Photon transmission method, atmospheric resistance reduction method, ionization method, and dielectric breakdown method

Abstract

To solve a problem with preventing laser leakage to the ground when photons and lasers are generated using space solar power generation or space power plants and transmitting energy from space to Earth.SOLUTION: This application provides a photon irradiation method and energy transmission system consisting of a photon emitter 1 that uses a photon laser such as UV-C that is absorbed by atmospheric molecular atoms including oxygen and nitrogen when in space during the power / energy transmission, and a photoreceiver 2. The light emitter can be placed in the air or in space, and a configuration is disclosed in which a focal point (FCS-2) of photons emitted by the multiple light emitters or a portion where photons are converged or concentrated can be formed in the photoreceiver by placing multiple light emitters. Furthermore, the application proposes a method in which the photoreceiver (2) irradiated with the laser is a part of the atmosphere, and the atmosphere of the photoreceiver (2) is ionized, reduced in resistance, and dielectric breakdown is caused.SELECTED DRAWING: Figure 13

Description

Technical Field

[0001] <Priority Claim Based on Prior Application>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 by reference herein the content thereof. Further, 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-mentioned transmission by wireless, laser, or fuel substance in the energy transmission from the space side to the ground or the air during space solar power generation (content 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-mentioned 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. ● Further, this application includes a device for utilizing the phenomenon 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 using carrier introduction by an electric double layer transistor. Further, it relates to electronic components and devices such as motors, actuators, and batteries using the wiring material. ● 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 according to the measured value of the sensor (Figure 10). · The high and low states mean that the high state is a state where carriers are introduced into 101 by the gate to form 104 and the conduction positive increases, and the low state is a state where the gate is off and no carriers are introduced into 101, or a case where the ionic species of the electric double layer generated in 105 act to reduce 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 and 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, lowering the conductivity of the electrode, and preventing a short circuit accompanied by rapid discharge when the positive and negative electrodes remain highly conductive and contact each other during an internal short circuit (Figure 9).

[0003] ● As shown in (B) and (A) of FIG. 1 of the present application (or as shown in FIG. 1 of Patent Document 1), there is a conductive layer 101 of a conductor, semiconductor, conductive polymer layer, or carbon-based material (such as CNT, graphene, graphite, etc.). There are 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 ions contained in the insulating layer 105 that can form 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 of 101 (the inversion layer 104 in a MOSFET). 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 in 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 related to the protective layer, the description is omitted.)

[0004] A capacitor is formed by a <MISFET and an electric double layer transistor> 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 part), 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 part. The thickness of the layer of the electric double layer part 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, and 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 104·1042, 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 may function to lower the conductivity contrary to 104 depending on the type of material of 101) 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 (acceleration, etc.) 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 (Figs. 9 and 10). ※ As shown in Fig. 2, 108 of the body B part 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 and 104, 105 in the drawings are not described as being the same as 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] <Gate breakdown of the gate portion> · The gate portion 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 portion is destroyed. When a voltage exceeding VGSA is applied 106 times, the capacitor portion is destroyed and 104 may not be able to be formed. (P2 in Fig. 9) <Fuse-like two-terminal conductor using gate breakdown of the gate portion> · 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 decreases. It may be possible to use this like a fuse. · 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 portion in the conductor is destroyed, 104 disappears, and the conductivity of 1-2TER decreases. As a result, it may be difficult for current to flow between the two terminals of 1-2TER, and it may have the effect of preventing a large current from flowing and spreading in a 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 some chemically doped conductive polymers with high carrier densities. ※ In this application, (even without chemical doping), high-mobility organic semiconductors, 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 conductor elements 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 a high-mobility organic semiconductor. · Regarding carbon materials such as CNTs, which are expected to have high mobility, it may also be possible to combine their high mobility with the high carrier density due to electric double-layer formation to form a good conductor. ● Also, in the configuration where 1012 is laminated on 101P in Figure 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 fee 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 or (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 part 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) or (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 between the flat 101 and 105 in (A) of FIG. 11 can be obtained, the conductor area A can be increased, (the resistance R of the conductor can be reduced), and 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 in (A), (B), and (C) of FIG. 11, since (B) and (C) are configurations in which 104 and 1042 can be taken as having a larger area than (A), in the present application, a configuration using 101P as in (B) and (C) of FIG. 11 can be preferably used. Further, in the case of 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 the sense of reducing the amount of metal used in the conducting wire and saving resources and reducing weight) can be laminated or deposited on the porous conductive carbon material conductor 101P to form 1012, and a carrier-introduced 1042 can 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 wire part of a motor. <Film Electrode Applications> ● An electrode-type conductor element 1FILM using the conductor element 1 in the form of a film, sheet, or foil. It is proposed to use it for 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 for 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 an 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 a human to carry. <Wire Applications> ● It is proposed to use the conductor element 1 as a wire-type element 1WIRE as shown in Fig. 5 for wires and the wire part of a motor. The conductor element 1 and 1WIRE are also assumed to be used for 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 wire. However, in a 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 wire is composed of a composite material gate electrode of a metal fiber such as aluminum and a carbon-based conductive material, 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 including 104 (the outer conductor part of a coaxial cable) is used for the conductor part of the wire. 1WIRE is designed with a configuration of a wire 1WIRE centered on 106 that can be made into a composite material for reasons such as being able to serve as a gate electrode for storing charges in the composite material so that 106 can withstand mechanical forces such as bending as a wire. ● 1WIRE in Fig. 5 is one example of the wire in the conductor element of this application, and the form of the wire-type conductor element of this application is not limited to the example of Fig. 5. For example, 1FILM may be processed (patterned, cut, etched, etc.) to make a wire device.

[0009] <Presence or Absence of Embedding the Conductor Element 1 in the Gate Electrode> In this application, three-terminal and two-terminal elements described in FIG. 8 were considered. ● In the 1WIRE and 1FILM of this application, a three-terminal element using the gate electrode 106 is formed. On the other hand, for applications such as forming a long wiring by connecting conductive films or conducting wires, two-terminal elements were considered. · A two-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 more than 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, driving 106 from Vcc by U1 may be possible 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 three-terminal type. · When used in the power generation section of large-scale solar cells such as ground 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 the conductor element 1 used in electrodes and wiring parts not only for solar cells but also for 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 three-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 that may differ in polarity and magnitude 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 many carriers and the n-type material having few carriers, and even if there is a difference in carrier density, it may be possible to control by making the voltage of the n-type gate electrode higher than the voltage of the p-type gate electrode, artificially generating carriers in the n-type portion, and obtaining a carrier amount commensurate with the p-type.

[0010] <Utilization in a thermoelectric conversion element> ● 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 a thermoelectric conversion element. 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 a carbon-based material, particularly an organic semiconductor or 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 resource constraints on specific elements are eliminated. By using a semiconductor material with an unlimited resource amount for 104 (101), mass production of the thermoelectric conversion element may become possible. (In a known thermoelectric conversion element, the use of a Bi2Te3 alloy can be 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 for 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, 1012 of 1 may use not only the conductors 101, 1012 but also the material parts 101, 1012 of a combination that behaves as a semiconductor when forming 104, 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 (among others, 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). 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, and display devices such as EL or liquid crystal) may be configured using the above-mentioned 1042. 101 and 1012 include materials used for transparent electrodes such as graphene, CNT, some organic semiconductors, the above-mentioned ZnO, SnO2, TiO2, ITO, and IGZO. 101, 101P, and 1012 include semiconductors and conductors. For example, it 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 or germanium Ge as a semiconductor material with a low bandgap, and may also include tin Sn or lead Pb as a conductor material.

[0011] <<Background of the present application>> ● The first reason is the soaring of metal resources due to the expansion of 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 itself to not using copper. Aluminum-containing gate electrodes may be used in 106 to form 104.

[0012] ● The second reason is the issue of recycling metal resources for large-scale devices, structures, and buildings used in outer space. The inventor discloses large-scale solar cells and secondary battery wiring and electrodes in JP-A-2022-058853 of Patent Document 2, or JP-A-2022-105726 related to the said Document 2, or aircraft, spacecraft, artificial satellites, and structures (orbital ring devices, orbital elevator devices) including the said electronic components. (The structures and aircraft claimed in Patent Document 2 may include secondary batteries, such as lithium-ion batteries, mounted on electric aircraft, 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). The said devices and structures are proposed to 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 incinerating 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 (such as 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 at low cost using 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 burden. 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 an accident and burn and fall to the ground, or even when using means such as orbital elevators, in case of an accident where the structure burns up, or when it is desired to reduce the labor of recovering the structure using human hands or robots, there may be a case where the structure is 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. Repeating this may make it impossible to sustain the construction and use of large-scale structures in space 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, the proportion of secondary batteries among the devices is large. Among vehicles, unmanned aircraft, and robots including humanoid and multi-legged types, robots with a long travel distance after charging, such as 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 travel 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. It was thought that if the use of resources such as copper for the motors, actuators, and wiring materials could be reduced, the constraints on metal resources would be reduced, which might contribute to the popularization of robot products. · It is also 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 most of the battery are aluminum electrodes and copper electrodes coated with active materials. Therefore, it was considered that if the amount of metal used can be reduced, it would lead to weight reduction and cost reduction of batteries, vehicles, airplanes, and robots. ● This application intends to constitute lightweight electric wires, motors, and batteries. It can be used for various machines and devices using these motors and batteries (transportation equipment such as electric vehicles, electric aircraft, 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, and portable / 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 in 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 (but not as good as metal materials), a means of generating an electric field effect is mounted on the wiring material and the electrode so that the mechanism for increasing the carriers of the electric double layer transistor can be utilized. Also, motors, actuators, electronic components, electrodes, battery electrodes, and batteries having the above means are 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 that is considered to have 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 will be no problem even if space development is carried out using devices and structures such as copper. Also, not only conductivity, but for devices that must be made of metals such as copper in terms of mechanical material properties and various performance aspects, the above metals should be used. 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). 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 yet 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 may include 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 collectors (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 carriers are 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 improve the current collection performance of the current collector and the electrode compared to the case without 104.

[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 is damaged), the internal electrodes may short-circuit, and the energy stored in the battery may be released, making it prone to explosion and combustion. · Therefore, in the present application, when the battery is short-circuited internally, such as being pierced by a nail, a safety mechanism as shown in FIGS. 9 and 10 is proposed. · The signs of the accident before the battery is destroyed (such as the battery being pierced, the 3BATT of the in-vehicle battery being collided and damaged in a traffic accident, the aircraft carrying the 3BATT crashing, etc.) (changes in impact and 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 collision sounds, changes in sound and abnormal detection when an ultrasonic probe is made to echo on the battery and other protected objects, changes in smell, sensors for detecting chemical substances, threats approaching the battery captured by a camera, changes in air pressure and pressure, temperature changes) are detected by the sensors of the control unit and the control section, 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 igniting 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 outside the transportation device (an object likely to collide with the vehicle itself detected by the camera) by the in-vehicle computer C1 mounted on the transportation device and the camera mounted on the C1, and the C1 transmits a control signal to the controller 3CBATT of the battery through the communication path of the signal. Then, the 3CBATT controls the gate driver circuit 3CGATE according to the received signal and data according to the stored procedure, and may vary the voltage VGS applied to the 106 of the 2BATT to control the gate electrode of the conductor element. Then, by controlling the voltage of the 106, the 104 of the 101 can be reduced or eliminated, or 104I can be generated, and the conductivity of the internal electrodes of the 2BATT can be reduced.

[0021] <Conductive Element 1 Whose Conductivity is Controlled by a Sensor>Regardless of the form of the battery, whether it is an electrical conducting 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 in 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 such as buildings, tunnels, and roads), the conductive element 1 of the present application may be used for wiring to detect sensors and sensor signals. · The element 1 may be used for wiring of signals and electric power for operating a sensor or input device including a temperature sensor or a camera, or for operating an output device including a motor or a buzzer.

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", Faculty of Science and Engineering, Waseda University, Department of Mechanical Science and Aeronautics, 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. It is also a problem 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 controlling the conductivity, and to provide a safe device and a safe battery.

[0026] · In space machines, electric aircraft, electric vehicles, and electric transportation equipment, reducing the amount of metal used in the electrode materials of secondary batteries has been an issue. It was also considered necessary to reduce the metal usage of motors. · It was necessary to devise carbon-based conductor wiring or conductor wiring that could reduce the amount of metal, as a substitute for 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 covalently bonded 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, etc., are difficult to introduce, inject, or dope carriers even though they have high carrier mobility, and the carrier density n tends to be lower than that of metals. Also, it cannot be denied that the molecular skeleton of carbon-based wiring materials 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> The portion 104 where carrier injection of the conductive material 101 in the electric double layer transistor is performed is used for conductive materials and conductor elements 1 of batteries, electronic components, conducting wires, actuators, motors, etc. including chemical batteries and physical batteries. (Using the said conductor element 1 in vehicles, transportation equipment, aircraft, robots, or household appliances, products, and components 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 having the carrier-introduced and 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 (and conductor) material that 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 during battery storage and when the battery is 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 the 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 the 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. · Examples of internal short circuits are the destruction and short circuit of the internal battery structure due to 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 than that, internal short circuits can also occur when metals derived from the electrode, electrolyte, electrolyte solution, and active material precipitate during charging and discharging of the battery and pass through the separator to cause a short circuit, or when there are defects during the manufacturing of the separator, electrode, etc., or when foreign substances and impurities are mixed in. ● The case where the electrode common ground of the positive electrode and the negative electrode of the present application is short-circuited inside the battery is shown in FIG. 9 as a figure in which a metal nail T1 is stabbed through the battery internally. In the case of the stabbing, 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 the conductivity of 101 is low, the conductivity of the positive electrode and the negative electrode using 101 becomes low. Even if the 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 applied to the battery (and changes in usage conditions such as altitude inferred from the sensor measurement values), 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 prepared for 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 odor, smell of fire, etc.) installed 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 to be in 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, it is intended to prevent the generation of a rapid internal short-circuit current due to the low conductivity of 101 and 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 on the conductor 101 and is a transistor, is constituted. 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] · 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, so the area that becomes a conductor is small. However, as shown in FIG. 11, by using 101P which may be a porous layer, 104 can be formed, or a second conductor 1012 can be formed on 101P and a carrier introduction layer 1042 can be formed on 1012, making it possible to increase the area and improve the conductivity of the conductor. (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. However, 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 state where 104 is formed with good conductivity 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 a carbon nanotube. 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 parts where current flows due to carriers in 101 including 104. 104 is a carrier introduction layer formed in 101. (It is the channel part of the transistor.)

[0039] <Increase in Interface> Pay attention to the interface where 104 that contacts 105 of 101 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 contacting surface of 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 of 104 as a conductor of 101P (conductor area A) 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 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 layer 1042 or 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-mentioned 101P to increase the surfaces where 104 and 1042 are generated, and as a result, the areas of 104 and 1042 as conductors increase, and the conductivity and the control width of the conductivity can be increased may be used for the conductor element 1, conducting wire, coil, motor, conductor sheet·film·foil, battery, 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 by 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 a perspective of increasing the conductivity of <101> and <104> by a gate electrode for use in conductor elements and electrode wires, and a 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>. · Also, there are combinations among the members constituting element 1 that cause chemical reactions, corrosion, and etching, and when this occurs depending on the polarity and the magnitude of the voltage, the gate electrode is set considering 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 the 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 the composite material 106. 106 is mainly an electrode wire for charging the capacitor part that forms the electric double layer, and for the purpose of giving the mechanical strength necessary as a conductive wire while achieving its purpose, a plurality of materials may be combined.) 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 101P and forming the film, 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 a gap with a material such as the sheet 101 or the thin wire 101 of 101 on which 105 is applied. (Just as the thin conductive wire of the mesh copper wire of the outer conductor of the coaxial cable is arranged to be 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. A plurality of 1WIREs may be used and made into thinner wires.) 5. When the 1WIRE is an insulated wire, apply the insulating coating 1COVER on 101. A plurality of bare wire 1WIREs may be bundled (while piling them up, 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 using the flat 101 in FIG. 11(A), it is better to use 104 and 1042 formed in (B) and (C) described in FIG. 11 in terms of increasing the surface area (conductive area A) of 104A per unit volume and improving the conductivity of the conductive element 1. Therefore, 101P may be used in the examples 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 a copper foil with an active layer such as a LiPo battery when implemented 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) utilizing 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, a magnetostrictive element with a configuration that generates a magnetic field with a magnetostrictive material and 2COIL and applies it to the magnetostrictive material can also be considered instead of the EAP and 1FILM. In Figure 6, for the piezo element that uses the 1FILM (and 1WIRE) of the present application for the wiring part of the longitudinal displacement type piezo actuator and the electrode part of the piezo element, it is the 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 (plus electrode) of 1FILM connected to the EAP drive line A and the source part (or gate part) of the beta (minus electrode) of 1FILM connected to the EAP drive line B to drive the EAP and piezo layers. · The electromechanical element that sandwiches the EAP and piezo in the configuration of Figure 6 with 1FILM can also be operated as an actuator, and can be used as a sensor that receives mechanical force due to the movement of humans or objects and generates electricity, or 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 utilize the present application. It is an explanatory diagram of a solar cell device (2PV) and a light emitting element such as an LED or laser diode that utilize 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 the conducting wire. The copper core wire portion of a coaxial cable-like cable is used as the gate electrode 106, which is covered by 105, and 105 is covered by a cylindrical 101 on the outer periphery. 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, it is only necessary to connect both ends of the 2-terminal element when connecting, which simplifies the extension of the conductor by the conductor element 1.

[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 of 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 cathode agent are applied to 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 applied to the outside thereof, and an active material 201 is applied to the outside thereof. · In the LiPo battery, when aluminum metal or a composite material of the metal and another material is used for the gate element, it is considered 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 the contact between 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, catch fire, or explode) it leads to preventing heat generation due to a short circuit, which may lead to improving the safety of the battery while 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) utilized in this application is stabbed by a metal nail (nail), and FIG. 10 is an explanatory diagram of 3BATT including the 2BATT, the protection sensor 3SEN, the gate driver 3CGATE, and the battery controller 3CBATT and its protection mechanism. In FIG. 10, the conductor element 1 of this application is used as the electrode foil for the 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, using 3SEN, a sensor value corresponding to the type of the 3SEN sensor 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 the control unit 3C and the 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, it controls the voltage applied to 106, causes 104 to disappear or generates 104I, increases the resistance value between the positive and negative electrodes of 2BATT to a high resistance, makes it difficult for a large current to flow between the positive and negative electrodes during an internal short - circuit, and aims to prevent the destruction (ignition and explosion) of the battery and make 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 "Explanation of Reference Numerals" section of this application specification, the system 3 using a sensor and the conductor element 1 can be utilized not only in the form of the battery system 3BATT but also in forms such as the wire system 3WIRE.

[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, can 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 can be used in the present application. (Semiconductor elements with a high bandgap such as aluminum nitride, or even insulators, can be used for 101 and 1012.)

[0055] <Ionic Liquid and Molten Salt> - In the creation of the present invention, it was difficult for individuals to procure ionic liquid reagents, so 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 are disclosed as an example, the introduction of the carrier is not limited to ionic liquids. As long as the carrier can be introduced into the material part 101 to form the carrier-introduced part 104. 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 forming 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 easy solubility of any substance, and can be cheaper 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 can be constructed using deep eutectic solvents. (It can be used as a medium for including the insulating layer 105 and the electrolytes of batteries, secondary batteries, capacitors, and electrochemical devices. It can also be used for the conductor element 1, the wire 1 WIRE, the battery electrode 1 FILM, the cable 12, etc. of the present application.) ● The configuration of the present application only needs to have substances, parts, and generation means necessary for generating an electric double layer formation at the interface between the insulating layer 105 and the materials 101 and 104. (As described above, it may be realized by other configurations not limited to ionic liquids.)

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

[0057] 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.

Industrial Applicability

[0058] The conductor element of the present application (element 1, component 2 and product 2 including element 1, system 3 of the element including a sensor) 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 section 1 whose conductivity can be turned on and off by a sensor (such as 3SEN etc. and a control section etc.). The function of the switch section can be used in 1WIRE, 1FILM, and battery 3BATT including 1FILM.

Explanation of Reference Signs

[0059] <<Transistor Portion>>1: Conductor element. (Since it is not limited to semiconductor elements, it is described as a conductor element). 101: Conductor or semiconductor. The material portion 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) (Conductivity-increasing type carrier introduction layer 104). 105: Insulator layer. ※ It may be the insulator layer 105 of a field effect transistor, or the insulator portion 105 that can be used to form 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 portion of the field effect transistor using an insulator or 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 conductor 101 of a carbon-based material. 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 portion where an electric double layer can be formed). 106: Gate electrode (G). (107: Protection layer). 108: Body portion (B). (Body terminal portion of a field effect transistor, MISFET). 201: Layer laminated on 101 (It may include a layer, material, or structure for realizing a certain function such as an active material layer of a battery, a semiconductor layer of a semiconductor element, or 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 conductor element 1. 3: System or device equipped with sensor 3SEN, control unit 3C, and gate drive circuit 3CGATE in conductor element 1 and components / products 2 using element 1, having the function of increasing or decreasing the conductivity of conductor 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, or 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 including the current collector or an electrode film including the 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 for which the ratio of the volume of the interstitial space to the total volume is sought. Different from 101 made of 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 interstitial space 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 voids 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 can be 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 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 described 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 1-2TER configuration, 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 in 1WIRE as 3SEN. <<Two-terminal element and three-terminal element>> 1-2TER: A two-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, and 3CGATE.) 1-3TER: A three-terminal conductor element 1. (A method capable of controlling 106 from outside 1.) <<Related to electrodes>> 1FILM: A film / foil / sheet using a conductor element. (Electrode foil / film electrode) ※1FILM can be used with the (A) or (B) of FIG. 1 as a wide plane, and one 201 can be laminated for each part of the gate electrode, which is a single-sided electrode type where either the front or back of 1FILM becomes the electrode, and as shown in (B) of FIG. 3, a double-sided electrode type where two 201s can be laminated for each part of the gate electrode (both the front and back of 1FILM become electrodes). 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 controlled by an electrode and causing 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 Electric 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: Layer for transporting holes. 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: Layer for transporting electrons. 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 a high resistance 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 in series. (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, and deform, and the contact of the electrodes occurs, the short-circuited part may be regarded as the part of the nail.) <Explanation 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 and 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 and 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 and communication means of 3C. It may be possible 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. (It may be possible to communicate and exchange the control method, program, algorithm, and control variables of the gate electrode of 3C by C1 through communication, and make changes and updates.)In addition, for the maintenance and inspection of 3 such as 3BATT, regarding C2 that can access 3C, it may be commanded to turn on or off the gate electrode from C2 to 3C, or commanded to change the voltage value or polarity. ). C1: A computer or the like that uses 3BATT. For example, it is an in-vehicle computer C1 that controls an automobile, is equipped with an in-vehicle camera CAM of the automobile connected thereto, captures the external environment from CAM, and detects automobiles and 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 crashes with a sensor before crashing. Detect a fall (or have a measuring means for sensing a fall and detect a fall), increase the resistance of the battery to a high resistance, which may lead to preventing the battery case from being damaged during a fall and the positive and negative electrodes from short-circuiting internally, resulting in a fire or explosion.). When there is a risk of damage to 3CBATT of C1, send voltage control data / commands for the gate electrode to lower the conductivity of the battery electrodes to 3C (3CBATT) of 3BATT, and control so that the electrodes are in a state with low conductivity. (When an automobile including C1 and 3BATT collides and 3CBATT is damaged, causing an internal short circuit, increase the resistance of the electrodes of 3BATT 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> - The example of FIG. 10 is to provide a sensor and a controller in a battery using a conductor element 1, control the gate drive circuit with the controller according to the value measured by the sensor, 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 to decrease the conductivity. The said configuration can be used not only for a battery but also 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 (3-axis acceleration sensor), a magnetic sensor, a temperature sensor, a humidity sensor, an air pressure sensor, a pressure sensor, a strain sensor, a contact sensor / touch sensor, an illuminance / light sensor, an infrared sensor, a camera / scanner / image sensor, an olfactory sensor, a fire sensor / smoke sensor, a sound sensor, a wireless sensor (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 an external computer C2 through wireless or wired communication via 3COMM of 3C.<Temperature Sensing Element>·For example, 3WIRE includes a temperature sensor 3T, a control unit, and a gate drive unit. 3WIRE may detect, using 3T, the heat during a leakage fire or the temperature rise due to heat generation before a leakage fire occurs, and 3WIRE may detect the temperature rise and perform control to increase the resistance of the conductor wire, making it difficult for current to flow, which may be considered a way to prevent a fire. During a building fire, the 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 room, etc. where the fire origin is located. (It may be possible to configure 3WIRE like a resistance-increasing type fuse element with 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 wire based on the direction of gravitational acceleration) can be configured.·Power distribution networks and transmission networks are constructed by using utility poles to stretch wires horizontally or sagging as overhead lines for power supply. Wires for tram applications and telecommunications are also stretched. In the above system (where the wires are not underground but in the air and will sag when cut), it is possible to see a scene where the wires stretched using utility poles are cut by a typhoon, fallen trees, etc. and fall down following gravity. The sagging conductor usually has a copper or aluminum part, and the conductivity of the metal part does not change due to sagging or inclination and is always a conductor, so electricity can flow even in the sagging state.·Therefore, when the 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.·The 3WIRE including the acceleration sensor 3A of the present application configuration measures the acceleration change or the acceleration during sagging when the wire sags due to gravitational acceleration, the 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). When it is determined as a result that it is hanging down, the gate 106 may be controlled to reduce the conductivity of 1WIRE or 3WIRE. · Alternatively, for conductive 1WIRE, 3WIRE (and 1FILM, 3FILM), a tilt sensor (using an acceleration sensor) may be provided, and control may be performed to increase or decrease the conductivity according to the tilt of 1WIRE, 3WIRE (1FILM, 3FILM).

[0060] <<Contents of the previous priority claim application, Japanese Patent Application No. 2023-007722>> This application cites Japanese Patent Application No. 2023-007722. The specification and drawings (Figs. 1 to 12) described in paragraph 0060 of this application are the same as the description and drawings of the drawings described in Japanese Patent Application No. 2023-007722. Figs. 1 to 12 described in paragraph 0060 of this application correspond to Figs. 14 to 25 described in paragraph 0037 of the "Brief Description of the Drawings" section of this application. <Document Name>Specification <Name 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 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 with power and energy demands on the ground. <0004><Wireless Power Transmission System> Therefore, wireless power transmission, wireless power transfer, and wireless transmission, which transmit power from SSPS through space and air to the ground as in Patent Document 1 and Non-Patent Document 1, are being 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, and their laser light 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-site near SSPS or manufactures fuel substances, energy storage substances, and objects on-site and transports them to the ground or the like without using wireless power transmission or wireless power transfer. ● It is preferable if the power generated by SSPS can be used on-site after generating power in space, a space base, a lunar base, etc. As a case of using it on-site, for example, as shown in FIG. 3 and FIG. 4, a system that uses power on the lunar surface (or in space) to manufacture some kind of fuel and deliver 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 is reduced, 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 marking means 9 for marking parts and base materials for the construction of SSPS. ● Since this application is not an invention related to the marking means, details regarding the marking means such as a mass driver are 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 on the ground are oxidized by some method 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. 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 in the system using SSPS in Fig. 4 of this application. <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 metal silicon mixed with silicon, polysilicon, and impurities that is not of solar cell grade (when not 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 energy utilization 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 utilizing solar cells and solar energy can be manufactured using the solar cell material. <0012>When launching from the ground, a resource-saving material that is a direct-transition type with a large absorption coefficient and requires a thin photoelectric conversion layer and functional film for photoelectric conversion (examples of such materials: compound semiconductor materials, used in CIGS solar cells, etc.) can 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 Transmission Method>This application discloses an energy transmission method including wireless power transmission, wireless power transfer, wireless power transmission, wireless transmission, and fuel transportation. 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 has been 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 devices, and communication devices 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 can be increased, and even with low transmission power, reception and light reception can 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 lasers). (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 worrying 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 a residential 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 worry people. ● Thus, there has been an issue that 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 the 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 for photons that do not penetrate the atmosphere, in order to 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), 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 and Fig. 2 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 with low atmospheric density. Laser light having a wavelength of photons that do not penetrate the atmosphere, transmitted, emitted, irradiated, or launched from a transmitting unit 1 / luminescent unit 1 (SSPS and an SSPS relay satellite 1LINK that links laser light from the SSPS, and a transmitting unit 1 / luminescent unit 1 that may be included in a plurality of SSPS and a constellation of SSPS relay satellites) arranged in outer space, is emitted, irradiated, or transmitted toward the receiving unit 2 / light-receiving unit 2 (or the laser light of the light-emitting unit 1 is made to hit, be received, and undergo 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 technology> 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 terms of the achievements of aircraft, there is an example of raising a balloon up to an altitude of 53 km with 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 are present as in the case of 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 stratosphere 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 near 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 oxygen, nitrogen, etc. 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 with oxygen and ultraviolet rays to reach the light-receiving part without attenuation in the radiation when reaching the light-receiving part, it is more preferable to be on the upper layer side of the stratosphere at an altitude of 32 km rather 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 as in the examples of FIGS. 1 and 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 allowed is also conceivable.) <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 (altitude 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, and the configuration that uses photons that are difficult to transmit through the atmosphere in the present application 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 arranged. The present application discloses using photons such as ultraviolet photons of oxygen, ozone, etc., or ultraviolet rays and some infrared photons absorbed by the atmosphere as photons and 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 photons, for example, in the present application, some cases of photons with a large energy of a single photon and on the short-wavelength side closer to ultraviolet rays that can be absorbed by the atmosphere, oxygen, or ozone are disclosed. Also, in the wavelength range of infrared rays, there are wavelengths absorbed by atmospheric molecules, and photons of the above 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. By using photons that are difficult to reach the ground and preventing photons escaped by the light-receiving unit 2 due to accidental emission 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 cause the aircraft 3 to move, change direction, and move, such as attitude control and propulsion, in addition to the motor and jet engine, the aircraft 3 may be equipped with a propulsion device 3TH such as a rocket, photon sail, or ion thruster. (The aircraft 3 in the present application may be the aircraft 3 that is a solar plane as shown in the configuration of 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 the 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 the aircraft 3 or the 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 the 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 (atmosphere at an altitude of 20 km to 50 km or more from the ground), such as UV-C or 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 the photons of the laser light may be short-wavelength photons such as near-ultraviolet UV-C (wavelength 280 - 200 nm), far-ultraviolet (200 - 10 nm), vacuum ultraviolet (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 the photons has the advantage 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 photoelectric 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 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 an advantage 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 or 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 photocatalysts or chemical reactions between light and substances 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 in 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 with 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. Disclosed is the search for tags from the aircraft 3, and transmitting the energy from the SSPS by laser light or radio waves and searching for tags from the aircraft (using it for monitoring). <0032> In the present application, the wavelength of the photons to be used and the absorption attenuation of the photons in the atmosphere are utilized in a fail-safe design in which photons do not reach and attenuate in the residential areas 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 house rather than the receiving unit 2 due to misalignment of the transmitting unit 1 or the like, the photons have a short wavelength, for example, photons from UV-B, UV-C to X-rays act on atoms and molecules, and for example, cause chemical reactions with atmospheric molecules and atoms (ozone generation in the case of UV-C) while being attenuated and absorbed by the atmosphere, and are photons that are absorbed by the atmosphere and do not reach the ground (the photons reaching the ground can be reduced). By assuming that photons do not reach the ground, safety is ensured for fixed-wing aircraft in the troposphere and houses and living organisms 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, mid-wavelength ultraviolet, and short-wavelength ultraviolet light 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 semiconductor light-emitting devices 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 infrared laser wavelength of 1064 nm by Nd:YAG crystal to ultraviolet light of 266 nm is assumed.), or an excimer laser device (for example, generating photons of UV-C with a wavelength of 248 nm when using KrF), a vacuum tube device, etc. may be used. <0036>Photons with short wavelengths such as the aforementioned UV-B, (UV-A,) UV-C, far ultraviolet light, vacuum ultraviolet light, X-rays, gamma rays, etc. may be generated in the light-emitting unit 1 and the transmitting unit 1, emitted, irradiated, and transmitted toward the light-receiving unit 2 and the receiving unit 2, and photoelectrically converted by the light-receiving element 2PCE provided in the light-receiving unit 2 and the receiving unit 2 to obtain electric power. ※Since this 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, generating hydrogen from water in the light-receiving unit 2, reducing carbon dioxide on the ground to carbon, hydrocarbons, and oxygen. In the light-receiving unit 2, the laser light is photoelectrically converted and used as power for 2, aircraft 3, transportation equipment 3, flight formation 3FORM of airplanes, flying cars 3FCAR, robots 3.) <0038>●As shown in FIG. 6(a), the electric power photoelectrically converted 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 3FORM including the aircraft 3 to move them. Also, 3 may be able to communicate with the things included in 3FORM such as 3A1, 3L1. Energy and power may be shared and loaned among the things included in 3FORM such as 3A1, 3L1 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 the aircraft can be used to transport passengers and luggage. <0040> As shown in Fig. 6(b), the aircraft 3 is provided with the light receiving unit 2. After appropriately charging the secondary battery such as the lithium ion battery of 3 by receiving the photons in the air so that the whale can breathe, it is lowered 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 by a smartphone terminal (summoning 3 from the air to the ground by a smartphone). ● It may also be used for monitoring operations. For example, it may be used for monitoring the movements and intimidation of wild animals in mountain villages suffering from wild animal damage, or for town security. <0041> In the case of 3 which is an unmanned aircraft, even if 3 encounters an accident, since there is no crew, the damage can be reduced. Also, the unmanned aircraft 3 can be positioned by GNSS or the like and perform known automatic driving as in the case of a drone or an autonomous vehicle. In addition to automatic driving, it can perform unmanned (programmed) formation flight 3FORM, or can be used for flying robots 3ROBOT for performing operations in the fields of agriculture, forestry, fisheries, and various industries, vehicles for passenger transportation, and housing, residence, and real estate operations such as an air hotel or an air station (an in-air stay facility / base like a space station). <0042> ● According to the present application, the aircraft 3 (this 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, and reduce / eliminate the time when the aircraft 3 returns to the ground and waits. <0043> ● Even when the ground airport does not function and it is not possible to stay at the airport or replenish fuel, in the system using 1, 2, and 3 of the present application, 3 can be charged / energized 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 replacing each other 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 and the charging / energy supply can be performed, the flight distance can be extended.● In FIG. 10, for example, a conceptual diagram is disclosed of a concept in which, from Japan, 3·3FCAR flies while receiving energy supply by the present application 1 and 2 over the Pacific Ocean, the Atlantic Ocean, or the sky over the ocean near New York on the way towards Uruguay near the back side of Japan, and transports passengers. (Even without landing on the ground for charging and refueling, it is possible to charge and supply energy at any time by 1, 2, and the photons, increasing the cruising range of 3FCAR) <0045>● In the configuration of FIG. 6(a), a device (3FORM-ACTING) that uses 3FORM to perform 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-like limbs and a torso by the formation mechanism for shows or something. A configuration using the 3FORM formation for a humanoid robot 3FORM-HUMANOID that can be used for labor, monitoring services, transportation services, entertainment, and robot competitions may also be disclosed. <0046>● The 3FORM-HUMANOID may be an aircraft and can be a somewhat large humanoid robot with little concern for its own weight, or it may be configured as a humanoid or object such as a puppet that imitates a human, an animal (such as a tiger, rabbit, zodiac animal, lion, dog, cat, etc.), a plant, a fictional creature (such as a dragon), or a character. ● In this case as well, by using the SSPS and 1 and 2, it may be possible to eliminate the need for charging and energy replenishment on the ground and enable continuous missions in the air. <0047>Photons in the ultraviolet to X-ray region have more 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. (For 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 above 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 absorption by the atmosphere 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, may 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. may be used. It is necessary to select the wavelength of the photons during actual verification. Although the present application discloses a system of photons absorbed by the atmosphere (such as oxygen and ozone), 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 to the ground using a system consisting of radio waves or lasers (a system of only photons) from space to the ground. Further, Non-Patent Document 4 discloses that energy is transmitted to the ground by a laser with a wavelength of around 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 power transmission line can be obtained up to the stratosphere with a cable, a method of converting electric power energy into chemical energy - fuel and delivering it is disclosed in FIG. 2. Further, FIGS. 3, 4, and 5 are disclosed as systems using fuel. Other forms and explanatory drawings 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 hangs 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 and the power transportation and fuel transportation using the structure, electric wire, and cable for the construction of the SSPS and the energy obtained by the SSPS. 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 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 compared to the so-called orbital ring and orbital elevator of Patent Document 2. <Prior Art Documents> <Patent Documents> <0054> <Patent Document 1> JP-A-2004-266929 <Patent Document 2> JP-A-2023-001372 <Patent Document 3> JP-A-2022-058853 <Patent Document 4> JP-A-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 energy for wireless transmission and power transmission are transmitted to the ground.In that form, even if the transmission power can be reduced, 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 for wireless power transmission by SSPS while ensuring the safety of people on the ground by limiting the photons transmitted by the transmission unit 1 to those with wavelengths that are easily absorbed by the Earth's atmosphere and operating in this way. <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 wavelengths of photons that are absorbed by chemical reactions such as oxygen and ozone in the atmosphere and are not transmitted by the atmospheric window, and the transmittance of which to the atmosphere is close to zero. <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 will diffuse and energy cannot be transmitted efficiently. 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. High-energy-density radio waves 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 unit 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 substances combined with oxygen (such as silicon oxide, aluminum oxide, iron oxide, water, etc.) among the lunar resources are reduced and dropped to the Earth as shown in FIG. 4. <0064> <Third problem, problem in the embodiment> <Hitting the photons of the light-emitting unit 1 to 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 hit the laser light from 1 to 2.<0065>As shown in FIG. 10, for example, when irradiating a plurality of 1 (a plurality of 1s included in the constellation of a plurality of 1SSPS-SATs) with an ultraviolet laser and the laser hits a target or misfires, although the design is such that the laser is attenuated by oxygen, ozone, and the atmosphere, energy is lost during misfiring. Therefore, a method for hitting the target without misfiring was required.<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 is configured such that 1SSPS-SAT always passes over Japan and can always irradiate photons to the light-receiving unit 2 on the ground and air side while being replaced. Also, similar to the 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 may communicate with 1SSPS-SAT or 1SSPS-SYS-QZSS-SEIZA by laser or radio wave, and 2 and 2POSI and 1SSPS-SAT or 1SSPS-SYS-QZSS-SEIZA may be equipped with the 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 on 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 provided with 2POSI using the 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 arranged, 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 a base or fuel tank 4STAT on the ground or at sea) in the ocean where there is demand. It may be transported from 4STAT to the ground 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 lifting only by itself.) <0072> ● The aircraft 3 can receive energy from the SSPS and use the energy for lifting both during the day and at night. It can fly in the troposphere or stratosphere. At this time, if the aircraft 3 can hold the cable and maintain the forces such as buoyancy and the force to maintain altitude during flight, and 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. Note that it is preferable that the electrical wiring members such as the cable and electrodes (motor and coil if a propeller is required) of the aircraft 3 used in the present application are lightweight. <0073>● Also, in the case of FIG. 5, it can meet the demand for not wanting to arrange 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 or 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 or 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 or 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 conversion to chemical energy) and used for transportation equipment, passenger transportation, work by robots, shows, formation flight, balloons, advertisements, and entertainment, the chemical energy conversion loss can be eliminated, which is considered important. Therefore, FIGS. 6, 7, 8, 9, 10, and 12 disclose usage examples of the aircraft 3. <0076><<When transporting the power and energy of SSPS to the aircraft 3 including 2 and using it not for ground use but for in-air applications>> An aircraft requires energy for flight and movement. Jet engine-powered aircraft 3, drones 3DRONE, or aircraft formations 3FORM powered 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 have a longer operating time, the performance of the aircraft body is restricted due to the limitation of the charging amount 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 of aircraft that can be constantly powered and operated using the aircraft 3, or a humanoid device or humanoid robot 3FORM-HUMANOID, 3FORM-DOLL(MACHINE) composed of formation flight, or a robot 3FORM-ACTING, 3ROBOT that moves with them, and further a 3FORM-AD-BALLOON used for advertising and 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 and product management, and beacons and tags for searching for lost hikers or people caught in avalanches during mountain climbing are well-known. Monitoring devices and wearable devices 2TAG for monitoring children and dementia patients are also well-known. However, there may be problems with the method of supplying power to the tag to move it 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 perform wireless communication and sensor operation beacon operation. <Means for Solving the Problem><0080><First Means for Solving the Problem>● 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, the transmitting unit 1 and the light receiving unit 2, the receiving unit 2, and the light receiving unit 2 is arranged at a high altitude, an altitude where it is difficult to absorb the short-wavelength photons, on a transportation means 3, a transportation device 3, an arrangement means 3 such as an aircraft 3 or a flying boat 3, so that the light receiving unit 2 can receive the photons from the light emitting unit 1. The light emitting unit 1 and the transmitting unit 1 may use an ultraviolet laser or a device for generating radiation light (generated using a particle accelerator and an undulator, etc.), and the operating power and energy thereof 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, among the lunar resources, substances combined with oxygen (such as silicon oxide, aluminum oxide, iron oxide, water, etc.) are reduced by the electric power from the solar power generation of SSPS and solar energy and then dropped to the earth. <0086> Fig. 10 is an explanatory diagram of the laser beam when irradiating the plurality of light-emitting parts 1 to 2 in the quasi-zenith orbit group in the present application, the focus of the laser energy, and the laser attenuated by the atmosphere. Also, an explanatory diagram of 3FCAR and 3 that receive energy replenishment by the energy transportation method of the SSPS in the present application on the way to a remote area is described. <0081> <Second problem-solving means> As shown in Fig. 2 and Fig. 5, a system that uses fuel instead of electric power or light when transporting energy from the light-receiving part 2 in the air to the ground part 4 and the user side 6 is proposed. 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 including the light-receiving part 2 and an aircraft 3FUEL for fuel synthesis that can be connected are connected using a connection line or a 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. Then, 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 an 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 through the light-receiving part 2 and the aircraft 3 to the ground part 4 and then using it on the user side 6, the energy is delivered to the user without using wireless power transmission and power transmission between the ground and space. <0082> <Third problem-solving means> Examples are described in Figs. 6 to 9, etc. as the uses during wireless power transmission.In FIG. 6, an aircraft 3 that can be constantly powered and operated using the aircraft 3, a formation flight group 3FORM of the 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 the 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 the humanoid robot perform formation flight while a robotic arm with an additive manufacturing nozzle 3A1-AM for painting is attached, and a painting operation is performed while firing paint bullets from the paint nozzle (description of the firing of paint bullets) is described. A figure showing the 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 shown in FIG. 8(b). ※ There may be a configuration of a competition, exhibition, or show that sprays paint bullets 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 or 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 section 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 (operated using the SSPS) can generate a force to counteract gravity for ascending, as well as forces for movement, flight, and propulsion, and can be used for the operations of ascending, floating, propelling, flying, and moving 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 enable wireless communication and the operation of sensors and beacon operations. <Advantages of the Invention> <0088>● While miniaturizing the light-receiving unit 2 and the receiving unit 2, the photons of the light-emitting unit 1 and the transmitting unit 1 are photons of a wavelength that is likely to attenuate 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 unit 2 to the ground, by using a system that uses chemical energy and fuel to eliminate the concerns about the weight of electric wires and the large area of the user-side receiving unit and the permeable radio waves in wireless power transmission, it may be possible to overcome the problems of power transmission by wireless power transmission, electric wires, and cable power transmission and deliver the energy produced by the SSPS 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 unit 2 can operate by receiving the energy supply from the SSPS, reducing the steps of refueling 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 holds, containers, trays, product shelves with a weight measurement function, as well as for 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 transport 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, and the aircraft 3, ground unit 4, user 6, clouds, regions of the troposphere and stratosphere, etc. (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 with 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 metals 5M and reduced substances 5MC, and transporting the metals 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 space vehicles (1SSPS - SAT) of the SSPS deployed in a constellation in the quasi - zenith orbit (QZO) are forming 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 (constantly) and operated using aircraft 3, or a humanoid device composed of formation flight, or a humanoid robot. It is an explanatory diagram for taxi and cargo transportation applications. (Example 5) <Figure 7> It is an explanatory diagram when power and energy are delivered to tag 2TAG by wireless power transmission of aircraft 3 and drone 3DRONE to manage the objects pasted with tags. (Example 6) <Figure 8> It is an explanatory diagram of a robot exhibit imitating a creature formed by 3FORM. (Example 7) <Figure 9> It is an explanatory diagram of an unmanned flying robot 3 equipped with a robot arm and tools (e.g., saw). (Example 8) <Figure 10> In this application, it is an explanatory diagram of the laser beam, laser energy focus, and laser energy scattering after passing through the focus during laser irradiation from a plurality of light emitting parts 1 in the quasi-zenith orbit group to the light receiving part 2. (An explanatory diagram of the claim that it is difficult to deliver energy to a house on the ground during laser irradiation in this application) <Figure 11> It is an explanatory diagram of a 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 an 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> It is an explanatory diagram of a water supply device 3 and a method of using water in which water collected by rainfall, rain, or snowfall or water supplied from 4H2O on the ground is input into 3 that may be equipped with a light receiving part 2 and delivered to places where water is needed, places to be extinguished, etc. (Example 9) <Mode 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 Wavelength> Figures 1, 2, and 5 are Example 1 and Example 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. It is preferable that other microwaves of the laser can also be turned on and off in the same way. ※ Note that, like 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 guidance 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. Water is electrolyzed and decomposed by 3 and 3FUEL that receive power and energy from the light receiving unit 2 and 2 to generate hydrogen and oxygen. Hydrogen may be stored in a tank inside the aircraft, transported to the ground, and stored and used in the ground tank 4. When in 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. Iron oxide is delivered from the ground to the light receiving unit 2 by the aircraft, and the iron oxide may be reduced by 3FUEL that receives power and energy from the light receiving unit 2 and 2. <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 and 2, in order to perform hydrogen ironmaking (hydrogen reduction ironmaking), water and iron oxide may be sent from the ground to the light receiving unit 2 by the aircraft 3FUEL. Using the energy for reducing water 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 and iron have the advantage that, for example, pressurization like a hydrogen cylinder is not required during transportation by 3 and can be handled at normal pressure. In order to produce iron by hydrogen ironmaking, 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, and 3FUEL, iron and oxygen can be produced in 2, 3, and 3FUEL by introducing iron oxide into the hydrogen ironmaking 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 hand warmer that oxidizes iron. There are also advantages in the large resource quantities 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 water / hydrogen, carbon dioxide / hydrocarbons>> In a system using water / hydrogen, a carbon dioxide / carbon source may be introduced to reduce carbon dioxide and produce hydrocarbon-based synthetic fuels. Carbon-based materials may be produced from carbon dioxide. ● The carbon dioxide stored and preserved on the ground is transported to the light-receiving unit 2 and the aircraft 3 system by 3FUEL or the like, and the carbon dioxide is reduced using energy that may also be derived from SSPS, separated into carbon and oxygen, and used to reduce carbon dioxide on Earth. ● In the systems of 2, 3, and 3FUEL, carbon dioxide may be separated from the air and the carbon / carbon components may be separated from the carbon dioxide to recover carbon dioxide in the atmosphere. For separation, known methods such as absorbing carbon dioxide in monoethanolamine, gas membrane separation, or cooling the air for separation may be used. <<Separation of atmospheric components from the atmosphere>> ● In the systems of 2, 3, and 3FUEL, the energy from SSPS is 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, the energy that may also be derived from SSPS may be used to separate and recover components constituting the atmosphere, such as noble gases like helium and neon, oxygen, nitrogen, and argon. Further, the separated and recovered noble gases may 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 the air for fractional flow may be used to separate the components of the atmosphere from the air. <<Production of ammonia>> For example, ammonia NH3 may 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 and drive the propulsion device 3TH, or the 1HNU received by 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 to heat and inject the propellant to drive 3TH. The 3TH including the light-receiving unit 2 and the transportation device 3 may be configured to float, levitate, or be propelled by the energy obtained by 2. <0096><<Floating and Propulsion of 3>> 3 may be propelled by using rockets, propellant injection, 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 is propelled by the reaction of emitting and reflecting photons such as rockets, propellant injection, ion thrusters, or photon sails. ● The 3 of the present application may be arranged and floating in the air by jetting or reflecting the photons or charged particles toward the ground and using the reaction. Thrust in the direction opposite to the direction of gravity may be generated by using rockets, propellant injection, 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 so as to balance gravity and its own weight in the sky and can 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 the configuration of Non-Patent Document 4 is adopted 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 also be a 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 light-receiving unit 1POSI-PL of the light-emitting unit 1 on the space side or SSPS side. The laser light-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 these, 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 have 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 located, 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 other systems, for example, a satellite 1LINK arranged in outer 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 QZSS positioning device, 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 etc. and 1 etc. (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 provided 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 from 1 on and off. For example, 1 may check the operation status, operation schedule, orbit information, and date and time of other artificial satellites and space crafts through the external Internet from 1CON, 1LINK, etc., and when a space craft etc. comes on the radiation line during the photon irradiation from 1 to 2, it may perform control to turn off the photon irradiation. For example, 1 turns the laser on and off under the control of 1CON.<0100><Supplement: Laser Irradiation on 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 arranging 1 in a certain orbit and irradiating a laser towards 2 in the stratosphere and the air like 1DBL in FIG. 10, if the spacecraft exists in the radiation from 1 to 2, the laser is turned off, and if the space debris passes through, it remains on, so that the debris is irradiated with 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 is an explanatory diagram of the case where metal oxides and oxides on the lunar surface are reduced 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 the metal 5M (or compound 5MC) is transported to the ground. (On the lunar surface, in addition to the metal oxides, when 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 in 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 and stations, or 5O2 may be introduced into the earth and used as terrestrial oxygen 4O2.) <0103>As a modification of Fig. 4, silicon oxide is 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 silicon-based compound 5MC in the fluid, such as silane (gas), silicon tetrachloride, or trichlorosilane (a raw material for crystalline silicon and a liquid). The 5MC of the fluid passing through 5PIP can be sent under pressure by a pump or the like. <0104>For example, 5MC may be transported as a fluid 5MC in the pipeline 5PIP and then converted to metallic silicon 5M at the conversion units 1CHEM1, 1CHEM2, and 1CHEM3 by chemical reactions. For example, from 5PIP to 1CHEM3, it may be transported as a fluid 5MC, and from 1CHEM3 to the launching device or dropping device 9 and the terrestrial 5TANKM, it may be converted to metallic silicon. (Also, when it is acceptable to transport 5MC instead of 5M to the ground, for example, 5MC may be loaded on 5TANKM instead of metallic silicon or the like 5M.))<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 multiple 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 of SSPS satellites 1SSPS-SYS-ORBIT formed in an orbit in space, or a constellation of 1SSPS-SYS-GEOS in a geostationary orbit, or a constellation of 1SSPS-SYS-MOON or a group of 1 in the vicinity of the moon to the ground. When energy and power lasers, signal lasers, etc. are sent from 1 connected to SSPS to 2 in the air (when communicating), a relay satellite 1LINK may be provided. ※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, or an optical component section 1OPT (or optical system 1OPT) such as a lens. Also, a relay satellite 1LINK equipped with a light receiving section 2, a light emitting section 1, and means for operating them may be used. ※1LINK and 1OPT correct the laser beam flux 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 beam flux with 1OPT, and / or reflect the beam flux with 1MRR towards 1LINK, 2, etc., and deliver it to the next relay satellite 1LINK or the light receiving section 2 in the air. ※1MRR is not limited to use in 1LINK. For example, for the solar cells of 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 irradiation of a laser from a plurality of 1SSPS-SATs on the quasi-zenith orbit to the light receiving section 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 also a plurality of constellations 1SSPS-SYS-SEIZA may be used to supply and power energy derived from SSPS to 3 including 2. Energy derived from SSPS may be supplied and powered to 2 and 3 from a plurality of 1 at different orbits and locations of the light-emitting part (constellations in LEO and constellations in geostationary orbit GEO·QZO, lunar surface, etc.). ● For example, in Fig. 10, the concept of using 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 to supply energy to the aircraft 3 during long-distance transportation or passenger transportation in the intermediate section (over the high seas in the ocean, etc.) 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 groups 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 the laser irradiation may be performed from the light-emitting part 1 to the light-receiving part 2. <0108>● The quasi-zenith satellite system QZSS·positioning device QZSS, i.e., 1SSPS-SYS-QZSSーSEIZA, may be used. The 2POSI of the light-receiving part 2 and the 1SSPS-SYS-QZSSーSEIZA, which is also the positioning device QZSS, may be used to measure the positional relationship between each 1 and the light-receiving part 2·2POSI. ● The 2POSI of the light-receiving part 2 and 1SSPS-SYS-QZSSーSEIZA or 1 may perform wireless communication·laser communication, and the position information of 2, etc. and 1, etc. and other data necessary for the energy transportation·transportation of the present application may be transmitted and received by 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 this application, the light-receiving unit 2 may be provided with positioning means for facilitating the hitting of the light-receiving unit 2 with a laser from the light-emitting unit 1, and 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, a constellation 1SSPS-SYS-ORBIT of a plurality of 1SSPS-SATs orbiting in a low earth orbit (LEO) can also perform laser irradiation from 1 to 2 (laser irradiation from the light-emitting unit 1 of each 1SSPS-SAT to the light-receiving unit 2, communication between the light-receiving unit 2 and the light-emitting unit 2, and positioning) in the same manner as in the case of 1SSPS-SYS-QZSS-SEIZA.)<Example 5><0111>FIG. 6 and FIG. 10 are explanatory diagrams of an aircraft group 3FORM / formation flight group 3FORM of aircraft that can be powered (constantly) using the aircraft 3 or taxi / cargo transportation / passenger transportation by the aircraft 3 or the 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 the communication network of the terminal or 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 branch trimming machine) from a location away from 3 via a communication path such as the Internet.<Example 6><0112>When attempting to monitor a person or object to be monitored using 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 this application, while searching for 3DRONE and 3 for 2TAG, wireless energy is irradiated from the 3DRONE to the 2TAG by wireless transmission to charge the 2TAG and cause it to perform beacon operation / wireless communication operation, and to search for the attached object 6OBJECT (6OBJECT-TAG-ATTACHED) is disclosed.Use 3 or 3DRONE as the tag scanner 6TAG - SCANNER, let the transport device 3 search for 2TAG, and when 3 approaches 2TAG, wirelessly charge 2TAG to perform wireless communication and beacon operation 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, and 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. 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 / acceleration sensor. For example, when a 3DRONE or a robot car 4CAR circulates while charging a 2TAG with a load sensor equipped 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 outside via the communication network. 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 shoes as related applications), the method and configuration of the wireless power transmission shown 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, HMDs, covers, helmets, gloves, watches, bracelets, rings, jewelry, ornaments, mobile terminals, etc., and the method and configuration of the wireless power transmission shown 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 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 by a 3DRONE driven by a 3DRONE or an SSPS, and the sensor unit, wireless communication unit, and beacon of 2TAG may be operated. ● When 2TAG is used for 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 on the sole of the foot during walking may be measured, and walking 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 GPS, GNSS, QZSS, or other positioning means by receiving signals from satellites or wireless stations, 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 positions. 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 tags. 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 the systems 1, 2, and 3 of the present application are added to the 2TAG and 6TAG-SCANNER systems in the sky as shown in FIGS. 6 and 10, it is also an airborne 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 formation flight and inter-aircraft cooperation in which energy sharing can be carried out by energy sharing means such as a wireless transmission device 3WEP. Although Figure 7 describes monitoring a single 3, an aircraft group capable of energy sharing between aircraft may also be used in Figure 7. For example, 3 equipped with 2 may be arranged in the upper airspace on the stratosphere side, 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 above 3, may be periodically connected for energy sharing and replenishment by charging and fuel replenishment. <Example 7><0117>Figure 8 is an explanatory diagram of a humanoid robot 3FORM-HUMANOID with a robot arm in a stationary state and an operating state (during flight or operation of the robot arm) in which an upper body type aircraft 3 and a lower body type aircraft 3 equipped with tools, instruments, and various devices can perform 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 communicating with an external wireless station or communication network, or may be equipped with computer-related devices such as a computer processing device, storage device, and 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 robot arm, motor, actuator, or 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 robot arm of an aircraft 3 or an aircraft 3 (3ROBOT), additive manufacturing is performed on 4WK-AM of a work target object 4WK, and subtractive manufacturing is performed on 4WK-RP. Further, 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 robot arm and a saw, cutting part, or grindstone, which may be 3A1-RP. ● In this application, it is powered by the energy of SSPS and operates. Even when 4WK exists in a place where it is difficult to work for a machine that moves on a human or land such as the side surface, slope, or cliff of the aircraft 3, it can be accessed by the aircraft 3ROBOT. (It may also be a high-altitude working device 3ROBOT.)It may also be used for monitoring and working on 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 perform continuous 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 ground 4H2O 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>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. (※ This application is based on an invention. It has not been verified at the time of filing.)<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 be 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.<Description of Reference Numerals><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 light-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 or chemical energy utilization type power plant, a large-scale battery, or a nuclear power-related power plant.)1PV: Solar cell (※1PV may be a 1PV launched from the ground, or a 1PV manufactured from raw materials sourced from celestial bodies such as the moon and then manufactured near the place of use using the in-situ vacuum in space.) 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 plant. 1SSPS - ETC: Other series of systems and component groups related to 1SSPS. 1SSPS - SYS: Series of systems of the space solar power plant. (1SSPS - SYS - QZSS: SSPS that is also QZSS (QZSS: Quasi-Zenith Satellite System). 1SSPS - SYS - GEOS: Space solar power generation system in geostationary orbit (GEO). 1SSPS - SYS - MOON: SSPS on the lunar surface or near the moon in 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 (such as an asymmetric figure-eight orbit when arranged over Japan) 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 such 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 made 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 closer to the ground than the quasi-zenith orbit or the geostationary orbit, and can reduce the length of the distance (in 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 (tens to tens of thousands are also possible) 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 such 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 made 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 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 through 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 portion 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, etc. in the atmosphere when the laser is directed outside the receiving unit 2 (ground direction) due to misalignment of the transmitting unit 1, etc., 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 from n units (a plurality of units) of 1SSPS-SAT or 1SSPS to one receiving unit 2. By using the plurality of units, the output of n units of 1SSPS-SAT to the receiving unit 2 can be reduced and dispersed from X watts in the case of one unit to X / n watts, reducing the energy of the laser emitted by each 1SSPS-SAT, reducing the output of the energy irradiated to the ground, and protecting the safety of people on the ground. (Regarding the light-emitting unit 1 of the present application. Instead of the light-emitting part 1 of a single SSPS satellite, a plurality of SSPS satellites equipped with the light-emitting part 1 are flown in formation to form a constellation. By irradiating the light-receiving part 2 with a laser while dispersing the light-emitting part 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 arranged in a quasi-zenith orbit or LEO to form a 1SSPS-SYS-SEIZA. When irradiating the light-receiving part 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, at the point of FCS-2, n×X watts (nX watts) can be received. On the other hand, at a point outside the focal point 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, which is outside the focal point FCS-2 and is about to go through the stratosphere and troposphere towards the ground, is below X watts and lower than the nX watts of the focal point FCS-2. Thus, it is possible to reduce the energy density at locations other than the focal point FCS-2. (Also, at the focal point FCS-2 in the stratosphere or above the troposphere, the air density is low, and there is little atmosphere, oxygen, or ozone, so photons are not absorbed and a photon convergence point can be formed at the focal point FCS-2. However, when the focal point FCS-2 is set at a location with a high air density near the ground and photons are irradiated from 1, it is expected that they will be attenuated by the atmosphere before reaching the focal point FCS-2.) ● As a result, at the ground part outside the focal point 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 these two elements. (In this application, in addition to being attenuated by the atmosphere, the constellation is assembled 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 n satellites in close proximity to the light-receiving unit 2 from the light-emitting unit 1. By receiving the lasers 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 can be 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 light-emitting units 2 with low output (X watts), the energy amount when not hitting 2 and going towards the ground can be reduced compared to when aiming at 2 with one high-output laser of nX watts, which may be safer. ※ In an SSPS satellite, a lunar base equipped with SSPS, etc., as the single laser output (output of one laser) of the light-emitting unit 1 becomes larger, it can 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 lasers 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 lasers or photons 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 3 for arranging in the air, the aircraft 3, the airship, the 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 orientation 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. It includes an antenna, a rectifier circuit, and a 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, 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 at the light receiving part 3 and uses it as electric power, chemical energy, or 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 propulsion, ion propulsion, photon sail, and propellers 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 a battery or fuel that drives 3, 3ETC, 3TH, etc.). 3ETC: Control system, computer system, communication system, power system, electrical wiring system, 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 and 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, or the ground. 3WIR: Device or wire, power cable, optical repeater, power or energy transmission path connecting 3 including the receiving part 2 and 3FUEL. 3WIRI: Electrical wiring path, power wiring path, signal wiring path, electric wire, cable, bus such as optical fiber of 3. 3REA: Reactor of 3. (3REA is a device that performs a chemical reaction. For example, it may perform reactions using heat, electricity, or light.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:3FUEL's fuel production section. 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 may convert (inverse conversion) chemical energy / fuel into electrical energy, thermal energy, mechanical energy, heat engine energy, i.e., an energy converter. 3TANK: Cargo compartment, tank, fuel tank [3FUEL-TANK:3FUEL's fuel tank (it may be a hydrogen gas fuel tank 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:3's cargo compartment. It may carry a battery or fuel for moving 3. It may carry a human who moves 3, 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 compartment, a device for collecting rainwater, or a water cargo compartment. ※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, apply the energy of the photons obtained by the light-receiving unit 2 to the propellant, and 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, heat water or the 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 to jet and propel 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 this application). It may also be obtained from a water source 4H2O on the ground. 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, it may be a cargo hold for loading a substance (water) that serves as the basis for fuel (hydrogen). 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 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. A storage location and flow path for fuel, and a flow path to users. <User section> 6: User section. A user section that consumes energy. A part that consumes energy by consuming the fuel transported and delivered from the 4FUEL-TANK to 6. (Or a user section that consumes 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 conductor element 1 and 1WIRE.) 14: The base part of the cable, which may be connected to 1100. 17: 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 for loading water or hydrogen when producing hydrogen from water using the electric power obtained from 1. 1FUEL-GEN: Fuel production section and chemical reaction section of 1. 5VALV: Connection port of 5 tanks. 5TANK: Tank (tank for loading water / hydrogen, oxidized metal / reduced metal, fuel raw material / produced fuel). 5TANK1: Tank loaded with fuel raw material (e.g., water, metal oxide, carbon dioxide). 5TANK2: Tank that is connected to 1VALV and is producing and loading fuel using the electric power or energy of SSPS (e.g., producing hydrogen and oxygen from water, producing metal and oxygen from metal oxide, producing hydrocarbon). 5TANK3: Tank loaded with fuel and dropped from SSPS towards the ground (e.g., tank loaded with hydrogen / hydrogen and oxygen, tank loaded with metal / metal and oxygen, carbon / hydrocarbon loaded with carbon / hydrocarbon and oxygen). 9: Launching means. Or a launcher that launches from the moon and drops towards the earth, planets, satellites, celestial bodies, 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, which disrupts the lunar mass balance and is not a sustainable cycle. However, in the short term (during the development of space exploration), it does not emit carbon dioxide, (it does not require launching water and oxides on the ground, and can directly drop the resources on the moon onto the Earth), and it is a method that enables the use of the 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 the power of SSPS in satellites and planets containing metal oxides.) 5MM: Mines, extraction sources, and collection sources of lunar resources such as metal oxides. And it may include a series of means from the collection, sorting, separation, purification, and transportation of resources to the production of fuel 5M. 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 at the local site in space (celestial bodies such as the moon, satellites, the asteroid belt, meteorites floating in space, comets, etc.) where the energy of SSPS can be stored. 1FUEL-GEN: The fuel production unit and chemical reaction unit of 1. Substances that store fuel or chemical energy may be produced using the power and energy of 5MOX and 1SSPS. 1CHEM: The chemical reaction unit of 1. The chemical plant of 1. 1CHEM1, 1CHEM2, 1CHEM3 (including devices and reaction units 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 part. 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 redox 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 oxygen obtained from lunar resources and SSPS. (For example, fluids such as silane and trichlorosilane.※ Although it requires special 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 ground, loaded with 5M and 5MC. A dropping container and a fuel dropping 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 on the moon out of the produced metal and oxygen, dropping the metal to the Earth, and reacting it 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 to 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> 1SSPS-SAT: An artificial satellite for SSPS including 1. 1SSPS-SYS: The SSPS system. (-SEIZA: An SSPS group consisting of artificial satellites for SSPS including 1, a constellation of artificial satellites. -QZSS-SEIZA: An SSPS group in the quasi-zenith orbit, a constellation. -ORBIT: An SSPS group in orbit, a constellation. -GEOS: An SSPS group in the geostationary orbit, a constellation. -MOON: An SSPS 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 attempting to pass between the light-emitting part 1 and the light-receiving part 2. ※ For example, a mirror 1MRR that reflects laser 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 equipped 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 with 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 as the distance the laser travels increases, and power is obtained. The power is used to emit photons again to the light-receiving part 2 of 3 in the air or another 1LINK.Once the light beam that has spread and reached using 2 and 1 of 1LINK is converted into electric power, it is emitted again as a laser beam that has not spread after being re-emitted. 1MMR: A mirror capable of reflecting photons, or a reflectable device. (Example: A mirror for sunlight reflection and collection, an aluminum mirror for ultraviolet laser reflection) It may be mounted on 1LINK. ※For example, it reflects the photons irradiated from 1 and changes the orbit and radiation of the photons. 1OPT: An optical system, optical components, 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, the light beam is converged 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. ※Work may be performed by 3FCAR or 3FORM robot. For example, forestry work may be performed by 3 or 3FCAR or 3FORM robot. The 3FCAR or 3FORM robot may be equipped with 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), and pruning may be performed. (Among various operations such as agriculture, forestry, and fishery, the operations that can be performed in the system of the aircraft of the present application may be performed by 3ROBOT.) ※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 transport equipment, or may be an aircraft that also serves as a hotel or housing, or a housing part (or an airplane-type camping car 3FCAR, a housing-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 the 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 mainly a tag used for monitoring objects, luggage, children, and the elderly, and has a part for receiving power from 3WEP. It obtains power through 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 or 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 michibiki, or 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 2TAG attached to an object, the 2TAG may be equipped with a sound-emitting device as 2TAG-OUT, and the 2TAG 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 2TAG 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 a person accompanying the tag scanner by sound. 2PATCH: A patch that may also 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 or patch for dementia treatment, a patch for smoking cessation, a plaster or tape for poultice, a patch that may also be a bandage for children's wounds, 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, etc., and has the function of emitting 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, worn, 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 sticking. For example, the support 2TAG-SP and the adhesive layer 2TAG-ADH of 2TAG. ※ For example, 2PATCH may be a film or tape, etc. 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, it is rivastigmine tape, a poultice of a poultice / tape agent.) 2PATCH may also be a band-aid or a bandage. ※ For example, 2PATCH may be a patch that does not contain drugs / 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, medical supplies, highly poisonous substances, goods, luggage, bags, identity cards, keys, car keys, automobiles and transportation equipment, buildings and furniture, important documents, antiques, treasures, precious metals, jewelry, ornaments, computers, watches, devices, clothing, underwear, footwear, humans, animals, plants, and organisms. 6TAG-SCANNER: A part that wirelessly powers 2TAG or 2TAG-PATCH, or receives the wireless communication signal or beacon 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 an automobile 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 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 search for the tag, or it can be an aircraft, transport equipment, or vehicle. ※3DRONE may transmit wireless power from 3WEP to the tag while flying and approaching the tag to search for it. Communication may be carried out between the tag and the drone. 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 in a measurement sensor of an object tagged with tags.) ※For example, attach and mount 2 tags with sensors and 2 TAG-PATCHes to the bottom of a storage bottle of a highly toxic substance that needs 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 manages the reagent by using the change in the bottle weight as the amount of highly toxic reagent used for the reagent change amount. 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 human or animal cooperate and fly in formation. The robot arm may operate, grip, hold, etc. devices, tools, and instruments for removal processing or additive manufacturing such as 3A1-RP or 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 airplane 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 that may be charged by a light receiving part 2 or driven by fuel manufactured by 2, and performing removal processing or additive manufacturing such as 3A1-RP or 3A1-AM with the robot arm for removal processing or additive manufacturing. 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 in the assumption of using 3ROBOT in forestry, 4WK is the tree to be pruned, 4WK-AM is the chemical solution such as pine shoot beetle 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: The focus that one or more 1s should aim at. FCS-2 may coincide with the point where the light of the light receiving unit 2 should be received. In the present 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 an 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). 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 and lasers from 1 to 2 to hit. <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 parts, 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 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 device, floating 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: Pipeline, piping, and tank 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 energy to other aircraft 3, 3FUEL, or 3FORM from 3 including 2, or share energy with them. <Reference figure, 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: Pipeline, 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 people, 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 transport device 3. The aircraft 3 and the transport device 3 may obtain the water from rainwater or the water resource 4H2O on the ground. The water may be used as a propellant to be ejected from the propulsion device 3TH of the transport machine 3 (aircraft 3, placement means 3, cage part 15 of the orbital elevator, space fountain, transporter, aerial structure 2, launch device, launch vehicle, vehicle for launching from the ground to space 3, 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 down from rain clouds over the sea to 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 harmful substance removal means 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 atom>The present application discloses the use of the atmosphere, oxygen, and oxygen atoms on the ground in the subordinate 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 with the oxygen atoms removed by reducing lunar oxides, manufacturing 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 upper 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 and 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, the 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 shoes, insoles, belts, or wearable devices with a built-in watch-type tag depending on their preferences, differences in condition, and level of interest. It was thought that there might be a tag that could 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 patch-type wireless tags that combine a patch for administering medicine to a dementia patient and a wireless tag, and the most important feature is that they can administer adhesive medicine to a dementia patient and attach and maintain the attachment state of the tag 2TAG. 2TAG may be charged by the wireless transmission means of an aircraft 3 that searches for tags and operate as a beacon or wireless communication. <Wireless Power Supply Method> The present application includes an invention for a passive RFID tag that stores power by wireless power supply and generates a wireless signal (beacon signal) from the stored power 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 a UHF tag function, use it as 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·Embodiment 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 strayed into the mountains, stick, include, or provide 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, beacon (or a signal transmitting device or 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 reading device (tag scanner) for searching for Tag 1. Also, automobiles, electric assist bicycles, and transportation equipment with a power source moving around in the city may be equipped with the tag scanner. For example, the drone 3DRONE may be used as a 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 handheld tag scanner.) For example, in the case of an elderly person, it is expected that it is difficult to remove the plaster from the back, but this is an example. For example, for living organisms such as dogs, cats, and pets, a tag in a form that can be worn by the organism such as a collar, and the tag that uses the power from the power supply for beacon generation may 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, 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 allowed to perform operations such as power supply and beacon operation. The 2TAG performs operations such as beacon according to the conditions for operating the 2TAG and the environment where the 2TAG is placed. Specifically, the 2TAG may be equipped with 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 the on / off or access of functions such as beacon functions, 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, it is a 2TAG with a password printed on it, and the printed password PWD is recorded and stored in the control unit or IC of the 2TAG. Based on the 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> Although the 2TAG is a patch as a medical product or medical means, the 2TAG may also be a device used for monitoring while being a medical means. For example, it may be a medical device or medical means such as a wristwatch-type device for measuring the heart rate. <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 devices capable of correcting vision, 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 looking 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 for assisting smoking cessation.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 a band-aid 1P, a bandage 1P, an eye patch, 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 laboratories such as universities, 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 inventions 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 tags 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. <Adhesive medicine> Based on such circumstances, as a result of observing the lives of the elderly, the inventor paid attention to the rivastigmine patch for adhesive medicine, which was recognized as an item that the elderly always wore, and proposed the patch-type wireless 2TAG of this application. <Attachment of adhesive medicine, patch, and tape to other than the skin> The adhesive 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 remove outdoors,) underwear, innerwear. The patch may be in a tape type or a type in which the underwear and the patch / tag are a hook-and-loop fastener. <Attachment location on the skin> If it is on the back, it may be difficult for the elderly to reach out to 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 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 his or her own personality, and it is unclear whether they will always wear fixed items such as shoes and watches properly. The task was to find items that they would continue to wear 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 above-mentioned tag, it was unclear whether they would always wear shoes, belts, or a wearable device with a watch-type tag incorporated, depending on the preferences, differences in conditions, and level of interest of the elderly. <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 in the 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 handheld tag scanner, or may search with a drone or 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 is charged. The drones may search for 2TAG while positioning their positions 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 (postal 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 facility vehicles, and the tag scanners may be used to search for the 2TAGs 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 problem> The tag 2TAG and the tag scanner 6TAG-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 the most important feature is that it is possible to administer the sticking medicine to dementia patients and attach and maintain the attachment state of the tag. Furthermore, the conditions for driving the tag after attachment are also disclosed. <Effects of the invention. >The tag 2TAG and the tag scanner of the present invention are a patch-type wireless tag that combines a patch for administering medicine to a dementia patient and a wireless tag, and have the advantage of being able to administer a sticking medicine to a dementia patient and attach and maintain the tag. <Example> The concept of the present invention is described in FIG. 7. The main body of the present invention incorporates a procedure of wearing and managing a wireless tag 2TAG into a treatment procedure performed by a relative, caregiver, or caregiver of an elderly person who administers a sticking medicine to an elderly dementia patient, so that the two procedures can be performed in one procedure. When searching for the wireless tag 2TAG, power is stored in the 2TAG by wireless power supply from automobiles, transportation equipment, drones, aircraft, artificial satellites, etc. in the city, and is released as the power of the beacon signal, so that the beacon signal can be transmitted to a tag scanner over a distance exceeding the wireless power supply range. This is a method for searching for the 2TAG that is expected to be attached to the elderly. ※ Detailed explanations of basic computers, electronic components and elements, communication, power supply, drones, aircraft, spacecraft, time synchronization technology, and positioning technology can be described 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 install lightning rods on buildings for lightning protection. Also, according to Patent Document 1 and Patent Document 2, a conductive wire (Figure 1 of Patent Document 1) or a region plasmaized by a laser (Figure 2 of Patent Document 1) is used from the ground towards rain clouds and thunderclouds, and the resistance value of a part that is insulated between the thundercloud and the ground and acts as a capacitor is reduced or short-circuited to intentionally change the direction of the flow of lightning strike charges or the direction where lightning strikes. In Patent Document 2, it is disclosed that the application of the fact that the synchrotron radiation generated using a free electron laser or a particle accelerator and an undulator is radiation or ionizing radiation having an ionization effect (Figure 1 of Patent Document 2) is being studied and developed for the lightning protection method using a laser. 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 thunderclouds, 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 thundercloud towards the ground, the laser may be scattered. Also, when the inventor was devising an energy transport method of SSPS from space, he considered a configuration in which ultraviolet rays and X-rays are received by the light receiving unit 2 in the air from the light emitting unit 1 on the space side.In the present application, instead of on the ground, photons or lasers of ionizing radiation such as X-rays are irradiated from a space solar power satellite 1SSPS or a plurality of light emitting parts 1 of a satellite constellation of 1SSPS from the air or space into the upper layer of a thundercloud (the space side and the stratosphere side) to the lower layer of the thundercloud (the ground side), and the short circuit of a 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 promoted using the ionized and plasma-formed region. An ionized region having conductivity is generated, which becomes a breakthrough (IONA-NAIL in FIG. 13, the nail-shaped part, or the part where the atmosphere is ionized, plasma-formed, and has low resistance due to the laser focus FCS-2) for weakening the insulation of the intra-thundercloud capacitor storing the positive and negative charges of the thundercloud, so that 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 ground waves to thunderclouds can be scattered by hail or the like, and a method of lightning protection using lasers such as X-rays from space to thunderclouds in the air is studied. The present application discloses a lightning protection method intended to facilitate short-circuiting the charges inside the thundercloud. ● As shown in FIG. 13, (considering that in the troposphere, when rain, hail, snow, etc. obstruct the straight propagation of the laser and cause diffuse reflection, making the laser ineffective, or when a laser is emitted upward from the ground, it may affect objects such as aircraft in the sky,) in order not to be affected by the meteorological environment such as rain in the troposphere and not to affect 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 thunderclouds in the troposphere to promote short-circuiting inside the thunderclouds, or to promote short-circuiting between the lower layer of the thunderclouds and the ground part. Induction may be made to facilitate the 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 effect and output control. (Broadly, ultraviolet rays such as UV-B and UV-C. If described without further limitation, lasers absorbed by the atmosphere with some infrared rays or the like, or radio waves that induce ionization effect, partial low resistance of the thundercloud, and insulation breakdown may also be used.) <Means for Solving the Problem> <0005> (1) Lightning Protection by Conductors The conductor element 1 described in FIG. 1 of Japanese Patent Application No. 2022-123161 may be used to assist discharge or short-circuiting across the thundercloud or 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 generating device, free electron laser) arranged in space or in the air (for example, artificial satellite groups, aircraft, airborne platforms), X-rays or gamma rays (and ultraviolet rays) are irradiated and emitted to the 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 lasers such as X-rays and gamma rays ionize 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. Using the plasma region, the positively charged region / layer and the negatively charged region / layer of the thundercloud are short-circuited, or the insulation property is reduced, 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 or above of the thundercloud, the stratosphere, mesosphere, thermosphere, or 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 the laser light emitting part 4 LASER on the ground and irradiating the air, it is possible to attempt to protect against lightning by irradiating with a laser at a place where lightning protection is required using artificial satellite groups.<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, during irradiation, 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, etc. 3 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 and drives the propulsion device 3TH, which may include a propellant provided in the 3KAGO, to move the 3KAGO up and down (in the 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 Figs. 12 and 13.<Example 1><0010>● From the light-emitting part 1 arranged in space, in the air, or in the 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, and the ground side. (1HNU is used as ultraviolet rays, visible light, or infrared rays for lightning protection purposes. Preferably, photons with wavelengths that react and are 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 at the upper part of the thundercloud and the negatively charged layer LCM at 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 at 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, and the conductive path IONA, IONA-LINE in the figure, is formed, discharging the charges of the capacitor composed of LCP and LCM, short-circuiting, and performing lightning protection.(In the concept of insulating the insulation between thunderclouds with a conductive wire, it is only necessary to discharge or short-circuit the charges of the thunderclouds using the conductive wire in FIG. 1 of Patent Document 1. As a conductor, the thundercloud can be used as a conductive path 12 or an orbital elevator section 10.) ● 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 laser trajectory is ionized, and a nail-shaped (or in the form where the laser is attenuated) 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 can be turned off. Also, the output of the laser can be controlled so that the laser output does not increase at locations other than the focal point FCS-2. Further, when radiation or X-rays cannot be used to avoid biological effects, an ultraviolet laser can be used and its output can 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 (using a cable shortened to the aerial arrangement means 3 instead of the long cable of the orbital elevator, and having 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, it is an explanatory diagram of a power transmission system and an energy transmission system in which 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 preferable to use the conductor element 1 and the cable 1WIRE of the present application in which the weight of the conductor is reduced compared to a conductor made of only copper by using a carbon material (such as CNT) in the material part 101 of the element 1 of the present application for the cable 12. ● 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 this 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 placement 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 through the 12, a current due to short-circuit flows through the 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, ascend and descend. ※ 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, removal 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) 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 laser irradiating 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 an artificial satellite having the light emitting part 1 orbits LEO or the like, and to 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 Signs> <0012> <Explanation of Fig. 13> 1: The light emitting part arranged in space or the air. 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, and paying attention to the photons that react and dissociate by ozone, oxygen molecules, nitrogen molecules, atmospheric 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 power. 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 air in the atmosphere 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 upper 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. The insulation breakdown part. A part of the insulated thundercloud becomes conductive due to the laser irradiation, becoming an escape path for the charges in the LCP part or the upper layer of the thundercloud, and being easily short-circuited. IONA-NAIL: (The ionized part, plasma part, low-resistance part that protrudes like a nail struck on a plate in the upper layer of the thundercloud formed by the laser, the protruding conductor part. Inducing 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-shaped laser. Inducing 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 be equipped with 1TH and 2 and receive photons from 1 for propulsion / acceleration. Spacecraft, launch vehicle, space structure, orbital ring, aerial structure, annular structure may be equipped 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. Equipped with 2, 1TH, and 3TH.) 3KAGO: The cage part 15 attached / guided by the cable 12 of the orbital elevator 10 and 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 for the pulley 10B, may include elements of a known traction rope-type elevator, and may include a counterweight, hoistway, rope, wire, deflecting sheave, 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 propulsion unit 3TH including a light-receiving unit 2 and a counterweight 15W. The right figure of Figure 26 shows an elevator 10AIR with a winch 10B having a 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 also be a cage part 15 that is an aircraft 3 or a transportation device 3 connected by a wire 10WIR with a propulsion unit 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, winding motor part of an elevator (the winding motor may also 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 also be an aircraft 3 or a transportation device 3, and 3 may be equipped with a propulsion unit 3TH and a light-receiving unit 2. * 15 and 15W are driven like the winding motor of a traction elevator, and the power may be obtained from the light-emitting part 1 through the light-receiving part 2. When 3TH of 15 and 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, 3TH receives laser irradiation from the light-emitting part 1 and moves up and down 3KAGO and 15 ( / 15W). Accordingly, 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 light-emitting unit from the above-ground part. It is affected by the troposphere such as hail and clouds. When it is directly below 15, power transmission may be performed by a laser (instead of the space-side light-emitting unit 1) at 15. 1: Photon light-emitting unit 1. (The orbital elevator and aerial platform in Fig. 26 are like a Ferris wheel, cable car and its carrier, and have a ring 10WIR that can be supported and rotated by pulleys 10B etc. in the space and aerial side device 17 and the above-ground part 14. 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 and 15W of 10WIR may be repeatedly lifted from 14 to 17 and then lowered. ※ A circular path that repeats returning from the ground 14 through the aerial side 17 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 and aerial structures, orbital rings, partial orbital rings, space fountains, launch loops, mass drivers, launching devices, transportation equipment, etc.) ※ For example, when it is desired to lift and arrange 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 (comprising 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 the 3TH from the ground through the 12 and 3. In the 3TH, operations such as propulsion, floating, lifting, moving, attitude control, launching, and lifting can be performed using the energy from the light-receiving part 2 and the propellant.It may be possible to supply the aerial platform 3 and the placement means 3 on the space side from the ground, heat and eject the supplied water and propellant by the energy obtained by the light receiving part 2, and lift and raise the placement means 3 while heating and ejecting, and move and place it near the structure 2 on the space side. 17: It may be provided with a connection part to the aerial or space side part and 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 be moved and 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 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 unit. 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, and may include a magnetic suspension functional part. It may also be a rotating (eddy current countermeasure) rail. 17TR: A 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 eddy current force (behavior of Arago's rotating disk and 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 (reducing copper and containing carbon) and its gate control circuit may be used. *From the perspective of controlling eddy current, it may be possible to control the ease of generation of 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 decrease 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) disposed in an artificial satellite or space and a light receiving unit (2) disposed 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 including the step of irradiating, emitting, relaying, transmitting, and transferring 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, including the step of irradiating, emitting, relaying, transmitting, and transferring 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, which can ionize oxygen molecules, ozone, oxygen atoms, or nitrogen molecules, nitrogen atoms, or molecular atoms in the atmosphere in the traveling path of the laser, and form an ionized region, a plasma region, or a region with high conductivity along the traveling path of the laser. <Claim EW3> A lightning protection method using the method for reducing the resistance of the atmosphere according to Claim EW2, wherein the ionized region, the plasma region, and the region with high conductivity are formed between the positively charged region of the thundercloud and the negatively charged layer of the thundercloud, reducing the resistance value between the positively charged layer and the negatively charged region of the thundercloud, and having the characteristic of destroying the insulation of the charged capacitor composed of the positively charged layer and the negatively charged layer of the thundercloud to prevent lightning, a method for canceling and neutralizing the electric charge of lightning or a lightning protection method. <Document Name> Abstract <Abstract> <Problem> When considering lightning pr...

Claims

1. A method for transmitting photons, which uses a photon generation unit (1) disposed in outer space or in the air and a light receiving unit (2) in the air or in the atmosphere capable of receiving photons irradiated and emitted from the photon generation unit (1), The method for transmitting photons includes a step of irradiating, emitting, relaying, transmitting, and transferring photons from the photon generation unit (1) to the light receiving unit (2), In the step of irradiating, emitting, relaying, transmitting, and transferring the photons, When the photons pass, move, and progress through the atmosphere, the molecular atoms in the atmosphere along the path of the passing, moving, and progressing photons can be ionized or turned into plasma, Or, A method for transmitting photons, when the photons pass, move, and progress through the atmosphere, the molecular atoms in the atmosphere along the path of the passing, moving, and progressing photons can make the atmosphere have a lower resistance.

2. A plurality of the light emitting units (1) are arranged, and in the light receiving unit (2), a focal point portion (FCS-2) of the photons emitted from the plurality of light emitting units (1) or a portion (FCS-2) where the photons converge and concentrate can be formed. The method for transmitting photons according to Claim 1.

3. A method for reducing the resistance of the atmosphere, which uses the method for transmitting photons according to Claim 1 to reduce the resistance of the atmosphere as the light receiving unit (2).

4. The method for reducing the resistance of the atmosphere according to Claim 3, wherein the light emitting unit (1) includes a process of irradiating and emitting a laser light beam using the photons.

5. The laser light beam has a traveling path that travels, crosses, and passes from the cosmic side or the air side to the ground direction through the atmosphere, thunderclouds, or the vicinity of thunderclouds, By ionizing oxygen molecules, ozone, oxygen atoms, or nitrogen molecules, nitrogen atoms, and molecular atoms in the atmosphere in the traveling path to form an ionized region or a plasma region, it is possible to form a low-resistance region with low electrical resistance, A first region where charges are accumulated in the upper layer of the atmosphere or thunderclouds, or a first region (LCP) where positive charges are accumulated, By forming the low-resistance region between and in the vicinity of a second region where charges are accumulated in the atmosphere and the lower layer of thunderclouds, or a second region (LCM) where negative charges are accumulated, The method for reducing the resistance of the atmosphere according to claim 3, which can reduce the resistance for insulating between the first region and the second region and induce induction, discharge, short circuit, and dielectric breakdown of charges between the first region and the second region.

6. The method for reducing the resistance of the atmosphere according to claim 3, wherein the photons are ultraviolet rays, X-rays, gamma rays, or ionizing radiation.

7. The method for reducing the resistance of the atmosphere according to claim 6, wherein the light-emitting unit (1) is provided with means or devices for generating radiation light or free electron laser.

8. A lightning protection method using the method for reducing the resistance of the atmosphere according to claim 3.

9. A dielectric breakdown method capable of short-circuiting and neutralizing positive and negative charges inside a thundercloud, which is a dielectric breakdown method using the method for reducing the resistance of the atmosphere according to claim 6.

10. A lightning protection method using the method for reducing the resistance of the atmosphere to reduce the resistance of the light-receiving unit (2) which is the atmosphere, using the method for transmitting photons capable of forming the focal portion of the photons according to claim 2, wherein the light-emitting unit (1) includes a process of irradiating and emitting a laser beam or light beam using the photons, the photons have the characteristic of attenuating as they travel through the atmosphere, the photons include infrared rays, visible light, ultraviolet rays, UV-C, X-rays, gamma rays, or ionizing radiation, the laser beam or light beam has a traveling path that travels, crosses, or passes through the atmosphere, thunderclouds, or the vicinity of thunderclouds from the cosmic side or the air side to the ground direction, it is possible to form a low-resistance region that is electrically low-resistance by ionizing the molecular atoms in the atmosphere in the traveling path and forming an ionized region or a plasma region, A lightning protection method using a method for reducing the resistance of the atmosphere, which forms the low-resistance region between and in the vicinity of a first region where charges are accumulated in the upper layer of the atmosphere and thunderclouds, or a first region (LCP) where positive charges are accumulated, and a second region where charges are accumulated in the lower layer of the atmosphere and thunderclouds, or a second region (LCM) where negative charges are accumulated, thereby reducing the resistance for insulating between the first region and the second region and enabling dielectric breakdown and short-circuit between the first region and the second region. A lightning protection method having a feature that positive and negative charges inside a thundercloud can be short-circuited and neutralized. A lightning protection method having a feature of inducing dielectric breakdown inside a thundercloud to short-circuit and neutralize the charges of the thundercloud for the purpose of preventing lightning generation between the lower layer of the thundercloud and the ground surface.

11. The method for transmitting photons according to claim 1, wherein the photons have a feature of being absorbed by ozone, oxygen molecules, oxygen atoms, nitrogen molecules, and nitrogen atoms through photoreaction and chemical reaction.

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