CN115520390A - High-altitude wind energy application system utilizing electromagnetic induction principle - Google Patents

High-altitude wind energy application system utilizing electromagnetic induction principle Download PDF

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Publication number
CN115520390A
CN115520390A CN202211377976.1A CN202211377976A CN115520390A CN 115520390 A CN115520390 A CN 115520390A CN 202211377976 A CN202211377976 A CN 202211377976A CN 115520390 A CN115520390 A CN 115520390A
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China
Prior art keywords
aircraft
electromagnetic induction
coil
signal
fan
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Pending
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CN202211377976.1A
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Chinese (zh)
Inventor
周明洋
邵垒
熊伟
黎涛
揭东杭
冯俊杰
李茂月
仇成诚
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Chongqing Jiaotong University
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Chongqing Jiaotong University
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Priority to CN202211377976.1A priority Critical patent/CN115520390A/en
Publication of CN115520390A publication Critical patent/CN115520390A/en
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C39/00—Aircraft not otherwise provided for
    • B64C39/02—Aircraft not otherwise provided for characterised by special use
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64B—LIGHTER-THAN AIR AIRCRAFT
    • B64B1/00—Lighter-than-air aircraft
    • B64B1/58—Arrangements or construction of gas-bags; Filling arrangements
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/04—Helicopters
    • B64C27/08—Helicopters with two or more rotors
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
    • B64C27/26—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
    • F03D—WIND MOTORS
    • F03D9/00—Adaptations of wind motors for special use; Combinations of wind motors with apparatus driven thereby; Wind motors specially adapted for installation in particular locations
    • F03D9/20—Wind motors characterised by the driven apparatus
    • F03D9/25—Wind motors characterised by the driven apparatus the apparatus being an electrical generator
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
    • F03D—WIND MOTORS
    • F03D9/00—Adaptations of wind motors for special use; Combinations of wind motors with apparatus driven thereby; Wind motors specially adapted for installation in particular locations
    • F03D9/30—Wind motors specially adapted for installation in particular locations
    • F03D9/32—Wind motors specially adapted for installation in particular locations on moving objects, e.g. vehicles
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
    • H02J50/00—Circuit arrangements or systems for wireless supply or distribution of electric power
    • H02J50/10—Circuit arrangements or systems for wireless supply or distribution of electric power using inductive coupling
    • 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
    • Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
    • Y02E10/00—Energy generation through renewable energy sources
    • Y02E10/70—Wind energy
    • Y02E10/72—Wind turbines with rotation axis in wind direction

Abstract

The invention discloses a high-altitude wind energy application system utilizing an electromagnetic induction principle, which belongs to the field of high-altitude energy development and utilization and comprises a power generation aircraft, a signal receiving tower and a sensor group. The power generation aircraft takes a component connecting frame as a structural foundation, and the connecting frame is rigidly connected with the wings and the fan connecting rod. The invention relates to a high-altitude wind energy application scheme utilizing the electromagnetic induction principle, wherein a sensor module is arranged for the performance of each aspect of an aircraft to master the flight condition of a power generation aerostat, so as to ensure the normal operation of a system. In addition, the energy loss in the process of electric energy transmission is reduced to the maximum extent. Meanwhile, the Internet part in the invention can realize automatic control, simplifies the operation process, reduces the dependence on the working experience of operators and improves the operation efficiency of the aircraft in task execution.

Description

High-altitude wind energy application system utilizing electromagnetic induction principle
Technical Field
The invention relates to the field of high-altitude energy development and utilization, in particular to a high-altitude wind energy application system utilizing an electromagnetic induction principle.
Background
Wind energy refers to kinetic energy of air flow, belongs to renewable energy, and has the characteristics of cleanness, richness, wide distribution and greenhouse effect. With the assistance of modern science and technology, high-altitude wind energy can be utilized through the assistance of the permanent magnet motor and the power transmission mooring rope. In terms of the total amount of available development energy, the wind energy available and developed globally is 10 times as much as the water energy. Among abundant and inexhaustible wind energy, the high-altitude wind energy is stable all the year round, the stability is improved along with the increase of the height, and the advantage in the aspect of stability is obvious. Meanwhile, the conventional power generation mode depends on large-scale and high-cost power generation equipment, the utilization of natural resources is very limited, and the cost of the power generation equipment is seriously influenced by the influence of various factors such as terrain, disasters, loss, regional differences and the like, and the related problems are greatly avoided in high-altitude wind power generation.
In the current advanced high-altitude wind power devices in the world, the common mode is that an aerial floating power generation device draws power through a cable and finally conveys the power to a ground fixed development station. The conventional high-altitude wind energy conversion mode can efficiently utilize wind energy in the high altitude of about five hundred meters, but has a pain point problem: the airplane mooring rope drives the permanent magnet motor to generate electricity and transmit electricity to the generator on the ground, when the airplane mooring rope reaches a certain height, the electric energy transmission mode of the generator recovery rope puts high requirements on the working environment of the floating air bag, and the special weather environment can cause great impact on the stability and efficiency of power transmission, so that the high-altitude wind energy cannot be utilized to the maximum extent. In addition, although the cable used in the conventional power transmission mode is made of high-strength and high-toughness material, it still cannot be effectively protected in special weather situations, and once the cable is damaged, the whole cable needs to be replaced, which results in waste of resources. Therefore, a new and efficient power transmission method is needed to replace the prior art to achieve a safe and efficient overhead power transmission process.
Chinese patent CN106150915A discloses an aerial wind power generation system based on an unmanned aerial vehicle platform, which mainly comprises a ground generator, an unmanned aerial vehicle and a mooring rope for power transmission, wherein the unmanned aerial vehicle is driven to ascend and fly at a large attack angle, an airplane cable drives a permanent magnet motor to generate power and transmit power to the ground generator, and the generator recovers the rope after reaching a certain height; the high-altitude power generation system can only supply power to a fixed ground base station, and the power supply range is limited. In addition, this system uses unmanned aerial vehicle to carry out the power transmission, has used conventional sensor system, does not adjust required sensor system according to the high altitude construction environment, can't guarantee that unmanned aerial vehicle accomplishes power transmission work safely under the special circumstances.
Chinese patent CN207459825U discloses an emergency rescue vehicle, which is provided with a solar folding sailboard mechanism and a data retention system and can be used as a temporary power station for emergency rescue. As a temporary power station, the emergency rescue vehicle is high in speed and accurate in positioning, and can quickly reach a target site to complete a power supply task. However, the return trip and the power generation coverage become problematic due to limitations in the size of the power generation cars, the efficiency of the on-board power generation devices, and the terrain of the area.
The invention provides a high-altitude wind energy application system utilizing the electromagnetic induction principle, so as to solve the above-mentioned problems.
Disclosure of Invention
The invention aims to provide a high-altitude wind energy application system utilizing the electromagnetic induction principle so as to solve the problems in the background technology.
In order to achieve the purpose, the invention provides the following technical scheme:
a high-altitude wind energy application system utilizing the electromagnetic induction principle comprises a power generation aircraft, a signal receiving tower and a sensor group. The power generation aircraft takes a component connecting frame as a structural foundation, and the connecting frame is rigidly connected with the wings and the fan connecting rod. The upper surface of the wing is provided with a tail wing and a rotor wing which are respectively used for controlling the attitude of the aircraft and providing additional lift force. The motor is equipped with to rotor lower extreme for control rotor. The fan is installed at the front end of the fan connecting rod, the fan rotates to generate power under the blowing of high-altitude strong wind, and the fan is connected with the fan connecting rod through a hexagon bolt. The fan is externally covered with a helium gas bag which provides the main lift force for the aircraft. The rear end of the component connecting frame is provided with a first device box body and a second device box body, the first device box body comprises an electromagnetic coil for electromagnetic induction transmission of electric energy, a main control chip and a sensor system for electromagnetic signal control, and a power transmission wire for transmitting the electric energy generated by the generator to the coil. The second device box comprises an alternating current generator, an input electrode and a voltage-stabilizing power supply line. The signal receiving tower comprises an insulating pipeline, a connecting shaft, a shaft support, a coil conveying electrode, a coil fixing plate, an electromagnetic coil and a signal box at the bottom. And the coil fixing plate is arranged on the pipe wall of the insulated pipeline and is used for installing an electromagnetic induction coil, and the induction voltage generated by the electromagnetic induction coil is transmitted to the signal box at the bottom through a loop. The power generation principle is that the fan rotates under the blowing of high-altitude strong wind, the generated mechanical energy is converted into an alternating current signal through the alternating current generator and is transmitted to the coil of the first device box through the electric wire, the alternating current signal is generated in the coil, electromagnetic induction is generated between the alternating current signal and a large-scale electromagnetic coil of the signal tower, and voltage is further generated in the coil of the signal tower. In addition, the generated voltage is transmitted to a signal box at the bottom end of the tower through a closed loop formed in the signal tower, so that the transmission of electric energy is completed.
The working principle of the technical scheme is as follows:
electric energy is generated by the generating aircraft. The power generation aircraft takes a component connecting frame as a structural foundation, and the connecting frame is rigidly connected with the wings and the fan connecting rod. The upper surface of the wing is provided with an empennage and a rotor wing which are respectively used for controlling the attitude of the aircraft and providing additional lift force. The motor is equipped with to rotor lower extreme for control rotor. The fan is installed at the front end of the fan connecting rod, the fan rotates to generate power under the blowing of high-altitude strong wind, and the fan is connected with the fan connecting rod through a hexagon bolt. The helium gas bag covers the fan, provides main lift for the aircraft, satisfies the aircraft demand of working for a long time.
As a further scheme of the invention: the rear end of the component connecting frame is provided with a first device box body and a second device box body placing groove, and the first device box body comprises an electromagnetic coil for electromagnetic induction transmission of electric energy, a main control chip and a sensor system for electromagnetic signal control and a power transmission wire for transmitting the electric energy generated by the generator to the coil. The second device box comprises an alternating current generator, an input electrode and a voltage-stabilizing power supply line. The fan rotates under the blowing of high-altitude strong wind, and the alternating-current generator can convert the generated mechanical energy into electric energy through the alternating-current generator.
As a further scheme of the invention: the lower end of the component connecting frame is connected with a landing gear connecting shaft. The undercarriage connecting shaft comprises an undercarriage bottom plate, a self-locking pulley limiting block and a self-locking pulley, and the undercarriage device is used for ensuring stable posture of the aircraft during landing and further ensuring the requirement of safe work.
As a further scheme of the invention: the signal receiving tower comprises an insulating pipeline, a connecting shaft, a shaft support, a coil conveying electrode, a coil fixing plate, an electromagnetic coil and a signal box at the bottom. The shaft support is arranged at the bottom end inside the signal receiving tower and used for stabilizing the structure, the lower end of the connecting shaft is arranged in the shaft support, and the upper end of the connecting shaft is connected with the insulating pipeline. The insulating pipeline is used for preventing the safety problem caused by overhigh voltage generated by electromagnetic induction. The coil fixing plate is installed on the wall of the insulating pipeline and used for installing an electromagnetic induction coil, and induction voltage generated by the electromagnetic induction coil is transmitted to the signal box at the bottom through a loop.
As a further scheme of the invention: the signal box comprises a PCB, a signal control board, a driving chip, a power element and a resistance-capacitance device. The use of said electrical components ensures the proper functioning of the circuit transmission.
As a further scheme of the invention: the sensor group is by the rain gauge that is used for monitoring the outside precipitation situation of aircraft, the hygrometer, and wet bulb thermometer, a barometer for monitoring the aircraft receives the wind pressure situation, the anemograph, wind vane and anemograph, a gyroscope for monitoring aircraft gesture steady state, altimeter and spirit level, a tachometer and passageway vibrations detector for monitoring the inside steady state of aircraft, a lightning locator for monitoring aircraft position and to data overall planning processing, airspeed meter and central control treater and be used for monitoring the special air current situation of aircraft, lightning-arrest equipment and current detector. In addition, the sensor group also comprises a directional transmission sensor and a signal amplifier, so that the accurate transmission of electromagnetic signals can be ensured, and the high level of the transmission efficiency is ensured.
Finally, the principle of high-altitude wind energy application and transmission is explained. The fan rotates under the blowing of high-altitude strong wind, the generated mechanical energy is converted into an alternating current signal through the alternating current generator and is transmitted to the coil of the first device box through the electric wire, the alternating current signal is generated in the coil, electromagnetic induction is generated between the alternating current signal and a large-scale electromagnetic coil of the signal tower, and voltage is further generated in the coil of the signal tower. In addition, the generated voltage is transmitted to a signal box at the bottom end of the tower through a closed loop formed in the signal tower, so that the transmission of electric energy is completed.
Compared with the prior art, the invention has the beneficial effects that:
1. the invention utilizes the high-altitude wind energy application scheme of the electromagnetic induction principle, and sets a sensor module for the performance of each aspect of the aircraft to master the flight condition of the power generation aerostat and ensure the normal operation of the system. In addition, a directional power transmission sensor is applied to the sensor module, so that electromagnetic induction power transmission is directional, and energy loss in the electric energy transmission process is reduced to the greatest extent. Not only can the Internet part in the invention realize automatic control, simplify the operation process, reduce the dependence on the working experience of operators and improve the operation efficiency of the aircraft in task execution.
2. According to the high-altitude wind energy application scheme based on the electromagnetic induction principle, by applying the electromagnetic induction principle, the traditional high-altitude cable transmission is changed into electromagnetic coil conduction, so that the defects of resource waste and insufficient power supply stability caused by special weather conditions when high-altitude wind energy is utilized are overcome. In addition, the aircraft replaces a floating air bag to generate power, so that the degree of freedom of an aerial operation unit is improved, and the continuity and the stability of the high-altitude power generation process are further ensured.
Drawings
FIG. 1 is a schematic view of the main structure of an aircraft according to embodiment 1 of the invention;
FIG. 2 is an enlarged partial view of an airbag for an aircraft according to embodiment 1 of the present invention;
FIG. 3 is an enlarged partial view of the aircraft landing gear structure according to embodiment 1 of the present invention;
FIG. 4 is an internal structure view of an electrical storage box of an aircraft according to embodiment 1 of the invention;
fig. 5 is a schematic diagram of a transmission device of a signal receiving tower according to embodiment 2 of the present invention;
fig. 6 is a sectional view showing an internal structure of a signal receiving tower according to embodiment 2 of the present invention;
FIG. 7 is a schematic diagram of the system of embodiment 3 for generating power and transmitting signals by electromagnetic induction;
fig. 8 is a diagram of components of a sensor system according to embodiment 4 of the present invention.
Description of reference numerals:
1. an airfoil; 2. a helium gas bladder; 3. a rotor; 4. a motor; 5. a tail wing; 6. a first loading box placing groove; 7. a second loading box loading groove; 8. a fan connecting rod; 9. a fan; 10. a connecting frame; 11. a rigid hexagon bolt; 12. a landing gear connecting shaft; 13. a landing gear chassis; 14. a self-locking pulley limiting block; 15. a self-locking pulley; 16. a first loading compartment; 17. a second loading bin; 18. an electromagnetic signal receiving tower; 19. a signal box; 20. a coil delivery electrode; 21. a coil fixing plate; 22. an alternator; 23. an alternating current signal; 24. a power transmission cable; 101. a rain gauge; 102. a hygrometer; 103. a wet and dry bulb thermometer; 104. a barometer; 161. an electromagnetic coil; 162. a main control chip; 163. a sensor system; 164. a power transmission wire; 171. a generator input electrode; 172. a voltage stabilizing power supply line; 181. an insulated pipe; 182. a connecting shaft; 183. a shaft support; 191. a PCB board; 192. a signal control board; 193. a driver chip; 194. a power element; 195. a resistance-capacitance device; 201. an anemometer; 202. a wind vane; 203. an anemometer; 301. a gyroscope; 302. an altimeter. 303. A level gauge; 401. a tachometer; 402. a channel vibration detector; 501. a GPS locator; 502. an airspeed meter; 503. a central control processor; 601. a lightning locator; 602. lightning protection equipment; 603. a current detector; 701. a directional transmission sensor; 702. a signal amplifier.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Example 1:
as shown in fig. 1-4, a high altitude wind energy application scheme using electromagnetic induction principle includes a power generation aircraft, a signal receiving tower 18 and a sensor group 163, wherein the power generation aircraft uses a component connection frame 10 as a structural foundation, and the connection frame 10 rigidly connects a wing 1 and a fan connection rod 8. The upper surface of the wing 1 is provided with a tail wing 5 and a rotor wing 3 which are respectively used for controlling the attitude of the aircraft and providing additional lift force. The lower end of the rotor wing 3 is provided with a motor 4 for controlling the rotor wing 4. The front end of the fan connecting rod 8 is provided with a fan 9, the fan 9 rotates to generate power under the blowing of high-altitude strong wind, and the fan 9 is connected with the fan connecting rod 8 through a hexagon bolt 11. The helium airbag 2 covers the outside of the fan 9, and the helium airbag 2 provides main lift force for the aircraft, so that the long-time working requirement of the aircraft is met.
The rear end of the component connecting frame 10 is provided with a first and a second device box accommodating groove, and the first device box 16 includes an electromagnetic coil 161 for electromagnetic induction transmission of electric energy, a main control chip 162 and a sensor system 163 for electromagnetic signal control, and a transmission wire 164 for transmitting the electric energy generated by the generator to the coil. The second device case 17 includes the alternator 22, the input electrode 171, and the voltage-stabilizing power supply line 172 therein. The fan 9 rotates under the blowing of high-altitude strong wind, and the alternator 22 can convert the generated mechanical energy into electric energy through the alternator.
In addition, the lower end of the member link 10 is connected to a landing gear link shaft 12. The landing gear connecting shaft 12 comprises a landing gear bottom plate 13, a self-locking pulley limiting block 14 and a self-locking pulley 15, and the landing gear device is used for ensuring the stable posture of the aircraft during landing and further ensuring the safe working requirement.
Example 2:
as shown in fig. 5 to 6, the signal receiving tower 18 includes an insulating pipe 181, a connecting shaft 182, a shaft support 183, a coil feeding electrode 20, a coil fixing plate 21, an electromagnetic coil 161, and a bottom signal box 19. A shaft support 183 is installed at the bottom end inside the signal receiving tower 18 for stabilizing the structure, and a connecting shaft 182 has a lower end installed in the shaft support 183 and an upper end connected to the insulating pipe 181. The insulating pipe 181 is used to prevent a safety problem caused by an excessively high voltage generated by electromagnetic induction. The coil fixing plate 21 is installed on the wall of the insulating pipe 181, and is used for installing the electromagnetic induction coil 161, and the induced voltage generated by the electromagnetic induction coil 161 is transmitted to the signal box 19 at the bottom through a loop. The signal box comprises a PCB board 191, a signal control board 192, a driving chip 193, a power element 194 and a resistance-capacitance device 195. The use of electrical components ensures proper operation of the circuit transmission.
Example 3:
as shown in fig. 7. The fan 9 rotates under the blowing of high-altitude strong wind, the generated mechanical energy is converted into an alternating current signal 23 through the alternating current generator 22 and is transmitted to the coil 161 of the first device box through a wire, the alternating current signal 23 is generated in the coil 161, meanwhile, electromagnetic induction is generated between the alternating current signal and the large-scale electromagnetic coil 161 of the signal tower 18, and voltage is further generated in the coil 161 of the signal tower 18. In addition, the generated voltage is transmitted to a signal box 19 at the bottom end of the tower through a closed loop formed in the signal tower 18, thereby completing the transmission of electric energy.
Example 4:
as shown in fig. 8. The sensor group comprises a rain gauge 101, a hygrometer 102 and a wet and dry bulb thermometer 103 for monitoring the precipitation condition outside the aircraft, a barometer 104, an anemometer 201, a wind vane 202 and a anemometer 203 for monitoring the wind pressure condition of the aircraft, a gyroscope 301, an altimeter 302 and a level meter 303 for monitoring the attitude stability condition of the aircraft, a tachometer 401 and a channel vibration detector 402 for monitoring the stability condition inside the aircraft, a GPS locator 501, an airspeed meter 502 and a central control processor 503 for monitoring the position of the aircraft and performing overall processing on data, and a lightning locator 601, a lightning arrester 602 and a current detector 603 for monitoring the special airflow condition of the aircraft. In addition, the sensor group further comprises a directional transmission sensor 701 and a signal amplifier 702, so that accurate transmission of electromagnetic signals can be ensured, and the transmission efficiency is ensured to be at a high level.
The working principle of the technical scheme is as follows:
the high-altitude wind energy application scheme utilizing the electromagnetic induction principle comprises a power generation aircraft, a signal receiving tower 18 and a sensor group 163. The power generation aircraft takes a component connecting frame 10 as a structural foundation, and the connecting frame 10 rigidly connects the wing 1 and the fan connecting rod 8. The upper surface of the wing 1 is provided with a tail wing 5 and a rotor wing 3 which are respectively used for controlling the attitude of the aircraft and providing additional lift force. The lower end of the rotor 3 is provided with a motor 4 for controlling the rotor 3. The front end of the fan connecting rod 8 is provided with a fan 9, the fan 9 rotates to generate power under the blowing of high-altitude strong wind, and the fan 9 is connected with the fan connecting rod 8 through a hexagon bolt 11. The fan 9 is externally covered with a helium gas bag 2, and the helium gas bag 2 provides the main lifting force for the aircraft. The rear end of the component connecting frame 10 is provided with a first and a second device box accommodating grooves, and the first device box 16 comprises an electromagnetic coil 161 for transmitting electric energy through electromagnetic induction, a main control chip 162 and a sensor system 163 for controlling electromagnetic signals, and a power transmission wire 164 for transmitting the electric energy generated by the generator to the coil. The second device case 17 includes therein the alternator 22, the input electrode 171, and the regulated power supply line 172. The signal receiving tower 18 includes an insulating pipe 181, a connecting shaft 182, a shaft support 183, a coil feeding electrode 20, a coil fixing plate 21, an electromagnetic coil 161, and a signal box 19 at the bottom. The coil fixing plate 21 is installed on the wall of the insulating pipe 181 and is used for installing the electromagnetic induction coil 161, and the induced voltage generated by the electromagnetic induction coil 161 is transmitted to the signal box 19 at the bottom through a loop. The power generation principle is that the fan 9 rotates under the blowing of high-altitude strong wind, the generated mechanical energy is converted into an alternating current signal 23 through the alternating current generator 22 and is transmitted to the coil 161 of the first device box 16 through the electric wire 24, the alternating current signal 23 is generated in the coil 161, meanwhile, electromagnetic induction is generated with the large-scale electromagnetic coil 161 of the signal tower 18, and further voltage is generated in the coil 161 of the signal tower 19. In addition, the generated voltage is transmitted to a signal box 19 at the bottom end of the tower through a closed loop formed in the signal tower, thereby completing the transmission of electric energy.
It will be evident to those skilled in the art that the invention is not limited to the details of the foregoing illustrative embodiments, and that the present invention may be embodied in other specific forms without departing from the spirit or essential attributes thereof. The present embodiments are therefore to be considered in all respects as illustrative and not restrictive, the scope of the invention being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein.
Furthermore, it should be understood that although the present description refers to embodiments, not every embodiment may contain only a single embodiment, and such description is for clarity only, and those skilled in the art should integrate the description, and the embodiments may be combined as appropriate to form other embodiments understood by those skilled in the art.

Claims (9)

1. A high-altitude wind energy application system utilizing an electromagnetic induction principle is characterized by comprising a power generation aircraft, a signal receiving tower and a sensor group;
the aircraft is used for generating electric energy and transmitting the electric energy to the signal receiving tower in an electromagnetic induction mode;
the signal receiving tower is used for receiving electric energy generated by the aircraft;
and the sensor group is arranged on the aircraft and used for detecting various parameters of the aircraft and transmitting the parameters to the control center.
2. The high altitude wind energy application system utilizing electromagnetic induction principle of claim 1, characterized in that, the electricity generation aircraft uses the component link as the structure basis, the link rigid coupling wing and fan connecting rod, wing upper surface is equipped with fin and rotor, the motor that is used for controlling the rotor is equipped with to the rotor lower extreme, fan that is used for rotating the electricity generation under the blowing of high altitude high strength wind is installed to fan connecting rod front end, passes through hexagon bolt connection between fan and the fan connecting rod, the fan outside covers there is the helium gasbag that is used for providing main lift for the aircraft.
3. The high altitude wind energy application system based on electromagnetic induction principle as claimed in claim 2, wherein the rear end of the component connection frame is provided with a first device box body and a second device box body, the first device box body comprises an electromagnetic coil for electromagnetic induction transmission of electric energy, a main control chip and a sensor system for electromagnetic signal control, and a transmission wire for transmission of electric energy generated by the generator to the coil, and the second device box body comprises an alternating current generator, an input electrode and a voltage-stabilizing power supply wire.
4. The high altitude wind energy application system based on the electromagnetic induction principle as claimed in claim 3, wherein the lower end of the member connecting frame is connected with an undercarriage connecting shaft, and the undercarriage connecting shaft comprises an undercarriage bottom plate, a self-locking pulley limiting block and a self-locking pulley.
5. The system for applying high altitude wind energy by utilizing the electromagnetic induction principle as claimed in claim 4, wherein the fan rotates under the blowing of high altitude strong wind, the generated mechanical energy is converted into alternating current signals by the alternating current generator and transmitted to the coil of the first device box through the electric wire, the alternating current signals are generated in the coil, electromagnetic induction is generated between the alternating current signals and the large scale electromagnetic coil of the signal tower, voltage is further generated in the coil of the signal tower, and the generated voltage is transmitted to the signal box at the bottom end of the tower through the closed loop formed in the signal tower, so that the transmission of the electric energy is completed.
6. The high altitude wind energy application system using electromagnetic induction principle as claimed in claim 1, wherein said signal receiving tower comprises an insulated pipe, a connecting shaft, a shaft support, a coil transmission electrode, a coil fixing plate, an electromagnetic coil and a bottom signal box, the lower end of said connecting shaft is mounted in the shaft support, the upper end of said connecting shaft is connected with the insulated pipe, said coil fixing plate is mounted on the wall of said insulated pipe, and the induced voltage generated by said electromagnetic induction coil is transmitted to the bottom signal box through a loop.
7. The high altitude wind energy utilization system based on the electromagnetic induction principle as claimed in claim 6, wherein the signal box comprises a PCB, a signal control board, a driving chip, a power element and a resistance-capacitance device.
8. The system of claim 1, wherein the sensors comprise a rain gauge, a hygrometer and a wet and dry bulb thermometer for monitoring the external precipitation status of the aircraft, a barometer, an anemometer, a wind vane and a anemometer for monitoring the wind pressure status of the aircraft, a gyroscope, an altimeter and a level meter for monitoring the attitude stability status of the aircraft, a tachometer and a channel vibration detector for monitoring the internal stability status of the aircraft, a GPS locator, an airspeed meter and a central control processor for monitoring the position of the aircraft and performing overall data processing, and a lightning locator, a lightning arrester and a current detector for monitoring the special airflow status of the aircraft.
9. The high altitude wind energy utilization system utilizing electromagnetic induction principle as claimed in claim 8, wherein said sensor group further includes a directional transmission sensor and a signal amplifier.
CN202211377976.1A 2022-11-04 2022-11-04 High-altitude wind energy application system utilizing electromagnetic induction principle Pending CN115520390A (en)

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