Projectile Countermeasure System and Satellite Integrated Command Center

Abstract

To enable tracking of a flying object which intermittently repeats jetting in a gliding stage.SOLUTION: A satellite integration order center includes a communication route search device having a list in which prediction time at which a communication satellite and a monitor satellite transmit flying object information to a next communication satellite and a next monitor satellite is listed, and a command for providing a communication order to a communication satellite group as product materials. The communication route search device searches for the monitor satellite capable of monitoring an area near a flying object launching point to conduct searches for flying object information transmission time and an optimal route to transmit the flying object information to the monitor satellite. The satellite integration order center transmits order commands to a monitor satellite group and the communication satellite group based on a communication route searched by the communication route search device and provides a monitor order to the monitor satellite group via the communication satellite passing through the neighbor to track and monitor a flying object.SELECTED DRAWING: Figure 9

Description

[Technical Field]

[0001] The present disclosure relates to a missile countermeasure system, a satellite integrated command center, a countermeasure ground center, a communication route search device, a flight path prediction device, a countermeasure asset selection device, an equatorial satellite system, an equatorial satellite, a polar orbiting satellite system, a polar orbiting satellite, an inclined orbit satellite system, an inclined orbit satellite, an integrated data library, and a satellite constellation. [Background technology]

[0002] In recent years, with the emergence of flying objects that glide at hypersonic speeds, there are high expectations for satellite-based monitoring, such as detecting the launch of flying objects, tracking their flight paths, and predicting their landing positions. One promising method for detecting and tracking a flying object during the gliding phase is to use infrared light to detect the temperature rise caused by atmospheric friction as the object enters the atmosphere. Another promising method for detecting a flying object during the gliding phase using infrared light is monitoring it from a constellation of low-earth orbiting satellites.

[0003] Patent Document 1 discloses a monitoring satellite for comprehensively monitoring an area at a specific latitude on the entire Earth's surface using a small number of satellites orbiting in low orbit. [Prior art documents] [Patent documents]

[0004] [Patent Document 1] Japanese Patent Application Laid-Open No. 2008-137439 Summary of the Invention [Problem to be solved by the invention]

[0005] In monitoring from low earth orbit, the distance from the satellite to the flying object is shorter than in monitoring from geostationary orbit. This allows for improved infrared detection performance. A huge number of LEO satellites are required for constant monitoring and maintaining communication lines. Furthermore, unlike geostationary satellites, which appear almost fixed relative to an Earth-fixed coordinate system, LEO satellites constantly move in position. Therefore, the monitoring equipment equipped with infrared monitoring devices, the configuration of communication satellite constellations, and data transmission methods present challenges.

[0006] The present disclosure aims to detect the launch of a missile and transmit missile information to a response system in near real time using a monitoring system having a group of monitoring satellites equipped with monitoring devices and a satellite information transmission system that forms a communication network using a group of communication satellites. [Means for solving the problem]

[0007] The flying object countermeasure system according to the present disclosure comprises: A flying object countermeasure system that detects a flying object by infrared rays and tracks the flying object, which enters the atmosphere during the gliding phase by repeatedly intermittently injecting and whose temperature rises due to atmospheric friction, a monitoring system having a monitoring satellite constellation of multiple monitoring satellites each having a monitoring device and a communication device; a satellite information transmission system having a constellation of communication satellites, which are a plurality of communication satellites each having a communication device; and a countermeasure system having land, sea, and air countermeasure assets for countering flying objects; It is composed of In a flying object countermeasure system, the monitoring system monitors flying objects and generates flying object information, and transmits the generated flying object information to the countermeasure system via the satellite information transmission system, a satellite integrated command center equipped with a satellite information communication route search device; The satellite integrated command center a communication route search device for the satellite information that generates a list enumerating a series of communication satellite IDs of the communication satellite group and monitoring satellite IDs of the monitoring satellite group, and predicted times at which the communication satellites and monitoring satellites will transmit flying object information to the next communication satellite and monitoring satellite, and a command that issues a communication command to the communication satellite group; The communication route search device Searching for the monitoring satellite ID of a monitoring satellite that can monitor the vicinity of the launch point of the missile, including changing the field of view, and searching for the time of missile information transmission, the monitoring satellite ID, and the optimal route for transmitting the missile information to the monitoring satellite ID; The satellite integrated command center Based on the communication route searched by the communication route search device, a command is sent to the group of monitoring satellites and the group of communication satellites, and a monitoring command is given to the group of monitoring satellites via a communication satellite passing nearby, thereby tracking and monitoring the flying object. [Effects of the Invention]

[0008] The flying object countermeasure system according to the present disclosure is a flying object countermeasure system that uses infrared rays to detect and track a flying object that repeatedly undergoes intermittent injections and that undergoes temperature rise due to atmospheric friction after entering the atmosphere. Therefore, the flying object countermeasure system according to the present disclosure has the effect of enabling tracking of a flying object that repeatedly undergoes intermittent injections during the gliding phase. [Brief explanation of the drawings]

[0009] [Figure 1] FIG. 1 illustrates an example of a satellite constellation with multiple intersecting orbital planes outside the polar regions. [Figure 2] FIG. 1 is a diagram showing an example of the configuration of a satellite constellation forming system according to a first embodiment. [Figure 3] FIG. 2 is a diagram showing an example of the configuration of satellites in a satellite constellation according to the first embodiment. [Figure 4] FIG. 4 is a diagram showing another example of the configuration of satellites in the satellite constellation according to the first embodiment. [Figure 5]1 is a diagram showing an example of the configuration of ground equipment provided in a satellite constellation forming system according to a first embodiment. [Figure 6] FIG. 1 is a diagram showing an example of the functional configuration of a satellite constellation forming system according to a first embodiment. [Figure 7] FIG. 2 is a diagram showing an example of the configuration of space object information according to the first embodiment. [Figure 8] FIG. 3 is a diagram showing an example of the configuration of orbit forecast information according to the first embodiment. [Figure 9] FIG. 1 is a diagram showing a configuration example of a flying object countermeasure system according to a first embodiment. [Figure 10] FIG. 10 is a diagram showing an example of an equatorial satellite system according to a third embodiment. [Figure 11] FIG. 10 is a diagram showing an example of a polar-orbiting satellite system according to a fourth embodiment. [Figure 12] FIG. 10 is a diagram showing an example of an inclined orbit satellite system according to a fifth embodiment. [Figure 13] FIG. 13 is a diagram showing a configuration example of a flying object countermeasure system according to a sixth embodiment. [Figure 14] FIG. 20 is a diagram showing an example of the configuration of an integrated data library according to the sixth embodiment. [Figure 15] FIG. 20 is a diagram showing an example of the configuration of an equatorial satellite equipped with an edge server according to a sixth embodiment. [Figure 16] FIG. 20 is a diagram showing an example of the configuration of a polar orbiting satellite equipped with an edge server according to a sixth embodiment. [Figure 17] FIG. 13 is a diagram showing an example of the configuration of an inclined orbit satellite equipped with an edge server according to a sixth embodiment. [Figure 18] FIG. 20 is a diagram showing an example of the configuration of a hybrid constellation according to a sixth embodiment. DETAILED DESCRIPTION OF THE INVENTION

[0010] Hereinafter, embodiments of the present disclosure will be described with reference to the drawings. In each drawing, identical or corresponding parts are designated by the same reference numerals. In the description of the embodiments, the description of identical or corresponding parts will be omitted or simplified as appropriate. In addition, the size relationships of the components in the following drawings may differ from the actual size relationships. In addition, in the description of the embodiments, directions or positions such as "upper," "lower," "left," "right," "front," "rear," "front," and "back" may be indicated. These notations are used merely for the convenience of explanation and do not limit the arrangement or orientation of components such as devices, instruments, or parts.

[0011] Embodiment 1 In this embodiment, we will explain an airborne object response system 401 that is composed of a monitoring system having multiple monitoring satellites, a satellite information transmission system having multiple communication satellites, and a response system that has land, sea, and air response assets to deal with airborne objects.

[0012] The projectile countermeasure system 401 is a system that assumes that the projectile will fly on a ballistic trajectory, detects the spray (plume) at launch using an infrared observation device mounted on a geostationary orbit satellite, predicts impact based on movement information from the early stages of flight, and responds with a countermeasure system. The spray released upon launch was extremely hot gas that spread over a wide area, making it detectable even from geostationary orbit.

[0013] However, recently, a new threat has emerged: a flying object called a Hypersonic Guided Vehicle (HGV), which changes its flight path by intermittently firing jets during flight. In order to track a flying object that has stopped firing, it is necessary to detect the temperature of the flying object's body as it heats up, which requires high-resolution and high-sensitivity infrared monitoring.

[0014] Therefore, there are high expectations for a surveillance system that uses a constellation of low earth orbit (LEO) satellites to monitor flying objects from much closer distances than geostationary orbit. There is a strong demand for a system that can constantly monitor using LEO satellite constellations and immediately transmit information to response assets after detecting a flying object launch.

[0015] In addition to surveillance systems using a group of surveillance satellites equipped with infrared surveillance equipment, there are also expectations for satellite information transmission systems, in which a group of communications satellites form a mesh-like satellite constellation network. This satellite information transmission system provides a means for detecting missile launches and transmitting missile information to response systems in near real time. The term "near real time" is used to take into account the time delay involved in information transmission and the waiting time until the satellites can send and receive information as quickly as possible.

[0016] FIG. 1 is a diagram showing an example of a satellite constellation 20 having a plurality of orbital planes 21 that intersect outside the polar regions. As mentioned above, the surveillance system and the satellite information transmission system are formed as a satellite constellation.

[0017] 1, multiple satellites 30 fly at the same altitude in the same orbital plane. The satellites 30 are also called artificial satellites. In the satellite constellation 20 of FIG. 1, the orbital planes 21 of the multiple orbital planes do not have an inclination angle of approximately 90 degrees, and the orbital planes 21 of the multiple orbital planes exist on different planes. In the satellite constellation 20 of FIG. 1, any two orbital planes intersect at a point other than the polar regions. As shown in FIG. 1, the intersection of multiple orbital planes with an inclination angle greater than 90 degrees moves away from the polar regions depending on the orbital inclination angle. Furthermore, depending on the combination of orbital planes, the orbital planes may intersect at various positions, including near the equator. In addition to the satellite constellation 20 of FIG. 1, there are also satellite constellations with multiple orbital planes each having an inclination angle of approximately 90 degrees, and multiple orbital planes intersecting near the polar regions.

[0018] 2 to 6, an example of a satellite 30 and a ground facility 700 in a satellite constellation forming system 600 that forms the satellite constellation 20 will be described. The satellite constellation forming system 600 may be simply referred to as a satellite constellation.

[0019] FIG. 2 shows an example of the configuration of a satellite constellation forming system 600. The satellite constellation forming system 600 includes a computer. While Fig. 2 shows the configuration of one computer, in reality, a computer is provided for each of the multiple satellites 30 that make up the satellite constellation 20 and for each of the ground facilities 700 that communicate with the satellites 30. The computers provided for each of the multiple satellites 30 and for each of the ground facilities 700 that communicate with the satellites 30 work together to realize the functions of the satellite constellation forming system 600. An example of the configuration of a computer that realizes the functions of the satellite constellation forming system 600 will be described below.

[0020] The satellite constellation forming system 600 includes a satellite 30 and a ground facility 700. The satellite 30 includes a communication device 32 that communicates with a communication device 950 of the ground facility 700. In Fig. 2, the communication device 32 is illustrated as one of the components included in the satellite 30.

[0021] The satellite constellation forming system 600 includes a processor 910, as well as other hardware such as a memory 921, an auxiliary storage device 922, an input interface 930, an output interface 940, and a communication device 950. The processor 910 is connected to the other hardware via signal lines and controls the other hardware.

[0022] The satellite constellation forming system 600 includes, as a functional element, a satellite constellation forming unit 11. The functions of the satellite constellation forming unit 11 are realized by hardware or software. The satellite constellation forming unit 11 controls the formation of the satellite constellation 20 while communicating with the satellites 30 .

[0023] FIG. 3 shows an example of the configuration of a satellite 30 in a satellite constellation forming system 600. The satellite 30 comprises a satellite control device 31, a communication device 32, a propulsion device 33, an attitude control device 34, and a power supply device 35. The satellite 30 may also comprise other components that realize various functions, but Fig. 3 will explain the satellite control device 31, the communication device 32, the propulsion device 33, the attitude control device 34, and the power supply device 35. The satellite 30 in Fig. 3 is an example of a communication satellite 308 that comprises a communication device 32.

[0024] The satellite control device 31 is a computer that controls the propulsion devices 33 and the attitude control device 34, and includes a processing circuit. Specifically, the satellite control device 31 controls the propulsion devices 33 and the attitude control device 34 in accordance with various commands transmitted from the ground facility 700. The communication device 32 is a device that communicates with the ground facility 700. Alternatively, the communication device 32 is a device that communicates with satellites 30 before and after it in the same orbital plane, or with satellites 30 in adjacent orbital planes. Specifically, the communication device 32 transmits various data related to its own satellite to the ground facility 700 or other satellites 30. The communication device 32 also receives various commands transmitted from the ground facility 700. The propulsion device 33 is a device that provides thrust to the satellite 30, changing the speed of the satellite 30. The attitude control device 34 is a device for controlling attitude elements such as the attitude of the satellite 30, its angular velocity, and line of sight. The attitude control device 34 changes each attitude element to a desired direction. Alternatively, the attitude control device 34 maintains each attitude element in a desired direction. The attitude control device 34 includes an attitude sensor, an actuator, and a controller. The attitude sensor is a device such as a gyroscope, an earth sensor, a sun sensor, a star tracker, a thruster, and a magnetic sensor. The actuator is a device such as an attitude control thruster, a momentum wheel, a reaction wheel, and a control moment gyro. The controller controls the actuator according to measurement data from the attitude sensor or various commands from the ground equipment 700. The power supply unit 35 includes devices such as solar cells, batteries, and a power control device, and supplies power to each device mounted on the satellite 30.

[0025] The processing circuitry provided in the satellite control device 31 will now be described. The processing circuitry may be dedicated hardware or may be a processor that executes a program stored in a memory. In the processing circuit, some functions may be realized by dedicated hardware and the remaining functions may be realized by software or firmware, i.e., the processing circuit may be realized by hardware, software, firmware, or a combination thereof. The dedicated hardware may specifically be a single circuit, a complex circuit, a programmed processor, a parallel programmed processor, an ASIC, an FPGA, or a combination thereof. ASIC stands for Application Specific Integrated Circuit, and FPGA stands for Field Programmable Gate Array.

[0026] FIG. 4 shows another example of the configuration of the satellites 30 of the satellite constellation forming system 600. The satellite 30 in FIG. 4 includes a monitoring device 36 in addition to the configuration in FIG. The monitoring device 36 is a device for monitoring objects. Specifically, the monitoring device 36 is a device for monitoring or observing objects such as space objects, flying objects, or land, sea, and air mobile objects. The monitoring device 36 is also called an observation device. For example, the monitoring device 36 is an infrared monitoring device that uses infrared rays to detect the temperature rise caused by atmospheric friction when the projectile enters the atmosphere. The monitoring device 36 detects the temperature of the plume or the projectile body when the projectile is launched. Alternatively, the monitoring device 36 may be an information gathering device using optical waves or radio waves. The monitoring device 36 may be a device that detects objects using an optical system. The monitoring device 36 uses an optical system to photograph objects flying at an altitude different from the orbital altitude of the observation satellite. Specifically, the monitoring device 36 may be a visible optical sensor. 4 is an example of a monitoring satellite 307 equipped with a monitoring device 36 and a communication device 32. The monitoring satellite 307 may be equipped with multiple monitoring devices 36. Furthermore, the monitoring satellite 307 may be equipped with multiple types of monitoring devices 36.

[0027] FIG. 5 shows an example of the configuration of the ground equipment 700 provided in the satellite constellation forming system 600. The ground equipment 700 controls the programs of multiple satellites in all orbital planes. The ground equipment 700 is also called a ground device or a ground system. The ground equipment is composed of a ground station such as a ground antenna device, a communication device connected to the ground antenna device, or a computer, and ground equipment as a server or terminal connected to the ground station via a network. The ground equipment may also include a communication device mounted on a moving object such as an aircraft, a self-propelled vehicle, or a mobile terminal.

[0028] The ground facility 700, i.e., the ground system, operates and controls the satellite constellation, the airborne object countermeasure system, the monitoring system, the satellite information transmission system, or the countermeasure system described in the embodiment of the present disclosure. The hardware configuration of the ground facility 700, i.e., the ground system, is similar to that of the ground response center or satellite integrated command center described in the embodiments of the present disclosure.

[0029] The ground equipment 700 forms the satellite constellation 20 by communicating with each satellite 30. The ground equipment 700 includes a processor 910 as well as other hardware such as a memory 921, an auxiliary storage device 922, an input interface 930, an output interface 940, and a communication device 950. The processor 910 is connected to the other hardware via signal lines and controls the other hardware.

[0030] The ground facility 700 includes, as functional elements, an orbit control command generation unit 510 and an analysis and prediction unit 520. The functions of the orbit control command generation unit 510 and the analysis and prediction unit 520 are realized by hardware or software.

[0031] The communication device 950 transmits and receives signals for tracking and controlling each satellite 30 in the satellite group that makes up the satellite constellation 20. The communication device 950 also transmits orbital maneuver commands 55 to each satellite 30. The analysis and prediction unit 520 analyzes and predicts the orbit of the satellite 30 . The orbital control command generator 510 generates the orbital control command 55 to be transmitted to the satellite 30 . The orbit control command generation unit 510 and the analysis prediction unit 520 implement the functions of the satellite constellation formation unit 11. That is, the orbit control command generation unit 510 and the analysis prediction unit 520 are an example of the satellite constellation formation unit 11.

[0032] FIG. 6 is a diagram showing an example of the functional configuration of a satellite constellation forming system 600. The satellite 30 further includes a satellite constellation forming unit 11b that forms the satellite constellation 20. The satellite constellation forming unit 11b of each satellite 30 of the multiple satellites and the satellite constellation forming unit 11 provided in each of the ground facilities 700 work together to realize the functions of the satellite constellation forming system 600. The satellite constellation forming unit 11b of the satellite 30 may be provided in the satellite control device 31.

[0033] FIG. 7 shows an example of space object information according to this embodiment. The space object information includes a space object ID (Identifier) ​​that identifies the space object, and orbit information. The orbit information includes predicted orbit information and actual orbit information. The space object is, for example, a satellite. The forecast orbit information includes the epoch, orbital elements, prediction error, information provider device ID, and information update date. The forecast orbit information includes UTS time, position coordinates, measurement error, information provider device ID, and information update date.

[0034] FIG. 8 is a diagram showing an example of orbit forecast information according to the present embodiment. The satellite constellation forming system 600, the ground facility 700, or the satellite 30 includes orbital forecast information that sets the predicted orbital values ​​of space objects.

[0035] The orbit forecast information includes satellite orbit forecast information and debris orbit forecast information. The satellite orbit forecast information contains forecast values ​​for satellite orbits. The debris orbit forecast information contains forecast values ​​for debris orbits.

[0036] The orbit forecast information includes, for example, information such as a space object ID, a forecast epoch, forecast orbital elements, and a forecast error.

[0037] A space object ID is an identifier that identifies a space object. In Figure 8, a satellite ID and a debris ID are set as space object IDs. Specifically, space objects include rockets launched into space, flying vehicles, artificial satellites, space stations, debris removal satellites, planetary exploration spacecraft, and satellites or rockets that have become debris after completing their missions.

[0038] A forecast epoch is a predicted epoch for each orbit of a plurality of space objects. The predicted orbital elements are orbital elements that specify the orbit of each of the multiple space objects. The predicted orbital elements are orbital elements that are predicted for the orbit of each of the multiple space objects. In Figure 8, the six Keplerian orbital elements are set as the predicted orbital elements.

[0039] Forecast errors are errors predicted for each orbit of multiple space objects. Forecast errors include a heading error, a cross-directional error, and the basis for the error. In this way, the forecast error explicitly indicates the amount of error contained in the actual value along with the basis. The basis for the amount of error includes some or all of the measurement means, the details of data processing performed as a means to improve the accuracy of position coordinate information, and the results of statistical evaluation of past data.

[0040] In the orbit forecast information according to this embodiment, a forecast origin and forecast orbital elements are set for the space object. The forecast origin and forecast orbital elements can be used to determine the time and position coordinates of the space object in the near future. For example, the time and position coordinates of the space object in the near future may be set in the orbit forecast information. In this way, the orbital forecast information includes orbital information of a space object, including the epoch and orbital elements, or the time and position coordinates, and explicitly indicates the predicted values ​​of the space object in the near future. Alternatively, the satellite constellation forming system 600, the ground facility 700, or the satellite 30 may be provided with orbit performance information in which performance values ​​of the orbit of a space object are set.

[0041] ***Explanation of the configuration and effectiveness of the Projectile Countermeasure System 401***

[0042] FIG. 9 is a diagram showing an example of the configuration of a flying object handling system 401 according to this embodiment. In this embodiment, the flying object countermeasure system 401 includes a satellite integrated command center 810 for integrated management of both satellite systems, the monitoring system 404 and the satellite information transmission system 403, which is a communication system. After a monitoring satellite detects the launch of the flying object 601, it is necessary to transmit the position coordinates to a group of monitoring satellites flying nearby so that they can continue to acquire information on the flying object 601. According to the flying object response system 401 of this embodiment, a monitoring command can be given to the group of monitoring satellites via a communication satellite passing nearby.

[0043] A flying object countermeasure system 401 according to this embodiment will be described with reference to FIG. The flying object response system 401 includes a monitoring system 404 , a satellite information transmission system 403 , and a response system 405 . The monitoring system 404 includes a plurality of monitoring satellites 307 equipped with monitoring and communication equipment. The satellite information transmission system 403 includes a plurality of communication satellites 308 equipped with communication devices. The countermeasure system 405 includes land, sea, and air countermeasure assets 801 that counter the air vehicle 601 .

[0044] The flying object response system 401 transmits flying object information generated by the monitoring system 404 monitoring the flying object 601 to the response system 405 via the satellite information transmission system 403 . The flying object response system 401 also has a satellite integrated command center 810 equipped with a communication route search device 811 that searches for a communication route for satellite information. The satellite integrated command center 810 transmits commands to the group of monitoring satellites owned by the monitoring system 404 and the group of communication satellites owned by the satellite information transmission system 403 based on the communication route searched for by the communication route search device 811.

[0045] The monitoring system 404 also has multiple monitoring satellites 307 equipped with infrared monitoring devices. The monitoring system 404 detects the plume generated when the flying object 601 is launched and the flying object 601 as it flies with its temperature rising, as high-temperature objects. The monitoring system 404 then transmits time information and position information regarding the flying object 601 as flying object information. Specifically, the monitoring satellite 307 uses an infrared monitoring device to detect the plume at the time of launch of the flying object 601 and the flying object 601 as a high-temperature object while it is flying with an increased temperature. Then, the monitoring system 404 transmits flying object information including time information and position information regarding the flying object 601 to the response system 405 via the satellite information transmission system 403.

[0046] Here, variations of the method for dealing with flying objects in the flying object dealing system 401 will be described.

[0047] <Example 1 of how to deal with flying objects> The communication satellites included in the satellite information transmission system 403 are cross-linked by communication devices to form a communication network. A two-way communication link is also called a communication cross-link. The satellite integrated command center 810 uses a communication route search device 811 to search for the shortest route for transmitting information, and sends an information transmission command to the communication satellite that will be the communication path.

[0048] <Example 2 of how to deal with flying objects> After the monitoring satellite A of the monitoring system 404 detects the launch of the flying object 601, the satellite integrated command center 810 transmits the launch time and position coordinates of the flying object 601 to the response system 405 as flying object information.

[0049] <Example 3 of how to deal with flying objects> The satellite integrated command center 810 uses the communication route search device 811 to search for the shortest route in the communication network from the position coordinates at which the monitoring satellite A issued the flying object information to the position coordinates of the response system 405, and sends an information transmission command to the group of communication satellites on the communication path. Based on the information transmission command, the group of communication satellites on the communication path transmits the launch time and position coordinates of the flying object 601 to the response system 405 as flying object information.

[0050] <Example 4 of how to deal with flying objects> After the launch of the missile, the satellite integrated command center 810 transmits missile information to the group of monitoring satellites flying around monitoring satellite A via the satellite information transmission system 403. After monitoring device B detects a high-temperature target, the communication route search device 811 searches for the shortest route in the communication network from the position coordinates of monitoring satellite B to the position coordinates of the response system 405. Then, the satellite integrated command center 810 transmits an information transmission command to the group of communication satellites on the communication path. Based on the information transmission command, the group of communication satellites on the communication path transmit the detection time, position coordinates, and brightness information of the high-temperature target to the response system 405 as missile information.

[0051] The satellite integrated command center 810 transmits flying object information to the group of monitoring satellites flying near the monitoring satellite B via the satellite information transmission system 403. When the monitoring satellite C detects a high-temperature target, the communication route search device 811 searches for the shortest route in the communication network from the position coordinates of the monitoring satellite C to the position coordinates of the response system 405. The satellite integrated command center 810 then transmits an information transmission command to the group of communication satellites on the communication path. Based on the information transmission command, the group of communication satellites on the communication path transmit the detection time, position coordinates, and brightness information of the high-temperature target to the response system 405 as flying object information.

[0052] The satellite integrated command center 810 transmits flying object information to the group of monitoring satellites flying near the monitoring satellite N via the satellite information transmission system 403. When the monitoring device N+1 detects a high-temperature target, the communication route search device 811 searches for the shortest route in the communication network from the position coordinates of the monitoring satellite N+1 to the position coordinates of the response system 405. The satellite integrated command center 810 then transmits an information transmission command to the group of communication satellites on the communication path. Based on the information transmission command, the group of communication satellites on the communication path transmit the detection time, position coordinates, and brightness information of the high-temperature target to the response system 405 as flying object information.

[0053] <Example 5 of how to deal with flying objects> The response system 405 is composed of a plurality of response assets 801 and a response ground center 802. The response ground center 802 is equipped with a flight path prediction device 803. The flight path prediction device 803 generates flight path prediction information composed of future time and position information based on the transition of time-series position information of the flying object information received from the monitoring system 404.

[0054] A response ground center 802 is equipped with a response asset selection device 804 and is connected to the response asset 801 via a communication line. The response ground center 802 selects a response asset 801 located near the position coordinates where the flying object is predicted to pass or arrive, based on flight path prediction information, using the response asset selection device 804, and transmits a command signal for response action.

[0055] The flight path prediction device 803 predicts the direction of movement of the flying object based on the position coordinates of monitoring satellite B, C, N, or N+1, which detected a high-temperature object after monitoring satellite A transmitted launch detection information, and generates flight path prediction information.

[0056] The response asset selection device 804 selects a response asset located near the flight path prediction information from multiple response assets 801 with different position coordinates. Then, the response ground center 802 transmits the flying object information and a response action command to the response asset 801.

[0057] <Example 6 of how to deal with flying objects> The response system 405 has a plurality of response ground centers 802 with different location coordinates. The satellite integrated command center 810 transmits information about the missiles launched and detected by the monitoring satellite A to all response ground centers 802.

[0058] Each of the plurality of ground response centers includes a flight path prediction device 803 that generates flight path prediction information that predicts the path of the flying object. The flight path prediction device 803 transmits flight path prediction information to the satellite integrated command center 810 via the satellite information transmission system 403 or a terrestrial communication line. The satellite integrated command center 810 transmits the flying object information to a ground response center 802 located near the flight path prediction information generated by the flight path prediction device 803.

[0059] For example, the initial launch detection information is transmitted as monitoring information (airborne object information) to all of the countermeasure ground centers 802 whose position information is known in advance. Monitoring information from subsequent monitoring satellites is received by multiple countermeasure ground centers 802. Flight path prediction information generated by a flight path prediction device 803 provided in the countermeasure ground center 802 is transmitted to the satellite information transmission system 403 or the satellite integrated command center 810 via a terrestrial communication line. In this way, the flying object response system 401 narrows down the target response ground centers 802 by repeatedly exchanging monitoring information on subsequent aircraft from the satellite integrated command center 810 to multiple response ground centers 802, and flight path prediction information from the response ground centers 802 to the satellite integrated command center 810.

[0060] Next, the communication route search device 811 provided in the satellite integrated command center 810 will be described.

[0061] <Function Example 1 of Communication Route Search Device 811> The communication route search device 811 acquires as input conditions the communication start time, position coordinates, and position coordinates of the other party to whom the airborne object information is to be transmitted. Based on these input conditions, the communication route search device 811 searches for an optimal route by stringing together satellite IDs that transmit the airborne object information. The communication route search device 811 generates a list of a series of satellite IDs and the predicted times when the satellite will transmit the airborne object information to the next satellite, and a command to issue a communication command to the group of communication satellites. Specifically, the communication route search device 811 searches for the optimal route for transmitting flying object information in the shortest time by analyzing the predicted error of the actual orbit of the communication satellite flight position relative to the planned orbit, the predicted time error when passing through specific position coordinates, the delay caused by information transmission, the satellite movement distance associated with the predicted error and delay time, and the relative position change of nearby passing satellites associated with satellite movement.

[0062] <Function Example 2 of Communication Route Search Device 811> The communication route search device 811 receives the launch detection signal from the monitoring satellite 307 as a communication start command and acquires as input conditions the position coordinates of the monitoring satellite 307 that emitted the launch detection signal, the position coordinates where the aerial vehicle launch was detected, and the field of view change range of the monitoring satellite. Based on these input conditions, the communication route search device 811 searches for an optimal route by stringing together satellite IDs that transmit aerial vehicle information. The communication route search device 811 generates a list of satellite IDs and the predicted times at which the satellite will transmit aerial vehicle information to the next satellite, as well as a command that issues a communication command to the group of communication satellites. The position coordinates of the aerial vehicle launch point are the position coordinates detected by the nadir monitoring device of the monitoring satellite that first detected the launch. Therefore, the "position coordinates of the monitoring satellite that emitted the launch detection signal and the position coordinates where the aerial vehicle launch was detected" are approximately close to each other. There is a difference due to the flight distance of the monitoring satellite, which depends on the time difference between the aerial vehicle launch detection and the emission of the launch detection signal. Specifically, the communication route search device 811 searches for a nearby passing monitoring satellite ID that can monitor the vicinity of the projectile launch point, including changes in field of view, and performs a search for the projectile information transmission time, the monitoring satellite ID, and the optimal route to transmit the projectile information to the monitoring satellite ID.

[0063] <Function Example 3 of Communication Route Search Device 811> The communication route search device 811 receives the launch detection signal from the monitoring satellite 307 as a communication start command and acquires as input conditions the position coordinates of the monitoring satellite 307 that issued the launch detection signal, the position coordinates where the missile launch was detected, the monitoring satellite's field of view change range, and the position coordinates of the monitoring satellite that issued the high-temperature detection signal, the position coordinates where the high-temperature object was detected, and the monitoring satellite's field of view change range among the nearby passing monitoring satellites that transmitted the missile information. Based on these input conditions, the communication route search device 811 searches for an optimal route by stringing together the satellite IDs that transmit the missile information. The communication route search device 811 generates a list of satellite IDs and the predicted times at which each satellite will transmit the missile information to the next satellite, as well as a command to issue a communication command to the communication satellite group. The "position coordinates of the monitoring satellite that issued the high-temperature detection signal and the position coordinates where the high-temperature object was detected" are detected by a rim monitoring device pointing toward the Earth's periphery. In this case, the position coordinates of the monitoring satellite and the position coordinates of the missile are extremely far apart. Specifically, the communication route search device 811 searches for a nearby passing monitoring satellite ID that can monitor the vicinity of the high-temperature object detection location, including changes in field of view, and performs a search for the time of flight object information transmission, the monitoring satellite ID, and the optimal route to transmit the flight object information to the monitoring satellite ID.

[0064] ***Description of the Function of this Embodiment*** In this embodiment, the flying object countermeasure system 401 includes a satellite integrated command center 810 for integrated management of both satellite systems, the monitoring system 404 and the satellite information transmission system 403, which is a communication system. After a monitoring satellite detects the launch of the flying object 601, it is necessary to transmit the position coordinates to a group of monitoring satellites flying nearby so that they can continue to acquire information on the flying object 601. According to the flying object response system 401 of this embodiment, a monitoring command can be given to the group of monitoring satellites via a communication satellite passing nearby.

[0065] In order to transmit information about a flying object from a monitoring satellite that has detected a launch to a response asset, it is necessary to search for the optimal route of the group of communication satellites that form a mesh communication network. For this reason, the flying object response system 401 according to this embodiment is equipped with a communication route search device 811. In addition, it is necessary to track and monitor the flight path of the flying object using multiple monitoring satellites and predict the flight direction. For this reason, the flying object response system 401 according to this embodiment is equipped with a flight path prediction device 803. Furthermore, assuming that response assets 801 are mobile objects deployed on land, sea, and air, as well as fixed ground assets, each response asset can be directly tasked under a centralized management system of the satellite integrated command center 810. However, in other cases, it is more reasonable to specify a response ground center 802, transmit aerial vehicle information in bulk, and then have the response ground center 802 assign tasks to each response asset 801.

[0066] In reality, since there are multiple response ground centers 802 scattered around, it is reasonable to select a response ground center 802 located in the direction of the predicted flight path of the flying object and transmit the flying object information to that center. For this reason, the flying object response system 401 according to this embodiment is equipped with a response asset selection device 804. Note that the response ground center 802 may also be a ship. It was also considered reasonable to transmit the initial detection information of the launch to all response ground centers 802 to alert them.

[0067] This section explains tracking of a missile by a constellation of surveillance satellites after its launch is detected. The launch detection position coordinates (x0, y0, z0) at time t0 when both the monitoring system 404 and the satellite information transmission system 403 detect the launch are taken as the position coordinates of the launch pad. At this time, the missile response system 401 must take into account the time delay before transmitting the launch detection information and issue a command to a monitoring satellite passing nearby to continue monitoring the missile via a communications satellite passing nearby the launch pad's position coordinates (x0, y0, z0) at transmission time t1. The monitoring satellite may be observing the launch pad from a distance, and the flight position coordinates of the monitoring satellite may differ from the launch pad's position coordinates (x0, y0, z0). Even for monitoring satellites passing nearby, the flight positions of the monitoring satellites that can monitor the vicinity of (x0, y0, z0) may be spread over a wide area due to the oblique observation. Therefore, the missile information transmission via communications satellite is sent to multiple monitoring satellites, and the monitoring satellite that detects a high-temperature object among them can track and monitor it. The flying object response system 401 further transmits the flying object information of the monitoring satellite that has acquired the tracking and monitoring information to a monitoring satellite that is passing nearby in the same manner, and repeats the operation of acquiring the next flying object information, thereby tracking the flying object. By arranging the position coordinates of the flying object tracked and monitored in chronological order, it becomes possible to predict the flying direction of the flying object, and this is defined as a function of the flight path prediction device 803. In the case of a ballistic missile, it is easy to predict the impact point of a missile flying on a ballistic trajectory, and the result is unique. On the other hand, with an HGV, it is difficult to predict the impact point because of the possibility of repeated intermittent firing, and only the flight path can be predicted. For this reason, the output of the flight path prediction device 803 is generated as a function of future time and position coordinates.

[0068] The spray generated during projectile launch is easily monitored because it is dispersed by the high-temperature atmosphere. On the other hand, the main body of the projectile in the post-boost phase after the injection has stopped has a small solid angle as seen from the monitoring satellite, and the temperature rise is not as pronounced as that of the plume. For this reason, there is a concern that the main body of the projectile in the post-boost phase after the injection has stopped may become indistinguishable if it is mixed with background land information. Therefore, a monitoring method called limb observation, which is aimed at the edge of the Earth, is used to monitor the main body of the projectile as it heats up against the background of deep space. This makes it possible to monitor the projectile without being drowned in noise. By integrating the projectile information detected by multiple monitoring satellites as a high-temperature target using a flight path prediction device and analyzing changes in position information over time, the projectile can be tracked and its flight path can be predicted.

[0069] Even if the HGV changes direction by intermittently re-injecting the jet mid-flight, it can be tracked by the flight path prediction device 803 and time-series information can be continuously acquired, making it possible to deal with the HGV. There are various means of response assets 801, such as aircraft, ships, and vehicles deployed on land, sea, and air, as well as ground-based facilities. There are also means of transmitting information directly to individual assets. However, when using a satellite information transmission system that is not dedicated to maintaining security, security restrictions may prevent the disclosure of location information for individual assets. Therefore, it is rational to aggregate information about flying objects at a response ground center, which receives commands to response assets, and to issue commands to response assets from the response ground center. For example, a mobile entity such as a ship with a dedicated communication line to the response assets may act as a response ground center.

[0070] ***Explanation of the effect of this embodiment*** In this embodiment, the flying object countermeasure system 401 is provided with an independent satellite integrated command center for integrated management of both the monitoring system and the communication system. The satellite integrated command center has both a surveillance satellite constellation and a communications satellite constellation under its umbrella, and can transmit commands that integrate surveillance and communications to operate and control both satellite constellations. After a surveillance satellite detects the launch of a missile, it needs to transmit its position coordinates to the surveillance satellite constellation flying nearby so that it can continue to obtain information on the missile. The satellite integrated command center can issue surveillance commands to the surveillance satellite constellation via communications satellites passing nearby.

[0071] Here, we will explain the hardware provided in the computers of each device, such as the satellite constellation forming system 600 that forms the satellite constellation 20, the ground facility 700, or each satellite 30. For example, we will explain using the ground facility 700 shown in Figure 2.

[0072] The processor 910 is a device that executes a program that realizes the functions of each device. The processor 910 is an integrated circuit (IC) that performs arithmetic processing. Specific examples of the processor 910 include a central processing unit (CPU), a digital signal processor (DSP), and a graphics processing unit (GPU).

[0073] The memory 921 is a storage device that temporarily stores data. Specific examples of the memory 921 include a static random access memory (SRAM) and a dynamic random access memory (DRAM). The auxiliary storage device 922 is a storage device that stores data. A specific example of the auxiliary storage device 922 is a HDD. The auxiliary storage device 922 may also be a portable storage medium such as an SD (registered trademark) memory card, CF, NAND flash, a flexible disk, an optical disk, a compact disk, a Blu-ray (registered trademark) disk, or a DVD. Note that HDD is an abbreviation for Hard Disk Drive. SD (registered trademark) is an abbreviation for Secure Digital. CF is an abbreviation for CompactFlash (registered trademark). DVD is an abbreviation for Digital Versatile Disk.

[0074] The input interface 930 is a port connected to an input device such as a mouse, a keyboard, or a touch panel. Specifically, the input interface 930 is a USB (Universal Serial Bus) terminal. Note that the input interface 930 may also be a port connected to a LAN (Local Area Network). The output interface 940 is a port to which a cable of a display device 941 such as a display is connected. Specifically, the output interface 940 is a USB terminal or an HDMI (registered trademark) (High Definition Multimedia Interface) terminal. Specifically, the display is an LCD (Liquid Crystal Display).

[0075] The communication device 950 includes a receiver and a transmitter, and is specifically a communication chip or a network interface card (NIC).

[0076] The programs that realize the functions of each device are loaded into the processor 910 and executed by the processor 910. The memory 921 stores not only the programs but also an OS (Operating System). The processor 910 executes the programs while running the OS. The programs and OS may be stored in an auxiliary storage device 922. The programs and OS stored in the auxiliary storage device 922 are loaded into the memory 921 and executed by the processor 910. Note that some or all of the programs that realize the functions of each device may be incorporated into the OS.

[0077] Each device may have multiple processors that replace the processor 910. These multiple processors share the task of executing a program. Each processor is a device that executes a program, just like the processor 910.

[0078] Data, information, signal values ​​and variable values ​​used, processed or output by the program are stored in memory 921, secondary storage device 922, or registers or cache memory within processor 910.

[0079] The "parts" of each device may be read as "processing," "procedure," "means," "steps," "circuitry," or "steps." Also, the "parts" of each device may be read as "program," "program product," or "computer-readable recording medium on which a program is recorded." "Processing," "procedure," "means," "steps," "circuitry," or "steps" may be read as interchangeable with each other.

[0080] Embodiment 2 In this embodiment, differences from and additions to the first embodiment will be mainly described. In this embodiment, components having the same functions as those in the first embodiment are given the same reference numerals, and the description thereof will be omitted.

[0081] In this embodiment, the function of the flight path prediction device 803 will be described with reference to FIG.

[0082] <Functional Example 1 of Flight Path Prediction Device 803> When a monitoring satellite 307 equipped with multiple monitoring devices detects a significantly high temperature object, the monitoring satellite 307 transmits the flying object information to a satellite integrated command center 810 via a satellite information transmission system 403 having multiple communication satellites 308. Here, the flying object information includes detection time information, a monitoring satellite ID, a monitoring device ID, and monitoring data. The satellite integrated command center 810 transmits this airborne object information to the response system 405, which is made up of the response asset 801 and the response ground center 802. Specifically, the satellite integrated command center 810 transmits this airborne object information to the response ground center 802. The flight path prediction device 803 derives the position information of the monitoring satellite with the ID at the time of detection in the flying object information, the direction of travel, and the line of sight direction of the monitoring device with the ID.The flight path prediction device 803 then extracts the high-temperature object brightness from the monitoring data and derives a line of sight vector pointing to the high-temperature object.

[0083] The flight path prediction device 803 arranges the line-of-sight vectors of high-temperature objects derived from the flying object information of multiple monitoring satellites 307 in chronological order in an Earth-fixed coordinate system, and predicts the position coordinates of the flying object over time using the principles of aerial triangulation.

[0084] When multiple flying objects are launched at short intervals, the flight path prediction device 803 integrates the flying object information obtained from multiple monitoring satellites 307 and determines that the flying objects whose paths have been predicted are multiple different flying objects.

[0085] In a monitoring device pointing toward the center of the earth, a bright spot detected in the center indicates the detection of the launch of a high-temperature object. This indicates that the launch point of the projectile is located directly below the monitoring satellite. By monitoring the flight position coordinates of the monitoring satellite at the time of launch detection, the position coordinates of the launch point can be derived. On the other hand, even with a monitoring device oriented toward the center of the earth, a bright spot of a high-temperature object detected away from the center of a wide monitoring field of view is far from the coordinates of the position directly below the monitoring satellite when converted into coordinates on the Earth's surface. Therefore, in order to derive the launch point of the flying object, the position coordinates and direction of travel of the monitoring satellite at the time of launch detection are confirmed, and the line-of-sight vector that captured the bright spot on the monitoring device is converted to derive the flying object position coordinates as the intersection of the line-of-sight vector originating from the monitoring satellite and the Earth's surface.

[0086] To predict the flight path of a projectile that continues firing immediately after launch detection, it is possible to track the projectile by integrating information from monitoring devices pointing toward the center of the earth that are equipped on monitoring satellites flying nearby. While the launch point on the Earth's surface can be derived from the spacecraft information of a single monitoring satellite, the position coordinates of a spacecraft flying in the air must be derived using the principle of aerial triangulation when viewed from multiple satellites.If two monitoring satellites with known position coordinates are simultaneously monitoring a spacecraft as a high-temperature target, the ID of the monitoring device can be converted into the line-of-sight vector for a bright spot in the field of view of the monitoring device, and the spacecraft's own position coordinates can be derived as the intersection of the line-of-sight vectors of the two monitoring satellites using the principle of aerial triangulation.

[0087] However, if there is a time difference between the monitoring timing of two monitoring satellites, an estimation is required to correct for the satellite movement resulting from that time difference. Furthermore, even if the line-of-sight vectors do not intersect due to an error factor, the error factor can be inversely estimated by assuming that the line-of-sight vectors intersect, assuming that the monitoring information is of the same flying object. Taking these uncertainties into account, the flying object trajectory prediction device integrates the flying object information obtained from multiple monitoring satellites and identifies its position using the principles of aerial triangulation. Furthermore, if the multiple monitoring satellites detect the high-temperature object at different times, the satellite movement is corrected for the time difference, and the flying object's position coordinates are predicted.

[0088] In a monitoring satellite equipped with a monitoring device pointing toward the Earth's rim for rim monitoring, the satellite's position coordinates that detected a high-temperature object and the position coordinates of the high-temperature object are far apart, and the distance cannot be determined without stereoscopic viewing. For this reason, the position coordinates of the same object are derived by integrating the information on the object from multiple monitoring satellites flying at different positions. Therefore, to predict the flight path of a projectile that continues firing immediately after launch detection, it is possible to track the projectile by integrating information from geocentric monitoring devices on nearby monitoring satellites. However, to stop firing and monitor the heated main body, high-resolution and high-sensitivity monitoring using deep space background through limb observation is required. Furthermore, to derive the projectile's position coordinates through aerial triangulation using multiple monitoring satellites, it is necessary to integrate the projectile information from multiple monitoring satellites flying at positions far from the position coordinates detected by launch. For this reason, the projectile information from all monitoring satellites that detected the hot object is integrated into a flight path prediction system, which derives the line-of-sight vector and inversely estimates error factors, and then derives the projectile's position coordinates.

[0089] Embodiment 3 In this embodiment, differences from the first and second embodiments and additional features to the first and second embodiments will be mainly described. In this embodiment, components having the same functions as those in the first and second embodiments are given the same reference numerals, and the description thereof will be omitted.

[0090] <Equatorial Satellite System 441> FIG. 10 is a diagram showing an example of an equatorial satellite system 441 according to this embodiment. The monitoring system 404 has a constellation of six or more equatorial monitoring satellites flying in equatorial orbits with the same mean orbital altitude. The constellation of equatorial satellites forms communication crosslinks with equatorial satellites flying ahead and behind in the same orbital plane. At least one or more of the equatorial satellites forms a communication crosslink with the countermeasure system 405 or a satellite integrated command center 810 equipped with a satellite information communication route search device 811. The monitoring system 404 transmits the flying object information to the response system 405 or the satellite integrated command center 810 without the intervention of the satellite information transmission system 403 .

[0091] The equatorial satellite system 441 is composed of a constellation of six or more equatorial monitoring satellites with the same mean orbital altitude, and forms communication crosslinks with equatorial satellites flying ahead and behind it. At least one or more equatorial satellites forms a communication crosslink with the countermeasure system 405 or the satellite integrated command center 810, which has a communication route search device for satellite information. The equatorial satellite then transmits orbital object information to the countermeasure system 405 or the satellite integrated command center 810.

[0092] The equatorial satellites constitute an equatorial satellite system 441 that transmits spacecraft information to the satellite integrated command center 810 .

[0093] In equatorial monitoring satellites, the nadir-looking monitoring device can comprehensively detect the launch of flying objects launched from near the equator. The high-temperature spray generated by the launch, called the plume, is hot and spreads over a wide area, making it detectable even against a background of ground or land. However, the post-boost phase projectile is difficult to track because it is not as hot as the plume and has a small solid angle, making it necessary to monitor the heated main body. In contrast, limb observations, which monitor the Earth's periphery, allow for the monitoring of projectiles flying over the mid-latitudes against the background of deep space, making it possible to monitor the temperature rise of the HGV itself during the post-boost phase.

[0094] By forming communication crosslinks with satellites in front and behind the same orbital plane, satellites above the equator can communicate simultaneously in a circular pattern with all satellites in the orbital plane. This has the effect of transmitting monitoring information about flying objects to a response system or ground system (satellite integrated command center, integrated control center, monitoring ground center, etc.) without the need for a separate satellite information transmission system.

[0095] Embodiment 4 In this embodiment, differences from the first to third embodiments and additional features to the first to third embodiments will be mainly described. In this embodiment, components having the same functions as those in the first to third embodiments are given the same reference numerals, and the description thereof will be omitted.

[0096] <Polar Orbiting Satellite System 442> FIG. 11 is a diagram showing an example of a polar-orbiting satellite system 442 according to this embodiment. The monitoring system 404 has a constellation of six or more polar-orbiting satellites that fly in polar orbits with the same orbital plane and equal mean orbital altitude. The polar-orbiting satellites form communication crosslinks with polar-orbiting satellites flying ahead and behind them. At least one or more polar-orbiting satellites form communication crosslinks with the countermeasure system 405 or a satellite integrated command center 810 that has a satellite information communication route search device 811. The monitoring system 404 transmits the flying object information to the response system 405 or the satellite integrated command center 810 without the intervention of the satellite information transmission system 403 .

[0097] The polar orbiting satellite system 442 is composed of a constellation of six or more polar orbit monitoring satellites with the same average orbital altitude in the same orbital plane, and forms communication crosslinks with polar orbiting satellites flying ahead and behind. At least one or more polar orbiting satellites forms a communication crosslink with the countermeasure system 405 or the satellite integrated command center 810, which has a communication route search device for satellite information. The polar orbiting satellite then transmits spacecraft information to the countermeasure system 405 or the satellite integrated command center 810.

[0098] The polar orbiting satellites constitute a polar orbiting satellite system 442 that transmits spacecraft information to the satellite integrated command center 810 .

[0099] Polar-orbiting satellites pass through the polar regions on every orbit, making it possible to comprehensively monitor high-latitude regions near the polar regions using only a group of satellites formed in a single orbital plane. In polar-orbiting monitoring satellites, the nadir-looking monitoring device can comprehensively detect the launch of flying objects launched from high-latitude regions near the polar regions. Furthermore, the high-temperature spray generated during launch, known as the plume, is hot and spreads over a wide area, making it detectable without being lost in noise, even against a land-based background. However, since it is necessary to monitor the heated projectile during the post-boost phase, tracking is difficult because the projectile is not as hot as the plume and has a small solid angle. In contrast, limb observation, which monitors the Earth's periphery, allows for monitoring projectiles flying far from the polar orbital plane against a deep space background, making it possible to monitor the temperature rise of the HGV's body during the post-boost phase.

[0100] Polar satellites can form communication crosslinks with satellites in front and behind them in the same orbital plane, enabling simultaneous communication among all satellites in the orbital plane in a circular fashion. This has the effect of transmitting monitoring information about flying objects to response systems or ground systems (satellite integrated command center, integrated control center, monitoring ground center, etc.) without the need for a separate satellite information transmission system.

[0101] Embodiment 5. In this embodiment, differences from the first to fourth embodiments and additional features to the first to fourth embodiments will be mainly described. In this embodiment, components having the same functions as those in the first to fourth embodiments are given the same reference numerals, and the description thereof will be omitted.

[0102] <Inclined Orbit Satellite System 443> FIG. 12 is a diagram showing an example of an inclined orbit satellite system 443 according to this embodiment. The monitoring satellite 307 constituting the monitoring system 404 is equipped with a monitoring device and a communication device pointing forward and backward, and flies between communication satellites at the same orbital altitude and in the same orbital plane as the communication system, forming communication crosslinks with the communication satellites in front and behind it. Here, the communication system is, for example, a satellite information transmission system. The monitoring system 404 transmits monitoring information of the flying object to the response system 405 or the satellite integrated command center 810 via a satellite information transmission system 403 included in the flying object response system 401.

[0103] The inclined orbit satellite system 443 is composed of a group of communication satellites flying in inclined orbits and multiple monitoring satellites in the satellite information transmission system 403. In the inclined orbit satellite system 443, the monitoring satellite is equipped with a monitoring device and a communication device pointing forward and backward, and flies between communication satellites at the same orbital altitude and in the same orbital plane as the communication satellites, forming communication crosslinks with the communication satellites before and after it.

[0104] The inclined orbit satellites constitute an inclined orbit satellite system 443 as described above.

[0105] Inclined orbit satellites provide communication and monitoring services in addition to high-latitude areas such as the polar regions (rim observations can also monitor the polar regions), and their advantage is that they can cover a wide area across the entire Earth. However, if the monitoring system and communication system are each composed of satellites in inclined orbits, the flight positions of all satellites change from moment to moment. Therefore, when transmitting information from the monitoring satellites via the communication system, it is necessary to determine the communication path at the time of transmission for each satellite ID, which creates the problem of making commands to the satellites cumbersome. Therefore, a monitoring satellite is inserted between the two satellites in the same orbital plane, where a communication crosslink has been established, and the communication crosslink between the two satellites is reconfigured. This configuration maintains a circular communication environment within the same orbital plane, and transmits monitoring information directly to the communication line. This eliminates the need for communication route searches for each satellite ID, which has the effect of eliminating the need for complicated commands. Furthermore, if the preceding and succeeding satellites form communication crosslinks with adjacent orbits, information transmission between adjacent orbits will be possible immediately.

[0106] Embodiment 6 In this embodiment, differences from the first to fifth embodiments and additional features to the first to fifth embodiments will be mainly described. In this embodiment, components having the same functions as those in the first to fifth embodiments are given the same reference numerals, and the description thereof will be omitted.

[0107] <Integrated Data Library 820> FIG. 13 is a diagram showing an example of the configuration of a flying object handling system 401 according to this embodiment. FIG. 14 is a diagram showing an example of the configuration of the integrated data library 820 according to this embodiment.

[0108] The integrated data library 820 in this embodiment is a library referenced by all or part of the monitoring system 404, satellite information transmission system 403, response system 405, satellite integrated command center 810, and response ground center 802 that constitute the flying object response system 401.

[0109] The integrated data library 820 includes a database 821 that stores all or some of the following information: -Trajectory information of the monitoring system 404 Orbital information of the Satellite Information Transmission System 403 Location information of the response system 405 A typical multiple flight path model in which the flight path is modeled using the launch position coordinates of the projectile, flight direction, and time-series flight distance and flight altitude profile from launch to impact.

[0110] With the recent diversification of threats and surveillance, communication, and response systems, there is an increasing need for JADC2, which allows various ground centers to operate using a common database. JADC2 is also known as Joint All Domain Command & Control. Ground center can be read as domain. The commonly used database can be used as a Unified Data Library (UDL) in a cloud or edge computing environment, allowing information to be shared among various ground centers. UDL is an abbreviation for Unified Data Library. Furthermore, a space data center concept using satellite IoT has also been proposed. According to the space data center concept, it will be possible to share information in a space data center in the same way as described above. IoT is an abbreviation for Internet of Things.

[0111] <Satellite with Edge Server 830> FIG. 15 is a diagram showing an example of the configuration of an equatorial satellite 341 equipped with an edge server 830 according to this embodiment. FIG. 16 is a diagram showing an example of the configuration of a polar orbiting satellite 342 equipped with an edge server 830 according to this embodiment.

[0112] The equatorial satellite 341 or polar orbiting satellite 342 according to this embodiment includes an edge server 830 having a database 822 that stores all or part of the following information: -Trajectory information of the monitoring system 404 Location information of the response system 405 A typical multiple flight path model in which the flight path is modeled using the launch position coordinates of the projectile, flight direction, and time-series flight distance and flight altitude profile from launch to impact.

[0113] FIG. 17 is a diagram showing an example of the configuration of an inclined orbit satellite 343 equipped with an edge server 830 according to this embodiment.

[0114] The inclined orbit satellite 343 according to this embodiment includes an edge server 830 that includes a database 822 that stores all or part of the following information: -Trajectory information of the monitoring system 404 Orbital information of the Satellite Information Transmission System 403 Location information of the response system 405 A typical multiple flight path model in which the flight path is modeled using the launch position coordinates of the projectile, flight direction, and time-series flight distance and flight altitude profile from launch to impact.

[0115] Each of the above-mentioned equatorial satellites 341, polar orbit satellites 342, and inclined orbit satellites 343 is equipped with an AI computer 840 that autonomously determines the transmission destination of the acquired flying object information by referring to the database 822 of the edge server 830. AI is an abbreviation for artificial intelligence.

[0116] <Cloud Computing> Explain cloud computing in space. As the amount of information increases with the advancement of the information society, the increase in power consumption and heat dissipation measures have become issues. In particular, in centralized systems, the increase in power consumption and heat dissipation measures for supercomputers and large-scale data centers have become serious issues. Meanwhile, in space, heat can be released into deep space through radiative cooling. In space cloud computing, a supercomputer or data center to realize the cloud environment is placed on the satellite constellation side. After processing is performed in orbit, only the necessary data is transmitted to users on Earth. This has the effect of maintaining the cloud environment and reducing greenhouse gas emissions, thereby contributing to the SDGs on Earth.

[0117] Edge Computing Explain edge computing in space. Edge computing, which places edge servers on the IoT side, is attracting attention as a method for realizing a distributed architecture. In IoT, data collected by sensors is typically sent to the cloud via the internet for analysis using a centralized system. In contrast, edge computing uses a system in which data processing is distributed to the device itself or to edge servers installed between the device and the cloud. This enables real-time, low-load data processing. Furthermore, with the increasing volume of information that accompanies the advancement of the information society, the increase in power consumption and heat dissipation measures have become issues. In particular, in centralized systems, the increasing power consumption and heat dissipation measures of supercomputers and large-scale data centers have become serious issues.

[0118] Meanwhile, in space, heat can be released into deep space through radiative cooling. In edge computing in space, satellites are treated as IoT devices, with edge servers located on the satellite constellation side. After performing distributed computing processing in orbit, only the necessary data is transmitted to the ground. With the hybrid constellation described below, information is exchanged with a cloud equipped with a data center at ground facilities via a circular or mesh communication network. This has the effect of achieving low latency and centralized data management.

[0119] <Artificial intelligence AI> Explain AI in space. AI neural networks can be divided into supervised learning, in which they are optimized for problems by inputting a teacher signal (correct answer), and unsupervised learning, which does not require a teacher signal. The system is trained in advance using training models based on the type of projectile, type of propellant, and a number of typical flight patterns. This makes it easier and faster to infer from the actual measurement data obtained by detecting launches and acquiring trajectory information. As a result of this inference, the projectile's trajectory and landing position are predicted. However, in order to predict the flight path of a flying object whose flight direction is unknown during the launch detection stage, it is necessary for subsequent monitoring satellites to track and monitor the flying object. Also, in order to transmit the launch detection information to the subsequent monitoring satellites, the launch detection information must be transmitted via a communications network formed by a constellation of communications satellites. In a communications network using a communications satellite constellation, the flight positions of the communications satellites change constantly. For this reason, it is necessary to search for the optimal communication route and determine the ID of the communications satellite that will exchange information about the satellite, as well as the time of transmission and reception. This situation is also true for the exchange of information about satellites between monitoring satellites and communications satellites. When optimal route search is performed by a ground system, it is necessary to send commands to the monitoring satellite and communication satellite, including the time to send and receive information about the flying object and the satellite ID. However, the communication network for sending these commands poses a challenge.

[0120] Therefore, it would be rational for communication satellites to be equipped with AI-based analytical devices, search for optimal routes in orbit, and generate and communicate commands in orbit to communication satellites that make up the communication route. An effective method for searching for the optimal route in orbit is to use an algorithm known as the Dijkstra algorithm. Note that the weighting for each route does not change in the static Dijkstra algorithm. However, in a communication network formed by a communication satellite constellation, the weighting for each route changes at each time due to changes in the flight position of the communication satellite. Therefore, for each communication satellite that performs the optimal route search while updating its orbital information, the communication satellite that receives the flight information performs the optimal route search and transmits the flight information to the next communication satellite, and this operation is repeated.

[0121] In addition, there are known two methods for route search: breadth-first search and depth-first search. For launch detection information, breadth-first search prioritizes transmitting information about the missile to the communication network as quickly as possible, and once tracking is repeated by subsequent satellites and the flight direction can be roughly estimated, it is rational to perform depth-first search.

[0122] In the flying object tracking system, the flying object is tracked and monitored by repeating the above-mentioned machine learning flight path prediction and Dijkstra's algorithm route search, and the final landing position is inferred.

[0123] Furthermore, after repeated tracking of flying objects, machine learning is performed on past tracking results, and deep learning is performed on examples of flying object behavior that differ from the multiple flying object models used as training models. This makes it possible to improve the accuracy and speed up predictions of flying object trajectories.

[0124] Since the flight direction and distance of projectiles launched from a mobile launch platform (TEL) rather than a fixed launch platform differ from typical flight models, it is effective to supplement the trajectory model with deep learning on actual measurement data.

[0125] <Hybrid Constellation 401a> FIG. 18 is a diagram showing an example of the configuration of hybrid constellation 401a according to this embodiment. The hybrid constellation 401a is a satellite constellation that constitutes the anti-missile system 401. In the hybrid constellation 401a, multiple satellites equipped with communication devices for communicating with satellites in front and behind in the direction of travel in the same orbital plane form a communication constellation that forms a circular communication network. Furthermore, in the hybrid constellation 401a, a monitoring satellite equipped with communication devices for communicating with satellites in front and behind flies between the multiple satellites that form the communication constellation. The monitoring satellite and the multiple satellites that form the communication constellation reconstruct a circular communication network or a mesh-like communication network that includes adjacent orbits, forming a hybrid constellation of monitoring and communication.

[0126] A hybrid constellation is a constellation that realizes multiple missions, including both non-communication missions such as observation or positioning and communication missions. For example, a communication satellite that forms a communication network may simultaneously carry equipment for non-communication missions such as observation or positioning. Also, a satellite other than a communication satellite, such as an observation satellite or a positioning satellite, may simultaneously carry communication equipment that plays a part in the communication network. Information can be exchanged between ground facilities and the hybrid constellation via a circular or mesh communication network. This also has the effect of enabling low-latency centralized data management for each satellite that makes up the hybrid constellation and distributed computing, which is considered IoT.

[0127] In a hybrid constellation, for example, some of the functions of a cloud data center that was previously installed on the ground are installed on a satellite as a space data center. Processing is then performed in orbit, and only the processing results are transmitted to ground facilities. This has the effect of contributing to reducing the burden of ground processing. For example, orbital information for individual communication satellites that make up a communication satellite constellation is aggregated in a space data center, which then searches for the shortest route when transmitting information via a circular or mesh communication network formed by the communication satellite constellation. Compared to a system where orbital information is collected, transmitted from the satellite to the ground, and then analyzed and evaluated on the ground before being transmitted back to the satellite, a hybrid constellation can handle this processing autonomously in space, thereby reducing the amount of data and the burden on ground processing.

[0128] Of the above-described first to sixth embodiments, a combination of two or more parts may be implemented. Alternatively, a single part of these embodiments may be implemented. In addition, any combination of these embodiments may be implemented, either as a whole or in part. That is, in the first to sixth embodiments, any part of the first to sixth embodiments can be freely combined, or any component can be modified, or any component can be omitted from the first to sixth embodiments.

[0129] It should be noted that the above-described embodiments are essentially preferred examples and are not intended to limit the scope of the present disclosure, the scope of application of the present disclosure, and the scope of use of the present disclosure. The above-described embodiments can be modified in various ways as necessary. [Explanation of symbols]

[0130] 11,11b Satellite constellation formation unit, 20 Satellite constellation, 21 Orbital plane, 30 Satellite, 31 Satellite control unit, 32 Communication equipment, 33 Propulsion unit, 34 Attitude control unit, 35 Power supply unit, 36 Monitoring equipment, 55 Orbit control command, 307 Monitoring satellite, 308 Communication satellite, 401 Aircraft countermeasure system, 403 Satellite information transmission system, 404 Monitoring system, 405 Countermeasure system, 441 Equatorial satellite system, 442 Polar orbit satellite system, 443 Inclined orbit satellite system, 510 Orbit control command generation unit, 520 Analysis and prediction unit, 601 Aircraft, 600 Satellite constellation formation system, 700 Ground equipment, 801 Countermeasure asset, 802 Countermeasure ground center, 803 Flight path prediction device, 804 Countermeasure asset selection device, 810 Satellite integrated command center, 811 Communication route search device, 910 processor, 921 memory, 922 auxiliary storage device, 930 input interface, 940 output interface, 941 display device, 950 communication device, 341 equatorial satellite, 342 polar orbit satellite, 343 inclined orbit satellite, 401a hybrid constellation, 820 integrated data library, 821, 822 database, 830 edge server, 840 AI computer.

Claims

1. A flying object countermeasure system that detects a flying object by infrared rays and tracks the flying object, which enters the atmosphere during the gliding phase by repeatedly intermittently injecting and whose temperature rises due to atmospheric friction, a monitoring system having a monitoring satellite constellation of multiple monitoring satellites each having a monitoring device and a communication device; a satellite information transmission system having a constellation of communication satellites, which are a plurality of communication satellites each having a communication device; and a countermeasure system having land, sea, and air countermeasure assets for countering flying objects; It is composed of In a flying object countermeasure system, the monitoring system monitors flying objects and generates flying object information, and transmits the generated flying object information to the countermeasure system via the satellite information transmission system, a satellite integrated command center equipped with a satellite information communication route search device; The satellite integrated command center a communication route search device for the satellite information that generates a list enumerating a series of communication satellite IDs of the communication satellite group and monitoring satellite IDs of the monitoring satellite group, and predicted times at which the communication satellites and monitoring satellites will transmit flying object information to the next communication satellite and monitoring satellite, and a command that issues a communication command to the communication satellite group; The communication route search device Searching for a monitoring satellite ID of a monitoring satellite that can monitor the vicinity of the launch point of the flying object, including changing the field of view, and searching for the flying object information transmission time, the monitoring satellite ID, and the optimal route for transmitting the flying object information to the monitoring satellite ID; The satellite integrated command center transmitting a command to the group of monitoring satellites and the group of communication satellites based on the communication route searched by the communication route search device, and giving a monitoring command to the group of monitoring satellites via a communication satellite passing nearby, thereby tracking and monitoring the flying object; Projectile countermeasure system.

2. the monitoring system, The system has a plurality of monitoring satellites equipped with infrared monitoring devices, which detect the plume at the time of launch of a flying object and the flying object flying with an increased temperature as high-temperature objects, and transmits time information and position information as flying object information.

2. The projectile protection system according to claim 1.

3. The communication satellites included in the satellite information transmission system are Cross-linking with communication devices to form a communication network, The satellite integrated command center: The communication route search device searches for the shortest route for transmitting information, Sending information transmission commands to the communication satellite that serves as the communication path, 3. The flying object countermeasure system according to claim 1 or 2.

4. After the monitoring satellite A of the monitoring system detects the launch of a flying object, The satellite integrated command center:

4. The flying object handling system according to claim 1, wherein the launch time and position coordinates of the flying object are transmitted to the handling system as flying object information.

5. The satellite integrated command center: The communication route search device searches for the shortest route in the communication network from the position coordinates at which the monitoring satellite A issued the flying object information to the position coordinates of the response system, and transmits an information transmission command to a group of communication satellites on the communication path; A group of communications satellites in the communication path, 5. The flying object countermeasure system according to claim 1, wherein the launch time and position coordinates of the flying object are transmitted as flying object information to the countermeasure system based on an information transmission command.

6. The satellite integrated command center: After the launch of the projectile, the group of monitoring satellites flying around the monitoring satellite A will: Transmitting flying object information via the satellite information transmission system; After monitoring device B detects a high temperature object, The communication route search device searches for the shortest route in the communication network from the position coordinates of the monitoring satellite B to the position coordinates of the response system, Send an information transmission command to a group of communication satellites on the communication path, A group of communications satellites in the communication path, 6. The flying object handling system according to claim 1, wherein the detection time, position coordinates, and brightness information of the high-temperature object are transmitted as flying object information to the handling system based on an information transmission command.

7. The satellite integrated command center: For the group of monitoring satellites flying near monitoring satellite B, Transmitting the flying object information via the satellite information transmission system; When monitoring satellite C detects a high-temperature object, The communication route search device searches for the shortest route in the communication network from the position coordinates of the monitoring satellite C to the position coordinates of the response system, Send an information transmission command to the group of communication satellites on the communication path, A group of communications satellites in the communication path, 7. The flying object countermeasure system according to claim 6, wherein the detection time, position coordinates and brightness information of the high temperature object are transmitted as flying object information to the countermeasure system based on an information transmission command.

8. The satellite integrated command center: For the group of monitoring satellites flying near the monitoring satellite N, Transmitting the flying object information via the satellite information transmission system; When monitoring device N+1 detects a high temperature object, The communication route search device searches for the shortest route in the communication network from the position coordinates of the monitoring satellite N+1 to the position coordinates of the response system, Send an information transmission command to the group of communication satellites on the communication path, A group of communications satellites in the communication path, 8. The flying object countermeasure system according to claim 7, wherein the detection time, position coordinates and brightness information of the high temperature object are transmitted as flying object information to the countermeasure system based on an information transmission command.

9. The response system comprises: It consists of multiple response assets and a response ground center. The response ground center: A flying object response system as described in any one of claims 1 to 8, comprising a flight path prediction device, and generating flight path prediction information consisting of future time and position information based on the transition of time-series position information of the flying object information received from the monitoring system.

10. The response ground center: A countermeasure asset selection device is provided, which is connected to the countermeasure asset via a communication line; 10. A flying object countermeasure system according to claim 9, which selects a countermeasure asset located near the position coordinates where the flying object is predicted to pass or arrive based on flight path prediction information, and transmits a command signal for countermeasure action.

11. The flight path prediction device After the monitoring satellite A transmits the launch detection information, the direction of movement of the flying object is predicted based on the position coordinates of the monitoring satellite B, C, N, or N+1 that detected the high-temperature object, and flight path prediction information is generated. The projectile protection system according to claim 10.

12. The countermeasure asset selection device, Selecting a response asset located near the flight path prediction information from among multiple response assets with different location coordinates, The response ground center: Transmitting missile information and countermeasure action commands to response assets; 12. The projectile protection system according to claim 11.

13. The response system comprises: There are multiple ground response centers with different location coordinates, The satellite integrated command center:

13. The system for dealing with a flying object according to claim 1, wherein the monitoring satellite A transmits information about the flying object that has been launched and detected to all of the ground centers for dealing with the flying object.

14. All or some of the plurality of ground response centers are equipped with a flight path prediction device that generates flight path prediction information; The flight path prediction device Transmitting flight path prediction information to the satellite integrated command center via the satellite information transmission system or a terrestrial communication line; The satellite integrated command center: transmitting the flying object information to a ground center located near the flight path prediction information generated by the flight path prediction device; 14. The projectile protection system according to claim 13.

15. A satellite integrated command center included in the flying object countermeasure system according to any one of claims 1 to 14.

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