A device for adsorbing space junk debris

Abstract

The application relates to the field of aerospace technology, in particular to a device for adsorbing space garbage fragments, which comprises a spacecraft body, a foldable solar panel, a foldable electromagnet plate, a propulsion system, a control system and a power supply system; the spacecraft body, the propulsion system, the control system and the power supply system constitute a main device; the foldable solar panel is connected to the symmetrical two sides of the main device; the foldable electromagnet plate is connected to the other side of the main device, and the side connected with the foldable electromagnet plate is located between the two sides connected with the foldable solar panel; the foldable solar panel is connected with the power supply system; the power supply system is connected with the control system, the control system controls the posture of the spacecraft body and controls the propulsion of the propulsion system; the power supply system is connected with the foldable electromagnet plate, and the control system controls the power supply of the power supply system to the foldable electromagnet plate. The device adsorbs space garbage fragments through the mounted electromagnet plate, and the difficulty of capturing the space garbage is reduced.

Description

Technical Field

[0001] This application relates to the field of aerospace technology, and in particular to a device for adsorbing space debris. Background Technology

[0002] With the increasing space activities in recent years, the amount of space debris is also increasing. The space debris that forms poses a threat to spacecraft in orbit, and collisions with spacecraft can even generate new space debris, with repeated consequences.

[0003] Currently, the general approach to handling space debris in geostationary orbit is to accelerate it and transfer it to a graveyard orbit. For low Earth orbit (LEO) debris, the approach is to lower its orbit, causing it to burn up in the atmosphere. Before lowering its orbit, LEO debris typically needs to be captured, using methods such as robotic arms, nets, and harpoons. However, due to the unpredictable attitudes of space debris, its tendency to tumble and become uncontrollable, and the lack of clear docking points, common capture methods (such as robotic arms, nets, and harpoons) are difficult to execute, significantly increasing the complexity of space debris management.

[0004] Therefore, how to reduce the difficulty of capturing space debris and thus successfully process it is a technical problem that urgently needs to be solved by those skilled in the art. Summary of the Invention

[0005] This application provides a device for adsorbing space debris fragments. By using an electromagnet plate to adsorb space debris fragments, the difficulty of capturing space debris is reduced, thereby enabling the smooth processing of space debris.

[0006] To solve the above-mentioned technical problems, this application provides the following technical solution:

[0007] A device capable of absorbing space debris includes: a spacecraft body, two foldable solar panels, a foldable electromagnet plate, a propulsion system, a control system, and a power supply system; wherein the spacecraft body, propulsion system, control system, and power supply system constitute the main device; the two foldable solar panels are respectively connected to two symmetrical sides of the main device; the foldable electromagnet plate is connected to the other side of the main device, and the side to which the foldable electromagnet plate is connected is located between the two sides to which the two foldable solar panels are connected; the foldable solar panels are connected to the power supply system; the power supply system is connected to the control system, which can control the attitude of the spacecraft body and control the propulsion system to perform propulsion operations; the power supply system is connected to the foldable electromagnet plate, and the control system can control the power supply system to supply power to the foldable electromagnet plate.

[0008] The device described above that can absorb space debris is preferably a spacecraft, such as a satellite, an unmanned space shuttle, or a space probe.

[0009] In the device described above that can absorb space debris, preferably, two foldable solar panels are connected to the left and right sides of the main body device via a connecting device.

[0010] In the device described above that can absorb space debris, preferably, the foldable electromagnet plate is connected to the upper side of the main body device by a fixing device.

[0011] In the device described above that can absorb space debris, preferably, the propulsion system, control system, power supply system, and spacecraft body are stacked and connected sequentially from bottom to top to form the main device.

[0012] In the device described above that can absorb space debris, preferably, both the foldable solar panel and the foldable electromagnet plate are connected to the deployment drive device, which is connected to the control system. The control system controls the deployment drive device to deploy the foldable solar panel and the foldable electromagnet plate.

[0013] In the aforementioned device for adsorbing space debris, preferably, the control system includes: a position sensor, a velocity sensor, a mass sensor, an attitude sensor, and a controller; the controller is connected to the position sensor, velocity sensor, mass sensor, and attitude sensor; after the foldable electromagnet plate is unfolded, the position sensor and velocity sensor begin to sense the surrounding space debris, and after obtaining the position and velocity information of the target space debris, they convert the position and velocity information into electrical signals and transmit them to the controller; the controller issues position control commands based on the received electrical signals to control the propulsion system to lift and lower the rail and adjust the speed, so that the foldable electromagnet plate adsorbs the target space debris within a predetermined distance.

[0014] In the aforementioned device for adsorbing space debris, preferably, the control system controls the power supply system to activate the power supply to the foldable electromagnet plate, making the foldable electromagnet plate magnetic and adsorbing surrounding target space debris; during the adsorption of space debris, the main device will undergo an attitude change, the attitude sensor senses the attitude information of the main device and transmits the attitude information to the controller, and the controller issues attitude control commands based on the attitude information to adjust the attitude of the main device.

[0015] In the aforementioned device for adsorbing space debris, preferably, when the weight of the space debris adsorbed by the foldable electromagnet plate reaches a set rated value and / or the remaining propellant in the propulsion system reaches the reserve propellant, and simultaneously the total weight of the device adsorbing space debris during deorbiting and re-entry is less than a predetermined value, the mass sensor issues an alarm signal and transmits the alarm information to the controller. The controller issues a deorbiting and re-entry command based on the alarm information, so that the foldable electromagnet plate adsorbing the space debris and the main device as a whole undergo orbital maneuvering through the propulsion system, reducing the flight speed, and ablation and decomposition after deorbiting and re-entry into the atmosphere.

[0016] Compared to the aforementioned background technology, this application, by mounting a foldable electromagnet plate on the spacecraft body, saves space by folding it before orbital insertion. After the spacecraft body completes its predetermined mission or reaches its predetermined lifespan, the foldable electromagnet plate is energized to attract space debris. When the weight of the space debris attracted to the foldable electromagnet plate reaches the rated value and / or the remaining propellant reaches the reserve propellant, and the total weight of the space debris attracting device during deorbiting and re-entry is less than the predetermined value, the spacecraft de-enters the atmosphere and burns up. This makes the handling of space debris convenient, makes full use of the spacecraft body, and reduces the cost of space debris handling. Furthermore, since the space debris attracting device of this application does not have a docking interface, the difficulty of capturing space debris is greatly reduced, thus enabling successful capture of space debris and significantly reducing the difficulty of space debris handling. Attached Figure Description

[0017] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments recorded in the present invention. For those skilled in the art, other drawings can be obtained based on these drawings.

[0018] Figure 1 This is a schematic diagram of the device for adsorbing space debris provided in the embodiments of this application;

[0019] Figure 2 This is a schematic diagram of the device for adsorbing space debris provided in this application during its orbital deployment.

[0020] Figure 3 This is a schematic diagram of the device for adsorbing space debris provided in the embodiments of this application after it has been deployed into orbit;

[0021] Figure 4 This is a schematic diagram of the adsorption state of the device for adsorbing space debris provided in the embodiments of this application;

[0022] Figure 5This is a schematic diagram of the device for adsorbing space debris fragments provided in the embodiments of this application, which is used for off-orbit reentry.

[0023] Figure 6 This is a schematic diagram of the control system of the device for adsorbing space debris provided in the embodiments of this application. Detailed Implementation

[0024] Embodiments of the present invention are described in detail below. Examples of these embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain the present invention, and should not be construed as limiting the present invention.

[0025] like Figures 1 to 3 As shown, this application provides a device for adsorbing space debris, comprising: a spacecraft body 110, two foldable solar panels 120, a foldable electromagnet plate 130, a propulsion system 140, a control system 150, and a power supply system 160; wherein, the spacecraft body 110 is an unmanned spacecraft, such as an artificial satellite, an unmanned space shuttle, or a space probe; the spacecraft body 110, propulsion system 140, control system 150, and power supply system 160 constitute the main device; the two foldable solar panels 120 are respectively connected to the symmetrical sides of the main device, each foldable solar panel 120 is folded to the corresponding side of the main device before entering orbit, and each foldable solar panel 120 unfolds outward from the opposite sides of the main device after entering orbit; the foldable electromagnet plate 130 is connected to the other side of the main device, and the side connected to the foldable electromagnet plate 130 is located between the two sides connected to the two foldable solar panels 120, thereby ensuring the balance of the main device.

[0026] Optionally, two foldable solar panels 120 are connected to the left and right sides of the main unit via a connecting device 170. Alternatively, a foldable electromagnet plate 130 is connected to the upper side of the main unit via a fixing device 180.

[0027] In addition, the foldable solar panel 120 is connected to the power supply system 160 to provide the power supply system 160 with the electrical energy converted from solar energy; the power supply system 160 is connected to the control system 150 to provide the control system 150 with electrical energy, so that the control system 150 can control the attitude of the spacecraft body 110 and control the propulsion system 140 to perform propulsion operations; the power supply system 160 is connected to the foldable electromagnet plate 130, and the control system 150 can control the power supply system 160 to supply power to the foldable electromagnet plate 130. After the power supply system 160 supplies power to the foldable electromagnet plate 130, the foldable electromagnet plate 130 can attract surrounding space debris.

[0028] Optionally, the propulsion system 140, control system 150, power supply system 160, and spacecraft body 110 are stacked sequentially from bottom to top. Since the propulsion system 140 is far from the foldable electromagnet plate 130, the foldable electromagnet plate 130 is prevented from affecting the propulsion of the propulsion system 140. Alternatively, both the foldable solar panel 120 and the foldable electromagnet plate 130 are connected to a deployment drive device, which is connected to the control system 150. The control system 150 controls the deployment drive device to deploy the foldable solar panel 120 and the foldable electromagnet plate 130.

[0029] After the device for adsorbing space debris in this application is put into orbit, the control system 150 controls the two foldable solar panels 120 to unfold. The foldable solar panels 120 absorb solar energy and convert it into electrical energy, which is then supplied to the power supply system 160. The power supply system 160 provides basic support for the spacecraft body 110 to perform subsequent tasks (such as scientific exploration, navigation, communication, weather forecasting, etc.).

[0030] like Figure 4 As shown, after the spacecraft body 110 completes its predetermined mission or reaches its predetermined lifespan, the control system 150 controls the foldable electromagnet plate 130 to unfold. After the foldable electromagnet plate 130 unfolds, the device for adsorbing space debris enters the debris adsorption process.

[0031] Based on the above, such as Figure 6 As shown, the control system 150 includes: a position sensor 151, a velocity sensor 152, a mass sensor 153, an attitude sensor 154, and a controller 155; the controller 155 is connected to the position sensor 151, velocity sensor 152, mass sensor 153, and attitude sensor 154; after the foldable electromagnet plate 130 is unfolded, the position sensor 151 and velocity sensor 152 of the control system 150 begin to sense the surrounding space debris. After obtaining the position and velocity information of the target space debris, they convert the position and velocity information into electrical signals and transmit them to the controller 155 of the control system 150; the controller 155 issues position control commands based on the received electrical signals to control the propulsion system 140 to lift and lower the rail and adjust the speed, so that the foldable electromagnet plate 130 and the target space debris are within a predetermined distance, and then the space debris is attracted.

[0032] During the adsorption of space debris, the control system 150 controls the power supply system 160 to activate the power supply to the foldable electromagnet plate 130, making the foldable electromagnet plate 130 magnetic, thereby adsorbing the surrounding target space debris fragments 200. During the adsorption process, the main device will change its attitude. At this time, the attitude sensor 154 of the control system 150 senses the attitude information of the main device and transmits the attitude information to the controller 155. The controller 1125 issues attitude control commands based on the attitude information to adjust the attitude of the main device and ensure the safety of the main device and the foldable electromagnet plate 130.

[0033] like Figure 5 As shown, when the weight of the space debris 200 adsorbed by the foldable electromagnet plate 130 reaches the set rated value and / or the remaining propellant of the propulsion system 140 reaches the reserve propellant, and at the same time the total weight of the device adsorbing the space debris during deorbiting and re-entry is less than the predetermined value, the mass sensor 153 of the control system 150 will issue an alarm signal and transmit the alarm information to the controller 155. The controller 155 issues a deorbiting and re-entry command based on the alarm information, so that the foldable electromagnet plate 130 adsorbing the space debris 200 and the main device as a whole perform orbital maneuvers through the propulsion system 140 of the main device, reduce the flight speed, and ablate and decompose after deorbiting and re-entering the atmosphere.

[0034] The rated value is set to prevent the device that adsorbs space debris and the overall mass of the adsorbed space debris from being too large to be completely burned up during reentry into the atmosphere, thus endangering the environment of the impact zone; the backup propellant is the minimum amount of propellant that can successfully deorbit and burn up the main device that has adsorbed the rated value of space debris and the overall mass of the adsorbed space debris during reentry into the atmosphere.

[0035] 1) Total weight of the device for adsorbing space debris before orbit insertion

[0036] M0 = m1 + m2 + m3 + m4 + m5 + m6 + m7 + m8

[0037] In the formula:

[0038] m1 - Mass of the spacecraft body;

[0039] m2=m 2备保 +m 2可用 +m 2结构 -The total mass of the propulsion system;

[0040] m 2备保 - Ensure propellant quality;

[0041] m 2可用 - Other available propellant mass;

[0042] m 2结构 -Propulsion system structural quality;

[0043] m3 - Quality of the control system;

[0044] m4 - Quality of the power supply system;

[0045] m5 - Weight of two foldable solar panels;

[0046] m6 - The mass of the foldable electromagnet plate;

[0047] m7 - Mass of the connecting device;

[0048] m8 - Fixture quality.

[0049] 2) Total weight of the device for adsorbing space debris during deorbiting and re-entry.

[0050] Scenario 1: The weight of space debris attracted by the foldable electromagnet plate reaches the set rated value:

[0051] M1=m1+(m 2备保 +m 2可用剩余 +m 2结构 )+m3+m4+m5+m6+m7+m8

[0052] +m 9额定

[0053] In the formula:

[0054] m 2可用剩余 - Remaining mass of other available propellant;

[0055] m 9额定 - The set rating.

[0056] Second scenario: Insufficient spare propellant:

[0057] M1=m1+(m 2备保 +m 2结构 )+m3+m4+m5+m6+m7+m8+m9

[0058] In the formula:

[0059] The weight of space debris attracted by the m9-foldable electromagnet plate.

[0060] This application utilizes a foldable electromagnet plate mounted on the spacecraft body. Folding it before orbital insertion saves space. After the spacecraft completes its predetermined mission or reaches its predetermined lifespan, the foldable electromagnet plate is energized to attract space debris. Once the weight of the space debris attracted to the foldable electromagnet plate reaches the rated value and / or the remaining propellant reaches the reserve propellant, and the total weight of the space debris attracting device during deorbiting and re-entry is less than the predetermined value, the spacecraft de-enters the atmosphere and burns up. This simplifies space debris handling, fully utilizes the spacecraft body, and reduces space debris disposal costs. Furthermore, since the space debris attracting device in this application does not have a docking interface, the difficulty of capturing space debris is greatly reduced, enabling successful capture and significantly simplifying space debris handling.

[0061] It will be apparent to those skilled in the art that the present invention is not limited to the details of the exemplary embodiments described above, and that the invention can be implemented in other specific forms without departing from its spirit or essential characteristics. Therefore, the embodiments should be considered in all respects as exemplary and non-limiting, and the scope of the invention is defined by the appended claims rather than the foregoing description. Thus, all variations falling within the meaning and scope of equivalents of the claims are intended to be included within the present invention. No reference numerals in the claims should be construed as limiting the scope of the claims.

[0062] Furthermore, it should be understood that although this specification describes embodiments, not every embodiment contains only one independent technical solution. This narrative style is merely for clarity. Those skilled in the art should consider the specification as a whole, and the technical solutions in each embodiment can also be appropriately combined to form other embodiments that can be understood by those skilled in the art.

Claims

1. A device capable of adsorbing space debris fragments, characterized in that, include: The spacecraft consists of the main body, two foldable solar panels, a foldable electromagnet plate, a propulsion system, a control system, and a power supply system. The main structure consists of the spacecraft body, propulsion system, control system, and power supply system; two foldable solar panels are connected to the two symmetrical sides of the main structure; a foldable electromagnet plate is connected to the other side of the main structure, and the side to which the foldable electromagnet plate is connected is located between the two sides to which the two foldable solar panels are connected. The foldable solar panel is connected to the power supply system; the power supply system is connected to the control system, which can control the attitude of the spacecraft and control the propulsion system to perform propulsion operations; the power supply system is connected to the foldable electromagnet plate, and the control system can control the power supply system to supply power to the foldable electromagnet plate. The control system includes: position sensors, speed sensors, mass sensors, attitude sensors, and controllers; The controller is connected to position sensors, speed sensors, mass sensors, and attitude sensors. After the foldable electromagnet plate is unfolded, the position sensor and velocity sensor begin to sense the surrounding space debris. After obtaining the position and velocity information of the surrounding target space debris, the position and velocity information are converted into electrical signals and transmitted to the controller. The controller issues position control commands based on the received electrical signals to control the propulsion system to lift and lower the rails and adjust the speed, so that the foldable electromagnet plate can attract the target space debris within a predetermined distance. The control system controls the power supply system to start supplying power to the foldable electromagnet plate, making the foldable electromagnet plate magnetic and attracting surrounding space debris. During the adsorption of space debris, the main device will undergo attitude changes. Attitude sensors detect the attitude information of the main device and transmit the attitude information to the controller. The controller issues attitude control commands based on the attitude information to adjust the attitude of the main device. When the weight of the space debris adsorbed by the foldable electromagnet plate reaches the set rated value and / or the remaining propellant of the propulsion system reaches the reserve propellant, and the total weight of the device adsorbing the space debris during deorbiting and re-entry is less than the predetermined value. The mass sensor sends out an alarm signal and transmits the alarm information to the controller. Based on the alarm information, the controller issues a deorbit and reentry command, which causes the foldable electromagnet plate that has adsorbed space debris to move along with the main device via the propulsion system to reduce the flight speed and then ablate and decompose upon re-entry into the atmosphere.

2. The device for adsorbing space debris according to claim 1, characterized in that, The spacecraft itself is an artificial satellite, an unmanned space shuttle, or a space probe.

3. The device for adsorbing space debris according to claim 1, characterized in that, Two foldable solar panels are connected to the left and right sides of the main unit via a connecting device.

4. The device for adsorbing space debris according to claim 1, characterized in that, The foldable electromagnet plate is connected to the upper side of the main body device through a fixing device.

5. The device for adsorbing space debris according to any one of claims 1 to 4, characterized in that, The propulsion system, control system, power supply system, and spacecraft body are stacked and connected sequentially from bottom to top to form the main unit.

6. The device for adsorbing space debris according to any one of claims 1 to 4, characterized in that, Both the foldable solar panel and the foldable electromagnet plate are connected to the unfolding drive device, which is connected to the control system. The control system controls the unfolding drive device to unfold the foldable solar panel and the foldable electromagnet plate.

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