Device for adsorbing space junk fragments

Abstract

The invention relates to the technical field of aerospace, in particular to a space junk fragment adsorption device which comprises a spacecraft body, a foldable solar turning plate, a foldable electromagnet plate, a propelling system, a control system and a power supply system. The spacecraft body, the propelling system, the control system and the power supply system form a main body device; the foldable solar turning plates are connected to two symmetrical sides of the main body device; the foldable electromagnet plate is connected to the other side face of the main body device, and the side face connected with the foldable electromagnet plate is located between the two side faces connected with the foldable solar panel; the foldable solar turning plate is connected with the power supply system; the power supply system is connected with the control system, and the control system controls the attitude of the spacecraft body and controls the propelling system to propel. The power supply system is connected with the foldable electromagnet plate, and the control system controls the power supply system to supply power to the foldable electromagnet plate. Space junk fragments are adsorbed by carrying the electromagnet plate, and the capture difficulty of the space junk is reduced.

Description

Technical Field

[0001] The present application relates to the field of aerospace technology, and in particular to a device for absorbing space debris. Background Art

[0002] With the increasing number of space activities in recent years, the amount of space debris is also increasing. The space debris formed will pose a threat to spacecraft in orbit, and even collide with spacecraft to produce new space debris, which will have serious consequences if repeated.

[0003] At present, the treatment of space debris in the geostationary orbit is generally carried out by accelerating it to the graveyard orbit; the treatment of space debris in the low orbit is to lower its orbit so that it burns up in the atmosphere. Before lowering the orbit, it is usually necessary to capture the space debris in the low orbit. Common capture methods include robotic arms, net bags, harpoons, etc. However, due to the changeable posture of space debris, there is a rolling out-of-control state, and there is no obvious docking interface, which makes it difficult to achieve the capture action with common capture methods (such as robotic arms, net bags, harpoons, etc.), and thus the space debris cannot be captured smoothly, which greatly increases the difficulty of handling space debris.

[0004] Therefore, how to reduce the difficulty of capturing space debris and thus smoothly dispose of it is a technical problem that technical personnel in this field urgently need to solve. Summary of the invention

[0005] The present application provides a device for absorbing space junk fragments, which reduces the difficulty of capturing space junk by carrying an electromagnet plate to absorb space junk fragments, thereby smoothly processing space junk.

[0006] In order to solve the above technical problems, this application provides the following technical solutions:

[0007] A device capable of absorbing space junk fragments comprises: a spacecraft body, two foldable solar flip panels, a foldable electromagnetic plate, a propulsion system, a control system and a power supply system; wherein the spacecraft body, the propulsion system, the control system and the power supply system constitute a main device; the two foldable solar flip panels are respectively connected to two symmetrical sides of the main device; the foldable electromagnetic plate is connected to the other side of the main device, and the side to which the foldable electromagnetic plate is connected is located between the two sides to which the two foldable solar panels are connected; the foldable solar flip panel is connected to the power supply system; the power supply system is connected to the control system, and the control system 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 electromagnetic plate, and the control system can control the power supply system to supply power to the foldable electromagnetic plate.

[0008] As described above, the device capable of absorbing space debris fragments, wherein preferably, the spacecraft body is an artificial satellite, an unmanned space shuttle or a space probe.

[0009] As described above, in the device capable of absorbing space debris fragments, preferably, the two foldable solar panels are connected to the left and right sides of the main device through a connecting device.

[0010] As described above, in the device capable of absorbing space debris fragments, preferably, the foldable electromagnet plate is connected to the upper side of the main device through a fixing device.

[0011] As described above, the device capable of absorbing space debris fragments, wherein preferably, the propulsion system, the control system, the power supply system and the spacecraft body are stacked and connected in sequence from bottom to top to form a main device.

[0012] As described above, the device capable of absorbing space junk fragments, wherein preferably, the foldable solar flap and the foldable electromagnetic plate are both connected to an unfolding drive device, the unfolding drive device is connected to a control system, and the control system controls the unfolding drive device to drive the foldable solar flap and the foldable electromagnetic plate to unfold.

[0013] The device capable of absorbing space junk fragments as described above, wherein preferably, the control system includes: a position sensor, a speed sensor, a mass sensor, an attitude sensor and a controller; the controller is connected to the position sensor, the speed sensor, the mass sensor and the attitude sensor; after the foldable electromagnet plate is unfolded, the position sensor and the speed sensor begin to sense the surrounding space junk fragments, and after obtaining the position information and speed information of the surrounding target space junk fragments, the position information and the speed information are converted into electrical signals and transmitted to the controller; the controller issues a position control instruction based on the received electrical signal to control the propulsion system to perform lifting and lowering orbits and adjust the speed, so that the foldable electromagnet plate and the target space junk fragments are within a predetermined distance to absorb the space junk fragments.

[0014] As described above, the device capable of absorbing space junk fragments, wherein preferably, the control system controls the power supply system to start supplying power to the foldable electromagnet plate, so that the foldable electromagnet plate has magnetism and absorbs the surrounding target space junk fragments; during the absorption process of the space junk fragments, the main device will undergo a posture change, the posture sensor senses the posture information of the main device, and transmits the posture information to the controller, and the controller issues a posture control instruction based on the posture information to adjust the posture of the main device.

[0015] The device capable of absorbing space junk fragments as described above, wherein preferably, when the weight of the space junk fragments absorbed by the foldable electromagnet plate reaches the set rated value and / or the remaining propellant of the propulsion system reaches the reserve propellant, and at the same time, the total weight of the device that absorbs the space junk fragments after deorbiting and re-entering is less than a predetermined value; the mass sensor sends out an alarm signal, and transmits the alarm information to the controller, and the controller sends out a deorbiting and re-entering instruction based on the alarm information, so that the foldable electromagnet plate that absorbs the space junk fragments and the main device as a whole perform orbital maneuvers through the propulsion system, reduce the flight speed, deorbit and re-enter the atmosphere, and then ablate and decompose.

[0016] Compared with the above-mentioned background technology, the present application carries a foldable electromagnet plate on the spacecraft body, which can be folded before entering orbit to save space; after the spacecraft body completes the predetermined mission or reaches the predetermined life, the foldable electromagnet plate is energized to absorb space junk fragments, and the weight of the space junk fragments absorbed on the foldable electromagnet plate reaches the rated value and / or the remaining propellant reaches the reserve propellant and the total weight of the device for adsorbing the space junk fragments after leaving orbit and re-entering is less than the predetermined value, and then the device leaves orbit and re-enters the atmosphere to burn, which makes the space junk disposal operation convenient, and can make full use of the spacecraft body, reducing the cost of space junk disposal; and because the device for adsorbing space junk fragments of the present application does not have a docking interface, the difficulty of capturing space junk fragments is greatly reduced, and thus the space junk can be successfully captured, greatly reducing the difficulty of space junk disposal. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments recorded in the present invention. For ordinary technicians in this field, other drawings can also be obtained based on these drawings.

[0018] Figure 1 is a schematic diagram of a device for absorbing space junk fragments provided in an embodiment of the present application;

[0019] Figure 2 This is a schematic diagram of a device for absorbing space debris provided by an embodiment of the present application being deployed into orbit;

[0020] Figure 3 This is a schematic diagram of a device for absorbing space debris provided by an embodiment of the present application after it is deployed into orbit;

[0021] Figure 4 is a schematic diagram of the adsorption state of the device for adsorbing space debris provided in an embodiment of the present application;

[0022] Figure 5It is a schematic diagram of the deorbiting and re-entering of the device for absorbing space debris fragments provided by an embodiment of the present application;

[0023] Figure 6 It is a schematic diagram of a control system of a device for absorbing space junk fragments provided in an embodiment of the present application. DETAILED DESCRIPTION

[0024] Embodiments of the present invention are described in detail below, examples of which are shown in the accompanying drawings, wherein the same or similar reference numerals throughout represent the same or similar elements or elements having the same or similar functions. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain the present invention, and cannot be interpreted as limiting the present invention.

[0025] like Figures 1 to 3 As shown, the present application provides a device for absorbing space debris, including: a spacecraft body 110, two foldable solar flip panels 120, a foldable electromagnetic 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 and a space probe, etc.; the spacecraft body 110, the propulsion system 140, the control system 150 and the power supply system 160 constitute a main device; the two foldable solar flip panels 120 are respectively connected to the two symmetrical sides of the main device, before entering orbit, each foldable solar panel 120 is folded to the corresponding side of the main device, and after entering orbit, each foldable solar panel 120 is unfolded outward from the opposite sides of the main device; the foldable electromagnetic plate 130 is connected to the other side of the main device, and the side to which the foldable electromagnetic plate 130 is connected is located between the two sides to which the two foldable solar panels 120 are connected, thereby ensuring the balance of the main device.

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

[0027] In addition, the foldable solar flap 120 is connected to the power supply system 160 to provide the electric energy converted from solar energy to the power supply system 160; the power supply system 160 is connected to the control system 150 to provide electric energy to the control system 150, 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 electromagnetic plate 130, and the control system 150 can control the power supply system 160 to supply power to the foldable electromagnetic plate 130. After the power supply system 160 supplies power to the foldable electromagnetic plate 130, the foldable electromagnetic plate 130 can absorb the surrounding space debris.

[0028] Optionally, the propulsion system 140, the control system 150, the power supply system 160 and the spacecraft body 110 are stacked and connected in sequence from bottom to top, and since the propulsion system 140 is away from the foldable electromagnetic plate 130, the foldable electromagnetic plate 130 is prevented from affecting the propulsion of the propulsion system 140. Optionally, the foldable solar flap 120 and the foldable electromagnetic plate 130 are both connected to the deployment drive device, and the deployment drive device is connected to the control system 150, and the control system 150 controls the deployment drive device to drive the foldable solar flap 120 and the foldable electromagnetic plate 130 to deploy.

[0029] After the device for absorbing space debris fragments of the present application enters orbit, the control system 150 controls the two foldable solar flaps 120 to unfold, and the foldable solar flaps 120 absorb solar energy and convert it into electrical energy, and provide the electrical energy to the power supply system 160. The power supply system 160 provides basic guarantee for the spacecraft body 110 to perform subsequent tasks (for example: scientific exploration, navigation, communication, weather forecasting, etc.).

[0030] like Figure 4 As shown, after the spacecraft body 110 has completed the predetermined mission or has reached the predetermined life, the control system 150 controls the foldable electromagnetic plate 130 to unfold, and after the foldable electromagnetic plate 130 is unfolded, the device for adsorbing space debris fragments enters the garbage adsorption program.

[0031] On the basis of the above, if Figure 6 As shown, the control system 150 includes: a position sensor 151, a speed sensor 152, a mass sensor 153, a posture sensor 154 and a controller 155; the controller 155 is connected to the position sensor 151, the speed sensor 152, the mass sensor 153, and the posture sensor 154; after the foldable electromagnetic plate 130 is unfolded, the position sensor 151 and the speed sensor 152 of the control system 150 begin to sense the surrounding space junk fragments, and after obtaining the position information and speed information of the surrounding target space junk fragments, the position information and speed information are converted into electrical signals and transmitted to the controller 155 of the control system 150; the controller 155 issues a position control instruction based on the received electrical signal to control the propulsion system 140 to perform lifting and lowering orbits and adjust the speed, so that the foldable electromagnetic plate 130 and the target space junk fragments are within a predetermined distance, and then the space junk fragments are adsorbed.

[0032] When adsorbing space junk, the control system 150 controls the power supply system 160 to start the power supply to the foldable electromagnet plate 130, so that the foldable electromagnet plate 130 has magnetism, so that the foldable electromagnet plate 130 adsorbs the surrounding target space junk fragments 200. During the adsorption process of space junk fragments, the main device will change its posture. At this time, the posture sensor 154 of the control system 150 senses the posture information of the main device and transmits the posture information to the controller 155. The controller 1125 issues a posture control instruction based on the posture information to adjust the posture of the main device to 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 junk fragments 200 absorbed by the foldable electromagnetic 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 that absorbs the space junk fragments after deorbiting and re-entering is less than a predetermined value, the mass sensor 153 of the control system 150 will send out an alarm signal and transmit the alarm information to the controller 155. The controller 155 sends out a deorbit re-entry command based on the alarm information, so that the foldable electromagnetic plate 130 that absorbs the space junk fragments 200 and the main device as a whole can perform orbital maneuvers through the propulsion system 140 of the main device, reduce the flight speed, and deorbit and re-enter the atmosphere after ablation and decomposition.

[0034] Among them, the rated value is set to prevent the device that absorbs space junk fragments and the absorbed space junk fragments from having a total mass that is too large to be completely burned when re-entering the atmosphere, thereby endangering the environment of the fall area; the backup propellant is the minimum propellant that can successfully deorbit the main device that absorbs the rated value of space junk fragments and the absorbed space junk fragments as a whole and re-enter the atmosphere for burning.

[0035] 1) The total weight of the device that absorbs space debris before it enters orbit

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

[0037] Where:

[0038] m1-mass of the spacecraft itself;

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

[0040] m 2备保 - Ensure the quality of propellant;

[0041] m 2可用 - other available propellant masses;

[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-mass of two foldable solar panels;

[0046] m6-mass of foldable electromagnet plate;

[0047] m7-connection device quality;

[0048] m8 - Fixture quality.

[0049] 2) The total weight of the device that absorbs space debris and reenters the orbit

[0050] Case 1: The weight of the space debris adsorbed 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] Where:

[0054] m 2可用剩余 - remaining usable propellant mass;

[0055] m 9额定 - The set rated value.

[0056] The second situation: insufficient backup propellant:

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

[0058] Where:

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

[0060] The present application carries a foldable electromagnet plate on the spacecraft body, which can be folded before entering orbit to save space; after the spacecraft body completes the predetermined mission or reaches the predetermined life, the foldable electromagnet plate is energized to absorb space junk fragments, and the weight of the space junk fragments absorbed on the foldable electromagnet plate reaches the rated value and / or the remaining propellant reaches the reserve propellant and the total weight of the device for adsorbing the space junk fragments is less than a predetermined value after deorbiting and re-entering the atmosphere to burn up. This makes the space junk disposal operation convenient, and can make full use of the spacecraft body, reducing the cost of space junk disposal; and because the device for adsorbing space junk fragments of the present application does not have a docking interface, the difficulty of capturing space junk fragments is greatly reduced, and thus the space junk can be successfully captured, greatly reducing the difficulty of space junk disposal.

[0061] It will be apparent to those skilled in the art that the 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 the spirit or essential features of the invention. Therefore, the embodiments should be considered exemplary and non-limiting in all respects, and the scope of the invention is defined by the appended claims rather than the foregoing description, and it is intended that all variations falling within the meaning and scope of the equivalent elements of the claims be included in the invention. Any reference numeral in a claim should not be considered as limiting the claim to which it relates.

[0062] In addition, it should be understood that although the present specification is described according to implementation modes, not every implementation mode contains only one independent technical solution. This description of the specification is only for the sake of clarity. Those skilled in the art should regard the specification as a whole. The technical solutions in each embodiment may also be appropriately combined to form other implementation modes that can be understood by those skilled in the art.

Claims

1. A device capable of absorbing space debris, characterized in that: include: The spacecraft body, two foldable solar panels, a foldable electromagnet panel, a propulsion system, a control system and a power supply system; The spacecraft body, propulsion system, control system and power supply system constitute a main device; two foldable solar panels are respectively connected to two symmetrical sides of the main device; a foldable electromagnetic plate is connected to the other side of the main device, and the side connected to the foldable electromagnetic plate is located between the two sides connected to the two foldable solar panels; The foldable solar flap is connected to the power supply system; the power supply system is connected to the control system, the control system 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.

2. The device for absorbing 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 absorbing space debris according to claim 1, characterized in that: The two foldable solar panels are connected to the left and right sides of the main device through a connecting device.

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

5. The device for absorbing 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 from bottom to top to form the main device.

6. The device for absorbing space debris according to any one of claims 1 to 4, characterized in that: The foldable solar flap and the foldable electromagnetic plate are both connected to an unfolding drive device, the unfolding drive device is connected to a control system, and the control system controls the unfolding drive device to drive the foldable solar flap and the foldable electromagnetic plate to unfold.

7. The device capable of absorbing space debris according to any one of claims 1 to 4, characterized in that: The control system includes: position sensor, speed sensor, mass sensor, attitude sensor and controller; The controller is connected to the position sensor, speed sensor, mass sensor, and attitude sensor; After the foldable electromagnet plate is unfolded, the position sensor and the speed sensor begin to sense the surrounding space junk debris, and after obtaining the position information and speed information of the surrounding target space junk debris, the position information and speed information are converted into electrical signals and transmitted to the controller; The controller sends out position control instructions based on the received electrical signals to control the propulsion system to raise and lower the orbit and adjust the speed so that the foldable electromagnet plate and the target space debris are within a predetermined distance to absorb the space debris.

8. The device for absorbing space debris according to claim 7, characterized in that: The control system controls the power supply system to start supplying power to the foldable electromagnet plate, so that the foldable electromagnet plate has magnetism and absorbs surrounding target space junk fragments; During the adsorption process of space debris fragments, the main device will undergo a change in attitude. The attitude sensor senses the attitude information of the main device and transmits the attitude information to the controller. The controller issues an attitude control instruction based on the attitude information to adjust the attitude of the main device.

9. The device for absorbing space debris according to claim 7, characterized in that: 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 at the same time, the total weight of the device adsorbing the space debris during deorbit and re-entry is less than a predetermined value; The mass sensor sends out an alarm signal and transmits the alarm information to the controller. The controller issues a deorbit and re-entry command based on the alarm information, so that the foldable electromagnet plate that has absorbed the space debris fragments and the main device as a whole can perform orbital maneuvers through the propulsion system, reduce the flight speed, deorbit and re-enter the atmosphere before ablation and decomposition.

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