CN203439271U - Middle-low-altitude floating monitor system - Google Patents
Middle-low-altitude floating monitor system Download PDFInfo
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- CN203439271U CN203439271U CN201320418378.4U CN201320418378U CN203439271U CN 203439271 U CN203439271 U CN 203439271U CN 201320418378 U CN201320418378 U CN 201320418378U CN 203439271 U CN203439271 U CN 203439271U
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Abstract
The utility model discloses a middle-low-altitude floating monitor system which comprises an aircraft, a shooting unit, a power supply unit, a monitor assembly and a traction control assembly. The shooting unit and the power supply unit are both arranged on the aircraft, the shooting unit transmits shot images to the monitor assembly on the ground. The traction control assembly comprises a traction controller, a traction execution mechanism and a traction wire, one end of the traction wire is connected with the aircraft, the other end of the traction wire is connected with the traction execution mechanism, and the traction execution mechanism is controlled by the traction controller. The middle-low-altitude floating monitor system has the advantages of being simple in structure, low in cost, convenient to operate, wide in motion range, reliable in performance and the like.
Description
Technical field
The utility model is mainly concerned with monitoring equipment field, refers in particular to the floating empty monitored control system of a kind of low-to-medium altitude.
Background technology
At present, having practitioner to propose many eurypalynous high-altitudes monitored control system, is mainly by camera being set in a large number to fix a point monitoring and take of ground on a large scale, with towards Military and civil fields such as low-to-medium altitude investigation, the network coverage, forest fire protection, business amusements.Such high-altitude watch-dog is to be all generally positioned on fixed buildings, tree or other high fixed positions, but due to camera installation site, once so after this class watch-dog installs, its monitoring range is just very limited.
For the follow shot of low-to-medium altitude, the solution generally adopting is at present by way of being to utilize unmanned vehicle to carry out inter-related task.General unmanned vehicle need to use electric power (battery), heat energy (fire balloon) or solar power to carry out energy supply, and therefore this usual manner exists following shortcoming: the first, Power supply difficulty, consume soon, and can not keep aircraft to navigate by water for a long time; The second, condition is harsh, needs sufficient sunlight (solar power) or sunny weather (fire balloon); Three, cost is expensive, and support price is high.
As from the foregoing, in this case, round-the-clock, high-resolution detection, low maintenance, floating empty monitored control system demand is day by day urgent cheaply.
Utility model content
The technical problems to be solved in the utility model is just: the technical matters existing for prior art, the utility model provide a kind of simple in structure, with low cost, easy to operate, action radius is wide, the floating empty monitored control system of the low-to-medium altitude of dependable performance.
For solving the problems of the technologies described above, the utility model by the following technical solutions:
A kind of low-to-medium altitude floats empty monitored control system, comprise aircraft, take unit, power subsystem unit, monitor component and traction control assembly, described shooting unit and power subsystem unit are all installed on aircraft, and described shooting unit sends the image photographing to the monitor component that is positioned at ground; Described traction control assembly comprises traction controller, traction actuating unit and draught line, and one end of described draught line is connected with aircraft, and the other end of described draught line is connected with traction actuating unit, and described traction actuating unit is controlled by traction controller.
As further improvement of the utility model:
Described shooting unit is connected with the monitor component that is positioned at ground by cable.
Described cable and draught line bind together.
Described shooting unit is connected with the monitor component on ground by wireless data transmitting apparatus.
Described power subsystem unit comprises battery, and described battery is used for as taking unit power supply.
Described aircraft is provided with wind power plant, and described wind power plant is used for powering and battery being charged taking unit.
Described aircraft is kite and balloon.
One end that described draught line is connected with aircraft is provided with line hook.
Compared with prior art, the utility model has the advantage of:
1, the utility model adopts kite or balloon as aircraft and carrier, and kite or balloon belong to unpowered flight platform, and restriction and the control of flying and being gone between.Particularly, for kite, wind is larger, fly more stable, and load-carrying capacity is stronger, and in the spatial domain among a small circle of its flight range centered by being limited in all the time discharging a little.
2, the utility model adopts transmission over radio vision signal, can pass through wireless access mobile communications network, receiving end variation; The utility model can directly receive wireless video signal, also can be by access mobile communications network access camera.
3, the utility model aerial photographing equipment is supplied with energy and is not needed other energy by wind, and aerial wind power plant can guarantee the self-sufficient of the aerial energy, thereby realizes the long-time stagnant empty flight of aerial platform.
4, the monitoring range of the utility model aircraft is wide, by the suitable capture apparatus position that arranges, can so that aircraft any can in-position and any angle to below take, take area large.
5, the utility model aircraft is adapted at flying under the weather of wind more, does not therefore have the problem of wind resistance flight, guarantees that 7 grades of strong wind still can work.
6, the utility model is taken cellular installation aloft on platform, and monitoring range increases along with the flying height of aerial platform, and the flying height of this platform is more than 200 meters, and monitoring range is larger more in the past than the monitoring range of camera that was fixed on ground.
7, the utility model cheap, use non-maintainingly, aerostatics is if any breakage, recyclable replacing, and change simply only need hook up down the line between draught line and kite, and hook is hooked on new aerial platform.
Accompanying drawing explanation
Fig. 1 is structural principle schematic diagram of the present utility model.
Fig. 2 is principle of work schematic diagram of the present utility model.
Marginal data:
1, aircraft; 101, take unit; 102, wind power plant; 103, power subsystem unit; 104, wireless data transmitting apparatus; 106, line hook; 2, monitor component; 301, traction controller; 302, traction actuating unit; 303, draught line.
The specific embodiment
Below with reference to Figure of description and specific embodiment, the utility model is described in further details.
As depicted in figs. 1 and 2, low-to-medium altitude of the present utility model floats empty monitored control system, comprise aircraft 1, take unit 101, power subsystem unit 103, monitor component 2 and traction control assembly, aircraft 1 can adopt the flyer of the carried out low-to-medium altitude suspension of kite, balloon or other types, taking unit 101 and power subsystem unit 103 is all installed on aircraft 1, when aircraft 1 carries out unsettled flight, take unit 101 and the image photographing is sent to the monitor component 2 that is positioned at ground.This shooting unit 101 can be connected with the monitor component 2 that is positioned at ground by cable, or is connected with the monitor component 2 on ground by wireless data transmitting apparatus 104.
In the present embodiment, traction control assembly comprises traction controller 301, traction actuating unit 302 and draught line 303, one end of draught line 303 is connected with aircraft 1, and the other end of draught line 303 is connected with traction actuating unit 302, and traction actuating unit 302 is controlled by traction controller 301.It will be appreciated, of course, that traction controller 301 can comprise automatic or manual manual two kinds of master modes, can automatically control according to parameter or the target set, also can under suitable environmental conditions, carry out artificial manual control.The cable that is used for connect taking unit 101 can become an integral body with draught line 303 bindings, is convenient to install and fixing.In this example, traction control assembly can be fixed on the fixed position on ground or directly grasp manipulation by people, and one end that draught line 303 is connected with aircraft 1 is provided with line hook 106, convenient connection, improves the reliability connecting.
In the present embodiment, power subsystem unit 103 can adopt battery or other electric energy storage devices, utilizes battery to power to taking unit 101.The utility model also further arranges wind power plant 102 on aircraft 1, can utilize 102 pairs of wind power plants to take unit 101 and power, and also battery is charged.
During work, the action radius of aircraft 1, for above the ground 200 meters to 500 meters, belongs to low-to-medium altitude region.Shooting unit 101 set on aircraft 1 is under power subsystem unit 103 power supplies are supported, its below is taken region on a large scale, and by wireless data transmitting apparatus 104, captured signal is sent in the monitor component 2 on ground (monitor component 2 can be fixing accepting device, can be also the receiving terminals such as mobile phone).Meanwhile, the wind power plant 102 on aircraft 1 generates electricity by the flight of aircraft 1, and electric energy is fed in battery unit 103 endlessly.
Below be only preferred implementation of the present utility model, protection domain of the present utility model is also not only confined to above-described embodiment, and all technical schemes belonging under the utility model thinking all belong to protection domain of the present utility model.It should be pointed out that for those skilled in the art, the some improvements and modifications not departing under the utility model principle prerequisite, should be considered as protection domain of the present utility model.
Claims (8)
1. a low-to-medium altitude floats empty monitored control system, it is characterized in that, comprise aircraft (1), take unit (101), power subsystem unit (103), monitor component (2) and traction control assembly, it is upper that described shooting unit (101) and power subsystem unit (103) are all installed on aircraft (1), and described shooting unit (101) sends the image photographing to the monitor component (2) that is positioned at ground; Described traction control assembly comprises traction controller (301), traction actuating unit (302) and draught line (303), one end of described draught line (303) is connected with aircraft (1), the other end of described draught line (303) is connected with traction actuating unit (302), and described traction actuating unit (302) is controlled by traction controller (301).
2. the floating empty monitored control system of low-to-medium altitude according to claim 1, is characterized in that, described shooting unit (101) is connected with the monitor component (2) that is positioned at ground by cable.
3. the floating empty monitored control system of low-to-medium altitude according to claim 2, is characterized in that, described cable and draught line (303) bind together.
4. the floating empty monitored control system of low-to-medium altitude according to claim 1, is characterized in that, described shooting unit (101) is connected with the monitor component (2) on ground by wireless data transmitting apparatus (104).
5. according to the floating empty monitored control system of the low-to-medium altitude described in claim 1 or 2 or 3 or 4, it is characterized in that, described power subsystem unit (103) comprises battery, and described battery is used for as taking unit (101) power supply.
6. low-to-medium altitude according to claim 5 floats empty monitored control system, it is characterized in that, described aircraft (1) is provided with wind power plant (102), and described wind power plant (102) is used for powering and battery being charged taking unit (101).
7. according to the floating empty monitored control system of the low-to-medium altitude described in claim 1 or 2 or 3 or 4, it is characterized in that, described aircraft (1) is kite and balloon.
8. according to the floating empty monitored control system of the low-to-medium altitude described in claim 1 or 2 or 3 or 4, it is characterized in that, one end that described draught line (303) is connected with aircraft (1) is provided with line hook (106).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320418378.4U CN203439271U (en) | 2013-07-15 | 2013-07-15 | Middle-low-altitude floating monitor system |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320418378.4U CN203439271U (en) | 2013-07-15 | 2013-07-15 | Middle-low-altitude floating monitor system |
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| CN203439271U true CN203439271U (en) | 2014-02-19 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201320418378.4U Expired - Lifetime CN203439271U (en) | 2013-07-15 | 2013-07-15 | Middle-low-altitude floating monitor system |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105652886A (en) * | 2016-03-18 | 2016-06-08 | 吴李海 | Internet unmanned aerial vehicle capable of achieving continuous endurance |
| CN105991977A (en) * | 2016-06-28 | 2016-10-05 | 齐鲁工业大学 | Air road condition detection device |
| CN106886223A (en) * | 2015-12-15 | 2017-06-23 | 北京电研华源电力技术有限公司 | A kind of kite floating platform |
| CN109005344A (en) * | 2018-08-08 | 2018-12-14 | 哈尔滨工业大学 | Multiple degrees of freedom is tethered at monitor supervision platform |
| CN110855936A (en) * | 2018-08-21 | 2020-02-28 | 尹盛煜 | Low-altitude unmanned monitoring system |
-
2013
- 2013-07-15 CN CN201320418378.4U patent/CN203439271U/en not_active Expired - Lifetime
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106886223A (en) * | 2015-12-15 | 2017-06-23 | 北京电研华源电力技术有限公司 | A kind of kite floating platform |
| CN105652886A (en) * | 2016-03-18 | 2016-06-08 | 吴李海 | Internet unmanned aerial vehicle capable of achieving continuous endurance |
| CN105652886B (en) * | 2016-03-18 | 2019-06-28 | 深圳市阿拉丁无人机有限公司 | A kind of internet unmanned plane persistently continued a journey |
| CN105991977A (en) * | 2016-06-28 | 2016-10-05 | 齐鲁工业大学 | Air road condition detection device |
| CN109005344A (en) * | 2018-08-08 | 2018-12-14 | 哈尔滨工业大学 | Multiple degrees of freedom is tethered at monitor supervision platform |
| CN109005344B (en) * | 2018-08-08 | 2020-09-01 | 哈尔滨工业大学 | Multi-degree-of-freedom mooring monitoring platform |
| CN110855936A (en) * | 2018-08-21 | 2020-02-28 | 尹盛煜 | Low-altitude unmanned monitoring system |
| US11358718B2 (en) * | 2018-08-21 | 2022-06-14 | Seung Hee CHOI | Low-altitude unmanned aerial vehicle surveillance system |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
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Granted publication date: 20140219 |
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| CX01 | Expiry of patent term |