Lunar Power Grid Assembly

Abstract

Two preselected lunar sites are provided with a pair of interconnected vertical solar arrays. A cable transfers power between one vertical solar array and the other vertical solar array and transmits collected energy from one vertical solar array to the other vertical solar array when the other vertical solar array is not collecting, allowing the temperature of the other vertical solar array to be maintained. A power storage device receives solar energy from the vertical solar arrays. A power feed interface distributes the energy to one or more lunar surface devices on the lunar surface. A payload is carried on the landing vehicle for carrying at least one of the pair of interconnected vertical solar arrays, the cable, the power storage device, and the power feed interface.

Description

[Technical field]

[0001] CROSS-REFERENCE TO RELATED APPLICATIONS This application claims the benefit under 35 U.S.C. § 119(e) of co-pending U.S. Provisional Application No. 63 / 209,664, entitled “METHODS, SYSTEMS, AND APPARATUS FOR ESTABLISHING A LUNAR POWER GRID,” filed on June 11, 2021, the contents of which are incorporated herein by reference.

[0002] The present disclosure relates to systems, methods, and apparatus for providing a lunar power grid. [Background technology]

[0003] All of our shared ambitions on the Moon depend on establishing continuous and reliable electrical power. Astronaut habitats, on-site resource pilot plants, long-duration rover travel, and commercial business programs all require significant amounts of uninterrupted power. The need for power comes not only from surface activities, but also from the need to survive the short, inhospitable lunar surface day.

[0004] Previously used conventional lunar power systems were developed for each mission. The operation of the system as well as its maintenance had to be determined well in advance. Such custom-designed systems added significant cost and complexity to the mission. Furthermore, the power provided through these systems was temporary and limited.

[0005] Most of the lunar power solutions proposed for future missions require significant technology development and / or utilize systems that are not yet technologically mature. For example, power beaming has not yet been deployed and used in space. Lunar fission power systems are still in the early stages of design and will require significant policy developments before they can be deployed and operated by the private sector. Thus, there is a need for improved lunar power systems that do not suffer from the shortcomings of conventional and proposed lunar power systems. Summary of the Invention

[0006] In various embodiments, a lunar power grid assembly is provided for deployment on a lunar surface. The lunar surface has a preselected pair of lunar sites, the pair consisting of a first lunar site and a second lunar site. A pair of interconnected vertical solar arrays is provided, the pair consisting of a first vertical solar array disposed at the first lunar site for collecting solar energy and a second vertical solar array disposed at the second lunar site for collecting solar energy. A cable transmits power between the first vertical solar array and the second vertical solar array and can transmit collected energy to one vertical solar array when the other vertical solar array is not collecting energy to maintain a temperature of the other vertical solar array. A power storage device receives solar energy from the first vertical solar array and the second vertical solar array. A power supply interface distributes the energy to one or more lunar devices on the lunar surface. A landing vehicle has a payload for carrying at least one of the pair of interconnected vertical solar arrays, the cable, the power storage device, and the power supply interface. [Brief description of the drawings]

[0007] [Figure 1] FIG. 1 is a schematic diagram of one embodiment of a lunar power grid in accordance with the disclosed subject matter.

[0008] [Diagram 2]FIG. 2 is a block diagram of an embodiment of a landing vehicle carrying components of a lunar power grid assembly in accordance with the disclosed subject matter.

[0009] [Diagram 3] FIG. 3 is a block diagram of a vertical solar array in accordance with the disclosed subject matter.

[0010] [Figure 4] FIG. 4 is an exemplary process in accordance with the disclosed subject matter.

[0011] [Diagram 5] FIG. 5 is a schematic diagram of another embodiment of a lunar power grid in accordance with the disclosed subject matter.

[0012] [Figure 6] FIG. 6 is another exemplary process in accordance with the disclosed subject matter. DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

[0013] The subject matter of this disclosure relates to systems, methods, and apparatus for providing a lunar power grid. The lunar power grid can be provided using one or more landing vehicles that deliver vertical solar arrays to two preselected lunar sites. A power interface and a power storage device are connected to the vertical solar arrays. The power interface can serve as a power port for various devices, including tools, rovers and other vehicles, and other equipment.

[0014] In some embodiments, a single landing vehicle carries all components of the lunar power grid to the lunar surface. In such embodiments, the landing vehicle lands at a first preselected lunar site to deploy one of the vertical solar arrays. The other vertical solar array can be carried on a lunar vehicle that can transport the vertical solar array to a second preselected lunar site. The two vertical solar arrays can be interconnected.

[0015] In another embodiment, multiple landing vehicles deliver components of the power grid to the surface: one landing vehicle delivers a first vertical solar array to a first lunar site; a second landing vehicle delivers a second vertical solar array to a second lunar site; and a lunar vehicle, such as a rover, delivers at least one end of a cable from one lunar site to the other lunar site, connecting the two vertical solar arrays to each other.

[0016] The lunar power grid that is the subject of this disclosure can power a variety of structures, functions, and missions, such as the Human Landing System (HLS), Lunar Exploration Vehicles (LTV), surface-based habitats, in-situ resource utilization (ISRU), Commercial Lunar Transportation Services (CLPS), Discovery class missions, etc. The power grid can power a variety of devices, including scientific instruments, surface exploration rovers, communications antennas, mining equipment, and other devices.

[0017] The detailed description provided below in conjunction with the accompanying drawings is intended as a description of the embodiments and is not intended to represent the only manner in which the embodiments may be constructed or utilized. The specification describes the functions of the embodiments and the sequence of steps for constructing and operating the embodiments. However, the same or equivalent functions and sequences may be accomplished by different embodiments.

[0018] References to "an embodiment," "an embodiment," "an example embodiment," "an implementation," "an implementation," "an example," "an example," or the like mean that a described embodiment, implementation, or example may include a particular feature, structure, or characteristic, but not all embodiments, implementations, or examples necessarily include the particular feature, structure, or characteristic. Moreover, such phrases do not necessarily refer to the same embodiment, implementation, or example. Furthermore, when a particular feature, structure, or characteristic is described in connection with an embodiment, implementation, or example, it is understood that such feature, structure, or characteristic may also be implemented in connection with other embodiments, implementations, or examples, whether or not explicitly stated.

[0019] Numerous specific details are set forth in order to provide a thorough understanding of one or more embodiments of the described subject matter, however, it is understood that such embodiments may be practiced without these specific details.

[0020] Various features of the subject disclosure will now be described in more detail with reference to the drawings, in which like reference numerals generally refer to like or corresponding elements throughout. The drawings and detailed description are not intended to limit the claimed subject matter to the particular forms described. Rather, the intention is to cover all modifications, equivalents, and alternatives within the spirit and scope of the claimed subject matter.

[0021] This disclosure relates to a system integrated into one or more launch vehicles capable of flying to the Moon that, once activated, can harness abundant and inexpensive solar energy via vertical solar arrays located at two interconnected strategically determined locations on the lunar surface to power multi-year surface systems.

[0022] During operation, each vertical solar array will take turns generating solar power to distribute power on the lunar surface. The vertical solar arrays will also store power in batteries to maintain warmth and survive during dark hours on the lunar surface. The system will distribute power to any surface asset in a local area (kilometer scale) using a tethered lunar rover equipped with wireless and / or wired chargers that act as mobile power outlets.

[0023] The system can be deployed at lunar sites with resource-rich deposits or features of scientific or commercial interest. It can also make lunar assets more robust and affordable, operating for years at a time. As lunar missions may extend beyond the typical 14-day duration, the system will be essential infrastructure for the development of the Moon for decades to come.

[0024] 1-3, there is shown a system, generally designated 100, for establishing a lunar power grid. The system 100 may include a landing vehicle 110 having a payload 112 thereon. The payload 112 may include a pair of vertical solar arrays 114-116, a power feed interface 118, and a power storage device 120. The vertical solar arrays 114-116, the power feed interface 118, and the power storage device 120 are connected to each other by a cable 121 for transmitting power therebetween.

[0025] One vertical solar array 116 is mounted on a lunar vehicle 122. The lunar vehicle 122 may be an autonomous self-driving trailer, a wheeled frame, or a set of wheels attached to the vertical solar array 116. The landing vehicle 110 lands on the lunar surface 124 at one of two preselected lunar sites 126-128 and deploys the system 100. The lunar vehicle 122 carries the vertical solar array 116 to a second lunar site 128. The lunar vehicle 122 may be tethered to the landing vehicle 110.

[0026] In some embodiments, the system 100 may be incorporated into a lunar vehicle 122, which may be a single lander such as the GRIFFIN® Launch Vehicle by Astrobotic Technology, Inc. of Pittsburgh, Pennsylvania.

[0027] The lunar sites 126-128 are preselected by selecting sites that meet certain predetermined criteria. For example, in some embodiments, the lunar sites 126-128 should be less than about 4 kilometers apart from one another. In other embodiments, the lunar sites 126-128 should be less than about 2 kilometers apart from one another. In such embodiments, the lunar sites 126-128 should have a gradient of less than about 10 degrees and together share greater than 95% illumination over a 365 day period.

[0028] When deployed at the lunar sites 126-128, the vertical solar arrays 114-116 can collect energy for storage in the power storage device 120. The vertical solar arrays 114-116 can alternately collect energy, such that the vertical solar array 114 can collect energy when the vertical solar array 116 is not able to collect energy, and vice versa. Thus, the vertical solar array 114 can send energy (or a portion of it) to the vertical solar array 116 to maintain the temperature of the vertical solar array 116 when it is not collecting energy.

[0029] Each of the vertical solar arrays 114-116 may include roll-out solar arrays that may follow the azimuth or may roll away from the azimuth during non-use. In some embodiments, the vertical solar arrays 114-116 may include solar cells approximately 10 meters away from the lunar surface 124, with the lunar vehicle 122 approximately 1 meter from the lunar surface. The solar cells may be positioned at an angle of approximately ±5 degrees.

[0030] 1-3 , the system 100 may include one or more mobile power outlets 130-134 connectable to the power supply interface 118. The mobile power outlets 130-134 may connect to the power supply interface 118 to receive power from the power storage device 120. The mobile power outlets 130-134 may then be disconnected from the power supply interface 118 and moved to various lunar assets 136 by moving across the lunar surface 124.

[0031] In some embodiments, the landing vehicle 110 may carry mobile power outlets 130-134 along with other components of the system 100. The landing vehicle 110 may include a braking stage 138 for carrying the payload 112.

[0032] The mobile power outlets 130-134 may be stored in the lunar vehicle 122 on the landing vehicle 110. In some embodiments, the lunar vehicle 122 may be a Lunar Infrastructure Trailer (LIT), a self-propelled wheeled vehicle, that may hold the vertical solar arrays 114-116, a battery, a wire reel for connecting to the landing vehicle 110, and the mobile power outlets 130-134 with wireless power supplies. The vertical solar array 116 may be supported by an inertial measurement unit and a gimbal to control the movement. In such an embodiment, the LIT may be configured to communicate at a data rate of 2.4 GHz WiFi on the LIT. The vertical solar arrays 114-115 may be configured to communicate at a rate of 900 MHz.

[0033] The LIT may be sized to fit onto the landing vehicle 110 and is deployable from the landing vehicle 110 without ramps or external robotic assistance. In some embodiments, the LIT may include a wireless power coil, a wireless power transmitter, a power management and distribution module (PMAD), command and data processing (C&DH), RF communications, altitude determination and control (ADC), and deployable mechanism actuation. The LIT may also include a power converter and a power interface.

[0034] The vertical solar arrays 114-116 may be vertical solar array technology generators, in particular vertical solar array technology (VSAT) generators. Each of the vertical solar arrays 114-116 is fitted with a ruggedized wireless power system capable of transmitting power to surface assets, such as the lunar asset 136, with an efficiency of 85%.

[0035] Operation of the system 100 is enhanced by the specific characteristics of the lunar surface sites 126-128, which are strategically located twin sites on the lunar surface 124, providing the vertical solar arrays 114-116 with the capability to generate power continuously for years at a time. There may be as many as 100's of strategically located twin sites on the lunar surface 124.

[0036] The power supply interface 118 may be a wireless proximity power supply and a self-aligning physical connector. When the power supply interface 118 is a wireless power supply, the power supply interface 118 can achieve a transmission efficiency of about 80% and is not affected by the dust coverage of the regolith.

[0037] The mobile power outlets 130-134 may be ultra-lightweight, modular, and expandable commercial lunar rovers. In this exemplary embodiment, the lunar rovers may be CUBEROVER® robotic delivery vehicles from Astrobotic Technology, Inc. of Pittsburgh, Pennsylvania.

[0038] The portable power outlets 130-134 may include a cable reel assembly for use on the lunar surface, which may be mounted within the payload bay and may include a reel, guides, actuators, heaters, and the cable itself.

[0039] The power storage device 120 may be any suitable power storage device or system and may include a battery. The power storage device 120 may include a power inverter that generates 5 kVAC and / or a power regulator that generates 120 VDC.

[0040] 3, the vertical solar array 114 may include one or more solar panels 140 and internal components 142. The internal components 142 may include one or more heaters that may receive power from the vertical solar array 116 shown in FIGS. 1-2 when the solar panels 140 are not collecting solar energy.

[0041] The internal components 142 may further include sensitive electronic devices or components that can be heated by the energy collected by the vertical solar array 116. It should be understood that the vertical solar array 116 shown in Figures 1-2 is similarly configured. By using this mechanism to heat the internal components 142, a system is provided that can function with a miniaturized battery.

[0042] 4, there is shown a process for establishing a lunar power grid on the moon, generally designated 200. Process 200 may be accomplished using system 100 of FIGS.

[0043] A preselected pair of lunar sites is identified, consisting of a first lunar site and a second lunar site, at 201. The identification of the lunar sites can be accomplished by a four-part sub-process.

[0044] The first part of the sub-process involves identifying pairs of sites corresponding to lunar sites 126-128 shown in Figure 1 using LUNARAY® software by Astrobotic Technology, Inc. of Pittsburgh, Pennsylvania. This software includes a simulation tool to identify candidate sites for vertical solar array deployment.

[0045] The software acts as a physically accurate planetary renderer and includes a suite of software tools for planning precision landing and rover traffic paths. The software uses topographical and ephemeris data to provide a photometrically accurate rendering of the lighting conditions on the lunar surface at any location and time. This capability is advantageous for polar missions where lighting conditions can change dramatically due to long and pervasive shadows.

[0046] The software can generate ground station line-of-sight maps and Earth elevation maps for communications planning. The software can incorporate real-time, physically based ray tracing and uses state-of-the-art photogrammetry techniques to synthesize high-resolution Digital Elevation Models (DEMs) from orbital imagery and Light Detection and Ranging (LiDAR) data.

[0047] The second part involves determining the illuminated percentage of the site by analyzing the data set to determine the percentage of time each pixel is illuminated versus dark.

[0048] The third part involves analyzing the dataset to calculate the maximum number of consecutive days that a pixel is illuminated, making areas with continuous sunlight a more attractive option for vertical solar array towers than areas with frequent days without sunlight.

[0049] The fourth part involves considering the cable length between each vertical solar array to be deployed and determining the distance of each cable length by laying out the grid of each graph in increments of 2 km.

[0050] The identification sub-process focuses on finding two locations where one of the two locations has always available sunlight. With this architecture, one of the vertical solar arrays is always powered, providing power to the entire grid.

[0051] Locations with high illumination fractions were used as starting points to find two locations that share illumination over a given time frame. Then, smaller sections of the full dataset were cut out and used for localized searches based on the initial starting point or landing site.

[0052] At 202, a landing vehicle is provided having a pair of interconnected vertical solar arrays, comprising a first vertical solar array and a second vertical solar array mounted on a lunar vehicle, a cable for transmitting power therebetween, a power feed interface, and a power storage device.

[0053] At 203, a landing vehicle lands at a first lunar site and deploys a first vertical solar array thereon. The landing vehicle carries a stationary vertical solar array disposed vertically on its lander and one movable vertical solar array mounted on a self-propelled tethered LIT. The LIT carries one or more tethered lunar rovers.

[0054] Upon landing, the LIT self-detaches from the landing vehicle and begins travel to its companion site, while remaining tethered to the landing vehicle by cable, step 204. The cable unfolds from the vertical solar array's reel during travel to avoid dragging or getting caught on the harsh lunar terrain. Once the LIT has ejected, the landing vehicle's stationary vertical solar array is positioned vertically and begins generating and storing electricity.

[0055] At 204, a second vertical solar array is delivered by the lunar vehicle to a second lunar site. When the LIT arrives at its other destination in the pair, the vertical solar array is deployed and awaits its turn to generate and store energy. Once both vertical solar arrays are deployed and connected, the two systems alternate generating power to keep the other system warm during the short periods of low sunlight.

[0056] At 205, power is collected by the first vertical solar array and the second vertical solar array for storage in the power storage device and transmission via the power feed interface. The Lunar Rover then exits the LIT under its own power and begins traveling towards the surface assets requiring power. As with the LIT, the cable is unrolled from a reel on the CubeSat itself while traveling to avoid dragging or getting caught on the lunar terrain. Once the assets are reached, the Lunar Rover begins delivering power via a wireless proximity feeder and, for particularly high power assets, via a self-aligning physical connector.

[0057] 5, with continuing reference to the previous figures, there is shown another embodiment of a system, generally designated 300, for establishing a lunar power grid. Similar to the embodiment shown in Figures 1-3, system 300 includes a landing vehicle 310, a pair of vertical solar arrays 312-314, a power feed interface 316, and a power storage device 318. Vertical solar arrays 312-314, power feed interface 316, and power storage device 318 are connected to each other by a cable 320 for transmitting power therebetween.

[0058] Landing vehicle 310 lands on the lunar surface 322 at one of two preselected lunar sites 324-326 and deploys vertical solar array 312. System 300 may include a number of mobile power outlets 328-332 that receive power from power interface 316 and are capable of traveling to various other lunar sites, such as lunar asset 334.

[0059] 1-3, the system 300 may include a second landing vehicle 336 for landing the vertical solar array 314 at a second one of the preselected lunar sites 324-326. In such an embodiment, a lunar vehicle, such as a mobile power outlet 328, may carry one end of a cable 320 to the vertical solar array 314 for connecting the vertical solar arrays 312-314 to one another.

[0060] Although FIG. 5 illustrates system 300 with two landing vehicles (i.e., landing vehicle 310 and landing vehicle 336), it should be understood that other systems are contemplated with three or more landing vehicles for transporting components of the lunar power grid.

[0061] 6, there is shown a process for establishing a lunar power grid on the moon, generally designated 400. The process 400 can be accomplished by using the system 300 of FIG.

[0062] At 401, a pre-selected pair of lunar sites is identified, the pair consisting of a first lunar site and a second lunar site. In this exemplary embodiment, the lunar sites may be identified in the same manner as the sites were identified in step 201 of process 200 shown in FIG. 4, or by any other suitable technique or method.

[0063] At 402, a first landing vehicle having a first vertical solar array lands at a first lunar site. In this exemplary embodiment, the landing vehicle may be landing vehicle 310 shown in FIG.

[0064] At 403, a second landing vehicle having a second vertical solar array lands at a second lunar site. In this exemplary embodiment, the landing vehicle may be landing vehicle 336 shown in FIG.

[0065] At 404, the power storage device and the power feed interface are connected to the first vertical solar array and the second vertical solar array with cables. At 405, power is collected by the first vertical solar array and the second vertical solar array for storage in the power storage device and transmission via the power feed interface. In this exemplary embodiment, the vertical solar arrays, the power feed interface, the power storage device, and the cable may be the vertical solar arrays 312-314, the power feed interface 316, the power storage device 318, and the cable 320 shown in FIG. 5.

[0066] Although the disclosed systems, methods, and apparatus are described within a system for constructing a lunar grid, it is understood that the disclosed systems, methods, and apparatus may be applied on other celestial bodies or on Earth.

[0067] Supported Features and Implementations Supported embodiments may provide various ancillary and / or technical advantages over a system that utilizes tethered vertical solar arrays placed at pairs of strategic lunar sites to alternately generate and store power. The system operates by continuously generating and storing power. Furthermore, batteries can be swapped out over time to provide continuous, uninterrupted power generation on the lunar surface.

[0068] The system is independent and self-contained. It can offload, transport, and install components without requiring support from NASA or from previously landed surface assets. The system has fully integrated its own escape, mobility, cable deployment, and cable attachment capabilities. The system may be delivered in a single launch and lunar landing prior to other mission activities.

[0069] The system is scalable, allowing for optional expansion: while the system can be integrated into a single launch vehicle and deployed with a single lunar landing vehicle, the system can be scaled up by adding additional vertical solar array units across the lunar surface, thus extending the range of operation and power supply to new areas beyond the initial system deployment site.

[0070] The system provides mobile power. Rather than statically generating power and offloading the power distribution and connectivity requirements to lunar assets, the system distributes power through the use of rovers, which act as mobile outlets to power habitats, experiments, rovers, and other hardware through wired and wireless power sources.

[0071] The detailed description provided above in conjunction with the accompanying drawings is intended as a description of the example embodiment and is not intended to represent the only form in which the example embodiment may be constructed or utilized. It is understood that the configurations and / or approaches described herein are exemplary in nature and that the described embodiments, implementations and / or examples are not to be considered in a limiting sense, as numerous variations are possible.

[0072] Although the present subject matter has been described in language specific to structural features and / or methodological acts, it is understood that the subject matter defined in the appended claims is not necessarily limited to the specific features or acts described above. Rather, the specific features and acts described above are presented as example forms of implementing the claims.

Claims

1. A lunar power grid assembly for deployment on a lunar surface having a pair of pre-selected lunar sites consisting of a first lunar site and a second lunar site, A pair of interconnected vertical solar arrays, comprising a first vertical solar array located at a first lunar site to collect solar energy, and a second vertical solar array located at a second lunar site to collect solar energy, A cable for transmitting power between the first vertical solar cell array and the second vertical solar cell array, A storage device that receives solar energy from a first vertical solar cell array and a second vertical solar cell array, A power supply interface for distributing energy to one or more lunar surface devices on the lunar surface, A landing vehicle having a payload including at least one of the interconnected pair of vertical solar cell arrays, the cables, the energy storage device, and the power supply interface, A lunar power grid assembly equipped with the above.

2. The lunar power grid assembly according to claim 1, wherein the payload includes the pair of interconnected vertical solar cell arrays, the cables, the energy storage device, and the power supply interface.

3. The lunar power grid assembly according to claim 2, wherein a second vertical solar cell array is mounted on a lunar vehicle, the landing vehicle lands on a first lunar site and positions the first vertical solar cell array, and the lunar vehicle transports the second vertical solar cell array to the second lunar site.

4. The lunar power grid assembly according to claim 3, wherein the lunar vehicle is an autonomous self-driving trailer.

5. The lunar power grid assembly according to claim 4, wherein the payload includes a plurality of mobile power outlets.

6. The lunar power grid assembly according to claim 5, wherein the plurality of mobile power outlets are stored in the autonomous self-driving trailer before the landing vehicle lands on the first lunar site.

7. The lunar power grid assembly according to claim 5, wherein each of the plurality of mobile power outlets is a lunar rover.

8. The lunar power grid assembly according to claim 3, wherein the lunar vehicle is connected to the landing vehicle.

9. The lunar power grid assembly according to claim 2, wherein the landing vehicle includes a braking stage.

10. It further includes at least one surface vehicle selected from a group consisting of lunar vehicles, mobile power outlets, and rovers. The landing vehicle is one of a pair of landing vehicles consisting of a first landing vehicle and a second landing vehicle, wherein the first vertical solar cell array is mounted on the first landing vehicle and the second vertical solar cell array is mounted on the second landing vehicle. The first landing vehicle lands at the first lunar site and deploys the first vertical solar array, the second landing vehicle lands at the second lunar site and deploys the second vertical solar array, The lunar power grid assembly according to claim 1, wherein the surface vehicle can carry one end of a cable across the lunar surface from one of the pair of vertical solar cell arrays to the other vertical solar cell array, thereby connecting the pair of vertical solar cell arrays to each other.

11. The lunar power grid assembly according to claim 1, wherein the power supply interface can supply power to lunar devices selected from the group consisting of mobile power supply outlets, scientific instruments, tools, surface rovers, communication antennas, and mining equipment.

12. The lunar power grid assembly according to claim 1, wherein the first vertical solar cell array and the second vertical solar cell array are vertical solar cell array technology generators.

13. The lunar power grid assembly according to claim 1, wherein the first lunar site and the second lunar site have landing surfaces having an inclination of less than approximately 10 degrees.

14. The lunar power grid assembly according to claim 1, wherein the energy storage device is a battery.

15. A method for constructing a lunar power grid on the lunar surface, A step of identifying a pre-selected pair of lunar sites, consisting of a first lunar site and a second lunar site, The process of preparing a landing vehicle having a pair of interconnected vertical solar arrays consisting of a first vertical solar array and a second vertical solar array mounted on a lunar vehicle, a cable for transmitting power between them, a power supply interface, and a power storage device connected thereto, The process involves landing the landing vehicle on a first lunar site and placing a first vertical solar cell array there, The process of transporting the second vertical solar cell array to the second lunar site by the lunar vehicle, The process involves collecting power in a first vertical solar cell array and a second vertical solar cell array for storage in the energy storage device and transmission via the power supply interface, Methods that include...

16. The process involves, when the first vertical solar cell array is not collecting power, sending power from the second vertical solar cell array to the first vertical solar cell array to heat the first vertical solar cell array, When the second vertical solar cell array is not collecting power, the process involves sending power from the first vertical solar cell array to the second vertical solar cell array to heat the second vertical solar cell array. The method according to claim 15, including the method described in claim 15.

17. A method for constructing a lunar power grid on the lunar surface, A step of identifying a pre-selected pair of lunar sites, consisting of a first lunar site and a second lunar site, The process of landing a first landing vehicle having a first vertical solar cell array on a first lunar site, The process of landing a second landing vehicle having a second vertical solar cell array on a second lunar site, The process involves connecting the energy storage device and the power supply interface to the first vertical solar cell array and the second vertical solar cell array with a cable, The process involves collecting power in a first vertical solar cell array and a second vertical solar cell array for storage in the energy storage device and transmission via the power supply interface, Methods that include...

18. The process involves, when the first vertical solar cell array is not collecting power, sending power from the second vertical solar cell array to the first vertical solar cell array to heat the first vertical solar cell array, When the second vertical solar cell array is not collecting power, the process involves sending power from the first vertical solar cell array to the second vertical solar cell array to heat the second vertical solar cell array. The method according to claim 17, including the method described in claim 17.

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