Method for transferring material between the earth and the moon based on a cluster of spacecraft in a distant retrograde orbit family

Abstract

The application provides a kind of method and system for transporting material between the earth and the moon based on a cluster of spacecrafts in distant retrograde orbit family.The method comprises: obtaining lunar material;plasma processing the lunar material to obtain target plasma material;launching the target plasma material from the moon to a first cluster of spacecrafts, which operates in a DRO orbit family;the first cluster of spacecrafts receives the target plasma material and transports it to a second cluster of spacecrafts, which operates in a geocentric orbit;and the second cluster of spacecrafts receives the target plasma material.Using this method and system for transporting material between the earth and the moon can form a transportation channel, significantly reducing the cost of transporting material between the earth and the moon and improving the efficiency of transportation.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of spaceflight, and in particular to a method and system for transferring lunar material based on a spacecraft cluster in a distant retrograde orbit family. BACKGROUND

[0002] The moon is rich in mineral resources such as titanium, thorium, uranium, helium, and new minerals not found on Earth. Exploiting and utilizing lunar mineral resources can effectively address global issues such as depletion of Earth's resources and environmental damage. Therefore, the Earth-moon space has become the focus of a new round of global space development competition. To achieve resource transportation between the moon and the Earth, it is essential to build a cargo transportation channel in the Earth-moon space. The traditional method is to use cargo ships to transfer materials in the Earth-moon space. However, the use of launch vehicles to launch ships has significant limitations in terms of launch cost, transportation period, transportation efficiency, and payload capacity.

[0003] The distant retrograde orbit (DRO) family in the Earth-moon space is a stable lunar distant retrograde orbit. Spacecrafts do not need to maintain their orbits and can operate stably in orbit for a long time. With the development of large-scale constellation technology, launch vehicle recovery technology, and satellite mass production technology, satellite launch costs have been reduced, making it possible to build large-scale transportation constellations in DRO orbits with different resonance ratios.

[0004] Scientific research has found that plasma materials are difficult to quench in the cosmic space with a thin gas. The present application combines the distant retrograde orbit family in the Earth-moon space and the characteristics of plasma materials to propose a method and system for transferring lunar material based on a spacecraft cluster in a distant retrograde orbit family. SUMMARY

[0005] The present application aims to provide a method and system for transferring lunar material at a low cost.

[0006] To solve the above technical problems, the present application provides a method for transferring lunar material based on a spacecraft cluster in a distant retrograde orbit family, which includes: obtaining lunar material; plasma processing the lunar material to obtain target plasma material; launching the target plasma material from the moon to a first spacecraft cluster operating in a DRO orbit family; the first spacecraft cluster receives the target plasma material and transfers it to a second spacecraft cluster operating in a lunar-earth cruise orbit; and the second spacecraft cluster receives the target plasma material.

[0007] In an embodiment of the present application, the first spacecraft cluster comprises a plurality of first spacecrafts, and the DRO orbit family comprises a plurality of DRO orbits at different altitudes around the Moon, each of the DRO orbits having at least one first spacecraft; the step of receiving the target plasma material by the first spacecraft cluster comprises: at least one first spacecraft on the DRO orbit closest to the Moon receives the target plasma material, and transmits the target plasma material to at least one first spacecraft on the next layer of DRO orbits, and the target plasma material is transmitted layer by layer until at least one first spacecraft on the DRO orbit farthest from the Moon.

[0008] In an embodiment of the present application, after the at least one first spacecraft receives the target plasma material, the method further comprises: storing the target plasma material; and when the at least one first spacecraft on the current DRO orbit and at least one first spacecraft on the next layer of DRO orbits have rendezvous transmission conditions, transmitting the target plasma material through space to the at least one first spacecraft on the next layer of DRO orbits.

[0009] In an embodiment of the present application, the second spacecraft cluster comprises at least one second spacecraft, and the step of transmitting the target plasma material to the second spacecraft cluster comprises: storing the target plasma material on at least one first spacecraft on the DRO orbit farthest from the Moon; and when the at least one first spacecraft on the DRO orbit farthest from the Moon and the second spacecraft cluster have rendezvous transmission conditions, transmitting the target plasma material through space to at least one second spacecraft in the second spacecraft cluster.

[0010] In an embodiment of the present application, the second spacecraft cluster comprises at least one second spacecraft, and the step of transmitting the target plasma material to the second spacecraft cluster comprises: storing the target plasma material on at least one first spacecraft on the current DRO orbit; and when the at least one first spacecraft on the current DRO orbit and the second spacecraft cluster have rendezvous transmission conditions, transmitting the target plasma material through space to at least one second spacecraft in the second spacecraft cluster.

[0011] In an embodiment of the present application, the step of launching the target plasma material from the Moon to the first spacecraft cluster comprises: continuously launching the target plasma material to at least one first spacecraft on the DRO orbit closest to the Moon.

[0012] In an embodiment of the present application, the method further comprises: transporting the received target plasma material to the Earth by the second spacecraft cluster.

[0013] In an embodiment of the present application, the lunar material includes mineral material on the moon.

[0014] To solve the above technical problems, the present application further provides a lunar material transfer system based on a distant retrograde orbit (DRO) cluster of spacecrafts, comprising: a lunar material plasma device arranged on the moon, configured to collect lunar material and plasmaize the lunar material to obtain target plasma material; a lunar material transfer device arranged on the moon, configured to transfer the target plasma material to a first spacecraft cluster; the first spacecraft cluster, which operates on a DRO orbit cluster, is configured to receive the target plasma material and transfer the target plasma material to a second spacecraft cluster; and the second spacecraft cluster, which operates on a lunar-earth cruise orbit, is configured to receive the target plasma material from the first spacecraft cluster.

[0015] In an embodiment of the present application, the first spacecraft cluster includes a plurality of first spacecrafts, the DRO orbit cluster includes a plurality of DRO orbits at different altitudes around the moon, each of the DRO orbits has at least one first spacecraft, at least one first spacecraft on a current DRO orbit and at least one first spacecraft on a next DRO orbit have at least one DRO transfer window meeting a rendezvous transfer condition, and the target plasma material is suitable for being spatially transferred from the at least one first spacecraft on the current DRO orbit to the at least one first spacecraft on the next DRO orbit in the DRO transfer window.

[0016] In an embodiment of the present application, the second spacecraft cluster includes at least one second spacecraft, at least one first spacecraft on a current DRO orbit and the at least one second spacecraft have at least one cruise transfer window meeting a rendezvous transfer condition, and the target plasma material is suitable for being spatially transferred from the at least one first spacecraft on the current DRO orbit to the at least one second spacecraft in the cruise transfer window.

[0017] The lunar material transfer method and system of the present application use the first spacecraft cluster on the DRO orbit as a distributed transfer node, and combine with the second spacecraft cluster on the lunar-earth cruise orbit, to realize long-term communication between the earth and the moon in the lunar-earth space, so as to realize the transfer of the target plasma material between the nodes, form a lunar-earth material transport channel, and no longer rely on cargo ships for material transfer, thereby greatly reducing the cost of material transfer in the lunar-earth space and improving the transport efficiency. BRIEF DESCRIPTION OF DRAWINGS

[0018] The accompanying drawings are included to provide a further understanding of the present application and are incorporated in and constitute a part of this application, illustrate embodiments of the present application and together with the description serve to explain the principles of the present application. In the drawings:

[0019] Figure 1 is an exemplary flow chart of a method for transferring material between the Moon and the Earth based on a spacecraft cluster of a distant retrograde orbit family according to an embodiment of the present application;

[0020] Figure 2 is a block diagram of a system for transferring material between the Moon and the Earth based on a spacecraft cluster of a distant retrograde orbit family according to an embodiment of the present application;

[0021] Figure 3 is an orbit diagram in a method for transferring material between the Moon and the Earth according to an embodiment of the present application;

[0022] Figure 4 is a diagram of a transfer path of target plasma material in a method for transferring material between the Moon and the Earth according to an embodiment of the present application. DETAILED DESCRIPTION

[0023] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the following will briefly introduce the drawings needed to be used in the embodiments description. Obviously, the drawings in the following description are only some examples or embodiments of the present application, and for those skilled in the art, the present application can be applied to other similar scenarios without creative labor on the basis of these drawings. Unless the context clearly indicates otherwise or otherwise stated, the same reference numbers in the drawings represent the same structure or operation.

[0024] As shown in the present application and claims, unless the context clearly indicates otherwise or otherwise stated, the words "one", "a", "an", and / or "the" do not specifically refer to the singular, but also include the plural. Generally speaking, the terms "comprise" and "include" only indicate the inclusion of the steps and elements explicitly identified, and these steps and elements do not constitute an exclusive list, and the method or device can also include other steps or elements.

[0025] Unless otherwise specifically stated, the relative arrangement, numerical expressions, and values ​​of the components and steps described in these embodiments do not limit the scope of this application. It should also be understood that, for ease of description, the dimensions of the various parts shown in the drawings are not drawn to actual scale. Techniques, methods, and devices known to those skilled in the art may not be discussed in detail, but where appropriate, such techniques, methods, and devices should be considered part of the specification. In all examples shown and discussed herein, any specific values ​​should be interpreted as merely exemplary and not as limitations. Therefore, other examples of exemplary embodiments may have different values. It should be noted that similar reference numerals and letters in the following drawings denote similar items; therefore, once an item is defined in one drawing, it need not be further discussed in subsequent drawings.

[0026] Furthermore, it should be noted that the use of terms such as "first" and "second" to define components is merely for the purpose of distinguishing the corresponding components. Unless otherwise stated, these terms have no special meaning and therefore should not be construed as limiting the scope of protection of this application. In addition, although the terminology used in this application is selected from commonly known and used terms, some terms mentioned in this application's specification may have been chosen by the applicant according to his or her judgment, and their detailed meanings are explained in the relevant sections of this description. Moreover, this application should be understood not only through the actual terms used, but also through the meaning implied by each term.

[0027] Flowcharts are used in this application to illustrate the operations performed by the system according to embodiments of this application. It should be understood that the preceding or following operations are not necessarily performed in exact order. Instead, various steps can be processed in reverse order or simultaneously. Furthermore, other operations may be added to these processes, or one or more steps may be removed from these processes.

[0028] The method and system for Earth-Moon material transfer based on a long-distance reverse orbital spacecraft cluster in this application are used for material transfer between Earth and the Moon, mainly for transferring lunar material to Earth, thereby facilitating human research and development of lunar material on Earth.

[0029] Figure 1 This is an exemplary flowchart of a lunar mass transfer method based on a long-distance reverse orbital spacecraft cluster according to an embodiment of this application. (Reference) Figure 1 The Earth-Moon material transport method of this embodiment includes the following steps:

[0030] Step S110: Obtain lunar material;

[0031] Step S120: Plasmonize lunar material to obtain the target plasma material;

[0032] Step S130: launching the target plasma substance from the moon to a first spacecraft cluster, the first spacecraft cluster operating on a DRO orbit family;

[0033] Step S140: the first spacecraft cluster receiving the target plasma substance and transferring the target plasma substance to a second spacecraft cluster, the second spacecraft cluster operating on a cislunar tour orbit; and

[0034] Step S150: the second spacecraft cluster receiving the target plasma substance.

[0035] The steps S110-S150 are described in detail below in combination with the accompanying drawings.

[0036] In step S110, the present application does not limit how to obtain the moon substance. In some embodiments, the moon substance can be excavated and obtained by a device launched to the moon by a human being, such as a lunar rover.

[0037] Figure 2 is a block diagram of a cislunar substance transfer system based on a distant retrograde orbit family spacecraft cluster according to an embodiment of the present application. The cislunar substance transfer system 200 can be used to perform the cislunar substance transfer method of the present application, and thus the description of the present application can be used to describe the cislunar substance transfer method and the cislunar substance transfer system of the present application at the same time. Referring to Figure 2 The cislunar substance transfer system 200 includes a moon substance plasma device 210, a moon substance transfer device 220, a first spacecraft cluster 230, and a second spacecraft cluster 240. The moon substance plasma device 210 is arranged on the moon and is used to collect moon substance and plasma the moon substance to obtain target plasma substance; the moon substance transfer device 220 is arranged on the moon and is used to transfer the target plasma substance to the first spacecraft cluster; the first spacecraft cluster 230 operates on a DRO orbit family, and the first spacecraft cluster 230 is used to receive the target plasma substance and transfer the target plasma substance to the second spacecraft cluster 240; the second spacecraft cluster 240 operates on a cislunar tour orbit, and the second spacecraft cluster 240 is used to receive the target plasma substance from the first spacecraft cluster 230.

[0038] In combination with Figure 1 and Figure 2 This step S110 can be performed by the moon substance plasma device 210.

[0039] The present application does not limit what the moon substance is. In some embodiments, the moon substance includes mineral substances on the moon, such as titanium, thorium, uranium, helium, etc. Other known and unknown substances existing on the moon are also moon substances.

[0040] In step S120, the present application does not limit how to plasmaize the lunar material. Any technical means that can plasmaize the material can be used in step S120 to obtain the target plasma material. Scientific research shows that the helium plasma can be generated by using the stellarator fusion device to simulate the continuous nuclear fusion reaction inside the star to heat the helium. This research result can be applied to hydrogen to generate hydrogen plasma, and can be further applied to other materials.

[0041] In combination Figure 1 and Figure 2 Step S120 can be performed by the lunar material plasmaization device 210.

[0042] In step S130, the present application does not limit how to launch the target plasma material from the moon to the first spacecraft cluster.

[0043] Figure 3 is a schematic diagram of an orbit in a lunar-earth material transmission method according to an embodiment of the present application. As shown in Figure 3 The space orbits involved in the present application include a DRO orbit family 310 around the moon 301 and a lunar-earth tour orbit 320. Figure 3 The multiple DRO orbits shown in Figure 3 have gradually increasing heights with the moon 301 as the center, and the DRO orbit closest to the moon 301 is called the near-moon DRO orbit 311, and the DRO orbit farthest from the moon 301 is called the near-earth DRO orbit 330. Assuming that there are n DRO orbits, the DRO orbits 311, 312, 313…31(i)…31(n-1) are included between the near-moon DRO orbit 311 and the near-earth DRO orbit 330. Among them, the DRO orbit 31(n-1) is the second-to-last DRO orbit numbered from the inside out, adjacent to the near-earth DRO orbit 330. As shown in

[0044] As shown in Figure 3 The lunar-earth tour orbit 320 surrounds the earth 302 in the shape of an 8 and intersects with some outer DRO orbits, and has the closest distance to the moon 301 at a perilune 340.

[0045] The spacecraft cluster running on the DRO orbit family is referred to as a first spacecraft cluster, and the spacecraft cluster running on the geocentric orbit is referred to as a second spacecraft cluster. The first spacecraft cluster includes a plurality of first spacecrafts, and each DRO orbit has at least one first spacecraft. The second spacecraft cluster includes at least one second spacecraft. The spacecraft running on the DRO orbit does not need fuel for orbit maintenance, and can achieve long-term, stable and low-cost operation. The number of first spacecraft clusters and the number of first spacecrafts included in the first spacecraft cluster are not limited in the present application. In order to perform the method for transferring lunar material according to the present application, a large-scale distributed lunar constellation based on the distant retrograde orbit family can be constructed at one time, so that there are enough first spacecraft clusters and second spacecraft clusters on the DRO orbit family and the geocentric orbit respectively. The more the number of spacecraft clusters on each orbit shell, the more the number of transfer windows can be increased, and the transfer speed can be improved.

[0046] Suppose that the spacecraft cluster running on the near-moon DRO orbit 311 is the first spacecraft cluster NM1, the spacecraft cluster on the DRO orbit 312 is the first spacecraft cluster NM2, and so on, and the spacecraft cluster running on the DRO orbit 31n is the first spacecraft cluster NM(n-1). Suppose that the spacecraft cluster running on the near-Earth DRO orbit 330 is the first spacecraft cluster NE1.

[0047] In combination Figures 1 to 3 In step S130, the target plasma material can be transferred to the first spacecraft cluster by the lunar material transfer device 220. Specifically, the lunar material transfer device 220 has a launching function for launching the target plasma material into at least one first spacecraft in the first spacecraft cluster. The at least one first spacecraft is provided with a plasma receiving device for receiving the target plasma material. The plasma state material is not easy to quench in the rarefied space, and there is no loss in the transfer process, so it can be completely transferred to the first spacecraft cluster.

[0048] Further, when launching the target plasma material, the launch time is when the lunar material transfer device 220 and any one first spacecraft have a transfer condition, that is, it can be ensured that the launched target plasma material can reach the first spacecraft and be received by the first spacecraft. The first spacecraft here can be a spacecraft in the first spacecraft cluster on the DRO orbit at any altitude.

[0049] In some embodiments, the step of launching the target plasma substance from the moon to the first spacecraft cluster in step S130 comprises continuously launching the target plasma substance to at least one first spacecraft on the DRO orbit closest to the moon. When there are multiple first spacecrafts in the first spacecraft cluster, the on-orbit positions of the multiple first spacecrafts are different, and the on-orbit positions are constantly changing in dynamics, and the moon substance transmission device 220 cannot track and aim at a certain first spacecraft at any time. In these embodiments, by continuously launching the target plasma substance, the multiple first spacecrafts in the first spacecraft cluster can respectively receive a part of the target plasma substance, and more target plasma substance can be obtained.

[0050] In some embodiments, the step of the first spacecraft cluster receiving the target plasma substance in step S140 comprises at least one first spacecraft on the DRO orbit closest to the moon receiving the target plasma substance, and transmitting the target plasma substance to at least one first spacecraft on the next layer of DRO orbit, and the target plasma substance is transmitted layer by layer until at least one first spacecraft on the DRO orbit farthest from the moon.

[0051] Figure 4 FIG. 1 is a schematic diagram of a transmission path of the target plasma substance in a moon-earth substance transmission method according to an embodiment of the present application. As shown in FIG. 1, the moon substance 410 is ionized to obtain the target plasma substance 420, which is first received by at least one first spacecraft in the first spacecraft cluster NM1 on the near-moon DRO orbit 311, and then transmitted by the first spacecraft to at least one first spacecraft in the first spacecraft cluster NM2 on the next layer of DRO orbit 312, and so on, until the target plasma substance 420 is transmitted to the first spacecraft cluster NE1 on the near-earth DRO orbit 330. Figure 3 and Figure 4 As shown in FIG. 1, the moon substance 410 is ionized to obtain the target plasma substance 420, which is first received by at least one first spacecraft in the first spacecraft cluster NM1 on the near-moon DRO orbit 311, and then transmitted by the first spacecraft to at least one first spacecraft in the first spacecraft cluster NM2 on the next layer of DRO orbit 312, and so on, until the target plasma substance 420 is transmitted to the first spacecraft cluster NE1 on the near-earth DRO orbit 330.

[0052] In some embodiments, it is assumed that the spatial transmission limit distance of the plasma substance is h. When transmitting, the target plasma substance can be transmitted from the farthest DRO orbit on the near-moon DRO orbit 311 to a DRO orbit with a distance of h from the near-moon DRO orbit 311. The DRO orbit is not limited to the next layer of DRO orbit 312 adjacent to the near-moon DRO orbit 311.

[0053] In some embodiments, the maximum distance between adjacent layers of DRO orbits participating in the target plasma substance transmission process is set to be equal to the spatial transmission limit distance h of the plasma substance.

[0054] In some embodiments, the step of receiving the target plasma material by the at least one first spacecraft is followed by the steps of:

[0055] Step S141: storing the target plasma material;

[0056] Step S142: transferring the target plasma material from the at least one first spacecraft on the current DRO orbit to the at least one first spacecraft on the next DRO orbit via space when the at least one first spacecraft on the current DRO orbit and the at least one first spacecraft on the next DRO orbit have a rendezvous transfer condition.

[0057] In step S141, the present application does not limit how to store the target plasma material. The first spacecraft has the condition and related equipment to store the target plasma material. In step S142, the rendezvous transfer condition is met, i.e., the two first spacecrafts on adjacent DRO orbits have a DRO transfer window that meets the rendezvous transfer condition, so that the target plasma material can be transferred from the first spacecraft on one DRO orbit to the first spacecraft on the adjacent DRO orbit during the transfer window.

[0058] In some embodiments, the step of transferring the target plasma material to the second spacecraft cluster in step S140 includes:

[0059] Step S143a: storing the target plasma material on the at least one first spacecraft on the DRO orbit farthest from the Moon;

[0060] Step S144a: transferring the target plasma material from the at least one first spacecraft on the DRO orbit farthest from the Moon to the at least one second spacecraft in the second spacecraft cluster via space when the at least one first spacecraft on the DRO orbit farthest from the Moon and the second spacecraft cluster have a rendezvous transfer condition.

[0061] Reference Figure 4 As shown in the above step S143a, the DRO orbit farthest from the Moon is the near-Earth DRO orbit 330, and the target plasma material 420 is transferred layer by layer until at least one first spacecraft in the first spacecraft cluster NE1 on the near-Earth DRO orbit 330, and the target plasma material 420 is stored by the at least one first spacecraft, and in step S144a, when the rendezvous transfer condition is met, the near-Earth DRO orbit 330 and the at least one second spacecraft have a transfer window that meets the rendezvous transfer condition, so that the target plasma material 420 can be transferred to the at least one second spacecraft on the near-Earth DRO orbit 330.

[0062] In other embodiments, the step of transferring the target plasma material to the second spacecraft cluster in step S140 includes:

[0063] Step S143b: The target plasma matter is stored on the at least one first spacecraft on the current DRO orbit.

[0064] Step S144b: When the at least one first spacecraft on the current DRO orbit and the second spacecraft cluster have a rendezvous transfer condition, the target plasma matter is transferred in space to at least one second spacecraft in the second spacecraft cluster.

[0065] The difference between step S143b and step S143a is that the current DRO orbit is not limited to the near-Earth DRO orbit 330, but can be any one of the DRO orbit family 310. In step S144b, when the first spacecraft on any DRO orbit has a transfer condition with a second spacecraft, the stored target plasma matter can be transferred.

[0066] In combination Figure 1 and Figure 4 In step S150, the second spacecraft in the second spacecraft cluster on the cislunar tour orbit 320 receives the target plasma matter. After this step, the target plasma matter can be stored in the second spacecraft for space research, or the target plasma matter can be transferred to the Earth. For example, the second spacecraft storing the target plasma matter transports the target plasma matter to the Earth.

[0067] The present application also proposes a lunar-earth matter transfer system 200, as shown in Figure 2 In some embodiments, the first spacecraft cluster includes a plurality of first spacecrafts, the DRO orbit family includes a plurality of different altitude DRO orbits around the Moon, each DRO orbit has at least one first spacecraft, the at least one first spacecraft on the current DRO orbit and the at least one first spacecraft on the next layer DRO orbit have at least one DRO transfer window meeting the rendezvous transfer condition, and the target plasma matter is suitable for being transferred in space from the at least one first spacecraft on the current DRO orbit to the at least one first spacecraft on the next layer DRO orbit in the DRO transfer window. The second spacecraft cluster includes at least one second spacecraft, the at least one first spacecraft on the current DRO orbit and the at least one second spacecraft have at least one tour transfer window meeting the rendezvous transfer condition, and the target plasma matter is suitable for being transferred in space from the at least one first spacecraft on the current DRO orbit to the at least one second spacecraft in the tour transfer window.

[0068] The method and system for transferring material between the earth and the moon in the application can realize long-term communication between the earth and the moon in the earth-moon space by taking the first spacecraft cluster on the DRO orbit as a distributed transfer node and combining with the second spacecraft cluster on the earth-moon cruise orbit, so as to realize the transfer of target plasma material between each node, form a material transfer channel between the earth and the moon, and no longer rely on cargo ships for material transfer, thereby greatly reducing the cost of material transfer in the earth-moon space and improving the transportation efficiency.

[0069] The foregoing has described the basic concepts, and it is obvious that the above-mentioned disclosure of the application is only used as an example and does not constitute a limitation on the application. Although it is not explicitly stated here, those skilled in the art can make various modifications, improvements and corrections to the application. Such modifications, improvements and corrections are suggested in the application, so such modifications, improvements and corrections still belong to the spirit and scope of the exemplary embodiments of the application.

[0070] At the same time, specific words are used in the application to describe the embodiments of the application. As "one embodiment", "an embodiment", and / or "some embodiments" means a certain feature, structure or characteristic related to at least one embodiment of the application. Therefore, it should be emphasized and noted that the "an embodiment" or "one embodiment" or "an alternative embodiment" mentioned in different places in the specification does not necessarily refer to the same embodiment. In addition, some features, structures or characteristics in one or more embodiments of the application can be properly combined.

[0071] Some embodiments use numbers to describe components, attributes and quantities. It should be understood that such numbers used in the description of the embodiments are modified by the adjectives "about", "approximately" or "generally" in some examples. Unless otherwise stated, "about", "approximately" or "generally" indicates that the number allows a ±20% variation. Accordingly, in some embodiments, the numerical parameters used in the specification and claims are approximations that can vary depending on the desired characteristics of individual embodiments. In some embodiments, numerical parameters should be considered in the context of the number of significant digits and rounding off methods conventionally used by those skilled in the art. Although the numerical ranges and parameters in some embodiments of the application are approximations, in specific embodiments, such numerical values are set forth in a manner that is as precise as reasonably possible.

Claims

1. A method for Earth-Moon material transport based on a long-distance inverse orbital spacecraft cluster, comprising: Obtain lunar materials; The lunar material is subjected to plasma treatment to obtain the target plasma material; The target plasma material was launched from the Moon to the first spacecraft cluster, which was operating in the DRO orbital family. The first spacecraft cluster receives the target plasma material and transfers it to a second spacecraft cluster, which operates in a lunar orbit; and The second spacecraft cluster receives the target plasma material.

2. The Earth-Moon material transport method as described in claim 1, characterized in that, The first spacecraft cluster includes multiple first spacecraft, and the DRO orbital family includes multiple DRO orbits at different altitudes orbiting the Moon, with at least one first spacecraft on each DRO orbit; the step of the first spacecraft cluster receiving the target plasma material includes: at least one first spacecraft located in the DRO orbit closest to the Moon receives the target plasma material and transfers the target plasma material to at least one first spacecraft in the next layer of DRO orbits, and the target plasma material is transferred layer by layer until at least one first spacecraft in the DRO orbit farthest from the Moon.

3. The method for transporting Earth-Moon matter as described in claim 2, characterized in that, After the at least one first spacecraft receives the target plasma material, the method further includes: Store the target plasma material; When at least one first spacecraft in the current DRO orbit and at least one first spacecraft in the next DRO orbit meet the rendezvous and transfer conditions, the target plasma material is transferred through space to at least one first spacecraft in the next DRO orbit.

4. The method for transporting Earth-Moon matter as described in claim 2, characterized in that, The second spacecraft cluster includes at least one second spacecraft, and the step of transferring the target plasma material to the second spacecraft cluster includes: The target plasma material is stored on at least one first spacecraft in the DRO orbit, which is the farthest from the Moon. When at least one first spacecraft in the DRO orbit farthest from the Moon has the conditions for rendezvous and transfer with the second spacecraft cluster, the target plasma material is transferred through space to at least one second spacecraft in the second spacecraft cluster.

5. The method for transporting Earth-Moon matter as described in claim 2, characterized in that, The second spacecraft cluster includes at least one second spacecraft, and the step of transferring the target plasma material to the second spacecraft cluster includes: The target plasma material is stored on at least one first spacecraft in the current DRO orbit; When at least one first spacecraft in the current DRO orbit has the conditions for rendezvous and transfer with the second spacecraft cluster, the target plasma material is transferred through space to at least one second spacecraft in the second spacecraft cluster.

6. The method for transporting Earth-Moon matter as described in claim 1, characterized in that, The steps of launching the target plasma material from the Moon to the first spacecraft cluster include: continuously launching the target plasma material to at least one first spacecraft in the DRO orbit closest to the Moon.

7. The Earth-Moon material transport method as described in claim 1, characterized in that, Also includes: The target plasma material received will be transported to Earth via the second spacecraft cluster.

8. The method for transporting Earth-Moon matter as described in claim 1, characterized in that, The lunar material includes minerals found on the moon.

9. A lunar mass transport system based on a long-range inverse orbital spacecraft cluster, characterized in that, include: A lunar material plasmaification device, installed on the moon, is used to collect lunar material and plasmaify the lunar material to obtain target plasma material; A lunar material transport device, located on the moon, is used to transport the target plasma material to the first spacecraft cluster; The first spacecraft cluster operates on the DRO orbital family and is used to receive the target plasma material and transfer the target plasma material to the second spacecraft cluster. as well as The second spacecraft cluster, operating in a lunar orbit, is used to receive the target plasma material from the first spacecraft cluster.

10. The Earth-Moon mass transport system as described in claim 9, characterized in that, The first spacecraft cluster includes multiple first spacecraft, and the DRO orbital family includes multiple DRO orbits at different altitudes orbiting the Moon. Each DRO orbit has at least one first spacecraft. At least one first spacecraft in the current DRO orbit and at least one first spacecraft in the next layer of DRO orbit have at least one DRO transfer window that meets the rendezvous and transfer conditions. The target plasma material is adapted to be transferred in space from the at least one first spacecraft in the current DRO orbit to the at least one first spacecraft in the next layer of DRO orbit within the DRO transfer window.

11. The Earth-Moon mass transport system as described in claim 10, characterized in that, The second spacecraft cluster includes at least one second spacecraft, and at least one first spacecraft in the current DRO orbit has at least one cruise transfer window with the at least one second spacecraft that meets the rendezvous transfer conditions, wherein the target plasma material is adapted to be transferred from the at least one first spacecraft in the current DRO orbit to the at least one second spacecraft in the cruise transfer window.

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