Power feeding device

Abstract

[Problem] To provide a power feeding device for collecting and supplying energy from the natural world. [Solution] A power feeding device 81 comprises: a power collection unit 811 having a first electrode 8112 that is formed from a conductor and is such that a distal-end part where the conductor is exposed is arranged underground or underwater in a body of water in contact with the Earth's crust, a second electrode 8113 that is formed from a conductor and is such that a distal-end part where the conductor is exposed is arranged in the atmosphere of the Earth, and an AC-DC conversion unit 8111 that converts an AC current inputted from the first electrode 8112 to a DC current; a superposition unit 812 that boosts the DC power outputted by the power collection unit 811 by serial connection; and a DC-AC conversion unit 813 that converts the DC power outputted by the superposition unit 812 to AC power.

Description

Power supply device

[0001] The present invention relates to a power supply device and an air defense system.

[0002] The reality is that wars never cease on Earth. In many wars, explosives are sent through the air into enemy territory and detonated to destroy enemy equipment and buildings. Many civilians who are not involved in the war become victims.

[0003] In this regard, Nikola Tesla (July 10, 1856 - January 7, 1943) once proposed using his own invention, the so-called Tesla coil, to destroy enemy missiles by irradiating them with an electron beam. Nikola Tesla apparently envisioned forming the beam using only one Tesla coil (see, for example, Non-Patent Document 1).

[0004] However, it is practically difficult to form a beam using only one Tesla coil.

[0005] One type of attack that is of concern in terms of defense is the so-called drone attack. This involves flying a large number of small suicide drones that approach and detonate near a target. In addition to attacks by projectiles, there are also concerns about attacks by guerrilla soldiers from the ground.

[0006] In this regard, development is underway on technology that irradiates drones with high-power microwaves to destroy the drone's body and control circuitry (for example, Non-Patent Document 2).

[0007] However, this technology cannot cope with extremely large numbers of drones or guerrilla attacks from the ground.

[0008] In outdoor areas where there are no power transmission facilities, or in areas where power supply from power transmission facilities is impossible due to disasters, etc., a power supply device independent of conventional power transmission facilities is required. Such power supply devices include internal combustion power supply devices that obtain power by burning gasoline or LPG, and power supply devices that use natural energy such as solar power.

[0009] However, in the case of an internal combustion engine power supply device, fuel must be continuously secured, and in the case of a power supply device that uses natural energy, it is easily affected by natural conditions such as weather.

[0010] In this regard, a device has been proposed in which two capacitors alternately charge each other, thereby permanently supplying power to the outside (for example, Non-Patent Document 3, p. 309, "Dr. Dorad's Free Energy Car").

[0011] However, this technology is suspected of being a so-called perpetual motion machine idea, and has not yet been widely put into practical use.

[0012] Aircraft vary in function, equipment, shape, etc. depending on their intended use. Recently, vertical take-off and landing aircraft such as the V-22 (commonly known as the Osprey; see, for example, Non-Patent Document 4) have been published for transport purposes and are primarily used for military purposes. Vertical landing aircraft that can be used as fighter jets, such as the F-35B (see, for example, Non-Patent Document 5), have also been published.

[0013] However, the V-22 is prone to instability when changing propeller direction, and the F-35B cannot take off vertically.

[0014] Furthermore, both aircraft have large components such as the main wings, which require a large space to store.

[0015] "The Tesla Files - Mysterious Top-Secret Research" (https: / / www.amazon.co.jp / %E3%82%B3%E3%83%AD%E3%83%A9%E3%83%89%E5%AE%9F%E9%A8%93 / dp / B09RK36KZT / ref=sr_1_1?__mk_ja_JP=%E3%82%AB%E3%82%BF%E3%82%AB%E3%83%8A&keywords=%E3%83%86%E3%82%B9%E3%83%A9%E3%83%95%E3%82%A1%E3%82%A4%E3%83%AB&qid=1705181624&s=inst ant-video&sr=1-1) “Ministry of Defense to Develop ‘High-Powered Microwave’ Weapon…to Neutralize Military Drones” (https: / / www.yomiuri.co.jp / national / 20220205-OYT1T50129 / ) “Nikola Tesla’s [Complete Technical] Manual,” by Nikola Tesla, translated by Kazumoto Iguchi, September 30, 2015, Hikaruland Co., Ltd. “MV-22 Osprey” https: / / www.mod.go.jp / j / approach / anpo / osprey / haibi / pdf / mv22_pamphlet.pdf “Reiwa 2 (2020) Defense White Paper <Commentary> Acquisition of F-35B Fighter Jets” https: / / www.mod.go.jp / j / publication / wp / wp2020 / html / nc007000.html

[0016] The problem to be solved by the present invention is to provide an air defense system that can efficiently destroy flying objects.

[0017] The problem to be solved by the present invention is to provide a shield barrier generating device that can effectively defend against attacks.

[0018] The problem to be solved by the present invention is to provide a power supply device that collects energy from nature and supplies it, and also to provide a wireless power transmission system that transmits power wirelessly.

[0019] The problem to be solved by the present invention is to provide a space-saving aerial vehicle.

[0020] It should be noted that the contents of the above "Background Art" and "Problem to be Solved by the Invention" indicate the opportunity (trigger) that led to the invention, and do not limit the technical scope of the invention, nor do they permit a limited interpretation of the technical scope of the invention (see Japan Patent Application No. 2005 (Gyo-Ke) No. 10042 and the Japan Patent Office Examination Guidelines as of the filing date, Part II, Chapter 2, Section 2, 3.2.1).

[0021] The present invention provides a power supply device comprising: a power collection unit having a first electrode formed of a conductor, the tip of which is exposed and placed underground or in water in a body of water in contact with the earth's crust; a second electrode formed of a conductor, the tip of which is exposed and placed in the earth's atmosphere; an AC-DC conversion unit that converts AC current input from the first electrode into DC current; a superposition unit that boosts the DC power output by the power collection unit by connecting it in series; and a DC-AC conversion unit that converts the DC power output by the superposition unit into AC power.

[0022] According to the present invention, it is possible to provide an air defense system that can efficiently destroy flying objects.

[0023] According to the present invention, it is possible to provide a shield barrier generating device that can effectively defend against attacks.

[0024] According to the present invention, it is possible to provide a power supply device that collects energy from nature and supplies it.

[0025] According to the present invention, a space-saving aerial vehicle can be provided.

[0026] 1. A block diagram showing the configuration of a phased array Tesla coil air defense system according to a first embodiment. A circuit diagram showing a Tesla coil. An exploded side view of a Tesla coil. A side view of a Tesla coil 41. A flowchart showing the operation of a main control unit. A block diagram showing the configuration of a phased array Tesla coil air defense system according to a second embodiment. A block diagram showing the configuration of a shield barrier generation device according to the first embodiment. A block diagram showing the configuration of a power supply device according to the first embodiment. An external view of an oscilloscope used for measurement. An external view of the oscilloscope during measurement. An enlarged view of the display of the oscilloscope in FIG. 10. A side external perspective view of an aerial vehicle. A view of an aerial vehicle as seen from an arrow A in FIG. 1. A view of an aerial vehicle as seen from an arrow B in FIG. 1. A plan view of an aerial vehicle with components removed. An end view of a receiving part as seen from an arrow C in FIG. 4. A perspective view showing a combat component. A view showing an example of a jet engine. A view showing an example of a jet engine with reverse thrust flaps open. A block diagram showing the configuration of a motion control device. A view showing an example of the data configuration of an attitude table. A view showing an example of the data configuration of an operation condition table. A view showing an example of the data configuration of a component control table. Fig. 1 is a block diagram showing a configuration of a power transmission system according to a first embodiment; Fig. 2 is a diagram showing changes in transmitted radio waves of the power transmission system; Fig. 3 is a block diagram showing a modified example of the power transmission system according to the first embodiment; Fig. 4 is a block diagram showing a configuration of a power transmission device that can be used in the power transmission system of the first embodiment; Fig. 5 is a block diagram showing a configuration of a direction conversion unit;

[0027] <<Phased Array Tesla Coil Air Defense System>> A phased array Tesla coil air defense system (hereinafter referred to as air defense system 1) according to one embodiment of the present invention will be described in detail below with reference to the drawings.

[0028] (First embodiment)

[0029] (System Configuration) Figure 1 is a block diagram showing the configuration of an air defense system 1 according to a first embodiment of the present invention. As shown in Figure 1, the air defense system 1 includes a power supply unit 11, a high-frequency signal generator 12, a gap switch 13, a capacitor 20, a coil-specific control unit 30, array Tesla coils 40 arranged in an array (two-dimensionally), a main control unit 19, a phase control unit 15, a combiner 17, and a signal processing unit 18.

[0030] The power supply unit 11 supplies AC power to a load housed therein. The power supply unit 11 may receive power from a power supply device 81 (described later) or may store the received power in a separate secondary battery.

[0031] The high-frequency signal generator 12 generates a high-frequency signal in the MHz to GHz range using power input from the power supply unit 11. The signal generation method may be, for example, a known method used in conventional phased array radar. Details of this technology are described, for example, in "Introduction to Radar Systems," by Merrill I. Skolnick (original author), translated by Masanori Ogura, Pleiades Publishing, July 25, 2023 (hereinafter referred to as Reference 1).

[0032] The output signal from the high frequency signal generator 12 is branched into two, one of which is output to the gap switch 13 and the other to each phase shifter 31 of the coil-specific control unit 30 via the first branch point 14 .

[0033] The gap switch 13 has two conductive ends, e.g., a sphere formed of conductive metal, which are arranged spaced apart in the atmosphere, and the output side is connected to the second connection point B (see Figure 2) of each Tesla coil 41 of the array Tesla coil 40 via the second branch point 16.

[0034] A capacitor 20 is provided on the input side of the gap switch 13 and the output side of the high frequency signal generator 12, with connection terminals connected to the input side of the gap switch 13 and the output side of the high frequency signal generator 12, respectively.

[0035] The coil-specific control unit 30 includes a phase shifter 31, an amplifier 32, a circulator 33, and a limiter 34.

[0036] The phase shifter 31 shifts the phase of the input high frequency signal by the phase shift amount set by the phase control device 15 and outputs the signal.

[0037] The amplifier 32 amplifies the high frequency signal input from the phase shifter 31 .

[0038] The circulator 33 outputs the input signal from the next output terminal in the clockwise direction. Therefore, the output signal from the amplifier 32 is input to the first connection point A (see FIG. 2) of each Tesla coil 41 of the array Tesla coil 40.

[0039] The circulator 33 also outputs the received signal input from the first connection point A of each Tesla coil 41 of the array Tesla coil 40 to the limiter 34 .

[0040] The limiter 34 filters out excessive power and frequencies that may be harmful to subsequent devices. The output signal from the limiter 34 is input to the combiner 17.

[0041] The combiner 17 combines the frequency signals from the limiters 34 of the individual coil control units 30 and outputs the combined signal to the signal processing device 18 .

[0042] The signal processing device 18 demodulates the combined received signal, converts it into a signal that can be processed by the main control unit 19, and outputs it to the main control unit 19.

[0043] The main control unit 19 can be a so-called computer equipped with an arithmetic unit, a storage unit, an input / output unit, etc. The main control unit 19 outputs a control signal to the high frequency signal generator 12 and a control signal to the phase control unit 15, and uses an input signal from the signal processing unit 18 to output an image to the input / output unit, as well as to perform vertical nose adjustment for the next attack posture.

[0044] The methods of forming, operating, and controlling the above-mentioned components can be known methods described in detail in the above-mentioned Reference 1.

[0045] (Tesla Coil) 1. Configuration of Tesla Coil Fig. 2 is a circuit diagram showing a Tesla coil 41. Fig. 3 is an exploded side view of the Tesla coil 41. Fig. 4 is a side view of the Tesla coil 41.

[0046] As shown in Figures 2 to 4, Tesla coil 41 includes a primary coil 41A having one end connected to first connection point A and the other end connected to gap switch 13 and secondary coil 41B via second connection point B, a secondary coil 41B having one end connected to gap switch 13 and secondary coil 41B and the other end connected to tertiary coil 41C, a tertiary coil 41C having one end connected to the other end of secondary coil 41B and the other end connected to spherical antenna 41E via lead delay 41D, a lead delay 41D having one end connected to the other end of tertiary coil 41C and the other end connected to spherical antenna 41E, and spherical antenna 41E connected to the other end of lead delay 41D.

[0047] The primary coil 41A, secondary coil 41B, tertiary coil 41C, lead delay 41D, spherical antenna 41E, and the connecting wires connecting these, which are the current-carrying parts of Tesla coil 41, can be made of a conductive metal such as copper or gold, or an alloy thereof. Each wire used in primary coil 41A, secondary coil 41B, tertiary coil 41C, and lead delay 41D is insulated.

[0048] The primary coil 41A, secondary coil 41B, tertiary coil 41C, lead delay 41D, spherical antenna 41E, and the connecting wires connecting these may be made of a superconducting material, such as a rare earth high-temperature superconducting wire, in addition to a commonly used conductive material.

[0049] Examples of rare earth high-temperature superconducting materials that can be used include HgBaCaCuO, TlBaCaCuO, BiSrCaCuO, and YBaCuO. Rare earth high-temperature superconducting materials exhibit a superconducting state even when cooled with liquid nitrogen. Conventional superconducting materials, such as MgB2 and Nb3Sn, can also be used. Conventional superconducting materials exhibit a superconducting state when cooled with liquid helium. These wires can be publicly known and are already commercially available from, for example, Fujikura Ltd.

[0050] As shown in Figures 3 and 4, it is desirable that the height L4H of the primary coil 41A, the height L3H of the secondary coil 41B, and the height L2H of the tertiary coil 41C be approximately the same length as the diameter of the spherical antenna 41E from the standpoint of efficiency, but they may be different from each other.

[0051] The primary coil 41A, secondary coil 41B, and tertiary coil 41C are cylindrical. The diameter L4D of the primary coil 41A is larger than the diameter L3D of the secondary coil 41B and is smaller than the size at which electromagnetic induction does not occur between them. The diameter L3D of the secondary coil 41B is larger than the diameter L2D of the tertiary coil 41C and is smaller than the size at which electromagnetic induction does not occur between them. The diameter L2D of the tertiary coil 41C is larger than the diameter of the horizontal cross section of the lead delay 41D in a plan view.

[0052] The height of the lead delay 41D is higher by a height H1 than the height L4H of the primary coil 41A, the height L3H of the secondary coil 41B, and the height L2H of the tertiary coil 41C. Therefore, the entire spherical antenna 41E is exposed outside the primary coil 41A, the secondary coil 41B, and the tertiary coil 41C.

[0053] The number of turns of the tertiary coil 41C is greater than the number of turns of the secondary coil 41B. For example, the number of turns of the tertiary coil 41C can be 10 to 100 times greater than the number of turns of the secondary coil 41B.

[0054] The number of turns of the secondary coil 41B is greater than the number of turns of the primary coil 41A. For example, the number of turns of the secondary coil 41B can be 10 to 100 times greater than the number of turns of the primary coil 41A.

[0055] The number of turns of the primary coil 41A may be, for example, one turn.

[0056] As shown in FIG. 4, when the primary coil 41A, secondary coil 41B, tertiary coil 41C, lead delay 41D, spherical antenna 41E, and the connecting wires connecting these are formed using superconducting materials, a cooling machine 50 is installed to accommodate all of these components.

[0057] 4, the cooling device 50 accommodates the primary coil 41A, secondary coil 41B, tertiary coil 41C, lead delay 41D, all of the connecting wires connecting these, and at least the upper half of the spherical antenna 41E. The cooling device 50 includes an inlet 51 for introducing liquid coolant into the cooling device 50, and a pressure valve 52 for releasing the vaporized liquid coolant.

[0058] The liquid coolant may be a liquid that can cool the superconducting material to a low temperature to the point where it becomes superconducting, such as liquid helium or liquid nitrogen.

[0059] 2. Operation of Tesla Coil The Tesla coil 41 uses electromagnetic induction to input a high-frequency signal to the primary coil 41A, which is then boosted using the secondary coil 41B and tertiary coil 41C to make the frequency higher.

[0060] Incidentally, the gap switch 13 and the capacitor 20 are connected to the Tesla coil 41, and their operation is as follows.

[0061] The core of the Earth's crust contains iron (Fe). In other words, the Earth can be said to be a sphere of conductive iron. The Earth rotates on its axis while revolving around the Sun, which has a magnetic field that changes frequently due to geomagnetic storms.

[0062] When the Earth, a sphere of iron, moves through this magnetic field, an induced current is generated inside the Earth, which is covered by an insulator and an atmosphere that has capacitance.

[0063] In other words, the Earth acts like a large capacitor, with current flowing through the crust and capacitance stored in the atmosphere.

[0064] Nikola Tesla discovered these electrical currents in the Earth's crust and called them standing waves.

[0065] When the input power to the capacitor 20 reaches its capacity, the capacitor 20 discharges in the direction of the gap switch 13 .

[0066] This discharge ionizes the air between the two conductor ends, causing the gap switch 13 to become electrically conductive.

[0067] At this time, a part of the electrostatic capacitance of the atmosphere flows into the Tesla coil 41 via the gap switch 13 .

[0068] Therefore, since the Tesla coil 41 also receives power from the gap switch 13, it is possible to discharge a spark that is much larger than the power supplied from the power supply unit 11.

[0069] (Beam Output) The air defense system 1 of this embodiment irradiates a beam spark in a desired direction using a method similar to the method of generating a beam transmission signal of a phased array radar.

[0070] Regarding beamforming methods, detailed examples are described in, for example, Reference 1, and these known methods can be used.

[0071] (Acquisition of Beam Irradiation Target) The air defense system 1 of this embodiment identifies the position of the beam irradiation target using a method similar to the target acquisition method of a phased array radar.

[0072] Regarding target acquisition methods for phased array radar, detailed examples are described in, for example, Reference 1, and these known methods can be used.

[0073] (Method of Destroying Equipment of an Object to be Destroyed) A flying object carrying explosives is usually equipped with an explosive device that destroys the flying object itself in order to prevent accidental detonation within the country.

[0074] If the projectile deviates from the desired launch, a signal is sent to the projectile, causing it to explode.

[0075] An antenna is required to receive this signal. This antenna has a length that is an integer multiple of λ / 4, where λ is the frequency of the high-frequency signal used in the internal circuit. This antenna receives the high-frequency signal with frequency λ and reflects other frequencies.

[0076] Therefore, if a spark is emitted at this frequency λ, a powerful electric power is input from the antenna, and the flying object can be destroyed effectively.

[0077] Figure 5 is a flowchart showing the operation of the main control unit 19 of the air defense system 1. As shown in Figure 5, in step S101, the main control unit 19 instructs the high-frequency signal generator 12 to sweep the frequency. The sweep range is within the frequency band used for normal communications.

[0078] In step S102, the main control unit 19 monitors the strength of the received signal for each sweep frequency, and detects a reflection gap frequency at which the strength of the received signal becomes lower than that of other frequencies.

[0079] In step S103, the main control unit 19 sets the reflection gap frequency to the output frequency of the spark.

[0080] In step S104, the main control unit 19 tracks the object to be destroyed using a reflection frequency that is a frequency other than the reflection gap frequency.

[0081] In step S105, the main control unit 19 determines whether a firing command has been issued. If the main control unit 19 determines that a firing command has been issued (Y in step S105), the process proceeds to step S106, and if the main control unit 19 does not determine that a firing command has been issued (N in step S105), the process returns to step S105.

[0082] In step S105, main control unit 19 causes phase control device 15 to calculate the phase for generating a beam in the spark irradiation direction and causes phase shifter 31 of each coil-specific control unit 30 to transmit the phase change amount. Then, main control unit 19 instructs high-frequency signal generator 12 to output a high-power high-frequency signal at the reflection gap frequency.

[0083] The generated high-power high-frequency signal at the reflected gap frequency is input to each Tesla coil 41 with its phase adjusted via the coil-specific control unit 30, and the gap switch 13 is turned ON (energized state) by the discharge of the capacitor 20, and the power stored in the atmosphere flows in from the gap switch 13.

[0084] The Tesla coil 41 then irradiates the phase-adjusted sparks in a beam onto the target, destroying the target.

[0085] As described above, the air defense system 1 of this embodiment comprises a power supply unit 11 that supplies AC power, a high frequency signal generator 12 that generates a high frequency signal using the power supplied from the power supply unit 11, a gap switch 13 that is connected to one of a pair of output terminals from the high frequency signal generator 12 and has two conductor ends spaced apart in the atmosphere, a capacitor 20 that is connected to both of the pair of output terminals from the high frequency signal generator 12, a coil-specific control unit 30 that has a phase shifter 31 that changes the phase of the high frequency signal generated by the high frequency signal generator 12 by a specified amount, and a primary coil 41A, a secondary coil 41B, and a tertiary coil 41C that have increasing numbers of turns in the order of primary coil 41A, secondary coil 41B, and tertiary coil 41C. The device comprises: an array Tesla coil 40 in which a plurality of Tesla coils 41 are arranged in an array, which is a two-dimensional arrangement method, in which a force is input to a first connection point A which is one end of a primary coil 41A, an output from a gap switch 13 is input to a second connection point B which is the connection between the primary coil 41A and the secondary coil 41B, and a spherical spherical antenna 41E is connected to the output side end of a tertiary coil 41C via a rod-shaped lead delay 41D; a phase control device 15 which generates for each Tesla coil 41 the amount of phase change required to form a beam in a desired direction and outputs it to the corresponding phase shifter 31; and a main control unit 19 which generates and outputs a control signal for a high-frequency signal generator 12 and a control signal for the phase control device 15.

[0086] Therefore, the present invention has the effect of providing an air defense system that can efficiently destroy flying objects.

[0087] Second Embodiment Fig. 6 is a block diagram showing the configuration of an air defense system 1 according to a second embodiment. Only the differences from the first embodiment will be explained below.

[0088] In this embodiment, a phase shifter 31A is further provided at the downstream of the second branch point 16 between the output side of the gap switch 13 and the input terminal to the second connection point B of each Tesla coil 41. The phase shifter 31A receives the phase change amount instructed to the phase shifter 31 from the phase control device 15 and changes the phase of the high-frequency signal input from the gap switch 13 based on the instructed phase change amount.

[0089] Therefore, according to the air defense system 1 of the second embodiment of the present invention, the input signal from the gap switch 13 can also be aligned in phase, which has the effect of enabling more efficient destruction of targets.

[0090] <<Shield Barrier Generating Device>> A shield barrier generating device (hereinafter referred to as a barrier generating device 71) capable of effectively defending against attacks according to one embodiment of the present invention will be described in detail below with reference to the drawings.

[0091] (First embodiment) (Basic concept) Frequency f １ and frequency f ２ When these electromagnetic waves are synthesized and irradiated in the same direction, the least common multiple of these frequencies is the frequency f Ｌ As the electromagnetic waves travel a wavelength λ, which corresponds to the wavelength λ, the amplitude increases as the waves overlap.

[0092] In the barrier generating device 71 of this embodiment, a fundamental frequency f selected from prime numbers is used. ０ The product of the combination of prime numbers P Ｃ The frequency f obtained by multiplying ｐ at frequency f ｐ１ to frequency f ｐｎ These are then phase-aligned and synthesized, and the synthesized wave is irradiated.

[0093] Then, f ｐ１ From f ｐｎ The frequency f is the least common multiple of the n frequencies ＰＬ The wavelength λ corresponds to Ｐ As it travels, the electromagnetic waves overlap and their amplitude increases.

[0094] λ Ｐ If λ is set at a certain distance from the irradiation device, Ｐ The energy is relatively small just before λ Ｐ At the position, the energy is f ｐ It becomes n times.

[0095] Therefore, λ Ｐ It can generate a shield barrier at a location, a curtain of high-energy electromagnetic waves that blocks enemy attacks and intrusions.

[0096] (Configuration example) Fig. 7 is a block diagram showing the configuration of a barrier generation device 71 of this embodiment. As shown in Fig. 7, the barrier generation device 71 includes a frequency-specific electromagnetic wave generation unit 711, a phase control unit 712, a combiner 713, an amplifier 714, and an antenna 715. The barrier generation device 71 may also include a power supply unit that supplies power received from a power feeding device 81 (described later) to a load housed inside, or may include a secondary battery separately provided to store the received power.

[0097] The frequency-specific electromagnetic wave generation unit 711 includes an electromagnetic wave generation unit 7111 and a phase shifter 7112. The frequency-specific electromagnetic wave generation unit 711 is provided in n units (n is an integer), namely, frequency-specific electromagnetic wave generation unit 711-1 to frequency-specific electromagnetic wave generation unit 711-n, for each frequency to be generated.

[0098] The first electromagnetic wave generating unit 7111-1, which is one of the electromagnetic wave generating units 7111, generates a frequency f Ｐ The frequency f Ｐ１ generates electromagnetic waves.

[0099] frequency f Ｐ１ is the fundamental frequency f selected from prime numbers ０ P is a combination of prime numbers Ｃ is the frequency obtained by multiplying

[0100] Fundamental frequency f selected from prime numbers ０ For example, the prime number 1 is selected from prime numbers greater than 3000, and specifically, 3011 can be selected.

[0101] Product P of combinations of prime numbers Ｃ For example, a combination of prime numbers selected from relatively small prime numbers can be used, and specifically, a product of a combination of prime numbers such as 1, 5, 7, and 11 can be selected.

[0102] When the above prime numbers are selected, the product P of the combination of prime numbers Ｃ For example, one of the following is selected: 1 1 x 5 = 5 1 x 7 = 7 : 1 x 5 x 7 = 35 : 1 x 5 x 7 x 11 = 385

[0103] The product P of this combination of prime numbers Ｃ Number of C Ｓ is 15 as shown in (1) below.

[0104] Therefore, in the above case, n = C Ｓ =15.

[0105] And the fundamental frequency f ０ is 3011, the product P of the combination of the above prime numbers Ｃ The frequency f obtained by multiplying ｐ f ｐ１ From f ｐ１５ 15 pieces, then f ｐ１ From f ｐ１５ The frequency f is the least common multiple of the 15 frequencies ＰＬ is 1,159,235.

[0106] In this case, the least common multiple frequency f ＰＬ The wavelength λ corresponds to Ｐ is expressed by the following equation (2) as λ Ｐ Solving for λ Ｐ = 258.791362 m.

[0107] However, C is the speed of light in a vacuum, and in the above calculation, the speed of electromagnetic waves in the atmosphere is high, C = 3 × 10 ８ The calculation is made by approximating m.

[0108] Therefore, under the above conditions, λ Ｐ Just before λ = 258.791362m, the energy is relatively small, but Ｐ At the position, the energy is f ｐA shield barrier 15 times larger than the original is generated.

[0109] The phase control section 712 adjusts the phase and changes the position of the adjusted phase. The phase control section 712 adjusts λ by periodically changing the position of the adjusted phase. Ｐ The thickness of the barrier at this position can be adjusted in the direction of travel.

[0110] The phase shifter 7112 aligns the phase of the electromagnetic wave generating unit 7111 in accordance with the control signal from the phase control unit 712 .

[0111] The combiner 713 combines the electromagnetic waves input from the n frequency-specific electromagnetic wave generators 711, namely, the frequency-specific electromagnetic wave generators 711-1 to 711-n.

[0112] The amplifier 714 amplifies the electromagnetic wave output from the combiner 713 .

[0113] The antenna 715 irradiates the electromagnetic waves amplified by the amplifier 714 into the air.

[0114] As described above, the barrier generating device 71 of this embodiment generates a fundamental frequency f ０ The product of the combination of prime numbers P Ｃ The frequency f obtained by multiplying ｐ Among these, frequency f ｐ１ to frequency f ｐｎ n electromagnetic waves (n is an integer) of frequency f ｐ The electromagnetic wave generating device 710 includes a frequency-specific electromagnetic wave generating unit 711 that generates n electromagnetic waves for each frequency, a combiner 713 that combines the n electromagnetic waves input from the frequency-specific electromagnetic wave generating unit 711, an amplifier 714 that amplifies the electromagnetic waves output from the combiner 713, and an antenna 715 that irradiates the electromagnetic waves amplified by the amplifier 714 into the air.

[0115] Therefore, according to the present invention, it is possible to provide a shield barrier generating device that can effectively defend against attacks.

[0116] Second Embodiment (Basic Concept) In the barrier generating device 71 of this embodiment, the basic angular velocity ω is selected from prime numbers. ０ The product of the combination of prime numbers P ＣAngular velocity ω obtained by multiplying ｐ Circularly polarized electromagnetic wave f ｐ Let ω be the angular velocity ｐ１ Circularly polarized electromagnetic wave f ｐ１ from angular velocity ω ｐｎ Circularly polarized electromagnetic wave f ｐｎ These are then phase-aligned and synthesized, and the synthesized wave is irradiated.

[0117] Then, ω ｐ１ From ω ｐｎ The least common multiple ω of the n frequencies ＰＬ The angle θ corresponding to Ｐ As it travels, the electromagnetic waves overlap and their amplitude increases.

[0118] Angle θ Ｐ If it is set to occur at a certain distance Z from the irradiation device, the energy is relatively small just before Z from the irradiation device, but at the position Z, the energy is f ｐ It becomes n times.

[0119] Therefore, a shield barrier, a curtain of high-energy electromagnetic waves that blocks enemy attacks and intrusions, can be generated at the Z position.

[0120] (Configuration Example) The configuration example of this embodiment differs from the configuration example of the first embodiment only in the electromagnetic wave generating unit 7111. Therefore, only the electromagnetic wave generating unit 7111 will be described below, and descriptions of the other components will be omitted.

[0121] Base angular velocity ω selected from prime numbers ０ is, for example, 3 radians. The combination of prime numbers is the prime numbers listed in the first embodiment.

[0122] Product P of combinations of prime numbers Ｃ is the product P of the combination of prime numbers in the first embodiment Ｃ Therefore, the angular velocity ω ｐ１ Circularly polarized electromagnetic wave f ｐ１ from angular velocity ω ｐｎ Circularly polarized electromagnetic wave f ｐｎ n circularly polarized electromagnetic waves f ｐ The amplitude of the composite wave is maximum when θ = 3 × 385 = 1,155 (radians).

[0123] Therefore, Z can be obtained by substituting θ = 3 × 385 = 1,155 (radians) into the following equation (3) and solving for Z.

[0124] However, β ０ is a phase constant, and t is time, which can be set arbitrarily.

[0125] In the above conditions, the energy is relatively small just before the distance Z from the irradiation device, but at the position of the distance Z, the energy is f ｐ A shield barrier 15 times larger than the original is generated.

[0126] As described above, the barrier generating device 71 of this embodiment uses a basic angular velocity ω ０ The product of the combination of prime numbers P Ｃ Angular velocity ω obtained by multiplying ｐ Circularly polarized electromagnetic wave f ｐ Of which, angular velocity ω ｐ１ Circularly polarized electromagnetic wave f ｐ１ from angular velocity ω ｐｎ Circularly polarized electromagnetic wave f ｐｎ n electromagnetic waves (n is an integer) of frequency f ｐ The electromagnetic wave generating device 710 includes a frequency-specific electromagnetic wave generating unit 711 that generates n electromagnetic waves for each frequency, a combiner 713 that combines the n electromagnetic waves input from the frequency-specific electromagnetic wave generating unit 711, an amplifier 714 that amplifies the electromagnetic waves output from the combiner 713, and an antenna 715 that irradiates the electromagnetic waves amplified by the amplifier 714 into the air.

[0127] Therefore, according to the present invention, it is possible to provide a shield barrier generating device that can effectively defend against attacks.

[0128] (Third embodiment) (Basic concept) Each frequency in the first embodiment and the second embodiment are improved and applied. That is, the frequency f ｐ１ to frequency f ｐｎ n electromagnetic waves (n is an integer) of frequency f ｐ and a frequency-specific electromagnetic wave generating unit 711 that generates a base angular velocity ω for the angular velocity selected from the prime numbers of the second embodiment. ０ The product of prime numbers P Ｃ Angular velocity ω obtained by multiplyingｐ Circularly polarized electromagnetic wave f ｐ Of which, angular velocity ω ｐ１ Circularly polarized electromagnetic wave f ｐ１ from angular velocity ω ｐｎ Circularly polarized electromagnetic wave f ｐｎ n electromagnetic waves (n is an integer) of frequency f ｐ and a frequency-specific electromagnetic wave generating unit 711 that generates electromagnetic waves for each λ Ｐ ω so that =Z ＰＬ and t are selected.

[0129] Then, the distance λ Ｐ At position Z, the energy is f ｐ A shield barrier that is 15 x 15 = 225 times the original amount is generated.

[0130] As described above, the barrier generating device 71 of this embodiment generates a fundamental frequency f ０ The product of prime numbers P Ｃ The frequency f obtained by multiplying ｐ Among these, frequency f ｐ１ to frequency f ｐｎ n (n is an integer) electromagnetic waves, and a base angular velocity ω of the angular velocity selected from prime numbers. ０ The product of prime numbers P Ｃ Angular velocity ω obtained by multiplying ｐ Circularly polarized electromagnetic wave f ｐ Of which, angular velocity ω ｐ１ Circularly polarized electromagnetic wave f ｐ１ from angular velocity ω ｐｎ Circularly polarized electromagnetic wave f ｐｎ n electromagnetic waves (n is an integer) of frequency f ｐ The electromagnetic wave generating device 710 includes a frequency-specific electromagnetic wave generating unit 711 that generates n electromagnetic waves for each frequency, a combiner 713 that combines the n electromagnetic waves input from the frequency-specific electromagnetic wave generating unit 711, an amplifier 714 that amplifies the electromagnetic waves output from the combiner 713, and an antenna 715 that irradiates the electromagnetic waves amplified by the amplifier 714 into the air.

[0131] Therefore, according to the present invention, it is possible to provide a shield barrier generating device that can more effectively defend against attacks.

[0132] <<Power Supply Device>> A power supply device 81 according to one embodiment of the present invention will be described in detail below with reference to the drawings.

[0133] (Earth's Crustal Power) Nikola Tesla (1856-1943) discovered that electric power exists in the form of waves inside the Earth. However, while Nikola Tesla seems to have tried to obtain electric power from these standing waves, he recalls that it was difficult to harness this electrical energy. Furthermore, it has traditionally been thought that the electric power inside the Earth (hereinafter referred to as "earth's crustal power" in this specification, to avoid confusion with so-called standing waves) is so weak that harnessing this power is impractical.

[0134] Therefore, we actually measured the electric power in the Earth's crust. Figure 9 shows the appearance of the oscilloscope used for the measurements. As shown in Figure 9, when both tips of the two probes are placed in the atmosphere, no electric power is observed. Also, when both tips of the two probes are buried underground, no electric power is observed.

[0135] Figure 10 is an external view of the oscilloscope during measurement. Figure 11 is an enlarged view of the display of the oscilloscope shown in Figure 10. As shown in Figure 10, the measurement involved burying the tip of one of the two probes, the red probe (detection probe, A in Figure 10), in the ground, and placing the tip of the other probe, the black probe (grounding probe, B in Figure 10), in the air. As shown in Figure 11 (see particularly the white box indicated by the arrow), the measured values ​​were an average frequency (F) of 59.83 kHz and an average amplitude voltage (V) of -18.87 mV. Additionally, the presence of multiple AC powers with different phases was observed. Note that when the tip of the black probe was buried in the ground and the tip of the red probe was placed in the air, no power was observed. Therefore, it is possible to extract power from the ground, i.e., from the earth's crust, and the power observed above is not power from atmospheric radio waves or the like.

[0136] The oscilloscope used for the observations was a HANMATEK model HO52S. Measurements were taken with this oscilloscope in auto mode after waveform correction with the average value calculation option turned on. The measurement date was September 22, 2024, with an air temperature of 19°C and cloudy weather after rain. The measurement location was Miyamori-cho, Tono City, Iwate Prefecture. The above observations were made after autocalibration with both probe tips placed in the atmosphere. Therefore, the above average amplitude voltage is the potential difference from the potential when both probe tips are placed in the atmosphere.

[0137] 9 is a block diagram showing the configuration of a power supply device 81 according to this embodiment. As shown in FIG. 9, the power supply device 81 includes a power collection unit 811, a superposition unit 812, a DC / AC conversion unit 813, and a voltage adjustment unit 814.

[0138] The power collection unit 811 includes an AC-DC conversion unit 8111. The AC-DC conversion unit 8111 includes a so-called rectifier that converts AC current into DC current, and may further include a smoothing circuit that smooths the voltage waveform of the DC current. Examples of the rectifier circuit and the smoothing circuit can be appropriately combined and used from known circuits published in books, websites, etc.

[0139] The AC-DC converter 8111 includes a first electrode 8112, which is one of the electrodes, and a second electrode 8113, which is the other electrode. The first electrode 8112 is formed of a conductor, and the tip where the conductor is exposed is placed underground or underwater in a body of water that is in contact with the Earth's crust (hereinafter, the ocean and the water in lakes and rivers are collectively referred to as "seawater"). This first electrode 8112 collects power from within the Earth's crust. The second electrode 8113 is also formed of a conductor, and the tip where the conductor is exposed is placed in the Earth's atmosphere. The AC power of the collected intracrustal power input from the first electrode 8112 is input to the AC-DC converter 8111.

[0140] The power collection unit 811 can receive one or more power depending on the power required by the load 82. The number of power collection units 811 may be one when the power required by the load 82 is relatively small or when the power collection efficiency of the power collection unit 811 is good. When there is only one power collection unit 811, the superposition unit 812 does not need to be provided.

[0141] The power collection efficiency of the power collection unit 811 can be improved by using materials with extremely low electrical resistance, such as superconducting wire, for the wiring of the power collection unit 811 and the AC / DC conversion unit 8111, and the wires used in each electrode, or by selecting a geographical location where particularly high power can be collected.

[0142] A plurality of power collection units 811 are provided when the load 82 requires a relatively large amount of power or when the power collection efficiency of the power collection units 811 is not very good. When a plurality of power collection units 811 are provided, a superposition unit 812 is provided.

[0143] The superimposing unit 812 increases the current and voltage by serially connecting the DC power output from the multiple power collecting units 811. The superimposing unit 812 regards one power collecting unit 811 as a DC power source and increases the current and voltage by connecting the positive or negative pole of this DC power source to the negative or positive pole of another power collecting unit 811.

[0144] The DC-AC converter 813 receives the output from the superimposing unit 812 when the superimposing unit 812 is provided, or receives the output from the power collecting unit 811 when the superimposing unit 812 is not provided. The DC-AC converter 813 includes a so-called inverter that converts DC current into AC current. The DC-AC converter 813 can be made by appropriately combining known circuits published in books, websites, etc.

[0145] The voltage adjustment unit 814 is provided when the output voltage of the DC / AC conversion unit 813 differs from the voltage required by the load 82. The specific configuration of the voltage adjustment unit 814 can be an appropriate combination of known circuits published in books, websites, etc. Alternatively, a commercially available transformer, particularly a transformer with a stabilizing device, can also be used.

[0146] Here, the operation of the power supply device 81 of this embodiment will be described. As shown in FIG. 11 , the intracrustal power collected from the first electrode 8112 and the second electrode 8113 is AC power, but this intracrustal power contains multiple AC powers with different phases. Aligning these AC powers in phase is difficult, if not impossible. Therefore, the collected intracrustal power is first converted to DC power, the phase of which is not an issue, by the AC-DC converter 8111 of the power collection unit 811. The DC power output from each power collection unit 811 is then superimposed by connecting each power collection unit 811 in series as if it were a DC power source, thereby increasing the voltage and current. This DC power is then converted to AC power by the DC-AC converter 813, and the voltage is adjusted by the voltage adjustment unit 814 according to the load 82, and the power is supplied to the load 82.

[0147] For example, in the case of the above observation results where the average frequency (F) is 59.83 kHz and the average amplitude voltage (V) is -18.87 mV, approximately 2,800 power collection units 811 are provided and connected in series. This makes it possible to obtain practical power. Because the configuration of the power collection units 811 is simple, approximately 100 units can be placed on one circuit board. This means that 28 of these circuit boards will be required.

[0148] In addition, the first electrode 8112 and the second electrode 8113 can be bundled together by bundling or connecting them together. By configuring in this way, the power supply device 81 can be made small and light enough to be carried by a person.

[0149] As described above, the power supply device 81 of this embodiment comprises a first electrode 8112 formed from a conductor and having its exposed tip placed underground or in water in a body of water in contact with the earth's crust, a second electrode 8113 formed from a conductor and having its exposed tip placed in the earth's atmosphere, a power collection unit 811 having an AC-DC conversion unit 8111 that converts the AC current input from the first electrode 8112 into DC current, a superposition unit 812 that boosts the DC power output by the power collection unit 811 by connecting them in series, and a DC-AC conversion unit 813 that converts the DC power output by the superposition unit 812 into AC power.

[0150] In addition, the power supply device 81 of this embodiment includes a first electrode 8112 formed of a conductor and having its exposed tip placed underground or in water in a body of water in contact with the earth's crust, a second electrode 8113 formed of a conductor and having its exposed tip placed in the earth's atmosphere, a power collection unit 811 having an AC-DC conversion unit 8111 that converts AC current input from the first electrode 8112 into DC current, and a DC-AC conversion unit 813 that converts DC power output by the power collection unit 811 into AC power.

[0151] Therefore, according to the present invention, it is possible to provide a power supply device 81 that collects energy from the natural world and supplies it.

[0152] <<Unmanned Aerial Vehicle and Aerial Carrier>> An unmanned aerial vehicle 91 (hereinafter referred to as the aerial vehicle 91) according to one embodiment of the present invention will be described in detail below with reference to the drawings.

[0153] (Basic concept) Conventional aircraft have large wings, which require a large storage space. Furthermore, models capable of vertical takeoff and landing mainly generate lift and thrust using propellers or fans. As a result, some models have a low travel speed and are prone to accidents due to unstable aircraft attitude. Furthermore, fighter aircraft in particular not only require time and money for pilot training, but sudden changes in attitude can be harmful to the pilot's body.

[0154] (Regarding the Main Wings) The aerial vehicle 91 of this embodiment does not generate lift using main wings, but is equipped with a power source for generating lift (hereinafter referred to as a lift engine 921). Specifically, the aerial vehicle 91 is equipped with a jet engine, which is a power source that takes in oxygen necessary for burning fuel from the atmosphere, or a rocket engine, which is a power source that loads the oxygen or oxidizer necessary for burning fuel into the aircraft and mixes and burns this oxygen or oxidizer with fuel.

[0155] Therefore, the aerial vehicle 91 does not have a main wing that generates a lift force greater than the lift force generated by the lift engine, and therefore the aerial vehicle 91 requires less space for storage.

[0156] The airborne vehicle 91 also uses a jet engine or rocket engine as a power source (hereinafter referred to as a propulsion engine 922) that generates power to move the aircraft in the forward and backward directions, and is provided in addition to the lift engine.

[0157] Therefore, not only is vertical takeoff and landing possible, but it is also possible to take off rapidly and travel at high speeds, such as the speed of sound.

[0158] (Regarding the Pilot) The aerial vehicle 91 can be operated unmanned by the motion control device 940. The motion control device 940 pre-stores the operations of the lift engine and the propulsion engine 922 required for the operation corresponding to the specified operation command, reads out these operations, and controls the operation of the lift engine and the propulsion engine 922, including the reverse thrust flap 9211.

[0159] Therefore, there is no need for a pilot to be on board the aircraft, which saves time and money associated with pilot training.

[0160] Furthermore, because the aerial vehicle 91 does not have a pilot on board, it is capable of rapid and complex attitude changes, such as rapid somersaults, that would be impossible with a human on board. Therefore, during a dogfight between fighter planes, the aerial vehicle 91 can assume a position and attitude that is extremely advantageous over enemy fighter planes piloted by humans, making it possible to effectively eliminate the enemy fighter planes.

[0161] (Regarding componentization of aircraft elements) The airborne vehicle 91 componentsize the aircraft elements, which are functional parts mounted on the fuselage section, etc., and is equipped with detachable members that allow the components of these aircraft elements (hereinafter simply referred to as components) to be easily replaced.

[0162] Therefore, by replacing these components, the air vehicle 91 can be converted into a vehicle with the functions required for its mission, such as a transport plane or a fighter plane, etc. This eliminates the need to carry both a transport plane and a fighter plane on an aircraft carrier, for example, and further saves space.

[0163] (Configuration Example) Figure 12 is a perspective view of the side exterior of the aerial vehicle 91 of this embodiment. Figure 13 is a view of the aerial vehicle 91 as seen from the arrow A in Figure 12. Figure 14 is a view of the aerial vehicle 91 as seen from the arrow B in Figure 12. Note that, hereinafter, as indicated by arrow X1 in Figure 12, the direction of the air intake port of the propulsion engine 922 (hereinafter, the right propulsion engine 922R and the left propulsion engine 922L will be collectively referred to as the propulsion engines 922) will be referred to as the front, and the direction of the exhaust gas outflow will be referred to as the rear. Below, an example will be described in which jet engines are used for the lift engines 921 and the propulsion engines 922 of the aerial vehicle 91.

[0164] The aerial vehicle 91 may also be equipped with a power supply unit that supplies power received from a power supply device 81 (described later) to a load housed therein, or may be provided with a separate secondary battery to store the received power. In this case, the aerial vehicle 91 can receive power from the power supply device 81 installed on the ground and store the received power in a secondary battery provided inside the aerial vehicle 91. Furthermore, the aerial vehicle 91 may also have the above-mentioned barrier generation device 71. The barrier generation device 71 can be supplied with power stored from the above-mentioned secondary battery. Similarly, the aerial carrier (described later) may also have the above-mentioned barrier generation device 71.

[0165] As shown in Figures 12 to 14, the aerial vehicle 91 includes a main body 910 and a transport component 931T, which is a component 931 for transportation as an example of a component 931.

[0166] The main aircraft body 910 comprises an equipment storage section 911, lift engines 921 (hereinafter, the front right engine 921FR, front left engine 921FL, rear right engine 921RR, and rear left engine 921RL are collectively referred to as the lift engines 921), and propulsion engines 922.

[0167] The device storage section 911 stores the motion control device 940 in the front end portion of the main body 910 .

[0168] Jet engines or rocket engines are used as the lift engines 921. The lift engines 921 include a front right engine 921FR installed on the front right side of the main body 910, a front left engine 921FL installed on the front left side of the main body 910, a rear right engine 921RR installed on the rear right side of the main body 910, and a rear left engine 921RL installed on the rear left side of the main body 910.

[0169] The lift engine 921 is installed with its air intake facing upward and its exhaust gas outlet facing downward. The lift engine 921 is attached to the main body 910 via a mounting member 913, but may also be attached directly to the main body 910.

[0170] The transport component 931T is provided with a hatch 931T1 on the side portion of the transport component 931T for loading and unloading items.

[0171] 14, the main body 910 has a support frame 9110 with wheels 9111 that can be stored inside the main body 910. When in use, the support frame 9110 opens in the direction of arrow X2.

[0172] 15 is a plan view of the aerial vehicle 91 from which the component 931 has been removed. As shown in FIG. 15, the aerial vehicle 91 includes a crosspiece 9121, a receiving portion 9122, and a lock 9123.

[0173] The crosspiece 9121 connects and supports the front part of the main body 910, which includes the equipment storage section 911, the front right engine 921FR, and the front left engine 922FL, and the rear part of the main body 910, which includes the rear right engine 921RR, the rear left engine 921RL, and the propulsion engine 922.

[0174] A plurality of receiving portions 9122 are hung above the crosspiece 9121 so as to intersect perpendicularly with the extending direction of the crosspiece 9121 .

[0175] Multiple locks 9123 are arranged on the surfaces facing the component 931 at the front and rear parts of the main body 910, and are inserted into insertion holes provided in advance in the component 931 to secure the component 931 to the main body 910.

[0176] The lock 9123 is protruded or retracted by the solenoid, and when the power to the solenoid is OFF, it protrudes and secures the component 931 to the main body 910, and when the power to the solenoid is ON, it is retracted and allows the component 931 to be removed from the main body 910.

[0177] Fig. 16 is an end view of the receiving portion 9122 as seen from the arrow C in Fig. 15. The solid line represents the receiving portion 9122, and the dashed line represents the component 931. As shown in Fig. 16, the receiving portion 9122 has a receiving groove 9122G on its upper side.

[0178] The receiving groove 9122G has approximately the same width as the roller 9322 of the roller portion 9321 on the lower surface of the component 931. When the solenoid is energized, the component 931 is placed on the main body 910 by placing the roller 9322 in the receiving groove 9122G and moving it. Thereafter, the solenoid is de-energized, and the component 931 is fixed to the main body.

[0179] Fig. 17 is a perspective view showing a combat component 931A, which is a combat component 931 as another example of the component 931. As shown in Fig. 17, the combat component 931A can selectively be equipped with a machine gun, a bomb to be dropped, or a suicide bomb to be dropped on an enemy facility to blow it up, in addition to a plurality of missiles 931A1.

[0180] In addition to these, component 931 can be newly installed depending on the purpose, such as a reconnaissance component equipped with reconnaissance equipment, a camping component equipped with facilities for camping at the landing site, a medical component equipped with facilities for performing medical procedures at the landing site, etc. It is also possible to leave component 931 at the selected site and return only the main vehicle 910.

[0181] Fig. 18 is a diagram showing an example of a jet engine 920 used as a lift engine 921 and a propulsion engine 922. Fig. 19 is a diagram showing an example of a jet engine 920 with a reverse thrust flap 9211 open. As shown in Figs. 18 and 19 , the jet engine 920 is provided with the reverse thrust flap 9211 near the exhaust port of the jet engine 920.

[0182] When jet engine 920 receives a mechanical or electrical command to perform reverse thrust, it extends arm 9212 and displaces flap 9211 to a position where it will hit the exhaust gas coming out of the exhaust port of jet engine 920. At this time, the flap 9211 changes the direction of the exhaust gas from jet engine 920 to a direction almost opposite to the direction of exhaust gas output. Therefore, the output of jet engine 920 acts in the direction opposite to the direction of travel.

[0183] Arm 9212 is extended by energizing a solenoid connected to arm 9212, and is retracted into the housing of jet engine 920 when the solenoid is de-energized.

[0184] Fig. 20 is a block diagram showing the configuration of the motion control device 940. The motion control device 940 controls the motion of the aerial moving object 91. As shown in Fig. 20 , the motion control device 940 includes a control unit 941, a sensor group 942, a storage unit 943, and a communication unit 944.

[0185] The control unit 941 includes a calculation device such as a CPU (Central Processing Unit).

[0186] The sensor group 942 may include, for example, an infrared sensor 9421, an imaging camera 9422 that captures visible light, an acceleration sensor 9423 that detects the acceleration of the airborne moving body 91 in each three-dimensional direction, a gyro sensor 9424 that detects the attitude displacement of the airborne moving body 91 in each three-dimensional direction, an altitude sensor 9425 that detects the altitude of the airborne moving body 91 from the ground surface using a laser beam or air pressure, etc. Each sensor included in the sensor group 942 outputs the detection result to the control unit 941.

[0187] The storage unit 943 includes a storage device selected from various types of memories and storage devices, and stores a posture table 9431, an operation condition table 9432, and a component control table 9433.

[0188] The communication unit 944 includes a master communication unit 9441, a master-slave communication unit 9442, and a location information acquisition unit 9443. The master communication unit 9441 includes a communication device for communicating with the base, and the master-slave communication unit 9442 includes a communication device for communicating between the master unit that issues instructions to other aerial vehicles 91 and the slave unit that is an aerial vehicle 91 that follows the instructions of the slave unit. The location information acquisition unit 9443 includes a communication device that acquires location information of its own vehicle from, for example, GPS (The Global Positioning System), and outputs the acquired location information to the control unit 941.

[0189] 21 is a diagram showing an example of the data configuration of the attitude table 9431. The attitude table 9431 stores the output of each engine for each change in the attitude of the aerial vehicle 91.

[0190] 21, the attitude table 9431 stores an attitude number, which is an identifier uniquely assigned to each attitude of the aerial vehicle 91, attitude change details indicating the changes in the attitude of the aerial vehicle 91, and the output of each engine of the lift engine 921 and each engine of the propulsion engine 922, quantified for each attitude change detail. Here, for example, +10 indicates that the output in the forward direction without operating the flaps 9211 is 10% of the maximum output, and -20 indicates that the output in the reverse direction with operating the flaps 9211 is 20% of the maximum output.

[0191] 22 is a diagram showing an example of the data configuration of the movement condition table 9432. The movement condition table 9432 stores conditions for stopping the change in attitude of the aerial moving object 91 for each movement content of the aerial moving object 91.

[0192] 22 , the movement condition table 9432 stores movement numbers, which are identifiers uniquely assigned to the respective movement contents of the aerial moving object 91, posture numbers corresponding to the postures used in each movement of the aerial moving object 91, and movement stop conditions indicating the conditions for stopping the maintenance of the posture indicated by the posture number.

[0193] Here, we will explain the operation of the control unit 941 when changing the attitude of the aerial moving object 1. First, when the control unit 941 determines that it has received an instruction for an operation to change the attitude of the aerial moving object 91, it searches the operation condition table 9432 and reads out the attitude number and operation stop condition corresponding to the operation content of the specified operation.

[0194] For example, when the control unit 941 receives an instruction to start movement No. Bn (forward somersault), the control unit 941 searches the movement condition table 9432 to read out the posture number corresponding to movement No. Bn and the movement stop condition.

[0195] Next, the control unit 941 searches the attitude table 9431 to read out the output of each engine corresponding to the attitude No., and adjusts the output of each engine according to the read-out output. In the above example, the control unit 941 reads out the attitude No.: "An+1", the operation stop condition: "model rotation angle = 180°", and the attitude No.: "An+2", the operation stop condition: "roll angle = 180°".

[0196] Next, the control unit 941 adjusts the output of each engine corresponding to the attitude No. An+1 to perform a nose-up. The control unit 941 then determines whether the aircraft's turning angle has reached 180°, and if so, changes the output of each engine corresponding to the attitude No. An+1 to the output of each engine corresponding to the attitude No. An+2.

[0197] The control unit 941 then determines whether the roll angle has reached 180°, and if so, returns the output of each engine to the default (for example, constant forward speed).

[0198] 23 is a diagram showing an example of the data configuration of the component control table 9433. The component control table 9433 stores the details of the operation of each component 931 and the conditions for stopping that operation.

[0199] 23, the component control table 9433 stores a component number which is an identifier uniquely assigned to each component 931, a component name, a control ID which is an identifier uniquely assigned to a control content, the control content, and a control stop condition which indicates a condition for stopping the operation of the control content.

[0200] For example, if the airborne vehicle 91 is equipped with a component for transporting equipment, when the control unit 941 determines that it has received control ID: C001-001, which is an instruction to open the hatch, it performs a pre-stored lock-and-open operation to open the hatch and an operation to open the door, and when it determines that the control stop condition "lock-and-open & door open sensor ON" is satisfied, it stops the operation to open the hatch.

[0201] (Other Examples of Aerial Vehicles) The aerial vehicle 91 is space-saving. Therefore, multiple aerial vehicles can be mounted on a large aircraft. For example, an aerial vehicle 91 equipped with a combat component 931A is loaded onto an aerial carrier, which is a large aircraft, and transported to the vicinity of an enemy base. Then, when an instruction to commence an attack is issued from the base, the aerial carrier releases the aerial vehicle 91, causing it to commence the attack. Operating in this manner makes it possible to reduce the fuel consumption of the aerial vehicle 91, and if a refueling device is installed on the aerial carrier, continuous attacks become possible.

[0202] (Effects) As described above, the unmanned aerial vehicle 91 of this embodiment comprises a plurality of lift engines which are jet engines or rocket engines that generate lift, a plurality of propulsion engines which are jet engines or rocket engines that generate thrust, a group of sensors that detect attitude, a memory unit that stores a plurality of actions for completing each attitude change action, and a control unit that, when it determines that an instruction to perform the attitude change action has been received, controls the output of the lift engines and the propulsion engines to start the plurality of actions corresponding to the attitude change action read from the memory unit, and continues the attitude change action until it determines that the attitude change action has been completed because all of the plurality of actions have been completed based on the output of the group of sensors, and does not comprise main wings that generate lift greater than the lift generated by the lift engines.

[0203] Therefore, the aerial vehicle 91 of the present invention has the effect of realizing space saving.

[0204] <<Power Transmission System>> A power transmission system 100 according to one embodiment of the present invention will be described in detail below with reference to the drawings.

[0205] (Basic Concept) Conventional wireless power transmission systems include various technologies such as magnetic field coupling and electric field coupling. All of the wireless power transmission systems in practical use use a coil on the power transmitting side and a coil on the power receiving side, and pass an AC current through them. Therefore, only one frequency of AC current is usually used.

[0206] When there is a distance between the power transmitting device and the power receiving device, or when the load requires a large amount of power, it is necessary to increase the voltage of the AC current, which results in a limit to the amount of power that can be transmitted.

[0207] Therefore, the power transmission system 100 of the present invention transmits power using alternating currents of multiple frequencies. Furthermore, the power transmission system 100 of the present invention uses a radio wave lens formed of a conductive medium in which radio waves propagate at a different speed than the atmosphere or outer space, and which outputs a transmitted wave from the medium at a transmission angle different from the incident angle of the incident wave.

[0208] The radio waves that carry the power to be transmitted are output from a single antenna. The radio waves output from the antenna spread out radially, and their direction is changed by a convex radio lens toward the convex radio lens of the receiving unit. The convex radio lens on the receiving side converges the radio waves and converts them into AC voltage of the desired voltage.

[0209] Therefore, the power transmission system 100 can transmit power that is at least several times higher than that of conventional power transmission technology, at a frequency that is used for power transmission radio waves.

[0210] 24 is a block diagram showing the configuration of a power transmission system 100 according to the first embodiment. As shown in FIG. 24 , the power transmission system 100 includes a power transmission unit 101, a power transmission-side radio wave lens 1016, a power receiving-side radio wave lens 1021, and a power receiving unit 102.

[0211] (Power transmission unit) The power transmission unit 101 includes a frequency-specific signal generation unit 1011 that generates AC signals of multiple frequencies for each frequency from power supplied from the power supply unit 103, a synthesis unit 1012 that synthesizes the AC signals of multiple frequencies generated by the frequency-specific signal generation unit 1011 into one signal, a bias voltage generation unit 1013 that generates a bias voltage from the power supplied from the power supply unit 103, a bias voltage application unit 1014 that applies the bias voltage generated by the bias voltage generation unit 1013 to the synthesized signal synthesized and output by the synthesis unit, and a power transmission antenna 1015 that transmits the synthesized signal to which the bias voltage has been applied by the bias voltage application unit 1014.

[0212] The power supply unit 103 may be external power or the power supply device 81 described above.

[0213] The frequency-specific signal generator 1011 generates AC signals for each of a plurality of frequencies. The AC signals may be sine waves or other waveforms. A known circuit can be appropriately selected and used as a signal generator to generate the AC signals. The generated frequency can be appropriately selected from a range of several KHz to tens of thousands of THz. In other words, frequencies ranging from so-called radio wave frequencies to gamma ray frequencies can be appropriately selected and used.

[0214] The combiner 1012 combines the AC signals generated and output by the frequency-specific signal generator 1011 into one signal and outputs the combined signal.

[0215] The bias voltage generating unit 1013 generates a bias voltage having a DC component. The bias voltage may be a simple DC current.

[0216] The bias voltage application section 1014 superimposes the bias voltage generated by the bias voltage generation section 1013 on the combined signal output by the combination section 1012 and applies the result.

[0217] The power transmitting antenna 1015 is formed of a conductor and transmits a composite signal to which a bias voltage is applied by the bias voltage application unit 1014. It is desirable that the power transmitting antenna 1015 has a spherical tip in order to make it easier to design a radio wave lens, but other shapes may also be used.

[0218] The material used for the power transmitting antenna 1015 can be appropriately selected from materials used for conventional antennas. For example, a spherical antenna with a copper tip can be used. In this case, there are no particular restrictions on the diameter of the sphere as long as it is large enough to withstand the voltage of the power transmitting radio waves.

[0219] (Radio wave lens) A radio wave lens is formed from a conductive medium in which radio waves propagate at a different speed than in the atmosphere or outer space, and outputs a transmitted wave from the medium at a transmission angle different from the incident angle of the incident wave. The material of the radio wave lens can be, for example, copper.

[0220] The shape of the radio wave lens is appropriately selected depending on the transmission distance and the frequency of the transmitted radio waves. For example, the shape of the radio wave lens can be selected appropriately from the shape of an optical convex lens. Therefore, the transmitting-side radio wave lens 1016 and the receiving-side radio wave lens 1021 may have the same shape or different shapes.

[0221] However, chromatic aberration can be a problem in optical magnifying glasses. Depending on the frequency used, it may be desirable to reduce the chromatic aberration of radio waves as well. In this case, an achromatic radio wave lens can be used to reduce the chromatic aberration of radio waves, just like a lens in an optical system. The shape of the achromatic radio wave lens can be selected appropriately based on the shape of the achromatic lens in the optical system.

[0222] If a material with a different radio wave propagation speed is required for an achromatic radio wave lens, a material with a different radio wave propagation speed can be prepared and used by doping a conductive material with another conductive material. For example, doping copper with a material with lower electrical resistance than copper, such as gold or platinum, can result in a material with a faster radio wave propagation speed than copper, while doping copper with a material with higher electrical resistance than copper, such as nickel or chromium, can result in a material with a slower radio wave propagation speed than copper. The relationship between propagation speed, incident angle, and transmission angle is described in detail in well-known literature (e.g., Chapter 4 of "Revised Edition: Fundamentals of Radio Wave Engineering," by Hideaki Wakabayashi, published by University Education Publishing Co., Ltd. on October 10, 2017).

[0223] Like optical lenses, radio wave lenses can be used in combination with convex and concave lenses. When it is necessary to transmit power transmission radio waves to a precise location, achromatic radio wave lenses can be used in combination with convex and concave radio wave lenses.

[0224] (Power receiving unit) The power receiving unit 102 includes a smoothing unit 1023 that smooths the transmission radio waves propagated from a receiving antenna 1022 that receives the transmission radio waves converged by a receiving-side radio wave lens 1021, a DC / AC conversion unit 1024 that converts the transmission radio waves smoothed by the smoothing unit 1023 to generate AC power, and a voltage adjustment unit 1025 that adjusts the voltage of the AC power output from the DC / AC conversion unit 1024 in accordance with the load 104.

[0225] A known smoothing circuit can be appropriately selected and used as the smoothing unit 1023. The smoothing unit 1023 smoothes each frequency of the power transmission radio waves.

[0226] For example, a known inverter circuit can be appropriately selected and used as the DC-AC conversion unit 1024. The frequency of the AC power to be output can be selected according to the frequency required by the load.

[0227] The voltage adjusting unit 1025 can use a known voltage adjusting circuit that performs voltage step-up or step-down.

[0228] (Power transmission radio wave) Here, the power transmission radio wave used in this embodiment will be described. Fig. 25 is a diagram showing changes in the power transmission radio wave.

[0229] Fig. 25(A) is a diagram schematically showing the composite signal output by the combining unit 1012. In Fig. 25(A), the vertical axis represents voltage (V) and the horizontal axis represents frequency (F). As shown in Fig. 25(A), the composite signal is a combination of multiple frequencies. The amplitude of this composite signal will be referred to as waveform amplitude W hereinafter. The composite signal is an AC signal.

[0230] 25(B) is a diagram schematically showing the composite signal to which the bias voltage output by the bias voltage application unit 1014 has been applied. In FIG. 25(B), the vertical axis represents voltage (V) and the horizontal axis represents frequency (F). As shown in FIG. 25(B), the composite signal to which the bias voltage has been applied has a component with waveform amplitude W and a DC component D of the bias voltage. Therefore, since the composite signal to which the bias voltage has been applied has a component with waveform amplitude W, it has wave properties and its propagation direction can be changed by a radio wave lens.

[0231] Fig. 25(C) is a diagram schematically showing the transmission radio wave smoothed by the smoothing unit 1023. In Fig. 25(C), the vertical axis represents voltage (V) and the horizontal axis represents frequency (F). As shown in Fig. 25(C), the smoothing unit 1023 smooths each frequency of the transmission radio wave, and as a result, all frequencies are smoothed, and the voltage becomes DC power which is the sum of the waveform amplitude W and the DC component D.

[0232] Therefore, the power transmission radio wave can be converted into AC power of a desired frequency using the DC / AC converter 1024, and further adjusted to a desired voltage by the voltage adjuster 1025.

[0233] (Modification) Fig. 26 is a block diagram showing a modification of the power transmission system 100 of the present embodiment. In the power transmission unit 101 of the embodiment shown in Fig. 24, the combiner 1012 combines AC signals of multiple frequencies generated by the frequency-specific signal generator 1011 into one signal, and then applies the resultant signal by superimposing a bias voltage generated by the bias voltage generator 1013. In contrast, as shown in Fig. 26, this modification differs in that the bias voltage generated by the bias voltage generator 1013 is superimposed on the AC signals of multiple frequencies generated by the frequency-specific signal generator 1011 and then applies the resultant signal by superimposing the bias voltage generated by the bias voltage generator 1013, and then applies the resultant signal by the combiner 1012. The effect is almost the same as that of the power transmission unit 101 of the embodiment shown in Fig. 24.

[0234] (Effects) As described above, the power transmission system 100 of this embodiment includes the power transmission unit 101 that transmits AC power of multiple frequencies to which a bias voltage is applied as transmission radio waves, the power transmitting-side radio wave lens 1016 and the power receiving-side radio wave lens 1021 that are formed of a conductive medium in which the propagation speed of radio waves differs from that of the atmosphere or outer space and that output transmitted waves from the medium at a transmission angle that differs from the angle of incidence of the incident wave, and the power receiving unit 102 that receives the transmission radio waves that are transmitted via the power transmitting-side radio wave lens 1016 and converged by the power receiving-side radio wave lens 1021.

[0235] Therefore, the present invention has an effect of providing a wireless power transmission system that transmits power wirelessly.

[0236] 27 is a block diagram showing the configuration of a power transmitting device that can be used in the power transmitting system 100 of this embodiment. As shown in Fig. 27, the power transmitting device includes the above-mentioned power transmitting unit 101, a power transmitting-side electromagnetic wave lens group 1016A, and a direction converting unit 1017.

[0237] The power transmission side radio wave lens group 1016A has multiple radio wave lenses such as convex radio wave lenses, concave radio wave lenses, and, if necessary, achromatic radio wave lenses, and generates a beam-shaped power transmission radio wave B from the power transmission radio wave output from the power transmission unit 101.

[0238] The direction changer 1017 has a magnetic force generator that applies a magnetic force to the beam-shaped power transmission radio waves B, and changes the propagation direction of the beam-shaped power transmission radio waves B output from the power transmission side radio wave lens group 1016A by the magnetic force.

[0239] Fig. 28 is a block diagram showing the configuration of the direction conversion unit 1017. In Fig. 28, the direction conversion unit 1017 is shown as viewed from the propagation direction of the beam-shaped power transmission radio wave B. As shown in Fig. 28, the direction conversion unit 1017 has a magnetic force generation unit that applies a magnetic force to the beam-shaped power transmission radio wave B, and a control unit 1017C, and changes the propagation direction of the beam-shaped power transmission radio wave B output from the power transmission-side radio wave lens group 1016A by the magnetic force.

[0240] The magnetic force generating unit includes, for example, a first coil pair (first coil 10171A, which is one coil of the first coil pair, and second coil 10171B, which is the other coil, collectively referred to as the first coil pair) and a second coil pair (third coil 10172A, which is one coil of the second coil pair, and fourth coil 10172B, which is the other coil, collectively referred to as the second coil pair) arranged so that their magnetic fluxes are perpendicular to each other. The magnetic force generating unit includes a variable power supply device that supplies power of a current direction and voltage to each of the first coil pair and the second coil pair in accordance with instructions from the control unit 1017C.

[0241] The multiple arrows shown pointing from the first coil 10171A to the second coil 10171B indicate magnetic flux and its direction. Power is supplied from the variable power supply device to the first coil 10171A and the second coil 10171B in response to an instruction from the control unit 1017C, and the first coil 10171A and the second coil 10171B generate magnetic flux that points from the first coil 10171A to the second coil 10171B in the direction of the arrows shown in FIG. 28.

[0242] The multiple arrows shown pointing from the third coil 10172A to the fourth coil 10172B indicate magnetic flux and its direction. Power is supplied from the variable power supply device to the third coil 10172A and the fourth coil 10172B in response to an instruction from the control unit 1017C, and the third coil 10172A and the fourth coil 10172B generate magnetic flux in the direction of the arrows shown in FIG. 28 from the third coil 10172A to the fourth coil 10172B.

[0243] The control unit 1017C includes a calculation device such as a CPU (Central Processing Unit), a storage device such as a memory, and a communication device for communicating with external devices. When the control unit 1017C receives location information of a power transmission destination such as an aerial moving object, the control unit 1017C calculates a direction in which the beam-shaped power transmission radio wave B is directed (for example, an angle between the reference axis, with the vertical direction as a reference axis, and the direction in which the beam-shaped power transmission radio wave B is directed) based on the location information of the power transmission device and the received location information of the power transmission destination, and calculates the power to be applied to the first coil pair and the second coil pair required to change the propagation direction of the beam-shaped power transmission radio wave B in this direction.

[0244] The control unit 1017C then instructs the variable power supply device to supply the calculated power, causing magnetic flux to be generated in the first coil pair and the second coil. In other words, the control unit 1017C adjusts the direction of the current and the voltage applied to the first coil pair and the second coil pair, thereby arbitrarily changing the propagation direction of the beam-shaped power transmission radio wave B.

[0245] Therefore, according to Fleming's law, the propagation direction of the beam-shaped power transmission radio waves B is changed depending on the direction and force of the resultant force F, which is the resultant force of the force generated by the first coil pair and the force generated by the second coil pair.

[0246] (Effects) As described above, the power transmitting device of this embodiment includes: a power transmitting unit 1017 that generates AC power of multiple frequencies to which a bias voltage is applied from power supplied from the power supply unit 103 and transmits the power as power transmission radio waves; a power transmitting-side radio wave lens group 1016A that has multiple radio wave lenses formed of a conductive medium whose radio wave propagation speed is different from that of the atmosphere or outer space and that output the power transmission radio waves as transmitted waves from the medium at a transmission angle that is different from the angle of incidence of the incident wave, and that generates a beam-shaped power transmission radio wave B from the power transmission radio waves; and a direction changing unit 1017 that has a magnetic force generating unit that applies a magnetic force to the beam-shaped power transmission radio wave B and that changes the propagation direction of the beam-shaped power transmission radio wave B output from the power transmitting-side radio wave lens group 1016A by using the magnetic force.

[0247] Therefore, according to the present invention, it is possible to transmit power to a moving object E moving through the air, for example, so as to follow the moving object E whose position changes as it continues to move through the air.

[0248] 1 Air defense system 11 Power supply unit 12 High frequency signal generator 13 Gap switch 14 First branch point 15 Phase control device 16 Second branch point 17 Combiner 18 Signal processing device 19 Main control unit 20 Capacitor 30 Coil-specific control unit 31 Phase shifter 31A Phase shifter 32 Amplifier 33 Circulator 34 Limiter 40 Array Tesla coil 41 Tesla coil 41A Primary coil 41B Secondary coil 41C Tertiary coil 41D Lead delay 41E Spherical antenna 50 Cooling machine 51 Inlet hole 52 Pressure valve A First connection point B Second connection point 71 Shield barrier generating device 72 Power supply unit 711 Frequency-specific electromagnetic wave generating unit 712 Phase control unit 713 Combiner 714 Amplifier 715 Antenna 7111 Electromagnetic wave generating unit 7112 Phase shifter 81 Power feeding device 82 Load 811 Power collecting unit 8111 AC / DC converting unit 8112 First electrode 8113 Second electrode 812 Superimposing unit 813 DC / AC converting unit 814 Voltage adjusting unit 91 Unmanned aerial vehicle 910 Main body 911 Device storage unit 913 Mounting member 920 Jet engine 921 Lift engine 921FL Front left engine 921FR Front right engine 921RL Rear left engine 921RR Rear right engine 922 Propulsion engine 922FL Front left engine 922L Left propulsion engine 922R Right propulsion engine 931 Component 931A Combat component 931A1 Missile 931T Transport component 931T1 Hatch 940 Motion control device 941 Control unit 942 Sensor group 943 Memory unit 944 Communication unit 9110 Support 9111 Wheel 9121 Crosspiece 9122 Receiving unit 9122G Receiving groove 9123 Lock 9211 Flap 9212 Arm 9321 Roller unit 9322 Roller 9421 Infrared sensor 9422 Imaging camera 9423 Acceleration sensor 9424 Gyro sensor 9425 Altitude sensor 9431 Posture table 9432 Operation condition table 9433 Component control table 9441 Main communication unit 9442 Main-slave communication unit 9443 Position information acquisition unit 100 Power transmission system 101 Power transmission unit 102 Power receiving unit 103 Power supply unit 104 Load1011 Frequency-specific signal generation unit 1012 Synthesis unit 1013 Bias voltage generation unit 1014 Bias voltage application unit 1015 Power transmission antenna 1016 Power transmission side radio wave lens 1016A Power transmission side radio wave lens group 1017 Direction conversion unit 1017C Control unit 10171A First coil 10171B Second coil 10172A Third coil 10172B Fourth coil 1021 Power reception side radio wave lens 1022 Power reception antenna 1023 Smoothing unit 1024 DC / AC conversion unit 1025 Voltage adjustment unit

Claims

1. A power supply device comprising: a power collection unit having a first electrode formed of a conductor, a tip of the conductor being exposed and disposed in water in an area in contact with the ground or the crust, a second electrode formed of a conductor, a tip of the conductor being exposed and disposed in the Earth's atmosphere, and an AC-DC conversion unit that converts an alternating current input from the first electrode into direct current power; a superimposing unit that boosts the direct current power output from the power collection unit by series connection; and a DC-AC conversion unit that converts the direct current power output from the superimposing unit into alternating current power.

2. A power supply device comprising: a power collection unit having a first electrode formed of a conductor, a tip of the conductor being exposed and disposed in water in an area in contact with the ground or the crust, a second electrode formed of a conductor, a tip of the conductor being exposed and disposed in the Earth's atmosphere, and an AC-DC conversion unit that converts an alternating current input from the first electrode into direct current power; and a DC-AC conversion unit that converts the direct current power output from the power collection unit into alternating current power.

3. A power supply unit that supplies AC power received from the power supply device according to claim 1, a high-frequency signal generator that generates a high-frequency signal using the power supplied from the power supply unit, a gap switch that is connected to one of a pair of output terminals from the high-frequency signal generator and has two conductor ends arranged at intervals in the air, a capacitor that is connected to both of the pair of output terminals from the high-frequency signal generator, a coil-by-coil control unit having a phase shifter that changes the phase of the high-frequency signal generated by the high-frequency signal generator by a specified amount, an array Tesla coil in which a 1st coil, a 2nd coil, and a 3rd coil have an increasing number of turns in this order, the output from the high-frequency signal generator is input to a 1st connection point that is one end of the 1st coil, the output from the gap switch is input to a 2nd connection point that is a connection portion between the 1st coil and the 2nd coil, and a spherical sphere antenna is connected to an output-side end of the 3rd coil via a rod-shaped lead delay, a phase control device that generates a phase change amount required for beam formation in a desired direction for each Tesla coil and outputs it to the corresponding phase shifter, and a main control unit that generates and outputs a control signal for the high-frequency signal generator and a control signal for the phase control device. A phased array Tesla coil air defense system comprising the above components.

4. A power supply unit that supplies the power received from the power supply device according to claim 1 to a load housed inside, a plurality of lift engines that are jet engines or rocket engines that generate lift, a plurality of propulsion engines that are jet engines or rocket engines that generate propulsion force, a sensor group that detects the attitude, a storage unit that stores a plurality of operations for completing the attitude change operation for each attitude change operation, and when it is determined that an instruction to perform the attitude change operation has been received, controls the outputs of the lift engine and the propulsion engine to start the plurality of operations corresponding to the attitude change operation read from the storage unit, and continues the attitude change operation until it is determined that the attitude change operation has been completed because all of the plurality of operations have been completed based on the output of the sensor group. An unmanned aerial vehicle without a main wing that generates lift greater than the lift generated by the lift engine.

5. The unmanned aerial vehicle according to claim 4, comprising one or more combat equipment selected from missiles, machine guns, bombs for dropping, and bombs for self-destruction.

6. The combat equipment according to claim 5, which is detachably formed on the unmanned aerial vehicle.

7. An airship comprising: a power supply unit that supplies power received from the power supply device according to claim 1 to a load accommodated therein; a plurality of lift engines that are jet engines or rocket engines that generate lift; a plurality of propulsion engines that are jet engines or rocket engines that generate propulsion force; a sensor group that detects the attitude; a storage unit that stores a plurality of operations for completing the attitude change operation for each attitude change operation; and a control unit that, when it is determined that an instruction to perform the attitude change operation has been received, controls the outputs of the lift engine and the propulsion engine to start the plurality of operations corresponding to the attitude change operation read from the storage unit, and continues the attitude change operation until it is determined that the attitude change operation has been completed because all of the plurality of operations have been completed based on the output of the sensor group; one or more combat equipment selected from missiles, machine guns, bombs for dropping, and bombs for self-destruction; a loading unit that loads an unmanned aerial vehicle without a main wing that generates lift greater than the lift generated by the lift engine therein; and a release unit that releases the aerial vehicle from the loading unit at a destination and causes the aerial vehicle to start an attack based on an instruction to start an attack.

8. A power transmission system comprising: a power supply unit that supplies power received from the power supply device according to claim 1; a power transmission unit that generates AC power of a plurality of frequencies to which a bias voltage is applied from the power supplied from the power supply unit and transmits the AC power as transmission radio waves; a power transmission side radio wave lens and a power reception side radio wave lens that are formed of a conductor medium having a different radio wave propagation speed from the atmosphere or outer space and output the transmission radio waves as transmission waves from the medium at a transmission angle different from the incident angle of the incident wave; and a power reception unit that receives the transmission radio waves transmitted through the power transmission side radio wave lens and converged by the power reception side radio wave lens.

9. The power transmission unit according to claim 8.

10. The power reception unit according to claim 8.

11. A power transmission device comprising: a power supply unit that supplies power received from the power supply device according to claim 1; a power transmission unit that generates AC power of a plurality of frequencies to which a bias voltage is applied from the power supplied by the power supply unit and transmits it as a transmission radio wave; a plurality of radio wave lenses formed of a conductive medium having a different radio wave propagation speed from the atmosphere or outer space, and outputting the transmission radio wave as a transmitted wave from the medium at a transmission angle different from the incident angle of the incident wave; a transmission-side radio wave lens group that generates a beam-shaped transmission radio wave from the transmission radio wave; and a direction conversion unit that has a magnetic force generation unit that applies a magnetic force to the beam-shaped transmission radio wave and changes the propagation direction of the beam-shaped transmission radio wave output from the transmission-side radio wave lens group by the magnetic force.