Information processing system, information processing method, and program

Abstract

The present invention comprises at least one processor that outputs information about a mission on a celestial body other than the Earth by executing the processing corresponding to the operation by a user in accordance with the operation using at least one of water resource data corresponding to each site of the celestial body other than the Earth, environment data corresponding to each site of the celestial body other than the Earth, a specification and / or a given set value of a rover, a specification and / or a given set value of a device, an input value by the user, and a given set value.

Description

Information processing system, information processing method and program

[0001] The present invention relates to an information processing system, an information processing method, and a program.

[0002] BACKGROUND ART Conventionally, exploration of celestial bodies other than the Earth (for example, the Moon, Mars, etc.) has been carried out, and rovers capable of traveling on celestial bodies (for example, the Moon, Mars, etc.) have been developed (see, for example, Patent Document 1).

[0003] Japanese Patent Application Publication No. 9-272473

[0004] An information processing system according to a first aspect of the present invention includes at least one processor that outputs information relating to a mission on a celestial body other than Earth by executing processing in response to a user operation using at least one of water resource data corresponding to each point on the celestial body other than Earth, environmental data corresponding to each point on the celestial body other than Earth, rover specifications and / or given setting values, device specifications and / or given setting values, user input values, and given setting values.

[0005] An information processing system according to a second aspect of the present invention is the information processing system according to the first aspect, wherein the output information relating to the mission is information relating to at least one of the rover's exploration route and / or energy consumption, the amount of water extracted by a water decomposition device, the amount of power generated by a fuel cell, or the amount of hydrogen or oxygen produced.

[0006] An information processing system according to a third aspect of the present invention is an information processing system according to the first or second aspect, further comprising at least one storage device in which water resource data including water reserves and / or predicted water content of regolith is stored for each position on a celestial body other than the Earth, and the at least one processor updates the water resource data corresponding to each point on the celestial body other than the Earth in accordance with the results of remote sensing by a sensor mounted on a satellite orbiting the celestial body other than the Earth and / or detection by a sensor mounted on the surface or underground of the celestial body other than the Earth.

[0007] An information processing system according to a fourth aspect of the present invention is the information processing system according to the third aspect, wherein the at least one processor uses the updated water resource data to simulate a mission on a celestial body other than Earth and outputs information regarding the simulation results.

[0008] An information processing system according to a fifth aspect of the present invention is an information processing system according to the first aspect, wherein the information relating to the mission is the acquisition cost of water resources at a location specified by the user, and the at least one processor outputs the acquisition cost of water resources at the location specified by the user using environmental data corresponding to each point on the celestial body other than the Earth.

[0009] An information processing system according to a sixth aspect of the present invention is the information processing system according to the first aspect, wherein the device is a water decomposition device, the information related to the mission is information related to water extraction, and the at least one processor outputs information related to water extraction by using the specifications of the water decomposition device and / or given setting values ​​in addition to the water resource data and performing processing corresponding to the operation in response to the operation by the user.

[0010] An information processing system according to a seventh aspect of the present invention is the information processing system according to the sixth aspect, wherein the information regarding water extraction is the amount of water produced per unit time and / or the time required to obtain the target amount of water, the water resource data is the predicted water content of the regolith, and the at least one processor outputs the amount of water produced per unit time and / or the time required to obtain the target amount of water using the efficiency of the water decomposition device to extract water from the regolith, the weight of regolith that can be processed per unit time by the water decomposition device, and the predicted water content of the regolith.

[0011] An information processing system according to an eighth aspect of the present invention is the information processing system according to the first aspect, wherein when a starting point on a celestial body other than Earth and at least one target point on the celestial body other than Earth are input, the at least one processor outputs at least one of a first candidate route from the starting point to the target point, the distance of the first candidate route, and the maximum slope of the first candidate route.

[0012] An information processing system according to a ninth aspect of the present invention is the information processing system according to the eighth aspect, wherein the at least one processor outputs the difference in maximum slope and / or the difference in distance between the first candidate route and one or more second candidate routes other than the first candidate route.

[0013] An information processing system according to a tenth aspect of the present invention is the information processing system according to the ninth aspect, wherein the at least one processor outputs recommended specifications for a rover corresponding to the second candidate route.

[0014] An information processing system according to an eleventh aspect of the present invention is the information processing system according to any one of the eighth to tenth aspects, and includes at least one storage device in which the relationship between the ratio of horizontal tractive force to vertical load and the slip ratio for each speed of the rover is stored, and when the set speed of the rover is received from a user, the at least one processor calculates the ratio of horizontal tractive force to vertical load at each point of movement of the rover, determines a slip ratio corresponding to the calculated ratio based on the relationship stored in the storage device, and outputs a predicted arrival time or required time to reach the target point using the slip ratio.

[0015] An information processing system according to a twelfth aspect of the present invention is the information processing system according to any one of the eighth to eleventh aspects, and includes at least one storage device in which a relationship between the ratio of horizontal traction force to vertical load and the slip ratio is stored for at least the minimum set speed of the rover, and the at least one processor updates the relationship between the ratio of horizontal traction force to vertical load and the slip ratio stored in the storage device using information acquired on the celestial body other than the Earth, and outputs the maximum climbable inclination angle of the rover by referring to the updated relationship.

[0016] An information processing system according to a thirteenth aspect of the present invention is the information processing system according to the first aspect, wherein the device is one or more fuel cells, and when a user inputs a mission period in addition to a target location on the celestial body other than Earth, the at least one processor calculates the amount of electricity to be generated by the rover's solar panels at the target location taking into account the mission period, and outputs the amount of hydrogen / oxygen to be generated by the fuel cell during the daytime of the mission period on the celestial body other than Earth using that amount of electricity.

[0017] An information processing system according to a fourteenth aspect of the present invention is the information processing system according to the thirteenth aspect, wherein the at least one processor outputs an extension period or a total period of the mission by operating the rover in low power mode at night on the celestial body other than Earth using a reserve amount of hydrogen and a reserve amount of oxygen obtained from the amount of hydrogen / oxygen produced in a fuel cell during the daytime on the celestial body other than Earth.

[0018] An information processing system according to a fifteenth aspect of the present invention is an information processing system according to any one of the first to fourteenth aspects, and includes a storage device in which the latitude, longitude, and altitude of the lunar surface are stored in association with each other, and when the at least one processor receives from a user a latitude, longitude, and a search range centered on a point of said latitude and longitude, it searches the storage device and outputs a point whose slope falls within a predetermined range as a candidate landing point.

[0019] An information processing system according to a sixteenth aspect of the present invention is an information processing system according to any one of the first to fifteenth aspects, wherein when the at least one processor receives a location and period of the celestial body other than the Earth from a user, the at least one processor outputs a period during which the mission can be continued for a divided period obtained by dividing the period.

[0020] An information processing system according to a seventeenth aspect of the present invention is an information processing system according to any one of the first to sixteenth aspects, comprising a storage device in which information on the daytime periods of the celestial body other than the Earth and / or the nighttime periods of the celestial body other than the Earth is stored in unit time increments, and the at least one processor refers to the storage device to obtain, for each mission start date, whether it is daytime or nighttime for each unit time after the mission start date, and if it is daytime, calculates the amount of power generated from the solar panel and the amount of oxygen and hydrogen produced by the fuel cell from that amount of power generation, and if it is nighttime, calculates how long the fuel cell will be able to generate power from oxygen and hydrogen, and thereby outputs the mission continuation period for each mission start date.

[0021] An information processing system according to an 18th aspect of the present invention is an information processing system according to any one of the first to 17 aspects, and includes a storage device in which information on the daytime periods of the celestial body other than the Earth and / or the nighttime periods of the celestial body other than the Earth is stored in unit time increments, and when the at least one processor receives latitude, longitude, and mission start date, it refers to the storage device and obtains whether it is daytime or nighttime for each unit time after the mission start date for each point within a predetermined range centered on the latitude and longitude specified by the user, and if it is daytime, calculates the amount of power generated from the solar panels and the amount of oxygen and hydrogen generated by the fuel cell from that amount of power generation, and if it is nighttime, calculates how long the fuel cell can generate power from oxygen and hydrogen and output the mission continuation period for each point.

[0022] An information processing system according to a 19th aspect of the present invention is an information processing system according to any one of the first to eighteenth aspects, and includes a storage device in which latitude, longitude, and altitude of the celestial body other than the Earth are stored in association with each other, and when the at least one processor receives a latitude and longitude that is a landing candidate on the celestial body other than the Earth, the at least one processor refers to the storage device and calculates the landing success probability for each point within a predetermined range centered on the latitude and longitude specified by the user according to a predetermined formula, thereby outputting the landing success probability for each point.

[0023] An information processing method according to a twentieth aspect of the present invention includes a step of outputting information related to a mission on a celestial body other than Earth by performing processing in response to a user operation using at least one of water resource data corresponding to each point on the celestial body other than Earth, environmental data corresponding to each point on the celestial body other than Earth, rover specifications and / or given setting values, device specifications and / or given setting values, user input values, and given setting values.

[0024] A program according to a 21st aspect of the present invention is a program for causing a computer to execute a step of outputting information regarding a mission on a celestial body other than Earth by performing processing in response to a user operation using at least one of water resource data corresponding to each point on the celestial body other than Earth, environmental data corresponding to each point on the celestial body other than Earth, rover specifications and / or given setting values, device specifications and / or given setting values, user input values, and given setting values.

[0025] According to one aspect of the present invention, a user can grasp information about a mission in advance, thereby making it possible to make a mission plan more efficient.

[0026] 1 is a conceptual diagram according to the present embodiment. FIG. 1 is a conceptual diagram of a flow for realizing efficiency or optimization of mission planning. FIG. 2 is a table showing an example of feedback between a digital virtual lunar space, the Earth, and the Moon. FIG. 3 is a schematic diagram for explaining data collection. FIG. 4 is a schematic diagram of an information processing system according to the present embodiment. FIG. 5 is a schematic diagram of a terminal according to the present embodiment. FIG. 6 is a schematic diagram of a computer system according to the present embodiment. FIG. 7 is an example of screen transitions related to water collection displayed on a terminal. FIG. 8 is an example of screen transitions related to a rover's exploration route displayed on a terminal. FIG. 9 is a schematic diagram showing a dynamic model of a wheel. FIG. 10 is a graph showing an example of the relationship between the ratio of horizontal traction force to vertical load and the slip ratio. FIG. 11 is a schematic cross-sectional view showing an example of a rover configuration. FIG. 12 is a schematic diagram explaining water splitting using a fuel cell. FIG. 13 is a schematic diagram explaining power generated by a fuel cell. FIG. 14 is an example of screen transitions related to power generation using solar panels. FIG. 14 is a diagram showing the angle of sunlight, the angle and tilt angle of the solar panel. FIG. 15 is an example of a search screen for candidate landing sites. FIG. 16 is an example of a bar graph showing the possible mission continuation period for each mission start date and time. FIG. 17 is an example of a screen displaying the possible mission continuation period for each point on the lunar surface in different colors. FIG. 18 is an example of a screen including a graph displaying the probability of landing success at each point on the lunar surface in different colors.

[0027] Hereinafter, each embodiment will be described with reference to the drawings. However, unnecessary detailed description may be omitted. For example, detailed description of well-known matters or redundant description of substantially the same configuration may be omitted. This is to avoid unnecessary redundancy in the following description and to facilitate understanding by those skilled in the art.

[0028] When exploring celestial bodies other than Earth (such as the Moon or Mars), a mission plan must be prepared in advance, but this process is labor-intensive and time-consuming, so there is a need to make the process more efficient.

[0029] One aspect of the present embodiment has been made in consideration of the above-mentioned problems, and one of its objectives is to provide an information processing system, an information processing method, and a program that enable efficient creation of mission plans.

[0030] In response to this problem, the inventors of the present application came up with the idea of ​​applying conventional digital twins to create a digital virtual space by recreating the conditions of celestial bodies other than Earth (e.g., the Moon, Mars, etc.) on a computer using various data collected from such bodies. The inventors then came up with the idea of ​​improving the efficiency or optimization of mission planning by performing simulations, analyses, or optimizations of rover exploration, water splitting, fuel cell power generation, etc. in this digital virtual space. Here, digital twins refer to technology for recreating various data collected from the real world on a computer.

[0031] In the following, as a specific example, the moon will be used as an example of a celestial body other than the Earth, and a digital virtual lunar space will be described as an example of a digital virtual space.

[0032] Figure 1 is a conceptual diagram of this embodiment. As shown in Figure 1, various data collected from the Moon are used to recreate the conditions on the Moon on a computer, creating a digital virtual lunar space. Furthermore, missing data is supplemented by data obtained from experimental results on Earth.

[0033] FIG. 2 is a conceptual diagram of a flow for achieving efficiency or optimization of mission planning. Mission planning is made more efficient or optimized by conducting simulations, analyses, or optimizations of rover exploration, water splitting, fuel cell power generation, etc. in a digital virtual lunar space on Earth. Meanwhile, data on exploration, water splitting, power generation, etc. during a mission on the actual lunar surface is collected, and the collected data is reflected in the digital virtual lunar space. This improves the accuracy of simulations, analyses, or optimizations in the digital virtual lunar space, thereby making mission planning more efficient or optimized. Repeating this cycle improves the degree of efficiency or optimization of mission planning.

[0034] Figure 3 is a table showing an example of feedback between the digital virtual lunar space, the Earth, and the Moon. Examples of feedback are explained for water exploration by a rover, water splitting, and power generation by fuel cells. Hereinafter, the digital virtual lunar space will also be referred to as digital space.

[0035] 1. Water exploration by rover (1) Feedback from the digital lunar virtual space to experiments on Earth: Using the simulation results in digital space, the most efficient route and rover hardware are reproduced in ground experiments at a scale of 1 / x (x is a natural number). (2) Feedback from experiments on Earth to digital space: The ground experiment values ​​(energy and cost efficiency) of tire slip conditions are reflected in the simulation. (3) Feedback from experiments on Earth to the lunar mission: The results of the ground experiment are used to determine the most energy-efficient tires and drive components. (4) Feedback from the lunar mission to experiments on Earth: The conditions of the experiments on Earth are modified based on the tire slip data obtained on the lunar surface. (5) Feedback from the digital lunar virtual space to the lunar mission: The simulation results are used to determine the most efficient route. (6) Feedback from the lunar mission to digital lunar virtual space: The tire slip data obtained on the lunar surface is fed back into the simulation equations in the digital lunar virtual space.

[0036] 2 Water Splitting (1) Feedback from the Digital Virtual Lunar Space to Experiments on Earth: Simulation results from the digital virtual lunar space are used to recreate the most efficient water splitting equipment hardware for experiments on Earth at a scale of 1 / x (x is a natural number). (2) Feedback from Experiments on Earth to Digital Space: Ground experimental values ​​(energy and cost efficiency) of water splitting conditions are reflected in the simulation. (3) Feedback from Experiments on Earth to the Lunar Mission: The results of the ground experiment are used to determine the most energy-efficient device components. (4) Feedback from the Lunar Mission to Experiments on Earth: The conditions of the ground experiment are modified based on the efficiency data of the water splitting equipment obtained on the lunar surface. (5) Feedback from the Digital Virtual Lunar Space to the Lunar Mission: Simulation results are used to determine the most efficient components and mission plan. (6) Feedback from the Lunar Mission to the Digital Virtual Lunar Space: The efficiency data of the water splitting equipment obtained on the lunar surface is fed back into the simulation calculations in the digital virtual lunar space.

[0037] 3 Power Generation by Fuel Cells (1) Feedback from the Digital Virtual Lunar Space to Experiments on Earth: Simulation results from the digital virtual lunar space are used to recreate the most efficient fuel cell hardware for experiments on Earth at a scale of 1 / x (x is a natural number). (2) Feedback from Experiments on Earth to Digital Space: Ground experimental values ​​(resource and cost efficiency) for power generation conditions are reflected in the simulation. (3) Feedback from Experiments on Earth to the Lunar Mission: The results of the experiments on Earth are used to determine the most energy-efficient device components. (4) Feedback from the Lunar Mission to Experiments on Earth: The conditions for the ground experiments are modified based on fuel cell efficiency data obtained on the lunar surface. (5) Feedback from the Digital Virtual Lunar Space to the Lunar Mission: Simulation results are used to determine the most efficient components and mission plan. (6) Feedback from the Lunar Mission to the Digital Virtual Lunar Space: Fuel cell efficiency data obtained on the lunar surface is fed back into the simulation calculations in the digital virtual lunar space.

[0038] For example, remote sensing from satellites orbiting celestial bodies other than Earth and / or detection results from sensors installed on the surface or underground of the celestial body other than Earth (e.g., the Moon, Mars, etc.) and / or infrastructure operation and management data for activities on the celestial body other than Earth (e.g., the Moon, Mars, etc.) are collected. By reflecting the collected data in a digital virtual space, which is a virtual model, events occurring in the physical space of the celestial body other than Earth (e.g., the Moon, Mars, etc.) are reproduced in the digital virtual space. This data collection is performed, for example, in real time.

[0039] <Data Management of Hydrogen Value Chain> Figure 4 is a schematic diagram for explaining data collection. First, using Figure 4, management of the hydrogen value chain on the lunar surface will be explained. Infrastructure operation management data (e.g., hydrogen value chain management data) for activities on the lunar surface is collected, for example, in real time, transferred to Earth via satellites 101, 102, and 103 orbiting the Moon, and accumulated as data in a digital virtual space on the lunar surface.

[0040] Here, the hydrogen value chain management data includes, for example, the amount of hydrogen stored at each location on the lunar surface. Specifically, for example, a tank for storing hydrogen (hereinafter also referred to as a hydrogen tank) may be provided with a sensor device. In this case, the sensor device may include, for example, a sensor for detecting the amount of stored hydrogen, a GPS receiver, and a wireless communication module for communicating with satellites 101, 102, and 103. If the hydrogen tank stores liquid hydrogen, the sensor may be a water level gauge for measuring the liquid level.

[0041] The satellites 101, 102, and 103 are, for example, GPS (Global Positioning System) satellites. The signals from the satellites 101, 102, and 103 include time data from the atomic clocks installed on the satellites, information about the satellite's astronomical ephemeris (orbit), and so on. The sensor device receives radio waves from the satellites 101, 102, and 103, measures the time of transmission, and determines the distance from the satellite by multiplying the time difference between transmission and reception by the propagation speed of the radio waves (the speed of light). The GPS receiver receives radio waves from three or more satellites 101, 102, and 103 and simultaneously calculates the exact time of reception and the receiver coordinates (a point in three-dimensional space) through positioning calculations.

[0042] Specifically, for example, the principle of GPS positioning is based on the fact that the speed of light, c, is constant in a local inertial system. If both the GPS satellite and the GPS receiver have clocks that can be considered accurate, the distance can be obtained by multiplying the difference between the transmission time (measurement value) T and the reception time, t, by the speed of light, c. If the position of GPS satellite i is represented by coordinates (Xi, Yi, Zi) and the position of the GPS receiver is represented by (x, y, z), the following relationship holds:

[0043]

[0044] To obtain the position of a GPS satellite, the navigation message signal superimposed on the received data is demodulated and combined with the transmission time. This reception time t is the value of the GPS receiver's clock. Here, as an example, we assume that the GPS receiver's clock is accurate. The three variables (unknowns) x, y, and z that represent the GPS receiver's position can be found by solving three simultaneous equations into which the coordinates of three different GPS satellites (here, satellites 101, 102, and 103) are substituted.

[0045] This determines the position on the lunar surface. The wireless communication module transmits pairs of the determined GPS receiver positions (i.e., the hydrogen tank positions) and the detected amount of hydrogen to satellites 101, 102, and 103, which then transfer them to Earth and store them as data in a digital virtual space on the lunar surface. This makes it possible to manage the amount of hydrogen stored at each position on the lunar surface on Earth, for example, without delay.

[0046] If the GPS receiver clock is not very accurate, the reception time t must also be an unknown, so these four unknowns can be determined by receiving signals from four or more satellites.

[0047] <Water Resources Data Management> Next, using FIG. 4 , we will explain how to manage data on water resources buried on the moon. The amount of water resources buried on the moon is estimated through remote sensing using sensors installed on satellites 101-103 orbiting the moon. For example, the satellites 101-103 may be equipped with a processor, an irradiation mechanism for emitting electromagnetic waves (e.g., a synthetic aperture radar (SAR)), and a sensor. The electromagnetic waves emitted from the irradiation mechanism are reflected by the lunar surface, and the sensors on the satellites 101-103 may estimate the amount of water resources by observing the reflected electromagnetic waves. If the irradiation mechanism is SAR, it may irradiate microwaves or millimeter waves. Alternatively, the irradiation mechanism may irradiate terahertz waves. While the example described here is one in which the satellites 101-103 are equipped with irradiation mechanisms, this is not limiting. The satellites 101-103 may also be equipped with, for example, a visible light camera or an infrared camera. In this case, the visible light camera or infrared camera may capture an image of the lunar surface, and the amount of water resources may be estimated from the captured image. Here, the estimation of the amount of water resources may be performed by a processor on one of the satellites 101 to 103, or by the processor 26 of the computer system 2 on Earth.

[0048] The following describes a case where the amount of water resources is estimated by the processors of the satellites 101 to 103. In this case, pairs of reflection positions on the lunar surface and amounts of water resources are transferred to Earth by the satellites 101, 102, and 103 and accumulated as part of the data of the digital virtual lunar space in a storage device on Earth (for example, the storage device 23 of the computer system 2). This makes it possible to manage the water resource data at each position on the lunar surface on Earth, for example, without delay.

[0049] Additionally or alternatively, the amount of water resources may be detected by a sensor device installed on the surface or underground of the moon, in which case the sensor device may include a sensor for detecting the amount of water resources, a wireless communication module for wirelessly communicating with the satellites 101 to 103, and a GPS receiver. As a result, the amount of water resources detected by the sensor and the position determined by the GPS receiver may be transmitted to the satellites 101 to 103 by the wireless communication module.

[0050] In this case, a set of the amount of water resources detected by the sensor and the position determined by the GPS receiver is transmitted to Earth via satellites 101, 102, and 103 and stored as part of the data of the digital virtual lunar space in a storage device on Earth (for example, storage device 23 of computer system 2). This makes it possible to manage water resource data at each position on the lunar surface on Earth, for example, without delay.

[0051] Fig. 5 is a schematic configuration diagram of an information processing system according to this embodiment. As shown in Fig. 5, the information processing system S includes terminals 1-1, ..., 1-N (N is a natural number) and a computer system 2. Each of the terminals 1-1, ..., 1-N is communicatively connected to the computer system 2 via a communication network CN. Here, the terminals 1-1, ..., 1-N are, for example, computers such as smartphones, tablet terminals, laptops, or personal computers. Hereinafter, the terminals 1-1, ..., 1-N will also be collectively referred to as terminals 1.

[0052] Fig. 6 is a schematic diagram of a terminal according to this embodiment. As shown in Fig. 6, the terminal 1 includes an input interface 11, a communication module 12, a storage device 13, a memory 14, an output interface 15, and a processor 16. While the terminal 1 is described as including one processor 16 in one embodiment, it may include multiple processors, i.e., it is sufficient to include one or more processors. Furthermore, the terminal 1 is described as including one storage device 13 in one embodiment, but it may include multiple processors, i.e., it is sufficient to include one or more storage devices.

[0053] The input interface 11 receives input from a user and outputs an input signal corresponding to the received input to the processor 16. The communication module 12 is connected to the communication network CN and communicates with the computer system 2. This communication may be wired or wireless.

[0054] The storage device 13 is, for example, a storage device, and stores programs that the processor 16 reads and executes. The memory 14 temporarily holds data and programs. The memory 14 is a volatile memory, for example, a random access memory (RAM). The output interface 15 can be connected to, for example, a display 17, and can output, for example, a video signal to the display 17. The processor 16 loads programs from the storage device 13 into the memory 14 and executes a series of instructions included in the programs to perform various processes. Note that, although the display 17 is described as being external to the terminal 1, it may also be built into the terminal 1.

[0055] 7 is a schematic diagram of a computer system according to this embodiment. As shown in FIG. 7, the computer system 2 includes an input interface 21, a communication module 22, a storage device 23, a memory 24, an output interface 25, and a processor 26. While the computer system 2 is described as including one processor 26 in one embodiment, it may include multiple processors, i.e., it may include one or more processors. Additionally, the computer system 2 is described as including one storage device 23 in one embodiment, but it may include multiple storage devices, i.e., it may include one or more storage devices.

[0056] The input interface 21 accepts input from an administrator of the computer system 2 (e.g., an employee of the management organization) and outputs an input signal corresponding to the accepted input to the processor 26. The communication module 22 is connected to the communication network CN and communicates with each of the terminals 1-1, ..., 1-N. This communication may be wired or wireless.

[0057] The storage device 23 is, for example, a storage device that stores programs and various data to be read and executed by the processor 26. The memory 24 temporarily holds data and programs. The memory 24 is a volatile memory, for example, a random access memory (RAM). The output interface 25 can be connected to an external device and can output signals to the external device. The processor 26 loads programs from the storage device 23 into the memory 24 and executes a series of instructions included in the programs to perform various processes.

[0058] <Outline of Processing by Processor 26> An outline of processing by the processor 26 will be described. In one aspect, the processor 26 outputs information about a mission on a celestial body other than the Earth (e.g., the Moon), using at least one of water resource data corresponding to each point on the celestial body other than the Earth, environmental data corresponding to each point on the celestial body other than the Earth, specifications and / or given setting values ​​of a rover, specifications and / or given setting values ​​of a device (e.g., a water cracking device, a fuel cell, etc.), a value input by a user, and a given setting value, by executing processing according to the operation in response to the user operation.

[0059] The mission-related information output here may be the cost of acquiring water resources at a location designated by the user. In this case, processor 26 may output the cost of acquiring water resources at a location designated by the user using environmental data (e.g., topography) corresponding to each location on the celestial body other than Earth. For example, the cost of acquiring water resources may be set to be greater the longer the distance from the start point to the destination point. Additionally or alternatively, the cost of acquiring water resources may be set to be greater the steeper the gradient of the topography from the start point to the destination point.

[0060] In one aspect, water resource data including water reserves and / or predicted water content of regolith is stored for each location on a celestial body other than the Earth in the storage device 23. In this case, the processor 26 updates the water resource data corresponding to each location on the celestial body other than the Earth (e.g., the Moon) in accordance with remote sensing results obtained by a sensor mounted on a satellite orbiting the celestial body other than the Earth (e.g., the Moon) and / or detection results obtained by a sensor mounted on the surface or underground of the celestial body other than the Earth.

[0061] In one aspect, processor 26 simulates a mission to the non-Earth celestial body (e.g., the Moon) using the updated water resource data and outputs information regarding the simulation results.

[0062] 8 shows an example of screen transitions related to water collection displayed on the terminal. As shown in FIG. 8, on screen G1, the user can input the latitude and longitude of the target spot for water collection on the lunar surface, the mission start time (e.g., start date), end time (e.g., end date), maximum efficiency of the water splitting device, and processing speed. Thus, the user of terminal 1 can set these parameters by inputting them.

[0063] As shown in Fig. 8, when the "Send" button is pressed on screen G1, the screen transitions to screen G2. Screen G2 visualizes a three-dimensional map of the vicinity of the latitude and longitude of the target point and areas of buried water on the three-dimensional map. As an example of visualization, the areas of buried water on the three-dimensional map are colored (e.g., colored light blue).

[0064] Also shown on screen G2 is a display of a preset water reserve percentage (e.g., 250 ppm) and the output of the water splitting device (e.g., 198.625 ppm). The output of the water splitting device is calculated by processor 26 as the product of the preset water reserve percentage and the maximum efficiency of the water splitting device.

[0065] <Specific Example of Method for Outputting Water Reserve Locations> The processing of the computer system 2 up to the output of the screen G2 will be described. Water resource data is stored in the storage device 23. Specifically, for example, the storage device 23 stores records of pairs of water reserves and positions on the lunar surface (e.g., latitude and longitude). The processor 26 of the computer system 2 may refer to the storage device 23 to obtain the water reserves at each point within a predetermined range based on the latitude and longitude of a target point input by the user, and output information visualizing the areas where water is buried on a three-dimensional map.

[0066] <Method of outputting the amount of water produced per unit time and / or the time required to obtain the target amount of water> The amount of water produced per unit time is calculated by multiplying the efficiency of the water splitting device for extracting water from regolith (e.g., 79.45%), the weight of regolith that can be processed per unit time by the water splitting device (e.g., 100 kg / h), and the predicted water content of the regolith (e.g., 250 ppm). Furthermore, if a target amount of water is set or input by the user, the time required to obtain the target amount of water can be obtained by dividing the target amount of water by the amount of water produced per unit time.

[0067] In this manner, the processor 26 may output information regarding water extraction by using the specifications of the water splitting device and / or given settings in addition to the water resource data and performing processing according to the user's operation.

[0068] Here, for example, the mission-related information may be the amount of water produced per unit time and / or the time required to obtain the target amount of water. In this case, processor 26 may output the amount of water produced per unit time and / or the time required to obtain the target amount of water using the efficiency of the water decomposition device for extracting water from regolith, the weight of regolith that can be processed per unit time by the water decomposition device, and the predicted water content of the regolith included in the water resource data.

[0069] 9 shows an example of screen transitions related to the rover's exploration route displayed on the terminal. As shown in FIG. 9, on screen G3, the user can specify the rover's start point and destination point on a three-dimensional map. The user can also input the latitude and longitude of one or more points of interest (i.e., intermediate points) desired by the user. When these are input by the user, for example, a line of a first candidate route passing through the points of interest is displayed on the three-dimensional map, and the maximum inclination angle and route length of the first candidate route are displayed as route specifications. For example, pressing the "Recommend" button on screen G3 causes a transition to screen G4.

[0070] On screen G4, for example, in addition to the route line displayed on the three-dimensional map, a second candidate route is displayed, for example, using a line of a different color. On screen G4, for example, the maximum inclination angle and route length of the second candidate route are displayed. On screen G4, for example, the difference in the maximum inclination angle of the second candidate route from the first candidate route, and the difference in route length of the second candidate route from the first candidate route are displayed. On screen G4, for example, information on necessary changes is also displayed. For example, the information on necessary changes is as follows: "The rover needs to be able to climb inclinations of up to 15.3 degrees. This is a difference of +0.8 degrees from the current specifications. If the new requirements are met, a new, shorter route will be possible. This will shorten travel time and allow more time for scientific observation."

[0071] Also, for example, screen G4 displays the types of components (e.g., motor, gearbox, etc.) that will affect movement along the second candidate route. Also, for example, screen G4 displays recommended components for movement along the second candidate route for each component type (e.g., motor, gearbox, etc.).

[0072] <Specific Example of Processing Method> An example of processing for displaying the first candidate route on screen G3 is as follows. The storage device 23 of the computer system 2 stores, for example, the altitude of each point on the lunar surface. When the user inputs the latitude and longitude of the rover's starting point, the destination point, and one or more relay points desired by the user, the processor 26 of the computer system 2 searches for a route from the rover's starting point to the destination point, passing through all of the one or more relay points desired by the user, within the range of the maximum slope that can be climbed using the preset default rover specifications. The processor 26 then outputs information to the terminal 1 for displaying a first candidate route that satisfies the search conditions. The terminal 1 then receives this information, and the processor 16 of the terminal 1 uses this information to control the display of the first candidate route. As a result, the first candidate route on screen G3 is displayed on the terminal 1.

[0073] An example of the process for displaying the second candidate route on screen G4 and the recommended components for the rover in the case of the second candidate route is as follows: For example, the altitude of each point on the lunar surface is stored in the storage device 23 of the computer system 2. The storage device 23 also stores, for example, the specifications of a combination of components and the maximum slope that can be climbed with that combination of components, in association with each other.

[0074] The processor 26 of the computer system 2 searches for the shortest route from the rover's start point to the destination point within the range of the maximum slope that can be climbed with the specifications of the component combination stored in the storage device 23. The processor 26 then outputs to the terminal 1, as a result of the search, a second candidate route that satisfies the conditions and information for displaying information (e.g., model numbers, specifications, etc.) that specifies the component combination that can climb the second candidate route. The terminal 1 then receives this information, and the processor 16 of the terminal 1 uses this information to display the second candidate route and information (e.g., model numbers, specifications, etc.) that specifies the component combination that can climb the second candidate route. As a result, a screen G4 is displayed on the terminal 1.

[0075] In this way, when a starting point on a celestial body other than the Earth (here, the Moon as an example) and at least one destination point on a celestial body other than the Earth (here, the Moon as an example) are input, the processor 26 may output at least one of a first candidate route from the starting point to the destination point, the distance of the first candidate route, and the maximum slope of the first candidate route.

[0076] The processor 26 may also output a difference in maximum slope and / or a difference in distance between the first candidate route and one or more second candidate routes different from the first candidate route, and may also output recommended specifications for a rover corresponding to the second candidate route.

[0077] <Slip rate> The lunar surface contains regolith, which causes the rover's wheels to slip, which changes the estimated time of arrival or the required time to reach the target point. Therefore, it is necessary to predict the slip rate in advance.

[0078] Fig. 10 is a schematic diagram showing a dynamic model of a wheel. If r is the wheel radius, b is the wheel width, σ is the normal stress, τ is the shear stress, ω is the wheel angular velocity, W is the normal load, DP is the net tractive force, and θ is the wheel rotation angle, then the angle at which the wheel starts to contact the ground is θ ｆ , the angle of departure is θ ｒas the driving torque T and the horizontal traction force F ｘ and vertical load F ｚ is expressed by the following formula:

[0079]

[0080] FIG. 11 is a graph showing an example of the relationship between the ratio of horizontal tractive force to vertical load and the slip ratio. As shown in FIG. 11, the ratio μ (=F ｘ / F ｚ The relationship between the horizontal tractive force and the vertical load and the slip ratio differs depending on the speed of the rover. In the example of Figure 11, the ratio μ of the horizontal tractive force to the vertical load reaches its maximum value when the speed of the rover is 1 km / h, and the value at that time is 0.281. The tilt angle θ in this case is calculated as tan －１ The maximum climbable angle is calculated as μ (= F) and is approximately 15.7 degrees. As shown in Figure 11, the slower the rover speed, the larger the maximum climbable angle at that speed. ｘ / F ｚ The relationship between the slip ratio and the velocity of the rover is determined in advance by experiments on the rover on sand on Earth.

[0081] Note that on the actual lunar surface, the regolith on the lunar surface is different from the sand on Earth, and the environment, such as gravity, is also different. For this reason, on the lunar surface, the ratio μ (= F ｘ / F ｚ On the lunar surface, the ratio of horizontal traction force to vertical load μ (= F ｘ / F ｚ ) is given, the slip ratio can be calculated by measuring the actual distance traveled by the rover. The rover's speed at that time can be calculated by dividing the traveled distance by the time it took to travel, so the ratio μ (= F ｘ / F ｚ The processor 26 may update the relationship between the speed and slip ratio.

[0082] In response to this update, the processor 26 may also update the maximum climbable inclination angle. That is, the storage device 23 may store the relationship between the ratio of the horizontal tractive force to the vertical load and the slip ratio for the rover's minimum set speed (e.g., 1 km / h). In this case, the processor 26 may update the relationship between the ratio of the horizontal tractive force to the vertical load and the slip ratio stored in the storage device 23 using information acquired from a celestial body other than the Earth (e.g., the Moon), and output the maximum climbable inclination angle of the rover by referring to the updated relationship.

[0083] In addition, for example, when the speed of the rover is 10 km / h, in the example of FIG. 11, the ratio μ (=F ｘ / F ｚ ) is 0.2, the slip ratio is calculated as 0.3 from the graph in Figure 11. In this way, if the relationship between the ratio of the horizontal tractive force to the vertical load and the slip ratio is set for each rover speed, the relationship between the rover speed and the ratio μ (= F ｘ / F ｚ ) to calculate the slip ratio.

[0084] <Processing for Estimating Slip Ratio and Estimating the Predicted Arrival Time or Required Time to Reach Destination Point> Next, an example of processing for estimating a slip ratio and estimating the predicted arrival time or required time to reach a destination point using the estimated slip ratio will be described. For example, the storage device 23 may store the relationship between the ratio of horizontal tractive force to vertical load and the slip ratio for each rover speed. In this case, when the set speed of the rover is received from the user, the processor 26 calculates the ratio μ (=F ｘ / F ｚ ) is calculated, and in the relationship stored in the storage device 23, the calculated ratio μ (=F ｘ / F ｚ) and output the predicted arrival time or required time to reach the target point using the determined slip ratio. Here, the travel distance can be determined by the product of the rover's movement speed, the slip ratio, and the rover's movement time. Since the distance to the target point is known, the required time to reach the target point can be estimated by dividing the distance to the target point by the product of the rover's movement speed and the slip ratio. In addition, the predicted arrival time to the target point can be estimated by adding this required time to the current time.

[0085] <Fuel Cell> Figure 12 is a schematic cross-sectional view showing an example of the configuration of the rover 3. As shown in Figure 12, the rover 3 comprises a housing 31, wheels 32-1 and 32-2, and a solar panel 33 provided on the surface (here, as an example, the side) of the housing 31. The rover 3 further comprises at least one fuel cell 34, a water tank 35, a hydrogen tank 36, an oxygen tank 37, a processor 38, and a motor 39 that drives the wheels 32-1 and 32-2, all of which are housed in the housing 31. The processor 38 controls at least the fuel cell 34 and the motor 39.

[0086] Next, water splitting by a fuel cell on the lunar surface and the power generated by the fuel cell will be described with reference to FIGS. 13A and 13B . FIG. 13A is a schematic diagram illustrating water splitting by a fuel cell. As shown in FIG. 13A , for example, on the lunar surface, power generated by a solar panel 33 is supplied to a fuel cell 34, which uses this power to split water into hydrogen and oxygen, storing the hydrogen in a hydrogen tank 36 and the oxygen in an oxygen tank 37. For example, hydrogen may be stored under pressure in the hydrogen tank 36, and oxygen may be stored under pressure in the oxygen tank 37. In this case, the hydrogen and oxygen may be in either a gaseous or liquid state. In this way, water splitting is performed using power generated by a solar panel mounted on a rover, for example, and hydrogen and oxygen are stored.

[0087] 13B is a schematic diagram illustrating the power generated by the fuel cell. As shown in FIG. 13B, the fuel cell 34 generates water and power from hydrogen and oxygen. The generated power is supplied to a processor 38 and a motor 39.

[0088] Figure 14 shows an example of screen transitions related to power generation by solar panels. As shown in screen G5 of terminal 1 in Figure 14, the latitude and longitude of the target area on the moon, the start and end times of the mission feasible period, the maximum efficiency and power requirements (e.g., the minimum amount of power generation required per square meter) as the power generation specifications of the solar panels, the power consumption when the rover is in low power mode, and the water volume of the water tank (e.g., the water tank 35 of the rover 3) are displayed in an inputtable manner. In this way, the user of terminal 1 can set the above parameters. When the "Send" button on screen G5 of terminal 1 in Figure 14 is pressed, the screen transitions to screen G6.

[0089] As shown on screen G6 of terminal 1 in Figure 14, a map of the vicinity of the target area on the lunar surface displays the amount of power generated per unit area (e.g., per square meter) by solar panels at each point as a color map. Furthermore, points selected by processor 26 from the minimum required amount of power generation per square meter input on screen G5 are displayed with, for example, a cross. To achieve this processing, the storage device 23 may store the amount of power generation per unit area and altitude at each point on the lunar surface. Then, processor 26 may refer to storage device 23 and select a point that is as flat as possible and has as few obstacles around it as possible from among the points that satisfy the minimum required amount of power generation per square meter input on screen G5.

[0090] Also displayed on screen G5 as an example are the maximum efficiency and power requirements (for example, the minimum amount of power required per square meter) as the power generation specifications of the solar panel, and the latitude and longitude of the target area on the moon.

[0091] The screen G6 of the terminal 1 displays the mission extension period that can be achieved by generating electricity using fuel cells at night on the moon and using low power mode at night on the moon. Here, low power mode is a mode that consumes less power than normal power mode, and is, for example, the power required to maintain the temperature of the rover's electronic devices at the lowest tolerable temperature (e.g., -40°C) at night on the lunar surface. For example, while the mission period would be 9 days, 10 hours, and 30 minutes if fuel cells were to generate electricity at night and the normal power mode were to be used at night, the screen G6 shows that the mission period can be extended by 3 days by using fuel cells to generate electricity at night and using low power mode at night.

[0092] <Calculation method for mission extension period> On the surface of the moon, day and night alternate every 14 days, for example. During the night, power generation by the solar panels is not possible, so the power supply is maintained by power generation by the fuel cell. Here, the power consumption per unit time in normal mode is set in advance, and the power consumption per unit time in low power mode is input by the user on screen G5.

[0093] During the daytime on the lunar surface, electricity generated by the solar panels 33 is used to electrolyze water stored in the water tank 35, storing hydrogen and oxygen. During the nighttime on the lunar surface, electricity cannot be generated by the solar panels using sunlight. Meanwhile, the extremely low temperatures on the lunar surface can cause malfunctions or other problems with the rover's electronic devices. Therefore, it is necessary to maintain the temperature of the rover's electronic devices above, for example, the lowest temperature possible (e.g., −40°C), raising the question of how to obtain power during this period. Therefore, during the nighttime on the lunar surface, electricity generated when water is synthesized from stored hydrogen and oxygen is used. Below, the processing performed when a mission period is specified by the user is explained in the following order: (1) calculation of the amount of electricity generated by the solar panels, (2) calculation of the amount of hydrogen and oxygen produced, and (3) the period during which operation is possible in low-power mode using a fuel cell as a power source.

[0094] (1) Calculation of the amount of power generated by a solar panel First, we will explain the amount of power generated by a solar panel using light from the sun. Figure 15 is a diagram showing the angle of sunlight, the angle of the solar panel, and the angle of inclination. As shown in Figure 15, θ sun is the angle of the sun to the surface of the moon, and θ slope is the angle of the slope on which the rover is located, and θ panel is the angle at which the solar panel is installed. Here, the energy of sunlight per unit area is Q sun , the area of ​​the solar panel is A, and the sun angle is θ sun The output reduction factor due to sun , solar panel angle θ panel The power reduction coefficient due to panel , the angle of the slope θ slope The power reduction factor due to slope Let α be the coefficient (energy absorption rate) due to the surface finish of the solar panel. The energy Q received by the solar panel is expressed by the following equation.

[0095] Q = Q sun × A × F sun × F panel × F slope ×α

[0096] In addition, if the conversion efficiency of the solar panel from solar power to electricity is β, the amount of power generated by the solar panel Q electric is expressed by the following formula:

[0097] Q electric = Q × β

[0098] (2) Amount of hydrogen and oxygen produced. For example, the following explanation will be given assuming that the first 10 days of the mission are daytime. The amount of power generated by the solar panel Q electric Here is a specific example of the amount of hydrogen and oxygen produced by a fuel cell in 10 days, assuming that the input voltage of the fuel cell is 1.8V and the input current is 0.7A. The amount of power required to perform water splitting in the fuel cell is 2.1 (=1.8 x 0.7) W. The amount of power generated by the solar panel, Q electricDividing 197W by 2.1W gives 91.4, meaning that up to 91 fuel cells can be powered and operated simultaneously.

[0099] One reversible fuel cell produces, for example, 420 ml / h of hydrogen and 210 ml / h of oxygen. Therefore, ten fuel cells can produce 100,800 (= 420 (ml / h) × 24 (h) × 10) ml, or 100.8 L, of hydrogen and 50,400 (= 210 (ml / h) × 24 (h) × 10) ml, or 50.4 L of oxygen during the initial ten daytime periods.

[0100] (3) Operational Period in Low Power Mode Powered by Fuel Cells For example, if the output voltage during power generation by water synthesis of a fuel cell is 0.6 V and the output current is 360 mA, the output power is 0.21 (= 0.6 × 0.36) W. If the user specifies 1.365 W as the power consumption in low power mode as shown in Figure 5, 1.365 W / 0.21 W is 6.5, so seven or more fuel cells are required to output the power consumption in low power mode. The fact that the rover is equipped with seven or more fuel cells or that the rover requires seven or more fuel cells may be displayed on the display 17 of the terminal 1.

[0101] To realize this display, the processor 26 may perform the above calculations to output information indicating that the rover will be configured with seven or more fuel cells, or information indicating the number of fuel cells required to configure the rover.

[0102] The following explanation will be given assuming that the rover 3 has seven fuel cells. If the amount of hydrogen consumed per unit time when generating electricity by the fuel cells is x (ml / h), the amount of oxygen consumed per unit time is y (ml / h), the amount of hydrogen stored in the hydrogen tank 36 is X, and the amount of oxygen stored in the oxygen tank 37 is Y, then the operable period Z in low power mode using the fuel cells as a power source can be expressed by the following equation:

[0103] Z = min(X / x, Y / y)

[0104] By calculating the above formula, the processor 26 may output the operable period Z in the low power mode as the extended period of the mission.

[0105] In this way, when a user inputs a mission duration in addition to a target location on a celestial body other than Earth (e.g., the Moon), the processor 26 may calculate the amount of power to be generated by the rover's solar panels at the target location based on the schedule, and output the amount of hydrogen / oxygen to be generated in the fuel cell on the celestial body other than Earth (e.g., the Moon) during the daytime of the mission duration using the amount of hydrogen and the amount of oxygen stored, which are obtained from the amount of hydrogen / oxygen generated in the fuel cell on the celestial body other than Earth (e.g., the Moon) during the daytime. The processor 26 may then output an extended duration or a total duration of the mission if the rover is operated in low power mode at night on the celestial body other than Earth.

[0106] <Search for Candidate Landing Site> Next, the search for candidate landing sites will be described with reference to Fig. 16. Fig. 16 is an example of a search screen for candidate landing sites. Screen G7 displays latitude and longitude, and the radius of a circle centered on the latitude and longitude point to specify the search range, so that the user can input them. When the "Search" button is pressed here, a search is executed. The lower half of screen G7 displays a list of candidate sites that fit within a circle of a specified radius centered on the specified latitude and longitude point.

[0107] To achieve this process, the storage device 23 may store the latitude, longitude, and altitude of the lunar surface in association with each other. In this case, when the processor 26 receives from the user the latitude, longitude, and a search range centered on the point of the latitude and longitude, the processor 26 may search the storage device 23 and output points whose slopes fall within a predetermined range as landing candidate points. This outputs flat points that meet the criteria. In this way, when the processor 26 receives the conditions desired by the user, it searches for points on celestial bodies other than Earth that meet the conditions, and outputs the search results.

[0108] <Mission continuation period> Next, we will explain the mission continuation period. Since the moon alternates between day and night every 14 days, the mission continuation period varies depending on the mission start date and time. To make it easier to understand the mission continuation period, the mission continuation period is displayed for each mission start date and time.

[0109] FIG. 17 is an example of a bar graph showing the possible mission continuation period for each mission start date and time. Screen G10 of FIG. 17 displays latitude, longitude, start and end dates of the period, and altitude on the lunar surface in an inputtable manner. When the "Send" button is pressed on screen G9 of FIG. 17, a bar graph is displayed on screen G9 of FIG. 17. The vertical axis represents the possible mission continuation period, and the horizontal axis represents the date. Here, as an example, January 1, 2022 to December 31, 2022 is entered as the period, so the bar graph shows the possible mission continuation period for each case where the mission is started on the first day of each month in 2022. In this way, the possible mission continuation period differs depending on the date the mission is started.

[0110] To achieve this display, information on the period of daylight and / or nighttime on the lunar surface is stored in unit time (e.g., hourly) increments in storage device 23. In this case, processor 26 refers to storage device 23 and, for each mission start date, obtains whether it is day or night for each unit time (e.g., hourly) after the mission start date, and if it is daytime, calculates the amount of power generated by the solar panel and the amounts of oxygen and hydrogen produced by the fuel cell from that amount of power generation, and if it is nighttime, calculates how long the fuel cell can generate power from oxygen and hydrogen, and outputs the possible mission continuation period for each mission start date.

[0111] <Display of mission continuation period at each point> Display of mission continuation period at each point will be described using Fig. 18. Fig. 18 is an example of a screen including a graph that displays the mission continuation period at each point on the lunar surface in different colors. The horizontal and vertical axes of the graph on screen G11 of Fig. 18 represent distance. The graph on screen G11 of Fig. 18 shows the mission continuation period at each point within a 500 km square area centered on a latitude and longitude specified by the user in different colors. The mission continuation period is for the mission start date specified by the user.

[0112] To achieve this display, the storage device 23 stores information about lunar daytime periods and / or lunar nighttime periods in increments of time (e.g., one hour). In this case, for example, when the processor 26 receives the latitude, longitude, and mission start date, it references the storage device 23 and determines whether each point within a predetermined range (e.g., a 500 km square) centered on the latitude and longitude specified by the user is daytime or nighttime for each unit of time (e.g., one hour) since the mission start date. If it is daytime, it calculates the amount of power generated by the solar panels and the amounts of oxygen and hydrogen produced by the fuel cell based on that power generation. If it is nighttime, it calculates the duration of power generation from oxygen and hydrogen in the fuel cell, and outputs the possible mission continuation period for each point. The processor 26 then outputs information for displaying the possible mission continuation period for each point in a graph, for example.

[0113] <Landing Success Probability at Each Point> Display of the landing success probability at each point will be described using Figure 19. Figure 19 is an example of a screen including a graph that displays the landing success probability at each point on the lunar surface in different colors. The horizontal and vertical axes of the graph on screen G12 of Figure 19 represent distance. The graph on screen G12 of Figure 19 shows the landing success probability at each point within a predetermined range centered on the latitude and longitude specified by the user in different colors. Furthermore, in the graph on screen G12 of Figure 19, candidate landing points are indicated by crosses.

[0114] To achieve this display, the storage device 23 stores associated latitudes, longitudes, and altitudes on the moon. In this case, for example, when the processor 26 receives the latitudes and longitudes of potential landing locations on the moon, it refers to the storage device 23 and calculates the landing success probability for each location within a predetermined range centered on the latitude and longitude specified by the user, according to a predetermined calculation formula, thereby outputting the landing success probability for each location. Furthermore, for example, when the processor 26 receives the latitudes and longitudes of potential landing locations on the moon, it may refer to the storage device 23 to identify the location and range of a crater. Furthermore, for example, when the processor 26 receives the latitudes and longitudes of potential landing locations on the moon, it may refer to the storage device 23 and select and output at least one landing location candidate according to a predetermined selection rule (e.g., the location with the highest success probability) from among locations where the landing success probability exceeds a predetermined threshold and where the location is not a crater.

[0115] As described above, the information processing system according to this embodiment includes at least one processor that outputs information related to a mission on a celestial body other than Earth by performing calculations according to a user operation using at least one of water resource data corresponding to each point on the celestial body other than Earth, environmental data corresponding to each point on the celestial body other than Earth, rover specifications and / or given setting values, device specifications and / or given setting values, user input values, and given setting values.

[0116] This allows the user to grasp information about the mission in advance, thereby improving the efficiency of mission planning.

[0117] At least a part of the computer system 2 described in the above embodiment may be configured with hardware or software. If configured with software, a program that realizes at least a part of the functions of the computer system 2 may be stored in a computer-readable recording medium and read and executed by a computer. The recording medium is not limited to removable media such as magnetic disks and optical disks, but may also be fixed recording media such as hard disk drives and memories.

[0118] In addition, a program that realizes at least some of the functions of the computer system 2 may be distributed via a communication line (including wireless communication) such as the Internet. Furthermore, the program may be encrypted, modulated, or compressed and distributed via a wired or wireless line such as the Internet, or stored on a recording medium.

[0119] Furthermore, the computer system 2 may be operated by one or more information devices. When multiple information devices are used, one of the devices may be a computer, and the computer may execute a predetermined program to realize the functions of at least one means of the computer system 2.

[0120] In the method invention, all processes (steps) may be automatically controlled by a computer. Alternatively, each process may be performed by a computer, with progress control between processes being performed manually. Furthermore, at least some of the processes may be performed manually.

[0121] As described above, the present invention is not limited to the above-described embodiments, and the components can be modified and embodied in practice without departing from the spirit of the invention. Furthermore, various inventions can be formed by appropriately combining multiple components disclosed in the above-described embodiments. For example, some components may be omitted from all the components shown in the embodiments. Furthermore, components from different embodiments may be appropriately combined.

[0122] REFERENCE SIGNS LIST 1 Terminal 11 Input interface 12 Communication module 13 Storage device 14 Memory 15 Output interface 16 Processor 17 Display 2 Computer system 21 Input interface 22 Communication module 23 Storage device 24 Memory 25 Output interface 26 Processor 3 Rover 31 Housing 32-1, 32-2 Wheels 33 Solar panel 34 Fuel cell 35 Water tank 36 Hydrogen tank 37 Oxygen tank 38 Processor 39 Motor

Claims

[Claim 1] An information processing system comprising at least one processor that outputs information relating to a mission on a celestial body other than Earth by executing processing in response to a user operation using at least one of water resource data corresponding to each point on the celestial body other than Earth, environmental data corresponding to each point on the celestial body other than Earth, rover specifications and / or given setting values, device specifications and / or given setting values, user input values, and given setting values.