CN201816723U - Intelligent sensing and pneumatic floating system of unmanned aerial vehicle for island surveying and mapping - Google Patents
Intelligent sensing and pneumatic floating system of unmanned aerial vehicle for island surveying and mapping Download PDFInfo
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- CN201816723U CN201816723U CN2010202706647U CN201020270664U CN201816723U CN 201816723 U CN201816723 U CN 201816723U CN 2010202706647 U CN2010202706647 U CN 2010202706647U CN 201020270664 U CN201020270664 U CN 201020270664U CN 201816723 U CN201816723 U CN 201816723U
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- air pressure
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- aerial vehicle
- pressure valve
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Abstract
The utility model discloses an intelligent sensing and pneumatic floating system of an unmanned aerial vehicle for island surveying and mapping, relating to a fault sensing and floating automatic control technology of an unmanned aerial vehicle. The intelligent sensing and pneumatic floating system comprises an air bottle, an air bag, a central control system, an intelligent sensor, a relay pneumatic valve and a power supply. The intelligent sensing and pneumatic floating system is characterized in that the system senses the uncontrolled drop of a platform of an unmanned aerial vehicle for island surveying and mapping by means of the intelligent sensor and transmits information to the central control system, the central control system processes the information, makes a judgment and sends out an enabled instruction, and the relay pneumatic valve automatically opens a valve of the air bottle to inflate the air bag, so that the inflated air bag enables the unmanned aerial vehicle to float on the water surface. The utility model first uses the floating system on an unmanned aerial vehicle, ensures that the unmanned aerial vehicle can float on the sea surface in case of going wrong and crashing in the process of surveying and mapping islands which can not be reached easily and appropriately, and prevents surveying and mapping instruments from being damaged as a result of sea water corrosion. Besides, rescue personnel can accurately lock the position range of the crashed unmanned aerial vehicle by means of a GPS (Global Positioning System) module. The system provided by the utility model has the advantages of high automation degree and simple structure, and is economical and practical.
Description
Technical field
The utility model belongs to the island survey field, relates to unmanned plane intelligent-induction and cursory automatic control technology.
Background technology
Because the space shuttle that unmanned plane is more general is with low cost, so fault happens occasionally, and existing unmanned plane does not generally have floating system, island mapping is with the main idle job on the marine site of unmanned plane, when et out of order falls, can sink to marine, make instrument of surveying and mapping be subjected to marine corrosion and go to pot, and can not determine in time that unmanned plane searches and rescues scope.
Summary of the invention
At above problem, the purpose of this utility model provides a kind of island mapping unmanned plane intelligent induction air pressure floating system of economy, the unmanned plane et out of order is fallen can swim in the water surface when marine, for unmanned plane is applied to the island mapping system that provides safeguard.
A kind of unmanned plane intelligent induction air pressure floating system that is used for the island mapping, comprise gas cylinder 100, air bag 200, central control system 300, intelligent inductor 400, relay air pressure valve 500 and power supply 600, gas cylinder 100 is fixed in ventral, air bag 200 is fixed in unmanned aerial vehicle body ringwise and links to each other with gas cylinder 100 by being flexible coupling, central control system 300, acceleration pick-up 410, height induction meter 420, relay air pressure valve 500 and power supply 600 are installed in the unmanned plane instrument compartment, and water sensitive accrued 430 is fixed on the air bag bottom at prow place.
This utility model by three grades of intelligent inductors 400 to guarantee accurately to sense island mapping unmanned plane platform non-controlling and descend or to arrive the water surface, carrying out induced signal by central control system 300 handles and threshold decision, and start 500 pairs of air bags 200 of relay air pressure valve and put on the air, after being fallen, unmanned plane can float at the water surface.This utility model can also be determined the unmanned plane position by height induction meter (GPS module) 420, with locking search and rescue scope.This utility model adopts independently power-supply system 600, when guaranteeing unmanned plane power system or Circuits System et out of order, and the floating system endure.
The characteristics of this utility model are floating system is applied on the unmanned plane, and are novel in design, degree of automation is high, simple in structure, economical and practical.
Description of drawings
Fig. 1 is the system architecture scheme drawing.
Fig. 2 is the system hardware connection diagram.
Fig. 3 is system works flow process figure.
Among the figure: the 100-gas cylinder; the 200-air bag, 210-air bag mat, 300-central control system (micro controller system); the 400-intelligent inductor; the 410-acceleration pick-up, 420-height induction meter (GPS module), the 430-water sensitive is accrued; 500-relay air pressure valve; 510-air pressure valve driving circuit, 520-air pressure valve, 600-power supply.
The specific embodiment
Describe in detail below in conjunction with drawings and Examples.
As depicted in figs. 1 and 2, native system comprises gas cylinder 100, air bag 200, central control system 300, intelligent inductor 400, relay air pressure valve 500 and power supply 600.Gas cylinder 100 is fixed in the unmanned plane ventral, air bag 200 is fixed in fuselage ringwise and links to each other with gas cylinder 100 by being flexible coupling, central control system 300, acceleration pick-up 410 and height induction meter 420, relay air pressure valve 500 and power supply 600 are installed in the unmanned plane instrument compartment, and water sensitive accrued 430 is fixed on the air bag bottom at prow place.Adopt AVR micro controller system (ATmega256) as central control system 300 in force, its operating voltage range is 2.7～6.0V.The function of central control system 300 is signals of sampling acceleration pick-up 410 output, and height and location information that the resolving GPS module receives compare accekeration or height value and setting threshold values and judge, send the unlatching drive signal of relay air pressure valve 500.Intelligent inductor 400 is realized three grades of induction mechanisms, comprise three kinds of induction meters: acceleration pick-up 410, height induction meter 420 and water sensitive accrued 430, acceleration pick-up 410 can be caught the unmanned plane fault by detecting the unmanned plane vibration, the non-controlling that detects unmanned plane by the measurement accekeration descends, fault can when taking place, fault in time be sensed, as the one-level inductor; Height induction meter 420 can obtain the altitude information of unmanned plane, and with the height threshold comparison to determine whether that starting relay air pressure valve 500 be air bag 200 inflations, the secondary inductor during as acceleration pick-up 410 inefficacies; When unmanned plane is not activated air bag 200 aloft, water sensitive accrued 430 can in time be sensed when unmanned plane hits the drink as third stage induction meter, and ejects air bags 200 by central control system 300.Adopt the GPS module as height induction meter 420 in the enforcement, the GPS module receives satellite positioning information, can calculate the unmanned plane elevation information by central control system 300; After unmanned plane falls into the water, can also determine the plan position information of unmanned plane to be the search and rescue lock-in range of unmanned plane by GPS module and central control system 300.Relay air pressure valve 500 comprises: air pressure valve driving circuit 510 and air pressure valve 520, the function of air pressure valve driving circuit 510 are unlatching drive signals of accepting by the relay air pressure valve 500 of central control system 300 outputs, the unlatching of control air pressure valve 520.Be equipped with mat 210 outside air bag 200, do not punctured by sharp object with the protection air bag, air bag 200 surperficial coated with luminescent material are beneficial to search-and-rescue work.
As shown in Figure 3, the specific implementation process of native system is as follows:
1, obtains unmanned plane non-controlling decline information by acceleration pick-up 410.When unmanned plane is carried out island mapping aerial mission, acceleration induction meter 410 continuous collecting unmanned plane acceleration informations, this information is transferred to central control system 300 by serial ports, central control system 300 is according to the certain hour interval sampling and handle acceleration information, obtain unmanned plane Ti accekeration constantly, accekeration is carried out integration obtain speed data.Its acceleration/accel should obtain the threshold range of the acceleration/accel of unmanned plane non-controlling decline when the unmanned plane non-controlling descended usually through experiment test in certain scope of gravity acceleration g.Central control system sampling and handle the Ti that obtains constantly unmanned plane accekeration therewith acceleration rate threshold compare, if in threshold range then can judge unmanned plane and be in non-controlling decline state.Ti velocity amplitude constantly can be used as the auxiliary data of judgement.Acceleration pick-up 410 can also detect the vibration of unmanned plane, obtain the unmanned plane failure message by the processing of central control system, the unmanned plane fault acquires a certain degree and just begins to fall, so can assist acceleration analysis to detect unmanned plane non-controlling decline information by the vibration of acceleration pick-up detection unmanned plane.
2, obtain the unmanned plane location information by GPS module 420.GPS module 420 receives satellite positioning information, pass to central control system 300 by serial ports, central control system 300 resolves unmanned plane Ti elevation information and plan position information constantly, elevation information that calculates and pre-determined height threshold (60m) compare, and can send the instruction of opening relay air pressure valve 500 when less than height threshold.Plan position information is passed to the unmanned aerial vehicle (UAV) control terminal by wireless telecommunication system (GPRS), can be used for locking its search and rescue scope when unmanned plane falls into water.
3, central control system 300 controls start relay air pressure valve 500.Central control system is judged the unmanned plane non-controlling according to acceleration pick-up 410 and is descended, or when the height of unmanned plane during less than height threshold, send the instruction of opening relay air pressure valve 500, air pressure valve driving circuit 510 receives instruction back self-opening air pressure valve 520, and high-pressure gas bottle 100 begins air bag 200 is put on the air.The air bag 200 that expands slows down the speed that unmanned plane falls on the one hand, on the other hand, when unmanned plane falls into the water, can make unmanned plane swim in the water surface.
4, the water sensitive of system accrued 430 guarantees that as three grades of standby induction meters air bag in time ejects.Preceding two-stage induction meter when improper reason intelligent inductor 400---acceleration pick-up 410 and height induction meter 420 do not make the unmanned plane of decline eject air bag 200 aloft, then working as unmanned plane falls into the water, water sensitive accrued 430 is met behind the water at once to central control system 300 transmission signals, central control system 300 starts electromagnetism air pressure valve 500 ejection air bags 200 after receiving signal, makes unmanned plane swim in the water surface, unlikely sinking under water.
5, system adopts independent current source 600.Native system adopts the independent current source 600 that separates with the unmanned plane Circuits System, when the power system of unmanned plane or Circuits System inefficacy, guarantees intelligent floating system endure like this.Power supply 600 adopts lithium ion battery to provide 5V direct supply for central control system 300, acceleration pick-up 410, GPS module 420 and relay air pressure valve 500.
The utility model will float system applies first on unmanned plane, guarantee in being difficult for, should not arriving the island mapping, when falling, the unmanned plane et out of order can float on the sea, avoid damaging because of marine corrosion makes expensive instrument of surveying and mapping, and by the GPS module make the rescue worker accurately lock the accident unmanned plane position range, system automation degree height, simple in structure, economical and practical.
Claims (7)
1. one kind is used for the unmanned plane intelligent induction air pressure floating system that the island is surveyed and drawn, comprise gas cylinder (100), air bag (200), central control system (300), intelligent inductor (400), relay air pressure valve (500) and power supply (600), it is characterized in that: gas cylinder (100) is fixed in ventral, air bag (200) is fixed in unmanned aerial vehicle body ringwise, and link to each other with gas cylinder (100) by being flexible coupling, intelligent inductor (400) comprises acceleration pick-up (410), height induction meter (420) and water sensitive accrued (430), central control system (300), acceleration pick-up (410), height induction meter (420), relay air pressure valve (500) and power supply (600) are installed in the unmanned plane instrument compartment, and water sensitive accrued (430) is fixed on the bottom of prow place air bag.
2. a kind of unmanned plane intelligent induction air pressure floating system that is used for the island mapping according to claim 1 is characterized in that intelligent inductor (400) comprises three grades of inductors: acceleration pick-up (410), height induction meter (420) and water sensitive accrued (430).
3. a kind of unmanned plane intelligent induction air pressure floating system that is used for the island mapping according to claim 2 is characterized in that the function of height induction meter (420) is realized by the GPS module.
4. a kind of unmanned plane intelligent induction air pressure floating system that is used for island mapping according to claim 1 is characterized in that central control system (300) is made up of a Single Chip Microcomputer (SCM) system.
5. a kind of unmanned plane intelligent induction air pressure floating system that is used for the island mapping according to claim 1, it is characterized in that relay air pressure valve (500) comprising: air pressure valve driving circuit (510) and air pressure valve (520), the function of air pressure valve driving circuit (510) is the switching drive signal of accepting by the relay air pressure valve (500) of central control system (300) output, and control air pressure valve (520) switch is to open or to cut out air pressure valve.
6. a kind of unmanned plane intelligent induction air pressure floating system that is used for island mapping according to claim 1 is characterized in that power supply (600) separates with the Circuits System of unmanned plane to adopt independent current source that the employing lithium ion battery is as power supply.
7. a kind of unmanned plane intelligent induction air pressure floating system that is used for the island mapping according to claim 1 is characterized in that: mat (210) is housed outside air bag (200) is not punctured by sharp object with protection air bag (200); The surperficial coated with luminescent material of air bag (200) is beneficial to search-and-rescue work.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010202706647U CN201816723U (en) | 2010-07-13 | 2010-07-13 | Intelligent sensing and pneumatic floating system of unmanned aerial vehicle for island surveying and mapping |
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| Application Number | Priority Date | Filing Date | Title |
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| CN2010202706647U CN201816723U (en) | 2010-07-13 | 2010-07-13 | Intelligent sensing and pneumatic floating system of unmanned aerial vehicle for island surveying and mapping |
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| CN201816723U true CN201816723U (en) | 2011-05-04 |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN105426121A (en) * | 2015-10-30 | 2016-03-23 | 山东科技大学 | Method for storing measurement data of multiple ship-borne sensors together in real time |
| WO2016172260A1 (en) * | 2015-04-21 | 2016-10-27 | Gopro, Inc. | Aerial capture platform |
| CN107632545A (en) * | 2017-09-14 | 2018-01-26 | 深圳市盛路物联通讯技术有限公司 | Data transfer control method and Related product |
| CN109131759A (en) * | 2018-10-22 | 2019-01-04 | 江苏东南测绘科技有限公司 | A kind of flotation gear of river channel mapping |
| US10696414B2 (en) | 2015-04-21 | 2020-06-30 | Gopro, Inc. | Aerial capture platform |
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2010
- 2010-07-13 CN CN2010202706647U patent/CN201816723U/en not_active Expired - Fee Related
Cited By (15)
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| EP3286079A4 (en) * | 2015-04-21 | 2018-03-14 | GoPro, Inc. | Aerial capture platform |
| CN107531322B (en) * | 2015-04-21 | 2021-02-05 | 高途乐公司 | Aerial capture platform |
| US9557738B2 (en) | 2015-04-21 | 2017-01-31 | Gopro, Inc. | Return path configuration for remote controlled aerial vehicle |
| CN107531322A (en) * | 2015-04-21 | 2018-01-02 | 高途乐公司 | Aerial capture platform |
| US11899472B2 (en) | 2015-04-21 | 2024-02-13 | Gopro, Inc. | Aerial vehicle video and telemetric data synchronization |
| US11530047B2 (en) | 2015-04-21 | 2022-12-20 | Gopro, Inc. | Unmanned aerial vehicle with rotating and overlapping rotor arms |
| WO2016172260A1 (en) * | 2015-04-21 | 2016-10-27 | Gopro, Inc. | Aerial capture platform |
| US10185318B2 (en) | 2015-04-21 | 2019-01-22 | Gopro, Inc. | Return path configuration for remote controlled aerial vehicle |
| US10942528B2 (en) | 2015-04-21 | 2021-03-09 | Gopro, Inc. | Return path configuration for remote controlled aerial vehicle |
| US10696414B2 (en) | 2015-04-21 | 2020-06-30 | Gopro, Inc. | Aerial capture platform |
| CN105426121B (en) * | 2015-10-30 | 2018-01-16 | 山东科技大学 | Boat-carrying multisensor integrated measuring data real-time storage method |
| CN105426121A (en) * | 2015-10-30 | 2016-03-23 | 山东科技大学 | Method for storing measurement data of multiple ship-borne sensors together in real time |
| CN107632545B (en) * | 2017-09-14 | 2021-01-26 | 深圳市盛路物联通讯技术有限公司 | Control method and device applied to space equipment |
| CN107632545A (en) * | 2017-09-14 | 2018-01-26 | 深圳市盛路物联通讯技术有限公司 | Data transfer control method and Related product |
| CN109131759A (en) * | 2018-10-22 | 2019-01-04 | 江苏东南测绘科技有限公司 | A kind of flotation gear of river channel mapping |
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Legal Events
| Date | Code | Title | Description |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20110504 Termination date: 20130713 |