System for manufacturing material using photon

Abstract

To solve the problem in measures for laser leaking on the ground, when generating photon and laser using space-based solar power or energy obtained in a power plant in a cosmic space and in the cosmic space, so as to transfer energy from the cosmic space to the earth and to solve the problem in transportation of energy obtained in the cosmic space to the earth.SOLUTION: A system for manufacturing materials using photon is a photon emitting method / energy transfer system constituted of a photon emitting part 1 that uses photon and laser such as UV-C that is absorbed by atmospheric molecules and atoms including oxygen and nitrogen between a cosmic space and air, when transferring electricity and energy, and a receiving part 2 for the photon. The receiving part 2 manufactures materials. As the photon, photon in a UV-C wavelength band which performs photocatalytic reaction and performs photoreaction with oxygen molecules, nitrogen molecules and materials may be used. The receiving part 2 may manufacture materials and fuel using the photon and raw materials. The photon may have photon energy that can release binding of oxygen molecules to nitrogen molecules.SELECTED DRAWING: Figure 15

Description

Technical Field

[0001] <Priority Claim Based on Earlier Applications>This application claims priority from Japanese Patent Application No. 2023-007722 (Priority Claim Application 2) filed in Japan on January 22, 2023, Japanese Patent Application No. 2023-063114 (Priority Claim Application 4) filed in Japan on April 9, 2023, Japanese Patent Application No. 2022-086263 filed in Japan on May 26, 2022 (Priority Claim Application 3), and Japanese Patent Application No. 2022-123161 filed in Japan on August 2, 2022 (Priority Claim Application 1), and incorporates their contents herein by reference. Also, PCT / JP2023 / 016185 (Priority Claim Application 5, filed on April 24, 2023) and Japanese Patent Application No. 2022-181631 (Priority Claim Application 6, filed on November 14, 2022) are also incorporated by reference. ● This application discloses a device for performing the above transmission by wireless, laser, or fuel substance in the energy transmission from space to the ground or the air during space solar power generation (contents of Priority Claim Application 2 such as paragraph number 0060, etc.), a device for power transmission and utilization by wire using an orbital elevator or an aerial platform and a conducting wire, and a device for lightning protection using the method and device used during the above transmission (related to paragraph number 0061, Priority Claim Application 4, Priority Claim Application 3, etc.). ● This application discloses three methods for energy transmission from space to the Earth (or a planet, satellite, celestial body), namely, a wired method, a wireless method, and a fuel transport method. ● This application also includes a device for utilizing the phenomena occurring during the operation of an electric double layer transistor (or a field effect transistor such as a MISFET or MOSFET) in a conducting wire, wiring, or electrode (paragraph numbers 0001 - 0059). ● (This application has not been demonstrated to operate at the time of filing.)

Background Art

[0002] ● This application relates to sheet, film, foil, or linear conductor elements or wiring materials that use carrier introduction by an electric double layer transistor. Furthermore, it relates to electronic components and devices such as motors, actuators, and batteries that use the above wiring materials. ● Also, by utilizing the fact that the carrier introduction to the conductor 101 can be controlled by the gate electrode portion 106 in the conductor element, the conductivity of the conductor element 1 is controlled using a sensor of an input device that detects the environment in which the conductive element 1 is placed and a control unit that controls the input of the sensor and the gate electrode 106 so that the conductivity of the conductor element can be controlled to be high or low according to the measured value of the sensor (Fig. 10). · The high or low state means that the high state is a state in which carriers are introduced into 101 by the gate to form 104 and the conduction positive increases, and the low state is a state in which the gate is off and 101 is not carrier-introduced, or a case where the ionic species of the electric double layer generated in 105 act to lower the conductivity of the portion 104 of 101. ● It is proposed to use the conductor element 1 of this application including 101 that can form 104 as a battery electrode. As an example where an effect is produced by controlling the high or low conductivity by 106, for example, when charging and discharging the battery, the gate electrode 106 is turned on, and when storing the battery or before the battery encounters an accident, 106 is turned off to lower the conductivity. A battery including a sensor and a control unit causes the control unit to perform an operation of turning off 106 when it senses impact or acceleration, lowers the conductivity of the electrode, and prevents a short circuit accompanied by rapid discharge when the positive and negative electrodes are in contact with high conductivity during an internal short circuit (Fig. 9).

[0003] ● As shown in (B) and (A) of FIG. 1 of the present application (or as shown in the representative FIG. 1 of Patent Document 1), there is a conductive conductor, semiconductor, conductive polymer layer, or carbon-based material (such as CNT, graphene, graphite, etc.) conductor layer 101, a source electrode 102, a drain electrode 103, and a gate electrode 106. For example, an ionic liquid of molten salt is between 102 - 103 and 106. (Taking 102 as GND), when a potential VGS is applied to 106, 106 is charged, and the ions contained in the insulating layer 105 capable of forming an electric double layer are arranged around 106 to form an electric double layer so as to cancel the VGS of 106. Also, a capacitor is formed. (The insulating layer 105 may be a separator layer such as a secondary battery containing an ionic liquid.) As a result, an electric double layer also appears near the carrier introduction layer 104 (inversion layer 104 in a MOSFET) of 101. Due to the electric field effect (of the field effect transistor), carriers are introduced into the semiconductor substrate 101 (or conductor substrate 101, carbon conductor substrate 101, conductive polymer substrate 101, organic semiconductor substrate 101, carbon-based conductor material substrate 101, substrate 101 through which electricity can flow) into the said 104, and the carrier density n increases in the carrier introduction layer 104 of 101. (※ In Patent Document 1, a configuration in which a protective layer 107 is disposed on the carrier introduction layer 104 is known. In the present application, the protective layer 107 may also be used in some cases. 107 prevents electrochemical reactions, etching reactions, etc. from occurring on 104 and 101 at a gate voltage exceeding a certain threshold in an electric double layer transistor. Since the present application is not an invention regarding the protective layer, the description is omitted.)

[0004] <MISFET and Electric Double Layer Transistor> A capacitor is formed by a MISFET 105 and 104 and 106 sandwiching 105. When 105 is an insulating film, it is a MISFET, and when 105 contains an ionic liquid (having an electric double layer capacitor portion), it becomes an electric double layer transistor. · In the electric double layer transistor, at the interface between 104 and 105, ions in the ionic liquid form an electric double layer so as to balance the charges in 104, and an electric double layer capacitor is formed in the 104 - 105 - 106 portion. The thickness of the layer of the electric double layer portion is said to be on the order of 1 nm. · In the electric double layer transistor, by forming an electric double layer capacitor such as an ionic liquid, more charges can be accumulated in 104 than in the capacitor formed by the insulating layer of the MISFET. · Applying the principle or method, in the present application, conductors 101, 101P, 1012 of organic semiconductors, conductive polymers, carbon-based materials including graphite, graphene, carbon nanotubes CNT, (and other films of general-purpose metals such as iron) are used for the conductors (or conductors / semiconductors) forming 104 and 1042, provided with a gate electrode 106 and an insulator layer 105 (capable of forming an electric double layer), applying VGS to form 104 and 1042, and attempting to improve the conductivity of the conductors including 104, 1042, and 104. · Also, taking advantage of the fact that the formation of 104 (and 104I which, depending on the type of material of 101, acts to lower the conductivity contrary to 104) is controlled by the voltage value of VGS applied using 106, in a battery with a high electromotive force or energy density, or a battery using a flammable electrolyte, etc., environmental data (such as acceleration) of the environment where the battery is placed, which may lead to battery damage, is detected by a sensor of an input device, and VGS is controlled so as not to generate 104 so as to reduce the conductivity of the battery electrode using 104, and before the battery is stored, damaged, or destroyed, the conductivity of the electrode is lowered to prevent an internal short circuit derived from the electrode (FIG. 9, FIG. 10). ※ As shown in FIG. 2, 108 in the body B portion can be defined in 101. ※ 105 in FIG. 1 or FIG. 2 may be able to form an electric double layer, and in that case, the thickness of 105 can be made thinner. The scales of 101, 101P in the drawings and 104, 105 are not described as being consistent with the actual scale. (It is a schematic diagram.) ※ MISFET: Abbreviation for Metal-Insulator-Semiconductor FET.※In MISFETs and electric double layer transistors, a configuration is adopted in which charges are stored in the capacitor portion of the gate electrode. It is preferable that the self-discharge of the capacitor portion is small. It is preferable that the gate leakage current and the leakage current are small.

[0005] <Breakdown of the gate part> - The gate part of the conductor element forms a capacitor, but the VGS that the capacitor can withstand has a limit (the absolute maximum rated voltage VGSA between GS). When a high voltage VGS is applied, the insulation of the gate part is destroyed. When a voltage exceeding VGSA is applied 106 times, the capacitor part is destroyed and 104 may not be able to be formed. (P2 in Fig. 9) <Fuse-like two-terminal conductor using breakdown of the gate part> - On the other hand, when the element of the present application is used as a two-terminal wire 1-2TER as shown in Fig. 8(B), the voltage applied to the two terminals has an absolute maximum value due to VGSA. · When a voltage exceeding VGSA is applied 106 times to 1-2TER, the capacitor is destroyed, 104 disappears, and the conductivity between the two terminals of 1-2TER that has lost 104 may be utilized like a fuse and decreased. · When a wire formed by connecting a plurality of 1-2TERs in series as a conductor 1WIRE is used in a power transmission network, when a lightning strike occurs and a high voltage such that 106 exceeds VGSA is applied by the lightning strike, the capacitor part in the conductor is destroyed, 104 disappears, and the conductivity of 1-2TER decreases, making it difficult for current to flow between the two terminals of 1-2TER. This may have the effect of preventing a large current from flowing and spreading in the power grid including a plurality of 1-2TERs.

[0006] <From the perspective of conductivity>● Conductivity SIGMA is defined as SIGMA = 1 / resistivity RHO = charge q × carrier density n × carrier mobility MU. With an increase in carrier density n, the conductivity SIGMA can increase. In this application, a conductor element 1 is proposed that utilizes this mechanism to introduce and inject carriers into conductors and semiconductors, increase the density n, and improve the conductivity. ● Note that the resistance R of a conductor is given by R = resistivity RHO × conductor length L / area A. For the cross-section of an object, it is preferable to increase the area A that contributes to conduction. ※ The carrier density n is on the order of 10^22 to 10^23 for metals among inorganic materials, 10^10 to 10^17 for semiconductors, and 10^1 to 10^4 for insulators. ※ There are also conductive polymers with a high carrier density after chemical doping. ※ In this application, (even without chemical doping,) organic semiconductors with high mobility, carbon materials such as CNTs, graphene, graphite, or materials with abundant resources such as iron are used as 101. It is proposed to use them as a conductor element that can increase the carrier density by an electric double layer transistor and control the conductivity by controlling the voltage of the gate electrode. ● If the carrier density n in an electric double layer transistor can be increased to 10^20 to 10^21 or higher, it may be possible to form a highly conductive conductor element 1 by combining it with an organic semiconductor with high mobility. · Regarding carbon materials such as CNTs, which are expected to have high mobility, it may also be possible to form a good conductor by combining their high mobility with the high carrier density due to electric double layer formation. ● Also, in the configuration where 1012 is laminated on 101P in FIG. 11, 1012 can be a thin metal film and 101P can be a porous film made of a conductive carbon-based material. It is proposed to form a carrier introduction layer 104 (and 104I) on the metal film 1012 to increase or decrease the conductivity while reducing the usage cost of metal elements.

[0007] <101P for increasing the area of the carrier introduction layer 104>● The resistance R of a conductor is given by R = resistivity RHO × conductor length L / conductor area A. For the cross-section of an object, it is preferable that the area A contributing to conduction can be increased. · As shown in (A) of FIG. 1 and (A) of FIG. 11, the 104 formed at the interface of the conductor element 1 having flat 101 and 105 is considered to be as thin as about 1 nm in thickness. The area (the conductor area A mentioned above) of the 104 portion for improving the conductivity of the conductor is small, and there may be a problem that even if 104 is formed, the resistance R of the conductor element cannot be reduced as intended. · Therefore, as shown in (B) and (C) of FIG. 11, 104 is formed using 101P including a comb shape, rod, pillar, or porous layer, or a layer of the second conductor 1012 is laminated or deposited on 101P, and a carrier introduction layer 1042 is formed on 1012. Thus, 104 and 1042 having a larger conduction area than the area of 104 generated in the flat 101 and 105 of (A) of FIG. 11 can be obtained, the conductor area A can be increased, and (the resistance R of the conductor can be reduced) the conductivity of the conductor can be improved. (By using 101P, the surface area per volume of the conductor capable of forming an electric double layer can be increased, and the area (conductor area A) where the carrier introduction layers 104 and 1042 are formed can be increased.) Comparing the cross-sectional schematic diagrams of the elements of (A), (B), and (C) of FIG. 11, since (B) and (C) are configurations in which 104 and 1042 can be obtained as larger areas than (A), in the present application, a configuration using 101P as in (B) and (C) of FIG. 11 can be preferably used. · Further, in a metal material, although it is necessary to prevent the metal from corroding etc. (it may be necessary to protect the material with a protective layer as in Patent Document 1), general-purpose metals such as iron ubiquitous on the earth (including aluminum, copper, etc. in terms of reducing the amount of metal used in the wire and achieving resource savings and weight reduction) can be laminated or deposited on the porous conductive carbon material conductor 101P to form 1012. A carrier-introduced 1042 may be formed by the electric double layer formed on the surface of the 1012. For example, the conductor element 1 may be constituted by 1042 formed in the porous electrode 101P.

[0008] <<Applications of Element 1>> ● It is proposed to form 104 in films of metal materials such as organic semiconductors, conductive polymers, carbon materials, and iron, and use it for the conductor part of the electrode of a secondary battery or the conducting wire part of a motor. <Film Electrode Applications> ● The conductor element 1 in the form of a film, sheet, or foil, i.e., the electrode-type conductor element 1FILM, is proposed for use in the conductor part of the electrode of a secondary battery, the conductor part of semiconductor elements such as solar cells, light-receiving elements, and light-emitting elements, and hardware such as computers, robots, vehicles, aircraft, and transportation equipment like display devices. ● It is proposed to use 1FILM as shown in Fig. 6 for the actuator 2ACT using EAP. In the actuator, it may be possible to reduce the use of metal electrodes and lower the metal resource cost and weight. If the weight of the secondary battery, actuator, and motor can be reduced in a robot suit or spacesuit worn by a person, the suit may become lighter and easier for the human to carry. <Conducting Wire Applications> ● It is proposed to use the conductor element 1 as the wire-type element 1WIRE as shown in Fig. 5 for the conducting wire part of electric wires and motors. The conductor element 1 or 1WIRE is also assumed for use in power distribution networks, aerial platforms, base stations, internal wiring, distribution, and power transmission of structures. ● In the configuration of Fig. 5, they are arranged as 106, 105, 104, 101 from the center of the cross-section of the conducting wire. However, in the configuration (1WIRE2) with the reverse arrangement, it is also possible to arrange them as 101, 104, 105, 106 from the center of the cross-section. ● In Fig. 5, 106 at the center of the conducting wire is composed of a composite material of a metal fiber such as aluminum and a carbon-based conductive material to form a gate electrode, which is arranged at the center of the cross-section as a gate electrode and wire core material. A voltage is applied to 106 to charge it, and a capacitor is formed by 104 of 105 and 101 surrounding it, and 101 (the outer conductor part of the coaxial cable) containing 104 is used for the conductor part of the conducting wire. 1WIRE is designed with the configuration of the conducting wire 1WIRE having 106 that can be made into a composite material as the central core wire because 106 of the composite material can be used as a gate electrode for charge storage purposes so that it can withstand mechanical forces such as bending as a conducting wire as described in Fig. 5. ● 1WIRE in Fig. 5 is one example of the conducting wire in the conductor element of the present application, and the form of the wire-type conductor element of the present application is not limited to the example of Fig. 5. For example, 1FILM may be processed (patterned, cut, etched, etc.) to make a conducting wire device.

[0009] <Presence or Absence of Embedding the Conductor Element 1 in the Gate Electrode> In this application, 3-terminal and 2-terminal elements described in FIG. 8 were considered. ● In the 1WIRE and 1FILM of this application, it becomes a 3-terminal element using the gate electrode 106. On the other hand, for applications such as connecting conductive films or conducting wires to form long wirings, 2-terminal elements were considered. · A 2-terminal conductor element 1 (1-2TER) is described in FIG. 8(B). (When the conductor 101 of the conductor element 1 is a semiconductor, 1-2TER operates like a so-called constant current diode with the source and gate of the FET short-circuited. Even when the conductor 101 is a conductor such as a carbon-based material, it cannot conduct current above the allowable current.) · U1 is a gate driver section (which may be a resistor or the like) that drives the gate 106 from Vcc during high-side switching. There may be a resistor between SG and S. U1 may include a sensor, a gate drive circuit, and a control section. · In the configuration of (B) above, it may be possible to drive 106 from Vcc by U1 when applying a potential by connecting electric wires, and the conductor element adopting 1-2TER may be easier to handle as a conducting wire, a conductive film, a sheet, or an electrode than a 3-terminal type. · When used in the power generation parts of large-scale solar cells such as terrestrial and space solar power plants, space structures, and space stations, it is assumed that the 1-3TER is provided with a circuit for driving the gate electrode and its wiring network. However, in the 1-2TER, voltage application to the gate electrode can be performed internally by the 1-2TER, making it easier to construct a large-scale solar power generation system or a large-scale circuit. (The use of 1-2TER is also considered for conductor element 1 used in electrodes and wiring parts of not only solar cells but also electronic components, batteries, motors, actuators, sensors, etc.) · The conductor element 1 can be operated in the same way as an electrical circuit example of a low-side switch type or a general transistor component instead of a high-side switch. (The conductor element 1 is also a transistor.) · For the 3-terminal type, there is an advantage that the magnitude of the voltage VGS applied to 106 and the polarity of VGS can be changed.For example, in the thermoelectric conversion element 2TCE shown in the drawings, voltages with different polarities and magnitudes can be individually applied to the n-type and p-type semiconductor portions. Even when the n-type and p-type materials are completely different material systems, with the p-type material having a large number of carriers and the n-type material having a small number of carriers, and even if there is a difference in carrier density, the voltage of the n-type gate electrode can be made higher than the voltage of the p-type gate electrode to artificially generate carriers in the n-type portion, and it may be possible to control the amount of carriers to match that of the p-type.

[0010] <Utilization in thermoelectric conversion elements> ● A thermoelectric conversion element 2TCE using the above-mentioned 104 with an increased carrier is devised. Regarding the conductor element 1 of the present application, if 1 is a P-type semiconductor or an N-type semiconductor and the carrier density can be increased by controlling the gate electrode while maintaining the mobility of the semiconductor, it may be applicable to thermoelectric conversion elements. As shown in FIG. 11, gate electrodes 106N, 106NG and 106P, 106PG corresponding to the N-type and P-type respectively are provided, and a voltage VGSN can be applied to 106N and a voltage VGSP can be applied to 106P respectively. Thus, it may become a thermoelectric conversion element with increased carriers in the P-type part and the N-type part. Also, in the present application, if the carrier density can be increased even for carbon-based materials, particularly organic semiconductors and some inorganic semiconductors (including inorganic semiconductors such as cuprates as in Patent Document 1 and perovskite semiconductors used in so-called perovskite solar cells), the constraints on the resource aspect of specific elements are eliminated, and by using a semiconductor material with an unlimited resource amount for 104 (101), mass production of thermoelectric conversion elements may become possible. (In known thermoelectric conversion elements, the use of Bi2Te3 alloy has been confirmed, and elements with limited resource amounts such as Te are used.) Thermoelectric elements are widely used from wearable devices for waste heat power generation, physical batteries for artificial satellites, to thermoelectric batteries. In particular, when popularizing in wearable applications, it may be desirable to be able to produce them inexpensively and in large quantities. <When the conductor element 1 uses a semiconductor or an insulator> 101, 101P, and 1012 of 1 may use not only the conductors 101 and 1012 but also the material parts 101 and 1012 of a combination that behaves as a semiconductor when forming 104 and 1042. For example, 1012 is a semiconductor layer with a high bandgap Eg (a material that can be regarded as an insulator in daily life), such as aluminum nitride AlN (or other materials like boron nitride BN, boron nitride nanotube BNNT, silicon carbide SiC, gallium nitride GaN, diamond C, titanium oxide TiO2, tin oxide SnO2, zinc oxide ZnO, indium tin oxide ITO, indium gallium zinc oxide IGZO). A semiconductor layer 1042 may be formed on the semiconductor / insulator (such as AlN with a high Eg) 1012 to function as an n-type or p-type semiconductor layer 1042. A semiconductor device using the above-mentioned 1042 may be configured.The electrode or transparent electrode (including solar cells, light-emitting elements, laser elements, ultraviolet laser elements, EL or liquid crystal display devices) may be configured using the aforesaid 1042. 101 and 1012 include materials used for transparent electrodes such as graphene, CNT, some organic semiconductors, the aforesaid ZnO, SnO2, TiO2, ITO, and IGZO. 101, 101P, and 1012 include semiconductors and conductors. For example, they may include Group 14 elements described in the periodic table of elements. The Group 14 elements may include diamond C as a material with a high bandgap, may include silicon Si and germanium Ge as semiconductor materials with a low bandgap, and may also include tin Sn and lead Pb as conductor materials.

[0011] <<Background of the present application>> ● The first reason is the soaring of metal resources due to the expanding demand for electric vehicles, in order to reduce the amount of copper used. ※ However, the device of the present application may be a hybrid electrode in which a carbon material or a conductive polymer is combined with an electrode formed by meshing aluminum or copper. The present application intends to reduce the use of metals such as copper for wiring materials. The present application does not limit not using copper. Aluminum-containing gate electrodes may be used for 106 to form 104.

[0012] ● The second reason is the problem of recycling metal resources for large-scale devices, structures, and buildings used in outer space. The inventor has disclosed large-scale solar cells and secondary batteries, their wirings and electrodes, or aircraft, spacecraft, artificial satellites, and structures (orbital ring devices, orbital elevator devices) including the said electronic components in JP-A-2022-058853 of Patent Document 2 or JP-A-2022-105726 related to the said Document 2. (The structures and aircraft claimed in Patent Document 2 may include secondary batteries mounted on electric aircraft, such as lithium-ion batteries, similar to electric vehicles. The said lithium-ion batteries contain copper foil and aluminum foil. Regarding solar cells, although the electrode thickness is not as thick as that of lithium-ion batteries, metal electrodes are used.) It has been proposed that the said devices and structures will be incinerated upon re-entry into the atmosphere after mission completion. If the said devices and structures carry finite resources such as copper, after re-entry into the atmosphere, they will fall while being incinerated towards somewhere on the Earth, such as the sea. If the remaining incinerated matter containing copper falls into the ocean or the like, mixes, sinks, and diffuses, it will be difficult to recover copper resources (like recycling copper from household appliances on the ground). When metal elements launched from the ground fall to the ground, there is a risk that they will diffuse and become diluted, making reuse and resource recovery difficult. · When large-scale structures in outer space have passed their useful life and need to be replaced, it is preferable if parts for replacement can be exchanged between space and the ground using low-cost transportation means (so-called orbital elevators, etc.). (Even if they do not contain metal atoms, the structures may contain sulfur that leads to the generation of SOx, and a large amount of sulfur may become SOx during re-entry into the atmosphere, potentially increasing the environmental load. Preferably, it is highly preferable if parts for replacement can be exchanged using means such as so-called orbital elevators.) · However, when large-scale structures are involved in accidents and burn and fall to the ground, or even when using means such as orbital elevators, in case it is desired to reduce the labor of recovering them from large-scale structures using human hands or robots, there may be cases where the structures are removed from orbit all at once (like demolishing a building on the ground by blasting) and incinerated by re-entry into the atmosphere (or may be incinerated as a result of an accident).· At that time, there is a risk that resources containing metals and rare elements inside aircraft and structures will spread to the ground, and if this is repeated, large-scale structure construction and utilization in space may not be sustainable in the future (it may not lead to sustainable development).

[0013] ● The third reason is for resource-saving actuator applications for robots. · In electric vehicles, a large proportion of the equipment is secondary batteries. Among vehicles, unmanned aircraft, and robots including humanoid and multi-legged types, robots with a long moving distance after charging, like transportation equipment, may use a large amount of metal resources in the batteries. · On the other hand, for humanoid and multi-legged robots that are connected to the power grid and receive power supply and have a short moving distance, the proportion of the cost of motors, actuators (including artificial muscles and actuators using dielectric elastomers described in Non-Patent Document 1), and wiring materials in the product is considered to increase as the capacity of the secondary battery and energy storage device can be reduced. If the use of resources such as copper for the motors, actuators, and power distribution materials can be reduced, the constraints on metal resources will be reduced, which may contribute to the popularization of robot products. · Also, it is considered necessary to reduce the weight of the batteries and motors of robots and robot suits.

[0014] ● The fourth reason is for use in lightweight actuators and wiring materials. In the applications described for the above three reasons, if copper wiring (and aluminum wiring) can be made from carbon-containing materials, it may lead to weight reduction of the wiring members of motors, actuators, and batteries. ● For example, in lithium-ion polymer batteries used in mobile computers, drones, etc., it can be confirmed that when decomposed, the metal members that occupy a large part of the battery are aluminum electrodes and copper electrodes coated with active materials. Therefore, it was thought that if the amount of metal used could be reduced, it would lead to weight reduction and cost reduction of batteries, vehicles, airplanes, and robots. ● This application is intended to constitute lightweight electric wires, motors, and batteries. These motors and batteries can be used in various machines and devices (transportation equipment such as electric vehicles, electric airplanes, drones, industrial machines such as electric agricultural implements and ships, office and industrial machines such as printers and processing machines, household appliances such as refrigerators, washing machines, portable and battery-powered vacuum cleaners, electric wires, mobile computers, and wearable devices).

[0015] For the above four reasons and perspectives, reducing the usage amount of wiring materials, wiring components, and metals for electrodes is an issue. In this application, to solve this problem, for carbon materials and organic conductive materials that are not usually as conductive as metal materials, a means of generating an electric field effect is mounted on the wiring materials and electrodes so that the mechanism for increasing the carriers of the electric double layer transistor can be utilized. In addition, motors, actuators, electronic components, electrodes, battery electrodes, and batteries having the above means are also proposed. For a safe device and system, in this application, it is proposed to provide a mechanism for improving conductivity to a carbon-based conductive material with few restrictions on the amount of elements, and a system 3 (3.3WIRE, 3BATT) that detects danger and changes the conductivity inside electronic components and batteries using the above mechanism is proposed. <Remarks> - The inventor believes that in the short term, there are no problems even if space development is carried out using devices and structures such as copper. Also, not only conductivity, but also mechanical material properties and various performance aspects, the above metals should be used for devices that must be made of metals such as copper. However, in the long term, considering that humans will advance into space and assume activities in space, it may not be preferable to re-enter the earth in a state where it is difficult to recycle the earth's copper resources (finite resources) and scatter them. Therefore, the above element 1 is proposed. - Considering the abundance of resources, carbon exists on the earth and satellites and planets near the earth (Venus and Mars), and these are the basis for the carbon-based conductive materials that this application wants to use. (It is also possible that conductor elements can be formed by the method of this application for silicon Si in addition to C. Si has been confirmed on the lunar surface in the form of SiO2.) - Therefore, in this application, in order to improve the conductivity of carbon-based materials, organic semiconductors, and conductive polymers based on carbon and use them for secondary batteries and motors, (although not proven), the 104 parts of the electric double layer transistor were attempted to be used for the copper electrode foil of the secondary battery and the conducting wire part of the motor. - The conductor 101 of this application is a carbon-based conductor (including graphite, graphene, carbon nanotubes, including organic semiconductors, conductive polymers, including inorganic semiconductors, inorganic conductors, and metals such as iron).

[0016] <<Examples and Hypothetical Examples>><Battery with High Energy Density> When the conductor element of the present application is a foil-shaped element, when used in a secondary battery, a secondary battery device with a higher electromotive force than a lithium-ion battery containing an ionic liquid or a lithium-ion battery using the wide potential window of the ionic liquid is also assumed.

[0017] ● For example, for a lithium-ion battery in which lithium ions as cations move, a fluoride ion battery in which fluoride ions as anions move, and a fluoride shuttle battery (FSB) are known. Patent Document 3 can be cited as a literature on fluoride ion batteries. ● From paragraph

[0041] to paragraph

[0057] of Patent Document 3, the components of a fluoride ion battery (which may be a primary battery or a secondary battery) are described. The FSB has a positive electrode current collector that collects current from the positive electrode active material layer and a negative electrode current collector that collects current from the negative electrode active material layer. Examples of the shape of the current collector include a foil shape, a mesh shape, and a porous shape. The electrolyte layer may be a liquid electrolyte. ● In the present application, the current collector (201NEC and 201PEC which are the negative electrode current collector and the positive electrode current collector) can be formed as a layer on 101 containing 104 into which a carrier is introduced. When 101 is a carbon material, the conductivity of the portion of 201NEC and 201PEC close to 104 (the region of 201NEC and 201PEC close to 101 close to 104) in the present application configuration with 104 may be higher than that without 104, which may improve the current collection performance of the current collector and the electrode.

[0018] <Battery and Element 1 Containing a Sensor> ● The use of a PTC thermistor as an element for protecting the battery of Patent Document 4 is known. In the present application, a battery device including a sensor 3SEN that can sense an input such as a strong impact applied to the battery, a gate driver 3CGATE, and a control unit / control unit 3C that control the gate electrode 106 of the conductor element 1 of the present application is proposed.

[0019] · When a battery with a high energy density (or high output density) is damaged, such as being pierced in an accident (bent inside the battery and the separator or the like is damaged), the internal electrodes may short-circuit, and (causing an internal short circuit,) the energy stored in the battery may be released, making it likely to explode or catch fire. · Therefore, in the present application, when the battery is pierced with a nail or the like and an internal short circuit occurs, a safety mechanism as shown in FIGS. 9 and 10 is proposed. · The signs (changes in impact / acceleration, changes in flight altitude, speed changes, swelling of the battery, strain of the battery due to deformation of other members surrounding the battery, changes in sound such as impact sound, changes in sound and abnormal detection when an ultrasonic probe is echoed to the battery or other objects to be protected, changes in smell, sensors for detecting chemical substances, threats approaching the battery captured by a camera, changes in air pressure / pressure, temperature changes) of an accident (the battery is damaged, such as the battery being pierced, the 3BATT of an in-vehicle battery is collided and damaged in a traffic accident, an aircraft equipped with 3BATT crashes, etc.) before the accident are detected by sensors of the control unit / controller of the present application, and an operation is performed to turn off the gate of the conductor element 1 of the present application, and by reducing the conductivity of the internal electrodes of the battery, accidents such as the internal positive and negative electrodes in a highly conductive state short-circuiting and rapidly discharging and catching fire are prevented.

[0020] · A battery for a transportation device such as an in-vehicle battery or an aircraft, wherein the control unit provided in the battery detects a danger from the outside of the transportation device (an object likely to collide with the vehicle detected by the camera) by the in-vehicle computer C1 mounted on the transportation device and the camera mounted on the C1, and C1 transmits a control signal to the controller 3CBATT of the battery through a signal communication path. Then, 3CBATT controls the gate driver circuit 3CGATE according to the received signal / data according to the stored procedure, and may vary the voltage VGS applied to 106 of 2BATT from 3CGATE to control the gate electrode of the conductor element. And by controlling the voltage of 106, 104 of 101 may be reduced or eliminated, or 104I may be generated, and the conductivity of the internal electrodes of 2BATT may be reduced.

[0021] <Conductive Element 1 Whose Conductivity is Controlled by a Sensor>Regardless of the form of the battery, whether it is an electric wire or in the form of electrodes of a sheet, film, or foil, it may be detected by the above-mentioned sensor and input device, and the VGS of the gate electrode may be controlled by the control unit according to the result. · An acceleration sensor or a speedometer for detecting speed may be attached to a motor (actuator) as a sensor. When the motor using the conductive element 1 is in a speed range above a specified speed or is accelerating at an acceleration above a specified value, it is detected by the sensor connected to the control unit, and the gate electrode 106 is controlled from the control unit to turn off the capacitor and reduce the conductivity so as not to increase the speed of the motor operation. · In the case of an actuator that can be used in a robot suit, a sensor and a control unit may also be used. · The gate electrode of the conductive element may be controlled according to the input result of wireless communication from the outside.

[0022] <Applications of Electricity and Power, Signal Applications>The wire device that can be configured according to the present application assumes the power transmission application of electricity. The use for signal applications is not denied. · For sensing the aging deterioration and the placed environment of each part of large-scale buildings or structures (space structures, structures and buildings such as buildings, tunnels, and roads), the conductive element 1 of the present application may be used for wiring that detects sensors and sensor signals. · The element 1 may be used for signals and electrical power wiring for operating sensors or input devices including temperature sensors and cameras, or for operating output devices including motors and buzzers.

Prior Art Documents

Patent Documents

[0023]

Patent Document 1

Patent Document 2

Patent Document 3

Patent Document 4

Non-Patent Documents

[0024] [Non-Patent Document 1] "DEA - Dielectric Elastomer Actuator", Department of Mechanical Science and Aeronautics, School of Fundamental Science and Engineering, Waseda University, Kawamoto Laboratory, www.kawamoto.mech.waseda.ac.jp / kawa / researches / actuator.html, Internet, viewed on July 13, 2022 [Non-Patent Document 2] "What is a DC Motor? Introduction to Its Features and Mechanisms", jp.aspina-group.com / ja / learning-zone / columns / what-is / 001 / , Shinano Kenshi Co., Ltd., Internet, viewed on July 17, 2022 [Summary of the Invention] [Problems to be Solved by the Invention]

[0025] <Problem> It is to increase the carrier density of a conductive material and improve its conductivity. Also, it is to be able to control the conductivity, to construct a device capable of performing the above control starting from the measurement results by a sensor and being able to control the conductivity, and to provide a safe device and a safe battery.

[0026] · In space machines, electric aircraft, electric vehicles, and electric transportation equipment, it has been an issue to reduce the amount of metal used in the electrode materials of secondary batteries. It was also considered necessary to reduce the amount of metal used in motors. · It was necessary to devise carbon-based conductor wiring or conductor wiring that can reduce the amount of metal, as an alternative to wiring materials such as metal foils and metal wires with limited amounts of resources used in secondary batteries, motors, etc. · Carbon materials such as graphene and carbon nanotubes based on covalent carbon, or carbon fibers, organic semiconductors, conductive polymers, and organic or inorganic semiconductors that can be produced by coating may have a lower carrier density than metal conductors, and it was necessary to increase the carrier density n. · Carbon-based wiring materials such as carbon nanotubes and graphene containing many covalent bonds, and organic semiconductors and conductive polymers are difficult to introduce, inject, or dope carriers even if they have high carrier mobility, and the carrier density n tends to be lower than that of metals. It is also undeniable that the molecular skeleton of the carbon-based wiring material becomes ionized and unstable due to doping, or the mobility also decreases due to doping. Therefore, it was considered desirable to increase the carrier density n while maintaining high mobility.

Means for Solving the Problem

[0027] <Solution means> Use the portion 104 where carrier injection of the conductive material 101 in the electric double layer transistor for conductive materials and conductor elements 1 of batteries, electronic components, conductive wires, actuators, motors, etc. including chemical batteries and physical batteries. (Using the said conductor element 1 for vehicles, transportation equipment, aircraft, robots, or household appliances, products, and parts using batteries or motors to reduce the weight and cost of the conductor)

[0028] ● In the present application, by using carrier injection into the substrate portion 104 of an electric double layer transistor, a conductive polymer, an organic semiconductor, an inorganic semiconductor, or a conductive carbon material, a conductor material, a wiring material, or a conductor element made of a conductive material, which has carrier introduction and the carrier-injected 104, is proposed. And a secondary battery, a motor, an actuator, and an electronic component using the wiring material using 104 are proposed. ● In the present application, for a semiconductor or conductor material that is a semiconductor (and a conductor) and has a high mobility but is difficult to dope and has a limit in improving the carrier density, carrier injection is performed by an electric field effect to increase the carrier density n while maintaining a high mobility. As a result, the increase and decrease of the carrier density n can be controllable at 106. In a secondary battery, the carrier density n is increased during charging and discharging of the battery, and the carrier density n is decreased when the battery is stored or not in use. It can be controlled using a gate electrode. Even if a short circuit occurs in the electrode in the secondary battery due to the low conductivity of the electrode during storage, the high resistance value of the electrode prevents a large current from flowing during the short circuit, leading to prevention of a battery ignition accident. (Figs. 9, 10)

[0029] <Battery device capable of preventing short circuit by controlling electrode resistance>● Lithium-ion batteries can be destroyed by overcharging, external short circuit, and internal short circuit. · Patent Document 4 is a patent regarding a configuration of a secondary battery with a safety element for a lithium-ion battery. In Patent Document 4, a PTC element is used as the safety element to ensure safety against overcharging. · An example of an internal short circuit is the destruction and short circuit of the internal structure of the battery due to an external impact. When the positive electrode and the negative electrode come into contact internally and a large current flows and shorts, phenomena such as burning and explosion occur when the electrolyte and the active material are highly reactive. · Other causes of internal short circuit include when metal derived from the electrode, electrolyte, electrolyte solution, and active material precipitates during charging and discharging of the battery and passes through the separator to cause a short circuit, or defects during the manufacture of the separator, electrode, etc., and the mixing of foreign substances and impurities. ● The case where the electrode grounds of the positive electrode and the negative electrode of the present application are short-circuited inside the battery is shown in FIG. 9 as a figure in which a metal nail T1 is pierced through the battery internally. In the case of such piercing, the charge of the gate electrode 106 flows to other electrodes, and the charges stored in 106 and 104 disappear. When 104 disappears, it becomes 101 whose conductivity is lower than that of 104. If 101 has low conductivity, the conductivity of the positive electrode and the negative electrode using 101 becomes low. Even if 101s of the positive electrode and the negative electrode are short-circuited internally, it may be possible to make it difficult for rapid discharge during internal short circuit to occur because the conductivity of 101 is low.

[0030] ● Before the series piercing, the battery is provided with a sensor, such as an acceleration sensor, and according to changes in acceleration, temperature, air pressure (and changes in usage conditions such as altitude inferred from sensor measurement values) applied to the battery, the gate voltage VGS is changed to control the conductor element so as to reduce the conductivity of the battery electrodes, and it may be provided against internal short circuits. ● In the event of an accident (such as a traffic accident) involving an electric aircraft or an electric vehicle equipped with a battery, and the battery is externally impacted and damaged, in order to prevent the battery from having an internal short circuit, a sensor device (acceleration, temperature, air pressure, humidity, special smell, smell of fire, etc.) provided in the battery, when the environmental value in the case where it is desired to avoid an internal short circuit of the battery, or when it is the value (measurement result) of the sensor, the voltage VGS of the gate 106 is changed to control so as not to apply VGS, and the carrier introduction layer of 104 is made into a state where it is not introduced, and as a result, the electrical conductivity and conductivity of 101 including 104 are reduced, which is disclosed as an invention in the present application. Even if the positive electrode 101 and the negative electrode 101 in the battery with reduced conductivity are internally short-circuited, the low conductivity of 101 prevents the generation of a rapid internal short-circuit current, and is intended to prevent heating, combustion, and explosion due to the internal short circuit.

Effect of the Invention

[0031] The gate voltage VGS is applied between the gate 106 and the source to increase the carrier density of 104 and improve the conductivity. As a result, a conductor element 1, which is a conductor capable of forming 104 in the conductor 101 and is a transistor, is configured. By changing the voltage VGS, the conductivity can be controlled. For example, when using a secondary battery, VGS is applied to make the electrodes conductive and perform charge and discharge of the secondary battery. When the secondary battery is not used or during storage, the application of VGS is stopped, the potential of VGS is reset or controlled, the carrier density n is reduced, and the conductivity is lowered, which may reduce the reaction, ignition, and heat generation during an inter-electrode short circuit. (Verification is required in the present application.)

[0032] · Also, since an ionic liquid with a wide potential window is used, it may also be applicable to a battery that uses a redox reaction or an electrochemical reaction with a high potential. · If the conductivity of a carbon-based conductive material lighter than copper or aluminum can be improved and used for the wiring parts of secondary batteries and motors, it will lead to weight reduction and resource conservation in robot suits, space suits (including wearable devices), electric vehicles, and electric aircraft.

[0033] · Although there may be a problem that the carrier introduction layer 104 (channel 104) formed by the conventional electric double layer is as thin as 1 nm class and the area that becomes a conductor is small, as shown in FIG. 11, 104 can be formed by using 101P which may be a porous layer, or a second conductor 1012 is formed on 101P and a carrier introduction layer 1042 is formed on 1012, so that the area can be increased and the conductivity of the conductor can be improved. (The surface area per unit volume of the conductor can be increased.)

[0034] · There is a problem with 104 in the electric double layer transistor that the layer is thin and the area cannot be increased, but in the present application, by using 101P, the area of 104 can be increased, and the conductivity of the conductor element 1 can be improved.

[0035] · Also, when 104I occurs instead of 104, a VGS that causes 104I is applied by switching the polarity of the electrode voltage VGS from the conductive state in which 104 is formed to cause 104I, and the conductivity of the conductor element 1 can be reduced below the state of the bare conductor.

[0036] In the case of a porous material, there remains a risk that the time required to charge the capacitor will increase. The element 1 of the present application requires a charge / discharge time for charging and discharging the capacitor portion including the electric double layer in order to achieve the desired operation mode.

Brief Description of the Drawings

[0037]

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Mode for Carrying Out the Invention

[0038] <Example of the structure of the conductor element 1> Regarding the element 1, 101 is composed of a carbon-based material including an organic semiconductor, a conductive polymer, a carbon material, graphene, and carbon nanotubes. 105 is an insulator layer. It may also be a porous separator layer containing an ionic liquid or the like. 106 is a gate electrode. 102 and 103 are the source and drain portions where current flows due to carriers in 101 including 104. 104 is a carrier introduction layer formed in 101. (It is the channel portion of the transistor.)

[0039] <Increase in interface> Pay attention to the interface where 104 of 101 that contacts 105 is formed. The thickness of the electric double layer is about 1 nm. As shown in (A) of FIG. 12 (FIG. 11 of the present application), if the contact surface between 101 and 105 is flat, 104 formed at the boundary between 101 and 105 may be a planar region of about 1 nm. Therefore, if 101P is used as shown in (B) of FIG. 12 (FIG. 11 of the present application), the ratio of the surface of the conductor 101·101P that contacts the ionic liquid to the total volume of the conductor layer 101P can be increased, (a gap is also generated with respect to the total volume, resulting in a so-called porous film 101P), when VGS is applied to the gate 106, the surface where 104 is generated is increased, and as a result, the area (conductor area A) of 104 as a conductor of 101P increases, and the conductivity of the conductor element 1 including 104 formed on 101P can be improved. (By using 101P, the area A can be increased, and the increase width of the conductivity due to the formation of 104 can be made large. Also, when the conductivity can be decreased due to the formation of 104I, the decrease width can be made large.) · 101P is the 101 part when 101 is a comb-shaped, pillar-shaped or porous electrode / conductor material. · As shown in (C) of FIG. 12 (FIG. 11 of the present application), a second conductor 1012 may be laminated on the surface of 101 or 101P. 1012 may be a metal such as iron, an inorganic material that becomes a semiconductor or a conductor such as Si, or a carbon-based conductor material. The thickness of 1012 may be in the order of several nanometers. · The carrier introduction layers 1042 and 1042I formed by applying VGS to the gate 106 using 1012 may be used. (The second conductor 1012 may be a conductor substance formed on the surface of 101 or 101P. 1012 may be thinner than 101.) ● The configuration that uses the above 101P to increase the surfaces where 104 and 1042 are generated, and as a result, increases the areas of 104 and 1042 as conductors, and can improve the conductivity and increase the control range of the conductivity may be used for the conductor element 1, conducting wire, coil, motor, conductor sheet / film / foil, battery, and electronic component (photoelectric conversion element, thermoelectric conversion element) of the present application.

[0040] <Control of Gate Electrode According to the Type of <101> (Carrier Type and Material Compatibility)> Depending on the polarity of the positive and negative of VGS applied to <106> and the magnitude of the voltage, the conductivity of <101> is controlled, and the present application claims a conductor element that becomes a conductor of a conducting wire, a battery, or an electronic component. · When using a metal (iron, copper, silver, gold, etc.) in which electrons are majority carriers as <101>, when applying a voltage to the gate electrode where anions are arranged on the surface of <101> and when applying a voltage to the electrode where cations are arranged on the surface of <101>, the conductivity of the metal is increased or decreased depending on the positive and negative polarities of the arranged ions. Depending on the magnitude and polarity of the voltage applied to <106> when <101> is a metal, <104> and <104I> may be formed. · The present application has the perspective of increasing the conductivity of <101> and <104> by a gate electrode for use in a conductor element or an electrode wire, and the perspective of reducing the conductivity of <101> for purposes such as protecting a high-energy battery from internal short circuits, and utilizes the voltage application to <106> that forms <104>, eliminates <104>, or generates <104I>. · In addition, there are combinations that cause chemical reactions, corrosion, and etching in the members constituting the element 1. When this occurs depending on the polarity and the magnitude of the voltage, the gate electrode is set in consideration of this.

[0041] <<Example of Manufacturing Conductor Element 1>><Manufacturing of <1FILM>> Devise regarding the manufacturing of the film or foil <1FILM> of the conductor element 1 in FIG. 3. 1. Prepare a foil or film of the gate electrode <106>. (A carbon material may be combined with a metal mesh.) Use the gate electrode film <106>. 2. Apply <105> to <106>. <105> may be a layer <105SEP> with a separator function that can insulate and prevent contact between <106> and <104> and <101>, includes a material for constituting an electric double layer transistor, and contains an ionic liquid. 3. After applying and forming the film of <105>, apply <101>. <101> may contain <101P>. (3-2. After applying and forming the film of <101P>, <1012> may be formed on <101P>.) 3A. Apply <105> to the layer of <106> and bond it to a sheet containing <101> or <101P>. 3B. Apply <105> to the layer of <101> and bond it to the sheet of <106>. ※It is necessary to impregnate <101P> with an ionic liquid.

[0042] <Manufacture of 1WIRE> Devise regarding the manufacture of the conductive wire 1WIRE in FIG. 5. 1. Prepare the gate wire 106. (The wire 106 may be a composite material of a thin wire of a metal such as aluminum and a carbon material, and a filamentous material with mechanical strength may be included in 106 and used in the composite material. 106 is mainly an electrode wire for charging the capacitor part that forms the electric double layer, and while achieving its purpose, multiple materials may be combined for the purpose of providing the mechanical strength required as a conductive wire.) 2. Apply 105 to 106. 105 can form an electric double layer and can also include 105SEP with a separator function. 3. After applying and forming the film of 105, apply 101. 101 may include 101P. (3-2. After applying and forming the film of 101P, 1012 may be formed on 101P.) ※ Or after applying and forming the film of 105, 101 may be arranged so as to surround 105. For example, it may be wound and covered without gaps with a material such as the sheet 101 or the thin wire 101 of 101 on which 105 is applied. (Similar to the arrangement where the thin conductive wire of the mesh-wound copper wire of the outer conductor of a coaxial cable is wound so as to surround the dielectric, 105 may be woven or wound so as to surround it using the wire of 101.) 4. It becomes the bare wire 1WIRE. (4-2. Multiple 1WIREs may be used and made into thinner wires.) 5. When the 1WIRE is an insulated wire, apply the insulating coating 1COVER on 101. Multiple bare wire 1WIREs may be bundled (while overlapping them, etc.) and then the insulating coating 1COVER may be applied to make an insulated wire.

Example

[0043] <Conductive Element 1 Using 101P and 1012 Described in FIG. 11> When implementing the present application, when using the flat 104 with the flat 101 in (A) of FIG. 11, using 104 or 1042 formed in (B) or (C) described in FIG. 11 can increase the surface area (conductive area A) of 104A per unit volume and can improve the conductivity of the conductive element 1, so 101P or 104 or 1042 of 101P can be used. Therefore, 101P may be used in the example of the present application.

[0044] <For electrodes, batteries, and electronic components> Figure 1 is an explanatory diagram of an electric double layer transistor (A) and the device of the present application (B). Figure 3 is an explanatory diagram of using a copper foil with an active layer such as a LiPo battery as an example when performing the operation in 1 of the present application. (It is an explanatory diagram of the conductor element 1FILM in the shape of a film, sheet, or foil.) Figure 4 is an example of a battery 2BATT that uses the conductor elements 1 and 1FILM of the present application.

[0045] <For electromechanical conversion applications> Figure 6 is an explanatory diagram of an actuator that uses an EAP (201EAP) using the present application. The configuration of Figure 6 can also be applied to a piezo actuator that uses a piezoelectric material instead of an EAP. In the configuration of Figure 6, instead of an EAP and 1FILM, a magnetostrictive element with a configuration that generates a magnetic field with a magnetostrictive material and 2COIL and applies it to the magnetostrictive material is also conceivable. In Figure 6, for a piezo element that uses the 1FILM (and 1WIRE) of the present application in the wiring part of a longitudinal displacement type piezo actuator and the electrode part of the piezo element, it is an element 2ACT with a configuration where the piezo element part is an EAP. · Apply a gate drive voltage from 2ACT-DRV to gate drive lines A and B, increase the conductivity, and then apply an EAP drive voltage from 2ACT-DRV to operate the actuator. · Apply an EAP drive voltage from 2ACT-DRV to the source part (or gate part) of the alpha (positive electrode) of 1FILM connected to the EAP drive line A and the source part (or gate part) of the beta (negative electrode) of 1FILM connected to the EAP drive line B to drive the EAP and piezo layers. · An electromechanical element that sandwiches an EAP or piezo included in the configuration of Figure 6 with 1FILM can also be operated as an actuator, receive mechanical force such as the movement of a human or an object and generate electricity, or be used as a sensor that senses mechanical force.

[0046] <For photoelectric conversion and thermoelectric conversion applications> Figure 7 is an explanatory diagram of a photoelectric conversion element 2PCE and a thermoelectric conversion element 2TCE that use the present application. It is an explanatory diagram of a solar cell device (2PV) and a light emitting element such as an LED or a laser diode that use the present application. The conductor element of the present application is used for the electrodes and semiconductor parts of the above elements.

[0047] <In the case of a conducting wire> Figure 5 shows an example of a conducting wire 2WIRE that utilizes the present application. It includes a motor coil 2COIL that can be configured using a conducting wire. The copper core wire portion of a coaxial cable-like cable is used as the gate electrode 106, 106 is covered with 105, 105 is covered with a cylindrical 101 on the outer periphery, and it is a wire-type conductor element 2WIRE that attempts to generate 104 in 101 when a gate voltage VGS (VG) is applied to 106. (It is also conceivable to reverse the arrangement from 106 to 104m101 in Figure 5.)

[0048] <Presence or absence of integration of the gate terminal 106 and its control unit into the conductive element 1> Figure 8 is an explanatory diagram of a conductor element (3-terminal type 1-3TER and 2-terminal type 1-2TER) that utilizes the present application. Although the present application uses the terminal configuration of 1-3TER, when extending a conductor in series using a conducting wire or the like, if the configuration of 1-2TER is used, the extension of the conductor by the conductor element 1 becomes easier because both ends of the 2-terminal element can be connected when connecting.

[0049] The forms of the conductor element 1 and 1-2TER of the present application are assumed to be used for electric wires and conducting wires (including coils and motors using conducting wires). Additionally, they may be used for electronic components (solar cells, LEDs, LDs, OLEDs, digital signage, liquid crystal displays, batteries, capacitors, piezoelectric / magnetostrictive / EAP actuator elements, microelectromechanical system elements / MEMS elements / NEMS elements, inkjet heads, digital mirror devices, imaging elements, thermal imaging elements, various electric circuits) that develop some large-area and large-scale electrodes or store them within the element.

[0050] <Use as Battery 2BATT>Examples in the case of a secondary battery are shown in FIGS. 3 and 4. In a lithium ion polymer LiPo battery, an active material and a positive electrode agent are coated on the front and back surfaces of a copper foil. In the present application, there is a configuration in which a gate foil 106 is made, a separator layer 105SEP capable of containing an ionic liquid is provided, electrode layers 101 and 101P are coated on the outside thereof, and an active material 201 is coated on the outside thereof. · In the LiPo battery, when a metal such as aluminum or a composite material of the metal and another material is used for the gate element, it is conceivable to replace or reduce a metal that is heavier and has a higher material cost than a carbon-based material such as copper. · For example, in a system using a copper electrode and an aluminum electrode such as a lithium ion battery, by using the conductor element of the present application for the positive electrode and an aluminum foil for the negative electrode, while reducing the amount of copper used compared to the configuration using copper for the existing positive electrode, the conductivity of the positive electrode can be turned on and off by the gate, and by turning off the gate 106 of the positive electrode during storage, during storage (although the aluminum side has a low resistance in contact with the low-resistance positive electrode and the existing aluminum negative electrode, the positive electrode has a high resistance, so a large current flows during an internal short circuit and the LiPo battery is less likely to swell or explode), it leads to preventing heat generation due to a short circuit, increasing the safety of the battery, and may lead to reducing the use of limited metal elements.

[0051] <Usage of Battery Systems 3 and 3BATT Equipped with Sensors and Control Units> FIG. 9 is an explanatory diagram for short - circuit prevention when the battery (2BATT) used in this application is stabbed with a metal nail (nail). FIG. 10 is an explanatory diagram of 3BATT including 2BATT, a protection sensor 3SEN, a gate driver 3CGATE, and a battery controller 3CBATT, and its protection mechanism. In FIG. 10, the conductor element 1 of the present application is used as an electrode foil for a battery electrode, and the sensor 3SEN and the gate driver 3CGATE connected to the gate 106 of the battery are connected to the controller 3CBATT. The controller 3CBATT measures a sensor value corresponding to the type of the sensor 3SEN using 3SEN for the environment 3BCE around the battery, and according to the measured sensor value, 3CBATT controls 3CGATE, and 3CGATE controls the VGS of 106 of 2BATT. 3BATT uses a control unit 3C and a sensor 3SEN (specific examples of sensors such as 3A, 3T, etc.) to control 106 of 2BATT of 3BATT. When 2BATT does not perform charge - discharge, or during storage, or when 2BATT is damaged and an internal short - circuit may occur, the voltage applied to 106 is controlled, 104 is made to disappear, or 104I is generated, and the resistance values of the positive and negative electrodes of 2BATT are made to be high - resistance, making it difficult for a large current to flow between the positive and negative electrodes during an internal short - circuit, preventing the destruction (ignition and explosion) of the battery and making the battery safe.

[0052] ● This application aims to provide a lightweight and safe battery that is lighter than a copper - containing battery due to the conductor element 1, eliminates the resource constraints derived from metal elements, or reduces the usage amount of metal resources, and is prepared for the internal short - circuit of the battery.

[0053] ● The 3BATT described above is one example of the embodiment of the system 3. As another example, as described in the "Description of Reference Numerals" section of the specification of this application, the system 3 using a sensor and the conductor element 1 can be used not only in the form of the battery system 3BATT but also in the form of a wire system 3WIRE, etc.

[0054] <Use for Conductor Elements 1 Such as 101 and 1012 Close to Insulators>· For 1012, a material that is usually regarded as close to an insulator, such as having a wide bandgap, etc., may be used to form 1042 into which carriers are introduced in 1012 and used as the conductor element of the present application.· Materials 101 and 1012 that emit high-energy photons (having a high bandgap and usually being an insulator) exceeding the photons emitted by ultraviolet LEDs, deep ultraviolet LEDs, or those may be used in the present application. (Semiconductor elements with a high bandgap such as aluminum nitride, or even insulators, may be used for 101 and 1012.)

[0055] <Ionic Liquid and Molten Salt> - In the creation of this application, it was difficult for individuals to procure ionic liquid reagents. Therefore, this application is at the idea level. Ionic liquids are not substances that can be easily obtained at the time of application and can be expensive. <Utilization of Deep Eutectic Solvents> Although ionic liquids were disclosed as an example, the introduction of the carrier may be performed on the material part 101 without being limited to ionic liquids as long as the portion 104 into which the carrier is introduced can be formed. For example, instead of ionic liquids, solvents with low flammability and low vapor pressure such as deep eutectic solvents can be used to dissolve electrolytes (substances that generate cations and anions necessary for the formation of an electric double layer) that can generate an electric double layer and include them in the insulating layer 105 such as the conductor element 1 and the wire 1 WIRE. (*Deep Eutectic Solvent (DES): A solvent formed by mixing a hydrogen bond donor compound and a hydrogen bond acceptor compound in a certain ratio to become liquid at room temperature. It has characteristics such as low vapor pressure, low flammability, high thermal stability, high electrochemical stability, a wide potential window, and the ability to easily dissolve any substance, and may be less expensive than ionic liquids. There are also natural deep eutectic solvents that are obtained naturally and are considered to have a low environmental impact. These can be used.) ● Batteries, secondary batteries, capacitors, transistors, wires, and electronic components using deep eutectic solvents may be constructed. (It may be used as a medium for including the insulating layer 105 and the electrolytes of batteries, secondary batteries, capacitors, and electrochemical devices. It may also be used for the conductor element 1, the wire 1 WIRE, the battery electrode 1 FILM, the cable 12, etc. of this application.) ● The configuration of this application only requires substances, parts, and generation means necessary for generating the formation of an electric double layer at the interface between the insulating layer 105 and the materials 101 and 104. (As described above, it may be realized not only with ionic liquids but also with other configurations.)

[0056] <Regarding the Claims> It is described in paragraph number 0063.

[0057] Although the embodiments of the present invention have been described, these embodiments are presented as examples and are not intended to limit the scope of the invention. These novel embodiments can be implemented in various other forms, and various omissions, replacements, and changes can be made without departing from the gist of the invention.

Industrial Applicability

[0058] The conductor element (Element 1, Component 2 and Product 2 including Element 1, System 3 of the element including the sensor) of the present application has the following intentions and possibilities. 1. In the field of batteries, to provide a battery that is lighter than a copper-containing battery, eliminates resource constraints derived from metal elements, and is safe. 2. In the field of motors, to provide a motor that is lightweight and reduces resource constraints derived from metal elements. 3. In the field of conducting wires, to provide a motor that is lightweight and reduces resource constraints derived from metal elements. 4. In the field related to sensors, the conductor element 1 of the present application may become a switch part 1 whose conductivity can be turned on and off by a sensor (such as 3SEN and a control unit, etc.). The function of the switch part can be used in 1WIRE, 1FILM, and battery 3BATT including 1FILM.

Explanation of Reference Signs

[0059] <<Transistor portion>> 1: Conductive element. (Since it is not limited to semiconductor elements, it is described as a conductive element). 101: Conductor or semiconductor. The material part that conducts carriers. It may include semiconductors that can usually be insulators like diamond. (101 includes conductors and semiconductors). 102: Source electrode (S). 103: Drain electrode (D). 104: Carrier introduction layer. (Channel portion 104 of a field-effect transistor) (Conductive-increasing type carrier introduction layer 104). 105: Insulator layer. ※ It may be the insulator layer 105 of a field-effect transistor, or the insulator part 105 that can be used for forming an electric double layer such as molten salt or ionic liquid (105 may be a porous material or separator that can contain ionic liquid. It may be an insulator layer 105 that can form an electric double layer. ※ In this application, the capacitor part of the field-effect transistor using an insulator / dielectric stores charge in 104 of 101 to increase the conductivity of 101 including 104, and this is applied not only to semiconductor 101 but also to carbon-based material conductor 101. Specifically, the configuration of an electric double layer transistor within the category of field-effect transistors is used. 105SEP: Insulator layer used for forming an electric double layer while separating physically so as not to cause internal short circuit, such as by including ionic liquid in the separator. (Separator part where an electric double layer can be formed). 106: Gate electrode (G). (107: Protection layer). 108: Body part (B). (Body terminal part of a field-effect transistor / MISFET). 201: Layer laminated on 101 (It may include a layer of an active material of a battery, a semiconductor layer of a semiconductor element, a layer / material / structure for realizing a certain function such as an EAP layer). 104I: Reverse carrier introduction layer. (Carrier introduction layer 104I that reduces conductivity) (Layer 104I that introduces carriers of a type that reduces conductivity). 2: Electronic component, conducting wire, sensor, electrical and electronic application product using conductive element 1. 3: System / device equipped with sensor 3SEN, control unit 3C, and gate drive circuit 3CGATE in conductive element 1 and components / products 2 using element 1, having a function of increasing or decreasing the conductivity of conductive element 1 according to the result of input from a sensor or input device. <Explanation of FIG. 11> 101P: Portion of conductor 101 when 101 is a comb-shaped, pillar-shaped, rod-shaped, porous layer, film, or electrode. (101P may be a porous membrane).)·Regarding the porous image, it is formed by applying fine particles of a conductor such as carbon black to a porous film obtained by sintering semiconductor fine particles of a dye-sensitized solar cell, the fuel electrode of a solid oxide fuel cell, or the conductor of an electrode in a battery including a dry battery, etc., a porous current collector or an electrode film including a current collector, or a nanorod structure or pillar structure grown or deposited on the electrode 101.·For example, the porosity of 101P may be within the range that can be taken in the case of a porous material. 101P may be a layer or portion where the ratio of the volume of the gap space to the total volume is sought. Different from 101 formed by a plane of a single crystal of a so-called semiconductor or conductor, 101P may be a conductor layer or film having a volume of gaps with respect to the total volume, not flat at the micro-nano level, and having many micro-nano level voids. It may also be a porous film having micro-nano level gaps like a sponge. 1012: The second 101.●It may also be a conductor material 1012 formed on the surface of 101 or 101P. 1012 may be thinner in layer thickness than 101. When 1012 is copper or aluminum, its thickness can be reduced, 1012 is deposited on 101, and 101 can be formed of a carbon-based material such as a carbon material, the usage amount of the copper or aluminum can be reduced. 1042: A carrier introduction layer formed on 1012. A carrier introduction layer for improving conductivity. 1042I: An inverse carrier introduction layer formed on 1012. (A type of carrier introduction layer 1042I that reduces conductivity) (A layer 1042I that introduces a type of carrier that reduces conductivity). <<Related to electric wires and conducting wires>> 1WIRE: A conducting wire using a conductor element. (An example of a conducting wire by a conductor element). 1COVER: A covering layer of a wiring member. 2COIL: A coil made of 1WIRE. 2CORE: A magnetic core. The core of the coil. 2CORE-MGS: A magnetostrictive material of a magnetostrictive element. 2MOTO: A motor (using 2COIL.) (When not limiting the specific type of the motor.) 2MOTO-BLDC: A brushless DC motor. (For example, in the case of an outer rotor or inner rotor type of a brushless DC motor, the coil 2COIL can be fixed to the stator side, the current flowing through the stator can be controlled to rotate the rotor, and the motor can be driven.)As in the article of Non-Patent Document 2, in the brushless method, a drive circuit for the motor is necessary, but the elements 1 or 2COIL of the present application can be used for the coils of the stator. )3C: A control unit / controller connected to the gate control unit 106 and the sensor. 3SEN: A sensor or an input device unit. 3WIRE: A wire system with a mechanism for controlling 106 based on the sensor measurement value of 3SEN. ※1WIRE may have a configuration of 1-2TER, and may also have a configuration including the sensor 3SEN and the control unit 3C. The temperature measurement sensor 3T or the acceleration sensor 3A may be included as 3SEN in 1WIRE. <<2-Terminal Element and 3-Terminal Element>> 1-2TER: A 2-terminal conductor element 1. (The terminal related to the gate 106 is incorporated inside 1, and 1WIRE of the 1-2TER type can be connected and used to connect existing electric wires and extend them to form a long electric wire. The 1-2TER type has the effect of eliminating the need for an external circuit / wiring for the gate electrode.). U1: A control unit or drive circuit of the gate. (It may include parts for constituting 3 such as 3C, 3SEN, 3CGATE, etc.). 1-3TER: A 3-terminal conductor element 1. (A method that can control 106 from outside 1.). <<Related to Electrodes>> 1FILM: A film / foil / sheet using a conductor element. (Electrode foil, film electrode). ※1FILM can be used by using (A) or (B) of FIG. 1 as a wide plane, and laminating one 201 for each part of the gate electrode. There are a single-sided electrode type (either the front or back surface of 1FILM becomes the electrode) and a double-sided electrode type (both the front and back surfaces of 1FILM become electrodes) that can be used by laminating two 201 for each part of the gate electrode as in (B) of FIG. 3. 3C: A control unit / controller connected to the gate control unit 106 and the sensor. 3SEN: A sensor or an input device unit. 3FILM: An electrode system, a conductive film / foil / sheet system with a mechanism for controlling 106 based on the sensor measurement value of 3SEN. 201: A layer laminated near 104 and 101. (It may include an electrode layer of a battery, an active material of a battery, an electrode layer or an active layer of a semiconductor element, a layer for charge transport, etc. 201 may be a layer that is controlled by an electrode and causes some function, for example, the liquid crystal layer 201-LC when using the conductor element 1FILM for the electrode of a liquid crystal element.). 201-LC: Liquid crystal layer.<Actuator, Converter, and Mechano-Electric Conversion Element Using Electrodes and Wires> 201EAP: 201 which is EAP. 2ACT: Actuator (including actuators using EAP. 1FILM may be used). 2ACTS: The element when 2ACT is used as a pressure detection sensor, a power generation device that converts mechanical force by which a human or an object moves into electric force, or a mechano-electric converter. 2ACT-EXC: External circuit for driving 2ACT. (When the gate drive unit and the drive circuit for driving functional layers such as EAP and piezo materials are separated and driven). 2MOTT: Motor. Electric motor. 2MOTTG: Generator using an electric motor, motor-type mechano-electric converter. <Photoelectric Conversion Element> 2PCE (2PV): Photoelectric conversion element. An example of a photo semiconductor element is a solar cell. (Or photodiode, LED, OLED). 2PV-E: Electrode. 2PV-HTM: Hole transport layer. 2PV-AL: Active layer. (In a light receiving element, it may be a layer that absorbs light and separates charges, or in a light emitting element, it may be a layer that emits light). 2PV-ETM: Electron transport layer. 2PV-TE: Transparent electrode. 1WIRE (Bus Bar Wiring Part): Conductor element 1 for current collection, parts of rod, wire, plate, sheet, and thick film by 1WIRE. <Thermoelectric Conversion Element> 2TCE: In the conductor element 1 of the present application, a thermoelectric conversion element using N-type and P-type semiconductors in the 104 part. 104N: n-type semiconductor layer into which carriers are introduced, 106N: Gate electrode for 104N. 104P: p-type semiconductor layer into which carriers are introduced, 106P: Gate electrode for 104P. 105N, 105P: Insulator layers made of ionic liquid that generate an electric double layer as a carrier introduction means. 106NGRID: Power distribution network for applying a voltage to 106N. 106PGRID: Power distribution network for applying a voltage to 106P (a power distribution network different from 106NGRID). (In FIG. 11, it is described that a voltage VGN can be applied to the gate 106N of the N-type semiconductor and a voltage VGP can be applied to the gate 106P of the P-type semiconductor. VGP is a voltage different from VGN, and the polarities of the voltages may be different for the two types of gates.) <Battery> 2BATT: Battery using conductor element 1. 104NE: Carrier introduction layer of the 1FILM of the negative electrode. 106NE: Gate electrode of the 1FILM of the negative electrode. 101NE: Conductor layer of the 1FILM of the negative electrode. 201NEC: 201 of the negative electrode current collector. 201NE: Negative electrode active material layer. 104PE: Carrier introduction layer of the 1FILM of the positive electrode. 106PE: Gate electrode of the 1FILM of the positive electrode.101PE: Conductor layer of the 1FILM of the positive electrode. 201PEC: 201 of the positive electrode current collector. 201PE: Positive electrode active material layer. 201EC: Electrode current collector. 202: Assumed example of the terminal part for taking out charges from the positive and negative electrodes. 105, 105SEP: Insulator layer of the 1FILM. 205: Separator of the battery. 205E: Electrolyte solution and electrolyte of the battery. P1: Charge disappearance region of the electric double layer due to the short circuit between 106 and 104. (The area where 104 disappears or the charge of 104 decreases due to the short circuit, and 101 including 104 becomes highly resistant as an electrode). P2: Area where the charge decreases when the gate 106 is broken down and short-circuited. Nail·Spike: Conductor nail·metal nail for piercing the battery. (The region that occurs when the positive and negative electrodes 104 and 106 inside the battery are short-circuited.) (When the battery is subjected to collisions, impacts, accidents, etc., and the structure of the battery causes each electrode to stretch, break, or deform, and the contact of the electrodes occurs, the short-circuited part may be regarded as the part of the nail.) <Description of Figure 10> 3BATT: Battery system obtained by adding a mechanism for controlling 106 according to the sensor measurement value to 2BATT. 3SEN: Sensor for obtaining information from the surrounding environment for controlling the conductivity of the conductor element 1. Measuring means. 3A: Acceleration sensor, shock sensor. 3S: Strain sensor (detects battery deformation due to external impact. When it is a strain sensor attached to the battery, it can also detect swelling of the battery or battery pack, etc.). 3K: Contact sensor (sensor when detecting the contact of an object approaching the battery). 3T: PTC element, temperature sensor, temperature measuring means. 3C: Controller, control unit, control means. (It may include a control unit such as a computer and a gate driving unit.) 3CBATT: Battery controller, 3CBATT among 3C. 3CGATE: Controller of the gate 106. Controlled by 3C. 3BC: Housing, container of the battery (container containing the battery system). 3BCE: Surrounding environment of the device including the conductor element 1 (in the figure, the surrounding environment of the battery 2BATT). 3COMM: Communication device, communication means of 3C. It may be able to perform wireless or wired communication with other communication devices. C2: External computer. A terminal that can communicate with 3C using the communication device 3COMM of 3C and the communication device of C2. (C1 may communicate, change, and update the control method, program, algorithm, and control variables of the gate electrode of 3C through communication.)In addition, for the maintenance and inspection of 3, such as 3BATT, regarding C2 that can access 3C, it may be possible to issue commands to turn on or off the gate electrode from C2 to 3C, or issue commands to change the voltage value or polarity. ). C1: A computer or the like that uses 3BATT. For example, an in-vehicle computer C1 that controls an automobile, which is equipped with an in-vehicle camera CAM of the automobile connected thereto, captures the external environment from CAM, and detects automobiles or collision objects that are likely to collide with C1. C1 may be a control unit C1 for an automobile for autonomous driving. (It may also be a control computer C1 for a transport machine such as an aircraft equipped with a battery. In the case of an aircraft, it falls with a sensor before crashing. When a fall is detected (or when there is a measuring means for sensing a fall and a fall is detected), the resistance of the battery is increased to a high resistance, which may lead to preventing the battery case from being damaged during a fall, causing an internal short circuit between the positive and negative electrodes, and resulting in a fire or explosion.). When there is a risk of damage to 3CBATT of C1, voltage control data and commands for a gate electrode for reducing the conductivity of the battery electrodes are sent to 3C (3CBATT) of 3BATT, and control is performed so that the electrodes are in a state of low conductivity. (When an automobile including C1 and 3BATT collides and 3CBATT is damaged, causing an internal short circuit, the resistance of the electrodes of 3BATT is increased to prevent ignition and explosion due to the internal short circuit between the positive and negative electrodes). C1SEN: Sensor of C1. CAM: Camera as a sensor of C1. <Supplement to FIG. 10> - In the example of FIG. 10, a battery using a conductor element 1 is provided with a sensor and a controller, and the gate drive circuit is controlled by the controller according to the value measured by the sensor to control the voltage applied to gate 106, control, form, or disappear 104 and 1042 (and 104I and 1042I depending on the types of 101 and 1012), increase or decrease the conductivity of 101 and 101P, and when it is preferable to decrease the conductivity, it is a configuration for decreasing the conductivity. The said configuration is not limited to a battery, and can also be used in a configuration of 3FILM using 1FILM or 3WIRE using 1WIRE. - Not limited to the form of the battery, widely, 3 that can be controlled by a sensor using 3SET, 3C, and 3CGATE can be used for an electronic component 2 and an electric and electronic product 2 using a conductor element 1. The said 3SEN may use a known type of sensor. - For example, for 3SEN, an acceleration sensor (a three-axis acceleration sensor), a magnetic sensor, a temperature sensor, a humidity sensor, a barometric pressure sensor, a pressure sensor, a strain sensor, a contact sensor - a touch sensor, an illuminance - light sensor, an infrared sensor, a camera - a scanner - an imaging element, an olfactory sensor, a fire sensor - a smoke sensor, a sound sensor, a wireless sensor (a wireless receiver) may be used. - An external computer C2 may access 3C through wireless or wired communication (using the communication device 3COMM of 3C) to change a program, variables, etc. for controlling the conductive element of the conductor element 1. - Also, the voltage VGS of the gate 106 of the conductor element 1 may be controlled by wireless or wired communication by the external computer C2 through 3COMM of 3C.<Temperature Sensing Element> - For example, 3WIRE includes a temperature sensor 3T, a control unit, and a gate driving unit. 3WIRE may detect an increase in temperature due to heat during a leakage fire or heat generation prior to a leakage fire using 3T, and 3WIRE may detect the temperature increase and perform control to increase the resistance of the conducting wire, making it difficult for current to flow, which may be considered a way to prevent a fire. During a building fire, 3WIRE of the power distribution network connected to the room or section where the fire origin is located may be able to cause the fuse to blow so that no current flows through the said room, etc. of the fire origin. (It may be possible to configure 3WIRE like an element with a fuse whose resistance increases due to temperature rise)<Acceleration Sensing Element><Conductor Element System Operating Using an Acceleration Sensor, a Control Unit, and a Gate Unit> - By mounting an acceleration sensor (which may be a three-axis acceleration sensor) on the 3SEN of not only 3BATT but also 3WIRE and 3FILM, a conductor element system with a control unit that increases or decreases the conductivity of 3WIRE and 3FILM according to acceleration (according to gravitational acceleration or sensing the inclination of the electric wire based on the direction of gravitational acceleration) can be configured. - Electric poles are used to string up electric wires in a horizontal or sagging form to construct a power distribution network and a power transmission network for power supply. Electric wires for tram use and telecommunications are also strung up. In the above system (where the electric wire is not buried underground, is in the air, and sags when cut), a scene can be seen where the electric wire strung up using electric poles is cut by a typhoon, fallen tree, etc. and falls and sags under gravity. The sagging conductor usually has a copper or aluminum part, and the said metal part does not change its conductivity due to sagging or inclination and is always a conductor, so electricity can flow even in the sagging state. - Therefore, when the electric wire sags, it is also possible to consider a conductor system 3WIRE that detects the sag using an acceleration sensor, reduces the conductivity of the conductor, and transmits the abnormality detected by the sensor to the external computer C2 through communication between the control unit 3C of the conductor system and the external computer C2. - 3WIRE including the acceleration sensor 3A of the present application configuration in 3SEN measures the acceleration change or the acceleration during sagging when the electric wire sags due to gravitational acceleration, the electric wire being cut and falling, or sagging, and controls the voltage VGS of the gate electrode 106 according to the measurement result.· Use a 3-axis acceleration sensor to measure, with the sensor, whether the measurement value of the acceleration sensor meets the condition when it drops (when the wire hangs down in the same direction as the gravitational direction). If it is determined as dropped as a result, gate 106 may be controlled to reduce the conductivity of 1WIRE or 3WIRE. · Alternatively, for conductive 1WIRE, 3WIRE (and 1FILM, 3FILM), an inclination sensor (using an acceleration sensor) may be provided, and control may be performed to increase or decrease the conductivity according to the inclination of 1WIRE, 3WIRE (1FILM, 3FILM).

[0060] <<Content of the previous priority claim application, Japanese Patent Application No. 2023-007722>> This application cites Japanese Patent Application No. 2023-007722. The specification, etc. and the drawings (FIGS. 1 to 12) described in paragraph number 0060 of this application are the same as the description of the drawings and the drawings described in Japanese Patent Application No. 2023-007722. FIGS. 1 to 12 described in paragraph number 0060 of this application correspond to FIGS. 14 to 25 described in paragraph number 0037 of the "Brief Description of Drawings" section of this application. <Document Name>Specification <Title of the Invention>Energy Transport Method of Space Solar Power Generation System, Energy Transport Method from Space to Earth <Technical Field><0001> This application relates to a power transmission system and an energy transport method among space, air, and ground of a space solar power generation system, and also includes an energy transport method from space to earth. <Background Art><0003> In a space solar power generation system (SSPS: Space Solar Power Systems), it is necessary to deliver the electric power and energy obtained by a solar power generation system (or a solar energy collection device) arranged in space to the ground part and user part having electric power and energy demands on the ground. <0004><Wireless Power Transmission System> Therefore, wireless power transmission, wireless power transfer, and wireless transmission for transmitting power from SSPS to the ground via space and air, as described in Patent Document 1 and Non-Patent Document 1, have been studied. For the wireless power transfer, those using radio waves such as microwaves which are also photons with long wavelengths and those using photons such as infrared rays which are photons with short wavelengths or their laser lights have been proposed and studied. Also, the wireless power transfer and power supply to electrical devices such as smartphones, electric vehicles, and wireless tags have been studied. <0005><System for Manufacturing Fuel Substances and Energy Storage Substances and Transporting Them to the Demand Areas> On the other hand, there may be a system that consumes power on the spot near SSPS or manufactures fuel substances, energy storage substances, and objects on the spot and transports them to the ground or the like without using wireless power transmission or wireless power transfer. ● It is preferable if the electric power generated by SSPS can be used on the spot after generating electric power in space, a space base, a lunar base, etc. As a case of using it on the spot, for example, as shown in FIG. 3 and FIG. 4, a system that manufactures some kind of fuel using electric power on the lunar surface (or in space) and delivers it to a space base or the ground can also be considered. <0006>● As shown in FIG. 3, when, for example, water (oxide of hydrogen) is sent from the ground for fuel synthesis, the water is electrolyzed on the lunar surface to obtain hydrogen and oxygen and then delivered to the ground again, there is a problem that the launching means 9 such as a rocket (or the dropping means 9 such as a rocket from the moon to the ground) is costly. ※ However, if the launch cost decreases, this method can be used. The realization of a method using a low-cost rocket or non-rocket methods such as a mass driver and an orbital elevator is expected.※ Also, it is preferable to have a low-cost printing means 9 for printing parts and base materials for the construction of SSPS. ● Since this application is not an invention related to the printing means, details regarding the printing means such as a mass driver will be omitted. <0007> ● As shown in Fig. 4, silicon dioxide (or metal oxides such as aluminum oxide, iron oxide, or substances containing water or oxidized hydrogen, i.e., lunar surface oxides) contained in resources such as lunar rocks is reduced by the electric power obtained by SSPS to obtain reduced substances such as metallic silicon, which are then transported, dropped, and delivered to the ground, and the reduced substances such as metallic silicon are oxidized by some method on the ground to obtain energy by redox. ※ However, in this system, the mass of the moon may be reduced. <0008> ● In the plan of transporting the above fuel substances, at the beginning of the fuel manufacturing business, lunar substances can be mined, reduced, or energy can be stored and fuel can be shipped to the ground. However, in the long term, it is necessary to launch objects to the moon to compensate for the amount of objects removed from the moon. When restoring the mass of the moon, an inexpensive launching method is required. ● There may also be an inexpensive method of launching from the ground to the moon or a mass driver 9 for sending and delivering from the lunar surface to the earth. (Progress in non-rocket launching methods and the use of reusable rockets in the fields mentioned in Patent Document 2 are desired.) <0009> According to Japanese Patent Application No. 2021-181539 and Japanese Patent Publication No. 2022-527127, there is a description regarding a method of manufacturing large-area components such as solar cells, radars, and mirror devices (telescopes, reflectors, large-area mirror devices for reflecting sunlight) by forming a functional film (semiconductor film, metal film, etc.) using the vacuum of space. In the system using SSPS in Fig. 4 of this application, these methods can also be used for on-site manufacturing of solar cells and devices for collecting and utilizing solar energy in the vicinity of space and lunar bases. <0010> ● Solar cells and devices for collecting and utilizing solar energy may be manufactured using inorganic substances such as silicon dioxide contained on the moon. In order to reduce the number of members launched from the ground, materials and resources on the moon may be used.For example, on the lunar surface shown in Fig. 4, solar cells can be manufactured using lunar resources (silicon dioxide and other inorganic substances), the power of SSPS, and manufacturing equipment brought from the Earth. Silicon dioxide SiO2 can be reduced to obtain silicon Si, and silicon solar cells can be manufactured and used for SSPS, or crystalline silicon Si manufactured for solar cells, or metallic silicon mixed with silicon, polysilicon, and impurities that are not of solar cell grade (when described without limiting the scope of the invention, the reduced substance 5MC may also be used) can be used as fuel on the lunar surface or dropped to the ground. ● Also, in order to reduce the number of members launched from the ground, the energy of SSPS can be accumulated in lunar resources and dropped to the Earth for use on the ground, and a fuel manufacturing method as shown in Fig. 4 can be used. <0011> Or, as described in the specification of Japanese Patent Application No. 2021-181539, a solar cell material can be transported from the ground to outer space and the moon using a launching device 9, and a device (solar cell, mirror, reflector) for collecting and using solar energy using the solar cell material can be manufactured. <0012> When launching from the ground, a resource-saving material (examples of such materials: compound semiconductor materials, used in CIGS solar cells, etc.) that is a direct transition type and has a large absorption coefficient and requires a thin photoelectric conversion layer and functional film for photoelectric conversion may be used. If materials such as gallium and indium that can be mined on the moon or opaque materials are required, they can be transported from the ground. <0013><Energy Transport Method>This application discloses an energy transport method including wireless power transmission, wireless power transfer, wireless power transmission, wireless transmission, and fuel transport. In this application, wireless power transmission means can be used from SSPS to the ground or the air. According to Non-Patent Document 1, power transmission using microwaves or laser light is being studied. However, in systems using microwaves or laser light, when receiving microwaves or lasers emitted from SSPS, if the transmission power is high, there is a risk of affecting and damaging the human body, organisms, environment, electrical equipment, etc., wireless equipment, and communication equipment near the receiving part and the light receiving part on the ground side. As a countermeasure for this, it is assumed that the operation is carried out with the transmission power reduced.<0014>● In this application, the area of the receiving unit 2 and the light-receiving unit 2 may be increased, and even with low transmission power, reception and light reception may be performed by a receiving unit 2 and a light-receiving unit 2 with a large area (such as a rectenna in the case of microwaves, a light-receiving element, a photovoltaic cell, a solar cell, a reactor, a chemical reactor, a chemical reactor by light or heat, etc. in the case of a laser). (For example, although the energy density of sunlight is low, the image is that the light emitted from the transmitting unit of the SSPS is received by a large-area receiving unit on the ground, just as sunlight is received by a large-area solar cell on the ground.) <0015>● In the method of operating with reduced transmission power, in the case of microwaves and radio waves, it is necessary for the receiving unit 2 and the light-receiving unit 2 to have a large area, which includes problems such as increased costs due to a large-area rectenna and securing land. ● Also, since the photons used for transmission (in the form of laser light and radio waves) have wavelengths that can penetrate the atmosphere, even if the transmission output is reduced, there is a risk of causing concern among residents near the receiving unit and the light-receiving unit that photons with wavelengths that can penetrate the atmosphere may reach or have reached. ● It may be an issue that photons and radio waves that can penetrate the atmosphere are transmitted and can reach an inhabited area that is not the receiving unit when the orientation of the SSPS satellite changes slightly, and using such types and wavelengths of photons that can cause concern among people. ● Thus, there has been an issue of whether delivering the power of the SSPS to the ground in the form of photons that can penetrate the atmospheric window may have an adverse impact on people, living organisms, and the environment on the ground. <0016><Method of receiving photons with wavelengths that are difficult to reach the ground by an aerial structure 3 in the Earth's upper atmosphere> When receiving by the ground facility 2, the above issues may occur by using photons that can penetrate the atmosphere. Therefore, in this application, it is proposed to use photons that do not easily penetrate the atmosphere to configure a wireless power transmission system (wireless power transfer system) of the SSPS and use it for the transmission, power transmission, transfer, and transmission of the power or energy of the SSPS.Even photons that do not penetrate the atmosphere can be received by the light-receiving unit 2 in Fig. 1 (e.g., in the upper part of the troposphere, the stratosphere, and the upper part of the stratosphere). In order to do so, the light-receiving unit 2 of the SSPS of the present application (airborne receiving unit / light-receiving unit 2, high-altitude receiving unit / light-receiving unit 2) as shown in Fig. 1, Fig. 2, etc. of the present application is provided on a high-altitude communication platform (HAPS) 3, an aircraft 3, or a helium balloon 3 that is placed at a high altitude where the atmosphere is thin and the air density is low. A laser beam having a wavelength of photons that do not penetrate the atmosphere, which is transmitted, emitted, irradiated, or launched from a transmitting unit 1 or a light-emitting unit 1 (SSPS and an SSPS relay satellite 1LINK that links the laser beam from the SSPS, and a transmitting unit 1 or a light-emitting unit 1 that may be included in a group or constellation of SSPS and SSPS relay satellites) arranged in outer space, is emitted, irradiated, or transmitted toward the receiving unit 2 / light-receiving unit 2 (or the laser beam of the light-emitting unit 1 hits, is received by, and undergoes photoelectric conversion by the receiving unit 2, and the object or substance is heated or undergoes a chemical reaction, etc.). The present application proposes to perform wireless power transmission and wireless energy transmission.<0018><Comparison with previously reported technologies>Fig. 1 of Patent Document 1 discloses a configuration in which a receiving unit (1) is provided on a flying ship (5) in the air or in the troposphere (at an altitude of 10 to 16 km) that receives microwaves and lasers. In the present application, the receiving unit 2 and the aircraft 3 may be arranged in the stratosphere at an altitude of 50 km to 20 km. (※In the case of an aircraft, there is an example of raising a balloon up to an altitude of 53 km in the case of a high-altitude balloon. Regarding the update of the world record for the altitude reached by an unmanned balloon, viewed on January 19, 2023, Internet, JAXA, https: / / www.jaxa.jp / press / 2013 / 09 / 20130920_ballon_j.html)<0019><Atmospheric density and composition at high altitudes>●In the troposphere, oxygen and ozone exist as they do on the ground, and the atmospheric density in the troposphere is 13% of the density on the ground (1.293 kg / cubic meter). In the stratosphere at a higher altitude (an altitude of 20 km or more where the stratospheric platform is arranged), the atmospheric pressure is 100 hPa at an altitude of 20 km, 0.013 kg / cubic meter at an altitude of 32 km, and 10 hPa at an altitude of 40 km.(Reference: Japan Meteorological Agency website, Structure and Flow of the Atmosphere, viewed on January 8, 2023, Internet, https: / / www.jma.go.jp / jma / kishou / know / whitep / 1-1-1.html) ● At an altitude of 16 km in the troposphere and above its boundary surface, the atmospheric density is 0.16 kg / cubic meter, and at an altitude of 32 km, it is 0.013 kg / cubic meter. (At an altitude of 68 km, it is 0.00011 kg / cubic meter, and in the vicinity of the stratosphere, the atmospheric density and the density of oxygen decrease.) From the ground to an altitude of 80 km, the atmospheric composition and the component ratios of components such as oxygen and nitrogen are the same as those on the ground. Since the amount of oxygen decreases to one-tenth from 16 km to 32 km, when allowing short-wavelength photons (short-wavelength photons from ultraviolet rays to X-rays) such as UV-C that undergo chemical reactions and photoreactions by oxygen and ultraviolet rays to reach the light-receiving part 2 without attenuation in the radiation, it is more preferable to be on the upper layer side of the stratosphere at an altitude of 32 km than the troposphere at an altitude of 16 km. Therefore, in the present application, it is preferable that the altitudes of the light-receiving part 2 and the aircraft 3 are in the stratosphere from 50 km to 20 km. (However, when using the aircraft 3 including the light-receiving part 2 and the fuel synthesis aircraft 3FUEL in the examples of FIG. 1 and FIG. 2, 3 which is also 3FUEL may fly from the ground to the stratosphere, and the use in a form where the altitude of 3 is not kept constant or is not restricted may also be considered.) <0020> <Air density and photon absorption degree in the troposphere and on the ground> ● The upper layer of the troposphere is about one-tenth of the air density on the ground at 13%. For example, the degree of absorption of short-wavelength photons closer to the ultraviolet side that react with oxygen and ozone also becomes about one-tenth of that on the ground in the upper layer of the troposphere and decreases compared to the absorption degree on the ground. Even when the altitude of the light-receiving part 2 that receives the short-wavelength photons is the altitude of the upper layer of the troposphere (16 km or not), for photons of a certain wavelength, if there is a certain amount (X%) at an altitude of 16 km. Even if photons are absorbed by the atmosphere, the remaining amount (100% - X%) may be received by the light-receiving unit 2. In the present application, a configuration that utilizes photons that are difficult to transmit through the atmosphere may be practically useful. Therefore, it is necessary to determine the conditions through demonstration development regarding the altitude from the ground where the light-receiving unit 2 should be placed. The present application discloses, for example, using photons such as ultraviolet photons of oxygen, ozone, etc., or ultraviolet rays and some infrared photons absorbed by the atmosphere as photons or laser light with atmospheric attenuation for energy transport from the air to the ground of the SSPS, and does not consider limiting the altitude of the light-receiving unit 2 to the stratosphere. (Regarding the above-mentioned photons, for example, in the present application, some cases are disclosed where the energy of one photon is large and the photon is on the short-wavelength side closer to ultraviolet rays that can be absorbed by the atmosphere, oxygen, or ozone. Also, in the wavelength range of infrared rays, there are wavelengths absorbed by atmospheric molecules, and photons of said wavelengths may be usable in the light-receiving unit 2 of the present application.) ● One object of the present application is to ensure the safety of houses on the ground and aircraft navigating in the troposphere, using photons that are difficult to reach the ground and preventing photons escaped by the light-receiving unit 2 due to misfiring from the light-emitting unit 1 from reaching the ground. The light-receiving unit 2 may be arranged at an altitude exceeding the troposphere (altitude 16 km or more) as described in Patent Document 1. The receiving unit 2 may be arranged at an altitude of 20 km to 50 km from the ground, or at an altitude of 50 km or more. <0021> ● The light-receiving unit 2 may be mounted on the aircraft 3. Even at an altitude where the propeller motor or jet engine of the aircraft 3 cannot operate (thin air), in order to perform movement, direction change, and movement of the aircraft such as attitude control and propulsion, in addition to the motor and jet engine, for example, a propulsion device 3TH such as a rocket, photon sail, or ion thruster may be mounted. (The aircraft 3 of the present application may be an aircraft 3 such as a solar plane 3 configured as shown in FIG. 11 of the present application or FIGS. 6 and 7 of Patent Document 2. The aircraft 3 may also be an aircraft 3 that becomes a high-altitude platform HAPS.) <0022> ● In an SSPS that can always transmit energy to the light-receiving unit 2, electric power and energy from the SSPS are transmitted from the light-emitting unit 1 to the light-receiving unit 2. For example, the energy obtained in the light-receiving unit 2 attached to the aircraft 3 is used as heat to warm the gas or fluid of a hot air balloon or a Roger balloon. The aircraft 3 may include elements of a hot air balloon or a Roger balloon, and may also be an aircraft 3 or a solar plane 3.<0023><Light pollution> ● In the format of this application, short-wavelength photons from ultraviolet rays to X-rays are invisible light to humans. Therefore, even at night, there is an advantage that light cannot be seen. It may be possible to reduce the influence such as light pollution at night. (When paying attention to invisible photons regarding light pollution, in addition to ultraviolet light, infrared rays and millimeter waves may also be used.) <0024><Short-wavelength photons proposed in this application> ● This application may use a system that is absorbed by reacting with oxygen and ozone in the atmosphere (the atmosphere at an altitude of 20 km to 50 km or more from the ground), such as UV-C and UV-B. This application utilizes the atmosphere. <0025> ● In this application, in the atmosphere and troposphere, the laser cannot penetrate the atmospheric window. For example, the wavelength of photons of laser light may be short-wavelength photons such as UV-C (wavelength 280 - 200 nm) in near-ultraviolet light, far-ultraviolet light (200 - 10 nm), vacuum ultraviolet light (or X-rays and gamma rays if safety can be confirmed during use). <0026> UV-B has the characteristic of being absorbed by ozone, and UV-C is absorbed by oxygen, the atmosphere, and ozone. While having the advantage of being difficult to reach the ground, the energy of photons has the merit of being larger than that of microwaves and millimeter waves, so it can be used in the system of this application. <0027> ● Since ultraviolet rays including UV-B and UV-C have a large photon energy per photon, it may be possible to increase the photovoltaic power by miniaturizing the reaction device having the energy obtained from the light receiving part 2, or increasing the semiconductor bandgap of the photoelectric conversion device (photovoltaic cell), which may lead to miniaturization and high output of the light receiving part 2. <0028> ● The ultraviolet rays mentioned above have higher energy per photon than visible light, infrared light, and radio waves, and are easy to use for causing chemical reactions in substances, so there is also a merit in terms of fuel production. For example, considering a photocatalyst, a photocatalytic reaction does not occur using low-energy photons such as millimeter waves and infrared rays. A photocatalytic reaction occurs with photons such as ultraviolet rays having energy above the bandgap of titanium oxide. ● If the light receiving part 2 is a photocatalytic device or reactor, a photocatalytic reaction cannot occur in the light receiving part 2 in a system using microwaves and millimeter waves, but in the system using ultraviolet rays (such as using UV-A, UV-B, and UV-C) claimed in this application, a photocatalytic reaction can occur in the light receiving part 2.<0029>● When producing fuel through a photocatalyst or a chemical reaction between light and a substance in this way, there may be an advantage in using photons such as ultraviolet rays in the light-receiving unit 2. <0030>● Photons in the form of radio waves such as millimeter waves and microwaves are difficult to use for chemical reactions, and the electromotive force of the photoelectric conversion device may also be low. (※ When heating an object regardless of the energy magnitude of photons in the receiving unit 2, heating can be achieved by radio waves such as millimeter waves and microwaves. Also, in 2 or 3 used for heating by microwave radio waves, in 3 which is a hot air balloon, it may be possible to utilize it for heating the hot air balloon or the gas heating element of the hot air balloon.) <0031>● For radio waves, a large-area rectenna etc. is required, and it is difficult to concentrate energy like laser light. On the other hand, in the form of the tag 2TAG, beacon tag, RFID tag described later, the fact that energy is easily diffused is used for the operation of the tag. Disclosure is made regarding tag search from the aircraft 3 and transmitting energy from SSPS in the form of laser light or radio waves for tag search from the aircraft (using for monitoring). <0032> In the present application, the wavelength of the photons used and the absorption attenuation of photons in the atmosphere are utilized in a fail-safe design in which photons do not reach and attenuate at the residences and houses below the atmosphere and troposphere. The intention of the fail-safe design is that even if photons are irradiated in the direction of the residence where there is a house rather than the receiving unit 2 due to misalignment of the transmitting unit 1 etc., the photons have a short wavelength, for example, photons from UV-B, UV-C to X-rays act on atoms and molecules and cause chemical reactions with, for example, atmospheric molecules and atoms (ozone generation in the case of UV-C), and are photons that are attenuated and absorbed by the atmosphere, and it is assumed that they are not absorbed by the atmosphere and do not reach the ground (photons reaching the ground can be reduced), and by ensuring that photons do not reach the ground, safety is ensured for fixed-wing aircraft in the troposphere and houses and living things on the ground. <0033><Generation and utilization of short-wavelength photons> An ultraviolet laser capable of emitting ultraviolet rays, or a synchrotron or other particle accelerator that can generate ultraviolet rays to X-rays, gamma rays, etc., and a radiation light generation device (or a free electron laser generation device) generated thereby may be used.<0034>●For example, among examples of ultraviolet lasers, solid devices such as laser diodes for long-wavelength ultraviolet, medium-wavelength ultraviolet, and short-wavelength ultraviolet, which are composed of semiconductors such as aluminum gallium nitride (AlGaN) having a bandgap corresponding to the energy of photons of ultraviolet light, are known, and such a light-emitting device using a semiconductor may be used. <0035>●Also, if listed without limiting the scope of the invention, a wavelength conversion device (for example, a device or element for converting the wavelength from infrared light to ultraviolet light may be used. A system using a crystal for converting the wavelength of an infrared laser of 1064 nm by an Nd:YAG crystal to 266 nm of ultraviolet light is assumed.), or an excimer laser device (for example, generating photons of UV-C having a wavelength of 248 nm when using KrF), a vacuum tube device, etc. may be used. <0036>The short-wavelength photons such as the aforementioned UV-B, (UV-A,) UV-C, far ultraviolet light, vacuum ultraviolet light, X-rays, gamma rays, etc. are generated in the light-emitting unit 1 and the transmitting unit 1, and the short-wavelength photons are emitted, irradiated, and transmitted toward the light-receiving unit 2 and the receiving unit 2, and photoelectric conversion may be performed by the light-receiving element 2PCE provided in the light-receiving unit 2 and the receiving unit 2 to obtain electric power. ※Since the present application is an invention and a device related to the energy transport method of SSPS and its utilization, detailed descriptions of devices and elements for generating photons are omitted. <0037>●Also, the energy of the short-wavelength photons may be irradiated onto the reactor 2REA and fuel raw materials to cause a chemical reaction to produce fuel. (For example, hydrogen is generated from water in the light-receiving unit 2, and carbon dioxide on the ground is reduced to carbon, hydrocarbons, and oxygen. The laser light is photoelectrically converted in the light-receiving unit 2 and used as power for 2, the aircraft 3, the transportation equipment 3, the formation 3FORM of airplanes, the flying car 3FCAR, and the robot 3.) <0038>●As shown in FIG. 6(a), the electric power obtained by photoelectric conversion in the light-receiving unit 2 may be used to fly the aircraft 3 including 2 and operate electrical equipment such as the actuator of the aircraft 3. Also, as shown in FIG. 6(a), the energy obtained in the light-receiving unit 2 by the aircraft 3 may perform wireless power transmission to and supply power to the aircraft 3A1, 3A2, 3L1, 3L2 included in the 3FORM including the aircraft 3 to move them. Also, 3 may be able to communicate with the objects included in 3FORM such as 3A1 and 3L1. The objects included in 3FORM such as 3A1 and 3L1 may be able to share and transfer energy and power by contact or non-contact means.<0039>● As shown in Fig. 6(b), the power generated by the photoelectric conversion in the light-receiving unit 2 can be used to fly the aircraft 3 (3FCAR) including 2, and passengers and cargo can be transported. <0040> As shown in Fig. 6(b), the aircraft 3 is provided with the light-receiving unit 2. After appropriately charging a secondary battery such as a lithium-ion battery of 3 or a hydrogen fuel-fuel cell system by receiving the photons in the air like a whale taking a breath, it can be made to descend again near the ground, and 3 can be used as a transportation device 3 for transportation purposes. ● The aircraft 3 may be manned or unmanned. ● The unmanned aircraft 3 may perform known operations, for example, navigation to the destination, automatic piloting / automatic driving, and dispatching of the aircraft 3 with a smartphone terminal (summoning 3 from the air to the ground with a smartphone). ● It may also be used for surveillance operations, for example, for monitoring the movements and intimidation of wild animals in mountain villages suffering from wildlife damage, or for use in town security. <0041> In the case of 3 which is an unmanned aircraft, even if 3 encounters an accident, there are no passengers, so the damage can be reduced. Also, the unmanned aircraft 3 can be positioned by GNSS etc. and perform known automatic driving as in a drone or an autonomous vehicle. In addition to automatic driving, it can perform unmanned (programmed) formation flight 3FORM, or be used as a flying robot 3ROBOT for performing operations in the flying type of agriculture, forestry, fishery, and various industries, a vehicle for passenger transportation, or for housing, residence, and real estate businesses such as an air hotel or an air station (an in-air staying facility / base like a space station). <0042> ● According to the present application, the aircraft 3 (which is an aircraft 3 that receives power supply or energy replenishment at any time by space solar power generation) can eliminate the refueling step like a jet engine aircraft or the charging step like a battery-powered drone, reducing or eliminating the time when the aircraft 3 returns to the ground and waits. <0043> ● Even when the ground airport does not function and it is impossible to stay at the airport or replenish fuel, in the system using 1, 2, and 3 of the present application, 3 can be charged and energy replenished in the air, and can continue flying even when the airport cannot be used. <0044> ● In Fig. 6(b), three flying cars 3FCAR are configured to transport passengers and cargo by swapping like taxis. ● On the other hand, when the flying car 3FCAR flies along a route between, for example, Tokyo and Okinawa or between Tokyo, the Ogasawara Islands, and Guam, if photons can be transmitted from 1 to the light-receiving unit 2 above the route for the above-mentioned charging / energy supply, the flight distance can be extended.● In FIG. 10, for example, a conceptual diagram is disclosed of a concept in which, from Japan, it flies towards Uruguay near the back side of Japan, and on the way, 3·3FCAR receives energy supply according to Claims 1 and 2 while flying over the Pacific Ocean, the Atlantic Ocean, or the airspace near New York over the ocean, etc., and transports passengers. (Even without landing on the ground for charging and refueling, it can be charged and energy-supplied at any time by Claims 1, 2, and the said photons, and the flight range of 3FCAR can be increased.) <0045>● In the configuration of FIG. 6(a), using 3FORM, a device (3FORM-ACTING) that performs shows, performances, competitions (for example, competitions, race competitions, and survival games by robot-type 3FORM), and missions in the air by the 3FORM-AD-BALLOON or the formation mechanism of 3FORM, or a humanoid robot with human-type limbs and a torso by the formation mechanism for shows or something. A configuration using the 3FORM formation for humanoid robots 3FORM-HUMANOID, which can also be used for labor, monitoring services, transportation services, entertainment, and robot competitions, is disclosed. <0046>● The 3FORM-HUMANOID can be an aircraft, a somewhat large humanoid robot with little concern for its own weight, or a humanoid, puppet, or other object imitating a human, animal (such as a tiger, rabbit, zodiac animal, lion, dog, cat), plant, mythical creature (such as a dragon), or character. ● In this case as well, by using the SSPS, 1, and 2, it may be possible to perform missions constantly in the air without the need for charging and energy replenishment on the ground. <0047>Photons in the ultraviolet to X-ray region have a higher energy per photon compared to microwaves. (They can be absorbed and attenuated by reacting with atmospheric molecules and undergoing chemical reactions, etc.) Since the wavelength is short, the size of the receiving unit 2 can be miniaturized. (In the case of photons in the microwave region, the receiving unit 2 is an antenna or rectenna, while for photons with a shorter wavelength than ultraviolet light, a photocell or a reactor that chemically changes substances such as water into fuel substances such as hydrogen may be used.) <0048><High-altitude receiving unit 2 for receiving photons attenuated in the atmosphere>In the present application, in order to use the attenuated photons, it is necessary to install the receiving unit 2 in a section of the high-altitude thin atmosphere as seen from the ground. <0049><Generation and utilization of photons that do not penetrate the atmosphere>The photons in the UV-C region (photons absorbed in the atmosphere by causing chemical reactions of oxygen and ozone) are shown as an example. For ultraviolet light with a wavelength of 1 nm to 280 nm, the atmospheric absorption is large. (The absorption is particularly large from 1 nm to 200 nm.) In a system using photons from 1 nm to 280 nm, light does not penetrate to the ground, and the safety on the ground may be ensured. In addition to ultraviolet light, photons that do not penetrate the atmosphere and photons blocked by the atmospheric window, such as photons in the infrared region with a wavelength of 1 micrometer to 10 micrometers and laser light using them, can also be considered. Non-Patent Document 3 and Patent Document 1 describe millimeter waves. Millimeter waves can also be absorbed in the atmosphere. In the present application, photons on the shorter wavelength side than ultraviolet light absorbed by molecules in the atmosphere, photons on the longer wavelength side than infrared light, millimeter waves, etc. can be used. It is necessary to select the wavelength of the photons during actual verification. The present application discloses a system of photons absorbed by the atmosphere (such as oxygen and ozone), but the wavelength of the photons is not limited.<0050><Means for transporting the energy obtained by the aircraft 3 including the light-receiving unit 2 in the air to the ground>According to Patent Document 1, it is disclosed that the energy of the SSPS is transported from space to the ground using a system consisting of radio waves or lasers (a system of only photons). Non-Patent Document 4 also discloses that energy is transmitted to the ground by a laser near a wavelength of 1070 nm (near infrared). <0051>In the present application, as shown in FIG. 1, the aircraft 3 including the light-receiving unit 2 is provided with a cable 12 to the ground unit (for example, referring to and citing the cable 12 connecting the aerial structure 2 and the ground unit in the previous application or the cable 12 of the orbital elevator unit connecting the space structure 1, the aerial structure 2 and the ground) or wireless power transmission means 3WEP. However, considering that radio waves are likely to spread in wireless power transmission and it is unclear whether a lightweight and low-resistance transmission line can be obtained up to the stratosphere in the case of a cable, a method of converting electric power energy into chemical energy - fuel and delivering it is disclosed in FIG. 2. Also, FIGS. 3, 4, and 5 are disclosed as systems using fuel. Other forms and explanatory diagrams are disclosed in the drawings of the present application. <0052>Patent Document 2 discloses descriptions regarding non-rocket launching methods such as orbital elevators, orbital ring systems - orbital rings, and mass drivers. ●In the field of space development including the construction of SSPS, low-cost launching means (including rockets and non-rocket methods) are highly desired. <0053>●For example, in FIGS. 1A and 1 of Patent Document 2, the cable 12 that becomes the orbital elevator unit may be an orbital ring. The annular structure (1 or 2) that rotates on a large scale generates centrifugal force and the like, and the annular structure is held at an altitude in the air and space. The cable is suspended from the annular structure, and this is the configuration of an orbital elevator in a low orbit that lifts and holds the weight of the cable in the air. ●The orbital ring and the orbital elevator enable the transportation of construction materials between space and the ground for the construction of SSPS and the energy obtained by SSPS, as well as the power transmission and fuel transportation using the structures, electric wires, and cables. However, the problem is that the device is large-scale.● However, in the present application, there is no such large-scale circular structure, and it is a system that does not have a large force to lift the cable 12 other than the force by aviation means such as the buoyancy of the aircraft 3. It can use a high-altitude balloon or the like, or even a hot air balloon heated by energy derived from SSPS. The gas for floating and ascending filled in the balloon may be a system that relies only on the buoyancy of gases such as hydrogen gas, helium, and methane that can float in the air. ● The present application is an invention for delivering energy from SSPS to the ground using, for example, a compact and small-scale balloon that may be the aircraft 3 as compared with the so-called orbital ring and orbital elevator of Patent Document 2. <Prior Art Documents> <Patent Documents> <0054> <Patent Document 1> Japanese Patent Application Laid-Open No. 2004-266929 <Patent Document 2> Japanese Patent Application Laid-Open No. 2023-001372 <Patent Document 3> Japanese Patent Application Laid-Open No. 2022-058853 <Patent Document 4> Japanese Patent Application Laid-Open No. 2022-105726 <Non-Patent Documents> <0055> <Non-Patent Document 1> Research on Space Solar Power System (SSPS) [JAXA, viewed on January 6, Reiwa 5, Internet, https: / / www.kenkai.jaxa.jp / research / ssps / ssps-ssps.html] <Non-Patent Document 2> The Atmospheric Window [National Oceanic and Atmospheric Administration NOAA, viewed on January 8, Reiwa 5, https: / / www.noaa.gov / jetstream / satellites / absorb] <Non-Patent Document 3> Atmospheric Window [Meteorological Satellite Center, Japan Meteorological Agency JMA, viewed on January 8, Reiwa 5, Internet, https: / / www.data.jma.go.jp / mscweb / ja / prod / band_window.html ] <Non-Patent Document 4> Research on Laser Wireless Energy Transmission Technology [JAXA, viewed on January 21, Reiwa 5, Internet, https: / / www.kenkai.jaxa.jp / research / ssps / ssps-lssps.html ] <Summary of the Invention> <Problems to be Solved by the Invention> <0056> Next, the problems and solutions in the present application will be described. <First Problem> In a transmission method in the form of radio waves such as laser light or microwaves that can pass through the atmospheric window toward the ground due to misalignment in the direction of the light emitting unit 1 and the transmitting unit 1, photons or the energy of wireless transmission and power transmission will be transmitted to the ground.Even if the transmitted power can be reduced in that form, there is a possibility of harm to people living on the ground. There was a need for a method to dispel people's concerns that photons in the form of radio waves or lasers might pass through the atmosphere and reach the ground. <0057>● It was necessary to devise a system that performs wireless power transmission by SSPS while ensuring the safety of people on the ground by limiting the photons transmitted by the transmitting unit 1 to those with wavelengths that are easily absorbed by the Earth's atmosphere and operating accordingly. <0058>● In this application, a configuration is proposed in which energy reaches the upper troposphere, the stratosphere, etc. in the air but does not reach the ground by using photons that are absorbed in the atmosphere and not transmitted to the ground. <0059>● In particular, as an example, it is proposed to use the wavelength of photons that are absorbed, such as by chemical reactions of oxygen, ozone, etc. in the atmosphere, and whose transmittance through the atmosphere is close to zero, as photons that are not transmitted by the atmospheric window. <0060><Second Problem>When transmitting energy while diffusing microwaves from an aircraft towards a rectenna, etc. on the ground, it is assumed that the energy diffuses and cannot be efficiently transmitted. For example, when using wireless in the section from 3WEP in FIG. 1 of this application to 2LAND·2TAG·2WEP on the ground, the radio waves reach the said section while diffusing. Radio waves with a high energy density have problems such as disturbing the residents on the ground. <0062>● Therefore, the applicant considered that it was an issue to devise a system for transporting energy between the aircraft 3 in the air and the ground section 4 without being limited to electromagnetic methods such as wireless power transmission or power transmission by electric wires and cables. (This application considered three methods for energy transmission: wired, wireless, and fuel transport.) <0063>● As a result, a system using fuel described in FIGS. 2 to 4 is disclosed. ● Also, when operating SSPS on the moon and sending energy as fuel, a form is also disclosed in which a substance combined with oxygen (such as silicon oxide, aluminum oxide, iron oxide, water, etc.) among the lunar resources is reduced and dropped to the Earth as shown in FIG. 4. <0064><Third Problem, Problem in the Embodiment><<Causing the Photons of the Light-Emitting Unit 1 to Hit the Light-Receiving Unit 2 and Positioning>>● It is preferable that the light-receiving unit 2 is small. In the case of a small size, it is necessary to irradiate (accurately) and cause the laser light to hit from 1 to 2.<0065>As shown in FIG. 10, for example, when irradiating a plurality of 1s (a plurality of 1s included in the constellation of a plurality of 1SSPS-SATs) of an ultraviolet laser with 2, even if it misses and misfires, although the laser is attenuated by oxygen, ozone, and the atmosphere, it results in energy loss during misfiring, so a method to hit without misfiring was necessary. <0066>● Paying attention to the use of the quasi-zenith orbit also used in the QZSS of positioning satellites in Patent Document 1, in FIG. 5, a plurality of light-emitting units 1 (or artificial satellites 1SSPS-SAT equipped with a plurality of issuing units 1) operating and moving along the quasi-zenith orbit may be arranged in a plurality of quasi-zenith orbits or as an artificial satellite constellation 1SSPS-SYS-QZSS-SEIZA. <0067>● By operating in the quasi-zenith orbit, 1SSPS-SYS-QZSS-SEIZA enables 1SSPS-SAT to always pass over Japan's sky, and while having a configuration where it can constantly irradiate photons to the light-receiving units 2 on the ground and air sides by switching, similar to a positioning system by the global positioning satellite system GNSS or QZSS, the positioning signal transmitted from 1SSPS-SYS-QZSS-SEIZA can be used for positioning by the positioning unit 2POSI additionally arranged at the light-receiving unit 2 using the positioning system by QZSS. <0068>● To examine the position of the light-receiving unit 2, the distance relationship between the light-receiving unit 2 and 1SSPS-SAT or 1SSPS-SYS-QZSS-SEIZA, and the coordinate information in the three-dimensional space, 2 and 2POSI and 1SSPS-SAT or 1SSPS-SYS-QZSS-SEIZA may communicate by laser or radio wave, and 2 and 2POSI and 1SSPS-SAT or 1SSPS-SYS-QZSS-SEIZA may be equipped with the said communication means. <0069>● To assist in the positioning of 2 and 2POSI, timepieces such as atomic clocks, altimeters, sensors, and instruments may be installed on 2POSI or the aircraft 3 including it. For example, it may be equipped with a gravity sensor and a gravity measurement system using the optical lattice clock method and may be equipped with an altimeter. The altitude component of the information of the three-dimensional space where 2 and 2POSI are located is measured by the altimeter, and it may be combined with the positioning result by the positioning system by the global positioning satellite system GNSS or QZSS for positioning and utilization (utilization for hitting the photons emitted from 1 to 2 to 2). ● Photons may be irradiated from 1 to 2 equipped with 2POSI using the said positioning result.<0070><<Separation between the SSPS light-emitting section 1 and the light-receiving section 2, and the four sections between the light-receiving section 2 and the ground>> ● In Fig. 5(a), there is no residential area on the ground at the latitude and longitude between 1 and 2, and it can be placed, for example, over the sea of Japan. The energy of light or electricity is converted into chemical energy (fuel) by 2 and 3·3FUEL, and can be transported by 3FUEL from over the sea of Japan to the fuel storage base 4STAT (or onshore or offshore base / fuel tank 4STAT) in the ocean where there is demand. It may be transported from 4STAT to onshore users 6 or residential areas 6, or fuel may be pumped through a pipeline. <0071> ● In the case of Fig. 5, there is no power transmission loss when the light-receiving section 2 is connected to the power grid by an electric wire. Also, the aircraft 3 for lifting the electric wire 12 is unnecessary. The aircraft 3 does not need to lift the electric wire. (For example, the aircraft 3 can have the performance of floating only for itself.) <0072> ● The aircraft 3 can use the energy from the SSPS to obtain the energy for floating both during the day and at night. can fly in the troposphere or stratosphere. In this case, if the aircraft 3 can maintain the forces such as the force, buoyancy, and the force to maintain altitude by flight to hold the electric wire and float in the air, and if the aircraft 3 can hold a cable 12 with a total length of, for example, 20 km, the process via fuel such as 3FUEL may not be necessary. It should be noted that the electric wire, electrodes (motor and coil if a propeller is required), and other electrical wiring members such as the aircraft 3 used in the present application are preferably lightweight. <0073> ● Also, in the case of Fig. 5, it is possible to meet the demand of not wanting to place the user parts 6 and 4, which are also residential areas, directly below or near the light receiving part 2. <0074> ● Even in that case, in the configuration of Fig. 5(a) of the present application, by sandwiching the energy conversion process to fuel and chemical substances, the section between the SSPS light emitting part 1 and the light receiving part 2 and the section between the light receiving part 2 and the ground 4 can be separated, and as a result, there may be an advantage of reassuring the people in the residential area 4. <0075> ● However, when the energy of photons and the electrical system in the section between the SSPS light emitting part 1 and the light receiving part 2 is converted into chemical energy used in the section between the light receiving part 2 and the ground 4, conversion loss (loss during conversion from light and electrical energy to chemical energy) occurs. Therefore, as shown in Fig. 6, if the energy can be consumed as electrical energy, thermal energy, etc. in the part of the aircraft 3 (before converting to chemical energy) and used for transportation equipment, passenger transportation, work by robots, shows, formation flight, air balloons, advertisements, and entertainment, the chemical energy conversion loss can be eliminated, which is considered important. Therefore, the usage examples of the aircraft 3 are disclosed in Figs. 6, 7, 8, 9, 10, and 12. <0076> <<When transporting the power and energy of SSPS to the aircraft 3 including 2 and then using it for aerial applications instead of for ground use>> Aircraft require energy for flight and movement. Jet engine-powered aircraft 3, drones 3DRONE, or aircraft formations 3FORM driven by fuel have limited flight time due to battery or fuel limitations, and fuel supply or charging steps are required during aircraft operation. <0077> Also, in the case of a solar plane aircraft 3 equipped with solar cells and batteries on the earth that can potentially extend the operating time, there are limitations in the aircraft's performance due to the charging amount constraint during the day. <0078> Therefore, a system that uses the energy obtained at the light receiving part 2 for driving the aircraft 3 without sending it to the ground is also disclosed.● Figures 6 and 8 disclose an aircraft formation flight group 3FORM or a humanoid device or humanoid robot 3FORM-HUMANOID, 3FORM-DOLL(MACHINE) composed of formation flight using the aircraft 3, or a robot 3FORM-ACTING, 3ROBOT that moves with them, and further a 3FORM-AD-BALLOON that uses them for advertising or display. ● Figure 9 describes examples of removal processing and additive manufacturing of a work target 4WK by the 3ROBOT (which may use a robotic arm). <0079><<After transporting the power of SSPS to 2 and using it for wireless power transmission>> An example is described in Figure 7 for use during wireless power transmission. Tags for monitoring, tags for product management, beacons and tags for searching for climbers or people who have encountered an avalanche are well-known. A monitoring device and wearable device 2TAG for monitoring children and dementia patients are also well-known. However, there may be problems with the method of supplying power to move the tag or charging the tag. Therefore, Figure 7 of the present application discloses a tag 2TAG·2TAG-PATCH that can be powered by wireless power transmission from the aircraft 3 and can operate wireless communication and sensors and beacon operations. <Means for Solving the Problems><0080><First Means for Solving the Problems>● A light receiving unit 2, an aircraft 3, and a system using fuel described in Figures 2, 3, 4, 5, 10, and 11 are disclosed. A configuration capable of wireless transmission and power transmission is adopted using short-wavelength photons absorbed by molecules in the atmosphere such as UV-C, UV-B to X-rays between the light emitting unit 1, transmitting unit 1 and the light receiving unit 2, receiving unit 2, and the light receiving unit 2 is attached to a transport means 3, transport equipment 3, arranging means 3 such as an aircraft 3 or a flying boat 3 arranged at a high altitude where it is difficult to absorb the short-wavelength photons, so that the light receiving unit 2 can receive the photons from the light emitting unit 1. The light emitting unit 1, transmitting unit 1 may use an ultraviolet laser or a radiation light generating device (generated using a particle accelerator and an undulator, etc.), and its operating power and energy may be obtained from solar power generation by a solar cell, SSPS, or solar energy.● Also, as shown in Fig. 4, when reducing the launches to the moon while manufacturing fuel on the moon and using the fuel on the moon or on the ground, a form is disclosed in which substances combined with oxygen (such as silicon oxide, aluminum oxide, iron oxide, water, etc.) among lunar resources are reduced by the electric power and solar energy of SSPS solar power generation and dropped to the earth. <0086> Fig. 10 is an explanatory diagram of the laser beam, the focus of the laser energy, and the laser attenuated by the atmosphere during laser irradiation from a plurality of light-emitting parts 1 to 2 of the quasi-zenith orbit group in the present application. Also, an explanatory diagram of 3FCAR and 3 receiving energy replenishment by the energy transport method of the SSPS of the present application on the way to a remote location is described. <0081> <Second Problem-Solving Means> As shown in Figs. 2 and 5, a system is proposed that uses fuel instead of electric power or light during energy transport from the light-receiving part 2 in the air to the ground part 4 and the user side 6. Specifically, it is assumed to use hydrogen obtained by reducing water, carbon or hydrocarbons obtained by reducing water and carbon dioxide, and metals obtained by reducing metal oxides. After the light-receiving part 2 receives the energy from the SSPS, an aircraft 3 or 3FUEL for fuel synthesis connectable to the aircraft 3 including the light-receiving part 2 is connected using a connection line or connection part 3WIR, and the electric power and energy are shared and transferred between 3 and 3FUEL, or energy is transmitted from 3 to 3FUEL. Fuel is synthesized from the energy held by the light-receiving part 2 and the aircraft 3 and 3FUEL and the raw materials for fuel in a reactor or electrolyzer 3FUEL-GEN, and the fuel is transported and stored in the flow path, pipeline, and tank 3TANK of the aircraft 3 and 3FUEL. The tank 4FUEL-TANK on the ground part 4 and 3TANK are connected using 3VALV, 4VALV, connection pipes, nozzles, etc., and the fuel is transported to the tank 4FUEL-TANK on the ground part 4. ● In this way, by transporting and storing the energy derived from SSPS from 1SSPS via the light-receiving part 2 and the aircraft 3 and then using it on the user side 6, the energy is delivered to the user without using wireless power transmission and power supply between the ground and space. <0082> <Third Problem-Solving Means> Examples are described in Figs. 6 to 9, etc. as applications during wireless power transmission.In FIG. 6, an aircraft 3 that can be powered and operated at all times using an aircraft 3, a formation flight group 3FORM of aircraft 3, or a humanoid device or humanoid robot 3FORM-HUMANOID, 3FORM-DOLL(MACHINE) composed of formation flight, or a robot 3FORM-ACTING that moves with them, and further a 3FORM-AD-BALLOON that uses them for advertising or display are disclosed. <0083> FIGS. 8(a) and 8(b) are examples of a formation flight group 3FORM of aircraft 3, an aircraft group 3FORM, or a humanoid device or humanoid robot 3FORM-HUMANOID composed of formation flight. An aircraft 3 equipped with a robotic arm, in which the upper body 3FORM-HUMANOID-UPPER and the lower body 3FORM-HUMANOID-LOWER of a humanoid robot perform formation flight while a robotic arm equipped with an additive manufacturing nozzle 3A1-AM for painting attaches a paint bullet from a paint nozzle and performs painting while performing an action of firing a paint bullet (description of firing a paint bullet) is described. A figure showing an operation of spraying a paint device held by the 3FORM-HUMANOID composed of the upper body and the lower body to the right side is described in FIG. 8(b). ※There may be a configuration of a competition, exhibition, or show in which a paint bullet is sprayed as shown in FIG. 8 in a robot competition. ※In FIG. 8, as a result of considering that the robotic arm can perform the same work as a human, such as painting, a humanoid robot is disclosed as an example. However, in the present application, it is not limited to humanoid, and it may imitate real animals and plants such as dog type, cat type, bird type, fish type, whale type, tree and flower plant type, or may imitate imaginary creatures and characters such as dragons. ※Also, a stage device for reproducing and expressing a certain scene in a play or the like may be configured in 3FORM. It may be used for advertisements, dynamic objects, billboards, exhibitions, and ad balloons arranged in the air. ※For example, formation flight 3FORM may be performed using each aircraft 3 equipped with a light emitting device 31, and a performance of drawing a pattern in the sky (such as the display of a sphere or pictogram by light emitting drones deployed in the night sky at the Tokyo 2020 Olympic Games as an example) may be performed. FIG. 8 may use a manned or unmanned aircraft 3. <0084> FIG. 9 describes an aircraft 3 equipped with a robotic arm having or equipped with an additive manufacturing device or a removal processing device.FIG. 9 includes an explanation of cutting a branch with the removing device 3, for example, when pruning a branch of a tree. <0087>● Also, when the aircraft 3 is provided with a balloon part for floating and ascending, using a rare gas such as helium may pose a resource constraint. Therefore, in the system using the SSPS disclosed in FIG. 11 of the present application, the hot air balloon can be heated using the energy received by 3 from the SSPS through 2, and the hot air balloon can be used for the ascent of the aircraft 3. (The propulsion device 3TH (operating using the SSPS)) can generate a force to ascend against gravity and forces for movement, flight, and propulsion, and can be used for the operations of ascent, floating, propulsion, flight, and movement of the aircraft 3.) <0085>FIG. 7 discloses the tag 2TAG and 2TAG-PATCH that can be powered by wireless power transmission from the aircraft 3 and can perform wireless communication and the operation beacon operation of the sensor. <Advantages of the Invention> <0088>● While miniaturizing the light receiving part 2 and the receiving part 2, the photons of the light emitting part 1 and the transmitting part 1 are photons of a wavelength that is easily attenuated in the atmosphere, making it difficult for them to reach the ground and protecting the safety of people and objects on the ground. (FIGS. 1, 2, 10, etc.) ● Regarding the energy transportation from the light receiving part 2 to the ground, by using a system that uses chemical energy and fuel to eliminate the concerns about weight in the case of electric wires and the enlargement of the user-side receiving part and the permeable radio waves in the case of wireless power transmission, the problems of power transmission by wireless power transmission, electric wires, and cable power transmission may be overcome, and the energy produced by the SSPS may be delivered to the user. (FIGS. 1, 2, 5, 10, 11, etc.) ● The aircraft 3, the formation flight 3FORM, and the aircraft group 3FORM equipped with the light receiving part 2 can operate by receiving the energy supply from the SSPS, reducing the steps of fuel replenishment and charging on the ground, and may be able to extend the operation time. And 3 can be used for applications such as transportation, monitoring, patrol, work, and entertainment. (FIGS. 6, 7, 8, 9, 10, 11, 12, etc.) ● The power supply and charging of the tag 2TAG by the aircraft 3 may be used for the driving, searching, sensing, and communication of the 2TAG. The 2TAG that can communicate with 3 may be used for reagent bottles, cargo compartments, containers, trays, commodity shelves with a weight measurement function, as well as the management of automobiles, aircraft, transportation equipment, keys, identity cards, objects, and organisms.<Brief Description of the Drawings><0089><Fig. 1>Fig. 1 is an explanatory diagram of an energy transportation method from space to the Earth, which describes the configuration of the present application, including the light emitting unit 1 and transmitting unit 1, the light receiving unit 2 and receiving unit 2 of the present application, the aircraft 3 including the light receiving unit 2, the ground unit 4, the user 6, the regions such as clouds, the troposphere and the stratosphere (Example 1). <Fig. 2>Fig. 2 is an explanatory diagram of transporting energy from the light receiving unit 2 and receiving unit 2 and the aircraft 3 to the energy demand area on the ground. (Example 1). <Fig. 3>Fig. 3 is an explanatory diagram of launching the raw material of fuel into the SSPS by a launching means, manufacturing fuel by the electric power obtained in the SSPS, and dropping and using the fuel towards the ground. (Example 2). <Fig. 4>Fig. 4 is an explanatory diagram of a system for reducing lunar resources and lunar metal oxides by the electric power or energy of an SSPS near the moon to obtain metal 5M and reduced substance 5MC, and transporting the metal 5M and 5MC to the ground. (Example 3). <Fig. 5>The upper part of Fig. 5 shows the energy from the system (1SSPS - SYS - QZSS - SEIZA) in which a plurality of artificial satellites and spacecrafts (1SSPS - SAT) of the SSPS deployed in a plurality of units in the quasi - zenith orbit (QZO) form a constellation to the ground. It is an explanatory diagram of transportation. (Example 4) <Figure 6> The upper part of Figure 6 is an explanatory diagram of a formation flight group 3FORM of aircraft that can be powered and operated (constantly) using aircraft 3, or a humanoid device composed of formation flight, or a humanoid robot. An explanatory diagram for taxi and cargo transportation applications. (Example 5) <Figure 7> An explanatory diagram of the case of delivering power and energy to tag 2TAG by wireless power transmission of aircraft 3 and drone 3DRONE to manage the objects pasted with tags. (Example 6) <Figure 8> An explanatory diagram of a robot or exhibit imitating a creature formed by 3FORM. (Example 7) <Figure 9> An explanatory diagram of a flight robot 3 without a pilot, which is equipped with a robot arm and tools (e.g., saw). (Example 8) <Figure 10> An explanatory diagram of the laser beam during laser irradiation from a plurality of light-emitting parts 1 in the quasi-zenith orbit group to the light-receiving part 2 in the present application, the laser energy focus, and the laser energy scattering after passing through the focus. (An explanatory diagram of the claim that it is difficult to deliver energy to a ground household during laser irradiation in the present application) <Figure 11> An explanatory diagram of the system of aircraft 3 that can output the energy obtained from the light-receiving part 2 as various energies such as power, light, fuel, or chemical substances to the outside. (Also, an explanatory diagram of aircraft 3 equipped with a hot air balloon 3HAB and a propulsion device 3TH that may operate with the energy of the battery, fuel, or SSPS of aircraft 3.) <Figure 12> An explanatory diagram of a water supply device 3 and a method of using water, in which water collected by rainfall, rainwater, snowfall or water supplied from ground 4H2O is input to 3 that may be equipped with a light-receiving part 2, and the water is delivered to a place where water is needed, a place to be extinguished, etc. (Example 9) <Modes for Carrying Out the Invention> <0090> Examples (configuration examples) are shown in Figures 1 to 7. <Example 1> <0091> <Energy transport system derived from SSPS using short wavelengths> Figures 1, 2, and 5 are Examples 1 and 4 of the present invention. When a communication satellite, its constellation, an artificial satellite constellation, or a spacecraft (e.g., a constellation of communication satellites) reaches on the ray during laser irradiation, it is recommended that the laser can be temporarily turned off. Similarly, it is preferable that microwaves other than the laser can be turned on and off. ※ Note that, as in the explanatory diagram of the beam of the pilot laser, beacon laser, and main laser of L-SSPS in Non-Patent Document 4, photons, lasers, and radio waves for guiding and communication may be exchanged between the light-emitting part 1 and the light-receiving part 2.For example, communication using a communication laser for guiding to control the orientation of the light receiving unit 2 with respect to the light emitting unit 1 may be performed between 1 and 2. <0092><Transport system of SSPS-derived energy by fuel from the light receiving unit 2 to the ground unit 4><<System using water / hydrogen>>An explanatory diagram of the internal elements of the light receiving unit 2 and the aircraft 3 is shown in FIG. 11. In the system of the light receiving unit 2 and the aircraft 3FUEL capable of fuel synthesis described in FIG. 2, water is delivered from the ground to the light receiving unit 2 (reactor 2REA of 2) or 3 (reactor 3REA of 3) including 2 by the aircraft. 3 and 3FUEL that receive power / energy from the light receiving unit 2 or 2 electrolyze / decompose water to generate hydrogen and oxygen, store hydrogen in a tank inside the aircraft, transport it to the ground, and store and use it in the ground tank 4. During use, hydrogen may be transported to drive a hydrogen engine, drive a fuel cell, execute hydrogen utilization type thermal power generation, and transmit power to the power system. <<System using iron>>In the system of the light receiving unit 2 and the aircraft 3FUEL capable of fuel synthesis described in FIG. 2, in addition to water, metal oxides may be used, for example, iron oxide may be used. The aircraft delivers iron oxide from the ground to the receiving unit 2, and 3FUEL that receives power / energy from the receiving unit 2 or 2 may reduce the iron oxide. <0093><<System using iron and water, system using metal and water>>In the system of the light receiving unit 2 and the aircraft 3FUEL capable of fuel synthesis described in FIG. 2, two oxidized substances may be used. For example, in the system of the aircraft 3 and the aircraft 3FUEL that can be connected to the light receiving unit 2 or 2, in order to perform hydrogen production from iron (hydrogen reduction iron production), water and iron oxide may be sent from the ground to the light receiving unit 2 by the aircraft 3FUEL. Using the energy for water reduction based on the energy of photons from the light emitting unit 1 in the light receiving unit 2 in the air and the system of the aircraft 3 or the aircraft 3FUEL, hydrogen may be produced, and then the iron oxide may be reduced with the hydrogen to produce iron. In the system of producing hydrogen and iron in 3, iron oxide and iron do not have a large volume like hydrogen, and a hydrogen cylinder for pressurized loading of gaseous hydrogen is not required when loading on 3. Iron oxide / iron has the advantage that it can be handled at normal pressure without the need for pressurization like a hydrogen cylinder during transportation by 3, for example. To produce iron from hydrogen, hydrogen is produced from water, iron oxide is reduced with hydrogen to obtain iron, and then the process returns to water. If water is kept in a certain amount in 2, 3, or 3FUEL, iron and oxygen can be produced in 2, 3, or 3FUEL by introducing iron oxide into the hydrogen production from iron system.On the ground, iron can be used to generate electricity and heat from chemical energy, such as in iron-air batteries or the iron powder in a warming stove that oxidizes iron. There are also advantages in the large resource amounts of water, hydrogen, and iron. (In 2, 3, and 3FUEL, in addition to the reduction of iron, zinc, metallic lithium, metallic sodium, metallic magnesium, metallic calcium, aluminum, etc. can also be used to reduce metal oxides in the same way.) <0094><<Systems using hydrogen, water, carbon dioxide, and hydrocarbons>> In a system using water and hydrogen, a carbon dioxide or carbon source can be introduced to reduce carbon dioxide and produce hydrocarbon-based synthetic fuels. Carbon-based materials can be produced from carbon dioxide. ● The carbon dioxide stored and preserved on the ground can be transported to the light-receiving unit 2 and the aircraft 3 system by 3FUEL or the like, and the carbon dioxide can be reduced and separated into carbon and oxygen using energy that may be derived from SSPS, which can be used to reduce carbon dioxide on Earth. ● In the systems of 2, 3, and 3FUEL, carbon dioxide can be separated from the air and the carbon dioxide can be recovered from the atmosphere by separating the carbon and carbon components from the carbon dioxide. For separation, known methods such as the method of absorbing carbon dioxide in monoethanolamine, gas membrane separation, or cooling and separating the air can be used. <<Separation of atmospheric components from the atmosphere>> ● In the systems of 2, 3, and 3FUEL, energy from SSPS can be used to constantly drive devices (such as pumps, machines, and reactors for separating air components) to recover carbon dioxide and the like from the air. Similarly, energy that may be derived from SSPS can be used to separate and recover components constituting the atmosphere, such as noble gases like helium and neon, oxygen, nitrogen, and argon. Furthermore, the separated and recovered noble gases can be loaded into 3GAB. ● For separation, a method of compressing and liquefying the gas with a compressor for separation (cryogenic separation) may also be used. Known methods such as gas membrane separation or cooling and diverting the air can be used to separate atmospheric components from the atmosphere. <<Production of ammonia>> For example, ammonia NH3 can be produced for gas applications, chemical applications, and fertilizer applications that lift 3 using nitrogen in the air and 3FUEL that transports 1, 2, 3, water, and hydrogen of the present application. <0095>3 may be in the form of a gas balloon system.● In Fig. 11, the 1HNU at 2 may be photoelectrically converted into 2PCE to obtain electric power to drive the propulsion device 3TH, or the 1HNU received at 2 from 1 may be absorbed by a photon absorber, the photon absorber may be heated, and the heat may be used to heat the propellant for driving 3TH, and the propellant may be heated and injected to drive 3TH. 3TH including the light-receiving unit 2 and the transport device 3 may be configured to float, levitate, and propel by the energy obtained at 2. <0096><<Floating and Propelling of 3>> 3 may be propelled using a rocket, propellant injection, or photons or charged particles, like the aircraft 3 disclosed in Patent Document 2, Patent Document 3, and Patent Document 4. For example, it may be an aircraft 3 that propels by the reaction of emitting and reflecting photons such as a rocket, propellant injection, ion thruster, or photon sail. ● 3 of the present application may be arranged and floating in the air by jetting and reflecting the said photons or charged particles toward the ground and using the reaction. A thrust opposite to the direction of gravity may be generated using a rocket, propellant injection, or photons or charged particles. (Similar to the case of obtaining buoyancy by a balloon, a drone 3 constantly charged by SSPS generates thrust by the propulsion device 3TH in the sky so that it can balance gravity and its own weight and continue hovering.) The aircraft 3 receiving energy supply by the SSPS of the present application may perform hovering, flight, propulsion, movement, attitude control, and movement of the airframe by the propulsion device 3TH. <0097> The FSM, pilot laser beam and its light-receiving unit, main laser beam, and beacon laser beam described in the L-SSPS schematic diagram of Non-Patent Document 4 may be used in the system of the present application. ● When implementing the configuration of Non-Patent Document 4 in the present application, for example, a pilot laser beam emitting unit 2POSI-PL may be provided in the light-receiving unit 2 (which may be the 2POSI unit) provided in the aircraft 3 such as Fig. 1 or Fig. 2 of the present application, and the pilot laser beam may be irradiated from the emitting unit 2POSI-PL to the pilot laser receiving unit 1POSI-PL of the light-emitting unit 1 on the space side / SSPS side. The laser emitting unit 1 may emit the main laser and the pilot laser to the light-receiving unit 2 or 2POSI of the aircraft 3. Then, using them, the main laser and beacon laser of the light-emitting unit 1 of the present application may be controlled to emit and irradiate photons from 1 to 2 and hit 2. <0098><<Positioning and Communication>> Fig. 5 describes an example of energy transport in the quasi-zenith orbit of the present application and examples of energy transport from the geostationary orbit and the moon.When configuring the system of the present application in the quasi-zenith orbit at the upper part of FIG. 5, the SSPS may also incorporate the functions of known artificial satellites such as positioning satellites, communication satellites, and ground observation satellites. ● In the quasi-zenith orbit where the SSPS satellite is deployed, the position of the light receiving unit 2 may be measured by the functions of the positioning satellite mounted on the SSPS or the QZSS positioning satellite, and used for positioning the photon irradiation from the light emitting unit 1 to the light receiving unit 2 and ensuring the accuracy of emission. Communication including positioning information and emission instructions for emitting the photons from 1 to 2 and hitting them may also be performed. ● 3, 2, and 1 may be connected to the Internet communication network from another system, for example, a satellite 1LINK deployed in space, or may be connected to the terminals and computers of the ground station 4 and the user station 6 via a communication device, or may be connected to the Internet communication network through 4 and 3. (The position of 2 may be measured by 1SSPS-SYS-QZSS-SEIZA which is also a positioning device of QZSS.) <0108> Using the 2POSI of the light receiving unit 2 and 1SSPS-SYS-QZSS-SEIZA which is also a positioning device of QZSS, the positional relationship between each 1 and the light receiving unit 2·2POSI may be measured. ● The 2POSI of the light receiving unit 2 and 1 may perform wireless communication and laser communication, and may transmit and receive position information and other necessary data between 2 and 1. (When there is position and time information and an artificial satellite passing between 1 and 2, share its operation information, laser direction, and on / off control of emission) <0099><<Attitude direction control, photon irradiation control>> ● The photon irradiation direction and on / off control to 2 may be performed. 1 may be provided with means for changing the emission direction of the photons emitted, emitted, and transmitted by 1 (the attitude control and direction control device of 1, the deflection device of 1), and may be provided with means for suppressing and controlling blurring (for example, 1 equipped on a stabilizer, gimbal, or pan-tilt), and the control may be performed from 1, 1SSPS, 1CON, or an external network or the Internet. ● 1 may be able to turn the emission of light on and off. For example, 1 may check the operation status, operation schedule, orbit information, and date and time of other artificial satellites and spacecraft through the external Internet from 1CON, 1LINK, etc., and when a spacecraft or the like comes on the radiation line during the photon irradiation from 1 to 2, control to turn off the photon irradiation may be performed. For example, 1 turns the laser on and off under the control of 1CON.<0100><Supplement: Laser Irradiation of Debris>The configuration of the present application (laser irradiation from 1 to 2) may be used for orbit change of space debris 1DBL. For example, when 1 is placed in a certain orbit and a laser is irradiated towards 2 in the stratosphere and the air, as shown by 1DBL in Fig. 10, if the spacecraft exists in the radiation from 1 to 2, the laser is turned off, and when the space debris passes through, it remains on, so that the debris is irradiated by the laser (and if possible, the debris is heated or the orbit of the debris is changed). The laser may be irradiated on the debris using the light emitting unit 1 of the present application. <Example 2><0101><Energy Transport System of SSPS by Fuel Transport>Fig. 3 shows an example of launching a fuel material into space, manufacturing fuel at 1, and transporting it to the ground. <Example 3><0102><Energy Transport System of Lunar SSPS with Reduction of Local Resources and Fuel Transport>. The example in Fig. 4 illustrates the case of reducing metal oxides and oxides on the lunar surface at 1 to obtain metallic silicon, metallic aluminum iron, etc. as 5M (or reduced powdered metal fuel), or as a compound 5MC related thereto, and transporting the metal 5M (or compound 5MC) to the ground. (On the lunar surface, in addition to the metal oxides, if there are oxides such as water, the oxides such as water may be reduced to produce and use reduced substances such as hydrogen as fuel.) Although the example in Fig. 4 has the drawback of consuming lunar metals and terrestrial oxygen in order to remove metal elements from the moon and combine them with terrestrial oxygen, it can deliver the power of space solar power generation to the ground while developing the moon, and may be useful when it is desired to utilize the energy by SSPS on the ground at the initial stage of lunar development. (Note that the oxygen 5O2 generated by oxide reduction on the moon may be used at lunar or space bases, or the 5O2 may be introduced into the earth and used as terrestrial oxygen 4O2.) <0103>As a modification of Fig. 4, silicon oxide may be reduced to obtain a reduced substance 5MC or a silicon compound 5MC, and the silicon compound 5MC may be transported between certain regions on the lunar surface (for example, from 1FUEL-GEN·1CHEM1 to a chemical plant 1CHEM2 in another region on the lunar surface or 1CHEM3 near the dropping means 9 through the pipeline 5PIP). (Note that metallic silicon and crude silicon may be produced by known methods using carbon or metallic magnesium. Also, metallic magnesium may be produced by using magnesium-containing raw materials obtained on the moon and the power of SSPS.) The bases 1CHEM1 and 1CHEM3 may be connected by a pipeline 5PIP of a fluid silicon-based compound 5MC such as silane (gas), silicon tetrachloride, or trichlorosilane (a raw material for crystalline silicon and a liquid). The 5MC of the fluid passing through the 5PIP may be sent under pressure by a pump or the like. <0104>For example, after being transported as a fluid 5MC in the pipeline 5PIP, the 5MC may be converted into metallic silicon 5M at the conversion units 1CHEM1, 1CHEM2, and 1CHEM3 by chemical reactions. For example, from the 5PIP to 1CHEM3, it may be transported as a fluid 5MC, and from 1CHEM3 to the launching device or dropping device 9 and the 5TANKM on the ground, it may be converted into metallic silicon. (Also, when it is acceptable to transport 5MC instead of 5M to the ground, for example, the 5TANKM may be loaded with 5MC instead of 5M such as metallic silicon.)<Example 4><0105>The upper part of Fig. 5 is an explanatory diagram of energy transportation from a system (1SSPS-SYS-QZSS-SEIZA) in which a plurality of SSPS satellites are deployed in a quasi-zenith orbit to the ground, forming a constellation. The lower part of Fig. 5 is an explanatory diagram of energy transportation from a constellation 1SSPS-SYS-ORBIT of SSPS satellites formed in an orbit in space, or a constellation 1SSPS-SYS-GEOS in a geostationary orbit, or a constellation 1SSPS-SYS-MOON or a group 1SSPS-SYS-MOON near the moon to the ground. When energy and power lasers, signal lasers, etc. are sent from 1 connected to the SSPS to 2 in the air (when communicating), there may be a relay satellite 1LINK. ※1LINK may relay not only lasers but also radio waves (also considering the case of relaying radio signals).<0106>1LINK may include relay means for relaying photons such as lasers. For example, it may include a mirror device 1MRR that changes the radiation and orbit of a laser beam by reflection of light, and an optical component part 1OPT (or optical system 1OPT) such as a lens. Also, a relay satellite 1LINK equipped with a light receiving part 2, a light emitting part 1, and means for operating them may be used. ※1LINK and 1OPT correct the light beam of the laser that has reached 1LINK and 1OPT (spread (blurred) by passing through the long distance between 1 and 1LINK) with an optical system 1OTP (such as a lens), converge the light beam with 1OPT, and / or reflect the light beam with 1MRR towards 1LINK, 2, etc., and deliver it to the next relay satellite 1LINK or the light receiving part 2 in the air. ※1MRR is not limited to use in 1LINK. For example, for the solar cells of the SSPS or the sunlight collection part for obtaining sunlight, 1MRR may be a means for delivering sunlight to the sunlight collection part, or a large-area mirror device 1MRR that reflects sunlight to the sunlight collection part may also be used.<0107>In Fig. 5, a diagram showing laser irradiation from a plurality of 1SSPS-SATs on the quasi-zenith orbit to the light receiving part 2 is shown. However, Fig. 5 is one of the conceptual explanatory diagrams, and the constellation 1SSPS-SYS-SEIZA in Fig. 5 is not limited to the description of the space machine group orbiting the quasi-zenith orbit in Fig. 5.● Also, as shown in FIG. 10, not only one but a plurality of constellations 1SSPS-SYS-SEIZA may be used to supply and power the SSPS-derived energy to 3 including 2. SSPS-derived energy may be supplied and powered to 2 and 3 from a plurality of 1 at different orbital and light-emitting part locations (constellations in LEO and constellations in geostationary orbit GEO·QZO, lunar surface, etc.). ● For example, in FIG. 10, three (a plurality) of constellations 1SSPS-SYS-SEIZA in a certain orbit arranged over the airspace of Japan, other countries' oceans, and the high seas are used to supply energy to the aircraft 3 during long-distance transportation or passenger transportation in the intermediate section (such as over the high seas in the ocean). The concept of energy replenishment to the aircraft 3 is described. ※ In the asymmetric figure-eight quasi-zenith orbit, the time that one artificial satellite can stay over Japan is about 7 hours. FIG. 5 may be configured such that the light-receiving part 2 sequentially receives laser irradiation from each of a plurality of 1SSPS-SAT satellite groups approaching the airspace of Japan (the small ring part covering the asymmetric figure-eight over the airspace of Japan). The light-receiving part 2 may look up at the light-emitting parts 1 of the satellite group orbiting QZO arranged in a plurality of small circular parts on the Japanese side of the asymmetric figure-eight of 1SSPS-SYS-QZSSーSEIZA at a quasi-zenith angle, and a configuration in which laser irradiation is performed from the light-emitting part 1 to the light-receiving part 2 may also be used. <0108>● The quasi-zenith satellite system QZSS·positioning device QZSS, which is also 1SSPS-SYS-QZSSーSEIZA, may be used. The 2POSI of the light-receiving part 2 and the positioning device QZSS, which is also 1SSPS-SYS-QZSSーSEIZA, may be used to measure the positional relationship between each 1, the light-receiving part 2, and 2POSI. ● The 2POSI of the light-receiving part 2 and 1SSPS-SYS-QZSSーSEIZA or 1 may perform wireless communication·laser communication, and may transmit and receive position information of 2, 1, etc. and other data necessary for the energy transportation·transportation of the present application through communication such as wireless communication·laser communication. ● When there is position·time information or an artificial satellite passing between 1 and 2, the operation information thereof may be shared, and for example, the direction of the laser and the on / off control of the emission may be performed. The on / off of photon emission may be controlled, and laser communication may be performed between the light-emitting part 1 and the light-receiving part 2. Laser·wireless communication may be performed between the light-receiving part 2 and the light-emitting part 1 (and further between the relay satellite 1LINL).<0109>In the present application, the light receiving unit 2 may be provided with positioning means for facilitating the hitting of the light receiving unit 2 by irradiating it with a laser from the light emitting unit 1, or the laser may be guided from 1 to 2 using the laser relay means 1LINK. (The positioning means may be 2POSI and a positioning system on the space side, such as GNSS, GPS, QZSS, etc., or 1SSPS-SYS-QZSS-SEIZA may be provided with a positioning system such as QZSS. For other positioning, known means may be used.)<0110>In addition, not limited to the quasi-zenith orbit, even in the case of a constellation 1SSPS-SYS-ORBIT of a plurality of 1SSPS-SATs orbiting in a low earth orbit (LEO), the laser irradiation from 1 to 2 (the irradiation of the laser from the light emitting unit 1 of each 1SSPS-SAT to the light receiving unit 2, communication and positioning between the light receiving unit 2 and the light emitting unit 2) can be performed in the same manner as in the case of 1SSPS-SYS-QZSS-SEIZA.) <Example 5><0111>FIGS. 6 and 10 are explanatory diagrams of an aircraft group 3FORM, an formation flight group 3FORM of aircraft that can be powered (constantly) by using an aircraft 3 or a taxi, cargo transportation, and passenger transportation by an aircraft 3 or a flying car 3FCAR. ● 3FORM may be connectable to a ground communication terminal 4CON, an airborne communication terminal 3CON, and a user's terminal 6CON, and may be connectable to the Internet using a communication network with the communication units of the terminals and 3. ● For example, in FIG. 6, a user portable terminal 6 may be provided. ● A user of the user portable terminal 6 may remotely control the humanoid 3FORM, the aircraft 3FCAR shown in FIG. 6, or the 3ROBOT in FIG. 9 (a forestry machine, which may be a tree pruning machine among forestry machines) from a location away from 3 via a communication path such as the Internet. <Example 6><0112>When trying to monitor a person or object to be monitored with a beacon, a wearable device 2TAG, a wireless terminal 2TAG, or an electronic tag 2TAG having an active wireless communication unit, it was necessary to install or replace a battery. Therefore, in FIG. 7(a) of the present application, while searching for 3DRONE and 3 for 2TAG, wireless energy is irradiated from 3DRONE to 2TAG by wireless transmission to charge 2TAG and cause it to perform beacon operation and wireless communication operation, and to search for an attached object 6OBJECT (6OBJECT-TAG-ATTACHED) is disclosed.Use 3 or 3DRONE as a tag scanner 6TAG - SCANNER, let the transport device 3 search for 2TAG, when 3 approaches 2TAG, wirelessly charge 2TAG and make it perform wireless communication and beacon operations to identify the tag. Note that the charging energy may be the energy derived from SSPS using 1, 2, and 3 of this application. (Although 3 or 3DRONE is the transport device 3, it is also the tag scanner 6TAG - SCANNER. When describing without limiting the scope of the invention of this application, the transport device 3 includes, in addition to the aircraft 3, vehicles such as automobiles 3, bicycles 3, self - propelled robots, and flying drones 3.)<0113>Also, a configuration with a sensor mounted on the 2TAG is disclosed in Fig. 7(b). For example, the 2TAG attached to or equipped on a person includes an acceleration sensor and a load sensor. Wireless transmission is performed by 3 or 3DRONE, or the scanner 6TAG - SCANNER to supply power to the 2TAG with a sensor and operate the sensor to collect the acceleration, load, and environmental data of the object while being powered or charged during charging. Fig. 7(b) shows, as an example, attaching a 2TAG with a load sensor as a sensor (2TAG - SENSOR) to the bottom of a reagent bottle such as a highly toxic substance whose weight should be managed to form an object 6OBJECT - TAG - SEN - ATTACHED with the 2TAG attached. When the 2TAG is charged by the wireless transmission of 3 or 3DRONE, the 2TAG operates as a load sensor and a weighing scale, the 2TAG acquires the measured value of the load sensor, and the measured value of the load sensor of the bottle can be transmitted from the 2TAG to the tag scanner 6TAG - SCANNER by means of communication. ● In addition to the weight of the tagged object, if you want to check the inclination (for example, whether a reagent bottle or a drum can tagged on the ground is lying on its side), the 2TAG can be used in combination with a load sensor and an inclination sensor or an acceleration sensor. For example, when a 3DRONE or a robot car 4CAR circulates while charging a 2TAG with a load sensor provided on a reagent bottle or a reagent shelf as a tag scanner in a building where reagents are stored, the charged 2TAG operates as a sensor and transmits the measured value by the load sensor to the 4CAR or 3DRONE, so that the weight information of the tagged reagent bottles in the building can be transmitted to the tag scanner or made viewable from the tag scanner via a communication network to the outside. It can be used for article management and reagent management.<<Example in footwear>> ● Regarding the insole-type wireless tag for monitoring described in Japanese Patent Application Laid-Open No. 2016-073366 (or the use of attaching and wearing two tags to socks, footwear, and footwear), the method and configuration of the wireless power transmission in FIG. 7(b) may also be used. ● As items to be worn, two tags may be attached or provided to insoles, shoes, socks, footwear, underwear, clothing, glasses, HMD, covers, helmets, gloves, watches, bracelets, rings, jewelry, ornaments, mobile terminals, etc., and the method and configuration of the wireless power transmission in FIG. 7(b) may be used. ● The wireless communication slave units (1b, 1a) described in Japanese Patent Application Laid-Open No. 2016-073366. Regarding (without mounting a charging function by walking), a built-in type wireless communication sub-device having a wireless communication and positioning function that can charge the wireless communication sub-devices (1b, 1a) from the SSPS in systems 1, 2, and 3 may be configured. ● It may be charged by a wireless transmission method using a 3DRONE driven by a 3DRONE or an SSPS to operate the sensor unit, wireless communication unit, and beacon of 2TAG. ● When 2TAG is used in the insole of a pedestrian, as described in JP-A-2016-073366, the wireless communication sub-device may measure the weight of a person getting on the insole when standing up, the pressure, load, and weight generated by being stepped on by walking, and the movement and acceleration of the toes as the acceleration of the insole. The pressure distribution of the sole of the foot during walking may be measured, and gait analysis may be performed. The weight may be measured, and the gait may be observed and measured. Information that can be used for personal biological characteristics and health management may be collected using 2TAG. Further, the 2TAG may be equipped with positioning means by receiving signals from GPS, GNSS, QZSS, or other satellites or wireless stations for communication, and the 2TAG may be made to perform position measurement. <0114> The 2TAG-SENSOR may be a device that senses wireless communication and signals from satellites, or a satellite positioning device such as GPS or GNSS, and may also be a device that measures and senses the position. As shown in FIG. 7 of the present application, a tag scanner 6TAG-SCANNER (this may also be a drone 3 or the user's smartphone 6CON) is used to search for a tag. When searching, the tag 2TAG is charged and powered, and stored in the power storage device of the 2TAG. The 2TAG receives signals from a wireless station (which may also be GPS, GNSS, QZSS, or other satellites, aircraft, or ground base stations) using the power stored in the 2TAG, obtains the position and time of the 2TAG, performs positioning by a wireless station or satellite, and transmits the positioning result from the 2TAG to the 6TAG-SCANNER to transmit the position information of the 2TAG. <0115> ● In the present application, when systems 1, 2, and 3 of the present application are added to the system of 2TAG and 6TAG-SCANNER in the sky as shown in FIGS. 6 and 10, it is also an air communication platform that can move to a remote location and stay in the sky without refueling or charging on the ground by the energy of the SSPS. A tag scanner 6TAG-SCANNER and a system of sensor-equipped tags searched by the tag scanner can be configured and can be used for constant monitoring from the sky. When 3 is a drone, it can be used as a patrol device for 2TAG.<0116>● Figures 8 and 6 describe an aircraft group 3FORM that can perform energy sharing through energy sharing means such as a wireless transmission device 3WEP and can perform formation flight and inter-aircraft cooperation. Figure 7 describes monitoring a single 3, but in Figure 7, a group of aircraft capable of energy sharing between aircraft may also be used. For example, a 3 equipped with 2 is arranged in the upper stratosphere, and a tag scanner 6TAG - SCANNER, which is also 3FUEL that can fly in the troposphere or on the ground side with respect to the 3, is periodically connected to perform energy sharing and replenishment through charging and fuel replenishment. <Example 7><0117>Figure 8 is an explanatory diagram of a humanoid robot 3FORM - HUMANOID with a robotic arm in a stationary state and an operating state (during flight or operation of the robotic arm) when an upper body type aircraft 3 and a lower body type aircraft 3 equipped with tools, instruments, and various devices are capable of formation flight and cooperation. The control form of the device in Figure 8 may be manned or unmanned. In the case of unmanned operation, 3CON may be equipped with a communication device for communication with an external wireless station or communication network, or may be equipped with computer-related devices such as a computer processing device, a storage device, and an input / output device. The aircraft 3 may be equipped with a battery or fuel. The aircraft 3 may use the battery or fuel to drive a robotic arm, a motor, an actuator, or a propulsion device. <Example 8><0118>Figure 9 is an explanatory diagram of a configuration in which tools, instruments, various devices, or additive manufacturing devices 3A1 - AM and subtractive manufacturing devices 3A1 - RP are provided on the robotic arms of an aircraft 3 or an aircraft 3 (3ROBOT) to perform additive manufacturing on 4WK - AM of a work target object 4WK and subtractive manufacturing on 4WK - RP. Also, Figure 9 shows an unmanned aircraft 3 or a flying robot 3ROBOT that performs branch cutting and removal, which is a type of subtractive manufacturing, by remote control from a base station (3CON, 4CON, 6CON) to cut and remove the branches of a tree. It is an explanatory diagram of a flying robot 3ROBOT equipped with a robotic arm and a 3A1 - RP that may be a saw, a cutting part, or a grindstone. ● In this application, it is powered by the energy of SSPS and can be accessed by the aircraft 3ROBOT even when the 4WK is in a location where it is difficult to work for a human or a land - moving machine on the side, slope, cliff, etc. of the aircraft 3. (It may also be a high - altitude work device 3ROBOT.)It may also be used for monitoring and working on iron towers, utility poles, and electric wires. ● In FIG. 4, a configuration in which 3 robots access 4WK is described. However, a configuration in which 3FORM composed of 3 robots with the tools of FIG. 3 is driven by the energy of SSPS and works on 4WK may also be used. Among the 3FORMs, the aircraft with reduced energy may be sequentially replaced with a charged machine to continuously perform work. <Example 9><0119>FIG. 12 is disclosed as a reference figure. FIG. 12 is an explanatory diagram of a method for producing hydrogen fuel by introducing water obtained by collecting rainfall and rainwater on the high seas or water supplied from 4H2O on the ground into 3FUEL that may be provided with a light receiving unit 2. (And an explanatory diagram of a method of using water in which rainfall and rainwater are collected by 3FUEL driven by SSPS and delivered to people, animals, and plants on the ground, user 6, and places where there is a need (places to be extinguished).)<0120>The embodiments of the present invention have been described, but these embodiments are presented as examples and are not intended to limit the scope of the invention. These novel embodiments can be implemented in various other forms, and various omissions, replacements, and changes can be made without departing from the gist of the invention. (※ This application is based on an invention application. It has not been verified at the time of application.)<Industrial Applicability><0121>It may be used for power transmission and energy transportation from the light emitting unit 1, which is also a space solar power plant, to the ground, including the aircraft 3, high altitude platform 3, and light receiving unit 2. Not limited to the use of space solar power generation, it can be used when transmitting power generated in space or on the lunar surface to the ground of the Earth with an atmosphere. <0122>If an aircraft, electric aircraft, or hot air balloon can be driven by energy derived from SSPS, the refueling and charging steps on the ground will become unnecessary, the flight duration will increase, and it may become an aircraft, airplane, airship, passenger aircraft (or a facility like a hotel in the air) capable of long-distance travel. <Explanation of Signs><0123><<Energy Transportation from SSPS by Short-Wavelength Photons to the Ground>><Light Emitting Unit 1, SSPS Section>1: Light emitting unit, transmitting unit (laser transmitting unit, laser emitting unit, photon emitting unit. It may also include a radio wave transmitting unit.). 1PP: Power plant, power plant. (In addition to a solar power plant, it may also be a thermal power or chemical energy utilization type power plant, a large-scale battery, or a nuclear power related power plant.)1PV: Solar cell (※1PV may be 1PV launched from the ground, or 1PV manufactured from raw materials sourced from celestial bodies such as the moon, and manufactured near the place of use using the on-site vacuum in space for the said raw materials.). 1PCL: Energy conversion means and solar energy collection part other than solar cells. 1LASER - GEN: Device part that converts the electric power and energy obtained by 1PV or 1PCL into laser light (laser generation means such as ultraviolet lasers and synchrotron radiation light generation devices by particle accelerators, light emission means, energy transmission means). 1CON: Communication part of 1. It may also be a control part. It includes SSPS and other parts necessary for transporting the energy of SSPS to the ground. 1FUEL―GEN: Part that synthesizes fuel substances using the energy obtained by SSPS. 1SSPS: SSPS, space solar power station. 1SSPS - ETC: Other series of systems and component groups related to 1SSPS. 1SSPS - SYS: Series of systems of the space solar power station. (1SSPS - SYS - QZSS: SSPS that is also QZSS (QZSS: Quasi - Zenith Satellite System). 1SSPS - SYS - GEOS: Space solar power generation system in the geostationary orbit (GEO). 1SSPS - SYS - MOON: SSPS on the lunar surface or near - lunar space in the lunar orbit (or space solar power generation systems on satellites like the moon or other planets). 1SSPS - SYS - QZSS - SEIZA: Group of artificial satellites, artificial satellite constellation of 1SSPS - SYS. 1SSPS - SYS - QZSS - SEIZA: Group of artificial satellites, artificial satellite constellation of 1SSPS - SYS - QZSS operating in QZSS.) <QZSS constellation> Although mentioned in Figure 5 etc. of Patent Document 1, 1 in this application may also be in the form of QZSS. A plurality of 1 and 1SSPS - SYS may be arranged in the quasi - zenith orbit of QZSS (when arranged over Japan, an asymmetric figure - eight orbit, etc.) and used as shown in Figure 5.<Constellation in Low Earth Orbit (LEO), etc.> (For example, provided by SpaceX or OneWeb,) in a Low Earth Orbit (LEO) satellite constellation, the satellites constituting the Low Earth Orbit (LEO) satellite constellation are SSPS satellites 1SSPS-SAT. The satellite formation can be arranged so that the artificial satellite 1SSPS-SAT always comes close to 2 as seen from a certain point on the ground, the light-receiving part 2. The artificial satellite group can be allowed to flow in orbit to operate the constellation 1SSPS-SYS-SEIZA. The configuration of 1SSPS-SYS-SEIZA (1SSPS-SYS-LEO-SEIZA) in this LEO can place the SSPS satellite and the light-emitting part 1 on the low orbit side closer to the ground than the quasi-zenith orbit or the geostationary orbit, and can reduce the length of the distance (in outer space) when emitting photons from 1 to 2 and hitting the target. ※ The case where an artificial satellite group forms a constellation while moving with a speed in a low orbit or a medium orbit can also be applied to the SSPS constellation. For example, a group of multiple (dozens to tens of thousands are also acceptable) SSPS satellites can be formed in a low orbit at an altitude of 300 km to 500 km or 1100 km (the satellite formation can be arranged so that the satellites always come close as seen from a certain point on the ground, the light-receiving part 2, and the artificial satellite group can be allowed to flow in orbit), and they can be used as the relay satellite 1LINK or used as 1SSPS-SYS-SEIZA to irradiate the energy of the light-emitting part 1 by SSPS to the light-receiving part 2. ● The 1SSPS-SYS-SEIZA of this application is a solar power satellite and an energy transmission satellite, but it can further provide an artificial satellite communication network and communication services by satellite constellation, or can also provide communication services between the ground and the satellite. (Communication, laser communication, and energy transmission can be carried out between SSPS satellites, between the light-emitting part 1 and the light-receiving part 2 of SSPS.) 1LINK: Relay satellite, relay aircraft, relay means for energy and signal from SSPS to the light-receiving part 2. 1LINK may be equipped with a mirror for photon reflection, relay, and transmission. For example, an ultraviolet mirror using aluminum is assumed. 1HNU: Photons irradiated, emitted, oscillated, and transmitted from 1, a group of photons that reach while dropping and passing through the air with a lower air density, oxygen, and nitrogen density than the ground, such as the stratosphere and the troposphere, from the light-emitting part 1 to the light-receiving part 2 (1HNU may be able to turn on and off its generation at 1).By turning on and off the generation and emission of 1HNU, laser communication and optical communication may be performed in the part from 1 to 2 by the laser. ) 1HNU-EXT: Photons that do not reach the ground or are attenuated. Photons having characteristics and wavelengths that are absorbed by the atmosphere. Short-wavelength laser photons emitted by 1 that are absorbed and attenuated by reactions or the like in the atmosphere when the laser is directed outside the receiving unit 2 (ground direction) due to misalignment of the transmitting unit 1 or the like, and photons that are absorbed before reaching the ground. LEO: Low Earth Orbit. GEO: Geostationary Orbit. QZO: Quasi-Zenith Orbit. <Figure 10, Satellite Output, Laser Focus, and Ground Safety> ● In the configuration of the present application, the laser is attenuated by the atmosphere, and the laser can be configured to be irradiated by n (a plurality of) 1SSPS-SATs or 1SSPSs with respect to one receiving unit 2. By using the plurality of units, the output of the n 1SSPS-SATs with respect to the receiving unit 2 can be reduced and dispersed from X watts in the case of one unit to X / n watts, the energy of the laser emitted by each 1SSPS-SAT can be reduced, the output of the energy irradiated to the ground can be decreased, and the safety of people on the ground can be protected. (Regarding the light emitting unit 1 of the present application. Instead of the light-emitting unit 1 of a single SSPS satellite, a plurality of SSPS satellites equipped with the light-emitting unit 1 are flown in formation to form a constellation. By irradiating the light-receiving unit 2 with a laser while dispersing the light-emitting unit 1 among a plurality of satellites, the energy of the laser per satellite can be reduced for operation. For example, there is a 1SSPS-SAT-LOWP with a low laser output that can be generated (specifically, a small amount of ultraviolet photons), and n units of it are placed in a quasi-zenith orbit or LEO to form a 1SSPS-SYS-SEIZA. When irradiating the light-receiving unit 2 with energy from n units of 1SSPS-SAT-LOWP, if all the lasers of the units can be received by 2 or FCS-2, n×X watts (nX watts) can be received at the point of FCS-2. On the other hand, at a point deviated from the focus FCS-2, the laser energy travels straight along the trajectory FHNU-EXT and is attenuated and diverged by the atmosphere. The output of the laser photons on the trajectory FHNU-EXT that deviates from FCS-2 and tries to reach the ground through the stratosphere and troposphere is less than X watts, which is lower than the nX watts of the focus FCS-2. Thus, the energy density can be reduced at locations other than the focus FCS-2. (Also, at the focus FCS-2 above the stratosphere and troposphere, the air density is low, and there is little atmosphere, oxygen, and ozone, so photons are not absorbed, and a photon convergence point can be formed at the focus FCS-2. However, when setting the focus FCS-2 at a location with a high air density near the ground and irradiating photons from 1, it is expected that the photons will be attenuated by the atmosphere before reaching the focus FCS-2.) ● As a result, at the ground part deviated from the focus FCS-2, the element that the laser is attenuated by the atmosphere and the element that the output of a single laser can be reduced and dispersed to 1 / n of the total laser output X of the constellation can be combined to ensure ground safety with the two elements. (In this application, in addition to being attenuated by the atmosphere, the constellation is formed to disperse the laser output to each unit to weaken the laser directed towards the ground.)) ● Arrange multiple satellites (which may be small or medium-sized) in a constellation in a quasi-zenith orbit, a low orbit, etc. When the satellite with the light-emitting unit 1 being Y watts approaches the light-receiving unit 2, lasers are emitted from a plurality of adjacent satellites, n satellites, from the light-emitting unit 1 to the light-receiving unit 2, and by receiving them at the light-receiving unit 2, electric power of nY watts can be obtained. Even if photons that cannot be received and try to go towards the ground are generated, their output is limited to Y watts, which may be useful for reducing the output of photons that go towards the ground due to poor aiming and ensuring ground safety. ※ When preparing n satellites equipped with a light-emitting unit 2 with a low output (X watts), compared to aiming at 2 with a single high-output laser of nX watts, the amount of energy when not hitting 2 and going towards the ground can be reduced, which may be safer. ※ In an SSPS satellite or a lunar base equipped with SSPS, etc., as the single laser output (output of one laser) of the light-emitting unit 1 increases, it may give a sense of uneasiness to people on the ground. Therefore, for laser output dispersion, a plurality of light-emitting units 1 may be arranged so that the energy density per light beam of one laser does not become too high. Considering the above, the device of the present application may also be configured to irradiate a light-receiving unit 2 in the sky with a laser using a plurality of light-emitting units 1. ※ Fig. 10 discloses the trajectory of the laser when it is emitted when it is deviated from the position of the light-receiving unit 2 or when there is no light-receiving unit 2. Fig. 10 describes the consideration of making it difficult for laser energy to reach the ground. FCS-2: The point that one light-emitting unit 1 should aim at, or the focus of the laser / photon that a plurality of light-emitting units 1 should aim at. FCS-2 may coincide with the point where the light-receiving unit 2 should receive light. In the present application, there is an intention to use the attenuation of ultraviolet lasers in the atmosphere for ensuring ground safety, and FCS-2 may be in the stratosphere. FHNU-EXT: The trajectory that deviates from FCS-2 and tries to go towards the ground through the stratosphere and troposphere. <Light-receiving unit 2, air section>2: The receiving unit, the light-receiving unit (laser receiving unit, laser light-receiving unit), which is mounted on the means for arranging in the air 3, aircraft 3, airship, platform 3. 2 is configured considering the orientation of the light-receiving surface so as to receive one laser. It may include a device for controlling the attitude and changing the direction of the light-receiving unit, and may include a gimbal, a deflection device, a stabilizer, etc.)2REA: Reactor of 2, chemical reactor, photoreactor, thermal reactor, heating furnace, chemical mechanical device (a reactor that causes a chemical reaction by photons having photon energy capable of exciting a semiconductor with a wide bandgap such as a photocatalyst, which can cause a chemical reaction such as heat or ultraviolet rays). 2WEP: Wireless power receiving device related to 2. 2PV: Photoelectric conversion element. 2RANT: Part that converts radio waves and electromagnetic waves into electric power (the part of the wireless power transmission method such as electromagnetic induction method, magnetic field resonance method, electric field coupling method, radio wave reception method, etc., which is the radio wave reception method. Includes antenna, rectifier circuit, rectenna). 2LAND: Receiving part arranged on the ground (mainly the part that receives power from 3WEP) <Aircraft 3, airspace, Figures 2 and 11, etc.> 3: Aircraft, etc., airship, etc. (Means for arranging the receiving part 2 at an altitude where the attenuation of ultraviolet laser of UV-C·B is small, high altitude, stratosphere, etc.). 3EPF-SYS: System of an aircraft that receives the energy derived from the SSPS of the present application by the light receiving part 3 and uses it as electric power, chemical energy, fuel. 3GAB: Gas balloon of 3. 3HAB: Hot air balloon of 3. 3GHAB: Gas hot air balloon of 3, Rogallo balloon. 3TH: Propeller of 3 and its related devices (including the propeller motor, motor, actuator, jet engine of an aircraft, and in addition, rocket propulsion, electric thruster, ion thruster, photon sail, and thruster by the reaction of photon emission and reflection of a spacecraft. It may include the propellant of the propulsion device). 3BATT: Battery of 3 (or battery or fuel for driving 3, 3ETC, 3TH, etc.). 3ETC: Control system, computer system, communication system, power system, electrical wiring system of 3, sensors, instruments, positioning devices, control device of 3HAB, hot air balloon heating device, control device of gas balloon 3GAB, control device of propeller 3TH, etc., other devices and equipment groups for driving 3. 3CON: Control part, communication part of 3 (including communication devices with external devices, external 3, 3FORM). 3SEN: Aviation instruments, sensors, etc. 3WEP: Wireless power transmission means from 3 to external 3, 3FORM, and the ground. 3WIR: Device or wire, power cable, optical repeater connecting 3 including the receiving part 2 and 3FUEL, transmission path of power or energy. 3WIRI: Electrical wiring path, power wiring path, signal wiring path of 3, wires, cables, buses such as optical fibers. 3REA: Reactor of 3. (3REA is a device that performs a chemical reaction. For example, reactions using heat, electricity, or light may be performed.It may be a device that performs a chemical reaction by light, an electrochemical reaction device / electrolysis, or a device that performs a chemical reaction by heat. For example, an electrolysis device, a photocatalyst or a photoreaction device, a reactor by heat, an ammonia synthesis device, various chemical devices, a firing kiln for materials such as ceramics, cement, and lime, a reactor / furnace for ironmaking). Means for transporting reactant and post-reaction substances (such as fuel) in the reactor 2REA of 3RPL:2, a pipeline for chemical substances, a pump, etc. 3VALV:3FUEL A fuel outlet / valve to the fuel tank inside. An aircraft that manufactures fuel using the electric power or energy obtained in 3FUEL:2 and / or an aircraft that transports the manufactured fuel. The fuel may be, for example, a metal such as hydrogen, lithium metal, sodium metal, magnesium metal, calcium metal, aluminum metal, silicon metal, iron, zinc, etc., or carbon, hydrocarbon, or an organic substance. 3FUEL-GEN: The fuel production section of 3FUEL. For example, a device that electrolyzes water by the electric power obtained from SSPS through 1 and 2 to generate hydrogen and oxygen as fuel. Conversely, it may also be a fuel cell / battery that generates electricity using water and oxygen as fuel. ※To express without further limiting the scope of the invention, it is a part that converts the energy (electrical energy, thermal energy, mechanical energy, heat engine energy) obtained by 2 or 3 from 1 via 2 by SSPS into chemical energy / fuel, and an energy converter that may convert (inverse conversion) chemical energy / fuel into electrical energy, thermal energy, mechanical energy, heat engine energy. 3TANK: Cargo hold, tank, fuel tank [3FUEL-TANK: The fuel tank of 3FUEL (it may be a fuel tank for hydrogen gas or a balloon. Also, oxidized metal may be reduced and used as fuel. For example, it may be a metal such as hydrogen, lithium metal, sodium metal, magnesium metal, calcium metal, aluminum metal, silicon metal, iron, zinc, etc., or carbon, hydrocarbon, or an organic substance.)] 3LUGG: The cargo hold of 3. It may carry a battery or fuel for moving 3. It may carry a human who moves 3, 3FORM, etc., and a control device. It may be equipped with a device / control device that moves 3, 3FORM, etc. unmanned. 3LUGG-H2O: A water cargo hold, a device for collecting rainwater, or a water cargo hold. ※The propulsion device 3TH may take in air, atmosphere, gas, or ionized gas from the outside and use it as a propellant.3TH may well use air, atmosphere, gas, water, or fluid as a propellant, and apply the energy of the photons obtained by the light-receiving unit 2 to the propellant to perform jet propulsion, rocket propulsion, propulsion by heating and injecting the propellant, propulsion by accelerating and injecting the propellant using an electric field or magnetic field, electric propulsion, propulsion by injecting the propellant through MHD acceleration, etc., and may inject the propellant for use in propulsion. 3TH may use air, water, hydrogen, liquid hydrogen, or a solid propellant (propulsion by laser ablation). 3TH may well use water, atmosphere, or air as a propellant, and may heat water and atmosphere with a laser (a laser built into 3TH, or photons / laser irradiated from the light-emitting unit 1 and received by the light-receiving unit 2) and use it for propulsion by injecting it from the aircraft 3 and 3TH. Water may be obtained in the form of precipitation, snowfall, hail, rainwater, or atmospheric water vapor that the aircraft 3 moves to receive, as shown in Fig. 12 (Fig. 25 of the present application). It may also be obtained from the ground water source 4H2O. Water may be used as a propellant or for synthesizing hydrogen fuel or hydrogen-containing compounds. ※When 3 is 3FUEL, similar to the 3TANK of 3FUEL, a cargo compartment for loading the substance (water) that is the source of the fuel (hydrogen) may also be used. SWP-ABS-LINE: The upper limit altitude at which photons absorbed and attenuated in the atmosphere reach. (It may include the range of the stratosphere.) TPS-LINE: The troposphere. AIR: Atmosphere. <Ground section> 4: Ground-side energy supply system, ground section. 4VALV: Connection part / valve connected to 3VALV. 4FUEL-TANK: A fuel tank for storing the fuel transported from the 3FUEL-TANK via 4VALV and 3VALV. After transporting the energy derived from SSPS received by the light-receiving unit 2 to the ground using a transport means such as 3, it is stored in a tank. A pipeline may also be used. The storage location and flow path of the fuel, and the flow path to the user. <User section> 6: User section. The user section that consumes energy. The part that consumes the fuel transported and delivered from the 4FUEL-TANK to 6 to consume energy. (Or the user section that consumes the energy derived from SSPS.) <Others> 12: Cable (may include a power cable. It may also be a cable / path that guides electricity in the form of light.) (May include the conductor element 1 and 1WIRE.) 14: The base part of the cable, which may be connected to 1100. 17: The connection part to 3 (may also be the connection part 17 described in Patent Document 2). 1100: Power grid.<Figure 3, Diagram of Hydrogen and Metal Fuel Production by Launching> 1VALV: Connection port for connecting tank 5TANK that fills with water or hydrogen when hydrogen is produced from water using the power obtained at 1. 1FUEL-GEN: Fuel production section and chemical reaction section of 1. 5VALV: Connection port of 5 tanks. 5TANK: Tank (tank that fills with water / hydrogen, oxidized metal / reduced metal, raw material of fuel / manufactured fuel). 5TANK1: Tank filled with raw material of fuel (example: water, metal oxide, carbon dioxide). 5TANK2: Tank that is connected to 1VALV and is manufacturing and filling fuel using the power or energy of SSPS (example: producing hydrogen and oxygen from water, producing metal and oxygen from metal oxide, producing hydrocarbon). 5TANK3: Tank filled with fuel and dropped from SSPS towards the ground (example: tank filled with hydrogen / hydrogen and oxygen, tank filled with metal / metal and oxygen, carbon / hydrocarbon filled with carbon / hydrocarbon and oxygen). 9: Launching means. Or a launcher that launches from the moon and drops towards the earth, planet, satellite, celestial body, and space. The following means. <Figure 4, Metal and fuel production by reduction of metal oxides on the lunar surface> ※ The configuration of Figure 4 is a process of removing metal elements from the moon and combining them with oxygen on Earth, so it is not a sustainable cycle as it disrupts the lunar mass balance. However, in the short term (during the development of space exploration), it does not emit carbon dioxide, (it does not require launching terrestrial water and oxides, and can directly drop the resources on the moon onto Earth), and it is a method that enables the use of power generated by space solar power near the moon on Earth (using substances as fuel), so it is disclosed. (The following 5O2 can be used for oxygen for residence, migration, and stay on the moon and other celestial bodies, as well as for terraforming. Not limited to the moon, oxygen for residence can be produced by SSPS power in satellites and planets containing metal oxides.) 5MM: Mines, extraction sources, and collection sources of lunar resources such as metal oxides. It may include a series of means from resource collection, sorting, separation, purification, and transportation to fuel 5M production. 5MOX: Raw materials for fuels that can be made into fuels by the energy of SSPS for metal oxides and the like mined and collected on the moon (metal oxides such as silicon oxide or aluminum oxide). To describe without limiting the scope of the invention, substances, objects, and devices that can be procured in the local space of the universe (the moon, satellites, the asteroid belt, small celestial bodies such as meteorites and comets floating in space, celestial bodies) where the energy of SSPS can be stored. 1FUEL‐GEN: The fuel production section and chemical reaction section of 1. Substances storing fuel or chemical energy may be produced using the power and energy of 5MOX and 1SSPS. 1CHEM: The chemical reaction section of 1. The chemical plant of 1. 1CHEM1, 1CHEM2, 1CHEM3 (including devices and reaction sections capable of chemical reactions by thermal energy, electrolysis, etc. For example, in addition to the production of 5M, it may also be the part where substances are chemically reacted by chemical or thermal energy to produce products such as cement and other earth and stone products at the lunar base). 5O2: The storage destination of oxygen generated by reducing metal oxides, pipelines, etc. The oxygen-related section. 5M: Metals derived from lunar resources produced by 1FUEL‐GEN, the power of 1 SSPS, and 5MOX (metals that can be oxidized by oxygen and generate oxidation-reduction energy). 5M may be, for example, powdered metal silicon, metal aluminum, or iron powder. Combustible powdered metal silicon or aluminum may also be used. 5MC: Substances that can combine with lunar resources and oxygen obtained by SSPS. (For example, fluids such as silane and trichlorosilane.※ Although it requires careful handling compared to metal silicon, it has the potential to be transported by pipeline as a fluid for 5MC. ) 5TANKM: A transport container for the Earth and the ground filled with 5M and 5MC. A drop container and a fuel drop pod. 4O2, 6O2: An oxygen source on the ground or on the user side. Used by user 6 to oxidize 5M. For example, when obtaining metal oxides on the moon, storing oxygen out of the metal and oxygen produced there on the moon and dropping the metal to the Earth to react with oxygen, the oxygen on the Earth decreases as it combines with the metal. Therefore, it may be preferable to drop both the oxygen and the metal synthesized on the moon onto the ground. 6: A user who consumes fuel and oxygen and utilizes energy. <Examples in SSPS in the quasi-zenith orbit, the moon, and the geostationary orbit in FIG. 5> 1SSPS-SAT: An artificial satellite for SSPS including 1. 1SSPS-SYS: The system of SSPS. (-SEIZA: A 1SSPS group formed and configured by artificial satellites for SSPS including 1, a constellation of artificial satellites. -QZSS-SEIZA: A 1SSPS group in the quasi-zenith orbit, a constellation. -ORBIT: A 1SSPS group in orbit, a constellation. -GEOS: A 1SSPS group in the geostationary orbit, a constellation. -MOON: A 1SSPS group in the orbit near the moon or on the lunar surface.) 1LINK: A relay satellite. It relays between the light-emitting part 1 and the light-receiving part 2 of 1SSPS. A satellite or device that relays photons trying to pass between the light-emitting part 1 and the light-receiving part 2. ※ For example, a mirror 1MRR that reflects a laser or photons, and a satellite equipped with an attitude control device for changing the direction of the mirror. When sending photons from 1 to 2 by laser from a distant place such as the geostationary orbit or the moon to the Earth, it prevents the lack of accuracy and the diffusion of the laser light generated from 1. It may be provided with an optical component 1OPT such as a lens for focusing light. When the laser beam diverges before reaching the relay satellite 1LINK from 1 of 1SSPS, the diverged laser can be optically corrected (or adjusted) to a laser that converges again by the lens of 1OPT of 1LINK. ※ For example, 1LINK including the light-receiving part 2 and the light-emitting part 1 of the laser. The diffusion of the laser beam is recovered as the energy of the laser light by the photoelectric conversion device and the light-receiving part 2 of the relay satellite 1LINK due to the increase in the distance the laser travels, and power is obtained, and photons are emitted again to the light-receiving part 2 of 3 in the air or other 1LINK using the power.Once convert the light beam that has spread and reached using 2 and 1 of 1LINK into electric power, emit it again as laser light that has not spread after re-emitting. 1MMR: A mirror or device capable of reflecting photons. (Example: A mirror for sunlight reflection and collection, an aluminum mirror for ultraviolet laser reflection) It may be mounted on 1LINK. ※ For example, reflect the photons irradiated from 1 and change the orbit and radiation of the photons. 1OPT: An optical system, optical component, or means for correcting light. It may be mounted on 1LINK. ※ For example, when the light beam spreads (or diffuses and blurs) when the photons irradiated from 1 pass through a long distance, converge the light beam again using an optical system. 2: Light receiving unit. 3: Aircraft. 3FUEL: Fuel synthesis aircraft, fuel transport aircraft. 4: Ground part. 6: User part. <Example of using the energy from 2 to 3 for driving 3 or services by 3> 3FCAR: Airplane, flying car. It may also be an emergency vehicle or emergency transport equipment. 3ROBOT: Flying robot. It may be equipped with a robotic arm with tools and may be in the form of a humanoid robot. ※ It may be made to perform work on 3FCAR or 3FORM robot. For example, forestry work may be performed by 3 or 3FCAR or a robot by 3FORM, and a device or means for pruning (a device for cutting branches, an attitude control device and propulsion device for changing the attitude and position of the aircraft with respect to the tree and each branch, a pruning device, pruning means) may be provided to make 3FCAR or 3FORM robot perform pruning. (3ROBOT may be made to perform the work that can be done in the system of the present application aircraft among various operations such as agriculture, forestry, and fishery.) ※ The aircraft 3 and 3FCAR may be used for object delivery or recovery purposes. (Example: Mail, fuel delivery, object delivery, e-commerce, resource recovery, water delivery, transportation and dropping of fire extinguishers) ※ The aircraft 3 and 3FCAR may be a transport device or may be an aircraft that also serves as a hotel or residential use or a residential part (or an airplane-type camper 3FCAR, a residential-type aircraft). <Example of using the energy from 2 to 3 for 2TAG> 2: Receiving unit. 2WEP: Wireless power receiving device and communication device related to 2. ※ Or the tag 2TAG performs wireless power transmission, communication, etc. with the tag scanner 6TAG-SCANNER and is used for monitoring and managing tagged objects, including a power transmission and communication unit and a power supply unit for the tag. 2RANT: Part for converting radio waves and electromagnetic waves into electric power.It may be included in 2WEP (the part of the wireless power transmission method of the radio wave reception method among wireless power transmission methods such as the electromagnetic induction method, the magnetic field resonance method, the electric field coupling method, and the radio wave reception method. It includes an antenna, a rectifier circuit, and a rectenna). 2TAG: A tag equipped with a receiving unit 2. It is a tag mainly used for monitoring objects, luggage, children, and the elderly, and has a part for receiving power from 3WEP. It obtains power by wireless power supply from 3WEP and performs wireless communication, beacon operation, sensing, and positioning. A wireless tag-beacon device that operates by obtaining power through wireless power transmission. 2TAG may have the functions of a computer and may be equipped with a processing device, a storage device, an input / output device, and a communication device. 2TAG-CAP: The part that stores the power obtained by the wireless power supply of 2TAG. 2TAG-SENSOR: A sensor attached to 2TAG (when measuring the acceleration of an object to which 2TAG is attached using 2TAG, it is an acceleration sensor; when measuring weight / load, it is a load sensor; when measuring temperature, it is a temperature sensor; when measuring altitude, it is an altimeter; when measuring magnetism, it is a magnetic sensor; when detecting smoke or fire, it is a dedicated fire sensor. When the aircraft 3 approaches close to 2TAG-TAG and wireless power transmission becomes possible and 2TAG-CAP is charged, the sensor is driven by the charging power. The positioning of 2TAG and time acquisition may be performed by a positioning system such as the aircraft 3 or a guidance, or by a radio wave signal from 1SSPS-SYS-QZSS - SEIZA). 2TAG-IN: The input device of the 2-tag. It includes the sensor 2TAG-SENSOR. 2TAG-OUT: The output device of the 2-tag. For example, when searching for a 2-tag attached to an object, the 2-tag may be equipped with a sound-emitting device as 2TAG-OUT, and the 2-tag may make a sound in response to the communication result by the communication device or the request of the processing unit controlled by the program in the processing device and the storage device. For example, when the 2-tag is charged simply by a tag scanner, the sound-emitting device may be sounded to notify the presence of the tag to the tag scanner or the person accompanying the tag scanner by sound. 2PATCH: A patch that may be a plaster. It may be a cloth, bandage, or film that can also be a tag. It may also be an attachment type or a sewn-on type patch for clothes and underwear. ※ It may be a plaster / patch for dementia treatment drugs, a patch for smoking cessation drugs, a plaster / tape for poultices, a patch that can also be a bandage for children, or a patch that can be attached to personal clothing and small items.※ To prevent diseases such as malaria from being bitten by mosquitoes, etc., an insect repellent patch that can be attached to clothes and has a function of releasing components that insects dislike and insecticidal components may be used. A patch for clothing insect repellent may also be used. 2TAG-PATCH: 2TAG equipped with 2PATCH. Or 2TAG that can be attached to or attached to and separated from 2PATCH. ※ 2TAG, 2PATCH, and 2TAG-PATCH are provided with parts or layers that function as tags, plasters, cloths for sticking, or films / tapes. For example, the support 2TAG-SP and the adhesive layer 2TAG-ADH of 2TAG. ※ For example, 2PATCH may be a film or tape support coated and laminated with an adhesive for sticking to an object and a drug-containing adhesive layer (paste) containing a drug. (As an example of 2PATCH, rivastigmine tape, a poultice for cataplasm / tape agent.) 2PATCH may also be a band-aid or bandage. ※ For example, 2PATCH may be a patch that does not contain drugs or pharmaceuticals, or a tape / film / patch containing an adhesive layer 2PATCH-ADH and a support 2PATCH-SP. (In the case of a pharmaceutical patch type tag 2TAG-PATCH, there is an advantage that the attachment of the tag can be confirmed, reattached, or replaced with a new tag when applying the plaster.) 6OBJECT-TAG-ATTACHED: An object to which 2TAG or 2TAG-PATCH is attached or worn. A person, animal, plant, or object to which a patch is attached. An object or article managed by a tag. ※ Examples of objects: Swords, firearms, weapons that need to be managed, drugs such as alcohol, medicine, and medical supplies, highly poisonous substances, goods, luggage, bags, identity cards, keys, car keys, cars and transportation equipment, buildings and furniture, important documents, antiques, treasures, precious metals, jewelry, ornaments, computers, watches, devices, clothing, underwear, footwear, humans, animals, plants, and living organisms. 6TAG-SCANNER: A part that wirelessly powers 2TAG or 2TAG-PATCH or receives the wireless communication signals or beacons emitted by 2TAG or 2TAG-PATCH and notifies the user that there is a tag. A tag scanner. ※ 6TAG-SCANNER may include, for example, an aircraft 3 equipped with a tag scanner, 3CON, a drone 3DRONE, a 4CON ground base station, 6CON, a 6-user station, 6SMART-PHONE, a 6HANDY-TAG-SCANNER, a tag scanner installed in a car or transportation equipment, etc.3. 3DRONE: It can be a tag scanner, perform tag search unmanned, conduct wireless power transmission and charging to the ground or in the air at the search destination during flight, and if there is a charged tag during that time, receive responses such as the beacon or communication of the tag, and may be a drone, aircraft, transportation equipment, or vehicle that can search for tags. ※3DRONE may wirelessly transmit power from 3WEP to the tag while flying and approaching the tag to search for it. Communication between the tag and the drone is allowed. 6TAG - MONITORING - USE: Tags are... Explanation section for the use in monitoring. (a) of FIG. 7. 6 OBJECT-TAG-SEN-ATTACHED: An object with 2 tags attached with sensors, 2 TAG-PATCHES attached. (Also an explanation section for the use of the tags on the measurement sensors of the tagged object.) ※ For example, attach and mount 2 tags with sensors and 2 TAG-PATCHES on the bottom of a storage bottle of highly toxic substances that need to monitor the amount used in a laboratory. When the bottle is placed, the force (bottle mass m × gravitational acceleration g) that the bottle presses with its weight through the load sensor of the tag is detected as the bottle weight. A system that reagent manages the change in bottle weight as the amount of highly toxic reagent used as the amount of reagent change. The driving power of the tag is by wireless power transmission. (b) of FIG. 7. <FIG. 8, Examples of 3FORM> ※ FIG. 8 shows examples of using the 3FORM of the present application for entertainment or work. ※ (a) and (b) of FIG. 8 are examples where two airplanes with robot arms, robot legs, and the torso, limbs, head, spine, and tail of a person or animal cooperate and fly in formation. The robot arm may operate, grasp, hold, etc. devices, tools, and instruments for removal processing and additive manufacturing such as 3A1-RP and 3A1-AM in FIG. 9 with a robot hand, or may be equipped with the tools and instruments, etc. The formation of airplanes (3A1, 3A2, 3L1, 3L2 in FIG. 8) may be equipped with robot hands. (b) of FIG. 8 is an example of using an aircraft like U.S. Patent Publication No. 20140231590 for a show. In FIG. 8, it may fly in formation like a humanoid robot (an operating humanoid device). ※ When 3FORM is in the stratosphere and propulsion by a jet engine or propeller is difficult, an electric propulsion device using photons, particles, or charged particles such as a photon sail or ion thruster, or a rocket thruster is required. <FIG. 9> FIG. 9 is an explanatory diagram of attaching a robot arm 3A1 to 3, which may be charged by the light receiving part 2 or driven by fuel manufactured by 2, and performing removal processing and additive manufacturing like 3A1-RP and 3A1-AM. 3A1-RP: Device for removal processing, robot arm. 3A1-AM: Device for additive manufacturing, robot arm. 4WK: Work object, part, product, object. 4WK-AM: Target part, laminated part for additive manufacturing, film formation, and lamination of 4WK. 4WK-RP: Target part for cutting, removal, cutting, and polishing of 4WK.※Note that assuming the use of 3ROBOT in forestry, 4WK is the tree to be pruned, 4WK-AM is the chemical solution such as pine sawyer control agent, paint agent, seeds, etc. added to the work target, and 4WK-RP is the object removed from the work target such as the branches to be pruned of the tree for pruning. <Figure 10> FCS-2: One or more foci to be targeted by 1. FCS-2 may coincide with the point where the light of the light receiving unit 2 should receive. In this application, there is an intention to use the attenuation of the laser in the ultraviolet region in the atmosphere for ensuring ground safety, and FCS-2 may be in the stratosphere. FHNU-EXT: The trajectory that deviates from FCS-2 and heads towards the ground through the stratosphere and troposphere. ※In Figure 10, as an example, there is a description diagram of the aircraft 3 moving without descending to the ground by the energy received from the light emitting unit 1 of SSPS using the light receiving unit 2 from Japan to Uruguay (the back side of the earth as seen from Japan, the distance of half the earth's circumference). (In Figure 10, it may be the case of traveling from Japan to Uruguay using 3, and 3 may receive photons from the light emitting unit 1 to the light receiving unit 2 and be replenished with energy over the high seas on the route between Japan and Uruguay or over the high seas far from New York, etc.) 1DBL: Space debris orbiting in the (atmosphere-free object such as the atmosphere that attenuates photons) space. ※In space, it is possible to converge the laser without attenuation with 1DBL as the focus. (The laser can be irradiated to 1DBL in FCS-2 formed by multiple 1s) <Figure 11, Description diagram of aircraft 3> 2: Light receiving unit. 2POSI: The part of the positioning device or positioning device for irradiating photons / laser from 1 to 2 and hitting. <Electricity, Power, Signal System> 2PCE: Photoelectric conversion device. 3ETC: The parts necessary for the operation of 3 such as electricity, power, computer, various circuits, communication part, etc. 3WIR: The part for exchanging power and photons with the outside. 3REA: The reactor of 3 (It may also be a device that inputs power and operates an electric furnace or an electrolysis operation). 3WIRI: Circuit, wiring. 3BATT: Battery. 3LUGG: Cargo hold. 3SEN: Sensor. Measuring device. Instruments. 3TH: Propulsion device, propulsion means. 3B: Balloon, floating device, floating means, floating up device, floating up means. 3HAB: Hot air balloon. The hot air balloon gas of 3HAB may be heated by the energy of the light receiving unit 2. 3GAB: Gas balloon. 3WEP: Wireless transmission means with the outside. 3CON: Communication part and control part with the outside. <Fuel, Chemical Substance System> 2REA: Device that causes a reaction by photons.(Photoreaction, thermal reaction,) 3RPL: Pipelines, pipes, and tanks for fuel-related substances. 3VALV: Fuel connection valve to the outside. 3REA: Reactor of 3. 3EPF-SYS: System of an aircraft that receives the energy derived from the SSPS of the present application at the light-receiving unit 3 and uses it as electrical / electric power or chemical energy / fuel. ※Figure 11 is an explanatory diagram of an aircraft 3 that may have a form of an aircraft having a propulsion device, motor, actuator, propeller, fixed wing, rotary wing, hot air balloon 3HAB, and gas balloon 3GAB driven by the SSPS. ※It is possible to deliver the energy derived from the SSPS to the aircraft 3 including 2 regardless of day or night, and it is possible to transfer the energy from 3 including 2 to other aircraft 3, 3FUEL, or 3FORM, or share the energy with them. <Reference diagram, Figure 12> 3LUGG-H2O: Cargo hold for water. It may receive and collect rainfall and use it as water. (Considering the impact on the environment.) 3H2O-LINE: Pipelines, tanks, and flow paths for water. 3H2O-VALV: Valve and nozzle for taking water out to the outside. 4H2O: Water supply section on the ground (mainly assumed water supply sources: including rivers, dams, and ponds) 6LIFE: Organisms that require watering or water supply (delivering water to humans, animals, plants, organisms, deserts, etc.) 6: User section. Houses, factories, towns, etc. that require water. 6FIRE: Fire source. (Extinguish by pouring water) ※Figure 12 discloses the possibility that 3 operates as a constantly water-supplying aircraft by the energy from the SSPS, supplies water from the outside of 3 to the inside of 3, and supplies water from the inside of 3 to consumers through the valve. It may be an emergency water supply device 3 or a water supply transportation device 3. The aircraft 3 and the transportation device 3 may obtain the water from rainwater or the ground water resource 4H2O. The water may be used as a propellant to be ejected from the propulsion device 3TH of the transportation machine 3 (aircraft 3, placement means 3, cage part 15 of the orbital elevator, space fountain, transporter, aerial structure 2, launching device, launch vehicle, vehicle 3 for launching from the ground to space, etc.). The water may go through processes such as heating, chemical reaction, filtration, and sterilization by the energy obtained from the light-receiving unit 2, and may be used for the injection propulsion operation of the propellant, fuel generation, cooling of the aircraft device and the light-receiving unit 2, generation of drinking water, etc. (4H2O includes water tanks, ponds, rivers, etc.)In the case where seawater can be converted into fresh water or for applications where seawater is acceptable, seawater is also included) ※ In particular, rainwater does not contain salts that need to be separated by membrane separation or the like like seawater (it is already separated from salts in the natural circulation), and it falls on land and over the ocean. Rain and snow that are not saltwater pour from rain clouds over the sea onto the sea surface. Therefore, the present application discloses obtaining rainwater, rainfall, and snowfall in the sky even over the open ocean by an aircraft 3 equipped with 2 with an extended operating time by the energy of SSPS, storing it in 3, and supplying it to the demand area 6. ※ With the configuration of Fig. 12, a filter membrane, a filtration tank, a sterilization means using ozone or chemicals, and a means for removing harmful substances are provided in 3 and the water flow path 3H2O-LINE to constitute a water purifier and a water purification section, and it may be used as a water supply aircraft 3. ※ Fig. 12 relates to the use of 3FUEL for collecting rainwater and 3FUEL carrying water. As a method of collecting rainfall and snowfall to obtain water and decomposing the water with the energy of SSPS to obtain hydrogen, on the lower right side of Fig. 11, for example, clouds, rain and rainfall falling from the clouds, and an aircraft 3 equipped with 3LUGG for collecting rainfall, 3FUEL are shown. <0124><O2, O, oxygen atoms>The present application discloses the use of the atmosphere, oxygen, and oxygen atoms on the ground in the sub-concepts of the claims. For example, the use of photons attenuated by oxygen and ozone in the atmosphere, and further in a system using oxygen as an oxidant, synthesizing fuel from which oxygen atoms have been removed by reducing lunar oxides, producing hydrogen and oxygen with the light-receiving section 2 in the air and the aircraft 3FUEL, and the use of the fuel and the oxygen atoms by the user 6 are disclosed. <0125><Method of transporting energy from space to the earth>In the superordinate concept of the claims of the present application, it is not limited to the use of space solar power generation. For example, a power plant using elementary particles or nuclear power (a power plant using elementary particles or nuclei such as radioisotopes, nuclear fission, nuclear fusion, antimatter - annihilation, etc.) is provided on the lunar surface, the power of the power plant 1PP is sent to the light-emitting section 1, energy is sent from the light-emitting section 1 to the light-receiving section 2 in the form of photons, and the aircraft 3 may be operated from the light-receiving section 2, or substances on the ground may be oxidized and reduced to synthesize fuel. (When sending from 1 to 2, a relay satellite like 1LINK may be used.) <0126><Space nuclear power generation, space physical battery power generation, space power plant>Where sunlight cannot be obtained, the power obtained by a nuclear-related power plant or a physical battery using elementary particles or nuclear power may be transmitted to the ground using 1, 2, and 3 of the present application.Launch the raw materials of nuclear fuel such as uranium (a mixture of uranium-235 and uranium-238) before enrichment on the ground, enrich the nuclear fuel on-site at a lunar base or the like to obtain nuclear fuel (uranium-235), and use it for nuclear power generation at a lunar nuclear power plant. The electric power generated may be delivered to the ground via 1 to 2. ※ Waste management is required after power generation. <0127>Regarding the monitoring tag, refer to and cite the content of paragraph number 0127 of Japanese Patent Application No. 2023-007722. <Problem> It is desired to provide a wearable tag or beacon for monitoring the elderly or for discovery when a person is missing. Regarding the tag 2TAG, it was unclear whether the elderly would necessarily wear shoe pads, belts, or wearable devices with built-in watch-type tags due to differences in the preferences and conditions of the elderly, as well as differences in their level of interest. It was considered that there may be a tag that can be worn by a monitoring relative as part of administering medicine to the elderly. <Solution> Attach a wireless tag to an adhesive medicine, charge it by wireless power supply, operate a beacon, etc., and search for the tag and the elderly person to whom the tag is attached. During the search, tag power supply and beacon radio wave detection by a drone may be performed. Also proposed is a configuration for tag power supply from a space vehicle such as SSPS, transmission of time information, positioning, and information useful for controlling the tag processing unit between an artificial satellite and the tag, and beacon detection. <Explanation> The tag 2TAG and the tag scanner of the present application are a patch-type wireless tag that combines a patch for administering medicine to a dementia patient and a wireless tag, and the most important feature is that it can perform the administration of adhesive medicine to a dementia patient, attachment of the tag 2TAG, and maintenance of the attached state. 2TAG may be charged by the wireless transmission means of an aircraft 3 that searches for the tag and operate as a beacon or wireless communication. <Wireless Power Supply Method> The present application includes an idea for a passive RFID tag to store power by wireless power supply and generate a wireless signal (beacon signal) from the stored power, and to search for the wireless IC tag and the object to which the tag is attached. ● According to known technology, a 10m-class power supply technology (space transmission type wireless power transmission system) using the 2.4GHz band that can supply power up to 10m away has been proposed. ● Mount the 10m-class power supply technology on an adhesive medicine, etc. equipped with a drone and UHF tag function, make it a patch-type wireless tag 2TAG, and after supplying power to the 2TAG by the wireless power transmission system, use the power obtained by the power supply for generating the beacon signal of the 2TAG and for searching for an object or person whose location is unknown.●[Scenario Example 1]: For example, for an elderly person (or a person such as a child who needs to be watched over, or a person to be searched for) who has got lost in the mountains, stick, include, or equip a plaster or patch with the 2TAG adhered to a position on the back of the person where it is difficult to peel off the patch 1P in advance. When in distress, fly a drone equipped with the 10m-class power supply technology around the mountains. If the 2TAG is within the power supply range of wireless power supply, the 2TAG powers up and operates a communication device, a beacon (or a signal transmitting device and communication device that includes information useful for searching for the object, etc.). The drone and the 2TAG detect the presence of the 2TAG by receiving the signal emitted by the communication device of the 2TAG, with the intention of using it for the search. (Or detect the 2TAG wirelessly and use it for detecting, searching, watching over, guarding, managing the object THG to which the 2TAG should be attached, and management during distribution and transportation.) ● An aircraft such as a drone or a spacecraft such as a satellite may be used for the power supply device and the reading device (tag scanner) for searching for tag 1. Also, an automobile, an electric assist bicycle, or a transportation device having a power source traveling in the street may be equipped with the tag scanner. For example, the drone 3DRONE may be used as the tag scanner. (The drone-type tag 1 scanner is an example, and it may also be searched for by an existing RFID tag handheld scanner or a handheld tag scanner.) For example, in the case of an elderly person, it is expected that the plaster is difficult to remove from the back, but this is just an example. For example, for living things such as dogs, cats, and pets, a tag in a form that can be worn by the living thing such as a collar, and the tag that uses the power obtained by the power supply for beacon generation may also be used. For example, in the case of a child, there is a risk that a person who intends to cause harm such as abduction to the child may transmit a power supply radio wave towards a place where the 2TAG is likely to be, power up the 2TAG, charge it, activate the 2TAG, and operate a beacon or the like to find the child. Therefore, in order to prevent this, communication may be performed during power supply, and only a tag scanner with the qualification to power up the tag 1 may be able to perform operations such as power supply and beacon operation. The 2TAG operates a beacon or the like depending on the conditions for operating the 2TAG and the environment where the 2TAG is placed. Specifically, the 2TAG may be equipped with an authentication means.For example, authentication means such as passwords or PINs, means for setting lock means such as buttons or input parts on the tag side, means for controlling on / off or access to beacon functions, etc., and one-time password authentication means provided in tag 1. <Actual tag 1> For example, in the use of the tag 2TAG of the patch 2PATCH for the elderly, a 2TAG with a password printed thereon, a 2TAG in which the printed password PWD is recorded and stored in the control unit or IC of the 2TAG, and based on that password, as an encryption key for encrypted communication, encrypted communication may be performed between the tag scanner or the terminal connected to the communication path / network destination and the 2TAG. Communication with the 2TAG, operations such as the beacon of the 2TAG, and power supply to the 2TAG may be performed only on the tag scanner in which the PWD is input and stored. The 2TAG may be provided with means for overlapping and attaching, fixing means, or adhesive means on the patch 2PATCH, or means for attaching and detaching like a hook-and-loop fastener between the 2TAG and the patch. <Form of the tag as a medical product> The 2TAG is a patch as a medical product and medical means, but the 2TAG may also be a device used for monitoring while being a medical means, for example, a medical device and medical means for measuring the heart rate with a wristwatch-type device. <Wearable tag> From the perspective of a device worn on the human body, the 2TAG may be wearable such as insoles, shoes, glasses, contact lenses, contact lens-type output devices, devices or apparatuses capable of vision correction, hearing aids, earphones / headphones, and wireless earphones. ● Also, it may be attached to the skin like a decorative seal (bindi) in India. The 2TAG may also be used for decorative seals, patches, and emblems on clothes. ● For example, although wireless earphones have the problem of being small and easy to lose, providing a part that acts as tag 1 claimed in the present application or attaching it may help find the lost wireless earphones in the street or at home. ● When a person searching for the 2TAG included in a lost object searches using vision or hearing, the 2TAG may be provided with a wireless beacon or a beeping, light-emitting, or vibrating beacon as is well known. <Patch of the tag> The patch 2PATCH may be a pharmaceutical product such as rivastigmine or rivastigmine tape. For example, it may be a drug for dilating the bronchus, a drug for dilating the blood vessels of the heart, or a drug to assist in quitting smoking.Examples may include a smoking cessation aid 1P containing nicotine for smoking cessation or a nicotine patch 1P. The patch 1P may be a transdermal absorption type preparation (patch agent 1P). The patch 1P may be a pharmaceutical product such as a wet compress 1P or an analgesic and anti-inflammatory agent 1P. The patch 1P may be a dressing, or may be an adhesive plaster 1P, a bandage 1P, an eye band, etc. 1P. ● Management use of drugs: 2PATCH may contain drugs. It may be attached to a device for handling drugs, etc. ● Use in drugs and items that require management: In the case of drugs that require a medical prescription or containers of highly toxic substances that are locked and managed in a laboratory such as a university, a method for searching, managing, and guarding lost items using beacons, etc. claimed by 2TAG may also be used. <Power supply by artificial satellite and transmission of time and other information> This application includes an invention for searching for the positions of articles and people. For example, it includes a method for wirelessly transmitting information and signals and wireless power supply from an artificial satellite or a group of artificial satellites (constellation) arranged in space to the above-mentioned tag on the ground (power transmission system in space solar power generation). In addition to artificial satellites, an aircraft in the air may also be used. <Background for using patches> The inventor recognized from the examples of close relatives that the elderly do not always wear wearable items such as shoes or bracelets, and also recognized that the degree of concentration on what the elderly wear changes depending on the progress of symptoms, etc. There were problems that the clothes could not be managed, and even if the caregiver prepared clothes, watches, or footwear with tags for monitoring or for emergency measures in case of distress, the elderly person could not wear, could not wear, or could not maintain them. <Patch medicine> Based on such circumstances, as a result of observing the lives of the elderly, the inventor paid attention to the rivastigmine patch for patch medicine, which was recognized as an item that the elderly always wore, and proposed the patch-type wireless 2TAG of this application. <Attachment of patch medicine, patch, and tape to other than the skin> The patch medicine is attached to the skin of the person to be administered, but there is a possibility that it may peel off from the skin. (For example, in summer, the patch may peel off due to the influence of sweat.) In this application, in addition to the skin of the elderly, it may be attached to the fabric of underwear, or (closer to the skin, difficult to take off outdoors,) underwear, innerwear. The patch may be in a tape type or a type in which the patch and tag are a hook-and-loop fastener with the underwear. <Attachment location to the skin> If it is on the back, it may be difficult for the elderly to reach out and remove the patch, and it may be difficult to peel off.<Problems to be Solved> The main problem to be solved is to provide a wearable tag for monitoring the elderly and others, or a wearable tag for discovery in case of being missing. <Devising a Tag Form That Is Easy to Maintain Wear> The problem to be solved is that even if a device is prepared as a wearable device, each elderly person has their own personality, and it is unclear whether they will always wear certain items such as shoes or watches properly. The task was to find items that can be worn continuously and devise an RFID tag function, a tag driving method, and a search method suitable for those items. ● It may have been a problem to devise a method of a tag that can be worn by a caregiver or the like as part of administering medicine to the elderly. ● Regarding the said tag, it was unclear whether the elderly would always wear shoes, belts, or a wearable device with a watch-type tag built in, depending on their preferences, differences in condition, and level of interest. <Problems During Search> ● The detection range by a tag scanner using the UHF method (for example, a sticker-type tag in the 900 MHz band) was about 2 to 5 m. When the elderly are lost in the city or mountains, it is preferable that the detection range be wide. For example, consider and disclose the configuration of a power supply method and power storage (capacitor type, primary battery type, secondary battery type) so that it is 5 m or more. It was a problem to provide an RFID tag function from a long distance (the driving form may include passive type, semi-active type, and active type) so that the tag can use power to transmit the presence and identification information of the tag to the tag scanner by the tag scanner. <Drone-Type Tag Scanner, Tag Scanner by Aircraft, Spacecraft, Artificial Satellite, and Retrofitted Tag Scanner for Transportation Machinery Such as Automobile, Motorcycle, and Taxi> When a person having 2TAG is in distress, the searcher may search with a handy tag scanner, or may search with a drone-type tag scanner. ● For example, to search for a person in distress in the mountains, release multiple drones to the mountain where the person is thought to be in distress. The drones perform wireless power transmission to the search location and radiate wireless energy so that 2TAG can be charged. The drones may search for 2TAG while positioning their location with signals such as GPS and operating automatically. ● For example, if the wireless communication power and the sensitivity of the antenna permit, instead of drones or aircraft, artificial satellites, constellations of artificial satellites, spacecraft, and space structures may be used to search for 2TAG.●For example, taxis, motorcycles, delivery vehicles, or public vehicles (mail vehicles, police vehicles, fire and medical vehicles, cleaning vehicles) may be pre-equipped with tag scanners to check if there are any wearers of the 2TAGs wandering in the streets. ●The 2TAGs may be attached to the keys of buildings or equipment vehicles, and by using the tag scanner to search for the 2TAGs, they may be used for key management and key search. <When a tag scanner is installed on a mobile terminal>A tag scanner may be installed on a mobile terminal such as a smartphone. The tag scanner may be installed on or retrofitted to a smartphone to search for the 2TAGs attached to people or important items with the 2TAGs attached. <Means for solving the problems>The tag 2TAG and the tag scanner 6TAG-SCANNER of the present invention are a patch-type wireless tag that combines a patch for administering medicine to dementia patients and a wireless tag, and the most important feature is that it can administer the patch medicine to dementia patients, attach the tag, and maintain the attached state. Furthermore, the conditions for driving the tag after attachment are also disclosed. <Effects of the invention. >The tag 2TAG and tag scanner of the present invention are patch-type wireless tags that combine a patch for administering medicine to dementia patients and a wireless tag, and have the advantage of being able to administer the patch medicine to dementia patients and attach and maintain the attachment state of the tag. <Example> The concept of the present invention is described in FIG. 7. The main body of the present invention incorporates the procedure of attaching and managing the wireless tag 2TAG into the treatment procedure performed by the relatives, caregivers, and nursing staff of the elderly who administer the patch medicine to the elderly dementia patients, so that the above two procedures can be performed in one procedure. When searching for the wireless tag 2TAG, the power is stored in the 2TAG by wireless power supply from automobiles, transportation equipment, drones, aircraft such as airplanes, and space machines such as artificial satellites in the street, and released as the power of the beacon signal, so that the beacon signal can be sent to the tag scanner over a distance beyond the range of wireless power supply. This is a method of searching for the 2TAG that is expected to be attached to the elderly. ※ Detailed descriptions of basic computers, electronic components and elements, communication, power supply, drones, aircraft, space machines, time synchronization technology, and positioning technology can be explained from known methods and previously reported patent documents, so they are omitted. In FIG. 7 and 2TAG of the present application, for example, wireless LAN (IEEE 802.11 series), tethering, or wireless PAN (IEEE 802.15 series), and wireless power supply are used, but since these technologies are obvious according to known documents, the explanations are omitted.

[0061] As an example of the use of the energy transport method disclosed in paragraph number [

[0060] ], a lightning protection method using the energy transport method from the light-emitting unit 1 using the laser to the light-receiving unit 2 is disclosed. (The lightning protection method of the present application is an idea.) <Technical Field> <0001> This application refers to and quotes Japanese Patent Application No. 2022-123161, Japanese Patent Application No. 2022-086263, and Japanese Patent Application No. 2023-007722, which are previous applications of this application. This application includes an idea regarding lightning protection against lightning strikes caused by thunderclouds. <Background Art> <0002> Lightning strikes affect electrical equipment, power grids, and information and communication equipment, and sometimes cause damage. Therefore, countermeasures are taken to equip buildings with lightning rods for lightning protection. Also, according to Patent Document 1 and Patent Document 2, a conductive wire (FIG. 1 of Patent Document 1) or a region plasmaized by a laser (FIG. 2 of Patent Document 1) is used from the ground toward rain clouds and thunder clouds, and the resistance value of a portion that is insulated between the thunder cloud and the ground and acts as a capacitor is reduced or short-circuited to intentionally change the direction in which the charge of the lightning strike flows or the direction where the lightning strikes. In Patent Document 2, it is disclosed that the application of the fact that the radiation light generated using a free electron laser or a particle accelerator and an undulator is radiation or ionizing radiation having an ionization effect (FIG. 1 of Patent Document 2) is disclosed, and currently, research and development of a lightning protection method using a laser is also underway. Also, according to the previous application Japanese Patent Application No. 2023-007722 of this application, a configuration is disclosed in which ultraviolet rays, X-rays, and gamma-ray photons are irradiated onto the air including oxygen molecules, ozone, oxygen atoms, nitrogen molecules, nitrogen atoms, and other molecular atoms in the atmosphere of the earth, which may include clouds, rain clouds, and thunder clouds, from space. <Prior Art Documents> <Patent Documents> <0003> <Patent Document 1> Japanese Patent Laid-Open No. 03-222295 <Patent Document 2> Japanese Patent Laid-Open No. 05-180954 <Summary of the Invention> <Problems to be Solved by the Invention> <0004> (1) When short-circuiting using a conductive wire from the ground part, (in order to reduce the weight to be lifted or suspended) the wire is preferably lightweight. (2) When a laser is emitted from the ground into the sky during rainfall, if hail exists in the laser beam due to snow, raindrops, hail, etc. being blown from the thunder cloud toward the ground, the laser may be scattered. Also, when the inventor was devising an energy transport method of SSPS from space, a configuration was considered in which ultraviolet rays and X-rays are received by the light-receiving unit 2 in the air from the space-side light-emitting unit 1.In the present application, instead of on the ground, photons or lasers of ionizing radiation such as X-rays are irradiated from a plurality of light-emitting parts 1 of a space solar power satellite 1 SSPS or a satellite constellation of 1 SSPS in the air or space, from the upper layer of the thundercloud (space side / stratosphere side) to the lower layer of the thundercloud (ground side), and the capacitor part (the capacitor part composed of the LCP region and the LCM region in Fig. 13) composed of the charged layers of the upper and lower layers of the thundercloud is short-circuited using the ionized / plasma region. By creating an ionized region with conductivity that serves as a breakthrough (IONA-NAIL in Fig. 13, the nail-shaped part, or the part of the atmosphere ionized / plasmaized / lowered in resistance by the laser focus FCS-2) to weaken the insulation of the capacitor inside the thundercloud storing positive and negative charges of the thundercloud, the charges for lightning strike can be short-circuited (discharged), and it is considered that this leads to lightning protection while reducing the influence of meteorological phenomena such as hail. ● In the present application, it is considered that laser irradiation from the ground wave to the thundercloud can be scattered by hail or the like, and a method of lightning protection by irradiating the thundercloud in the air from space with a laser such as X-rays is studied. The present application discloses a lightning protection method intended to facilitate short-circuiting of the charges inside the thundercloud. ● As shown in Fig. 13, (considering that in the troposphere, the laser is not effective due to objects that obstruct the straight propagation of the laser and cause diffuse reflection such as rain, hail, and snow, and when the laser is emitted upward from the ground, it may affect objects such as aircraft in the sky), without being affected by the meteorological environment such as rain in the troposphere and without affecting houses and objects below the troposphere, photons absorbed by the atmosphere, oxygen, nitrogen, atoms, and molecules are irradiated from space or the stratosphere toward the thundercloud in the troposphere to promote short-circuiting inside the thundercloud, or to promote short-circuiting between the lower layer of the thundercloud and the ground part. It may also be possible to induce easy flow of charges in the upper layer of the thundercloud and the part above the thundercloud. The photons: preferably X-rays and gamma rays with ionization action and output control. (Broadly, ultraviolet rays such as UV-B and UV-C. If described without further limitation, lasers or radio waves that are absorbed by the atmosphere with some infrared rays or the like and induce ionization action, partial lowering of the resistance of the thundercloud, and breakdown of insulation may also be used.) <Means for Solving the Problem> <0005> <(1) Lightning Protection by a Conductor> The conductor element 1 described in Fig. 1 of Japanese Patent Application No. 2022-123161 may be used so as to cross the thundercloud or assist in discharging / short-circuiting inside the thundercloud.Also, the cable part 12 that may have conductivity of the orbital elevator part 10 described in Japanese Patent Application No. 2022-086263 may be arranged so as to vertically cross the thundercloud. <0006><(2) Lightning protection by ionization> Using a light emitting part 1 (radiation light generation device, free electron laser) arranged in space or in the air (for example, a group of artificial satellites, an aircraft, an aerial platform), X-rays or gamma rays (and ultraviolet rays) are irradiated and emitted to a light receiving part 2 THCL which is a thundercloud or rain cloud in the air. The laser may have a laser trajectory that crosses, passes through, or penetrates the thundercloud 2 THCL from the space side toward the ground. The ionization radiation laser such as the X-rays and gamma rays ionizes oxygen molecules, ozone, oxygen atoms, nitrogen molecules, nitrogen atoms, or other molecular atoms in the atmosphere in the traveling path of the laser, forming an ionized region, a region with high conductivity, or a plasma region, and using the plasma region to short-circuit the positively charged region / layer and the negatively charged region / layer of the thundercloud, or reduce the insulation, with the intention of neutralizing, short-circuiting, protecting against lightning, or controlling lightning strikes. In addition to short-circuiting the positive and negative charges inside the thundercloud, the laser may also be able to induce, discharge, or release the charges of the thundercloud to a layer or part different from the thundercloud. For example, when the laser passes through the upper layer / above of the thundercloud, the stratosphere, the mesosphere, the thermosphere, or the ionosphere, ionized parts or low-resistance parts are generated in those parts, and the charges of the thundercloud may flow or escape to those parts. The laser may be irradiated to form a low-resistance part and directed so that electricity flows upward from the thundercloud such as a sprite. Also, when the laser is a photon with a shorter wavelength than UV-B, it is expected that the laser will be absorbed and attenuated by the atmosphere due to photoreaction, chemical reaction, and ionization of atomic molecules, and it will be difficult to reach the ground. <Advantages of the Invention><0007>According to the method of the present application, the laser is not scattered by rain and hail in the troposphere, and an ionized and low-resistance conductive path IONA can be formed for the thundercloud from space, and it is possible to attempt to break down the insulation, discharge, and protect against lightning of the thundercloud. Compared with the case of arranging a laser light emitting part 4 LASER on the ground and irradiating the air, it is possible to attempt to protect against lightning by irradiating a laser to a place where lightning protection is required using a group of artificial satellites.<Brief Description of the Drawings><0008><Fig. 13>Explanation diagram of a lightning protection method for irradiating photons with a shorter wavelength than UV-B, such as X-rays and gamma rays, from the light-emitting part 1 in the sky to the thundercloud 2THCL (the light-receiving part 2 in the air). (In Fig. 1, when irradiating, the light-emitting part 1 used for the space laser SSPS in outer space or the light-emitting part 1 of the stratospheric platform aircraft 3 etc. may be used.)<Fig. 12>Explanation diagram of short-circuiting the thundercloud 2THCL with the conductive cable 1WIRE·12 for lightning protection. *(a) Explanation diagram of the orbital elevator 10 having the cage part 15·3KAGO connecting the ground part 14 and the space structure with the cable 12. (b) Explanation diagram of the system connecting the ground part 14, the aircraft 3, the airborne platform, etc. with the cable 12.* The cage part 3KAGO receives energy from the light-emitting part 1 by the light-receiving part 2, drives the propulsion device 3TH which may include the propellant provided in the 3KAGO, and raises and lowers the 3KAGO in the vertical direction (space / ground direction). The 3KAGO may be guided by 12 to move up and down.<Mode for Carrying Out the Invention><0009>It will be described with reference to Fig. 12 and Fig. 13.<Example 1><0010>● From the light-emitting part 1 arranged in space or in the air / stratosphere, ionizing radiation photons 1HNU-X such as X-rays or photons 1HNU such as ultraviolet rays are irradiated toward the ground side so as to pass through the thundercloud 2THCL from the upper side of the thundercloud, the stratosphere side to the lower layer side of the troposphere, the ground side. (1HNU is used as ultraviolet rays, visible light, and infrared rays for lightning protection purposes. Preferably, photons having a wavelength that reacts and is absorbed by oxygen molecules, nitrogen molecules, and atomic molecules in the atmosphere are preferred.) At this time, the insulation between the positively charged layer LCP in the upper part of the thundercloud and the negatively charged layer LCM in the upper part of the thundercloud is destroyed (expected to be destroyed) by the low-resistance conductive path IONA formed by penetrating the positively charged layer LCP in the upper part of the thundercloud. (When there is an insulation gap between LCP and LCM in the thundercloud, a low-resistance part is formed in the insulation gap part by laser irradiation, and a part like an electric wire that weakens the insulating force in the thundercloud is formed to induce insulation breakdown and discharge.)● On the lower right of Fig. 13, the laser penetrates the thundercloud 2THCL, the conductive path IONA, IONA-LINE in the figure is formed, the charges of the capacitor composed of LCP and LCM are discharged, short-circuited, and lightning protection is performed.(In the concept of insulating the insulation between thunderclouds with a conductive wire, it is only necessary to use the conductive wire in FIG. 1 of Patent Document 1 to discharge or short-circuit the charges of the thunderclouds. The thundercloud can be used as a conductor 12, and the orbital elevator part 10 may also be used.) ● On the left at the bottom of FIG. 13, the laser travels so as to punch through the layer LCP of positive charges at the upper part of the thundercloud. The part of the trajectory of the laser is ionized, and a nail-shaped (or in the form of laser attenuation) low-resistance conductive path IONA-NAIL is formed. When a conductive path IIONA-NAIL is suddenly formed in the insulated gap distance between LCP and LCM, only the part of the conductive path IIONA-NAIL has a shortened insulation distance, and lightning protection is performed by discharging L-SCN from there. When there are objects that should avoid laser irradiation to reduce the impact on living organisms and aircraft in the air, the laser may be turned off. Also, the output of the laser may be controlled so that the laser output does not increase at locations other than the focal point FCS-2. Also, when radiation or X-rays cannot be used to avoid biological effects, an ultraviolet laser may be used and its output may be controlled to attempt to ionize the atmosphere. <Example 2> The left diagram of FIG. 12 is an explanatory diagram of the case where a power plant on the cosmic side, a space solar power plant, a cosmic structure 1 and the ground part 14 are electrically connected, and the power of the power plant on the cosmic side is transmitted to the ground part 14 via the cable 12. Also, the right diagram of FIG. 12 is (a system that uses a cable shortened to the aerial arrangement means 3 instead of the long cable of the orbital elevator and has the merit of being able to shorten the cable), and the section from the light-emitting part 1 on the cosmic side to the light-receiving part 2 in the air is transmitted or energy-transported by the laser SSPS method. Then, the arrangement means 3 (aircraft 3, HAPS, etc.) including the light-receiving part 2 and the ground part 14 are electrically connected via the cable 12, and the power is transmitted from the light-receiving part 2 to the ground part 14 and the ground-side power grid 1100. It is an explanatory diagram of a power transmission system and an energy transmission system. It may be preferable to use the conductor element 1 and the cable 1WIRE of the present application, in which the cable 12 uses a carbon material (such as CNT) in the material part 101 of the element 1 of the present application and reduces the amount of copper used, and thus reduces the weight of the conductor compared to a conductor made of only copper. ● In the right diagram of FIG. 12, the arrangement means 3 needs to support the cable 12 so as to lift it and hang it from the air to the ground part. At that time, it is preferable that the cable 12 is lightweight.(The specific gravity of CNT is 2.0 and that of copper is about 8. CNT and carbon materials are lightweight. By using 1WIRE made of carbon materials for the cable 12, the weight of the cable that the arranging means 3 should lift into the air can be reduced.) ● All the configurations in FIG. 12 are systems in which the cable 12 crosses the upper and lower layers LCP and LCM of the thundercloud to short-circuit the charges of the thundercloud via 12. ● FIG. 12 is a system in which the cable 12 crosses the upper and lower layers LCP and LCM of the thundercloud to short-circuit the charges of the thundercloud via 12. The ground part 14 is positively charged, and by connecting it to the negatively charged part of the thundercloud via the said 12, a current due to short-circuit flows through 12, and electrical energy is transported and transmitted. Although lightning protection is intended in the present application, with the configuration of FIG. 12, it is possible to collect the energy of the thundercloud on the ground part using 12 and 14, and the thundercloud energy obtained by 12 and 14 may be supplied in a form usable for the power grid 1100 by a circuit or device provided in 14 or the like. ( Power generation by lightning and lightning charging may use 14 and 12. ) ● The cage part 3KAGO may receive energy from the light emitting part 1 by the light receiving part 2 and move forward, up and down. ※ The aircraft 3, 3KAGO, and the aerial platform 3 may be equipped with devices capable of generating electricity in the air, such as solar cells and airborne wind turbines. They may also be equipped with auxiliary power sources and batteries. ● The aircraft 3 (aerial platform) connected to the ground part 14 in the right figure of Fig. 12 may lift and lower loads like a ladder truck, ladder elevator, or crane, or may supply power to the ground part. It may also be equipped with a robotic arm or crane to perform additive manufacturing, subtractive processing, various operations, and the transportation of goods. ● In this application, when transmitting energy from SSPS (laser type, or in some forms of this application, millimeter wave, microwave, radio wave type is also possible) to the ground, two forms are disclosed: a method of transmitting power using the cable 12, and a method of converting it into the form of fuel or chemical substances by the arrangement means 3 and transporting the substances to the ground part 14 by an aircraft or the like. <Industrial Applicability> <0011> In the case of the configuration of Fig. 13, it can be used when attempting to avoid lightning by irradiating a laser on the area 2 where lightning may occur from the light emitting part 1 of the artificial satellite group. (The configuration having the light emitting part 1 in Fig. 13 can easily respond immediately to the user's desire to irradiate photons toward the thunderclouds and the atmosphere at locations where lightning is likely to strike when the artificial satellite having the light emitting part 1 orbits LEO or the like, and promote the short - circuit or discharge of the capacitor of the thundercloud to avoid lightning. On the other hand, in the case of the configuration of Fig. 12, it is necessary to deploy the cable 12.) <Explanation of Reference Signs> <0012> <Explanation of Fig. 13> 1: A light emitting part arranged in space or the air. A laser light emitting part. A light emitting part of ultraviolet rays including UV - B and UV - C or photons including X - rays and gamma rays. ※ Without limiting the scope of the invention of this application, when irradiating photons from the stratosphere or space side to the thunderclouds and making the photons act on the thunderclouds, paying attention to the photons that react and dissociate by ozone, oxygen molecules, nitrogen molecules, air molecules, etc. and are attenuated in the atmosphere, gamma rays, X - rays, some ultraviolet rays, infrared light, and some radio waves such as millimeter waves may be included. 1SSPS: The SSPS part including the light emitting part 1. A light emitting part using space solar power generation. 1SSPS - SYS - SEIZA: The light emitting part 1 of the satellite constellation. Example: Satellite constellations of LEO and GEO.1LLR: Free electron laser device (output-controlled X-ray laser) 1HNU-X: Ionizing radiation photons such as X-rays, lasers. 1HNU: Photons emitted from the light-emitting part 1. 2: The part / object that receives the photons of the light-receiving part 1. 2THCL: Thundercloud. (When a cumulonimbus cloud, etc. is used as the light-receiving part 2) 2AIR: The air containing 2. Or when a part of the atmosphere in the air is the energy irradiation target of the light-emitting part 1. 3: Aircraft, transportation equipment, means for arranging the light-receiving part 2 in the air. LCM: Negative charge region of the thundercloud, negative charge on the ground side of the lower layer of the thundercloud. LCP: Positive charge region of the thundercloud, positive charge on the upper layer side of the thundercloud. L-SCN: The part expected to discharge using as a clue the ionized part that protrudes like a nail in the upper layer of the thundercloud, the internal discharge location of the thunderstorm. Dielectric breakdown part. A part of the thundercloud that was insulated becomes more conductive due to the laser irradiation, becoming a path for the escape of charges in the LCP part or the upper layer of the thundercloud, and being prone to short-circuit. IONA-NAIL: (The ionized part that protrudes like a nail struck on a plate in the upper layer of the thundercloud formed by the laser, the plasma part, the low-resistance part. The protruding conductor part. Induces discharge in the thundercloud. It may be a low-resistance part formed by the focal point FCS-2 of multiple lasers irradiated from multiple light-emitting parts 1.) IONA-LINE: (The short-circuit conductor part / low-resistance part formed by a linear / conductor-like laser. Induces discharge / short-circuit in the thundercloud) VL: Voltage of the thundercloud (capacitor voltage) 1100: Power transmission network 6: Power user <Explanation of Figure 12> 10: Orbital elevator part space structure. 1: Space structure / artificial satellite space base, etc. (Example: The space structure 1 and the aerial structure 2 which are the so-called orbital ring parts described in Figure 1B of Japanese Patent Application No. 2022-086263. It may have 1TH and 2, receive photons from 1, and be propelled / accelerated. The spaceship, launch vehicle, space structure, orbital ring, aerial structure, and annular structure may be provided with 1TH or 3TH and the light-receiving part 2, transmit photons from the light-emitting part 1, and accelerate, propel, move, fly, float, control the attitude, and drive them.) 1TH: Spacecraft propulsion device. 3SPACESHIP (Spacecraft, spaceship, launch vehicle, etc. Mounts 2, 1TH, and 3TH.) 3KAGO: The cage part 15 that is attached / guided by the cable 12 of the orbital elevator 10 and is propelled, lifted, and moved by the propulsion device. 3TH: Propulsion device of 3KAGO, propulsion device and its attached equipment / propellant, etc. 2: Light-receiving part.12: Cable (may use 1WIRE), 14: Above-ground part, the above-ground part of 10, 17: Connection part, 1: Light-emitting part. 1PP: Power plant. 1100: Ground-side power grid. 1100S: Space-side power transmission grid. <Figure 26, Explanation of Orbital Elevator and Aerial Platform> ※Figure 26 may include a combined pulley in the pulley 10B, may include elements of a known traction rope-type elevator, and may include a counterweight, hoistway, rope, wire, deflection pulley, combined pulley, sheave, winch, cage, landing door, landing station machinery room, control device, buffer, bit, brake. The cage 15 may be a cage 15 with a thruster 3TH including a light-receiving part 2 and a counterweight 15W. The right figure of Figure 26 shows an elevator 10AIR with a winch 10B having weight installed at the lower part, and the upper part is a combined pulley 10B. An elevator with a known winch installed at the lower part (note that the configuration of the elevator 10AIR or the orbital elevator 10 with the winch installed at the upper or lower part is possible. 10B may include a combined pulley, winch, and multiple pulleys) 15: Cage part, cargo compartment, transporter of an elevator or ropeway. 15 may be a cage part 15 that is an aircraft 3 or a transport device 3 connected by a wire 10WIR with a thruster 3TH. (It may also be the cage 15 of the cable 12 of the orbital elevator 10 or the aerial platform 3.) 15W: Counterweight of an elevator, cableway, pulley, crane part, counterweight of the cage 15. 10B: Pulley part (may use a pulley or a combined pulley), sheave, winch, hoisting motor part of an elevator (the hoisting motor may be a motor with a non-contact magnetic levitation bearing. Pulley, winding part, power part of 12 and 10WIR) *3TH has a propellant such as water, and the propellant of 3TH may be replenished when 15 reaches the base part 14. *15 and 15W may be an aircraft 3 or a transport device 3, and 3 may be equipped with a thruster 3TH and a light-receiving part 2. *15 and 15W are driven like the hoisting motor of a traction elevator, and the power may be obtained from the light-emitting part 1 through the light-receiving part 2. When the 3TH of 15·15W is at an altitude higher than the stratosphere and troposphere where the light (e.g., UVC light) of the light-emitting part 1 reaches, the 3TH receives laser irradiation from the light-emitting part 1 and moves up and down the 3KAGO·15 ( / 15W). Accordingly, the 15W ( / 3KAGO·15) connected by the wire 10WIR (using the pulley 10B) moves up and down.When 15W is at the high altitude, irradiate the light of the light-emitting unit 1 on the 3TH of 15W, move 15W, and move 15. 10WIR: 15·15W rope·wire. 14: Above-ground part. 4LASER: Laser emitting unit from the above-ground part. It is affected by the troposphere such as hail and clouds, but when directly below 15, power transmission may be performed by a laser (instead of the space-side light-emitting unit 1) to 15. 1: Photon light-emitting unit 1. (The orbital elevator and aerial platform in Fig. 26 are equipped with a ring 10WIR that can be supported and rotated by pulleys 10B etc. on the space / aerial side device 17 and the above-ground part 14 like a Ferris wheel, cable car and their carriers, and laser irradiation is performed on the light-receiving part 2 of each thruster 3TH of the cage 15 attached to the 10WIR using pulleys (like a Ferris wheel or multiple carriers of a cable car) to rotate each 15 in one direction (from space to the ground and then back to space again) and operate it to repeat the rotation. Propellant, water, etc. for 3TH may be replenished to 15 at the above-ground part 14. (Like a space fountain or fountain, each 15 and the 10WIR connected to 15 may be supported and rotated by 10B, 14, and 17 by propulsion by 3TH. Each 15 or 15W of 10WIR may be repeatedly lifted from 14 to 17 and then lowered. ※A circular path that repeats returning from the ground 14 to the aerial side 17 and then back to the ground 14 like a cable car or Ferris wheel may also be used.) The light-emitting unit 1 and the light-receiving unit 2 of the present application may be used for propulsion, acceleration, and driving of space / aerial structures, orbital rings, partial orbital rings, space fountains, launch loops, mass drivers, launch devices, transportation equipment, etc.) ※For example, when it is desired to lift and place the device 17 from the ground near the space-side structure 2, the platform 3 including the device 17 on the left side of Fig. 26 (equipped with the device 17, the propulsion device 3TH, and the light-receiving part 2 for photons transmitted from the light-receiving part 1, and having a cage 15, a cable 12, and a pulley 10B that can lift and lower luggage, propellant, and water from the ground 14 and supply them to the thruster 3TH). In a balloon or rocket launched from the ground, or an aerial elevator system 10AIR including a series of the above elements (an aerial version of a space elevator), propellant and water are supplied to 3TH from the ground through 12 and 3, and in 3TH, operations such as propulsion, floating, ascending, descending, moving, attitude control, launching, and lifting can be performed using the energy by the light-receiving part 2 and the propellant.It may be possible to lift and raise the aerial platform 3 and the placement means 3 on the space side by heating and injecting the water and propellant supplied from the ground with the energy obtained by the light receiving part 2, and move and place them near the structure 2 on the space side. 17: A connection part with the aerial or space side part may be provided with a non-contact lowering mechanism. 17TR: A transport device part and a train part that are suspended non-contact from the structure 2 and can move and be guided along the structure 2. It may be provided with the light receiving part 2. It may be propelled and operated by receiving photons from the light emitting part 1. <Figure 27, Explanation of the Orbital Elevator and the Space Structure> 1100: Power and communication network. 1000: Ground, Earth, Moon, Planet, Satellite, Celestial body. 10: Orbital elevator. 12: Cable. 15: Space elevator cage part. 17: Connection part. It may include a functional part of a magnetic suspension part (magnetic attraction method, electromagnetic induction levitation support method EDS, etc.). It may also be an aircraft 3 or a spacecraft. ) 171: Magnetic suspension means of 17. 171C: Coil (for magnetic suspension and magnetic suspension between 17 and the space / aerial structure). 171S: Sensor, gap sensor for magnetic suspension. 171E: Circuit, control circuit, magnetic attraction feedback circuit, magnetic suspension control part. 171R,E: Propulsion device 1TH·3TH of 17. Space structure 1·Aerial structure 2: Structures (ring-shaped, linear, base station, aircraft / spacecraft) arranged in the air or space may include a magnetic suspension functional part. It may also be a rotating (eddy current countermeasure) rail. 17TR: The transport device that is magnetically levitated, magnetically suspended, non-contact supported, guided, moved, and propelled using the said rail. It may be provided with 3TH and the light receiving part 2 and be driven. 317: Magnetic suspension means on the structure side. A part that magnetically acts, attracts, and repels with 171C such as a magnetic body, core, magnet PMG, conductor, etc. (a part of the magnetic suspension part) *317 may be sectorized or provided with a part that increases the resistance of 317. *In order to reduce the eddy current in the rotating 317 and the stationary 17, in case the force by the eddy current (the behavior of the rotating disk of Arago and the U-shaped magnet) hinders the magnetic suspension aimed at in the present application, an element that can lower or increase the conductivity of 317 may be used, and a conductor element 1, 1FILM containing less copper and carbon and its gate control circuit may be used. *From the viewpoint of controlling the eddy current, it may be possible to control the ease of generation of the eddy current in the 317 part and the 317MG part.When increasing the eddy current, turn on the gate of the 1FILM of 317 to reduce the resistance of 317 and change the repulsive force between 317 and 171C. When decreasing the eddy current, turn off the gate and increase the resistance. 3171S: sensor, gap sensor. 32: circuit, control circuit. 32-wir: wiring <Document name> Claims <Claim EW1> An energy transport method using a photon generation unit (1) arranged in a satellite or space and a light receiving unit (2) arranged and positioned in the stratosphere or at an altitude above the troposphere that can receive photons irradiated and emitted from the photon generation unit (1), wherein the photon generation unit... The energy transport method includes a step of irradiating, emitting, relaying, transmitting, and sending photons from (1) to the light receiving part (2), wherein the photons are UV-B or photons with a wavelength shorter than 315 nm, and the photons have the characteristic of being absorbed by ozone, oxygen molecules, oxygen atoms, nitrogen molecules, nitrogen atoms, and molecular atoms in the atmosphere through photoreaction and chemical reaction. <Claim EW2> A method for reducing the resistance of the atmosphere using the energy transport method according to Claim EW1, which includes a step of irradiating, emitting, relaying, transmitting, and sending a laser containing the photons from the light emitting part 1 to the light receiving part 2, which is the atmosphere or thunderclouds in the air. The laser has a trajectory that crosses, passes through, and penetrates the atmosphere and thunderclouds from the cosmic side to the ground direction. The laser is a laser using photons in the wavelength range of X-rays and gamma rays, and can ionize oxygen molecules, ozone, oxygen atoms, or nitrogen molecules, nitrogen atoms, or molecular atoms in the atmosphere along the traveling path of the laser, and form an ionized region, a plasma region, or a region with high conductivity along the traveli...

Claims

1. A photon transmission method using a photon generation unit (1) arranged in outer space or in the air, and a light receiving unit (2) in the air or in the atmosphere that can receive photons irradiated and emitted from the photon generation unit (1), the method being capable of irradiating, emitting, relaying, transmitting, and transferring photons from the photon generation unit (1) to the light receiving unit (2).

2. The photon transmission method according to claim 1, wherein the photons are photons having a wavelength capable of causing a photocatalytic reaction or a photoreaction.

3. The photons are photons having a wavelength capable of causing a photodissociation reaction of oxygen molecules, a wavelength capable of dissociating oxygen molecules into oxygen atoms, or a wavelength shorter than 243 nm, and the photons have the characteristic of being absorbed by oxygen molecules, oxygen atoms, nitrogen molecules, and nitrogen atoms through photoreactions and chemical reactions. Or The photons are photons having a wavelength capable of causing a photodissociation reaction of nitrogen molecules, a wavelength capable of dissociating nitrogen molecules into nitrogen atoms, or a wavelength shorter than 126 nm, and the photons have the characteristic of being absorbed by nitrogen molecules and nitrogen atoms through photoreactions and chemical reactions. The photon transmission method according to claim 1.

4. A substance manufacturing system using the photon transmission method according to claim 1.

5. A substance manufacturing system using the photon transmission method according to claim 4, the system having a reactor, a chemical mechanical device, a catalyst, or means for performing a reaction by a photocatalyst or a photoreaction and a chemical reaction.

6. A substance manufacturing system using the photon transmission method according to claim 4, the system having the feature of using a process of breaking the bonds of molecules of a raw material substance using the photons.

7. A manufacturing system for the substance according to claim 6, wherein the bond of the molecule is a nitrogen-nitrogen bond, the photon is a photon having a wavelength capable of causing photodissociation of nitrogen molecules, a wavelength capable of dissociating nitrogen molecules into nitrogen atoms, or a wavelength shorter than 126 nm, the photon has a characteristic of being absorbed by a photoreaction and a chemical reaction with nitrogen-nitrogen molecules, the raw material substance contains nitrogen-nitrogen molecules, and the manufacturing system for the substance has a characteristic of manufacturing a nitrogen compound from the raw material substance.

8. A manufacturing system for a substance using the photon transmission method according to claim 2.

9. A manufacturing system for a substance having a chemical mechanical device / means for performing a reaction by a photocatalyst, using the photon having a wavelength capable of causing a photocatalytic reaction, using the raw material substance and water as the raw material substance, and manufacturing hydrogen from the raw material substance and water by a photocatalytic reaction, the manufacturing system for a substance according to claim 8.

10. A manufacturing system using the manufacturing system for a substance according to claim 9, reacting oxidized metal / iron oxide with the hydrogen, reducing the oxidized metal / iron oxide, and manufacturing a reduced metal compound / metal / iron.

11. A manufacturing system for a substance using the photon transmission method according to claim 3.

12. A manufacturing system for a substance according to claim 11, wherein the raw material substance contains nitrogen molecules, oxygen molecules, water molecules, carbon-containing substances, and raw materials, using photons having an effect of breaking the bonds and chemical bonds of the substances absorbed by the nitrogen molecules, oxygen molecules, water molecules, carbon-containing substances, and raw materials, and having a process / chemical process of breaking the bonds and chemical bonds. A manufacturing method for hydrogen, hydrocarbons, fuels, fertilizers, and substances.

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