CN110155327A - A kind of low-to-medium altitude flight monitoring unmanned system - Google Patents
A kind of low-to-medium altitude flight monitoring unmanned system Download PDFInfo
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- CN110155327A CN110155327A CN201910415656.2A CN201910415656A CN110155327A CN 110155327 A CN110155327 A CN 110155327A CN 201910415656 A CN201910415656 A CN 201910415656A CN 110155327 A CN110155327 A CN 110155327A
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- 238000012544 monitoring process Methods 0.000 title claims abstract description 33
- 238000001931 thermography Methods 0.000 claims abstract description 12
- 230000005540 biological transmission Effects 0.000 claims abstract description 6
- 239000013307 optical fiber Substances 0.000 claims abstract description 6
- 238000004891 communication Methods 0.000 claims description 6
- 230000006837 decompression Effects 0.000 claims description 6
- 238000003780 insertion Methods 0.000 claims description 3
- 230000037431 insertion Effects 0.000 claims description 3
- 230000002159 abnormal effect Effects 0.000 abstract description 4
- 238000000034 method Methods 0.000 description 5
- 238000010586 diagram Methods 0.000 description 4
- 238000009826 distribution Methods 0.000 description 3
- 230000005611 electricity Effects 0.000 description 3
- 238000011835 investigation Methods 0.000 description 3
- 238000009434 installation Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 208000035473 Communicable disease Diseases 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000003086 colorant Substances 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 208000015181 infectious disease Diseases 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000013507 mapping Methods 0.000 description 1
- 238000012806 monitoring device Methods 0.000 description 1
- 238000012634 optical imaging Methods 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- 230000005855 radiation Effects 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60L—PROPULSION OF ELECTRICALLY-PROPELLED VEHICLES; SUPPLYING ELECTRIC POWER FOR AUXILIARY EQUIPMENT OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRODYNAMIC BRAKE SYSTEMS FOR VEHICLES IN GENERAL; MAGNETIC SUSPENSION OR LEVITATION FOR VEHICLES; MONITORING OPERATING VARIABLES OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRIC SAFETY DEVICES FOR ELECTRICALLY-PROPELLED VEHICLES
- B60L53/00—Methods of charging batteries, specially adapted for electric vehicles; Charging stations or on-board charging equipment therefor; Exchange of energy storage elements in electric vehicles
- B60L53/10—Methods of charging batteries, specially adapted for electric vehicles; Charging stations or on-board charging equipment therefor; Exchange of energy storage elements in electric vehicles characterised by the energy transfer between the charging station and the vehicle
- B60L53/14—Conductive energy transfer
- B60L53/16—Connectors, e.g. plugs or sockets, specially adapted for charging electric vehicles
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60L—PROPULSION OF ELECTRICALLY-PROPELLED VEHICLES; SUPPLYING ELECTRIC POWER FOR AUXILIARY EQUIPMENT OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRODYNAMIC BRAKE SYSTEMS FOR VEHICLES IN GENERAL; MAGNETIC SUSPENSION OR LEVITATION FOR VEHICLES; MONITORING OPERATING VARIABLES OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRIC SAFETY DEVICES FOR ELECTRICALLY-PROPELLED VEHICLES
- B60L53/00—Methods of charging batteries, specially adapted for electric vehicles; Charging stations or on-board charging equipment therefor; Exchange of energy storage elements in electric vehicles
- B60L53/10—Methods of charging batteries, specially adapted for electric vehicles; Charging stations or on-board charging equipment therefor; Exchange of energy storage elements in electric vehicles characterised by the energy transfer between the charging station and the vehicle
- B60L53/14—Conductive energy transfer
- B60L53/18—Cables specially adapted for charging electric vehicles
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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
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- 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
- B64D47/08—Arrangements of cameras
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01J—MEASUREMENT OF INTENSITY, VELOCITY, SPECTRAL CONTENT, POLARISATION, PHASE OR PULSE CHARACTERISTICS OF INFRARED, VISIBLE OR ULTRAVIOLET LIGHT; COLORIMETRY; RADIATION PYROMETRY
- G01J5/00—Radiation pyrometry, e.g. infrared or optical thermometry
- G01J5/0014—Radiation pyrometry, e.g. infrared or optical thermometry for sensing the radiation from gases, flames
- G01J5/0018—Flames, plasma or welding
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01J—MEASUREMENT OF INTENSITY, VELOCITY, SPECTRAL CONTENT, POLARISATION, PHASE OR PULSE CHARACTERISTICS OF INFRARED, VISIBLE OR ULTRAVIOLET LIGHT; COLORIMETRY; RADIATION PYROMETRY
- G01J5/00—Radiation pyrometry, e.g. infrared or optical thermometry
- G01J5/0066—Radiation pyrometry, e.g. infrared or optical thermometry for hot spots detection
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S17/00—Systems using the reflection or reradiation of electromagnetic waves other than radio waves, e.g. lidar systems
- G01S17/02—Systems using the reflection of electromagnetic waves other than radio waves
- G01S17/06—Systems determining position data of a target
- G01S17/08—Systems determining position data of a target for measuring distance only
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S19/00—Satellite radio beacon positioning systems; Determining position, velocity or attitude using signals transmitted by such systems
- G01S19/01—Satellite radio beacon positioning systems transmitting time-stamped messages, e.g. GPS [Global Positioning System], GLONASS [Global Orbiting Navigation Satellite System] or GALILEO
- G01S19/13—Receivers
- G01S19/33—Multimode operation in different systems which transmit time stamped messages, e.g. GPS/GLONASS
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04N—PICTORIAL COMMUNICATION, e.g. TELEVISION
- H04N5/00—Details of television systems
- H04N5/30—Transforming light or analogous information into electric information
- H04N5/33—Transforming infrared radiation
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04N—PICTORIAL COMMUNICATION, e.g. TELEVISION
- H04N7/00—Television systems
- H04N7/18—Closed-circuit television [CCTV] systems, i.e. systems in which the video signal is not broadcast
- H04N7/181—Closed-circuit television [CCTV] systems, i.e. systems in which the video signal is not broadcast for receiving images from a plurality of remote sources
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01J—MEASUREMENT OF INTENSITY, VELOCITY, SPECTRAL CONTENT, POLARISATION, PHASE OR PULSE CHARACTERISTICS OF INFRARED, VISIBLE OR ULTRAVIOLET LIGHT; COLORIMETRY; RADIATION PYROMETRY
- G01J5/00—Radiation pyrometry, e.g. infrared or optical thermometry
- G01J2005/0077—Imaging
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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
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T10/00—Road transport of goods or passengers
- Y02T10/60—Other road transportation technologies with climate change mitigation effect
- Y02T10/70—Energy storage systems for electromobility, e.g. batteries
-
- 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
- Y02T10/00—Road transport of goods or passengers
- Y02T10/60—Other road transportation technologies with climate change mitigation effect
- Y02T10/7072—Electromobility specific charging systems or methods for batteries, ultracapacitors, supercapacitors or double-layer capacitors
-
- 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
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
- Y02T90/10—Technologies relating to charging of electric vehicles
- Y02T90/14—Plug-in electric vehicles
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- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Radar, Positioning & Navigation (AREA)
- Remote Sensing (AREA)
- General Physics & Mathematics (AREA)
- Transportation (AREA)
- Computer Networks & Wireless Communication (AREA)
- Power Engineering (AREA)
- Electromagnetism (AREA)
- Mechanical Engineering (AREA)
- Spectroscopy & Molecular Physics (AREA)
- Aviation & Aerospace Engineering (AREA)
- Multimedia (AREA)
- Signal Processing (AREA)
- Plasma & Fusion (AREA)
- Alarm Systems (AREA)
Abstract
The invention discloses low-to-medium altitude flight monitoring unmanned system, including ground power supply component and aircraft, ground power supply component includes surface power supply module, low-voltage power supply module and high-tension bus-bar, and being tethered at includes current supply line and two single mode optical fibers in cable；Ground power supply component side is provided with bracket, Wiinding cartridge is installed on bracket, it states and thermal imaging system, visible light high definition camera and laser range finder is installed in monitoring box, CPU module, GPS positioning module, Beidou positioning module, data transmission module and alarm chip interconnected are respectively arranged in control cabinet；Aircraft and ground are established data connection in the form of broadband by the present invention, can obtain monitoring data at the first time；Using thermal imaging, high definition monitoring data can be accurately obtained, provide authentic data for staff；Using positioning system and alarm chip, can quick obtaining alarm place accurate location information, convenient for quickly taking measures to abnormal conditions.
Description
Technical field
The present invention relates to safety-security area, specially a kind of low-to-medium altitude flight monitoring unmanned system.
Background technique
Referred to as " unmanned plane ", english abbreviation is " UAV " to UAV, is using radio robot and to provide for oneself
The not manned aircraft of presetting apparatus manipulation, or fully or intermittently automatically operated by car-mounted computer.With someone
It drives an airplane and compares, unmanned plane is often more suitable for the task of those too " slow-witted, dirty or dangerous ".Unmanned plane presses application field,
Can be divided into it is military with it is civilian.Military aspect, unmanned plane are divided into reconnaissance plane and target drone.Civilian aspect, unmanned plane+industrial application are
Unmanned plane has really just needed；It taking photo by plane at present, agricultural, plant protection, miniature self-timer, express transportation, disaster relief, observing wild move
The application in object, monitoring infectious disease, mapping, news report, electric inspection process, the disaster relief, movies-making, manufacture romance etc. field, greatly
The big purposes for having expanded unmanned plane itself, developed country also in actively extension industrial application and develop unmanned air vehicle technique.
The flight of low-to-medium altitude is monitored at present, as forest protection, highway patrol, fire alarm investigation, urgent handling, city are wide
Lack more effectively convenient and high flexibility monitoring device in the field of the interim monitoring in field etc., therefore unmanned plane is applied upper
Stating monitoring field is very important.
Summary of the invention
The purpose of the present invention is to provide a kind of low-to-medium altitude flight monitoring unmanned systems, to solve in above-mentioned background technique
The problem of proposition.
To achieve the above object, the invention provides the following technical scheme: a kind of low-to-medium altitude flight monitoring unmanned system, packet
Ground power supply component and aircraft are included, the ground power supply component includes surface power supply module, low-voltage power supply module and high-voltage electricity
Line, connection is tethered at cable connection between the ground power supply component and aircraft, and being tethered at includes current supply line and two in cable
Single mode optical fiber；Ground power supply component side is provided with bracket, and Wiinding cartridge is equipped on bracket, is provided in the Wiinding cartridge
Roll, Wiinding cartridge is interior to be equipped with bearing in roll one end, and the side far from bearing is equipped with fixed shell outside Wiinding cartridge,
Coiling electric motor is installed, roll one end is mounted in bearing, the output shaft of the other end and coiling electric motor in the set casing body
Connection, fixed hull outside are provided with the control button connecting with coiling electric motor；
Flight power supply is provided in the aircraft, aircraft bottom is provided with gondola, is equipped with monitoring box on aircraft,
Thermal imaging system, visible light high definition camera and laser range finder are installed in the monitoring box, are provided with control in the aircraft
Case is respectively arranged with CPU module interconnected, GPS positioning module, Beidou positioning module, number in the control cabinet
According to transmission module and alarm chip.
Preferably, the power input of the surface power supply module terminates AC power source, the power supply output of surface power supply module
End is connected by high voltage supply line with the power input for being depressured power supply module.
Preferably, the first voltage output end of the decompression power supply module and second voltage output end pass through current supply line point
It is not connected with the first power input of flight power supply and second source input terminal.
Preferably, the Wiinding cartridge two sides are respectively arranged with line outlet groove, and the setting of one of line outlet groove with roll
End corresponding position is tethered in cable one end insertion roll, and is pierced by from the line outlet groove of roll end and ground power supply
Component connection, the other end are wrapped on roll and are pierced by from another line outlet groove and connect with flight power supply.
Preferably, be provided in the gondola searchlight, communication relays, quickly light-duty lifting platform, in light-duty throwing arm
One or more.
Preferably, the ground power supply component is arranged in earth station or command car.
Compared with prior art, the beneficial effects of the present invention are:
Aircraft and ground are established data connection in the form of broadband by the present invention, can obtain monitoring data at the first time,
Monitoring efficiency is high；It will be seen that light high definition camera, thermal imaging system and laser range finder combine, using thermal imaging, can accurately obtain
High definition monitoring data are taken, provide authentic data for staff；It, can quick obtaining alarm using positioning system and alarm chip
The accurate location information of point, convenient for quickly taking measures to abnormal conditions；Gondola can be changed quickly as searchlight, communication relay
Device, quickly light-duty lifting platform, light-duty throwing arm, the application feature of change of flight device, can be used in forest protection, highway patrols at any time
It patrols, the low-to-medium altitudes flight such as fire alarm investigation, urgent handling, city square temporarily monitor.
Detailed description of the invention
Fig. 1 is overall structure diagram of the invention；
Fig. 2 is the concrete structure schematic diagram for being tethered at cable of the invention；
Fig. 3 is the specific attachment structure schematic diagram of Wiinding cartridge of the invention；
Fig. 4 is the inside concrete structure schematic diagram of control cabinet of the invention.
In figure: 1, ground power supply component；2, aircraft；3, surface power supply module；4, low-voltage power supply module；5, high-voltage electricity
Line；6, it is tethered at cable；7, current supply line；8, single mode optical fiber；9, bracket；10, Wiinding cartridge；11, roll；12, bearing；13, solid
Fixed shell；14, coiling electric motor；15, control button；16, line outlet groove；17, flight power supply；18, gondola；19, monitoring box；20, hot
Imager；21, visible light high definition camera；22, laser range finder；23, control cabinet；24, CPU module；25, GPS positioning
Module；26, Beidou positioning module；27, data transmission module；28, alarm chip；.
Specific embodiment
Following will be combined with the drawings in the embodiments of the present invention, and technical solution in the embodiment of the present invention carries out clear, complete
Site preparation description, it is clear that described embodiments are only a part of the embodiments of the present invention, instead of all the embodiments.It is based on
Embodiment in the present invention, it is obtained by those of ordinary skill in the art without making creative efforts every other
Embodiment shall fall within the protection scope of the present invention.
In the description of the present invention, it should be noted that the orientation of the instructions such as term "vertical", "upper", "lower", "horizontal"
Or positional relationship is to be based on the orientation or positional relationship shown in the drawings, and is merely for convenience of description of the present invention and simplification of the description, and
It is not that the device of indication or suggestion meaning or element must have a particular orientation, be constructed and operated in a specific orientation, therefore
It is not considered as limiting the invention.
In the description of the present invention, it is also necessary to which explanation is unless specifically defined or limited otherwise, term " setting ",
" installation ", " connected ", " connection " shall be understood in a broad sense, for example, it may be fixedly connected, may be a detachable connection or one
Connect to body；It can be mechanical connection, be also possible to be electrically connected；It can be directly connected, it can also be indirect by intermediary
It is connected, can be the connection inside two elements.For the ordinary skill in the art, it can manage as the case may be
Solve the concrete meaning of above-mentioned term in the present invention.
Fig. 1-4 is please referred to, the present invention provides a kind of technical solution: a kind of low-to-medium altitude flight monitoring unmanned system, including
Ground power supply component 1 and aircraft 2, the ground power supply component 1 include surface power supply module 3, low-voltage power supply module 4 and high pressure
Electric wire 5, connection is tethered at the connection of cable 6 between the ground power supply component 1 and aircraft 2, and being tethered at includes current supply line in cable 6
7 and two single mode optical fibers 8；1 side of ground power supply component is provided with bracket 9, and Wiinding cartridge 10 is equipped on bracket 9, described
Roll 11 is provided in Wiinding cartridge 10, Wiinding cartridge 10 is interior to be equipped with bearing 12 in 11 one end of roll, and 10 outside of Wiinding cartridge is remote
The side for holding 12 off axis is equipped with fixed shell 13, and coiling electric motor 14,11 one end of roll are equipped in the fixed shell 13
It is mounted in bearing 9, the output axis connection of the other end and coiling electric motor 14, is provided with and coiling electric motor 14 outside fixed shell 13
The control button 15 of connection；
Flight power supply 17 is provided in the aircraft 2,2 bottom of aircraft is provided with gondola 18, is equipped on aircraft 2
Monitoring box 19 is equipped with thermal imaging system 20, visible light high definition camera 21 and laser range finder 22 in the monitoring box 19, described to fly
It is provided with control cabinet 23 in row device 2, CPU module 24 interconnected, GPS are respectively arranged in the control cabinet 23
Locating module 25, Beidou positioning module 26, data transmission module 27 and alarm chip 28.
Further, the power input of the surface power supply module 3 terminates AC power source, the power supply of surface power supply module 3
Output end is connected by high voltage supply line 5 with the power input for being depressured power supply module 4.
Further, the first voltage output end of the decompression power supply module 4 and second voltage output end pass through for conductance
Line 7 is connected with the first power input of flight power supply 17 and second source input terminal respectively.
Further, 10 two sides of Wiinding cartridge are respectively arranged with line outlet groove 16, and the setting of one of line outlet groove 16 exists
It with 11 end corresponding position of roll, is tethered in 6 one end of cable insertion roll 11, and the line outlet groove from 11 end of roll
16 are pierced by and connect with ground power supply component 1, and the other end is wrapped on roll 11 and is pierced by and flies from another line outlet groove 16
Power supply 17 connects.
Further, searchlight, communication relays, quickly light-duty lifting platform, light-duty throwing are provided in the gondola 18
One or more of device.
Further, the ground power supply component 1 is arranged in earth station or command car.
Working principle: ground power supply component 1 by 220V convert alternating current be high pressure after by be tethered at cable 6 be transferred to it is airborne
Flight power supply 17, then it is transformed to the power supply of aircraft 2 and mission payload.Specifically: the power input of surface power supply module 3
Terminate AC power source, the electricity that the power output end of surface power supply module 3 passes through high voltage supply line 5 and the decompression power supply module 4
Source input terminal is connected, the first voltage output end of 4 pieces of mould of decompression power supply and the flight with aircraft 2 respectively of second voltage output end
First power input of power supply 17 is connected with second source input terminal；Surface power supply module 3 carries out the AC power source of access
High voltage direct current is converted to after boosting, and the HVDC transmission is extremely depressured by power supply module 4, institute by high voltage supply line 5
It states decompression power supply module 4 to be depressured the high voltage direct current, to obtain low-voltage DC as the aircraft 2 power supply.System
It stays in cable 6 in addition to current supply line 7, there are also two single mode optical fibers 8, the width that can be used between airborne mission payload and ground installation
It takes a message signal communication.The opening and closing of coiling electric motor 14 is controlled by control button 15, it is adjustable to be tethered between cable 6 and aircraft 2
Extension elongation, to adjust the flying height of aircraft 2.
Thermal imaging system 20, visible light high definition camera 21 and laser range finder 22 are installed, it is seen that light high definition in monitoring box 19
Camera 21 obtains high-definition image in real time, and thermal imaging system 20 is thermal infrared imager, will using infrared detector and optical imaging objective
In the infrared radiation energy distribution pattern reflection to the light-sensitive element of infrared detector of measured target, to obtain infrared thermal imagery
Figure, this thermography is corresponding with the heat distribution field of body surface, the invisible infrared energy that object issues is changed into visible
Thermal image；The different colours of the upper surface of thermal image represent the different temperatures of testee, by checking thermal image, can observe
To the bulk temperature distribution situation of measured target, the heat condition of goal in research, and control cabinet 23 is sent by temperature signal
CPU module 24 then carries out alert process by internal alarm chip 28 if target temperature exceeds ordinary temperature；At this time
The longitude and latitude of 26 positioning aircraft 2 of GPS positioning module 25 and Beidou positioning module, laser range finder 22 orient heat source and aircraft
The distance between direction and calculate the accurate location of abnormal heat source, transmit information to command car.
Meanwhile aircraft 2 can be used in non-pending flight, can utilize GPS positioning module by earth station, command car
25 and Beidou positioning module 26 carry out planning course line, permanent patrol flight can be carried out in prebriefed pattern.
Aircraft and ground are established data connection in the form of broadband by the present invention, can obtain monitoring data at the first time,
Monitoring efficiency is high；It will be seen that light high definition camera, thermal imaging system and laser range finder combine, using thermal imaging, can accurately obtain
High definition monitoring data are taken, provide authentic data for staff；It, can quick obtaining alarm using positioning system and alarm chip
The accurate location information of point, convenient for quickly taking measures to abnormal conditions；Gondola can be changed quickly as searchlight, communication relay
Device, quickly light-duty lifting platform, light-duty throwing arm, the application feature of change of flight device, can be used in forest protection, highway patrols at any time
It patrols, the low-to-medium altitudes flight such as fire alarm investigation, urgent handling, city square temporarily monitor.
It is worth noting that: whole device realizes control to it by main control button, sets since control button is matched
Standby is commonly used equipment, belongs to existing Changshu technology, details are not described herein its electrical connection and specific circuit structure.
It although an embodiment of the present invention has been shown and described, for the ordinary skill in the art, can be with
A variety of variations, modification, replacement can be carried out to these embodiments without departing from the principles and spirit of the present invention by understanding
And modification, the scope of the present invention is defined by the appended.
Claims (6)
1. a kind of low-to-medium altitude flight monitoring unmanned system, which is characterized in that including ground power supply component (1) and aircraft (2),
The ground power supply component (1) includes surface power supply module (3), low-voltage power supply module (4) and high-tension bus-bar (5), the ground
Connection is tethered at cable (6) connection between power supply module (1) and aircraft (2), be tethered in cable (6) include current supply line (7) and
Two single mode optical fibers (8)；Ground power supply component (1) side is provided with bracket (9), and bracket is equipped with Wiinding cartridge on (9)
(10), it is provided with roll (11) in the Wiinding cartridge (10), bearing is installed in roll (11) one end in Wiinding cartridge (10)
(12), the external side far from bearing (12) of Wiinding cartridge (10) is equipped with fixed shell (13), peace in the fixed shell (13)
Equipped with coiling electric motor (14), roll (11) one end is mounted in bearing (9), and the output shaft of the other end and coiling electric motor (14) connects
It connects, is provided with the control button (15) connecting with coiling electric motor (14) outside fixed shell (13)；
It is provided with flight power supply (17) in the aircraft (2), aircraft (2) bottom is provided with gondola (18), on aircraft (2)
It is equipped with monitoring box (19), thermal imaging system (20), visible light high definition camera (21) and laser is installed in the monitoring box (19)
Rangefinder (22), the aircraft (2) is interior to be provided with control cabinet (23), is respectively arranged with interconnection in the control cabinet (23)
CPU module (24), GPS positioning module (25), Beidou positioning module (26), data transmission module (27) and alarm
Chip (28).
2. a kind of low-to-medium altitude flight monitoring unmanned system according to claim 1, it is characterised in that: the surface power supply
The power input of module (3) terminates AC power source, the power output end of surface power supply module (3) by high voltage supply line (5) with
The power input for being depressured power supply module (4) is connected.
3. a kind of low-to-medium altitude flight monitoring unmanned system according to claim 1, it is characterised in that: the decompression power supply
The first voltage output end and second voltage output end of module (4) by current supply line (7) respectively with flight power supply (17) the
One power input is connected with second source input terminal.
4. a kind of low-to-medium altitude flight monitoring unmanned system according to claim 1, it is characterised in that: the Wiinding cartridge
(10) two sides are respectively arranged with line outlet groove (16), and one of line outlet groove (16) is arranged in position corresponding with roll (11) end
Place is set, is tethered in cable (6) one end insertion roll (11), and is pierced by from the line outlet groove (16) of roll (11) end and ground
Power supply module (1) connection, the other end are wrapped on roll (11) and are pierced by and flight power supply from another line outlet groove (16)
(17) it connects.
5. a kind of low-to-medium altitude flight monitoring unmanned system according to claim 1, it is characterised in that: the gondola (18)
Inside it is provided with searchlight, communication relays, quickly one or more of light-duty lifting platform, light-duty throwing arm.
6. a kind of low-to-medium altitude flight monitoring unmanned system according to claim 1, it is characterised in that: the ground power supply
Component (1) is arranged in earth station or command car.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910415656.2A CN110155327A (en) | 2019-05-18 | 2019-05-18 | A kind of low-to-medium altitude flight monitoring unmanned system |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111307291A (en) * | 2020-03-02 | 2020-06-19 | 武汉大学 | Surface temperature anomaly detection and positioning method, device and system based on unmanned aerial vehicle |
| CN112629667A (en) * | 2020-12-02 | 2021-04-09 | 众源科技(广东)股份有限公司 | Double-spectrum thermal imaging temperature measurement system |
| CN112762909A (en) * | 2021-02-01 | 2021-05-07 | 安徽科技学院 | Portable mapping equipment |
| CN113682220A (en) * | 2020-05-19 | 2021-11-23 | 马自达汽车株式会社 | Control system for vehicle-mounted flight vehicle |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105516691A (en) * | 2016-02-02 | 2016-04-20 | 中科融通物联科技无锡有限公司 | Long-hovering unmanned aerial vehicle base station communicating and monitoring system |
| CN207697997U (en) * | 2018-01-03 | 2018-08-07 | 江苏和正特种装备有限公司 | A kind of more rotors of measurement type are tethered at unmanned vehicle system |
| CN210101992U (en) * | 2019-05-18 | 2020-02-21 | 太原裕昌泰科贸有限公司 | Middle and low altitude unmanned aerial vehicle monitoring system |
-
2019
- 2019-05-18 CN CN201910415656.2A patent/CN110155327A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105516691A (en) * | 2016-02-02 | 2016-04-20 | 中科融通物联科技无锡有限公司 | Long-hovering unmanned aerial vehicle base station communicating and monitoring system |
| CN207697997U (en) * | 2018-01-03 | 2018-08-07 | 江苏和正特种装备有限公司 | A kind of more rotors of measurement type are tethered at unmanned vehicle system |
| CN210101992U (en) * | 2019-05-18 | 2020-02-21 | 太原裕昌泰科贸有限公司 | Middle and low altitude unmanned aerial vehicle monitoring system |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111307291A (en) * | 2020-03-02 | 2020-06-19 | 武汉大学 | Surface temperature anomaly detection and positioning method, device and system based on unmanned aerial vehicle |
| CN113682220A (en) * | 2020-05-19 | 2021-11-23 | 马自达汽车株式会社 | Control system for vehicle-mounted flight vehicle |
| TWI771941B (en) * | 2020-05-19 | 2022-07-21 | 日商馬自達汽車股份有限公司 | Control system for vehicle-mounted flying objects |
| CN113682220B (en) * | 2020-05-19 | 2024-02-13 | 马自达汽车株式会社 | Control system for vehicle-mounted flying body |
| CN112629667A (en) * | 2020-12-02 | 2021-04-09 | 众源科技(广东)股份有限公司 | Double-spectrum thermal imaging temperature measurement system |
| CN112762909A (en) * | 2021-02-01 | 2021-05-07 | 安徽科技学院 | Portable mapping equipment |
| CN112762909B (en) * | 2021-02-01 | 2023-07-07 | 安徽科技学院 | Portable mapping equipment |
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