CN205883457U - Laser night vision monitored control system based on many rotor crafts - Google Patents
Laser night vision monitored control system based on many rotor crafts Download PDFInfo
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- CN205883457U CN205883457U CN201620860524.2U CN201620860524U CN205883457U CN 205883457 U CN205883457 U CN 205883457U CN 201620860524 U CN201620860524 U CN 201620860524U CN 205883457 U CN205883457 U CN 205883457U
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Abstract
The utility model discloses a laser night vision monitored control system based on many rotor crafts, including information acquisition subsystem and display control subsystem, the sub - system configuration of information acquisition is on many rotor crafts, the information acquisition subsystem includes aircraft main control unit, rotor motor drive unit, camera, laser illuminator, radio communication unit no. 1, power no. 1 and makes the steady accuse unit of aircraft smooth flight that laser illuminator is connected with the primary antenna, the display control subsystem includes industrial computer the control unit, press unit, liquid crystal display, two -dimentional control lever, three -dimensional control pole, power no. 2 and radio communication unit no. 2, radio communication unit no. 1 is connected with radio communication unit no. 2 in order to realize the communication between information acquisition subsystem and the display control subsystem. This system is when running into that the place ahead is sheltered from or during the barrier, the position of accessible adjustment aircraft hide shelter from or the barrier in order to realize continuing the control, and can realize real time monitoring round the clock.
Description
Technical field
This utility model relates to a kind of monitoring system, and the monitoring of a kind of laser night vision based on multi-rotor aerocraft is
System.
Background technology
In recent years, the technology utilizing laser lighting to carry out imaging has been widely used in the diversification such as civilian, police
Market, because it can be implemented in imaging under daytime, night two kinds of environment, especially still can be in reality under complicated night environment
Time, clearly monitored picture feature and by the most well known.
But existing laser night vision monitoring system is based on bulky and the The Cloud Terrace of heaviness, mounting means phase mostly
To fixing, do not possesses the feature that can move flexibly.When laser night-vision device front is blocked or when barrier, traditional swashs
Light night vision device just cannot continue the function of night vision monitoring, and meanwhile, monitoring distance compares limitation, can only monitor field of excursion model
Enclose internal object.
Utility model content
This utility model is in order to overcome the deficiency of above technology, it is provided that a kind of laser night vision based on multi-rotor aerocraft
Monitoring system.
This utility model overcomes its technical problem be the technical scheme is that
A kind of laser night vision monitoring system based on multi-rotor aerocraft, controls son including information gathering subsystem and display
System, information gathering subsystem is arranged on multi-rotor aerocraft；
Described information gathering subsystem includes aircraft main control unit, rotor electric-motor drive unit, video camera, laser lighting
Device, wireless communication unit one, power supply one and make aircraft smooth flight surely control unit, laser illuminator connects illumination sky
Line, video camera, laser illuminator, power supply one and the steady unit input respectively with aircraft main control unit of controlling are connected, rotor
Electric-motor drive unit is connected with the outfan of aircraft main control unit, and wireless communication unit one is two-way with aircraft main control unit
Connect；
Described display controls subsystem and includes Industrial Computer Control unit, push-button unit, LCDs, Two dimensional control
Bar, Three dimensions control bar, power supply two and wireless communication unit two, push-button unit, Two dimensional control bar, Three dimensions control bar and power supply two
Input with Industrial Computer Control unit is connected respectively, LCDs and the outfan of Industrial Computer Control unit
Being connected, wireless communication unit two is bi-directionally connected with Industrial Computer Control unit；
Wireless communication unit one is connected to realize information gathering subsystem and controls son with display with wireless communication unit two
Communication between system.
Preferred according to this utility model, described information gathering subsystem also includes steady as unit, steady picture unit and flight
The input of device main control unit is connected, can solve aircraft on high in there is the phenomenon of shake, make the output image will not
Produce shake along with the acute variation of rotor craft, observer will not be allowed when watching monitored picture to have the sensation of dizziness.
Preferred according to this utility model, described steady control unit includes that big-dipper satellite positioning unit, electronic compass course are single
Unit, three-axis gyroscope unit and three axis accelerometer unit.
Preferred according to this utility model, described push-button unit includes that target lock-on button, target following button, laser are opened
Close button, a key takes off button, key landing button and a power switch button.
Preferred according to this utility model, described aircraft main control unit uses TMS320DM368 chip；Industrial computer
Control unit uses PCM-B251 mainboard；Wireless communication unit one and wireless communication unit two all use WIFI transceiver module；Take the photograph
Camera uses 36 times of all-in-ones of Sony；Power supply one is 10000mAh lithium battery group；Power supply two is 5000mAh lithium battery group.
Preferred according to this utility model, described multi-rotor aerocraft include Y type rotor craft, quadrotor,
Six rotorcraft.
The beneficial effects of the utility model are:
1, night vision monitoring system of the present utility model is blocked or during barrier when running into front, can be by adjusting aircraft
Position hide block or barrier with realize continue monitoring.
2, this system utilizes laser illuminator to be illuminated, and overcomes visible light camera in the environment of night or light difference
Cannot the shortcoming of imaging, achieve the most dual-purpose real-time monitoring together with video camera.
3, the system increases steady picture unit, greatly reduce and make because of being continually changing of air travel position
The flating phenomenon become.
4, this system is provided with big-dipper satellite positioning unit, electronic compass course unit, three-axis gyroscope unit and three axles
Accelerometer unit, completes the control to aircraft motor part jointly so that position is more accurate, flight is more steady.
5, this internal system is integrated with wireless WIFI transceiver module, without entity between information gathering end and display control end
Line, message transmission rate is fast, and flight controls more flexible.
6, information gathering subsystem and display control subsystem all have employed considerable low-temperature lithium battery group, both ensure that and flown
Row device skyborne cruising time, substantially increase again the work persistency of aobvious control terminal.
7, display control subsystem have employed the industrial control computer core as aobvious control so that divides image
Analysis disposal ability strengthens, and is more applicable for modernizing the development trend of Intelligent Laser night vision monitoring system.
Accompanying drawing explanation
Fig. 1 is the theory structure schematic diagram of information gathering subsystem of the present utility model.
Fig. 2 is the theory structure schematic diagram that display of the present utility model controls subsystem.
In figure, 1, big-dipper satellite positioning unit, 2, rotor electric-motor drive unit, 3, aircraft main control unit, 4, three axle tops
Spiral shell instrument unit, 5, three axis accelerometer unit, 6, electronic compass course unit, 7, wireless communication unit one, 8, power supply one, 9, swash
Light illuminator, 10, primary antenna, 11, video camera, 12, steady as unit, 13, push-button unit, 14, wireless communication unit two, 15,
Industrial Computer Control unit, 16, LCDs, 17, Two dimensional control bar, 18, Three dimensions control bar, 19, power supply two.
Detailed description of the invention
It is better understood from this utility model, below in conjunction with the accompanying drawings with specific embodiment to this reality for the ease of those skilled in the art
Being described in further details with novel, following is only exemplary not limit protection domain of the present utility model.
The utility model discloses a kind of laser night vision monitoring system based on multi-rotor aerocraft, including information gathering
System and display control subsystem, and information gathering subsystem is arranged on multi-rotor aerocraft；Described multi-rotor aerocraft includes Y
Type rotor craft, quadrotor, six rotorcraft, this utility model is preferably used six rotorcraft.
As it is shown in figure 1, described information gathering subsystem includes aircraft main control unit 3, rotor electric-motor drive unit 2, takes the photograph
Camera 11, laser illuminator 9, wireless communication unit 1, power supply 1, steady as unit 12 and make the steady of aircraft smooth flight
Control unit, described steady control unit includes big-dipper satellite positioning unit 1, electronic compass course unit 6, three-axis gyroscope unit 4 and
Three axis accelerometer unit 5, laser illuminator 9 connects a primary antenna 10, video camera 11, laser illuminator 9, power supply 1, steady
As unit 12, big-dipper satellite positioning unit 1, electronic compass course unit 6, three-axis gyroscope unit 4 and three axis accelerometer
Unit 5 input with aircraft main control unit 3 respectively is connected, rotor electric-motor drive unit 2 and aircraft main control unit 3
Outfan is connected, and wireless communication unit 1 is bi-directionally connected with aircraft main control unit 3.
Described aircraft main control unit 3 uses the TMS320DM368 of Texas Instruments (TI) as control chip, has
Powerful coding and decoding video function, is suitable for current portable, the exploitation of embedded product；Rotor electric-motor drive unit 2 is rotor
The driver of aircraft motor, accurately controls the operational proof skyborne smooth flight of aircraft of motor；Big-dipper satellite is fixed
Bit location 1 gathers current geographic coordinate information real-time Transmission to aircraft main control unit 3；Electronic compass course unit 6 gathers
The azimuth information of aircraft real-time Transmission are to aircraft main control unit 3；Three-axis gyroscope unit 4 and three axis accelerometer unit
5 attitude angle gathering aircraft respectively and linear acceleration change real-time Transmission are to aircraft main control unit 3；By collect
Geographical coordinate, orientation, attitude angle and linear acceleration information Real-time Feedback, to aircraft main control unit 3, control flight the most again
The operating of device motor, adjusts flight condition at that time in time；Video camera 11 uses 36 times of all-in-ones of Sony, can realize zoom,
The functions such as focusing, automatic focusing, are the main video acquisition entrances of this system, and the image information collected can be transferred to aircraft
Main control unit 3 is analyzed processing；Laser illuminator 9 and primary antenna 10, as night vision illumination auxiliary imaging system, overcome
In the environment of night or light difference visible light camera cannot the shortcoming of imaging, achieve the most dual-purpose reality together with video camera
Time monitoring；Power supply 1 uses the low temperature 18650 lithium battery group of 10000mAh, can realize the electric current output of the highest 10A, it is ensured that
Aircraft skyborne cruising time；Surely as unit 12 be in order to solve aircraft on high in there is the phenomenon shaken and design
, make output image will not produce shake along with the acute variation of rotor craft, observer will not be allowed at viewing monitoring picture
The sensation of dizziness is had during face.
As in figure 2 it is shown, described display controls subsystem includes Industrial Computer Control unit 15, push-button unit 13, liquid crystal
Display screen 16, Two dimensional control bar 17, Three dimensions control bar 18, power supply 2 19 and wireless communication unit 2 14, push-button unit 13, two
Dimension control bar 17, Three dimensions control bar 18 with power supply 2 19 respectively input with Industrial Computer Control unit 15 be connected, liquid
Crystal display screen 16 is connected with the outfan of Industrial Computer Control unit 15, wireless communication unit 2 14 and industrial computer control
Unit 15 processed is bi-directionally connected.
Described Industrial Computer Control unit 15 uses 2.5 cun of industrial master board PCM-of this Electronics Co., Ltd. of Germany and Britain
B251, volume is little, lightweight, low in energy consumption；Push-button unit 13 include target lock-on button, target following button, laser switch by
Key, a key take off button, a key landing button and power switch button；LCDs 16 is the LCD screen of 7 inches,
Can be shown that the more details of object；Two dimensional control bar 17 realizes aircraft in the horizontal direction, the control of vertical direction motion；
Three dimensions control bar 18 realizes video camera 11 and the control of primary antenna 10, to complete the zoom of video camera 11, focusing, illuminates sky
The operations such as the aperture change of line 10 is big, diminish；Power supply 2 19 uses the low temperature 18650 lithium battery group of 5000mAh, it is ensured that continuation of the journey same
Time also reduce the volume of complete machine.
Wireless communication unit 1 is connected to realize information gathering subsystem and controls with display with wireless communication unit 2 14
Communication between subsystem, it is achieved that display controls the subsystem control to information gathering subsystem, wireless communication unit 1 He
Wireless communication unit 2 14 all have employed WIFI transceiver module, and message transmission rate is fast, and flight controls more flexible.
The use process of this utility model laser night vision based on multi-rotor aerocraft monitoring system: turn on the power switch,
System is energized, and first carries out self-inspection；After self-inspection is logical, operator control aircraft at water by controlling Two dimensional control bar 17
Flat, the motion of vertical direction；Control the zoom of video camera, focusing operation by the 3rd road AD of Three dimensions control bar 18, work as laser
When illumination apparatus is in open mode, it is also possible to the aperture controlling primary antenna 10 becomes big, diminishes；By the of Three dimensions control bar 18
One, two road AD control carrying video cameras The Cloud Terrace in the horizontal direction before and after left and right four orientation change.Information gathering subsystem
Unite and the data collected are carried out data by wireless communication unit 1 and wireless communication unit 2 14 with display control subsystem
Transmission exchange, it can be clearly seen that ask for the target of observation in LCDs 16；After pressing target lock-on button, liquid crystal
Suspicious target can be locked by display screen, the action of moment supervision suspicious object；After pressing target following button, flight
Device can carry out synchronizing moving with suspicious object, follows the tracks of the suspect path of target；Pressing next key and take off after button, aircraft can be automatically
Flight is to aerial settling position；After pressing next key landing button, aircraft can fly back operator at one's side automatically.
Above only describes ultimate principle of the present utility model and preferred implementation, those skilled in the art can be according to above-mentioned
Many changes and improvements are made in description, and these changes and improvements should belong to protection domain of the present utility model.
Claims (6)
1. a laser night vision monitoring system based on multi-rotor aerocraft, it is characterised in that:
Controlling subsystem including information gathering subsystem and display, information gathering subsystem is arranged on multi-rotor aerocraft；
Described information gathering subsystem includes aircraft main control unit (3), rotor electric-motor drive unit (2), video camera (11), swashs
Light illuminator (9), wireless communication unit one (7), power supply one (8) and make aircraft smooth flight surely control unit, laser shines
Funerary objects (9) connects a primary antenna (10), video camera (11), laser illuminator (9), power supply one (8) and surely control unit respectively with
The input of aircraft main control unit (3) is connected, rotor electric-motor drive unit (2) and the output of aircraft main control unit (3)
End is connected, and wireless communication unit one (7) is bi-directionally connected with aircraft main control unit (3)；
Described display control subsystem include Industrial Computer Control unit (15), push-button unit (13), LCDs (16),
Two dimensional control bar (17), Three dimensions control bar (18), power supply two (19) and wireless communication unit two (14), push-button unit (13),
Two dimensional control bar (17), Three dimensions control bar (18) and power supply two (19) respectively with the input of Industrial Computer Control unit (15)
Being connected, LCDs (16) is connected with the outfan of Industrial Computer Control unit (15), wireless communication unit two
(14) it is bi-directionally connected with Industrial Computer Control unit (15)；
Wireless communication unit one (7) is connected to realize information gathering subsystem and controls with display with wireless communication unit two (14)
Communication between subsystem.
Monitoring system the most according to claim 1, it is characterised in that: described information gathering subsystem also includes steady as unit
(12), steady picture unit (12) is connected with the input of aircraft main control unit (3).
Monitoring system the most according to claim 1 and 2, it is characterised in that: described steady control unit includes that big-dipper satellite positions
Unit (1), electronic compass course unit (6), three-axis gyroscope unit (4) and three axis accelerometer unit (5).
Monitoring system the most according to claim 1 and 2, it is characterised in that: described push-button unit (13) includes target lock-on
Button, target following button, laser switch button, a key take off button, a key landing button and power switch button.
Monitoring system the most according to claim 1, it is characterised in that: described aircraft main control unit (3) uses
TMS320DM368 chip；Industrial Computer Control unit (15) uses PCM-B251 mainboard；Wireless communication unit one (7) and nothing
Line communication unit two (14) all uses WIFI transceiver module；Video camera (11) uses 36 times of all-in-ones of Sony；Power supply one (8) is
10000mAh lithium battery group；Power supply two (19) is 5000mAh lithium battery group.
Monitoring system the most according to claim 1, it is characterised in that: described multi-rotor aerocraft includes Y type rotor flying
Device, quadrotor, six rotorcraft.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620860524.2U CN205883457U (en) | 2016-08-10 | 2016-08-10 | Laser night vision monitored control system based on many rotor crafts |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620860524.2U CN205883457U (en) | 2016-08-10 | 2016-08-10 | Laser night vision monitored control system based on many rotor crafts |
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| Publication Number | Publication Date |
|---|---|
| CN205883457U true CN205883457U (en) | 2017-01-11 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201620860524.2U Active CN205883457U (en) | 2016-08-10 | 2016-08-10 | Laser night vision monitored control system based on many rotor crafts |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106101657A (en) * | 2016-08-10 | 2016-11-09 | 山东神戎电子股份有限公司 | A kind of laser night vision monitoring system based on multi-rotor aerocraft |
| CN107883927A (en) * | 2017-11-09 | 2018-04-06 | 陕西科技大学 | Quadrotor plant growth inspection system |
-
2016
- 2016-08-10 CN CN201620860524.2U patent/CN205883457U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106101657A (en) * | 2016-08-10 | 2016-11-09 | 山东神戎电子股份有限公司 | A kind of laser night vision monitoring system based on multi-rotor aerocraft |
| CN107883927A (en) * | 2017-11-09 | 2018-04-06 | 陕西科技大学 | Quadrotor plant growth inspection system |
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