Debris removal method, rocket recovery method, recovery type rocket, rocket reuse system, and rocket

Abstract

To safely recover a rocket which has descended into an orbit after satellite separation.SOLUTION: A rocket recovery method recovers a rocket, which has been re-ignited from a rocket firing site located between 30 degrees and 50 degrees latitude and has descended into an orbit after satellite separation, in a region different from the rocket firing site. A recovery type rocket 202a comprises an atmospheric deceleration device, and is recovered by the rocket recovery method. The rocket firing site executes the rocket re-ignition method.SELECTED DRAWING: Figure 20

Description

[Technical field]

[0001] The present disclosure relates to a rocket launch method, a rocket launch control device, an orbit insertion method, a satellite constellation maintenance method, a debris removal method, a rocket recovery method, a recoverable rocket, a rocket launch site, a rocket reuse system, a rocket, a satellite constellation, and ground equipment. [Background technology]

[0002] In recent years, the construction of large-scale satellite constellations, so-called mega-constellations, consisting of hundreds to thousands of satellites, has begun, increasing the risk of satellite collisions in orbit. In addition, the amount of space debris, such as satellites that have become uncontrollable due to malfunctions and rocket debris, is increasing. With the rapid increase in space objects such as satellites and space debris in outer space, there is an increasing need for international rules in space traffic control (STM) to avoid collisions of space objects.

[0003] In recent years, mega-constellation operators have emerged that operate mega-constellations. The same mega-constellation operators plan to deploy satellites across the entire sky. Orbital altitude approximately 336km: Orbital inclination 42 degrees, approximately 2500 aircraft Orbital altitude approximately 341km: Orbital inclination 48 degrees, approximately 2500 aircraft Orbital altitude approximately 346km: Orbital inclination 53 degrees, approximately 2500 aircraft Orbital altitude approximately 550km: Orbital inclination 53 degrees, approximately 1600 aircraft Orbital altitude approximately 1150km: orbital inclination 53 degrees, approximately 1600 aircraft

[0004] Additionally, another megaconstellation operator has announced plans to deploy a total of 3,236 satellites in the following orbits, with inclinations ranging from 39 degrees to 56 degrees: Orbital altitude approximately 590km: 784 aircraft Orbital altitude approximately 610km: 1296 aircraft Orbital altitude approximately 630km: 1156 aircraft For example, there is a plan to develop a rocket launch site in Taiki Town, Hokkaido, Japan, which is located at 42 degrees north latitude.

[0005] Patent Document 1 discloses a technique for forming a satellite constellation consisting of multiple satellites in the same circular orbit. [Prior art documents] [Patent documents]

[0006] [Patent Document 1] JP 2017-114159 A Summary of the Invention [Problem to be solved by the invention]

[0007] As mentioned above, the skies above latitudes of 42 degrees, 48 ​​degrees, and 53 degrees are latitude zones where satellites that make up megaconstellations are densely concentrated. This poses a challenge for rocket launch operators, as it is extremely difficult to avoid collisions with satellites when launching rockets. However, Patent Document 1 does not disclose any measures to avoid such collisions.

[0008] The present disclosure aims to safely recover a rocket that descends into orbit after satellite separation. [Means for solving the problem]

[0009] The rocket recovery method according to the present disclosure includes: A rocket launched from a rocket launch site located between 30 and 50 degrees latitude, The rocket that descends into orbit after separation of the satellite is recovered in an area different from the rocket launch site. Effect of the Invention

[0010] The rocket launch control method according to the present disclosure has the advantage of being able to safely recover the rocket that descends into orbit after satellite separation. [Brief description of the drawings]

[0011] [Figure 1] An example of multiple satellites working together to provide global communications services. [Diagram 2] An example of multiple satellites in a single orbital plane providing an Earth observation service. [Diagram 3] An example of a satellite constellation with multiple intersecting orbital planes near the poles. [Figure 4] An example of a satellite constellation with multiple intersecting orbital planes outside of the polar regions. [Diagram 5] A configuration diagram of a satellite constellation formation system. [Figure 6] A diagram showing the configuration of satellites in the satellite constellation formation system. [Figure 7] A diagram showing the configuration of the ground equipment for the satellite constellation formation system. [Figure 8] An example of the functional configuration of a satellite constellation formation system. [Figure 9] An example of a satellite constellation near 42 degrees north latitude. [Figure 10] FIG. 1 is a configuration diagram of a rocket launch control device according to a first embodiment. [Figure 11] FIG. 4 is a diagram showing an example of satellite orbit forecast information according to the first embodiment. [Figure 12] FIG. 2 is an image diagram of a rocket launch according to the first embodiment. [Figure 13] 1 is a schematic diagram showing a rocket launch method according to a first embodiment. [Figure 14] FIG. 2 is a diagram showing an example of a rocket launch according to the first embodiment. [Figure 15] FIG. 2 is a diagram showing an example of passing through an inclined orbit with an orbital inclination angle of 50 degrees in the rocket launch method according to the first embodiment. [Figure 16] FIG. 2 is a diagram showing an example of passing through a plurality of inclined orbits in the rocket launch method according to the first embodiment. [Figure 17] FIG. 2 is a diagram showing an orbit insertion method according to the first embodiment. [Figure 18] FIG. 2 is a diagram showing an example of an orbit insertion method according to the first embodiment. [Figure 19] FIG. 2 is a diagram showing a configuration example of a debris removal satellite according to the first embodiment. [Figure 20] FIG. 2 is a diagram showing Example 1 of a rocket recovery method according to the first embodiment. [Figure 21] FIG. 4 is a diagram showing Example 2 of the rocket recovery method according to the first embodiment. [Figure 22] FIG. 2 is a diagram showing an example of a satellite constellation formation method according to the first embodiment. [Diagram 23] FIG. 2 is a diagram showing an example of overtaking an adjacent orbital plane by a satellite according to the first embodiment. DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

[0012] Hereinafter, the embodiments of the present disclosure will be described with reference to the drawings. In each drawing, the same or corresponding parts are denoted by the same reference numerals. In the description of the embodiments, the description of the same or corresponding parts will be omitted or simplified as appropriate. In addition, the relationship between the sizes of the components in the following drawings may differ from the actual relationship. In addition, in the description of the embodiments, directions or positions such as "upper", "lower", "left", "right", "front", "rear", "front" and "back" may be indicated. These notations are written in this way only for the convenience of explanation, and do not limit the arrangement and orientation of the components such as devices, instruments, or parts.

[0013] Embodiment 1 An example of a satellite constellation that is the premise of the following embodiment will be described.

[0014] FIG. 1 is a diagram showing an example in which multiple satellites cooperate to provide communication services across the entire globe (Earth 70) to the ground. FIG. 1 shows a satellite constellation 20 that provides global communication services. The communication service range of each of the multiple satellites flying at the same altitude in the same orbital plane overlaps with the communication service range of the succeeding satellite. Therefore, such multiple satellites can provide communication services to a specific point on the ground by alternating between the multiple satellites on the same orbital plane in a time-division manner. In addition, by providing adjacent orbital planes, it becomes possible to provide communication services to the ground between the adjacent orbits in a planar manner. Similarly, by arranging multiple orbital planes approximately evenly around the earth, communication services to the ground over the entire globe can be provided.

[0015] FIG. 2 is a diagram showing an example of an Earth observation service provided by multiple satellites in a single orbital plane. Figure 2 shows a satellite constellation 20 that realizes an earth observation service. In the satellite constellation 20 in Figure 2, satellites equipped with earth observation equipment, which is a radio wave sensor such as an optical sensor or a synthetic aperture radar, fly in the same orbital plane at the same altitude. In this way, in a satellite group 300 in which the imaging range of the ground is time-delayed and subsequent satellites overlap, multiple satellites in orbit take turns taking ground images of a specific point on the ground in a time-division manner to provide an earth observation service.

[0016] In this way, the satellite constellation 20 is composed of a group of satellites 300 consisting of multiple satellites in each orbital plane. In the satellite constellation 20, the group of satellites 300 cooperate to provide services. Specifically, the satellite constellation 20 refers to a satellite constellation consisting of one group of satellites provided by a communications business service company as shown in FIG. 1 or an observation business service company as shown in FIG. 2.

[0017] FIG. 3 is an example of a satellite constellation 20 having multiple orbital planes 21 that intersect near the polar regions. FIG. 4 is an example of a satellite constellation 20 having multiple orbital planes 21 that intersect outside of the polar regions. In the satellite constellation 20 of FIG. 3, the orbital inclination angle of each of the multiple orbital planes 21 is approximately 90 degrees, and each of the multiple orbital planes 21 exists in a different plane from each other. In the satellite constellation 20 of FIG. 4, the orbital inclination angle of each of the multiple orbital planes 21 is not approximately 90 degrees, and each of the multiple orbital planes 21 exists in a different plane from each other.

[0018] In the satellite constellation 20 of FIG. 3, any two orbital planes intersect at a point near the polar regions. In the satellite constellation 20 of FIG. 4, any two orbital planes intersect at a point other than the polar regions. In FIG. 3, a collision of satellites 30 may occur near the polar regions. Also, as shown in FIG. 4, the intersection of multiple orbital planes with an orbital inclination angle of more than 90 degrees moves away from the polar regions according to the orbital inclination angle. Also, depending on the combination of orbital planes, the orbital planes may intersect at various positions including near the equator. This diversifies the locations where a collision of satellites 30 may occur. The satellites 30 are also called artificial satellites.

[0019] In particular, in recent years, the construction of large-scale satellite constellations consisting of hundreds to thousands of satellites has begun, increasing the risk of satellite collisions in orbit. In addition, the amount of debris, such as satellites that have become uncontrollable due to malfunctions or rocket debris, is increasing. Large-scale satellite constellations are also called mega-constellations. Such debris is also called space debris. As a result of the increase in space debris and the rapid increase in the number of satellites, including megaconstellations, the need for STM is growing. STM is an abbreviation for Space Traffic Management.

[0020] 5 to 8, an example of a satellite 30 and a ground facility 700 in a satellite constellation forming system 600 that forms the satellite constellation 20 will be described. For example, the satellite constellation forming system 600 is operated by an operator that operates a satellite constellation business, such as a megaconstellation operator, a LEO constellation operator, or another satellite operator.

[0021] FIG. 5 is a configuration diagram of a satellite constellation forming system 600. The satellite constellation forming system 600 includes a computer. Although Fig. 5 shows the configuration of one computer, in reality, a computer is provided for each of the multiple satellites 30 that make up the satellite constellation 20 and for each of the ground facilities 700 that communicate with the satellites 30. The computers provided for each of the multiple satellites 30 and for each of the ground facilities 700 that communicate with the satellites 30 work together to realize the functions of the satellite constellation forming system 600. An example of the configuration of a computer that realizes the functions of the satellite constellation forming system 600 will be described below.

[0022] The satellite constellation forming system 600 includes a satellite 30 and a ground facility 700. The satellite 30 includes a satellite communication device 32 that communicates with a communication device 950 of the ground facility 700. In Fig. 5, the satellite communication device 32 is illustrated as one of the components included in the satellite 30.

[0023] 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 the other hardware via a signal line and controls the other hardware. The hardware of the satellite constellation forming system 600 is similar to the hardware of the rocket launch control device 100 described later in FIG. 10.

[0024] The satellite constellation forming system 600 includes, as a functional element, a satellite constellation forming unit 11. The functions of the satellite constellation forming unit 11 are realized by hardware or software. The satellite constellation forming unit 11 controls the formation of the satellite constellation 20 while communicating with the satellites 30 .

[0025] FIG. 6 is a configuration diagram of a satellite 30 of a satellite constellation forming system 600. The satellite 30 comprises 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 30 also comprises other components that realize various functions, but only 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 with reference to FIG.

[0026] 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 in accordance with various commands transmitted from the ground facility 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. In addition, the satellite communication device 32 receives various commands transmitted from the ground facility 700. The propulsion device 33 is a device that provides 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 is a device for controlling attitude elements such as the attitude of the satellite 30, the angular velocity of the satellite 30, and the line of sight (Line Of Sight). The attitude control device 34 changes each attitude element to a desired direction. Alternatively, the attitude control device 34 maintains each attitude element in a desired direction. The attitude control device 34 includes an attitude sensor, an actuator, and a controller. The attitude sensor is a device such as a gyroscope, an earth sensor, a sun sensor, a star tracker, a thruster, and a magnetic sensor. The actuator is a device such as an attitude control thruster, a momentum wheel, a reaction wheel, and a control moment gyro. The controller controls the actuator according to the measurement data of the attitude sensor or various commands from the ground equipment 700. The power supply unit 35 includes devices such as solar cells, batteries, and a power control device, and supplies power to each device installed on the satellite 30.

[0027] The processing circuitry provided in the satellite control device 31 will now be described. The processing circuitry may be dedicated hardware or may be a processor that executes a program stored in a memory. In the processing circuit, some functions may be realized by dedicated hardware and the remaining functions may be realized by software or firmware, i.e. the processing circuit may be realized by hardware, software, firmware or a combination thereof. The dedicated hardware may specifically be a single circuit, a complex circuit, a programmed processor, a parallel programmed processor, an ASIC, an FPGA, or a combination of these. ASIC is an abbreviation for Application Specific Integrated Circuit. FPGA is an abbreviation for Field Programmable Gate Array.

[0028] FIG. 7 is a configuration diagram of a ground facility 700 provided in the satellite constellation forming system 600. The ground equipment 700 controls programs of multiple satellites in all orbital planes. The ground equipment 700 is an example of a ground device. The ground equipment is composed of a ground station such as a ground antenna device, a communication device connected to the ground antenna device, or a computer, and ground equipment as a server or terminal connected to the ground station via a network. The ground equipment may also include a communication device mounted on a moving object such as an aircraft, a self-propelled vehicle, or a mobile terminal.

[0029] The ground facility 700 forms the satellite constellation 20 by communicating with each satellite 30. The ground facility 700 is provided in the rocket launch control device 100. The ground facility 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 the other hardware via a signal line and controls the other hardware. The hardware of the ground facility 700 is similar to the hardware of the rocket launch control device 100 described later in FIG. 10.

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

[0031] The communication device 950 transmits and receives signals for tracking and controlling each satellite 30 of the group of satellites 300 that make up the satellite constellation 20. The communication device 950 also transmits orbit control commands 55 to each satellite 30. The analysis and prediction unit 520 analyzes and predicts the orbit of the satellite 30 . The orbital control command generator 510 generates the orbital control command 55 to be transmitted to the satellite 30 . The orbit control command generation unit 510 and the analysis prediction unit 520 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 an example of the satellite constellation formation unit 11.

[0032] FIG. 8 is a diagram showing an example of the functional configuration of the satellite constellation forming system 600. As shown in FIG. The satellite 30 further includes a satellite constellation forming unit 11b that forms the satellite constellation 20. The satellite constellation forming unit 11b of each of the multiple satellites 30 and the satellite constellation forming unit 11 provided in each of the ground facilities 700 work together to realize the functions of the satellite constellation forming system 600. The satellite constellation forming unit 11b of the satellite 30 may be provided in the satellite control device 31.

[0033] FIG. 9 is a diagram showing an example of a satellite constellation in the vicinity of 42 degrees north latitude. There is a plan to develop a new rocket launch site in Taiki-cho, Hokkaido, Japan, which is located at 42 degrees north latitude. However, as shown in Figure 9, the skies above 42 degrees, 48 ​​degrees, and 53 degrees north latitude are latitude zones where satellites that make up megaconstellations are densely concentrated. For this reason, it is extremely difficult for rocket launch operators to avoid collisions with satellites when launching rockets.

[0034] ***Configuration Description*** FIG. 10 is a configuration diagram of a rocket launch control device 100 according to this embodiment. The rocket launch control system 500 includes a rocket launch control device 100. The rocket launch control device 100 according to this embodiment controls the launch of a rocket so that the rocket is launched without colliding with a satellite 30 of a satellite constellation 20 flying above a rocket launch site. The rocket launch control device 100 communicates with the management business device 40. The rocket launch control device 100 is mounted on, for example, a ground facility 700. The rocket launch control device 100 may also be mounted on the satellite constellation forming system 600. Alternatively, the rocket launch control 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 control device 100 may be mounted on a device of another business entity, such as an orbit analysis service provider.

[0035] The management business device 40 provides information about a space object 60, such as an artificial satellite or debris. The management business device 40 is a computer of an operator that collects information about a space object 60, such as an artificial satellite or debris. The management business equipment 40 includes equipment such as a megaconstellation business equipment 41, a LEO constellation business equipment 42, and a satellite business equipment 43. The management business equipment 40 further includes equipment such as an orbital transfer business equipment 44, a debris collection business equipment 45, a rocket launch business equipment 46, and an SSA business equipment 47. LEO is an abbreviation for Low Earth Orbit.

[0036] The megaconstellation business device 41 is, for example, a computer of a megaconstellation business operator that operates a megaconstellation consisting of 100 or more satellites. The LEO constellation business equipment 42 is a computer of a LEO constellation operator that operates a low earth orbit constellation, i.e., a LEO constellation business. The satellite business device 43 is a computer of a satellite operator that handles one to several satellites. The orbital transfer business device 44 is a computer of an orbital transfer business operator that controls the rocket launch of the satellite. The debris collection business device 45 is a computer of a debris collection business operator that carries out the business of collecting debris. The debris collection business device 45 is also called a debris removal business device. The rocket launch business device 46 is a computer of a rocket launch business operator that carries out rocket launch business. The SSA business equipment 47 is a computer of an SSA business operator that performs an SSA business, i.e., a space situational awareness business.

[0037] The management business device 40 may be any other device that collects information about space objects such as artificial satellites or debris and provides the collected information to the rocket launch control device 100. In addition, when the rocket launch control device 100 is mounted on a public server of the SSA, the rocket launch control device 100 may be configured to function as the public server of the SSA. The information provided from the management business device 40 to the rocket launch control device 100 will be explained in detail later.

[0038] The rocket launch control device 100 includes a processor 910, as well as other hardware such as a memory 921, an auxiliary storage device 922, an input interface 930, an output interface 940, and a communication device 950. The processor 910 is connected to the other hardware via signal lines and controls the other hardware.

[0039] The rocket launch control device 100 includes, as functional elements, a control unit 110 and a memory unit 130. The memory unit 130 stores satellite orbit forecast information 51.

[0040] The functions of the control unit 110 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. Moreover, the storage unit 130 may be divided into the memory 921 and the auxiliary storage device 922.

[0041] The processor 910 is a device that executes a rocket launch control program. The rocket launch control program is a program that realizes the functions of the control unit 110. The processor 910 is an integrated circuit (IC) that performs arithmetic processing. Specific examples of the processor 910 include a central processing unit (CPU), a digital signal processor (DSP), and a graphics processing unit (GPU).

[0042] The memory 921 is a storage device that temporarily stores data. Specific examples of the memory 921 include a static random access memory (SRAM) and a dynamic random access memory (DRAM). The auxiliary storage device 922 is a storage device that stores data. A specific example of the auxiliary storage device 922 is a HDD. The auxiliary storage device 922 may also be a portable storage medium such as an SD (registered trademark) memory card, CF, NAND flash, a flexible disk, an optical disk, a compact disk, a Blu-ray (registered trademark) disk, or a DVD. Note that HDD is an abbreviation for Hard Disk Drive. SD (registered trademark) is an abbreviation for Secure Digital. CF is an abbreviation for CompactFlash (registered trademark). DVD is an abbreviation for Digital Versatile Disk.

[0043] The input interface 930 is a port connected to an input device such as a mouse, a keyboard, or a touch panel. Specifically, the input interface 930 is a Universal Serial Bus (USB) terminal. The input interface 930 may be a port connected to a Local Area Network (LAN). 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).

[0044] 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 control device 100 communicates with the management business device 40 via the communication device 950.

[0045] The rocket launch control program is read into the processor 910 and executed by the processor 910. Memory 921 stores not only the rocket launch control program but also an OS (Operating System). The processor 910 executes the rocket launch control program while executing the OS. The rocket launch control program and the OS may be stored in an auxiliary storage device 922. The rocket launch control program and the OS stored in the auxiliary storage device 922 are loaded into the memory 921 and executed by the processor 910. Note that a part or all of the rocket launch control program may be incorporated into the OS.

[0046] The rocket launch control device 100 may include multiple processors that replace the processor 910. These multiple processors share the task of executing a program. Each processor is a device that executes a program, just like the processor 910.

[0047] Data, information, signal values ​​and variable values ​​used, processed or output by the programs are stored in the memory 921, the secondary storage device 922, or in registers or cache memory within the processor 910.

[0048] The "part" of each part of the rocket launch control system may be read as a "process," "procedure," "means," "stage," or "step." Also, the "process" of the control process may be read as a "program," "program product," or "computer-readable recording medium on which a program is recorded." The rocket launch control program causes a computer to execute each process, procedure, means, stage, or step of the rocket launch control system, where "part" is replaced with "process," "procedure," "means," "stage," or "process." Also, the rocket launch method is a method performed by the rocket launch control device 100 executing the rocket launch control program. The rocket launch control program may be provided by being stored in a computer-readable recording medium. Also, each program may be provided as a program product.

[0049] FIG. 11 is a diagram showing an example of satellite orbit forecast information 51 according to the present embodiment. The rocket launch control device 100 stores satellite orbit forecast information 51 in which the forecast value of the orbit of the space object 60 is set in the memory unit 130. The rocket launch control device 100 may obtain the forecast value of the orbit of each of the multiple space objects 60 from a management business device 40 used by a management business that manages multiple space objects 60, for example, and store it as the satellite orbit forecast information 51. Alternatively, the rocket launch control device 100 may obtain the satellite orbit forecast information 51 in which the forecast value of the orbit of each of the multiple space objects 60 is set from the management business, and store it in the memory 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. As described above, the management business device 40 used by each management company is a computer such as a megaconstellation business device 41, a LEO constellation business device 42, a satellite business device 43, and other business devices.

[0050] In the satellite orbit forecast information 51, information such as a space object ID (identifier) ​​511, a forecast origin 512, forecast orbital elements 513, and a forecast error 514, for example, is set.

[0051] The space object ID 511 is an identifier for identifying the space object 60. In Fig. 11, a satellite ID and a debris ID are set as the space object ID 511. Specifically, the space object is an object such as a rocket launched into outer space, an artificial satellite, a space station, a debris collection satellite, a planetary exploration spacecraft, or a satellite or rocket that has become debris after completing a mission.

[0052] Predicted epoch 512 is the epoch predicted for the orbit of each of the plurality of space objects. The predicted orbital elements 513 are orbital elements that specify the orbit of each of the multiple space objects. The predicted orbital elements 513 are orbital elements that are predicted for the orbit of each of the multiple space objects. In Fig. 11, six Keplerian orbit elements are set as the predicted orbital elements 513.

[0053] The forecast error 514 is an error predicted for each orbit of a plurality of space objects. A forward error and an orthogonal error are set in the forecast error 514. The forecast error 514 explicitly indicates the amount of error contained in the actual value.

[0054] In the satellite orbit forecast information 51 according to this embodiment, a forecast origin 512 and forecast orbital elements 513 are set for the space object 60. The forecast origin 512 and forecast orbital elements 513 can be used to determine the time and position coordinates in the near future of the space object 60. For example, the time and position coordinates in the near future for the space object 60 may be set in the satellite orbit forecast information 51. In this way, the satellite orbit forecast information 51 includes space object orbit information including the epoch and orbital elements, or time and position coordinates, and explicitly indicates the near future forecast values ​​of the space object 60. Note that the satellite orbit forecast information 51 may have a configuration other than that shown in FIG. 11, so long as the information explicitly indicates the near-future forecast values ​​of the space object 60.

[0055] The rocket launch control device 100 may also include satellite orbit performance information in which a performance value of the orbit of the space object 60 is set. The configuration of the satellite orbit performance information is similar to that of the satellite orbit forecast information.

[0056] ***Explanation of Operation*** Megaconstellation operators are emerging that operate megaconstellations. The same megaconstellation operators plan to deploy satellites across the entire sky as follows: Orbital altitude approximately 336km: Orbital inclination 42 degrees, approximately 2500 aircraft Orbital altitude approximately 341km: Orbital inclination 48 degrees, approximately 2500 aircraft Orbital altitude approximately 346km: Orbital inclination 53 degrees, approximately 2500 aircraft Orbital altitude approximately 550km: Orbital inclination 53 degrees, approximately 1600 aircraft Orbital altitude approximately 1150km: orbital inclination 53 degrees, approximately 1600 aircraft

[0057] Additionally, another megaconstellation operator has announced plans to deploy a total of 3,236 satellites in the following orbits, with inclinations ranging from 39 degrees to 56 degrees: Orbital altitude approximately 590km: 784 aircraft Orbital altitude approximately 610km: 1296 aircraft Orbital altitude approximately 630km: 1156 aircraft For example, there is a plan to develop a rocket launch site in Taiki Town, Hokkaido, Japan, which is located at 42 degrees north latitude.

[0058] FIG. 12 is a diagram showing an example of rocket launch according to this embodiment. FIG. 13 is an image diagram of a rocket launch according to this embodiment. As explained in Figure 9, there is a plan to develop a rocket launch site in Taiki Town, Hokkaido, Japan, at 42 degrees north latitude. If rocket 202 is launched from rocket launch site 201 at latitude 42 degrees north, the sky above latitudes 42 degrees, 48 ​​degrees, and 53 degrees is a latitude zone where satellites that make up megaconstellations are densely concentrated. For this reason, it is extremely difficult for rocket operators to avoid collisions during launch.

[0059] A rocket 202 is launched from a rocket launch site 201 under the control of a rocket launch control device 100. The rocket launch control device 100 is mounted on a ground facility 700, for example. The rocket launch control device 100 according to this embodiment controls the launch of the rocket 202 so that the rocket 202 is launched without colliding with the satellite 30 of the satellite constellation 20 flying above the rocket launch site 201.

[0060] ***Rocket Launch Variations*** Below, variations of rocket launch according to this embodiment will be described.

[0061] <How to launch a rocket> FIG. 14 is a schematic diagram showing a rocket launch method according to the present embodiment. The rocket launch method according to the present embodiment is realized, for example, by the control of the control unit 110 of the rocket launch control device 100. Alternatively, it may be realized by the control of a computer installed in the management business device 40. 13 shows a configuration in which the rocket launch control device 100 is mounted on a ground facility 700 and controls the launch of the rocket 202. However, the rocket launch control device 100 may be mounted on a ground facility 700 at another location and control the launch of the rocket 202 via a network.

[0062] The rocket 202 is launched from a rocket launch site 201 located, for example, between latitudes 30 degrees and 50 degrees. The control unit 110 of the rocket launch control device 100 controls the velocity vector of the rocket 202 when the rocket passes through the orbital altitude of the mega constellation satellite group 411 flying at an orbital inclination angle of 40 degrees to 60 degrees. Specifically, the control unit 110 controls the launch of the rocket 202 so that the velocity vector of the rocket 202 heading from west to east in the east-west direction at latitudes of 40 degrees to 60 degrees is the same as the orbital velocity of the mega constellation satellite group 411 and passes by the satellites constituting the mega constellation satellite group 411 with a shift in passing timing. At that time, the ground equipment 700 sends and receives tracking and control signals for the rocket 202.

[0063] The three orbital planes in Figure 14 have the same orbital inclination and orbital altitude, and the normal vectors are divergent in the longitude direction. Therefore, the orbital altitude when the satellite passes the northernmost point in each orbital plane is the same. Whether or not the satellites in the three orbital planes pass the northernmost point at the same time depends on whether or not they are operated synchronously, so when the rocket is launched, the passing timing is shifted for each orbital plane, and it is necessary and sufficient that the passing timing is shifted for all orbital planes.

[0064] A specific example of a rocket launch site 201 developed between latitudes 30 degrees and 50 degrees is Taiki Town in Hokkaido. When launching a rocket from such a rocket launch site 201, it is necessary to launch the rocket safely by passing through an area where satellites on inclined orbits fly densely. The rocket launch control device 100 according to this embodiment provides a means for launching a rocket safely. In a region where the northernmost satellite on an inclined orbital plane flies from west to east, the rocket launch control device 100 controls the rocket to fly from west to east in the same direction, reducing the relative speed difference with multiple satellites flying nearby, and passing through the gaps between the satellites and overtaking them in altitude, thereby passing through the dense altitude.

[0065] When launching a satellite into orbit using a rocket, it is rational to use the rotation of the Earth to obtain the speed required to maintain the satellite's altitude. For this reason, when an inclined orbit satellite passes through the northernmost point of the orbital plane, it flies from west to east. Although there are some special satellites that are launched to the west, the megaconstellation satellites 411 fly from west to east at the north-south end. The orbital velocity of a satellite in routine operation is determined depending on the orbital altitude, and the velocity vector at the northernmost point of the orbital plane always heads from west to east. Therefore, the latitude and orbital velocity of a megaconstellation of satellites, whose orbital inclination and orbital altitude are published, when they pass the northernmost point of the orbital plane can be known by rocket launch operators.

[0066] Therefore, during rocket launch, if the latitude band in which the megaconstellation satellites 411 fly is passed so that the velocity vector component pointing from west to east is the same as the orbital velocity of the satellites, the relative velocity difference will only be the component perpendicular to the direction of travel of the satellites. In other words, when the rocket passes through the orbital plane of the megaconstellation satellites 411, the magnitude of the east-west component of the rocket's velocity vector is the same as the orbital velocity of the satellites. During the rocket's passage, a velocity component in the altitude direction remains depending on the altitude the rocket will ultimately reach. Satellites fly at high speeds of several km / s in their direction of travel, so if there is a speed difference of several km / s when crossing the direction of travel, there is a high risk of collision and the timing for safe passage is extremely limited. However, if there is no speed difference in the direction of travel, it is easy to shift the timing of passage with satellites flying in the same orbital plane and pass between the satellites. Similarly, since the speed difference between satellites passing through adjacent orbits is small, it is easy for satellites in adjacent orbits to pass each other without colliding.

[0067] It should be noted that flight safety can be ensured even in launches from Tanegashima by using the same means as in this embodiment.

[0068] FIG. 15 is a diagram showing an example of passing through an inclined orbit with an orbital inclination angle of 50 degrees in the rocket launch method according to this embodiment. Figure 15 shows an example of a rocket launch site in Hokkaido at approximately 40 degrees north latitude, passing through an inclined orbit with an inclination of 50 degrees. Flight safety is ensured by launching through the gaps between the satellites flying in formation like a daisy chain on an inclined orbit.

[0069] FIG. 16 is a diagram showing an example of passing through a plurality of inclined orbits in the rocket launch method according to the present embodiment. In mega-constellation satellites, the nominal orbital altitude is the same, and satellites flying in multiple orbital planes are arranged with the relative angles of the normal vectors of the orbital planes shifted in the longitude direction. The multiple orbital planes rotate relatively from east to west. For this reason, when a rocket is launched, it must weave through the gaps between the satellites in all orbital planes to ensure flight safety.

[0070] <Orbit insertion method> The orbit insertion method according to the present embodiment is realized, for example, by the control of the control unit 110 of the rocket launch control device 100. Alternatively, it may be realized by the control of a computer mounted on the management operation device 40.

[0071] FIG. 17 is a diagram showing an orbit insertion method according to this embodiment. FIG. 17 shows a method for injecting a satellite into an inclined orbit. The satellites are launched by rockets from launch sites located at latitudes between 30 and 50 degrees. The satellites are placed in the northern or southern end of an orbit with an inclination angle of 40 to 60 degrees, heading from west to east.

[0072] When launching a rocket from a rocket launch site located at latitudes between 30 and 50 degrees, and inserting it into an orbit with an orbital inclination of 40 to 60 degrees (equivalent to 140 to 120 degrees depending on how the orbital inclination is defined), the procedure is as follows. In the region where the satellites fly from west to east at the northernmost or southernmost end of the orbital plane, if the rocket is accelerated to a speed that will allow it to reach the orbital altitude at which the satellites fly, it will reach approximately the same speed as a satellite flying from west to east. This makes it easy to insert the rocket into the gap between satellites, and has the effect of ensuring flight safety.

[0073] In this orbit injection method, if the rocket is launched during the time when the orbital plane rotates over the rocket launch site, it can easily reach the desired orbital altitude in the orbital plane. Also, if the satellite is separated from the rocket at a lower altitude, it will be injected into an orbit that flies roughly in the vicinity of the orbital plane, so it can safely join the formation flight.

[0074] In addition, the distance from the rocket launch site to rocket separation can be minimized, resulting in lower costs. When multiple satellites fly in the same orbital plane, if it is not necessary to launch a replacement satellite in the same configuration as the failed satellite, it is possible to adjust the orbital altitudes of the satellites in the same orbital plane to create a gap through which a replacement satellite can be safely launched.

[0075] FIG. 18 is a diagram showing an example of the orbit insertion method according to the present embodiment. FIG. 18 shows an orbit injection method according to the present embodiment for injecting a satellite into a specific orbital position.

[0076] For example, when inter-satellite communications are carried out between satellites in the same orbital plane, it is necessary to inject a replacement satellite into orbit at the same orbital position as the failed satellite's original configuration. In the orbit injection method shown in Figure 18, if the rocket is launched during the time when the orbital plane rotates over the rocket launch site, it is possible to easily reach the desired orbital altitude in the orbital plane. Also, if the satellite is separated from the rocket at a lower altitude, it will be injected into an orbit that flies roughly in the vicinity of the orbital plane, so it is possible to safely join the formation flight.

[0077] A low-earth orbit satellite orbits the Earth once every 90 minutes or so, so if there is a maximum 45-minute leeway in the timing of the rocket launch, it is possible to put it into orbit at the optimal position. By choosing the appropriate launch timing after taking into consideration the time it takes for the rocket to reach the desired orbital altitude from launch and the time it takes for the satellite to join the formation flight, it is possible to inject the satellite into a specific orbital position in the orbital plane. In this way, it is possible to achieve the effect of enabling appropriate orbit injection at low cost and in a short period of time.

[0078] <Satellite constellation maintenance method> The satellite constellation maintenance method according to the present embodiment is realized, for example, by the control of the control unit 110 of the rocket launch control device 100. Alternatively, it may be realized by the control of a computer mounted on the management business device 40.

[0079] The satellite constellation maintenance method according to the present embodiment is a method for injecting a successor satellite into orbit when a satellite fails or reaches the end of its life after the initial satellite group is prepared in a satellite constellation consisting of 10 or more satellites. In the satellite constellation maintenance method according to the present embodiment, the successor satellite is injected into orbit by the above-mentioned orbit injection method.

[0080] When a mega-constellation satellite group is first constructed, all satellites flying in the same orbital plane can be launched at once by a large rocket. However, if one of the satellites malfunctions and a replacement satellite needs to be launched, it is necessary to launch only the replacement satellite into the missing orbital plane. For this reason, it is rational to load the replacement satellite onto a small rocket and launch it into the orbit of the relevant orbital plane individually.

[0081] There are also cases where a successor satellite to a satellite that has deorbited after completing its design lifespan and undergoes PMD (Post Mission Disposal) is launched into orbit. In this case, too, in order to maintain the satellite constellation, it is necessary to launch replacement satellites into orbit in the order in which the satellites PMD in multiple orbital planes. This is because the actual orbital lifespans of satellites launched at the same time vary, so it is rational to launch them into orbit individually.

[0082] In the case of multiple satellites being launched simultaneously, all satellites to be put into the same orbital plane must be completed before launch, which means there is a waiting period before launch. In addition, if satellites experience PMD in multiple orbital planes, the number of launches required corresponds to the number of orbital planes, so there is no cost reduction effect as in the initial preparation stage, and instead there is an issue of wasting time waiting to prepare replacement satellites. Therefore, it would be rational to launch the replacement vehicle separately using a small rocket and put it into orbit.

[0083] If small rockets are prepared in advance as solid rockets and kept ready to be launched at any time, it will be possible to put replacement rockets into orbit when needed. In this way, according to the satellite constellation maintenance method of this embodiment, it is possible to maintain a megaconstellation at low cost and without waiting time.

[0084] The rocket 202 performs the rocket launch method or orbit insertion method described above. Furthermore, the rocket launch site 201 executes the rocket launch method or orbit insertion method described above. The satellite constellation 20 also performs the orbit injection method or the satellite constellation maintenance method described above.

[0085] This rocket launch method involves passing through the constellation's orbital altitude and launching the rocket to a higher altitude. The orbit injection method is a method for injecting a new satellite into the constellation. In either method, it is safe to make the velocity component from west to east in the east-west direction the same as the constellation. In the rocket launch method, there is a velocity vector in the altitude direction, whereas in the orbit injection method, the velocity vector in the altitude direction is approximately zero. In the orbit injection method, the satellite is separated from the rocket before reaching the orbit, so the rocket does not reach the orbit altitude, and the separated satellite operates its thruster to transition to the regular position.

[0086] <Debris removal method example 1> The debris removal method according to this embodiment is realized, for example, by the control of the control unit 110 of the rocket launch control device 100 mounted on the debris collection business device 45. Alternatively, it may be realized by the control of a computer mounted on another management business device 40.

[0087] The debris removal method example 1 according to the present embodiment is a method for active debris removal (ADR) of satellites that cannot be deorbited (PMD) due to a malfunction after initial satellite constellation development in a satellite constellation consisting of 10 or more satellites. ADR is an abbreviation for Active Debris Removal. In a first example of a debris removal method according to this embodiment, a debris removal satellite for removing debris is placed into orbit by the above-mentioned orbit injection method.

[0088] FIG. 19 is a diagram showing an example of the configuration of a debris removal satellite 301 according to this embodiment. The debris removal satellite 301 includes a capture device 36 that captures debris in addition to the components of the satellite 30 in Fig. 6. The debris removal satellite 301 captures debris in response to control commands, and performs active control operation during orbit descent to avoid areas with a high risk of collision with space objects during the deorbit process before re-entering the atmosphere. Active control operation during orbit descent is also called active deorbit operation.

[0089] If a satellite that cannot perform autonomous PMD due to a failure in its propulsion device or other reasons continues to remain in the orbit of a megaconstellation, there is a risk of collision with other satellites, and therefore ADR is required to actively deorbit the satellite. When ADR is performed by a debris removal satellite 301 equipped with a means for capturing a failed satellite, if the debris removal satellite 301 is injected into orbit using the above-mentioned orbit injection method, it has the effect of being able to approach and capture the failed satellite while ensuring flight safety.

[0090] <Rocket recovery method example 1> The rocket recovery method according to the present embodiment is realized, for example, by the control of the control unit 110 of the rocket launch control device 100 mounted on the debris recovery business device 45. It may also be realized by the control of a computer mounted on another management business device 40.

[0091] FIG. 20 is a diagram showing Example 1 of the rocket recovery method according to this embodiment. The rocket recovery method according to this embodiment is a method for recovering a rocket launched from a rocket launch site located at latitudes between 30 degrees and 50 degrees. In the rocket recovery method according to this embodiment, the rocket descends into orbit after satellite separation and is recovered in a safe area different from the rocket launch site.

[0092] The rocket is equipped with measures to ensure resistance to frictional heat during atmospheric re-entry, and after launching and separating the satellite, the rocket is lowered into orbit and recovered. The rocket may be equipped with a parachute, or a thruster may be fired just before landing to slow down the landing speed. For example, it would be reasonable to have a rocket launched into an inclined orbit from a rocket launch site in Hokkaido and then fall into the Pacific Ocean.

[0093] <Rocket recovery method example 2> FIG. 21 is a diagram showing a second example of the rocket recovery method according to the present embodiment. The thin line trajectory in Figure 21 represents the orbit the rocket will follow. If sufficient measures against atmospheric re-entry can be secured, such as equipping the rocket with a re-firing function after orbital insertion, it will be possible to slow down the rocket by thrusting it in the opposite direction to its travel direction after several orbits, and then to descend to the desired area.

[0094] In rocket recovery method examples 1 and 2, the rocket is a recoverable rocket 202a that is equipped with an atmospheric deceleration device and is recovered by the rocket recovery method.

[0095] The recovery rocket 202a is realized by providing resistance to passing through the atmosphere and landing, such as by selecting heat-resistant ceramic materials or paint to withstand frictional heat caused by the atmosphere, providing a parachute, and firing a propulsion device.

[0096] <Rocket Launch Site 201> The rocket launch site 201 is a rocket launch site that launches rockets that perform the above-mentioned rocket launch method or orbit insertion method, and may be rented to realize the above-mentioned satellite constellation maintenance method.

[0097] Assuming a rocket launch site in Hokkaido, the rocket launch site may be rented to the mega-constellation operator or rocket launch operator. This would make it possible for the mega-constellation operator or rocket launch operator to take charge of ensuring flight safety to avoid collisions with the mega-constellation satellites during rocket launch, which would be rational.

[0098] <Rocket Reuse System> The rocket reuse system is a system (method or method) for reusing the recoverable rocket 202a through a rocket reuse cycle in which the recoverable rocket 202a is launched multiple times. The rocket reuse system includes a reusable rocket vehicle. The reusable rocket vehicle is a means for transporting a rocket to be reused. In the rocket reuse system, a recoverable rocket 202a is launched from a rocket launch site 201, and the recoverable rocket 202a is recovered by the rocket recovery method. Then, in the rocket reuse system, the recoverable rocket 202a is transported to the rocket launch site 201 by a reuse rocket transport means. Then, in the rocket reuse system, the recoverable rocket 202a is launched again.

[0099] Assuming a rocket launch site in Hokkaido, the site will be rented to mega-constellation operators or rocket launch operators. This makes it rational for the mega-constellation operators or rocket launch operators to be responsible for ensuring flight safety to avoid collisions with mega-constellation satellites during rocket launch. The recoverable rocket 202a can be landed on a barge in the Pacific Ocean, recovered, and refurbished at a rocket factory, such as by repairing any damaged areas, before being transported back to Hokkaido, creating a rocket reuse system for multiple launches.

[0100] <Debris removal method example 2> Example 2 of the debris removal method according to this embodiment is a method for active debris removal (ADR) of satellites that are unable to be deorbited (PMD) due to a malfunction after the initial satellite group development in a satellite constellation consisting of 10 or more satellites. In the second example of the debris removal method, the rocket that performs the orbit injection method is equipped with a capture device, which is a debris removal means for capturing the failed satellite, and an orbit control device. Then, in the second example of the debris removal method, after the successor vehicle is injected into orbit, the rocket captures the failed satellite and performs a reverse thrust to de-orbit it.

[0101] The capture device provided on the rocket is similar to the capture device provided on a satellite, for example. The orbit control device of the rocket is the same as, for example, a satellite control device of a satellite. The orbit control device is a satellite control device that controls the propulsion device and the attitude control device of the rocket, and controls the propulsion device and the attitude control device according to various commands transmitted from the ground facility 700.

[0102] In the debris removal method example 2, the rocket is equipped with a debris removal means, which captures the debris after the rocket launch operation is completed and de-orbits by reverse thrust. If the rocket is equipped with a capture device that can operate after the satellite is separated, debris removal will be possible without relying on a debris removal satellite.

[0103] An example of overtaking by the satellite 30b in an adjacent orbital plane that can be used in the rocket launch method according to this embodiment will be described below.

[0104] FIG. 22 is a diagram showing an example of a satellite constellation formation method. 22 shows a state in which the orbital altitudes of the two orbital planes 21a, 21b are different from each other, and the satellite pass timings of the satellites 30a, 30b are shifted at the intersection point Pc of each orbital plane 21a, 21b. The satellite constellation forming unit 11 gradually matches the orbital altitudes of the two orbital planes 21a, 21b while maintaining the state in which the satellite pass timings are shifted.

[0105] When satellites fly at the same altitude in orbital planes with different normal angles, there is a risk of collision at the intersection. In addition, the risk of collision is high when additional satellites are launched into orbit after multiple satellites have been deployed in their respective orbital planes. Therefore, the same number of satellites are flown in formation in a roughly even arrangement in advance, and their orbital altitudes are gradually brought closer. By gradually bringing their orbital altitudes closer, the ground speeds of the satellites at nearby altitudes become roughly the same. Therefore, the satellites flying in formation with a phase shift in advance can change their orbital altitudes without colliding with each other.

[0106] Furthermore, the satellite constellation forming unit 11 makes the orbital altitude of one of the two orbital planes overtake the orbital altitude of the other orbital plane while maintaining the satellite pass timing shifted from a state in which the satellite pass timings are shifted at the intersection vicinity point Pc on each orbital plane. The satellite constellation forming unit 11 makes the satellite of one orbital plane overtake the orbital altitude of the other orbital plane from the intersection vicinity point Pc of each orbital plane 21 to the next intersection vicinity point Pc.

[0107] FIG. 23 illustrates an overtaking of an adjacent orbital plane by satellite 30b. 23 shows a state in which satellite 30b in orbital plane 21b overtakes orbital plane 21a. Satellite 30b in orbital plane 21b overtakes orbital plane 21a during interval R from node vicinity point Pc1 to the next node vicinity point Pc2.

[0108] When changing the overtaking satellite altitude in multiple orbital planes with different angles between their normals, there is a risk of collision at two points near the intersections of the two orbital planes. Since there is no risk of collision at any other points, if the overtaking orbit altitude is performed between passing a point near an intersection and the next point near an intersection, the orbital altitude can be changed without collision.

[0109] In this embodiment, the control unit 110 controls the velocity vector of the rocket 202 when the rocket 202 passes through the orbital altitude of the mega constellation satellite group 411 that flies at an orbital inclination angle of 40 degrees to 60 degrees. Specifically, the control unit 110 controls the launch of the rocket 202 so that the velocity vector of the rocket 202 heading from west to east in the east-west direction at latitudes of 40 degrees to 60 degrees is the same as the orbital velocity of the mega constellation satellite group 411 and passes by shifting the passing timing of the satellites that make up the mega constellation satellite group 411.

[0110] ***Other configurations*** In this embodiment, the functions of the control unit 110 are realized by software. As a modification, the functions of the control unit 110 may be realized by hardware.

[0111] The rocket launch control device 100 includes an electronic circuit in place of the processor 910. The electronic circuit is a dedicated electronic circuit for implementing the functions of the control unit 110. The electronic circuit 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 of Gate Array. ASIC is an abbreviation of Application Specific Integrated Circuit. FPGA is an abbreviation of Field-Programmable Gate Array. The functions of the control unit 110 may be realized by one electronic circuit, or may be distributed across multiple electronic circuits. As another modification, some of the functions of the control unit 110 may be realized by electronic circuits, and the remaining functions may be realized by software.

[0112] Each of the processor and the electronic circuit is also called a processing circuitry. That is, in the rocket launch control system 100, the functions of the control unit 110 are realized by the processing circuitry.

[0113] In the above-mentioned first embodiment, each part of the rocket launch control device has been described as an independent functional block. However, the configuration of the rocket launch control device does not have to be as in the above-mentioned embodiment. The functional blocks of the rocket launch control device may have any configuration as long as they can realize the functions described in the above-mentioned embodiment. In addition, the rocket launch control device may be a single device or a system composed of multiple devices.

[0114] In addition, it is possible to combine a plurality of parts of the first embodiment. Alternatively, it is possible to implement only one part of these embodiments. In addition, it is possible to implement any combination of these embodiments, either as a whole or in part. That is, the first embodiment may be partially combined freely. Alternatively, the components of the first embodiment may be modified in any way. That is, the components of the first embodiment may be added or omitted.

[0115] It should be noted that the above-described embodiment is essentially a preferred example, and is not intended to limit the scope of the present disclosure, the scope of application of the present disclosure, and the scope of use of the present disclosure. The above-described embodiment can be modified in various ways as necessary. [Explanation of symbols]

[0116] 20 Satellite constellation, 21, 21a, 21b Orbital plane, 30, 30a, 30b Satellite, 301 Debris removal satellite, 31 Satellite control device, 32 Satellite communication device, 33 Propulsion device, 34 Attitude control device, 35 Power supply device, 36 Capture device, 40 Management business device, 41 Mega constellation business device, 411 Mega constellation satellite group, 42 LEO constellation business device, 43 Satellite business device, 44 Orbit transfer business device, 45 Debris collection business device, 46 Rocket launch business device, 47 SSA business device, 51 Satellite orbit forecast information, 511 Space object ID, 512 Forecast origin, 513 Forecast orbital elements, 514 Forecast error, 60 Space object, 70 Earth, 100 Rocket launch control device, 110 Control unit, 130 Memory unit, 55 Orbit control command, 201 Rocket launch site, 202 rocket, 202a recoverable rocket, 600 satellite constellation formation system, 11,11b satellite constellation formation unit, 300 satellite group, 700 ground equipment, 500 rocket launch control system, 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

1. A rocket recovery method for recovering a rocket that is launched from a rocket launch site located at a latitude of 30 degrees to 50 degrees and that descends into orbit after satellite separation in an area different from the rocket launch site.

2. Equipped with an atmospheric deceleration device, A recovery type rocket that is recovered by the rocket recovery method according to claim 1.

3. A rocket reuse system for reusing a recoverable rocket according to claim 2 through a rocket reuse cycle in which the recoverable rocket is launched multiple times, the rocket reuse system comprising: A rocket launch method for a rocket launched from a rocket launch site established at latitudes between 30 degrees and 50 degrees, comprising the steps of: The rocket launch site controls the launch of the rocket so that when the rocket passes through the orbital altitude of a mega constellation satellite group consisting of 100 or more satellites and flying at an orbital inclination angle of 40 degrees to 60 degrees, the velocity vector of the rocket moving in an east-west direction from west to east at latitudes of 40 degrees to 60 degrees is the same as the orbital velocity of the mega constellation satellite group, and the passing timing of the satellites constituting the mega constellation satellite group is shifted. It is a rocket launch site that launches rockets to carry out the The rocket launch site is a rocket launch site for launching a rocket to execute an orbit injection method for a satellite flying in an inclined orbit, the method being to inject a satellite from west to east to the northern end or southern end of an inclined orbit having an orbital inclination angle of 40 degrees to 60 degrees; The rocket launch site is a rocket launch site rented to realize a satellite constellation maintenance method for injecting a successor satellite into orbit when a satellite fails or reaches the end of its life after an initial satellite group development in a satellite constellation consisting of 10 or more satellites, the satellite constellation maintenance method being a method for injecting a successor satellite into orbit by the orbit injection method; launching the recoverable rocket from the rocket launch site; The rocket is recovered by the rocket recovery method according to claim 1, A rocket reuse system in which the reuse rocket transport means transports the recoverable rocket to the rocket launch site and launches the recoverable rocket again.

4. A rocket reuse system for reusing a recoverable rocket according to claim 2 through a rocket reuse cycle in which the recoverable rocket is launched multiple times, the rocket reuse system comprising: A rocket launch method for a rocket launched from a rocket launch site established at latitudes between 30 degrees and 50 degrees, comprising the steps of: The rocket launch site controls the launch of the rocket so that when the rocket passes through the orbital altitude of a mega constellation satellite group consisting of 100 or more satellites and flying at an orbital inclination angle of 40 degrees to 60 degrees, the velocity vector of the rocket moving in an east-west direction from west to east at latitudes of 40 degrees to 60 degrees is the same as the orbital velocity of the mega constellation satellite group, and the passing timing of the satellites constituting the mega constellation satellite group is shifted. It is a rocket launch site that launches rockets to carry out the The rocket launch site is a rocket launch site that launches a rocket to execute an orbit injection method for a satellite flying in an inclined orbit, the method being to inject a satellite from west to east into the northern end or southern end of an inclined orbit having an orbital inclination angle of 40 degrees to 60 degrees, and to inject the satellite into a specific orbital position on the orbital plane of the inclined orbit; The rocket launch site is a rocket launch site rented to realize a satellite constellation maintenance method for injecting a successor satellite into orbit when a satellite fails or reaches the end of its life after an initial satellite group development in a satellite constellation consisting of 10 or more satellites, the satellite constellation maintenance method being a method for injecting a successor satellite into orbit by the orbit injection method; launching the recoverable rocket from the rocket launch site; The rocket is recovered by the rocket recovery method according to claim 1, A rocket reuse system in which the reuse rocket transport means transports the recoverable rocket to the rocket launch site and launches the recoverable rocket again.

5. A rocket reuse system for reusing a recoverable rocket according to claim 2 through a rocket reuse cycle in which the recoverable rocket is launched multiple times, the rocket reuse system comprising: A method for orbital injection of a satellite flying in an inclined orbit, comprising the steps of: launching a rocket from a rocket launch site established at a latitude of 30 degrees to 50 degrees; and launching a rocket for executing the orbital injection method in which the satellite is injected in a west-to-east direction at the northern or southern end of an inclined orbit with an orbital inclination angle of 40 degrees to 60 degrees; The rocket launch site is a rocket launch site rented to realize a satellite constellation maintenance method for injecting a successor satellite into orbit when a satellite fails or reaches the end of its life after an initial satellite group development in a satellite constellation consisting of 10 or more satellites, the satellite constellation maintenance method being a method for injecting a successor satellite into orbit by the orbit injection method; launching the recoverable rocket from the rocket launch site; The rocket is recovered by the rocket recovery method according to claim 1, A rocket reuse system in which the reuse rocket transport means transports the recoverable rocket to the rocket launch site and launches the recoverable rocket again.

6. A rocket reuse system for reusing a recoverable rocket according to claim 2 through a rocket reuse cycle in which the recoverable rocket is launched multiple times, the rocket reuse system comprising: A method for orbiting a satellite flying in an inclined orbit, comprising: a rocket launching site which launches a rocket from a rocket launching site maintained at a latitude of 30 degrees to 50 degrees, and launches the satellite in a west-to-east direction at the northern or southern end of an inclined orbit having an orbital inclination angle of 40 degrees to 60 degrees, and launches the satellite into a specific orbital position on the orbital plane of the inclined orbit; The rocket launch site is a rocket launch site rented to realize a satellite constellation maintenance method for injecting a successor satellite into orbit when a satellite fails or reaches the end of its life after an initial satellite group development in a satellite constellation consisting of 10 or more satellites, the satellite constellation maintenance method being a method for injecting a successor satellite into orbit by the orbit injection method; launching the recoverable rocket from the rocket launch site; The rocket is recovered by the rocket recovery method according to claim 1, A rocket reuse system in which the reuse rocket transport means transports the recoverable rocket to the rocket launch site and launches the recoverable rocket again.

7. A debris removal method for actively removing debris from a satellite that is unable to deorbit due to a malfunction after an initial satellite group development in a satellite constellation consisting of 10 or more satellites, comprising: A method for injecting a satellite into an inclined orbit, comprising the steps of: launching the satellite by a rocket from a rocket launch site located at a latitude of 30 degrees to 50 degrees; and injecting the satellite from west to east into the northern or southern end of the inclined orbit with an orbital inclination angle of 40 degrees to 60 degrees; a rocket performing an orbit injection method for injecting a satellite into a specific orbital position on an orbital plane of the inclined orbit, The satellite is equipped with a debris removal means for capturing a malfunctioning satellite and an orbit control device, A debris removal method in which a failed satellite is captured after a successor has been launched into orbit and deorbited using reverse thrust.

8. This rocket is equipped with a debris removal means, and after the rocket launch operation is completed, it captures the debris and deorbits by reverse thrust.

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