JP2021054166A - Rocket launching support device, rocket launching support method, rocket launching support program, rocket, rocket launching method, and rocket launching support system - Google Patents

Abstract

To effectively support collision avoidance between a rocket and satellites constituting a satellite constellation in rocket launching.SOLUTION: A region calculation part 110 calculates, based upon position coordinates of a rocket launching place and satellite orbit prediction information 51 in which a predicted value of an orbit of a satellite is set, a time region in which there is no risk of collision against a satellite constituting a satellite constellation that a rocket launched at the rocket launching place 201 passes through above the rocket launching place as a passable time region 111. A region notification part 120 outputs the passable time region 111.SELECTED DRAWING: Figure 10

Description

The present invention relates to a rocket launch support device, a rocket launch support method, a rocket launch support program, a rocket, a rocket launch method, and a rocket launch support system.

In recent years, the construction of hundreds to thousands of large-scale satellite constellations, so-called mega constellations, has begun, increasing the risk of satellite collisions in orbit. In addition, space debris such as satellites that have become uncontrollable due to breakdowns or rocket debris is increasing.
With the rapid increase of space objects such as satellites and space debris in outer space, there is an increasing need for international rules to avoid collisions of space objects in space traffic control (STM).

In recent years, mega constellation companies that operate mega constellations have appeared. There is a plan to deploy satellites comprehensively in the sky as follows by the same mega constellation operator.
Orbital altitude about 336km: Orbital inclination 42 degrees, about 2500 Orbital altitude about 341km: Orbital inclination 48 degrees, about 2500 Orbital altitude about 346km: Orbital inclination 53 degrees, about 2500 Orbital altitude about 550km: Orbital inclination about 550km 53 degrees, about 1600 orbit altitude about 1150 km: orbit inclination angle 53 degrees, about 1600

In addition, another mega constellation operator has announced plans to deploy a total of 3236 satellites as follows: The orbit inclination angle is 39 to 56 degrees.
Orbital altitude about 590km: 784 orbital altitude about 610km: 1296 Orbital altitude about 630km: 1156 For example, there is a concept of rocket launch site development in Taiki-cho, Hokkaido, Japan at 42 degrees north latitude.

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

JP-A-2017-114159

As described above, the sky above a place such as a latitude of 42 degrees, 48 degrees, or 53 degrees is a latitude zone where satellites constituting a mega constellation are concentrated. Therefore, there is a problem that it is extremely difficult for a rocket launcher to avoid a collision with a satellite when launching a rocket.
However, Patent Document 1 does not describe a measure for avoiding such a collision.

An object of the present invention is to effectively support collision avoidance between a rocket and a satellite constituting a satellite constellation at the time of launching a rocket.

The rocket launch support device according to the present invention is
Based on the position coordinates of the rocket launch site and the satellite orbit forecast information in which the predicted value of the satellite orbit is set, the satellite constellation in which the rocket launched from the rocket launch site passes over the rocket launch site is performed. An area calculation unit that calculates a time area that does not have the risk of colliding with the constituent satellites as a passable time area,
It is provided with an area notification unit that outputs the passable time area.

According to the rocket launch support device according to the present invention, there is an effect that collision avoidance between the rocket and the satellites constituting the satellite constellation can be effectively supported at the time of rocket launch.

An example in which multiple satellites work together to realize communication services throughout the globe. An example in which multiple satellites with a single orbital plane realize earth observation services. An example of a satellite constellation with multiple orbital planes that intersect near the polar regions. An example of a satellite constellation with multiple orbital planes that intersect outside the polar regions. A block diagram of a satellite constellation formation system. The block diagram of the satellite of the satellite constellation formation system. A block diagram of the ground equipment of the satellite constellation formation system. Functional configuration example of satellite constellation formation system. An example of a satellite constellation near 42 degrees north latitude. The block diagram of the rocket launch support device which concerns on Embodiment 1. FIG. The figure which shows the example of the satellite orbit forecast information which concerns on Embodiment 1. FIG. FIG. 6 is an image diagram of a rocket launch according to the first embodiment. FIG. 5 is a flow chart of a rocket launch support process by the rocket launch support device according to the first embodiment. The figure which shows the example which launches the rocket which concerns on Embodiment 1 directly above. The figure which shows the example which launches the rocket which concerns on Embodiment 1 in an oblique direction. The figure which shows the example of the passable time region which expects the prediction error which concerns on Embodiment 1. FIG. The figure which shows the display example 1 and the display example 2 of the passable time area which concerns on Embodiment 1. The figure which shows the display example 3 of the passable time area which concerns on Embodiment 1. FIG. The figure which shows the structure of the rocket launch support device which concerns on the modification of Embodiment 1. The block diagram of the rocket launch support device which concerns on Embodiment 2. FIG. 5 is a flow chart of a rocket launch support process by the rocket launch support device according to the second embodiment. Image of satellite flight near an orbital altitude of 340 km. The figure which shows an example of the satellite constellation near an orbital altitude of 340 km. The figure which shows the rocket launch example. The figure which shows the example of the relative distance A between a rocket and another space object which is an index of the flight safety area which concerns on the modification of Embodiment 1. FIG. FIG. 6 is a diagram showing an example of a relative distance B between a rocket and another space object, which is an index of a collision danger region according to a modified example of the first embodiment. The figure which shows the state which the flight safety area which concerns on the modification of Embodiment 1 is not secured. The figure which shows the state of the launch window by the size of the error range which concerns on the modification of Embodiment 1.

Hereinafter, embodiments of the present invention will be described with reference to the drawings. In each figure, the same or corresponding parts are designated by the same reference numerals. In the description of the embodiment, the description will be omitted or simplified as appropriate for the same or corresponding parts. Further, in the drawings below, the relationship between the sizes of each configuration may differ from the actual one. Further, in the description of the embodiment, when the direction or position such as "top", "bottom", "left", "right", "front", "rear", "front", "back" is indicated. There is. These notations are merely described as such for convenience of explanation, and do not limit the arrangement and orientation of configurations such as devices, appliances, or parts.

Embodiment 1.
An example of a satellite constellation as a premise of the following embodiment will be described.

FIG. 1 is a diagram showing an example in which a plurality of satellites cooperate with each other to realize a communication service over the entire globe of the earth 70.
FIG. 1 shows a satellite constellation 20 that realizes a communication service all over the world.
For each satellite of a plurality of satellites flying on the same orbital plane at the same altitude, the communication service range for the ground overlaps with the communication service range of the succeeding satellite. Therefore, according to such a plurality of satellites, it is possible to provide a communication service to a specific point on the ground while a plurality of satellites on the same orbital plane alternate with each other in a time-division manner. Further, by providing the adjacent track surface, it is possible to cover the communication service between the adjacent tracks on the ground. Similarly, if a large number of orbital planes are arranged approximately evenly around the earth, communication services to the ground can be provided all over the globe.

FIG. 2 is a diagram showing an example in which a plurality of satellites having a single orbital plane realize an earth observation service.
FIG. 2 shows a satellite constellation 20 that realizes an earth observation service. In the satellite constellation 20 of FIG. 2, a satellite equipped with an earth observation device, which is a radio wave sensor such as an optical sensor or a synthetic aperture radar, flies on the same orbital surface at the same altitude. In this way, in the satellite group 300 in which the subsequent satellites overlap with each other due to a time delay in the imaging range on the ground, a plurality of satellites in orbit alternately alternate with each other at a specific point on the ground to capture a ground image. By providing earth observation services.

As described above, the satellite constellation 20 is composed of a satellite group 300 composed of a plurality of satellites in each orbital plane. In the satellite constellation 20, the satellite group 300 cooperate to provide the service. Specifically, the satellite constellation 20 refers to a satellite constellation consisting of a group of satellites by a communication business service company as shown in FIG. 1 or an observation business service company as shown in FIG.

FIG. 3 is an example of a satellite constellation 20 having a plurality of orbital surfaces 21 intersecting in the vicinity of the polar region.
FIG. 4 is an example of a satellite constellation 20 having a plurality of orbital planes 21 that intersect outside the polar region.
In the satellite constellation 20 of FIG. 3, the orbital inclination angles of the orbital surfaces 21 of the plurality of orbital surfaces are about 90 degrees, and the orbital surfaces 21 of the plurality of orbital surfaces are present on different surfaces.
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 about 90 degrees, and the orbital planes 21 of the plurality of orbital planes are present on different planes.

In the satellite constellation 20 of FIG. 3, any two orbital planes intersect at a point near the polar region. Further, in the satellite constellation 20 of FIG. 4, any two orbital planes intersect at points other than the polar region. In FIG. 3, a collision of the satellite 30 may occur in the vicinity of the polar region. Further, as shown in FIG. 4, the intersections of a plurality of orbital surfaces whose orbit inclination angles are inclined more than 90 degrees depart from the polar region according to the orbit inclination angles. In addition, depending on the combination of orbital surfaces, the orbital surfaces may intersect at various positions including the vicinity of the equator. Therefore, the places where the collision of the satellite 30 may occur are diversified. Satellite 30 is also called an artificial satellite.

In particular, in recent years, the construction of hundreds to thousands of large-scale satellite constellations has begun, increasing the risk of satellite collisions in orbit. In addition, debris such as artificial satellites that have become uncontrollable due to breakdowns or rocket debris is increasing. Large-scale satellite constellations are also called mega constellations. Such debris is also called space debris.
As described above, the need for STM is increasing with the increase in debris in outer space and the rapid increase in the number of satellites including mega constellations. STM is Space
Abbreviation for Traffic Management.

Here, an example of the satellite 30 and the ground equipment 700 in the satellite constellation formation system 600 for forming the satellite constellation 20 will be described with reference to FIGS. 5 to 8. For example, the satellite constellation formation system 600 is operated by a satellite constellation operator such as a mega constellation operator, a LEO constellation operator, or another satellite operator.

FIG. 5 is a block diagram of the satellite constellation formation system 600.
The satellite constellation formation system 600 includes a computer. Although FIG. 5 shows the configuration of one computer, in reality, each satellite 30 of the plurality of satellites constituting the satellite constellation 20 and the ground equipment 700 communicating with the satellite 30 are equipped with a computer. Be done. Then, the computers provided in each of the satellites 30 of the plurality of satellites and the ground equipment 700 communicating with the satellites 30 cooperate to realize the function of the satellite constellation formation system 600. Hereinafter, an example of a computer configuration that realizes the functions of the satellite constellation formation system 600 will be described.

The satellite constellation formation system 600 includes a satellite 30 and ground equipment 700. The satellite 30 includes a satellite communication device 32 that communicates with the communication device 950 of the ground equipment 700. FIG. 5 illustrates the satellite communication device 32 among the configurations included in the satellite 30.

The satellite constellation forming system 600 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 a signal line and controls these other hardware. The hardware of the satellite constellation formation system 600 is the same as the hardware of the rocket launch support device 100 described later in FIG.

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

FIG. 6 is a block diagram of the satellite 30 of the satellite constellation formation 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, although it includes components that realize various functions, FIG. 6 describes 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.

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 equipment 700. Specifically, the satellite communication device 32 transmits various data related to its own satellite to the ground equipment 700. Further, the satellite communication device 32 receives various commands transmitted from the ground equipment 700.
The propulsion device 33 is a device that gives a propulsive force to the satellite 30, and changes the speed of the satellite 30. Specifically, the propulsion device 33 is an electric propulsion device. Specifically, the propulsion device 33 is an ion engine or a Hall thruster.
The attitude control device 34 uses the attitude of the satellite 30, the angular velocity of the satellite 30, and the line-of-sight direction (Line Of).
It is a device for controlling a posture element such as Sign). 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 described.
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 realized by hardware, software, firmware or a combination thereof.
Dedicated hardware is specifically a single circuit, a composite circuit, a programmed processor, a parallel programmed processor, an ASIC, an FPGA or a combination thereof.
ASIC is an abbreviation for Application Special Integrated Circuit. FPGA is an abbreviation for Field Programmable Gate Array.

FIG. 7 is a configuration diagram of the ground equipment 700 included in the satellite constellation formation system 600.
The ground equipment 700 programmatically controls a large number of satellites in all orbital planes. The ground equipment 700 is an example of a ground device. The ground device is composed of a ground station such as a ground antenna device, a communication device connected to the ground antenna device, or a computer, and ground equipment as a server or a terminal connected to the ground station by a network. Further, the ground device may include a communication device mounted on a moving body such as an aircraft, a self-propelled vehicle, or a mobile terminal.

The ground equipment 700 forms a satellite constellation 20 by communicating with each satellite 30. The ground equipment 700 is provided in the rocket launch support device 100. The ground equipment 700 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 a signal line and controls these other hardware. The hardware of the ground equipment 700 is the same as the hardware of the rocket launch support device 100 described later in FIG.

The ground equipment 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.

The communication device 950 transmits / receives a signal for tracking and controlling each satellite 30 of the satellite group 300 constituting the satellite constellation 20. Further, the communication device 950 transmits an orbit control command 55 to each satellite 30.
The analysis prediction unit 520 analyzes and predicts the orbit of the satellite 30.
The orbit control command generation unit 510 generates an orbit control command 55 to be transmitted to the 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 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 formation system 600.
The satellite 30 further includes a satellite constellation forming unit 11b that forms the satellite constellation 20. Then, 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 equipment 700 cooperate to realize the function of the satellite constellation forming system 600. .. The satellite constellation forming unit 11b of the satellite 30 may be provided in the satellite control device 31.

FIG. 9 is a diagram showing an example of a satellite constellation near 42 degrees north latitude.
There is a plan to develop a new rocket launch site in Taiki-cho, Hokkaido, Japan at 42 degrees north latitude. However, as shown in FIG. 9, the sky near 42 degrees, 48 degrees, or 53 degrees north latitude is a latitude zone where satellites constituting the mega constellation are concentrated. For this reason, it is extremely difficult for a rocket launcher to avoid a collision with a satellite when launching a rocket.

*** Explanation of configuration ***
FIG. 10 is a configuration diagram of the rocket launch support device 100 according to the present embodiment.
The rocket launch support system 500 includes a rocket launch support device 100.
The rocket launch support device 100 communicates with the management business device 40. The rocket launch support device 100 is mounted on the ground equipment 701. Further, the rocket launch support device 100 may be mounted on the satellite constellation formation system 600. Alternatively, the rocket launch support device 100 may be mounted on at least one of the management business devices 40 such as the rocket launch business device 46. Alternatively, the rocket launch support device 100 may be mounted on a device of another business operator such as an orbit analysis service business operator.

The management business apparatus 40 provides information on a space object 60 such as an artificial satellite or debris. The management business device 40 is a computer of a business operator that collects information about a space object 60 such as an artificial satellite or debris.
The management business device 40 includes a mega constellation business device 41, a LEO constellation business device 42, a satellite business device 43, an orbit transition business device 44, a debris recovery business device 45, a rocket launch business device 46, and an SSA business device 47. Equipment is included. LEO is an abbreviation for Low Earth Orbit.

The mega constellation business device 41 is a computer of a mega constellation business operator that carries out a mega constellation business.
The LEO constellation business apparatus 42 is a computer of a low-earth orbit constellation, that is, a computer of a LEO constellation business operator that carries out a LEO constellation business.
The satellite operator 43 is a computer of a satellite operator that handles one to several satellites.
The orbit transition operator 44 is a computer of an orbit transition operator that supports the launch of a satellite rocket.
The debris collection business device 45 is a computer of a debris collection business operator that conducts a business of collecting debris.
The rocket launch business device 46 is a computer of a rocket launch business that carries out a rocket launch business.
The SSA business device 47 is a computer of an SSA business operator that carries out an SSA business, that is, a space condition monitoring business.

The management business device 40 may be any other device as long as it is a device that collects information on space objects such as artificial satellites or debris and provides the collected information to the rocket launch support device 100. Further, when the rocket launch support device 100 is mounted on the public server of the SSA, the rocket launch support device 100 may function as the public server of the SSA.
The information provided from the management business apparatus 40 to the rocket launch support apparatus 100 will be described in detail later.

The rocket launch 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 a signal line and controls these other hardware.

The rocket launch support device 100 includes an area calculation unit 110, an area notification unit 120, and a storage unit 130 as functional elements. The storage unit 130 stores satellite orbit forecast information 51.

The functions of the area calculation unit 110 and the area notification unit 120 are realized by software. The storage unit 130 is provided in the memory 921. Alternatively, the storage unit 130 may be provided in the auxiliary storage device 922. Further, the storage unit 130 may be provided separately as a memory 921 and an auxiliary storage device 922.

Processor 910 is a device that executes a rocket launch support program. The rocket launch support program is a program that realizes the functions of the area calculation unit 110 and the area notification 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), GPU (Graphics Processing Unit).

The memory 921 is a storage device that temporarily stores data. A specific example of the memory 921 is a SRAM (Static Random Access Memory) or a DRAM (Dynamic Random Access Memory).
The 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 disc, optical disk, compact disc, Blu-ray (registered trademark) disc, or DVD. 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 Versaille 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. 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. Specifically, the output interface 940 is a USB terminal or an HDMI (registered trademark) (High Definition Multimedia Interface) terminal. Specifically, the display is an LCD (Liquid Crystal Display).

The communication device 950 has a receiver and a transmitter. Specifically, the communication device 950 is a communication chip or a NIC (Network Interface Card). The rocket launch support device 100 communicates with the management business device 40 via the communication device 950.

The rocket launch support program is loaded into processor 910 and executed by processor 910. In the memory 921, not only the rocket launch support program but also the OS (Operating System) is stored. The processor 910 executes the rocket launch support program while executing the OS. The rocket launch support program and the OS may be stored in the auxiliary storage device 922. The rocket launch support program and the OS stored in the auxiliary storage device 922 are loaded into the memory 921 and executed by the processor 910. A part or all of the rocket launch support program may be incorporated in the OS.

The rocket launch support device 100 may include a plurality of processors that replace the processor 910. These multiple processors share the execution of the program. Each processor, like the processor 910, is a device that executes a program.

Data, information, signal values and variable values used, processed or output by the program are stored in a memory 921, an auxiliary storage device 922, or a register or cache memory in the processor 910.

The "part" of each part of the rocket launch support system may be read as "processing", "procedure", "means", "step" or "process". Further, the "process" of the area calculation process and the area notification process may be read as "program", "program product", or "computer-readable recording medium on which the program is recorded".
The rocket launch support program is a process, each procedure, each means, each stage in which the "part" of each part of the rocket launch support system is read as "process", "procedure", "means", "step" or "process". Alternatively, let the computer execute each process. The rocket launch support method is a method performed by the rocket launch support device 100 executing a rocket launch support program.
The rocket launch support program may be provided stored in a computer-readable recording medium. In addition, each program may be provided as a program product.

*** Explanation of operation ***
FIG. 11 is a diagram showing an example of satellite orbit forecast information 51 according to the present embodiment.
The rocket launch support device 100 stores the satellite orbit forecast information 51 in which the forecast value of the orbit of the space object 60 is set in the storage unit 130. The rocket launch support device 100 acquires forecast values of the orbits of each of the plurality of space objects 60 from the management business device 40 used by the management company that manages the plurality of space objects 60, and satellite orbit forecast information. It may be stored as 51. Alternatively, the rocket launch support device 100 may acquire satellite orbit forecast information 51 in which forecast values of 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.
The management company is a company that manages space objects 60 flying in space such as satellite constellations, various satellites, rockets, and debris. Further, as described above, the management business equipment 40 used by each management business operator is a mega constellation business equipment 41, a LEO constellation business equipment 42, a satellite business equipment 43, an orbit transition business equipment 44, and a debris collection business equipment. Computers such as 45, rocket launch business equipment 46, and SSA business equipment 47.

Information such as a space object ID (Identifier) 511, a forecast epoch 512, a forecast orbit element 513, and a forecast error 514 is set in the satellite orbit forecast information 51.

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. Specifically, space objects are objects such as rockets launched into outer space, artificial satellites, space stations, debris recovery satellites, planetary exploration spacecraft, and satellites or rockets that have become debris after the mission is completed.

The forecast epoch 512 is the epoch predicted for each orbit of a plurality of space objects.
The forecast orbital element 513 is an orbital element that specifies the orbit of each of a plurality of space objects. The forecast orbital element 513 is an orbital element that is predicted for each orbit of a plurality of space objects. In FIG. 11, six Kepler orbital elements are set as the forecast orbital elements 513.

The forecast error 514 is an error predicted in each orbit of a plurality of space objects. A traveling direction error and an orthogonal direction error are set in the forecast error 514. The forecast error 514 explicitly indicates the amount of error included in the actual value.

In the satellite orbit forecast information 51 according to the present embodiment, the forecast epoch 512 and the 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, the near future time and position coordinates of the space object 60 may be set in the satellite orbit forecast information 51.
As described above, the satellite orbit forecast information 51 includes the orbit information of the space object including the original period and the orbital elements, or the time and position coordinates, and the near future forecast value of the space object 60 is explicitly shown. ing.
The satellite orbit forecast information 51 may have a configuration other than that shown in FIG. 11 as long as the forecast value of the space object 60 in the near future is explicitly shown.

FIG. 12 is an image diagram of the rocket launch according to the present embodiment.
The rocket 202 is launched from the rocket launch site 201 under the control of the launch control device 200. The launch control device 200 is mounted on the ground equipment 702, for example.
The rocket launch support device 100 according to the present embodiment supports the launch of the rocket 202 so that the rocket 202 can be launched without colliding with the satellite 30 of the satellite constellation 20 flying over the rocket launch site 201.

FIG. 13 is a flow chart of the rocket launch support process S100 by the rocket launch support device 100 according to the present embodiment.
In step S101, the area calculation unit 110 calculates the passable time area 111 based on the position coordinates of the rocket launch site 201 and the satellite orbit forecast information 51 in which the forecast value of the satellite orbit is set. The passable time domain 111 is a time domain in which the rocket 202 launched from the rocket launch site 201 does not have a risk of colliding with the satellite 30 constituting the satellite constellation 20 passing over the rocket launch site 201. In other words, the passable time domain 111 is the time at which the rocket 202 launched from the rocket launch site 201 whose position coordinates are fixed and known is not at risk of colliding with the satellite 30 constituting the satellite constellation 20 formed at a specific altitude. It is an area.

FIG. 14 is a diagram showing an example of launching the rocket 202 according to the present embodiment directly above.
For example, it is assumed that there is a mega constellation A formed at an orbital altitude of about 336 km and an orbital inclination of 42 degrees and composed of about 2500 satellites. Then, it is assumed that the rocket 202 is launched directly above from the rocket launch site 201 constructed in Taiki-cho, Hokkaido, which is located at 42 degrees north latitude and 143 degrees east longitude. At this time, the rocket 202 has a risk of colliding with the satellite 30 constituting the mega constellation A at an altitude of 336 km. However, satellites flying in the same orbital plane are operated at intervals of approximately 100 km or more. Therefore, there is a return waiting time of 10 seconds or more between the time when one satellite passes over the sky and the time when the succeeding satellite passes.
While operating satellites on adjacent orbital planes at intervals in the same way, in order to avoid collisions with satellites on different orbital planes near 42 degrees north latitude, the satellites will fill the gap between satellites at 42 degrees north latitude. The operation is controlled so as to pass through.

The area calculation unit 110 takes into account the time required to reach an altitude of 336 km after launching the rocket, and excludes the time zone in which the satellite happens to pass over the sky as the “time zone at risk of collision”. The area calculation unit 110 may calculate, for example, a time zone excluding the “time zone at risk of collision” from the time zone of the day as the passable time zone 111. Alternatively, the area calculation unit 110 may calculate as the passable time area 111 a time zone excluding the “time zone at risk of collision” from the time zone designated by the user. In this way, if the "time zone with collision risk" of the satellite on the orbital surface passing near the sky above the rocket launch site 201 is excluded from the time zone, as a result, the "time domain without collision risk", that is, The passable time region 111 remains. If this information is disclosed to the rocket launcher at the rocket launch site with the time required to reach a specific altitude after launch as an incidental condition, the rocket can be launched without collision risk.

FIG. 15 is a diagram showing an example of launching the rocket 202 according to the present embodiment in an oblique direction.
Rocket 202 is not always launched directly above. For example, the area calculation unit 110 may acquire the rocket launch prediction value Ox, which is the rocket launch prediction trajectory, from the rocket launch operator in advance. The area calculation unit 110 calculates the passable time area 111 based on the rocket launch predicted value Ox and the satellite orbit forecast information 51. Specifically, the rocket launch predicted value Ox is the desired passage time and the passage position coordinates at a specific altitude, for example, an altitude of 336 km. The reason for the desire to pass is that the launch control device 200 needs to correct the launch timing according to the "time region without collision risk".

As described above, the area calculation unit 110 acquires the predicted rocket launch value Ox in which the rocket 202 launched from the rocket launch site 201 passes through the orbit of the satellite constellation 20. The area calculation unit 110 may calculate the passable time area 111 by using the rocket launch predicted value Ox acquired from the rocket launch operator.

FIG. 16 is a diagram showing an example of a passable time region 111 in which a prediction error is expected according to the present embodiment.
On the rocket launcher side, for example, the position coordinates when passing at an altitude of 336 km may include a significant prediction error. Alternatively, the satellite transit time and position coordinates on the side of the mega constellation operator may contain significant prediction errors. In FIG. 16, when such a prediction error exists, there is a concern that the time domain without collision risk, that is, the passable time domain 111 does not exist, and it is suggested that a safe rocket launch cannot be performed unless the accuracy is improved. ing.

In step S102, the area notification unit 120 outputs the passable time area 111. Specifically, the area notification unit 120 displays the passable time area 111 on the display device 941 via the output interface 940. Alternatively, the area notification unit 120 may transmit the passable time area 111 to the management business device 40 via the communication device 950.

Further, the satellite constellation 20 may be a plurality of satellite constellations formed at a plurality of orbital altitudes different from each other. For example, the plurality of satellite constellations may belong to a specific mega constellation operator. The region calculation unit 110 calculates the passable time region 111 for each of the plurality of orbital altitudes. The area notification unit 120 displays on the display device a time area in which a plurality of passable time areas 111 calculated for each of the plurality of orbital altitudes are integrated.

FIG. 17 is a diagram showing a display example 1 and a display example 2 of the passable time region 111 according to the present embodiment.
As shown in Display Example 1 of FIG. 17, the passable time region 111, which is a time region without a risk of collision, may be displayed for each of the plurality of orbital altitudes operated by the specific mega constellation operator.

For example, three types of mega constellations formed near an orbital altitude of 340 km are operated asynchronously with each other. Therefore, the movement of the orbital plane as seen from the coordinates of the specific rocket launch site or the flight position of the satellite is uncorrelated for each orbital altitude. Therefore, even if the rocket launch support device 100 displays the passable time region 111 for each orbital altitude, it is only a necessary condition of "a time region where there is no risk of collision in all orbits", and is not a sufficient condition.

For example, it is assumed that the following satellite constellation 20 exists.
Orbital altitude about 336km: Orbital inclination 42 degrees, about 2500 Orbital altitude about 341km: Orbital inclination 48 degrees, about 2500 Orbital altitude about 346km: Orbital inclination 53 degrees, about 2500

In the rocket launch support device 100 according to the present embodiment, the above three altitudes and a plurality or all orbital altitudes operated by the same mega constellation operator are "time domain without collision risk", that is, passage. The available time domain 111 is integrated. Then, as shown in Display Example 2 of FIG. 17, the “time region without risk of collision in a plurality of orbits” is displayed as the passable time region 111. As a result, the rocket launcher can safely launch all satellites operated by the mega constellation operator without collision.

Further, the satellite constellation 20 may be a plurality of satellite constellations operated by a plurality of satellite constellation operators different from each other. At this time, the area calculation unit 110 calculates the passable time area 111 for each of the plurality of satellite constellations. Then, the area notification unit 120 displays the passable time area 111 for each of the plurality of satellite constellations.

FIG. 18 is a diagram showing a display example 3 of the passable time region 111 according to the present embodiment.
In FIG. 18, the passable time region 111 is displayed for a plurality of mega constellation operators A and B.
Since the high-precision forecast values of the satellites that make up the mega-constellation are usually owned only by the mega-constellation company, it is difficult for a third party to share the high-precision forecast values of a plurality of mega-constellation companies.
In addition, the outlook at this stage is that if SPACE-X can pass through the orbital surface planned for maintenance under the Starlink concept without collision, the risk of collision with another mega constellation satellite at the time of launch is sufficiently small. However, in the future, for example, different mega constellation operators may build another mega constellation near an altitude of 400 km. Therefore, in order to realize launch without collision with any of the mega constellations, the display of Display Example 3 in FIG. 18 is preferable.
High accuracy in international coordination and space law development to avoid space collisions when mega-constellation operators, rocket launch operators, and operators that provide support services with rocket launch support devices span multiple countries. It is preferable to make the information disclosure of forecast values an international rule.

The display example of the passable time region 111 in FIGS. 17 and 18 is an example, and any display format may be used as long as the passable time region 111 can be notified.

*** Explanation of the effect of this embodiment ***
According to the rocket launch support device according to the present embodiment, it is possible to notify the rocket launcher of the passable time area of the rocket launched from the rocket launch site. In this way, if the information on the passable time area is disclosed to the rocket launcher at the rocket launch site, with the time required to reach a specific altitude as an incidental condition after the rocket is launched, the rocket can be launched without the risk of collision.

*** Other configurations ***
<Modification example 1>
The rocket launch support system acquires space object information from a space information recorder that records space object information acquired from a management business device used by a management company that manages a plurality of space objects. The rocket launch support system assists in avoiding a collision between the rocket and a space object at the time of launch.
The rocket launch support system according to the present embodiment includes a database that stores space object information acquired from the space information recorder, and a server that supports avoidance of collision between the rocket and the space object at the time of launch.

Specifically, the database may be a memory, an auxiliary storage device, or a file server. The space information recorder records space object information acquired from a management business device used by a management business operator that manages a plurality of space objects. The rocket launch support device may be equipped with a space information recorder. The space information recorder may include satellite orbit forecast information.

Specifically, the server is a rocket launch support device. The database may be provided in the server, or may be a device separate from the server. A server realizes the following stages (also called means or parts) by a processing circuit such as a processor or an electronic circuit.

The database acquires and stores the space object information of the rocket and the satellite orbit forecast information of the satellite group of the mega constellation from the space information recorder. The space object information of the rocket is the information acquired from the management business equipment of the rocket launcher by the space information recorder. The satellite orbit forecast information of the satellite group of the mega constellation is the information acquired by the space information recorder from the management business equipment of the mega constellation where there is a risk of rocket collision. The space object information of the rocket includes the position coordinates of the rocket launch site, the scheduled launch time information of the rocket, and the predicted orbit information.

The server has the following stages:
-The stage of analyzing the delay time and orbit position until the rocket launched at the scheduled launch time reaches the vicinity of the satellite constellation from the position coordinates of the rocket launch site.
-The stage of determining the relative distance A between the rocket and other space objects, which is an index of the flight safety area.
-The stage of determining the relative distance B between the rocket and other space objects, which is an index of the collision danger area.
-A stage in which satellites that may approach a shorter distance than the relative distance B are extracted from the satellite group of the satellite constellation and identified as satellites requiring attention.
-The stage where all of the satellites requiring attention simultaneously extract a safe time region that flies a longer distance than the relative distance A.
-The stage of displaying the safe time area.
-A stage where a safety confirmation message is displayed when the scheduled rocket launch time is included in the safe time area.
-When the scheduled rocket launch time is not included in the safe time area, the recommended launch time is displayed as the launch time change recommended message from the safe time area.
-The stage of notifying the rocket launcher of a safety confirmation message or a launch time change recommendation message.

The safe time domain is an example of a time domain where there is no risk of collision.

FIG. 25 is a diagram showing an example of a relative distance A between a rocket and another space object, which is an index of a flight safety area according to a modified example of the present embodiment.
FIG. 26 is a diagram showing an example of a relative distance B between a rocket and another space object, which is an index of a collision danger region according to a modified example of the present embodiment.
As shown in FIG. 25, when the server determines the relative distance A between the rocket and another space object, which is an index of the flight safety area, it needs to be regarded as the size of the space object including the error range.
Further, as shown in FIG. 26, when the server determines the relative distance B between the rocket and another space object, which is an index of the collision danger region, it is regarded as the size of the space object including the error range. When the relative distance of is 0 or less, the actual relative distance is the relative distance B.

FIG. 27 is a diagram showing a state in which the flight safety area according to the modified example of the present embodiment is not secured.
The upper part of FIG. 27 is a diagram in which a mega constellation is modeled in a two-dimensional space. In the lower part of FIG. 27, the relative distance between the rocket and the space object is almost 0 (because it is regarded as the object size including the error), and although the collision does not occur at the last minute, the flight safety area cannot be secured. ..

FIG. 28 is a diagram showing a state of the launch window depending on the size of the error range according to the modified example of the present embodiment.
The upper part of FIG. 28 is a diagram showing a state in which the flight safety area according to the present embodiment is secured. Specifically, the upper part of FIG. 28 shows a state in which the flight safety area of the rocket is secured in the own system of the mega constellation operator. Within the own system of the mega constellation operator, there is a possibility that the amount of error can be reduced by a method such as difference evaluation of intersatellite distance measurement data or GPS measurement value, and statistical data evaluation. Therefore, there is a high possibility that a flight safety area can be secured within the own system of the mega constellation operator.

On the other hand, the lower part of FIG. 28 shows a case where the precise forecast value of the mega constellation is not disclosed and the error is large. If the mega constellation operator does not disclose the amount of error, the forecast value of the mega constellation will depend on external measurement information such as the SSA operator. If the rocket launcher only knows the forecast value with a large amount of error, there is a concern that the launch window cannot be secured. That is, if the rocket launcher and the megaconste operator monopolize the precision orbit forecast value, there is a concern that the launch business will be monopolized.

<Modification 2>
In the present embodiment, the function of the rocket launch support device 100 is realized by software. As a modification, the function of the rocket launch support device 100 may be realized by hardware.

FIG. 19 is a diagram showing a configuration of a rocket launch support device 100 according to a modified example of the present embodiment.
The rocket launch support device 100 includes an electronic circuit 909 instead of the processor 910.
The electronic circuit 909 is a dedicated electronic circuit that realizes the function of the rocket launch support device 100.
The electronic circuit 909 is specifically a single circuit, a composite circuit, a programmed processor, a parallel programmed processor, a logic IC, a GA, an ASIC, or an FPGA. GA is an abbreviation for Gate Array.
The function of the rocket launch support device 100 may be realized by one electronic circuit, or may be realized by being distributed in a plurality of electronic circuits.
As another modification, some functions of the rocket launch support device 100 may be realized by an electronic circuit, and the remaining functions may be realized by software.

Each of the processor and the electronic circuit is also called a processing circuit. That is, the function of the rocket launch support device 100 is realized by the processing circuit.

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

*** Explanation of configuration ***
FIG. 20 is a diagram showing a configuration of a rocket launch support device 100 according to the present embodiment.
In the present embodiment, the area calculation unit 110 calculates the possible passage area 112. Then, the area notification unit 120 outputs the possible passage area 112 calculated by the area calculation unit 110. Other configurations are the same as those in the first embodiment.

*** Explanation of operation ***
FIG. 21 is a flow chart of the rocket launch support process S100a by the rocket launch support device 100 according to the present embodiment.
In step S101a, the area calculation unit 110 calculates the possible passage area 112 based on the position coordinates of the rocket launch site 201 and the satellite orbit forecast information 51 in which the forecast value of the satellite orbit is set. The possible passage area 112 is a passage area where the rocket 202 launched from the rocket launch site 201 does not have a risk of colliding with the satellite 30 constituting the satellite constellation 20 passing over the rocket launch site 201.

In step S102a, the area notification unit 120 outputs the possible passage area 112. For example, the area notification unit 120 displays the possible passage area 112 on the display device 941 via the output interface 940. Alternatively, the area notification unit 120 notifies the management business device 40 or the launch control device 200 of the possible passage area 112 via the communication device 950.
As a result, the launch control device 200 can launch the rocket 202 while avoiding a collision by using the possible passage region 112.

FIG. 22 is an image of satellite flight near an orbital altitude of 340 km.
FIG. 23 is a diagram showing an example of a satellite constellation near an orbital altitude of 340 km.
FIG. 24 is a diagram showing an example of launching a rocket.
Specific examples of rocket launch will be described with reference to FIGS. 22 to 24.

For example, the rocket 202 is launched from a rocket launch site 201 located at latitude 40 degrees or more north to an orbit in the latitude direction having an orbit altitude of 300 km or more and latitude 50 degrees north or more. That is, the launch control device 200 launches the rocket 202 from the rocket launch site 201 located at latitude 40 degrees or more north to the orbit in the latitude direction at an orbit altitude of 300 km or more and latitude 50 degrees north or more.

As shown in FIGS. 22 and 23, there is a plan to construct a constellation of about 7,500 aircraft at an altitude of 340 km and an orbit inclination angle of 50 degrees or less. After this plan is completed, there is a possibility that the launch window will not exist, for example, when launching directly above or south of the rocket launch site constructed in Hokkaido.
A rocket launched from a rocket launch site with a north latitude of 40 degrees or more through an orbit in a high latitude direction with an orbit altitude of 300 km or more and a north latitude of 50 degrees or more passes through a region where there is no mega constellation near the pole, so it is safe without collision risk. Can be launched.
Currently, there is a plan to develop a rocket launch site in Taiki-cho, Hokkaido, which is about 42 degrees north latitude. In addition, there is a plan to operate about 2,500 aircraft on an inclined orbit with an altitude of about 340 km and an orbit inclination angle of 42 degrees in the mega constellation concept. Since 42 degrees north latitude is a dense area where satellites turn back, it is difficult to secure a launch window directly above. Furthermore, there is a plan for an orbit inclination angle of 50 degrees, and it is extremely difficult to launch it to the south without colliding with these constellations.
On the other hand, since the constellation satellite does not exist at a latitude of 50 degrees or more north, it has the effect of avoiding a collision and launching.

As shown in FIG. 24, when launching from Taiki-cho at 42 degrees north latitude, if the orbit goes through the north at an altitude of 336 km at 42 degrees north latitude, 346 km at 53 degrees north latitude, and 590 km at 56 degrees north latitude, a mega constellation Launch is possible without the risk of collision with.

*** Explanation of the effects of this embodiment ***
In the rocket launch support device according to the present embodiment, a rocket launched from a rocket launch site having fixed position coordinates and known has a passing area where there is no risk of collision with satellites constituting a satellite constellation formed at a specific altitude. Display as a possible passage area. Therefore, the rocket launcher has the effect of avoiding a collision and launching.

In the above embodiments 1 and 2, each part of the rocket launch support device has been described as an independent functional block. However, the configuration of the rocket launch support device does not have to be the configuration as in the above-described embodiment. The functional block of the rocket launch support device may have any configuration as long as it can realize the functions described in the above-described embodiment. Further, the rocket launch support device may be one device or a system composed of a plurality of devices.

Further, in the first and second embodiments, a plurality of parts may be combined and carried out. Alternatively, one part of these embodiments may be implemented. In addition, these embodiments may be implemented in any combination as a whole or partially.
That is, the first and second embodiments may be partially and freely combined. Alternatively, in the first and second embodiments, the components may be modified in any way. That is, in the first and second embodiments, the components may be added or omitted.

It should be noted that the embodiments described above are essentially preferred examples and are not intended to limit the scope of the invention, the scope of application of the invention, and the scope of use of the invention. The above-described embodiment can be variously modified as needed.

20 satellite constellation, 21 orbital plane, 30 satellites, 31 satellite control device, 32 satellite communication device, 33 propulsion device, 34 attitude control device, 35 power supply device, 40 management business device, 41 mega constellation business device, 42 LEO constellation Ration business equipment, 43 satellite business equipment, 44 orbit transition business equipment, 45 debris recovery business equipment, 46 rocket launch business equipment, 47 SSA business equipment, 51 satellite orbit forecast information, 511,521 space object ID, 512 forecasting period, 513 Forecast orbital element, 514 Forecast error, 60 Space object, 70 Earth, 100 Rocket launch support device, 110 area calculation unit, 111 passable time area, 112 possible pass area, 120 area notification unit, 130 storage unit, 55 orbit control Command, 200 launch control device, 201 rocket launch site, 202 rocket, 600 satellite constellation formation system, 11,11b satellite constellation formation unit, 300 satellite group, 700,701,702 ground equipment, 500 rocket launch support system, 510 Orbit control command generator, 520 analysis prediction unit, 909 electronic circuit, 910 processor, 921 memory, 922 auxiliary storage device, 930 input interface, 940 output interface, 941 display device, 950 communication device, Ox rocket launch prediction value.

Claims (12)

Based on the position coordinates of the rocket launch site and the satellite orbit forecast information in which the predicted value of the satellite orbit is set, the satellite constellation in which the rocket launched from the rocket launch site passes over the rocket launch site is performed. An area calculation unit that calculates a time area that does not have the risk of colliding with the constituent satellites as a passable time area,
A rocket launch support device including an area notification unit that outputs the passable time area. The area calculation unit
Claim 1 to acquire a rocket launch predicted value which is a predicted value for a rocket launched from the rocket launch site to pass through the orbit of the satellite constellation, and calculate the passable time region using the rocket launch predicted value. The rocket launch support device described in. The satellite constellations are a plurality of satellite constellations formed at a plurality of orbital altitudes different from each other.
The area calculation unit
The passable time region is calculated for each of the plurality of orbital altitudes.
The area notification unit
The rocket launch support device according to claim 1 or 2, wherein a time domain in which a plurality of passable time domains calculated for each of the plurality of orbital altitudes are integrated is output. The satellite constellation is a plurality of satellite constellations operated by a plurality of satellite constellation operators different from each other.
The area calculation unit
The passable time domain was calculated for each of the plurality of satellite constellations.
The area notification unit
The rocket launch support device according to any one of claims 1 to 3, which outputs the passable time region for each of the plurality of satellite constellations. A rocket launched from the rocket launch site passes over the rocket launch site based on the position coordinates of the rocket launch site and satellite orbit forecast information in which the predicted value of the satellite orbit is set by the region calculation unit. The time region where there is no risk of collision with the satellites that make up the satellite constellation is calculated as the passable time region.
A rocket launch support method in which the area notification unit outputs the passable time area. Based on the position coordinates of the rocket launch site and the satellite orbit forecast information in which the predicted value of the satellite orbit is set, the satellite constellation in which the rocket launched from the rocket launch site passes over the rocket launch site is performed. Area calculation processing that calculates the time area where there is no risk of collision with the constituent satellites as the passable time area, and
A rocket launch support program that causes a computer to execute an area notification process that outputs the passable time area. Based on the position coordinates of the rocket launch site and the satellite orbit forecast information in which the predicted value of the satellite orbit is set, the satellite constellation in which the rocket launched from the rocket launch site passes over the rocket launch site is performed. An area calculation unit that calculates a passing area that does not have the risk of colliding with the constituent satellites as a possible passing area,
A rocket launch support device including an area notification unit that outputs the possible passage area. A rocket launched from the rocket launch site passes over the rocket launch site based on the position coordinates of the rocket launch site and satellite orbit forecast information in which the predicted value of the satellite orbit is set by the region calculation unit. Calculate the passing area without the risk of colliding with the satellites that make up the satellite constellation as the possible passing area.
A rocket launch support method in which the area notification unit outputs the possible passage area. Based on the position coordinates of the rocket launch site and the satellite orbit forecast information in which the predicted value of the satellite orbit is set, the satellite constellation in which the rocket launched from the rocket launch site passes over the rocket launch site is performed. Area calculation processing that calculates the passing area without the risk of colliding with the constituent satellites as the possible passing area,
A rocket launch support program that causes a computer to execute an area notification process that outputs the possible passage area. A rocket launched from a rocket launch site located at latitude 40 degrees or more north to an orbit in the latitude direction with an orbit altitude of 300 km or more and latitude 50 degrees or more north. A rocket launch method for launching a rocket from a rocket launch site located at latitude 40 degrees or more north to an orbit at an orbit altitude of 300 km or more and latitude 50 degrees or more north latitude. Management business used by management companies that manage multiple space objects Space object information is acquired from a space information recorder that records space object information acquired from equipment, and collisions between rockets and space objects during launch are avoided. It is a rocket launch support system,
It is equipped with a database for storing space object information acquired from the space information recorder and a server.
The database is
The space object information of the rocket acquired by the space information recorder from the management business equipment of the rocket launcher and the satellite orbit of the satellite group of the satellite constellation acquired from the management business equipment of the satellite constellation at which the rocket is at risk of collision. Obtain and store forecast information from the space information recorder,
The space object information of the rocket includes the position coordinates of the rocket launch site, the scheduled launch time information of the rocket, and the predicted orbit information.
The server
From the position coordinates of the rocket launch site, the stage of analyzing the delay time and orbital position until the rocket launched at the scheduled launch time reaches the vicinity of the satellite constellation, and
The stage of determining the relative distance A between the rocket and other space objects, which is an index of the flight safety area, and
The stage of determining the relative distance B between the rocket and other space objects, which is an index of the collision danger area, and
From the satellite constellation satellite group, the stage of extracting satellites that may approach a shorter distance than the relative distance B and identifying them as satellites requiring attention,
At the same time, all of the above-mentioned satellites needing attention are in the stage of extracting a safe time region in which they fly a distance longer than the relative distance A.
The stage of displaying the safe time area and
When the scheduled rocket launch time is included in the safe time domain, the stage of displaying a safety confirmation message and
When the scheduled rocket launch time is not included in the safe time area, the stage of displaying the recommended launch time from the safe time area as the launch time change recommended message, and
A rocket launch support system that has a stage of notifying the rocket launcher of a safety confirmation message or a launch time change recommendation message.

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