Rocket reuse system, debris removal method, and rocket

Abstract

The objective is to safely recover the rocket that has descended into orbit after satellite separation, and to reuse the recovered rocket. [Solution] A rocket is launched from a rocket launch site located between 30 and 50 degrees latitude, and a rocket recovery method is used to recover the rocket, which has descended into orbit after satellite separation, in an area different from the rocket launch site. The recoverable rocket 202a is equipped with an atmospheric deceleration device, and the recoverable rocket 202a recovered by the above rocket recovery method is transported to the rocket launch site by a reusable rocket transport means. The rocket launch site then performs a rocket launch method to launch the recoverable rocket again.

Description

Technical Field

[0001] The present disclosure relates to a rocket launch method, a rocket launch control device, an orbit injection method, a satellite constellation maintenance method, a debris removal method, a rocket recovery method, a reusable rocket, a rocket launch site, a rocket reuse system, a rocket, a satellite constellation, and ground facilities.

Background Art

[0002] In recent years, the construction of large-scale satellite constellations, so-called mega constellations, ranging from several hundred to several thousand satellites has begun, and the risk of satellite collisions in orbit has increased. In addition, the number of space debris such as satellites that have become uncontrollable due to failures or rocket debris has been increasing. With the rapid increase in space objects such as satellites and space debris in such outer space, in space traffic management (STM), the need for international rule-making to avoid collisions of space objects has been increasing.

[0003] In recent years, mega constellation operators who operate mega constellations have emerged. There is a plan to deploy satellites comprehensively across the sky by the same mega constellation operator. Orbit altitude of about 336 km: Orbit inclination angle of 42 degrees, about 2,500 satellites Orbit altitude of about 341 km: Orbit inclination angle of 48 degrees, about 2,500 satellites Orbit altitude of about 346 km: Orbit inclination angle of 53 degrees, about 2,500 satellites Orbit altitude of about 550 km: Orbit inclination angle of 53 degrees, about 1,600 satellites Orbit altitude of about 1,150 km: Orbit inclination angle of 53 degrees, about 1,600 satellites

[0004] Furthermore, another mega constellation operator has announced a plan to deploy a total of 3,236 satellites as follows. The orbit inclination angle is from 39 degrees to 56 degrees. Orbit altitude of about 590 km: 784 satellites Orbit altitude of about 610 km: 1,296 satellites Orbit altitude of about 630 km: 1,156 satellites Furthermore, for example, there is a plan to develop a rocket launch site in Taiki Town, Hokkaido, Japan, 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] Japanese Patent Publication No. 2017-114159 [Overview of the Initiative] [Problems that the invention aims to solve]

[0007] As mentioned above, the skies above latitudes 42, 48, and 53 degrees are latitude zones where satellites that make up megaconstellations are densely concentrated. Therefore, it is extremely difficult for rocket launch operators to avoid collisions with satellites when launching rockets. However, Patent Document 1 does not describe any measures to avoid such collisions. Nor does it describe any measures to recover and reuse the rocket that has descended into orbit after satellite separation.

[0008] This disclosure aims to safely recover recoverable rockets equipped with atmospheric deceleration devices and to reuse them through a rocket reuse cycle that involves launching the recoverable rockets multiple times. [Means for solving the problem]

[0009] The rocket reuse system related to this disclosure is A rocket reuse system that reuses a recoverable rocket by a rocket reuse cycle that involves launching multiple recoverable rockets equipped with reusable rocket transport means and atmospheric deceleration devices, A rocket launch method for rockets launched from rocket launch sites located between 30 and 50 degrees latitude, The rocket launch site is a rocket launch method that controls the launch of the rocket so that, when the rocket passes the orbital altitude of a megaconstellation of 100 or more satellites, which is flying at an orbital inclination of 40 to 60 degrees, the velocity vector of the rocket, which is moving from west to east in an east-west direction between 40 and 60 degrees latitude, is the same as the orbital velocity of the megaconstellation, and the timing of the rocket's passage through the satellites constituting the megaconstellation is staggered. It is a rocket launch site that launches rockets to carry out the task. The aforementioned rocket launch site is a rocket launch site for launching rockets that perform an orbit insertion method for satellites flying in an inclined orbit, in which the satellite is inserted from west to east into the northern or southern end of an inclined orbit with an orbital inclination angle of 40 to 60 degrees. The aforementioned rocket launch site is a rocket launch site rented to implement a satellite constellation maintenance method in which, in a satellite constellation consisting of 10 or more satellites, a successor satellite is placed into orbit after the initial satellite constellation has been set up, due to satellite failure or the end of its lifespan. The recovery type rocket is launched from the aforementioned rocket launch site, The rocket, which descended into orbit after satellite separation, is recovered using a rocket recovery method that recovers it in an area different from the rocket launch site. The reusable rocket is transported to the rocket launch site by the aforementioned reusable rocket transport means, and the recoverable rocket is launched again. [Effects of the Invention]

[0010] The rocket reuse system described in this disclosure has the effect of safely recovering a recoverable rocket equipped with an atmospheric deceleration device, and reusing it through a rocket reuse cycle in which the recoverable rocket is launched multiple times.

Brief Description of Drawings

[0011] [Figure 1] An example in which multiple satellites cooperate to provide communication services across the globe of the Earth. [Figure 2] An example in which multiple satellites in a single orbital plane provide Earth observation services. [Figure 3] An example of a satellite constellation having multiple orbital planes intersecting near the polar region. [Figure 4] An example of a satellite constellation having multiple orbital planes intersecting outside the polar region. [Figure 5] A configuration diagram of a satellite constellation formation system. [Figure 6] A configuration diagram of a satellite in a satellite constellation formation system. [Figure 7] A configuration diagram of ground facilities in a 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] A configuration diagram of a rocket launch control device according to Embodiment 1. [Figure 11] A diagram showing an example of satellite orbit prediction information according to Embodiment 1. [Figure 12] An image diagram of a rocket launch according to Embodiment 1. [Figure 13] A schematic diagram showing a rocket launch method according to Embodiment 1. [Figure 14] A diagram showing an example of a rocket launch according to Embodiment 1. [Figure 15] In the rocket launch method according to Embodiment 1, a diagram showing an example of passing through an inclined orbit with an orbital inclination angle of 50 degrees. [Figure 16] In the rocket launch method according to Embodiment 1, a diagram showing an example of passing through multiple inclined orbits. [Figure 17] A diagram showing an orbit injection method according to Embodiment 1. [Figure 18] A diagram showing an example of an orbital insertion method according to Embodiment 1. [Figure 19] A diagram showing an example configuration of a debris removal satellite according to Embodiment 1. [Figure 20] A diagram showing Example 1 of the rocket recovery method according to Embodiment 1. [Figure 21] A diagram showing example 2 of the rocket recovery method according to Embodiment 1. [Figure 22] A diagram showing an example of a satellite constellation formation method according to Embodiment 1. [Figure 23] A diagram showing an example of an overtaking maneuver by a satellite in an adjacent orbital plane according to Embodiment 1. [Modes for carrying out the invention]

[0012] The embodiments of this disclosure will be described below 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. Also, the size relationships of the components in the following drawings may differ from those of the actual components. In addition, in the description of the embodiments, directions or positions such as "top," "bottom," "left," "right," "front," "back," "front," and "back" may be indicated. These notations are used for the convenience of explanation only and do not limit the arrangement and orientation of components such as devices, equipment, or parts.

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

[0014] Figure 1 shows an example of how multiple satellites work together to provide global communication services to the Earth. Figure 1 shows the satellite constellation 20 that provides global communication services. For multiple satellites orbiting in the same orbital plane at the same altitude, the communication service range to the ground from each satellite overlaps with the communication service range of the following satellite. Therefore, with such multiple satellites, communication services to a specific point on the ground can be provided by multiple satellites on the same orbital plane, taking turns in a time-division manner. Furthermore, by establishing adjacent orbital planes, it becomes possible to comprehensively cover communication services to the ground between adjacent orbits. Similarly, if a large number of orbital planes are roughly evenly distributed around the Earth, communication services to the ground can be provided globally.

[0015] Figure 2 shows an example of multiple satellites in a single orbit plane providing Earth observation services. Figure 2 shows a satellite constellation 20 that provides Earth observation services. In the satellite constellation 20 of Figure 2, satellites equipped with Earth observation instruments such as optical sensors or radio sensors such as synthetic aperture radar fly in the same orbital plane at the same altitude. In this way, in a satellite constellation 300 where the imaging range of the ground overlaps with that of subsequent satellites with a time delay, Earth observation services are provided by having multiple satellites in orbit take turns acquiring ground images of a specific point on the ground in a time-division manner.

[0016] Thus, a satellite constellation 20 is composed of satellite constellations 300, each consisting of multiple satellites in a different orbital plane. In a satellite constellation 20, the satellite constellations 300 work together to provide services. Specifically, a satellite constellation 20 refers to a satellite constellation consisting of a single satellite group operated by a communications service company, as shown in Figure 1, or an observation service company, as shown in Figure 2.

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

[0018] In the satellite constellation 20 shown in Figure 3, any two orbital planes intersect near the poles. In the satellite constellation 20 shown in Figure 4, any two orbital planes intersect outside the poles. In Figure 3, a collision of satellite 30 is possible near the poles. Also, as shown in Figure 4, the intersection of multiple orbital planes with orbital inclinations greater than 90 degrees moves further away from the poles depending on the orbital inclination. Furthermore, depending on the combination of orbital planes, the orbital planes can intersect at various locations, including near the equator. Therefore, the locations where a collision of satellite 30 could occur are diverse. Satellite 30 is also called an artificial satellite.

[0019] In particular, the construction of large-scale satellite constellations, sometimes numbering in the hundreds or thousands, has begun in recent years, increasing the risk of satellite collisions in orbit. Furthermore, the amount of space debris, such as malfunctioning satellites that have become uncontrollable or rocket wreckage, is increasing. Large-scale satellite constellations are also called megaconstellations. Such debris is also known as space debris. Thus, with 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] Here, using Figures 5 to 8, we will describe an example of satellites 30 and ground facilities 700 in a satellite constellation formation system 600 that forms a satellite constellation 20. For example, the satellite constellation formation system 600 is operated by a satellite constellation business operator such as a megaconstellation operator, a LEO constellation operator, or other satellite operator.

[0021] Figure 5 is a diagram showing the configuration of the satellite constellation formation system 600. The satellite constellation formation system 600 is equipped with a computer. Figure 5 shows the configuration of one computer, but in reality, each of the multiple satellites 30 that make up the satellite constellation 20, and each of the ground facilities 700 that communicate with the satellites 30, are equipped with a computer. The computers equipped in each of the multiple satellites 30 and each of the ground facilities 700 that communicate with the satellites 30 work together to realize the functions of the satellite constellation formation system 600. Below, an example of the configuration of the computer that realizes the functions of the satellite constellation formation system 600 will be described.

[0022] The satellite constellation forming system 600 comprises a satellite 30 and ground facilities 700. The satellite 30 is equipped with a satellite communication device 32 that communicates with a communication device 950 of the ground facilities 700. Figure 5 illustrates the satellite communication device 32, which is part of the configuration of the satellite 30.

[0023] The satellite constellation formation system 600 includes a processor 910, as well as other hardware such as memory 921, auxiliary storage device 922, input interface 930, output interface 940, and communication device 950. The processor 910 is connected to the other hardware via signal lines and controls this other hardware. The hardware of the satellite constellation formation system 600 is the same as the hardware of the rocket launch control device 100, which will be described later in Figure 10.

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

[0025] Figure 6 is a diagram showing the configuration of satellite 30 in the satellite constellation forming system 600. 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. While it also includes other components for various functions, Figure 6 will focus on explaining the satellite control device 31, satellite communication device 32, propulsion device 33, attitude control device 34, and power supply device 35.

[0026] The satellite control device 31 is a computer that controls the propulsion system 33 and the attitude control device 34, and is equipped with processing circuits. Specifically, the satellite control device 31 controls the propulsion system 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. The satellite communication device 32 also receives various commands transmitted from the ground equipment 700. The propulsion device 33 is a device that provides thrust to the satellite 30 and changes the speed of the satellite 30. Specifically, the propulsion device 33 is an electric propulsion system. 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, its angular velocity, and its line of sight. The attitude control device 34 changes each attitude element in a desired direction, or maintains each attitude element in a desired direction. The attitude control device 34 comprises attitude sensors, actuators, and a controller. The attitude sensors include devices such as a gyroscope, Earth sensor, solar sensor, star tracker, thruster, and magnetic sensor. The actuators include devices such as attitude control thrusters, momentum wheels, reaction wheels, and control moment gyros. The controller controls the actuators according to the measurement data from the attitude sensors or various commands from the ground equipment 700. The power supply unit 35 is equipped with devices such as solar cells, batteries, and a power control device, and supplies power to each device mounted on the satellite 30.

[0027] The processing circuits provided in the satellite control device 31 will now be described. The processing circuit may be dedicated hardware, or it may be a processor that executes a program stored in memory. In a processing circuit, some functions may be implemented by dedicated hardware, while the remaining functions are implemented by software or firmware. In other words, a processing circuit can be implemented using hardware, software, firmware, or a combination thereof. The dedicated hardware specifically includes single circuits, complex circuits, programmed processors, parallel programmed processors, ASICs, FPGAs, or combinations thereof. ASIC is an abbreviation for Application Specific Integrated Circuit. FPGA is an abbreviation for Field Programmable Gate Array.

[0028] Figure 7 is a diagram showing the configuration of the ground facilities 700 provided by the satellite constellation forming system 600. Ground equipment 700 programmatically controls multiple satellites in all orbital planes. Ground equipment 700 is an example of ground equipment. Ground equipment consists of ground stations such as ground antenna equipment, communication equipment connected to the ground antenna equipment, or computers, and ground equipment such as servers or terminals connected to the ground stations via a network. Ground equipment may also include communication equipment mounted on mobile devices such as aircraft, self-propelled vehicles, or mobile terminals.

[0029] The ground equipment 700 forms a satellite constellation 20 by communicating with each satellite 30. The ground equipment 700 is installed in the rocket launch control device 100. The ground equipment 700 includes a processor 910, as well as other hardware such as memory 921, auxiliary storage device 922, input interface 930, output interface 940, and communication device 950. The processor 910 is connected to the other hardware via signal lines and controls this other hardware. The hardware of the ground equipment 700 is the same as the hardware of the rocket launch control device 100, which will be described later in Figure 10.

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

[0031] The communication device 950 transmits and receives signals to track and control each satellite 30 of 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 orbit control command generation unit 510 generates orbit control commands 55 to be transmitted to the satellite 30. The orbit control command generation unit 510 and the analysis and prediction unit 520 implement the functions of the satellite constellation formation unit 11. In other words, the orbit control command generation unit 510 and the analysis and prediction unit 520 are examples of the satellite constellation formation unit 11.

[0032] Figure 8 shows an example of the functional configuration of the satellite constellation formation system 600. Satellite 30 further includes a satellite constellation forming unit 11b that forms a satellite constellation 20. The satellite constellation forming unit 11b of each satellite 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 satellite 30 may also be provided in the satellite control device 31.

[0033] Figure 9 shows an example of a satellite constellation near 42 degrees north latitude. There is a plan to develop a new rocket launch site in Taiki Town, Hokkaido, Japan, at 42 degrees north latitude. However, as shown in Figure 9, the skies above 42, 48, and 53 degrees north latitude are latitude zones where satellites that make up megaconstellations are densely concentrated. Therefore, it is extremely difficult for rocket launch operators to avoid collisions with satellites when launching rockets.

[0034] ***Explanation of the structure*** Figure 10 is a diagram showing the configuration of the 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 the rocket so that the rocket can be launched without colliding with the satellites 30 of the satellite constellation 20 flying above the rocket launch site. The rocket launch control device 100 communicates with the management equipment 40. The rocket launch control device 100 is, for example, mounted on ground equipment 700. Alternatively, the rocket launch control device 100 may be mounted on the satellite constellation forming system 600. Or, the rocket launch control device 100 may be mounted on at least one of the management equipment 40, such as the rocket launch equipment 46. Or, the rocket launch control device 100 may be mounted on equipment of other operators, such as orbit analysis service providers.

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

[0036] The megaconstellation business equipment 41 is, for example, the computer of a megaconstellation operator that conducts business on megaconstellations consisting of 100 or more satellites. The LEO constellation business equipment 42 is the computer of the LEO constellation business operator that conducts low orbit constellation, i.e., LEO constellation business. The satellite operation equipment 43 is a computer used by satellite operators that manage one to several satellites. The orbital transfer operation device 44 is a computer for the orbital transfer operator that controls the rocket launch of satellites. The debris recovery operation device 45 is a computer used by a debris recovery operator that carries out the operation of recovering debris. The debris recovery operation device 45 is also called a debris removal operation device. The rocket launch operation device 46 is a computer for a rocket launch operator that conducts rocket launch operations. SSA business equipment 47 is the computer of the SSA business, that is, the space situational awareness business.

[0037] The management 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. Furthermore, if the rocket launch control device 100 is installed on the SSA's public server, the rocket launch control device 100 may function as the SSA's public server. The information provided from the management 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 memory 921, auxiliary storage device 922, input interface 930, output interface 940, and communication device 950. The processor 910 is connected to the other hardware via signal lines and controls this other hardware.

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

[0040] The functions of the control unit 110 are implemented 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. Furthermore, the storage unit 130 may be divided and provided in the memory 921 and the auxiliary storage device 922.

[0041] The processor 910 is a device that executes the rocket launch control program. The rocket launch control program is a program that implements 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 the CPU (Central Processing Unit), DSP (Digital Signal Processor), and GPU (Graphics Processing Unit).

[0042] Memory 921 is a storage device that temporarily stores data. Specific examples of memory 921 include SRAM (Static Random Access Memory) or DRAM (Dynamic Random Access Memory). The auxiliary storage device 922 is a storage device for storing data. A specific example of the auxiliary storage device 922 is an HDD. Alternatively, the auxiliary storage device 922 may be a portable storage medium such as an SD® memory card, CF, NAND flash, flexible disk, optical disk, compact disk, Blu-ray® 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 Versatile Disk.

[0043] The input interface 930 is a port to which input devices such as a mouse, keyboard, or touch panel are connected. Specifically, the input interface 930 is a USB (Universal Serial Bus) terminal. Alternatively, the input interface 930 may be a port connected to a LAN (Local Area Network). The output interface 940 is a port to which the cable of a display device 941, such as a display, is connected. Specifically, the output interface 940 is a USB terminal or an HDMI® (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 NIC (Network Interface Card). The rocket launch control device 100 communicates with the management equipment 40 via the communication device 950.

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

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

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

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

[0049] Figure 11 shows an example of satellite orbit forecast information 51 according to this embodiment. The rocket launch control device 100 stores satellite orbit forecast information 51, in which the predicted orbital values ​​of the space objects 60 are set, in the storage unit 130. The rocket launch control device 100 may, for example, obtain the predicted orbital values ​​of each of the multiple space objects 60 from a management device 40 used by a management company that manages multiple space objects 60, and store them as satellite orbit forecast information 51. Alternatively, the rocket launch control device 100 may obtain satellite orbit forecast information 51, in which the predicted orbital values ​​of each of the multiple space objects 60 are set, from a management company and store it in the storage unit 130. The management operators are those who manage space objects 60 that fly in space, such as satellite constellations, various satellites, rockets, and debris. As mentioned above, the management equipment 40 used by each management operator are computers such as the mega-constellation equipment 41, the LEO constellation equipment 42, the satellite equipment 43, and other equipment.

[0050] The satellite orbit forecast information 51 includes information such as the space object ID (Identifier) ​​511, the forecast epoch 512, the forecast orbit elements 513, and the forecast error 514.

[0051] Space object ID 511 is an identifier that identifies space object 60. In Figure 11, the satellite ID and debris ID are set as space object ID 511. Specifically, space objects include rockets launched into space, artificial satellites, space bases, debris collection satellites, planetary exploration spacecraft, and satellites or rockets that have become debris after the completion of their missions.

[0052] Forecast epoch 512 is the epoch predicted for the individual orbits of multiple cosmic objects. The predicted orbital elements 513 are orbital elements that specify the individual orbits of multiple cosmic objects. The predicted orbital elements 513 are the orbital elements predicted for each of the orbits of multiple cosmic objects. In Figure 11, the six Kepler orbital elements are set as the predicted orbital elements 513.

[0053] The forecast error 514 is the error predicted for each orbit of multiple space objects. The forecast error 514 includes both a forward error and a perpendicular error. The amount of error inherent in the actual value is explicitly indicated for the forecast error 514.

[0054] In this embodiment, the satellite orbit forecast information 51 includes a forecast epoch 512 and a forecast orbit element 513 for the space object 60. The forecast epoch 512 and forecast orbit element 513 allow us to determine the time and position coordinates of the space object 60 in the near future. For example, the time and position coordinates of the space object 60 in the near future may be set in the satellite orbit forecast information 51. Thus, the satellite orbit forecast information 51 includes orbital information of the space object, including its epoch and orbital elements, or time and position coordinates, and explicitly shows the forecast values ​​for the near future of the space object 60. Furthermore, the satellite orbit forecast information 51 may be configured in a way other than that shown in Figure 11, as long as it explicitly shows the forecast values ​​for the near future of the space object 60.

[0055] Furthermore, the rocket launch control device 100 may also be equipped with satellite orbit performance information in which the actual orbital values ​​of the space object 60 are set. The configuration of the satellite orbit performance information is the same as that of the satellite orbit forecast information.

[0056] ***Explanation of operation*** Mega-constellation operators are emerging who will operate mega-constellations. One such operator plans 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] Furthermore, another mega-constellation operator has announced plans to deploy a total of 3,236 satellites, with orbital inclinations ranging from 39 to 56 degrees. Orbital altitude approximately 590km: 784 aircraft Orbital altitude approximately 610km: 1296 aircraft Orbital altitude approximately 630km: 1156 aircraft Furthermore, for example, there is a plan to develop a rocket launch site in Taiki Town, Hokkaido, Japan, located at 42 degrees north latitude.

[0058] Figure 12 shows an example of a rocket launch according to this embodiment. Figure 13 is an illustrative 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 were launched from launch site 201 at 42 degrees north latitude, the latitudes of 42, 48, and 53 degrees would be densely populated with satellites that make up the megaconstellation. Therefore, it would be extremely difficult for the rocket operator to avoid a collision during launch.

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

[0060] ***Variations of rocket launches*** The following describes variations of the rocket launch according to this embodiment.

[0061] <Rocket launch method> Figure 14 is a schematic diagram showing the rocket launch method according to this embodiment. The rocket launch method according to this embodiment is implemented, for example, by the control of the control unit 110 of the rocket launch control device 100. Alternatively, it may be implemented by the control of a computer mounted on the management device 40. Figure 13 shows a configuration in which the rocket launch control device 100 is mounted on ground equipment 700 and controls the launch of rocket 202. However, the rocket launch control device 100 may be mounted on ground equipment 700 at a different location and control the launch of rocket 202 via a network.

[0062] Rocket 202 will be launched, for example, from rocket launch site 201, which is located between latitudes 30 and 50 degrees. The control unit 110 of the rocket launch control device 100 controls the velocity vector of the rocket 202 as it passes the orbital altitude of the megaconstellation satellite group 411, which is flying at an orbital inclination angle of 40 to 60 degrees. Specifically, the control unit 110 controls the launch of the rocket 202 so that the velocity vector of the rocket 202, which is traveling from west to east in the east-west direction between 40 and 60 degrees of latitude, is the same as the orbital velocity of the megaconstellation satellite group 411, and that the timing of passing over the satellites constituting the megaconstellation satellite group 411 is staggered. During this time, ground equipment 700 will send and receive tracking and control signals for rocket 202.

[0063] Figure 14 shows that the three orbital planes have the same orbital inclination and orbital altitude, and their normal vectors are diverging in the longitude direction. Therefore, the orbital altitude when the satellite passes the northernmost point is the same for each orbital plane. Whether or not the satellites in the three orbital planes pass the northernmost point simultaneously depends on whether or not synchronous operation is performed, so at the time of rocket launch, it is necessary and sufficient to stagger the passing timing for each orbital plane so that the passing timing is staggered for all orbital planes.

[0064] A concrete example of a rocket launch site 201, located between latitudes 30 and 50 degrees, is Taiki Town in Hokkaido. When launching a rocket from such a launch site 201, it is necessary to safely launch the rocket by passing through an area where inclined orbiting satellites are densely flying. The rocket launch control device 100 according to this embodiment provides a means for safely launching a rocket. In the region where the northernmost satellite on the inclined orbit plane is flying from west to east, the rocket is controlled to fly from west to east as well, reducing the relative velocity difference with multiple satellites flying nearby, and passing through the gaps between satellites to overtake them in altitude, thereby passing through a densely populated altitude.

[0065] When launching a satellite into orbit via rocket, it is rational to use the Earth's rotation to obtain the speed necessary to maintain the satellite's altitude. Therefore, when an inclined orbital satellite passes the northernmost edge of its orbital plane, it will fly from west to east. While there are special satellites that are launched westward, the Mega Constellation 411 will fly from west to east along its northern and southern edges. The orbital velocity of a satellite in regular operation is determined by its orbital altitude, and the velocity vector at the northernmost point of the orbital plane always points from west to east. Therefore, the latitude and orbital velocity at the northernmost point of the orbital plane of a megaconstellation of satellites, for which the orbital inclination and orbital altitude are publicly available, can be determined by the rocket launch operator.

[0066] Therefore, during a rocket launch, if the rocket passes through the latitude zone in which the Mega Constellation 411 is flying, such that the velocity vector component pointing from west to east is the same as the orbital velocity of the satellite constellation, the relative velocity difference will consist only of the component perpendicular to the direction of the satellite constellation's movement. In other words, when the rocket passes through the orbital plane of the Mega Constellation 411 satellites, the magnitude of the east-west component of the rocket's velocity vector is equal to 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. Since satellites fly at high speeds of several kilometers per second relative to their direction of travel, a speed difference of several kilometers per second when crossing their path significantly increases the risk of collision, and the timing for a safe passage is extremely limited. However, if there is no speed difference in the direction of travel, it is easy to stagger the timing of passages with a group of satellites flying in the same orbital plane, allowing the satellite to pass between them. Similarly, because the speed difference between adjacent satellites is small, it is easy for them to pass between adjacent satellites without colliding.

[0067] Furthermore, flight safety can be ensured using the same means as in this embodiment even when launching from Tanegashima.

[0068] Figure 15 shows an example of a rocket launch method according to this embodiment, in which the rocket passes through an inclined trajectory with an orbital inclination angle of 50 degrees. Figure 15 shows an example of a rocket launch site in Hokkaido, approximately 40 degrees north latitude, where the rocket passes through an inclined orbit with an orbital inclination of 50 degrees. Flight safety is ensured by launching the rocket through the gaps between satellites flying in a chain-like formation along the inclined orbit.

[0069] Figure 16 shows an example of a rocket launch method according to this embodiment, in which the rocket passes through multiple inclined trajectories. In a megaconstellation satellite group, numerous satellites with the same nominal orbital altitude are arranged with the relative angles of the normal vectors of the orbital planes shifted in the longitude direction. Furthermore, these multiple orbital planes rotate relatively from east to west. Therefore, during rocket launch, flight safety must be ensured by navigating through the gaps between satellites in all orbital planes.

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

[0071] Figure 17 shows the orbital insertion method according to this embodiment. Figure 17 shows the method for inserting a satellite flying in an inclined orbit into orbit. The satellite will be launched by rockets from launch sites located between 30 and 50 degrees latitude. The satellite will be placed into an inclined orbit with an orbital inclination of 40 to 60 degrees, either at the northern or southern end, moving from west to east.

[0072] When launching a rocket from a launch site located between 30 and 50 degrees latitude and inserting it into orbit with an orbital inclination of 40 to 60 degrees (equivalent to 140 to 120 degrees depending on the definition of orbital inclination), the following applies: In the region where the satellite constellation flies from west to east at the northernmost or southernmost edge of the orbital plane, accelerating the rocket to a speed that reaches the orbital altitude of the satellite constellation will result in a speed almost identical to that of the satellites flying from west to east. Therefore, inserting the rocket into the gaps between satellites is easy, and flight safety can be ensured.

[0073] With this orbital insertion method, if the rocket is launched when the orbital plane is over the launch site, it is easy to reach the desired orbital altitude in that orbital plane. Furthermore, if the satellite is separated from the rocket at a lower altitude, it will be placed into an orbit that generally flies near the orbital plane, allowing it to safely join a formation flight.

[0074] Furthermore, since the distance from the rocket launch site to the rocket separation point can be minimized, costs can be reduced. When multiple satellites are flying in the same orbital plane, if it is not necessary to deploy a replacement satellite in the same configuration as the malfunctioning satellite, it is possible to adjust the orbital altitude of the satellite group in the same orbital plane to create a gap for safely deploying the replacement satellite.

[0075] Figure 18 shows an example of an orbital insertion method according to this embodiment. Figure 18 shows an orbit insertion method according to this embodiment, in which a satellite is inserted into a specific orbital position.

[0076] For example, if inter-satellite communication is being conducted between satellites in the same orbital plane, it is necessary to place a replacement satellite into orbit at the same orbital position as the original array of the malfunctioning satellite. In the orbital insertion method shown in Figure 18, if the rocket is launched when the orbital plane is over the rocket launch site, it is possible to easily reach the desired orbital altitude in that orbital plane. Furthermore, if the satellite is separated from the rocket at a lower altitude, it will be placed into an orbit that generally flies near the orbital plane, allowing it to safely join a formation flight.

[0077] Since low Earth orbit satellites complete one orbit around the Earth in about 90 minutes, a maximum of 45 minutes of leeway in the rocket launch timing allows for optimal orbit placement. By selecting an appropriate launch timing, taking into account the time it takes for the rocket to reach the desired orbital altitude and the time required for the satellite to join a formation flight, it is possible to insert the satellite into a specific orbital position in the orbital plane. This has the effect of enabling appropriate orbit insertion at low cost and in a short period of time.

[0078] <Methods for maintaining satellite constellations> The satellite constellation maintenance method according to this embodiment is implemented, for example, by the control of the control unit 110 of the rocket launch control device 100. Alternatively, it may be implemented by the control of a computer mounted on the management equipment 40.

[0079] The satellite constellation maintenance method according to this embodiment is a method for placing a successor satellite into orbit in a satellite constellation consisting of 10 or more satellites after the initial satellite constellation has been set up, in the event of a satellite failure or the end of its lifespan. In the satellite constellation maintenance method according to this embodiment, the successor satellite is placed into orbit using the orbit placement method described above.

[0080] When initially setting up a mega-constellation of satellites, all satellites orbiting in the same orbital plane can be launched together using a large rocket. However, if one of the satellites malfunctions and a replacement satellite needs to be launched, only the replacement satellite must be launched into the missing orbital plane. Therefore, it is more rational to load the replacement satellite onto a small rocket and individually place it into the orbital plane.

[0081] Furthermore, after a satellite has reached the end of its design life, it may undergo Post-Mission Disposal (PMD) to de-orbit, and a successor satellite may be placed back into orbit. In this case as well, in order to maintain the satellite constellation, it is necessary to place replacement satellites into orbit in the order in which the satellites underwent PMD across multiple orbital planes. This is because the actual on-orbit lifespans of satellites launched simultaneously vary, making it rational to place them into orbit individually.

[0082] In the case of simultaneous launch of multiple satellites, there is a waiting period before launch because all satellites to be placed into the same orbital plane must be completed before launch. Furthermore, if satellites undergo PMD (Pre-Migration Displacement) in multiple orbital planes, the number of launches required will be equal to the number of orbital planes. This means that the cost reduction effect is not as significant as in the initial preparation phase, and instead, the waiting time for preparing replacement satellites becomes a wasted opportunity. Therefore, it is rational to launch alternative rockets individually using small rockets and place them into orbit.

[0083] If small rockets are pre-built as solid-fuel rockets and ready for launch at any time, it becomes possible to place a replacement rocket into orbit when needed. Thus, 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] Rocket 202 will perform the rocket launch method or orbital insertion method described above. Furthermore, rocket launch site 201 will execute the rocket launch method or orbital insertion method described above. Furthermore, satellite constellation 20 will perform the orbit insertion method or satellite constellation maintenance method described above.

[0085] In rocket launch methods, this refers to a method used when the rocket is launched to an even higher altitude after passing through the orbital altitude of the constellation. Furthermore, the orbit insertion method involves placing a new satellite into orbit as part of a constellation. In either method, it is safest to keep the velocity component in the east-west direction (from west to east) the same as that of the constellation. In rocket launch methods, there is a velocity vector in the altitude direction, whereas in orbit insertion methods, the velocity vector in the altitude direction is approximately zero. In orbit insertion methods, the satellite is separated from the rocket before reaching orbit, so the rocket does not reach the orbital altitude; instead, the separated satellite activates its propulsion system and transitions to its correct position.

[0086] <Example 1 of debris removal method> The debris removal method according to this embodiment is implemented, for example, by the control of the control unit 110 of the rocket launch control device 100 mounted on the debris recovery operation device 45. Alternatively, it may be implemented by the control of a computer mounted on other management operation devices 40.

[0087] Example 1 of the debris removal method according to this embodiment is a method for actively removing debris (ADR) from satellites that cannot be deorbited (PMD) due to failure after the initial satellite constellation setup in a satellite constellation consisting of 10 or more satellites. ADR is an abbreviation for Active Debris Removal. In Example 1 of the debris removal method according to this embodiment, a debris removal satellite for removing debris is placed into orbit using the orbital insertion method described above.

[0088] Figure 19 shows an example of the configuration of the debris removal satellite 301 according to this embodiment. The debris removal satellite 301 is equipped with a capture device 36 for capturing debris, in addition to the configuration of satellite 30 shown in Figure 6. The debris removal satellite 301 captures debris via control commands and performs active deorbit operations during its deorbit process until atmospheric re-entry, avoiding areas with a high risk of collision with space objects. This active deorbit operation is also called active deorbit operation.

[0089] If a satellite that cannot perform autonomous PMD due to a propulsion system failure or other reasons remains in the orbit of a megaconstellation, there is a risk of collision with other satellites, making ADR (Autonomous Deorbital Removal) necessary to actively deorbit it. When ADR is carried out by the debris removal satellite 301, which is equipped with means to capture the malfunctioning satellite, if the debris removal satellite 301 is put into orbit using the orbit insertion method described above, it has the effect of being able to approach and capture the malfunctioning satellite while ensuring flight safety.

[0090] <Example 1 of a rocket recovery method> The rocket recovery method according to this embodiment is implemented, for example, by the control of the control unit 110 of the rocket launch control device 100 mounted on the debris recovery operation device 45. Alternatively, it may be implemented by the control of a computer mounted on other management operation devices 40.

[0091] Figure 20 shows an example 1 of the rocket recovery method according to this embodiment. The rocket recovery method according to this embodiment is a method for recovering rockets launched from rocket launch sites located between 30 and 50 degrees latitude. 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, it is brought down to orbit and the rocket is recovered. The rocket may be equipped with a parachute, or it may fire its thrusters just before landing to reduce the landing velocity. For example, it is rational to allow a rocket launched from a rocket launch site in Hokkaido, placed into an inclined orbit, to fall into the Pacific Ocean.

[0093] <Example 2 of rocket recovery methods> Figure 21 shows an example 2 of the rocket recovery method according to this embodiment. The thin lines in Figure 21 represent the orbit the rocket will follow. If sufficient measures are in place to counter atmospheric re-entry, such as the ability to re-fire after orbital insertion, it becomes possible to decelerate by lingering near an inclined orbit, then performing multiple orbits, and finally descending to a desired orbit by firing in the opposite direction of travel.

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

[0095] The recoverable rocket 202a is realized by incorporating features that ensure resistance during atmospheric transit and landing, such as the selection of heat-resistant ceramic materials or paints to withstand frictional heat from the atmosphere, the provision of a parachute, and the firing of the propulsion system.

[0096] <Rocket Launch Site 201> Rocket launch site 201 is a rocket launch site for launching rockets that perform the rocket launch method or orbit insertion method described above, and may be rented to implement the satellite constellation maintenance method described above.

[0097] Assuming a rocket launch site in Hokkaido is planned, the launch site could be rented to a mega-constellation operator or rocket launch operator. This would allow the mega-constellation operator or rocket launch operator to take responsibility for ensuring flight safety to avoid collisions with the mega-constellation satellite group during rocket launches, which would be a rational approach.

[0098] <Rocket Reuse System> The rocket reuse system is a system (method or system) that reuses the recoverable rocket 202a by launching the recoverable rocket 202a multiple times in a rocket reuse cycle. A rocket reusability system includes means for transporting reusable rockets. These means are for transporting rockets intended for reuse. In the rocket reuse system, a recoverable rocket 202a is launched from the rocket launch site 201, and the recoverable rocket 202a is recovered using the rocket recovery method described above. The rocket reuse system then transports the recoverable rocket 202a back to the rocket launch site 201 using a reusable rocket transport means. Finally, the rocket reuse system launches the recoverable rocket 202a again.

[0099] Assuming a rocket launch site in Hokkaido, the plan is to rent the launch site to a mega-constellation operator or rocket launch company. This would allow the mega-constellation operator or rocket launch company to take responsibility for ensuring flight safety to avoid collisions with the mega-constellation satellite group during rocket launches, which is a rational approach. A rocket reuse system can be constructed in which the recoverable rocket 202a is landed on a barge in the Pacific Ocean for recovery, rehabilitated by repairing damaged parts at a rocket factory, and then transported back to Hokkaido for multiple launches.

[0100] <Example 2 of debris removal methods> Example 2 of the debris removal method according to this embodiment is a method for actively removing debris (ADR) from satellites that cannot be deorbited (PMD) due to malfunction after the initial satellite constellation setup in a satellite constellation consisting of 10 or more satellites. In Example 2 of the debris removal method, the rocket performing the orbital insertion method is equipped with a capture device and an orbital control device, which are debris removal means for capturing the malfunctioning satellite. Then, in Example 2 of the debris removal method, after the successor satellite is inserted into orbit, the rocket captures the malfunctioning satellite and de-orbits by firing a retro-fire.

[0101] The capture devices on rockets are similar to those on satellites, for example. The orbit control system on a rocket is similar to, for example, the satellite control system on a satellite. The orbit control system is a satellite control system that controls the propulsion system and attitude control system on the rocket, and controls the propulsion system and attitude control system according to various commands transmitted from the ground equipment 700.

[0102] In Example 2 of the debris removal method, the rocket is equipped with debris removal means, captures the debris after the rocket launch operation is completed, and de-orbits by firing a reverse thrust. By equipping the rocket with a capture device that becomes operational after satellite separation, it becomes possible to remove debris without relying on debris removal satellites.

[0103] The following describes an example of overtaking an adjacent orbital plane by satellite 30b, which can be used in the rocket launch method according to this embodiment.

[0104] Figure 22 shows an example of a satellite constellation formation method. Figure 22 shows a state where the orbital altitudes of the two orbital planes 21a and 21b are different, and the satellite passage timings of satellites 30a and 30b are staggered at point Pc near the intersection of each orbital plane 21a and 21b. The satellite constellation forming unit 11 gradually brings the orbital altitudes of the two orbital planes 21a and 21b to match while maintaining the state of staggered satellite passage timings.

[0105] When satellites flying at the same altitude in orbital planes with different angles of normality, there is a risk of collision at the intersection point. Furthermore, the risk of collision is high when additional satellites are placed into orbit after a large number of satellites have been established in their respective orbital planes. Therefore, the same number of satellites are pre-arranged in a formation with roughly equal spacing, and their orbital altitudes are gradually brought closer together. By gradually bringing their orbital altitudes closer together, the satellites at nearby altitudes will have roughly the same velocity relative to the ground. Thus, satellites that are pre-arranged in phase to fly in formation can change their orbital altitudes without colliding with each other.

[0106] Furthermore, the satellite constellation formation unit 11 maintains the state in which the satellite passage timings are staggered at the intersection points Pc of each orbital plane, and causes the orbital altitude of one orbital plane to overtake the orbital altitude of the other orbital plane. Between the intersection points Pc of each orbital plane 21 and the next intersection point Pc, the satellite constellation formation unit 11 causes the satellites of one orbital plane to overtake the orbital altitude of the other orbital plane.

[0107] Figure 23 shows the overtaking of the adjacent orbital plane by satellite 30b. Figure 23 shows satellite 30b in orbital plane 21b overtaking satellite 21a. Satellite 30b in orbital plane 21b overtakes satellite 21a over a distance R between the intersection vicinity Pc1 and the next intersection vicinity Pc2.

[0108] When changing the satellite's altitude overtaking maneuver across multiple orbital planes with different angles of normals, there is a risk of collision at two points near the intersection of two orbital planes. Since there is no risk of collision anywhere else, the orbital altitude can be changed without collision by overtaking between the points near the intersections.

[0109] In this embodiment, the control unit 110 controls the velocity vector of the rocket 202 as it passes the orbital altitude of the megaconstellation satellite group 411, which is flying at an orbital inclination angle of 40 to 60 degrees. Specifically, the control unit 110 controls the launch of the rocket 202 so that the velocity vector of the rocket 202, which is traveling from west to east in the east-west direction between 40 and 60 degrees latitude, is the same as the orbital velocity of the megaconstellation satellite group 411, and that the timing of passing over the satellites constituting the megaconstellation satellite group 411 is staggered.

[0110] ***Other configurations*** In this embodiment, the functions of the control unit 110 are implemented in software. As an alternative, the functions of the control unit 110 may be implemented in hardware.

[0111] The rocket launch control device 100 is equipped with electronic circuits in place of the processor 910. The electronic circuit is a dedicated electronic circuit that implements the functions of the control unit 110. Electronic circuits specifically include single circuits, complex circuits, programmed processors, parallel programmed processors, logic ICs, GAs, ASICs, or FPGAs. GA stands for Gate Array. ASIC stands for Application Specific Integrated Circuit. FPGA stands for Field-Programmable Gate Array. The functions of the control unit 110 may be implemented by a single electronic circuit, or they may be implemented by distributing them across multiple electronic circuits. As another variation, some functions of the control unit 110 may be implemented by electronic circuits, while the remaining functions are implemented by software.

[0112] The processor and electronic circuit are also called processing circuits. In other words, in the rocket launch control device 100, the functions of the control unit 110 are realized by the processing circuits.

[0113] In the above Embodiment 1, each part of the rocket launch control device was described as an independent functional block. However, the configuration of the rocket launch control device does not have to be as in the above embodiment. The functional blocks of the rocket launch control device can be configured in any way as long as they can realize the functions described in the above embodiment. Furthermore, the rocket launch control device may be a single device or a system composed of multiple devices.

[0114] Furthermore, multiple parts of Embodiment 1 may be combined and implemented. Alternatively, only one part of these embodiments may be implemented. In addition, these embodiments may be combined and implemented in any way, either as a whole or in part. In other words, the elements of Embodiment 1 may be partially combined as desired. Alternatively, the components of Embodiment 1 may be modified in any way. That is, components may be added or omitted in Embodiment 1.

[0115] The embodiments described above are essentially preferred examples and are not intended to limit the scope of the Disclosure, the scope of the Applications of the Disclosure, or the scope of Uses of the Disclosure. The embodiments described above can be modified in various ways as needed. [Explanation of symbols]

[0116] 20 Satellite constellation, 21, 21a, 21b orbital plane, 30, 30a, 30b satellites, 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 device, 41 Megaconstellation device, 411 Megaconstellation satellite group, 42 LEO constellation device, 43 Satellite device, 44 Orbital transfer device, 45 Debris recovery device, 46 Rocket launch device, 47 SSA device, 51 Satellite orbit forecast information, 511 Space object ID, 512 Forecast epoch, 513 Forecast orbital element, 514 Forecast error, 60 Space object, 70 Earth, 100 Rocket launch control device, 110 Control unit, 130 Memory unit, 55 Orbital control command, 201 Rocket launch site, 202 rocket, 202a recovery 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 and 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 reuse system that reuses a recoverable rocket by launching multiple recoverable rockets equipped with reusable rocket transport means and atmospheric deceleration devices, wherein the recoverable rocket is reused through a rocket reuse cycle, A rocket launch method for rockets launched from rocket launch sites located between 30 and 50 degrees latitude, The rocket launch site is a rocket launch method that controls the launch of the rocket so that, when the rocket passes the orbital altitude of a megaconstellation of 100 or more satellites, which is flying at an orbital inclination of 40 to 60 degrees, the velocity vector of the rocket, which is moving from west to east in an east-west direction at a latitude of 40 to 60 degrees, is the same as the orbital velocity of the megaconstellation, and the timing of the rocket's passage through the satellites constituting the megaconstellation is staggered. It is a rocket launch site that launches rockets to carry out the task. The aforementioned rocket launch site is a rocket launch site for launching rockets that perform an orbit insertion method for satellites flying in an inclined orbit, in which the satellite is inserted from west to east into the northern or southern end of an inclined orbit with an orbital inclination angle of 40 to 60 degrees. The aforementioned rocket launch site is a rocket launch site rented to implement a satellite constellation maintenance method in which, in a satellite constellation consisting of 10 or more satellites, a successor satellite is placed into orbit after the initial satellite constellation has been set up, due to satellite failure or the end of its lifespan. The recovery type rocket is launched from the aforementioned rocket launch site, The rocket, which descended into orbit after satellite separation, is recovered using a rocket recovery method that recovers it in an area different from the rocket launch site. A rocket reuse system that transports the rocket to the rocket launch site using the aforementioned reusable rocket transport means and launches the recoverable rocket again.

2. A rocket reuse system that reuses a recoverable rocket by launching multiple recoverable rockets equipped with reusable rocket transport means and atmospheric deceleration devices, wherein the recoverable rocket is reused through a rocket reuse cycle, A rocket launch method for rockets launched from rocket launch sites located between 30 and 50 degrees latitude, The rocket launch site is a rocket launch method that controls the launch of the rocket so that, when the rocket passes the orbital altitude of a megaconstellation of 100 or more satellites, which is flying at an orbital inclination of 40 to 60 degrees, the velocity vector of the rocket, which is moving from west to east in an east-west direction at a latitude of 40 to 60 degrees, is the same as the orbital velocity of the megaconstellation, and the timing of the rocket's passage through the satellites constituting the megaconstellation is staggered. It is a rocket launch site that launches rockets to carry out the task. The aforementioned rocket launch site is a rocket launch site for launching rockets that perform an orbital insertion method for satellites flying in an inclined orbit, which involves inserting a satellite from west to east into the northern or southern end of an inclined orbit with an orbital inclination angle of 40 to 60 degrees, and inserting the satellite into a specific orbital position on the orbital plane of the inclined orbit. The aforementioned rocket launch site is a rocket launch site rented to implement a satellite constellation maintenance method in which, in a satellite constellation consisting of 10 or more satellites, a successor satellite is placed into orbit after the initial satellite constellation has been set up, due to satellite failure or the end of its lifespan. The recovery type rocket is launched from the aforementioned rocket launch site, The rocket, which descended into orbit after satellite separation, is recovered using a rocket recovery method that recovers it in an area different from the rocket launch site. A rocket reuse system that transports the rocket to the rocket launch site using the aforementioned reusable rocket transport means and launches the recoverable rocket again.

3. A rocket reuse system that reuses a recoverable rocket by launching multiple recoverable rockets equipped with reusable rocket transport means and atmospheric deceleration devices, wherein the recoverable rocket is reused through a rocket reuse cycle, A method for inserting a satellite flying in an inclined orbit, wherein the rocket is launched from a rocket launch site located between 30 and 50 degrees latitude, and the rocket is used to perform an orbit insertion method in which the satellite is inserted from west to east into the northern or southern end of an inclined orbit with an orbital inclination angle of 40 to 60 degrees. The aforementioned rocket launch site is a rocket launch site rented to implement a satellite constellation maintenance method in which, in a satellite constellation consisting of 10 or more satellites, a successor satellite is placed into orbit after the initial satellite constellation has been set up, due to satellite failure or the end of its lifespan. The recovery type rocket is launched from the aforementioned rocket launch site, The rocket, which descended into orbit after satellite separation, is recovered using a rocket recovery method that recovers it in an area different from the rocket launch site. A rocket reuse system that transports the rocket to the rocket launch site using the aforementioned reusable rocket transport means and launches the recoverable rocket again.

4. A rocket reuse system that reuses a recoverable rocket by launching multiple recoverable rockets equipped with reusable rocket transport means and atmospheric deceleration devices, wherein the recoverable rocket is reused through a rocket reuse cycle, A method for inserting a satellite flying in an inclined orbit, wherein the rocket is launched from a rocket launch site located at latitudes between 30 and 50 degrees, and the rocket is launched from a rocket launch site that performs an orbit insertion method in which the satellite is inserted from west to east towards the northern or southern end of an inclined orbit with an orbital inclination angle of 40 to 60 degrees, thereby inserting the satellite into a specific orbital position on the orbital plane of the inclined orbit. The aforementioned rocket launch site is a rocket launch site rented to implement a satellite constellation maintenance method in which, in a satellite constellation consisting of 10 or more satellites, a successor satellite is placed into orbit after the initial satellite constellation has been set up, due to satellite failure or the end of its lifespan. The recovery type rocket is launched from the aforementioned rocket launch site, The rocket, which descended into orbit after satellite separation, is recovered using a rocket recovery method that recovers it in an area different from the rocket launch site. A rocket reuse system that transports the rocket to the rocket launch site using the aforementioned reusable rocket transport means and launches the recoverable rocket again.

5. A debris removal method for a satellite constellation consisting of 10 or more satellites, in which, after the initial satellite constellation has been set up, satellites that are unable to deorbit due to malfunctions are actively removed as debris. A method for inserting a satellite flying in an inclined orbit, wherein the satellite is launched by a rocket from a rocket launch site located between 30 and 50 degrees latitude, and is inserted into the northern or southern end of an inclined orbit with an orbital inclination of 40 to 60 degrees, moving from west to east. A rocket that performs an orbit insertion method to place a satellite into orbit at a specific orbital position on the orbital plane of the aforementioned inclined orbit, It is equipped with a debris removal system and orbital control device for capturing a malfunctioning satellite. This debris removal method involves capturing the malfunctioning satellite after a successor satellite has been placed into orbit, and then using reverse thrust to deorbit it.

6. A rocket equipped with debris removal capabilities, which, after the rocket launch operation is complete, captures the debris and uses reverse thrust to deorbit it.

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