Space debris removal system, space debris removal method, space debris removal apparatus, and injection object

Abstract

To provide a novel space debris removal system.SOLUTION: A space debris removal system includes: a space debris removal apparatus for removing space debris by injecting an injection object; and the injection object. The space debris removal apparatus includes an injection part for injecting the injection object. In the space debris removal system, the injection part injects the injection object by utilizing a magnetic field generated when electric current is caused to flow to a coil.SELECTED DRAWING: Figure 1

Description

[Technical field]

[0001] The present invention relates to a space debris removal system, a space debris removal method, a space debris removal device, and a projectile. [Background technology]

[0002] As space development advances, the amount of space debris is increasing year by year.

[0003] If space debris collides with active satellites, manned spacecraft, the International Space Station (ISS), or other such objects, it could destroy equipment or pose a risk to the lives of the crew.

[0004] Therefore, there is an increasing need to remove space debris. Summary of the Invention [Problem to be solved by the invention]

[0005] At least one object of the present invention is to provide a novel space debris removal system. [Means for solving the problem]

[0006] The object of the present invention is to [1] A space debris removal system comprising a space debris removal device that removes space debris by ejecting a projectile, and a projectile, wherein the space debris removal device comprises an ejection unit that ejects the projectile, and the ejection unit ejects the projectile by utilizing a magnetic field generated by passing a current through a coil; [2] The space debris removal system according to [1] above, comprising a plurality of space debris removal devices; [3] The space debris removal system according to [1] or [2], wherein the projectile has an adhesive portion having adhesive properties; [4] The space debris removal system according to any one of [1] to [3] above, wherein the projectile has a planar portion that can be deployed in a planar shape; [5] A space debris removal system according to any one of [1] to [4] above, comprising a voltage application control means for controlling the application of voltage to the coil and an injection detection means for detecting that an object has been injected, and the voltage application control means controls to stop the application of voltage when the injection detection means detects that an object has been injected; [6] A space debris removal system according to any one of [1] to [5] above, comprising: an image acquisition means for acquiring an image of outer space; a distance determination means for determining the distance between the space debris removal device and the space debris by using laser light; and a position determination means for determining information on the position of the space debris based on the image of outer space acquired by the image acquisition means and the distance between the space debris removal device and the space debris determined by the distance determination means; [7] A method for removing space debris by ejecting a projectile, the method comprising the step of ejecting the projectile, the step of ejecting the projectile utilizing a magnetic field generated by passing a current through a coil; [8] A space debris removal device that removes space debris by ejecting a projectile, the device comprising an ejection unit that ejects the projectile, the ejection unit ejecting the projectile by utilizing a magnetic field generated by passing a current through a coil; [9] A projectile for use in a space debris removal device that removes space debris by ejecting the projectile, the projectile having an adhesive portion having adhesive properties;

[10] A projectile used in a space debris removal device that removes space debris by ejecting a projectile, the projectile having a planar portion that can be deployed into a planar shape; This is achieved by: Effect of the Invention

[0007] According to the present invention, a novel space debris removal system can be provided. [Brief description of the drawings]

[0008] [Figure 1] 1 is a schematic diagram for explaining the configuration of a space debris removal system according to an embodiment of the present invention. [Diagram 2] FIG. 2 is a schematic diagram for explaining a mode of connection of a space debris removal device according to an embodiment of the present invention. [Diagram 3] 2 is a schematic diagram for explaining a connection state between a space debris removal device and a power supply device according to an embodiment of the present invention. FIG. [Figure 4] 1A-1C are schematic diagrams illustrating examples of projectiles according to an embodiment of the present invention. [Diagram 5] 1A-1C are schematic diagrams illustrating examples of projectiles according to an embodiment of the present invention. [Figure 6] 4 is a flowchart of a position identification process according to an embodiment of the present invention. [Figure 7] 4 is a flowchart of an injection process according to an embodiment of the present invention. DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

[0009] The following describes an embodiment of the present invention, but the present invention is not limited to the following embodiment, as long as it does not go against the spirit of the present invention. The order of each process constituting the flowchart described below is random as long as there is no contradiction or inconsistency in the process content, and it is also possible to omit a part of each process constituting the flowchart or add a new process to each process constituting the flowchart, as long as there is no contradiction or inconsistency in the process content. In addition, the device that executes each process constituting the flowchart can be changed to another device, as long as it does not go against the spirit of the present invention. In that case, the process content can be changed so that there is no contradiction or inconsistency in the process content.

[0010] The space debris removal system of the present invention includes a space debris removal device that removes space debris by ejecting a projectile, and the projectile. "Removal of space debris" includes moving space debris, changing the orbit of space debris, collecting space debris, etc.

[0011] The space debris removal device can be mounted on a satellite and launched into space. The space debris removal device can be provided, for example, on the exterior of the satellite. When mounted on the satellite, the space debris removal device can eject a projectile at space debris present in space and remove the space debris. The satellite may be launched to remove space debris, or may be launched for another purpose. An application for using the space debris removal system of the present invention may be installed in a device constituting a control system provided in a satellite equipped with the space debris removal device.

[0012] Fig. 1 is a schematic diagram for explaining the configuration of a space debris removal system according to an embodiment of the present invention. The space debris removal system 1 shown in Fig. 1 includes a space debris removal device 11, a projectile 12, a power supply device 13, and a control device 14. The space debris removal device 11 shown in Fig. 1 also includes an ejection unit 111, a switch circuit 112, a sensor 113, and a housing 114. The ejection unit 111 and the switch circuit 112, the power supply device 13 and the switch circuit 112, the control device 14 and the switch circuit 112, the control device 14 and the sensor 113, and the switch circuit 112 and the sensor 113 may be connected by communication, or may be electrically connected by a conductor or the like.

[0013] The ejection unit 111 ejects the ejection object 12. The ejection unit 111 includes at least one coil. The coil may be an air-core solenoid coil. For example, the ejection unit 111 may be a cylindrical body with a coil wound around the outside. The cylindrical body may be a cylindrical body or a rectangular tube. In other words, the cross-sectional shape of the cylindrical body in a direction perpendicular to the length of the tube is not particularly limited. A magnetic field can be generated by applying a voltage to the coil and passing a current through it.

[0014] The projectile 12 can be placed inside the ejection part 111. Hereinafter, placing the projectile 12 inside the ejection part 111 is referred to as loading the projectile 12 into the ejection part 111 or the space debris removal device 11. In addition, the position inside the ejection part 111 where the projectile 12 is placed is referred to as the loading position of the projectile 12.

[0015] In FIG. 1, the projectile 12 is loaded at the end of the ejection section 111. The projectile 12 passes through the inside of the ejection section 111 and is ejected from the end opposite to the end where the projectile 12 is loaded in FIG. 1. In the ejection section 111 and the housing 114, the portion from which the projectile 12 is ejected is preferably open. The opening from which the projectile 12 is ejected in the space debris removal device 11 is also referred to as the ejection port. Hereinafter, in the space debris removal device 11, the side where the ejection port is provided is referred to as the front, and the side opposite to the side where the ejection port is provided is referred to as the rear. The loading position of the projectile 12 may be the rear side inside the ejection section 111.

[0016] The projectile 12 uses a material having a magnetic body for at least a part of the material constituting the projectile 12. By using a material having a magnetic body for the projectile 12, a magnetic force acts on the projectile 12 existing in a magnetic field generated by passing a current through the coil, and the projectile 12 moves from the rear to the front of the projectile 111. As a result, the projectile 12 can be projected by the projectile 111 using the magnetic field generated by passing a current through the coil. The speed at which the projectile 12 is projected can be appropriately designed depending on the material used for the projectile 12, the configuration of the coil, the voltage applied to the coil, and the like.

[0017] The material having a magnetic body is not particularly limited and can be appropriately designed. For example, a ferromagnetic material such as iron, cobalt, or nickel, or a paramagnetic material such as aluminum, titanium, or zirconium can be used as the material having a magnetic body.

[0018] The shape of the ejection section 111 is not particularly limited and can be designed appropriately. For example, the ejection section 111 may have a tubular shape. The tubular shape may be a cylindrical shape or a square tube shape. The cross-sectional area of ​​the ejection section 111 in a direction perpendicular to the front-rear direction (hereinafter also referred to as the cross-sectional area of ​​the ejection section 111) may be uniform or non-uniform. For example, the cross-sectional area of ​​the ejection section 111 may be configured to increase from the rear to the front. By configuring the cross-sectional area of ​​the ejection section 111 to increase from the rear to the front, when an ejection object 12 having a planar portion that can be expanded in a planar shape is ejected, the ejection object 12 is easily expanded in a planar shape.

[0019] The number of coils included in the emission unit 111 is not particularly limited and can be designed as appropriate. The number of coils included in the emission unit 111 may be 1, 3, or 5. When the emission unit 111 includes multiple coils, the multiple coils can be arranged in front and behind each other so that the central axes of the multiple coils are aligned on the same line.

[0020] The configuration of the coil is not particularly limited and can be designed appropriately. The configuration of the coil may be designed according to the size of the projectile 12, etc. The configuration of the coil includes, for example, the length in the front-rear direction, the number of turns, the number of turns per unit length, the shape of the cross section in a direction perpendicular to the front-rear direction of the coil, the area of ​​the cross section, the diameter of the conductor constituting the coil, the material of the conductor, etc. When the projection unit 111 includes multiple coils, the configuration of each coil may be the same or different.

[0021] Furthermore, when the projection unit 111 includes multiple coils, it is also possible to change the magnitude of the current flowing through each coil. The stronger the current flowing through a coil, the stronger the magnetic field that is generated. Therefore, for example, by making the current flowing through the front coils larger than the current flowing through the rear coils, the magnetic field on the front side can be made stronger, and the projection 12 can be accelerated as it moves forward.

[0022] The power supply device 13 stores power for applying a voltage to the coil. The power supply device 13 may convert the stored power into power suitable for applying to the coil. For example, the power supply device 13 may generate power suitable for ejecting the projectile 12 by converting the voltage, frequency, waveform, etc. of the stored power.

[0023] The power supply device 13 may also be connected to a power supply system provided in the satellite on which the space debris removal device 11 is mounted. The power supply system provided in the satellite may be capable of obtaining power through solar power generation. The power supply device 13 and the power supply system provided in the satellite may be connected by communication, or may be electrically connected by a conductor or the like. The power supply device 13 may be capable of receiving power from the power supply system provided in the satellite.

[0024] The power supply device 13 may be connected to the coil via a switch circuit 112. The switch circuit 112 switches the application of a voltage to the coil on and off.

[0025] The on / off switching of the voltage application to the coil in the switch circuit 112 may be controlled by the control device 14. The control device 14 controls the ejection of the projectile 12 by the space debris removal device 11.

[0026] 1, when the control device 14 controls the switch circuit 112 to switch on the application of voltage to the coil, the application of voltage to the coil included in the emission unit 111 is started, and a current flows from the front to the rear of the coil. When the control device 14 controls the switch circuit 112 to switch off the application of voltage to the coil, the application of voltage to the coil included in the emission unit 111 is stopped.

[0027] In addition, if the space debris removal device 11 does not have the switch circuit 112, the control device 14 may control the start and stop of application of voltage to the coil provided in the emission unit 111 without going through the switch circuit 112.

[0028] The control device 14 may be connected to a control system of the satellite on which the space debris removal device 11 is mounted. The control device 14 and the control system of the satellite may be connected by communication or may be electrically connected by a conductor or the like. The control device 14 may control the ejection of the projectile 12 by the space debris removal device 11 according to the control from the control system of the satellite.

[0029] The sensor 113 detects that the projectile 12 has been ejected. "Projectile 12 has been ejected" refers to the projectile 12 having moved from the loaded position. For example, "projectile 12 has been ejected" may refer to the projectile 12 no longer being at the loaded position, the projectile 12 having reached a predetermined position in the ejection section 111, the projectile 12 having been ejected from the ejection port, etc.

[0030] The sensor 113 may detect that the ejected object 12 has passed through the ejection section 111. The type of the sensor 113 is not particularly limited and may be designed as appropriate. For example, a photoelectric sensor, a laser sensor, or the like may be adopted as the sensor 113. The configuration of the sensor 113 may be, for example, a separate amplifier type, a built-in amplifier type, a fiber type, a built-in battery type, or the like. The type of detection method used by the sensor 113 may be, for example, a transmission type, a diffuse reflection type, a retroreflective type, or the like.

[0031] The position where the sensor 113 is provided in the space debris removal device 11 is not particularly limited and can be designed appropriately. For example, the sensor 113 may be provided near the front end of the loaded projectile 12, at a substantially middle position in the front-rear direction of the ejection part 111, or near the ejection port.

[0032] When the sensor 113 detects that the projectile 12 has been ejected, a signal indicating that the projectile 12 has been ejected (hereinafter, referred to as an ejection detection signal) may be transmitted to the control device 14. When the control device 14 receives the ejection detection signal, the control device 14 may perform control to stop the application of a voltage to the coil corresponding to the ejected projectile 12. For example, when the control device 14 receives the ejection detection signal, the control device 14 may perform control to switch off the application of a voltage to the coil in the switch circuit 112.

[0033] Alternatively, the injection detection signal may be transmitted to the switch circuit 112. Furthermore, when the switch circuit 112 receives the injection detection signal, it may switch off the application of the voltage to the coil. In this case, the switch circuit 112 may be provided with a control unit such as a microcomputer. Then, the control unit provided in the switch circuit 112 may receive the injection detection signal. Furthermore, the control unit provided in the switch circuit 112 may perform control to switch off the application of the voltage to the coil.

[0034] The injection detection signal may also be transmitted to a control system included in the satellite. In this case, the injection detection signal may be transmitted to the control system via the control device 14, or may be transmitted directly from the sensor 113 to the control system. When the control system receives the injection detection signal, the control system may perform control so as to switch off the application of voltage to the coil in the switch circuit 112.

[0035] 1, emission unit 111, switch circuit 112, and sensor 113 are provided inside housing 114. Although not shown, housing 114 may have an opening serving as an emission outlet in front of emission unit 111. It is sufficient that housing 114 has at least one emission unit 111 inside housing 114.

[0036] Although not shown, for example, two or more emitters 111 may be provided inside one housing 114. Also, for example, two or more switch circuits 112 and / or two or more sensors 113 may be provided inside one housing 114. Alternatively, for example, the control device 14 and / or the power supply device 13 may be provided inside the housing 114. Also, for example, the switch circuit 112 and / or the sensor 113 may be provided outside the housing 114.

[0037] The size, material, shape, etc. of the housing 114 can be designed appropriately.

[0038] The housing 114 may have a connecting portion for connecting to another housing 114. The shape of the connecting portion and the method for connecting the housings 114 to each other are not particularly limited and can be designed appropriately.

[0039] From the viewpoint of facilitating the connection of a plurality of housings 114, it is preferable that the shape of the housing 114 is a substantially rectangular parallelepiped shape. The space debris removal device 11 may be capable of being mounted on an artificial satellite in a state in which a plurality of housings 114 are connected to each other.

[0040] When multiple housings 114 are connected, the sizes, materials, shapes, etc. of the multiple housings 114 may be the same or may differ partially or entirely. From the viewpoint of facilitating connection of multiple housings 114, it is preferable that the sizes and shapes of the multiple housings 114 are the same.

[0041] FIG. 2 is a schematic diagram for explaining a mode of connection of a space debris removal apparatus according to an embodiment of the present invention.

[0042] In Fig. 2, the space debris removal device 11 includes one housing 114 and one emission unit 111. A plurality of housings 114 are connected to each other to thereby connect a plurality of space debris removal devices 11. In Fig. 2, the emission port of the space debris removal device 11 is viewed from the front. In Figs. 2(A) to (C), reference numerals are omitted except for the one emission unit 111, the housing 114, and the space debris removal device 11.

[0043] Fig. 2(A) is a diagram showing a state in which a plurality of space debris removal devices 11 are connected in a row horizontally. In Fig. 2(A), four space debris removal devices 11 are connected in a row horizontally.

[0044] Fig. 2(B) is a diagram showing a state in which a plurality of space debris removal devices 11 are connected vertically in a row. In Fig. 2(B), four space debris removal devices 11 are connected vertically in a row.

[0045] Fig. 2(C) is a diagram showing a state in which multiple space debris removal devices 11 are connected vertically and horizontally. In Fig. 2(C), four rows of space debris removal devices 11 are connected vertically and four rows of space debris removal devices 11 horizontally. The number of connected space debris removal devices 11 is 16 in total.

[0046] In addition, the "vertical" and "horizontal" in the above may refer to the "vertical" and "horizontal" of the space debris removal device 11, or may refer to the "vertical" and "horizontal" of the artificial satellite on which the space debris removal device 11 is mounted. For example, if the space debris removal device 11 has a definition of the up, down, left, and right directions, the space debris removal device 11 may be connected in the up and down direction as "vertical connection", and the space debris removal device 11 may be connected in the left and right direction as "horizontal connection". Alternatively, for example, if the artificial satellite on which the space debris removal device 11 is mounted has a definition of the up, down, left, and right directions, the space debris removal device 11 may be connected in the up and down direction of the artificial satellite when mounted on the artificial satellite as "vertical connection", and the space debris removal device 11 may be connected in the left and right direction of the artificial satellite when mounted on the artificial satellite as "horizontal connection".

[0047] In addition, the manner in which the space debris removal devices 11 are connected is not limited to the above description and can be designed as appropriate. For example, the space debris removal devices 11 may be connected in a manner that does not form a row, or in a manner that does not line up "vertically" or "horizontally". When the space debris removal system 1 includes multiple space debris removal devices 11, some or all of the multiple space debris removal devices 11 can be connected in any manner. Each of the multiple space debris removal devices 11 only needs to be connected to a power supply device 13 and a control device 14.

[0048] When the space debris removal system 1 includes a plurality of space debris removal devices 11, the manner in which the power supply device 13 and the space debris removal devices 11 are connected is not particularly limited and can be designed as appropriate.

[0049] For example, if the space debris removal system 1 includes multiple space debris removal devices 11, two or more space debris removal devices 11 may be connected to one power supply device 13. The manner in which two or more space debris removal devices 11 are connected to one power supply device 13 is not particularly limited and can be designed as appropriate. For example, two or more space debris removal devices 11 may be connected in parallel to one power supply device 13.

[0050] Fig. 3 is a schematic diagram showing an example of the connection state between the space debris removal device and the power supply device according to the embodiment of the present invention. Fig. 3 is a schematic diagram showing an example of the connection state between the space debris removal device 11 and the power supply device 13 when four rows of space debris removal devices 11 are connected vertically and four rows of space debris removal devices 11 horizontally, as in Fig. 2(C).

[0051] 3, 16 space debris removal devices 11 (11a, 11b, ..., and 11p) are connected in parallel to one power supply device 13. Inside each space debris removal device 11, the power supply device 13 may be connected to the coil of the emission part 111 via a switch circuit 112.

[0052] Alternatively, for example, if the space debris removal system 1 includes multiple space debris removal devices 11, the space debris removal system 1 may include multiple power supply devices 13, and one space debris removal device 11 may be connected to one power supply device 13.

[0053] Alternatively, for example, if the space debris removal system 1 is equipped with multiple space debris removal devices 11, the power supply device 13 may be connected sequentially to the space debris removal device 11 that will next eject the projectile 12.

[0054] Although not shown, the space debris removal system 1 may include two or more power supply devices 13 and / or two or more control devices 14. The manner of connection between the space debris removal device 11, the power supply device 13, and the control device 14 is not particularly limited and can be designed as appropriate. When the space debris removal system 1 includes two or more power supply devices 13 and / or two or more control devices 14, even if one or more power supply devices 13 and / or one or more control devices 14 fail, the space debris removal device 11 can be operated by connecting it to a power supply device 13 and / or control device 14 that is not broken.

[0055] Next, the projectile 12 used in the space debris removal device 11 will be described. The shape of the projectile 12 is not particularly limited and can be designed as appropriate. The shape of the projectile 12 may be, for example, a sphere, an egg, a cone, a pyramid, a rectangular parallelepiped, a cylinder, a prism, or a bullet-like shape. In addition, the method by which the projectile 12 removes space debris is also not particularly limited and can be designed as appropriate.

[0056] 4 is a schematic diagram showing an example of a projectile according to an embodiment of the present invention. Projectile 12 shown in Figs. 4(A) to (C) has a shape like a cannonball, and includes body 121 and head 122. Hereinafter, in projectile 12 shown in Figs. 4(A) to (C), the tip (apex) side of head 122 is defined as the upper side, and the side of body 121 not in contact with head 122 is defined as the lower side. Projectile 12 shown in Figs. 4(A) to (C) may be loaded into projectile 111 with the lower side facing rearward of projectile 111 and the upper side facing forward of projectile 111.

[0057] The ejection object 12a shown in FIG. 4(A) has a shape obtained by combining the upper surface of a substantially cylindrical main body 121a with the bottom surface of a substantially conical head 122a.

[0058] 4B, the ejection object 12b has a shape obtained by combining the upper surface of a substantially cylindrical main body 121b with the bottom surface of a substantially conical head 122b. The head 122b of the ejection object 12b has a cone shape with a rounded apex.

[0059] The projectiles 12a and 12b are ejected from the space debris removal device 11 and can move the space debris and / or change the orbit of the space debris by colliding with the space debris.

[0060] In addition, by physically connecting the space debris removal device 11 and the projectile 12a, or the space debris removal device 11 and the projectile 12b with a string or the like, it is possible to collect the projectile 12a or 12b after it collides with the space debris.

[0061] 4(C) has a shape that combines the upper surface of a substantially cylindrical main body 121c and the bottom surface of a substantially conical head 122c. A substantially circular sheet-like adhesive portion 123 is provided at the apex of the head 122c of the ejection object 12c.

[0062] The adhesive portion 123 has adhesiveness. The material of the adhesive portion 123 is not particularly limited and can be appropriately designed. For example, an adhesive gel sheet or the like may be used as the adhesive portion 123.

[0063] The shape of the adhesive portion 123 is not particularly limited and can be designed appropriately. The shape of the adhesive portion 123 may be, for example, a sheet-like shape, a string-like shape, or a three-dimensional shape. In addition, when the adhesive portion 123 is sheet-like, the shape of the sheet may be, for example, a circular shape, an elliptical shape, a polygonal shape, or any other shape. In addition, when the adhesive portion 123 is three-dimensional, the three-dimensional shape may be, for example, a spherical shape, an egg shape, a conical shape, a pyramidal shape, a rectangular parallelepiped shape, a cylindrical shape, a prismatic shape, or any other shape.

[0064] The position of the adhesive portion 123 in the ejection object 12c is not particularly limited and can be appropriately designed. The position of the adhesive portion 123 may be, for example, near the tip of the ejection object 12c (the end portion on the front side in the traveling direction when the ejection object 12c is ejected) or may be other than near the tip of the ejection object 12c.

[0065] Alternatively, for example, the surface of the main body portion 121c and / or the head portion 122c of the projectile 12c may have adhesiveness and function as the adhesive portion 123.

[0066] The projectile 12c is projected from the space debris removal device 11, collides with the space debris, and can adhere to the space debris. As a result, the projectile 12c is not repelled and transmits the kinetic energy of the projectile 12c to the space debris (a part of the kinetic energy of the projectile 12c is converted into the kinetic energy of the space debris), and can move the space debris and / or change the orbit of the space debris. Since the projectile 12c has the adhesive portion 123, it is possible to transmit the kinetic energy of the projectile 12c to the space debris regardless of the angle of collision with the space debris, the shape of the surface of the space debris, and the like.

[0067] In addition, by physically connecting the space debris removal device 11 and the projectile 12c with a string or the like, it is possible to collect the attached space debris.

[0068] The ejection object 12 may or may not have a cavity therein.

[0069] Fig. 5 is a schematic diagram showing an example of a projectile according to an embodiment of the present invention. Projectile 12d has a planar portion 124 that can be expanded into a planar shape. In Fig. 5, planar portion 124 is made of a net. Also, in Fig. 5, three weights 125 (125a, 125b, and 125c) are provided at the end of planar portion 124.

[0070] When the projectile 12d is ejected from the space debris removal device 11, as shown in the figure, the weight 125 spreads, and the planar portion 124 is pulled by the weight 125, so that the planar portion 124 develops into a planar shape. Note that "the weight 125 spreads" refers to the weight 125 moving in a direction perpendicular to the direction in which the projectile 12d is ejected (hereinafter also referred to as the ejection direction of the projectile 12d). Also, "the weight 125 moves in a direction perpendicular to the ejection direction of the projectile 12d" refers to the fact that, when the movement of the weight 125 is expressed as a vector, the vector has a vector component perpendicular to the ejection direction of the projectile 12d.

[0071] When the planar portion 124 reaches the space debris, it can engulf the space debris or entangle it. Then, it can move and / or change the orbit of the engulfed or entangled space debris. When there are multiple space debris, the projectile 12d can move and / or change the orbit of the multiple space debris collectively.

[0072] In addition, by physically connecting the space debris removal device 11 and the projectile 12d with a string or the like, it is possible to collect the space debris that is wrapped up or entangled therewith.

[0073] The material constituting the planar portion 124 is not particularly limited and can be appropriately designed. The material constituting the planar portion 124 may be, for example, a net, a cloth, a resin sheet, leather, or paper.

[0074] The material of the weight 125 is not particularly limited and can be appropriately designed. For example, the material of the weight 125 may be a magnetic material.

[0075] The shape of weight 125 is not particularly limited and can be designed appropriately. For example, the shape of weight 125 may be a three-dimensional shape such as a sphere, an egg shape, a cone shape, a pyramid shape, a rectangular parallelepiped shape, a cylindrical shape, or a prismatic shape, or may be a planar shape such as a circle, an ellipse, or a polygon.

[0076] The number of weights 125 provided on the planar portion 124 is not particularly limited and can be designed as appropriate. The number of weights 125 provided on the planar portion 124 may be, for example, three, five, or ten. The number of weights 125 provided on the planar portion 124 may be designed according to the size of the planar portion 124, etc.

[0077] Furthermore, the position at which weight 125 is provided on planar portion 124 is not particularly limited and can be designed as appropriate. Weight 125 may be provided, for example, at the end of planar portion 124, or may be provided on the outer edge near the end of planar portion 124. Weight 125 is preferably provided at a position that allows planar portion 124 to be easily deployed on a surface.

[0078] In the above, an example has been described in which the planar portion 124 includes the weight 125, and the weight 125 spreads to cause the planar portion 124 to expand into a planar shape, but the manner in which the planar portion 124 expands into a planar shape is not particularly limited and can be designed as appropriate. For example, the planar portion 124 may include a framework that can expand like an umbrella, and after the projectile 12d is ejected, the framework expands to cause the planar portion 124 to expand into a planar shape.

[0079] The projectile 12d having the planar portion 124 may be loaded into the ejection section 111 with the planar portion 124 folded compactly.

[0080] There are no particular limitations on the materials constituting the devices constituting the space debris removal system 1, and they can be designed as appropriate. It is preferable that the materials constituting the devices constituting the space debris removal system 1 are ones that can withstand use in outer space, use at high temperatures, and shocks during launch.

[0081] The space debris removal system 1 of the present invention may be capable of identifying the location, moving direction, moving speed, etc. of space debris (hereinafter also referred to as information on the location of space debris) and launching a projectile 12 toward the space debris. Hereinafter, an embodiment of identifying information on the location of space debris will be described.

[0082] FIG. 6 is a flowchart of a location specification process according to an embodiment of the present invention.

[0083] The space debris removal system 1 acquires an image of outer space (step S101). Next, the space debris removal system 1 identifies the distance between the space debris removal device 11 and the space debris (step S102). Then, the space debris removal system 1 identifies information about the position of the space debris based on the image of outer space acquired in step S101 and the distance between the space debris removal device 11 and the space debris identified in step S102 (step S103), and ends the position identification process.

[0084] The processing of steps S101 to S103 may be executed by any device, functional unit, or system included in the space debris removal system 1. The processing of steps S101 to S103 may be executed, for example, by the control device 14 included in the space debris removal device 11, or may be executed by a control system included in the artificial satellite on which the space debris removal device 11 is mounted. The following mainly describes an example in which the processing of steps S101 to S103 is executed by a control system included in the artificial satellite on which the space debris removal device 11 is mounted.

[0085] In step S101, the method of acquiring the image of the outer space is not particularly limited and can be designed appropriately. For example, the space debris removal system 1 may include an imaging device such as a camera, and the imaging device may capture the image of the outer space. The image captured by the imaging device may be transmitted to a control system. The imaging device may be mounted on the exterior of the artificial satellite on which the space debris removal device 11 is mounted.

[0086] Alternatively, if the satellite carrying the space debris removal device 11 is equipped with an imaging device such as a camera, an image captured by the imaging device of the satellite may be transmitted to the control system. Alternatively, an image captured by an imaging device of another satellite may be transmitted to the control system of the satellite carrying the space debris removal device 11. The other satellite may be equipped with another space debris removal device 11 or may not be equipped with another space debris removal device 11.

[0087] The "image taken of outer space" is not particularly limited as long as it is an image taken of the inside of outer space. The "image taken of outer space" may be a moving image or a still image. It is preferable that the "image taken of outer space" shows some or all of the space debris present in outer space. From the viewpoint of making it easy to identify the presence of space debris and the direction in which the space debris is moving, it is preferable that the "image taken of outer space" is a moving image showing the entire space and the space debris present in the outer space (the whole image).

[0088] In step S102, the method of determining the distance between the space debris removal device 11 and the space debris is not particularly limited and can be designed appropriately. For example, the space debris removal system 1 may determine the distance between the space debris removal device 11 and the space debris by using a laser light. In that case, the space debris removal system 1 may be equipped with a laser range finder. It is preferable that the laser range finder has a high output and low power consumption.

[0089] The laser range finder can measure the distance between the space debris and the laser range finder by irradiating the space debris in the image captured in step S101 with a laser beam and measuring the time it takes for the laser beam reflected by the space debris to reach the light receiving unit. The laser range finder may transmit the measured distance to the control system.

[0090] The control system can determine the distance between the space debris and the space debris based on the distance between the laser rangefinder and the space debris received from the laser rangefinder, the position of the laser rangefinder on the satellite, and the position of the space debris removal device 11 on the satellite. Information on the position of the laser rangefinder on the satellite and the position of the space debris removal device 11 on the satellite may be stored in the control system in advance. If the space debris removal system 1 includes multiple space debris removal devices 11, the space debris removal system 1 may determine the distance between the space debris and the space debris removal device 11 that will next launch the projectile 12.

[0091] The "information on the position of the space debris" in step S103 may include the position of the space debris, the direction of movement of the space debris, the speed of movement of the space debris, etc. The position of the space debris may be the relative position of the space debris with respect to the space debris removal device 11, or the absolute position of the space debris expressed by a predetermined coordinate system, etc. The direction of movement of the space debris may be the relative movement direction of the space debris with respect to the space debris removal device 11, or the absolute movement direction of the space debris expressed by a predetermined coordinate system, etc.

[0092] In step S103, the method of identifying information about the location of the space debris is not particularly limited and can be designed as appropriate.

[0093] The control system may, for example, identify the direction in which the space debris exists based on the image of outer space acquired in step S101. Then, the control system may identify the position of the space debris based on the direction in which the space debris exists and the distance between the space debris removal device 11 and the space debris identified in step S102.

[0094] The control system may also determine the direction of movement of the space debris and / or the speed of movement of the space debris, for example, by determining the position of the space debris at predetermined times.

[0095] Alternatively, the control system may determine the direction of movement of the space debris based on, for example, an image of outer space acquired in step S101.

[0096] Based on the information about the position of the space debris identified by the above-mentioned position identification process, the control system may specify the direction in which to launch the projectile 12. In addition, the control system may specify the direction in which to launch the projectile 12 by using information about the movement status of the artificial satellite on which the space debris removal device 11 is mounted, the launch speed (movement speed) of the projectile 12 of the space debris removal device 11, and the like, in addition to the information about the position of the space debris.

[0097] When the space debris removal system 1 includes a plurality of space debris removal devices 11, the control system may specify which space debris removal device 11 will eject the projectile 12. The space debris removal system 1 may change the orientation of the satellite and / or the space debris removal device 11 so that the ejection port of the specified space debris removal device 11 faces the specified direction. The change in orientation of the satellite and / or the space debris removal device 11 may be controlled and executed by the control system. With the ejection port of the specified space debris removal device 11 facing the specified direction, the following ejection process may be executed.

[0098] FIG. 7 is a flow chart of an injection process according to an embodiment of the present invention.

[0099] The space debris removal system 1 starts applying a voltage to the coil provided in the emission unit 111 of the space debris removal device 11 (step S201). When the space debris removal system 1 detects that the projectile 12 has been emitted (step S202), it stops applying a voltage to the coil provided in the emission unit 111 of the space debris removal device 11 (step S203) and ends the emission process.

[0100] The application of voltage to the coil in step S201 may be controlled by the control device 14 included in the space debris removal device 11. For example, the control device 14 may control the switch circuit 112 included in the space debris removal device 11 identified by the control system to switch on the application of voltage to the coil. The control device 14 may control to start the application of voltage to the coil in response to receiving a command to eject the projectile 12 or a signal that serves as a trigger to eject the projectile 12 from the control system.

[0101] In step S201, when application of a voltage to the coil begins, the projectile 12 passes through the ejection section 111 and is ejected from the ejection port of the space debris removal device 11.

[0102] In step S202, the detection of the ejection of the ejection material 12 may be performed by the sensor 113. In addition, when the sensor 113 detects the ejection of the ejection material 12 in step S202, the sensor 113 may transmit an ejection detection signal to the control device 14.

[0103] In step S203, in response to receiving the ejection detection signal, the control device 14 may control to stop the application of voltage to the coil to which the application of voltage was started in step S201. For example, when the control device 14 receives the ejection detection signal, the control device 14 may control to switch off the application of voltage to the coil in the switch circuit 112 provided in the space debris removal device 11 specified by the control system.

[0104] Alternatively, the ejection detection signal may be transmitted to a switch circuit 112 included in the space debris removal device 11 that ejected the ejected object 12. In addition, in response to receiving the ejection detection signal, the switch circuit 112 may switch off the application of voltage to the coil in step S203.

[0105] In the above, the application of voltage to the coil is stopped in response to detection of the ejection of the projectile 12. However, the space debris removal system 1 may stop applying voltage to the coil when other conditions are met without detecting the ejection of the projectile 12. For example, the space debris removal system 1 may stop applying voltage to the coil when a predetermined time has elapsed since starting application of voltage to the coil. In that case, step S202 may not be executed.

[0106] If the space debris removal system 1 includes multiple space debris removal devices 11, the space debris removal system 1 may start to control the ejection of the projectile 12 from the other space debris removal devices 11 after ejecting the projectile 12 from a specific space debris removal device 11. For example, when the control device 14 and / or the control system receives an ejection detection signal, it may identify the space debris removal device 11 that will next eject the projectile 12 and start applying a voltage to the coil of the space debris removal device 11. For the ejection of the projectile 12 from the other space debris removal devices 11, the above description of the position identification process and / or the ejection process may be adopted to the extent necessary.

[0107] In this way, in a space debris removal system comprising a space debris removal device and a projectile, the space debris removal device is equipped with a projection unit that projects the projectile, and the projection unit projects the projectile using a magnetic field generated by passing an electric current through a coil, thereby providing a novel space debris removal system.

[0108] The space debris removal system of the present invention is mounted on a satellite and transported into space by a rocket. Therefore, it is preferable that the space debris removal system is inexpensive and lightweight. The space debris removal device of the present invention ejects projectiles using a magnetic field generated by passing a current through a coil, so that the structure is simple and the number of required parts is small. Therefore, it is possible to provide an inexpensive and lightweight space debris removal system.

[0109] Furthermore, by providing a space debris removal system with multiple space debris removal devices in this way, it becomes easy to remove multiple pieces of space debris using a single space debris removal system.

[0110] Furthermore, the space debris removal system thus comprises a voltage application control means for controlling the application of voltage to the coil, and an ejection detection means for detecting that a projectile has been ejected, and when the ejection detection means detects that a projectile has been ejected, the voltage application control means controls to stop the application of voltage, thereby stopping the application of voltage to the coil when the projectile has been ejected.

[0111] In this way, the space debris removal system is capable of identifying the location of space debris by comprising an image acquisition means for acquiring images of outer space, a distance determination means for determining the distance between the space debris removal device and the space debris by utilizing laser light, and a position determination means for determining information regarding the location of the space debris based on the image of outer space acquired by the image acquisition means and the distance between the space debris removal device and the space debris determined by the distance determination means.

[0112] The system for determining information on the location of space debris based on the image of space and the distance between the space debris removal device and the space debris can also be used in a system for removing space debris without ejecting a projectile. That is, a space debris location determination system comprising an image acquisition means for acquiring an image of space, a distance determination means for determining the distance between the space debris removal device and the space debris, and a location determination means for determining information on the location of the space debris based on the image of space acquired by the image acquisition means and the distance between the space debris removal device and the space debris determined by the distance determination means can be used alone. The distance between the space debris removal device and the space debris may also be determined using laser light. [Explanation of symbols]

[0113] 1. Space Debris Removal System 11 Space debris removal equipment 12 Projectile 13 Power supply 14 Control device 111 Injection part 112 Switch Circuit 113 Sensors 114 Case 121 Main body 122 Head 123 Adhesive part 124 Planar part 125 Weight

Claims

1. A space debris removal system including a space debris removal device that removes space debris by ejecting a projectile, and the projectile, Space debris removal equipment, The ejection section ejects the projectile. Equipped with The projection unit projects the projectile by utilizing a magnetic field generated by passing a current through a coil. Space debris removal system.

2. Equipped with multiple space debris removal devices, 2. A space debris removal system according to claim 1.

3. The ejected object has an adhesive portion having adhesiveness.

3. A space debris removal system according to claim 1 or 2.

4. The projectile has a surface portion that can be expanded into a surface shape.

3. A space debris removal system according to claim 1 or 2.

5. A voltage application control means for controlling application of a voltage to the coil; an injection detection means for detecting that the injection object has been injected; Equipped with the voltage application control means controls to stop the application of voltage when the ejection detection means detects that the ejection object has been ejected; 3. A space debris removal system according to claim 1 or 2.

6. An image acquisition means for acquiring an image of outer space; A distance determination means for determining the distance between the space debris removal device and the space debris by using a laser beam; a position identification means for identifying information regarding the position of the space debris based on the image of outer space acquired by the image acquisition means and the distance between the space debris removal device and the space debris identified by the distance identification means; Equipped with 3. A space debris removal system according to claim 1 or 2.

7. A method for removing space debris by ejecting a projectile, comprising: An injection step for injecting a projectile having The ejection step ejects the projectile by utilizing a magnetic field generated by passing a current through a coil. How to remove space debris.

8. A space debris removal device that removes space debris by ejecting a projectile, The ejection section ejects the projectile. Equipped with The projection unit projects the projectile by utilizing a magnetic field generated by passing a current through a coil. Space debris removal equipment.

9. A projectile for use in a space debris removal device that removes space debris by ejecting the projectile, Adhesive part with adhesive properties Equipped with projectile.

10. A projectile for use in a space debris removal device that removes space debris by ejecting the projectile, A surface part that can be expanded into a surface Equipped with projectile.

Images