A method, device, system and equipment for transporting goods between the earth and the moon

Abstract

The application discloses a kind of earth-moon interplanetary cargo transport method, device, system and equipment, applied to space technology field, to solve the problems that existing transport scheme in prior art is difficult to meet small volume, flight and individualized earth-moon interplanetary transport.Therein, transport direction includes from ground to moon and from moon to ground;According to transport direction, flight time and fuel consumption, determine target transfer upper stage and target crane from multiple transfer upper stages on near-earth orbit and multiple cranes on near-moon orbit;According to transport direction, the transport task is executed in the way of relay by target upper stage and target crane.This way, the optimization of earth-moon interplanetary transport path can be realized, fuel is saved, and the setting of multiple transfer upper stages and multiple cranes can realize all-weather, normal, small volume, individualized earth-moon interplanetary transport.

Description

Technical Field

[0001] This application relates to the field of aerospace technology, and in particular to a method, apparatus, system and equipment for inter-Earth-Moon cargo transportation. Background Technology

[0002] In recent years, with the continuous deepening of lunar exploration, the construction and long-term operation of future lunar surface and lunar orbit research stations will involve a large amount of transportation of various goods between the Earth and the Moon.

[0003] Currently, there are two main transportation options between Earth and the Moon. The first involves using a heavy-lift rocket to send the payload into a lunar transfer orbit in a single mission, followed by lunar braking and a powered descent for a soft landing using the payload's own propulsion system (e.g., cargo module or experimental module). However, this option requires each payload to have an independent propulsion system, significantly impacting ground-based tracking and control systems for each mission. It is also limited by the production capacity and high cost of heavy-lift rockets, and the limited window of only 2-3 lunar transfers per month. The second option involves launching a fully reusable, integrated cargo spacecraft. Through multiple refuelings, the cargo ship completes the entire process of lunar transfer, lunar landing, and lunar return, with the payload contained within the cargo spacecraft's cargo bay. Because the entire process is completed independently by the cargo ship and requires reusability, it consumes a significant amount of velocity increments and involves 7-8 or more on-orbit refuelings of the same type of spacecraft during flight, resulting in low transportation efficiency and poor reliability. Furthermore, both of the above schemes involve transporting a large amount of payload at once. Therefore, they are less efficient for personalized transportation of time-sensitive materials, different targets, and different orbits. Existing transportation schemes are difficult to meet the needs of future small-scale, flight-like, and personalized inter-Earth-Moon transportation missions. Summary of the Invention

[0004] This application provides a method, apparatus, system, and equipment for inter-Earth-Moon cargo transportation, which addresses the problem that existing transportation solutions are insufficient to meet the needs of small-volume, scheduled, and personalized inter-Earth-Moon transportation.

[0005] The technical solutions provided in this application are as follows:

[0006] On one hand, embodiments of this application provide a method for inter-Earth-Moon cargo transportation, including:

[0007] Obtain the current transportation task and determine the transportation direction of the current transportation task; wherein, the transportation direction includes from Earth to Moon and from Moon to Earth;

[0008] Based on the transport direction, flight time, and fuel consumption, the target transfer upper stage and target crane are determined from multiple transfer upper stages in low Earth orbit and multiple cranes in lunar orbit;

[0009] According to the direction of transport, the transport task is carried out in a relay manner through the target upper stage and the target crane.

[0010] In one possible implementation, the step of determining the target transfer upper stage and the target crane from multiple transfer upper stages in low Earth orbit and multiple cranes in lunar orbit, based on the transport direction, flight time, and fuel consumption, includes:

[0011] When the current transportation mission is determined to be from Earth to the Moon, the first flight time and first fuel consumption of each of the multiple transfer upper stages for docking and transporting the modular cargo compartment of the transportation mission are determined; the transfer upper stage with the shortest first flight time and the shortest first fuel consumption is determined as the target transfer upper stage; the second flight time and second fuel consumption of each of the multiple cranes for docking and transporting the modular cargo compartment on the target transfer upper stage are determined; the crane with the shortest second flight time and the shortest second fuel consumption is determined as the target crane;

[0012] When the current transport mission is determined to be from the moon to the earth, the third flight time and third fuel consumption of each of the multiple cranes docking with and transporting the modular cargo hold are determined; the crane with the shortest third flight time and the shortest third fuel consumption is determined as the target crane; based on the fourth flight time and fourth fuel consumption of each of the multiple transfer upper stages docking with and transporting the modular cargo hold on the target crane, the transfer upper stage with the shortest fourth flight time and the shortest fourth fuel consumption is determined as the target transfer upper stage.

[0013] In one possible implementation, the steps of performing the transportation task in a relay manner via the target upper stage and the target crane, according to the direction of transportation, include:

[0014] When the current transportation mission is determined to be from Earth to the Moon, the modular cargo module is directly sent into low Earth orbit by the launch vehicle to wait; the target transfer upper stage docks with the modular cargo module to carry out the Earth-Moon transfer, transporting the modular cargo module to the lunar orbit; the target crane docks with the modular cargo module to lower the orbit and complete the fixed-point soft landing.

[0015] When the current transport mission is determined to be from the moon to the earth, the target crane docks with the modular cargo compartment, completes lunar takeoff, and enters a near-lunar orbit to wait; the target transfer upper stage docks with the modular cargo compartment, performs a lunar-to-Earth injection, transports the modular cargo compartment to a near-Earth orbit, and achieves cargo compartment recovery.

[0016] In one possible implementation, before obtaining the current transportation task, the following is also included:

[0017] At preset time intervals, the transfer upper stage is sent directly into low Earth orbit via a launch vehicle, and the crane is then sent into lunar transfer orbit via the launch vehicle, so that the crane can enter lunar orbit by its own engine.

[0018] In one possible implementation, before determining the target transfer upper stage and target crane from multiple transfer upper stages in low Earth orbit and multiple cranes in lunar orbit, based on the transport direction, flight time, and fuel consumption, when the transport direction of the current transport mission is determined to be from Earth to the Moon, the method further includes:

[0019] Based on the current transportation task, determine the corresponding cargo for the transportation task;

[0020] The cargo compartment is structured according to the transported goods, and the transported goods are loaded into the cargo compartment to obtain a modular cargo compartment.

[0021] In one possible implementation, the method for transporting goods between the Earth and the Moon further includes:

[0022] Determine the transfer of fuel-deficient upper stage and fuel-deficient crane;

[0023] The modular cargo compartment, carrying fuel, is sent directly into low Earth orbit by a launch vehicle to wait.

[0024] When fuel is low, the transfer upper stage docks with a modular cargo hold carrying fuel for refueling;

[0025] The fully fueled transfer upper stage docks with the fuel-carrying modular cargo module to perform a lunar transfer. After transporting the fuel-carrying modular cargo module to a near-lunar orbit, the crane with insufficient fuel docks with the fuel-carrying modular cargo module to replenish fuel.

[0026] In one possible implementation, the cargo compartment structure includes a docking module, and the cargo compartment structure also includes at least one of a sealed cargo compartment, an open cargo compartment, a fuel storage and replenishment module, a heat recovery module, and a pressurization and temperature control module.

[0027] On the other hand, embodiments of this application provide an inter-Earth-Moon cargo transportation device, comprising:

[0028] The task acquisition module is used to acquire the current transportation task and determine the transportation direction of the current transportation task; the transportation direction includes from Earth to Moon and from Moon to Earth.

[0029] The equipment determination module is used to determine the target transfer upper stage and the target crane from multiple transfer upper stages in low Earth orbit and multiple cranes in lunar orbit, based on the transport direction, flight time and fuel consumption.

[0030] The task execution module is used to execute transportation tasks in a relay manner through the target superstructure and the target crane, according to the transportation direction.

[0031] On the other hand, embodiments of this application provide an inter-Earth-Moon cargo transportation system, including: multiple transfer upper stages, multiple cranes, multiple modular cargo compartments, and multiple launch vehicles;

[0032] Transfer upper stage for transporting modular cargo compartments between low Earth orbit and lunar orbit;

[0033] A crane was used to assist the modular cargo module in its powered descent to the lunar surface.

[0034] Modular cargo compartments are used to configure and load cargo for transport.

[0035] Launch vehicles are used to transport modular cargo modules from the ground to low Earth orbit.

[0036] On the other hand, embodiments of this application provide an electronic device, including: a memory, a processor, and a computer program stored in the memory and executable on the processor. When the processor executes the computer program, it implements the Earth-Moon cargo transportation method provided in embodiments of this application.

[0037] The beneficial effects of the embodiments of this application are as follows:

[0038] In this embodiment, a target transfer upper stage and a target crane are determined from multiple transfer upper stages in low Earth orbit and multiple cranes in lunar orbit, based on the transport direction, flight time, and fuel consumption. The transport task is executed in a relay manner by the target upper stage and the target crane according to the transport direction, which can optimize the transport path between Earth and the Moon, save fuel, and enable all-weather, routine, small-volume, and personalized transport between Earth and the Moon, meeting the needs of transporting time-sensitive materials and various personalized materials.

[0039] Other features and advantages of this application will be set forth in the following description, and will be apparent in part from the description, or may be learned by practicing the application. The objectives and other advantages of this application may be realized and obtained by means of the structures particularly pointed out in the written description, claims, and drawings. Attached Figure Description

[0040] The accompanying drawings, which are included to provide a further understanding of this application and form part of this application, illustrate exemplary embodiments and are used to explain this application, but do not constitute an undue limitation of this application. In the drawings:

[0041] Figure 1This is a schematic diagram of the Earth-Moon cargo transportation system framework in the embodiments of this application;

[0042] Figure 2 This is a schematic diagram of the structure for transferring the upper level in an embodiment of this application;

[0043] Figure 3 This is a schematic diagram of the crane's engine mount when it is retracted, as shown in the embodiment of this application.

[0044] Figure 4 This is a schematic diagram of the crane in the embodiments of this application;

[0045] Figure 5 This is a structural schematic diagram of the modular cargo compartment in an embodiment of this application;

[0046] Figure 6 This is a schematic diagram outlining the general flow of the Earth-Moon cargo transportation method in the embodiments of this application;

[0047] Figure 7 This is a schematic diagram of the structure for docking the transfer upper stage with the modular cargo compartment in an embodiment of this application;

[0048] Figure 8 This is a schematic diagram of the structure of the crane docking with the modular cargo compartment in an embodiment of this application;

[0049] Figure 9 This is a functional structure diagram of the inter-Earth-Moon cargo transportation device in an embodiment of this application;

[0050] Figure 10 This is a schematic diagram of the hardware structure of the electronic device in the embodiments of this application. Detailed Implementation

[0051] To make the objectives, technical solutions, and beneficial effects of this application clearer, the technical solutions in the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of this application, and not all of the embodiments. Based on the embodiments of this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0052] First, a brief introduction will be given to the Earth-Moon inter-cargo transportation system provided in the embodiments of this application, such as... Figure 1 As shown, the Earth-Moon cargo transportation system 100 provided in this application embodiment includes at least: multiple transfer upper stages 110, multiple cranes 120, multiple modular cargo compartments 130, and multiple launch vehicles 140;

[0053] Transfer upper stage 110 for transporting modular cargo compartment 130 between low Earth orbit and lunar orbit;

[0054] Crane 120 is used to assist modular cargo compartment 130 in completing a powered descent to the lunar surface;

[0055] Modular cargo compartment 130 is used to complete the setup for matching transported goods and to load transported goods;

[0056] Launch vehicle 140 is used to transport modular cargo module 130 from the ground to low Earth orbit.

[0057] In practical applications, refer to Figure 2 As shown, the transfer upper stage mainly includes an orbit control engine 200, solar panels 210, the upper stage body 220, and a docking surface 230 with the payload. (See reference...) Figure 3 As shown, the crane mainly includes a crane body 300, a payload docking surface 310, a power lowering engine 320, and its engine mount 330. The engine mount of this crane is retractable and can be deployed. It can be retracted during launch. The retracted engine mount of the crane is as follows: Figure 4 As shown. See also Figure 5 As shown, the modular cargo compartment includes a payload docking surface 500, a universal cargo compartment 510, and an inflatable landing cushion 520.

[0058] Next, combined with, for example Figure 1 The Earth-Moon inter-cargo transportation system shown in this application provides a detailed description of the Earth-Moon inter-cargo transportation method provided in the embodiments of this application. Specifically, in order to solve the problem that existing transportation solutions in the prior art cannot meet the needs of small-volume, scheduled, and personalized Earth-Moon inter-cargo transportation, the embodiments of this application provide an Earth-Moon inter-cargo transportation method, see reference. Figure 6 As shown in the embodiments of this application, the general flow of the Earth-Moon inter-cargo transportation method is as follows:

[0059] Step 601: Obtain the current transportation task and determine the transportation direction of the current transportation task; wherein, the transportation direction includes from Earth to Moon and from Moon to Earth.

[0060] In practical applications, transportation tasks include information such as transported goods, transport time, and transport direction. Current transportation tasks can be retrieved from the task queue in priority or chronological order. The task queue stores multiple externally input transportation tasks, which can be arranged in priority or chronological order.

[0061] Step 602: Based on the transport direction, flight time, and fuel consumption, determine the target transfer upper stage and the target crane from multiple transfer upper stages in low Earth orbit and multiple cranes in lunar orbit.

[0062] In practical applications, the transport direction refers to the direction of transport of the cargo in the current transport mission, and flight time refers to the total time spent transporting the cargo in the current transport mission. Fuel consumption refers to the total amount of fuel consumed to complete the current transport mission. The current transport mission requires a transfer upper stage in low Earth orbit and a crane in lunar orbit to work in a relay. The methods for determining the target transfer upper stage and the target crane differ depending on the transport direction; specifically, they can be divided into, but are not limited to, the following two:

[0063] The first method: When the current transportation mission is determined to be from Earth to the Moon, determine the first flight time and first fuel consumption of each of the multiple transfer upper stages for docking and transporting the modular cargo compartment of the transportation mission; determine the transfer upper stage with the shortest first flight time and the shortest first fuel consumption as the target transfer upper stage; determine the second flight time and second fuel consumption of each of the multiple cranes for docking and transporting the modular cargo compartment on the target transfer upper stage; determine the crane with the shortest second flight time and the shortest second fuel consumption as the target crane.

[0064] In practical applications, the first flight time is the time for the upper stage to dock and transport the modular cargo hold of the current transport mission when the transport direction is from Earth to the Moon, and the first fuel consumption is the total amount of fuel consumed during the upper stage transfer within the first flight time. The second flight time is the time for the crane to dock and transport the modular cargo hold of the current transport mission when the transport direction is from Earth to the Moon, and the second fuel consumption is the total amount of fuel consumed during the upper stage transfer within the second flight time. When the transport direction is from Earth to the Moon, the target upper stage for transfer is first determined, and then the target crane is determined based on the target upper stage for transfer.

[0065] The second approach: When the current transport mission is determined to be from the moon to the earth, determine the third flight time and third fuel consumption of each of the multiple cranes docking with and transporting the modular cargo hold; determine the crane with the shortest third flight time and the shortest third fuel consumption as the target crane; based on the fourth flight time and fourth fuel consumption of each of the multiple transfer upper stages docking with and transporting the modular cargo hold on the target crane, determine the transfer upper stage with the shortest fourth flight time and the shortest fourth fuel consumption as the target transfer upper stage.

[0066] In practical applications, the third flight time is the time it takes for the crane to dock and transport the modular cargo hold for the current transport mission when the transport direction is from the moon to the earth. The third fuel consumption is the total amount of fuel consumed during the transfer of the upper stage within the third flight time. The fourth flight time is the time it takes for the upper stage to dock and transport the modular cargo hold for the current transport mission when the transport direction is from the moon to the earth. The fourth fuel consumption is the total amount of fuel consumed during the transfer of the upper stage within the fourth flight time. When the transport direction is from the moon to the earth, the target crane is first determined, and then the target transfer upper stage is determined based on the target crane.

[0067] In practical implementation, the first flight time can be calculated based on the orbital altitude and true perihelion angle. Specifically, the design aims to ensure that all transfer upper stages, after near-Earth waiting, are in orbits with the same inclination angle, differing only in orbital altitude. The cargo module launch also enters an orbital plane with the same inclination angle. The orbital altitude of the transfer upper stages is defined as an n-order row vector (r1, r2, ..., r...). n Let the true anomaly angle difference between the upper stage and the cargo compartment during the Earth-Moon transfer be (θ1, θ2, ..., θ). n Assuming the required phase difference between the two at the start of the orbital transfer is (β1, β2, ..., β...), n In the initial screening process, targets with θ≤β are excluded. The time required from the current moment to the start of the orbit transfer is t. In equation (1), T is calculated as in equation (2). The time t1 required for the orbit transfer process is calculated as in equation (3). The time for the docking mechanism to pull back and lock and the close-range guidance phase is fixed at t0. Assuming that the disturbances and collisions during the docking process do not significantly affect the orbit, it is approximately assumed that the orbit of the combined body after docking is the initial orbit of the initial cargo compartment entry point. Assuming that various orbital perturbations are not considered and the entire launch and docking process is completed within one day, this has little impact on the Earth-Moon transfer start angle. The true perimeter angle of the Earth-Moon transfer start point in a certain launch is defined as α0. The time required to wait for the Earth-Moon transfer after docking is t2.

[0068]

[0069] Where T1 is the initial orbital period before orbital transfer, and T2 is the orbital period of the target orbit. The calculation method is shown in Equation (2). Where r is the orbital radius of the spacecraft, β represents the phase difference required between the two at the start of orbital transfer, G is the gravitational constant, M is the mass of the orbiting celestial body, and μ = GM.

[0070]

[0071]

[0072]

[0073] Based on the above calculations, the first flight time is...

[0074] T = T0 + t + t0 + t1 + t2 (5)

[0075] The initial fuel consumption can be determined based on the upper-stage decision variables and the velocity increment of the upper-stage docking with the cargo compartment. Specifically, assume that among all waiting upper stages in low Earth orbit, the number of transfer upper stages whose fuel, electrical energy, and spacecraft status conditions meet the mission requirements is m, and there are n cargo compartments in a waiting state after launch. Now, define the upper-stage decision variable H for selecting the i-th upper stage and the j-th cargo compartment. ij .

[0076]

[0077] Considering that the upper stage generally does not make any additional orbital changes after returning from each near-Earth mission, the orbital altitude of the upper stage is different on the near-Earth waiting orbit. Therefore, the speed increment of different upper stages docking with the cargo compartment is different, and thus the fuel consumption is also different. The fuel consumption matrix between any two upper stages and the cargo compartment is defined as shown in Equation (7).

[0078]

[0079] Assuming the docking employs a dual-pulse Hohmann transfer scheme and neglecting fuel consumption during the close-range guidance phase, the fuel consumption matrix is ​​equivalent to the velocity increment matrix of the Hohmann transfer between different targets. The velocity increment under a dual-pulse Hohmann transfer is only related to the relative orbital altitude. Furthermore, assuming the cargo module performs a standard launch at a fixed orbital altitude, meaning the modular cargo modules have the same initial orbital altitude, the consumption matrix is ​​also equivalent to the upper-stage orbital altitude matrix. The relationship between velocity increment and orbital altitude is given by equation (8), and the relationship between fuel mass consumption and velocity increment according to the Tsiolkovsky formula is given by equation (10).

[0080]

[0081]

[0082]

[0083] Where m0 represents the dry weight of the aircraft; w represents the engine jet velocity; and the orbital radius of the upper stage is X. ij The initial test track radius for the cargo compartment that the target needs to dock with is X0.

[0084] The first fuel consumption is

[0085]

[0086] Wherein, coefficient k is the coefficient corresponding to the fuel consumption and the orbital altitude of the upper stage.

[0087] It is worth mentioning that the methods for determining the first flight time and the first fuel consumption described above also apply to the second flight time and the second fuel consumption, the third flight time and the third fuel consumption, and the fourth flight time and the fourth fuel consumption. The difference lies in the fact that the second flight time and the second fuel consumption are calculated between the transfer upper stage and the crane, and the target object is selected as the crane, as well as the different orbits during the corresponding calculations; the third flight time and the third fuel consumption are calculated between the modular cargo compartment and the crane, and the target object is selected as the crane, as well as the different orbits during the corresponding calculations; the fourth flight time and the fourth fuel consumption are calculated between the crane and the transfer upper stage, and the target object is selected as the transfer upper stage, as well as the different orbits during the corresponding calculations.

[0088] Step 603: In accordance with the transport direction, the transport task is carried out in a relay manner through the target upper stage and the target crane.

[0089] In practical applications, the target upper stage primarily handles the transport of modular cargo modules between the ground and lunar orbit, while the target crane primarily handles the transport of modular cargo modules between lunar orbit and the lunar surface. Because the transport directions differ, the methods by which the target upper stage and target crane relay the transport missions differ, and can be categorized into, but are not limited to, the following two:

[0090] The first method involves sending the modular cargo module directly into low Earth orbit via a launch vehicle when the current transport mission is determined to be from Earth to the Moon. The target transfer upper stage then docks with the modular cargo module to perform an Earth-Moon transfer, transporting the modular cargo module to a near-lunar orbit. Finally, the target crane docks with the modular cargo module to lower it to a lower orbit and complete a soft landing.

[0091] The second method: When the current transportation mission is determined to be from the moon to the earth, the target crane docks with the modular cargo compartment, completes the lunar takeoff and enters the near-lunar orbit to wait; the target transfer upper stage docks with the modular cargo compartment, performs a lunar-to-Earth injection, transports the modular cargo compartment to the near-Earth orbit, and realizes the cargo compartment recovery.

[0092] In practice, Figure 7 The diagram shows the docking of the transfer upper stage 110 with the modular cargo compartment 130. The transfer upper stage 110 independently completes the docking with the modular cargo compartment 130 to form a combined unit. Figure 8The diagram shows the docking of crane 120 and modular cargo compartment 130. The docking of crane 120 and modular cargo compartment 130 can be assisted by a robotic arm to complete the connection between the cargo compartment and the crane. After the crane carries the cargo compartment away from the space station, it will descend to orbit and complete a fixed-point landing.

[0093] It's worth noting that after transferring the modular cargo module to the crane from the lunar orbit, the upper stage returns to low Earth orbit. The upper stage can use atmospheric-assisted deceleration and its engines to return to low Earth orbit. After completing its cargo transport mission, the crane can take off from the lunar surface and perform multiple orbital maneuvers to return to the lunar orbit and wait. Generally, after the upper stage and crane return to their respective orbits, no special adjustments to their orbital altitude and phase are needed. Alternatively, the upper stage and crane can adjust their orbital altitude and phase using their self-propulsion systems to ensure that the waiting upper stage and crane are as evenly distributed as possible, meeting the needs of future transport missions.

[0094] In this way, based on the transport direction, flight time, and fuel consumption, the target transfer upper stage and target crane can be selected from multiple transfer upper stages in low Earth orbit and multiple cranes in lunar orbit. According to the transport direction, the transport task can be carried out in a relay manner by the target upper stage and target crane, which can optimize the transport path between Earth and the Moon, save fuel, and enable all-weather, routine, small-volume, and personalized Earth-Moon transport by setting up multiple transfer upper stages and multiple cranes. This can meet the needs of transporting time-sensitive materials and various personalized materials.

[0095] In one possible implementation, before obtaining the current transportation task, the following is also included:

[0096] At preset time intervals, the transfer upper stage is sent directly into low Earth orbit via a launch vehicle, and the crane is then sent into lunar transfer orbit via the launch vehicle, so that the crane can enter lunar orbit by its own engine.

[0097] In practical applications, before carrying out a transportation mission, multiple transfer upper stages need to be sent into low Earth orbit, and multiple cranes into lunar orbit. During launch, the cranes need to be in a folded position, and after entering orbit, their supports unfold for orbital transfer and maneuvering. By launching densely at preset time intervals, forming a cluster of upper stages and cranes, a relatively uniform arrangement is ensured upon entering orbit. Deploying a large number of transfer upper stages and cranes can relatively evenly cover various orbital altitudes and phases, providing as many launch options as possible from Earth and the Moon, essentially covering a wide transportation window, and providing optimal decision-making options for transportation, achieving the highest efficiency in inter-Earth-Moon transportation.

[0098] In one possible implementation, in order to achieve personalized configuration based on the transported cargo, before determining the target transfer upper stage and target crane from multiple transfer upper stages in low Earth orbit and multiple cranes in lunar orbit based on the transport direction, flight time, and fuel consumption when the transport direction of the current transport mission is determined to be from Earth to the Moon, the method further includes:

[0099] First, based on the current transportation task, determine the cargo to be transported.

[0100] Then, the structure of the cargo compartment is set according to the transported goods, and the transported goods are loaded into the cargo compartment to obtain a modular cargo compartment.

[0101] In practical applications, the modular cargo compartment is a cargo compartment structurally configured according to the transported cargo. The cargo compartment structure includes docking modules, and may also include at least one of the following: a sealed cargo compartment, an open cargo compartment, a fuel storage and replenishment module, a heat recovery module, and a pressurization and temperature control module. Transported cargo can be propellant, nitrogen, oxygen, or other gaseous / liquid ascending cargo, as well as materials and equipment needed for lunar base construction, modular experimental cabinets, food and water supplies for the lunar base and space station, and experimental materials. The cargo compartment can be modularly replaced for each type of transported cargo. Furthermore, to adapt to the needs of various transport missions, the cargo compartment is also equipped with an inflatable heat shield and parachute recovery system, and has an enhanced thermal control system, enabling cargo reentry and return. The configuration of the modular cargo compartment is shown in Table 1 below.

[0102] Table 1 Modular Cargo Compartment Configuration

[0103]

[0104] In one possible implementation, the Earth-Moon cargo transport method, in order to refuel the transfer upper stage and crane, further includes:

[0105] First, determine the transfer upper stage and the crane with insufficient fuel;

[0106] Then, the modular cargo compartment carrying fuel will be sent directly into low Earth orbit by a launch vehicle to wait;

[0107] Next, the upper stage with insufficient fuel docks with the modular cargo compartment carrying fuel for refueling;

[0108] Finally, the fully fueled transfer upper stage docks with the fuel-carrying modular cargo module to perform a lunar transfer. After transporting the fuel-carrying modular cargo module to a near-lunar orbit, the crane with insufficient fuel docks with the fuel-carrying modular cargo module to replenish fuel.

[0109] In practical applications, a modular cargo module carrying fuel is directly launched into low Earth orbit via a launch vehicle, allowing a refueling upper stage to dock and refuel if fuel is insufficient. A crane docking with a fuel-carrying modular cargo module requires a lunar transfer via a fully fueled upper stage. Furthermore, due to the high modularity of the spacecraft, the upper stage and crane can also provide emergency repair support for buddy aircraft, thereby ensuring long-term stable flight of the spacecraft within the system.

[0110] Based on the above embodiments, this application provides an inter-Earth-Moon cargo transportation device, see reference. Figure 9 As shown, the Earth-Moon inter-cargo transport device 900 provided in this application embodiment includes at least:

[0111] The task acquisition module 901 is used to acquire the current transportation task and determine the transportation direction of the current transportation task; wherein, the transportation direction includes from Earth to Moon and from Moon to Earth;

[0112] Equipment determination module 902 is used to determine the target transfer upper stage and the target crane from multiple transfer upper stages in low Earth orbit and multiple cranes in lunar orbit based on the transport direction, flight time and fuel consumption.

[0113] Task execution module 903 is used to execute transportation tasks in a relay manner through the target superstructure and the target crane, according to the transportation direction.

[0114] In one possible implementation, the device determination module 902 is specifically used for:

[0115] When the current transportation mission is determined to be from Earth to the Moon, the first flight time and first fuel consumption of each of the multiple transfer upper stages for docking and transporting the modular cargo compartment of the transportation mission are determined; the transfer upper stage with the shortest first flight time and the shortest first fuel consumption is determined as the target transfer upper stage; the second flight time and second fuel consumption of each of the multiple cranes for docking and transporting the modular cargo compartment on the target transfer upper stage are determined; the crane with the shortest second flight time and the shortest second fuel consumption is determined as the target crane;

[0116] When the current transport mission is determined to be from the moon to the earth, the third flight time and third fuel consumption of each of the multiple cranes docking with and transporting the modular cargo hold are determined; the crane with the shortest third flight time and the shortest third fuel consumption is determined as the target crane; based on the fourth flight time and fourth fuel consumption of each of the multiple transfer upper stages docking with and transporting the modular cargo hold on the target crane, the transfer upper stage with the shortest fourth flight time and the shortest fourth fuel consumption is determined as the target transfer upper stage.

[0117] In one possible implementation, the task execution module 903 is specifically used for:

[0118] When the current transportation mission is determined to be from Earth to the Moon, the modular cargo module is directly sent into low Earth orbit by the launch vehicle to wait; the target transfer upper stage docks with the modular cargo module to carry out the Earth-Moon transfer, transporting the modular cargo module to the lunar orbit; the target crane docks with the modular cargo module to lower the orbit and complete the fixed-point soft landing.

[0119] When the current transport mission is determined to be from the moon to the earth, the target crane docks with the modular cargo compartment, completes lunar takeoff, and enters a near-lunar orbit to wait; the target transfer upper stage docks with the modular cargo compartment, performs a lunar-to-Earth injection, transports the modular cargo compartment to a near-Earth orbit, and achieves cargo compartment recovery.

[0120] In one possible implementation, the Earth-Moon cargo transport device further includes:

[0121] The equipment system establishment unit 904 is used to send the transfer upper stage directly into low Earth orbit via a launch vehicle at preset time intervals, and to send the crane into the Earth-Moon transfer orbit via the launch vehicle, so that the crane can enter the near-lunar orbit by its own engine.

[0122] In one possible implementation, the Earth-Moon cargo transport device further includes:

[0123] The cargo determination unit 905 is used to determine the cargo to be transported corresponding to the current transport task.

[0124] Modular cargo compartment unit 906 is used to set up the structure of the cargo compartment according to the transported goods, and to load the transported goods into the cargo compartment to obtain a modular cargo compartment.

[0125] In one possible implementation, the Earth-Moon cargo transport device further includes:

[0126] Fuel determination unit 907 is used to determine the transfer upper stage and the crane that are low on fuel;

[0127] Fuel transport unit 908 is used to send a modular cargo compartment carrying fuel directly into low Earth orbit via a launch vehicle.

[0128] The first replenishment unit 909 is used to dock the upper stage with the modular cargo compartment carrying fuel when the fuel is insufficient for refueling.

[0129] The second replenishment unit 910 is used to dock the fully fueled transfer upper stage with the fuel-carrying modular cargo module for Earth-Moon transfer. After transporting the fuel-carrying modular cargo module to the lunar orbit, the crane with insufficient fuel docks with the fuel-carrying modular cargo module to replenish fuel.

[0130] In one possible implementation, the cargo compartment structure includes a docking module, and the cargo compartment structure also includes at least one of a sealed cargo compartment, an open cargo compartment, a fuel storage and replenishment module, a heat recovery module, and a pressurization and temperature control module.

[0131] It should be noted that the principle of the Earth-Moon cargo transportation device 900 provided in this application embodiment to solve the technical problem is similar to the Earth-Moon cargo transportation method provided in this application embodiment. Therefore, the implementation of the Earth-Moon cargo transportation device 900 provided in this application embodiment can refer to the implementation of the Earth-Moon cargo transportation method provided in this application embodiment, and the repeated parts will not be described again.

[0132] After introducing the Earth-Moon cargo transportation system, method, and apparatus provided in the embodiments of this application, the electronic equipment provided in the embodiments of this application will be briefly introduced next.

[0133] See Figure 10 As shown, the electronic device 1000 provided in this application embodiment includes at least: a processor 1001, a memory 1002, and a computer program stored in the memory 1002 and executable on the processor 1001. When the processor 1001 executes the computer program, it implements the Earth-Moon cargo transportation method provided in this application embodiment.

[0134] It should be noted that, Figure 10 The electronic device 1000 shown is merely an example and should not impose any limitations on the functionality and scope of use of the embodiments of this application.

[0135] The electronic device 1000 provided in this application embodiment may further include a bus 1003 connecting different components (including processor 1001 and memory 1002). The bus 1003 represents one or more types of bus structures, including memory bus, peripheral bus, local area bus, etc.

[0136] The memory 1002 may include a readable medium in the form of volatile memory, such as random access memory (RAM) 10021 and / or cache memory 10022, and may further include read-only memory (ROM) 10023.

[0137] The memory 1002 may also include a program tool 10025 having a set (at least one) of program modules 10024, including but not limited to: an operating subsystem, one or more application programs, other program modules, and program data, each or some combination of these examples may include an implementation of a network environment.

[0138] Electronic device 1000 can also communicate with one or more external devices 1004 (e.g., keyboard, remote control, etc.), and with one or more devices that enable a user to interact with electronic device 1000 (e.g., mobile phone, computer, etc.), and / or with any device that enables electronic device 1000 to communicate with one or more other electronic devices 1000 (e.g., router, modem, etc.). This communication can be performed through input / output (I / O) interface 1005. Furthermore, electronic device 1000 can also communicate with one or more networks (e.g., local area network (LAN), wide area network (WAN), and / or public networks, such as the Internet) through network adapter 1006. Figure 6 As shown, network adapter 1006 communicates with other modules of electronic device 1000 via bus 1003. It should be understood that, although... Figure 6 As not shown, other hardware and / or software modules may be used in conjunction with electronic device 1000, including but not limited to: microcode, device drivers, redundant processors, external disk drive arrays, Redundant Arrays of Independent Disks (RAID) subsystems, tape drives, and data backup storage subsystems.

[0139] The computer-readable storage medium provided in the embodiments of this application is described below. The computer-readable storage medium provided in the embodiments of this application stores computer instructions, which, when executed by a processor, implement the Earth-Moon cargo transportation method provided in the embodiments of this application. Specifically, the computer instructions can be built into or installed in the electronic device 1000, so that the electronic device 1000 can implement the Earth-Moon cargo transportation method provided in the embodiments of this application by executing the built-in or installed computer instructions.

[0140] Furthermore, the Earth-Moon cargo transportation method provided in this application embodiment can also be implemented as a program product, which includes program code. When the program product can be run on the electronic device 1000, the program code is used to cause the electronic device 1000 to execute the Earth-Moon cargo transportation method provided in this application embodiment.

[0141] The program product provided in this application embodiment can be any combination of one or more readable media, wherein the readable media can be a readable signal medium or a readable storage medium, and the readable storage medium can be, but is not limited to, an electrical, magnetic, optical, electromagnetic, infrared, or semiconductor system, device or apparatus, or any combination thereof. Specifically, more specific examples of readable storage media (a non-exhaustive list) include: electrical connections with one or more wires, portable disks, hard disks, RAM, ROM, erasable programmable read-only memory (EPROM), optical fibers, portable compact disc read-only memory (CD-ROM), optical storage devices, magnetic storage devices, or any suitable combination thereof.

[0142] The program product provided in this application embodiment can be a CD-ROM and include program code, and can also run on a computing device. However, the program product provided in this application embodiment is not limited thereto. In this application embodiment, the readable storage medium can be any tangible medium that contains or stores a program, which can be used by or in conjunction with an instruction execution system, apparatus, or device.

[0143] It should be noted that although several units or sub-units of the device have been mentioned in the detailed description above, this division is merely exemplary and not mandatory. In fact, according to embodiments of this application, the features and functions of two or more units described above can be embodied in one unit. Conversely, the features and functions of one unit described above can be further divided and embodied by multiple units.

[0144] Furthermore, although the operations of the method of this application are described in a specific order in the accompanying drawings, this does not require or imply that these operations must be performed in that specific order, or that all the operations shown must be performed to achieve the desired result. Additionally or alternatively, certain steps may be omitted, multiple steps may be combined into one step, and / or one step may be broken down into multiple steps.

[0145] Although preferred embodiments of this application have been described, those skilled in the art, upon learning the basic inventive concept, can make other changes and modifications to these embodiments. Therefore, the appended claims are intended to be interpreted as including the preferred embodiments as well as all changes and modifications falling within the scope of this application.

[0146] Obviously, those skilled in the art can make various modifications and variations to the embodiments of this application without departing from the spirit and scope of the embodiments of this application. Therefore, if these modifications and variations to the embodiments of this application fall within the scope of the claims of this application and their equivalents, this application also intends to include these modifications and variations.

Claims

1. A method for transporting goods between the Earth and the Moon, characterized in that, include: At preset time intervals, the transfer upper stage is directly sent into low Earth orbit by a launch vehicle, and the crane is sent into the lunar transfer orbit by the launch vehicle, so that the crane can enter the lunar orbit by its own engine; wherein, the crane includes a crane body, a payload docking surface, a power descent engine and a retractable and deployable engine mount; Obtain the current transportation task and determine the transportation direction of the current transportation task; wherein, the transportation direction includes from Earth to Moon and from Moon to Earth; Based on the transport direction, flight time, and fuel consumption, the target transfer upper stage and target crane are determined from multiple transfer upper stages in low Earth orbit and multiple cranes in lunar orbit; The transportation task is carried out in a relay manner through the target upper stage and the target crane, according to the transport direction; The step of performing the transportation task in a relay manner through the target superstructure and the target crane according to the transportation direction includes: When the current transportation mission is determined to be from Earth to the Moon, the modular cargo module is directly sent into the near-Earth orbit by the launch vehicle to wait; the target transfer upper stage docks with the modular cargo module to perform an Earth-Moon transfer, transporting the modular cargo module to the near-lunar orbit; the target crane docks with the modular cargo module to lower the orbit and complete a fixed-point soft landing; When the current transportation mission is determined to be from the moon to the earth, the target crane docks with the modular cargo compartment, completes lunar takeoff, enters a near-lunar orbit, and waits; the target transfer upper stage docks with the modular cargo compartment, performs a lunar-to-Earth injection, transports the modular cargo compartment to a near-Earth orbit, and achieves cargo compartment recovery.

2. The method for transporting goods between the Earth and the Moon as described in claim 1, characterized in that, The step of determining the target transfer upper stage and target crane from multiple transfer upper stages in low Earth orbit and multiple cranes in lunar orbit based on transport direction, flight time, and fuel consumption includes: When the current transportation mission is determined to be from Earth to the Moon, the first flight time and first fuel consumption of each of the multiple transfer upper stages for docking and transporting the modular cargo compartment of the transportation mission are determined; the transfer upper stage with the smallest first flight time and the smallest first fuel consumption is determined as the target transfer upper stage; the second flight time and second fuel consumption of each of the multiple cranes for docking and transporting the modular cargo compartment on the target transfer upper stage are determined; the crane with the smallest second flight time and the smallest second fuel consumption is determined as the target crane; When the current transport mission is determined to be from the moon to the earth, the third flight time and third fuel consumption of each of the multiple cranes docking with the modular cargo compartment and transporting the modular cargo compartment are determined; the crane with the smallest third flight time and the smallest third fuel consumption is determined as the target crane; based on the fourth flight time and fourth fuel consumption of each of the multiple transfer upper stages docking with the modular cargo compartment on the target crane and transporting the modular cargo compartment, the transfer upper stage with the smallest fourth flight time and the smallest fourth fuel consumption is determined as the target transfer upper stage.

3. The method for transporting goods between the Earth and the Moon as described in claim 1, characterized in that, When the current transport mission's transport direction is determined to be from Earth to the Moon, before determining the target transfer upper stage and target crane from multiple transfer upper stages in low Earth orbit and multiple cranes in lunar orbit based on the transport direction, flight time, and fuel consumption, the method further includes: Based on the current transportation task, determine the transportation goods corresponding to the transportation task; The cargo compartment is structured according to the transported goods, and the transported goods are loaded into the cargo compartment to obtain a modular cargo compartment.

4. The method for transporting goods between the Earth and the Moon as described in claim 3, characterized in that, Also includes: Determine the transfer of fuel-deficient upper stage and fuel-deficient crane; The modular cargo module, carrying fuel, will be directly sent into the low Earth orbit by a launch vehicle to await further instructions. The transfer upper stage, which is low on fuel, docks with the modular cargo compartment carrying fuel for refueling; A fully fueled transfer upper stage docks with the fuel-carrying modular cargo module to perform a lunar transfer. After transporting the fuel-carrying modular cargo module to the lunar orbit, a crane with insufficient fuel docks with the fuel-carrying modular cargo module to replenish fuel.

5. The method for transporting goods between the Earth and the Moon as described in claim 4, characterized in that, The cargo compartment structure includes a docking module, and the cargo compartment structure also includes at least one of the following: a sealed cargo compartment, an open cargo compartment, a fuel storage and replenishment module, a heat recovery module, and a pressurization and temperature control module.

6. A cargo transportation device for Earth-Moon interplanetary space, characterized in that, include: The equipment system establishment unit is used to send the transfer upper stage directly into low Earth orbit via a launch vehicle at preset time intervals, and to send the crane into the Earth-Moon transfer orbit via the launch vehicle, so that the crane can enter the near-lunar orbit by its own engine; wherein, the crane includes a crane body, a payload docking surface, a power descent engine, and a retractable and deployable engine mount; The task acquisition module is used to acquire the current transportation task and determine the transportation direction of the current transportation task; wherein, the transportation direction includes from Earth to Moon and from Moon to Earth; The equipment determination module is used to determine the target transfer upper stage and the target crane from multiple transfer upper stages in low Earth orbit and multiple cranes in lunar orbit, based on the transport direction, flight time and fuel consumption. The task execution module is used to execute the transportation task in a relay manner through the target superstructure and the target crane, according to the transportation direction. The mission execution module is specifically used for: when the current transportation mission's direction is determined to be from Earth to the Moon, sending the modular cargo module directly into the near-Earth orbit via a launch vehicle; the target transfer upper stage docks with the modular cargo module to perform an Earth-Moon transfer, transporting the modular cargo module to the near-lunar orbit; the target crane docks with the modular cargo module to perform orbit descent and complete a precise soft landing; when the current transportation mission's direction is determined to be from Moon to Earth, the target crane docks with the modular cargo module, performs lunar takeoff and enters the near-lunar orbit; the target transfer upper stage docks with the modular cargo module to perform a lunar-Earth launch, transporting the modular cargo module to the near-Earth orbit and achieving cargo module recovery.

7. A cargo transportation system between the Earth and the Moon, characterized in that, include: Multiple transfer upper stages, multiple cranes, multiple modular cargo bays, and multiple launch vehicles; The transfer upper stage is used for transporting modular cargo compartments between low Earth orbit and lunar orbit; The crane is used to assist the modular cargo module in completing a powered descent to the lunar surface; the crane includes a crane body, a payload docking surface, a powered descent engine, and a retractable and deployable engine mount. The modular cargo compartment is used to complete the setup for matching transported goods and to load the transported goods; The launch vehicle is used to transport modular cargo modules from the ground to near-Earth orbit.

8. An electronic device, characterized in that, include: A memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor, when executing the computer program, implements the method for transporting goods between the Earth and the Moon as described in any one of claims 1-5.

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