CN102815397A - Miniature multi-rotor aircraft capable of taking off from and landing on water and land and being self-charged - Google Patents
Miniature multi-rotor aircraft capable of taking off from and landing on water and land and being self-charged Download PDFInfo
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- CN102815397A CN102815397A CN2012103014685A CN201210301468A CN102815397A CN 102815397 A CN102815397 A CN 102815397A CN 2012103014685 A CN2012103014685 A CN 2012103014685A CN 201210301468 A CN201210301468 A CN 201210301468A CN 102815397 A CN102815397 A CN 102815397A
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Abstract
The invention discloses a miniature multi-rotor aircraft capable of taking off from and landing on water and land and being self-charged in the technical field of small-size aircrafts. An inflating module, a charging module and a release module are installed on the miniature multi-rotor aircraft, wherein the inflating module is installed on a landing gear at the bottom of the multi-rotor aircraft and consists of a gas generator, miniature electronic valves, gas transmission pipes and airbags which are installed on landing gear bottom rods; the charging module consists of miniature solar energy receiving panels arranged on the surface of the rack of the aircraft, an energy management and a battery; and the release module is connected with the landing gear bottom rods and the airbags. The miniature multi-rotor aircraft capable of taking off from and landing on water and land and being self-charged has the characteristics of light weight and small resistance during flying in air and high stability of landing in water, can be widely used for image pickup, environmental detection, field rescue and the like in spaces above water surfaces, and has a wide prospect.
Description
Technical field
The invention belongs to the small aircraft technical field, but landing of particularly a kind of land and water and autonomous electrically-charged miniature multi-rotor aerocraft.
Background technology
Miniature multi-rotor aerocraft just is being widely used in fields such as aerial shooting, environment measuring, traffic supervision, electric power inspection and field rescue, has wide military and civilian prospect.For now; Miniature multi-rotor aerocraft is limited to the land landing mostly, for remote shooting waterborne, task such as patrol and examine, is prone to send out not enough or other faults of electric weight in the way; Miniature multi-rotor aerocraft is fallen into the water, therefore limited the application and the development of miniature multi-rotor aerocraft.
Summary of the invention
But the present invention proposes landing of a kind of land and water and autonomous electrically-charged miniature multi-rotor aerocraft, purpose is to solve miniature multi-rotor aerocraft in water surface landing and autonomous charging problem, expands its field of application.
The technical scheme that the present invention adopts is:
This aircraft self is mounted with the GPS module, and inflator module, charging module and disengaging module three parts are installed,
Said inflator module is installed on the alighting gear of multi-rotor aerocraft bottom, is made up of gas generator, miniature electronic valve, gas delivery tube and air bag; Gas generator is installed on the alighting gear connecting rod, and two air bags are installed in respectively in two grooves on the alighting gear bottom bar; Gas generator is connected with two air bags with gas delivery tube through the miniature electronic valve; Know through GPS module inquiry map whether the aircraft below is the water surface, if be that air bag is inflated automatically then through inflator module;
Said charging module is made up of miniature solar panel, energy management system and battery; Miniature solar panel is arranged in the aircraft frame surface; Behind the water landing, the miniature solar panel of energy management system automatic guidance is a battery charge, is its energy accumulation that takes off once more; According to the location information that the GPS module provides, calculate the distance between itself and nearest land, and flight to land the needed energy content of battery, thereby confirm the charging duration of charging module;
Said disengaging module is made up of four electronic snap closes; Two and the electronic snap close of air bag bonded assembly are installed on each alighting gear bottom bar; When aircraft takes off from the water surface once more, open electronic snap close, air bag is removed from aircraft.
Beneficial effect of the present invention is: through inflator module, charging module, disengaging module, safety has realized land and water landing function.Air bag is in contraction-likely before the water landing, has removed air bag behind the water landing, and omnidistance flight light weight, resistance is little, consumed power is little, it is stable to land in the water, can be widely used in the overhead shooting of the water surface, environment measuring, field rescue etc., has bright prospects.
Description of drawings
Fig. 1 is for being the bottom alighting gear scheme drawing of example with four rotor crafts.
Label among the figure:
The 1-gas generator; 2-miniature electronic valve; 3-alighting gear connecting rod; The 4-gas delivery tube; 5-alighting gear bottom bar; The 6-air bag.
The specific embodiment
But the invention provides landing of a kind of land and water and autonomous electrically-charged miniature multi-rotor aerocraft, the present invention is described further below in conjunction with the accompanying drawing and the specific embodiment.
With four rotor crafts is example, and structure is as shown in Figure 1.Inflator module, charging module and disengaging module three parts are installed on miniature multi-rotor aerocraft.
Inflator module is installed on the alighting gear of multi-rotor aerocraft bottom, is made up of gas generator 1, miniature electronic valve 2, gas delivery tube 4 and air bag 6; Gas generator 1 is installed on the alighting gear connecting rod 3, and two air bags 6 are installed in respectively in two grooves on the alighting gear bottom bar 5, and gas delivery tube 4 is through being bolted on the alighting gear connecting rod 3; Gas generator 1 is connected with two air bags 6 with gas delivery tube 4 through miniature electronic valve 2; The switching of flight control system control miniature electronic valve 2.Multi-rotor aerocraft is received falling signal or is detected battery electric quantity when being lower than aircraft and can flying out the required electric weight in waters; It will know according to Airborne GPS information inquiry map whether its below is the water surface by the GPS module, if be that air bag is inflated automatically through inflator module then.
Charging module is made up of miniature solar panel, energy management system and battery; Miniature solar panel is arranged in the aircraft frame surface; Behind the water landing, the miniature solar panel of energy management system automatic guidance is a battery charge, is its energy accumulation that takes off once more.Multi-rotor aerocraft calculates its nearest land and distance therebetween according to the Airborne GPS location information, and the needed energy content of battery of flying to land, thereby confirms the charging duration of solar power.
Breaking away from module is made up of four electronic snap closes; Two and the electronic snap close of air bag 6 bonded assemblys are installed on each alighting gear bottom bar 5; When aircraft takes off from the water surface once more, open electronic snap close, air bag 6 is removed from aircraft.In order to reclaim air bag, air bag to around send signal so that be identified signal and reclaim.
Claims (1)
1. but a land and water landing and autonomous electrically-charged miniature multi-rotor aerocraft self are mounted with the GPS module, it is characterized in that: inflator module, charging module and disengaging module three parts are installed on miniature multi-rotor aerocraft,
Said inflator module is installed on the alighting gear of multi-rotor aerocraft bottom, is made up of gas generator (1), miniature electronic valve (2), gas delivery tube (4) and air bag (6); Gas generator (1) is installed on the alighting gear connecting rod (3), and two air bags (6) are installed in respectively in the groove on two alighting gear bottom bars (5); Gas generator (1) is connected with two air bags (6) with gas delivery tube (4) through miniature electronic valve (2); Know through GPS module inquiry map whether the aircraft below is the water surface, if be air bag (6) inflation automatically then through inflator module;
Said charging module is made up of miniature solar panel, energy management system and battery; Miniature solar panel is arranged in the aircraft frame surface; Behind the water landing, the miniature solar panel of energy management system automatic guidance is a battery charge, is its energy accumulation that takes off once more; According to the location information that the GPS module provides, calculate the distance between itself and nearest land, and flight to land the needed energy content of battery, thereby confirm the charging duration of charging module;
Said disengaging module is made up of four electronic snap closes; Each alighting gear bottom bar (5) is gone up two and the electronic snap close of air bag (6) bonded assembly is installed; When aircraft takes off from the water surface once more, open electronic snap close, air bag (6) is removed from aircraft.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210301468.5A CN102815397B (en) | 2012-08-22 | 2012-08-22 | Can the Miniature multi-rotor aircraft of land and water landing and recharging |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201210301468.5A CN102815397B (en) | 2012-08-22 | 2012-08-22 | Can the Miniature multi-rotor aircraft of land and water landing and recharging |
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| Publication Number | Publication Date |
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| CN102815397A true CN102815397A (en) | 2012-12-12 |
| CN102815397B CN102815397B (en) | 2016-01-13 |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103895462A (en) * | 2014-04-15 | 2014-07-02 | 北京航空航天大学 | Land and air search and rescue device capable of detecting human face and achieving photovoltaic power generation |
| CN104163241A (en) * | 2014-08-12 | 2014-11-26 | 中国航空工业经济技术研究院 | Unmanned logistics helicopter |
| CN104753144A (en) * | 2015-04-19 | 2015-07-01 | 中南大学 | Rotor-wing unmanned aerial vehicle charging pile and charging method thereof |
| CN104808666A (en) * | 2015-04-22 | 2015-07-29 | 深圳市视晶无线技术有限公司 | Method for increasing movement distance of automatic movement device |
| CN106103274A (en) * | 2015-07-02 | 2016-11-09 | 深圳市大疆创新科技有限公司 | Unmanned plane, its control system and method, and unmanned plane landing control method |
| JP2018024431A (en) * | 2017-10-24 | 2018-02-15 | エスゼット ディージェイアイ テクノロジー カンパニー リミテッドＳｚ Ｄｊｉ Ｔｅｃｈｎｏｌｏｇｙ Ｃｏ．，Ｌｔｄ | Unmanned aerial vehicle, control system and method therefor, and landing control method for unmanned aerial vehicle |
| CN109436305A (en) * | 2018-11-20 | 2019-03-08 | 南京信息工程大学 | Can water surface landing unmanned plane |
| CN111470035A (en) * | 2020-04-30 | 2020-07-31 | 中国飞机强度研究所 | Complex terrain self-adaptive landing gear of vertical take-off and landing aircraft and landing method thereof |
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| CN104163241A (en) * | 2014-08-12 | 2014-11-26 | 中国航空工业经济技术研究院 | Unmanned logistics helicopter |
| CN104753144A (en) * | 2015-04-19 | 2015-07-01 | 中南大学 | Rotor-wing unmanned aerial vehicle charging pile and charging method thereof |
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| CN106103274A (en) * | 2015-07-02 | 2016-11-09 | 深圳市大疆创新科技有限公司 | Unmanned plane, its control system and method, and unmanned plane landing control method |
| CN107697286A (en) * | 2015-07-02 | 2018-02-16 | 深圳市大疆创新科技有限公司 | Unmanned plane, its control system and method, and unmanned plane landing control method |
| CN107600398B (en) * | 2015-07-02 | 2019-11-19 | 深圳市大疆创新科技有限公司 | Unmanned plane, unmanned aerial vehicle control system and unmanned aerial vehicle (UAV) control method |
| US10669024B2 (en) | 2015-07-02 | 2020-06-02 | SZ DJI Technology Co., Ltd. | Unmanned aerial vehicle, control system and method thereof, and unmanned aerial vehicle landing control method |
| CN107697286B (en) * | 2015-07-02 | 2020-10-23 | 深圳市大疆创新科技有限公司 | Unmanned aerial vehicle, control system and method thereof, and unmanned aerial vehicle landing control method |
| JP2018024431A (en) * | 2017-10-24 | 2018-02-15 | エスゼット ディージェイアイ テクノロジー カンパニー リミテッドＳｚ Ｄｊｉ Ｔｅｃｈｎｏｌｏｇｙ Ｃｏ．，Ｌｔｄ | Unmanned aerial vehicle, control system and method therefor, and landing control method for unmanned aerial vehicle |
| CN109436305A (en) * | 2018-11-20 | 2019-03-08 | 南京信息工程大学 | Can water surface landing unmanned plane |
| CN111470035A (en) * | 2020-04-30 | 2020-07-31 | 中国飞机强度研究所 | Complex terrain self-adaptive landing gear of vertical take-off and landing aircraft and landing method thereof |
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Inventor after: Wu Hua Inventor after: Feng Meifang Inventor after: Liu Changan Inventor after: Zhang Hongyuan Inventor after: Lin Lvfan Inventor after: Yang Meng Inventor before: Wu Hua Inventor before: Feng Meifang Inventor before: Liu Changan Inventor before: Zhang Hongyuan Inventor before: Lin Lvfan Inventor before: Yang Meng |
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