A lunar resource rotating throwing device

Abstract

The application discloses a device for rotating, throwing and returning lunar surface resources, which comprises a rotating arm, a combination body fixed at the front end of the rotating arm through a first separation locking mechanism, a magnetic suspension driving system for providing rotating power and suspension force for the rotating arm, and a returner in the combination body. The first separation locking mechanism releases the combination body to achieve the throwing purpose after the combination body obtains the lunar escape velocity. The device adopts the magnetic suspension driving to provide the acceleration module with acceleration driving force and suspension force, so that the combination body is suspended on the orbit, the acceleration process has no friction loss, and the low-temperature and high-vacuum environment of the lunar surface can be fully utilized to reduce the working power consumption. In addition, the device adopts a unique rotating arm structure, which can bear most of the centrifugal overload during the rotating and accelerating process, the upper limit of the bearable overload can be more than 10,000 g, the system size (radius≯100 m) is greatly reduced, and the returner can be directly accelerated to the lunar escape velocity.

Description

Technical Field

[0001] This invention relates to the field of deep space exploration technology, specifically to a lunar surface resource rotation ejection and return device. Background Technology

[0002] In the process of lunar resource development, returning lunar resources to Earth is one of the most crucial steps. Launching a return capsule carrying lunar resources from the lunar surface using traditional technologies consumes a large amount of chemical propellant. Transporting this propellant from Earth to the Moon is extremely costly, significantly reducing the economic value of returning lunar resources. To reduce the use of chemical propellant, global research has been conducted on technologies that utilize lunar resources to power the return capsule launch, yielding some results. However, these researches all have varying degrees of shortcomings, as documented in the following publicly available documents:

[0003] The document, with publication number CN113235736A, is titled "A Lunar Base Capable of In-situ Utilization of Lunar Resources." It primarily designs a lunar surface electromagnetic launch system powered by a nuclear power source, focusing on in-situ resource utilization and lacking the capability to transport lunar resources back to Earth.

[0004] The document, with publication number CN116198744A, is titled "A Lunar Electromagnetic Launch System Powered by a Nuclear Power Source." It primarily designs a lunar electromagnetic launch system powered by a nuclear power source, employing a linear acceleration method. The system is large-scale and has high requirements for its power system.

[0005] The publication number is CN109573104B, and the title is "Manned Lunar Electromagnetic Launch Acceleration Orbit". This document mainly proposes a manned lunar electromagnetic launch acceleration orbit scheme, which adopts a circular acceleration method. The system is huge in scale, with a rotation radius of 2km. It can withstand relatively small centrifugal overloads, and the centrifugal overloads are all borne by the orbit. It can only accelerate to about one-quarter of the lunar return velocity.

[0006] In summary, the aforementioned return units suffer from high power consumption, high requirements for track load capacity, and large system size during acceleration. Summary of the Invention

[0007] The technical problem to be solved by the present invention is that the existing technology has shortcomings such as high power consumption, high requirements for track bearing capacity and large system scale during the acceleration process of the return unit.

[0008] The present invention solves the above-mentioned technical problems through the following technical means:

[0009] A lunar resource rotary ejection and return device includes a rotary arm, with a combined assembly fixed to the front end of the rotary arm via a first separation and locking mechanism. A magnetic levitation drive system provides rotational power and levitation force to the rotary arm, enabling the combined assembly to achieve lunar escape velocity. The first separation and locking mechanism then releases the combined assembly, achieving the ejection purpose. A returner is located within the combined assembly. This invention employs magnetic levitation drive, providing acceleration driving force to the acceleration module while simultaneously providing levitation force, allowing the combined assembly (comprising the returner and a skid, etc.) to levitate on a track. The acceleration process is friction-free, and this solution fully utilizes the low temperature and high vacuum environment of the lunar surface, reducing power consumption. Furthermore, this invention employs a unique rotary arm structure that bears most of the centrifugal overload during rotational acceleration, with an overload capacity exceeding 10,000 g, significantly reducing the system size (radius ≤ 100 meters) and enabling direct acceleration of the returner to above lunar escape velocity.

[0010] Furthermore, the magnetic levitation drive system includes a magnetic levitation drive track, with a linear auxiliary correction section and a braking section sequentially arranged along the tangent direction from the launch point of the magnetic levitation drive track; the magnetic levitation drive track includes a track body and a magnetic levitation drive module; the track body is circular, providing an installation base for the magnetic levitation drive module; the rotating arm has a counterweight section from the axis of rotation to one end and a rotation section from the axis of rotation to the other end; the counterweight section is fixed with a first superconducting magnet, which, together with the magnetic levitation drive module, constitutes a first superconducting linear motor.

[0011] Furthermore, a second superconducting magnet is fixed at the end of the rotating section, and the second superconducting magnet and the magnetic levitation drive module form a second superconducting linear motor.

[0012] Furthermore, the magnetic levitation drive system includes a drive track and a suspension track; the diameter of the drive track is smaller than that of the suspension track, and the drive track and the suspension track are concentric circular tracks; a straight auxiliary correction section and a braking section are arranged sequentially from the tangent direction of the launch point of the suspension track; the rotation axis of the rotating arm is suspended at the center of the drive track; the assembly is suspended on the suspension track.

[0013] Furthermore, the drive track includes a track body and a magnetic levitation drive module; the track body provides an installation base for the magnetic levitation drive module; the rotating arm has a counterweight section at one end and a rotation section at the other end; the counterweight section is fixed with a first superconducting magnet, which together with the magnetic levitation drive track constitutes a first superconducting linear motor.

[0014] Furthermore, a second superconducting magnet is fixed in the drive track of the rotating section, forming a second superconducting linear motor with the magnetic levitation drive module.

[0015] Furthermore, a third superconducting magnet is fixed at the end of the rotating section, and the third superconducting magnet and the magnetic levitation module fixed in the levitation track constitute a levitation mechanism.

[0016] Furthermore, it also includes a balancing unit, which includes a slider and a groove opened along the length of the rotating segment. The slider and the groove are slidably engaged. In the initial state, the slider is fixed to one end of the groove near the rotating arm shaft by a second separation locking mechanism, and the slider and the assembly are released simultaneously.

[0017] Furthermore, the assembly includes a skid and a third separation and locking mechanism; the third separation and locking mechanism is fixed to the skid, and the skid is restrained by a first separation and locking mechanism; the return device is restrained by the third separation and locking mechanism; and the third superconducting magnet is fixed to the bottom of the skid.

[0018] Furthermore, once the combined vehicle reaches the predetermined speed, the control system determines the release timing based on the real-time lunar return trajectory parameters and releases it rapidly at a set angle. When the launch speed is low or the separation time accuracy control of the first separation locking mechanism meets the accuracy requirements of the launch angle, the swing arm and the skid do not separate. That is, the first separation locking mechanism does not perform a separation action during the working process and remains locked. When the return vehicle accelerates to the required speed, the control system controls the third separation locking mechanism to execute the separation command at a set angle and directly launch the return vehicle. Subsequently, the cantilever carrying the skid decelerates to a standstill using the electromagnetic force of the magnetic levitation drive track.

[0019] When the combined body's speed is too high, the first separation and locking mechanism releases the combined body; when the combined body enters the straight correction section and completes the launch angle correction, the third separation and locking mechanism releases the returner, the returner enters the lunar-Earth return orbit at high speed, and the combined body of the third superconducting magnet, the skid, and the third separation and locking mechanism enters the braking section and decelerates to a standstill.

[0020] The advantages of this invention are:

[0021] This invention employs a superconducting linear motor to provide acceleration driving force and levitation force to the acceleration module, allowing the acceleration module (a combination of the returner and the skid, etc.) to levitate on the track. The acceleration process is friction-free, and this design fully utilizes the low temperature and high vacuum environment of the lunar surface, reducing power consumption. Furthermore, this invention uses a spiral arm structure to bear most of the centrifugal overload during rotational acceleration, with an overload capacity exceeding 10,000 g, significantly reducing the system size (radius ≤ 100 meters) and enabling the returner to be directly accelerated to above lunar escape velocity.

[0022] This invention features a launch window on the lunar surface that allows for launch at any time, and the launch time and frequency can be adjusted according to the lunar resource extraction situation.

[0023] This invention can accelerate the return capsule to a speed exceeding the lunar escape velocity, at which point it can be launched into a lunar-Earth return orbit and return directly to Earth. In this state, the return capsule can be designed to carry a small amount of propellant for attitude and orbital corrections. Alternatively, the return capsule can be accelerated to a certain speed (ΔV lower than the lunar escape velocity) before being launched. In this state, the return capsule must carry sufficient propellant to supplement some of the velocity increment ΔV and for attitude and orbital corrections.

[0024] The weight of the rotatable, accelerating returner of this invention is adjustable within a certain range as needed.

[0025] This invention has a significant impact on the mode of transportation between Earth and the Moon, and can effectively reduce the cost of transporting lunar resources back to Earth. Its core electromagnetic levitation rotational launch technology is based on existing magnetic levitation flywheel technology and superconducting magnetic levitation technology, making full use of the lunar surface environment to form an overall implementation plan for lunar resource development. It has a high input-output ratio and no technical bottlenecks. Attached Figure Description

[0026] Figure 1 This is a top view of the lunar resource rotational ejection and return device in Embodiment 1 of the present invention;

[0027] Figure 2 for Figure 1 Enlarged structural diagram of section A in the middle;

[0028] Figure 3 for Figure 1 Enlarged structural diagram of section B;

[0029] Figure 4 This is a schematic diagram of the cross-sectional structure of the drive track 41 in Embodiments 1 and 2 of the present invention;

[0030] Figure 5 These are schematic diagrams of the track support mechanism in Embodiments 1 and 2 of the present invention;

[0031] Figure 6 This is a schematic diagram of the structure of the assembly in Embodiment 1 of the present invention;

[0032] Figure 7 These are the modified schematic diagrams for Embodiments 1 and 2 of the present invention;

[0033] Figure 8 This is a top view of the lunar resource rotational ejection and return device in Embodiment 2 of the present invention;

[0034] Figure 9 This is a schematic diagram of the cross-sectional structure of the combined body and the suspended track in Embodiment 2 of the present invention. Detailed Implementation

[0035] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below in conjunction with the embodiments of the present invention. Obviously, the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0036] This embodiment describes a lunar resource rotary ejection and return device, including a rotary arm 1 and a combined body 2 fixed to the front end of the rotary arm 1 by a first separation and locking mechanism 3. A magnetic levitation drive system 4 provides rotational driving force and levitation force to the rotary arm 1, enabling the combined body 2 to achieve lunar escape velocity. Afterward, the first separation and locking mechanism 3 releases the combined body 2, achieving the ejection purpose. A returner 6 is located within the combined body 2. This device utilizes lunar energy sources such as solar cell arrays and lunar space nuclear power sources to provide electrical energy, which is stored in an energy storage system. The energy storage system transmits the electrical energy to the magnetic levitation drive system 4 through a converter, and the magnetic levitation drive system 4 provides rotational power and levitation force to the rotary arm 1. This embodiment provides three schemes, as follows:

[0037] Example 1

[0038] like Figure 1 As shown, in this embodiment, the magnetic levitation drive system 4 includes a magnetic levitation drive track 41, and a straight-line auxiliary correction section 42 and a braking section 43 are sequentially arranged along the tangential direction from the launch point of the drive track 41; as shown... Figure 4 As shown, the drive track 41 includes a track body 411 and a magnetic levitation drive module 412; the track body 411 is ring-shaped and provides an installation base for the magnetic levitation drive module 412.

[0039] The rotating arm 1 has a counterweight section 11 from the pivot to one end, and a rotating section 12 from the pivot to the other end. For example... Figure 2 As shown, a first superconducting magnet 413 is fixed to the counterweight section 11, forming a first superconducting linear motor with the magnetic levitation drive module 412. To increase the driving force, a second superconducting magnet 414 is also fixed to the end of the rotating section 12 in this embodiment, as shown. Figure 3 As shown, the second superconducting magnet 414 and the magnetic levitation drive module 412 form a second superconducting linear motor.

[0040] like Figure 1As shown, to compensate for the dynamic imbalance after the combined body 2 is released and to maintain the dynamic balance of the high-speed rotating arm 1, this embodiment also includes a balancing unit. The balancing unit includes a groove 121 along the length of the rotating section 12 of the arm 1, and a slider 122 slidingly fitted within the groove 121. Before the combined body 2 is released, the slider 122 is bound to the end of the groove 121 near the rotating shaft by a second separation locking mechanism (not shown in the figure). When the control system controls the release of the projectile combined body 2, it simultaneously releases the slider 122. Under the action of a strong centrifugal force, the slider 122 moves rapidly outward from the arm 1. When the combined body 2 is released, the center of mass of the arm 1 deviates from the axis. At this time, the slider 122 moves outward, which can quickly adjust the center of mass of the arm 1 back to its original position, ensuring the rotational dynamic balance of the arm 1. The weight, moving distance, and installation position of the slider 122 can be obtained based on actual dynamic balance calculations, and are mainly affected by parameters such as the weight of the return device 6. In this embodiment, the rotating arm 1 is made of high-performance mechanical materials, such as carbon fiber, to ensure that it has high mechanical strength and low structural mass, meeting the requirements of withstanding ultra-high centrifugal overload under high-speed rotation. The counterweight section 11 is mainly used for balancing the rotating arm 1, ensuring that it maintains a stable dynamic balance during high-speed rotation. During a single launch, the center of mass position and weight of the counterweight section 11 can be adjusted according to the actual changes in the weight of the return device 6 carried on one side of the rotating section 12, maintaining the dynamic balance between the rotating section 12 and the counterweight section 11. The rotating arm 1 uses a magnetic levitation main shaft 10 to suspend it above the magnetic levitation drive track 41, avoiding mechanical friction during high-speed rotation, improving system lifespan, and reducing energy consumption.

[0041] In this embodiment, as Figure 5As shown, the track body 411 comprises a load-bearing beam 4111 and a track support mechanism 4112. The track support mechanism 4112 installs the load-bearing beam 4111 onto the lunar regolith. Multiple track support mechanisms 4112 can be installed around the track body 411 according to mechanical requirements. In this embodiment, the track support mechanism 4112 includes a drilling section and a support section. The drilling section uses a spiral drilling method. To increase the grip on the lunar regolith, this embodiment uses two spiral drill bits. Additionally, an adhesive injection method can be used to further enhance the mechanical strength between the mechanism and the lunar regolith. The support section is detachably fixed above the drilling section, exposed outside the lunar regolith. The main body of the support section uses a pneumatic or electric telescopic rod. A locking device (a three-jaw locking device) for fixing the track body 411 is provided at the top of the telescopic rod, and the bottom of the telescopic rod is fixed to the drilling section. This embodiment uses a telescopic track support mechanism 4112, which allows for adjustment of the launch pitch angle within a certain range by uniformly adjusting multiple track support mechanisms 4112 around the track. In this embodiment, the structure of the track support mechanism 4112 is relatively conventional and is not limited to the above description. As long as it can satisfy the fixing of the track body 411 and the adjustment of the launch pitch angle, it is acceptable.

[0042] like Figure 6 As shown, the assembly 2 includes a pry bar 21 and a third separation locking mechanism 22; the third separation locking mechanism 22 is fixed on the pry bar 21, and the pry bar 21 is bound to the front end of the rotating section 12 of the rotating arm 1 by the first separation locking mechanism 3; the return device 6 is bound to the pry bar 21 by the third separation locking mechanism 22.

[0043] In this embodiment, multiple straight correction sections 42 and braking sections 43 (which are suspended modules and do not have driving force) can be selectively constructed at suitable locations around the drive track 41, tangentially positioned according to the actual launch angle requirements of different tasks. The straight correction section 42 is mainly used to correct the launch angle of the assembly 2. Its correction principle is as follows: Figure 7 As shown, the directional deviation of the combined body 2 is corrected by two pairs of lateral magnetic constraints F between the suspension module and the superconducting magnet, a conventional technology in the aerospace field. The braking section 43 is mainly used for braking and deceleration of the combined body 2. The combined body 2 contains enormous kinetic energy; to ensure safe and reliable deceleration, the braking section 43 employs a composite braking method to prevent safety hazards caused by the failure of a single braking system. Its main braking system is an eddy current braking system, which is frictionless and consumes no electrical energy. Simultaneously, it is equipped with auxiliary braking systems such as mechanical brakes as an emergency backup in case of eddy current braking failure, ensuring reliable deceleration and stopping of the high-speed combined body 2 and maintaining system safety. In this embodiment, both eddy current braking and mechanical braking are conventional technologies in the aerospace field.

[0044] In this embodiment, the magnetic levitation drive system 4, the rotating arm 1, multiple separation and locking mechanisms, and the maintenance system are all modularly designed according to the requirements of the heavy-duty launch vehicle fairing envelope and lunar surface assembly. The various components of the device are transported to the lunar surface and assembled using a heavy-duty launch vehicle. In this embodiment, all separation and locking mechanisms are commonly used equipment in the aerospace field. The fixing methods between the superconducting magnet and the rotating arm, and between the separation and locking mechanisms and their corresponding components, are not unique; fixing methods suitable for the lunar environment and operational requirements can be selected, such as bolt fixing or snap-locking.

[0045] In this embodiment, the maintenance system includes an energy storage system, a thermal control subsystem, a system protective cover, and a maintenance robot, etc., to provide the device with power, thermal control, protection, operating status monitoring, and equipment maintenance.

[0046] The energy storage system can preferably be a high-temperature superconducting energy storage device, which is suitable for working in the low-temperature environment of the lunar surface and can use the same cooling system as the superconducting magnet of the superconducting motor.

[0047] The thermal control subsystem provides a suitable temperature environment for the lunar resource magnetic levitation rotary ejection and return device. Based on the lunar surface thermal radiation characteristics, it provides a low-temperature environment for superconducting energy storage and superconducting magnets, thereby reducing the power consumption of the cooling system.

[0048] The system's protective shield provides protection during the rotational acceleration process of the lunar resource magnetic levitation rotary ejection and return device. Working in conjunction with the thermal control subsystem, it reduces the impact of solar radiation on the device's operating temperature and prevents lunar debris from entering. The shield preferably employs a thin-shell structure to reduce weight and improve efficiency. The system's protective shield is made of suitable materials, capable of protecting the system from damage caused by space rays, high-energy particle radiation, and micrometeorite bombardment.

[0049] The maintenance robot provides maintenance services for the lunar resource magnetic levitation rotary launcher and return device. Equipped with maintenance tools and a small robotic arm, it can be used to fasten the mechanical structure and repair or replace parts of the device.

[0050] The specific working principle of this embodiment is as follows: The first separation and locking mechanism 3 is used to lock the assembly 2 and the rotating arm 1 during high-speed rotation. When the assembly 2 reaches a predetermined speed, the control system determines the release timing based on the real-time lunar return trajectory parameters and releases quickly at a set angle. When the launch speed is low or the separation time accuracy control of the first separation and locking mechanism 3 meets the accuracy requirements of the launch angle, the rotating arm 1 and the skid 21 do not separate. That is, the first separation and locking mechanism 3 does not perform separation action during the working process and always remains locked. When the returner 6 accelerates to the required speed, the control system controls the third separation and locking mechanism 22 to execute the separation command at a set angle and directly launch the returner 6. Subsequently, the skid 21 and the rotating arm 1 decelerate together on the magnetic levitation drive track 41 using electromagnetic force to stop. At this time, it is not necessary to use the straight auxiliary correction section 42 and the braking section 43 to assist the launch. The launch yaw angle can be adjusted by controlling the separation timing of the first separation and locking mechanism 3 and the third separation and locking mechanism 22 through the control system.

[0051] The third separation and locking mechanism 22 is used for the separation and locking of the skid 21 and the returner 6. It locks during rotational acceleration. When the combined body 2's speed is too high, the control system controls the first separation and locking mechanism 3 to release the combined body 2. When the combined body 2 enters the straight-line correction section 42 and completes the launch angle correction, the third separation and locking mechanism 22 releases the returner 6. The returner 6 enters the lunar-Earth return orbit at high speed. The combined body 2, consisting of the second superconducting magnet 414 (in the case of Example 1) or the third superconducting magnet 51 (in the case of Example 2), the skid 22, and the third separation and locking mechanism 22, enters the braking section 43 and decelerates to a standstill.

[0052] This embodiment employs a superconducting linear motor to provide acceleration and levitation force for the combined body 2, allowing it to levitate on the track. The acceleration process is friction-free, and this design fully utilizes the low temperature and high vacuum environment of the lunar surface, reducing power consumption. Furthermore, this embodiment uses a rotating arm 1 structure to bear most of the centrifugal overload during rotational acceleration, with an overload capacity exceeding 10,000 g, significantly reducing the system size (radius ≤ 100 meters) and enabling direct acceleration of the returner 6 to above lunar escape velocity. This embodiment also features a launch window on the lunar surface, allowing for adjustments to launch time and frequency based on lunar resource extraction conditions.

[0053] In this embodiment, the return capsule 6 can be rotated and accelerated to a speed exceeding the lunar escape velocity. At this point, the return capsule 6 is launched into a lunar-Earth return orbit and returns directly to Earth. In this state, the return capsule 6 only needs to carry a small amount of propellant for attitude and orbital corrections. Alternatively, the return capsule 6 can be rotated and accelerated to a certain speed (ΔV lower than the lunar escape velocity) before launch. In this state, the return capsule 6 needs to carry sufficient propellant to supplement some of the velocity increment ΔV and for attitude and orbital corrections.

[0054] The weight of the rotatable, accelerating returner 6 in this embodiment can be adjusted within a certain range according to requirements.

[0055] Example 2

[0056] The difference between this embodiment and embodiment 1 is that, Figure 8 , Figure 9 As shown, the size and radius of the magnetic levitation drive track 4 are reduced, while a new magnetic levitation track 5 is set in the original position of the magnetic levitation drive track 4, with both forming a concentric circle structure. Specifically:

[0057] The diameter of the magnetic levitation track 5 is larger than that of the magnetic levitation drive track 41, and they are concentrically arranged. A first superconducting magnet 413 is fixed to the end of the counterweight section 11, forming a first superconducting linear motor with the magnetic levitation drive module 412. A second superconducting magnet 414 is fixed in the middle of the rotating section 12, forming a second superconducting linear motor with the magnetic levitation drive module 412. Of course, the second superconducting magnet 414 can be selectively set or not set according to the drive size requirements. Figure 8 The illustration shows the configuration of the second superconducting magnet 414. A third superconducting magnet 51 is fixed to the front end of the rotating segment 12, and combined with the magnetic levitation module 52 in the magnetic levitation track 5, the end of the rotating segment 12 is in a suspended state. The assembly 2 is located at the end of the rotating segment 12 and suspended above the magnetic levitation track 5. In this embodiment, the magnetic levitation main shaft 10 of the rotating arm 1 is located above the center of the magnetic levitation drive track 41. In this embodiment, the rotating arm 1 has four points with upward levitation force, further improving stability during rotation. Of course, more levitation points can be designed as needed, such as side arms extending from the rotating arm 1 with superconducting magnets fixed to the side walls, combined with existing magnetic levitation tracks or magnetic levitation drive tracks.

[0058] The other operating principles of this embodiment are the same as those of Embodiment 1. Compared with Embodiment 1, the advantages are as follows: First, the length of the counterweight arm 11 of the rotating arm 1 is reduced, thus reducing some of the mass and the size of the rotating arm 1; Second, the size of the magnetic levitation drive track 4 is reduced, and a new magnetic levitation track 5 is set at the original position of the magnetic levitation drive track. The unit mass of the magnetic levitation drive track 4 is more than twice that of the magnetic levitation track 5. Therefore, by reducing the size of the magnetic levitation drive track 4, the levitation function and the drive function are executed separately, which can effectively reduce the mass of the track system; Third, the inner and outer double track design allows the rotating arm 1 to have an upward levitation force at four points, further improving the stability of the rotation process.

[0059] Example 3

[0060] The difference between this embodiment and Embodiment 2 is that a magnetic levitation drive track is used instead of a magnetic levitation track, giving the rotating arm three drive points and stronger rotational acceleration capability. Other advantages are the same as in Embodiment 2.

[0061] The above embodiments are only used to illustrate the technical solutions of the present invention, and are not intended to limit it. Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A lunar resource rotary ejection and return device, characterized in that, The assembly includes a rotating arm (1), and a combined body (2) is fixed to the front end of the rotating arm (1) by a first separation locking mechanism (3). The rotating arm (1) bears the centrifugal force during the rotation acceleration process of the combined body (2). The magnetic levitation drive system (4) provides rotational power and levitation force to the rotating arm (1), so that the combined body (2) obtains the lunar escape velocity. Then, the first separation locking mechanism (3) releases the combined body (2) to achieve the purpose of launching. The return device (6) is located in the combined body (2). The magnetic levitation drive system (4) includes a drive track (41) and a suspension track (5). The diameter of the drive track (41) is smaller than that of the suspension track (5), and it is a concentric ring track with the suspension track (5). A straight auxiliary correction section (42) and a braking section (43) are arranged sequentially from the tangent direction of the launch point of the suspension track (5). The rotating shaft of the rotating arm (1) is suspended at the center of the drive track (41). The combined body (2) is suspended on the suspension track (5).

2. The lunar resource rotary ejection and return device according to claim 1, characterized in that, The drive track (41) includes a track body (411) and a magnetic levitation drive module (412); the track body (411) provides an installation base for the magnetic levitation drive module (412); the rotating arm (1) has a counterweight section (11) from the pivot to one end and a rotating section (12) from the pivot to the other end; the counterweight section (11) is fixed with a first superconducting magnet (413), which together with the magnetic levitation drive track (41) constitutes a first superconducting linear motor.

3. The lunar resource rotary ejection and return device according to claim 2, characterized in that, A second superconducting magnet is fixed in the rotating section (12) on the drive track (41), forming a second superconducting linear motor with the magnetic levitation drive module (412).

4. A lunar resource rotary ejection and return device according to any one of claims 1 to 3, characterized in that, A third superconducting magnet (51) is fixed at the end of the rotating section (12), and the third superconducting magnet (51) and the magnetic levitation module (52) fixed in the levitation track (5) constitute a levitation mechanism.

5. A lunar resource rotary ejection and return device according to any one of claims 1 to 3, characterized in that, It also includes a balancing unit, which includes a slider (122) and a groove (121) opened along the length of the rotating section (12). The slider (122) and the groove (121) are slidably engaged. In the initial state, the slider (122) is fixed to one end of the groove (121) near the rotating shaft of the rotating arm (1) by a second separation locking mechanism. The slider (122) and the assembly (2) are released at the same time.

6. The lunar resource rotary ejection and return device according to claim 4, characterized in that, The assembly (2) includes a skid (21) and a third separation locking mechanism (22); the third separation locking mechanism (22) is fixed on the skid (21), and the skid (21) is restrained by the first separation locking mechanism (3); the return device (6) is restrained by the third separation locking mechanism (22); the third superconducting magnet (51) is fixed at the bottom of the skid (21).

7. A lunar resource rotary ejection and return device according to claim 6, characterized in that, When the combined body (2) reaches the predetermined speed, the control system determines the release timing based on the real-time lunar return trajectory parameters and releases it quickly at the set angle. When the launch speed is low or the separation time accuracy control of the first separation locking mechanism meets the accuracy requirements of the launch angle, the rotating arm (1) and the skid (21) do not separate. That is, the first separation locking mechanism (3) no longer performs separation action during the working process and always remains locked. When the returner (6) accelerates to the speed required, the control system controls the third separation locking mechanism (22) to execute the separation command at the set angle and directly launch the returner (6). Afterward, the skid (21) and the rotating arm (1) together decelerate to a stop using electromagnetic force on the magnetic levitation drive track (41).

8. A lunar resource rotary ejection and return device according to claim 7, characterized in that, When the combined body (2) has too high a speed, the first separation locking mechanism (3) releases the combined body (2); when the combined body (2) enters the straight correction section (42) and completes the launch angle correction, the third separation locking mechanism (22) releases the returner (6), the returner (6) enters the lunar return orbit at high speed, and the combined body (2) of the third superconducting magnet (51), the skid (21) and the third separation locking mechanism (22) enters the braking section (43) and decelerates to a standstill.

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