JP7394801B2 - Gliding flying object tracking method, flying object tracking system, flying object countermeasure system, and ground system - Google Patents

Description

The present disclosure relates to a gliding projectile tracking method, a projectile tracking system, a projectile countermeasure system, and a ground system.

In recent years, with the advent of flying objects that glide at supersonic speeds, there are expectations for satellite monitoring such as detecting the launch of flying objects, tracking their flight paths, and predicting their landing positions.
As a means of detecting and tracking a flying object during its gliding stage, it is seen as promising to use infrared light to detect the temperature rise caused by atmospheric friction when a flying object enters the atmosphere. Additionally, monitoring from a group of low-orbit satellites is considered to be a promising means of detecting flying objects in the gliding stage using infrared light.

Patent Document 1 discloses a monitoring satellite for comprehensively monitoring an area at a specific latitude within the entire spherical surface of the earth with a small number of satellites orbiting in a low orbit.

Japanese Patent Application Publication No. 2008-137439

In monitoring from a low earth orbit (LEO), the distance from an artificial satellite to a flying object is shorter than monitoring from a geostationary orbit. Monitoring satellites in low orbit are also called LEO satellites. Therefore, it is possible to improve the detection performance using infrared rays. On the other hand, a huge number of satellites are required to constantly monitor and maintain communication lines using LEO satellites. Furthermore, unlike geostationary satellites that appear almost fixed relative to the earth-fixed coordinate system, the flight position of LEO satellites changes from time to time, so there is a method of data transmission between a group of monitoring equipment equipped with infrared monitoring equipment and a group of communication satellites. becomes an issue.

In addition, a new threat has emerged with the appearance of a flying object called HGV (Hypersonic Glide Vehicle), which intermittently ejects fuel to change its flight path during flight. In order to track a flying object that has stopped ejecting, it is necessary to detect the temperature of the flying object's body, which has risen in temperature, which requires high-resolution and highly sensitive infrared monitoring.

In the case of a gliding flying object that is intermittently ejected, the present disclosure provides information on the flying object launched and detected by a monitoring satellite and tracked by a subsequent monitoring satellite via a communication network consisting of communication satellites in low orbit. The purpose of the present invention is to provide a method for tracking flying objects.

The gliding flying object tracking method according to the present disclosure includes:
A ground system analyzes airborne object monitoring information obtained by a satellite constellation consisting of multiple monitoring satellites equipped with infrared monitoring equipment and flying in low orbit.
A method for tracking a gliding flying object that glides after lowering its orbital altitude to above the atmosphere after launch, the method comprising:
The monitoring satellite is
a first infrared monitoring device oriented toward the geocenter;
a second infrared monitoring device oriented toward the Earth's periphery;
Equipped with
Detecting high-temperature spray accompanying the projectile launch by the first infrared monitoring device and using it as a starting point for a flight path model;
The second infrared monitoring device detects the body of the flying object whose temperature has increased after the injection is completed in the space background,
The ground system includes:
It models the flight path consisting of the launch position coordinates of the projectile, the flight direction, and the time-series flight distance and flight altitude profile from launch to impact, and is equipped with a database that stores multiple typical flight path models. ,
Using the projectile launch detection information detected by the infrared monitoring device as a starting point, a subsequent monitoring satellite whose flight path can be monitored at the predicted time is selected from a plurality of flight path models, and from the monitoring satellite whose launch was detected, Transmits information to the selected subsequent monitoring satellite,
A monitoring satellite with a line-of-sight vector in the north-south direction looks at the main body of the projectile after injection.
Measures the passing time, longitude, and altitude information of the flying object,
A surveillance satellite with a line of sight vector in the east-west direction
Measuring the passing time, latitude, and altitude information of the flying object,
The ground system includes:
Evaluate the deviation between the flight path model and the actual trajectory and correct the flight path model.
Aircraft monitoring will continue with the next follow-on monitoring satellite.

According to the gliding projectile tracking method according to the present disclosure, when the projectile is a gliding projectile that is intermittently ejected, the projectile information launched and detected by a monitoring satellite is sent via a communication network consisting of communication satellites in low orbit. and can be tracked by subsequent monitoring satellites.

FIG. 2 is a diagram illustrating an example of a satellite constellation having multiple orbital planes that intersect in non-polar regions. 1 is a diagram showing a configuration example of a satellite constellation formation system according to Embodiment 1. FIG. 1 is a diagram illustrating an example of a configuration of satellites in a satellite constellation according to Embodiment 1. FIG. 7 is a diagram illustrating another example of the configuration of satellites in the satellite constellation according to the first embodiment. FIG. 1 is a diagram illustrating a configuration example of ground equipment included in the satellite constellation formation system according to Embodiment 1. FIG. 1 is a diagram showing an example of a functional configuration of a satellite constellation forming system according to Embodiment 1. FIG. FIG. 3 is a diagram illustrating a configuration example of space object information according to the first embodiment. FIG. 3 is a diagram illustrating a configuration example of trajectory forecast information according to Embodiment 1. FIG. 1 is a diagram illustrating a configuration example of a flying object handling system and a flying object tracking system according to Embodiment 1. FIG. FIG. 3 is a diagram illustrating an example of a flight path model of the distance from the launch area to the landing area of a flying object and the flight direction. A diagram showing an example of a flight path model of a ballistic flying object. The figure which shows the example of a flight path model of an intermittent injection flying object. The figure which shows the comparative example of the flight path model of a suborbital flying object, and the flight path model of an intermittent injection flying object. A diagram showing rim observation in which a monitoring satellite near the equator monitors a ballistic trajectory from the side. A diagram showing rim observation monitored by a monitoring satellite near the northernmost tip of an inclined orbit from the flight direction from the launch area to the impact area. FIG. 7 is a diagram illustrating an example of a gliding flying object identification method according to a second embodiment. FIG. 7 is a diagram showing an example of a gliding flying object tracking method according to Embodiment 3; 6 is a diagram illustrating an example of a gliding flying object tracking method according to Embodiment 4. FIG. FIG. 2 is a schematic diagram showing an example of a time-series information transmission order in a flying object handling system and a flying object tracking system. FIG. 3 is a diagram showing an example 1 of the time-series information transmission order of the flying object countermeasure system. FIG. 3 is a diagram illustrating a second example of the time-series information transmission order of the flying object countermeasure system. FIG. 7 is a diagram illustrating a third example of the time-series information transmission order of the flying object countermeasure system.

Embodiments of the present disclosure will be described below with reference to the drawings. In each figure, the same or corresponding parts are denoted by the same reference numerals. In the description of the embodiments, the description of the same or corresponding parts will be omitted or simplified as appropriate. Further, in the following drawings, the size relationship of each component may differ from the actual one. In addition, in the description of the embodiments, when directions or positions such as "top", "bottom", "left", "right", "front", "rear", "front", "back" are indicated There is. These notations are only described as such for the convenience of explanation, and do not limit the arrangement or orientation of components such as devices, instruments, or parts.

Embodiment 1.
In this embodiment, a flying object countermeasure system is constructed of a monitoring system having a plurality of monitoring satellites, a satellite information transmission system having a plurality of communication satellites, and a countermeasure system having land, sea, and air countermeasure assets for dealing with flying objects. The system 401 will be explained. Also, a flying object tracking system 406 that is configured by the above-mentioned monitoring system and satellite information transmission system will be explained.

For example, there is a projectile countermeasure system that detects the spray (plume) when a projectile is launched using an infrared observation device mounted on a geostationary orbit satellite, predicts impact based on movement information from the initial stage of flight, and responds with a countermeasure system. exist.
The spray during launch spreads extremely hot gas over a wide area, so it could be detected even by monitoring from geostationary orbit.

However, recently, a flying vehicle called HGV, which intermittently ejects fuel to change its flight path during flight, has appeared, posing a new threat. In order to track a flying object that has stopped ejecting, it is necessary to detect the temperature of the flying object's body, which has risen in temperature, which requires high-resolution and highly sensitive infrared monitoring.

Therefore, low earth orbit (LEO) satellite constellations are expected to provide a surveillance system that monitors flying objects from a much closer distance than in geostationary orbit. There is a long-awaited system for constantly monitoring LEO satellite constellations and immediately transmitting information to response assets after a projectile launch is detected.

A huge number of satellites are required for constant monitoring and communication line maintenance using LEO satellites. Furthermore, unlike geostationary satellites that appear almost fixed relative to the earth-fixed coordinate system, LEO satellites change their flight position from time to time. A mechanism for transmission method is required.

In addition to a monitoring system having a monitoring satellite group equipped with such an infrared monitoring device, a satellite information transmission system in which a group of communication satellites forms a mesh-like satellite constellation communication network is expected. This satellite information transmission system is used to detect a projectile launch and provide a means for transmitting projectile information to a countermeasure system in near real time. It is called near real-time because it takes into account the time delay that contributes to information transmission and the waiting time until the satellite can send and receive information at the fastest timing.

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

In the satellite constellation 20 of FIG. 1, a plurality of satellites 30 are flying at the same altitude in the same orbital plane. The satellite 30 is also called an artificial satellite.
In the satellite constellation 20 of FIG. 1, the orbital inclination angle of each orbital plane 21 of the plurality of orbital planes is not approximately 90 degrees, and each orbital plane 21 of the plurality of orbital planes exists in a different plane from each other. 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 points of a plurality of orbital planes whose orbital inclination angle is more than 90 degrees move away from the polar region according to the orbital inclination angle. Furthermore, depending on the combination of orbital planes, there is a possibility that the orbital planes intersect at various positions including near the equator.
In addition to the satellite constellation 20 shown in Figure 1, there is also a satellite constellation in which the orbital inclination angle of each orbital plane is approximately 90 degrees, and the plurality of orbital planes intersect near the polar regions. .

An example of the satellite 30 and ground equipment 700 in the satellite constellation formation system 600 that forms the satellite constellation 20 will be described using FIGS. 2 to 6. Satellite constellation formation system 600 is sometimes simply referred to as a satellite constellation.

FIG. 2 shows a configuration example of a satellite constellation formation system 600.
Satellite constellation formation system 600 includes a computer. Although FIG. 2 shows the configuration of one computer, in reality, each satellite 30 of the plurality of satellites configuring the satellite constellation 20 and each ground facility 700 that communicates with the satellite 30 are equipped with a computer. It will be done. Then, computers provided in each of the plurality of satellites 30 and each of the ground equipment 700 that communicates with the satellites 30 cooperate to realize the functions of the satellite constellation forming system 600. An example of the configuration of a computer that implements the functions of the satellite constellation formation system 600 will be described below.

Satellite constellation formation system 600 includes satellite 30 and ground equipment 700. Satellite 30 includes a communication device 32 that communicates with communication device 950 of ground facility 700 . FIG. 2 illustrates the communication device 32 among the components included in the satellite 30.

Satellite constellation formation system 600 includes a processor 910 and other hardware such as memory 921, auxiliary storage 922, input interface 930, output interface 940, and communication device 950. Processor 910 is connected to other hardware via signal lines and controls these other hardware.

Satellite constellation formation system 600 includes satellite constellation formation section 11 as a functional element. The functions of the satellite constellation forming section 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.

FIG. 3 is an example of the configuration of the satellite 30 of the satellite constellation formation system 600.
The satellite 30 includes a satellite control device 31, a communication device 32, a propulsion device 33, an attitude control device 34, and a power supply device 35. In addition, the satellite control device 31, the communication device 32, the propulsion device 33, the attitude control device 34, and the power supply device 35 will be explained in FIG. Satellite 30 of FIG. 3 is an example of a communications satellite 308 that includes communications equipment 32. Satellite 30 of FIG.

The satellite control device 31 is a computer that controls the propulsion device 33 and the attitude control device 34, and includes a processing circuit. Specifically, satellite control device 31 controls propulsion device 33 and attitude control device 34 according to various commands transmitted from ground equipment 700.
The communication device 32 is a device that communicates with the ground equipment 700. Alternatively, the communication device 32 is a device that communicates with satellites 30 before and after the same orbit plane, or with satellites 30 in adjacent orbit planes. Specifically, the communication device 32 transmits various data regarding its own satellite to the ground facility 700 or other satellites 30. Furthermore, the communication device 32 receives various commands transmitted from the ground equipment 700.
The propulsion device 33 is a device that provides propulsion to the satellite 30 and changes the speed of the satellite 30.
The attitude control device 34 is a device for controlling attitude factors such as the attitude of the satellite 30, the angular velocity of the satellite 30, and the line of sight. The attitude control device 34 changes each attitude element in 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. Attitude sensors are devices such as gyroscopes, earth sensors, sun sensors, star trackers, thrusters and magnetic sensors. Actuators are devices such as attitude control thrusters, momentum wheels, reaction wheels and control moment gyros. The controller controls the actuator according to the measurement data of the attitude sensor or various commands from the ground equipment 700.
The power supply device 35 includes devices such as a solar cell, a battery, and a power control device, and supplies power to each device mounted on the satellite 30.

The processing circuit provided in the satellite control device 31 will be explained.
The processing circuit may be dedicated hardware or a processor that executes a program stored in memory.
In the processing circuit, some functions may be realized by dedicated hardware, and the remaining functions may be realized by software or firmware. That is, the processing circuit can be implemented in hardware, software, firmware, or a combination thereof.
The dedicated hardware is specifically a single circuit, a complex circuit, a programmed processor, a parallel programmed processor, an ASIC, an FPGA, or a combination thereof.
ASIC is an abbreviation for Application Specific Integrated Circuit. FPGA is an abbreviation for Field Programmable Gate Array.

FIG. 4 shows another example of the configuration of the satellites 30 of the satellite constellation formation 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 that monitors objects. Specifically, the monitoring device 36 is a device for monitoring or observing objects such as space objects, flying objects, or moving objects on land, sea, and air. The monitoring device 36 is also referred to as an observation device.
For example, the monitoring device 36 is an infrared monitoring device that uses infrared light to detect a temperature increase due to atmospheric friction when a flying object enters the atmosphere. The monitoring device 36 detects the temperature of the plume or the body of the flying object when the flying object is launched. An infrared monitoring device is also called an infrared monitoring device.
Alternatively, the monitoring device 36 may be a light wave or radio wave information gathering device. 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 an object flying at an altitude different from the orbital altitude of the observation satellite. Specifically, monitoring device 36 may be a visible optical sensor.
Satellite 30 in FIG. 4 is an example of a monitoring satellite 307 that includes monitoring device 36 and communication device 32. Satellite 30 in FIG. The monitoring satellite 307 may include a plurality of monitoring devices 36. Furthermore, the monitoring satellite 307 may include multiple types of monitoring devices 36.

FIG. 5 is a configuration example of ground equipment 700 included in satellite constellation formation system 600.
Ground facilities 700 programmatically control multiple satellites in all orbital planes. The ground equipment 700 is also referred to as ground equipment or ground system. The ground equipment includes 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. Further, the ground device may include a communication device mounted on a mobile object such as an aircraft, a self-propelled vehicle, or a mobile terminal.

The ground equipment 700, that is, the ground system, operates and controls a satellite constellation, a flying object countermeasure system, a monitoring system, a satellite information transmission system, or a countermeasure system described in the embodiments of the present disclosure.
The hardware configuration of the ground equipment 700, that is, the ground system, is similar to the response ground center or satellite integrated command center described in the embodiment of the present disclosure.

Ground equipment 700 forms satellite constellation 20 by communicating with each satellite 30 . Ground equipment 700 includes a processor 910 and other hardware such as memory 921, auxiliary storage 922, input interface 930, output interface 940, and communication device 950. Processor 910 is connected to other hardware via signal lines and controls these other hardware.

The ground equipment 700 includes an orbit control command generation section 510 and an analysis prediction section 520 as functional elements. The functions of the orbit control command generation section 510 and the analysis prediction section 520 are realized by hardware or software.

The communication device 950 transmits and receives signals for tracking and controlling each satellite 30 of the satellite group that constitutes the satellite constellation 20. Furthermore, the communication device 950 transmits the orbit control command 55 to each satellite 30.
The analysis prediction unit 520 analyzes and predicts the orbit of the satellite 30.
Orbit control command generation section 510 generates orbit control command 55 to be transmitted to satellite 30.
The orbit control command generation unit 510 and the analysis prediction unit 520 realize the functions of the satellite constellation formation unit 11. That is, the orbit control command generation section 510 and the analysis prediction section 520 are examples of the satellite constellation formation section 11.

FIG. 6 is a diagram showing an example of the functional configuration of the satellite constellation formation system 600.
The satellite 30 further includes a satellite constellation forming section 11b that forms the satellite constellation 20. The satellite constellation forming unit 11b of each satellite 30 of the plurality of satellites and the satellite constellation forming unit 11 provided in each of the ground facilities 700 cooperate to realize the functions of the satellite constellation forming system 600. . Note that the satellite constellation forming unit 11b of the satellite 30 may be included in the satellite control device 31.

FIG. 7 is an example of space object information according to this embodiment.
The space object information includes a space object ID (Identifier) for identifying a space object and orbit information. The trajectory information includes forecast trajectory information and actual trajectory information. A space object is, for example, a satellite.
The forecast trajectory information includes an epoch, a trajectory element, a prediction error, an information providing business device ID, and an information update date.
The forecast trajectory information includes UTS time, position coordinates, measurement error, information providing business device ID, and information update date.

FIG. 8 is a diagram showing an example of trajectory forecast information according to the present embodiment.
The satellite constellation formation system 600, the ground equipment 700, or the satellite 30 is equipped with orbit forecast information in which a predicted value of the orbit of a space object is set.

The orbit forecast information includes satellite orbit forecast information and debris orbit forecast information. The satellite orbit forecast information includes a predicted value of the orbit of the satellite. The debris trajectory forecast information includes a predicted value of the debris trajectory.

Information such as a space object ID, a forecast period, a forecast orbit element, and a forecast error are set in the orbit forecast information, for example.

The space object ID is an identifier that identifies a space object. In FIG. 8, a satellite ID and a debris ID are set as space object IDs. Specifically, space objects include objects such as rockets launched into outer space, flying objects, artificial satellites, space bases, debris removal satellites, planetary exploration spacecraft, and satellites or rockets that become debris after their missions are completed.

The forecast epoch is the epoch for which the orbits of each of a plurality of space objects are predicted.
The predicted orbit element is an orbit element that specifies the orbit of each of a plurality of space objects. The predicted orbit element is an orbit element predicted for each orbit of a plurality of space objects. In FIG. 8, six Keplerian orbit elements are set as forecast orbit elements.

The forecast error is an error predicted in each orbit of a plurality of space objects. The forecast error includes a forward direction error, an orthogonal direction error, and a basis for the error. In this way, the forecast error clearly shows the amount of error included in the actual value along with the basis. The basis for the amount of error includes the measurement means, the content of data processing performed as a means for improving the accuracy of position coordinate information, and some or all of the results of statistical evaluation of past data.

Note that in the orbit forecast information according to the present embodiment, a forecast era and forecast orbit elements are set for a space object. Using the forecast epoch and forecast orbit elements, the time and position coordinates of a space object in the near future can be determined. For example, the time and position coordinates of a space object in the near future may be set in the orbit forecast information.
In this way, the orbit forecast information includes the orbit information of the space object including the epoch and orbit elements, or the time and position coordinates, and explicitly indicates the predicted value of the space object in the near future.
Alternatively, the satellite constellation formation system 600, the ground equipment 700, or the satellite 30 may be provided with orbit track record information in which track record values of the orbits of space objects are set.

***Summary of configuration and functions of the projectile object countermeasure system 401***
***Configuration and functional overview of the flying object tracking system 406***
FIG. 9 is a diagram illustrating a configuration example of a flying object handling system 401 and a flying object tracking system 406 according to the present embodiment.
Note that FIG. 9 is an example of the flying object countermeasure system 401 and the flying object tracking system 406, and other configurations may be used as long as the following functions can be realized.

Aircraft tracking system 406 is comprised of satellite constellation 20 and ground system 810. The flying object tracking system 406 performs launch detection and tracking of the flying object 601.
For example, the ground system 810 tracks intermittent jetting projectiles using a glide projectile tracking method described below. Alternatively, the ground system 810 tracks the ballistic projectile using a gliding projectile tracking method described below.

The flying object countermeasure system 401 includes a satellite constellation 20, a ground system 810, and a countermeasure asset 801.
For example, the ground system 810 tracks the intermittent jetting flying object using a gliding flying object tracking method described below, and transmits the flying object information to the countermeasure asset 801 near the expected impact area. Alternatively, the ground system 810 tracks the ballistic projectile using a gliding projectile tracking method to be described later, and transmits the projectile information to the countermeasure asset 801 near the expected impact area.

The satellite constellation 20 is a monitoring system 404 comprising a plurality of monitoring satellites 307 equipped with infrared monitoring equipment and flying in low orbit.

The flying object countermeasure system 401 includes a monitoring system 404 and a ground system 810 that transmits and receives information to and from both satellite systems, such as a satellite information transmission system 403 that is a communication system.
After the monitoring satellite 307 detects the launch of the flying object 601, it is necessary to transmit the position coordinates in order for the monitoring satellite group flying nearby to continue acquiring information about the flying object 601. According to the flying object countermeasure system 401 according to the present embodiment, a monitoring command can be given to the monitoring satellite group via the communication satellite 308 passing nearby.

The flying object countermeasure system 401 includes a monitoring system 404 , a satellite information transmission system 403 , and a countermeasure system 405 .
The monitoring system 404 includes a plurality of monitoring satellites 307 equipped with monitoring equipment and communication equipment.
Satellite information transmission system 403 includes a plurality of communication satellites 308 equipped with communication devices.
The response system 405 includes land, sea, and air response assets 801 that respond to the flying object 601. Response system 405 may receive information via response ground center 802 or may receive information from ground system 810 , monitoring satellite 307 , or communication satellite 308 .

The flying object countermeasure system 401 transmits the flying object information generated by monitoring the flying object 601 by the monitoring system 404 to the countermeasure system 405 via the satellite information transmission system 403.
For example, the monitoring satellite 307 uses an infrared monitoring device to detect the plume of the flying object 601 at the time of launch and the flying object 601 flying with an increased temperature as high-temperature objects. Then, the monitoring system 404 transmits the 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.

***Explanation of how to track a gliding flying object***
The gliding flying object tracking method analyzes the flying object monitoring information acquired by the satellite constellation 20 consisting of a plurality of monitoring satellites 307 using the ground system 810, and after the launch, the flying object lowers its orbit altitude to above the atmosphere and then glides. It's a way to track your body.

The monitoring satellite 307 includes, as the monitoring device 36, a first infrared monitoring device oriented toward the earth's center and a second infrared monitoring device oriented toward the circumference of the earth.
The first infrared monitoring device detects the high-temperature spray that accompanies a projectile launch and uses it as the starting point for a flight path model.
The second infrared monitoring device detects the body of the flying object, which has increased in temperature after the injection is completed, in the space background.

The ground system 810 models a flight path consisting of a projectile's launch position coordinates, flight direction, time-series flight distance from launch to impact, and flight altitude profile, and stores a plurality of typical flight path models. A database 811 is provided.
The ground system 810 uses the projectile launch detection information detected by the first infrared monitoring device of the monitoring device 36 as a starting point, and selects a subsequent monitoring satellite that can monitor the flight path at the predicted time from among a plurality of flight path models. select. Then, the ground system 810 transmits information from the monitoring satellite whose launch was detected to the selected subsequent monitoring satellite.

After the injection is complete, a monitoring satellite with a line of sight vector in the north-south direction measures the passing time, longitude, and altitude information of the flying object. In addition, a monitoring satellite having a line-of-sight vector in the east-west direction measures the passing time, latitude, and altitude information of the flying object after the injection is completed.

The ground system 810 evaluates the deviation between the flight path model and the actual orbit, corrects the flight path model, and continues monitoring the flying object with the next subsequent monitoring satellite.

FIG. 10 is a diagram showing an example of a flight path model of the distance from the launch area to the landing area of the flying object 601 and the flight direction.
FIG. 11 is a diagram showing an example of a flight path model of a suborbital flying object.
FIG. 12 is a diagram showing an example of a flight path model of an intermittent jetting flying object.
FIG. 13 is a comparison example between a flight path model of a suborbital flying object and a flight path model of an intermittent jetting object.

For projectiles that pose a security threat, the areas in which they are expected to be launched and the areas in which they are expected to land can be assumed in advance. For this reason, such a projectile can be set as a typical flight path model, including the distance from the launch area to the impact area, flight direction, arrival time, and trajectory and arrival altitude in the case of suborbital flight. be.
In recent years, the appearance of a flying object called a glide projectile that repeatedly fires intermittently has increased the variety of flight path models compared to ballistic projectiles. However, it is possible to assume a flight path model to the impact area as a flight model in which the missile glides in the upper atmosphere after the injection is completed during launch. Even if there is a deviation from the flight path model due to intermittent injection, the amount of change in both the altitude and horizontal directions is minute compared to the entire flight path profile from launch to impact. Further, by assuming a typical flight path model as a provisional flight path and correcting the actual trajectory using measurement information from monitoring satellites, it is possible to improve the accuracy of flight path prediction.

In addition to the HGV, which performs intermittent injection after injection is completed after launch, there are also known glide missiles such as HCMs (Hypersonic Cruise Missiles), which glide at supersonic speeds in the upper atmosphere without intermittent injection.

FIG. 14 is a diagram showing rim observation in which a monitoring satellite near the equator monitors a ballistic trajectory from the side.
FIG. 15 is a diagram showing rim observation monitored from the flight direction from the launch area to the impact area by a monitoring satellite near the northernmost tip of the inclined orbit.
The left diagram of FIG. 14 is a side view of the rim observation by a monitoring satellite near the equator, and the right diagram of FIG. 14 is a diagram of the rim observation from the side by a monitoring satellite near the equator.

The body of the flying object, which has increased in temperature after injection, is not as high as the temperature of the spray, and the object to be monitored is limited to the dimensions of the flying object. Identification may be difficult because it is buried in infrared radiation information from other sources. Therefore, by using a second infrared monitoring device, which uses a monitoring method called rim observation that focuses on the Earth's periphery, it is possible to identify the flying object as a bright spot in the low-temperature background by monitoring the flying object against the background of space. effective.

For a suborbital projectile, the flight profile is determined by the flight direction and speed at the end of the propulsion injection at the time of launch, and the impact area can be predicted by measuring the time and distance to reach the highest altitude after launch. On the other hand, in the case of a flying object that repeats injections intermittently, the flight path changes each time it is ejected, so it is necessary to track and monitor changes in the path over time.

In order to detect the body of the projectile whose temperature has risen after the injection, it is necessary to perform rim observations directed toward the Earth's periphery. A monitoring satellite suitable for monitoring is not a monitoring satellite that flies near the projectile, but a monitoring satellite that flies at a relative position suitable for rim observation.
In addition, in rim observation, the accuracy of measurement in the altitude and horizontal directions as seen from the monitoring satellite is high, but there may be large measurement errors in the distance direction.
Therefore, by using a monitoring satellite that monitors the ballistic trajectory from the side and information on the flying object from the monitoring satellite that monitors the trajectory from the launch area to the landing area, it is possible to track the ballistic trajectory with high precision.

As shown in Figure 14, for a suborbital projectile that is launched toward a landing area east of the launch area, a monitoring satellite that flies near the equator is suitable for monitoring the ballistic trajectory from the side. ing.
As shown in FIG. 15, a monitoring satellite flying from west to east near the northernmost end of an inclined orbit is suitable for monitoring from the direction of flight if it looks backward.
Therefore, monitoring satellites flying near the equator measure the passing time, longitude, and altitude information of the flying object, and monitoring satellites flying around the northernmost tip of the inclined orbit measure the passing time, latitude, and altitude information of the flying object. Measure information. This makes it possible to accurately measure the trajectory of a suborbital flight, and by transmitting highly accurate information on the flying object to the subsequent monitoring satellite, it becomes possible to track intermittent projectiles.

***Explanation of effects of this embodiment***
In this embodiment, the flying object countermeasure system 401 measures the passing time, longitude, and altitude information of the flying object using a monitoring satellite that flies near the equator, and uses a monitoring satellite that flies around the northernmost point of an inclined orbit to measure the passing time, longitude, and altitude information of the flying object. , to measure the passing time, latitude, and altitude information of the flying object. This makes it possible to accurately measure the flight path of a suborbital flight, and by transmitting highly accurate information on the flying object to the next succeeding satellite, it becomes possible to track the intermittent jetting object.

***Hardware Description***
Here, the hardware included in the computers of each device such as the satellite constellation forming system 600, the ground equipment 700, the ground system 810, or each satellite 30 that form the satellite constellation 20 will be described. For example, explanation will be given using ground equipment 700 shown in FIG. 2.

The processor 910 is a device that executes programs that implement the functions of each device.
The processor 910 is an IC (Integrated Circuit) that performs arithmetic processing. Specific examples of the processor 910 are a CPU (Central Processing Unit), a DSP (Digital Signal Processor), and a GPU (Graphics Processing Unit).

Memory 921 is a storage device that temporarily stores data. A specific example of the memory 921 is SRAM (Static Random Access Memory) or DRAM (Dynamic Random Access Memory).
Auxiliary storage device 922 is a storage device that stores data. A specific example of the auxiliary storage device 922 is an HDD. Further, the auxiliary storage device 922 may be a portable storage medium such as an SD (registered trademark) memory card, CF, NAND flash, flexible disk, optical disk, compact disc, Blu-ray (registered trademark) disc, or 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®. DVD is an abbreviation for Digital Versatile Disk.

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

Communication device 950 has a receiver and a transmitter. The communication device 950 is specifically a communication chip or NIC (Network Interface Card).

A program that implements the functions of each device is loaded into the processor 910 and executed by the processor 910. The memory 921 stores not only programs but also an OS (Operating System). Processor 910 executes programs while running the OS. The program and OS may be stored in the auxiliary storage device 922. The programs and OS stored in auxiliary storage device 922 are loaded into memory 921 and executed by processor 910. Note that part or all of the programs that implement the functions of each device may be incorporated into the OS.

Each device may include multiple processors to replace processor 910. These multiple processors share the responsibility of executing programs. Each processor, like processor 910, is a device that executes a program.

Data, information, signal values, and variable values utilized, processed, or output by the program are stored in memory 921, auxiliary storage 922, or registers or cache memory within processor 910.

The term "unit" in each part of each device may be read as "process," "procedure," "means," "step," "circuitry," or "step." Furthermore, the term "section" for each section of each device may be replaced with "program," "program product," or "computer-readable recording medium on which a program is recorded." "Process", "procedure", "means", "step", "circuitry", or "process" can be read interchangeably.

Embodiment 2.
In this embodiment, points different from Embodiment 1 and points added to Embodiment 1 will be mainly described.
In this embodiment, components having the same functions as those in Embodiment 1 are denoted by the same reference numerals, and the description thereof will be omitted.

In this embodiment, the ground system 810 analyzes the flying object monitoring information acquired by the satellite constellation 20 composed of a plurality of monitoring satellites 307, and identifies that the flying object is a gliding flying object rather than a ballistic flying object. A method for identifying gliding flying objects will be explained.

The flying object tracking system 406 includes a satellite constellation 20 and a ground system 810, and performs launch detection and tracking of flying objects.
The ground system 810 identifies the gliding aircraft using the gliding aircraft identification method according to the present embodiment.

The flying object countermeasure system 401 includes a satellite constellation 20, a ground system 810, and a countermeasure asset 801.
The ground system 810 identifies the gliding aircraft using the gliding aircraft identification method according to the present embodiment, tracks the flying object, and transmits the flying object information to the countermeasure asset 801 near the expected flight path.

***Explanation of how to identify gliding flying objects***
In the gliding projectile identification method according to the present embodiment, a ground system 810 analyzes projectile monitoring information acquired by a satellite constellation 20 composed of a plurality of monitoring satellites 307 equipped with an infrared monitoring device, Identifies that it is a gliding projectile rather than a ballistic projectile.
The ground system 810 models a flight path consisting of a projectile's launch position coordinates, flight direction, time-series flight distance from launch to impact, and flight altitude profile, and stores a plurality of typical flight path models. A database 811 is provided.
The ground system 810 uses the projectile launch detection information detected by the infrared monitoring device as a starting point to simultaneously perform suborbital flight using a subsequent monitoring satellite at different flight altitudes after the flight path models of the ballistic projectile and the gliding projectile are launched. The system monitors the predicted height band of the gliding object and the predicted altitude band of the gliding object, and identifies the gliding object.

FIG. 16 is a diagram showing a gliding flying object identification method according to the present embodiment.
Since the projectile that posed a security threat was a ballistic projectile, by detecting the launch and measuring the flight direction and altitude, it was possible to predict the impact area and take countermeasures. However, the gliding projectiles that have appeared in recent years have the characteristic of lowering their orbital altitude to above the atmosphere immediately after launch, and then flying at extremely high speeds while gliding at an altitude close to the atmosphere and landing, which can make it difficult to take countermeasures. be. As gliding flying vehicles, there are known HGVs, which repeatedly inject intermittently after lowering the orbital altitude after launch, and HCMs, which do not inject and only glide after lowering the orbital altitude after launch.

In particular, for gliding aircraft, it is necessary to track the body of the flying object, which has risen in temperature after injection, by infrared detection, so if a ballistic flying object cannot be detected by infrared monitoring from a distance such as that monitored from a geostationary orbit satellite. There is. Therefore, the realization of an infrared monitoring system using a low-orbit satellite constellation is eagerly awaited.
In a low-orbit satellite constellation, individual satellites pass at high speed, so in order to track and monitor a specific projectile after its launch, multiple satellites work together to send and receive projectile information and predict the projectile's flight. Routes need to be monitored.
In the future, when ballistic and gliding objects coexist, it will be necessary to identify the gliding object at an early stage and take appropriate countermeasures.
The present embodiment aims to provide a method for identifying gliding flying objects at the fastest speed.

As explained in Embodiment 1, the area where a flying object that poses a security threat is expected to be launched and the area where it is expected to land can be assumed in advance, so it is set as a typical flight path model. Is possible. In recent years, the appearance of a flying object called a glide projectile that repeatedly fires intermittently has increased the variety of flight path models compared to ballistic projectiles. However, it is possible to assume a flight path model to the impact area as a flight model in which the missile glides in the upper atmosphere after the injection is completed during launch. Even if there is a deviation from the flight path model due to intermittent injection, the amount of change in both the altitude and horizontal directions is minute compared to the entire flight path profile from launch to impact. By comparing typical flight path models for ballistic and gliding vehicles, it becomes possible to distinguish them by focusing on changes in trajectory altitude immediately after launch.

In FIG. 16, it is difficult to distinguish between a ballistic projectile and a gliding projectile at the launch detection stage T0. If launch detection information is transmitted to a continuous monitoring satellite and detected at elapsed time T1, a ballistic projectile can be detected by continuous monitoring A1, a gliding projectile can be detected by continuous monitoring B1, and at least a ballistic projectile flying over a long distance can be detected by continuous monitoring A1. can be identified.
However, there remains a possibility that it may not be possible to distinguish it from a short-range ballistic projectile. At elapsed time T2, it is determined that the flying object detected by continuous monitoring B2 is a gliding flying object.
Continuous Monitoring If the monitoring satellite has a field of view that includes the altitudes of A1 and B1, long-range ballistic objects can be identified by analyzing the altitude detected by one monitoring satellite.
However, if the monitoring field of view is limited in order to monitor the body of the flying object after the injection is completed, identification may be made by having two monitoring satellites share and monitor different altitude zones during the elapsed time T1. It becomes possible.
When a flying object is detected by continuous monitoring B1 at elapsed time T1, the field of view altitude of continuous monitoring is set to altitude band B, and when a flying object is detected by continuous monitoring B2, it is identified as a gliding flying object.
By identifying a gliding flying object at an early stage, the monitoring range of the continuous satellite can be limited to altitude band B, which has the effect of allowing concentration on countermeasures.

Embodiment 3.
In this embodiment, differences from Embodiments 1 and 2 and points added to Embodiments 1 and 2 will be mainly described.
In this embodiment, components having the same functions as those in Embodiments 1 and 2 are denoted by the same reference numerals, and the description thereof will be omitted.

In this embodiment, in the gliding projectile tracking method described in Embodiment 1, a case will be described in which a projectile launched from a mid-latitude zone and flying mainly in an east-west direction is tracked.

FIG. 17 is a diagram illustrating an example of the gliding flying object tracking method according to the present embodiment.
FIG. 17 shows a gliding projectile tracking method for tracking a projectile launched from a mid-latitude zone and flying primarily in an east-west direction.

Satellite constellation 20 includes at least inclined orbit satellites.
After the injection is completed, a monitoring satellite flying near the equator in an inclined orbit or in an orbit above the equator measures the time of passage, longitude, and altitude information of the flying object. Furthermore, a monitoring satellite flying in a mid-latitude zone in an inclined or polar orbit measures the passing time, latitude, and altitude information of the flying object after the injection is completed.

A projectile flying in an east-west direction in mid-latitudes is characterized by its ability to perform high-precision monitoring in the cosmic background by monitoring its rim from above the equator. However, there are cases where the measurement error in the latitudinal direction is large using only a satellite orbiting over the equator.
According to the gliding flying object tracking method according to the present embodiment, it is possible to provide means for measuring the position in the longitudinal direction and the latitude direction using a satellite constellation in an equatorial orbit, an inclined orbit, or a polar orbit.

Embodiment 4.
In this embodiment, differences from Embodiments 1 to 3 and points added to Embodiments 1 to 3 will be mainly described.
In this embodiment, components having the same functions as those in Embodiments 1 to 3 are denoted by the same reference numerals, and the description thereof will be omitted.

In this embodiment, a case will be described in which, in the gliding projectile tracking method described in Embodiment 1, a projectile launched from a high latitude zone and flying through a polar region is tracked.

FIG. 18 is a diagram showing an example of the gliding flying object tracking method according to the present embodiment.
FIG. 18 shows a gliding projectile tracking method for tracking a projectile launched from a high latitude zone and flying through a polar region.

Satellite constellation 20 includes at least inclined orbit satellites.
After injection, a monitoring satellite flying in a mid-latitude zone in an inclined or polar orbit measures the passing time, longitude, and altitude information of the flying object. Furthermore, a monitoring satellite flying in a mid-latitude zone with an inclined orbit measures the passing time, latitude, and altitude information of the flying object after the injection is completed.

Projectiles launched from high latitudes and passing through the polar regions may not be monitored from orbits above the equator.
According to the gliding flying object tracking method according to the present embodiment, it is possible to provide means for measuring the position in the longitudinal direction and the latitude direction using a satellite constellation in an inclined orbit or a polar orbit.

Embodiment 5.
In this embodiment, differences from Embodiments 1 to 4 and points added to Embodiments 1 to 4 will be mainly described.
In this embodiment, components having the same functions as those in Embodiments 1 to 4 are denoted by the same reference numerals, and the description thereof will be omitted.

In this embodiment, each function of the flying object handling system 401 and the flying object tracking system 406 described in Embodiments 1 to 3 will be further described.

The spray generated when a projectile is launched is easily monitored because the high-temperature atmosphere disperses it. On the other hand, the body of the projectile in the post-boost phase after injection has stopped has a small solid angle as seen from the monitoring satellite, and the temperature rise is not as pronounced as in the plume. For this reason, there is a concern that if background land area information is mixed into the body of the flying object in the post-boost phase after injection is stopped, it will become indistinguishable. Therefore, a monitoring method called rim observation that aims at the Earth's periphery will be used to monitor the body of the flying object, which has risen in temperature against the background of deep space. This makes it possible to monitor flying objects without being buried in noise. By integrating the information of flying objects detected by multiple monitoring satellites on high-temperature objects using a flight path prediction device and analyzing changes in positional information over time, it is possible to track flying objects and predict their flight paths. becomes.

Even if the aircraft re-injects intermittently during flight and changes its direction of travel, it is possible to deal with HGVs by tracking the aircraft using a flight path prediction device and continuously acquiring time-series information.
As the response assets 801, there are various means such as aircraft, ships, and vehicles deployed on land, sea, and air, and ground-based equipment. There is also a means of directly transmitting information to individual assets. However, if the satellite information transmission system is not dedicated to ensuring safety, it may not be possible to disclose the location information of individual assets due to security restrictions. Therefore, it is rational to aggregate the flying object information to the response ground center where commands to the response assets are delivered, and to execute the commands to the response assets from the response ground center.
For example, a mobile object such as a ship with a dedicated line of communication with the response assets may take on the role of the response ground center.
The operation method of the satellite information transmission system differs depending on the configuration and operation method of the entire flying object countermeasure system.

FIG. 19 is a schematic diagram showing an example of the time-series information transmission order in the flying object countermeasure system 401 and the flying object tracking system 406.
FIG. 20 is a diagram showing an example 1 of the time-series information transmission order in the flying object countermeasure system 401.
The flying object countermeasure system 401 in FIG. 20 predicts the flight position coordinates of the flying object at future times (t3, t6, . . . tn, tn+4, tn+6, . , A3, An, . . .) and the communication satellites (B1, B2, Bn, Bn+1, . . .) that are scheduled to pass nearby.
Furthermore, it is necessary to finally transmit information to the coping assets (C1, C2, . . . ).
However, at the time of launching the projectile, the flight path of the projectile is unknown, and it is necessary to predict the flight path. Furthermore, in order to predict the flight path, it is necessary to repeatedly exchange information between the monitoring satellite and the communication satellite, and it is necessary to search for the optimal communication route each time.
Furthermore, it is necessary to select a coping asset on the predicted route.

FIG. 21 is a diagram illustrating a second example of the time-series information transmission order in the flying object countermeasure system 401.
In the projectile countermeasure system 401 in FIG. 21, a monitoring satellite or a communication satellite that passes near the future flight location of the projectile is flying at position coordinates that are far away at the time of launch (t0) of the projectile. The flight position coordinates of the flying object at future times (t3, t6,...tn, tn+4, tn+6,...) are predicted and the monitoring satellites (A1, A2, A3, An,...) scheduled to pass nearby are predicted. It is necessary to select communication satellites (B1, B2, Bn, Bn+1, . . . ) that are scheduled to pass nearby.
It is highly likely that the orbit planes and flight directions of monitoring and communication satellites are different, making it difficult to create an algorithm for selecting monitoring and communication satellites that will meet near the flying object at a future time.

With respect to monitoring satellites, by transmitting information on all monitoring satellites that have acquired significant monitoring information, there is no need to select a unique monitoring satellite. However, for example, when transmitting wide field of view (WFOV) monitoring satellite information to a medium field of view (MFOV) monitoring satellite as foresight information, selection of the monitoring satellite is essential.
WFOV is an abbreviation for Wide-field of View.
MFOV is an abbreviation for Multiple-Field-Of-View.

The flight path of the projectile is unknown at the launch detection stage, and it is necessary to evaluate the projectile position coordinates at times t3 and t6 based on the tracking and monitoring information of the monitoring satellites A2 and A3.
It is necessary to predict the flight path based on the projectile position coordinates at t0, t3, t6, ... tn, ..., predict the position coordinates at tn+4, tn+6, and select a countermeasure asset deployed nearby. .
Therefore, optimal communication route search, flight route prediction, and countermeasure asset selection are required as a mechanism for exchanging information.

FIG. 22 is a diagram illustrating a third example of the time-series information transmission order in the flying object countermeasure system 401.
In the flying object countermeasure system 401 in FIG. 22, a monitoring satellite that tracks and monitors a flying object in flight is not necessarily an observation satellite flying near the flying object. The flight position of a monitoring satellite based on Earth's circumferential rim observations may be far away from the flight position coordinates of the projectile.
For example, a monitoring satellite flying near the equator is suitable for photographing a flying object flying in a mid-latitude zone with a high S/N ratio in the background space.
Furthermore, since there is a large error in estimating latitudinal coordinates when observing the rim from near the equator, it is necessary to estimate the position by aerial triangulation in combination with information obtained from monitoring satellites flying at different locations.

<Communication route search>
In order to detect a projectile launched at any time and place and transmit the projectile information to a subsequent monitoring satellite, the launch position coordinates (ground surface) detected by the monitoring satellite are estimated and the nearby It is necessary to select a communication satellite to pass through and transmit information. In order to transmit launch detection information to subsequent monitoring satellites, it may be necessary to select monitoring satellites and communication satellites that will pass nearby.
Further, at the time of launch detection, the flying direction and destination of the flying object are unknown, so the target point to which the flying object information is transmitted may not be determined.
In order to understand the flight direction of a flying object, it is necessary to estimate the flight position coordinates from tracking information from subsequent monitoring satellites. In the case of a ballistic projectile, its behavior after launch can be estimated using the laws of physics, but in the case of a projectile that repeatedly injects intermittently, it is possible to move both in the altitude direction and in the horizontal direction, so it is difficult to estimate the position coordinates of the projectile. It can be difficult.
Additionally, although rim observation is effective for detecting the body of the projectile after injection, the distance between the monitoring satellite and the projectile is long, so there are a wide range of options for monitoring satellites, and communication that passes nearby Satellite selection can also be difficult.

While solving these cases, the distribution of coping assets is identified based on the flight path prediction results, and the information transmission target is determined. In the process of sending and receiving the above series of flying object information, the communication route between the communication satellites at each step, the planning of the sending and receiving of the flying object information between the monitoring satellite and the communication satellite, which are necessary in the process of flight route prediction, and the communication satellites that will pass through. You need to select an ID.
As time elapses after the projectile is launched, the projectile position coordinates change from moment to moment. For this reason, it is necessary for the following monitoring satellite to capture the flying object after it has moved, and to transmit the flying object information to a communication satellite passing nearby. However, monitoring satellites and communication satellites are also flying depending on the time that has passed since the projectile was launched. Therefore, in order to search for communication routes, it is necessary to develop a communication route search method that can respond flexibly to the fact that the monitoring satellites that can be monitored differ depending on the moving speed of the flying object, and the communication satellites passing nearby also vary. It is.

<Flight path prediction>
At the launch detection stage, it is necessary to predict the future flight path of a flying object whose flight path is unknown using tracking information acquired by subsequent monitoring satellites.
Furthermore, unlike suborbital flight, HGVs operate their propulsion systems intermittently during flight, and tracking information from monitoring satellites must be updated frequently.
Tracking information from Earth's circumferential rim observations has large errors in line-of-sight vector direction, so it is necessary to improve the estimation accuracy of position coordinates through aerial triangulation using tracking information from multiple monitoring satellites.
It is necessary to take into account the effect of flying object movement due to the difference in monitoring time between multiple monitoring satellites.
When multiple flying objects are launched at approximately the same time, it is necessary to identify the multiple flying objects based on consistency of time-series position information.

<Selection of coping assets>
It is necessary to transmit information to response assets deployed near the future flight path of the projectile. Since the flight path is unknown at the time of launch, it is necessary to transmit information to a large number of response assets over a wide area during the initial flight stage. Alternatively, it is necessary to transmit information to a response ground center that provides integrated control of response assets.
In the case of a ballistic projectile, it is possible to estimate the impact position if the flight direction, velocity, or altitude information after injection is completed is known, but in the case of a projectile that repeatedly ejects intermittently, the impact position cannot be estimated, and the flight path cannot be estimated. Coping actions need to be taken along the way.
Therefore, it is necessary to select a countermeasure asset based on the flight path prediction result based on the time-series flight position information of the flying object.

<Mechanism for exchanging information between algorithms for communication route search, flight path prediction, and response asset selection>
As mentioned above, communication route search and flight path prediction are interdependent, and in order to select countermeasure assets and transmit flying object information, a mechanism for exchanging information between each algorithm is required.
For flying objects with unknown flight paths, communication route search for tracking by monitoring satellites, flight path prediction based on tracking information, tracking by monitoring satellites on the predicted route, selection of response assets on the predicted final route, information on response assets It is necessary to search for communication routes for transmission in chronological order. Therefore, a mechanism for exchanging information between each algorithm is required.
As for the mechanism for exchanging information, there may be variations in the information exchange or integration of the ground systems that operate and control the surveillance satellite group, the ground systems that operate and control the communication satellite group, and the ground systems that operate and control the response assets.
In addition, it is necessary to construct a system for exchanging information that takes into account the characteristics of ground systems that handle confidential information that contributes to security, and ground systems that are difficult to keep confidential, such as commercial communication systems.

Among the first to fifth embodiments described above, a plurality of parts may be combined and implemented. Alternatively, one part of these embodiments may be implemented. In addition, these embodiments may be implemented in any combination, in whole or in part.
That is, in Embodiments 1 to 5, any part of Embodiments 1 to 5 can be freely combined, any component can be modified, or any component can be omitted in Embodiments 1 to 5. It is.

Note that the embodiments described above are essentially preferable examples, and are not intended to limit the scope of the present disclosure, the scope of applications of the present disclosure, and the scope of uses of the present disclosure. The embodiments described above can be modified in various ways as necessary.

11, 11b satellite constellation formation unit, 20 satellite constellation, 21 orbital surface, 30 satellite, 31 satellite control device, 32 communication device, 33 propulsion device, 34 attitude control device, 35 power supply device, 36 monitoring device, 55 orbit control Command, 307 Monitoring satellite, 308 Communication satellite, 401 Flying object countermeasure system, 403 Satellite information transmission system, 404 Monitoring system, 405 Countermeasure system, 406 Flying object tracking system, 510 Orbit control command generation unit, 520 Analysis prediction unit, 601 Flight body, 600 satellite constellation formation system, 700 ground equipment, 801 response asset, 802 response ground center, 810 ground system, 811 database, 910 processor, 921 memory, 922 auxiliary storage device, 930 input interface, 940 output interface, 941 display Equipment, 950 Communication equipment.

Claims (6)

A ground system analyzes airborne object monitoring information obtained by a satellite constellation consisting of multiple monitoring satellites equipped with infrared monitoring equipment and flying in low orbit.
A method for tracking a gliding flying object that glides after lowering its orbital altitude to above the atmosphere after launch, the method comprising:
The monitoring satellite is
a first infrared monitoring device oriented toward the geocenter;
a second infrared monitoring device oriented toward the Earth's periphery;
Equipped with
Detecting high-temperature spray accompanying the projectile launch by the first infrared monitoring device and using it as a starting point for a flight path model;
The second infrared monitoring device detects the body of the flying object whose temperature has increased after the injection is completed in the space background,
The ground system includes:
It models the flight path consisting of the launch position coordinates of the projectile, the flight direction, and the time-series flight distance and flight altitude profile from launch to impact, and is equipped with a database that stores multiple typical flight path models. ,
Using the projectile launch detection information detected by the infrared monitoring device as a starting point, a subsequent monitoring satellite whose flight path can be monitored at the predicted time is selected from a plurality of flight path models, and from the monitoring satellite whose launch was detected, Transmits information to the selected subsequent monitoring satellite,
A monitoring satellite with a line-of-sight vector in the north-south direction looks at the main body of the projectile after injection.
Measures the passing time, longitude, and altitude information of the flying object,
A surveillance satellite with a line of sight vector in the east-west direction
Measuring the passing time, latitude, and altitude information of the flying object,
The ground system includes:
Evaluate the deviation between the flight path model and the actual trajectory and correct the flight path model.
A method of tracking a gliding flying object that continues monitoring the flying object with the next subsequent monitoring satellite. A gliding projectile tracking method for tracking a projectile launched from a mid-latitude zone and flying mainly in an east-west direction,
the satellite constellation includes at least an inclined orbit satellite;
The satellite constellation is
After the injection is complete, a monitoring satellite that flies near the equator in an inclined orbit or above the equator measures the passing time, longitude, and altitude information of the projectile.
Monitoring satellites flying in mid-latitude zones in inclined or polar orbits measure passing time, latitude, and altitude information of flying objects.
The method for tracking a gliding flying object according to claim 1. A gliding projectile tracking method for tracking a projectile launched from a high latitude zone and flying through a polar region,
the satellite constellation includes at least an inclined orbit satellite;
The satellite constellation is
After the injection is complete, a monitoring satellite that flies in a mid-latitude zone in an inclined or polar orbit measures the passing time, longitude, and altitude information of the projectile.
Monitoring satellites flying in mid-latitudes on inclined orbits measure the passing time, latitude, and altitude information of flying objects.
The method for tracking a gliding flying object according to claim 1. A flying object tracking system consisting of a satellite constellation and a ground system that detects and tracks the launch of a flying object,
The ground system is
Tracking a ballistic projectile by the gliding projectile tracking method according to any one of claims 1 to 3.
Projectile tracking system. A flying object countermeasure system comprising a satellite constellation, a ground system, and a countermeasure asset,
The ground system is
Tracking a ballistic projectile by the gliding projectile tracking method according to any one of claims 1 to 3, and transmitting projectile information to a countermeasure asset near a predicted impact area.
Projectile countermeasure system. A ground system included in the projectile tracking system according to claim 4 or the projectile object countermeasure system according to claim 5.

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