CN103625641B - Laterally folded formula quadrotor - Google Patents
Laterally folded formula quadrotor Download PDFInfo
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- CN103625641B CN103625641B CN201310576919.0A CN201310576919A CN103625641B CN 103625641 B CN103625641 B CN 103625641B CN 201310576919 A CN201310576919 A CN 201310576919A CN 103625641 B CN103625641 B CN 103625641B
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- laterally folded
- arm
- support arm
- detachable
- fuselage
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Abstract
The invention discloses a kind of laterally folded formula quadrotor, comprise fuselage, the sidepiece of fuselage is provided with multiple laterally folded support arm, and the bottom of fuselage or laterally folded support arm is provided with multiple detachable alighting gear, and the end of laterally folded support arm is provided with detachable rotor.Solve traditional four rotor cross bares and alighting gear stationary structure takes up room greatly, stores the inconvenient problem of transport, structure be simple, efficient, can Portable belt and operation.
Description
Technical field
The present invention relates to a kind of quadrotor, particularly relate to a kind of laterally folded formula quadrotor.
Background technology
Quadrotor realizes various action by changing the speed of rotor, and compared to other unmanned vehicles, four rotor unmanned aircrafts are driven by four groups of motors, have have a smooth flight, hover, side flies and the feature such as inverted flight.Without the need to swinging radius, flexibly.Be applicable to performing the tasks such as fixed point scouting, shooting, aerial mapping.
The rotor of quadrotor of the prior art and landing gear structure are all fixing, this just make aircraft carry with transportation in bring larger volume.Although some quadrotor also adopts accordion structure, the such as MD4-1000 type aircraft of Germany, although have employed accordion structure, the volume after it is folding is still very large, makes troubles to transport and use.
Summary of the invention
The object of this invention is to provide a kind of structure and simple to operate, volume is little, the laterally folded formula quadrotor that is convenient for carrying and transports.
The object of the invention is to be achieved through the following technical solutions:
Laterally folded formula quadrotor of the present invention, comprise fuselage, the sidepiece of described fuselage is provided with multiple laterally folded support arm, and the bottom of described fuselage or laterally folded support arm is provided with multiple detachable alighting gear, and the end of described laterally folded support arm is provided with detachable rotor.
As seen from the above technical solution provided by the invention, the laterally folded formula quadrotor that the embodiment of the present invention provides, sidepiece due to fuselage is provided with multiple laterally folded support arm, the bottom of fuselage or laterally folded support arm is provided with multiple detachable alighting gear, the end of laterally folded support arm is provided with detachable rotor, solve traditional four rotor cross bares and alighting gear stationary structure takes up room greatly, stores the inconvenient problem of transport, structure be simple, efficient, can Portable belt and operation.
Accompanying drawing explanation
The integral structure schematic diagram of the laterally folded formula quadrotor application state that Fig. 1 provides for the embodiment of the present invention;
Fig. 2 a, 2b, 2c are the folding process schematic diagram of laterally folded support arm in the embodiment of the present invention;
Fig. 3 a, 3b are the local structure schematic diagram at the folding position of laterally folded support arm in the embodiment of the present invention;
Fig. 4 a, 4b are the local structure schematic diagram of detachable alighting gear and fuselage plugging position in the embodiment of the present invention;
Fig. 5 a, 5b are respectively the structural representation of detachable alighting gear and upper end thereof in the embodiment of the present invention.
In figure: 1, detachable alighting gear, 2, fuselage, 3, detachable rotor, 4, laterally folded support arm, 5, bearing pin, 6, protruding, 7, draw-in groove, 8, card.
Detailed description of the invention
To be described in further detail the embodiment of the present invention below.
Laterally folded formula quadrotor of the present invention, its preferably detailed description of the invention be:
Comprise fuselage, the sidepiece of described fuselage is provided with multiple laterally folded support arm, and the bottom of described fuselage or laterally folded support arm is provided with multiple detachable alighting gear, and the end of described laterally folded support arm is provided with detachable rotor.
Described laterally folded support arm comprises inner arm and outer arm, described inner arm and outer arm side are hinged, the opposite side of described inner arm is provided with bearing pin, the opposite side of described outer arm is provided with elastomeric projection, under described inner arm and outer arm deployed condition, described projection is stuck on described bearing pin, and under described inner arm and outer arm folded state, described projection departs from described bearing pin.
The bottom of described fuselage or laterally folded support arm is provided with socket, the both sides of described socket are respectively equipped with draw-in groove, the both sides of the upper end of described detachable alighting gear are provided with elastomeric card, and the upper end of described detachable alighting gear is inserted into after in described socket, and the card of its both sides snaps in described draw-in groove.
Laterally folded formula quadrotor of the present invention, by laterally folded support arm and detachable alighting gear, realize quadrotor quick despatch, thus reach reduction accumulating volume, improve the object of portability, solve traditional four rotor cross bares and alighting gear stationary structure takes up room greatly, store the inconvenient problem of transport, structure simply, efficiently, can Portable belt and operation, and can conveniently preserve, singlely can carry carrying.
Specific embodiment:
As shown in Fig. 1 to Fig. 5 b, comprise detachable alighting gear 1, fuselage 2, the detachable part such as rotor 3, laterally folded support arm 4.
As shown in Figure 1, detachable rotor 3 realizes fast folding, support by laterally folded support arm 4, and concrete folding mode is as shown in Fig. 2 a, 2b, 2c, and its support, fixed form are as shown in Fig. 3 a, 3b.The dismounting of detachable alighting gear 1 and fixed form are as shown in Fig. 4 a, 4b, and the close-up schematic view of detachable alighting gear 1 is as shown in Fig. 5 a, 5b.
Each component part is described below respectively:
(1) aircraft four laterally folded support arms can be laterally folded, is in folded state, as shown in Figure 2 c, can reduces transport space when storage, transport.Support arm can be opened in work, as shown in Figure 2 a.Support arm utilizes the bulge-structure of support arm burst to complete and fixes fast and be separated, as shown in Fig. 3 a, 3b when opening or fold.
(2) the detachable alighting gear of aircraft is used for aircraft when taking off and land to the support of aircraft entirety.Work is that detachable alighting gear interface is inserted the fixing room be positioned at below fuselage, and utilize the card of interface and the draw-in groove of interface to be fixed, dismounting is the elastic force utilizing card self, and support fast dismantling can remove by light pressure card, and concrete structure as shown in Figure 5.
(3) aircraft fuselage is for placing internal cell, circuit card and other work components and parts.
The beneficial effect that technical solution of the present invention is brought:
Support arm is laterally folded, and can fast folding with fixing, not only reduce to store, transport space, also reduce the setup time before equipment use simultaneously; Support is detachable and can quick despatch, can reduce equally to store, transport space, also reduces the setup time before equipment use.
The above; be only the present invention's preferably detailed description of the invention, but protection scope of the present invention is not limited thereto, is anyly familiar with those skilled in the art in the technical scope that the present invention discloses; the change that can expect easily or replacement, all should be encompassed within protection scope of the present invention.Therefore, protection scope of the present invention should be as the criterion with the protection domain of claims.
Claims (1)
1. a laterally folded formula quadrotor, it is characterized in that, comprise fuselage, the sidepiece of described fuselage is provided with multiple laterally folded support arm, the bottom of described fuselage or laterally folded support arm is provided with multiple detachable alighting gear, and the end of described laterally folded support arm is provided with detachable rotor;
Described laterally folded support arm comprises inner arm and outer arm, described inner arm and outer arm side are hinged, the opposite side of described inner arm is provided with bearing pin, the opposite side of described outer arm is provided with elastomeric projection, under described inner arm and outer arm deployed condition, described projection is stuck on described bearing pin, and under described inner arm and outer arm folded state, described projection departs from described bearing pin;
The bottom of described fuselage or laterally folded support arm is provided with socket, the both sides of described socket are respectively equipped with draw-in groove, the both sides of the upper end of described detachable alighting gear are provided with elastomeric card, and the upper end of described detachable alighting gear is inserted into after in described socket, and the card of its both sides snaps in described draw-in groove.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310576919.0A CN103625641B (en) | 2013-11-18 | 2013-11-18 | Laterally folded formula quadrotor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310576919.0A CN103625641B (en) | 2013-11-18 | 2013-11-18 | Laterally folded formula quadrotor |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103625641A CN103625641A (en) | 2014-03-12 |
| CN103625641B true CN103625641B (en) | 2016-01-20 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201310576919.0A Active CN103625641B (en) | 2013-11-18 | 2013-11-18 | Laterally folded formula quadrotor |
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| CN104002964B (en) * | 2014-05-30 | 2016-02-03 | 深圳一电科技有限公司 | Many rotor wing unmanned aerial vehicles |
| CN104260878A (en) * | 2014-10-16 | 2015-01-07 | 北京理工大学 | Four-rotor aircraft rack with capacity of automatic folding and spreading |
| CN104401484A (en) * | 2014-10-16 | 2015-03-11 | 北京理工大学 | Six-rotor aircraft rack capable of being folded and expanded automatically |
| CN104260605A (en) * | 2014-10-16 | 2015-01-07 | 北京理工大学 | Air-ground amphibious spherical metamorphic robot based on metamorphic principle |
| CN105752329B (en) * | 2014-10-21 | 2018-02-16 | 江苏锦程航空科技有限公司 | A kind of four rotor wing unmanned aerial vehicles with remote control system |
| CN105730696B (en) * | 2014-10-21 | 2017-12-19 | 哈工大机器人集团（哈尔滨）资产经营管理有限公司 | It is a kind of that there is remote control system, the unmanned plane of flight control system |
| CN105752328B (en) * | 2014-10-21 | 2017-12-08 | 双峰援农机械制造有限公司 | It is a kind of that there are remote control system, four rotor wing unmanned aerial vehicles of flight control system |
| CN104401490B (en) * | 2014-10-21 | 2016-06-08 | 东莞市粤钢不锈钢制品有限公司 | Wide spectrum lures moth unmanned plane |
| CN104386249B (en) * | 2014-11-17 | 2016-03-30 | 马鞍山市靓马航空科技有限公司 | The mapping method of the many rotor wing unmanned aerial vehicles of a kind of quick mapping |
| KR101766031B1 (en) | 2015-09-01 | 2017-08-08 | 한국항공우주연구원 | Propeller allocation re-configurable drone |
| CN105129082B (en) * | 2015-09-01 | 2018-07-27 | 湖南云顶智能科技有限公司 | Propeller Folding device for unmanned plane |
| CN105035305B (en) * | 2015-09-01 | 2017-09-15 | 湖南云顶智能科技有限公司 | Propeller folding device for unmanned plane |
| CN205440846U (en) * | 2015-12-24 | 2016-08-10 | 亿航智能设备（广州）有限公司 | Unmanned aerial vehicle and horn folding mechanism thereof |
| CN106314772B (en) * | 2016-02-03 | 2019-06-11 | 曹萍 | Non-planar eight arms, 32 rotor craft |
| CN106347626A (en) * | 2016-11-16 | 2017-01-25 | 北京韦加无人机科技股份有限公司 | Foldable multi-rotor plant protection unmanned aerial vehicle |
| CN108910012A (en) * | 2018-07-26 | 2018-11-30 | 瀚伦贝尔通用航空器有限公司 | A kind of big boom device of folding aircraft |
| CN113335514B (en) * | 2021-07-15 | 2022-06-17 | 黑龙江省农业科学院水稻研究所 | Unmanned aerial vehicle spore capture instrument and method for disease monitoring of rice |
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| KR101042200B1 (en) * | 2010-09-02 | 2011-06-16 | 드림스페이스월드주식회사 | Unmanned flying vehicle made with pcb |
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| CN201793017U (en) * | 2010-09-16 | 2011-04-13 | 中国计量学院 | Rotary retractable four-rotor flight device |
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| Publication number | Publication date |
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| CN103625641A (en) | 2014-03-12 |
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