WO2020031266A1

WO2020031266A1 - Object orbit changing system and object orbit changing method

Info

Publication number: WO2020031266A1
Application number: PCT/JP2018/029633
Authority: WO
Inventors: 藤村　浩; 雄一中田
Original assignee: 株式会社日本製鋼所
Priority date: 2018-08-07
Filing date: 2018-08-07
Publication date: 2020-02-13

Abstract

Provided are an object orbit changing system and object orbit changing method that can change the orbit of an object in space. This object orbit changing system (100) has a projectile (3), a towing body (4), and a main body (5). A launcher (1) is attached to the main body (5) and launches the projectile (3) so as to capture an object (10) that orbits the celestial body. The towing body (4) is connected to the projectile (3) so as to be capable of towing the object captured by the projectile (3).

Description

Object trajectory changing system and object trajectory changing method

The present invention relates to an object orbit changing system and an object orbit changing method.

In recent years, the impact of space debris orbiting the earth has become a problem. Therefore, various techniques for removing space debris have been proposed (

Patent Documents

1 and 2, Non-Patent Documents 1-3).

For example, a method of changing the trajectory of space debris using a conductive tether has been proposed (Patent Document 1). In this method, an artificial satellite is brought close to space debris, and a conductive tether is attached to space debris by a robot hand. Since an electromagnetic effect (Lorentz force) acts on the conductive tether under the influence of the surrounding magnetic field, the space debris is pulled by the effect and the space debris falls.

手法 Also, a technique has been proposed in which a harpoon is launched from an artificial satellite and is driven into a cavity of space debris and captured (Patent Document 2). A speed reducer such as a conductive tether is connected to the harpoon so that the orbit of the space debris can be changed. This method can also be applied to space debris with irregular movements that are difficult to rendezvous or dock.

JP 2016-2813 A Japanese Patent No. 5781623

(4) When using the technique of changing the orbit of space debris to remove space debris orbiting the earth, a method capable of changing the orbit with high probability is required.

{Other problems and novel features will be apparent from the description of this specification and the accompanying drawings.

The present invention has been made in view of the above circumstances, and an object of the present invention is to provide an object trajectory changing system and an object trajectory changing method that can change the trajectory of an object in outer space. is there.

An object trajectory changing system according to one embodiment includes a projectile that captures an object orbiting an orbit around a celestial body, a main body, and the projectile mounted on the main body to capture the object. And a towing body connected to the projectile so as to be able to tow an object captured by the projectile.

The method of changing the trajectory of an object according to one embodiment includes launching a projectile that captures an object circling an orbit around a celestial body from a launch unit attached to a main body, and projecting the object captured by the projectile. , Which is towed by a towable body connected to be able to tow.

According to one embodiment, it is possible to provide an object orbit changing system and an object orbit changing method that can change the orbit of an object in outer space.

FIG. 1 is a diagram schematically illustrating a basic configuration of an object trajectory changing system according to a first embodiment. FIG. 1 is a diagram schematically illustrating a configuration of an object trajectory changing system according to a first embodiment. FIG. 2 is a diagram showing an operation method of the object trajectory changing system according to the first embodiment. 4 is a flowchart illustrating a trajectory changing operation of the object trajectory changing system according to the first embodiment; FIG. 4 is a diagram illustrating a relationship between a launch direction of a projectile and an object. FIG. 3 is a diagram illustrating a movement path of a main body of the object trajectory changing system according to the first exemplary embodiment; It is a figure which shows the positional relationship of a wire and an object, and the motion of a projectile. It is a figure which shows Lorentz force which acts when a tow body has a positive charge. It is a figure which shows the Lorentz force which acts when a towing body has a negative charge. It is a figure which shows typically the structure of the trajectory change system of the object concerning Embodiment 2. It is a figure which shows the harpoon which is an example of a projectile. It is a figure which shows the net which is another example of a projectile. 9 is a flowchart illustrating a trajectory changing operation of the object trajectory changing system according to the second exemplary embodiment; It is a figure showing an example where a harpoon captures an object. It is a figure which shows typically the structure of the trajectory change system of the object concerning Embodiment 3. 13 is a flowchart illustrating a trajectory changing operation of the object trajectory changing system according to the third embodiment. FIG. 15 is a diagram showing the development of a parachute in the third embodiment. It is a figure which shows typically the structure of the trajectory change system of the object concerning Embodiment 4. 14 is a flowchart showing a trajectory changing operation of the object trajectory changing system according to the fourth embodiment. FIG. 14 is a diagram showing the development of the parachute according to the fourth embodiment.

Hereinafter, embodiments of the present invention will be described with reference to the drawings. In the drawings, the same elements are denoted by the same reference numerals, and a repeated description will be omitted as necessary.

In the following embodiment, a system that changes the trajectory of an object orbiting a predetermined trajectory by applying a central force in outer space will be described.

Generally, to remove space debris orbiting, for example, it is necessary for a satellite to approach the space debris and rendezvous or dock with the space debris so as not to collide with the space debris. In this case, not only does it take time to control the speed and attitude of the artificial satellite, but also it is difficult in principle to respond to space debris that is moving irregularly.

銛 It is also conceivable to launch a harpoon from a position away from space debris and capture the space debris by driving a harpoon into the cavity of the space debris. However, if the space debris is moving irregularly, it is difficult to selectively hammer into the cavity. If a harpoon is driven into an unexpected position, the space debris may be damaged and the space debris may increase.

物体 The object trajectory changing system described in the following embodiment is configured to solve the above problem. The trajectory changing system for an object according to the following embodiments is configured as a system that changes the trajectory of an object by firing a projectile and capturing the object, and the towing body pulls the object through a wire. . Here, as an example, a trajectory change system that changes the trajectory of an object such as space debris orbiting on a predetermined trajectory around the celestial body under the gravity of the celestial body (for example, the earth) will be described.

Embodiment 1
Hereinafter, embodiments of the present invention will be described with reference to the drawings. FIG. 1 schematically shows a basic configuration of an object trajectory changing system 100 according to the first embodiment. The object trajectory changing system 100 includes at least a launch unit 1, a wire 2, a projectile 3, a towing unit 4, and a main unit 5.

The launching unit 1 is configured to launch the projectile 3 into outer space outside the main body 5. The launching unit 1 includes various types of devices such as an electromagnetic accelerator such as a rail gun that launches the projectile 3 by electromagnetic acceleration, a device that pushes the projectile 3 by spring force, and a device that launches the projectile 3 by explosive force of explosive. You may comprise as a launching apparatus. In consideration of launching the projectile 3 in outer space, it is preferable to use an electromagnetic accelerator that can reduce the number of movable parts and generates less waste after launch.

The towing body 4 is configured to have a positive or negative charge. The electric charge may be given to the towing body 4 in advance by the object orbit changing system 100, or the towing body 4 may generate the electric charge autonomously. The towing body 4 can be configured as a necessary housing in a metal housing, for example. Electric charges are generated when the traction body 4 collides with ions or electrons in plasma in outer space. When an artificial satellite or the like is exposed to sunlight, electrons on the surface of the housing are likely to be emitted into space as photoelectrons, so that the towing body 4 in this case is positively charged. On the other hand, when the vehicle is in a shade where no sunlight is exposed, the towing body 4 is negatively charged. In general, measures are taken to prevent electrification in artificial satellites, etc., but in this configuration, the polarity of the charge is controlled by an ion emitter or current emitter by utilizing the above-mentioned property that objects in outer space are easily charged. The towing body 4 can be charged.

One end 2A of the wire 2 is connected to the projectile 3, and the other end 2B is connected to the towing body 4. Note that the projectile 3 and the towing body 4 may be connected to the wire 2 at a position other than the end. As the projectile 3 is launched from the launch unit 1 and moves away from the main unit 5, the wire 2 is sent out of the main unit 5.

It is desirable that the wire 2 is made of a lightweight and tough material. For example, as the wire 2, it is desirable to use a carbon fiber cable reinforced with a material woven from carbon fibers. Further, the wire 2 may be made of a resin material having a sufficient strength or various metals.

The configuration of the object trajectory changing system 100 will be described in more detail. FIG. 2 schematically shows a configuration of the object trajectory changing system 100 according to the first embodiment. The object orbit changing system 100 is configured as an artificial satellite capable of moving in space by itself. The object trajectory changing system 100 shown in FIG. 2 includes a wire sending unit 6 and a propulsion unit 7 in addition to the launch unit 1, the wire 2, the projectile 3, the towing unit 4, and the main unit 5.

(5) The launch unit 1, the wire sending unit 6, and the propulsion unit 7 are fixed to the main body unit 5, and integrally constitute an artificial satellite. The wire 2 and the projectile 3 are housed in an artificial satellite constituted by the launching unit 1, the main unit 5, the wire sending unit 6, and the propulsion unit 7, and are stored in an outer space outside the artificial satellite as necessary, as described later. Released. The towing body 4 is detachably attached to the main body 5 as needed.

The object trajectory changing system 100 is configured to be accommodated in a mother ship such as a space station, for example, and released into space as needed. The object trajectory changing system 100 can move in space by itself by the propulsion unit 7 such as a thruster.

The wire feeding section 6 stores the wire 2 of a predetermined length. As the projectile 3 is fired from the firing unit 1 and moves away from the main unit 5, the wire 2 is sent out of the main unit 5 from the wire sending unit 6.

The wire feeder 6 can measure the length of the wire 2 that has been sent out. For example, when detecting that the wire 2 has been sent out by a predetermined length, the wire feeder 6 can stop sending out the wire 2 as necessary. . Further, the wire feeder 6 can also cut the wire 2 as necessary.

Next, an operation of changing the trajectory of the object by the trajectory changing system 100 will be described. FIG. 3 shows an operation method of the object trajectory changing system 100 according to the first embodiment. The object trajectory changing system 100 is configured to be accommodated in a mother ship 20 such as a space station. The mother ship 20 can search for the object 10 orbiting the earth, such as space debris, using a search device such as a radar. Further, the object 10 can be found by a radar or the like installed at a base on the ground. Upon finding an object 10 orbiting the earth, the object orbit changing system 100 is released from the mother ship 20 into space.

FIG. 4 is a flowchart showing a trajectory changing operation of the object trajectory changing system 100 according to the first embodiment. Hereinafter, each step of the trajectory changing operation of the object trajectory changing system 100 will be described.

Step S11: Object Position Tracking The object orbit changing system 100 continuously tracks the position of the object 10 such as space debris orbiting a predetermined orbit after being released into the outer space. The object orbit changing system 100 may track the position of the object 10 by receiving position information of the object 10 from another artificial satellite such as the ground or a mother ship, or may be provided in the object orbit changing system 100. The position of the object 10 may be tracked using a detection device such as a radar.

Step S12: Object Capture The firing unit 1 fires the projectile 3 to capture the object 10. Here, a method of capturing the object 10 by winding the wire 2 sent from the object trajectory changing system 100 by moving the projectile 3 around the object 10 (referred to as a winding method) will be described.

Step S121: Approaching the Object The object trajectory changing system 100 drives the propulsion unit 7 to approach the object 10 based on the position information of the object 10. At this time, the object trajectory changing system 100 approaches the object 10 to a position closer than the length of the wire 2 connecting the projectile 3 and the towed body 4.

Step S122: Launch the projectile After the approach to the object 10 is completed, the launching unit 1 launches the projectile 3 near the object 10 so that the projectile 3 does not collide with the object 10. FIG. 5 shows the relationship between the launch direction of the projectile 3 and the object.

Step S123: Movement of main body After firing projectile 3, main body 5 moves in a direction D2 (second direction) that is not parallel to moving direction D1 (first direction) of projectile 3. FIG. 6 shows a movement route of the main body unit 5 according to the first embodiment. As a result, the main body 5 moves to a position outside the moving direction D1 of the projectile 3.

At this time, in order to wind the wire 2 around the object 10 efficiently, the main body 5 is at least orthogonal to the moving direction D1 which is the path along which the projectile moves, and passes through the center of gravity of the object 10 from the moving direction D1. It is desirable to move in the direction D2 which is the direction.

Step S124: Stop Wire Feeding After the movement of the main body 5 is completed, the wire feeding unit 6 stops feeding the wire 2. The wire feed stop may be performed by a feed stop mechanism provided in the wire feed unit 6. The feeding of the wire 2 can also be stopped when the entire wire 4 is sent out and pulled by the pulling body 4.

Step S125: Wire Contact with Object After sending out the wire 2, the projectile 3 moves and the wire 2 is tensioned. FIG. 7 shows the relationship between the wire 2 and the object 10 and the movement of the projectile 3. Based on the positional relationship between the main body 5, the projectile 3, and the object 10, if the projectile 3 continues to move after the wire 2 is stopped, a part of the wire 2 comes into contact with the object 10 at a certain point. Needless to say, the wire 2 may come into contact with the object 10 before the feeding of the wire 2 is stopped. Further, as long as the wire 2 can come into contact with the object 10, the above-mentioned wire sending stop can be performed before the movement of the main body 5 is completed.

Step S126: Wire Winding When the wire 2 comes into contact with the object 10, the projectile 3 is pulled by the wire 2 and starts rotating with respect to the object 10. As a result, the wire 2 is wound around the object 10. As the wire 2 is wound, the length of the wire 2 between the contact portion between the wire 2 and the object 10 and the projectile 3 becomes shorter, so that the rotation speed of the projectile 3 increases. In the outer space, the wire 2 is wound around the object 10 a plurality of times by taking a sufficient length of the wire 2 because it is in a weightless state or a low gravity state that can approximate the weightless state.

In order to efficiently wind the wire 2 around the object 10, it is desirable that the main body 5 moves within a plane where the center of gravity of the projectile 3 and the center of gravity of the object 10 belong. In other words, the moving direction D1 (first direction) and the direction D2 (second direction) of the projectile 3 are desirably parallel to the plane to which the center of gravity of the projectile 3 and the center of gravity of the object 10 belong. . However, it is not required that the main body 5 move strictly within this plane, but it is desirable that the main body 5 move along this plane to the extent that the wire 2 can be wound around the object 10.

(4) The projectile 3 may be provided with a clamp member such as a hook for clamping irregularities on the surface of the object 10 when the projecting body 3 comes into contact with the object 10 as the winding of the wire 2 proceeds. When the object 10 is metal other than the hook, the projectile 3 may be provided with a magnet, or the projectile 3 may be made of a magnet so that the projectile 3 is attracted to the object 10. Thereby, the firing 4 is fixed to the object 10 and the wire 2 can be prevented from being unraveled.

Step S13: Disconnect
After the winding of the wire 2 is completed, the main body 5 separates the towing body 4 and discharges it to outer space. In addition, as long as the wire 2 cannot be unwound, the towing body 4 may be disconnected even before the winding of the wire 2 is completed.

Step S14: Recovery After separating the towing body 4, the main unit 5 drives the propulsion unit 7 to return to the mother ship such as a space station. Thereby, the mother ship can collect | recover the main-body part 5 suitably. Needless to say, by replenishing the consumed wire 2, the projectile 3 and the towed body 4 as needed after collection, the object can be reused as a trajectory change system for the object. Further, a mother ship such as a space station may collect the main body 5 using a collection device such as a robot arm.

Next, the behavior of the object 10 after the towing body 4 is separated from the main body 5 will be described. Since the towing body 4 is connected to the object 10 by the wire 2, the towing body 4 moves along the trajectory of the object 10. Since the towing body 4 has a positive or negative charge, Lorentz force acts on the towing body 4.

FIG. 8 shows the Lorentz force F acting when the towing body 4 has a positive charge. In FIG. 8, the direction perpendicular to the paper surface and going from the front to the back of the paper surface is defined as the direction of the geomagnetism B. In FIG. 8, the speed at which the object 10 orbits the orbit ORB before being captured by the projectile 3 is V0. The towing body 4 moves along the trajectory ORB of the object 10 in a direction intersecting the direction of the geomagnetism B. Therefore, the Lorentz force F is applied to the towing body 4 in the same direction as the gravity G, that is, in the direction toward the celestial body AST (vertically downward). Since the object 10 is pulled downward by the wire 2 that has been tensioned by the Lorentz force F, the object 10 moves in the direction DF and decreases in altitude, and as a result, the trajectory changes.

FIG. 9 shows the Lorentz force F acting when the towing body 4 has a negative charge. 9, the direction of the geomagnetism B is perpendicular to the plane of the paper and goes from the front to the rear of the plane of the paper as in FIG. The towing body 4 moves in the direction crossing the direction of the geomagnetism B along the trajectory ORB of the object 10 as in the case of FIG. Therefore, the Lorentz force F is applied to the towing body 4 in the direction opposite to the gravity G, that is, in the direction opposite to the celestial body AST (vertically upward). Since the object 10 is pulled upward by the wire 2 that has been tensioned by the Lorentz force F, the object 10 moves in the direction DF and increases in altitude, and as a result, the trajectory changes.

によって Depending on the state of movement of the object 10, a situation in which the wire 2 is entirely wrapped around the object 10 and the object 10 and the towing body 4 are substantially integrated can be considered. However, even in this case, it can be understood that the trajectory of the object 10 can be changed as described above by the Lorentz force acting on the charged traction body 4. In contrast, when a conductive tether is used as in the above-described patent documents and non-patent documents, if the conductive tether is wound around the object 10, the current control of the conductive tether cannot be performed, and the trajectory of the object is changed. It will be difficult. However, in the present configuration, unlike a general method using a conductive tether, the trajectory of the object 10 can be changed without being affected by the motion of the object 10.

As described above, in the present configuration, since the Lorentz force F acts on the towing body 4 in a direction that makes a tolerance with the trajectory of the object 10 and the direction of the geomagnetism, the trajectory of the object 10 is changed to a lower trajectory or a higher trajectory. Can be done. Accordingly, by moving or removing an object in a desired orbit, it is possible to prevent an artificial satellite or the like to be put into the desired orbit from colliding with another object such as space debris.

In addition, in the present embodiment, unlike the general method of docking or rendezvous approaching the object 10, the distance between the main body 5 and the object 10 can be sufficiently increased. Therefore, the collision between the main body 5 and the object 10 can be prevented, and the main body 5 can be quickly approached to the object 10 without fear of collision. As a result, it is possible to quickly change the trajectory of the object.

Embodiment 2
An object trajectory changing system 200 according to the second embodiment will be described. In the object trajectory changing system 100 according to the first embodiment, the projectile 3 captures the object 10 by wrapping the wire 2 around the object 10 without colliding with the object 10. On the other hand, the trajectory changing system 200 according to the present embodiment is configured as one in which the projectile launched from the launch unit 1 contacts and captures the object 10 (referred to as a direct capture method).

FIG. 10 schematically shows a configuration of an object trajectory changing system 200 according to the second embodiment. The object trajectory changing system 200 has a configuration in which the projectile 3 of the object trajectory changing system 100 is replaced with a projectile 8. The launch unit 1 launches the projectile 8 toward the object 10, and the projectile 8 comes into direct contact with the object 10 so that the object 10 is captured.

FIG. 11 shows a harpoon 81 which is an example of the projectile 8. The harpoon 81 has a sharp tip 81A so as to penetrate the object 10. In order to prevent the harpoon 81 from coming out after penetrating the outer shell 10A of the object 10, the harpoon 81 may have a coming-off prevention mechanism. As the detachment preventing mechanism, for example, a return 81B for preventing detachment may be provided near the distal end 81A, or an anchor 81C that automatically deploys after the harpoon 81 has penetrated the outer shell 10A of the object 10 may be provided.

FIG. 12 shows a net 82 which is another example of the projectile 8. The net 82 is loaded in a state where it is folded into the launching unit 1, deploys after being launched from the launching unit 1, and heads toward the object 10. The object 10 is captured when the net 82 reaches the object 10 and wraps around the object 10. The net 82 may naturally wrap the object 10 by inertial force, or may be configured to automatically close and capture the object 10 when it comes into contact with the object 10. The net 82 may be provided with a hook or the like for clamping the object 10.

The net 82 can reduce the probability that a part of the object 10 separates or scatters when the object 10 is captured, as compared with the harpoon 81, and thus can capture the object 10 more preferably. When the object 10 is space debris, by using the net 82, the probability that new space debris will occur due to collision with the object 10 can be reduced, so that space debris can be removed more efficiently. .

Here, the net 82 has been described, but it goes without saying that a member other than the net, such as a sheet, may be used as the projectile as long as the object 10 can be wrapped.

In the present embodiment, the harpoon 81 and the net 82 have been described, but it goes without saying that, as long as the object 10 can be captured, a member of another shape may be appropriately used as the projectile.

Next, the operation of changing the trajectory of the object by the object trajectory changing system 200 will be described. FIG. 13 is a flowchart illustrating a trajectory changing operation of the object trajectory changing system 200 according to the second embodiment. Hereinafter, each step of the trajectory changing operation of the object trajectory changing system 200 will be described.

Step S21: Object Position Tracking As in step S11, the object trajectory changing system 200 continuously performs an operation of tracking the position of the object 10 such as space debris orbiting a predetermined orbit.

Step S22: Object Capture The launch unit 1 launches the projectile 8 toward the object 10 and captures the object 10. Here, a case where the harpoon 81 is used as the projectile will be described.

Step S221: Approaching the Object Similar to step S121, the trajectory changing system 200 for the object approaches the object 10 based on the position information of the object 10.

Step S222: Launch the projectile After the approach to the object is completed, the launching unit 1 launches the harpoon 81 toward the object 10. FIG. 14 shows an example in which the harpoon 81 captures the object 10. At this time, as the harpoon 81 moves, the wire 2 is fed from the wire feeder 6.

Step S223: Projectile Captures Object When the harpoon 81 reaches the object 10, it penetrates the object 10 and captures the object 10.

Step S23: Separation When the harpoon 81 captures the object 10, the feeding of the wire 2 is decelerated or stopped, so that the wire feeding unit 6 can detect that the harpoon 81 has captured the object 10. When the capture of the object 10 is detected, the main body 5 disconnects the traction body 4 connected to the wire 2 and discharges the traction body 4 into outer space.

Step S24: Recovery As in step S14, the main unit 5 drives the propulsion unit 7 to return to the mother ship such as a space station.

As described above, according to the present configuration, the object 10 is captured by the projectile 8 and the object 10 is towed by the towing body 4, so that the trajectory of the object 10 is reduced to a lower trajectory or a higher trajectory as in the first embodiment. Can be changed to orbit. Accordingly, by moving or removing an object in a desired orbit, it is possible to prevent an artificial satellite or the like to be put into the desired orbit from colliding with another object such as space debris.

Since the main body 5 does not need to be moved after the projectile 8 is fired, the object 10 can be captured more easily and in a shorter time than the object trajectory changing system 100.

Embodiment 3
In the trajectory changing system 200 for an object according to the second embodiment, the trajectory of the object is changed by towing the object captured by the direct capture method by the Lorentz force acting on the charged towing body 4. On the other hand, the object trajectory changing system 300 according to the present embodiment changes the trajectory of the object by using the parachute as a towing body. Hereinafter, the trajectory change system 300 will be described.

FIG. 15 schematically shows a configuration of an object trajectory changing system 300 according to the third embodiment. The object trajectory changing system 300 uses the parachute 4A stored in the storage unit 9 as a towing body. As shown in FIG. 15, in the object trajectory changing system 300, the wire feeding unit 6 of the object trajectory changing system 200 is removed. The wire 2 and the parachute 4 are stored in a storage section 9, and the storage section 9 is fired together with the projectile 8 from the firing section 1.

It is desirable that the parachute 4A be made of a lightweight and tough material. For example, for the parachute 4A, it is desirable to use a carbon fiber composite material reinforced with a material woven from carbon fibers. The parachute 4A may be made of a resin material having sufficient strength, a metal foil, a laminate of a resin film and a metal film, or the like.

Next, an object trajectory changing operation performed by the object trajectory changing system 300 will be described. FIG. 16 is a flowchart illustrating a trajectory changing operation of the object trajectory changing system 300 according to the third embodiment. Hereinafter, each step of the trajectory changing operation of the object trajectory changing system 300 will be described.

Step S31: Object Position Tracking As in step S21, the object trajectory changing system 300 continuously performs an operation of tracking the position of the object 10 such as space debris orbiting a predetermined trajectory.

Step S32: Object Capture The launching unit 1 launches the projectile 8 and the storage unit 9 toward the object 10 to capture the object 10. Hereinafter, the object capture will be described.

Step S321: Approaching the Object Similar to step S221, the trajectory changing system 300 of the object approaches the object 10 based on the position information of the object 10.

Step S322: Launch the projectile As in step S222, after the approach to the object is completed, the launch unit 1 launches the harpoon 81 and the storage unit 9 toward the object 10.

Step S323: Parachute Release FIG. 17 shows the development of the parachute 4A. The parachute 4 </ b> A is stored at the rear of the storage unit 9, and is discharged to the storage unit 9 in a direction opposite to the traveling direction of the storage unit 9 by, for example, a release mechanism using a spring or the like.

Step S324: Parachute Deployment The parachute 4A naturally deploys by receiving the drag (that is, fluid resistance) of the diluted atmosphere in outer space. Since the deployment of the parachute 4A is performed by the drag of the lean atmosphere, the deployment of the parachute 4A may be performed before the projectile 8 captures the object 10, or even after the projectile 8 captures the object 10. Good.

Step S325: Projectile Captures Object When harpoon 81 reaches object 10, it penetrates object 10 and captures object 10. Since the parachute 4A has already been deployed, it receives the drag of the lean atmosphere. Thus, the object 10 moving on the orbit is decelerated by being pulled in the direction opposite to the moving direction.

Step S33: Recovery As in step S24, the main unit 5 drives the propulsion unit 7 to return to the mother ship such as a space station.

As described above, according to this configuration, the trajectory of the object 10 can be changed to a lower trajectory by capturing the object 10 with the projectile 8 and decelerating the object 10 with a parachute. Accordingly, by moving or removing an object in a desired orbit, it is possible to prevent an artificial satellite or the like to be put into the desired orbit from colliding with another object such as space debris.

Also, in this configuration, the parachute receives the resistance of the lean atmosphere, but the density of the lean atmosphere increases as the altitude of the object 10 decreases, so that the deceleration effect increases. That is, since the deceleration of the object 10 increases as the altitude decreases, the trajectory of the object 10 can be changed efficiently.

Further, in the present configuration, unlike the towing body 4 to be charged described in the first and second embodiments, the parachute 4A does not require a mechanism or an electric component for charging. Therefore, the configuration becomes simpler, and the cost required for changing the trajectory of the object can be reduced.

Embodiment 4
In the object orbit changing system 100 according to the first embodiment, the object captured by the winding method is towed by Lorentz force acting on the charged towing body 4 to change the orbit of the object. On the other hand, the object trajectory changing system 400 according to the present embodiment is configured to change the trajectory of the object by using a parachute as a towed body, as in the third embodiment. Hereinafter, an object trajectory changing system 400 according to the fourth embodiment will be described.

FIG. 18 schematically shows a configuration of an object trajectory changing system 400 according to the fourth embodiment. The object trajectory changing system 400 uses the parachute 4A as a towing body. The object trajectory changing system 400 is configured to decelerate the object 10 captured by the winding method according to the first embodiment with the parachute 4A according to the third embodiment.

Next, an object trajectory changing operation performed by the object trajectory changing system 400 will be described. FIG. 19 is a flowchart illustrating the trajectory changing operation of the object trajectory changing system 400 according to the fourth embodiment. Hereinafter, each step of the trajectory changing operation of the object trajectory changing system 400 will be described.

Step S41: Object Position Tracking As in step S11, the object trajectory changing system 400 continuously performs an operation of tracking the position of the object 10 such as space debris orbiting a predetermined orbit.

Step S42: Object Capture The launch unit 1 launches the projectile 3 in order to capture the object 10. Here, the object 10 is captured by the winding method as in the object trajectory changing system 100 according to the first embodiment. Hereinafter, the object capture will be described.

Step S421: Approaching the Object Similar to step S121, the trajectory changing system 400 of the object approaches the object 10 based on the position information of the object 10.

Step S422: Launch the projectile As in step S122, after the approach to the object 10 is completed, the launch unit 1 launches the projectile 3 near the object 10 so that the projectile 3 does not collide with the object 10.

Step S423: Movement of the main body As in step S123, after firing the projectile 3, the main body 5 moves in a direction D2 that is not parallel to the moving direction D1 of the projectile 3. As a result, the main body 5 moves to a position outside the moving direction D1 of the projectile 3.

Step S424: Parachute Release FIG. 20 shows the development of the parachute 4A. As in step S323, the parachute 4A is stored at the rear of the storage unit 9, and is discharged into the storage unit 9 in a direction opposite to the traveling direction of the storage unit 9 by, for example, a release mechanism using a spring or the like. You.

Step S425: Parachute Deployment Like the step S324, the parachute 4A naturally deploys by receiving the drag (ie, fluid resistance) of the lean atmosphere in outer space. Since the deployment of the parachute 4A is performed by the drag of the lean atmosphere, the deployment of the parachute 4A may be performed before the projectile 3 captures the object 10, or even after the projectile 3 captures the object 10. Good.

Step S426: Stop Wire Feeding After the movement of the main body 5 and the development of the parachute are completed, the wire feeding unit 6 stops feeding the wire 2.

Step S427: Wire Contact with Object Similar to Step S125, after the feeding of the wire 2 is stopped, the tension of the wire 2 is generated by the movement of the projectile 3. As a result, a part of the wire 2 comes into contact with the object 10 at a certain time.

Step S428: Wire Wrapping As in step S126, when the wire 2 comes into contact with the object 10, the projectile 3 is pulled by the wire 2 and starts rotating with respect to the object 10. As a result, the wire 2 is wound around the object 10. As the wire 2 is wound, the length of the wire 2 between the contact portion between the wire 2 and the object 10 and the projectile 3 becomes shorter, so that the rotation speed of the projectile 3 increases. In the outer space, the wire 2 is wound around the object 10 a plurality of times by taking a sufficient length of the wire 2 because it is in a weightless state or a low gravity state that can approximate the weightless state.

Step S43: Wire Cutting After the winding of the wire is completed, the wire feeder 6 cuts the wire 2.

Step S44: Recovery As in step S14, the main unit 5 drives the propulsion unit 7 after cutting the wire 2 and returns to the mother ship such as a space station.

As described above, according to this configuration, similarly to the object trajectory changing system 300 according to the third embodiment, the trajectory of the object 10 can be changed to a lower trajectory by decelerating the object 10 with a parachute. Accordingly, by moving or removing an object in a desired orbit, it is possible to prevent an artificial satellite or the like to be put into the desired orbit from colliding with another object such as space debris.

Also, in this configuration, the parachute receives the drag of the lean atmosphere, but the lower the altitude of the object 10, the greater the density of the lean atmosphere, and thus the greater the deceleration effect. That is, since the deceleration of the object 10 increases as the altitude decreases, the trajectory of the object 10 can be changed efficiently, similarly to the object trajectory changing system 300 according to the third embodiment.

Other Embodiments The present invention is not limited to the above-described embodiment, and can be appropriately changed without departing from the gist. For example, it goes without saying that the projectile may be fired a plurality of times, and the trajectory may be changed by towing the object 10 with the plurality of towed bodies. As a result, the trajectory of the object 10 can be changed more quickly.

In the above embodiment, the material of the wire 2 is not particularly limited, and a conductive or insulating material may be appropriately used.

In the first and fourth embodiments, the configuration using the towing body 4 to be charged is described, but a conductive tether may be used instead of the towing body to be charged.

DESCRIPTION OF SYMBOLS 1 Launch part 2

Wire

2A, 2B end

part

3, 8 Projectile 4 Traction body 4A Parachute 5 Main part 6 Wire sending part 7 Propulsion part 9 Storage part 10 Object 20 Mother ship 81 Harpoon 81A Tip 82B Return 81C Anchor 82

Net

100, 200 , 300, 400 Orbit change system

Claims

Projectiles capturing objects that orbit around the celestial body;
The main body,
A launch unit attached to the main body unit and launching the projectile to capture the object;
A tow body connected to the projectile so as to be able to tow an object captured by the projectile,
Object trajectory change system.
Further comprising a wire connecting the projectile and the towed body,
The projectile captures the object by performing a rotational motion on the object and winding the wire around the object.
An object trajectory changing system according to claim 1.
A propulsion unit attached to the main body, for moving the main body relative to the object,
Further, a wire delivery unit that sends out the wire after the projectile has been fired,
The launching unit launches the projectile toward the vicinity of the object so as not to collide with the object,
The propulsion unit is at least orthogonal to a path along which the projectile travels, and moves the main body from the path in a direction passing through the center of gravity of the object,
The wire feeding unit, during or after the movement of the main body, stops sending the wire,
An object trajectory changing system according to claim 2.
The projectile has a clamp member that clamps the object when it comes into contact with the object,
An object trajectory changing system according to claim 2 or 3.
Part or all of the projectile is formed of a magnet that can be attracted to a metal part of the object,
An object trajectory changing system according to claim 2 or 3.
The projectile penetrates the object and captures the object;
An object trajectory changing system according to claim 1.
The projectile has a return portion that prevents the object from falling off, and an anchor portion that expands after penetrating the object to prevent the object from falling off.
An object trajectory changing system according to claim 6.
The projectile is a member that can be deployed after firing, and the deployed member captures the object by wrapping the object,
An object trajectory changing system according to claim 1.
The towing body is charged,
The tow body is tow the object by Lorentz force acting under the influence of geomagnetism,
An object trajectory changing system according to any one of claims 1 to 8.
The tow body is fixed to the main body, and is separated from the main body after the projectile is fired.
An object trajectory changing system according to claim 9.
The tow body is configured as a member that receives a drag of a rare atmosphere in outer space, and pulls the object by the drag.
An object trajectory changing system according to any one of claims 1 to 8.
The towing body is folded and stored in a storage unit fired from the firing unit together with the projectile,
Released into outer space after the housing is fired,
An object trajectory changing system according to claim 11.
The orbit changing system for the object is configured to be accommodated in another artificial satellite,
When the object is detected, the object's orbit change system is released from the other satellite,
After releasing the projectile and the towed body into outer space, the main body is recovered by the other satellite.
An object trajectory changing system according to any one of claims 1 to 12.
A projectile that captures an object that orbits around the celestial body is launched from a launch unit attached to the main unit,
Towing the object captured by the projectile with a towing body connected to the object so that the object can be towed;
How to change the trajectory of an object.
The projectile performs a rotational motion with respect to the object, and captures the object by winding a wire connecting the projectile and the towed body around the object,
The method for changing the trajectory of an object according to claim 14.
Firing the projectile toward the vicinity of the object so as not to collide with the object,
At least, the main body is moved in a direction orthogonal to a path along which the projectile advances, and in a direction passing through the center of gravity of the object from the path,
During or after the movement of the main body, stopping the sending of the wire sent from the wire sending unit attached to the main body,
The method for changing the trajectory of an object according to claim 15.
The projectile has a clamp member that clamps the object when it comes into contact with the object,
The method for changing the trajectory of an object according to claim 15.
Part or all of the projectile is formed of a magnet that can be attracted to a metal part of the object,
The method for changing the trajectory of an object according to claim 15.
The projectile penetrates the object and captures the object;
The method for changing the trajectory of an object according to claim 14.
The projectile has a return portion that prevents the object from falling off, and an anchor portion that expands after penetrating the object to prevent the object from falling off.
The method for changing the trajectory of an object according to claim 19.
The projectile is a member that can be deployed after firing, and the deployed member captures the object by wrapping the object,
The method for changing the trajectory of an object according to claim 14.
The towing body is charged,
The tow body is tow the object by Lorentz force acting under the influence of geomagnetism,
A method for changing the trajectory of an object according to any one of claims 14 to 21.
The tow body is fixed to the main body, and is separated from the main body after the projectile is fired.
The method for changing the trajectory of an object according to claim 22.
The tow body is configured as a member that receives a drag of a rare atmosphere in outer space, and pulls the object by the drag.
A method for changing the trajectory of an object according to any one of claims 14 to 21.
The towed body is folded and stored in a storage unit fired from the firing unit together with the projectile, and is released into outer space after the storage unit is fired.
The method for changing the trajectory of an object according to claim 24.