Space debris removal method and system

Abstract

The present invention provides a space debris removal method and system. When an aerostat floats to the stratosphere, a controller controls a laser generator to continuously emit lasers multiple times, and guides each laser emission from the laser generator to a laser refractor via a laser guide tube. The controller controls a rotation mechanism to drive the laser refractor based on real-time first satellite positioning data of the aerostat and second satellite positioning data of the target space debris, adjusting the laser refraction angle of the laser refractor corresponding to each laser emission from the laser generator. The laser refractor refracts each laser emission from the laser generator, thereby changing the orbit of the target space debris through the refracted laser light, thereby lowering the perigee altitude of the target space debris and achieving its removal. The present invention can alleviate problems existing in existing laser space debris removal technologies.

Description

Technical Field

[0001] The present invention relates to the technical field of space debris removal, and in particular to a space debris removal method and system. Background Art

[0002] In recent years, the removal of space debris in low-Earth orbit has garnered increasing attention. Laser space debris removal technology is considered a viable solution. Currently, laser space debris removal technologies are primarily categorized as space-based and ground-based lasers, both of which have been fully validated in experiments. Space-based lasers are primarily deployed on space stations for small-scale removal of small pieces of space debris. Due to their high precision, rapid response, and relatively long range, space-based lasers can assist space stations in avoiding and removing smaller pieces of space debris, ensuring their safe operation. However, due to their high energy consumption and maintenance requirements, space-based lasers are limited to space stations and are not widely used for satellite safety. While ground-based lasers have been proven feasible in principle, due to atmospheric scattering and refraction, most laboratories for ground-based laser space debris removal are located at high altitudes and are only able to achieve limited removal effectiveness within a narrow range of true anomaly angles, making widespread application difficult and their efficiency in space debris removal relatively low.

[0003] In summary, the current laser space debris removal technology has the following main problems:

[0004] (1) High manufacturing costs, mainly reflected in the high cost of building laboratories and clearance facilities in high-altitude areas, and the high cost of manufacturing and launching spacecraft into low-Earth orbit.

[0005] (2) The efficiency of space debris removal is low, which is mainly reflected in the following aspects: the energy dissipation of ground-based lasers in the atmosphere is large, and the true anomaly angle for normal operation is small; the range in which space-based lasers can work normally is small.

[0006] (3) Low economic benefits, mainly reflected in the following: the current laser space debris removal system cannot be commercialized and is difficult to maintain its own operation.

[0007] (4) Maintenance difficulties, mainly reflected in the following aspects: ground-based lasers often use high-power chemical lasers due to the reduction of laser energy by the atmosphere, which are difficult to maintain and operate continuously in high-altitude areas; space-based lasers have high maintenance costs and are difficult to maintain in a space environment.

[0008] (5) The working environment is harsh, mainly reflected in the following: ground-based lasers have high requirements for altitude and weather conditions. Summary of the Invention

[0009] In view of this, an object of the present invention is to provide a space debris removal method and system to alleviate the above-mentioned problems existing in the existing laser space debris removal technology.

[0010] In a first aspect, an embodiment of the present invention provides a method for removing space debris, which is applied to a space debris removal system, wherein the space debris removal system includes an aerostat, a laser generator, a laser refraction assembly, a rigid laser guide tube and a controller; the rigid laser guide tube is arranged on the aerostat in a vertical direction, a first mounting surface is provided at the lower end of the rigid laser guide tube, and a second mounting surface is provided at the upper end of the rigid laser guide tube; the laser generator and the controller are both fixedly mounted on the first mounting surface, and the laser emitting end of the laser generator corresponds to the lower end of the rigid laser guide tube; the laser refraction assembly includes a laser refraction mirror and a rotation mechanism; the laser refraction mirror is rotatably mounted on the rotation mechanism; the rotation mechanism is fixedly mounted on the second mounting surface; the controller is respectively connected to the aerostat and the laser generator. and connected to the rotation mechanism; the method comprises: when the aerostat floats to the stratosphere, the controller controls the laser generator to continuously emit lasers for multiple times, and guides the laser emitted by the laser generator each time to the laser refraction mirror through the laser guide tube; the controller obtains first satellite positioning data of the aerostat and second satellite positioning data of the target space debris in real time; the controller controls the rotation mechanism to drive the laser refraction mirror to rotate according to the first satellite positioning data and the second satellite positioning data, so as to adjust the laser refraction angle of the laser refraction mirror corresponding to each laser emission by the laser generator; the laser refraction mirror refracts the laser emitted by the laser generator each time, so as to change the orbit of the target space debris through the refracted laser, thereby reducing the perigee height of the target space debris to achieve the removal of the target space debris.

[0011] In the second aspect, an embodiment of the present invention further provides a space debris removal system, which includes an airship, a laser generator, a laser refraction assembly, a rigid laser guide tube and a controller; the rigid laser guide tube is arranged on the airship in a vertical direction, and a first mounting surface is provided at the lower end of the rigid laser guide tube, and a second mounting surface is provided at the upper end of the rigid laser guide tube; the laser generator and the controller are both fixedly mounted on the first mounting surface, and the laser emitting end of the laser generator corresponds to the lower end of the rigid laser guide tube; the laser refraction assembly includes a laser refraction mirror and a rotating mechanism; the laser refraction mirror is rotatably mounted on the rotating mechanism; the rotating mechanism is fixedly mounted on the second mounting surface; the controller is respectively connected to the airship, the laser generator and the controller. the rotating mechanism is connected; when the aerostat floats to the stratosphere, the controller is used to: control the laser generator to continuously emit lasers for multiple times, and guide the laser emitted by the laser generator each time to the laser refraction mirror through the laser guide tube; obtain the first satellite positioning data of the aerostat and the second satellite positioning data of the target space debris in real time; control the rotating mechanism to drive the laser refraction mirror to rotate according to the first satellite positioning data and the second satellite positioning data, so as to adjust the laser refraction angle of the laser refraction mirror corresponding to each laser emission by the laser generator; the laser refraction mirror is used to: refract the laser emitted by the laser generator each time, so as to change the orbit of the target space debris through the refracted laser, thereby reducing the perigee height of the target space debris to achieve the removal of the target space debris.

[0012] An embodiment of the present invention provides a space debris removal method and system. The space debris removal system includes an aerostat, a laser generator, a laser refraction assembly, a rigid laser guide tube, and a controller. The rigid laser guide tube is vertically arranged on the aerostat. The laser generator and the controller are both fixedly mounted on a first mounting surface located at the lower end of the rigid laser guide tube, and the laser emitting end of the laser generator corresponds to the lower end of the rigid laser guide tube. The laser refraction assembly includes a laser refraction mirror and a rotation mechanism. The laser refraction mirror is rotatably mounted on the rotation mechanism. The rotation mechanism is fixedly mounted on a second mounting surface located at the upper end of the rigid laser guide tube. The controller is respectively connected to the aerostat, the laser generator, and the rotation mechanism. When the aerostat floats to the stratosphere, a controller controls the laser generator to continuously emit lasers multiple times, and guides each laser emission from the laser generator to the laser refraction mirror through a laser guide tube. The controller obtains the aerostat's first satellite positioning data and the target space debris' second satellite positioning data in real time. The controller controls the rotation mechanism to drive the laser refraction mirror to rotate based on the first and second satellite positioning data, thereby adjusting the laser refraction angle of the laser refraction mirror corresponding to each laser emission from the laser generator. The laser refraction mirror refracts each laser emission from the laser generator, thereby changing the orbit of the target space debris through the refracted laser light, thereby lowering the perigee altitude of the target space debris and achieving the removal of the target space debris. Using the above technology, by installing the laser emitter and laser refraction mirror on the aerostat and adjusting the laser refraction angle to achieve space debris removal using the principle of laser refraction, the system has low manufacturing, operation, and maintenance costs, a wide range of space debris removal capabilities, high space debris removal efficiency, and low operating environment requirements.

[0013] Other features and advantages of the present invention will be described in the following description, and in part will become apparent from the description, or understood by practicing the present invention. The purposes and other advantages of the present invention are realized and obtained by the structures particularly pointed out in the description, claims and drawings.

[0014] In order to make the above-mentioned objects, features and advantages of the present invention more obvious and easy to understand, preferred embodiments are given below and described in detail with reference to the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] In order to more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the specific embodiments or the description of the prior art. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0016] Figure 1 This is a schematic structural diagram of a space debris removal system according to an embodiment of the present invention;

[0017] Figure 2 This is a structural example diagram of a space debris removal system according to an embodiment of the present invention;

[0018] Figure 3 This is an example diagram of the process of releasing a binary super-pressure balloon in an embodiment of the present invention;

[0019] Figure 4 This is an example diagram of the recovery-maintenance-reissue process of the space debris removal system in an embodiment of the present invention;

[0020] Figure 5 The figure is a flow chart of a method for clearing space debris according to an embodiment of the present invention. DETAILED DESCRIPTION

[0021] To make the objectives, technical solutions, and advantages of the embodiments of the present invention more clear, the technical solutions of the present invention will be clearly and completely described below in conjunction with the embodiments. Obviously, the embodiments described are only part of the embodiments of the present invention, not all of them. All other embodiments obtained by ordinary technicians in this field based on the embodiments of the present invention without making any creative efforts shall fall within the scope of protection of the present invention.

[0022] Currently, existing laser space debris removal technology suffers from numerous issues, including high manufacturing costs, low space debris removal efficiency, low economic benefits, difficult maintenance, and harsh working environments. Based on these issues, the present invention provides a space debris removal method and system that can alleviate these issues with existing laser space debris removal technology.

[0023] To facilitate understanding of this embodiment, a space debris removal system disclosed in an embodiment of the present invention is first introduced in detail. Figure 1 As shown, the space debris removal system may include an aerostat 2, a laser generator 4, a laser refraction assembly 1, a rigid laser guide tube 3 and a controller (not shown in the figure); the rigid laser guide tube 3 is arranged on the aerostat 2 in a vertical direction, and a first mounting surface 5 is provided at the lower end of the rigid laser guide tube 3, and a second mounting surface 6 is provided at the upper end of the rigid laser guide tube 3; the laser generator 4 and the controller are both fixedly mounted on the first mounting surface 5, and the laser emitting end of the laser generator 4 corresponds to the lower end of the rigid laser guide tube 3; the laser refraction assembly 1 may include a laser refraction mirror 11 and a rotating mechanism 12; the laser refraction mirror 11 can be rotatably mounted on the rotating mechanism 12; the rotating mechanism 12 is fixedly mounted on the second mounting surface 6; the controller is respectively connected to the aerostat 2, the laser generator 4 and the rotating mechanism 12.

[0024] Among them, the rigid laser guide tube 3 can support the overall structure of the airship 2, and can also provide an installation position for the laser generator 4 and the controller by setting a first installation surface 5, and provide an installation position for the rotating mechanism 12 by setting a second installation surface 6. The layout of the installation positions can also maintain the stability of the entire space debris removal system during the floating process.

[0025] In actual application, in order to further ensure the stability of the above-mentioned space debris removal system during the floating process, additional counterweights may be added to the above-mentioned space debris removal system.

[0026] The above-mentioned controller can be used to: control the laser generator 4 to emit lasers continuously multiple times, and guide the laser 401 emitted by the laser generator 4 each time to the laser refraction mirror 11 through the laser guide tube 3; obtain the first satellite positioning data of the airship 2 and the second satellite positioning data of the target space debris in real time; control the rotation mechanism 12 to drive the laser refraction mirror 11 to rotate according to the first satellite positioning data and the second satellite positioning data, so as to adjust the laser refraction angle of the laser refraction mirror 11 corresponding to each laser 401 emitted by the laser generator 4.

[0027] The laser refraction mirror 11 can be used to refract the laser 401 emitted by the laser generator 4 each time, so as to change the orbit of the target space debris through the refracted laser 1101, thereby reducing the perigee height of the target space debris to achieve the removal of the target space debris.

[0028] An embodiment of the present invention provides a space debris removal system. When an aerostat floats to the stratosphere, a controller controls a laser generator to continuously emit lasers multiple times, and guides each laser emission from the laser generator to a laser refraction mirror via a laser guide tube. The controller obtains the aerostat's first satellite positioning data and the target space debris' second satellite positioning data in real time. Based on the first and second satellite positioning data, the controller controls a rotation mechanism to drive the laser refraction mirror to rotate, thereby adjusting the laser refraction angle of the laser refraction mirror corresponding to each laser emission from the laser generator. The laser refraction mirror refracts each laser emission from the laser generator, thereby changing the orbit of the target space debris through the refracted laser light, thereby lowering the perigee altitude of the target space debris and achieving removal of the target space debris. Using the above technology, the laser emitter and laser refraction mirror are installed on the aerostat, and space debris removal is achieved by utilizing the principle of laser refraction by adjusting the laser refraction angle. The system has low manufacturing, operation, and maintenance costs, a wide range of space debris removal capabilities, high space debris removal efficiency, and low requirements for the working environment.

[0029] As a possible implementation, the controller may also be used to calculate the expected laser refraction angle value of the laser refraction mirror 11 based on the first satellite positioning data and the second satellite positioning data before each laser emission by the laser generator 4, and send a corresponding control signal to the rotation mechanism 12 based on the expected laser refraction angle value, so that the rotation mechanism 12 drives the laser refraction mirror 11 to rotate to the target position corresponding to the expected laser refraction angle value after receiving the control signal.

[0030] Illustratively, the first satellite positioning data may include the position coordinates of the aerostat 2, and the second satellite positioning data may include the position coordinates of the target space debris. At a certain moment, after obtaining the position coordinates of the aerostat 2 and the target space debris at that moment from the satellite, the controller may calculate an expected laser refraction angle value of the laser refraction mirror 11 at that moment based on the two position coordinates (used to indicate that if the laser refraction angle of the laser refraction mirror 11 is at the expected laser refraction angle value, the refracted laser light will hit the target space debris). The controller then calculates the difference between the expected laser refraction angle value and the laser refraction angle of the laser refraction mirror 11 at that moment, and generates a corresponding control signal based on the difference and sends it to the rotation mechanism 12, so that after receiving the control signal, the rotation mechanism 12 drives the laser refraction mirror 11 to rotate to a target position where the laser refraction angle of the laser refraction mirror 11 is at the expected laser refraction angle value, thereby causing the laser light refracted by the laser refraction mirror 11 to hit the target space debris, thereby changing the orbit of the target space debris, thereby lowering the perigee altitude of the target space debris, and achieving the removal of the target space debris.

[0031] The principle of changing the orbit of target space debris by refracting laser light is mainly as follows: when the refracted laser light hits the target space debris, it will generate a normal impulse acting on the target space debris in the direction of the tangent of the orbit of the target space debris. Under the action of this normal impulse, the orbit of the target space debris is changed, the perigee height of the target space debris is lowered, and the process of the target space debris falling into the atmosphere and burning is accelerated, thereby achieving the purpose of clearing the target space debris.

[0032] As a possible embodiment, the aerostat 2 may include an aerostat body and a height adjustment device; the height adjustment device is connected to the controller. Based on this, the controller can also be used to control the height adjustment device to adjust the floating height of the aerostat 2.

[0033] In actual application, the height adjustment device can usually adopt a combination of an air pump and a valve, and the specific combination is not limited here.

[0034] As a possible embodiment, the aerostat 2 may further include an energy device and a propulsion device. The energy device is fixedly mounted on the first mounting surface 5 and is respectively connected to the laser generator 4, the rotation mechanism 12, the controller, the altitude adjustment device, and the propulsion device; the propulsion device is also connected to the controller. Therefore, the energy device can be used to respectively power the laser generator 4, the rotation mechanism 12, the controller, the altitude adjustment device, and the propulsion device. The controller can also be used to control the propulsion device to propel the aerostat 2 into the air.

[0035] In actual application, the above-mentioned propulsion device may generally include a power motor, a propeller, a steering mechanism, a braking mechanism, etc., which is not limited.

[0036] As a possible embodiment, the energy device may include an energy storage battery pack and an inclined solar panel; the solar panel is connected to the energy storage battery pack. Accordingly, the solar panel can be used to convert collected solar energy into electricity to charge the energy storage battery pack and, during the day, use this electricity to power the laser generator 4, the rotation mechanism 12, the controller, the height adjustment device, and the propulsion device. The energy storage battery can be used to power the laser generator 4, the rotation mechanism 12, the controller, the height adjustment device, and the propulsion device during the night when it is in a discharged state.

[0037] In actual application, in order to avoid as much as possible that the discharge capacity of the above-mentioned energy storage battery is insufficient to support the normal operation of the electrical equipment at night, the inclined installation angle of the above-mentioned solar panel can be set to be greater than 10° and not greater than 40°.

[0038] As a possible embodiment, the aerostat 2 may further include a recovery device connected to the controller. Based on this, the controller may also be configured to control the recovery device to adjust the overall density of the aerostat 2, thereby achieving a descent of the aerostat 2.

[0039] For ease of understanding, the above-mentioned space debris removal system is described below by taking the aerostat using a binary superpressure balloon as an example.

[0040] See also Figure 2As shown, the space debris removal system may include a binary super-pressure balloon 20, a laser generator 4, a laser refraction assembly 1, a rigid laser guide tube 3 and a controller (not shown in the figure); the rigid laser guide tube 3 passes through the binary super-pressure balloon 20 in a vertical direction, and a first mounting surface 5 for fixing the bottom of the binary super-pressure balloon 20 is provided at the lower end of the rigid laser guide tube 3, and a second mounting surface 6 for fixing the top of the binary super-pressure balloon 20 is provided at the upper end of the rigid laser guide tube 3; the laser generator 4 and the controller are both fixedly mounted on the first mounting surface 5, and the laser emitting end of the laser generator 4 corresponds to the lower end of the rigid laser guide tube 3; the laser refraction assembly 1 may include a laser refraction mirror 11 and a rotating mechanism 12; the laser refraction mirror 11 can be rotatably mounted on the rotating mechanism 12; the rotating mechanism 12 is fixedly mounted on the second mounting surface 6; the controller is respectively connected to the binary super-pressure balloon 20, the laser generator 4 and the rotating mechanism 12.

[0041] above Figure 2 In the illustrated space debris removal system, the binary super-pressure balloon 20 includes a sphere and an altitude adjustment device. The sphere includes a main airbag 21 and a secondary airbag 22. The secondary airbag 22 is located within the main airbag 21. The secondary airbag 22 is inflated with helium, while the main airbag 21 is inflated with air. The altitude adjustment device is located at the bottom of the main airbag 21 and is connected to a controller. Based on this, the controller can also be used to control the altitude adjustment device to pressurize or expel air into or out of the main airbag 21 to adjust the floating altitude of the binary super-pressure balloon 20.

[0042] above Figure 2 In the illustrated space debris removal system, the binary superpressure balloon 20 may further include a pod and a propulsion device. The pod is connected to the first mounting surface 5 via a rigid connecting rod. The pod may include an energy device. The energy device is respectively connected to the laser generator 4, the rotating mechanism 12, the controller, the altitude adjustment device, and the propulsion device. The propulsion device is mounted on the rigid connecting rod and is connected to the controller. The energy device may include an energy storage battery pack and an inclined solar panel (with an inclined mounting angle greater than 10° and not greater than 40°). The solar panel is connected to the energy storage battery pack via a maximum power point tracking (MPPT) solar charge controller. Based on this, the energy device can be used to: convert solar energy collected by the solar panel into electrical energy, and use the electrical energy to charge the energy storage battery via the MPPT solar charge controller; use the electrical energy to power the laser generator 4, the rotating mechanism 12, the controller, the altitude adjustment device, and the propulsion device during the day; and use the energy storage battery to power the laser generator 4, the rotating mechanism 12, the controller, the altitude adjustment device, and the propulsion device at night when the energy storage battery is in a discharged state. The controller can also be used to control the propulsion device to drive the binary super pressure balloon 20 into the air.

[0043] above Figure 2 In the illustrated space debris removal system, the binary super-pressure balloon 20 may also include a recovery device located on top of the secondary balloon 22 and connected to a controller. The controller can also be used to control the recovery device to discharge helium from the secondary balloon 22 to adjust the overall density of the binary super-pressure balloon 20, thereby enabling the balloon 20 to descend.

[0044] In actual application, the above-mentioned recovery device can generally include auxiliary tools (such as cutters, etc.) for creating a deflation port in the binary super-pressure balloon 20 and a parachute, etc., which are not limited to this.

[0045] above Figure 2 The working principle of the space debris removal system shown mainly includes: before the laser generator 4 emits a laser each time, the controller first obtains the position coordinates of the binary superpressure balloon 20 and the target space debris at that moment from the satellite and calculates the expected laser refraction angle value of the laser refraction mirror 11 at that moment based on the two position coordinates, and then calculates the difference between the expected laser refraction angle value and the laser refraction angle size of the laser refraction mirror 11 at that moment and generates a corresponding control signal based on the difference and sends it to the rotating mechanism 12 to drive the laser refraction mirror 11 to rotate through the rotating mechanism 12; in this way, the controller can control the laser generator 4 to emit a laser each time and refract it through the laser refraction mirror 11 to hit the target space debris, thereby reducing the perigee height of the target space debris by changing the orbit of the target space debris to achieve the removal of the target space debris.

[0046] In actual application, the above Figure 2 The space debris removal system shown can be put into operation according to the typical binary superpressure balloon launch process. Figure 3 As shown in the figure, the typical binary super pressure balloon launch process mainly includes: installing the auxiliary balloon; inflating the auxiliary balloon; lifting the sphere of the binary super pressure balloon; inflating the main balloon; sealing the main balloon; partially deploying the main balloon; the sphere of the binary super pressure balloon is lifted into the air; the auxiliary balloon falls off; the main balloon is fully deployed; the binary super pressure balloon reaches the predetermined height; the movement of the binary super pressure balloon tends to be stable; and the space debris removal system is put into operation.

[0047] After the above-mentioned space debris removal system has finished its work, it can also be recycled, maintained, and redistributed to maximize the efficiency of the use of the above-mentioned space debris removal system. Figure 4As shown, one cycle of the space debris removal system's recovery, maintenance, and redistribution process primarily includes: landing the space debris removal system; positioning the space debris removal system; on-site maintenance of the space debris removal system; redistribution of the space debris removal system; and commissioning of the space debris removal system. After completing one cycle of the recovery, maintenance, and redistribution process, the next cycle of the recovery, maintenance, and redistribution process can be performed.

[0048] The above-mentioned space debris removal system combines laser emission with an aerostat flying in the stratosphere, thereby achieving the goals of reducing manufacturing costs, improving space debris removal efficiency, increasing economic benefits, optimizing maintenance processes, and improving the fault tolerance of the working environment.

[0049] Existing laser space debris removal systems often cannot cover their operating costs, which means they can only be used in scientific experiments or on important spacecraft (such as the International Space Station) to ensure their safety. Within the Earth's atmosphere, the space around 30 km above the surface has not been fully utilized by humans and has high utilization value. The working environment of the above-mentioned space debris removal system in the embodiment of the present invention (i.e., the stratosphere) is located precisely within this space. By carrying various equipment used for scientific research, commercial services, etc., the above-mentioned space debris removal system can generate additional economic benefits to share the relevant costs. In addition, the manufacturing cost of the aerostat is relatively low, and the relevant costs of the above-mentioned space debris removal system can be further reduced in large-scale production.

[0050] The stratosphere and above only account for about 25% of the total mass of the Earth's atmosphere. The laser energy loss caused by scattering and refraction in the atmosphere is greatly reduced, which allows the above-mentioned space debris removal system working at this altitude to have a larger space debris range.

[0051] The weather conditions in the stratosphere are good, which is suitable for solar panels to work during the day, and the laser generator uses electricity as energy, which provides the possibility for the above-mentioned space debris removal system to replenish energy at high altitudes.

[0052] Based on the above-mentioned space debris removal system, an embodiment of the present invention further provides a space debris removal method, which is applied to the above-mentioned space debris removal system. Figure 5 As shown, the method may include the following steps:

[0053] Step S502: When the aerostat floats to the stratosphere, the controller controls the laser generator to emit laser light multiple times in succession, and guides the laser light emitted by the laser generator each time to the laser refraction mirror through the laser guide tube.

[0054] Step S504: the controller acquires the first satellite positioning data of the aerostat and the second satellite positioning data of the target space debris in real time.

[0055] In step S506 , the controller controls the rotation mechanism to drive the laser refraction mirror to rotate according to the first satellite positioning data and the second satellite positioning data, so as to adjust the laser refraction angle of the laser refraction mirror corresponding to each laser emission by the laser generator.

[0056] In step S508, the laser refraction mirror refracts the laser light emitted by the laser generator each time, so as to change the orbit of the target space debris through the refracted laser light, thereby reducing the perigee height of the target space debris to achieve the removal of the target space debris.

[0057] In the above-mentioned space debris removal method, when the aerostat floats to the stratosphere, the controller controls the laser generator to emit lasers continuously for multiple times, and guides the laser emitted by the laser generator each time to the laser refraction mirror through the laser guide tube; the controller controls the rotation mechanism to drive the laser refraction mirror to rotate according to the first satellite positioning data of the aerostat and the second satellite positioning data of the target space debris obtained in real time, so as to adjust the laser refraction angle of the laser refraction mirror corresponding to each laser emission of the laser generator; the laser refraction mirror refracts the laser emitted by the laser generator each time, so as to change the orbit of the target space debris through the refracted laser, thereby reducing the perigee height of the target space debris to achieve the removal of the target space debris, which can alleviate the problems of high manufacturing cost, low space debris removal efficiency, low economic benefit, difficult maintenance, and harsh working environment existing in the existing laser space debris removal technology.

[0058] As a possible implementation manner, the controller in the above step S506 controls the rotation mechanism to drive the laser refraction mirror to rotate according to the first satellite positioning data and the second satellite positioning data, which may include: the controller calculates the expected laser refraction angle value of the laser refraction mirror according to the first satellite positioning data and the second satellite positioning data before the laser generator emits the laser each time, and sends a corresponding control signal to the rotation mechanism according to the expected laser refraction angle value, so that the rotation mechanism drives the laser refraction mirror to rotate to the target position corresponding to the expected laser refraction angle value after receiving the control signal.

[0059] As a possible implementation manner, the above-mentioned space debris removal method may further include: the controller controlling the height adjustment device to adjust the floating height of the aerostat.

[0060] As a possible implementation, the above-mentioned space debris removal method may further include: the energy device supplies power to the laser generator, the rotation mechanism, the controller, the height adjustment device and the propulsion device respectively; and the controller controls the propulsion device to drive the airship into the air.

[0061] As a possible implementation manner, the step of the energy device supplying power to the laser generator, the rotating mechanism, the controller, the height adjustment device and the propulsion device respectively may include: the solar panel converts the collected solar energy into electrical energy, and uses the electrical energy to charge the energy storage battery through a maximum power point tracking solar charging controller, and uses the electrical energy to supply power to the laser generator, the rotating mechanism, the controller, the height adjustment device and the propulsion device respectively during the day; the energy storage battery supplies power to the laser generator, the rotating mechanism, the controller, the height adjustment device and the propulsion device respectively when it is in a discharged state at night.

[0062] As a possible implementation, the inclined installation angle of the solar panel is greater than 10° and not greater than 40°.

[0063] As a possible implementation, the above-mentioned space debris removal method may further include: the controller controlling the recovery device to adjust the overall density of the aerostat, thereby achieving the descent of the aerostat.

[0064] The space debris removal method provided in the embodiment of the present invention has the same implementation principle and technical effects as the aforementioned space debris removal system embodiment. For the sake of brief description, for matters not mentioned in the method embodiment, reference can be made to the corresponding content in the aforementioned system embodiment.

[0065] Unless otherwise specifically stated, the relative steps, numerical expressions and values of the components and steps set forth in these embodiments do not limit the scope of the present invention.

[0066] If the functions are implemented in the form of software functional units and sold or used as independent products, they can be stored in a non-volatile computer-readable storage medium that is executable by a processor. Based on this understanding, the technical solution of the present invention, or the part that contributes to the prior art, or the part of the technical solution, can be embodied in the form of a software product. The computer software product is stored in a storage medium and includes several instructions for enabling a computer device (which can be a personal computer, server, or network device, etc.) to execute all or part of the steps of the method described in each embodiment of the present invention. The aforementioned storage medium includes various media that can store program codes, such as a USB flash drive, a mobile hard disk, a read-only memory (ROM), a random access memory (RAM), a magnetic disk, or an optical disk.

[0067] In the description of the present invention, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings and are intended solely to facilitate and simplify the description of the present invention. They are not intended to indicate or imply that the devices or components referred to must have, be constructed, or operate in a specific orientation, and therefore should not be construed as limitations on the present invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0068] Finally, it should be noted that the above-described embodiments are only specific implementation methods of the present invention, which are used to illustrate the technical solutions of the present invention, rather than to limit them. The scope of protection of the present invention is not limited thereto. Although the present invention has been described in detail with reference to the above-described embodiments, those skilled in the art should understand that any person skilled in the art can modify or easily conceive of changes to the technical solutions described in the above-described embodiments within the technical scope disclosed by the present invention, or replace some of the technical features therein with equivalents. Such modifications, changes, or replacements do not deviate from the spirit and scope of the technical solutions of the embodiments of the present invention, and should be included in the scope of protection of the present invention. Therefore, the scope of protection of the present invention shall be subject to the scope of protection of the claims.

Claims

1. A space debris removal method, characterized in that: The method is applied to a space debris removal system, which includes an aerostat, a laser generator, a laser refraction assembly, a rigid laser guide tube, and a controller; the rigid laser guide tube is arranged on the aerostat in a vertical direction, a first mounting surface is provided at the lower end of the rigid laser guide tube, and a second mounting surface is provided at the upper end of the rigid laser guide tube; the laser generator and the controller are both fixedly mounted on the first mounting surface, and the laser emitting end of the laser generator corresponds to the lower end of the rigid laser guide tube; the laser refraction assembly includes a laser refraction mirror and a rotation mechanism; the laser refraction mirror is rotatably mounted on the rotation mechanism; the rotation mechanism is fixedly mounted on the second mounting surface; the controller is connected to the aerostat, the laser generator, and the rotation mechanism, respectively; the method includes: When the aerostat floats to the stratosphere, the controller controls the laser generator to continuously emit laser light multiple times, and guides the laser light emitted by the laser generator each time to the laser refraction mirror through the laser guide tube; The controller acquires first satellite positioning data of the aerostat and second satellite positioning data of the target space debris in real time; The controller controls the rotating mechanism to drive the laser refraction mirror to rotate according to the first satellite positioning data and the second satellite positioning data, so as to adjust the laser refraction angle of the laser refraction mirror corresponding to each laser emission of the laser generator; The laser refraction mirror refracts the laser light emitted by the laser generator each time, so as to change the orbit of the target space debris through the refracted laser light, thereby reducing the perigee height of the target space debris to achieve the removal of the target space debris.

2. The method according to claim 1, characterized in that The aerostat comprises an aerostat body and a height adjustment device; the height adjustment device is connected to the controller; and the method further comprises: The controller controls the height adjustment device to adjust the floating height of the aerostat.

3. The method according to claim 2, characterized in that The aerostat further includes an energy device and a propulsion device; the energy device is fixedly mounted on the first mounting surface; the energy device is respectively connected to the laser generator, the rotation mechanism, the controller, the height adjustment device and the propulsion device; The propulsion device is connected to the controller; the method further includes: The energy device respectively supplies power to the laser generator, the rotating mechanism, the controller, the height adjustment device and the propulsion device; The controller controls the propulsion device to drive the aerostat to ascend.

4. The method according to claim 3, characterized in that The energy device includes an energy storage battery pack and a solar panel installed on an inclined surface; the solar panel is connected to the energy storage battery pack; the energy device supplies power to the laser generator, the rotating mechanism, the controller, the height adjustment device and the propulsion device, respectively, and includes: The solar panel converts the collected solar energy into electrical energy to charge the energy storage battery, and uses the electrical energy to power the laser generator, the rotating mechanism, the controller, the height adjustment device and the propulsion device during the day; When the energy storage battery is in a discharging state at night, it supplies power to the laser generator, the rotating mechanism, the controller, the height adjustment device and the propulsion device respectively.

5. The method according to claim 4, characterized in that The inclined installation angle of the solar cell panel is greater than 10° and not greater than 40°.

6. The method according to claim 1, characterized in that The controller controls the rotation mechanism to drive the laser refraction mirror to rotate according to the first satellite positioning data and the second satellite positioning data, including: Before the laser generator emits laser each time, the controller calculates the expected laser refraction angle value of the laser refraction mirror based on the first satellite positioning data and the second satellite positioning data, and sends a corresponding control signal to the rotation mechanism based on the expected laser refraction angle value, so that the rotation mechanism drives the laser refraction mirror to rotate to the target position corresponding to the expected laser refraction angle value after receiving the control signal.

7. The method according to claim 2, characterized in that The aerostat further includes a recovery device; the recovery device is connected to the controller; and the method further includes: The controller controls the recovery device to adjust the overall density of the aerostat, thereby achieving the descent of the aerostat.

8. A space debris removal system, characterized in that: The space debris removal system includes an aerostat, a laser generator, a laser refraction assembly, a rigid laser guide tube and a controller; the rigid laser guide tube is arranged on the aerostat in a vertical direction, a first mounting surface is provided at the lower end of the rigid laser guide tube, and a second mounting surface is provided at the upper end of the rigid laser guide tube; the laser generator and the controller are both fixedly mounted on the first mounting surface, and the laser emitting end of the laser generator corresponds to the lower end of the rigid laser guide tube; the laser refraction assembly includes a laser refraction mirror and a rotation mechanism; the laser refraction mirror is rotatably mounted on the rotation mechanism; the rotation mechanism is fixedly mounted on the second mounting surface; the controller is respectively connected to the aerostat, the laser generator and the rotation mechanism; When the aerostat floats to the stratosphere, the controller is configured to: control the laser generator to continuously emit lasers multiple times, and guide the laser emitted by the laser generator each time to the laser refraction mirror through the laser guide tube; obtain first satellite positioning data of the aerostat and second satellite positioning data of the target space debris in real time; and control the rotation mechanism to drive the laser refraction mirror to rotate according to the first satellite positioning data and the second satellite positioning data, so as to adjust the laser refraction angle of the laser refraction mirror corresponding to each laser emission by the laser generator; The laser refraction mirror is used to refract the laser light emitted by the laser generator each time, so as to change the orbit of the target space debris through the refracted laser light, thereby reducing the perigee height of the target space debris to achieve the removal of the target space debris.

9. The system according to claim 8, characterized in that The aerostat includes an aerostat body and a height adjustment device; the height adjustment device is connected to the controller; and the controller is further configured to control the height adjustment device to adjust the floating height of the aerostat.

10. The system according to claim 8, wherein: The controller is also used to: before the laser generator emits laser each time, calculate the expected laser refraction angle value of the laser refraction mirror based on the first satellite positioning data and the second satellite positioning data, and send a corresponding control signal to the rotation mechanism based on the expected laser refraction angle value, so that the rotation mechanism drives the laser refraction mirror to rotate to the target position corresponding to the expected laser refraction angle value after receiving the control signal.

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