JP7329402B2 - Orbit transition support device, orbit transition support method, and orbit transition support program - Google Patents

Description

The present invention relates to an orbit transition support device, an orbit transition support method, and an orbit transition support program.

In recent years, the construction of large-scale satellite constellations of hundreds to thousands of satellites has begun, increasing the risk of satellite collisions in orbit. In addition, space debris such as uncontrollable satellites due to malfunctions and debris from rockets is increasing.
With such a rapid increase in space objects such as satellites and space debris in outer space, there is an increasing need for creating international rules for avoiding collisions of space objects in space traffic control (STM).

Patent Document 1 discloses a technique for forming a satellite constellation composed of a plurality of satellites in the same circular orbit.

JP 2017-114159 A

A geostationary orbit satellite or a quasi-zenith orbit satellite injected into a geostationary transfer orbit GTO must overtake the orbital altitude of a satellite constellation formed on the way from perigee to apogee. In recent years, when a geostationary orbit satellite or a quasi-zenith orbit satellite inserted into a geostationary transfer orbit GTO undergoes an orbit transition, there is an increasing risk of collision in an equatorial orbit.
However, Patent Literature 1 does not describe measures for avoiding such a collision risk.

SUMMARY OF THE INVENTION An object of the present invention is to effectively support orbit transition in a geostationary orbit satellite or a quasi-zenith orbit satellite inserted into a geostationary transfer orbit GTO.

An orbit transition assisting apparatus according to the present invention assists orbit transition of a transition satellite that is injected into a geostationary transfer orbit and overtakes an orbital altitude of a satellite constellation formed on the way from perigee to apogee in the geostationary transfer orbit. in the support device,
From the orbital forecast information in which the predicted values of the orbits of the space objects are set, the orbital forecast values of each of the plurality of satellites constituting the satellite constellation are collected, and the support information used to support the orbit transition of the transition satellite is obtained. a support information generation unit to generate;
and a support information display unit for displaying the support information on a display device.

In the orbit transition support device according to the present invention, the support information generation unit collects the orbit forecast values of each of the plurality of satellites forming the satellite constellation from the orbit forecast information. Then, the support information generation unit generates support information used to support orbit transition of the transition satellite. The support information display unit displays the support information on the display device. Therefore, according to the orbit transition support device according to the present invention, there is an effect that the orbit transition of the transition satellite injected into the geostationary transfer orbit GTO can be effectively supported by the support information displayed on the display device. .

An example in which multiple satellites work together to provide a global communication service. An example of multiple satellites in a single orbital plane providing an earth observation service. An example of a satellite constellation with multiple orbital planes intersecting near the polar regions. An example of a satellite constellation with multiple orbital planes that intersect outside the polar regions. The block diagram of a satellite constellation formation system. A configuration diagram of a satellite of the satellite constellation forming system. The block diagram of the ground equipment of a satellite constellation formation system. An example of the functional configuration of a satellite constellation forming system. 1 is a configuration diagram of a track transition support device according to Embodiment 1; FIG. The figure which shows the relationship between a geostationary transfer orbit and a satellite constellation. The figure which shows the relationship between a geostationary transfer orbit and a satellite constellation. A diagram showing a satellite flight image near an orbital altitude of 340 km. FIG. 4 is a diagram showing an example of track forecast information according to Embodiment 1; FIG. 4 is a flow diagram of orbit transition support processing by the orbit transition support device according to the first embodiment; FIG. 4 is a diagram showing example 1 of support information according to the first embodiment; FIG. FIG. 10 is a diagram showing example 2 of support information according to the first embodiment; FIG. 11 is a diagram showing an example 3 of support information according to the first embodiment; FIG. FIG. 10 is a diagram showing an example 4 of support information according to the first embodiment; FIG. Schematic representation of the technique by which a transition satellite overtakes the orbital altitude. FIG. 2 is a configuration diagram of a track transition support device according to a modification of Embodiment 1;

BEST MODE FOR CARRYING OUT THE INVENTION Embodiments of the present invention will be described below with reference to the drawings. In each figure, the same reference numerals are given to the same or corresponding parts. In the description of the embodiments, the description of the same or corresponding parts will be omitted or simplified as appropriate. In addition, in the following drawings, the size relationship of each component may differ from the actual one. In addition, in the description of the embodiments, directions or positions such as "top", "bottom", "left", "right", "front", "back", "front", and "back" are indicated. There is These notations are provided as such for convenience of explanation only and are not intended to limit the arrangement and orientation of structures such as devices, instruments or components.

Embodiment 1.
An example of a satellite constellation that is a premise of an orbit transition support system according to the following embodiments will be described.

FIG. 1 is a diagram showing an example in which a plurality of satellites work together to realize a communication service over the entire globe of the earth 70 with respect to the ground.
FIG. 1 shows a satellite constellation 20 that provides global communication services.
Each satellite of a plurality of satellites flying in the same orbital plane at the same altitude overlaps the communication service range to the ground with the communication service range of the following satellite. Therefore, according to such a plurality of satellites, a communication service can be provided to a specific point on the ground while a plurality of satellites on the same orbital plane are alternately alternated in a time division manner. In addition, by providing adjacent orbital planes, it is possible to cover the area of communication services to the ground between adjacent orbits. Similarly, a number of orbital planes approximately evenly spaced around the earth would allow communication services to the ground over the globe.

FIG. 2 illustrates an example of multiple satellites in a single orbital plane providing an earth observation service.
FIG. 2 shows a satellite constellation 20 for implementing earth observation services. In the satellite constellation 20 of FIG. 2, satellites equipped with earth observation devices, which are radio sensors such as optical sensors or synthetic aperture radars, fly in the same orbital plane at the same altitude. In this way, in the satellite constellation 300, in which the imaging range of the ground is delayed by time and the following satellites overlap, a plurality of satellites on orbit alternately alternately time-divisionally to capture a ground image with respect to a specific point on the ground. provide earth observation services.

Thus, the satellite constellation 20 consists of a constellation 300 of satellites in each orbital plane. In the satellite constellation 20, satellite constellations 300 cooperate to provide services. The satellite constellation 20 specifically refers to a satellite constellation consisting of one group of satellites by a telecommunications service company as shown in FIG. 1 or an observation service company as shown in FIG.

FIG. 3 is an example of a satellite constellation 20 having multiple orbital planes 21 that intersect near the poles. Also, FIG. 4 is an example of a satellite constellation 20 having multiple orbital planes 21 that intersect outside the polar regions.
In the satellite constellation 20 of FIG. 3, the orbital inclination angle of each orbital plane 21 of the plurality of orbital planes is approximately 90 degrees, and the orbital planes 21 of the plurality of orbital planes exist on different planes.
In the satellite constellation 20 of FIG. 4, the orbital inclination angles of the orbital planes 21 of the plurality of orbital planes are not approximately 90 degrees, and the orbital planes 21 of the plurality of orbital planes are on different planes.

In the satellite constellation 20 of FIG. 3, any two orbital planes intersect at points near the poles. Also, in the satellite constellation 20 of FIG. 4, any two orbital planes intersect at points other than the polar regions. In FIG. 3, collisions of satellites 30 may occur near the poles. Also, as shown in FIG. 4, the intersections of a plurality of orbital planes with an orbital inclination angle of more than 90 degrees move away from the polar regions according to the orbital inclination angle. Moreover, there is a possibility that the orbital planes intersect at various positions including near the equator depending on the combination of the orbital planes. This diversifies the locations where satellites 30 may collide. The satellite 30 is also called an artificial satellite.

In particular, in recent years, the construction of large-scale satellite constellations of several hundred to several thousand has begun, increasing the risk of collision of satellites in orbit. Debris such as uncontrollable satellites and rocket wreckage is also increasing. A large satellite constellation is also called a mega constellation. Such debris is also called space debris.
As described above, with the increase of debris in outer space and the rapid increase in the number of satellites including mega-constellations, the need for space traffic control (STM) is increasing.

In addition, for the orbital transition of space objects, post-mission deorbit (PMD) in orbit, malfunctioned satellites, and debris such as floating rocket upper stages are deorbited by external means such as debris recovery satellites. The need is growing. An international discussion has started on the necessity of such ADR as STM. Here, PMD is an abbreviation for Post Mission Disposal. ADR is an abbreviation for Active Debris Removal. STM is an abbreviation for Space Traffic Management.

In addition, due to the strengthening of the system including international cooperation in Space Situational Awareness (SSA) and the improvement of observation accuracy, the size of space objects that can be grasped can be monitored even smaller. Also, the total number of space objects that can be monitored is increasing.

Here, an example of satellites 30 and ground facilities 700 in satellite constellation forming system 600 forming satellite constellation 20 will be described with reference to FIGS. 5 to 8. FIG. For example, the satellite constellation forming system 600 is operated by a satellite constellation business operator such as the mega constellation operator 41 , the LEO constellation operator 42 , or the satellite operator 43 .

FIG. 5 is a configuration diagram of a satellite constellation forming system 600. As shown in FIG.
Satellite constellation forming system 600 comprises a computer. Although FIG. 5 shows the configuration of one computer, in reality, each satellite 30 of the plurality of satellites forming the satellite constellation 20 and each of the ground facilities 700 communicating with the satellites 30 are equipped with computers. be done. The satellites 30 of the plurality of satellites and the computers provided in each of the ground facilities 700 communicating with the satellites 30 cooperate to implement the functions of the satellite constellation forming system 600 . An example of the configuration of a computer that implements the functions of satellite constellation forming system 600 will be described below.

Satellite constellation forming system 600 comprises satellites 30 and ground equipment 700 . Satellite 30 includes a satellite communication device 32 that communicates with communication device 950 of ground facility 700 . In FIG. 5, the satellite communication device 32 is illustrated among the components of the satellite 30. As shown in FIG.

Satellite constellation forming system 600 comprises processor 910 and other hardware such as memory 921 , secondary storage 922 , input interface 930 , output interface 940 and communication device 950 . The processor 910 is connected to other hardware via signal lines and controls these other hardware. The hardware of the satellite constellation forming system 600 is the same as the hardware of the orbit transition support device 100 described later with reference to FIG.

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

FIG. 6 is a block diagram of satellite 30 of satellite constellation forming system 600 .
The satellite 30 includes a satellite control device 31 , a satellite 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 satellite communication device 32, the propulsion device 33, the attitude control device 34, and the power supply device 35 will be described in FIG. Satellite 30 is an example of space object 60 .

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, the satellite control device 31 controls the propulsion device 33 and the attitude control device 34 according to various commands transmitted from the ground equipment 700 .
The satellite communication device 32 is a device that communicates with the ground facility 700 . Specifically, the satellite communication device 32 transmits various data related to its own satellite to the ground facility 700 . The satellite communication device 32 also receives various commands transmitted from the ground equipment 700 .
The propulsion device 33 is a device that gives propulsion force to the satellite 30 and changes the speed of the satellite 30 . Specifically, the propulsion device 33 is an apogee kick motor or a chemical propulsion device or an electric propulsion device. The Apogee Kick Motor (AKM) is the upper-stage propulsion device used to put satellites into orbit, and is also called an apogee motor (when using a solid rocket motor) or an apogee engine (when using a liquid engine). ing.
A chemical propulsion system is a thruster that uses mono- or bi-propellants. The electric propulsion device is an ion engine or a Hall thruster. An apogee kick motor is the name of a device used for orbital transition, and is sometimes a type of chemical propulsion device.
The attitude control device 34 controls the attitude of the satellite 30, the angular velocity of the satellite 30, and the line-of-sight direction (Line Of
Sight) is a device for controlling attitude elements. The attitude control device 34 changes each attitude element in a desired direction. Alternatively, attitude controller 34 maintains each attitude element in the desired orientation. 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 actuators according to measurement data from 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 .

A processing circuit provided in the satellite control device 31 will be described.
The processing circuitry may be dedicated hardware or a processor executing a program stored in memory.
In the processing circuit, some functions may be implemented in dedicated hardware and the remaining functions may be implemented in software or firmware. That is, processing circuitry can be implemented in hardware, software, firmware, or a combination thereof.
Dedicated hardware is specifically a single circuit, multiple circuits, programmed processors, parallel programmed processors, ASICs, FPGAs, or combinations thereof.
ASIC is an abbreviation for Application Specific Integrated Circuit. FPGA is an abbreviation for Field Programmable Gate Array.

FIG. 7 is a configuration diagram of a ground facility 700 included in the satellite constellation forming system 600. As shown in FIG.
Ground facility 700 programs multiple satellites in all orbital planes. Ground equipment 700 is an example of ground equipment. 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 a terminal connected to the ground station via a network. Further, the ground equipment may include a communication device mounted on a moving body such as an aircraft, a self-propelled vehicle, or a mobile terminal.

Ground facility 700 forms satellite constellation 20 by communicating with each satellite 30 . Ground facility 700 is provided in orbit transition support device 100 . Ground facility 700 includes processor 910 and other hardware such as memory 921 , secondary storage 922 , input interface 930 , output interface 940 and communication device 950 . The processor 910 is connected to other hardware via signal lines and controls these other hardware. The hardware of the ground facility 700 is the same as the hardware of the track transition support device 100 described later with reference to FIG. 9 .

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

Communication device 950 transmits and receives signals for tracking and controlling each satellite 30 of satellite constellation 300 comprising satellite constellation 20 . The communication device 950 also transmits orbit control commands 55 to each satellite 30 .
The analytical prediction unit 520 analyzes and predicts the orbit of the satellite 30 .
The orbit control command generator 510 generates an orbit control command 55 to be transmitted to the satellite 30 .
The orbit control command generation unit 510 and analysis prediction unit 520 realize the function of the satellite constellation formation unit 11 . That is, the orbit control command generation unit 510 and the analysis prediction unit 520 are examples of the satellite constellation formation unit 11 .

FIG. 8 is a diagram showing a functional configuration example of the satellite constellation forming system 600. As shown in FIG.
The satellite 30 further comprises a satellite constellation forming part 11 b forming the satellite constellation 20 . The satellite constellation forming unit 11b of each satellite 30 of the plurality of satellites cooperates with the satellite constellation forming unit 11 provided in each of the ground facilities 700 to realize the functions of the satellite constellation forming system 600. . Note that the satellite constellation forming unit 11 b of the satellite 30 may be provided in the satellite control device 31 .

Next, the trajectory transition support device 100 according to this embodiment will be described.
The orbit transition support device 100 supports the orbit transition of a transition satellite 301 that is injected into the geostationary transfer orbit GTO and overtakes the orbital altitude of the satellite constellation 20 formed on the way from perigee to apogee in the geostationary transfer orbit GTO.
The transition satellite 301 is a satellite such as a geostationary orbit satellite or a quasi-zenith orbit satellite. After the transition satellite 301 is put into the geostationary transfer orbit GTO after launching the rocket, the transition satellite 301 operates the propulsion device of its own satellite to transition to a desired orbit. The orbit transition support device 100 avoids collision with a mega-constellation satellite group formed at an orbit altitude from the perigee to the apogee of the geostationary transfer orbit GTO when the transition satellite 301 orbit transitions. Realize support for

*** Configuration description ***
FIG. 9 is a configuration diagram of a track transition support device 100 according to this embodiment.
The track transition support device 100 communicates with the management business device 40 . The orbit transition support device 100 may be mounted on ground equipment. Orbit transition support device 100 may be installed in satellite constellation forming system 600 . Alternatively, the track transition support device 100 may be mounted on at least one of the management business devices 40 .

Management business unit 40 provides information about space objects 60 such as satellites or debris. The management enterprise device 40 is an enterprise computer that collects information about space objects 60 such as satellites or debris.
Management business equipment 40 includes mega constellation business equipment 41 , LEO constellation business equipment 42 , satellite business equipment 43 , orbit transition business equipment 44 , debris collection business equipment 45 , rocket launch business equipment 46 , and SSA business equipment 47 . Includes equipment. LEO is an abbreviation for Low Earth Orbit.

The mega-constellation business device 41 is a large-scale satellite constellation, that is, a mega-constellation business operator's computer that conducts mega-constellation business.
The LEO constellation business unit 42 is the computer of the LEO constellation operator that conducts the low earth orbit constellation, ie the LEO constellation business.
The satellite operator 43 is a satellite operator's computer that handles one to several satellites.
The orbital transition business unit 44 is a computer of an orbital transition business operator that supports satellite orbital transitions.
The debris collection business device 45 is a computer of a debris collection business that conducts a business of collecting debris.
Rocket launcher equipment 46 is the rocket launcher's computer that conducts the rocket launch business.
The SSA business device 47 is a computer of the SSA business that conducts the SSA business, that is, the space situational awareness business.

The management business device 40 may be any other device as long as it collects information about space objects such as satellites or debris and provides the collected information to the orbit transition support device 100 . Further, when the track transition support device 100 is installed on the SSA public server, the track transition support device 100 may function as the SSA public server.
Information provided from the management business device 40 to the track transition support device 100 will be described later in detail.

The track transition support device 100 includes a processor 910 and 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 other hardware via signal lines and controls these other hardware.

The track transition support device 100 includes a support information generation unit 110, a support information display unit 120, and a storage unit 130 as functional elements. Trajectory forecast information 51 is stored in the storage unit 130 .

The functions of the support information generation unit 110 and the support information display unit 120 are implemented by software. Storage unit 130 is provided in memory 921 . Alternatively, storage unit 130 may be provided in auxiliary storage device 922 . Also, the storage unit 130 may be divided into a memory 921 and an auxiliary storage device 922 .

Processor 910 is a device that executes an orbit transition support program. The orbit transition support program is a program that implements the functions of the support information generation unit 110 and the support information display unit 120 .
The processor 910 is an IC (Integrated Circuit) that performs arithmetic processing. A specific example of the processor 910 is a CPU (Central Processing
Unit), DSP (Digital Signal Processor), and GPU (Graphics Processing Unit).

The 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. 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 disk, Blu-ray (registered trademark) disk, or DVD. Note that HDD is an abbreviation for Hard Disk Drive. SD® is an abbreviation for Secure Digital. CF is an abbreviation for CompactFlash®. DVD is an abbreviation for Digital Versatile Disk.

The input interface 930 is a port connected to an input device such as a mouse, keyboard, or touch panel. The input interface 930 is specifically a USB (Universal Serial Bus) terminal. 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. The display is specifically an LCD (Liquid Crystal Display).

Communication device 950 has a receiver and a transmitter. The communication device 950 is specifically a communication chip or a NIC (Network Interface Card). The track transition support device 100 communicates with the management business device 40 via the communication device 950 .

The trajectory transition assistance program is read into processor 910 and executed by processor 910 . The memory 921 stores not only the trajectory transition support program but also an OS (Operating System). The processor 910 executes the track transition support program while executing the OS. The trajectory transition support program and OS may be stored in the auxiliary storage device 922 . The trajectory transition support program 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 orbit transition support program may be incorporated in the OS.

Trajectory transition support device 100 may include a plurality of processors that substitute for processor 910 . These multiple processors share program execution. Each processor, like processor 910, is a device that executes a program.

The data, information, signal values and variable values used, processed or output by the programs may be stored in memory 921 , secondary storage 922 , registers or cache memory within processor 910 .

The “part” of each part of the support information generation unit 110 and the support information display unit 120 may be read as “processing”, “procedure” or “process”. Also, the "processing" of the support information generation process and the support information display process may be read as "program", "program product", or "computer-readable recording medium recording the program".
The trajectory transition support program causes the computer to execute each process, each procedure, or each process, where the "section" of each section is read as "processing,""procedure," or "step." Further, the orbit transition support method is a method performed by the orbit transition support device 100 executing the orbit transition support program.
The track transition assistance program may be stored in a computer-readable recording medium and provided. Each program may also be provided as a program product.

Next, the relationship between the geostationary transfer orbit and the satellite constellation, which is the premise of this embodiment, will be described with reference to FIGS. 10 and 11. FIG.
Specifically, the mega-constellation operator plans to build a constellation of satellites at three different orbital altitudes near an orbital altitude of 340 km. The satellite constellations consist of approximately 2500 satellites each, for a total of 7500 satellites.
When launching a transition satellite 301 such as a geostationary orbit satellite or a quasi-zenith orbit satellite, first, the transition satellite 301 is put into an orbit called a geostationary transfer orbit GTO by a rocket. The rocket and transition satellite 301 are then separated. The transition satellite 301 operates the propulsion device to orbit transition to the target geostationary orbit position. The orbital transition is an elliptical orbit above the equator. For example, in a propulsion device using chemical propulsion, the propulsion device is operated at the apogee, the perigee altitude is raised, and this operation is repeated until the target orbit is reached. In the orbit transition by electric propulsion, the electric propulsion device is continuously jetted in the traveling direction to increase the speed, and when the desired speed is reached, injection into the geostationary orbit or the quasi-zenith orbit is completed.

In this process, transition satellite 301 must overtake the orbital altitude of the constellation, which is built at an altitude of, for example, 340 km. However, mega-constellations are equipped with satellites all over the sky and fly like a mesh. Therefore, there is a risk that the transition satellite 301, when passing over the equator, will collide with a constituent satellite of the mega-constellation that happens to cross over the equator.

FIG. 12 is a diagram showing a satellite flight image near an orbital altitude of 340 km.
For example, as a satellite constellation near an altitude of 340 km, a mega constellation consisting of 2400 satellites with 40 orbital planes and 60 satellites/surface is assumed. At this time, the interval from when the satellite in the same orbital plane passes over the equator to when the subsequent satellite passes over the equator is about 90 seconds. Also, the interval from when the satellite passes over the equator to when another satellite in an adjacent orbit passes over the equator is about 18 minutes.
When a satellite constellation with a total of 3 altitudes is constructed at different orbital altitudes near an orbital altitude of 340 km, the orbital planes at different orbital altitudes rotate without synchronism. varies in many ways.

Assume that a rocket launcher with a launch point above the equator launches a rocket. In order to avoid a collision when passing near an orbital altitude of 340 km and reaching the sky above it, it is necessary to launch the satellite in the gap where the satellite crosses the orbital plane above the launch point. There is only a margin of a few minutes for the to pass through.
The rocket can manage its launch timing, so it is possible to precisely avoid this gap. However, it is an extremely severe condition for a satellite in the middle of an orbital transition to intentionally cross this gap and overtake the orbital altitude.
Also, when a rocket is launched into the sky, it can instantly pass through a dense altitude of about 340 km at an angle close to the normal direction. However, since the geostationary transfer orbit ellipse has a similar circular ratio, the orbit crossing angle for overtaking 340 km altitude is shallow and the transit time is long, so the risk of collision is much higher.
For this reason, an orbit transition support device is required to pass through the dense altitude.

***Description of operation***
FIG. 13 is a diagram showing an example of trajectory forecast information 51 according to this embodiment.
The orbit transition support device 100 stores the orbital forecast information 51 in which the orbital forecast value of the space object 60 is set in the storage unit 130 . The orbit transition support device 100 acquires orbit forecast values for each of the plurality of space objects 60 from, for example, a management business device 40 used by a management operator who manages the plurality of space objects 60, and generates orbit forecast information 51. may be stored as Alternatively, the orbit transition support device 100 may acquire orbit forecast information 51 in which forecast values for the orbits of each of the plurality of space objects 60 are set from the management company and store it in the storage unit 130 .
Management companies are companies that manage space objects 60 flying in space, such as satellite constellations, various satellites, rockets, and debris. In addition, as described above, the management business equipment 40 used by each management company includes the mega constellation business equipment 41, the LEO constellation business equipment 42, the satellite business equipment 43, the orbit transition business equipment 44, and the debris collection business equipment. 45, Rocket Launch Enterprise Equipment 46, and SSA Enterprise Equipment 47.

A space object ID (Identifier) 511, a forecast epoch 512, a forecast orbit element 513, a forecast error 514, and a forecast flight state 515 are set in the orbit forecast information 51, for example.

The space object ID 511 is an identifier that identifies the space object 60 . In FIG. 11 , a satellite ID and a debris ID are set as the space object ID 511 . Space objects are, specifically, objects such as rockets launched into outer space, artificial satellites, space stations, debris collection satellites, planetary exploration spacecraft, and satellites or rockets that have been turned into debris after the end of their missions.

Predicted epochs 512 are epochs that are predicted for the orbits of each of a plurality of space objects.
Forecast orbital elements 513 are orbital elements that specify the orbits of each of a plurality of space objects. Predicted orbital elements 513 are orbital elements predicted for the orbits of each of a plurality of space objects. In FIG. 11, six Keplerian orbital elements are set as forecast orbital elements 513 .

Forecast error 514 is the error predicted in the orbits of each of a plurality of space objects. The forecast error 514 includes the heading error, the orthogonal error, and the basis for the error. In this way, the forecast error 514 explicitly indicates the amount of error included in the actual value along with the grounds. The grounds for the amount of error include part or all of the measurement means, the content of data processing performed as means for improving the accuracy of position coordinate information, and the results of statistical evaluation of past data.

Forecast flight conditions 515 are forecasts of flight conditions for each of a plurality of space objects. In the predicted flight state 515, it is set whether the predicted flight state of each of the plurality of space objects is a steady operation state, a launch transient state, or a post-leaving transient state. Further, the predicted flight state 515 may include whether or not avoidance operation is to be performed or whether autonomous avoidance operation is to be performed.

In the orbit forecast information 51 according to the present embodiment, a forecast epoch 512 and a forecast orbit element 513 are set for the space object 60 . The time and position coordinates of the space object 60 in the near future can be obtained from the forecast epoch 512 and the forecast orbital element 513 . For example, near-future time and position coordinates of the space object 60 may be set in the orbit forecast information 51 .
Thus, the orbital forecast information 51 is provided with orbital information of the space object including the epoch and orbital elements, or time and position coordinates, and explicitly indicates near-future forecast values of the space object 60. there is

FIG. 14 is a flow diagram of the trajectory transition support processing S100 by the trajectory transition support device 100 according to the present embodiment.
In step S101, the support information generation unit 110 collects orbital forecast values for each of the plurality of satellites that make up the satellite constellation from the orbital forecast information 51, and obtains the support information 111 that is used to assist the orbital transition of the transition satellite 301. to generate As described above, the transition satellite 301 is specifically a geostationary orbit satellite or a quasi-zenith orbit satellite injected into the geostationary transfer orbit GTO.
In step S<b>102 , the support information display unit 120 displays the support information 111 on the display device 941 .

<Example 1 of Support Information 111>
The support information generation unit 110 generates, as the support information 111, the orbital altitude of each of the plurality of satellites and the equatorial sky transit time, which is the time at which each of the plurality of satellites crosses the equatorial sky. Specifically, the support information generator 110 calculates the orbital altitude and the equatorial flight time of each of the plurality of satellites based on the orbital forecast information 51 .
The support information display unit 120 displays the orbital altitude and equatorial flight time of each of the plurality of satellites on the display device 941 .

FIG. 15 is a diagram showing Example 1 of support information 111 according to the present embodiment.
As shown in FIG. 15, the support information display unit 120 displays the satellite ID of each satellite in the satellite constellation, the orbital altitude, and the equatorial flight time on the display device 941 in a table format. Further, the support information display unit 120 may display prediction errors such as distance prediction errors and time prediction errors.

<Example 2 of Support Information 111>
The support information generation unit 110 generates, as support information 111, an interval between the equatorial overpass time of each of a plurality of satellites and the equatorial overpass time of a succeeding satellite flying in the same orbit or another satellite flying in an adjacent orbit. . Specifically, based on the orbital forecast information 51, the support information generation unit 110 calculates the equatorial overpass time of each of the plurality of satellites and the equatorial overflight of a subsequent satellite flying in the same orbit or another satellite flying in an adjacent orbit. Calculate the interval with the passage time.
The support information display unit 120 displays on the display device 941 the interval between the equatorial overpass time of each of the plurality of satellites and the equatorial overpass time of a succeeding satellite flying in the same orbit or another satellite flying in an adjacent orbit.

FIG. 16 is a diagram showing Example 2 of support information 111 according to the present embodiment.
As shown in FIG. 16, the time 112 when the satellite 30 of the satellite constellation 20 passes over the equator and the interval 113 until the next time when the satellite 30 crosses the equator may be displayed superimposed on the figure.
In FIG. 16, satellite 30a crosses the equator at time ta, then satellite 30b crosses the equator at time tb, then satellite 30c crosses the equator at time tc, and satellite 30d next crosses the equator at time td. is superimposed on the figure. Furthermore, the interval I1 from ta to tb, the interval I2 from tb to tc and the interval I3 from tc to td are superimposed on the diagram.
The time 112 when the satellite 30 passes over the equator and the interval 113 until the next time when the satellite 30 crosses over the equator may be displayed in a tabular form.

<Example 3 of Support Information 111>
The support information generation unit 110 analyzes the components obtained by projecting the velocity vectors of the plurality of satellites onto the equatorial plane as the support information 111, and generates the equator passage timing and the circumferential direction velocity vector projected onto the circular orbit above the equator. . The equatorial passage timing of the satellite is the equatorial air passage time 112 of the satellite. Specifically, based on the orbital forecast information 51, the support information generation unit 110 calculates the equatorial passage timing and the circumferential direction velocity vector projected onto the circular orbit above the equator for each of the plurality of satellites.
The support information display unit 120 displays on the display device 941 the equatorial passage timing and the circumferential direction velocity vector projected onto the circular orbit above the equator for each of the plurality of satellites.

FIG. 17 is a diagram showing example 3 of support information 111 according to the present embodiment.
In FIG. 17, the upper part shows an image of satellites 30a, 30b, 30c, and 30d passing over the equator in the satellite constellation 20, for example.

The middle part shows the equator passage timing ta and the circumferential velocity vector va of the satellite 30a, which is a single satellite. For example, when the user selects the satellite ID of a single satellite 30a, a diagram representing the equatorial passage timing ta and the circumferential velocity vector va of the satellite 30a is displayed.

The lower part shows equator passage timings ta, tb, tc, and td of satellites 30a, 30b, 30c, and 30d, which are multiple satellites, and circumferential velocity vectors va, vb, vc, and vd. For example, when the user designates a time range from ta to td, the equator passage timings ta, tb, tc, and td of the satellites 30a, 30b, 30c, and 30d and the circumferential velocity vectors va, vb, vc, and vd is displayed.

<Example 4 of Support Information 111>
The support information generation unit 110 generates, as the support information 111, the satellite passage timing T at which the transition satellite 301 passes the orbital altitude at which the satellite constellation is constructed. Specifically, based on the orbital forecast information 51, the support information generator 110 calculates the satellite passage timing T at which the transition satellite 301 passes at the orbital altitude where the satellite constellation is constructed.
The support information display unit 120 displays on the display device 941 the satellite passage timing T at which the transition satellite 301 passes at the orbital altitude where the satellite constellation is constructed.

In the transition satellite 301, such as a geostationary orbit satellite and a quasi-zenith orbit satellite, in the process of reaching a target orbital position, the optimum timing for operating the propulsion device is determined depending on the flight altitude and position of the orbit. Therefore, it is not possible to freely choose the timing of crossing the orbital altitude where the mega-constellation is formed.
The orbit transition support device 100 acquires in advance the optimum transition orbit of the transition satellite 301 as an orbit transition planning orbit. The support information generation unit 110 analyzes the satellite passage timing T that is suitable as the timing for crossing the orbital altitude where the mega-constellation is formed and that can ensure a sufficiently long interval. Based on the orbital forecast information 51 of the constituent satellites of the mega-constellation, the support information generating unit 110 generates an image within the interval between the time when an arbitrary satellite crosses the equatorial sky and the time when a subsequent satellite or another satellite in an adjacent orbit crosses the equator. to calculate the most appropriate satellite passing timing.
The support information display unit 120 displays the appropriate satellite passage timing T for the transition satellite 301 to pass the specific altitude.

FIG. 18 is a diagram showing example 4 of support information 111 according to the present embodiment.
FIG. 18 displays candidates for the optimum satellite passage timing T at which the transition satellite 301 passes through a specific altitude, which is the mega-constellation orbital altitude. As shown in FIG. 18, one candidate for the optimum satellite passage timing T may be displayed for a specific altitude, or a plurality of candidates for the satellite passage timing T may be displayed.

***Description of the effects of the present embodiment***
According to the orbit transition support apparatus 100 according to the present embodiment, useful support information is displayed when the transition satellite overtakes the orbit altitude of the satellite constellation, so collision can be avoided and safe orbit transition can be supported. can be done.

FIG. 19 is a diagram schematically showing a method for the satellite to overtake the orbital altitude.
As a method for the transition satellite 301 to overtake the orbital altitude of the satellite constellation 20, overtaking is performed at an orbital position and timing that stitches the gap from when the constituent satellites of the satellite constellation 20 pass over the equator until the following satellite passes. It is effective to
According to the orbit transition support device 100 according to the present embodiment, since the equator passage timing and the circumferential velocity vector at which the constituent satellites of the satellite constellation cross the equator are displayed, the optimal satellite passage timing and orbit for the transition orbit can be obtained. Time required for altitude passage can be analyzed. Therefore, it becomes possible to perform orbit transition after confirming that it is possible to safely pass through the orbital altitude by avoiding collision.

***Other Configurations***
In the present embodiment, as a specific example, the support information for the geostationary orbit satellite in the equatorial orbit has been used for explanation. For example, when the transition satellite is a quasi-zenith orbit satellite, it is as follows.
The support information generation unit calculates the orbital altitude of each of the plurality of satellites and the quasi-zenith orbit plane transit time as support information based on the orbital forecast information. The quasi-zenith orbit plane crossing time is the time when each of the plurality of satellites crosses the orbital plane during the orbital transition of the quasi-zenith orbit satellite. Then, the support information display unit displays the orbital altitude and the quasi-zenith orbit plane transit time of each of the plurality of satellites on the display device.

In the present embodiment, the functions of trajectory transition support device 100 are realized by software. As a modification, the functions of the trajectory transition support device 100 may be realized by hardware.

FIG. 20 is a diagram showing the configuration of track transition support device 100 according to a modification of the present embodiment.
The orbit transition support device 100 includes an electronic circuit instead of the processor 910 .
The electronic circuit is a dedicated electronic circuit that realizes the functions of the orbit transition support device 100 .
Electronic circuits are specifically single circuits, compound circuits, programmed processors, parallel programmed processors, logic ICs, GAs, ASICs or FPGAs. GA is an abbreviation for Gate Array.
The functions of the trajectory transition support device 100 may be implemented by one electronic circuit, or may be implemented by being distributed among a plurality of electronic circuits.
As another modification, some functions of the trajectory transition support device 100 may be realized by electronic circuits, and the remaining functions may be realized by software.

Each of the processor and electronic circuitry is also called processing circuitry. That is, the functions of the trajectory transition support device 100 are realized by the processing circuitry.

In the first embodiment described above, each part of the track transition support device has been described as an independent functional block. However, the configuration of the trajectory transition support device may be different from that of the above-described embodiment. The functional blocks of the trajectory transition support device may have any configuration as long as they can realize the functions described in the above embodiments. Further, the orbit transition support device may be a single device or a system composed of a plurality of devices.

Moreover, it is also possible to combine a plurality of portions of the first embodiment. Alternatively, one portion of this embodiment may be implemented. In addition, this embodiment may be implemented as a whole or partially in any combination.
That is, in Embodiment 1, it is possible to freely combine portions of Embodiment 1, modify arbitrary constituent elements, or omit arbitrary constituent elements in Embodiment 1. FIG.

The above-described embodiments are essentially preferable examples, and are not intended to limit the scope of the invention, the scope of applications of the invention, or the scope of applications of the invention. Various modifications can be made to the above-described embodiments as required.

20 satellite constellation, 21 orbital plane, 30, 30a, 30b, 30c, 30d satellite, 301 transition satellite, 31 satellite control device, 32 satellite communication device, 33 propulsion device, 34 attitude control device, 35 power supply device, 40 management business equipment, 41 mega constellation business equipment, 42 LEO constellation business equipment, 43 satellite business equipment, 44 orbit transfer business equipment, 45 debris collection business equipment, 46 rocket launch business equipment, 47 SSA business equipment, 51 orbit forecast information, 511 , 521 space object ID, 512 forecast epoch, 513 forecast orbital element, 514 forecast error, 515 forecast flight state, 60 space object, 70 earth, 100 orbit transition support device, 110 support information generator, 111 support information, 112 equator Sky passage time 113 Interval 120 Support information display unit 130 Storage unit 55 Orbit control command 600 Satellite constellation formation system 11, 11b Satellite constellation formation unit 300 Satellite group 700 Ground equipment 510 Orbit control command Generation Unit 520 Analysis Prediction Unit 910 Processor 921 Memory 922 Auxiliary Storage Device 930 Input Interface 940 Output Interface 941 Display Device 950 Communication Device.

Claims (10)

An orbit transition support device for supporting orbit transition of a transition satellite that is injected into a geostationary transfer orbit and overtakes an orbital altitude of a satellite constellation formed on the way from perigee to apogee in the geostationary transfer orbit,
The satellite constellation is a large-scale satellite constellation in which a plurality of satellites ranging from hundreds to thousands are deployed exhaustively in the sky and the plurality of satellites fly in a mesh pattern,
Assistance information used for assisting the orbit transition of the transition satellite by collecting orbit forecast values of each of the plurality of satellites forming the satellite constellation from the orbit forecast information in which the orbit forecast values of space objects are set. wherein the interval between the equatorial overflight time of each of the plurality of satellites and the equatorial overflight time of a succeeding satellite flying in the same orbit or another satellite flying in an adjacent orbit is supported. a support information generation unit that generates information ;
and a support information display unit that displays the support information on a display device. An orbit transition support device for supporting orbit transition of a transition satellite that is injected into a geostationary transfer orbit and overtakes an orbital altitude of a satellite constellation formed on the way from perigee to apogee in the geostationary transfer orbit,
The satellite constellation is a large-scale satellite constellation in which a plurality of satellites ranging from hundreds to thousands are deployed exhaustively in the sky and the plurality of satellites fly in a mesh pattern,
Assistance information used for assisting the orbit transition of the transition satellite by collecting orbit forecast values of each of the plurality of satellites forming the satellite constellation from the orbit forecast information in which the orbit forecast values of space objects are set. which analyzes the components obtained by projecting the velocity vectors of each of the plurality of satellites onto the equatorial plane, and calculates the equatorial passage timing and the circumferential direction velocity vector projected onto the circular orbit above the equator. a support information generation unit that generates information;
a support information display unit that displays the support information on a display device;
Trajectory transition support device with. 3. The orbit transition support device according to claim 1, wherein said transition satellite inserted into said geostationary transfer orbit is a geostationary orbit satellite or a quasi-zenith orbit satellite. The support information generation unit
4. The method according to any one of claims 1 to 3, wherein an orbital altitude of each of the plurality of satellites and an equatorial flight time at which each of the plurality of satellites crosses the equatorial sky are generated as the support information. Orbit transition support device described. The support information generation unit
The orbital altitude of each of the plurality of satellites and the quasi-zenith orbit plane crossing time, which is the time at which each of the plurality of satellites crosses the orbital plane during orbit transition of the quasi-zenith orbit satellite, is generated as the support information. The orbit transition support device according to any one of claims 1 to 3. The support information generation unit
6. The orbit transition support device according to any one of claims 1 to 5 , wherein, at an orbit altitude at which the satellite constellation is constructed, passage timing at which the transition satellite passes is generated as the support information. An orbit transition support method for supporting orbit transition of a transition satellite that is injected into a geostationary transfer orbit and overtakes an orbital altitude of a satellite constellation formed on the way from perigee to apogee in the geostationary transfer orbit,
The satellite constellation is a large-scale satellite constellation in which a plurality of satellites ranging from hundreds to thousands are deployed exhaustively in the sky and the plurality of satellites fly in a mesh pattern,
A computer collects predicted values of orbits of each of the plurality of satellites constituting the satellite constellation from orbital forecast information in which predicted values of orbits of space objects are set, and assists orbit transition of the transition satellite. Generating support information to be used, which is an interval between the equatorial overflight time of each of the plurality of satellites and the equatorial overflight time of a subsequent satellite flying in the same orbit or another satellite flying in an adjacent orbit. ,
A track transition support method in which a computer displays the support information on a display device. An orbit transition support method for supporting orbit transition of a transition satellite that is injected into a geostationary transfer orbit and overtakes an orbital altitude of a satellite constellation formed on the way from perigee to apogee in the geostationary transfer orbit,
The satellite constellation is a large-scale satellite constellation in which a plurality of satellites ranging from hundreds to thousands are deployed exhaustively in the sky and the plurality of satellites fly in a mesh pattern,
orbits of said transition satellites obtained by a computer collecting predicted values of orbits of each of said plurality of satellites constituting said satellite constellation from orbital forecast information in which predicted values of orbits of space objects are set; Equator passage timing and circumferential velocity projected onto a circular orbit above the equator, which are support information used for transition support, and are obtained by analyzing components obtained by projecting the velocity vectors of each of the plurality of satellites onto the equatorial plane. generate the supporting information, which is a vector,
A track transition support method in which a computer displays the support information on a display device. In an orbit transition support program for supporting orbit transition of a transition satellite that is injected into a geostationary transfer orbit and overtakes an orbital altitude of a satellite constellation formed on the way from perigee to apogee in the geostationary transfer orbit,
The satellite constellation is a large-scale satellite constellation in which a plurality of satellites ranging from hundreds to thousands are deployed exhaustively in the sky and the plurality of satellites fly in a mesh pattern,
Assistance information used for assisting the orbit transition of the transition satellite by collecting orbit forecast values of each of the plurality of satellites forming the satellite constellation from the orbit forecast information in which the orbit forecast values of space objects are set. wherein the interval between the equatorial overflight time of each of the plurality of satellites and the equatorial overflight time of a succeeding satellite flying in the same orbit or another satellite flying in an adjacent orbit is supported. a support information generation process for generating information ;
A track transition support program for causing a computer to execute a support information display process for displaying the support information on a display device. In an orbit transition support program for supporting orbit transition of a transition satellite that is injected into a geostationary transfer orbit and overtakes an orbital altitude of a satellite constellation formed on the way from perigee to apogee in the geostationary transfer orbit,
The satellite constellation is a large-scale satellite constellation in which a plurality of satellites ranging from hundreds to thousands are deployed exhaustively in the sky and the plurality of satellites fly in a mesh pattern,
Assistance information used for assisting the orbit transition of the transition satellite by collecting orbit forecast values of each of the plurality of satellites forming the satellite constellation from the orbit forecast information in which the orbit forecast values of space objects are set. Analyzing components obtained by projecting the velocity vector of each of the plurality of satellites onto the equatorial plane, and calculating the equatorial passage timing and the circumferential direction velocity vector projected onto the circular orbit above the equator. a support information generation process for generating information;
a support information display process for displaying the support information on a display device;
orbit transition support program that causes a computer to execute

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