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WO2018198593A1 - Gestion de la récolte d'énergie dans le plan solaire - Google Patents

Gestion de la récolte d'énergie dans le plan solaire Download PDF

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Publication number
WO2018198593A1
WO2018198593A1 PCT/JP2018/010666 JP2018010666W WO2018198593A1 WO 2018198593 A1 WO2018198593 A1 WO 2018198593A1 JP 2018010666 W JP2018010666 W JP 2018010666W WO 2018198593 A1 WO2018198593 A1 WO 2018198593A1
Authority
WO
WIPO (PCT)
Prior art keywords
wireless relay
power generation
relay device
battery
relay station
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Ceased
Application number
PCT/JP2018/010666
Other languages
English (en)
Japanese (ja)
Inventor
明彦 田近
田中　伸一
弘 石原
武伸 千葉
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
SoftBank Corp
Original Assignee
SoftBank Corp
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by SoftBank Corp filed Critical SoftBank Corp
Publication of WO2018198593A1 publication Critical patent/WO2018198593A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64B—LIGHTER-THAN AIR AIRCRAFT
    • B64B1/00—Lighter-than-air aircraft
    • B64B1/06—Rigid airships; Semi-rigid airships
    • B64B1/14—Outer covering
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D47/00—Equipment not otherwise provided for
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U30/00—Means for producing lift; Empennages; Arrangements thereof
    • B64U30/10—Wings
    • B64U30/12—Variable or detachable wings, e.g. wings with adjustable sweep
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U50/00—Propulsion; Power supply
    • B64U50/30—Supply or distribution of electrical power
    • B64U50/31—Supply or distribution of electrical power generated by photovoltaics
    • H—ELECTRICITY
    • H04—ELECTRIC COMMUNICATION TECHNIQUE
    • H04B—TRANSMISSION
    • H04B7/00—Radio transmission systems, i.e. using radiation field
    • H04B7/14—Relay systems
    • H04B7/15—Active relay systems
    • H04B7/185—Space-based or airborne stations; Stations for satellite systems
    • H—ELECTRICITY
    • H04—ELECTRIC COMMUNICATION TECHNIQUE
    • H04W—WIRELESS COMMUNICATION NETWORKS
    • H04W16/00—Network planning, e.g. coverage or traffic planning tools; Network deployment, e.g. resource partitioning or cells structures
    • H04W16/24—Cell structures
    • H04W16/26—Cell enhancers or enhancement, e.g. for tunnels, building shadow
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U10/00—Type of UAV
    • B64U10/25—Fixed-wing aircraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U2101/00—UAVs specially adapted for particular uses or applications
    • B64U2101/20—UAVs specially adapted for particular uses or applications for use as communications relays, e.g. high-altitude platforms
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/50—On board measures aiming to increase energy efficiency

Definitions

  • the present invention relates to a wireless relay device in a three-dimensional network such as fifth generation communication.
  • LTE-AdvancedPro which is an extension of 3GPP LTE (Long Term Evolution) -Advanced
  • Non-Patent Document 1 which is a communication standard for mobile communication systems
  • Non-Patent Document 2 a communication standard for mobile communication systems
  • LTE-AdvancedPro specifications for providing communication to devices for recent IoT (Internet of Things) have been formulated.
  • IoT Internet of Things
  • the fifth generation mobile that supports simultaneous connection and low delay to many terminal devices (also referred to as “UE (user equipment)”, “mobile station”, “communication terminal”) such as devices for IoT. Communication has been studied (for example, see Non-Patent Document 3).
  • the propagation delay of wireless communication with a terminal device including an IoT device is low, it can be connected to a large number of terminals simultaneously, high-speed communication is possible, and the system capacity per unit area is large. There is a problem that it is desired to stably realize a three-dimensional network over a long period regardless of the area.
  • a radio relay device is a radio relay device including a radio relay station that relays radio communication with a terminal device, and the radio relay station is a predetermined cell between the ground and the sea surface.
  • the radio relay station is a predetermined cell between the ground and the sea surface.
  • a wing provided with a photovoltaic power generation panel; and a propeller that can be rotationally driven by a rotational drive source.
  • the wing mainly assists solar power generation in the main wing and the main wing that generates buoyancy.
  • an auxiliary wing part provided with a photovoltaic power generation panel separately from the main wing part.
  • a wireless relay device is a wireless relay device including a wireless relay station that relays wireless communication with a terminal device, wherein the wireless relay station is a predetermined relay between the ground and the sea surface.
  • the wireless relay station is a predetermined relay between the ground and the sea surface.
  • the solar power generation panel includes a wing provided with a solar power generation panel and a propeller that can be rotationally driven by a rotational drive source, and the light receiving surface of the solar power generation panel has a plurality of light receiving surface portions whose directions perpendicular to the surface are different from each other. .
  • the light receiving surface of the photovoltaic power generation panel may be formed such that a plurality of planar light receiving surface portions whose directions perpendicular to the surface are different from each other are continuously arranged repeatedly, or wavy
  • the surface shape may change continuously.
  • a wireless relay device is a wireless relay device including a wireless relay station that relays wireless communication with a terminal device, wherein the wireless relay station is a predetermined between the ground and the sea surface.
  • the floating body is controlled to be positioned in a floating airspace of altitude of 100 km or less by autonomous control or external control, and the floating body Includes a wing provided with a photovoltaic power generation panel and a propeller that can be driven to rotate by a rotational drive source, and is tilted so that the surface of the wing provided with the photovoltaic power generation panel faces the sun.
  • Flight control means for controlling the flight path of the vehicle to fly.
  • the wireless relay station forms a beam for wireless communication with the terminal device toward a ground surface or a sea surface, and at least one of a direction and a divergence angle of the beam based on an inclination of the levitation body. You may further provide the beam adjustment means to adjust one.
  • a wireless relay device is a wireless relay device including a wireless relay station that relays wireless communication with a terminal device, wherein the wireless relay station is a predetermined between the ground and the sea surface.
  • the floating body is controlled to be positioned in a floating airspace of altitude of 100 km or less by autonomous control or external control, and the floating body Includes a wing provided with a photovoltaic power generation panel, a propeller that can be rotationally driven by a rotational drive source, and a battery, and the rotation transmitted from the propeller when power is not supplied to the rotational drive source And regenerative energy supply means for generating electric power and charging the battery.
  • a wireless relay device is a wireless relay device including a wireless relay station that relays wireless communication with a terminal device, and the wireless relay station is between the ground and the sea surface.
  • the floating body controlled to be located in the floating airspace of altitude of 100 [km] or less by autonomous control or external control
  • the levitation body includes a wing provided with a photovoltaic power generation panel, a propeller that can be rotationally driven by a rotational drive source, a battery, a wind turbine for power generation, and power generated by the rotation transmitted from the wind turbine for power generation. And a generator for charging.
  • the power generated by the solar power generation panel is supplied to the rotary drive source and the battery during a time period in which the solar power generation panel receives sunlight.
  • the propeller or the wind turbine for power generation is rotated by the rotation of the propeller or the power generation windmill or the rotation of the propeller or the wind turbine for power generation when the solar power generation panel is lowered due to its own weight during a time period when the solar power generation panel is not receiving sunlight.
  • the electric power generated by the rotary drive source or the generator to which is transmitted may be supplied to the battery.
  • a wireless relay device is a wireless relay device including a wireless relay station that relays wireless communication with a terminal device, wherein the wireless relay station is a predetermined between the ground and the sea surface.
  • the floating body is controlled to be positioned in a floating airspace of altitude of 100 km or less by autonomous control or external control, and the floating body Includes a wing provided with a photovoltaic power generation panel, a propeller that can be driven to rotate by a rotation drive source, and a battery, and generates electric power by the temperature difference generated by the heat generated by the heat generating part of the wireless relay device.
  • the heating unit is connected to the wireless relay station, the photovoltaic power generation panel, a charge adjustment unit that adjusts charging of the battery, the rotation drive source, or the wireless relay station or the rotation drive source. It may be a power supply adjustment unit that adjusts the power to be supplied.
  • a communication system includes any one of the wireless relay devices and a remote control device that remotely controls the wireless relay device.
  • a communication system includes a wireless relay device including a wireless relay station that relays wireless communication with a terminal device, and a remote control device that remotely controls the wireless relay device.
  • the radio relay station is located in a floating airspace having an altitude of 100 km or less by autonomous control or external control so as to form a three-dimensional cell in a predetermined cell formation target airspace between the ground and the sea surface.
  • the levitation body includes a wing provided with a photovoltaic power generation panel, a propeller that can be rotationally driven by a rotational drive source, and a battery.
  • the wireless relay device includes a flight control means for controlling the surface of the wing on which the photovoltaic power generation panel is provided to be directed toward the sun and flying on a predetermined circular flight path, and the rotational drive source.
  • a flight control means for controlling the surface of the wing on which the photovoltaic power generation panel is provided to be directed toward the sun and flying on a predetermined circular flight path, and the rotational drive source.
  • the remote control device includes: the amount of light received by the photovoltaic power generation panel; the altitude of the wireless relay device; the temperature difference; the airflow around the wireless relay device; the remaining amount of the battery; and the power consumption of the wireless relay device Based on at least one of the above, the photovoltaic power generation panel, the flight control means, the regenerative energy supply means, and the temperature difference power generation means are controlled remotely.
  • the levitation body includes a power generation windmill, a generator that generates electric power by rotation transmitted from the power generation windmill, and an energy supply that supplies electric power generated by the generator to the battery for charging. And a means.
  • the altitude of the cell formation target airspace may be 10 [km] or less.
  • the radio relay apparatus may be located in a stratosphere having an altitude of 11 [km] or more and 50 [km] or less, and the radio relay station may be a base station or a repeater of a mobile communication network. .
  • FIG. 1 is a schematic configuration diagram showing an example of the overall configuration of a communication system that realizes a three-dimensional network according to an embodiment of the present invention.
  • FIG. 2 is a perspective view showing an example of HAPS used in the communication system of the embodiment.
  • FIG. 3 is a side view showing another example of HAPS used in the communication system of the embodiment.
  • FIG. 4 is a block diagram illustrating a configuration example of a HAPS wireless relay station according to the embodiment.
  • FIG. 5 is a block diagram illustrating another configuration example of the HAPS wireless relay station of the embodiment.
  • FIG. 6 is a block diagram illustrating still another configuration example of the HAPS wireless relay station according to the embodiment.
  • FIG. 1 is a schematic configuration diagram showing an example of the overall configuration of a communication system that realizes a three-dimensional network according to an embodiment of the present invention.
  • FIG. 2 is a perspective view showing an example of HAPS used in the communication system of the embodiment.
  • FIG. 3 is a side view showing another example of HAPS
  • FIG. 7 is an explanatory diagram illustrating an example of a state of remote energy beam power supply to the HAPS of the embodiment.
  • FIG. 8 is a block diagram illustrating a configuration example of the remote energy beam power receiving unit of the HAPS according to the embodiment.
  • FIG. 9A is a top view showing still another configuration example of the solar plane type HAPS of the embodiment.
  • FIG. 9B is a top view illustrating still another configuration example of the solar plane type HAPS according to the embodiment.
  • FIG. 10A is a partial perspective view illustrating a main wing portion in still another configuration example of the solar plane type HAPS according to the embodiment.
  • FIG. 10B is a partial cross-sectional view of the main wing portion of the HAPS when the sun's south-middle altitude is low.
  • FIG. 10C is a partial cross-sectional view of the main wing portion of the HAPS when the sun's south-middle altitude is high.
  • FIG. 11A is an explanatory diagram illustrating an example of a cyclic flight route of the solar plane type HAPS according to the embodiment.
  • FIG. 11B is an explanatory diagram showing the state of the HAPS bank at the F1 point in the cyclic flight route of FIG. 11A.
  • FIG. 12A is an explanatory diagram illustrating another example of the cyclic flight route of the solar plane type HAPS according to the embodiment.
  • FIG. 12B is an explanatory diagram showing a state of the HAPS bank at the point F2 in FIG. 12A.
  • FIG. 13A is an explanatory diagram illustrating an example of the relationship between the HAPS central axis and the beam when the HAPS is not banked and when the bank is banked.
  • FIG. 13B is an explanatory diagram illustrating an example of the relationship between the HAPS central axis and the beam when the HAPS is not banked and when the bank is banked.
  • FIG. 14 is an explanatory diagram illustrating an example of a multi-beam formed by the HAPS of the embodiment.
  • FIG. 15A is an explanatory diagram illustrating an example of ascending flight during the daytime of the solar plane type HAPS of the embodiment.
  • FIG. 15B is an explanatory view showing an example of descending flight at night of the HAPS.
  • FIG. 15A is an explanatory diagram illustrating an example of ascending flight during the daytime of the solar plane type HAPS of the embodiment.
  • FIG. 15B is an explanatory view showing an example of descending flight at night of the HAPS.
  • FIG. 16A is a top view illustrating still another configuration example of the HAPS including the wind turbine for power generation according to the embodiment.
  • FIG. 16B is a top view illustrating still another configuration example of the HAPS including the wind turbine for power generation according to the embodiment.
  • FIG. 17 is an explanatory diagram illustrating a configuration example of a temperature difference power generation (exhaust heat power generation) system in the HAPS of the embodiment.
  • FIG. 18 is a block diagram illustrating a configuration example of a power supply control system in HAPS that can support power supply using a plurality of types of power generation methods.
  • FIG. 1 is a schematic configuration diagram showing an example of the overall configuration of a communication system according to an embodiment of the present invention.
  • the communication system according to the present embodiment is a fifth generation that supports simultaneous connection to a large number of terminal devices (also referred to as “mobile station”, “mobile device”, or “user equipment (UE)”), low delay, and the like. Suitable for realizing a three-dimensional network for mobile communications.
  • the mobile communication standards applicable to the communication system, radio relay station, base station, repeater, and terminal device disclosed in this specification are the fifth generation mobile communication standards and the fifth generation and later. Includes standards for next generation mobile communications.
  • the communication system includes high altitude platform stations (HAPS) (also referred to as “high altitude pseudo satellites”) 10 and 20 as a plurality of radio relay apparatuses, and a cell formation target airspace 40 of a predetermined altitude. Then, three-dimensional cells (three-dimensional areas) 41 and 42 as shown by hatching areas in the figure are formed.
  • the HAPS 10 and 20 are controlled to float in a high altitude floating airspace (hereinafter also simply referred to as “airspace”) 50 from the ground or the sea surface by autonomous control or external control.
  • a radio relay station is mounted on a floating body (eg, solar plane, airship).
  • the airspace 50 where the HAPS 10 and 20 are located is, for example, a stratospheric airspace with an altitude of 11 km or more and 50 km or less.
  • the airspace 50 where the HAPS 10 and 20 are located may be an airspace in which the altitude where the weather conditions are relatively stable is in the range of 15 [km] or more and 25 [km] or less, and particularly the altitude is approximately 20 [km].
  • the airspace may be Hrsl and Hrsu in the figure indicate relative altitudes of the lower end and the upper end of the airspace 50 where the HAPSs 10 and 20 are located with respect to the ground (GL), respectively.
  • the cell formation target airspace 40 is a target airspace that forms a three-dimensional cell with one or a plurality of HAPS in the communication system of the present embodiment.
  • the cell formation target airspace 40 is a predetermined altitude range (for example, 50 [ m] to an altitude range of 1000 [m] or less.
  • Hcl and Hcu in the figure respectively indicate the relative altitudes of the lower end and the upper end of the cell formation target airspace 40 with respect to the ground (GL).
  • the cell formation target airspace 40 in which the three-dimensional cell of the present embodiment is formed may be above the sea, river, or lake.
  • the wireless relay stations of the HAPS 10 and 20 respectively form beams 100 and 200 for wireless communication with a terminal device that is a mobile station toward the ground.
  • the terminal device may be a communication terminal module incorporated in the drone 60 which is a small helicopter capable of being remotely controlled, or may be a user terminal device used by the user in the airplane 65.
  • the regions through which the beams 100 and 200 pass in the cell formation target airspace 40 are three-dimensional cells 41 and 42.
  • the plurality of beams 100 and 200 adjacent to each other in the cell formation target airspace 40 may partially overlap.
  • the wireless relay stations of the HAPS 10 and 20 are connected to the core network of the mobile communication network 80 via a feeder station 70 that is a relay station installed on the ground or the sea.
  • Each of the HAPS 10 and 20 may autonomously control its own floating movement (flight) and processing at the radio relay station by executing a control program by a control unit configured by a computer or the like incorporated therein.
  • each of the HAPS 10 and 20 acquires its own current position information (for example, GPS position information), pre-stored position control information (for example, flight schedule information), position information of other HAPS located in the vicinity, etc. Based on this information, the levitating movement (flight) and the processing at the radio relay station may be autonomously controlled.
  • the floating movement (flight) of each of the HAPS 10 and 20 and the processing at the radio relay station may be controlled by a remote control device 85 of a communication operator provided in a communication center of the mobile communication network 80 or the like.
  • the HAPS 10, 20 is incorporated with a control communication terminal device (for example, a mobile communication module) so as to receive control information from the remote control device 85, and terminal identification information (for example, an IP address, a telephone number, etc.) may be assigned.
  • terminal identification information For example, an IP address, a telephone number, etc.
  • the MAC address of the communication interface may be used for identifying the control communication terminal device.
  • Each of the HAPSs 10 and 20 receives information on the levitation movement (flight) of itself or the surrounding HAPS, processing at the wireless relay station, observation data acquired by various sensors, etc. You may make it transmit to a transmission destination.
  • a region where the beams 100 and 200 of the HAPS 10 and 20 do not pass may occur.
  • a radial beam 300 is formed upward from the ground side or the sea side to form a three-dimensional cell 43 to form an ATG (Air To Ground) connection.
  • a base station (hereinafter referred to as “ATG station”) 30 may be provided.
  • the radio relay station of the HAPS 10 and 20 can be three-dimensionally arranged in the cell formation target airspace 40.
  • the beams 100 and 200 covering the entire upper end surface of the cell formation target airspace 40 may be formed so that the cells are formed throughout.
  • the three-dimensional cell formed by the HAPS 10 and 20 may be formed so as to reach the ground or the sea level so as to be able to communicate with a terminal device located on the ground or the sea.
  • FIG. 2 is a perspective view illustrating an example of the HAPS 10 used in the communication system according to the embodiment.
  • the HAPS 10 in FIG. 2 is a solar plane type HAPS.
  • a solar power generation panel (hereinafter referred to as a “solar panel”) 102 as a solar power generation unit having a solar power generation function on the upper surface is provided.
  • a plurality of motor-driven propellers 103 as a propulsion device for a bus power system are provided at one end edge in the short direction.
  • a pod 105 serving as a plurality of device accommodating portions in which mission devices are accommodated is connected to two places in the longitudinal direction of the lower surface of the main wing portion 101 via a plate-like connecting portion 104.
  • Each pod 105 accommodates a radio relay station 110 as a mission device and a battery 106.
  • wheels 107 used at the time of taking off and landing are provided on the lower surface side of each pod 105.
  • the electric power generated by the solar panel 102 is stored in the battery 106, the electric power supplied from the battery 106 drives the motor of the propeller 103 to rotate, and the wireless relay station 110 performs wireless relay processing.
  • the solar plane type HAPS 10 can be levitated by lift by performing, for example, turning flight or 8-shaped flight, and can be levitated so as to stay in a predetermined range in a horizontal direction at a predetermined altitude.
  • the solar plane type HAPS 10 can fly like a glider when the propeller 103 is not driven to rotate. For example, when the power of the battery 106 is surplus due to the power generation of the solar panel 102 at daytime or the like, the battery 106 rises to a high position, and when the solar panel 102 cannot generate power at night or the like, the power supply from the battery 106 to the motor is stopped and the glider is stopped. Can fly like.
  • FIG. 3 is a perspective view showing another example of the HAPS 20 used in the communication system of the embodiment.
  • the HAPS 20 in FIG. 2 is an unmanned airship-type HAPS and has a large payload, so that a large-capacity battery can be mounted.
  • the HAPS 20 includes an airship body 201 filled with a gas such as helium gas for buoyancy, a motor-driven propeller 202 as a propulsion device for a bus power system, and a device storage unit 203 for storing mission devices.
  • a radio relay station 210 and a battery 204 are housed inside the device housing unit 203. With the electric power supplied from the battery 204, the motor of the propeller 202 is driven to rotate, and the wireless relay processing by the wireless relay station 210 is executed.
  • a solar panel having a solar power generation function may be provided on the top surface of the airship body 201 so that the electric power generated by the solar panel is stored in the battery 204.
  • FIG. 4 is a block diagram illustrating a configuration example of the wireless relay stations 110 and 210 of the HAPS 10 and 20 according to the embodiment.
  • the wireless relay stations 110 and 210 in FIG. 4 are examples of repeater type wireless relay stations.
  • Each of the radio relay stations 110 and 210 includes a 3D cell (three-dimensional cell) forming antenna unit 111, a transmission / reception unit 112, a feed antenna unit 113, a transmission / reception unit 114, a repeater unit 115, a monitoring control unit 116, and a power supply unit 117. .
  • the 3D cell formation antenna unit 111 includes antennas that form the radial beams 100 and 200 toward the cell formation target airspace 40, and forms three-dimensional cells 41 and 42 that can communicate with the terminal device.
  • the transmission / reception unit 112 includes a duplexer (DUP: DUPlexer), an amplifier, and the like, and transmits a radio signal to a terminal device located in the three-dimensional cell 41 or 42 via the 3D cell forming antenna unit 111 or a terminal Receive radio signals from the device.
  • DUP DUPlexer
  • the feed antenna unit 113 includes a directional antenna for wireless communication with the ground or sea feeder station 70.
  • the transmission / reception unit 114 includes a duplexer (DUP: DUPlexer), an amplifier, and the like, and transmits a radio signal to the feeder station 70 and receives a radio signal from the feeder station 70 via the 3D cell forming antenna unit 111. To do.
  • DUP DUPlexer
  • the repeater unit 115 relays the signal of the transmission / reception unit 112 transmitted / received to / from the terminal device and the signal of the transmission / reception unit 114 transmitted / received to / from the feeder station 70.
  • the repeater unit 115 may have a frequency conversion function.
  • the monitoring control unit 116 is configured by, for example, a CPU and a memory, and monitors the operation processing status of each unit in the HAPS 10 and 20 and controls each unit by executing a program incorporated in advance.
  • the power supply unit 117 supplies the power output from the batteries 106 and 204 to each unit in the HAPS 10 and 20.
  • the power supply unit 117 may have a function of storing in the batteries 106 and 204 power generated by a solar power generation panel or the like or power supplied from the outside.
  • FIG. 5 is a block diagram illustrating another configuration example of the wireless relay stations 110 and 210 of the HAPS 10 and 20 according to the embodiment.
  • the radio relay stations 110 and 210 in FIG. 5 are examples of base station type radio relay stations.
  • the same components as those in FIG. 4 are denoted by the same reference numerals, and the description thereof is omitted.
  • Each of the radio relay stations 110 and 210 in FIG. 5 further includes a modem unit 118 and a base station processing unit 119 instead of the repeater unit 115.
  • the modem unit 118 performs, for example, a demodulation process and a decoding process on the reception signal received from the feeder station 70 via the feed antenna unit 113 and the transmission / reception unit 114, and outputs the data signal to the base station processing unit 119 side. Is generated. Further, the modem unit 118 performs encoding processing and modulation processing on the data signal received from the base station processing unit 119 side, and transmits to the feeder station 70 via the feed antenna unit 113 and the transmission / reception unit 114. Generate a signal.
  • the base station processing unit 119 has a function as e-NodeB that performs baseband processing based on, for example, a method compliant with the LTE / LTE-Advanced standard.
  • the base station processing unit 119 may perform processing by a method based on a standard for future mobile communication such as the fifth generation or the next generation after the fifth generation.
  • the base station processing unit 119 performs demodulation processing and decoding processing on the received signals received from the terminal devices located in the three-dimensional cells 41 and 42 via the 3D cell forming antenna unit 111 and the transmission / reception unit 112. A data signal to be output to the modem unit 118 side is generated. In addition, the base station processing unit 119 performs encoding processing and modulation processing on the data signal received from the modem unit 118 side, and the 3D cells 41 and 42 via the 3D cell forming antenna unit 111 and the transmission / reception unit 112. A transmission signal to be transmitted to the terminal device is generated.
  • FIG. 6 is a block diagram illustrating still another configuration example of the wireless relay stations 110 and 210 of the HAPS 10 and 20 according to the embodiment.
  • the radio relay stations 110 and 210 in FIG. 6 are examples of high-function base station type radio relay stations having an edge computing function.
  • FIG. 6 the same components as those in FIGS. 4 and 5 are denoted by the same reference numerals, and description thereof is omitted.
  • Each of the radio relay stations 110 and 210 of FIG. 6 further includes an edge computing unit 120 in addition to the components of FIG.
  • the edge computing unit 120 is configured by a small computer, for example, and can execute various types of information processing related to wireless relaying in the wireless relay stations 110 and 210 of the HAPS 10 and 20 by executing a program incorporated in advance. it can.
  • the edge computing unit 120 determines the transmission destination of the data signal based on the data signal received from the terminal device located in the three-dimensional cell 41 or 42, and relays the communication based on the determination result. Executes the process of switching. More specifically, when the transmission destination of the data signal output from the base station processing unit 119 is a terminal device located in its own three-dimensional cell 41 or 42, the data signal is not passed to the modem unit 118. Then, it returns to the base station processing unit 119 and transmits it to the transmission destination terminal device located in its own three-dimensional cell 41, 42.
  • the transmission destination of the data signal output from the base station processing unit 119 is a terminal device residing in a cell other than its own three-dimensional cells 41 and 42
  • the data signal is passed to the modem unit 118.
  • the data is transmitted to the feeder station 70 and transmitted to the terminal device of the transmission destination located in another cell of the transmission destination via the mobile communication network 80.
  • the edge computing unit 120 may execute processing for analyzing information received from a large number of terminal devices located in the three-dimensional cells 41 and 42. This analysis result may be transmitted to a large number of terminal devices located in the three-dimensional cells 41 and 42, or may be transmitted to a server of the mobile communication network 80 or the like.
  • the uplink and downlink duplex schemes for wireless communication with the terminal devices via the radio relay stations 110 and 210 are not limited to specific schemes. For example, even in a time division duplex (TDD) scheme Alternatively, a frequency division duplex (FDD) method may be used.
  • the access method of wireless communication with the terminal device via the wireless relay stations 110 and 210 is not limited to a specific method, for example, FDMA (Frequency Division Multiple Access) method, TDMA (Time Division Multiple Access) method, It may be a CDMA (Code Division Multiple Access) system or OFDMA (Orthogonal Frequency Division Multiple Access).
  • the wireless communication has functions such as diversity coding, transmission beamforming, and spatial division multiplexing (SDM), and by using multiple antennas simultaneously for both transmission and reception, MIMO (multi-input and multi-output) technology capable of increasing the transmission capacity of the network may be used.
  • the MIMO technology may be a SU-MIMO (Single-User MIMO) technology in which one base station transmits a plurality of signals at the same time and the same frequency as one terminal device. Even in the MU-MIMO (Multi-User MIMO) technology in which signals are transmitted to different communication terminal devices at the same time and the same frequency, or a plurality of different base stations transmit signals to one terminal device at the same time and the same frequency. Good.
  • FIG. 7 is an explanatory diagram showing an example of a state of remote energy beam power supply to the HAPS (solar plane type) 11 capable of handling high latitudes.
  • the high-latitude HAPS 11 includes power receiving pods 108 at both ends in the longitudinal direction of the main wing 101. Inside the power receiving pod 108, a microwave power receiving unit 130 and a battery 106 as a remote energy beam power receiving unit are accommodated.
  • the microwave power reception unit 130 receives the high-power microwave beam 750 or 250 for power transmission transmitted from the microwave power supply station 75 as a power supply device on the ground or the sea or the power supply airship 25 as a power supply device in the air. Convert to and output.
  • the electric power output from the microwave power reception unit 130 is stored in the battery 106.
  • the power supply airship 25 drifts by, for example, an air current, and sequentially supplies power to the stationary HAPS by transmitting a power supply microwave beam.
  • FIG. 8 is a block diagram illustrating a configuration example of the microwave power receiving unit 130 of the HAPS 11 capable of handling high latitudes.
  • the microwave power reception unit 130 includes a rectenna unit 131, a rectenna control unit 132, an output device 133, a pilot signal transmission antenna unit 134, and a beam direction control unit 135.
  • the rectenna unit 131 receives and rectifies the high-power feed microwave beam 750 or 250 transmitted from the ground or sea microwave feed station 75 or the power supply airship 25.
  • the rectenna control unit 132 controls power reception processing and rectification processing of the feeding microwave beam by the rectenna unit 131.
  • the output device 133 outputs the rectified power output from the rectenna unit 131 to the battery 106.
  • the pilot signal transmitting antenna unit 134 transmits a pilot signal beam including a laser beam or the like for guiding the feeding microwave beam to the microwave feeding station 75 or the feeding airship prior to receiving the feeding microwave beam 750 or 250. To 25.
  • the beam direction control unit 135 controls the beam direction of the pilot signal.
  • FIGS. 9A and 9B are top views showing still other configuration examples of the solar plane type HAPS 12 according to the embodiment.
  • the HAPS 12 of FIGS. 9A and 9B includes an auxiliary wing portion 109 provided with a solar panel 102, in addition to the main wing portion 101 that mainly generates buoyancy due to the flight of the HAPS 12.
  • the auxiliary wing part 109 may be provided so as to be in contact with the main wing part 101 as shown in FIG. 9A or may be provided by talking from the main wing part 101 as shown in FIG. 9B.
  • the solar panel 102 of the auxiliary wing part 109 can assist solar power generation in the main wing part 101 and enhance the solar power generation function of the HAPS 12, which is suitable for use in high latitude areas.
  • the auxiliary wing 109 may have a shape that reduces the air resistance of the entire wing formed integrally with the main wing 101 during flight.
  • the auxiliary wing 109 may be configured to be foldable, and when rising from the ground to a predetermined floating airspace altitude, the auxiliary wing 109 may be folded to shorten the ascending time. After that, when the altitude of the predetermined levitation airspace is raised, the power generation by the solar panel 102 of the auxiliary wing portion 109 can be started by deploying the folded auxiliary wing portion 109.
  • FIG. 10A is a partial perspective view showing a main wing part 101 in still another configuration example of the solar plane type HAPS of the embodiment
  • FIGS. 10B and 10C are partial cross-sectional views of the main wing part 101 of the HAPS. 10A to 10C, the description of the components common to those in FIG. 2 is omitted.
  • the direction A in the figure is the longitudinal direction of the main wing 101.
  • the HAPS solar panel 102 is provided in a panel housing portion 101 a formed on the upper surface of the main wing portion 101.
  • a transparent plate 101b that protects the solar panel 102 while transmitting light is provided on the upper surface of the panel housing portion 101a.
  • the light receiving surface of the solar panel 102 is formed in a bellows shape (sawtooth shape) so that a plurality of planar light receiving surface portions 102a and 102b whose directions perpendicular to the surface are different from each other are continuously arranged in the A direction. ing.
  • the light receiving surface of the solar panel 102 may have a surface shape that continuously changes in a wave shape.
  • the solar panel 102 is configured to be capable of expansion and contraction control in the longitudinal direction (A direction) of the main wing portion 101 in accordance with the south-central altitude ⁇ [°] of the sun 900.
  • a direction the longitudinal direction of the main wing portion 101
  • the solar panel 102 is placed in the longitudinal direction of the arrow A. Control to shrink.
  • the incident angle of sunlight 901 with respect to the light receiving surface portion 102a (the angle formed by the direction perpendicular to the light receiving surface portion 102a and the incident direction of sunlight 901) is reduced, and the amount of received light per unit area of the solar panel 102 is reduced. The decrease can be suppressed.
  • solar panel 102 when solar altitude ⁇ [°] is large and sunlight 901 is incident from a relatively high angle with respect to the upper surface of main wing 101, solar panel 102 is placed in the longitudinal direction of arrow A. Control to stretch. Thereby, the incident angle of the sunlight 901 with respect to the light-receiving surface part 102a can be made small, and the fall of the light reception amount per unit area of the solar panel 102 can be suppressed. By controlling the expansion and contraction of the solar panel 102 in this way, it is possible to suppress a decrease in the amount of light received per unit area of the solar panel 102 even when the south-central altitude of the sun 900 relative to the upper surface of the main wing 101 changes.
  • both ends of the main wing 101 are warped upward. Therefore, the degree of expansion / contraction in the longitudinal direction of the arrow A of the solar panel 102 is set to the distance from the center in the longitudinal direction of the main wing 101 so that the decrease in the amount of light received per unit area of the solar panel 102 is more reliably suppressed. It may be changed accordingly. More specifically, for example, the longitudinal direction of the arrow A of the solar panel 102 so that the incident angle of the sunlight 901 with respect to the light receiving surface portion 102a is constant regardless of the distance from the center in the longitudinal direction of the main wing 101. The degree of expansion / contraction in may be changed.
  • FIG. 11A is an explanatory diagram illustrating an example of a patrol flight route 910 of the solar plane type HAPS 10 of the embodiment, and FIG. It is explanatory drawing. 11A and 11B show the cyclic flight route of the HAPS 10, but the other HAPSs 11 and 12 described above may also fly by the same cyclic flight route.
  • the HAPS 10 is not a circular circular flight route 910, but a modified oval shape that is set so that the flight path in which the incident angle of the sunlight 901 with respect to the solar panel 102 on the upper surface of the main wing 101 becomes small is as long as possible. Is traveling on the patrol flight route 911. For example, at the F1 point in the cyclic flight route 910 of FIG. 11A, the HAPS 10 flies in a banked state as shown in FIG. 11B so that the solar panel 102 on the upper surface of the main wing part 101 faces the sun 900. I have to.
  • FIG. 12A is an explanatory diagram illustrating another example of the cyclic flight route 910 of the solar plane type HAPS 10 of the embodiment
  • FIG. 12B is a state of the bank (tilt) of the HAPS 10 at the point F2 in the cyclic flight route 910 of FIG. It is explanatory drawing which shows. 12A and 12B also show the cyclic flight route of the HAPS 10, but the other HAPSs 11 and 12 described above may also fly by the same cyclic flight route.
  • the HAPS 10 is set so that the flight path in which the incident angle of the sunlight 901 with respect to the solar panel 102 on the upper surface of the main wing part 101 becomes small is as long as possible, instead of the usual 8-shaped patrol flight route 915.
  • the vehicle travels on a circular flight route 916 having a shape of a deformation 8.
  • the HAPS 10 flies in a banked state as shown in FIG. 12B so that the solar panel 102 on the upper surface of the main wing portion 101 faces the sun 900. I have to.
  • the HAPS 10 When the HAPS 10 flies on the cyclic flight routes 911 and 916 in FIGS. 11A, 11B, 12A, and 12B, the HAPS 10 is located in substantially the same area on the upper end surface of the cell formation target airspace 40 (see FIG. 1).
  • the beam direction and divergence angle (beam width) may be adjusted based on the bank (tilt) of the HAPS 10 so that the spots of three-dimensional cells having substantially the same size are located.
  • the HAPS 10 when the HAPS 10 is not inclined with respect to the horizontal direction H as shown in FIG. 13A, the HAPS 10 forms a beam 100 in the direction along the central axis C, and the HAPS 10 is in the horizontal direction H as shown in FIG.
  • the HAPS 10 adjusts the direction of the beam 100 from the central axis C in a direction tilted by the same angle ⁇ ′ as the angle ⁇ .
  • the above-described cell formation target airspace 40 (see FIG. 1) is based on the altitude change.
  • the divergence angle (beam width) of the beam 100 may be adjusted so that the spot size of the three-dimensional cell on the upper end surface of () is maintained at a predetermined size.
  • the beam formed by the HAPS 10 toward the cell formation target airspace 40 may be a single beam 100 as shown in FIGS. 13A and 13B, or a predetermined upper end surface of the cell formation target airspace 40 (see FIG. 1).
  • the HAPS 10 to 12 of the present embodiment charges the battery 106 by generating electric power by the rotation transmitted from the propeller 103 rotating by an air current or the like when the electric power is not supplied to the motor that is the rotation driving source of the propeller 103.
  • a regenerative energy supply means may be provided. This regenerative energy supply means can also serve as a motor that drives the propeller 103, for example.
  • FIG. 15A is an explanatory diagram illustrating an example of the ascending flight during the daytime of the solar plane type HAPS 10 of the embodiment
  • FIG. 15B is an explanatory diagram illustrating an example of the descending flight at night of the HAPS 10.
  • 15A and 15B show the ascending flight and the descending flight of the HAPS 10, but the same ascending flight and descending flight may be performed for the other HAPSs 11 and 12 described above.
  • the power generated by the solar panel 102 is supplied to the motor of the propeller 103 and the battery 106 so that the HAPS 10 is Raise in a spiral.
  • the HAPS 10 descends spirally in a glider mode using potential energy.
  • the electric power generated by the motor to which the rotation of the propeller 103 or the rotation of the propeller 103 due to the airflow flowing around the propeller 103 is transmitted to the battery 106 when the spiral lowering due to the weight of the HAPS 10 is supplied to the battery 106, and the battery 106 is charged.
  • the battery 106 can be charged by the regenerative energy from the propeller motor at night, the capacity of the battery 106 can be reduced and the amount of the battery 106 can be reduced.
  • the HAPS of this embodiment is driven in addition to charging the battery 106 by regenerative energy using the rotation of the propeller 103 when no power is supplied to the motor, or instead of charging the battery 106 by the regenerative energy.
  • the battery 106 may be charged with electric power (electric energy) generated by a wind turbine for power generation provided separately from the propeller 103 for use.
  • FIG. 16A and FIG. 16B are top views showing still other configuration examples of the HAPS 13 including the wind turbine 125 for power generation according to the embodiment.
  • symbol is attached
  • the HAPS 13 of FIG. 16A further includes a power generating windmill 125 and a generator 126 that generates power by the rotation transmitted from the power generating windmill 125 and charges the battery 106 at a front portion of the upper surface of the main wing portion 101 in the traveling direction. Yes.
  • the HAPS 13 in FIG. 16B further includes a power generation wind turbine 125 and a generator 126 that generates power by the rotation transmitted from the power generation wind turbine 125 and charges the battery 106 on the side surfaces at both ends in the longitudinal direction of the main wing portion 101. ing.
  • the power generation windmill 125 may be a horizontal axis windmill used in a state where the direction of the airflow (wind direction) and the rotation axis are substantially parallel, or the direction of the airflow (wind direction) and the rotation axis intersect. It may be a vertical axis windmill used in a state (a state of being substantially vertical).
  • the horizontal axis wind turbine may be a propeller type wind turbine having two or three blades, a multi-blade type wind turbine having four or more blades, a sail wing type wind turbine, or a Dutch type wind turbine.
  • Vertical wind turbines are cross-flow type wind turbines, Savonius type wind turbines in which the wind turbine cylinder is cut in half vertically and shifted in the circumferential direction, and vertical airfoil gyromill type wind turbines having the same cross section as the blades of the windmill airplane , A Darrieus-type windmill that is bent on an airfoil with the same cross section as the blade of a windmill airplane and attached to the vertical axis (rotary axis) Further, a tornado type windmill in which two upper and lower blades rotate in both directions may be used.
  • Power generation using the wind turbine 125 for power generation and charging of the battery 106 can be performed both when the propeller 103 is driven to rotate and when it is not driven.
  • the battery 106 can be charged with the electric power generated by the wind turbine 125 for power generation both when the HAPS rises in FIG. 15A and when the HAPS falls in FIG. 15B.
  • the capacity of the battery 106 can be reduced, It can be reduced.
  • the HAPS 10 to 13 of the present embodiment may include temperature difference power generation means for generating power by the temperature difference generated by the heat generation of the heat generating parts of the HAPS 10 to 13 and supplying the generated power to the battery 106.
  • FIG. 17 is an explanatory diagram showing a configuration example of a temperature difference power generation (exhaust heat power generation) system in the HAPS 10 of the embodiment.
  • FIG. 17 shows the HAPS 10, the other HAPS 11, 12, and 13 described above may include a similar temperature difference power generation (exhaust heat power generation) system.
  • the charge adjustment device (regulator) 145 generates heat when the power, voltage, or current output from the solar panel 102 is adjusted and supplied to the battery 106.
  • the wireless relay station 110 generates heat when operating with power supplied from the battery 106.
  • Thermoelectric elements as temperature difference power generation means for example, the temperature difference power generation means for converting the temperature difference generated between the surfaces of the charge adjustment device 145 and the wireless relay station 110, which are the heat generating parts, and the surrounding low temperature portion into electric power by the Seebeck effect (for example, , A spin Seebeck element and a Seebeck element (also referred to as “Peltier element”) 150 are provided on the surfaces of the charge adjustment device 145 and the wireless relay station 110, respectively.
  • thermoelectric element 150 may have a structure in which a P-type semiconductor and an N-type semiconductor are sandwiched by conductors.
  • the electric power output from the thermoelectric element 150 is supplied to the battery 106 via the charge adjustment device 145 and used for charging the battery 106.
  • the low temperature portion may be a portion in contact with the outside air of the HAPS that is air-cooled with the outside air during the movement of the HAPS.
  • the heat source provided with the thermoelectric element is a rotational drive source such as a motor that rotationally drives the propeller, a generator 126 connected to the wind turbine 125 for power generation, or It may be a power supply adjustment unit that adjusts the power supplied to the radio relay station 110 or the motor.
  • the heat generation source provided with the thermoelectric element 150 may be the solar panel 102 that receives sunlight during the day and becomes high temperature.
  • other temperature difference power generation means such as a Stirling engine power generation device may be used as the temperature difference power generation means provided in the heat generation source.
  • the Stirling engine power generator is, for example, a displacer type low temperature difference Stirling engine in which a displacer and a power piston move due to a temperature difference, or a two piston type in which two pistons move with a predetermined phase difference due to a temperature difference.
  • the low temperature difference Stirling engine may be used.
  • a heat pipe may be used as a heat conduction path between temperature difference power generation means heat such as the thermoelectric element 150 or the Stirling engine power generator and at least one of the high temperature part and the low temperature part.
  • FIG. 18 is a block diagram showing a configuration example of a power supply control system (energy management system) 140 in HAPS that can support power supply by a plurality of types of power generation methods (power generation systems).
  • the HAPS power supply control system 140 includes a bus power system power supply 141, a mission system power supply 142, a power supply adjustment device 143, a control unit 144, a charge adjustment device 145, and a control communication terminal device (for example, a mobile communication module).
  • the bus power system power supply 141 supplies power to a bus power system such as the propeller 103 driven by the motor 141a
  • the mission system power supply 142 supplies power to communication equipment (mission system) such as the radio relay station 110.
  • the power supply adjustment device 143 adjusts the power supplied to each of the bus power system power supply 141 and the mission system power supply 142 with respect to the power output from the battery 106.
  • the charge adjustment device 145 switches charging paths from the solar panel (solar power generation panel) 102, the thermoelectric element 150, and the motor 141a that supplies regenerative energy, which are a plurality of types of power generation methods (power generation systems). Change the combination of power generation methods (power generation systems), or adjust the power of each charging path.
  • the plurality of types of power generation methods (power generation systems) may include power generation by the power generator 126 connected to the power generation wind turbine 125, or may include the microwave power receiving unit 130.
  • the control unit 144 outputs power from the battery 106, adjusts power supply by the power supply adjustment device 143, outputs power from the bus power system power supply 141 and the mission system power supply 142, and outputs a plurality of power from the charge adjustment device 145. Controls the combination, switching and charge power adjustment of different types of power generation methods (power generation systems).
  • the control by the control unit 144 may be performed autonomously by a control program incorporated in the control unit 144 in advance, or transmitted from a remote control device 85 of a communication operator in a communication center provided on the ground or the like. You may perform based on the control information which comes.
  • the control in the power supply control system (energy management system) 140 in FIG. 18 is executed so as to perform efficient energy management by an algorithm according to the situation as follows.
  • the power supply adjustment device 143 adjusts and changes the balance between the power supplied to the bus power system and the power supplied to the mission system according to the situation. To do.
  • the altitude of the high-latitude HAPS is increased by accommodating the amount of power supplied from the mission system to the bus power system (see the above-described figure). 15A), and may be controlled so as to be stored as potential energy.
  • the supply amount to the bus power system is reduced, and the HAPS flight mode is controlled to shift to the glider mode using potential energy (see FIG. 15B described above). May be.
  • control unit 144 can control the external environment (for example, the amount of sunlight, air current, the number of surrounding HAPS, the number of connected terminal devices, by autonomous control or by control based on control information from the remote control device 85. Number), altitude, remaining battery power, power consumption of the wireless relay station 110, etc., a combination of multiple types of power generation methods (power generation systems), switching and charge power adjustment, folding solar panels (for example, The expansion and contraction of FIG. 10A and FIG. 10B) may be controlled.
  • the external environment for example, the amount of sunlight, air current, the number of surrounding HAPS, the number of connected terminal devices, by autonomous control or by control based on control information from the remote control device 85. Number
  • altitude for example, the amount of sunlight, air current, the number of surrounding HAPS, the number of connected terminal devices, by autonomous control or by control based on control information from the remote control device 85. Number
  • altitude for example, the amount of sunlight, air current, the number of surrounding HAPS, the number of connected terminal devices, by autonomous control or by control
  • the cell formation target airspace 40 in a predetermined altitude range (for example, an altitude range of 50 [m] or more and 1000 [m] or less) on the ground or the sea surface.
  • Wide-area three-dimensional cells 41 and 42 can be formed, and communication between a plurality of terminal devices located in the three-dimensional cells 41 and 42 and the mobile communication network 80 can be relayed.
  • the terminal devices and mobile communication networks located in the three-dimensional cells 41 and 42 are located at a lower altitude (for example, the stratospheric altitude) than the artificial satellites, the terminal devices and mobile communication networks located in the three-dimensional cells 41 and 42
  • the propagation delay in wireless communication with 80 is smaller than that in the case of satellite communication via an artificial satellite.
  • the three-dimensional cells 41 and 42 can be formed and the propagation delay of the wireless communication is low, a three-dimensional network for fifth generation mobile communication having a low propagation delay of the wireless communication can be realized.
  • the solar power generation function by the solar panel 102 is enhanced by using the bellows-like or wavy solar panel 102 or by controlling the flight route of the HAPS,
  • a temperature difference power generation (exhaust heat power generation) system By charging the battery 106 with regenerative energy or providing a temperature difference power generation (exhaust heat power generation) system, a three-dimensional network for fifth generation mobile communication with low propagation delay of wireless communication even in high latitude areas and at night Can be stably realized over a long period of time.
  • processing steps described in this specification and the components of the base station device in the radio relay station, feeder station, remote control device, terminal device (user device, mobile station, communication terminal) and base station of the radio relay device are as follows: Can be implemented by various means. For example, these steps and components may be implemented in hardware, firmware, software, or a combination thereof.
  • entity eg, wireless relay station, feeder station, base station device, wireless relay station device, terminal device (user device, mobile station, communication terminal), remote control device, hard disk drive device, or optical disk
  • processing units used to implement the above steps and components in the drive device
  • ASIC application specific IC
  • DSP digital signal processor
  • DSPD digital signal processor
  • PLD Programmable logic device
  • FPGA field programmable gate array
  • processor controller, microcontroller, microprocessor, electronic device, designed to perform the functions described herein
  • Other electronic units Yuta, or it may be implemented in a combination thereof.
  • firmware and / or software implementation means such as processing units used to implement the above components may be programs (eg, procedures, functions, modules, instructions) that perform the functions described herein. , Etc.).
  • any computer / processor readable medium that specifically embodies firmware and / or software code is means such as a processing unit used to implement the steps and components described herein. May be used to implement
  • the firmware and / or software code may be stored in a memory, for example, in a control device, and executed by a computer or processor.
  • the memory may be implemented inside the computer or processor, or may be implemented outside the processor.
  • the firmware and / or software code is, for example, random access memory (RAM), read only memory (ROM), nonvolatile random access memory (NVRAM), programmable read only memory (PROM), electrically erasable PROM (EEPROM) ), FLASH memory, floppy disk, compact disk (CD), digital versatile disk (DVD), magnetic or optical data storage, etc. Good.
  • the code may be executed by one or more computers or processors, and may cause the computers or processors to perform the functional aspects described herein.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Computer Networks & Wireless Communication (AREA)
  • Signal Processing (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • Astronomy & Astrophysics (AREA)
  • General Physics & Mathematics (AREA)
  • Radio Relay Systems (AREA)
  • Mobile Radio Communication Systems (AREA)

Abstract

La présente invention permet d'obtenir de façon stable, pendant une longue période de temps et quelles que soient les zones, un réseau tridimensionnel avec lequel, dans une communication mobile de cinquième génération, par exemple : le retard de propagation de la communication sans fil entre des dispositifs terminaux comprenant des dispositifs destinés à l'IdO est faible ; la connexion simultanée parmi un grand nombre de terminaux sur une large plage est possible ; une communication à grande vitesse est possible ; et une capacité de système par unité de surface est importante. Une station relais sans fil conçue pour relayer une communication sans fil avec un dispositif terminal est fournie à un corps flottant qui est commandé de façon à être situé dans un espace aérien flottant à une altitude ne dépassant pas 100 km, soit par une commande autonome soit par une commande à partir de l'extérieur, de façon à former une cellule tridimensionnelle dans un espace aérien cible prédéterminé de formation de cellule sur terre ou mer. Le corps flottant comporte des ailes sur lesquelles sont fixés des panneaux photovoltaïques solaires, et une hélice qui peut être entraînée en rotation par une source d'entraînement en rotation. Les ailes comprennent une section d'aile principale conçue pour produire principalement une flottabilité et une section d'aile auxiliaire sur laquelle les panneaux photovoltaïques solaires sont fixés à distance de la section d'aile principale, de façon à compléter la génération d'énergie solaire au niveau de la section d'aile principale.
PCT/JP2018/010666 2017-04-24 2018-03-17 Gestion de la récolte d'énergie dans le plan solaire Ceased WO2018198593A1 (fr)

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JP7142617B2 (ja) 2019-10-03 2022-09-27 Ｈａｐｓモバイル株式会社 システム、通信装置、プログラム、及び制御方法
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