CN111422343A - Special unmanned aerial vehicle of half aviation transition electromagnetic detection receiving system - Google Patents
Special unmanned aerial vehicle of half aviation transition electromagnetic detection receiving system Download PDFInfo
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- CN111422343A CN111422343A CN202010243335.1A CN202010243335A CN111422343A CN 111422343 A CN111422343 A CN 111422343A CN 202010243335 A CN202010243335 A CN 202010243335A CN 111422343 A CN111422343 A CN 111422343A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/061—Frames
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plant in aircraft; Aircraft characterised thereby
- B64D27/02—Aircraft characterised by the type or position of power plant
- B64D27/24—Aircraft characterised by the type or position of power plant using steam, electricity, or spring force
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D47/00—Equipment not otherwise provided for
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/19—Propulsion using electrically powered motors
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01V—GEOPHYSICS; GRAVITATIONAL MEASUREMENTS; DETECTING MASSES OR OBJECTS; TAGS
- G01V3/00—Electric or magnetic prospecting or detecting; Measuring magnetic field characteristics of the earth, e.g. declination, deviation
- G01V3/08—Electric or magnetic prospecting or detecting; Measuring magnetic field characteristics of the earth, e.g. declination, deviation operating with magnetic or electric fields produced or modified by objects or geological structures or by detecting devices
- G01V3/10—Electric or magnetic prospecting or detecting; Measuring magnetic field characteristics of the earth, e.g. declination, deviation operating with magnetic or electric fields produced or modified by objects or geological structures or by detecting devices using induction coils
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
- H01M50/00—Constructional details or processes of manufacture of the non-active parts of electrochemical cells other than fuel cells, e.g. hybrid cells
- H01M50/20—Mountings; Secondary casings or frames; Racks, modules or packs; Suspension devices; Shock absorbers; Transport or carrying devices; Holders
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- 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
- Y02E60/00—Enabling technologies; Technologies with a potential or indirect contribution to GHG emissions mitigation
- Y02E60/10—Energy storage using batteries
Abstract
The invention discloses a special unmanned aerial vehicle for a semi-aviation transient electromagnetic detection receiving system, which comprises: the coil receiving device comprises an air-core frame, a coil receiving cabin and a coil processing system, wherein the air-core frame is provided with a plurality of arms, the end part of each arm is provided with a power system, and the middle of the air-core frame is provided with the coil receiving cabin for accommodating a split type receiving coil; the power system comprises a rotor shaft, an insulating wing and a double-layer motor which are coaxially distributed, wherein the insulating wing is divided into an upper layer and a lower layer which are connected to the rotor shaft; the inner-layer motor and the outer-layer motor of the double-layer motor are opposite in rotating direction and used for eliminating electromagnetic signal interference generated when the inner rotor rotates, and the insulating wing cannot generate electromagnetic interference due to cutting of magnetic induction lines.
Description
Technical Field
The invention belongs to the technical field of exploration, and particularly relates to a special unmanned aerial vehicle for a semi-aviation transient electromagnetic detection receiving system.
Background
The statements in this section merely provide background information related to the present disclosure and may not necessarily constitute prior art.
The semi-aviation transient electromagnetic method has the advantages that the excitation source is placed on the ground surface, and a man-machine or unmanned-machine mounted receiving device is used for acquiring transient response in the air, so that the semi-aviation transient electromagnetic method integrates the advantages of a ground transient electromagnetic method and an aviation transient electromagnetic method, has the characteristics of high signal-to-noise ratio, flexibility, high efficiency, large detection depth and the like of acquired data, can be suitable for areas with complex geological and topographic conditions such as alpine regions, high-altitude mountain regions, deserts, gobi, forest coverage areas, karst development areas and the like, and has a wider application range compared with other exploration methods.
However, the inventor finds in research that, during the existing semi-aviation transient electromagnetic acquisition, a transient electromagnetic receiving coil is suspended below the unmanned aerial vehicle through a cable, so as to avoid the influence of the unmanned aerial vehicle system on the transient electromagnetic signal (the transient electromagnetic receiving coil is directly placed on the unmanned aerial vehicle, and there is a problem of the influence of the unmanned aerial vehicle on the transient electromagnetic signal during operation).
At present, a helicopter system and an unmanned aerial vehicle system are all mounted with a receiving coil through flexible connection and are issued by an airplane, a rope is generally adopted for mounting, the helicopter system is generally mounted below the airplane by about 100 plus 130m, and the unmanned aerial vehicle system is generally mounted below the airplane by about 5-10 m.
This mounting method brings about a number of problems:
1. there is the error in aircraft location and receiving coil location, and the error is unfixed, because flight in-process aircraft turn etc. can cause the speed to change, and this distance also can change, causes unmanned aerial vehicle location and coil location inaccurate, and then influences the location problem in the data processing in later stage.
2. Through the flexible coupling carry, cause receiving coil's rocking, sway etc. easily, the gesture of coil can produce great change, leads to the magnetic flux of passing through in the coil constantly to produce the change, finally makes the quality variation of data of gathering can't gather accurate signal even, need increase extra sensor and just can gather these gesture information to the analysis is complicated.
3. Unmanned aerial vehicle's load is limited, and at aircraft turn etc. in-process, can produce great centrifugal force, make the coil (heavier) of carry in the below produce outside power down to relatively fixed position when the skew steadily flies, in case turn too fiercely, cause the aircraft to fall into the air easily.
4. The heavy object hung below the airplane is easy to hang down due to hanging on external objects such as trees and the like.
5. The heavy objects are hung below the airplane, the operation is very complicated, the requirement on operators is high, and accidents are easy to happen.
Disclosure of Invention
In order to overcome the defects of the prior art, the invention provides the special unmanned aerial vehicle for the semi-aviation transient electromagnetic detection receiving system, which can improve the safety of the semi-aviation transient electromagnetic acquisition system while ensuring the quality of received data.
In order to achieve the above object, one or more embodiments of the present invention provide the following technical solutions:
the utility model provides a special unmanned aerial vehicle of half aviation transition electromagnetic detection receiving system, adopts many rotor unmanned aerial vehicle, includes:
the coil receiving device comprises an air-core frame, a coil receiving cabin and a coil processing system, wherein the air-core frame is provided with a plurality of arms, the end part of each arm is provided with a power system, and the middle of the air-core frame is provided with the coil receiving cabin for accommodating a split type receiving coil;
the power system comprises a rotor shaft, an insulating wing and a double-layer motor which are coaxially distributed, wherein the insulating wing is divided into an upper layer and a lower layer which are connected to the rotor shaft;
the inner-layer motor and the outer-layer motor of the double-layer motor are opposite in rotating direction and used for eliminating electromagnetic signal interference generated when the inner rotor rotates, and the insulating wing cannot generate electromagnetic interference due to cutting of magnetic induction lines.
According to a further technical scheme, the power system further comprises a flight control unit which is communicated with the double-layer motor and used for automatic flight control of the unmanned aerial vehicle.
Further technical solution, the coil storage compartment includes: the coil receiving groove is internally provided with the coil anti-skidding damping pad, and the coil receiving groove is uniformly provided with a plurality of coil fixing lock catches for fixing the split type receiving coil.
In a further technical solution, the split receiving coil includes: coil shell, internal coil and upper cover, coil shell and upper cover are connected fixedly, and the inside standing groove that is equipped with of coil shell places the internal coil of different turns and different materials according to the different demands of surveying.
According to a further technical scheme, a data transmission port is arranged on the coil cover and is used for being connected with the internal coil data transmission port to transmit data of the internal coil.
According to a further technical scheme, a signal receiving and recording module, a signal synchronization module, a signal storage module, a data simultaneous transmission module, a coil posture recording module and a control module are integrated in a coil shell;
the control module sets various parameters of signal receiving, including fundamental frequency of signal acquisition, gain multiple of signal acquisition and signal acquisition mode;
the signal receiving and recording module receives the set parameters, starts to collect electromagnetic signals and collects flight attitude information by using the coil attitude recording module;
the signal storage module is used for transmitting the acquired electromagnetic signals and the attitude information to signals for storage;
the signal synchronization module is synchronized with the transmitter through a GPS (global positioning system) so as to ensure normal operation of electromagnetic signal receiving;
and the data simultaneous transmission module is used for transmitting the acquired electromagnetic signals and the attitude information to the ground station in real time.
According to the further technical scheme, radiating holes are distributed in the side face of the hollow rack, and the air intake is guaranteed to meet the radiating requirements of internal components during flying.
According to the technical scheme, a battery cabin is arranged on the horn of the hollow rack and comprises a battery shock pad, a battery accommodating groove and a battery cabin cover, wherein the battery shock pad is arranged in the battery accommodating groove, and the battery accommodating groove is covered by the battery cabin cover.
According to the further technical scheme, a circle of rubber pad is fixed inside the battery hatch cover which is in contact with the battery, and the battery cannot be exposed after the hatch cover is fastened.
In another aspect of the present invention, a semi-airborne transient electromagnetic detection system is disclosed, comprising:
the system comprises semi-aviation transient electromagnetic detection receiving equipment, a ground station and a transmitter;
the ground station control transmitter transmits signals, the signals are transmitted to the semi-aviation transient electromagnetic detection receiving equipment through the GPS, the split type receiving coil of the semi-aviation transient electromagnetic detection receiving equipment acquires electromagnetic signals, and the acquired electromagnetic signals and attitude information are transmitted to the ground station in real time.
The above one or more technical solutions have the following beneficial effects:
this unmanned aerial vehicle's components and parts are all fixed inside high strength light hollow frame through hasp or support, and the louvre is all laid in the frame side, guarantees the intake in order to satisfy the heat dissipation demand of inside components and parts when flying to close a whole set of receiving arrangement and unmanned aerial vehicle as an organic whole.
The two pairs of wings are divided into two layers and are connected to a rotor shaft through a lock catch, and the installation directions of the two pairs of wings are opposite; when the unmanned aerial vehicle flies, the inner layer and outer layer rotating directions of the coaxial double-layer motor are opposite, so that electromagnetic signal interference generated when the inner rotor rotates is eliminated, and electromagnetic interference generated by cutting a magnetic induction line can be avoided by the high-strength insulating wing;
the coil anti-skidding damping pad disclosed by the invention is made of a material with good elasticity and a memory function, is soft in surface, large in friction coefficient and strong in friction force, and can provide enough protection for a receiving coil; the coil fixing lock catch adopts a soft leather lock catch, so that the coil can be fixed, and the damage of the hard lock catch to the appearance of the coil can be avoided;
the battery shock pad disclosed by the invention adopts a circle of rubber pad which is made of a slightly hard material, so that the battery can be protected, the stability of connection between the battery and the unmanned aerial vehicle can be ensured, and a power source is continuously provided for the unmanned aerial vehicle; the battery hatch cover is made of high-strength materials the same as that of the rack, a circle of rubber pad is fixed inside the battery hatch cover which is in contact with the battery, and the battery cannot be exposed after the hatch cover is fastened.
The coil main body and the coil upper shell of the split type coil are of split type structures, can be opened at any time to replace an internal coil, can also be used for placing a fluxgate and the like to receive signals, and can be used for replacing the internal coil or other signal receivers according to field exploration requirements and data requirements at any time.
This is disclosed with signal reception record module, signal synchronization module, signal storage module, data are with biography module, coil gesture record module and control module are whole to be integrated to split type coil's centre, and the modularization combination is easily dismantled, changes easily, has changed the disconnect-type structure of coil and receiver in the past, though increased the degree of difficulty of after-repair maintenance, but the integral type structure makes to carry more convenient, and the reduction of weight also makes it be applicable to the unmanned aerial vehicle that original load is just not high more.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this specification, are included to provide a further understanding of the invention, and are incorporated in and constitute a part of this specification, illustrate exemplary embodiments of the invention and together with the description serve to explain the invention and not to limit the invention.
FIG. 1 is a block diagram of an apparatus of the present disclosure;
FIG. 2 is a diagram of a coaxial double layer motor of the present disclosure;
FIG. 3 is a coaxial bi-directional rotor shaft diagram of the present disclosure;
fig. 4 is a split receiver coil diagram of the present disclosure;
wherein: 1. the high-strength light hollow rack comprises a high-strength light hollow rack body, 2, a split type receiving coil, 3, a coil storage cabin, 4, a battery cabin, 5, high-strength insulating wings, 6, a coaxial bidirectional rotor shaft, 7, a coaxial double-layer motor, 8, an aviation ceramic shell, 9, a coil main body shell, 10, a coil upper shell, 11, an internal acquisition coil, 12, a signal receiving and recording module, 13, a signal synchronization module, 14, a signal storage module, 15, a data simultaneous transmission module, 16, a coil posture recording module, 17, a control module, 18 and a coil placement groove, 19, a split type coil storage groove, 20, a coil anti-skidding damping pad, 21, a coil fixing lock catch, 22, a battery damping pad, 23, a battery storage groove, 24 and a battery cabin cover.
Detailed Description
It is to be understood that the following detailed description is exemplary and is intended to provide further explanation of the invention as claimed. Unless defined otherwise, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs.
It is noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of exemplary embodiments according to the invention. As used herein, the singular forms "a", "an" and "the" are intended to include the plural forms as well, and it should be understood that when the terms "comprises" and/or "comprising" are used in this specification, they specify the presence of stated features, steps, operations, devices, components, and/or combinations thereof, unless the context clearly indicates otherwise.
The embodiments and features of the embodiments of the present invention may be combined with each other without conflict.
Example one
The embodiment discloses a special unmanned aerial vehicle for a semi-aviation transient electromagnetic detection receiving system, which is a special multi-rotor unmanned aerial vehicle and comprises a high-strength light hollow rack (1), a power system, a split type receiving coil (2), a coil storage cabin and a battery cabin (3); unmanned aerial vehicle's components and parts are all fixed inside high strength light hollow frame through hasp or support, and the louvre is all laid in the frame side, guarantees the air intake in order to satisfy the heat dissipation demand of inside components and parts when the flight.
As shown in fig. 1, the power system of the unmanned aerial vehicle comprises a flight control unit (4), a high-strength insulating wing (5), a coaxial rotor shaft (6), a coaxial double-layer motor (7) and an aviation ceramic shell (8); the two pairs of wings are divided into two layers and are connected to the rotor shaft through lock catches, and the mounting directions of the two pairs of wings are opposite; when unmanned aerial vehicle flies, the outer lane rotation direction is opposite in coaxial double-deck motor to eliminate the electromagnetic signal interference that produces when inside rotor rotates, and the insulating wing that excels in also can not produce electromagnetic interference because of cutting the magnetic induction line.
In the above embodiment, because the wings of the drone rotate in the forward direction, the drone will rise and rotate in the reverse direction. In the design, the rotation directions of the coaxial double-layer motors are opposite, and in order to enable the two pairs of wings to generate downward driving force, one pair of each layer of the two layers and one pair of the other layer of the two layers are installed oppositely.
In the above embodiment, the two pairs of wings are mounted in opposite directions, in a manner similar to the twin wing system of a helicopter, which is a coaxial contra-rotating propeller.
In the above embodiment, the selected detection mode is a semi-aerial detection system, the emission source is placed on the ground, and signal emission is performed continuously, that is, the wings of the unmanned aerial vehicle can also cut magnetic induction lines, so that signals received by the receiving coil are affected.
In addition to the induced electromagnetic field mentioned above, the earth also has a geomagnetic field, and when the metal is extremely easy to rotate at high speed, the geomagnetic field is cut to generate a certain potential difference, and the signal can interfere with the observed signal.
Specifically, the split type receiving coil (2) comprises a coil main body shell (9), a coil upper shell (10) and an internal acquisition coil (11), wherein a signal receiving and recording module (12), a signal synchronization module (13), a signal storage module (14), a data simultaneous transmission module (15), a coil posture recording module (16) and a control module (17) are integrated in the coil main body shell, and the split type receiving coil also comprises a coil placing groove (18) for placing the internal acquisition coil; the signal control module sets various parameters of signal receiving, including fundamental frequency of signal acquisition, gain multiple of signal acquisition, signal acquisition mode and the like, then sends a set instruction into the signal receiving and recording module to start electromagnetic signal acquisition, and simultaneously acquires flight attitude information by using the coil attitude recording module, and transmits the acquired electromagnetic signals and attitude information to the signal storage module for storage; the signal synchronization module is synchronized with the transmitter through a GPS (global positioning system) so as to ensure normal operation of electromagnetic signal receiving; and the data simultaneous transmission module is used for transmitting the acquired electromagnetic signals and the attitude information to the ground station in real time.
The coil containing cabin comprises a split type coil containing groove (19), a coil anti-skidding damping pad (20) and a coil fixing lock catch (21); the coil anti-skidding damping pad is made of a material with good elasticity and a memory function, is soft in surface, large in friction coefficient and strong in friction force, and can provide enough protection for the receiving coil; the coil fixing lock catch adopts a soft leather lock catch, so that the coil can be fixed, and the damage to the appearance of the coil caused by the hard lock catch can be avoided. Wherein, split type coil accomodates the recess and is used for placing the split type coil of installation specially, plays fixed and guard action.
The battery compartment (3) comprises a battery shock pad (22), a battery accommodating groove (23) and a battery compartment cover (24); the battery shock pad adopts a circle of rubber pad made of a slightly hard material, so that the battery can be protected, the stability of connection between the battery and the unmanned aerial vehicle can be ensured, and a power source is continuously provided for the unmanned aerial vehicle; the battery hatch cover is made of high-strength materials the same as that of the rack, a circle of rubber pad is fixed inside the battery hatch cover which is in contact with the battery, and the battery cannot be exposed after the hatch cover is fastened.
The battery compartment sets up on the unmanned aerial vehicle horn, and every horn sets up a battery compartment, and the unmanned aerial vehicle frame is the air frame, and the coil is accomodate the cabin and is set up in frame air department for place split type receiving coil.
The hollow rack is provided with a plurality of arms, the end part of each arm is provided with a power system, the middle of the hollow rack is provided with an assembled split type receiving coil, and the coil can be quickly disassembled;
the flight control unit is similar to the existing common unmanned aerial vehicle and is used for controlling the state of the aircraft, and in addition, preset control information can be imported into the flight control unit in advance to realize the automatic flight and control of the unmanned aerial vehicle;
the split type receiving coil is divided into a coil shell, an internal coil and an upper cover, the coil shell and the upper cover are fixedly connected through a lock catch, soft rubber and the like are paved at the contact position of the shell and the upper cover, the effects of sealing, water proofing and dust proofing are achieved, a placing groove is formed in the coil shell, the internal coil with different turns and different materials can be placed according to different detection requirements, and other acquisition equipment such as a fluxgate can also be placed; the coil is covered with a data transmission port which is used for connecting with the internal coil data transmission port and transmitting the data to the signal receiving and recording module.
The hollow rack is provided with radiating holes which are all distributed on the side surface of the rack, so that the air intake is ensured to meet the radiating requirement of internal components during flying.
The two groups of wings are divided into an upper layer and a lower layer, and are connected to the rotor shaft through lock catches.
The inner layer and the outer layer of the double-layer motor are opposite in rotating direction, so that electromagnetic signal interference generated when the inner rotor rotates is eliminated, and the high-strength insulating wing cannot generate electromagnetic interference due to cutting of magnetic induction lines.
The controller can set the fundamental frequency of signal acquisition, the gain multiple of signal acquisition, the signal acquisition mode and the like.
The signal synchronization module is synchronized with the transmitter through a GPS or Beidou satellite positioning system and the like.
Be provided with the coil in the hollow frame and accomodate the cabin, the coil is accomodate the cabin and is included coil storage groove, coil anti-skidding shock pad and the fixed hasp of coil, is provided with coil anti-skidding shock pad in the coil storage groove, and the equipartition has the fixed hasp of a plurality of coils in order to fix split type receiving coil.
The coil is installed in the mode, so that the coil is convenient to fix, stable work is kept in the operation process, and data acquisition is accurate.
The battery cabin is arranged on the horn of the hollow rack and comprises a battery shock pad, a battery accommodating groove and a battery cabin cover, wherein the battery accommodating groove is internally provided with a plurality of battery shock pads, and the battery accommodating groove is covered by the battery cabin cover.
A circle of rubber pad is fixed inside the battery compartment cover which is contacted with the battery.
The flight control unit device is arranged at the joint of the horn and the fuselage and used for controlling the flight of the unmanned aerial vehicle.
All the non-electronic component parts are demagnetized first, so that electromagnetic interference caused by common assembly is avoided.
Example two
The purpose of this embodiment is to provide and disclose a semi-aviation transient electromagnetic detection system, include:
the unmanned aerial vehicle, the ground station and the transmitter in the above embodiment;
the ground station control transmitter transmits signals, the signals are transmitted to the semi-aviation transient electromagnetic detection receiving equipment through the GPS, the split type receiving coil of the semi-aviation transient electromagnetic detection receiving equipment acquires electromagnetic signals, and the acquired electromagnetic signals and attitude information are transmitted to the ground station in real time.
Specifically, the ground station controls the transmitter to transmit electromagnetic signals, and the unmanned aerial vehicle receives electromagnetic data and records attitude information in the air. The transmitter and the receiver fixed in the coil are time-synchronized through the GPS module, and the transmitter and the receiver can be used for data acquisition (namely acquisition of a secondary field) after the turn-off time and recording the time of transmission and acquisition, so that subsequent data screening processing is facilitated. And then, transmitting the electromagnetic data and the attitude information acquired in the split coil of the unmanned aerial vehicle to a ground station in real time through a data co-transmission module in the coil so as to monitor the data quality in real time.
The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Although the embodiments of the present invention have been described with reference to the accompanying drawings, it is not intended to limit the scope of the present invention, and it should be understood by those skilled in the art that various modifications and variations can be made without inventive efforts by those skilled in the art based on the technical solution of the present invention.
Claims (10)
1. The utility model provides a special unmanned aerial vehicle of half aviation transition electromagnetic detection receiving system, adopts many rotor unmanned aerial vehicle, characterized by includes:
the coil receiving device comprises an air-core frame, a coil receiving cabin and a coil processing system, wherein the air-core frame is provided with a plurality of arms, the end part of each arm is provided with a power system, and the middle of the air-core frame is provided with the coil receiving cabin for accommodating a split type receiving coil;
the power system comprises a rotor shaft, an insulating wing and a double-layer motor which are coaxially distributed, wherein the insulating wing is divided into an upper layer and a lower layer which are connected to the rotor shaft;
the inner-layer motor and the outer-layer motor of the double-layer motor are opposite in rotating direction and used for eliminating electromagnetic signal interference generated when the inner rotor rotates, and the insulating wing cannot generate electromagnetic interference due to cutting of magnetic induction lines.
2. The special unmanned aerial vehicle for the semi-aviation transient electromagnetic detection receiving system as claimed in claim 1, wherein the power system further comprises a flight control unit, in communication with the double-layer motor, for automatic flight control of the unmanned aerial vehicle flight.
3. The unmanned aerial vehicle special for the semi-aviation transient electromagnetic detection receiving system as claimed in claim 1, wherein the coil receiving chamber comprises: the coil receiving groove is internally provided with the coil anti-skidding damping pad, and the coil receiving groove is uniformly provided with a plurality of coil fixing lock catches for fixing the split type receiving coil.
4. The unmanned aerial vehicle special for the semi-aviation transient electromagnetic detection receiving system as claimed in claim 1, wherein the split type receiving coil comprises: coil shell, internal coil and upper cover, coil shell and upper cover are connected fixedly, and the inside standing groove that is equipped with of coil shell places the internal coil of different turns and different materials according to the different demands of surveying.
5. The unmanned aerial vehicle special for the semi-aviation transient electromagnetic detection receiving system as claimed in claim 1, wherein the coil upper cover is provided with a data transmission port for connecting with an internal coil data transmission port for transmitting internal coil data.
6. The unmanned aerial vehicle special for the semi-aviation transient electromagnetic detection receiving system as claimed in claim 1, wherein a signal receiving and recording module, a signal synchronization module, a signal storage module, a data simultaneous transmission module, a coil attitude recording module and a control module are integrated in the coil housing;
the control module sets various parameters of signal receiving, including fundamental frequency of signal acquisition, gain multiple of signal acquisition and signal acquisition mode;
the signal receiving and recording module receives the set parameters, starts to collect electromagnetic signals and collects flight attitude information by using the coil attitude recording module;
the signal storage module is used for transmitting the acquired electromagnetic signals and the attitude information to signals for storage;
the signal synchronization module is synchronized with the transmitter through a GPS (global positioning system) so as to ensure normal operation of electromagnetic signal receiving;
and the data simultaneous transmission module is used for transmitting the acquired electromagnetic signals and the attitude information to the ground station in real time.
7. The unmanned aerial vehicle special for the semi-aviation transient electromagnetic detection receiving system as claimed in claim 1, wherein heat dissipation holes are arranged on the side surface of the hollow rack, and air intake is guaranteed to meet the heat dissipation requirements of internal components during flight.
8. The unmanned aerial vehicle special for the semi-aviation transient electromagnetic detection receiving system as claimed in claim 1, wherein a battery compartment is disposed on a horn of the air core frame, the battery compartment comprises a battery shock pad, a battery receiving groove and a battery compartment cover, a plurality of battery shock pads are disposed in the battery receiving groove, and the battery receiving groove is covered by the battery compartment cover.
9. The unmanned aerial vehicle special for the semi-aviation transient electromagnetic detection receiving system as claimed in claim 1, wherein a circle of rubber pad is fixed inside the battery hatch cover in contact with the battery, and the battery is not exposed after the hatch cover is fastened.
10. A semi-airborne transient electromagnetic detection system, comprising:
the drone, ground station, and transmitter of any of claims 1-9;
the ground station control transmitter transmits signals, the signals are transmitted to the semi-aviation transient electromagnetic detection receiving equipment through the GPS, the split type receiving coil of the semi-aviation transient electromagnetic detection receiving equipment acquires electromagnetic signals, and the acquired electromagnetic signals and attitude information are transmitted to the ground station in real time.
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112124609A (en) * | 2020-09-11 | 2020-12-25 | 广东省惠州七五六地质测绘工程公司 | Special aerial survey unmanned aerial vehicle of geographic information data acquisition bears frame |
| CN113226933A (en) * | 2020-08-27 | 2021-08-06 | 深圳市大疆创新科技有限公司 | Unmanned vehicles suit, unmanned vehicles and storage device |
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