is unknown, the acceleration / deceleration analysis device 700 obtains monitoring information from the monitoring device for object A three or more times to derive the six orbital elements in period t0, which are then used as parameter set 0, representing the estimated initial orbital information, which is the estimated value of the orbital information of object A in period t0. Period t0 is sometimes denoted as time t0.

[0051] <Example of operation of this embodiment 2> The purpose of space situational awareness is to provide information that can help in taking countermeasures by predicting risks such as dangerously close approaches or collisions of debris or suspicious space objects to critical infrastructure 55, including communication satellites, weather satellites, and positioning satellites, which play an active role as social infrastructure. Here, critical infrastructure 55 consists of a constellation of satellites that form and operate social infrastructure. Therefore, if 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 a 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 obtaining the orbital information of space object A early. However, if we assume that the difference information that space object A and space object B are monitored as different objects is the difference in the argument of perigee, then it 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] First, the acceleration / deceleration analysis device 700 detects space object A using a monitoring device, and if space object B is flying around space object A and its orbital information is known, it uses five elements from the six orbital elements of space object B's orbital information, excluding the perigee argument, as the five elements from the six orbital elements of space object A's orbital information, and derives the perigee argument of space object A's orbital information using the monitoring information of the monitoring device for space object A. The area around space object A is considered to be the vicinity of space object A. Next, the acceleration / deceleration analysis device 700 uses the five cited elements and the derived perigee argument as parameter set 0, which represents the estimated initial orbital information, that is the estimated orbital information of space object A in epoch t0. Note that operation examples 3 to 8 of this embodiment are based on operation example 1 or 2 of this embodiment.

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

[0054] First, the acceleration / deceleration analyzer 700 derives parameter set 1 from the difference between the orbital period derived from the monitoring information for space object A at time t1 and the orbital period of parameter set 0, with the direction of motion of space object A as the X-axis. Time t1 is a time later than epoch t0. Parameter set 1 represents the estimated orbital information update value, which is an estimated value of the orbital information of space object A at time t1. Next, the acceleration / deceleration analysis device 700 derives ΔV and acceleration for the direction of motion of space object A between epoch t0 and time t1 from the monitoring information.

[0055] <Example of operation of this embodiment 4> First, the acceleration / deceleration analyzer 700 uses the direction of motion of space object A as the X-axis to calculate the difference between the orbital period derived from the monitoring information for space object A at time t1, the orbital period derived from the monitoring information for space object A at time t2, and the orbital period of parameter set 0. Time t2 is later than time t1. Next, the acceleration / deceleration analyzer 700 derives parameter set 1 and parameter set 2 from the obtained difference, deriving ΔV and acceleration for the direction of motion of space object A between epoch t0 and time t1, and deriving ΔV and acceleration for the direction of motion of space object A between time t1 and time t2. Parameter set 2 represents the estimated orbital information update value, which is the estimated orbital 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 analysis errors due to measurement errors. In these cases, monitoring space object A multiple times can improve the accuracy of the analysis. Furthermore, this example demonstrates the ability to detect fluctuating acceleration and deceleration amounts when the acceleration and deceleration of space object A significantly changes from epoch t0 to time t2.

[0057] <Example of operation of this embodiment 5> Increasing the number of measurements of space object A reduces measurement errors and enables high-precision analysis of space object A. Furthermore, it is considered rational to measure space object A from multiple geometrically dispersed locations. Specifically, by combining measurement information from near the perigee and apogee of an elliptical orbit, it becomes possible to rationally reduce measurement errors by ground monitoring equipment. Moreover, 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; thus, the characteristics of measurement errors differ. For this reason, it is considered rational to collect information from multiple monitoring methods and improve measurement accuracy by fusion of the collected information. Needless to say, it is also permissible to use measurement information from monitoring devices of other businesses.

[0058] First, the acceleration / deceleration analyzer 700 uses the direction of motion of space object A as the X-axis and calculates the difference between the orbital period i derived from the monitoring information of space object A at time ti (where i is a natural number between 1 and n, and n is a natural number greater than or equal to 3) and the orbital period of parameter set 0. Next, the acceleration / deceleration analyzer 700 derives a parameter set i from the obtained difference and derives ΔV and acceleration for the direction of motion of space object A between time t(i-1) and time ti. Here, the parameter set i represents the estimated orbital information update value, which is an estimated value of the orbital information of space object A at time ti, time t0 is the same as the epoch t0, and time ti is a later time as the value of i increases.

[0059] <Example of operation 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 at or down at space object B from an out-of-plane direction. To adjust the orbital inclination, it is reasonable to fire the thrusters in the direction normal to the orbital plane near the ascending and descending nodes, and it is assumed that the direction of the thrust will be reversed at the ascending and descending nodes. Therefore, in the orbital analysis model of space object A contained within the acceleration / deceleration analysis device 700, as a typical analysis parameter setting, conditions are input where the absolute values ​​of Aya1 at the ascending node and Ayd1 at the descending node are equal and the sign of the out-of-plane direction is reversed, and conditions that fit the difference in orbital inclination angles shown by parameter set 0 and parameter set 1 are derived. Strictly speaking, the effects of thruster firing extend to orbital elements other than the orbital inclination, but focusing on the orbital inclination is considered a reasonable indicator for determining whether or not space object A is intentionally performing out-of-plane control.

[0060] Figure 8 illustrates the adjustment of orbital inclination and shows a specific example of orbital inclination change behavior in a low Earth orbit satellite. As shown in Figure 8, if the propulsion system of satellite 30 generates thrust in a direction perpendicular to the orbital plane of satellite 30 at the point (equinox) when satellite 30 crosses the equator of Earth 70, the orbital inclination can be effectively fine-tuned.

[0061] First, the acceleration / deceleration analyzer 700 uses the direction of motion of space object A as the X-axis and the direction of the normal to the orbital plane of space object A as the Y-axis, and calculates the difference between the orbital inclination angle derived from the monitoring information for space object A at time t1 and the orbital inclination angle of parameter set 0. Next, the acceleration / deceleration analyzer 700 derives parameter set 1 from the difference, and derives the acceleration of space object A in the out-of-plane direction at the ascending node and the acceleration of space object A in the out-of-plane direction at the descending node between the epoch t0 and time t1.

[0062] <Example of operation of this embodiment 7> First, the acceleration / deceleration analyzer 700 uses the direction of motion of space object A as the X-axis and the direction of the normal to the orbital plane as the Y-axis, and calculates the difference between the orbital inclination angle derived from the monitoring information for space object A at time t1, the orbital inclination angle derived from the monitoring information for space object A at time t2, and the orbital inclination angle of parameter set 0. Next, the acceleration / deceleration analyzer 700 derives parameter set 1 and parameter set 2 from the obtained difference, and derives the acceleration of space object A in the out-of-plane direction at the ascending node and the acceleration of space object A in the out-of-plane direction at the descending node between period t0 and time t1, and derives the acceleration of space object A in the out-of-plane direction at the ascending node and the acceleration of space object A in the out-of-plane direction at the descending node between time t1 and time t2. Furthermore, this example of operation has the same effect as Example 4 of this embodiment.

[0063] <Example of operation of this embodiment 8> First, the acceleration / deceleration analyzer 700 uses the direction of motion of space object A as the X-axis and the direction of the normal to the orbital plane of space object A as the Y-axis, and calculates the difference between the orbital inclination angle i derived from the monitoring information for space object A at time ti (where 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 parameter set 0. Next, the acceleration / deceleration analyzer 700 derives a parameter set i from the obtained difference, and derives the acceleration of space object A in the out-of-plane direction at the ascending node and the acceleration of space object A in the out-of-plane direction at the descending node between time t(i-1) and time ti. Note that this example of operation is the same as example of operation 5 in this embodiment.

[0064] <Example of operation of this embodiment 9> Furthermore, although the change in the right ascension of the ascending node was not considered in operation examples 3 to 8 of this embodiment, the right ascension of the ascending node changes because the orbital period of the orbital plane of space object A changes with acceleration and deceleration in the direction of motion and in the out-of-plane direction. In addition, since the argument of perigee also changes when the orbital period changes, it is considered appropriate to evaluate all changes in the six orbital elements using the orbital analysis model of space object A in order to perform the analysis with relatively high accuracy.

[0065] Therefore, the acceleration / deceleration analyzer 700 uses the monitoring information for space object A at time t1, the monitoring information for space object A at time t2, and the monitoring information for space object A at time tn, with the direction of motion of space object A as the X-axis and the direction normal to the orbital plane of space object A as the Y-axis, to derive a parameter set n and the acceleration for space object A at time t1 to time tn, assuming that the acceleration for space object A at time t1 is constant.

[0066] For the sake of simplification, assuming constant acceleration, such as during rocket launch or orbital descent, this example demonstrates that fitting with minimal discrepancies in orbital information is possible.

[0067] <Example of operation of this embodiment 10> When space object A changes its acceleration over time, and the orbital analysis model of space object A evaluates the six orbital elements under the condition that its acceleration is fixed, a large discrepancy remains in the orbital information from time t1 to time tn. Considering the measurement error of the monitoring device and the analysis error that occurs in the analysis process of deriving the six orbital elements from the measured orbital information, it is expected that there will be a certain degree of variability in the measurement results of space object A. However, if the discrepancy remains that is clearly larger than the measurement error and analysis error, it can be concluded that space object A has acceleration.

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

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

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

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

[0072] According to this example, it can be determined that space object A has acceleration from period t0 to time tn. Furthermore, if a large discrepancy remains in the orbital information of space object A when a constant acceleration value is assumed, it can be determined that there is a change in the amount or direction of acceleration of space object A, that is, that space object A is accelerating or decelerating. Since the change in the orbital period can be measured with high precision regarding the direction of movement of space object A, this example makes it possible to evaluate even the acceleration and deceleration fluctuations of space object A.

[0073] <Example of operation 13 of this embodiment> In any of the 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 space object A at time t(n+1), which is later than time tn, based on the derived parameter set n, and tracks and monitors space object A at time t(n+1) using the monitoring device. This example demonstrates a tracking and monitoring method.

[0074] <Example of operation 14 of this embodiment> In any of the operation examples 10 to 12 of this embodiment, the acceleration / deceleration analyzer 700 further determines whether space object A is accelerating or decelerating, and issues an alarm to the operator of space object B if there is space object B that is expected to approach or collide with space object A.

[0075] <Example of operation 15 of this embodiment> The space situation monitoring system 47 manages space object information 501. The acceleration / deceleration analysis system 700 comprises a first monitoring device 810 that flies around geostationary orbit, a second monitoring device 840 installed on the ground, and a catalog 590 that records orbital information of multiple space objects. Catalog 590 records at least one of the following: orbital information acquired by the Space Situational Monitoring System 47, first orbital information acquired by the first monitoring device, and second orbital information acquired by the second monitoring device. The orbital information acquired by the Space Situational Monitoring System 47 includes, as a specific example, at least one of the following: publicly available orbital information acquired free of charge from publicly available information, paid orbital information purchased by the SSA operator, and orbital information including non-public information obtained through inter-operator agreements. In any of the operation examples 1 to 9 of this embodiment, the acceleration / deceleration analysis device 700 further derives a parameter set n using the orbital information acquired by the first monitoring device 810 and the second monitoring device 840, and the orbital information acquired by the space situation monitoring device 47, and registers the derived parameter set n in the catalog 590.

[0076] <Example of operation 16 of this embodiment> The space situational awareness system 47 in this operational example is the same as the space situational awareness system 47 in operational example 15 of this embodiment. In any of the operation examples 10 to 12 of this embodiment, the acceleration / deceleration analysis device 700 further derives the parameter set n using orbital information acquired by the space situation monitoring device 47. Subsequently, the acceleration / deceleration analysis device 700 performs at least one of the following actions of space object A: suspicious target identification, behavior tracking, behavioral intent analysis, and information transmission to a response asset, using the acceleration / deceleration analysis method shown in any of the operation examples 10 to 12 of this embodiment.

[0077] <Example of operation 17 of this embodiment> The space situational awareness system 47 in this operational example is the same as the space situational awareness system 47 in operational example 15 of this embodiment. In the operation example 13 of this embodiment, the acceleration / deceleration analysis device 700 further generates a parameter set n that represents the estimated orbital information update value, which is an estimated value of the orbital information of space object A at time tn, using orbital information acquired by the space situation monitoring device 47. Subsequently, the acceleration / deceleration analysis device 700 tracks and monitors the space object A using the tracking and monitoring method shown in Operation Example 13 of this embodiment.

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

[0079] ***Other configurations*** <Example 1> The functions of the acceleration / deceleration analyzer 700 may be implemented in hardware instead of software. Figure 9 shows the configuration of an acceleration / deceleration analysis device 700 according to a modified example of this embodiment. The acceleration / deceleration analyzer 700 is equipped with a processor 910, a processor 910 and memory 921, a processor 910 and auxiliary storage device 922, or an electronic circuit 909 instead of a processor 910, memory 921 and auxiliary storage device 922. The electronic circuit 909 is a dedicated electronic circuit that implements the functions of the acceleration / deceleration analysis device 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 implemented in a single electronic circuit or distributed across multiple electronic circuits. As another variation, some functions of the acceleration / deceleration analyzer 700 may be implemented by the electronic circuit 909, while the remaining functions are implemented by software.

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

[0081] Embodiment 2. The following will explain the differences from the previously described embodiment, primarily with reference to the drawings.

[0082] ***Explanation of the structure*** Figure 10 shows an example of the overall configuration of the satellite monitoring system 500 according to this embodiment. The satellite monitoring system 500 comprises a constellation of monitoring satellites 56 that monitor the critical infrastructure 55, and a monitoring center 57. In addition to the constellation of monitoring satellites 56 and the monitoring center 57, the satellite monitoring system 500 may also include the critical infrastructure 55. The monitoring satellite 521 is also called a monitoring satellite or monitoring device.

[0083] Critical Infrastructure 55 is infrastructure in outer space. Specifically, Critical Infrastructure 55 is formed by a constellation of satellites that constitute social infrastructure, such as the exchange of information with distant or remote regions via communication satellites, weather forecasting using images from the Himawari weather satellite, and 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. In addition, ground equipment 58 for each infrastructure corresponding to the critical infrastructure 55 is installed on the ground.

[0084] The monitoring satellite constellation 56 consists of monitoring satellites 521 that monitor infrastructure satellites 551, which make up the critical infrastructure 55. The monitoring center 57 is located on the ground and exchanges information with the monitoring satellite 521 of the monitoring satellite constellation 56. The monitoring satellite 521 of the monitoring satellite constellation 56 and the monitoring center 57 exchange information via the communication equipment installed on the infrastructure satellite 551.

[0085] The satellite constellation Infrastructure satellite 551 includes all or part of the following: communications satellite 401, data relay satellite 402, weather satellite 403, observation satellite 404, first observation and surveillance satellite 405, positioning satellite 406, second observation and surveillance satellite 407, space station 408, lunar and planetary exploration satellite 409, exploration satellite 410, and transport vehicle 411. Exploration satellite 410 is an exploration satellite that explores planets other than the Moon or resources. The 1st Observation and Surveillance Satellite 405, also known as an early warning satellite, is deployed in high orbits such as geostationary or Molniya orbit to conduct wide-area observations or surveillance of the ground. The 2nd Observation and Surveillance Satellite 407, also known as the Information Gathering Satellite, is an observation or surveillance satellite used to collect various important imagery, such as large-scale disasters. In addition, ground equipment 701 is installed on the ground for each infrastructure corresponding to the critical infrastructure 55.

[0086] Factors such as debris collisions due to the increasing number of objects in the space environment are increasing the risk of hazardous events that involve the failure or loss of critical infrastructure 55. Therefore, a system is needed to monitor critical infrastructure 55 and take hazard avoidance actions if necessary.

[0087] The monitoring satellite constellation 56 includes an infrastructure satellite 551 equipped with communication equipment for communicating with the monitoring center 57, which is designated as monitoring satellite 521. The monitoring satellite 521 includes all or part of the optical monitoring satellite 421, the radio monitoring satellite 423, the infrared monitoring satellite 422, the service satellite 424, and the debris removal satellite 425. The optical monitoring satellite 421 monitors the infrastructure satellite 551 using optics. The radio monitoring satellite 423 monitors the infrastructure satellite 551 using radio waves. The infrared monitoring satellite 422 monitors the infrastructure satellite 551 using infrared detection. The service satellite 424 provides on-orbit services to the infrastructure satellite 551. The debris removal satellite 425 removes debris.

[0088] On-orbit services include, in whole or in part, capture, inspection, repair, refueling, relocation, de-orbiting (ADR: Active Debris Removal), and laser irradiation.

[0089] The monitoring service provided by the 56 monitoring satellite constellation is easier to understand when considered in analogy to the roles of eyes, ears, hands, and mouth. To achieve the objective of visually monitoring critical infrastructure 55 using satellites, methods such as visually monitoring suspicious objects like debris using optical telescopes or radar images are effective. Infrared detection is also an effective method for monitoring abnormal temperature environments.

[0090] Furthermore, monitoring services that use auditory means to keep an eye on things have the objective of monitoring radio waves in outer space where sound waves do not propagate. To achieve the objective of monitoring critical infrastructure 55 using satellites, an effective method is to receive radio waves flying around the area and monitor the radio wave conditions that could cause malfunctions.

[0091] Furthermore, as an extension of monitoring services, on-orbit services can be cited as an analogy to the role of manual operation. On-orbit services include services such as capturing, inspecting, and repairing malfunctioning satellites. They also include services such as refueling satellites that have run out of fuel, relocation services to move the service location, and active orbital removal (ADR) for satellites that cannot deorbit on their own after the end of their lifespan. Additionally, there are services that use lasers to monitor the distance to suspicious objects such as debris.

[0092] Thus, it is hoped that the monitoring satellite 521 will fulfill the roles of eyes, ears, or hands. However, there are limitations to the role of the mouth, that is, the means of communication for transmitting monitoring information 560, and ingenuity is required.

[0093] In this embodiment, the infrastructure satellite 551 is used as the monitoring satellite 521 that acts as the mouth, that is, the monitoring satellite 521 that transmits monitoring information 560. The monitoring satellite 521 includes the infrastructure satellite 551, which acts as the mouth of the monitoring satellite 521. Similarly, the infrastructure satellite 551 includes the monitoring satellite 521, which also acts as the mouth. In other words, the satellite monitoring system 500 contains satellites that are both monitoring satellites 521 and infrastructure satellites 551. While this description primarily focuses on the infrastructure satellite 551 acting as the mouth, such satellites could also function as eyes, ears, and hands.

[0094] As shown in Figure 10, the monitoring satellite 521 that performs long-distance communication includes the communications satellite 401 and the data relay satellite 402 in the first satellite constellation 601. It also includes the communications satellite 401 in the second satellite constellation 602. Furthermore, it includes the lunar and planetary exploration satellite 409 in the third satellite constellation 603. The monitoring satellite 521, which conducts short-range communications, includes the weather satellite 403, the positioning satellite 406, and the observation satellite 404 in the first satellite constellation 601.

[0095] As shown in Figure 10, the satellite monitoring system 500 comprises a first satellite constellation 601, a second satellite constellation 602, a third satellite constellation 603, and a monitoring center 57. The first satellite in the constellation, 601, is in geostationary orbit (GEO: Geostationary Earth). It consists of satellites orbiting near a quasi-zenith orbit (QZO). The second satellite constellation, 602, consists of satellites orbiting in the vicinity of medium-altitude Earth orbit (MEO) or low-altitude Earth orbit (LEO). The third satellite constellation, 603, consists of satellites orbiting in cislunar space, which is the space between the Moon and the Earth, or beyond the Moon.

[0096] Figure 11 shows an example of the configuration of the monitoring center 57 according to this embodiment. The monitoring center 57 is also called the ground equipment 701, which is installed on the ground. Here, we will explain assuming that the monitoring center 57 is installed on the ground equipment 701.

[0097] The memory unit 720 stores monitoring information 560.

[0098] Ground equipment 701 exchanges monitoring information 560 with monitoring satellite 521 via infrastructure satellite 551. The monitoring management unit 710 uses the monitoring information 560 exchanged with monitoring satellite 521 to implement functions to address the risk of failure or loss of critical infrastructure 55. For example, the monitoring management unit 710 implements functions such as warning of hazards, preventing hazards, or avoiding hazards in critical infrastructure 55.

[0099] ***Explanation of operation*** The operating procedure of the satellite monitoring system 500 corresponds to the satellite monitoring method. Furthermore, the program that implements the operation of the satellite monitoring system 500 corresponds to the 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 satellite constellation 601> Figure 12 shows the first communication method in the first satellite constellation 601 according to this embodiment. The satellite monitoring system 500 includes a first satellite constellation 601, which consists of satellites orbiting near geostationary orbit (GEO) or near quasi-zenith orbit (QZO). The first satellite constellation 601 includes a monitoring satellite 521 and an infrastructure satellite 551, which is either a communications satellite 401 or a data relay satellite 402, and which has a communication environment with the ground. When the monitoring satellite 521 passes within the communication range of the communication satellite 401 or the data relay satellite 402, it exchanges monitoring information 560 with the communication satellite 401 or the data relay satellite 402. Then, the communication satellite 401 or the data relay satellite 402 exchanges monitoring information 560 with the monitoring center 57.

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

[0102] In Figure 12, the monitoring satellite 521a, which acts as the eyes, and the monitoring satellite 521b, which acts as the ears, exchange monitoring information 560 with the communication satellite 401 or the data relay satellite 402 as they pass near these satellites. The communication satellite 401 or the data relay satellite 402 then exchanges the monitoring information 560 with the monitoring center 57.

[0103] <Second communication method for satellite constellation 601, the first constellation> Figure 13 shows the second communication method in the first satellite constellation 601 according to this embodiment. The first satellite constellation 601 includes infrastructure satellite 551, which is either a weather satellite 403, a positioning satellite 406, or an observation satellite 404. Infrastructure satellite 551, which is either a weather satellite 403, a positioning satellite 406, or an observation satellite 404, has a communication environment in place to communicate with communication satellite 401 or data relay satellite 402. When the monitoring satellite 521 passes within the communication range of the weather satellite 403, the positioning satellite 406, or the observation satellite 404, it exchanges monitoring information 560 with the weather satellite 403, the positioning satellite 406, or the observation satellite 404. Weather satellite 403, positioning satellite 406, or observation satellite 404 exchange monitoring information 560 with communication satellite 401 or data relay satellite 402. Then, communication satellite 401 or data relay satellite 402 exchanges monitoring information 560 with monitoring center 57.

[0104] Figure 13 shows the second communication method, which is the method of exchanging information between the monitoring satellite 521 and the monitoring center 57 in the first satellite constellation 601. The weather satellite 403, positioning satellite 406, or observation satellite 404, which constitute the critical infrastructure 55, are equipped with a communication environment for communicating with the communications satellite 401 or data relay satellite 402.

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

[0106] <First communication method of the second satellite constellation 602> Figure 14 shows the first communication method in the second satellite constellation 602 according to this embodiment. The Satellite Monitoring System 500 consists of a constellation of satellites orbiting in the vicinity of medium-altitude Earth orbit (MEO) or low-altitude Earth orbit (LEO). The second satellite constellation 602 includes a monitoring satellite 521 and an infrastructure satellite 551, which is a communications satellite 401, and which has a communication environment with the ground. When the monitoring satellite 521 passes within the communication range of the communication satellite 401, it exchanges monitoring information 560 with the communication satellite 401. The communication satellite 401 then exchanges monitoring information 560 with the monitoring center 57.

[0107] Figure 14 shows the first communication method of the second satellite constellation 602, which is a method of exchanging information between the monitoring satellite 521 and the monitoring center 57 in the second satellite constellation 602, which consists of satellites orbiting near medium-altitude Earth orbit (MEO) or near low-altitude Earth orbit (LEO). Infrastructure satellite 551, specifically communications satellite 401, has a well-established communication environment with the ground.

[0108] In Figure 14, when the monitoring satellite 521b, which acts as the ears, passes near the communication satellite 401, which acts as both a monitoring satellite and an infrastructure satellite 551, it exchanges monitoring information 560 with the communication satellite 401. The communication satellite 401 then exchanges the monitoring information 560 with the monitoring center 57.

[0109] <Second communication method for the second satellite constellation 602> Figure 15 shows the second communication method in the second satellite constellation 602 according to this embodiment. The second satellite constellation 602 includes multiple communication satellites, designated as communication satellites 401, for which a communication environment is established for communication with each other. When the monitoring satellite 521 passes within communication range of one of the multiple communication satellites, it exchanges monitoring information 560 with the communication satellite 401. The communication satellite 401, which has received the monitoring information 560, will exchange the monitoring information 560 with other communication satellites among the multiple communication satellites. Other communication satellites exchange monitoring information 560 with the monitoring center 57.

[0110] Figure 15 shows the second communication method of the second satellite constellation 602, which is the method of exchanging information between the monitoring satellite 521 and the monitoring center 57 in the second satellite constellation 602. Infrastructure satellite 551, specifically communications satellite 401, has established communication infrastructure with the ground, and also has a communication infrastructure that allows multiple communications satellites to communicate with each other.

[0111] In Figure 15, the monitoring satellites 521a (acting as eyes), 521b (acting as ears), and 521c (acting as hands) pass near the communication satellite 401, which is both a monitoring satellite and infrastructure satellite 551 (acting as a mouth). At that time, they exchange monitoring information 560 with the communication satellite 401. The communication satellite 401 then exchanges the monitoring information 560 with other communication satellites via the communication environment. The communication satellite 401 that has received the monitoring information 560 then exchanges the monitoring information 560 with the monitoring center 57.

[0112] <First communication method of the third satellite constellation 603> Figure 16 shows the first communication method in the third satellite constellation 603 according to this embodiment. The satellite monitoring system 500 consists of a third satellite constellation 603, which comprises satellites orbiting in cislunar space, the space between the Moon and the Earth, or beyond the Moon. The third satellite constellation 603 includes a monitoring satellite 521 and an infrastructure satellite 551, which is a lunar and planetary exploration satellite 409, and is equipped with a communication environment with the ground. When monitoring satellite 521 passes within the communication range of lunar and planetary exploration satellite 409, it exchanges monitoring information 560 with lunar and planetary exploration satellite 409. Then, lunar and planetary exploration satellite 409 exchanges monitoring information 560 with monitoring center 57.

[0113] Figure 16 shows the first communication method of the third satellite constellation 603, which is the method of exchanging information between the monitoring satellite 521 and the monitoring center 57 in the third satellite constellation 603. Lunar and Planetary Exploration Satellite 409, as part of Infrastructure Satellite 551, has established a communication environment with the ground. Lunar and Planetary Exploration Satellite 409 is both an infrastructure satellite 551 and a monitoring satellite that plays the role of a mouthpiece.

[0114] In Figure 16, the monitoring satellite 521a, which acts as the eyes of the system, exchanges monitoring information 560 with the lunar and planetary exploration satellite 409 as it passes near the satellite. The lunar and planetary exploration satellite 409 then exchanges the monitoring information 560 with the monitoring center 57.

[0115] <Second communication method for the third satellite constellation, 603> Figure 17 shows the second communication method in the third satellite constellation 603 according to this embodiment. The satellite monitoring system 500 consists of a third satellite constellation 603, which comprises satellites orbiting in cislunar space, the space between the Moon and the Earth, or beyond the Moon. The third satellite constellation 603 includes the monitoring satellite 521 and the infrastructure satellite 551, which is the lunar and planetary exploration satellite 409, and includes the lunar and planetary exploration satellite 409 which has a communication environment with the ground. As the monitoring satellite 521 passes through the communication range of the lunar and planetary exploration satellite 409, it exchanges monitoring information 560 with gateway 412, which operates in cislunar space. Gateway 412 exchanges monitoring information 560 with monitoring center 57.

[0116] Specifically, Gateway 412 is a gateway built through international cooperation, such as a space base near the moon, and has communication lines to communicate with ground facilities. Gateway 412 is an infrastructure satellite 551 and also one of the monitoring satellites that serve as a mouthpiece.

[0117] Figure 17 shows the second communication method of the third satellite constellation 603, which is the method of exchanging information between the monitoring satellite 521 and the monitoring center 57 in the third satellite constellation 603. When the monitoring satellite 521a, which acts as the eyes of the satellite, passes near the lunar and planetary exploration satellite 409, it exchanges monitoring information 560 with the gateway 412. The gateway 412 then exchanges the monitoring information 560 with the monitoring center 57.

[0118] <Third communication method of the 603 satellite constellation, third group> Figure 18 shows the third communication method in the third satellite constellation 603 according to this embodiment. The satellite monitoring system 500 consists of a third satellite constellation 603, which comprises satellites orbiting in cislunar space, the space between the Moon and the Earth, or beyond the Moon. The third satellite constellation 603 includes the monitoring satellite 521 and the infrastructure satellite 551, which is the lunar and planetary exploration satellite 409, and includes the lunar and planetary exploration satellite 409 which has a communication environment with the ground. As 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. Gateway 412 exchanges monitoring information 560 with the monitoring center 57 via gateway ground equipment 59 installed on the ground.

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

[0120] <Example of operation of this embodiment 1> The satellite monitoring system 500 determines whether space object A is accelerating or decelerating using the acceleration / deceleration analysis method shown in any of the operation examples 10 to 12 of Embodiment 1, and issues an alert to the operator of the critical infrastructure 55 if an impact on the critical infrastructure 55 is foreseen.

[0121] <Example of operation of this embodiment 2> The satellite monitoring system 500 tracks and monitors space object A using the tracking and monitoring method described in Operation Example 17 of Embodiment 1.

[0122] Embodiment 3. The following will explain the differences from the previously described embodiment, primarily with reference to the drawings.

[0123] ***Explanation of the structure*** Figure 19 shows an example configuration of the collision avoidance support system 510 according to this embodiment. The space situation monitoring system 47 is equipped with a collision avoidance support system 100 instead of an acceleration / deceleration analysis system 700. However, the collision avoidance support system 100 analyzes the acceleration and deceleration of space object A in the same way as the acceleration / deceleration analysis system 700. The collision avoidance support system 510 is basically the same as the collision avoidance support system disclosed in [Patent Document 1]. In other words, this embodiment is a technology that appropriately extends the technology disclosed in [Patent Document 1]. The collision avoidance support 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 supports collision avoidance between space objects among multiple space objects. The collision avoidance support device 100 supports collision avoidance between space objects among multiple space objects flying in space.

[0124] The functions of the recorder processing unit 110, alarm control unit 120, performance presentation unit 130, avoidance decision unit 150, and machine learning unit 160 are all implemented by software.

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

[0126] The alarm control unit 120 controls an alarm when a collision-prone object or approaching object is present. Based on orbital forecast information, the alarm control unit 120 determines whether there are multiple space objects among several space objects whose relative positions are dangerous at the same time, and outputs a danger alarm 25 indicating the presence of danger objects 65. Danger objects 65 are multiple space objects among several space objects whose relative positions are dangerous at the same time.

[0127] The performance display unit 130, when any of the multiple space objects collide with each other, extracts the orbital performance information 54 at the time of the collision from the orbital performance information 54 as the collision performance 131, and displays the extracted collision performance 131 to the output device.

[0128] When the avoidance decision unit 150 outputs a danger alert 25, it determines the avoidance space object 69, which is a space object among the space objects included in the predicted danger object 65 that will perform avoidance operations. The avoidance decision unit 150 may determine the avoidance space object 69 based on whether or not each space object included in the predicted danger object 65 is a rocket at the time of launch. The avoidance decision unit 150 may determine the avoidance space object 69 based on whether or not each space object included in the predicted danger object 65 belongs to a megaconstellation. The avoidance decision unit 150 may determine the avoidance space object 69 based on whether or not each space object included in the predicted danger object 65 is in a steady-state operation state or an unsteady-state operation state. The avoidance decision unit 150 may determine the avoidance space object 69 based on whether or not each space object included in the predicted danger object 65 is an orbital transition satellite performing orbital transitions. The avoidance decision unit 150 may determine the avoidance space object 69 based on whether or not each space object included in the predicted danger object 65 has a collision avoidance function. The avoidance decision unit 150 may determine the space objects to avoid 69 based on whether each space object included in the predicted hazard object 65 is in a dense orbit. The avoidance decision unit 150 may also output an avoidance object notification 151 that notifies the space objects to avoid 69.

[0129] The machine learning unit 160 updates the algorithm for the avoidance decision process that determines the avoidance object 69 by machine learning using the result of determining the avoidance object 69, that is, the result of determining the avoidance object 69 by the avoidance decision unit 150. The avoidance object 69 is a space object that is subject to avoidance operations among the space objects included in the predicted dangerous object 65.

[0130] The space information recorder 50 includes orbital forecast information 51 and orbital performance information 54 in which orbital performance values ​​have been set. The memory unit 720 stores the space information recorder 50. The collision avoidance support device 100 acquires flight forecast information 491 from the management device 40 used by the management operator that manages space objects, and based on the acquired flight forecast information 491, sets the forecast primacy for each of the orbits of multiple space objects, the forecast orbital elements that identify the orbit, and the forecast error that is forecasted in the orbit as orbital forecast information, and is equipped with a space information recorder 50 that includes orbital forecast information. The flight forecast information 491 represents the forecast for each of the multiple space objects' flights. Orbital forecast information 51 consists of predicted values ​​for the time and orbit of multiple space objects.

[0131] The collision avoidance support system 510 may include a database for storing space object information and a server equipped with collision avoidance operator determination means for determining a collision avoidance operator to perform 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 part of a group of space objects, is foreseen; obtaining the estimated time or time period in which the collision is foreseen, orbital forecast information for space object A, and orbital forecast information for space object B from the space information recorder 50; notifying all or some of the operators of space object A, space object B, and debris removal operators of a danger warning, which is a collision warning or proximity warning, for the estimated time or time period; selecting a collision avoidance operator; and requesting collision avoidance action from the selected collision avoidance operator. The server may also implement the step of notifying space insurance operators, which apply an insurance payment system that assesses accident liability and insurance claims based on the difference between orbital forecast information and orbital actual information, of the danger warning, which is a collision warning or proximity warning. Note that the server having each step is equivalent to the server implementing each step. The collision avoidance support system 510 takes into account the future acceleration and deceleration of space object A and, if a risk of approach or collision between space object A and space object B is foreseen, issues a warning to the operator managing space object B. The information on space objects may include information indicating whether or not the space objects have collision avoidance capabilities. The information on space objects may also include a history of past space collision accidents. The collision avoidance operator selection means may select a management company that manages space objects equipped with collision avoidance capabilities as the collision avoidance operator if either space object A or space object B is equipped with collision avoidance capabilities. The collision avoidance operator selection means may select a collision avoidance operator using whether the object is a steadily operating object or a transient space object as an evaluation criterion if both space object A and space object B are equipped with collision avoidance capabilities. The collision avoidance operator selection means may select a collision avoidance operator using whether the object is a mega-constellation satellite as an evaluation criterion if both space object A and space object B are equipped with collision avoidance capabilities. The collision avoidance operator selection means may select a collision avoidance operator by adding evaluation criterion data from the selection process of collision avoidance operators in past space collision accidents to the selection evaluation criterion.

[0132] The management unit 40 comprises a mega-constellation unit 41, a LEO-constellation unit 42, a satellite unit 43, an orbital transfer unit 44, a debris recovery unit 45, and a rocket launch unit 46. The management unit 40 may also be configured to include a space situation monitoring unit 47.

[0133] The database may also obtain the scheduled launch time and launch forecast information for space object C from the rocket launch operator via the space information recorder. The server may implement the following steps: the step of notifying the mega-constellation operator, which manages the mega-constellation satellites at risk of collision by space object C, of ​​the launch forecast information in the scheduled launch time information; the step of the avoidance operator determination means requesting collision avoidance action from the mega-constellation operator or requesting the provision of information necessary for collision avoidance during rocket launch; and the step of notifying the rocket launch operator of space object information of the mega-constellation satellites at risk of collision by space object C. The server may also implement the step of notifying the launch forecast information to a space insurance operator that operates an insurance payment system that can be contracted when a collision risk during rocket launch is foreseeable. The server may also implement the step of providing launch time information that can ensure flight safety during rocket launch. The collision avoidance support system 510 may issue a warning to the operator managing space object B if it foresees 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.

[0134] The database obtains the planned orbital transition time and transition forecast information for space object D from the orbital transition satellite operator via the space information recorder 50. The server implements the following steps: the step of notifying the megaconstellation operator, which manages the megaconstellation satellites at risk of collision by space object D, of the transition forecast information for the scheduled time of the orbital transition; the step of the avoidance operator determination means requesting collision avoidance action from the megaconstellation operator or the provision of information necessary for collision avoidance during the orbital transition; and the step of notifying the orbital transition satellite operator of the space object information of the megaconstellation satellites at risk of collision by space object D. The server may also include a step of notifying the transition forecast information to a space insurance operator that operates an insurance payment system that can be contracted when a collision risk during orbital transition is foreseeable. The server may also implement a step of providing transition forecast information that can ensure flight safety during orbital transition. The collision avoidance support system 510 may issue a warning to the operator managing space object B if it foresees 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.

[0135] The database may obtain the scheduled deorbit time and deorbit forecast information for space object E from the space information recorder, which is obtained from the satellite operator or debris removal operator that deorbits space object E. The server may implement the following steps: the step of notifying the mega-constellation operator, which manages the mega-constellation satellites at risk of collision by space object E, of the deorbit forecast information for the scheduled deorbit time; the step of the avoidance operator determination means requesting collision avoidance action from the mega-constellation operator, or requesting the provision of information necessary for collision avoidance during deorbit; and the step of notifying the satellite operator or debris removal operator that deorbits the mega-constellation satellites at risk of collision by space object E. The server may also implement the step of notifying 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 foreseeable. The server may also implement the step of providing deorbit forecast information that can ensure flight safety during deorbit. The collision avoidance support system 510 may issue a warning to the operator managing space object B if it foresees 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.

[0136] ***Explanation of operation*** The operating procedure of the collision avoidance support device 100 corresponds to the collision avoidance support method. Furthermore, the program that implements the operation of the collision avoidance support device 100 corresponds to the collision avoidance support program. <Example of operation of this embodiment 1> First, the space situation monitoring device 47 measures space object A, whose orbital elements are unknown and which are composed of an epoch and six orbital elements based on Kepler's laws, multiple times using the monitoring device to calculate initial estimated values ​​for the orbital elements of space object A. Next, the space situation monitoring device 47 acquires orbital information of space object A four or more times and calculates updated estimated values ​​for the orbital elements of space object A. Next, the space situation monitoring device 47 determines that there is an acceleration or deceleration effect on space object A if there is a significant fluctuation that exceeds the effects of measurement errors and estimation errors, and the fluctuation from the initial estimate is present in the updated estimate.

[0137] <Example of operation of this embodiment 2> In Operation Example 1 of this embodiment, the space situation monitoring device 47 further generates trajectory prediction information for space object A after determining that space object A is accelerating or decelerating, measures space object A by directing the monitoring device to the generated trajectory prediction information, and tracks and monitors space object A using the results of the measurement of space object A.

[0138] <Example of operation of this embodiment 3> In operation example 1 or 2 of this embodiment, the space situation monitoring system 47 further takes into account the future acceleration and deceleration of space object A and, if a risk of approach or collision between space object A and space object B is foreseen, issues an alarm to the operator managing space object B.

[0139] <Example of operation of this embodiment 4> The collision avoidance support device 100 takes into account the future acceleration and deceleration of space object A and, if a risk of approach or collision between space object A and space object B is foreseen, issues a warning to the operator managing space object B.

[0140] <Example of operation of this embodiment 5> The collision avoidance support device 100 performs a danger warning output process that outputs a danger warning 25 to an insurance provider of a space insurance program that pays insurance money from pre-collected insurance premiums when space object A and space object B collide among multiple space objects, and to a space object management provider that manages at least one of the multiple space objects.

[0141] <Example of operation 6 of this embodiment> In the operation example 4 of this embodiment, the collision avoidance support device 100 further performs a danger warning output process that identifies the presence of a predicted danger object 65 based on orbital forecast information and outputs a danger warning 25 before the space objects in the multiple space objects collide with each other. In the danger warning output process, the collision avoidance support device 100 determines whether or not a predicted danger object 65 exists based on the orbital forecast information 51 provided by the space information recorder 50, and if it is determined that a predicted danger object 65 exists, it outputs a danger warning.

[0142] <Example of operation of this embodiment 7> In the operation example 4 of this embodiment, when a danger warning 25 is output, the collision avoidance support device 100 further executes a process to determine the space object to be avoided 69. In the process to determine the space object to be avoided, the collision avoidance support device 100 determines the space object to be avoided from among the space objects included in the predicted danger object 65, based on the orbital forecast information 51 provided by the space information recorder 50.

[0143] ***Other Embodiments*** The embodiments described above can be freely combined, any component of each embodiment can be modified, or any component can be omitted in each embodiment. Furthermore, the embodiments are not limited to those shown in Embodiments 1 to 3, and various modifications can be made as needed. The procedures described in the operation examples may be modified as appropriate. [Explanation of symbols]

[0144] 25 Danger Warning, 30 Satellite, 32 Satellite Communication Equipment, 33, 122, 114, 204 Propulsion System, 34, 115, 205 Attitude Control System, 35, 123, 116, 206 Power Supply Unit, 121, 113, 203 Communication Equipment, 100 Collision Avoidance Support System, 110 Recorder Processing Unit, 111, 201 Observation Equipment, 112, 202, 310 Satellite Control Unit, 117, 124 Camera, 120 Warning Control Unit, 121E First Directional Antenna, 121N Omnidirectional Antenna, 121W Second Directional Antenna, 130 Performance Display Unit, 131 Collision Performance, 150 Avoidance Decision Unit, 151 Avoidance Object Notification, 160 Machine Learning Unit, 242 Performance Position Coordinates, 40 Management Business Equipment, 41 Mega Constellation Business Equipment, 42 LEO Constellation Business Equipment, 43 Satellite operations equipment, 44 Orbital transfer operations equipment, 45 Debris recovery operations equipment, 46 Rocket launch operations equipment, 47 Space situational awareness operations equipment, 401 Communications satellite, 402 Data relay satellite, 403 Weather satellite, 404 Observation satellite, 405 First observation and monitoring satellite, 406 Positioning satellite, 407 Second observation and monitoring satellite, 408 Space station, 409 Lunar and planetary exploration satellite, 410 Exploration satellite, 411 Transport vehicle, 412 Gateway, 421 Optical monitoring satellite, 422 Infrared monitoring satellite, 423 Radio monitoring satellite, 424 Service satellite, 425 Debris removal satellite, 491 Flight forecast information, 492 Flight performance information, 50 Space information recorder, 51 Orbital forecast information, 52 Satellite orbit forecast information, 53 Debris orbit forecast information, 54 Orbital performance information, 55 Critical infrastructure, 56 Monitoring satellite constellation, 57 Monitoring Center, 58 Ground Equipment for Each 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 hazardous object, 69 Space object to avoid, 601 First satellite constellation, 602 Second satellite constellation, 603 Third satellite constellation, 70 Earth, 700 Acceleration / deceleration analyzer, 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. A space situation monitoring system is provided that monitors space objects using a monitoring device, and an acceleration / deceleration analysis device is provided that analyzes the orbit of the space object and analyzes whether or not the space object is accelerating or decelerating, When the monitoring device detects a space object A whose orbital information, composed of an epoch t0 and six orbital elements based on Kepler's laws, is unknown, the acceleration / deceleration analysis device obtains monitoring information from the monitoring device for the space object A three or more times to derive the six orbital elements in the epoch t0, which is used as a parameter set 0 indicating the estimated initial orbital information, which is an estimated value of the orbital information of the space object A in the epoch t0, With the direction of motion of the aforementioned space object A as the X-axis, the difference between the orbital period derived from the monitoring information for the space object A at time t1, which is a time later than the epoch t0, and the orbital period of the parameter set 0, A parameter set 1 is derived that represents the estimated orbital information update value, which is the estimated orbital information of the space object A at the aforementioned time t1. An acceleration / deceleration analysis device for deriving ΔV and acceleration for the direction of motion of the space object A between the aforementioned period t0 and the aforementioned time t1.

2. A space situation monitoring system is provided that monitors space objects using a monitoring device, and an acceleration / deceleration analysis device is provided that analyzes the orbit of the space object and analyzes whether or not the space object is accelerating or decelerating, When the monitoring device detects a space object A whose orbital information, composed of an epoch t0 and six orbital elements based on Kepler's laws, is unknown, the acceleration / deceleration analysis device obtains monitoring information from the monitoring device for the space object A three or more times to derive the six orbital elements in the epoch t0, which is used as a parameter set 0 indicating the estimated initial orbital information, which is an estimated value of the orbital information of the space object A in the epoch t0, With the direction of motion of the aforementioned space object A as the X-axis, the difference between the orbital period derived from the monitoring information for the space object A at time t1, which is later than the epoch t0, the orbital period derived from the monitoring information for the space object A at time t2, which is later than time t1, and the orbital period of parameter set 0, A parameter set 1 is derived that represents the estimated orbital information update value, which is the estimated orbital information of the space object A at the aforementioned time t1. A parameter set 2 is derived that represents the estimated orbital information update value, which is the estimated orbital information of the space object A at the aforementioned time t2. Derive the ΔV and acceleration of the cosmic object A in the direction of motion between the aforementioned period t0 and the aforementioned time t1. An acceleration / deceleration analysis device for deriving ΔV and acceleration for the direction of motion of the space object A between the aforementioned time t1 and the aforementioned time t2.

3. A space situation monitoring system is provided that monitors space objects using a monitoring device, and an acceleration / deceleration analysis device is provided that analyzes the orbit of the space object and analyzes whether or not the space object is accelerating or decelerating, When the monitoring device detects a space object A whose orbital information, composed of an epoch t0 and six orbital elements based on Kepler's laws, is unknown, the acceleration / deceleration analysis device obtains monitoring information from the monitoring device for the space object A three or more times to derive the six orbital elements in the epoch t0, which is used as a parameter set 0 indicating the estimated initial orbital information, which is an estimated value of the orbital information of the space object A in the epoch t0, With the direction of motion of the aforementioned space object A as the X-axis, the difference between the orbital period i derived from the monitoring information of the space object A at time ti (where i is a natural number between 1 and n, and n is a natural number between 3 and n) and the orbital period of the parameter set 0, A parameter set i is derived that represents the estimated orbital information update value, which is the estimated orbital information of the space object A at time ti. Derive the ΔV and acceleration of the space object A in the direction of motion between time t(i-1) and time ti. Time t0 is the same as the aforementioned period t0, The acceleration / deceleration analyzer uses a variable where a larger value of i indicates a later time.

4. The acceleration / deceleration analysis device according to claim 2, which detects the fluctuation in the amount of acceleration / deceleration of the space object A between the period t0 and the time t2, based on the results obtained from deriving ΔV and acceleration for the direction of motion of the space object A between the period t0 and the time t1, and the results obtained from deriving ΔV and acceleration for the direction of motion of the space object A between the time t1 and the time t2.

5. The acceleration / deceleration analysis device according to claim 3, wherein the direction of motion of the space object A is the X-axis, the direction normal to the orbital plane of the space object A is the Y-axis, and using monitoring information for the space object A at time t1, monitoring information for the space object A at time t2, and monitoring information for the space object A at time tn, the device derives a parameter set n and the acceleration for the direction of motion of the space object A such that the difference between the monitoring information and the orbital information for the space object A from time t1 to time tn is minimized, assuming that the acceleration for the direction of motion of the space object A is constant.

6. A space situation monitoring device according to any one of claims 1 to 5, The space situation monitoring device is a space situation monitoring device equipped with the acceleration / deceleration analysis device.

7. A space situation monitoring device according to any one of claims 1 to 5, A space situational awareness system that determines whether space object A is accelerating or decelerating based on the results of the acceleration / deceleration analysis device provided in the space situational awareness system, and issues an alert to the operator of space object B if there is a space object B that is foreseeable to approach or collide with space object A.

8. Critical infrastructure consists of a constellation of satellites that form and operate social infrastructure, A constellation of monitoring satellites flying through space to monitor and provide on-orbit services to the aforementioned critical infrastructure, A monitoring center installed on the ground exchanges information with the aforementioned monitoring satellite constellation. In a satellite monitoring system composed of the following, The aforementioned monitoring center is equipped with a space situation monitoring device according to any one of claims 1 to 5, The aforementioned space situation monitoring device is a satellite monitoring system equipped with the aforementioned acceleration / deceleration analysis device.

9. Critical infrastructure consists of a constellation of satellites that form and operate social infrastructure, A constellation of monitoring satellites flying through space to monitor and provide on-orbit services to the aforementioned critical infrastructure, A monitoring center installed on the ground exchanges information with the aforementioned monitoring satellite constellation. In a satellite monitoring system composed of the following, The aforementioned monitoring center is equipped with a space situation monitoring device according to any one of claims 1 to 5, A satellite monitoring system that determines whether or not the space object A is accelerating or decelerating based on the results of the acceleration / deceleration analysis device provided in the space situation monitoring device, and issues a warning to the operator of the critical infrastructure if an impact on the critical infrastructure is foreseeable.

10. Critical infrastructure consists of a constellation of satellites that form and operate social infrastructure, A constellation of monitoring satellites flying through space to monitor and provide on-orbit services to the aforementioned critical infrastructure, A monitoring center installed on the ground exchanges information with the aforementioned monitoring satellite constellation. In a satellite monitoring system composed of the following, The aforementioned monitoring center is equipped with the space situation monitoring device described in claim 3 or 5, A satellite monitoring system that tracks and monitors space object A by tracking and monitoring the space object A at time t(n+1) using the monitoring device, based on a parameter set n derived by the acceleration / deceleration analysis device equipped in the space situation monitoring device, 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 space object A at time t(n+1), which is later than time tn.

11. A space situation monitoring device according to any one of claims 1 to 5, The acceleration / deceleration analysis device provided in the aforementioned space situation monitoring device, A first monitoring device flying near geostationary orbit, A second monitoring device installed on the ground, A catalog that records the orbital information of multiple space objects, It is equipped with, A space situational awareness system for managing information on space objects, The catalog records at least one of the orbital information acquired by the space situation monitoring device, the first orbital information acquired by the first monitoring device, and the second orbital information acquired by the second monitoring device. The acceleration / deceleration analysis device uses the orbital information acquired by the first monitoring device and the second monitoring device, and the orbital information acquired by the space situation monitoring business device, to derive a parameter set n which is an estimated orbital information update value, which is an estimated value of the orbital information of the space object A at time tn, which is a time later than the epoch t0, and registers the derived parameter set n in the catalog.

12. A space situation monitoring device according to any one of claims 1 to 5, The acceleration / deceleration analysis device provided in the aforementioned space situation monitoring device, A first monitoring device flying near geostationary orbit, A second monitoring device installed on the ground, A catalog that records the orbital information of multiple space objects and It is equipped with, A space situational awareness system for managing information on space objects, The catalog records at least one of the orbital information acquired by the space situation monitoring device, the first orbital information acquired by the first monitoring device, and the second orbital information acquired by the second monitoring device. The acceleration / deceleration analysis device uses the orbital information acquired by the space situation monitoring device to derive a parameter set n that represents an estimated orbital information update value, which is an estimated value of the orbital information of the space object A at time tn, which is a time later than the epoch t0. A space situation monitoring device that performs at least one of the following actions by using the acceleration / deceleration analysis method of the acceleration / deceleration analysis device: identification of a suspicious target of space object A, tracking of its actions, analysis of its intentions, and transmission of information to a response asset.

13. A space situation monitoring device according to any one of claims 1 to 5, The acceleration / deceleration analysis device provided in the aforementioned space situation monitoring device, A first monitoring device flying near geostationary orbit, A second monitoring device installed on the ground, A catalog that records the orbital information of multiple space objects and It is equipped with, A space situational awareness system for managing information on space objects, The catalog records at least one of the orbital information acquired by the space situation monitoring device, the first orbital information acquired by the first monitoring device, and the second orbital information acquired by the second monitoring device. The acceleration / deceleration analysis device generates a parameter set n that represents an estimated orbital information update value, which is an estimated value of the orbital information of the space object A at time tn, which is a time later than the epoch t0, using orbital information acquired by the space situation monitoring device. A space situation monitoring system that tracks and monitors the space object A using the tracking and monitoring method of the acceleration / deceleration analysis device described above.

14. An acceleration / deceleration analysis method comprising a space situation monitoring system that monitors space objects using a monitoring device, and an acceleration / deceleration analysis device that analyzes the orbit of the space object and analyzes whether or not the space object is accelerating or decelerating, A method for accelerating and decelerating, in which, when the monitoring device detects a space object A whose orbital information, composed of an epoch t0 and six orbital elements based on Kepler's laws, is unknown, the monitoring device acquires monitoring information for the space object A three or more times to derive the six orbital elements in epoch t0, and uses this as a parameter set 0 that indicates the estimated initial orbital information, which is an estimated value of the orbital information of the space object A in epoch t0. With the direction of motion of the aforementioned space object A as the X-axis, the difference between the orbital period derived from the monitoring information for the space object A at time t1, which is a time later than the epoch t0, and the orbital period of the parameter set 0, A parameter set 1 is derived that represents the estimated orbital information update value, which is the estimated orbital information of the space object A at the aforementioned time t1. An acceleration / deceleration analysis method for deriving ΔV and acceleration for the direction of motion of the space object A between the aforementioned period t0 and the aforementioned time t1.

15. An acceleration / deceleration analysis program is executed by an acceleration / deceleration analysis device, which is a computer that performs orbital analysis of the space object and analyzes whether or not the space object is accelerating or decelerating, comprising a space situation monitoring system that monitors space objects using a monitoring device, When the monitoring device detects an object A whose orbital information, composed of epoch t0 and six orbital elements based on Kepler's laws, is unknown, the monitoring device obtains monitoring information for the object A three or more times to derive the six orbital elements in epoch t0, which is used as parameter set 0, representing the estimated initial orbital information, which is the estimated value of the orbital information of the object A in epoch t0. An acceleration / deceleration analysis program that causes the acceleration / deceleration analysis device to perform control processing, With the direction of motion of the aforementioned space object A as the X-axis, the difference between the orbital period derived from the monitoring information for the space object A at time t1, which is a time later than the epoch t0, and the orbital period of the parameter set 0, A parameter set 1 is derived that represents the estimated orbital information update value, which is the estimated orbital information of the space object A at the aforementioned time t1. An acceleration / deceleration analysis program for deriving ΔV and acceleration for the direction of motion of the space object A between the aforementioned period t0 and the aforementioned time t1.

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