JP2021126908A - Space debris removal apparatus - Google Patents

Abstract

To provide a space debris removal apparatus having a charging type film member which increases resistance.SOLUTION: A space debris removal apparatus 1 is mounted on a space debris 2 orbiting around the Earth and changes an orbit of the space debris 2 by reducing the orbital speed of the space debris 2. The space debris removal apparatus 1 includes: a film member 20 which has a first surface 21a facing the space debris 2 and a second surface 22a that is a surface opposite to the first surface 21a, and has such a configuration as to charge the first surface 21a and the second surface 22a to different potentials; a charging device 30 which is electrically connected to the film member 20 and charges the film member 20 so that the first surface 21a is charged to a negative potential lower than the second surface 22a by a predetermined potential difference; and a mounting device 40 for fitting the film member 20 to the space debris 2.SELECTED DRAWING: Figure 1

Description

The present invention relates to a space debris removing device.

Space debris (space debris) such as used rockets at the time of launching an artificial satellite is steadily increasing, and the space debris currently existing in orbit is expected to exceed 100 million with 1 mm or more. .. When such space debris collide with each other, hundreds or thousands of new smaller space debris are generated, and the space debris grows exponentially. Therefore, urgent measures are required to remove space debris.

Patent Document 1 discloses a space debris removing device. This space debris removing device includes a drag force increasing device made of a circular or polygonal membrane member or a gas pressure-fillable balloon or air mat-like structure. This space debris removing device is attached to the space debris and receives a small amount of atmospheric and solar radiation pressure by the drag increasing device to change the trajectory of the space debris. In this way, space debris is separated from the important satellite orbits that should be protected.

Japanese Unexamined Patent Publication No. 2010-285137

However, since the atmospheric density decreases remarkably as the orbital altitude increases, the drag force obtained from the atmosphere decreases as the orbital altitude increases in the space debris removing device of Patent Document 1. It has been confirmed that the atmospheric density decreases to about 1/50 to 1/100 at an altitude of about 1000 km as compared with, for example, an altitude of 400 km to 600 km. Therefore, the space debris removing device of Patent Document 1 may not be able to obtain sufficient execution ability in the region of orbital altitude where the atmospheric density is not sufficient.

In the above-mentioned region of orbital altitude where the atmospheric density is not sufficient, it is composed of an electrically neutral gas and an ionized gas (ion and electron) partly ionized by solar ultraviolet rays. Therefore, when the change in atmospheric density is confirmed in detail, the density of the neutral atmosphere decreases remarkably as the altitude increases as described above, but the decrease in ion density is less than this. In other words, in regions of orbital altitude where the atmospheric density is not sufficient, it may be more effective to receive drag from ions than to receive drag from the neutral atmosphere. For that purpose, for example, the membrane member of Patent Document 1 is charged to form a sheath (an electrically non-neutral space charge layer having a potential gradient) around the membrane surface, and the collected ions are electrostatically charged in the sheath. As a result of the acceleration, it is considered that the resistance force from the ion can be increased.

However, even in the method of charging the membrane member of Patent Document 1, if the absolute value of the voltage applied to the membrane member increases, the drag force may not be increased. Specifically, when the absolute value of the applied voltage to the membrane member increases, a sheath (an electrically non-neutral space charge layer having a potential gradient) is formed isotropically around the membrane member, and the orbit of the membrane surface. In the flow field of ions flowing at the equivalent of the motion velocity, ion collection can occur on both sides of the membrane member facing the upstream side and the downstream side. That is, there is a possibility that the ions wrap around to the downstream side surface of the membrane member. As a result, the momentum exchange between the ions and the membrane surface cancels out on the upstream side surface and the downstream side surface, and sufficient drag cannot be obtained from the ions in the traveling direction of the membrane surface, making it practically difficult to increase the drag. There is a risk of becoming.

An object of the present invention is to increase drag in a space debris removing device having a charged film member.

The first aspect of the present invention is
A space debris removal device that is attached to space debris that orbits the earth and changes the orbit of the space debris by reducing the orbital speed of the space debris.
A film having a first surface facing the space debris and a second surface opposite to the first surface, and having a structure capable of charging the first surface and the second surface to different potentials. Members and
A charging device that is electrically connected to the membrane member and charges the membrane member so that the first surface has a negative potential that is lower than that of the second surface by a predetermined potential difference.
Provided is a space debris removing device including an attachment device for attaching the film member to the space debris.

According to this configuration, since the potential difference is provided between the first surface and the second surface of the film member, it is possible to prevent the sheath from being isotropically formed around the film member. At this time, the first surface facing the space debris is the surface on the upstream side of the ion flow (the surface on the pressure receiving side), and the second surface is the surface on the downstream side of the ion flow. Therefore, the sheath on the first surface on the upstream side of the ion flow expands, positive ions (hereinafter, also simply referred to as ions) can be efficiently collected on the first surface, and the sheath on the second surface shrinks. However, the wraparound of ions to the second surface is suppressed. As a result, it is possible to suppress the momentum exchange of ions with respect to the membrane member from canceling each other on the upstream side (first surface side) and the downstream side (second surface side) of the ion flow, and it is possible to obtain sufficient drag from the ions. can. Further, in the above configuration, since the charging device is mounted on the space debris removing device, the above-mentioned drag force increasing function can be achieved by the space debris removing device alone without the need to supply power from the outside. Here, the charging device may be, for example, simply a power source or an ion source.

A second aspect of the present invention is
A space debris removal device that is attached to space debris that orbits the earth and changes the orbit of the space debris by reducing the orbital speed of the space debris.
It has a first surface facing the space debris and a second surface opposite to the first surface, and when power is supplied, the first surface is lower than the second surface by a predetermined potential difference. A film member that is charged so as to have a negative potential,
Provided is a space debris removing device including an attachment device for attaching the film member to the space debris.

According to this configuration, since the potential difference is provided between the first surface and the second surface of the film member, it is possible to prevent the sheath from being isotropically formed around the film member. At this time, the first surface facing the space debris is the surface on the upstream side of the ion flow (the surface on the pressure receiving side), and the second surface is the surface on the downstream side of the ion flow. Therefore, the sheath on the first surface on the upstream side of the ion flow expands, positive ions (hereinafter, also simply referred to as ions) can be efficiently collected on the first surface, and the sheath on the second surface shrinks. However, the wraparound of ions to the second surface is suppressed. As a result, it is possible to suppress the momentum exchange of ions with respect to the membrane member from canceling each other on the upstream side (first surface side) and the downstream side (second surface side) of the ion flow, and it is possible to obtain sufficient drag from the ions. can. Further, in the above configuration, since the space debris removing device is not equipped with the charging device, the number of parts can be reduced as compared with the first aspect.

A satellite body mechanically connected to the membrane member and the mounting device and having a propulsion function is further provided.
The attachment device has a predetermined length and may include a capture mechanism for capturing the space debris.

According to this configuration, space debris that already exists in outer space can be positively removed. It is said that there are two types of methods for removing space debris. The first method is PMD (Post Mission Disposal), which is a self-removal of satellites and rockets that have been discontinued from their orbits. The second method is ADR (Active Debris Removal), which removes space debris that already exists in the orbit around the earth. The former PMD needs to be equipped with the space debris removing device in advance before launching a satellite or a rocket, and the space debris removing device is deployed when the operation of the space debris removing device is completed. However, the latter ADR does not need to be equipped with the above space debris removal device in advance before launching the satellite or rocket, and actively captures the debris of the satellite or rocket that became space debris at the end of their operation. Can be removed. Here, the above-mentioned predetermined length is a length capable of exerting a sufficient ion collecting ability, and differs depending on the size of space debris. Behind the large space debris, a space (ion wake) is created in which the closer to the space debris, the lower the proportion of ions whose thermal velocity is relatively slow with respect to the orbital speed of the space debris. When the membrane member is located in this ion wake region, the ion collecting ability of the membrane member is reduced. Therefore, in order to avoid the film member from being located in the ion wake region, it is necessary to separate the film member from the space debris by a certain amount or more. Therefore, the mounting device needs to have a predetermined length. For example, the upper part of the rocket has a diameter of about 2 m to 4 m, an orbital velocity of about 700-1000 km at an altitude of about 7.5 km / s, and a thermal velocity of oxygen ions having a large momentum among the ions is about 1.1 km / s. Therefore, the predetermined length is assumed to be at least 10 to 20 m, preferably about 30 m.

The membrane member is
A first conductor made of a conductive material constituting the first surface and
A second conductor made of a conductive material constituting the second surface, and
A third conductor made of a conductive material arranged between the first conductor and the second conductor,
A first non-conductor made of an insulator material or a dielectric material arranged between the first conductor and the third conductor,
A second non-conductor made of an insulator material or a dielectric material arranged between the second conductor and the third conductor may be provided.

According to this configuration, the film member is composed of a five-layer structure, and a predetermined potential difference can be specifically provided with respect to the first surface and the second surface. In particular, by arranging the third conductor in the center, the potential difference from the third conductor can be accurately given to the first conductor and the second conductor, respectively.

The membrane member is
A first conductor made of a conductive material constituting the first surface and
A second conductor made of a conductive material constituting the second surface, and
A non-conductor made of an insulator material or a dielectric material arranged between the first conductor and the second conductor may be provided.

According to this configuration, the film member is composed of a three-layer structure, and a predetermined potential difference can be specifically provided with respect to the first surface and the second surface. Generally, it is assumed that the membrane member is stored in a folded state until it is deployed in outer space. Therefore, as the number of film members increases, the number of members and electrical connections and wiring increases, which makes it difficult to store the film members and may make it difficult to handle them in order to prevent problems with the connections and wiring. Therefore, by forming the film member into three layers, the structure can be simplified and the handling can be facilitated.

The predetermined potential difference may be 10V to 1000V. However, it is desirable that the potential of the first surface is set to −10 V or less (larger on the negative side).

According to this configuration, it is possible to prevent the sheath from being formed isotropically around the membrane member, and it is possible to form a sheath capable of efficiently collecting ions on the first surface. In addition, the ions can be sufficiently electrostatically accelerated and accelerated in the sheath. In other words, with a potential difference of less than 10V, it is not possible to form a sheath large enough to efficiently collect ions on the first surface, and the potential on the first surface is set to be greater than -10V (smaller on the negative side). If so, the ions are electrostatically accelerated in the sheath, but the acceleration is not sufficient. If the potential difference is 1000 V or more, the power consumption due to the electron or ion current flowing into the film surface becomes large, and this system may become inefficient from the viewpoint of power consumption.

According to the present invention, in a space debris removing device having a charged type film member, the film member is charged to a plurality of potentials, so that the drag force can be increased.

The schematic block diagram of the space debris removal apparatus which concerns on 1st Embodiment of this invention. FIG. 3 is a cross-sectional view of a part of the membrane member according to the first embodiment. The schematic diagram which shows the sheath around the single potential type membrane member different from 1st Embodiment. The schematic diagram which shows the sheath around the multi-potential type membrane member in 1st Embodiment. FIG. 2 is a cross-sectional view of a part of the membrane member in the modified example of FIG. FIG. 5 is a cross-sectional view of a part of the membrane member in the modified example of FIG. The schematic block diagram of the space debris removal apparatus which shows the modification of the film member of FIG. The front view of the membrane member which shows the modification of the charging device of FIG. The schematic block diagram of the space debris removal apparatus which concerns on 2nd Embodiment.

Hereinafter, embodiments of the present invention will be described with reference to the accompanying drawings.

(First Embodiment)
FIG. 1 is a schematic configuration diagram of the space debris removing device 1 according to the first embodiment of the present invention. The space debris removing device 1 of the present embodiment is attached to the space debris 2 orbiting the earth, and changes the orbit of the space debris 2 by reducing the orbiting speed of the space debris 2. As a result, the space debris 2 is dropped to the ground to protect important orbits used for artificial satellites and the like.

In FIG. 1, the traveling direction of the space debris 2 is indicated by an arrow A1. Seen from the space debris removing device 1, the ion flow is relatively flowing in the direction opposite to the arrow A1. Further, a part of the space debris removing device 1 shown by the broken line circle is shown in an enlarged manner.

The space debris removing device 1 of the present embodiment includes a satellite main body 10, a film member 20, a charging device 30, and a mounting device 40.

The satellite body 10 is mechanically connected to the membrane member 20 and the attachment device 40 and has a propulsion function. Although not shown in detail, the propulsion function can be achieved by a known mechanism such as an ion engine.

The film member 20 has a substantially hemispherical shell shape or an umbrella shape having a convex shape toward the space debris 2. As will be described later, the membrane member 20 receives a drag force from the ion flow to reduce the orbiting speed of the space debris 2.

FIG. 2 is a cross-sectional view of a part of the film member 20. The film member 20 has a structure capable of charging a plurality of potentials as described below. The film member 20 has a first surface 21a facing the space debris 2 and a second surface 22a opposite to the first surface 21a. The first surface 21a and the second surface 22a have a structure capable of being charged at different potentials. Specifically, the film member 20 includes a first conductor 21 made of a conductive material forming the first surface 21a, a second conductor 22 made of a conductive material forming the second surface 22a, and a first conductor. A third conductor 23 made of a conductive material is provided between the conductor 21 and the second conductor 22. Further, the film member 20 includes a first non-conductor 24 made of an insulator material or a dielectric material arranged between the first conductor 21 and the third conductor 23, and the second conductor 22 and the third conductor 23. It includes a second non-conductor 25 made of an insulating material or a dielectric material arranged between them. In the present embodiment, both the first non-conductor 24 and the second non-conductor 25 are made of polyimide.

The charging device 30 includes a power supply 31. The power supply 31 is electrically connected to the film member 20. Specifically, the negative electrode of the power supply 31 is electrically connected to the first conductor 21, and the positive electrode of the power supply 31 is electrically connected to the second conductor 22. The third conductor 23 is connected to the grounding portion 10, which indicates that the third conductor 23 is electrically connected to the satellite body 10. Therefore, here, the grounding portion 10 and the satellite main body 10 are indicated by the same reference numerals. In outer space, the potential of the satellite body 10 is not necessarily zero, and the potential of the satellite body 10 fluctuates depending on the surrounding environment of the satellite body 10. Therefore, the potential of the grounding portion 10 indicates the so-called spacecraft potential at the position where the satellite body 10 exists. In the present embodiment, the charging device 30 charges the first surface 21a to a negative potential that is lower than that of the second surface 22a by a predetermined potential difference. The spacecraft potential here is considered to be the reference potential of the spacecraft (satellite body 10) in outer space.

Alternatively, the power supply 31 may be replaced by an ion source. By emitting positive and / or negative ions into outer space, the ion source can change its reference potential from the initial state to the opposite potential to the charge of the emitted ions. According to this principle, the membrane member 20 connected to the reference potential of the ion source can be charged to a plurality of potentials as described above. In this case, at least one of the ion sources replaced with the power supply 31 needs to be electrically floating with the grounding portion 10. Here, the charging mode of the membrane member 20 by the ion source as described above is also included in the electrical connection. Further, when an ion source is used, the reaction force for releasing ions can be utilized as a propulsive force for approaching the space debris 2 or a drag force for decelerating the space debris 2.

The predetermined potential difference between the first conductor 21 (first surface 21a) and the second conductor 22 (second surface 22a) is preferably set to 10V to 1000V, more preferably 100V to 1000V. Is set. Further, preferably, the potential of the first conductor 21 (first surface 21a) is set to −10 V or less (larger on the negative side), and more preferably set to −100 V or less (larger on the negative side). The potential of −10 V or less or −100 V or less here is a potential based on the spacecraft potential. According to the potential difference and the potential, it is possible to suppress the isotropic formation of the sheath around the membrane member 20, and it is possible to form a sheath capable of efficiently collecting ions on the first surface 21a. In addition, the ions can be sufficiently electrostatically accelerated and accelerated in the sheath. In other words, with a potential difference of less than 10V, it is not possible to form a sheath large enough to efficiently collect ions on the first surface 21a, and the potential on the first surface is greater than -10V (smaller on the negative side). When set, the ions electrostatically accelerate in the sheath, but the acceleration is not sufficient. If the potential difference is 1000 V or more, the power consumption due to the electron or ion current flowing into the film surface becomes large, and this system may become inefficient from the viewpoint of power consumption.

With reference to FIG. 1, the attachment device 40 has a predetermined length and has a capture mechanism 41 for capturing the space debris 2.

The capture mechanism 41 includes a harpoon 41a to be driven into the space debris 2, an injection device 41b to eject the harpoon 41a to drive into the space debris 2, and a tether 41c connecting the harpoon 41a and the injection device 41b. Such a capture mechanism 41 is peculiar to ADR (Active Debris Removal).

The space debris removing device 1 having the above configuration approaches the space debris 2 by the propulsion function of the satellite main body 10, ejects a harpoon 41a with a tether 41c from the injection device 41b, and drives the harpoon 41a into the space debris 2 to capture the space debris 2. do. Next, the membrane member 20 is unfolded and the orbit of the space debris 2 is changed by reducing the orbital speed of the space debris 2. Therefore, it can be said that the space debris removing device 1 of the present embodiment is compatible with ADR.

Behind the large space debris 2, there is a space (ion wake) in which the proportion of ions whose thermal velocity is relatively slow with respect to the orbital speed of the space debris decreases as the space debris 2 approaches. If the membrane member 20 is located in this ion wake region, the ion collecting ability of the membrane member 20 may decrease. Therefore, the tether 41c needs to have a predetermined length in order to prevent the membrane member 20 from being located in the region of the ion wake. For example, as space debris 2, the upper stage of a rocket that has finished operation is assumed. In that case, the upper part of the rocket has a diameter of about 2 m to 4 m, an orbital velocity of about 700-1000 km at an altitude of about 7.5 km / s, and a thermal velocity of oxygen ions having a large momentum among the ions is about 1.1 km / s. Therefore, the predetermined length is assumed to be at least 10 to 20 m, preferably about 30 m.

In the present embodiment, an example in which the capture mechanism 41 includes the harpoon 41a is shown, but the capture mode of the capture mechanism 41 is not limited to the one using the harpoon 41a. Alternatively, other aspects of the capture device, such as a robot arm, may be used.

The difference between the single-potential type film member 200 and the multi-potential type film member 20 will be described with reference to FIGS. 3 and 4. For the sake of simplicity, the shape of the film member 20 is a flat plate.

FIG. 3 shows the shape of the sheath Sm when a single-potential type film member 200 different from the present embodiment is used. FIG. 4 shows the shape of the sheath Sm when the same multi-potential type film member 20 as in the present embodiment is used. Sheath Sm in FIGS. 3 and 4 shows a region for collecting ions.

First, with reference to FIG. 3, in the single-potential type membrane member 200, the sheath Sm is formed isotropically (generally spherical) around the membrane member 200. In such an isotropic sheath Sm, ions are collected not only on the first surface 210 facing the space debris 2 but also on the second surface 220 opposite to the first surface 210. As a result, wraparound of the ion flow A2 occurs, and the momentum exchange of the ions cancels out on the upstream side (first surface 21a side) and the downstream side (second surface 22a side) of the ion flow A2, which is sufficient from the ions. There is a risk that drag will not be obtained.

Next, referring to FIG. 4, in the multi-potential type membrane member 20, a sheath Sm (in this case, an ion sheath) that effectively contributes to ion collection is formed only on the first surface 21a side. In other words, the sheath on the second surface 22a is significantly reduced from the state shown in FIG. 3 and does not effectively contribute to ion collection when the potential of the second surface 22a is equal to the spatial potential. Therefore, it is possible to suppress the exchange of ion momentum on the upstream side (first surface 21a side) and the downstream side (second surface 22a side) of the ion flow A2, and the ions are collected only on the first surface 21a. However, the drag force can be received only on the first surface 21a. In addition, in FIG. 4, the region Sp (in this case, the electron sheath) based on the positive potential of the second surface 22a is also shown by the broken line. In the region Sp, the collection of ions is suppressed, that is, the wraparound of the ion flow A2 is suppressed.

According to the space debris removing device 1 of the present embodiment, since the potential difference is provided between the first surface 21a and the second surface 22a of the film member 20, the sheath is isotropically around the film member 20. It can be suppressed from being formed. At this time, the first surface 21a facing the space debris 2 is the surface on the upstream side of the ion flow (the surface on the pressure receiving side), and the second surface 22a is the surface on the downstream side of the ion flow. Therefore, the sheath on the first surface 21a on the upstream side of the ion flow expands, the ions can be efficiently collected on the first surface, and the sheath on the second surface 22a shrinks, so that the second surface of the ions The wraparound to 22a is suppressed. Further, in the sheath on the first surface 21a, ions are greatly accelerated by electrostatic acceleration and contribute to an increase in drag (see ion flow A2 in FIG. 4). In this embodiment, not only the sheath Sm is reduced on the second surface 22a, but also a region Sp based on a positive potential is formed. As a result, it is possible to prevent the momentum exchange of ions with respect to the membrane member 20 from canceling each other on the upstream side (first surface 21a side) and the downstream side (second surface 22a side) of the ion flow, and sufficient drag from the ions can be obtained. Obtainable. Further, in the above configuration, since the charging device 30 is mounted on the space debris removing device 1, the above-mentioned drag force increasing function can be achieved by the space debris removing device 1 alone without the need to supply power from the outside.

Further, since the film member 20 is composed of a five-layer structure, a predetermined potential difference can be specifically provided with respect to the first surface 21a and the second surface 22a. In particular, by arranging the third conductor 23 in the center, the potential difference from the third conductor 23 can be accurately given to the first conductor 21 and the second conductor 22.

Various modifications can be considered for the space debris removing device 1 of the present embodiment.

For example, the charging device 30 and the satellite body 10 are not essential configurations for the space debris removing device 1. That is, only the film member 20 and the mounting device 40 may be packaged to form the space debris removing device 1, and the satellite body 10 and the charging device 30 may be used as external devices. In this way, the space debris removing device 1 packaged in the existing satellite can be additionally mounted.

FIG. 5 is a cross-sectional view of a part of the film member 20 in the modified example of FIG.

In the modified example shown in FIG. 5, the film member 20 has a first surface 26a facing the space debris 2 and a second surface 27a opposite to the first surface 26a, as in the above embodiment. There is. The first surface 26a and the second surface 27a have a structure capable of being charged at different potentials. Specifically, the film member 20 includes a first conductor 26 made of a conductive material forming the first surface 26a, a second conductor 27 made of a conductive material forming the second surface 27a, and a first conductor. It includes a non-conductor 28 made of an insulating material or a dielectric material arranged between the conductor 26 and the second conductor 27. In this modification, the non-conductor 28 is made of polyimide.

In the charging device 30, the negative electrode of the power supply 31 is electrically connected to the first conductor 26, and the positive electrode of the power supply 31 is electrically connected to the second conductor 27. In FIG. 5, neither the first conductor 26 nor the second conductor 27 is electrically connected to the grounding portion (satellite main body) 10, but the second conductor 27 is grounded as in another modification shown in FIG. It may be electrically connected to the unit (satellite main body) 10. In either case, the charging device 30 can charge the first surface 26a to a negative potential lower than that of the second surface 27a by a predetermined potential difference. As a result, the film member 20 is charged to a plurality of potentials as in the above embodiment.

FIG. 7 is a schematic configuration diagram of the space debris removing device 1 showing a modified example of the film member 20 of FIG. In FIG. 7, the traveling direction of the space debris 2 is indicated by an arrow A1 as in FIG. Seen from the space debris removing device 1, the ion flow is relatively flowing in the direction opposite to the arrow A1. Further, a part of the space debris removing device 1 shown by the broken line circle is shown in an enlarged manner.

In the modified example shown in FIG. 7, the film member 20 has a flat plate shape. The shape of the film member 20 in the front view (view view facing the space debris 2) can be, for example, a square, a rectangle, another polygon, or a circle. The other structures are the same as those in the above embodiment shown in FIG. As described above, the shape of the film member 20 is not particularly limited.

FIG. 8 is a front view of the film member 20 showing a modification of the charging device 30 of FIG. 7. In the example of FIG. 8, the shape of the film member 20 in front view is square.

In the modification shown in FIG. 8, the charging device 30 includes a solar cell 32. The solar cell 32 is shown by a shaded area and is attached to the four edges 20a to 20d of the film member 20. In other words, the solar cell 32 is not provided in the central portion 20e of the film member 20.

In the modified example shown in FIG. 8, in the film member 20, the portion of the solar cell 32 is not charged, but the central portion 20e excluding the portion of the solar cell 32 is charged.

According to this modification, since the solar cell 32 is used, the useful life of the charging device 30 can be secured for a long time. Further, the charging device 30 can be configured together with the membrane member 20, and the charging device 30 can be housed together with the membrane member 20, so that the handling becomes easy.

(Second Embodiment)
The space debris removing device 1 of the second embodiment shown in FIG. 9 is compatible with PMD (Post Mission Disposal). Except for the configuration described below, the configuration may be substantially the same as the configuration of the ADR-compatible space debris removing device 1 of the first embodiment. Therefore, the same parts as those shown in the first embodiment may be designated by the same reference numerals and the description thereof may be omitted.

Unlike the first embodiment, the space debris removing device 1 of the present embodiment does not have the satellite main body 10 (see FIG. 1) or the capture mechanism 41 (see FIG. 1). In the present embodiment, the mounting device 40 includes a fixture 42 that directly fixes the space debris 2 to the film member 20. Alternatively, the mounting device 40 may include a tether 41c as shown in FIG. 1 and mechanically connect the space debris 2 and the film member 20 via the tether 41c.

The space debris removing device 1 of the present embodiment is mounted on the satellite or rocket in advance before the launch of the satellite or rocket. Then, the space debris removing device 1 is deployed at the end of those operations. Therefore, it is not necessary to capture the debris of the satellite or rocket to be removed in outer space, and reliable removal of the removal target can be expected. The fixture 42 may have a member and a membrane member 20 that can become space debris 2 fixed in advance before the launch of the satellite or rocket, or a member and a membrane member that can become space debris 2 when the operation of the satellite or rocket ends. 20 may be fixed.

Although specific embodiments of the present invention and variations thereof have been described above, the present invention is not limited to the above embodiments, and various modifications can be made within the scope of the present invention.

For example, in the first and second embodiments, the second surfaces 22a and 27a (that is, the second conductors 22 and 27) are formed smaller than the first surfaces 21a and 26a (that is, the first conductors 21 and 26). May be good. Further, slits, notches and the like may be provided in the second surfaces 22a and 27a (that is, the second conductors 22 and 27). These can further suppress the isotropic formation of the sheath.

1 Space debris removal device 2 Space debris 10 Satellite body (grounding part)
20 Membrane member 20a to 20d Edge part 20e Central part 21 First conductor 21a First surface 22 Second conductor 22a Second surface 23 Third conductor 24 First non-conductor 25 Second non-conductor 26 First conductor 26a First Surface 27 Second conductor 27a Second surface 28 Non-conductor 30 Charging device 31 Power supply 32 Solar cell 40 Mounting device 41 Capture mechanism 41a 銛 41b Injection device 41c Tether 42 Fixture 200 Membrane member 210 First surface 220 Second surface

Claims (7)

A space debris removal device that is attached to space debris that orbits the earth and changes the orbit of the space debris by reducing the orbital speed of the space debris.
A film having a first surface facing the space debris and a second surface opposite to the first surface, and having a structure capable of charging the first surface and the second surface to different potentials. Members and
A charging device that is electrically connected to the membrane member and charges the membrane member so that the first surface has a negative potential that is lower than that of the second surface by a predetermined potential difference.
A space debris removing device including an attachment device for attaching the film member to the space debris. A space debris removal device that is attached to space debris that orbits the earth and changes the orbit of the space debris by reducing the orbital speed of the space debris.
It has a first surface facing the space debris and a second surface opposite to the first surface, and when power is supplied, the first surface is lower than the second surface by a predetermined potential difference. A film member that is charged so as to have a negative potential,
A space debris removing device including an attachment device for attaching the film member to the space debris. A satellite body mechanically connected to the membrane member and the mounting device and having a propulsion function is further provided.
The space debris removing device according to claim 1 or 2, wherein the mounting device has a predetermined length and includes a capturing mechanism for capturing the space debris. The membrane member is
A first conductor made of a conductive material constituting the first surface and
A second conductor made of a conductive material constituting the second surface, and
A third conductor made of a conductive material arranged between the first conductor and the second conductor,
A first non-conductor made of an insulator material or a dielectric material arranged between the first conductor and the third conductor,
The space debris according to any one of claims 1 to 3, further comprising a second non-conductor made of an insulator material or a dielectric material arranged between the second conductor and the third conductor. Removal device. The membrane member is
A first conductor made of a conductive material constituting the first surface and
A second conductor made of a conductive material constituting the second surface, and
The space debris removing device according to any one of claims 1 to 3, further comprising an insulator material or a non-conductor made of a dielectric material arranged between the first conductor and the second conductor. .. The space debris removing device according to any one of claims 1 to 5, wherein the predetermined potential difference is 10 V to 1000 V. The space debris removing device according to any one of claims 1 to 6, wherein the potential of the first surface is set to −10 V or less.

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