DEBRIS REMOVAL SYSTEM AND DEBRIS REMOVAL METHOD

Abstract

Provided is a system capable of eliminating complex functions and high-precision control which are necessary when a service satellite approaches space debris to remove the debris. A system 1 is for removing space debris C existing in outer space, and comprises a first spacecraft S and a second spacecraft R that are configured to move in outer space, and a cooperative interface M that is attached to a surface of the space debris C by the first spacecraft S. The second spacecraft R is configured to approach the space debris C using the cooperative interface M, capture the space debris C, and enter the atmosphere together with the space debris C, or release the space debris C at low altitude.

Description

[Technical field]

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

[0002] In recent years, a technology has been proposed for a servicing satellite that is configured to provide a service of approaching and capturing space debris that does not have an interface such as a marker, and then entering the atmosphere together with the space debris to remove it (see, for example, Patent Document 1). Such a servicing satellite is equipped with advanced sensing functions and relative position and attitude control functions required for approaching and connecting to objects whose shapes, thermo-optical properties, etc. are unknown. [Prior art documents] [Patent documents]

[0003] [Patent Document 1] JP 2015-174647 A Summary of the Invention [Problem to be solved by the invention]

[0004] However, such servicing satellites have the following problems: The sensing functions and position and attitude control functions required to approach and remove space debris are often complicated, and it is difficult to perform sensing and position and attitude control with high accuracy.

[0005] The present invention has been made in consideration of the above circumstances, and aims to provide a system that can eliminate the complex functions and high-precision control required when a servicing satellite approaches space debris to remove the debris. [Means for solving the problem]

[0006] In order to achieve the above-mentioned object, the first debris removal system of the present invention is a system for removing space debris present in outer space, comprising first and second spacecraft configured to move in outer space, and a cooperative interface attached to a surface of the space debris by the first spacecraft, and the second spacecraft is configured to approach the space debris using the cooperative interface to capture the space debris and enter the atmosphere together with the space debris.

[0007] A second debris removal system according to the present invention is a system for removing space debris present in outer space, comprising first and second spacecraft configured to move in outer space, and a cooperative interface attached to a surface of the space debris by the first spacecraft, the second spacecraft configured to use the cooperative interface to approach the space debris, capture the space debris, and release the space debris at a low altitude.

[0008] In addition, a first debris removal method according to the present invention is a method for removing space debris present in outer space, and includes an attachment step of attaching a cooperative interface to a surface of the space debris by a first spacecraft configured to move in outer space, a capture step of bringing a second spacecraft close to the space debris using the cooperative interface and capturing the space debris with the second spacecraft, and a re-entry step of re-entering the atmosphere together with the space debris.

[0009] A second debris removal method according to the present invention is a method for removing space debris present in outer space, and includes an attachment step of attaching a cooperative interface to a surface of the space debris by a first spacecraft configured to move in outer space, a capture step of bringing a second spacecraft close to the space debris using the cooperative interface and capturing the space debris with the second spacecraft, and a release step of releasing the space debris captured in the capture step at a low altitude.

[0010] When such a configuration and method are adopted, the cooperative interface can be attached to the surface of the space debris by a first spacecraft configured to move in space. Therefore, a second spacecraft (e.g., a servicing satellite) can easily approach the space debris using the cooperative interface, capture the space debris, and enter the atmosphere together with the space debris (or release the space debris at a low altitude) to remove the debris. This makes it possible to omit complex functions and highly accurate control required when the second spacecraft approaches the space debris for debris removal, and facilitates the debris removal work. As a result, the cost required for debris removal can be reduced, and the debris removal service can be provided more safely. In addition, various design margins required for ensuring safety can be kept to a minimum, so that the cost required for debris removal can also be reduced.

[0011] In the debris removal system according to the present invention, a plate-like body having an optical marker configured to reflect light can be used as the cooperative interface. In such a case, the surface of the plate-like body is provided with an adhesive force, a gripping part for gripping the plate-like body is provided on the first spacecraft, and the surface of the plate-like body gripped by the gripping part is pressed against the surface of the space debris, so that the surface of the plate-like body is attached to the space debris by adhering to the surface of the space debris. The surface of the plate-like body can be provided with an adhesive force by utilizing Adhesive Textile, Gecko, Velcro, and / or cold welding.

[0012] In addition, in the debris removal system according to the present invention, the first spacecraft may be provided with an application unit that applies an approach marker as a cooperative interface to the surface of the space debris.

[0013] In addition, the debris removal system according to the present invention may employ a first spacecraft having a robot arm and a gripping mechanism provided at the tip of the robot arm, the gripping mechanism being configured to be attached to the cooperative interface, to grip space debris, and to be detached from the robot arm together with the cooperative interface.

[0014] By adopting such a configuration, the cooperative interface can be attached to a gripping mechanism of a robotic arm of a spacecraft configured to move in outer space, the space debris can be gripped by the gripping mechanism, and the gripping mechanism together with the cooperative interface can be detached from the robotic arm, thereby integrating the cooperative interface with the space debris. Effect of the Invention

[0015] According to the present invention, it is possible to provide a system that can eliminate the complex functions and high-precision control required when a servicing satellite approaches space debris to remove the debris. [Brief description of the drawings]

[0016] [Figure 1] 1 is a diagram showing an overview of a debris removal system according to a first embodiment of the present invention. FIG. [Diagram 2] FIG. 2 is a diagram showing another application example (an embodiment in which a single spacecraft processes a plurality of space debris) of the debris removal system according to the first embodiment of the present invention. [Diagram 3] 1 shows an overview of a debris removal system for a second embodiment of the present invention, in which (A) is a diagram showing the state in which space debris is being grasped by the grasping mechanism of the robot arm of a first spacecraft, and (B) is a diagram showing the state in which the grasping mechanism of the first spacecraft has been detached from the robot arm. DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

[0017] Hereinafter, embodiments of the present invention will be described with reference to the drawings.

[0018] First, the configuration of a debris removal system (hereinafter referred to as "this system") 1 according to a first embodiment of the present invention will be described with reference to Figure 1. This system 1 is a system for removing space debris C present in outer space, and includes a first spacecraft S and a second spacecraft R configured to move in outer space, and a cooperative interface M attached to the surface of the space debris C by the first spacecraft S.

[0019] In this embodiment, a plate-like body having an optical marker is adopted as the cooperative interface M. The optical marker is attached to one surface of the plate-like body and is configured to reflect light. The optical marker may have, for example, a retroreflective material that can make the light emission direction coincide with the light incidence direction. When a heat insulating film is formed on the surface to which the optical marker is attached, an optical marker that reflects light in a predetermined wavelength range (for example, near-ultraviolet light having a wavelength range of 300 to 400 nm) that is absorbed by the heat insulating film may also be adopted. In addition, the other surface of the plate-like body in this embodiment is provided with an adhesive force by utilizing Adhesive Textile, Gecko, Velcro, and / or Coldwelding.

[0020] The first spacecraft S in this embodiment has a gripping unit (such as a robot arm) that grips a plate-like body as a cooperative interface M. By gripping the plate-like body with the gripping unit of the spacecraft S and pressing a surface of the plate-like body (a surface having an adhesive force on the side opposite to the optical marker) against the surface of the space debris C, the surface of the plate-like body can be attached to the space debris C by adsorbing the surface of the plate-like body to the surface of the space debris C.

[0021] The second spacecraft R in this embodiment is a so-called service satellite, and is configured to approach the space debris C using the cooperative interface M, capture the space debris C, and enter the atmosphere together with the space debris C. Note that instead of (or in addition to) the function of entering the atmosphere together with the space debris C, the second spacecraft R may be configured to transfer to a low altitude (an altitude significantly lower than the ISS altitude, for example, about 350 km) together with the space debris C and release the space debris C at the low altitude. The configuration of the second spacecraft R may be any configuration that can perform the above function, and is not particularly limited.

[0022] A method for removing space debris C using this system 1 (debris removal method) includes a step (attachment step) of attaching a cooperative interface M to the surface of the space debris C by a first spacecraft S configured to move in outer space, a step (capture step) of bringing a second spacecraft R close to the space debris C using the cooperative interface M and capturing the space debris C with the second spacecraft R, and a step (re-entry step) of making the second spacecraft R enter the atmosphere together with the space debris C. Note that instead of the re-entry step, a release step can be adopted in which the space debris C captured in the capture step is released at a low altitude.

[0023] In the attachment process of the method according to this embodiment, for example, as already described, a plate-shaped body serving as a cooperative interface M is grasped by the gripping portion of the spacecraft S, and the surface of the plate-shaped body (the surface having adhesive force opposite the optical marker) is pressed against the surface of the space debris C, thereby adsorbing the surface of the plate-shaped body to the surface of the space debris C and attaching the plate-shaped body to the space debris C.

[0024] In the debris removal system 1 according to the above embodiment, the cooperative interface M can be attached to the surface of the space debris C by the first spacecraft S configured to move in space. Therefore, the second spacecraft R can easily approach the space debris C using the cooperative interface M, capture the space debris C, and enter the atmosphere together with the space debris C (or release the space debris C at a low altitude) to remove the debris. This makes it possible to omit complex functions and highly accurate control required when the second spacecraft R approaches the space debris C for debris removal, and facilitates the debris removal work. As a result, the cost required for debris removal can be reduced, and the debris removal service can be provided more safely. In addition, various design margins required for ensuring safety can be kept to a minimum, so that the cost required for debris removal can also be reduced.

[0025] The configurations of the first spacecraft and the cooperative interface are not limited to those described in this embodiment. For example, an approach marker applied to the surface of the space debris C may be used as the cooperative interface, and the first spacecraft may have an application unit that applies the approach marker to the surface of the space debris C.

[0026] In addition, in the embodiment of Figure 1, an example is shown in which a single first spacecraft S is used to attach a cooperative interface M to a "single" space debris C and remove the space debris C, but it is also possible to remove "multiple" space debris C using a single first spacecraft S.

[0027] That is, as shown in Fig. 2, a single Servicer (first spacecraft S) traveling in low Earth orbit at an altitude of, for example, 400 km is brought close to Target-A (first space debris C) in an orbit at an altitude of, for example, 800 km, and a cooperative interface M is attached to Target-A. Then, it is brought close to Target-B (second space debris C) in a different orbit or in the same orbit, and a cooperative interface M is attached to Target-B. Then, it is brought close again to Target-C (third space debris C) in a different orbit or in the same orbit, and a cooperative interface M is attached to Target-C.

[0028] In this way, the "multiple" space debris C (Target-A, Target-B, Target-C) to which the cooperative interface M is attached by a single first spacecraft S (Servicer) can be processed by separate or the same service satellite (second spacecraft R). For example, as shown in FIG. 2, a "multiple" debris removal service satellite (second spacecraft R) can approach each of the "multiple" space debris C using the cooperative interface M. Then, these service satellites (second spacecraft R) can capture each of the "multiple" space debris C, re-enter the atmosphere together with the "multiple" space debris C (or release the space debris C at a low altitude), and perform debris removal.

[0029] Second Embodiment Next, the configuration of a debris removal system 1A according to a second embodiment of the present invention will be described with reference to Fig. 3. As with the first embodiment, this system 1A is a system for removing space debris C present in outer space, and includes a first spacecraft S and a second spacecraft R configured to move through outer space, and a cooperative interface M attached to the surface of the space debris C by the first spacecraft S. Note that since the second spacecraft R in this embodiment is substantially the same as that in the first embodiment, illustration and detailed description thereof will be omitted.

[0030] The first spacecraft S in this embodiment has a robot arm SA and a gripping mechanism SG provided at the tip of the robot arm SA. The gripping mechanism SG is configured so that a cooperative interface M can be attached, so that the gripping mechanism SG grips space debris C, and so that the gripping mechanism SG can be detached from the robot arm SA together with the cooperative interface M. The configuration of the gripping mechanism SG is not particularly limited as long as it can perform the above functions.

[0031] In addition, various devices such as a docking interface, an angular velocity detumbling device, a drag sail device, and an orbital descent tether device can be attached to the gripping mechanism SG together with the cooperative interface M. In this way, the device and the space debris C can be integrated by gripping the space debris C with the gripping mechanism SG and detaching the gripping mechanism SG together with the device from the robot arm SA.

[0032] A method for removing space debris C using this system 1A (debris removal method) includes a step (attachment step) of attaching a cooperative interface M to the surface of the space debris C by a first spacecraft S configured to move in outer space, a step (capture step) of bringing a second spacecraft R close to the space debris C using the cooperative interface M and capturing the space debris C with the second spacecraft R, and a step (re-entry step) of making the second spacecraft R enter the atmosphere together with the space debris C. As in the first embodiment, instead of the re-entry step, a release step can be adopted in which the space debris C captured in the capture step is released at a low altitude.

[0033] In this embodiment, the cooperative interface M can be attached to the gripping mechanism SG of the robot arm SA of the spacecraft S, the space debris C is gripped by the gripping mechanism SG, and the gripping mechanism SG is detached from the robot arm SA together with the cooperative interface M, thereby attaching the cooperative interface M to the space debris C.

[0034] The debris removal system 1A according to the above embodiment can also provide the same advantageous effects as those of the first embodiment.

[0035] The present invention is not limited to the above-described embodiments, and those in which a person skilled in the art makes appropriate design changes to these embodiments are also included within the scope of the present invention as long as they include the features of the present invention. In other words, the elements of the above-described embodiments and their arrangements, materials, conditions, shapes, sizes, etc. are not limited to those exemplified, and can be modified as appropriate. In addition, the elements of the above-described embodiments can be combined to the extent technically possible, and combinations of these are also included within the scope of the present invention as long as they include the features of the present invention. [Explanation of symbols]

[0036] 1·1A…Debris Removal System C…Space debris M…Cooperative interface S...First spacecraft SA…Robot arm SG…Gripping mechanism R...Second spacecraft

Claims

1. A debris removal system for removing space debris present in outer space, first and second spacecraft configured to travel in space; a cooperative interface attached to a surface of the space debris by the first spacecraft; A debris removal system, wherein the second spacecraft is configured to utilize the cooperative interface to approach the space debris, capture the space debris, and reenter the atmosphere together with the space debris.

2. A debris removal system for removing space debris present in outer space, first and second spacecraft configured to travel in space; a cooperative interface attached to a surface of the space debris by the first spacecraft; A debris removal system, wherein the second spacecraft is configured to utilize the cooperative interface to approach the space debris, capture the space debris, and release the space debris at a low altitude.

3. The debris removal system according to claim 1 or 2, wherein the cooperative interface is a plate having optical markers configured to reflect light.

4. The surface of the plate-like body has an adhesive force, the first spacecraft has a gripping portion that grips the plate-like body, The debris removal system described in claim 3, wherein the surface of the plate-shaped body held by the holding portion is pressed against the surface of the space debris, so that the surface of the plate-shaped body is adsorbed to the surface of the space debris, thereby attaching the plate-shaped body to the space debris.

5. The debris removal system according to claim 4 , wherein the surface of the plate-like body is provided with the adhesive force by utilizing Adhesive Textile, Gecko, Velcro, and / or Coldwelding.

6. The debris removal system according to claim 1 or 2, wherein the first spacecraft has an application unit that applies an approach marker as the cooperative interface to the surface of the space debris.

7. the first spacecraft has a robot arm and a gripping mechanism provided at a tip of the robot arm; The collaborative objectification system of claim 1 or 2, wherein the gripping mechanism is configured to have the collaborative interface attached to it, to grip the space debris, and to be detached from the robot arm together with the collaborative interface.

8. A method for removing space debris in outer space, comprising: attaching a cooperative interface to a surface of the space debris by a first spacecraft configured to move in space; a capture step of bringing a second spacecraft close to the space debris using the cooperative interface and capturing the space debris with the second spacecraft; a re-entry step of re-entering the second spacecraft together with the space debris into the atmosphere; A debris removal method comprising:

9. A method for removing space debris in outer space, comprising: attaching a cooperative interface to a surface of the space debris by a first spacecraft configured to move in space; a capture step of bringing a second spacecraft close to the space debris using the cooperative interface and capturing the space debris with the second spacecraft; a release step of releasing the space debris captured in the capture step at a low altitude; A debris removal method comprising:

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