Devices, lightning protection devices

Abstract

Since weather conditions could affect lightning protection when using lasers from the ground, we will consider a method of lightning protection that uses lasers emitted from space. [Solution] This invention proposes a photon irradiation method and energy transmission system comprising a photon generation unit using photons and lasers, and a photon receiving unit. The generation unit can be placed in the air or in outer space, and by arranging multiple generation units, a configuration is disclosed that allows for the formation of a focal point (FCS-2) or a focused portion of photons emitted by the multiple generation units in the receiving unit. Furthermore, a method is proposed in which the laser-irradiated receiving unit is located in the atmosphere, and the atmosphere surrounding the receiving unit is ionized, reduced in resistance, and subjected to dielectric breakdown. The generation unit may constitute a satellite constellation. The satellite may also be placed in low Earth orbit.

Description

Technical Field

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

Background Art

[0002] ●This invention relates to sheet, film, foil, or linear conductive elements or wiring materials that utilize carrier introduction by an electric double-layer transistor. Furthermore, it relates to electronic components and devices such as motors, actuators, and batteries that use the wiring material. ●In addition, by utilizing the fact that the carrier introduction into the conductor 101 of the conductive element can be controlled by the gate electrode 106, the conductivity of the conductive element 1 can be controlled to be high or low according to the measurement value of the sensor by 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 (Figure 10). The high and low states refer to a state in which a high state is when a carrier is introduced into 101 by the gate, forming 104 and increasing positive conductivity, and a low state is when the gate is off and no carrier is introduced into 101, or when the ion species of the electric double layer formed in 105 causes the 104 portion of 101 to decrease conductivity. ●We propose using the conductive element 1 of this invention, which includes 101 that can form 104, as a battery electrode. One example of an effect achieved by controlling the conductivity level using 106 is to turn on the gate electrode 106 during battery charging and discharging, and to turn off 106 to lower conductivity during battery storage or before the battery encounters an accident. When a battery including a sensor and control unit detects an impact or acceleration, the control unit is instructed to turn off 106, lowering the conductivity of the electrodes and preventing a short circuit accompanied by rapid discharge, as the positive and negative electrodes would remain highly conductive while in contact during an internal short circuit (Figure 9).

[0003] ●As shown in Figures 1(B) and (A) of this application (or as shown in the representative figure 1 of Patent Document 1), there is a conductive layer 101 of an electrically conductive conductor, semiconductor, conductive polymer layer, or carbon-based material (such as CNT or graphene graphite), a source electrode 102, a drain electrode 103, and a gate electrode 106, for example, an ionic liquid of a molten salt between 102-103 and between 106, and when a potential VGS is applied to 106 (with 102 as GND), 106 is charged, and ions contained in an insulating layer 105 that can form an electric double layer are arranged around 106 to cancel out the VGS of 106, forming an electric double layer. It also forms a capacitor. (The insulating layer 105 may also be a separator layer of a secondary battery or the like containing an ionic liquid.) As a result, an electric double layer appears near the carrier introduction layer 104 of 101 (the inversion layer 104 in a MOSFET), and carriers are introduced into 104 of the semiconductor substrate 101 (or a conductive substrate 101, a carbon conductive substrate 101, a conductive polymer substrate 101, an organic semiconductor substrate 101, a carbon-based conductive material substrate 101, or an electrically conductive substrate 101) due to the field effect (of a field-effect transistor), and the carrier density n increases in the carrier introduction layer 104 of 101. (※Patent Document 1 describes a configuration in which a protective layer 107 is placed on top of the carrier introduction layer 104. In this application, a protective layer 107 may also be used depending on the circumstances. 107 prevents electrochemical reactions, etching reactions, etc. from occurring in 104 and 101 at gate voltages exceeding a certain threshold in an electric double-layer transistor. This application is not an invention relating to a protective layer, so the explanation 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 an 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 an 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 a 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 nanotube CNT (and other general-purpose metal films such as iron) are used for the conductor (or conductor·semiconductor) 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 conductor including 104·1042 or 104. · Also, taking advantage of the fact that the formation of 104 (and 104I which, depending on the type of material of 101, functions to lower the conductivity contrary to 104) is controlled by the voltage value of VGS applied using 106, in a battery with a high electromotive force or energy density, or a battery using a flammable electrolyte, etc., environmental data (such as acceleration) of the environment where the battery is placed, which may lead to battery damage, is detected by a sensor of an input device, and VGS is controlled so as not to generate 104 so as to reduce the conductivity of the battery electrode using 104, and before the battery is stored, damaged, or destroyed, the conductivity of the electrode is lowered to prevent an internal short circuit derived from the electrode (Fig. 9, Fig. 10). ※ As shown in Fig. 2, 108 in the body B 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 in the drawings and 104, 105 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, the capacitor portion of the gate electrode is charged. It is preferable that the self-discharge of the capacitor portion is low. It is also preferable that the gate leakage current and leakage current are low.

[0005] <Dielectric breakdown at the gate portion> The gate portion of the conductor element constitutes a capacitor, but the VGS that the capacitor can withstand has a limit (absolute maximum rated voltage VGSA between GS), and if a high voltage VGS is applied, the insulation at the gate portion is broken. If a voltage exceeding VGSA is applied, the capacitor portion may be destroyed, and it may become impossible to form 104. (P2 in Figure 9) <Fuse-like two-terminal conductor using dielectric breakdown at the gate portion> On the other hand, when the element of the present invention is used as a two-terminal wire 1-2TER as shown in Figure 8 (B), the voltage applied to the two terminals has an absolute maximum rated value due to VGSA. When a voltage exceeding VGSA is applied to 106 in 1-2TER, the capacitor is destroyed and 104 disappears, and the conductivity between the two terminals of 1-2TER decreases due to the loss of 104, which may be used like a fuse. When a power transmission network uses a wire in which multiple 1-2TERs are connected in series as a conductor 1WIRE, if a lightning strike applies a high voltage such that 106 exceeds VGSA, the capacitor section within the conductor may be destroyed, 104 disappears, and the conductivity of 1-2TER decreases. This may make it difficult for current to flow between the two terminals of 1-2TER, potentially preventing a large current from flowing and spreading throughout the power grid containing multiple 1-2TERs.

[0006] <Perspective on Conductivity> ●The conductivity SIGMA is given by SIGMA = 1 / resistivity RHO = charge q × carrier density n × carrier mobility MU, and the aforementioned 104 with increased carrier density n can have increased conductivity SIGMA. In this application, we propose a conductive element 1 that utilizes 104 whose conductivity has been improved by introducing and injecting carriers into a conductor or semiconductor using this mechanism and increasing the density n. ●The resistance R of a conductor is given by R = resistivity RHO × conductor length L / area A, and it is preferable that the area A that contributes to conductivity can be made large in the cross-section of the object. *Carrier density n is said to be 10^22 to 23 for metals among inorganic materials, 10^10 to 17 for semiconductors, and 10^1 to 4 for insulators. *Some chemically doped conductive polymers also have high carrier densities. *In this application, we propose using highly mobile organic semiconductors, carbon materials such as CNTs, graphene, and graphite, or materials with abundant resources such as iron, as 101 (without chemical doping), and using them as conductive elements in which the carrier density can be increased by an electric double-layer transistor and the conductivity can be controlled by controlling the voltage of the gate electrode. ●If the carrier density n in an electric double-layer transistor can be made to 10^20 to the power of 21 or more, it may be possible to form a highly conductive conductive element 1 by combining it with a highly mobile organic semiconductor. ·For carbon materials such as CNTs that can be expected to have high mobility, it may be possible to make a good conductor by combining the high mobility with the high carrier density achieved by forming an electric double layer. ●Furthermore, in the configuration in Figure 11 in which 1012 is stacked on 101P, 1012 can be made into a thin metal film and 101P into a porous film made of a conductive carbon-based material, and we propose to increase or decrease conductivity by forming a carrier introduction layer 104 (and 104I) on the metal film 1012 while reducing the amount of metal elements used.

[0007] <Increasing the area of ​​the carrier introduction layer 104 101P> ●The resistance R of a conductor is R = resistivity RHO × conductor length L / conductor area A, and it is preferable to increase the area A that contributes to conductivity in the cross-section of the object. ·As shown in Figure 1(A) and Figure 11(A), the 104 formed at the interface of the conductor element 1 having flat 101 and 105 is thought to be thin, with a thickness of about 1 nm, and the area that becomes the 104 part that improves the conductivity of the conductor (conductor area A mentioned above) is small, and even if 104 is formed, there may be a problem in that the resistance R of the conductor element cannot be reduced as intended. Therefore, as shown in Figures 11(B) and (C), by forming 104 using 101P which includes comb-shaped, rod-shaped, pillar-shaped, and porous layers, or by forming a layer of second conductor 1012 on top of 101P and forming a carrier introduction layer 1042 on 1012, it is possible to obtain 104 and 1042 which have a larger conductive area than the area of ​​104 that occurs on the flat 101 and 105 in Figure 11(A), making it possible to increase the conductor area A and (reduce the resistance R of the conductor) improve the conductivity of the conductor. (By using 101P, the surface area per unit volume of the conductor that can form an electric double layer can be increased, and the area (conductor area A) on which the carrier introduction layers 104 and 1042 are formed can be increased.) Comparing the schematic cross-sectional diagrams of the elements in (A), (B), and (C) of Figure 11, (B) and (C) have configurations in which 104 and 1042 can be made to have a larger area than (A). Therefore, in this application, configurations using 101P as shown in (B) and (C) of Figure 11 are preferably used. Furthermore, in the case of metal materials, 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), but a general-purpose metal such as iron, which is ubiquitous on Earth (including aluminum, copper, etc., in the sense of reducing the amount of metal used in the conductor and conserving resources and weight), may be laminated and deposited as 1012 on a porous conductive carbon material conductor 101P, and a carrier-introduced 1042 may be formed by an electric double layer formed on the surface of 1012, for example, the conductor element 1 may be composed of 1042 formed in the porous electrode 101P.

[0008] <<Applications of Element 1>> ● We propose forming 104 in films of organic semiconductors, conductive polymers, carbon materials, and metal materials such as iron, and using it in the conductive parts of electrodes for secondary batteries and in the conductive parts of motors. <Applications of Film Electrodes> ● We propose using conductive element 1 in the form of an electrode-type conductive element 1FILM, such as a film, sheet, or foil, in the conductive parts of electrodes for secondary batteries, in the conductive parts of semiconductor elements such as solar cells, photodetectors, and light-emitting elements, and in hardware such as computers, robots, vehicles, aircraft, and transportation equipment, such as display devices. ● We propose an actuator 2ACT using EAP that uses 1FILM as shown in Figure 6. In actuators as well, it may be possible to reduce the use of metal electrodes and lower the cost and weight of metal resources. If the weight of secondary batteries, actuators, and motors can be reduced in robotic suits and spacesuits worn by people, the suits may become lighter and easier for people to carry. <Applications of Conductors> ● We propose using conductive element 1 as a conductive wire-type element 1WIRE as shown in Figure 5, in the conductive parts of electric wires and motors. The aforementioned conductor elements 1 and 1WIRE are also intended for use in power transmission and distribution networks, aerial platforms, base stations, internal wiring for power in structures, power distribution, and power transmission. ●In the configuration shown in Figure 5, the elements are arranged as 106, 105, 104, and 101 from the center of the cross-section of the conductor. However, in a configuration (1WIRE2) that reverses this arrangement (1WIRE), the elements can also be arranged as 101, 104, 105, and 106 from the center of the cross-section. ·In Figure 5, the gate electrode 106 at the center of the conductor is made of a composite material of metal fiber such as aluminum and carbon-based conductive material, and is placed at the center of the cross-section as both the gate electrode and the core material of the wire. Voltage is applied to 106 to charge it, and a capacitor is formed with 104 of 105 and 101 surrounding it, and 101 (the outer conductor part of the coaxial cable) including 104 is used as the conductor part of the conductor. 1WIRE was designed with a core wire made of 106, which can be made into a composite material, as shown in Figure 5, for reasons such as the fact that 106 can withstand mechanical forces such as bending as a conductor, and that the composite material can be used as a gate electrode for charge storage. The 1WIRE in Figure 5 is just one example of a conductor in the present invention, and the form of the conductor-type conductor in this invention is not limited to the example in Figure 5. For example, 1FILM may be processed (patterned, cut, etched) to create a conductor device.

[0009] <Presence or absence of gate electrode integrated into conductor element 1> In this application, 3-terminal and 2-terminal elements as shown in Figure 8 were considered. ●In the 1WIRE and 1FILM of this application, a 3-terminal element using a gate electrode 106 is used. On the other hand, for use in applications such as connecting conductive films or wires to form long wiring, a 2-terminal element was considered. ·Figure 8(B) shows a 2-terminal conductor element 1 (1-2TER). (1-2TER operates like a so-called constant current diode, where the source and gate of an FET are short-circuited, when the conductor 101 of the conductor element 1 is a semiconductor. Even if the conductor 101 is a conductor made of carbon-based material, it cannot flow more than the allowable current.) ·U1 is a gate driver section (which may be a resistor, etc.) 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, gate drive circuit, and control unit. • In the configuration of (B) above, driving 106 from Vcc by U1 becomes possible when wires are connected and a potential is applied, and the conductor element employing 1-2TER may be easier to handle as a conductor, conductive film / sheet / electrode than the 3-terminal type. • When used in the power generation section of large-scale solar cells in terrestrial and space solar power plants, space structures, space stations, etc., 1-3TER may require a circuit to drive the gate electrode and its wiring network, but with 1-2TER, the voltage to the gate electrode can be applied internally by 1-2TER, making it easier to construct large-scale solar power generation systems and large-scale circuits. (The use of 1-2TER can be considered not only for solar cells, but also for conductor elements 1 used in electrodes and wiring sections of electronic components, batteries, motors, actuators, sensors, etc.) • Conductor element 1 can be operated as a low-side switch type instead of a high-side switch, or in the same way as the electrical circuit example of a general transistor component. (Conductor element 1 is also a transistor.) • The 3-terminal type has the advantage of being able to change the magnitude of the voltage VGS applied to 106 and the polarity of VGS.For example, in the thermoelectric conversion element 2TCE shown in the drawing, voltages with different polarities and magnitudes can be applied individually to the n-type and p-type semiconductor parts. Even if 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, and there is a difference in carrier density, it may be possible to artificially generate carriers in the n-type part by making the voltage of the gate electrode of the n-type higher than the voltage of the gate electrode of the p-type, and control the amount of carriers to match that of the p-type.

[0010] <Use in Thermoelectric Conversion Elements> A thermoelectric conversion element 2TCE is devised that uses the aforementioned 104 with increased carriers. If the conductor element 1 of this invention is a P-type semiconductor and 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 possible to use it in a thermoelectric conversion element. As shown in Figure 11, gate electrodes 106N, 106NG and 106P, 106PG corresponding to the N-type and P-type respectively can be provided, and voltages VGSN and VGSP can be applied to 106N and 106P respectively, so it may become a thermoelectric conversion element with increased carriers in the P-type and N-type parts. Furthermore, if the present invention can increase the carrier density even with carbon-based materials, especially organic semiconductors and some inorganic semiconductors (including inorganic semiconductors such as copper oxide as in Patent Document 1, and perovskite semiconductors used in so-called perovskite solar cells), then the resource constraints of specific elements will be eliminated, and it may be possible to mass-produce thermoelectric conversion elements by using semiconductor materials with unlimited resource quantities for 104 (101). (In known thermoelectric elements, the use of Bi2Te3 alloy has been confirmed, and it uses elements such as Te, which are limited in resource quantity.) Thermoelectric elements are widely used in wearable devices, waste heat power generation, physical batteries for artificial satellites, and thermal batteries, and it may be desirable that they be produced cheaply and in large quantities, especially when they are to be popularized for wearable applications. <When the conductive element 1 uses semiconductors and insulators> When forming 104 and 1042, 101, 101P, and 1012 of 1 may use not only conductive 101 and 1012, but also material parts 101 and 1012 that behave as semiconductors. For example, 1012 is a semiconductor layer with a high band gap Eg (a material that can also be considered an insulator in everyday life), such as aluminum nitride (AlN) (or boron nitride (BN), boron nitride nanotubes (BNNT), silicon carbide (SiC), gallium nitride (GaN), diamond (C), titanium oxide (TiO2), tin oxide (SnO2), zinc oxide (ZnO), indium tin oxide (ITO), or indium gallium zinc oxide (IGZO)). 1042 may be formed on 1012 (the semiconductor / insulator such as AlN with a high Eg) to function as an n-type or p-type semiconductor layer 1042. A semiconductor device using the 1042 may also be constructed.The above 1042 may be used to construct electrodes or transparent electrodes (including solar cells, light-emitting elements, laser elements, ultraviolet laser elements, EL or liquid crystal display devices). 101 and 1012 include graphene, CNTs, some organic semiconductors, and the above ZnO, SnO2, TiO2, ITO, and IGZO include materials used for transparent electrodes. 101, 101P, and 1012 include semiconductors and conductors. For example, they may include Group 14 elements listed in the periodic table of elements, and the Group 14 elements may include diamond C as a material with a high band gap, silicon Si and germanium Ge as semiconductor materials with a low band gap, and tin Sn and lead Pb as conductive materials.

[0011] <<Background of this application>> ●The first reason is the soaring price of metal resources due to the expanding demand for electric vehicles, and the need to reduce the amount of copper used. *However, the device of this application may also be a hybrid electrode combining carbon material or conductive polymer with electrodes formed from a mesh of aluminum or copper. The intention of this application is to reduce the amount of copper and other metals used in wiring materials. This application does not limit the use of copper. A gate electrode containing aluminum may be used in 106 to form 104.

[0012] ●The second reason is the recycling problem of metal resources from large devices, structures, and buildings used in outer space. The inventor has disclosed large-scale solar cells and secondary battery wiring and electrodes, or aircraft, spacecraft, satellites, and structures (orbital ring devices, orbital elevator devices) containing such electronic components in Patent Document 2, JP 2022-058853, or JP 2022-105726, etc. (The structures and aircraft claimed in Patent Document 2 may include secondary batteries mounted on electric aircraft, such as lithium-ion batteries, which contain copper foil and aluminum foil. Solar cells also utilize metal electrodes, although not as thick as those of lithium-ion batteries.) The devices and structures are proposed with the expectation that they will be incinerated upon re-entering the atmosphere after the mission is accomplished. If such devices and structures are equipped with finite resources such as copper, they will fall to Earth somewhere, such as the ocean, incinerating as they go after re-entering the atmosphere. If copper-containing incinerated materials fall into the ocean, mix with other materials, sink, and disperse, it becomes difficult to recover copper resources (similar to recycling copper from household appliances on Earth). Metal elements launched from Earth may disperse and become diluted when they fall back to Earth, making reuse and resource recovery difficult. When large structures in space exceed their service life and require replacement, it would be preferable to be able to exchange replacement parts via low-cost means of transportation between space and Earth (such as orbital elevators). (Even if metal atoms are not present, the structure may contain sulfur, which leads to the generation of SOx, and a large amount of sulfur may be released as SOx upon re-entry into the atmosphere, potentially increasing the environmental burden. Preferably, it would be highly desirable if replacement parts could be exchanged using a so-called orbital elevator, etc.) However, in the event of a large-scale structure being involved in an accident and burning up and falling to the ground, or when it is desirable to reduce the effort required to recover a large structure using manpower or robots, even with means such as an orbital elevator, it may be desirable to remove the structure from orbit all at once (like demolishing a building on the ground) and incinerate it upon re-entry into the atmosphere (or it may be incinerated as a result of an accident).• At that time, there is a risk that resources, including metals and rare elements, from inside the aircraft and structures will be dispersed to the ground, and if this continues, the construction and use of large-scale structures in space may not be sustainable in the future (and may not lead to sustainable development).

[0013] ●The third reason is the use of resource-saving actuators for robots. ·In electric vehicles, secondary batteries make up a large proportion of the equipment. Among vehicles, unmanned aerial vehicles, and robots including humanoid and multi-legged robots, robots that travel long distances after charging, such as transportation equipment, may use a lot of metal resources in their batteries. ·On the other hand, for humanoid, multi-legged, and other robots that are connected to the power grid and receive power from it, the capacity of secondary batteries and energy storage devices can be reduced, so it is thought that the proportion of the cost of motors and actuators (including artificial muscles and actuators using dielectric elastomers as described in Non-Patent Literature 1) and wiring materials in the product will be higher. We thought that if the use of resources such as copper in the aforementioned motors, actuators and power distribution materials can be reduced, the constraints on metal resources will be lessened and it may contribute to the spread of robot products. ·We also think it is necessary to lighten the batteries and motors of robots and robot suits.

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

[0015] For the four reasons and perspectives mentioned above, reducing the amount of metal used in wiring materials, wiring components, and electrodes is a challenge. To address this, this application proposes the idea of ​​incorporating a means to generate an electric field effect into wiring materials and electrodes, so that a mechanism for increasing carriers in electric double-layer transistors can be utilized in carbon materials and organic conductive materials, which normally do not have the same conductivity as metallic materials. We also propose motors, actuators, electronic components, electrodes, battery electrodes, and batteries that incorporate the aforementioned means. For safe devices and systems, this application proposes incorporating a mechanism to improve conductivity into carbon-based conductive materials, which are thought to have fewer restrictions on the amount of elements, and proposes a system 3 (3.3WIRE, 3BATT) that uses the aforementioned mechanism to detect danger and change the conductivity within electronic components and batteries. <Note> The inventors believe that, in the short term, there will be no problem even if devices and structures made of copper, etc. are used in space development. Furthermore, metals such as copper should be used in devices where they must be metal not only for conductivity but also for mechanical material properties and various performance aspects. However, in the long term, assuming that humanity will venture into space and operate in space, it may be undesirable to re-enter Earth's atmosphere in a state where it is difficult to recycle and scatter the Earth's copper resources (finite resources), and therefore, we propose the aforementioned element 1. In terms of resource abundance, Earth and nearby satellites and planets (Venus and Mars) contain carbon, which forms the basis of the carbon-based conductive material we wish to utilize in this application. (In addition to C, conductive elements may also be formed using silicon Si with this method. 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 and use them for secondary batteries and motors, we attempted to use the 104 portion of an electric double-layer transistor (although this has not been demonstrated) as the copper electrode foil of a secondary battery or the conductor of a motor. The conductor 101 of this application is a carbon-based conductor (may include graphite, graphene, carbon nanotubes, organic semiconductors, conductive polymers, inorganic semiconductors, inorganic conductors, and metals such as iron).

[0016] <<Examples and Hypothetical Cases>> <<Batteries with High Energy Density>> When the conductive element of this invention is used as a foil-shaped element in a secondary battery, we also consider lithium-ion batteries containing ionic liquid, and secondary battery devices with higher electromotive force than lithium-ion batteries that utilize the wide potential window of ionic liquid.

[0017] ●For example, in contrast to lithium-ion batteries in which cationic lithium ions move, fluoride-ion batteries and fluoride shuttle batteries (FSBs) in which anionic fluoride ions move are known. Patent document 3 is cited as a document on fluoride-ion batteries. ●Paragraphs

[0041] to

[0057] of Patent Document 3 describe the components of a fluoride-ion battery (which may be a primary or secondary battery). 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 collectors include foil-like, mesh-like, porous, etc. The electrolyte layer may be a liquid electrolyte. ●In this application, the current collectors (negative electrode current collector and positive electrode current collector, 201NEC and 201PEC) can be formed as layers on 101 containing 104 into which a carrier has been introduced. When 101 is a carbon material, the conductivity of the portion of 201NEC·201PEC close to 104 (the region of 201NEC·201PEC close to 101 close to 104) may be improved in the present configuration with 104 compared to the absence of 104, potentially improving the current collection performance of the current collector or electrode.

[0018] <Battery and Element 1 Including Sensor> ●The use of a PTC thermistor as an element to protect the battery is known in Patent Document 4. In this application, we propose a battery device that includes a sensor 3SEN that controls the gate electrode 106 of the conductive element 1 of this application, a gate driver 3CGATE, and a control unit / control unit 3C, which allows a sensor attached to the battery to sense inputs such as strong shocks being applied to the battery.

[0019] • Batteries with high energy density (or high power density) are prone to explosion and combustion when damaged, such as when impaled in an accident (bent and damaged internally, such as separators), causing a short circuit in the internal electrodes. This releases the energy stored in the battery. • Therefore, this invention proposes safety mechanisms, as shown in Figures 9 and 10, to prevent internal short circuits when a battery is impaled with a nail or similar object. The control unit and control unit sensors detect signs of an accident that could destroy the battery (such as impalement of the battery, a 3-battery in a vehicle being hit and destroyed in a traffic accident, or an aircraft carrying a 3-battery crashing), such as changes in impact and acceleration, changes in flight altitude, changes in speed, battery distortion due to swelling of the battery or deformation of other components surrounding the battery, changes in sound such as collision sounds, changes in sound or abnormality detection when ultrasonic probes or echoes are applied to the battery or other protected object, changes in odor, sensors that detect chemical substances, threats approaching the battery captured by a camera, changes in atmospheric pressure and pressure, and changes in temperature. The control unit and control unit sensors then turn off the gate of the conductor element 1 of this invention, thereby reducing the conductivity of the battery's internal electrodes. This prevents accidents such as internal short circuits between the highly conductive positive and negative electrodes, rapid discharge, and ignition.

[0020] - In the case of batteries for vehicles or aircraft and other transportation equipment, the control unit provided in the battery detects external hazards to the transportation equipment (objects that may collide with the equipment as detected by the camera) using an automobile computer C1 mounted on the transportation equipment and a camera mounted on C1. C1 transmits a control signal to the battery controller 3CBATT via a signal communication path. The 3CBATT then controls the gate driver circuit 3CGATE according to a stored procedure in response to the received signal / data, and may vary the voltage VGS applied from 3CGATE to 106 of 2BATT, thereby controlling the gate electrode of the conductive element. By controlling the voltage of 106, the 104 of 101 may be reduced or eliminated, or 104I may be generated, thereby reducing the conductivity of the internal electrodes of 2BATT.

[0021] <Conductive element 1 whose conductivity is controlled by a sensor> Regardless of the form of the battery, even if it is in the form of an electrical wire or an electrode in the form of a sheet, film, or foil, it may be detected by the sensor / input device described above, and the control unit may control the VGS of the gate electrode according to the result. An acceleration sensor or a speedometer for detecting speed may be attached to the motor (actuator) as a sensor, and if the motor using the conductor element 1 is in a speed range above a specified speed or is accelerating at an acceleration above a specified speed, the sensor connected to the control unit may detect this, and the control unit may control the gate electrode 106 to turn off the capacitor, reduce conductivity and prevent the motor from increasing speed. Sensors and a control unit may also be used in the case of an actuator that can be used in a robot suit. The gate electrode of the conductor element may be controlled according to the input result of wireless communication from an external source.

[0022] <Electrical / Power Applications, Signal Applications> The conductive device that can be constructed according to this application is intended for electrical power transmission applications. Its use for signal applications is not ruled out. The conductive element 1 of this application may be used for wiring to detect sensors and sensor signals in order to sense the aging deterioration of various parts of buildings and structures (space structures, buildings, tunnels, roads, etc.) and the environment in which they are placed. The element 1 may be used for wiring signals and electrical power to operate sensors or input devices including temperature sensors and cameras, or to operate output devices including motors and buzzers. [Prior art documents] [Patent Documents]

[0023] [Patent Document 1] Japanese Patent Publication No. 2022-013089 [Patent Document 2] Japanese Patent Publication No. 2022-058853 [Patent Document 3] Patent No. 6313345 [Patent Document 4] Patent No. 3035677 [Non-patent literature]

[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 Mechanism", 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 controlling the conductivity starting from the measurement results by a sensor, and to provide a safe device and a safe battery.

[0026] • In spacecraft, electric aircraft, electric vehicles, and electric transport equipment, reducing the amount of metal used in the electrode material of secondary batteries has been a challenge. We also considered the need to reduce the amount of metal used in motors. • It was necessary to devise carbon-based conductive wiring, or conductive wiring that could reduce the amount of metal used, as an alternative to wiring materials such as metal foil and metal wire, which are limited in resource availability and used in secondary batteries and motors. • In carbon materials such as graphene and carbon nanotubes, which are based on covalently bonded carbon, or in organic or inorganic semiconductors that can be made by carbon fibers, organic semiconductors, conductive polymers, or coatings, the carrier density may be lower than that of metal conductors, and it was necessary to increase the carrier density n. • Carbon-based wiring materials such as carbon nanotubes and graphene, which contain many covalent bonds, and organic semiconductors and conductive polymers tend to have lower carrier densities n than metals, even if they have high carrier mobility, because they are difficult to introduce, inject, or dope. Furthermore, we do not deny that carbon-based wiring materials may become unstable due to the ionization of their molecular skeleton by doping, or that doping may cause a decrease in mobility. Therefore, we wanted to increase the carrier density n while maintaining high mobility. [Means for solving the problem]

[0027] <Solution> The portion 104 in which the conductive material 101 in an electric double-layer transistor is injected with a carrier is used in batteries including chemical batteries and physical batteries, electronic components, wires, actuators, motors, and other conductive materials and conductor elements 1. (These conductor elements 1 are used in vehicles, transportation equipment, aircraft, robots, or in home appliances, products, and components that use batteries or motors, thereby reducing the weight and cost of the conductor.)

[0028] ●This invention proposes a conductive material, wiring material, and conductive element made of conductive polymer, organic semiconductor, inorganic semiconductor, conductive carbon material, or conductive material, having a carrier-injected 104 by using carrier injection into 104 in the substrate portion of an electric double-layer transistor. Furthermore, it proposes a secondary battery, motor, actuator, and electronic component using the wiring material with 104. ●This invention increases the carrier density n while maintaining high mobility by injecting carriers into semiconductor and conductive materials that have high mobility but are difficult to dope and have limitations in improving carrier density, using the field effect. As a result, the increase or decrease of the carrier density n can be controlled by 106, and in a secondary battery, the carrier density n can be increased during battery charging and discharging, and decreased during battery storage and non-use, using the gate electrode. During storage, even if a short circuit occurs in the secondary battery due to the low conductivity of the electrodes, the high resistance of the electrodes prevents a large current from flowing during the short circuit, thus preventing battery fire accidents. (Figures 9, 10)

[0029] <Battery device capable of preventing short circuits by controlling electrode resistance> ●Lithium-ion batteries can be destroyed by overcharging, external short circuits, and internal short circuits. ·Patent Document 4 is a patent relating to a configuration of a secondary battery with a safety element for lithium-ion batteries. Patent Document 4 uses a PTC element as the safety element to ensure safety against overcharging. ·An example of an internal short circuit is the destruction and short circuit of the battery's internal structure due to external impact. The positive electrode and negative electrode come into contact internally, a large current flows and a short circuit occurs, and if the electrolyte and active material are highly reactive, phenomena such as burning and explosion may occur. ·Other internal short circuits include when metals derived from the electrodes, electrolyte, electrolyte solution, and active material are deposited during the charging and discharging of the battery and pass through the separator to cause a short circuit, or when there are defects in the manufacturing of the separator and electrodes, or when foreign matter and impurities are mixed in. ●Figure 9 shows a case in which the positive electrode and negative electrode grounds of the present application are short-circuited inside the battery, with a metal nail T1 pierced through the inside of the battery. In the aforementioned piercing case, the charge of gate electrode 106 flows to the other electrodes, depleting the charge stored in 106 and 104. With 104 gone, 101 becomes less conductive than 104. If 101 has low conductivity, the conductivity of the positive and negative electrodes using 101 will also be low. Even if the positive and negative electrodes 101 short-circuit internally, the low conductivity of 101 may make it less likely for a rapid discharge to occur during the internal short circuit.

[0030] ●Before the aforementioned impalement occurs, the battery may be equipped with a sensor, such as an acceleration sensor, and the gate voltage VGS may be changed in response to changes in acceleration, temperature, and atmospheric pressure applied to the battery (and changes in operating conditions such as altitude estimated from sensor measurements) to control the conductive elements in order to reduce the conductivity of the battery electrodes and prepare for an internal short circuit. ●In order to prevent an internal short circuit in the battery caused by an accident (such as a traffic accident) in which an electric aircraft or electric vehicle equipped with a battery is damaged by an external impact, the voltage VGS of the gate 106 may be changed to control the application of VGS when the sensor device attached to the battery (acceleration, temperature, atmospheric pressure, humidity, special odor, smell of fire, etc.) is at an environmental value or sensor value (measurement result) that would be undesirable to avoid an internal short circuit in the battery, thereby reducing the electrical conductivity and conductivity of 101 which contained 104. Even if the positive electrode 101 and the negative electrode 101 in the battery, whose conductivity has decreased, undergo an internal short circuit, the low conductivity of 101 prevents the generation of a sudden internal short-circuit current, thereby preventing heating, combustion, and explosion due to the internal short circuit. [Effects of the Invention]

[0031] A gate voltage VGS is applied between the gate 106 and the source to increase the carrier density of 104 and improve conductivity. As a result, a conductor element 1 is constructed that is a conductor and a transistor, capable of forming 104 on the conductor 101. By changing the voltage VGS, conductivity can be controlled. For example, when using a secondary battery, VGS is applied to enable conductivity between the electrodes for charging and discharging the secondary battery. When the secondary battery is not in use or is stored, the application of VGS is stopped, and the potential of VGS is reset or controlled to reduce the carrier density n and lower conductivity, which may reduce reactions, ignition, and heat generation during short circuits between electrodes. (This invention requires demonstration.)

[0032] Furthermore, because it uses ionic liquids with a wide potential window, it may also be usable in batteries that utilize oxidation-reduction reactions and electrochemical reactions that can achieve high potentials. If the conductivity of carbon-based conductive materials, which are lighter than copper and aluminum, can be improved and used in the wiring of secondary batteries and motors, it will lead to weight reduction and resource conservation in robotic suits, spacesuits (including wearable devices), electric vehicles and electric aircraft.

[0033] • While the carrier introduction layer 104 (channel 104) formed by conventional electric double layers is thin (1 nm class), which may result in a small conductive area, as shown in Figure 11, it is possible to form 104 by using a porous layer 101P, or by forming a second conductor 1012 on 101P and then forming a carrier introduction layer 1042 on 1012, thereby increasing the area and improving the conductivity of the conductor. (The surface area per unit volume of the conductor can be increased.)

[0034] • Electric double-layer transistors have a problem with the thin layer of 104, which limits the area available. However, in this invention, by using 101P, the area of ​​104 can be increased, thereby improving the conductivity of the conductive element 1.

[0035] Furthermore, if 104I is generated instead of 104, the polarity of the electrode voltage VGS is reversed from the highly conductive state in which 104 is formed, and a VGS that generates 104I is applied to generate 104I, thereby lowering the conductivity of the conductor element 1 to a level lower than that of the original conductor state.

[0036] However, in the case of porous materials, there remains a risk that the time required to charge the capacitor will increase. Element 1 of this invention requires a charge-discharge time to charge and discharge the capacitor portion, including the electric double layer, in order to achieve the desired operating mode. [Brief explanation of the drawing]

[0037] [Figure 1] Diagram illustrating an electric double-layer transistor (A) and the present invention's device (B). <Figure 1 of the earlier application, Japanese Patent Application No. 2022-123161 (hereinafter referred to as Priority Claim Application 1)> [Figure 2]Connection diagram of the electrical circuit between the external circuit EXC1 and the conductive element 1. <Figure 2 of the same application> [Figure 3] Diagram illustrating the process of using the copper foil with active layer for a LiPo battery according to Application 1 (explanatory diagram of the conductive element 1FILM in the form of a film, sheet, or foil) <Figure 3 of Application 1> [Figure 4] An example of a 2BATT battery utilizing the conductive element of this application. <Figure 4 of Application 1> [Figure 5] An example of a 2WIRE conductor utilizing this application. (Including a motor coil) (This is a 2WIRE conductor element of the conductor type in which the copper core wire portion of a coaxial cable-like cable is used as the gate electrode 106, 106 is covered with 105, and the outer circumference of 105 is covered with a cylindrical 101, and when a gate voltage VGS (VG) is applied to 106, 104 is generated at 101.) (An arrangement in which 106 to 104 and 101 are reversed in Figure 5 is also conceivable.) <Figure 5 of the same application> [Figure 6] Diagram illustrating an actuator using EAP (201EAP) based on this application (EAP: Electroactive Polymer. The configuration in Figure 6 can also be adapted for a piezo actuator using EAP as a piezoelectric element. A magnetostrictive element configuration in which a magnetic field is generated by the coils (2COIL) in Figure 5 and applied to the magnetostrictive material is also conceivable.) <Figure 6 of the same application> [Figure 7] Diagram illustrating photoelectric and thermoelectric elements utilizing this application. (Diagram illustrating solar cell device (2PV) and light-emitting elements such as LEDs and laser diodes utilizing this application.) <Figure 7 of Application 1> [Figure 8] Diagram illustrating the conductive elements (3-terminal type 1-3TER and 2-terminal type 1-2TER) utilizing this application. <Figure 8 of Application 1> [Figure 9] An explanatory diagram illustrating the prevention of short-circuiting when a battery (2BATT) utilizing this invention is impaled with a metal nail. <Figure 9 of the same application> [Figure 10]3BATT is a battery or battery device / battery system including 2BATT, a protective sensor 3SEN, a gate driver 3CGATE, and a battery controller 3CBATT. (The gate 106 and its control unit 3CBATT and gate drive unit 3CGATE may perform control to eliminate the gate voltage or discharge the charge of the capacitor section when the battery is stored.) <Figure 10 of the same application> [Figure 11] An example where the interface between 101 and 105 is large. (For illustrative purposes, the planar 101-105 plane and the comb-shaped 101P-105 plane are shown. Also, 1012 deposited on top of 101P is shown, and the carrier introduction layers 104 and 1042 are also illustrated.) <Figure 11 of the same application> [Figure 12] Diagram illustrating the transmission of photons with shorter wavelengths than UV-B and UV-C from the light-emitting unit 1 to the light-receiving unit 2, and the transport of energy to the ground, aircraft, spacecraft, transport equipment, and carriers (3, 3KAGO). Diagram also illustrating the short-circuiting of the atmosphere and thunderclouds 2THCL by conductive cables 1WIRE, 12 to prevent lightning. Left: Diagram illustrating the orbital elevator 10 having a cage section 15, 3KAGO, with the ground section 14 and space structures connected by cables 12. Right: Diagram illustrating the system with the ground section 14, aircraft 3, and aerial platforms connected by cables 12. [Figure 13] This diagram illustrates a lightning protection method in which photons with shorter wavelengths than UV-B and UV-C, such as X-rays and gamma rays, are irradiated from an upper-air emitter 1 to a thundercloud 2THCL (a light-receiving unit 2, which is the atmosphere in the air). (In Figure 1, the emitter 1 used in a space laser SSPS or an emitter 1 from a stratospheric platform or aircraft 3 may be used during irradiation.) [Figure 14] This is an explanatory diagram of an energy transport method from outer space to Earth, describing the configuration of the present application, which includes a light-emitting unit 1 and a transmitting unit 1, a light-receiving unit 2 and a receiving unit 2, an aircraft 3 including the light-receiving unit 2, a ground-based unit 4, a user 6, and regions such as clouds and the troposphere / stratosphere (Example 1) <Figure 1 of the prior application, Japanese Patent Application No. 2023-007722 (hereinafter referred to as Priority Claim Application 2)>. [Figure 15] An explanatory diagram illustrating the transportation of energy from the light-receiving unit 2, the receiving unit 2, and the aircraft 3 to the energy demand site on the ground. (Example 1) <Figure 2 of the same application> [Figure 16]This is an explanatory diagram illustrating how fuel raw materials are launched to the SSPS by the launching means 9, fuel is manufactured using electricity generated by the SSPS, and the fuel is then dropped to the ground for use. It also includes an explanatory diagram of the launching device 2MS·2MS-SYS-SPIN (Figure 1N of priority application 6) as an example of the launching means 9. (Example 2) <Figure 3 of the same application 2> [Figure 17] This diagram illustrates a system for reducing the metal oxide 5MOX5, collected from celestial bodies such as the Moon and asteroids, using the power and energy of 1PP or SSPS to obtain the reduced material 5M / 5MC, and then transporting the 5M / 5MC to Earth. It also includes a diagram illustrating a transport device 3 / spacecraft that utilizes the 5M / 5MC and 5O2 / 5MOX as propellants in a propulsion device 3TH. (Example 3) <Figure 4 of the same application 2> [Figure 18] The upper part of Figure 5 is an explanatory diagram of energy transport from a system (1SSPS-SYS-QZSS-SEIZA) to the ground, in which multiple SSPS satellites / spacecraft (1SSPS-SAT) are deployed in quasi-zenith orbit (QZO) and form a constellation. (Example 4) <Figure 5 of the same application 2> [Figure 19] The upper part of Figure 6 is an explanatory diagram of a formation of aircraft 3FORM, or a humanoid doll device or humanoid robot, which can be operated by being (constantly) powered by aircraft 3. It is an explanatory diagram for taxi and cargo transport applications. (Example 5) <Figure 6 of the same application> [Figure 20] An explanatory diagram illustrating how power and energy are delivered to tags 2TAG via wireless power transmission from aircraft 3 or drone 3DRONE to manage the tags and the objects attached to them. (Example 6) <Figure 7 of the same application> [Figure 21] Diagram illustrating a robot / exhibit modeled after a living organism, formed using 3FORM. (Example 7) <Figure 8 of the same application> [Figure 22] An explanatory diagram of an unmanned flying robot 3, which is equipped with a robotic arm and tools (e.g., a saw). (Example 8) <Figure 9 of the same application> [Figure 23]Figure 10 of the same application illustrates the laser emission lines, laser energy focus, and laser energy scattering after passing the focus when lasers are irradiated from multiple light-emitting units 1 of the quasi-zenith orbit group to light-receiving units 2. (Figure 10 of the same application illustrates the claim that laser energy will be less likely to reach houses on the ground when irradiated.) [Figure 24] An explanatory diagram of an aircraft 3 system capable of outputting energy obtained from a light-receiving unit 2 to the outside as electricity, light, fuel, chemical substances, or various other forms of energy. (Also an explanatory diagram of an aircraft 3 equipped with a hot air balloon 3HAB and a propulsion system 3TH that may be operated using the energy of the aircraft 3's battery, fuel, or SSPS.) <Figure 11 of the same application> [Figure 25] Diagram illustrating a water supply device 3 and a method of using water, which may include a light receiving unit 2, into which water obtained by collecting rainwater, snow, or 4H2O from the ground is supplied, and water is delivered to places where there is a demand for water, places where fires need to be extinguished, etc. (Example 9) <Figure 12 of the same application> [Figure 26] Diagram illustrating the orbital elevator 10 and aerial platform 3. [Figure 27] Diagram illustrating the orbital elevator 10 and the ring-shaped space structure 1 (e.g., Figure 1A-B of priority application 3) [Modes for carrying out the invention]

[0038] <Example of Conductor Element 1 Configuration> In the above element 1, 101 is composed of a carbon-based material including an organic semiconductor, conductive polymer, carbon material, graphene, and carbon nanotubes. 105 is an insulating layer. A porous separator layer containing an ionic liquid or the like may also be used. 106 is the gate electrode. 102 and 103 are the source and drain portions of 101, including 104, through which current flows due to carriers. 104 is a carrier introduction layer formed on 101 (this is the channel portion of the transistor).

[0039] <Increase in Interface> We focus on the interface where 104 of 101 is formed in contact with 105. The thickness of the electric double layer is about 1 nm. As shown in (A) of Figure 12 (Figure 11 of this application), if the contact surface of 101 and 105 is flat, the 104 formed at the boundary between 101 and 105 may be a planar region of about 1 nm. Therefore, by using 101P as shown in (B) of Figure 12 (Figure 11 of this application), the ratio of the surface of conductor 101·101P in contact with the ionic liquid to the total volume of the conductive layer 101P can be increased (a gap is also created in the total volume, resulting in a so-called porous film 101P), and when VGS is applied to the gate 106, the surface area where 104 is generated is increased, and as a result the area of ​​104 of 101P as a conductor (conductor area A) is increased, and the conductivity of the conductive element 1 including 104 formed on 101P can be improved. (By using 101P, the area A can be increased, and the increase in conductivity due to the formation of 104 can be made larger. Also, if the decrease in conductivity due to the formation of 104I can be made larger.) · 101P is the portion of 101 when 101 is a comb-shaped, pillar, or porous electrode / conductor material. · As shown in (C) of Figure 12 (Figure 11 of this 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 class of several nanometers. · Carrier introduction layers 1042 or 1042I formed by using 1012 and applying VGS to the gate 106 may be used. (The second conductor 1012 may be a conductive material formed on the surface of 101 or 101P. 1012 may be thinner than 101.) ●The configuration that uses 101P to increase the surface area of ​​104 and 1042, thereby increasing the conductive area of ​​104 and 1042, and improving conductivity and increasing the controllable range of conductivity, may be used in the conductor element 1, conductors, coils, motors, conductive sheets, films, foils, batteries, and electronic components (photoelectric conversion elements, thermoelectric conversion elements) of this application.

[0040] <Control of gate electrode according to the type of 101 (carrier type and material compatibility)> This invention proposes a conductive element that controls the conductivity of 101 according to the positive and negative polarity and magnitude of the voltage of VGS applied to 106, thereby becoming a conductor for wires, batteries, and electronic components. When a metal (iron, copper, silver, gold, etc.) in which electrons are the majority of carriers is used as 101, the conductivity of the metal is increased or decreased depending on the positive and negative polarity of the arranged ions when a voltage is applied to a gate electrode with anions arranged on the surface of 101 and when a voltage is applied to an electrode with cations arranged on the surface of 101. When 101 is a metal, 104 and 104I may be formed depending on the magnitude and polarity of the voltage applied to 106. • This invention has two main perspectives: increasing the conductivity of 101 and 104 with a gate electrode for use in conductive elements and electrode wires, and reducing the conductivity of 101 for purposes such as protecting high-energy batteries from internal short circuits. It utilizes the application of voltage to 106 to form 104, eliminate 104, or generate 104I. • Furthermore, there are combinations of materials constituting element 1 that can cause chemical reactions, corrosion, and etching, and if these occur depending on the polarity and voltage, the gate electrode is designed taking this into consideration.

[0041] <<Example of Manufacturing Conductor Element 1>> <<Manufacturing of 1FILM>> We will now consider the manufacturing of the film or foil 1FILM of the conductor element 1 shown in Figure 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. Coat 105 onto 106. 105 may be a separator layer 105SEP that can insulate 106 and 104-101, and contains material for constructing an electric double layer transistor, and contains an ionic liquid. 3. After coating and forming the film of 105, coat 101. 101 may contain 101P. (3-2. After coating and forming the film of 101P, 1012 may be formed on 101P.) 3A. 105 may be coated onto the layer of 106 and bonded to a sheet containing 101 or 101P. You may apply 105 to layer 3B.101 and bond it to sheet 106. *It is necessary to impregnate 101P with ionic liquid.

[0042] <Manufacturing of 1WIRE> We will now discuss the manufacturing of the 1WIRE conductor shown in Figure 5. 1. Prepare a gate wire 106. (The wire 106 may be a composite material of a thin metal wire such as aluminum and a carbon material, and a thread-like material with mechanical strength may be included in the composite material of 106. 106 is mainly an electrode wire for charging the capacitor section that forms an electric double layer, and multiple materials may be combined to achieve this purpose while providing the necessary mechanical strength as a conductor.) 2. Apply 105 to 106. 105 can form an electric double layer and may also include 105SEP, which has a separator function. 3. After applying and forming the 105 film, apply 101. 101 may include 101P. (3-2. After applying and forming the 101P film, 1012 may be formed on top of 101P.) *Alternatively, after applying and forming the 105 film, it is sufficient to arrange 101 so as to surround 105. For example, the 106 coated with 105 can be wrapped tightly with a material that can be wound, such as a sheet 101 or a thin wire 101. (Similar to how the thin wires of the braided copper wire of the outer conductor of a coaxial cable are arranged to surround the dielectric, 105 can be braided or wound around using the wire of 101.) 4. This becomes a bare wire 1WIRE. (4-2. Multiple 1WIREs can be used to make a stranded wire.) 5. If the 1WIRE is an insulated wire, an insulating cover 1COVER is applied on top of 101. Multiple bare wires 1WIRE can be bundled together (by twisting them together, etc.) and then an insulating cover 1COVER is applied to make an insulated wire. [Examples]

[0043] <Conducting element 1 using 101P or 1012 as shown in Figure 11> When implementing the present invention, using 104 or 1042 formed as shown in (B) or (C) in Figure 11 increases the surface area (conductive area A) of 104A per unit volume, and can improve the conductivity of the conductive element 1, compared to using a flat 104 with a flat 101 as shown in (A) in Figure 11. Therefore, 101P or 104 or 1042 formed with 101P can be used. In this embodiment of the present invention, 101P may be used.

[0044] <In the case of electrodes, batteries, and electronic components> Figure 1 is an explanatory diagram of an electric double-layer transistor (A) and the present invention's device (B), and Figure 3 is an explanatory diagram of the case in which copper foil with an active layer, such as in a LiPo battery, is used in the present invention. (This is an explanatory diagram of the conductive element 1FILM in the shape of a film, sheet, or foil.) Figure 4 is an example of a battery 2BATT that uses the conductive elements 1 and 1FILM of the present invention.

[0045] <Mechanical-electrical conversion applications> Figure 6 is an explanatory diagram of an actuator using EAP (201EAP) utilizing the present invention, and the configuration in Figure 6 can also be adapted for a piezo actuator that uses a piezoelectric material instead of EAP. In the configuration of Figure 6, instead of EAP and 1FILM, a magnetostrictive element can also be considered in which a magnetic field is generated using a magnetostrictive material and 2COIL and applied to the magnetostrictive material. In Figure 6, for a piezo element using 1FILM (and 1WIRE) of the present invention in the wiring part and electrode part of the piezo element of a vertical displacement type piezo actuator, element 2ACT is a configuration in which the piezo element part is EAP. · A voltage for gate driving is applied from 2ACT-DRV to gate drive lines A and B to increase conductivity, and then a voltage for EAP driving is applied from 2ACT-DRV to operate the actuator. • The source (or gate) of the alpha (positive electrode) of 1FILM connected to EAP drive line A, and the source (or gate) of the beta (negative electrode) of 1FILM connected to EAP drive line B, are subjected to an EAP drive voltage from 2ACT-DRV to drive the EAP or piezoelectric layer. • The electromechanical element, which includes an EAP or piezoelectric element sandwiched between 1FILMs as shown in the configuration of Figure 6, can also be operated as an actuator and can be used to generate electricity by receiving mechanical forces from the movement of people or objects, or as a sensor to sense mechanical forces.

[0046] <Applications of Photoelectric and Thermoelectric Conversion> Figure 7 is an explanatory diagram of the photoelectric conversion element 2PCE and the thermoelectric conversion element 2TCE that utilize the present invention. 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 invention. The conductive elements of the present invention are used in the electrodes and semiconductor parts of the aforementioned elements.

[0047] <In the case of a conductor> Figure 5 shows an example of a 2WIRE conductor utilizing the present invention. It includes a motor coil 2COIL that can be constructed using a conductor. The copper core wire portion of a coaxial cable-like cable is the gate electrode 106, 106 is covered with 105, and the outer circumference of 105 is covered with a cylindrical 101. When a gate voltage VGS (VG) is applied to 106, 104 is generated at 101. This is a 2WIRE conductor element of the conductor type. (It is also conceivable to reverse the arrangement of 106 to 104m101 in Figure 5.)

[0048] <Integration of gate terminal 106 and its control unit into conductive element 1> Figure 8 is an explanatory diagram of conductive elements (3-terminal type 1-3TER and 2-terminal type 1-2TER) that utilize the present invention. The present invention uses the terminal configuration of 1-3TER, but if the conductor is extended by connecting conductors in series with wires, etc., the 1-2TER configuration can be used, as it is only necessary to connect both ends of the 2-terminal element when connecting, thus simplifying the extension of the conductor by conductive element 1.

[0049] The conductor elements 1 and 1-2TER of this invention are intended for use in electric wires and conductors (including coils and motors that use conductors). They may also be used in electronic components that deploy or house large-area, large-scale electrodes (solar cells, LEDs, LDs, OLEDs, digital signage, liquid crystal displays, batteries, capacitors, piezoelectric, magnetostrictive, and EAP actuator elements, micro-electromechanical system elements, MEMS elements, NEMS elements, inkjet heads, digital mirror devices, image sensors, thermal imaging sensors, and various electrical circuits).

[0050] <Use as a 2-Battery> Figures 3 and 4 show examples of secondary batteries. In lithium-ion polymer LiPo batteries, active material and positive electrode material are coated on both sides of the copper foil. In this application, a gate foil 106 is made and a separator layer 105SEP that can contain an ionic liquid is provided, electrode layers 101 and 101P are coated on the outside of it, and active material 201 is coated on the outside of that. In the LiPo battery, when aluminum metal or a composite material of that metal and other materials is used for the gate element, it is conceivable that this could be used to replace or reduce metals that are heavier and have higher material costs than carbon-based materials such as copper. For example, in a system using copper and aluminum electrodes, such as a lithium-ion battery, by using the conductive element of this invention for the positive electrode and aluminum foil for the negative electrode, the amount of copper used can be reduced compared to existing configurations that use copper for the positive electrode. Furthermore, the conductivity of the positive electrode can be switched on and off by the gate, and by turning off the gate 106 of the positive electrode during storage, it is possible to prevent overheating due to short circuits during storage (it is expected that the contact between the low-resistance positive electrode and the existing aluminum negative electrode will result in low resistance on the aluminum side, but high resistance on the positive electrode, making it less likely for a large current to flow during an internal short circuit, causing the LiPo battery to swell or catch fire and explode). This may lead to increased battery safety and a reduction in the use of limited metal elements.

[0051] <Use of Battery System 3 and 3BATT Equipped with Sensors and Control Units> Figure 9 is an explanatory diagram for preventing short circuits when a battery (2BATT) using the present invention is impaled with a metal nail. Figure 10 is an explanatory diagram for 3BATT and its protection mechanism, including 2BATT, a protective sensor 3SEN, a gate driver 3CGATE, and a battery controller 3CBATT. In Figure 10, the conductive element 1 of the present invention is used as electrode foil for the battery electrodes, and the sensor 3SEN and the gate driver 3CGATE connected to the battery gate 106 are connected to the controller 3CBATT. The controller 3CBATT measures sensor values ​​corresponding to the sensor type of 3SEN for the environment 3BCE around the battery using 3SEN, and controls 3CGATE according to the measured sensor values, and 3CGATE controls the VGS of 106 of 2BATT. The 3BATT unit uses a control unit 3C and sensors 3SEN (specific examples of sensors include 3A and 3T) to control the 106 of the 2BATT unit. When the 2BATT unit is not charging or discharging, or during storage, or when the 2BATT unit is damaged and an internal short circuit may occur, the voltage applied to the 106 is controlled to either eliminate the 104 or generate the 104I, thereby increasing the resistance between the positive and negative electrodes of the 2BATT unit. This makes it difficult for a large current to flow between the positive and negative electrodes during an internal short circuit, preventing battery damage (ignition and explosion) and ensuring battery safety.

[0052] ●This invention aims to provide a lightweight and safe battery that, by using a conductive element 1, is lighter than batteries containing copper, eliminates resource constraints derived from metal elements, or reduces the amount of metal resources used, and protects against internal short circuits in the battery.

[0053] ●The 3BATT mentioned above is one embodiment of System 3. As another example, as described in the section "Explanation of Reference Numerals" in this specification under the headings <Acceleration Sensing Element> and <Temperature Sensing Element>, System 3, which uses sensors and conductive elements 1, can be used not only in the form of a battery system 3BATT, but also in the form of a wire system 3WIRE, etc.

[0054] <Use of 101 and 1012, which are close to insulators, in conductive element 1> • A material that is normally considered close to an insulator due to its wide bandgap, etc., may be used for 1012 to form 1042 with carriers introduced into 1012, and this can be used as the conductive element of this invention. • Materials 101 and 1012 that emit high-energy photons exceeding those emitted by ultraviolet LEDs, deep ultraviolet LEDs, or other such materials (which have a high bandgap and can be considered normally insulators) may be used in this invention. (Semiconductor elements with high bandgap, such as aluminum nitride, or even insulators, may be used for 101 and 1012.)

[0055] <Ionic Liquids / Molten Salts> In developing this invention, it was difficult for individuals to procure ionic liquid reagents, therefore this application is at the idea stage. Ionic liquids are not easily obtainable substances at the time of filing and can be expensive. <Use of Deep Eutectic Solvents> Although ionic liquids are disclosed as an example, the invention is not limited to ionic liquids, and it is acceptable as long as the carrier introduction is performed on the material portion 101 to form the carrier-introduced portion 104. For example, instead of ionic liquids, a flame-retardant solvent with a low vapor pressure, such as a deep eutectic solvent, may be used to dissolve an electrolyte (a substance that generates cations and anions necessary for the formation of an electrical double layer) that can create an electrical double layer, and this electrolyte may be incorporated into the insulating layer 105 of a conductor element 1, a wire 1WIRE, etc. (*Deep Eutectic Solvent (DES): A solvent that becomes liquid at room temperature when hydrogen bond donor compounds and hydrogen bond acceptor compounds are mixed in a certain ratio. It has characteristics such as low vapor pressure, flame retardancy, high thermal stability and electrochemical stability, a wide potential window, and ease of dissolving arbitrary substances, and may be cheaper than ionic liquids. Naturally occurring deep eutectic solvents also exist, which are obtained naturally and are considered to have a low environmental impact. These may be used.) ●Batteries, secondary batteries, capacitors, transistors, wires, and electronic components may be constructed using deep eutectic solvents. (It may be used as a medium for containing the electrolyte in the insulating layer 105 or in batteries, secondary batteries, capacitors, and electrochemical devices. It may also be used in the conductor element 1, wire 1WIRE, battery electrode 1FILM, cable 12, etc. of this application.) ●The configuration of this application only requires the substances, parts, and means of production necessary to create an electric double layer at the interface between the insulating layer 105 and materials 101 and 104. (As mentioned above, it may be realized with other configurations, not just ionic liquids.)

[0056] The scope of the claims is described in paragraph 0063.

[0057] While embodiments of the present invention have been described, these embodiments are presented as examples only and are not intended to limit the scope of the invention. These novel embodiments can be implemented in various other forms, and various omissions, substitutions, and modifications can be made without departing from the spirit of the invention. [Industrial applicability]

[0058] The conductive element of this application (element 1, component 2 / product 2 including element 1, and system 3 of the element including a sensor) has the following intentions and possibilities: 1. In the field of batteries, it provides a battery that is lighter than batteries containing copper, eliminates resource constraints due to metallic elements, and is safer. 2. In the field of motors, it provides a motor that is lightweight and reduces resource constraints due to metallic elements. 3. In the field of wires, it provides a motor that is lightweight and reduces resource constraints due to metallic elements. 4. In the field of sensors, the conductive element 1 of this application may become a switch unit 1 that can turn the conductivity of 1 on and off by a sensor (such as 3SEN and a control unit). The function of the switch unit can be used in 1WIRE, 1FILM, and a battery 3BATT including 1FILM. [Explanation of Symbols]

[0059] <<Transistor Part>> 1: Conductor element. (Not limited to semiconductor elements, so it is written as a conductor element). 101: Conductor or semiconductor. The material part that conducts carriers. May include semiconductors that can normally be considered insulators, such as diamond. (101 includes conductors and semiconductors.) 102: Source electrode (S). 103: Drain electrode (D). 104: Carrier introduction layer. (Channel part 104 of a field-effect transistor) (Carrier introduction layer 104 of a conductivity-increasing type). 105: Insulator layer. * The insulating layer 105 of a field-effect transistor may be used, or an insulating portion 105 that can be used to form an electric double layer, such as a molten salt or ionic liquid (105 may be a porous material or separator that can contain an ionic liquid. Any insulating layer 105 capable of forming an electric double layer is acceptable. * In this application, the purpose is to apply the principle that the capacitor portion of the field-effect transistor using an insulator or dielectric increases the conductivity of 101 including 104 by accumulating charge in 104 of 101, not only to a semiconductor 101, but also to a conductor 101 made of a carbon-based material. Specifically, the configuration of an electric double layer transistor within the field-effect transistor category is used. 105SEP: An insulating layer used for forming an electric double layer, while physically separating it to prevent internal short circuits by including an ionic liquid in the separator, etc. (Separator portion capable of forming an electric double layer). 106: Gate electrode (G). (107: Protective layer) 108: Body part (B). (Body terminal part of field-effect transistor / MISFET). 201: Layers stacked on 101 (may include layers, materials, or structures for realizing a certain function, such as a battery active material layer, a semiconductor layer of a semiconductor device, or an EAP layer). 104I: Reverse carrier introduction layer. (Carrier introduction layer 104I that reduces conductivity) (Layer 104I that introduces a type of carrier that reduces conductivity). 2: Electronic components, wires, sensors, and electrical and electronic application products using the conductor element 1. 3: A system or device equipped with a sensor 3SEN, a control unit 3C, and a gate drive circuit 3CGATE, which increases or decreases the conductivity of the conductor element 1 according to the result of input from a sensor or input device. <Explanation of Figure 11> 101P: Part of the conductor 101 when 101 is a comb-shaped, pillar-shaped, rod-shaped, or porous layer, film, or electrode. (101P may also be a porous film.))・The image of the porous material is a porous film formed by sintering semiconductor nanoparticles in dye-sensitized solar cells, a porous current collector or electrode film containing a current collector formed by coating conductive nanoparticles such as carbon black in the conductor of an electrode in a battery including a dry cell, 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 for a porous material. 101P may be a layer or part for which the ratio of the volume of gap space to the total volume can be determined. Unlike 101 which is made of a plane of a so-called semiconductor or conductor single crystal, 101P may be a conductive layer or film that has many micro- and nano-level voids, is not flat at the micro- and nano-level, and has a volume of gaps relative to the total volume. It may also be a porous film with micro- and nano-level gaps like a sponge. 1012: Second 101. ●It may also be a conductive material 1012 formed on the surface of 101 or 101P. Layer 1012 may be thinner than layer 101. When 1012 is copper or aluminum, its thickness can be reduced, and 1012 is deposited on 101, and 101 can be formed from a carbon-based material such as carbon material, the amount of copper or aluminum used 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 carrier introduction layer 1042I that reduces conductivity) (A layer 1042I that introduces a type of carrier that reduces conductivity). <<Related to electric wires and conductors>> 1WIRE: A conductor using a conductor element. (Example of a conductor using a conductor element). 1COVER: A covering layer for wiring components. 2COIL: A coil made of 1WIRE. 2CORE: A magnetic core. The core of a coil. 2CORE-MGS: A magnetostrictive material for a magnetostrictive element. 2MOTO: Motor (using 2 COILs). (When the specific type of motor is not specified.) 2MOTO-BLDC: Brushless DC motor. (For example, in outer rotor and inner rotor types of brushless DC motors, the 2 COILs can be fixed to the stator side, and the rotor can be rotated by controlling the current flowing to the stator, thereby driving the motor.)As described in Non-Patent Document 2, in the brushless system, a motor drive circuit is necessary, but the elements 1 and 2COIL of this application can be used for the stator coils. 3C: Control unit / controller connected to the gate control unit 106 and sensors. 3SEN: Sensor or input device unit. 3WIRE: Conductor system with a mechanism to control 106 based on sensor measurements from 3SEN. *It is also possible for 1WIRE to have a 1-2TER configuration, and for 1WIRE to include sensor 3SEN and control unit 3C. 1WIRE may also include a temperature measurement sensor 3T or an acceleration sensor 3A as 3SEN. <<2-terminal elements and 3-terminal elements>> 1-2TER: Conductor element 1 with 2 terminals. (The terminals related to the gate 106 are built into 1, and 1WIRE of the 1-2TER type can be connected and used in the same way that existing wires are connected and extended to form a long wire. The 1-2TER type has the effect of eliminating the need for an external circuit / wiring for the gate electrode.) U1: Gate control unit or drive circuit. (May include parts that constitute 3, such as 3C, 3SEN, and 3CGATE). 1-3TER: Conductive element 1 with 3 terminals. (A method in which 106 can be controlled from outside 1.) <<Related to electrodes>> 1FILM: Film, foil, or sheet using a conductive element. (Electrode foil / film electrode). *1FILM can be used as a wide plane as shown in Figure 1 (A) or (B), and there are single-sided electrode types (where either the front or back of the 1FILM becomes an electrode) where one 201 can be stacked for each gate electrode portion, and double-sided electrode types (where both the front and back of the 1FILM become electrodes) where two 201 can be stacked for each gate electrode portion, as shown in Figure 3 (B). 3C: Control unit / controller connected to the gate control unit 106 or sensor. 3SEN: Sensor or input device unit. 3FILM: Electrode system, conductive film / conductive foil / conductive sheet system with a mechanism to control 106 based on the sensor measurement value of 3SEN. 201: A layer stacked near 104·101. (This may include battery electrode layers, battery active materials, semiconductor device electrode layers or active layers, charge transport layers, etc. 201 may also be a layer controlled by electrodes that performs some function; for example, it may be the liquid crystal layer 201-LC when a conductive element 1FILM is used as the electrode for a liquid crystal device.) 201-LC: Liquid crystal layer.<Actuators, converters, and mechanoelectric conversion elements using electrodes and wires> 201EAP: 201 which is an EAP. 2ACT: Actuator (including actuators using EAP; 1FILM may be used). 2ACTS: Element used when 2ACT is used as a pressure sensing sensor, a power generation device that converts the mechanical force of movement of people or objects into electrical force, or a mechanoelectric converter. 2ACT-EXC: External circuit for driving 2ACT. (When the gate drive unit and the drive circuit that drives the functional layer such as EAP or piezoelectric material are driven separately). 2MOTT: Motor. Electric motor. 2MOTTG: Generator using an electric motor, motor-type mechanoelectric converter. <Photoelectric conversion elements> 2PCE(2PV): Photoelectric conversion element. Solar cell as an example of a photosemiconductor element. (Or photodiode, LED, OLED). 2PV-E: Electrode. 2PV-HTM: Hole transport layer. 2PV-AL: Active layer. (In photodetectors, this may be a layer that absorbs light and separates charge; in light-emitting elements, it may be a layer that emits light.) 2PV-ETM: Electron transport layer. 2PV-TE: Transparent electrode. 1WIRE (busbar wiring section): Rod, wire, plate, sheet, or thick film portion made of current-collecting conductor element 1 and 1WIRE. <Thermoelectric conversion element> 2TCE: A thermoelectric conversion element in the conductor element 1 of this application, using N-type and P-type semiconductors in the 104 portion. 104N: Carrier-introduced n-type semiconductor layer, 106N: Guard gate for 104N. 104P: Carrier-introduced p-type semiconductor layer, 106P: Guard gate for 104P. 105N, 105P: Insulator layer made of ionic liquid that creates an electric double layer as a means of introducing carriers. 106NGRID: Power distribution network for applying voltage to 106N. 106PGRID: A power distribution network for applying voltage to 106P (a different power distribution network from 106NGRID). (In Figure 11, it is shown that voltage VGN can be applied to the gate 106N of the N-type semiconductor, and voltage VGP can be applied to the gate 106P of the P-type semiconductor. VGP is a different voltage from VGN, and the polarity of the voltage may be different for the two types of gates.) <Battery> 2BATT: A battery using conductive element 1. 104NE: Carrier introduction layer of 1FILM of the negative electrode. 106NE: Token gate of 1FILM of the negative electrode. 101NE: Conductor layer of 1FILM of the negative electrode. 201NEC: 201 of the negative electrode current collector. 201NE: Negative electrode active material layer. 104PE: Carrier introduction layer of 1FILM of the positive electrode. 106PE: Token gate of 1FILM of the positive electrode.101PE: 1FILM conductive layer of the positive electrode. 201PEC: 201 of the positive electrode current collector. 201PE: Positive electrode active material layer. 201EC: Electrode current collector. 202: Example of a terminal section for extracting charge from the positive and negative electrodes. 105, 105SEP: 1FILM insulating layer. 205: Battery separator. 205E: Battery electrolyte. P1: Charge loss region of the electric double layer due to a short circuit between 106 and 104. (The area where 104 disappears or its charge decreases due to the short circuit, making 101, including 104, a high-resistance electrode). P2: Area where the charge decreases when gate 106 undergoes dielectric breakdown and short-circuits. Nail / Spike: Conductive nail / metal nail for piercing the battery. (A region that occurs when the positive and negative electrodes 104 and 106 inside the battery are short-circuited.) (The short-circuited area when the battery is subjected to collision, impact, accident, etc., and the structure of the battery is altered, with each electrode stretching, breaking, or deforming, causing contact between the electrodes, may be likened to the nail portion.) <Explanation of Figure 10> 3BATT: A battery system that adds a mechanism to control 106 based on sensor measurements to 2BATT. 3SEN: A sensor that obtains information from the surrounding environment to control the conductivity of the conductive element 1. Measuring means. 3A: Acceleration sensor, shock sensor. 3S: Strain sensor (detects battery deformation due to external impact. In the case of a strain sensor attached to the battery, it also detects swelling of the battery / battery pack, etc.). 3K: Contact sensor (a sensor for detecting contact of an object approaching the battery). 3T: PTC element, temperature sensor, temperature measuring means. 3C: Controller, control unit, control means. (May include a control unit such as a computer and a gate drive unit.) 3CBATT: Battery controller, 3CBATT of 3C. 3CGATE: Controller of gate 106. Controlled by 3C. 3BC: Battery housing, container (container housing the battery system). 3BCE: Surrounding environment of the device including conductor element 1 (surrounding environment of battery 2BATT in the figure). 3COMM: Communication device, means of communication for 3C. May communicate wirelessly or wired with other communication devices. C2: External computer. A terminal that can communicate with 3C using the communication device 3COMM of 3C and the communication device of C2. (C1 may exchange, change, and update the control method, program, algorithm, and control variables of the gate electrode of 3C via communication.)In addition, for maintenance and inspection of 3BATT and other components, C2, which has access to 3C, may be commanded to turn the gate electrode on or off, or to change the voltage value or polarity from C2 to 3C. C1: A computer that utilizes 3BATT. For example, an on-board computer C1 that controls a car, which is equipped with an on-board camera CAM connected to the car, and takes pictures of the external environment from the CAM to detect cars and objects that are likely to collide with C1. C1 may also be the control unit C1 of an autonomous vehicle. (It may also be the control computer C1 of a transport machine such as an aircraft equipped with a battery. In the case of an aircraft, sensors detect the crash before it occurs. ) If a crash is detected (or if a crash is detected using a means of sensing a crash), the battery's resistance is increased to prevent the battery case from being destroyed during a crash, which could lead to an internal short circuit between the positive and negative electrodes and potentially a fire or explosion. ). If there is a risk of damage to C1's 3CBATT, voltage control data / commands are sent to the gate electrode of the 3C (3CBATT) of the 3BATT to reduce the conductivity of the battery electrodes, controlling the electrodes to a state of low conductivity. (If a car containing C1 and 3BATT collides and the 3CBATT is destroyed, causing an internal short circuit, the resistance of the 3BATT electrodes is increased to prevent ignition and explosion due to the internal short circuit between the positive and negative electrodes). C1SEN: Sensor for C1. CAM: Camera acting as a sensor for C1. <Supplement to Figure 10> The example in Figure 10 is a battery using a conductive element 1 equipped with a sensor and a controller, in which the controller controls the gate drive circuit according to the value measured by the sensor to control the voltage applied to the gate 106, thereby controlling, forming or eliminating 104 and 1042 (and 104I and 1042I depending on the type of 101 and 1012), increasing or decreasing the conductivity of 101 and 101P, and decreasing the conductivity when it is preferable to decrease it. The above configuration can be used not only in batteries but also in 3FILM using 1FILM and 3WIRE using 1WIRE. Not limited to the form of a battery, a sensor-controlled 3 using 3SET, 3C and 3CGATE can be widely used in electronic components 2 and electrical and electronic products 2 using a conductive element 1. The 3SEN may be a known type of sensor. For example, 3SEN may use an acceleration sensor (3-axis acceleration sensor), a magnetic sensor, a temperature sensor, a humidity sensor, a barometric pressure sensor, a pressure sensor, a strain sensor, a contact sensor / touch sensor, an illuminance / light sensor, an infrared sensor, a camera / scanner / image sensor, an odor sensor, a fire sensor / smoke sensor, a sound sensor, or a wireless sensor (wireless receiver). An external computer C2 may access 3C via wireless or wired communication (using the communication device 3COMM of 3C) to change the program, variables, etc. for controlling the conductive elements of the conductive element 1. Furthermore, the voltage VGS of the gate 106 of the conductive element 1 may be controlled by the external computer C2 via wireless or wired communication through 3COMM of 3C.<Temperature-sensing element> For example, 3WIRE is equipped with a temperature sensor 3T and a control unit / gate drive unit. 3WIRE detects the temperature rise caused by heat during a short-circuit fire or by heat generated before a short-circuit fire occurs using 3T. 3WIRE detects the temperature rise and controls the wire to increase its resistance, thereby preventing the current from flowing and thus preventing the fire. In the event of a building fire, 3WIRE in the power distribution network connected to the room or compartment where the fire originated may be able to fuse itself to prevent current from flowing to the aforementioned room. (3WIRE may be configured as a fuse-equipped element that increases resistance with temperature rise.) <Acceleration-sensing element> <Conducting element system that moves using acceleration sensor, control unit, and gate unit> By equipping not only 3BATT but also 3SEN of 3WIRE and 3FILM with acceleration sensors (3-axis acceleration sensors may also be used), a conducting element system can be configured that has a control unit that increases or decreases the conductivity of 3WIRE or 3FILM according to acceleration (according to gravitational acceleration, or by sensing the inclination of the wire based on the direction of gravitational acceleration). Power distribution and transmission networks are constructed by stringing overhead wires horizontally or in a sagging manner using utility poles, and are used to supply electricity. Power lines for trains and telegraph and telephone lines are also strung. In the above system (where the power lines are not underground but are in the air and sag when cut), it is possible to see power lines strung using utility poles being cut by typhoons, fallen trees, etc., and falling and sagging due to gravity. The sagging wires usually have copper or aluminum parts, and the conductivity of these metal parts does not change due to sagging or tilting, and they are always conductors, so electricity can flow even when they are sagging. Therefore, a wire system 3WIRE can be considered in which an acceleration sensor detects the sagging of the power line, reduces the conductivity of the conductor, or transmits the abnormality detected by the sensor to an external computer C2 via communication between the control unit 3C of the conductor system and C2. The 3WIRE configuration, which includes the acceleration sensor 3A in 3SEN, measures the acceleration change and acceleration during sagging when the wire sags due to gravity, or when the wire breaks and falls or sags, and controls the voltage VGS of the gate electrode 106 according to the measurement results.- A 3-axis accelerometer can be used to measure whether the accelerometer readings indicate that the wire is sagging (when the wire is sagging in the same direction as gravity). If it is determined that the wire is sagging, the gate 106 can be controlled to reduce the conductivity of the 1WIRE and 3WIRE wires. - Alternatively, the conductive 1WIRE and 3WIRE wires (and 1FILM and 3FILM wires) can be equipped with tilt sensors (using an accelerometer), and the conductivity can be increased or decreased according to the tilt of the 1WIRE and 3WIRE wires (1FILM and 3FILM wires).

[0060] <<Contents of the Prior Priority Claim Application, Japanese Patent Application No. 2023-007722>> This application references and uses Japanese Patent Application No. 2023-007722 as a reference. The specification and drawings (Figures 1 to 12) described in paragraph 0060 of this application are the same as the description and drawings described in Japanese Patent Application No. 2023-007722. Figures 1 to 12 described in paragraph 0060 of this application correspond to Figures 14 to 25 described in paragraph 0037 of the "Brief Description of the Drawings" section of this application. <Document Name>Specification<Title of Invention>Energy Transport Method for Space Solar Power Generation System, Energy Transport Method from Space to Earth<Technical Field> <0001> This application relates to a power transmission system and energy transport method for space-based solar power generation systems between space, air, and ground. It also includes a method for transporting energy from space to Earth. <Background Technology> <0003> In Space Solar Power Systems (SSPS), it was necessary to deliver the electricity and energy obtained from solar power generation systems (or solar energy collection devices) placed in space to the ground-based users who had electricity and energy needs. <0004> <Wireless Power Transmission System> As described in Patent Document 1 and Non-Patent Document 1, wireless power transmission, wireless power transfer, and wireless transmission are being considered to transmit power from SSPS to the ground via outer space and air. For the aforementioned wireless power transfer, methods using radio waves such as microwaves, which are long-wavelength photons, and methods using photons such as infrared light or laser light, which are short-wavelength photons, have been proposed and are being considered. Wireless power transfer and supply to electrical devices such as smartphones, electric vehicles, and wireless tags are also being considered. <0005> <System for manufacturing and transporting fuel materials and energy storage materials to demand sites> On the other hand, there may be systems that do not use wireless power transmission or wireless power distribution, but instead consume power on-site near the SSPS, or manufacture fuel materials, energy storage materials, or objects on-site and transport them to the ground, etc. ●It is preferable that the power generated at the SSPS can be used on-site after generating power in outer space, a space station, a lunar base, etc. As an example of on-site use, a system that uses power on the lunar surface (or outer space) to manufacture some kind of fuel and delivers it to a space station or the ground can also be considered, as shown in Figures 3 and 4. <0006> ●As shown in Figure 3, if, for example, water (hydrogen oxide) is sent from Earth to synthesize fuel, and the water is electrolyzed on the lunar surface to obtain hydrogen and oxygen which are then sent back to Earth, there is a problem in that the launch means 9 (or the means 9 for dropping rockets etc. from the Moon to Earth) are high cost. *However, if launch costs decrease, this method may be used. The realization of low-cost rocket-based methods, as well as non-rocket methods such as mass drivers and orbital elevators, is expected.*Furthermore, it is desirable to have a low-cost launching means 9 for launching components and base materials for the construction and building of the SSPS. ●Since this invention is not a design relating to a launching means, details regarding the mass driver and other launching means are omitted. <0007> ●As shown in Figure 4, energy can be obtained through oxidation-reduction by reducing silicon dioxide (or lunar surface oxides such as metal oxides like aluminum oxide, iron oxide, or substances containing water or oxidized hydrogen) contained in lunar rocks and other resources using electricity obtained from SSPS, thereby obtaining reduced materials such as metallic silicon, which can then be transported and dropped to Earth, where the reduced materials such as metallic silicon are oxidized by some method. *However, this system may reduce the mass of the Moon. <0008> ●In the proposed method for transporting the above-mentioned fuel material, in the initial stages of the fuel manufacturing operation, material from the lunar surface could be mined, reduced or stored as energy, and then shipped to Earth as fuel. However, in the long term, it will be necessary to launch objects to the moon to compensate for the amount of material removed from the moon, and in order to restore the lunar mass, an inexpensive launch method is required. ●An inexpensive method of launching from Earth to the moon, or a mass driver, etc., to deliver from the lunar surface to Earth may be possible. (The progress of non-rocket launch methods in the field mentioned in Patent Document 2 and the progress of the use of reusable rockets are desirable.) <0009> According to Japanese Patent Application No. 2021-181539 and Japanese Patent Publication No. 2022-527127, there is a description of a method for manufacturing large-area components such as solar cells, radar, and mirror devices (telescopes, reflectors, and large-area mirror devices that reflect sunlight) by using the vacuum of outer space to fabricate functional films (semiconductor films, metal films, etc.). The system using SSPS shown in Figure 4 of this application may also be used for the (in-situ) manufacturing of solar cells and devices that collect and utilize solar energy in space or near lunar bases using these methods. <0010> ●Solar cells and devices that collect and utilize solar energy may be manufactured using inorganic materials such as silicon dioxide found on the moon. Materials and resources available on the moon may be used to reduce the amount of components that need to be launched from Earth.For example, on the lunar surface as shown in Figure 4, solar cells may be manufactured using lunar resources (silicon oxide and other inorganic materials), electricity from the SSPS, and manufacturing equipment brought from Earth. Silicon oxide (SiO2) may be reduced to silicon (Si), and silicon solar cells may be manufactured and used in the SSPS. Alternatively, crystalline silicon (Si) manufactured for solar cells, or non-solar-grade silicon, polysilicon, or metallic silicon mixed with impurities (if the description is not to limit the scope of the invention, the reduced substance 5MC may also be used) may be used as fuel on the lunar surface or dropped to Earth. Furthermore, in order to reduce the amount of materials launched from Earth, the energy of the SSPS may be stored in lunar resources and dropped to Earth for use on the ground, and a fuel manufacturing method like that shown in Figure 4 may be used. <0011> Alternatively, as described in Japanese Patent Application No. 2021-181539, a launch device 9 may be used to transport solar cell materials from the ground to outer space / the Moon, and a device (solar cell, mirror, reflector) that collects and utilizes solar energy using the solar cell materials may be manufactured. <0012> When launching from Earth, resource-saving materials (examples of such materials: compound semiconductor materials, used in CIGS solar cells, etc.) may be used, as they have a high absorption coefficient in direct transition type solar cells, allowing for thinner photoelectric conversion layers and functional films. If materials such as gallium or indium are needed and it is uncertain whether they can be mined on the Moon, they may be transported from Earth. <0013> <Methods of Energy Transport> This application discloses methods of energy transport, including wireless power transmission, wireless power transfer, wireless transmission, and fuel transport. In this application, wireless power transmission means may be used from SSPS to the ground or air. According to Non-Patent Literature 1, power transmission using microwaves and laser light has been considered. However, in systems using microwaves and laser light, when receiving microwaves and lasers emitted from SSPS, if the transmission power is high, there is a risk of affecting or damaging people, living organisms, the environment, electrical equipment, wireless equipment, and communication equipment near the receiving and light-receiving parts on the ground. As a countermeasure to this, it is envisioned that the system will be operated with reduced transmission power.<0014> ●In this application, the receiving unit 2 and light-receiving unit 2 may be made larger in area, and even with low transmission power, the receiving unit 2 and light-receiving unit 2 (rectenna, etc. in the case of microwaves, photodetector, solar cell, reactor, chemical reactor, chemical reactor using light or heat, etc.) may be used to receive and receive light. (For example, although the energy density of sunlight is rarefied, just as large-area solar cells on the ground receive it, the light emitted from the transmitting unit of the SSPS can be received by a large-area receiving unit on the ground.) <0015> ●In the operation method that reduces the transmission power, in the case of microwaves and radio waves, the receiving unit 2 and light receiving unit 2 need to be large in area, which involves high costs due to large-area rectennas and other issues related to securing land. ●Also, since the photons used for transmission (in the form of laser light and radio waves) have wavelengths that penetrate the atmosphere, even if the transmission power is reduced, there is a risk that residents near the receiving unit and light receiving unit may be worried that photons with wavelengths that penetrate the atmosphere are reaching them or may be reaching them. ●If the orientation of the SSPS satellite changes slightly, photons and radio waves that penetrate the atmosphere may be transmitted and reach residential areas that are not receiving units, and it may be an issue to use types and wavelengths of photons that could cause such worry to people. ●Thus there was an issue that delivering SSPS power to the ground in the form of photons that can penetrate the window of the atmosphere may have adverse effects on people living on the ground, living organisms, and the environment. <0016> When receiving with ground-based equipment 2, the above problem may arise if photons that penetrate the atmosphere are used. Therefore, this invention proposes to construct a wireless power transmission system (wireless power transmission system) for SSPS using photons that do not or do not easily penetrate the atmosphere, and to use it for transmitting, transmitting, and transmitting power or energy for SSPS.<0017> Even photons that do not penetrate the atmosphere can be received by the light-receiving unit 2 in Figure 1 (for example, in the upper troposphere, stratosphere, and upper stratosphere). In order to receive them, the light-receiving unit 2 (air receiving unit / light-receiving unit 2, high-altitude receiving unit / light-receiving unit 2) of the present SSPS is provided as shown in Figures 1 and 2 of the present application on a high-altitude communication platform (HAPS) 3 or on an aircraft 3 / electric balloon 3 located at high altitude in a low-density / rare atmosphere, and the light-receiving unit 2 of the present SSPS is provided on an SSPS etc. located in outer space (SSPS and SSPS This invention proposes wireless power transmission and wireless energy transmission by transmitting, emitting, irradiating, and transmitting laser light with a wavelength of photons that does not penetrate the atmosphere, from an SSPS relay satellite 1LINK (which may be included in multiple transmitters 1 and emitters 1) that link laser light from SSPS and SSPS relay satellites, toward the receiver 2 and light-receiving unit 2 (or by hitting the light-receiving unit 2 with the laser light from the emitter 1, receiving it, converting it into photoelectricity, heating an object or chemical reaction, etc.). <0018> <Comparison with Previously Reported Information> Figure 1 of Patent Document 1 discloses a configuration in which a receiving unit (1) is provided on an airship (5) in the air / troposphere (altitude 10 to 16 km) that receives microwaves and lasers. In this application, the receiving unit 2 and the aircraft 3 may be positioned in the stratosphere at an altitude of 50 km to 20 km. (*Regarding aircraft experience, there is an example of a high-altitude balloon reaching an altitude of 53 km. For information on the world record for the highest altitude reached by an unmanned balloon, please refer to the internet, JAXA, accessed January 19, 2013, 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 they are at ground level, and the atmospheric density in the troposphere is 13% of the density at ground level (1.293 kg / cubic meter). In the stratosphere at higher altitudes (above 20 km where stratospheric platforms are located), the atmospheric pressure is 100 hPa at an altitude of 20 km, and 0.013 kg / cubic meter at an altitude of 32 km. The atmospheric pressure is 10 hPa at an altitude of 40 km.(Reference: Japan Meteorological Agency website, Atmospheric Structure and Flow, accessed January 8, 2023, Internet, https: / / www.jma.go.jp / jma / kishou / know / whitep / 1-1-1.html) ● At an altitude of 16 km, the atmospheric density is 0.16 kg / cubic meter above the troposphere and its boundary, and at an altitude of 32 km, it is 0.013 kg / cubic meter. (At an altitude of 68 km, the density is 0.00011 kg / cubic meter, and atmospheric density and oxygen density decrease near the stratosphere.) From the ground to an altitude of 80 km, the atmospheric composition and the ratio of components such as oxygen and nitrogen are the same as at ground level. From 16 km to 32 km, the amount of oxygen decreases to one-tenth. Therefore, in order to receive short-wavelength photons such as UV-C (short-wavelength photons from ultraviolet to X-rays) that undergo chemical and photochemical reactions with oxygen and ultraviolet light at the light-receiving unit 2 without attenuation in the radiation path, the upper stratosphere at an altitude of 32 km is preferable to the troposphere at an altitude of 16 km. Accordingly, in this application, it is preferable that the altitude of the light-receiving unit 2 and the aircraft 3 be in the stratosphere between 50 km and 20 km. (However, in the case of using an aircraft 3 including the light-receiving unit 2 and a fuel synthesis aircraft 3FUEL, as in the examples in Figures 1 and 2, 3, which is also 3FUEL, may fly from the ground to the stratosphere, and use in a form where the altitude of 3 is not kept constant or irrelevant may also be considered.) <0020> <Air density and photon absorption rate in the troposphere and on the ground> ● The air density in the upper troposphere is 13% of that on the ground, which is about one-tenth. For example, the absorption rate of short-wavelength photons closer to the ultraviolet side, which react with oxygen and ozone, is also about one-tenth that of the ground in the upper troposphere, and is lower than that of the ground. Even if the altitude of the light-receiving unit 2 that receives the short-wavelength photons is set to the altitude of the upper troposphere (16 km altitude), for a certain wavelength of photon, a certain amount (X%) is assumed at an altitude of 16 km. Even if some photons are absorbed by the atmosphere, the remaining amount (100%-X%) may still be received by the light-receiving unit 2, and the present invention may be practically usable with a configuration that utilizes photons that are less likely to penetrate the atmosphere. For this reason, the altitude from the ground at which the light-receiving unit 2 should be placed needs to be determined through demonstration development. This invention discloses the use of photons of ultraviolet light such as oxygen and ozone, or ultraviolet and some infrared photons absorbed by the atmosphere, as atmospherically attenuated photons / laser light for energy transport of SSPS to the air and ground, and does not consider limiting the altitude of the light-receiving unit 2 to the stratosphere. (Regarding the aforementioned photons, for example, this application discloses several cases of photons with high energy, specifically those on the ultraviolet-leaning, shorter wavelength side that can be absorbed by the atmosphere, oxygen, and ozone. In addition, there are wavelengths in the infrared range that are absorbed by atmospheric molecules, and photons of these wavelengths may be usable in the light-receiving unit 2 of this application.) One of the objectives of this application is to ensure the safety of houses on the ground and aircraft navigating the troposphere, by using photons that do not easily reach the ground, and by preventing photons missed by the light-receiving unit 2 due to misfires from the light-emitting unit 1 from reaching the ground. As described in Patent Document 1, the light-receiving unit 2 may be placed at an altitude above the troposphere (altitude 16 km or higher). The receiving unit 2 may be placed at an altitude of 20 km to 50 km above the ground, or at an altitude of 50 km or higher. <0021> ●The light-receiving unit 2 may be mounted on the aircraft 3, and the aircraft 3 may be equipped with propulsion devices 3TH such as rockets, photon sails, or ion propulsion systems in addition to motors and jet engines, in order to perform aircraft movement, such as attitude control and propulsion, even at altitudes where propeller motors and jet engines cannot operate (due to thin air). (The aircraft 3 of this application may be an aircraft 3 that is a solar plane 3 as shown in Figure 11 of this application or in Figures 6 and 7 of Patent Document 2. It may also be an aircraft 3 that is a high-altitude platform HAPS.) <0022> ●In an SSPS capable of continuously transmitting energy to a light-receiving unit 2, the power and energy from the SSPS are transmitted from the light-emitting unit 1 to the light-receiving unit 2, and the energy obtained at the light-receiving unit 2, for example, attached to an aircraft 3, is used to heat 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, or it may be an aircraft 3 or a solar plane 3.<0023> <Light Pollution> ●In the form of this application, short-wavelength photons from ultraviolet to X-rays are invisible to humans, so there is the advantage that the light is not visible even at night. This may reduce the effects of light pollution at night. (When focusing on invisible photons in relation to light pollution, infrared and millimeter waves may also be used in addition to ultraviolet light.) <0024> <Short-wavelength photons proposed in this application> ●This application may use a system in which photons are absorbed by chemical reactions with oxygen and ozone in the atmosphere (at altitudes of 20km to 50km or higher above the ground), such as UV-C and UV-B. This application utilizes the atmosphere. <0025> ●In this application, the laser cannot penetrate the atmospheric window in the atmosphere and troposphere, and 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 or gamma rays if safety can be confirmed during use and it is possible). <0026> UV-B rays are absorbed by ozone, and UV-C rays are absorbed by oxygen, the atmosphere, and ozone. These have the advantage of being difficult to reach the Earth's surface, while also offering the benefit of higher photon energy than microwaves and millimeter waves, making them suitable for use in the present invention's system. <0027> ●Ultraviolet light, including UV-B and UV-C, has a large photon energy per photon, so it may be possible to increase the photovoltaic power by miniaturizing the reactor that uses the energy obtained from the light-receiving unit 2, or by increasing the semiconductor bandgap of the photoelectric converter (photocell), which could lead to miniaturization and increased output of the light-receiving unit 2. <0028> ●The aforementioned ultraviolet light has higher energy per photon than visible light, infrared light, and radio waves, making it easier to use to cause chemical reactions in materials, thus offering advantages in fuel production. For example, considering photocatalysis, photocatalytic reactions using titanium dioxide do not occur with low-energy photons such as millimeter waves or infrared rays. Photocatalytic reactions occur with photons such as ultraviolet light that have energy greater than the band gap of titanium dioxide. ●If the light-receiving unit 2 is a photocatalytic device or reactor, photocatalytic reactions cannot occur in the light-receiving unit 2 in systems using microwaves or millimeter waves, but as claimed in this application, for example, in systems using ultraviolet light (UV-A, UV-B, UV-C), photocatalytic reactions can occur in the light-receiving unit 2.<0029> ●When producing fuel using photocatalysis or a chemical reaction between light and matter, there may be an advantage in using photons such as ultraviolet light 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 converter may be low. (※When heating an object regardless of the energy of the photons in receiver 2, heating can be done using radio waves such as millimeter waves and microwaves. Also, in 2 and 3, which are used for heating with microwave radio waves, 3, which is a hot air balloon, may be usable for heating the hot air balloon or the gas heating element of the hot air balloon.) <0031> ●Radio waves require large-area rectennas, etc., and it is difficult to concentrate the energy like laser light. On the other hand, in the form of tags described later, such as 2TAG, beacon tags, and RFID tags, the ease with which energy dissipates is used for the operation of the tags.Disclosures will be made regarding tag retrieval from aircraft 3, and the transmission of energy derived from SSPS as laser light or radio waves for tag retrieval from aircraft (for monitoring purposes). <0032> This invention utilizes the wavelength of the photons used and the absorption and attenuation of photons in the atmosphere to create a fail-safe design where photons do not reach and are attenuated in residential areas and houses below the atmosphere and troposphere. The intention of this fail-safe design is that even if the attenuation is caused by a misalignment of the transmitting unit 1, and photons are irradiated in the direction of houses rather than the receiving unit 2, the photons have short wavelengths, such as UV-B, UV-C, and X-rays, which act on atoms and molecules, causing chemical reactions with atmospheric molecules and atoms (for example, ozone generation in the case of UV-C), and are attenuated and absorbed by the atmosphere, thus not reaching the ground (reducing the number of photons that reach the ground). This design ensures safety for fixed-wing aircraft in the troposphere and for houses and living organisms on the ground by preventing photons from reaching the ground. <0033> <Generation and utilization of short-wavelength photons> An ultraviolet laser capable of emitting ultraviolet light, or a synchrotron or other particle accelerator capable of generating X-rays, gamma rays, etc. from ultraviolet light (or a free electron laser generator) may be used.<0034> ●For example, in the case of ultraviolet lasers, solid-state devices such as laser diodes for long-wavelength ultraviolet, medium-wavelength ultraviolet, and short-wavelength ultraviolet light, which are made of semiconductors such as aluminum gallium nitride (AlGaN) whose band gap is the same size as the energy of ultraviolet photons, are known and such semiconductor light-emitting devices may be used. <0035> ●To further list without limiting the scope of the invention, wavelength conversion devices (for example, devices or elements that convert wavelengths from infrared light to ultraviolet light may be used. A system using a crystal that converts the wavelength of an infrared laser of 1064 nm using Nd:YAG crystal to ultraviolet light of 266 nm is envisioned) or excimer laser devices (for example, generating UV-C photons with a wavelength of 248 nm when using KrF), vacuum tube devices, etc. may be used. <0036> Short-wavelength photons such as UV-B, (UV-A,)UV-C, far-ultraviolet, vacuum ultraviolet, X-rays, and gamma rays may be generated in the light-emitting unit 1 and transmission unit 1, and these short-wavelength photons may be emitted, irradiated, and transmitted toward the light-receiving unit 2 and receiving unit 2, and power may be obtained by photoelectric conversion by the light-receiving elements 2PCE provided in the light-receiving unit 2 and receiving unit 2. *Since this application is an invention / design relating to an energy transport method of SSPS and its utilization, detailed descriptions of the apparatus and elements that generate photons are omitted. <0037> ●Furthermore, the energy of the short-wavelength photons may be used to irradiate the reactor 2REA or fuel raw materials to cause a chemical reaction and produce fuel. (For example, hydrogen may be produced from water in the receiving unit 2, or carbon dioxide on the ground may be reduced to carbon hydrocarbons and oxygen. The receiving unit 2 may also convert the laser light into photoelectric power and use it to power 2, aircraft 3, transport equipment 3, aircraft formation 3FORM, flying car 3FCAR, and robot 3.) <0038> ●As shown in Figure 6(a), the power converted photoelectrically by the light receiving unit 2 may be used to fly aircraft 3, which includes 2, and to operate the aircraft 3's actuators and other electrical equipment. Alternatively, as shown in Figure 6(a), aircraft 3 may use the energy obtained by the light receiving unit 2 to wirelessly transmit power to aircraft 3A1, 3A2, 3L1, and 3L2, which are included in 3FORM, and power them to operate. Furthermore, 3 may be able to communicate with 3A1, 3L1, and other items included in 3FORM. Energy and power may be shared and exchanged with 3A1, 3L1, and other items included in 3FORM by means of contact or non-contact.<0039> ●As shown in Figure 6(b), the power converted by photoelectricity at the light receiving unit 2 may be used to fly the aircraft 3 (3FCAR) including 2, and to transport passengers and luggage. <0040> As shown in Figure 6(b), the aircraft 3 is equipped with a light receiving unit 2, and like a whale coming up for air, it is used to periodically receive photons in the air to charge the lithium-ion battery or other secondary battery or hydrogen fuel cell system of 3, and then descend again to near the ground, and 3 can be used as transport equipment 3 for transport purposes. ● The aircraft 3 may be manned or unmanned. ● Known operations such as navigation to a destination, autopilot / autonomous driving, and dispatching the aircraft 3 via a smartphone terminal (summoning 3 from the air to the ground with a smartphone) may be performed with the unmanned aircraft 3. ● It may also be used for monitoring operations, for example, to monitor the movements and deterrence of wild animals in mountain villages suffering from damage caused by wild animals, or for town security. <0041> In the case of an unmanned aerial vehicle (3), even if 3 is involved in an accident, the absence of a crew can reduce the damage. Furthermore, the unmanned aerial vehicle 3 can perform positioning using GNSS, etc., and can be used for autonomous driving, which is already known for drones and self-driving cars. In addition to autonomous driving, it can also perform unmanned (programmed) formation flight 3FORM, and can be used as a flying robot 3ROBOT for agricultural, forestry, fisheries, and various industrial tasks, as a vehicle for passenger transport, and for housing, residence, and real estate operations such as aerial hotels and aerial stations (aerial lodging facilities / bases like space stations). <0042> ●This invention allows aircraft 3 (which receives power or energy replenishment as needed from space-based solar power generation) to eliminate refueling steps like those of jet-engine aircraft and charging steps like those of battery-powered drones, thereby reducing or eliminating the time aircraft 3 spends waiting on the ground. <0043> ●Even if ground airports are not functioning and it is not possible to stay at an airport or refuel, in the system using 1, 2, and 3 of this application, 3 can be charged and energy replenished in the air, allowing flight to continue even if airports are unavailable. <0044> ●Figure 6(b) shows a configuration in which three flying cars 3FCAR take turns transporting passengers and cargo like taxis. ●On the other hand, when the flying car 3FCAR flies a route such as between Tokyo and Okinawa or between Tokyo, the Ogasawara Islands, and Guam, if photons can be transmitted from 1 to the light receiving unit 2 in the air above the route to supply the charging and energy, it will be possible to extend the flight range.●Figure 10 illustrates a concept in which, for example, a 3-3FCAR flies from Japan to Uruguay, near the opposite side of the world from Japan, receiving energy replenishment via 1 and 2 of this invention at various points along the way, such as over the Pacific and Atlantic Oceans or the ocean near New York, while transporting passengers. (Without having to land to charge or refuel, charging and energy replenishment can be performed at any time in the air using 1 and 2 and the aforementioned photons, thereby increasing the range of the 3FCAR.) <0045> ●The configuration in Figure 6(a) uses 3FORM to create an advertising balloon 3FORM-AD-BALLOON in the air, or a device (3FORM-ACTING) that performs shows, acts, competitions (for example, races, survival games, etc. using robot-type 3FORM) and missions using a formation mechanism of 3FORM, or a humanoid robot with human-like limbs and torso that performs shows and what. A configuration for the 3FORM-HUMANOID humanoid robot, which uses a 3FORM formation for labor, monitoring, transportation, entertainment, and robot competitions, has also been disclosed. <0046> ●3FORM-HUMANOID is a flying machine and does not require much consideration of its own weight. It may be configured as a somewhat large humanoid robot, or as an object such as a doll or papier-mâché modeled after a human, animal (tiger, rabbit, zodiac animal, lion, dog, cat, etc.), plant, fictional creature (dragon, etc.), or character. ●In this case as well, by using SSPS and 1 and 2, it may be possible to conduct continuous missions in the air without needing to charge or replenish energy on the ground. <0047> Compared to microwaves, photons in the ultraviolet to X-ray range have higher energy per photon (and can be absorbed and attenuated by reactions with atmospheric molecules and other chemical reactions), and their shorter wavelengths allow for a smaller receiver unit 2. (While the receiver unit 2 is an antenna / rectenna for microwave photons, for photons with wavelengths shorter than ultraviolet, it can be a photocell or a reactor that chemically transforms substances such as water into fuel substances such as hydrogen.) <0048> <High-altitude receiving unit 2 for receiving photons that are attenuated in the atmosphere> In this invention, since the attenuated photons are used, it is necessary to install the receiving unit 2 in a section of the atmosphere that is thin and at a high altitude as seen from the ground. <0049> <Generation and Utilization of Photons That Do Not Penetrate the Atmosphere> The above example shows photons in the UV-C region (photons absorbed into the atmosphere by causing a chemical reaction between oxygen and ozone). Ultraviolet light with wavelengths from 1 nm to 280 nm is greatly absorbed by the atmosphere. (Absorption is especially high from 1 nm to 200 nm) In a system using photons from 1 nm to 280 nm, the light may not penetrate to the ground, thus maintaining safety on the ground. In addition to ultraviolet light, photons in the infrared region with wavelengths from 1 micrometer to 10 micrometers and laser light using them can also be considered as photons that do not penetrate the atmosphere or are blocked by the atmospheric window. Non-patent document 3 describes millimeter waves, as described in patent document 1. Millimeter waves can also be absorbed in the atmosphere. In this application, photons with wavelengths shorter than ultraviolet light that are absorbed by molecules in the atmosphere, photons with wavelengths longer than infrared light, and millimeter waves may be used. In actual demonstration, it is necessary to select the wavelength of the photons, and although this application discloses a system of photons absorbed by the atmosphere (e.g., oxygen and ozone), the wavelength of the photons is not limited.<0050> <Means for transporting energy obtained by an aircraft 3 including an aerial light-receiving unit 2 to the ground> Patent Document 1 discloses transporting SSPS energy to the ground from outer space to the ground using a system consisting of radio waves or lasers (a system consisting only of photons). Non-Patent Document 4 discloses transmitting energy to the ground using a laser with a wavelength of around 1070 nm (near-infrared). <0051> In this application, we considered equipping the aircraft 3, which includes a light-receiving unit 2 as shown in Figure 1, with a cable 12 to the ground (for example, the cable 12 connecting the airborne structure 2 and the ground in a previous application, or the cable 12 of the orbital elevator section connecting the space structure 1 and airborne structure 2 to the ground) and wireless power transmission means 3WEP. However, considering that radio waves tend to disperse easily in wireless power transmission, and that it is unclear whether lightweight and low-resistance transmission lines can be obtained to the stratosphere with cables, we disclose in Figure 2 a method of converting electrical energy into chemical energy / fuel for delivery. Figures 3, 4, and 5 also disclose systems that use fuel. Other forms and explanatory diagrams are disclosed in the drawings of this application. <0052> Patent document 2 discloses descriptions of non-rocket launch 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 launch methods (including rockets and non-rocket methods) are highly desirable. <0053> ●For example, in Figure 1A and Figure 1 of Patent Document 2, the cable 12 which becomes the orbital elevator section may also be an orbital ring. This is a configuration of an orbital elevator in low Earth orbit in which a large-scale rotating annular structure (1 or 2) is held at an altitude in the air or space by centrifugal force etc. generated in the annular structure, and the cable hangs from the annular structure, lifting and holding the weight of the cable in the air. ●While the orbital ring and orbital elevator enable the construction of SSPS and the transportation of construction materials between space and the ground, as well as the transportation of power and fuel via the structure, wires and cables, the large scale of the equipment has been a challenge.●However, in this application, there is no such large-scale annular structure, and the system does not have a large force to lift the cable 12 other than the force from aerial means such as the buoyancy of the aircraft 3. A high-altitude balloon may be used, or a hot air balloon heated by energy from the SSPS may be used, and the system may consist only of buoyancy from gases that can float in the air, such as hydrogen gas, helium, or methane, which are used to fill the balloon for floating and lifting. ●This application is a device for delivering energy from the SSPS to the ground using an aircraft 3, which may be a compact and small-scale balloon, compared to, for example, the so-called orbital ring / orbital elevator described in Patent Document 2. <Prior Art Documents><Patent Documents> <0054> <Patent Document 1> JP 2004-266929 A <Patent Document 2> JP 2023-001372 A <Patent Document 3> JP 2022-058853 A <Patent Document 4> JP 2022-105726 A <Non-Patent Document> <0055> <Non-Patent Literature 1> Research on Space-Based Solar Power Generation Systems (SSPS) [JAXA, accessed January 6, 2023, Internet, https: / / www.kenkai.jaxa.jp / research / ssps / ssps-ssps.html] <Non-Patent Literature 2> The Atmospheric Window [National Oceanic and Atmospheric Administration (NOAA), accessed January 8, 2023, https: / / www.noaa.gov / jetstream / satellites / absorb] <Non-Patent Literature 3> Atmospheric Window [Meteorological Satellite Center, Japan Meteorological Agency (JMA), accessed January 8, 2023, Internet, https: / / www.data.jma.go.jp / mscweb / ja / prod / band_window.html] <Non-Patent Literature 4> Research on Laser Wireless Energy Transmission Technology [JAXA, accessed January 21, 2023, 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 this application are described. <Problem 1> In transmission methods using laser light or microwaves, which can penetrate the atmospheric window toward the ground, due to misalignment of the light-emitting unit 1 and the transmitting unit 1, photons or wireless transmission / power transmission energy are transmitted to the ground.Even if this configuration could reduce transmission power, there was still a possibility of harm to people living on the ground. A method was needed to alleviate people's concerns that photons, in the form of radio waves or lasers, might penetrate the atmosphere and reach the ground. <0057> ●It was necessary to devise a system that would ensure the safety of people on the ground while performing wireless power transmission via SSPS by limiting the photons transmitted by the transmitter 1 to wavelengths that are easily absorbed by the Earth's atmosphere. <0058> ●This invention proposes a configuration in which energy reaches the upper troposphere and stratosphere, but not the ground, by using photons that are absorbed in the atmosphere and not transmitted to the ground. <0059> ●In particular, we propose using wavelengths of photons that are absorbed by atmospheric oxygen, ozone, etc., through chemical reactions, as photons that are not transmitted through the atmospheric window, resulting in a transmittance to the atmosphere that is close to zero. <0060> <Second Challenge> When transmitting energy from an aircraft to a ground-based rectenna or similar device using microwaves while spreading the energy, it is anticipated that the energy will spread, making efficient energy transfer difficult. For example, if wireless communication is used in the section from 3WEP to 2LAND·2TAG·2WEP on the ground as shown in Figure 1 of this application, the radio waves will spread as they reach the aforementioned section. High-energy-density radio waves pose problems such as causing anxiety to residents on the ground. <0062> ●Therefore, the applicant considered it a challenge to devise a system for transporting energy between an aircraft 3 in the air and a ground-based unit 4, without being limited to electromagnetic methods such as wireless power transmission or power transmission via wires and cables. (This application considered three types of energy transmission: wired, wireless, and fuel-transported.) <0063> ●As a result, we disclose a system using the fuels shown in Figures 2 to 4. ●Furthermore, when operating an SSPS on the Moon and sending energy as fuel, we also disclose a method in which substances combined with oxygen from lunar resources (silicon oxide, aluminum oxide, iron oxide, water, etc.) are reduced and dropped to Earth, as shown in Figure 4. <0064> <Third challenge, challenges in the embodiment> <<Hitting the photons of the light-emitting unit 1 onto the light-receiving unit 2 and positioning>> ●It is preferable that the light-receiving unit 2 be small. If it is small, it is necessary to irradiate and hit the laser beam from 1 to 2 (with good accuracy).<0065> As shown in Figure 10, when, for example, an ultraviolet laser is irradiated from multiple 1s (multiple 1s included in a constellation of multiple 1SSPS-SATs) to 2, the design ensures that the laser is attenuated by oxygen, ozone, and the atmosphere even if it is misfired and misses its target. However, since misfires result in energy loss, a method was needed to ensure that the target is hit without misfires. <0066> ●Noting that Patent Document 1 uses a quasi-zenith orbit, which is also used for the QZSS positioning satellite, Figure 5 shows multiple light-emitting units 1 (or SSPS-equipped satellites 1SSPS-SAT equipped with multiple light-emitting units 1) that operate and move along a quasi-zenith orbit, arranged in a quasi-zenith orbit or as a satellite constellation 1SSPS-SYS-QZSS-SEIZA. <0067> ●By operating in a quasi-zenith orbit, 1SSPS-SYS-QZSS-SEIZA is configured to constantly emit photons, alternating with the ground and air-side light receiving unit 2, while also being configured to allow positioning using the QZSS positioning system, similar to the GNSS or QZSS positioning systems, by using a positioning unit 2POSI, which is added to the light receiving unit 2, to receive positioning signals transmitted from 1SSPS-SYS-QZSS-SEIZA. <0068> ●In order to investigate 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 coordinate information in three-dimensional space, 2 or 2POSI and 1SSPS-SAT or 1SSPS-SYS-QZSS-SEIZA may communicate using lasers or radio waves, and 2 or 2POSI and 1SSPS-SAT or 1SSPS-SYS-QZSS-SEIZA may be equipped with the aforementioned communication means. <0069> ●In order to assist in positioning 2 and 2POSI, 2POSI and the aircraft 3 including it may be equipped with clocks such as atomic clocks, altimeters, sensors, and instruments. For example, it may be equipped with an optical lattice clock type gravity sensor and gravity measurement system, and an altimeter. The altitude component of the information in the three-dimensional space in which 2 and 2POSI are arranged may be measured by the altimeter and combined with the positioning results from a positioning system using a global navigation satellite system (GNSS) or QZSS for positioning and utilization (for example, to hit 2 with photons emitted from 1). ●Photons may be irradiated from 1 to 2, which is equipped with 2POSI, using the positioning results.<0070><<Separation between the SSPS light-emitting section 1 and the light-receiving section 2, and between the light-receiving section 2 and the ground section 4>> ● In (a) of Fig. 5, between 1 and 2, there is no residential area on the ground at that latitude and longitude, and it can be placed, for example, over the sea of Japan. Energy such as light and electricity can be converted into chemical energy (fuel) by 2 and 3·3FUEL, and the fuel 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) where there is a 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 performance of the aircraft 3 to float can be achieved only for itself.) <0072> ● The aircraft 3 can use the energy from the SSPS for floating both during the day and at night. It can fly in the troposphere or stratosphere. At this time, if the aircraft 3 can maintain the forces such as the force to hold the cable, buoyancy, and the force to maintain altitude by flight while holding the cable 12, which can be, for example, 20 km in total length, 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 of 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 a merit 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 the 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 converting into chemical energy) and used for transportation equipment, passenger transportation, work by robots, shows, formation flight, airships, 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 examples of the use of the aircraft 3. <0076><<When transporting the power and energy of SSPS to the aircraft 3 including 2 and then using it for aerial applications instead of ground applications>> An aircraft requires energy for flight and movement. Jet engine-type aircraft 3, drones 3DRONE, or aircraft formations 3FORM driven by fuel have limited flight time due to battery or fuel limitations, and steps for fuel supply and charging are required during the operation of the aircraft. <0077> Also, in the solar-powered aircraft 3 equipped with solar cells and batteries on the earth, which can potentially extend the 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 instead of sending it to the ground is also disclosed.● In FIGS. 6 and 8, an aircraft formation flight group 3FORM of aircraft that can be constantly powered and operated using an 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 exhibition are disclosed. ● FIG. 9 describes examples of removal processing and additive manufacturing of a work target 4WK by 3ROBOT (which may use a robot arm). <0079><<After transporting the power of SSPS to 2 and using it for wireless power transmission>> An example is described in FIG. 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 move the tag or charging the tag. Therefore, FIG. 7 of the present application discloses a tag 2TAG·2TAG-PATCH that can be powered by wireless power transmission from an aircraft 3 and can perform wireless communication and sensor operation beacon operation. <Means for Solving the Problems><0080><First Problem-Solving Means>● A light receiving part 2, an aircraft 3, and a system using fuel described in FIGS. 2, 3, 4, 5, 10, and 11 are disclosed. A configuration enabling wireless transmission and power transmission is adopted between the light emitting part 1, the transmitting part 1 and the light receiving part 2, the receiving part 2 using short wavelength photons absorbed by molecules in the atmosphere from UV-C, UV-B to X-rays, and the light receiving part 2 is attached to a transportation means 3, a transportation device 3, an arrangement means 3 such as an aircraft 3 or a flying boat 3 arranged at a high altitude and at an altitude where it is difficult to absorb the short wavelength photons, so that the light receiving part 2 can receive the photons from the light emitting part 1. The light emitting part 1 and the transmitting part 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 cells, the power generated by solar power generation of SSPS, and solar energy.●Furthermore, as shown in Figure 4, when reducing launches to the moon and manufacturing fuel on the moon and using the fuel on the moon or on Earth, we disclose a method in which substances that have combined with oxygen from lunar resources (silicon oxide, aluminum oxide, iron oxide, water, etc.) are reduced using electricity and solar energy generated by SSPS's solar power generation and then dropped to Earth. <0086> Figure 10 is an explanatory diagram of the laser emission lines, the focal point of the laser energy, and the laser attenuation by the atmosphere when lasers are irradiated from multiple light-emitting units 1 to 2 of the quasi-zenith orbit group in this application. It also includes an explanatory diagram of 3FCAR and 3, which receive energy replenishment by the energy transport method using SSPS in this application while traveling to a remote location. <0081> <Second solution to the problem> As shown in Figures 2 and 5, we propose a system that uses fuel instead of electricity or light when transporting energy from the light receiving unit 2 in the air to the ground 4 and the user side 6. Specifically, we envision the use of hydrogen obtained by reducing water, carbon and hydrocarbons obtained by reducing water and carbon dioxide, and metals obtained by reducing metal oxides. After the light receiving unit 2 receives energy from the SSPS, the aircraft 3, which includes the light receiving unit 2, and the fuel synthesis aircraft 3FUEL, which can be connected to 3, are connected using connecting wires or connecting unit 3WIR. Power and energy are shared and exchanged between 3 and 3FUEL, or energy is transferred from 3 to 3FUEL. Fuel is synthesized in the reactor or electrolysis unit 3FUEL-GEN from the energy held by the light receiving unit 2 and aircraft 3 / 3FUEL and the raw materials that will become the fuel. The fuel is then transported and stored in the flow paths, pipelines, and tanks 3TANK of aircraft 3 / 3FUEL. The tanks 4FUEL-TANK and 3TANK on the ground 4 are connected using 3VALV / 4VALV and connecting pipes / nozzles, etc., and the fuel is transported to tank 4FUEL-TANK on the ground 4. ●In this way, energy derived from the SSPS is transported from 1SSPS through the light receiving unit 2 and aircraft 3 to the ground 4 for storage and then made available to the user 6, thereby delivering energy to the user without using ground-to-air wireless power transmission. <0082> <Third Solution to the Problem> Examples of applications for wireless power transmission are shown in Figures 6 to 9, etc.Figure 6 discloses a formation flight group 3FORM or humanoid doll device or humanoid robot 3FORM-HUMANOID, 3FORM-DOLL(MACHINE), or robot 3FORM-ACTING that operates using aircraft 3, which are constantly powered and operated by aircraft 3, as well as 3FORM-AD-BALLOON, which uses them for advertising and exhibitions. <0083> Figures 8(a) and (b) show examples of a humanoid doll device or humanoid robot 3FORM-HUMANOID composed of a formation flight group 3FORM of aircraft 3, or a formation flight group 3FORM. The diagram illustrates the action of firing paint projectiles from a paint nozzle attached to the paint nozzle while the humanoid robot 3FORM-HUMANOID, consisting of the upper body 3FORM-HUMANOID-UPPER and the lower body 3FORM-HUMANOID-LOWER, flies in formation with an aircraft 3 equipped with a robotic arm. Figure 8(b) shows the 3FORM-HUMANOID, consisting of the upper and lower body, spraying paint projectiles from a paint device held in its hand to the right. *A competition, exhibition, or show configuration such as spraying paint projectiles as shown in Figure 8 may be included in robot competitions. *Figure 8 shows a humanoid robot as an example, as a result of considering how a robotic arm can perform tasks the same as a human, such as painting. However, this application does not limit the robot to humanoids; it may also mimic real animals and plants such as dogs, cats, birds, fish, whales, trees, flowers, and plants, or it may mimic fictional creatures and characters such as dragons. *Furthermore, a stage device for recreating and expressing a certain scene in a play or theatrical performance may be constructed using 3FORM. It may be used for advertisements, dynamic objects, signs, displays, and advertising balloons placed in the air. *For example, each aircraft 3 equipped with a light-emitting device 31 may be used to perform a formation flight 3FORM to create a performance drawing patterns in the sky (for example, the display of spheres and pictograms by luminous drones deployed in the night sky at the Tokyo 2020 Olympic Games). Figure 8 may use manned or unmanned aircraft 3. <0084> Figure 9 describes aircraft 3 equipped with a robotic arm that has an additive manufacturing device or a removal processing device attached to it.Figure 9 includes an explanation of how branches are cut using the pruning device shown in 3, for example, when pruning tree branches. <0087> ●Furthermore, if the aircraft 3 is equipped with a balloon section for levitation and lift, using noble gases such as helium may lead to resource constraints. Therefore, in the system using the SSPS disclosed in Figure 11 of this application, the energy received by 3 from the SSPS through 2 may be used to heat the hot air balloon, and the hot air balloon may be used for the lift of the aircraft 3. (The propulsion device 3TH, which operates using the SSPS, generates a force to lift against gravity, as well as forces for movement, flight, and propulsion, which may be used for the lift, levitation, propulsion, flight, and movement of the aircraft 3.) <0085> Figure 7 discloses the 2TAG and 2TAG-PATCH tags, which are powered by wireless transmission from aircraft 3 and capable of wireless communication and sensor operation beacon function. <Effects of the Invention> <0088> ● By miniaturizing the light-receiving unit 2 and the photons emitted from the light-emitting unit 1 and the transmitting unit 1 are of wavelengths that are easily attenuated in the atmosphere, it becomes more difficult for them to reach the ground, thus protecting the safety of people and objects on the ground. (Figures 1, 2, 10, etc.) ● Regarding energy transport from the light-receiving unit 2 to the ground, by using a system that employs chemical energy and fuel to eliminate concerns about weight in power lines and the large area of ​​the user-side receiving unit and penetrating radio waves in wireless power transmission, it may be possible to overcome the challenges of power transmission by wireless power transmission and power line / cable transmission and deliver energy produced by SSPS to the user. (Figures 1, 2, 5, 10, 11, etc.) ● Aircraft 3 equipped with the light-receiving unit 2, or formation flight 3FORM / aircraft group 3FORM, can operate by receiving energy from SSPS, potentially reducing the steps of refueling and charging on the ground and extending operating time. 3 can then be used for transportation, monitoring / patrolling, work, entertainment, etc. (Figures 6, 7, 8, 9, 10, 11, 12, etc.) ● Power supply and charging of the 2TAG by aircraft 3 may be used for driving, searching, sensing, and communication of the 2TAG. The 2TAG, which may be able to communicate with 3, may be used for managing reagent bottles, luggage compartments, containers, trays, and product shelves with weight measurement functions, as well as for managing automobiles, aircraft, transportation equipment, keys, identification documents, objects, and living organisms.<Brief explanation of the drawing> <0089> <Figure 1>Figure 1 is an explanatory diagram of an energy transport method from outer space to Earth, showing the configuration of the present invention, including the light-emitting unit 1 and transmitting unit 1, the light-receiving unit 2 and receiving unit 2, an aircraft 3 including the light-receiving unit 2, a ground-based unit 4, a user 6, and regions such as clouds and the troposphere / stratosphere (Example 1). <Figure 2>Figure 2 is an explanatory diagram of energy transport from the light-receiving unit 2 and receiving unit 2 and the aircraft 3 to an energy demand site on the ground (Example 1). <Figure 3>Figure 3 is an explanatory diagram of fuel raw materials being launched to an SSPS by a launch means, fuel being manufactured using electricity obtained at the SSPS, and the fuel being dropped towards the ground for use (Example 2). <Figure 4>Figure 4 is an explanatory diagram of a system that reduces lunar resources and lunar metal oxides using electricity or energy from an SSPS near the Moon to obtain metal 5M and reduced substance 5MC, and then transports the metal 5M and 5MC to the ground. (Example 3) <Figure 5> The upper part of Figure 5 shows the energy to the ground from a system (1SSPS-SYS-QZSS-SEIZA) in which multiple SSPS satellites / spacecraft (1SSPS-SAT) are deployed in quasi-zenith orbit (QZO) and form a constellation. This is an explanatory diagram for transportation. (Example 4) <Figure 6> The upper part of Figure 6 is an explanatory diagram for a formation flight group 3FORM of aircraft that can be operated by being (constantly) powered by aircraft 3, or a humanoid doll device or humanoid robot composed of formation flight. Explanatory diagram for taxi and cargo transport applications. (Example 5) <Figure 7> An explanatory diagram for managing tags 2TAG by delivering power / energy to tags via wireless power transmission from aircraft 3 or unmanned aircraft 3DRONE. (Example 6) <Figure 8> An explanatory diagram for a robot / exhibit that imitates a living organism formed by 3FORM. (Example 7) <Figure 9> An explanatory diagram for an unmanned flying robot 3, which is equipped with a robotic arm and tools / equipment (e.g., saw). (Example 8) <Figure 10> An explanatory diagram for the laser emission line, laser energy focus, and laser energy scattering after passing the focus when lasers are irradiated from multiple light-emitting units 1 of a quasi-zenith orbit group to a light-receiving unit 2 in this application. (Diagram illustrating the claim in this application to make it difficult for energy to reach houses on the ground when laser irradiation occurs) <Figure 11>Diagram illustrating the system of an aircraft 3 that can output energy obtained from a light receiving unit 2 to the outside as electricity, light, fuel, chemical substances, etc., or various other forms of energy. (Diagram illustrating an aircraft 3 equipped with a hot air balloon 3HAB and a propulsion system 3TH that may be powered by the batteries, fuel, or SSPS energy of the aircraft 3.) <Figure 12>Diagram illustrating a water supply device 3 and a method of using water that delivers water to places where it is needed, places where fires need to be extinguished, etc., by supplying water obtained by collecting rain, rainwater, snow, or water supplied from 4H2O on the ground to a light receiving unit 3 which may be equipped with a light receiving unit 2 (Example 9) <Modes for Carrying Out the Invention> <0090> Examples (configuration examples) are shown in Figures 1 to 7. <Example 1> <0091> <Energy Transport System Derived from SSPS Using Short Wavelengths> Figures 1, 2, and 5 show Examples 1 to 4 of the present invention. It is recommended that the laser be temporarily turned off if a communication satellite, its constellation, a constellation of artificial satellites, or a spacecraft (e.g., a communication satellite constellation) reaches the laser beam during laser irradiation. It is also preferable that microwaves can be similarly turned on and off. *Note that, as shown in the explanatory diagram of the pilot laser, beacon laser, and main laser beams of the L-SSPS in Non-Patent Literature 4, guide photons, lasers, or radio waves can be exchanged between the light-emitting unit 1 and the light-receiving unit 2 for communication.For example, communication between the light-emitting unit 1 and the light-receiving unit 2 may be performed using a guide communication laser to control the orientation of the light-emitting unit 1 relative to the light-receiving unit 2. <0092> <Transportation system of SSPS-derived energy from the light-receiving unit 2 to the ground-level part 4 using fuel> <<System using water and hydrogen>> Figure 11 shows an explanatory diagram of the internal elements of the light-receiving unit 2 and aircraft 3. In the system of the light-receiving unit 2, receiving unit 2 and aircraft 3 FUEL capable of fuel synthesis shown in Figure 2, the aircraft delivers water from the ground to the light-receiving unit 2 (reactor 2REA of 2) and 3 (reactor 3REA of 3) which includes 2. The water is electrolyzed and decomposed by 3 and 3 FUEL, which receive electricity and energy from the light-receiving unit 2 and 2, to generate hydrogen and oxygen. The hydrogen may be stored in a tank inside the aircraft, transported to the ground, and stored in a tank 4 on the ground for use. When in use, the hydrogen may be transported to drive a hydrogen engine, drive a fuel cell, run a hydrogen-utilizing thermal power plant, or transmit power to the power system. <<System using iron>> In the system of the light-receiving unit 2 and aircraft 3 FUEL capable of fuel synthesis shown in Figure 2, metal oxides may be used in addition to water, for example, iron oxide may be used. Iron oxide may be delivered from the ground to the receiving unit 2 by an aircraft, and the iron oxide may be reduced by the receiving unit 2 or by 3FUEL, which receives power and energy from 2. <0093> <<Systems using iron and water, systems using metal and water>> In the system of the light-receiving unit 2 and the aircraft 3FUEL capable of fuel synthesis shown in Figure 2, two oxidized substances may be used. For example, in the system of the light-receiving unit 2, the aircraft 3 connected to 2, and the aircraft 3FUEL, water and iron oxide may be delivered to the light-receiving unit 2 from the ground by the aircraft 3FUEL in order to perform hydrogen ironmaking (hydrogen reduction ironmaking). In the system of the light-receiving unit 2 in the air and the aircraft 3 or aircraft 3FUEL, hydrogen may be produced using the energy of water reduction based on the energy of photons from the light-emitting unit 1, and then iron may be produced by reducing iron oxide with the hydrogen. In the system in which hydrogen and iron are produced in 3, iron oxide and iron do not have a large volume like hydrogen, so hydrogen cylinders for pressurizing and loading gaseous hydrogen are not necessary when loading them into 3. Iron oxide and iron have the advantage that they can be handled at atmospheric pressure without pressurization like hydrogen cylinders when transported by 3, for example. For hydrogen-based ironmaking, hydrogen is produced from water, iron oxide is reduced with the hydrogen to obtain iron, and this process is repeated, with a constant amount of water being maintained in 2, 3, or 3-fuel. By introducing iron oxide into the hydrogen-based ironmaking system, iron and oxygen can be produced in 2, 3, or 3-fuel.Furthermore, on Earth, iron can be used to generate electricity and heat from chemical energy, such as in iron-air batteries or as iron powder in hand warmers that oxidize iron. The abundance of water, hydrogen, and iron resources is also an advantage. (In 2, 3, and 3FUEL, in addition to the reduction of iron mentioned above, zinc, metallic lithium, metallic sodium, metallic magnesium, metallic calcium, aluminum, etc., can also be utilized by similarly reducing their metal oxides.) <0094> <<Systems using hydrogen, water, carbon dioxide, and hydrocarbons>> Carbon dioxide and a carbon source may be introduced into a water and hydrogen system to reduce carbon dioxide and produce hydrocarbon-based synthetic fuels. Carbon-based materials may be produced from carbon dioxide. ● Carbon dioxide stored on the ground may be transported to the system of the light receiving unit 2 and aircraft 3 using 3FUEL, etc., and carbon dioxide may be reduced and separated into carbon and oxygen using energy which may be derived from SSPS, thereby contributing to the reduction of carbon dioxide on Earth. ● Carbon dioxide may also be recovered from the atmosphere by separating carbon dioxide from the air using the system of 2 and 3 or 3FUEL and separating the carbon and carbon components from the carbon dioxide. For separation, known methods such as the method of absorbing carbon dioxide with monoethanolamine, gas membrane separation, and the method of separation by cooling the atmosphere may be used. <<Separation of atmospheric components from the atmosphere>> ●In the system of 2 and 3 or 3FUEL, the energy from SSPS is used to continuously drive the apparatus (e.g., pumps, machines, reactors for separating air components) to recover carbon dioxide and other substances from the air. Similarly, energy derived from SSPS may be used to separate and recover components that make up the atmosphere, such as noble gases like helium and neon, oxygen, nitrogen, and argon. Furthermore, the separated and recovered noble gases may be loaded into 3GAB. ●For separation, a method of compressing and liquefying the gas with a compressor (cryogenic separation) may be used. Known methods such as membrane separation of gases or cooling and separating the atmosphere may be used to separate atmospheric components from the atmosphere. <<Production of ammonia>> For example, ammonia NH3 may be produced for gas applications, chemical applications, and fertilizer applications by using nitrogen from the air, 1, 2 and 3 of this application, and 3FUEL which transports water and hydrogen, to float 3. <0095> Option 3 could also be a gas balloon system.●In Figure 11, 2 may convert 1HNU into electricity using 2PCE to drive the propulsion device 3TH, or 2 may absorb the 1HNU received from 1 with a photon absorber, generate heat in the photon absorber, and use this heat to heat the propellant that drives 3TH, causing the propellant to be heated and ejected to drive 3TH. Alternatively, 3TH, including the light receiving unit 2, and the transport equipment 3 may be configured to float, levitate, and propel themselves using the energy obtained in 2. <0096> <<3 Floating and Propulsion>>3 may be propelled using rockets, propellant jets, photons, or charged particles, as disclosed in Patent Documents 2, 3, and 4. For example, aircraft 3 may be propelled by rockets, propellant jets, ion thrusters, or photon sails, which emit and reflect photons to propel themselves. ●3 of this application may be propelled by emitting and reflecting the aforementioned photons or charged particles toward the ground and using the resulting recoil to position and float in the air. Thrust in the opposite direction to gravity may be generated using rockets, propellant jets, photons, or charged particles. (Similar to obtaining buoyancy with a balloon, so that a drone 3 that is constantly charged by SSPS can generate thrust with a propulsion device 3TH to balance gravity and its own weight in the air and continue to hover.) Aircraft 3 that receives energy from SSPS of this application may perform hovering, flight, propulsion, movement, attitude control, and aircraft motion using 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 Literature 4 may be used in the system of this application. ●When the configuration of Non-Patent Literature 4 is implemented in this 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) of the aircraft 3 as shown in Figures 1 and 2 of this application, and a pilot laser 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 / SSPS side. The laser emitting unit 1 may emit a main laser and a 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 this application may be controlled to emit and irradiate photons from 1 to 2 and hit 2. <0098> <<Positioning and Communication>> Figure 5 shows examples of energy transport in the quasi-zenith orbit of this invention, as well as examples of energy transport from geostationary orbit and the Moon.When the present system is configured in the quasi-zenith orbit shown in the upper part of Figure 5, the SSPS may also perform the functions of known artificial satellites such as positioning satellites, communication satellites, and ground observation satellites. ● The position of the light-receiving unit 2 may be determined by the functions of the positioning satellites mounted on the SSPS or the QZSS positioning satellites in the quasi-zenith orbit where the SSPS satellites are positioned, and this can be used to position the photon irradiation from the light-emitting unit 1 to the light-receiving unit 2 and to ensure the accuracy of the emission. Communication including positioning information and emission instructions for emitting the photons from 1 to 2 to hit them may be communicated between 2 and 1. ● 3, 2, and 1 may be connected to other systems, for example, to the Internet / communication network from satellite 1LINK located in space, or to the Internet / communication network via communication devices to terminals / computers of ground stations 4 and user stations 6, or to the Internet / communication network through 4 and 3. (The position of 2 may be determined by 1SSPS-SYS-QZSS-SEIZA.) <0108> The relative positions of each of 1 and the light receivers 2 and 2POSI may be determined using the 2POSI of the light receiver 2 and the QZSS positioning device 1SSPS-SYS-QZSS-SEIZA. ●The 2POSI of the light receiver 2 and 1 may communicate wirelessly and via laser communication, and may send and receive position information of the 2nd and 1st order satellites and other necessary data. (This includes sharing position and time information, as well as operational information of any satellites passing between 1 and 2, and controlling the direction and on / off status of the laser.) <0099> <<Attitude and Direction Control, Photon Irradiation Control>> ●1 may control the direction of photon irradiation of 1 to 2 and whether it is on or off. 1 may be equipped with means to change the emission direction of the photons emitted by 1 (attitude control / direction control device of 1, deflection device of 1), and may be equipped with means to suppress and control shaking (for example, 1 mounted on a stabilizer, gimbal, or tripod head), and the above control may be performed from 1, 1SSPS, 1CON, or an external network / Internet. ●1 may turn the emission of 1 on or off. For example, 1 may check the operating status, flight schedule, orbital information, date and time of other artificial satellites / spacecraft via the external Internet from 1CON or 1LINK, etc., and control to turn off photon irradiation if a spacecraft etc. comes in the line of sight when 1 is irradiating 2. For example, 1 turns the laser on or off by control of 1CON.<0100> <Supplement: Laser irradiation of debris> The configuration of this invention (laser irradiation from 1 to 2) may be used to change the orbit of space debris 1DBL. For example, as in 1DBL in Figure 10, when 1 is placed in a certain orbit and a laser is irradiated toward 2 in the stratosphere / air, the laser is turned off when a spacecraft is in the line of sight from 1 to 2, and remains on when space debris passes by, so that the debris is irradiated by the laser (and if possible, the debris is heated or its orbit is changed). The light-emitting unit 1 of this invention may be used to irradiate the debris with a laser. <Example 2> <0101> <Energy transport system for SSPS using fuel transport> Figure 3 shows an example where fuel materials are launched into space, fuel is manufactured at 1, and then transported to Earth. <Example 3> <0102> <A lunar SSPS energy transport system involving the return of local resources and fuel transport.> Figure 4 illustrates an example in which metal oxides and oxides on the lunar surface are reduced in step 1 to form metallic silicon, metallic aluminum iron, etc., 5M (or reduced powdered metal fuel), or related compounds 5MC, and then transported to Earth. (If, in addition to the aforementioned metal oxides, there are other oxides such as water on the lunar surface, the oxides such as water may be reduced to produce reduced substances such as hydrogen as fuel, which can then be used.) The example in Figure 4 involves removing metal elements from the moon and combining them with Earth's oxygen, which has the drawback of consuming lunar metals and Earth's oxygen. However, it allows for the delivery of power from space-based solar power generation to Earth while developing the moon, and may be useful when it is desired to utilize energy from SSPS on Earth in the early stages of lunar development. (Note that the oxygen 5O2 produced by oxide reduction on the moon may be used at lunar or space bases, or the 5O2 may be introduced to Earth and used as oxygen 4O2 on Earth.) <0103> As a modification of Figure 4, silicon oxide may be reduced to obtain the reduced substance 5MC or silicon compound 5MC, and the silicon compound 5MC may be transported between regions on the lunar surface (for example, from 1FUEL-GEN·1CHEM1 to a chemical plant 1CHEM2 or 1CHEM3 near the drop device 9 via pipeline 5PIP). (Note that metallic silicon and crude silicon may be produced by known methods using carbon or metallic magnesium. Metallic magnesium may also be produced using magnesium-containing raw materials obtained on the moon and electricity from SSPS.) The bases 1CHEM1 and 1CHEM3 may be connected by a pipeline 5PIP of fluid silicon-based compound 5MC, such as silane (gas), silicon tetrachloride, or trichlorosilane (a raw material for crystalline silicon and a liquid). The fluid 5MC passing through 5PIP may be sent under pressure by a pump or the like. <0104> For example, 5MC may be transported as a fluid within pipeline 5PIP, and then converted to metallic silicon 5M in chemical reaction conversion units 1CHEM1, 1CHEM2, and 1CHEM3. For example, 5MC may be transported as a fluid from 5PIP to 1CHEM3, and then converted to metallic silicon from 1CHEM3 to the launch / deployment device 9 or the ground-based 5TANKM. (Also, if it is acceptable to transport 5MC instead of 5M to the ground, for example, 5TANKM may be loaded with metallic silicon or other materials instead of 5M.))<Example 4> <0105> The upper part of Figure 5 is an explanatory diagram of energy transport to the ground from a system (1SSPS-SYS-QZSS-SEIZA) consisting of multiple satellites deployed in quasi-zenith orbit to form a constellation of SSPS satellites. The lower part of Figure 5 is an explanatory diagram of energy transport to the ground from the SSPS satellite constellation 1SSPS-SYS-ORBIT formed in space orbit, or the geostationary orbit constellation 1SSPS-SYS-GEOS, or the lunar or near-lunar constellation 1SSPS-SYS-MOON, or the group 1SSPS-SYS-MOON. When sending (exchanging) energy / power lasers or signal lasers from 1 connected to the SSPS to 2 in the air, a relay satellite 1LINK may be present. *1LINK may relay not only lasers but also radio waves (considering the case of relaying radio signals). <0106> 1LINK may include relay means for relaying photons such as lasers, for example, a mirror device 1MRR that changes the trajectory and path of a laser beam by light reflection, or an optical component section 1OPT (or optical system 1OPT) such as a lens. Alternatively, 1LINK may be a relay satellite 1LINK equipped with a light receiving section 2, a light emitting section 1, and means for operating them. *1LINK and 1OPT may correct the laser beam (which has spread out (blurred) due to passing the long distance between 1 and 1LINK) that has reached 1LINK or 1OPT with an optical system 1OTP (such as a lens), focus the beam with 1OPT, or / or reflect the beam towards 1LINK or 2 with 1MRR, and deliver it to the next relay satellite 1LINK or an aerial light receiving section 2. *1MRR is not limited to use in 1LINK. For example, in the case of an SSPS solar cell or a sunlight collection section that aims to obtain sunlight, 1MRR may serve as a means of delivering sunlight to the sunlight collection section, or it may be a large-area mirror device 1MRR that reflects sunlight to the sunlight collection section. <0107> Figure 5 shows a diagram in which lasers are shone onto the light-receiving unit 2 from multiple 1SSPS-SATs in a quasi-zenith orbit. However, Figure 5 is just one conceptual diagram, and the constellation 1SSPS-SYS-SEIZA in Figure 5 is not limited to the group of spacecraft orbiting in the quasi-zenith orbit shown in Figure 5.●Furthermore, as shown in Figure 10, not just one but multiple constellation 1SSPS-SYS-SEIZA may be used to supply energy from SSPS to 3, including 2. Energy from SSPS may be supplied to 2 and 3 from multiple 1s in different orbits and light-emitting locations (LEO constellations, geostationary orbit GEO / QZO constellations, or the lunar surface, etc.). ●For example, Figure 10 describes a concept in which three (multiple) constellations 1SSPS-SYS-SEIZA in a certain orbit, positioned over Japan or the open ocean / high seas of other countries, are used to supply energy to aircraft 3 during long-distance transport or passenger transport, at intermediate points (over the open ocean, etc.). *In an asymmetrical figure-eight quasi-zenith orbit, the time that one artificial satellite can stay over Japan is said to be about 7 hours. Figure 5 may show a configuration in which the light-receiving unit 2 receives laser irradiation sequentially from each of the multiple 1SSPS-SAT satellites in a constellation that are approaching the skies above Japan (the small ring portion of the asymmetric figure-eight shape that falls over Japan). Alternatively, the light-receiving unit 2 may be positioned at a quasi-zenith angle, looking up at the light-emitting units 1 of the satellite constellation orbiting QZO, which are lined up in the small circular portion of the asymmetric figure-eight shape of 1SSPS-SYS-QZSS-SEIZA that falls over Japan, and the laser irradiation is performed from the light-emitting unit 1 to the light-receiving unit 2. <0108> ●The Quasi-Zenith Satellite System (QZSS) and the QZSS positioning device, 1SSPS-SYS-QZSS-SEIZA, may be used. The relative positions of each of 1 and 2POSI of the light receiving unit 2 and 1SSPS-SYS-QZSS-SEIZA, which is also the QZSS positioning device, may be determined. ●The 2POSI of the light receiving unit 2 and 1SSPS-SYS-QZSS-SEIZA and 1 may communicate wirelessly or via laser communication, and may transmit and receive positional information of 2 and 1, and other data necessary for energy transport and transport in this application, via wireless communication or laser communication. ●Position and time information, and if there is an artificial satellite passing between 1 and 2, its operation information may be shared, and for example, the direction of the laser and on / off control of the emission may be performed. The on / off control of photon emission may be performed and laser communication may be performed between the light receiving unit 1 and the light receiving unit 2. Laser and wireless communication may be performed between the light receiving unit 2 and the light receiving unit 1 (and further between the relay satellite 1LINL).<0109> In this application, a positioning means may be provided to irradiate the light-receiving unit 2 with a laser from the light-emitting unit 1 to facilitate hit detection, and a laser relay means 1LINK may be used to guide the laser from 1 to 2. (The aforementioned positioning means may be 2POSI and a space-based positioning system such as GNSS, GPS, QZSS, etc., or 1SSPS-SYS-QZSS-SEIZA may be equipped with a positioning system such as QZSS. Other known means may be used for positioning.) <0110> Furthermore, even in the case of a constellation of multiple 1SSPS-SATs orbiting low Earth orbit (LEO), such as the 1SSPS-SYS-ORBIT, laser irradiation from 1 to 2 (irradiation of 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) can be performed in the same way as in the case of 1SSPS-SYS-QZSS-SEIZA. <Example 5> <0111> Figures 6 and 10 are explanatory diagrams of aircraft formations 3FORM, aircraft formations 3FORM, or taxi, cargo transport, and passenger transport using aircraft 3 or flying cars 3FCAR, which can be powered (continuously) by aircraft 3 and operated. ● 3FORM may be able to connect to ground communication terminals 4CON, airborne communication terminals 3CON, and user terminals 6CON, and may be able to connect to the internet using a communication network with the aforementioned terminals and the communication unit of 3. ● For example, in Figure 6, a user mobile terminal 6 may be provided. ● The user of the user mobile terminal 6 may remotely control the humanoid 3FORM or aircraft 3FCAR described in Figure 6, or the 3ROBOT (forestry machinery, which may be forestry machinery such as a tree pruning machine) shown in Figure 9, from a location far from 3 via a communication path such as the internet. <Example 6> <0112> When attempting to monitor a person or object using a wearable device 2TAG, wireless terminal 2TAG, or electronic tag 2TAG equipped with a beacon or active wireless communication unit, it was necessary to install or replace batteries. Therefore, Figure 7(a) of this application discloses a method in which 3DRONE or 3 searches for 2TAG while wirelessly transmitting wireless energy to 2TAG via 3DRONE to charge 2TAG, enabling beacon operation and wireless communication operation, and searching for the attached object 6OBJECT (6OBJECT-TAG-ATTACHED).3 or 3DRONE is used as a tag scanner 6TAG-SCANNER, causing the transport device 3 to search for 2TAG, and when 3 approaches 2TAG, wireless power is supplied to 2TAG to enable wireless communication and beacon operation for tag identification. The energy for the aforementioned charging may be energy derived from SSPS using 1, 2, and 3 of this application. (3 or 3DRONE are both transport devices 3 and tag scanners 6TAG-SCANNER. To avoid limiting the scope of the invention, transport devices 3 include not only aircraft 3 but also vehicles such as automobiles 3 and bicycles 3, as well as self-propelled robots and flying drones 3.) <0113> Furthermore, a configuration in which a sensor is mounted on the 2TAG is disclosed in Figure 7(b). For example, a 2TAG attached to or equipped on a person includes an acceleration sensor and a load sensor, and wireless transmission is performed by 3, 3DRONE, or scanner 6TAG-SCANNER to supply power to the sensor-equipped 2TAG, allowing the sensor to operate while being powered or charged to collect acceleration, load, and environmental data of the object. As an example, Figure 7(b) shows a 2TAG equipped with a load sensor (2TAG-SENSOR) attached to the bottom of a reagent bottle containing toxic or hazardous substances whose weight needs to be managed, forming an object 6OBJECT-TAG-SEN-ATTACHED. When the 2TAG is charged by wireless transmission from 3 or 3DRONE, the 2TAG operates as a load sensor / weight scale, acquiring the measured value of the load sensor, and the 2TAG can transmit the position value of the load sensor on the bottle to the tag scanner 6TAG-SCANNER via communication means. ●If you want to check the tilt of tagged objects in addition to their weight (for example, whether tagged reagent bottles or drums are lying on their sides on the ground), you may use a combination of a load sensor, tilt sensor, and acceleration sensor with the 2TAG. For example, if a 3DRONE or robot car 4CAR patrols a building where reagents are stored, charging 2TAGs equipped with load sensors on reagent bottles and reagent shelves as tag scanners, the charged 2TAGs will function as sensors and transmit the measured values ​​from the load sensors to the 4CAR or 3DRONE, thereby transmitting weight information of tagged reagent bottles and other items in the building to the tag scanners, or making it possible to view this information externally via a communication network from the tag scanners. This can be used for managing goods and reagents.<<Examples in footwear>> ●The insole-type wireless monitoring tag described in Japanese Patent Publication No. 2016-073366 (or related uses such as attaching or wearing 2TAG on socks, footwear, etc.) may also use the wireless power transmission method and device configuration shown in Figure 7(b). ●2TAG may be attached or installed on wearable items such as insoles, shoes, socks, footwear, underwear, clothing, glasses, HMDs, head coverings, helmets, gloves, watches, bracelets, rings, jewelry, accessories, mobile terminals, etc., and the wireless power transmission method and device configuration shown in Figure 7(b) may be used. ●The wireless communication slave unit described in Japanese Patent Publication No. 2016-073366 (1b, 1a. Regarding this, (without incorporating a walking-based charging function,) an insole-type wireless communication slave unit equipped with wireless communication and positioning functions may be configured that can charge the wireless communication slave units (1b, 1a) from SSPS via a system of 1, 2, and 3. ●The sensor unit, wireless communication unit, and beacon of 2TAG may be operated by charging via a wireless transmission method using 3DRONE or 3DRONE driven by SSPS. ●When 2TAG is used in a pedestrian's insole, as described in Japanese Patent Application Publication No. 2016-073366, the wireless communication slave unit may measure the weight of the person standing on the insole, measure the pressure, load, and weight generated by being stepped on while walking, measure the movement and acceleration of the toes as the acceleration of the insole. It may also measure the pressure distribution on the sole of the foot while walking and perform gait analysis. It may also measure weight and observe and measure gait. It may also collect information that can be used for individual biological characteristics and health management using 2TAG. Alternatively, the 2TAG may be equipped with GPS, GNSS, QZSS, or other positioning means that receive signals from satellites or radio stations or communicate with them, and the 2TAG may be used to perform position measurement. <0114> The 2TAG-SENSOR may be a device that senses wireless communication signals from satellites, or a satellite positioning device such as GPS or GNSS, or a device that measures and senses position. As shown in Figure 7 of this application, a tag scanner 6TAG-SCANNER (which may be a drone 3 or a user's smartphone 6CON) is used to search for the tag, and during the search, the tag 2TAG is charged and powered, and stored in the 2TAG's power storage device. Using the power stored in the 2TAG, the 2TAG receives signals from a radio station (GPS, GNSS, QZSS, or other satellites, aircraft, or ground base stations) to obtain the 2TAG's position and time, and positioning is performed by the radio station or satellite. The positioning results are then transmitted from the 2TAG to the 6TAG-SCANNER, transmitting the 2TAG's position information. <0115> ●In this application, if 1, 2, and 3 of this application are added to the 2TAG and 6TAG-SCANNER system in the air as shown in Figures 6 and 10, a system can be constructed in which the 6TAG-SCANNER, an aerial communication platform that can move to remote locations without refueling or charging on the ground using the energy of the SSPS and can stay in the air, and sensor-equipped tags searched by the tag scanner can be configured, which can be used for continuous monitoring from the air. If 3 is an unmanned aircraft, it can be used as a patrol device for the 2TAG.<0116> ●Figures 8 and 6 describe a group of aircraft 3FORM capable of formation flight and inter-aircraft communication, where energy can be shared using energy sharing means such as a wireless transmission device 3WEP. Figure 7 describes monitoring by a single 3, but even in Figure 7, a group of aircraft capable of sharing energy among aircraft may be used. For example, a 3 equipped with 2 may be placed in the stratosphere, and a tag scanner 6TAG-SCANNER, which is also 3FUEL and may fly in the troposphere or on the ground, may periodically connect to the 3 to share and replenish energy through charging and refueling. <Example 7> <0117> Figure 8 is an explanatory diagram of the stationary and operational (flight and robot arm operation) humanoid robot 3FORM-HUMANOID, which consists of an upper-body aircraft 3 equipped with tools, equipment, and various devices, and a lower-body aircraft 3, capable of formation flight and coordinated operation. The operation mode of the device in Figure 8 may be manned or unmanned. In the unmanned case, 3CON may be equipped with communication equipment for external radio stations and communication networks, and may also be equipped with computer-related devices such as a computer processing unit, memory device, and input / output device. Aircraft 3 may be equipped with batteries and fuel. Aircraft 3 may use the batteries and fuel to power the robot arm, motors, actuators, and propulsion system. <Example 8> <0118> Figure 9 is an explanatory diagram illustrating a configuration in which tools, implements, various devices, or additive manufacturing device 3A1-AM and removal processing device 3A1-RP are mounted on the robotic arm of aircraft 3 or aircraft 3 (3ROBOT), and additive manufacturing is performed on the work target object 4WK 4WK-AM and removal processing is performed on 4WK-RP. Also, Figure 9 is an explanatory diagram illustrating an unmanned aircraft 3 or flying robot 3ROBOT that performs pruning, which involves cutting and removing tree branches as one of the removal processes, via remote control from a base station (3CON, 4CON, 6CON), and the flying robot 3ROBOT is equipped with a robotic arm and 3A1-RP which may be a saw, cutting part, or grinding wheel. ●In this application, the system is powered by the energy of SSPS and can be accessed by aircraft 3ROBOT even when 4WK is located in a place that is difficult for humans or ground-based machines to work on, such as the side of aircraft 3, on a slope, or on a cliff. (A high-altitude work device 3ROBOT may also be used.)(It may also be used for monitoring and working on transmission towers, utility poles, and power lines.) ●Figure 4 shows a configuration in which 3 ROBOTs access 4WK, but it may also be a configuration in which 3FORM, consisting of 3 ROBOTs equipped with the tools shown in Figure 3, is driven by the energy of SSPS to work on 4WK. Among the 3FORM, machines with depleted energy may be sequentially replaced by machines that have been recharged to keep them working continuously. <Example 9> <0119> Figure 12 is disclosed as a reference diagram. Figure 12 is an explanatory diagram of a method for producing hydrogen fuel by feeding water obtained by collecting rainwater from the open ocean or water supplied from 4H2O on the ground into a 3FUEL which may be equipped with a light receiving unit 2. (And, an explanatory diagram of a water utilization method in which rainwater is collected by a 3FUEL driven by SSPS and delivered to people, animals and plants on the ground, users 6, and places of demand (places where fires need to be extinguished).) <0120> While embodiments of the present invention have been described, these embodiments are presented as examples only and are not intended to limit the scope of the invention. These novel embodiments can be implemented in various other forms, and various omissions, substitutions, and modifications can be made without departing from the spirit of the invention. (※This application is based on a design. It has not been demonstrated at the time of filing.) <Industrial Applicability> <0121> It may be used for transmitting power and energy from the light-emitting unit 1, which also functions as a space solar power plant, to an aircraft 3 or high-altitude platform 3, including the light-receiving unit 2, and to the ground. Beyond space solar power generation, it could be used to transmit electricity generated in space or on the lunar surface to the Earth's atmosphere. <0122> If airplanes, electric aircraft, and hot air balloons could be powered by energy derived from SSPS (Splitting-Splitting Energy), ground refueling and charging steps would be unnecessary, increasing flight time and potentially creating aircraft, airplanes, airships, and passenger planes (or facilities like hotels in the air) capable of long-distance travel. <Explanation of symbols> <0123> <<Energy transport from SSPS to Earth by short-wavelength photons>><Emitting unit 1, SSPS section>1: Emitting unit, transmitting unit (laser transmitting unit, laser emitting unit, photon emitting unit. May also include a radio wave transmitting unit). 1PP: Power plant. (In addition to solar power plants, this may include thermal / chemical energy-utilizing power plants, large-scale battery plants, and nuclear-related power plants.)1PV: Solar cell (※1PV may be a PV launched from Earth, or a PV manufactured near the site of use using the vacuum of space after raw materials have been produced from resources on celestial bodies such as the Moon). 1PCL: Energy conversion means other than solar cells / solar energy collection unit). 1LASER-GEN: Device unit that converts electricity and energy obtained from 1PV or 1PCL ​​into laser light (laser generation means such as ultraviolet lasers or synchrotron radiation generators, light emission means, and energy transmission means). 1CON: Communication unit of 1. May also be a control unit. Includes SSPS and other parts necessary for transporting SSPS energy to Earth. 1FUEL-GEN: Unit that synthesizes fuel material using energy obtained from SSPS. 1SSPS: SSPS, space solar power plant. 1SSPS-ETC: A series of other systems and components related to 1SSPS. 1SSPS-SYS: A series of systems for the space solar power plant. (1SSPS-SYS-QZSS: SSPS (QZSS: Quasi-Geographic Orbit Satellite System), which is also QZSS. 1SSPS-SYS-GEOS: Geostationary orbit (GEO) space-based solar power generation system. 1SSPS-SYS-MOON: SSPS (or space-based solar power generation systems on satellites like the Moon or other planets) operating in geostationary orbit on the lunar surface or in the space near the Moon. 1SSPS-SYS-QZSS-SEIZA: A group of satellites or satellite constellation of 1SSPS-SYS. 1SSPS-SYS-QZSS-SEIZA: A group of satellites or satellite constellation of 1SSPS-SYS-QZSS operated by QZSS.)<QZSSコンステレーション> As mentioned in Figure 5 of Patent Document 1, etc., in this application, 1 may also be in the form of QZSS. Multiple 1s or 1SSPS-SYSs may be arranged in the quasi-zenith orbit of QZSS (such as an asymmetrical figure-eight orbit when placed over Japan) and used as shown in Figure 5.<Constellations in Low Earth Orbit (LEO)> In a low Earth orbit (LEO) satellite constellation (provided by, for example, SpaceX or OneWeb), the satellites constituting the low Earth orbit (LEO) satellite constellation are SSPS satellites 1SSPS-SAT, and the satellite formation is arranged so that the satellite 1SSPS-SAT is always close to a certain point on the ground / photodetector 2 when viewed from 2, and the constellation of satellites is allowed to flow into orbit to operate the constellation 1SSPS-SYS-SEIZA. The configuration of 1SSPS-SYS-SEIZA (1SSPS-SYS-LEO-SEIZA) in LEO allows the SSPS satellites and the light-emitting unit 1 to be positioned in low Earth orbit, which is closer to the ground than quasi-zenith orbit or geostationary orbit, and the length of the distance (in space) when 1 emits photons to 2 and hits it can be reduced. *The method of forming a constellation of artificial satellites moving at speed in low or medium Earth orbit can also be applied to SSPS constellations. For example, a group of multiple SSPS satellites (tens to tens of thousands) may be formed in low Earth orbit at an altitude of 300km to 500km or 1100km (the satellites are arranged in a formation such that they are always close to a certain point on the ground / photodetector 2, and the group of artificial satellites is allowed to flow into orbit), and these may be used as relay satellites 1LINK or as 1SSPS-SYS-SEIZA to irradiate the photodetector 2 with the energy of the light-emitting unit 1 from the SSPS. ●The 1SSPS-SYS-SEIZA of this application is a solar power generation satellite and an energy transmission satellite, but it may also provide a satellite communication network and communication services using a satellite constellation, or provide communication services between the ground and satellites. (Communication, laser communication, and energy transmission may be performed between SSPS satellites and between the light-emitting unit 1 and light-receiving unit 2 of the SSPS.) 1LINK: A relay satellite, relay aircraft, or relay means for energy and signals from the SSPS to the light-receiving unit 2. 1LINK may be equipped with mirrors for photon reflection, relay, and transmission; for example, an ultraviolet reflecting mirror made of aluminum is envisioned. 1HNU: Photons irradiated, emitted, oscillated, and transmitted from 1, and a group of photons that reach the light-receiving unit 2 by being dropped and passing through the air, such as the stratosphere and troposphere, where the air density and oxygen / nitrogen density are lower than on the ground (the generation of 1HNU may be turned on and off by 1).By turning the generation and emission of 1HNU on and off in 1, laser communication and optical communication may be performed in the section from 1 to 2. 1HNU-EXT: Photons that do not reach the ground or are attenuated. Photons with characteristics and wavelengths that are absorbed by the atmosphere. When the laser is pointed outwards (towards the ground) from the receiving unit 2 due to a misalignment of the transmitting unit 1, etc., short-wavelength laser photons emitted by 1 that are absorbed and attenuated by reactions in the atmosphere, 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 present configuration, the laser is attenuated by the atmosphere, and the laser can be irradiated from n (multiple) 1SSPS-SATs or 1SSPS to one light-receiving unit 2. By using multiple units, the output of the n 1SSPS-SATs to the light-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, lowering the output of energy irradiated to the ground, and protecting the safety of people on the ground. (Regarding the light-emitting unit 1 of this invention.) Instead of a single SSPS satellite with a light-emitting unit 1, multiple SSPS satellites equipped with light-emitting units 1 are flown in formation to form a constellation, and the light-emitting units 1 are distributed among multiple satellites, irradiating the light-receiving units 2 with lasers, thereby reducing the laser energy per satellite and enabling operation. For example, if there is a 1SSPS-SAT-LOWP with a low output (specifically, a small amount of ultraviolet photons) of output X watts, and n of these are placed in quasi-zenith orbits or LEOs to form a 1SSPS-SYS-SEIZA, and energy is irradiated from the n 1SSPS-SAT-LOWP satellites to the light-receiving units 2, then if the lasers from all satellites are received by FCS-2, then n × X watts (nX watts) can be received at the point of FCS-2. On the other hand, at points outside the focal point of FCS-2, the laser energy travels in a straight line along the trajectory FHNU-EXT and is attenuated and diverged by the atmosphere. The laser / photon output on the trajectory FHNU-EXT, which deviates from FCS-2 and heads towards the ground through the stratosphere and troposphere, is less than X watts, which is lower than the nX watts of the focal point FCS-2. Thus, energy density reduction is possible in locations other than the focal point FCS-2. (Also, at the focal point FCS-2 in the stratosphere and troposphere, the air density is low and there is little atmosphere, oxygen, and ozone, so photons are not absorbed and a photon convergence point can be formed at the focal point FCS-2. However, if the focal point FCS-2 is set in a location with 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, in the ground area outside the focal point FCS-2, the element of laser attenuation by the atmosphere and the element of reducing and dispersing the output of one laser to the aforementioned 1 / n of the total laser output X of the constellation can be combined, and these two elements aim to ensure safety on the ground. (In this application, in addition to attenuation by the atmosphere, the laser heading towards the ground is weakened by forming a constellation and dispersing the laser output to 1 each.)●By arranging multiple satellites (small or medium-sized) in a constellation in quasi-zenith orbit or low Earth orbit, when a satellite with a light-emitting unit 1 having a power output of Y watts approaches a light-receiving unit 2, multiple or n satellites in close proximity emit lasers from their light-emitting units 1 to the light-receiving unit 2, which receives the lasers, thereby obtaining nY watts of power. Even if some photons are not received and attempt to reach the ground, their output will be limited to Y watts, which may help reduce the output of photons that miss the target and head towards the ground, thus ensuring safety on the ground. *If n satellites equipped with low-power (X watt) light-emitting units 2 are prepared, it may be safer than when aiming at 2 with one nX watt high-power laser, as it may reduce the amount of energy of photons that miss 2 and head towards the ground. *In SSPS satellites and lunar bases equipped with SSPS, the greater the laser output of a single light-emitting unit 1 (output of one laser), the more unsettling it may be to people on the ground. Therefore, multiple light-emitting units 1 may be arranged to distribute the laser output and prevent the energy density per laser beam from becoming too high. Considering the above, the device of this application may be configured to use multiple light-emitting units 1 and irradiate lasers toward a light-receiving unit 2 in the upper atmosphere. *Figure 10 discloses the trajectory of the laser when emitted from a position shifted from the light-receiving unit 2 or when there is no light-receiving unit 2. Figure 10 describes considerations for making it difficult for laser energy to reach the ground. FCS-2: The focal point of the laser / photon that one light-emitting unit 1 should aim at, or that multiple light-emitting units 1 should aim at. FCS-2 may coincide with the point where the light-receiving unit 2 should receive the light. In this application, the aim is to use the atmospheric attenuation of ultraviolet lasers to ensure safety on the ground, and FCS-2 may be located in the stratosphere. FHNU-EXT: The trajectory that deviates from FCS-2 and heads towards the ground through the stratosphere and troposphere. <Light receiving unit 2, aerial section> 2: Receiving unit, light receiving unit (laser receiving unit, laser receiving unit, which is mounted on means of placement in the air 3, aircraft 3, airship, platform 3. 2 is configured to receive the laser of 1, taking into consideration the orientation of the light receiving surface, etc. It may include devices for attitude control and changing the orientation of the light receiving unit, and may include gimbals, deflection devices, stabilizers, etc.)2REA: Reactor, chemical reactor, photoreactor, thermal reactor, heating furnace, chemical machinery and equipment (a reactor that causes chemical reactions using photons with photon energy capable of exciting semiconductors with a wide bandgap, such as photocatalysts, which can cause chemical reactions using heat, ultraviolet light, etc.)2WEP: Wireless power receiving device related to 2.2PV: Photoelectric conversion element.2RANT: Part that converts radio waves / electromagnetic waves into electricity (the part of the radio wave receiving method among wireless power transmission methods such as electromagnetic induction method, magnetic field resonance method, electric field coupling method, and radio wave receiving method. Includes antenna, rectifier circuit, and rectenna)2LAND: Receiver located on the ground (mainly the part that receives power from 3WEP) <Aircraft 3, air section, Figures 2 and 11, etc.>3: Aircraft, airship, etc. (means for placing the receiver 2 at an altitude where the attenuation of ultraviolet lasers, which may be UV-C or B, is low, such as high altitude or stratosphere). 3EPF-SYS: An aircraft system that receives energy derived from the SSPS of this application with a light receiving unit 3 and uses it as electricity, power, chemical energy, or fuel. 3GAB: The gas balloon of 3. 3HAB: The hot air balloon of 3. 3GHAB: The gas hot air balloon and Roger balloon of 3. 3TH: The thruster of 3 and its related devices (including aircraft propeller motors, motors, actuators, and jet engines, as well as rocket propulsion, electric thrusters, ion thrusters, photon sails, and thrusters based on the reaction of photon emission and reflection for spacecraft. Propellant for the thruster may also be included). 3BATT: The battery of 3 (or batteries and fuel that drive 3, 3ETC, 3TH, etc.). 3ETC: Other devices and equipment for driving 3, including the control system, computer system, communication system, power system, electrical wiring system of 3, sensors, instruments, positioning devices, control device of 3HAB, hot air balloon heating device, gas balloon 3GAB control device, thruster 3TH control device, etc. 3CON: Control unit and communication unit of 3 (including communication devices with external devices, external 3, and 3FORM). 3SEN: Aviation instruments, sensors, etc. 3WEP: Wireless power transmission means from 3 to external 3, 3FORM, or the ground. 3WIR: Devices connecting 3 and 3FUEL, including the receiving unit 2, or wire, power cable, optical repeaters, power or energy transmission paths. 3WIRI: Electrical wiring, power wiring, signal wiring, optical fibers, etc., wires, cables, and buses of 3. 3REA: Reactor of 3. (3REA is a device that performs chemical reactions. For example, it may perform reactions using heat, electricity, or light.)This can be any device that performs chemical reactions using light, electrochemical reactions / electrolysis, or chemical reactions using heat. For example, an electrolysis device, a photocatalyst or photoreaction device, a thermal reactor, an ammonia synthesis device, various chemical devices, a kiln for firing materials such as ceramics, cement, and lime, and a reactor / furnace for steelmaking. 3RPL: Means for transporting pre-reaction and post-reaction substances (fuel, etc.) in reactor 2REA of 2, such as a pipeline for chemical substances, a pump, etc. 3VALV: Fuel outlet / valve to the fuel tank inside 3FUEL. 3FUEL: An aircraft that manufactures fuel using the electricity or energy obtained in 2 and / or an aircraft that transports the manufactured fuel. The fuel may be, for example, hydrogen, metallic lithium, metallic sodium, metallic magnesium, metallic calcium, metallic aluminum, metallic silicon, iron, zinc, or other metals, or carbon, hydrocarbons, or organic substances. 3FUEL-GEN: The fuel manufacturing section of 3FUEL. For example, a device that electrolyzes water from SSPS using electricity obtained through 1 and 2 to produce hydrogen and oxygen as fuel. Alternatively, it could be a fuel cell or battery that generates electricity using water and oxygen as fuel. *To further avoid limiting the scope of the invention, it could be described as an energy converter that converts the energy obtained by 2 and 3 (electrical energy, thermal energy, mechanical energy, thermal engine energy) from 1 to 2 via SSPS into chemical energy or fuel, and which can also convert (reverse convert) chemical energy or fuel into electrical energy, thermal energy, mechanical energy, or thermal engine energy. 3TANK: Cargo compartment, tank, fuel tank [3FUEL-TANK: Fuel tank for 3FUEL (May also be a hydrogen gas fuel tank or balloon. Oxidized metals may also be reduced and used as fuel. For example, hydrogen, metallic lithium, metallic sodium, metallic magnesium, metallic calcium, metallic aluminum, metallic silicon, iron, zinc, and other metals, or carbon, hydrocarbons, or organic matter.)] 3LUGG: Cargo compartment for 3. May also carry batteries and fuel to power 3. May carry a person to operate 3 and control devices such as 3 and 3FORM. May also carry equipment and control devices to operate 3 and 3FORM unmanned. 3LUGG-H2O: Cargo compartment for water, may also be a rainwater collection device and a water compartment. *The propulsion system 3TH may take in air, atmosphere, gas, or ionized gas from the outside and use it as propellant.3TH may use air, atmosphere, gas, water, or fluid as a propellant, and the energy of the photons obtained by the light receiving unit 2 is given to the propellant to perform jet propulsion, rocket propulsion, propulsion by heating and ejecting the propellant, propulsion by accelerating and ejecting the propellant using an electric field or magnetic field, electric propulsion, propulsion by ejecting the propellant by MHD acceleration, etc., and the propellant may be ejected and used for propulsion. 3TH may use air, water, hydrogen, liquid hydrogen, or solid propellant (propulsion by laser ablation). 3TH may use water, atmosphere, or air as a propellant, and water or atmosphere may be heated 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 ejected from aircraft 3 / 3TH for propulsion. Water may be obtained by aircraft 3 moving and receiving precipitation, snowfall, hail, rainwater, or atmospheric water vapor as shown in Figure 12 (Figure 25 of this application). It may also be obtained from a ground water source 4H2O. Water may be used as a propellant or for the synthesis of hydrogen fuel and hydrogen-containing compounds. *If 3 is 3FUEL, it may be a cargo compartment for carrying the substance (water) that will become the fuel (hydrogen), similar to the 3TANK of 3FUEL. SWP-ABS-LINE: The upper limit altitude to which photons absorbed and attenuated in the atmosphere can reach. (May include the stratosphere) TPS-LINE: Troposphere. AIR: Atmosphere. <Ground section> 4: Ground-side energy supply system, above ground. 4VALV: Connection part / valve that connects to 3VALV. 4FUEL-TANK: Fuel tank that stores fuel transported from 3FUEL-TANK via 4VALV and 3VALV. A tank for storing energy after it has been transported to the ground using means such as 3, based on the energy derived from SSPS received by the light receiving unit 2. It may also be a pipeline. Fuel storage location, flow path, and flow path to the user. <User section> 6: User section. User section that consumes energy. 4 The part that consumes energy by consuming fuel transported and delivered from the FUEL-TANK to 6. (Or the user part that consumes energy derived from SSPS.) <Others> 12: Cable (may include power cables. May also be a cable / path that guides power in the form of light.) (May include conductor elements 1 and 1WIRE.) 14: Base part of the cable, may be connected to 1100. 17: Connection part with 3 (may also be connection part 17 described in Patent Document 2). 1100: Power grid.<Figure 3, Diagram of hydrogen and metal fuel production by launch> 1VALV: Connection port for connecting tank 5TANK, which is loaded with water and hydrogen when hydrogen is produced from water using electricity obtained from 1VALV. 1FUEL-GEN: Fuel production section and chemical reaction section of 1. 5VALV: Connection port for tank 5. 5TANK: Tank (a tank that loads water / hydrogen, oxidized metal / reduced metal, fuel raw materials / produced fuel). 5TANK1: Tank loaded with fuel raw materials (e.g., water, metal oxides, carbon dioxide). 5TANK2: Tank connected to 1VALV that is producing and loading fuel using electricity or energy from SSPS (e.g., producing hydrogen and oxygen from water, producing metals and oxygen from metal oxides, producing hydrocarbons). 5TANK3: Tank loaded with fuel that is dropped from SSPS toward the ground (e.g., hydrogen / tank loaded with hydrogen and oxygen, metal / tank loaded with metal and oxygen, carbon / hydrocarbon / tank loaded with carbon, hydrocarbons and oxygen). 9. Launch method. Or, a method of launching from the moon and dropping onto Earth, planets, satellites, celestial bodies, or outer space. The following method. <Figure 4, Metal and fuel production by reduction of metal oxides on the lunar surface> *The configuration in Figure 4 is a process of removing metal elements from the moon and combining them with oxygen from Earth, which disrupts the lunar material balance and is therefore not a sustainable cycle. However, (in the course of space development) it does not emit carbon dioxide in the short term, (it does not require launching water and oxides from the ground, and resources on the moon can be dropped directly to the ground), and it is disclosed as a method that allows the electricity generated by space-based solar power near the moon to be used on Earth (using materials as fuel) while reducing the amount of material launched to the moon. (The following 5O2 may be used for oxygen for habitation, migration, and stay on the moon, etc., or for terraforming. Oxygen for habitation may be produced using electricity from SSPS on satellites and planets containing metal oxides, not limited to the moon.) 5MM: Mine, extraction source, and source of lunar resources such as metal oxides. It may also include a series of means from the extraction, sorting, separation, purification, and transportation of materials to the production of fuel 5M. 5MOX: A fuel raw material (metal oxide such as silicon oxide or aluminum oxide) that can be used as fuel by the energy of SSPS such as metal oxides mined and collected on the Moon. To avoid limiting the scope of the invention, it refers to a substance, object, or device that can be procured locally in outer space where the energy of SSPS can be stored (Moon, satellites, asteroid belt, meteorites, comets and other small celestial bodies, celestial bodies drifting in space). 1FUEL-GEN: The fuel production unit and chemical reaction unit of 1. It may produce fuel or a substance that stores chemical energy using the electricity or 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 or electrolysis using thermal energy. For example, in addition to the production of 5M, it may also be a part that uses chemical or thermal energy to chemically react substances to produce products when manufacturing earth and stone products such as cement at a lunar base.) 5O2: A storage location, pipeline, etc. for oxygen produced by the reduction of metal oxides. Oxygen-related section. 5M: A metal produced by 1 FUEL-GEN, 1 SSPS power, and 5 MOX (a lunar resource-derived metal that can be oxidized by oxygen and generate oxidation-reduction energy). 5M may be, for example, powdered metallic silicon, metallic aluminum, or iron powder. It may also be flammable powdered metallic silicon or aluminum. 5MC: A substance that can combine with oxygen obtained from lunar resources and SSPS (for example, the fluid silane or trichlorosilane).*Although it requires more careful handling compared to metallic silicon, its fluid nature makes it potentially possible to transport 5MC via pipeline. ) 5TANKM: A transport container loaded with 5M or 5MC for use on Earth / ground. Drop container / fuel drop pod. 4O2, 6O2: Oxygen source on the ground or user side. Used by user 6 to oxidize 5M. For example, if metal oxides are obtained on the moon, and the oxygen from the metal and oxygen produced from them is stored on the moon and the metal is dropped to Earth and reacted with the oxygen, the Earth's oxygen will decrease as it combines with the metal. Therefore, it may be preferable to drop both the oxygen and metal synthesized on the moon to the ground. 6: A user that consumes fuel and oxygen and utilizes energy. <Figure 5, Examples in SSPS in quasi-zenith orbit, lunar or geostationary orbit> 1SSPS-SAT: An artificial satellite for SSPS including 1. 1SSPS-SYS: SSPS system. (-SEIZA: A group of SSPS satellites, a constellation of artificial satellites, including 1.-QZSS-SEIZA: A group of SSPS satellites, a constellation, in a quasi-zenith orbit.-ORBIT: A group of SSPS satellites, a constellation, in orbit.-GEOS: A group of SSPS satellites, a constellation, in geostationary orbit.-MOON: A group of SSPS satellites in orbit near the Moon or on the lunar surface.) 1LINK: A relay satellite. It relays between the light-emitting unit 1 and the light-receiving unit 2 of 1SSPS. A satellite or device that relays photons that are about to pass between the light-emitting unit 1 and the light-receiving unit 2. *For example, a mirror 1MRR that reflects lasers and photons, and a satellite equipped with an attitude control device that changes the orientation of the mirror. This prevents insufficient accuracy and diffusion of laser light generated from 1 when sending photons from 1 to 2 by laser from a distant location such as a geostationary orbit or the Moon to Earth. It may be equipped with optical components 1OPT such as a lens that focuses light. If the laser beam diverges from 1SSPS to relay satellite 1LINK, the diverged laser may be optically corrected (or adjusted) to a focused laser again using the lens of 1OPT on 1LINK. *For example, 1LINK includes a laser receiver 2 and a laser emitter 1. The diffusion of the laser beam occurs as the distance the laser travels increases, and this is recovered as laser light energy by the photoelectric converter and receiver 2 of relay satellite 1LINK to obtain power, which is then used to re-emit photons to receiver 2 on 3 in the air or to other 1LINKs.1LINK uses 2 and 1 to convert the diffused light beam into electricity, which is then re-emitting as undiffused laser light. 1MMR: A mirror or device capable of reflecting photons. (Examples: sunlight reflection / focusing mirror, ultraviolet laser reflection aluminum mirror) May be mounted on 1LINK. *For example, it reflects photons irradiated from 1 to change the trajectory / emission of the photons. 1OPT: Optical system, optical components, means for correcting light. May be mounted on 1LINK. *For example, if the light beam spreads (or diffuses and blurs) when photons irradiated from 1 travel a long distance, the optical system is used to refocus the light beam. 2: Light receiving unit. 3: Aircraft. 3FUEL: Fuel synthesis aircraft / fuel transport aircraft. 4: Ground unit. 6: User unit. <Figure 6, Example of using energy from 2 to 3 to drive 3 or service by 3> 3FCAR: Airplane, flying car. May also be an emergency vehicle / emergency transport equipment. 3ROBOT: Flying robot. It may be equipped with a robotic arm with tools, and may also be in the form of a humanoid robot. *The 3FCAR or 3FORM robot may be made to perform the work. For example, forestry work may be made to a robot based on 3, 3FCAR or 3FORM, and the 3FCAR or 3FORM robot may be equipped with pruning devices and means (devices for cutting branches, attitude control devices and propulsion devices that change the attitude and position of the aircraft relative to the tree and each branch, pruning devices and pruning means) to prune trees in a forest. (The 3ROBOT may be made to perform any work that can be done by the aircraft system of this invention from among various tasks in agriculture, forestry, fisheries, etc.) *The aircraft 3 or 3FCAR may be used for the delivery or retrieval of objects. (For example, mail, fuel delivery, object delivery, e-commerce, resource recovery, water delivery, transport and drop of fire extinguishing agents) *The aircraft 3 or 3FCAR may be transport equipment, or it may be an aircraft or living unit that also serves as a hotel or residence (or an aircraft-type camper van 3FCAR, a residential aircraft). <Figure 7, Example of using energy from 2 to 3 in 2TAG> 2: Receiver. 2WEP: Wireless power receiving device and communication device related to 2. *Alternatively, the power transmission and communication unit for the tag 2TAG to transmit wireless power and communicate with the tag scanner 6TAG-SCANNER for monitoring and managing tagged objects, and the power supply unit for the tag. 2RANT: The part that converts radio waves and electromagnetic waves into electricity.2WEP may include (the radio wave receiving method among wireless power transmission methods such as electromagnetic induction, magnetic field resonance, electric field coupling, and radio wave reception methods, including antenna, rectifier circuit, and rectenna). 2TAG: A tag equipped with a receiving unit 2. A tag mainly used for monitoring objects, luggage, children, and the elderly, equipped with a part that receives power from 3WEP, and obtains power through wireless power supply from 3WEP to perform wireless communication, beacon operation, sensing, and positioning. A wireless tag / beacon device that operates by obtaining power through wireless power transmission. 2TAG may be equipped with computer functions, and may be equipped with a processing unit, memory device, input / output device, and communication device. 2TAG-CAP: A part that stores power obtained from the wireless power supply of 2TAG. 2TAG-SENSOR: A sensor attached to the 2TAG (an acceleration sensor when measuring the acceleration of an object to which the 2TAG is attached using the 2TAG; a load sensor when measuring weight / load; a temperature sensor when measuring temperature; an altimeter when measuring altitude; a magnetic sensor when measuring magnetic fields; and dedicated fire-fighting sensors when detecting smoke or fire. When aircraft 3 approaches close to the 2TAG-TAG, wireless power transmission becomes possible, and the 2TAG-CAP is charged, the sensor is driven by the charged power. Positioning and time acquisition of the 2TAG may also be performed by radio signals from aircraft 3, positioning systems such as Michibiki, or 1SSPS-SYS-QZSS-SEIZA.) 2TAG-IN: Input device for the 2TAG. Includes the 2TAG-SENSOR sensor. 2TAG-OUT: Output device for the 2TAG. 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 emit a sound in response to the communication result from the communication device or a request from the processing unit controlled by a program in the processing unit / storage unit. For example, if 2TAG is charged by a tag scanner, it may emit a sound to alert the tag scanner or the person accompanying the tag scanner of the tag's presence. 2PATCH: A patch that can be a patch or adhesive patch. It can also be a piece of cloth, a bandage, or a film that can also be used as a tag. It can also be an adhesive or sew-on patch for clothing or underwear. *This includes patches used for treating dementia, patches for smoking cessation, adhesive patches or tapes for medicated patches, children's bandages or adhesive bandages, and patches that can be attached to people's clothing, underwear, or accessories.* To prevent diseases such as malaria caused by mosquito bites, insect repellent patches that emit insect-repelling and insecticidal components and can be applied to clothing are also acceptable. Clothing insect repellent patches are also acceptable. 2TAG-PATCH: A 2TAG equipped with 2PATCH. Or a 2TAG that can be attached to or attached to 2PATCH, or a 2TAG that can be attached and detached. * 2TAG, 2PATCH, and 2TAG-PATCH have parts or layers that function as tags, adhesive patches, or adhesive cloth, film, or tape. For example, a 2TAG support 2TAG-SP and an adhesive layer 2TAG-ADH. * For example, a 2PATCH may be a film or tape with an adhesive for attaching to an object and a drug-containing adhesive layer (ointment) coated or laminated onto a support. (Examples of 2PATCH include rivastigmine tape and poultices / tapes.) A 2PATCH may also be a bandage or dressing. *For example, 2PATCH may be a patch that does not contain medicine or pharmaceuticals, or it may be a tape, film, or patch that includes an adhesive layer 2PATCH-ADH and a support 2PATCH-SP. (In the case of a pharmaceutical patch-type tag 2TAG-PATCH, there is the advantage that the tag can be checked for attachment, reattached, or replaced with a new tag when applying a patch.) 6 OBJECT-TAG-ATTACHED: An object to which 2TAG or 2TAG-PATCH is attached. 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, alcohol, medicines, pharmaceuticals, highly toxic substances, etc. that require item management, cargo, luggage, bags, identification cards, keys, car keys, automobiles and transportation equipment, buildings and furniture, important documents, antiques, treasures, precious metals, jewelry, accessories, computers, watches, devices, clothing, underwear, footwear, people, animals, plants, and living things. 6TAG-SCANNER: A part that wirelessly powers 2TAG and 2TAG-PATCH, or receives wireless communication signals and beacons emitted by 2TAG and 2TAG-PATCH to inform the user of the presence of a tag. Tag scanner. *6TAG-SCANNER may include, for example, aircraft equipped with tag scanners, 3CON, drones, 3DRONE and 4CON, ground base stations, 6CON, 6 user stations, 6SMART-PHONE, 6HANDY-TAG-SCANNER, tag scanners mounted on automobiles and transportation equipment, etc.3. 3DRONE: A drone, aircraft, transport equipment, or vehicle that may act as a tag scanner, perform tag searches unmanned, wirelessly transmit and charge power to the ground or air at the search location during flight, and receive responses such as beacons or communications from charged tags during this process, and search for the tags. *3DRONE may fly towards and approach tags to search for them, while wirelessly transmitting power from 3WEP to the tags. Communication between the tag and the drone is permitted. 6TAG-MONITORING-USE: Tags. Description of applications for monitoring. Figure 7(a). 6OBJECT-TAG-SEN-ATTACHED: An object to which a sensor-equipped 2TAG or 2TAG-PATCH has been attached. (Also, a description of applications in which the tag is used as a measurement sensor for the tagged object.) *For example, a system in which a sensor-equipped 2TAG or 2TAG-PATCH is attached to the bottom of a storage bottle of a toxic or hazardous substance whose amount used needs to be monitored in a laboratory. When the bottle is placed down, the force exerted by the bottle's weight through the tag's load sensor (bottle mass m × gravitational acceleration g) is detected as the bottle weight, and the change in bottle weight is used to manage the amount of toxic or hazardous substance reagent used. Power for driving the tag is transmitted wirelessly. Figure 7(b). <Figure 8, Example of 3FORM> *Figure 8 shows an example of using the 3FORM configuration of this application for entertainment or work purposes. *Figures 8(a) and (b) show examples of two aircraft, each equipped with a robotic arm, robotic legs, or the torso, limbs, head, spine, and tail of a human or animal, performing coordinated formation flight. The robotic arm may manipulate, grasp, or hold devices, tools, or implements for removal or additive manufacturing, as shown in Figures 9 (3A1-RP and 3A1-AM), and may also be fitted with such devices. The group of aircraft (3A1, 3A2, 3L1, and 3L2 in Figure 8) may be equipped with robotic hands. Figure 8(b) shows an example of using an aircraft like the one in U.S. Patent Publication No. 20140231590 in a show. In Figure 8, the aircraft may fly in formation like humanoid robots (moving doll devices). *If 3FORM is in the stratosphere and propulsion by jet engines and propellers is difficult, electric propulsion systems using photons, particles, or charged particles, such as photon sails and ion propulsion systems, or rocket propulsion systems are required. <Figure 9> Figure 9 is an explanatory diagram of a robot arm robot arm that performs removal processing and additive manufacturing, such as 3A1-RP and 3A1-AM, by attaching a robot arm 3A1 to 3 which may be charged by the light receiving unit 2 or driven by fuel produced by 2. 3A1-RP: Removal processing device / robot arm. 3A1-AM: Additive manufacturing device / robot arm. 4WK: Workpiece, part / product / object. 4WK-AM: Target part of 4WK for additive manufacturing / film deposition / lamination, laminated part. 4WK-RP: Target part of 4WK for cutting / removal processing / cutting / polishing.*Note that in the scenario of using 3ROBOT in forestry, 4WK is the tree to be pruned, 4WK-AM is the substance added to the work target such as pine beetle control agents, paints, seeds, etc., and 4WK-RP is the substance removed from the work target such as branches to be pruned from trees to be pruned. <Figure 10> FCS-2: The focal point to be aimed at by one or more units. FCS-2 may coincide with the point to which the light from the light receiving unit 2 should be received. In this application, the aim is to use the atmospheric attenuation of ultraviolet lasers to ensure safety on the ground, so FCS-2 may be in the stratosphere. FHNU-EXT: The trajectory that deviates from FCS-2 and passes through the stratosphere and troposphere towards the ground. *Figure 10 shows an example of an aircraft 3 traveling from Japan to Uruguay (on the opposite side of the Earth from Japan, half the circumference of the Earth) without landing on the ground, using the energy received from the light-emitting unit 1 of the SSPS via the light-receiving unit 2. (In Figure 10, it is also possible to travel from Japan to Uruguay using 3, and 3 may receive photons from the light-emitting unit 1 to the light-receiving unit 2 to replenish energy over international airspace or the open sea off New York along the route between Japan and Uruguay.) 1DBL: Space debris orbiting in outer space (where there are no objects such as the atmosphere that attenuate photons). *In outer space, the laser can be focused without attenuation using 1DBL as the focal point. (It is possible to irradiate 1DBL in the FCS-2 created by multiple 1s with a laser.) <Figure 11, explanatory diagram of aircraft 3> 2: Light-receiving unit. 2POSI: Positioning device or positioning device part for irradiating photons / lasers from 1 to 2 and hitting them. <Electrical / Power / Signal System> 2PCE: Photoelectric converter. 3ETC: Parts necessary for the operation of 3, such as electricity, power, computer, various circuits, and communication unit. 3WIR: Part that exchanges power and photons with the outside. 3REA: Reactor of 3 (may also be a device that operates an electric furnace or electrolysis operation when power is supplied). 3WIRI: Circuit, wiring. 3BATT: Battery. 3LUGG: Luggage compartment. 3SEN: Sensor, measuring device, instrument. 3TH: Propulsion device, propulsion means. 3B: Balloon, levitation device, levitation means, lifting device, lifting means. 3HAB: Hot air balloon. The hot air balloon gas of 3HAB may be heated by the energy from the light receiving unit 2. 3GAB: Gas balloon. 3WEP: Wireless transmission means to the outside. 3CON: Communication unit / control unit to the outside. <Fuel / chemical system> 2REA: Device that causes a reaction using photons.(Photoreaction, thermal reaction) 3RPL: Pipeline, piping, and tanks for fuel-related materials. 3VALV: External fuel connection valve. 3REA: Reactor for 3. 3EPF-SYS: Aircraft system that receives energy derived from the SSPS of this application at the light receiving unit 3 and uses it as electricity, power, chemical energy, or fuel. *Figure 11 is an explanatory diagram of aircraft 3, which may have the form of an aircraft with a propulsion system, motor, actuator, propeller, fixed wing, rotary wing, hot air balloon 3HAB, or gas balloon 3GAB driven by the SSPS. *It is possible to deliver energy derived from the SSPS to aircraft 3 including 2 day or night, and energy may be transmitted from 3 including 2 to other aircraft 3, 3FUEL, or 3FORM, or energy may be shared with them. <Reference diagram, Figure 12> 3LUGG-H2O: Cargo compartment for water. Rainfall may be received and recovered and used as water. (Consideration of environmental impact.) 3H2O-LINE: Water pipelines, tanks, and flow paths. 3H2O-VALV: Valve / nozzle for drawing water to the outside. 4H2O: Ground-based water supply section (mainly assumed water sources: including rivers, dams, and reservoirs). 6LIFE: Organisms requiring watering or water supply (delivering water to people, animals, plants, living things, deserts, etc.). 6: User section. Houses, factories, towns, etc. that require water. 6FIRE: Fire source. (Extinguished by adding water). *Figure 12 shows the possibility of 3 operating as a continuously water-supplied aircraft using energy from SSPS, and discloses that water is supplied from the outside of 3 to the inside of 3, and then supplied to consumers from the inside of 3 via the valve. Emergency water supply equipment 3 / water supply transport equipment 3 may also be used. The aircraft 3 / transport equipment 3 may obtain the water from rainwater or ground-based water resources 4H2O. The water may be used as propellant ejected from the propulsion device 3TH of the transport machine 3 (aircraft 3, placement means 3, orbital elevator cage 15, space fountain, carrier, aerial structure 2, launch device, launch vehicle, vehicle 3 for launching from the ground into space, etc.). The water may undergo processes such as heating, chemical reaction, filtration, and sterilization using energy obtained from the light receiving unit 2, and may be used for propellant ejection, fuel generation, cooling of aircraft equipment and light receiving unit 2, and production of drinking water. (4H2O includes water tanks, ponds, rivers, etc.)In cases where seawater can be converted into fresh water or where seawater can be used for certain applications, seawater is also included) ※In particular, rainwater does not contain salts that need to be separated by membrane separation or the like like seawater (as water that has already been separated from salts in the natural circulation), and it falls on land and over the ocean, and rain and snow that are not saltwater pour down from rain clouds over the sea surface to the sea. Therefore, the present application discloses obtaining rainwater, rainfall, and snowfall in the sky even over the open ocean by means of 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 unit, and it may be used as a water supply aircraft 3. ※FIG. 12 relates to the utilization 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 illustrated. <0124><O2, O, oxygen atoms>The present application discloses the utilization of the earth's atmosphere, oxygen, and oxygen atoms in the subordinate concepts of the claims. For example, the utilization of photons attenuated by oxygen and ozone in the atmosphere, and further, in a system using oxygen as an oxidant, synthesizing fuel from which oxygen atoms have been removed by reducing lunar oxides, manufacturing hydrogen and oxygen with the light receiving part 2 in the air and the aircraft 3FUEL, and the utilization of the fuel and the oxygen atoms by the user 6 are disclosed. <0125><Method of transporting energy from space to the earth>In the superordinate concept of the claims of the present application, it is not limited to the use of space solar power generation. For example, a power plant using elementary particles or nuclear power (a power plant using elementary particles and nuclei such as radioisotopes, nuclear fission, nuclear fusion, antimatter, and pair annihilation) is provided on the lunar surface, the electric power of the power plant 1PP is sent to the light emitting part 1, energy is sent from the light emitting part 1 to the light receiving part 2 in the form of photons, and the aircraft 3 may be operated from the light receiving part 2, or substances on the ground may be oxidized and reduced to synthesize fuel. (When sending from 1 to 2, a relay satellite such as 1LINK may be used.) <0126><Space nuclear power generation, space physical battery power generation, space power plant>Where sunlight cannot be obtained, electric power obtained from 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.The raw materials for nuclear fuel, such as uranium (a mixture of uranium-235 and uranium-238), can be launched from Earth before enrichment. The nuclear fuel can then be enriched on-site at a lunar base or similar location to obtain nuclear fuel (uranium-235), which can then be used for nuclear power generation at a lunar nuclear power plant. The electricity generated can then be delivered to Earth via 1 to 2. *Waste management is required after power generation. <0127> Regarding the monitoring tag, please refer to and quote the content of paragraph 0127 of Japanese Patent Application No. 2023-007722. <Problem> We want to provide a wearable tag or beacon for monitoring the elderly or for finding them when they go missing. With the aforementioned tag 2TAG, it was unclear whether the elderly would necessarily wear the wearable device with a built-in tag on their shoes, insoles, belts, or watches, due to differences in their preferences, conditions, and level of interest. We thought it would be good to have a tag that relatives or others who are watching over the elderly could attach as part of administering medication. <Solution> A wireless tag is attached to a patch, charged by wireless power supply, and the beacon etc. is activated to search for the tag and the elderly person to whom the tag is attached. Tag power supply and beacon radio wave detection may be performed by a drone during the search. We also propose a configuration in which tag power supply is provided from spacecraft such as SSPS, and information useful for time information, positioning, and tag processing unit control is transmitted between the satellite and the tag, and beacon detection is performed. <Description> The most important feature of the present invention's tag 2TAG and tag scanner is that it is a patch-type wireless tag that combines a patch for administering medication to dementia patients with a wireless tag, enabling the administration of transdermal medication to dementia patients and the attachment and maintenance of the 2TAG tag. The 2TAG may be charged by the wireless transmission means of aircraft 3 that patrols and searches for tags, and may perform beacon and wireless communication operations. <Wireless power supply method> The present invention includes a passive type RFID tag that stores power by wireless power supply and generates a wireless signal (beacon signal) from the stored power, and a device for finding the wireless IC tag and the object to which the tag is attached. ●According to prior art, a 10m class power supply technology (spatial transmission type wireless power transmission system) using the 2.4GHz band that can supply power up to 10m away has been proposed. ● The aforementioned 10m-class power supply technology is mounted on a drone and a patch equipped with a UHF tag function, creating a patch-type wireless tag called 2TAG. After power is supplied to the 2TAG by the aforementioned wireless power transmission system, the power obtained from the power supply is used to generate a beacon signal for the 2TAG, which is then used to search for objects or people whose location is unknown.●[Hypothetical Example / Implementation 1]: For example, for an elderly person (or a child or other person to be watched over or searched for) who has gotten lost in the mountains, a patch or adhesive patch equipped with the 2TAG attached to the person's back in advance in a position that is difficult to peel off, is applied. In the event of an emergency, a drone equipped with the 10m class power supply technology is flown around the mountain, and if the 2TAG is within the wireless power supply range, the 2TAG will be powered to operate a communication device / beacon (or a signal transmitting device / communication device containing information useful for searching for the object), and the drone and the 2TAG will receive the signal emitted by the 2TAG's communication device to detect the presence of the 2TAG, with the intention of using this to aid in the search. (Alternatively, the 2TAGs may be detected wirelessly and used for detecting, searching, monitoring, guarding, and managing objects THG to which the 2TAGs are supposed to be attached, as well as for management during distribution and transportation.) ● Aircraft such as drones or spacecraft such as satellites may be used as power supply devices or reading devices (tag scanners) for searching for Tag 1. Also, the tag scanners may be equipped on automobiles, electric assist bicycles, and transportation equipment that have power sources and travel around town. For example, a drone 3DRONE may be used as a tag scanner. (The drone-type Tag 1 scanner is just an example, and existing RFID tag handheld scanners or handheld tag scanners may also be used for searching.) For example, in the case of elderly people, it is hoped that it will be difficult to remove adhesive patches from their backs, but this is just an example, and the tag may also be in a form that can be attached to living things such as dogs, cats, or pets, such as collars, and the power supplied by the power supply is used to generate beacons. For example, in the case of a child, there is a risk that someone attempting to harm the child, such as kidnapping, might transmit a power supply radio wave towards a location where a 2TAG is likely to be located, power up the 2TAG, charge it, activate the 2TAG, and use it to operate a beacon or other function to find the child. To prevent this, power supply and beacon operation may be limited to tag scanners that are authorized to communicate and power the tag 1 during power supply. The 2TAG will operate a beacon or other function depending on the conditions under which it operates and the environment in which it is located. Specifically, the 2TAG may be equipped with authentication means.For example, authentication means using a password or PIN, locking means using buttons or inputs on the tag, means to control the on / off status and access of beacon functions, etc., and one-time password authentication means provided within tag 1. <Actual tag 1> For example, in the application of a tag 2TAG for the 2PATCH adhesive patch for the elderly, the 2TAG has a password printed on it, and the 2TAG has the printed password PWD recorded and stored in the control unit or IC of the 2TAG, and based on that password, encrypted communication may be performed between the tag scanner or a terminal connected to the communication path / network destination and the 2TAG as an encryption key for encrypted communication. Only tag scanners that have input and stored the PWD may communicate with the 2TAG, operate the 2TAG's beacon, etc., and supply power to the 2TAG. The 2TAG may be provided with means for overlapping and attaching it on top of the 2PATCH adhesive patch, means for fixing it, means for adhesive, or means for attaching and detaching it between the 2TAG and the adhesive patch, such as hook and loop fasteners. <Form of the tag as a medical product> 2TAG is a patch, which is a medical product / medical device, but 2TAG may also be a device used for monitoring while being a medical device, for example, a medical device / medical device that measures heart rate, such as a wristwatch-type device. <Wearable tag> From the perspective of a device worn on the human body, 2TAG may be a wearable such as an insole, shoe, eyeglasses, contact lenses, contact lens-type output device, vision correction device or apparatus, hearing aid, earphones / headphones, or wireless earphones. ●It may also be attached to the skin like a decorative sticker (bindi) in India. 2TAG may also be used as a decorative sticker / patch / appliqué for clothing. ●For example, wireless earphones are small and easily lost, but by equipping them with a part that acts as tag 1 as claimed in this application, or by attaching them, it may be useful in finding lost wireless earphones in the city or at home. ●When a person looking for a 2TAG contained in a lost object uses their sight or hearing to search, 2TAG may be equipped with a wireless beacon or a sound-emitting, light-emitting, or vibration-emitting beacon, as is well known. <Tag Patch> For Patch 2, any medication such as rivastigmine or rivastigmine tape will suffice. For example, medications that widen the bronchi, medications that widen the blood vessels in the heart, or medications that help with smoking cessation would also be suitable.For example, it could be a nicotine-containing smoking cessation aid (1 pc) or a nicotine patch (1 pc). The patch (1 pc) could be a transdermal formulation (1 pc) patch. The patch (1 pc) could also be a medicine such as a poultice (1 pc) or an analgesic / anti-inflammatory agent (1 pc). The patch (1 pc) could also be a dressing cloth, a bandage (1 pc), an eye patch (1 pc), etc. ● Drug management use: 2PATCH may contain medicines. It may be attached to equipment that handles medicines. ● Use in medicines and items requiring management: Even in cases of prescription medicines or containers of highly toxic substances that are locked and managed in laboratories such as universities, the method of searching for, managing, and guarding lost items using beacons etc. as claimed by 2TAG may be used. <Power supply and transmission of time and other information by artificial satellite> This application includes inventions for finding the location of items and people. For example, it includes a method of wirelessly transmitting information and signals and wirelessly supplying power from an artificial satellite or a group of artificial satellites / constellations placed in space to the aforementioned tag on the ground (power transmission system in space-based solar power generation). In addition to artificial satellites, aircraft in the air may also be used. <Background for using the patch> Based on examples from close relatives, the inventor recognized that elderly people do not necessarily wear wearables such as shoes or bracelets, and that the degree of attention elderly people pay to what they wear changes depending on the progression of their symptoms. Even if guardians prepare clothing, watches, or footwear with tags for monitoring or emergency situations, elderly people themselves may not wear, be unable to wear, or maintain them. <Transdermal patch> Based on these considerations, and after observing the lives of elderly people, the inventor focused on rivathymine patches for transdermal patches as an item that elderly people were found to wear constantly, and proposed the patch-type wireless 2TAG of this application. <Application of transdermal patches, patches, and tapes to surfaces other than the skin> Transdermal patches are applied to the skin of the person receiving the medication, but there is a possibility that they may peel off the skin. (For example, patches may peel off due to the effects of sweat in the summer.) In this application, in addition to the skin of elderly people, they may be applied to the fabric of underwear, or to underwear or innerwear (closer to the skin, difficult to remove outdoors). The patch can be tape-type or have a hook-and-loop fastener attached to the underwear. <Location of application to the skin> If applied to the back, it may be difficult for elderly people to reach out and remove the patch.<Problems to be solved> The main problem to be solved is to provide a wearable tag for monitoring the elderly, or a wearable tag for finding them when they go missing. <Development of a tag form that is easy to maintain> The problem to be solved is that even if a device is prepared as a wearable device, each elderly person has their own individuality and it is uncertain whether they will properly wear a specific item such as shoes or a wristwatch. The challenge was to find an item that they would continue to wear and to devise an RFID tag function, tag driving method, and search method that is suitable for that item. ● It may have been a challenge to devise a tag system that can be attached by relatives or others who are watching over the elderly as part of medication administration. ● Regarding the above tags, it was uncertain whether they would necessarily wear a shoe, belt, or watch-type tag-embedded wearable device due to differences in the elderly person's preferences, condition, and level of interest. <Challenges during search> ● The detection range of a tag scanner using the UHF method (e.g., adhesive tags in the 900MHz band) was about 2 to 5m. When elderly people get lost in urban areas or mountains, a wide detection range is desirable, for example, 5m or more. We will consider and disclose the configuration of the power supply method and power storage (capacitor type, primary battery type, or secondary battery type) to achieve this. The challenge was to equip the device with long-range RFID tag functionality (including passive, semi-active, and active drive modes) and enable the tag scanner to transmit the tag's presence and identification information to the tag scanner using power. <Drone-type tag scanners, tag scanners on aircraft, spacecraft, and satellites, tag scanners retrofitted to transportation machines such as cars, motorcycles, and taxis> If a person with 2TAG gets lost, searchers may use handheld tag scanners to search, or they may use drone-type tag scanners to search. ●For example, to search for a person lost in the mountains, multiple drones can be launched into the mountain where the person is thought to have gotten lost. The drones wirelessly transmit power to the search area and radiate energy wirelessly so that the 2TAG can be charged. The unmanned aircraft may be positioned using signals such as GPS and operated autonomously while searching for 2TAG. ●For example, if the wireless communication power and antenna sensitivity allow, artificial satellites, satellite constellations, spacecraft, or space structures may be used to search for 2TAG instead of drones or aircraft.●For example, tag scanners may be pre-installed on taxis, motorcycles, delivery vehicles, or public vehicles (postal vehicles, police vehicles, fire / medical vehicles, garbage trucks) to check for people wearing 2TAGs wandering around town. ●2TAGs may be attached to the keys of buildings or equipment vehicles, and the 2TAGs may be searched for using the tag scanners to manage and find keys. <When a tag scanner is installed on a mobile device> A tag scanner may be installed on a mobile device such as a smartphone. A tag scanner may be installed on or retrofitted to a smartphone to search for people to whom 2TAGs are attached, or 2TAGs attached to important items. <Means for solving the problem> The most important feature of the present invention is that the tag 2TAG and tag scanner 6TAG-SCANNER are a patch-type wireless tag that combines a patch for administering medication to dementia patients with a wireless tag, enabling the administration of transdermal medication to dementia patients and the attachment and maintenance of the tag. Furthermore, the conditions for activating the tag after attachment are also disclosed. <Effects of the invention. The 2TAG tag and tag scanner of the present invention have the advantage of being able to administer transdermal medication to dementia patients and to attach and maintain the attachment of the tag by combining a patch for administering medication to dementia patients with a wireless tag. <Example>Figure 7 illustrates the concept of the present invention. The main point of the present invention is to incorporate the procedure of attaching and managing the wireless tag 2TAG into the therapeutic procedure performed by relatives, nurses, and caregivers of elderly dementia patients, which is to administer transdermal medication, thereby enabling the two procedures to be performed in one procedure. Furthermore, when searching for the wireless tag 2TAG, power is stored in the 2TAG by wireless power supply from automobiles and transportation equipment in the city, aircraft such as drones, and spacecraft such as artificial satellites, and this power is released as a beacon signal. This beacon signal is then sent to the tag scanner at a distance beyond the range of wireless power supply, thereby enabling the search for the 2TAG that is expected to be attached to the elderly person. *Detailed explanations of basic computers, electronic components and elements, communications, power supply, drones, aircraft, spacecraft, time synchronization technology, and positioning technology are omitted as they can be explained using known methods and previously published patent documents. Figure 7 and 2TAG of this application use, for example, wireless LAN (IEEE 802.11 series), tethering or wireless PAN (IEEE 802.15 series), and wireless power supply, but these technologies are clear from known literature, so their explanations are omitted.

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

[0060] , a lightning protection method using the energy transport method from the light-emitting unit 1 to the light-receiving unit 2 using the laser is disclosed. (The lightning protection method of this application is an idea.) <Technical Field> <0001> This application references to its prior applications, Japanese Patent Application Nos. 2022-123161, 2022-086263, and 2023-007722. This application includes an idea relating to lightning protection for lightning strikes caused by thunderclouds. <Background Art> <0002> Lightning strikes affect and sometimes damage power equipment, power grids, and information and communication equipment. Therefore, measures are taken to protect buildings from lightning strikes by installing lightning rods. Furthermore, according to Patent Documents 1 and 2, lightning protection methods have been devised that use conductive wires (Patent Document 1, Figure 1) or plasma regions created by lasers (Patent Document 1, Figure 2) directed from the ground toward rain clouds and thunderclouds to reduce the resistance value of the capacitor portion insulated between the thundercloud and the ground, or to short-circuit it, thereby intentionally changing the direction to which the lightning charge flows and the direction in which the lightning strikes. Patent Document 2 discloses the application of the fact that synchrotron radiation generated using a free electron laser or a particle accelerator and undulator has an ionizing effect (Patent Document 2, Figure 1), and lightning protection methods using lasers are currently being researched and developed. Furthermore, according to the prior application for this application, Japanese Patent Application No. 2023-007722, a configuration is disclosed for irradiating air containing Earth's oxygen molecules, ozone, oxygen atoms, nitrogen molecules, nitrogen atoms, and other atmospheric molecules and atoms from outer space with ultraviolet rays, as well as X-rays and gamma-ray photons. <Prior Art Documents><Patent Documents> <0003> <Patent Document 1> Japanese Unexamined Patent Publication No. 03-222295 <Patent Document 2> Japanese Unexamined Patent Publication No. 05-180954 <Summary of the Invention> <Problems to be Solved by the Invention> <0004> (1) When short-circuiting from the ground using a conductive wire, it is desirable that the wire be lightweight (in order to reduce the weight to be lifted and suspended). (2) When a laser is emitted from the ground into the sky during rainfall, if snow, raindrops, hail, etc. are blown from thunderclouds toward the ground and hail is present in the laser beam, it may scatter the laser. Also, when the inventor was devising a method for transporting energy from space to the SSPS, he considered a configuration in which ultraviolet and X-rays are received from the space-side light-emitting unit 1 by the light-receiving unit 2 in the air.In this invention, instead of being on the ground, multiple light-emitting units 1 of the space-based solar power generation satellite 1SSPS or the 1SSPS satellite constellation irradiate the thundercloud from the upper layer (space side / stratosphere side) to the lower layer (ground side) of the thundercloud with ionizing radiation such as X-rays. This ionized and plasma-like region is used to promote a short circuit in the capacitor section (capacitor section consisting of the LCP region and LCM region in Figure 13) which is made up of charged layers in the upper and lower layers of the thundercloud. By creating a conductive ionized region that acts as a breakthrough (IONA-NAIL, nail-shaped portion in Figure 13, or the ionized, plasma-like, and low-resistance portion of the atmosphere due to the laser focus FCS-2) that weakens the insulation of the capacitor inside the thundercloud which has accumulated positive and negative charges, it is thought that the charges necessary for lightning can be short-circuited (discharged), leading to lightning protection while reducing the effects of meteorological phenomena such as hail. ●In this application, considering that laser irradiation from ground waves to thunderclouds may be scattered by hail, etc., we will investigate a method of lightning protection using X-rays or other lasers directed from outer space to thunderclouds in the air.This application discloses a lightning protection method intended to facilitate short-circuiting of the electric charge inside the thundercloud. ●As shown in Figure 13, (considering that in the troposphere, lasers may be less effective due to objects that obstruct the straight propagation of lasers and cause diffuse reflection, such as rain, hail, and snow, and that when a laser is emitted from the ground towards the upper atmosphere, it may affect objects such as aircraft in the upper atmosphere,) so as not to be affected by meteorological conditions 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 may be irradiated from outer space or the stratosphere toward the thundercloud in the troposphere to promote short-circuiting within the thundercloud, or to promote short-circuiting between the lower layer of the thundercloud and the ground.Charge may also be guided to flow more easily in the upper layer of the thundercloud and in the part of the air above the thundercloud. The aforementioned photons: Preferably, ionizing, power-controlled X-rays or gamma rays. (Broadly speaking, ultraviolet rays such as UV-B and UV-C. To be more precise, if a laser or radio wave that is absorbed by the atmosphere, such as some infrared rays, is used to induce ionization, partial low resistance of thunderclouds, or dielectric breakdown.) <Means for solving the problem> <0005> <(1) Lightning protection by conductors> Conductor element 1 as shown in Figure 1 of Japanese Patent Application No. 2022-123161 may be used to cross a thundercloud or to assist in discharge / short circuit within a thundercloud.Furthermore, the conductive cable section 12 of the orbital elevator section 10 described in Japanese Patent Application No. 2022-086263 may be arranged to cross the thundercloud vertically and vertically. <0006> <(2) Lightning protection by ionization> A light-emitting unit 1 (synchrotron radiation generator, free electron laser) placed in outer space or air (e.g., satellite constellation, aircraft, or air platform) is used to irradiate and emit (ultraviolet or) X-rays or gamma rays to a light-receiving unit 2THCL, which is a thundercloud or rain cloud in the air. The laser may have a trajectory that crosses, passes through, or penetrates the thundercloud 2THCL from the space side towards the ground. The ionizing radiation laser, such as X-rays or gamma rays, ionizes oxygen molecules, ozone, oxygen atoms, or nitrogen molecules, nitrogen atoms, or other molecules and atoms in the atmosphere along the laser's path, forming an ionized region, a highly conductive region, or a plasma region. The plasma region is used to short-circuit or reduce the insulation between the positively charged region / layer and the negatively charged region / layer of the thundercloud, with the intention of neutralizing the charge, short-circuiting, protecting against lightning, or controlling lightning strikes. In addition to short-circuiting the positive and negative charges within the thundercloud, the laser may also be used to induce, discharge, or dissipate the thundercloud's charge to a different layer or part of the cloud. For example, the laser could pass through the upper layers, stratosphere, mesosphere, thermosphere, or ionosphere of the thundercloud, creating ionized or low-resistance areas in those regions, allowing the thundercloud's charge to flow or escape to these areas. The laser irradiation could also be used to create low-resistance areas, causing electricity to flow upward from the thundercloud, such as into sprites. Furthermore, if the laser uses photons with wavelengths shorter than UV-B, it is expected that the laser will be absorbed and attenuated by photoreactions, chemical reactions, and ionization of atoms and molecules in the atmosphere, making it difficult for the laser to reach the ground. <Effects of the Invention> <0007> According to the method of this invention, the laser is not scattered by rain and hail in the troposphere, and an ionized, low-resistance conductive path IONA can be formed on thunderclouds from space, allowing for attempts at dielectric breakdown, discharge, and lightning protection of thunderclouds. Compared to placing a laser emission unit 4LASER on the ground and irradiating the air, it is possible to attempt lightning protection by irradiating locations with lasers using a constellation of artificial satellites.<Brief explanation of the drawing> <0008> <Figure 13>Diagram illustrating a lightning protection method in which photons with wavelengths shorter than UV-B, such as X-rays and gamma rays, are irradiated from an upper-air light-emitting unit 1 to a thundercloud 2THCL (aerial light-receiving unit 2). (In Figure 1, the light-emitting unit 1 used in the SSPS laser in outer space or the light-emitting unit 1 of a stratospheric platform / aircraft 3 may be used during irradiation.) <Figure 12>Diagram illustrating lightning protection by short-circuiting the thundercloud 2THCL with a conductive cable 1WIRE 12. *(a)Diagram illustrating an orbital elevator 10 having a cage section 15 3KAGO connected to a ground section 14 and a space structure by a cable 12. (b)Diagram illustrating a system in which the ground section 14 and an aircraft 3, aerial platform, etc. are connected by a cable 12. *The cage section 3KAGO receives energy from the light-emitting unit 1 via the light-receiving unit 2, drives a propulsion device 3TH which may contain propellant, and raises and lowers 3KAGO in the vertical direction (space / ground direction). 3KAGO may be guided up and down by 12. <Modes for carrying out the invention> <0009> This will be explained using Figures 12 and 13. <Example 1> <0010> ● From a light-emitting unit 1 located in space or in the atmosphere / stratosphere, ionizing radiation photons 1HNU-X, such as X-rays, or photons 1HNU, such as ultraviolet light, are irradiated toward the ground side of the thundercloud 2THCL, passing from the upper side / stratosphere to the lower troposphere / ground side. (1HNU is used for lightning protection purposes in the form of ultraviolet, visible light, and infrared light. Preferably, photons with wavelengths that react with oxygen molecules, nitrogen molecules, and atmospheric atoms and molecules and are absorbed through photoreactions and chemical reactions are preferred.) At this time, the low-resistance conductive path IONA formed by penetrating the positively charged layer LCP at the top of the thundercloud destroys (or is expected to destroy) the insulation between the positively charged layer LCP and the negatively charged layer LCM at the top of the thundercloud. (When there is an insulation gap between the LCP and LCM within a thundercloud, laser irradiation creates a low-resistance region in the insulation gap, forming a wire-like area that weakens the insulating force within the thundercloud, with the intention of inducing dielectric breakdown and discharge.) ●In the lower right of Figure 13, the laser penetrates the thundercloud 2THCL, forming a conductive path IONA, or IONA-LINE in the figure, which discharges the charge of the capacitor made up of the LCP and LCM, causing a short circuit and lightning protection.(In the concept of insulating between thunderclouds with a conductive wire, it is sufficient to use the conductive wire shown in Figure 1 of Patent Document 1 to release the charge from the thundercloud or short-circuit it, and the thundercloud can be made conductive 12 and the orbital elevator section 10 as conductors.) ● In the lower left of Figure 13, the laser travels so as to penetrate the positively charged layer LCP at the top of the thundercloud, and the part of the laser's trajectory is ionized, forming a nail-shaped (or laser-attenuated) low-resistance conductive path IONA-NAIL. Because the conductive path IIONA-NAIL is (suddenly) formed in the gap / distance that was previously insulated between LCP and LCM, the insulation distance is shortened only in the part of the conductive path IIONA-NAIL, and lightning protection is achieved by discharge L-SCN from there. If there are objects that should be avoided by laser irradiation in order to reduce the impact on living organisms, aircraft, etc. in the air, the laser may be turned off. The laser output may also be controlled so that the laser output does not become large in places other than the focal point FCS-2. In addition, if radiation / X-rays cannot be used to avoid biological effects, an ultraviolet laser may be used and its output controlled to attempt to ionize the atmosphere. <Example 2> The left diagram of Figure 12 is an explanatory diagram of a case in which a power plant on the space side, a space solar power plant, a space structure 1, and the ground-level part 14 are electrically connected, and power from the power plant on the space side is transmitted to the ground-level part 14 via cable 12. The right diagram of Figure 12 is an explanatory diagram of a power transmission system / energy transmission system (a system that uses a shortened cable to the aerial placement means 3 instead of the long cable of the orbital elevator, and has the advantage of being able to shorten the cable) in which power or energy is transmitted from the light-emitting part 1 on the space side to the light-receiving part 2 in the air using the laser SSPS method, and then the placement means 3 (aircraft 3, HAPS, etc.) including the light-receiving part 2 and the ground-level part 14 are electrically connected via cable 12, and power is transmitted from the light-receiving part 2 to the ground-level part 14 and the ground-side power grid 1100. It may be preferable to use the conductor element 1 or cable 1WIRE of the present invention (which uses carbon material (CNT, etc.) in the material part 101 of the element 1 of the present invention to reduce the amount of copper used) and reduce the weight of the conductor compared to a conductor made of copper only. ●The right-hand diagram of Figure 12 shows that the placement means 3 needs to support the cable 12 by lifting it and letting it hang from the air to the ground. In this case, it is preferable that the cable 12 is lightweight.(CNTs have a specific gravity of 2.0, and copper has a specific gravity of about 8. CNTs and carbon materials are lightweight, and by using a 1WIRE made of carbon material for the cable 12, the weight of the cable that the placement means 3 must lift into the air can be reduced.) ● In all configurations of Figure 12, the cable 12 crosses the upper and lower layers LCP and LCM of the thundercloud, thereby short-circuiting the charge of the thundercloud via 12. ● Figure 12 shows a system in which the cable 12 crosses the upper and lower layers LCP and LCM of the thundercloud, thereby short-circuiting the charge of the thundercloud via 12. The ground portion 14 is positively charged, and by connecting it with the negatively charged portion of the thundercloud via 12, a current flows through 12 due to the short circuit, and electrical energy is transported and transmitted. Although this invention is intended for lightning protection, the configuration in Figure 12 allows for the collection of thundercloud energy on the ground using 12 and 14, and the thundercloud energy obtained by 12 and 14 may be supplied to the power grid 1100 in a usable form by circuits and devices provided in 14, etc. 14 and 12 may be used for power generation and charging by lightning.) The cage section 3KAGO may receive energy from the light-emitting section 1 via the light-receiving section 2 and be propelled and raised / lowered. *The aircraft 3, 3KAGO, and the aerial platform 3 may be equipped with devices capable of generating power in the air, such as solar cells or aerial wind turbines. They may also be equipped with auxiliary power supplies or batteries. The aircraft 3 (aerial platform) connected to the ground section 14 in the right diagram of Figure 12 may raise and lower cargo like a ladder truck, ladder lifter, or crane, and may exchange power with the ground section. It may also be equipped with a robotic arm or crane to perform additive manufacturing, removal processing, various operations, and cargo transport. In this application, when transmitting energy from SSPS (laser type, or in some forms of this application, millimeter wave, microwave, or radio wave type) to the ground, two forms are disclosed: a method of transmitting power using a cable 12, and a method of converting the energy in the form of fuel or chemical substances in the placement means 3 and transporting the substances to the ground section 14 by an aircraft or the like. <Industrial applicability> <0011> In the configuration shown in Figure 13, it can be used to attempt lightning protection by irradiating a potential lightning strike area 2 from the light-emitting unit 1 of a satellite constellation with a laser. (The configuration with the light-emitting unit 1 in Figure 13 allows the satellite with the light-emitting unit 1 to irradiate photons towards thunderclouds and the atmosphere in areas prone to lightning strikes when orbiting LEOs, etc., thereby promoting short circuits or discharges of capacitors in thunderclouds, and can easily respond to user requests for lightning protection. On the other hand, in the configuration shown in Figure 12, it is necessary to deploy the cable 12.) <Explanation of symbols> <0012> <Explanation of Figure 13> 1: Light-emitting unit placed in outer space / air. Laser light-emitting unit. Light-emitting unit of photons including ultraviolet rays such as UV-B and UV-C, or X-rays and gamma rays. *Without limiting the scope of the present invention, when irradiating thunderclouds with photons from the stratosphere / space side and acting on the thunderclouds with photons, and focusing on photons that react and dissociate with ozone, oxygen molecules, nitrogen molecules, atmospheric molecules, etc. and are attenuated by the atmosphere, gamma rays, X-rays, some ultraviolet and infrared light, and some radio waves such as millimeter waves may be included. 1SSPS: SSPS portion including light-emitting unit 1. Light-emitting unit utilizing space-based solar power generation. 1SSPS-SYS-SEIZA: Light-emitting unit 1 of a satellite constellation. Example: LEO and GEO satellite constellations.1LLR: Free electron laser device (output-controlled X-ray laser) 1HNU-X: Ionizing radiation photons such as X-rays, laser. 1HNU: Photons emitted from light-emitting unit 1. 2: Part or object that receives photons from light-receiving unit 1. 2THCL: Thundercloud. (When cumulonimbus clouds etc. are used as light-receiving unit 2) 2AIR: Air including 2. Or when a part of the air is the target of energy irradiation by light-emitting unit 1. 3: Aircraft, transport equipment, means of arranging light-receiving unit 2 in the air. LCM: Negative charge region of thundercloud, negative charge on the ground side of the lower layer of the thundercloud. LCP: Positive charge region of thundercloud, positive charge on the upper layer of the thundercloud. L-SCN: Part where discharge is expected to occur using an ionized part that protrudes like a nail in the upper layer of the thundercloud as a guide, internal discharge point of the thunderstorm. Dielectric breakdown part. A part of the thundercloud that was previously insulated becomes more conductive due to the laser irradiation, becoming a pathway for the LCP part or the charge in the upper layer of the thundercloud, making it prone to short circuits. IONA-NAIL: (Ionized, plasma-formed, and low-resistance parts that protrude in the shape of a nail driven into a plate in the upper part of a thundercloud created by a laser. Protruding conductive parts. Induces discharge within the thundercloud. Can be a low-resistance part formed by the focal point FCS-2 of multiple lasers irradiated from multiple light-emitting parts 1.) IONA-LINE: (Short-circuit conductor parts and low-resistance parts created by a straight, conductive laser. Induces discharge and short circuit within the thundercloud.) VL: Voltage of the thundercloud (capacitor voltage) 1100: Power grid 6: Power user <Explanation of Figure 12> 10: Space structure of the orbital elevator. 1: Space structure, artificial satellite, space base, etc. (Example: Space structure 1 and aerial structure 2, which are the so-called orbital ring portion as shown in Figure 1B of Japanese Patent Application No. 2022-086263. Equipped with 1TH and 2, they may receive photons from 1 and be propelled and accelerated. Spacecraft, launch vehicles, space structures, orbital rings, aerial structures, and ring structures may be equipped with 1TH and 3TH and a photo-receiving unit 2, and photons may be transmitted from the light-emitting unit 1 to accelerate, propel, move, fly, float, attitude control, and drive them.) 1TH: Spacecraft propulsion system. 3SPACESHIP (Spacecraft, spacecraft, launch vehicle, etc. Equipped with 2, 1TH, and 3TH.) 3KAGO: Cage section 15 attached and guided by the cable 12 of the orbital elevator 10, and propelled, raised and lowered and moved by the propulsion system. 3TH: Propulsion system of 3KAGO, propulsion system and its attached equipment and propellant, etc. 2: Photo-receiving unit.12: Cable (1WIRE may be used) 14: Ground part, 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, Description of orbital elevator and aerial platform> *Figure 26 may include a combination pulley 10B and may include elements of a known traction-type rope elevator, and may include a counterweight, hoistway, rope, wire, deflector, combination pulley, sheave, hoisting machine, cage, landing door, landing station machine room, control device, shock absorber, bit, and brake. Cage 15 may be equipped with a thruster 3TH including a light-receiving part 2 and a counterweight 15W. The right diagram of Figure 26 shows elevator 10AIR with a heavy hoisting machine 10B installed at the bottom and a combination pulley 10B at the top. 15: Elevator with a known hoisting machine installed at the bottom (Note that an elevator 10AIR or orbital elevator 10 configuration is possible with the hoisting machine installed at the top or bottom. 10B may include a combination pulley, hoisting machine, and multiple pulleys) 15: Cage, cargo compartment, and carrier of an elevator or ropeway. 15 may also be the cage 15 of an aircraft 3 or transport equipment 3 connected by a wire 10WIR with a thruster 3TH. (It may also be the cage 15 of the cable 12 of an orbital elevator 10 or an aerial platform 3.) 15W: Counterweight of the elevator, cableway, pulley, and crane section, and counterweight of the cage 15. 10B: Pulley section (a pulley or a combination pulley may be used), sheave, hoisting machine, elevator hoisting motor section (the hoisting motor may be a non-contact type motor with magnetic levitation bearings. Pulley, winding section, and power section of 12 or 10WIR) *3TH has a propellant such as water, and the propellant of 3TH may be replenished when 15 reaches the base section 14. *15 and 15W may be an aircraft 3 or transport equipment 3, and 3 may be equipped with a thruster 3TH and a light receiving unit 2. *15 and 15W are driven like the hoisting motor of a traction elevator, and their power may be obtained from the light emitting unit 1 via the light receiving unit 2. When the 3TH of 15 and 15W is at an altitude higher than the stratosphere or troposphere to which the light from the light emitting unit 1 (e.g., UVC light) reaches, the 3TH receives laser irradiation from the light emitting unit 1 and moves 3KAGO and 15 ( / 15W) up and down. Accordingly, the 15W ( / 3KAGO·15), which is connected by wire 10WIR (using pulley 10B), moves and moves up and down.If 15W is at the aforementioned high altitude, the light from the light-emitting unit 1 is shone onto the 3TH of 15W to move 15W and move 15. 10WIR: Rope / wire of 15 / 15W. 14: Ground part. 4LASER: Laser light-emitting unit from the ground. It is affected by tropospheric influences such as hail and clouds, but if it is directly below 15, power may be transmitted to 15 by laser (instead of the space-side light-emitting unit 1). 1: Photon light-emitting unit 1. (The orbital elevator / air platform in Figure 26 is equipped with a ring 10WIR that can be supported and rotated by pulleys 10B etc. on the space / air side device 17 and the ground part 14, like a Ferris wheel / cableway and its carriers, and lasers are shone onto the light-receiving units 2 of each thruster 3TH of each cage 15 attached to the 10WIR using pulleys (like a Ferris wheel or multiple carriers of a cableway), causing each 15 to rotate in one direction (like a cableway, from space to the ground and back to space) and repeat the rotation.) It may be operated in the manner described above. Propellant, water, etc. for 3TH may be supplied to 15 at the ground level 14. (Like a space fountain, each 15 and 10WIR connected to 15 may be supported by 10B, 14 and 17 and rotate by propulsion from 3TH. Each 15 and 15W of 10WIR may be lifted from 14 to 17 and then lowered repeatedly. *A circular route that returns to ground level 14 via the air side 17, like a cable car or Ferris wheel, is also acceptable.) The light-emitting part 1 of this invention and the receiving The optical unit 2 may be used for propulsion, acceleration, and driving of space / airborne structures, orbital rings, partial orbital rings, space fountains, launch loops, mass drivers, launch devices, transport equipment, etc.) *For example, if it is desired to lift the device 17 from the ground and place it near a space-side structure 2, then in the platform 3 (an aerial platform 3 comprising the device 17, a propulsion device 3TH, and a photo receiver 2 for photons transmitted from the optical unit 1, and having a cage 15, cable 12, and pulley 10B that can raise and lower cargo, propellant, and water from the ground 14 and supply them to the propulsion device 3TH, the aerial platform 3 includes the device 17 shown on the left side of Figure 26. In this platform 3, propellant and water are supplied to 3TH from the ground via 12 and 3, and 3TH can perform propulsion, levitation, raising and lowering, movement, attitude control, launch, and lifting operations using the energy from the photo receiver 2 and the propellant.The aerial platform 3 and placement means 3 on the space side may be launched and raised by heating and ejecting water and propellant supplied from the ground using energy obtained from the light receiving unit 2, and then moved and placed near the structure 2 on the space side. 17: Connection part to the aerial or space side part, may be equipped with a non-contact suspension mechanism. 17TR: Transport equipment part, train part, suspended non-contact from the structure 2 and movable and guided along the structure 2. May be equipped with a light receiving unit 2. May be propelled and operated by receiving photons from the light emitting unit 1. <Figure 27, description of orbital elevator and space structure> 1100: Power and communication network. 1000: Ground, Earth, Moon, planet, satellite, celestial body. 10: Orbital elevator. 12: Cable. 15: Space elevator cage. 17: Connection part. May include functional parts of a magnetic suspension part (magnetic attraction type, electromagnetic induction levitation support type EDS, etc.). May also be an aircraft 3 or a spacecraft. )171: Magnetic suspension means for 17. 171C: Coil (for magnetic suspension between 17 and space / airborne structures) 171S: Sensor, gap sensor for magnetic suspension. 171E: Circuit, control circuit, magnetic attraction feedback circuit, magnetic suspension control unit. 171R,E: Propulsion devices 1TH and 3TH for 17. Space structure 1 and airborne structure 2: Structures located in the air or space (annular, linear, base station, aircraft / spacecraft), which may include magnetic suspension functional parts. They may also be rotating (eddy current countermeasures) rails. 17TR: Transportation equipment that uses the rails to magnetically levitate, magnetically suspend, non-contact supported, guided, move, and propel. It may also be driven by 3TH and a light receiving unit 2. 317: Magnetic suspension means on the structure side. Parts that magnetically interact, attract, or repel 171C, such as magnetic material, core, magnet PMG, conductor, etc. (Part of the magnetic suspension section) *317 may be divided into sectors or may have a section that increases the resistance of 317. *In order to reduce eddy currents in the rotating 317 and the stationary 17, in case the force due to eddy currents (the behavior of Arago's rotating disk and U-shaped magnet) interferes with the magnetic suspension aimed at this invention, an element that can decrease or increase the conductivity of 317 may be used, and a conductive element 1, 1FILM (with reduced copper and containing carbon) and its gate control circuit may be used. *From the viewpoint of eddy current control, the ease with which eddy currents are generated in the 317 section and the 317MG section may be controlled.To increase eddy currents, the gate of 317's 1FILM is turned on to decrease the resistance of 317 and change the repulsive force between 317 and 171C. When decreasing eddy currents, the gate is turned off and the resistance is increased. 3171S: Sensor, gap sensor. 32: Circuit, control circuit. 32-wir: Wiring <Document name> Claims <Claim EW1> An energy transport method using a photon generator (1) placed in an artificial satellite or outer space, and a light-receiving unit (2) placed and positioned in the air at an altitude of the stratosphere or troposphere or higher, capable of receiving photons irradiated and emitted from the photon generator (1), wherein the photon generator. An energy transport method comprising the steps and procedures of irradiating, emitting, relaying, transmitting, and transmitting photons from (1) to the light receiving unit (2), wherein the photons are UV-B or photons with a wavelength shorter than 315 nm, and the photons are characterized by being absorbed by photoreactions and chemical reactions with ozone, oxygen molecules, oxygen atoms, nitrogen molecules, nitrogen atoms, and molecules and atoms in the atmosphere. <Claim EW2> A method for reducing atmospheric resistance using the energy transport method described in Claim EW1, comprising the steps of irradiating, emitting, relaying, transmitting, and transmitting a laser containing photons from the light-emitting unit 1 to the light-receiving unit 2, which is the atmosphere or thundercloud in the air, wherein the laser has a trajectory that crosses, passes through, and penetrates the atmosphere or thundercloud from the space side toward the ground, wherein the laser is a laser using photons in the wavelength range of X-rays and gamma rays, and is capable of ionizing oxygen molecules, ozone, oxygen atoms, or nitrogen molecules, nitrogen atoms, or molecules and atoms in the atmosphere along the path of the laser, thereby forming an ionized region, a plasma region, or a highly conductive region along the path of the laser. <Claim EW3> A method for lightning protection using the atmospheric resistance reduction method described in Claim EW2, characterized in that the ionized region, plasma region, and highly conductive region are formed between the positively charged region and the negatively charged layer of the thundercloud, reducing the resistance between the positively charged layer and the negatively charged region of the thundercloud, thereby destroying the insulation of a charged capacitor consisting of the positively charged layer and the negatively charged layer of the thundercloud and preventing lightning. A method for canceling or neutralizing the charge of lightning or a method for lightning protection. <Document Name> Abstract <Abstract> <Problem> When lightning protection is performed using lasers from the ground, weather conditions are a concern, so we will investigate a method of lightning protection using laser irradiation from outer space. <Solution> X-rays and gamma rays are irradiated and emitted from a light-emitting unit 1 (synchrotron radiation generator, free electron laser) placed in outer space or air to a light-receiving unit 2THCL which is a thundercloud or rain cloud in the air. The laser may have a trajectory that crosses, passes through, or penetrates the thundercloud 2THCL from space towards the ground.The aforementioned ionizing radiation lasers, such as X-rays and gamma rays, ionize oxygen molecules, ozone, oxygen atoms, or nitrogen molecules, nitrogen atoms, and other molecules and atoms in the atmosphere along the laser's path, forming ionized regions, highly conductive regions, and plasma regions. Using these plasma regions, an attempt is made to short-circuit or reduce the insulating properties (low-resistance of the atmosphere and thunderclouds) between positively charged regions and negatively charged regions and layers of a thundercloud, thereby preventing lightning strikes or controlling lightning. <Selected Figure> Figure 13.

[0062] <lp0004>(Protection of Cable 12 from AO and Conductor Element 1) In this application, ladders 12 or cables 12 that are likely to come into contact with atomic oxygen AO (for example, orbital elevator cables 12 that come into contact with AO which may exist in the high altitudes of the stratosphere or in low Earth orbit space) may be configured as shown in Figure 11(C) by plating and coating carbon fibers with a metal film (or silicon-based film / film with barrier properties against AO) such as copper, so as to withstand erosion from atomic oxygen AO. In low Earth orbit and the stratosphere, atomic oxygen AO exists which is generated when Earth's oxygen molecules dissociate (through photoreaction with vacuum ultraviolet rays, etc.), and it is assumed that this reacts with carbon materials including CNTs and plastics, degrading the materials (ultimately decomposing the carbon materials into carbon dioxide, etc.), resulting in the degradation and destruction of the cable 12. In order to protect the carbon-based material of the cable 12 from the AO, the carbon material may be coated with a metal film, etc. By applying the aforementioned coating, the conductive element 1 can be driven as a carrier introduction function utilizing the electric double-layer transistor structure claimed in this application as shown in Figures 1 and 11, and may also have the effect of preventing the carbon material from being corroded and decomposed by the AO. The cable 12 of this application may be made of a carbon material and may have a metal film, a barrier film deposition layer, a coating, or a plating layer that acts as a barrier to the AO. For example, in the configuration of the left and right in Figure 12, the cable 12·1WIRE may be coated as described above. *Since the cable 12 will be a conductor of the 10km, 20km, or 100km class, exceeding the altitude of the troposphere, carbon-based materials or deep eutectic solvents may be used for 101 and 105 of 12 to reduce material costs. <lp0005>(Thunderclouds and wire insulation) For example, in the configurations shown on the left and right of Figure 12 (left: a space elevator connecting ground 14 and space structure 1 with cable 12, right: ground 14 and aerial platform 3 connected via cable 12), both cables 12 and 1WIRE pass through the thundercloud, forming a path that short-circuits the positive and negative charges in the upper and lower layers of the thundercloud. The 1WIRE may have the aforementioned metal film with AO barrier properties formed on the 1COVER portion, or it may be used in a conductive portion that short-circuits the thundercloud's charge due to the effect of the metal film. (The metal film may be used to allow the thundercloud's charge to flow, or to reduce the resistance of the 1WIRE to prevent heat generation and overheating of the wire due to the electrical resistance caused by the instantaneous large current generated when the thundercloud charge flows through the 1WIRE. *In this application, even if the 1WIRE or 12 does not have an electric double-layer transistor structure or carrier introduction mechanism, it may be coated with a metal film to allow the thundercloud's charge to escape or flow, or to protect the wire from AO.) <lp0006>(A flexible substrate such as a film substrate, wire, thread, or fiber material containing a conductor element 1, or an electrical circuit on a substrate) An electrical circuit using the conductor element 1 and the conductor 1WIRE, formed on a flexible substrate, may constitute an electrical circuit used in electronic equipment, electrical devices, sensors, computers, wireless communication terminals, or wireless tags (2TAG). If the number of carriers can be increased by introducing carriers while retaining the lightweight and flexible characteristics of carbon materials and organic semiconductor materials, the conductivity of the electrical circuit will be improved. Furthermore, effects such as a reduction in the electrical resistance of the circuit may occur. <lp0007>Natural resources such as silicon oxide and silicon oxide 5MOX (or metal oxide 5MOX) obtained from celestial bodies such as the lunar surface, satellites, and asteroids (and also natural resource collection sites on celestial bodies containing silicon resources such as the Moon and Mars 5MM) may be reduced on-site at the said celestial bodies such as the lunar surface, satellites, and asteroids using solar energy, power plant electricity, etc. to obtain silicon compounds 5MC, metallic silicon 5M, and oxygen 5O2. These 5MC, 5M, and 5O2 may then be loaded onto a spacecraft and used as propellants for the spacecraft. *The gravity acting on a spacecraft is weak on the moon, satellites, and asteroids. On the other hand, there are planets like Jupiter that contain a lot of hydrogen, etc., but have strong gravity like the sun, and escaping from such planets and celestial bodies into space may require considerable effort. This application focuses on the moon, asteroids, etc. ●For example, if you want to travel through space from the moon to Mars in a spacecraft equipped with a rocket propulsion system 3TH, the propellant launched from Earth (liquid hydrogen, chemical rocket fuel, liquid oxygen, water, etc.) may run out during the journey. Considering the cost of launching from Earth into space, one might be tempted to generate and procure propellant from resources already present in celestial bodies such as the Moon, Mars, Venus, planets, asteroids, and moons. (The Moon has water, which can be broken down into hydrogen and oxygen and used as propellant.) As argued in this application, the Moon is believed to have abundant natural resources (other than water), such as silicon dioxide and metal oxide 5MOX. By reducing these to obtain the reduced substances 5MC / 5M (or reducing agents) and oxygen 5O2 (or oxidizing agents), and loading them onto the spacecraft (as shown in Figure 17, 3SPACESHIP / transport equipment 3 loaded with 5M and 5O2), the amount of propellant in the spacecraft 3SPACESHIP can be increased (procured locally), which is thought to be helpful in securing propellant when the spacecraft attempts to propel itself from the Moon to Mars, Venus, or even more distant celestial bodies. The intention is to increase the operating time of the propulsion system 3TH and increase the distance that spacecraft 3 can reach and the speed at which it can travel.●In this case, the silicon may be readily reactive powdered silicon 5M (silicon 5M that has been powdered to make it more readily reactive with oxygen; imagine a dust explosion of 5M, Figure 173TH-ROCKET) rather than bulk metallic silicon in order to facilitate the reaction with oxygen. Alternatively, the rocket may be propelled by the reaction of reacting liquefied oxygen 5OX with powdered 5M in the rocket's propulsion section (rocket, pressure chamber, nozzle) and releasing the heated 5MOX at the rear of the spacecraft. Alternatively, a light receiving unit 2 may be provided on the spacecraft, and the energy obtained from the light receiving unit 2 may be supplied to 5M, and 5M (or a propellant / solid propellant made from 5M) may be released at the rear of the spacecraft by laser ablation, plasma injection, or heated injection. <lp0008>●As shown in Figures 16 and 17, the launch object 2MS-OBJ may be made of silicon oxide 5MOX (or metal oxide 5MOX), a natural resource obtained from celestial bodies s...

Claims

1. A photon generator positioned in satellite orbit above a satellite or planet, A method for transmitting photons using a photon generator and a light-receiving unit in the air or atmosphere capable of receiving photons irradiated and emitted from the aforementioned photon generator, A method for transmitting photons, comprising steps and procedures of irradiating, emitting, relaying, transmitting, and transmitting photons from the photon generating unit to the light receiving unit, In the steps and procedures for irradiating, emitting, relaying, transmitting, and transmitting the aforementioned photons, When the aforementioned photons pass through, move, and propagate through the atmosphere, the molecules and atoms in the atmosphere along the path they pass through and propagate can be ionized or turned into plasma. Alternatively, A device using a photon transmission method that can reduce the resistance of the atmosphere when the photon passes through, moves, and propagates through the atmosphere, affecting the molecules and atoms in the atmosphere along the path through which the photon passes, moves, and propagates.

2. The device comprises multiple light-emitting units arranged in satellite orbit, and the light-receiving unit is capable of forming a focal point or a converged portion of photons emitted by the multiple light-emitting units.

3. The aforementioned laser beam has a propagation path that travels, crosses, and passes through the atmosphere, thunderclouds, and the vicinity of thunderclouds from the space side / air side towards the ground. By ionizing oxygen molecules, ozone, oxygen atoms, or nitrogen molecules, nitrogen atoms, or atmospheric molecules and atoms along the aforementioned propagation path, it is possible to form an electrically low-resistance low-resistance region by creating an ionized region or plasma region. A first region where charge is accumulated in the upper atmosphere and thunderclouds, or a first region where positive charge is accumulated, By forming the low-resistance region between or near the second region where charge is accumulated in the atmosphere and the lower layer of thunderclouds, or between the second region where negative charge is accumulated, The apparatus according to claim 2, which can reduce the insulating resistance between the first region and the second region, and induce charge induction, discharge, short circuit, and dielectric breakdown between the first region and the second region.

4. Using the aforementioned satellites, a satellite constellation is formed in a low Earth orbit. The apparatus according to claim 1, wherein a satellite in a satellite constellation is equipped with a light-emitting unit.

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