CN104260879A - High-reliability high-stability multi-rotor-wing unmanned aerial vehicle with quick-dismounting function - Google Patents
High-reliability high-stability multi-rotor-wing unmanned aerial vehicle with quick-dismounting function Download PDFInfo
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- CN104260879A CN104260879A CN201410548586.5A CN201410548586A CN104260879A CN 104260879 A CN104260879 A CN 104260879A CN 201410548586 A CN201410548586 A CN 201410548586A CN 104260879 A CN104260879 A CN 104260879A
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Abstract
The invention provides a high-reliability high-stability multi-rotor-wing unmanned aerial vehicle with a quick-dismounting function. In order to quickly dismount the unmanned aerial vehicle, the central disc and arms of the unmanned aerial vehicle are split, fan-shaped plates with central angles of more than 180 degrees are arranged on the end surfaces of arm inner parts in arm connecting structures to serve as first limiting convex grooves, fan-shaped plates with central angles of less than 180 degrees are arranged on the end surfaces of central disc inner parts in the arm connecting structures to serve as second limiting convex grooves, and each first limiting convex groove and each second limiting convex groove are clamped together to form a round plate anti-twist structure; meanwhile, in order to prevent twisting of each anti-twist structure, two column positions are added in each connecting structure to reinforce the anti-twist effect, and the arm inner parts are integrally and fixedly connected with the central disc inner parts through thread suites on the outer sides of the formed anti-twist structures, so that the firmness of the unmanned aerial vehicle during flight is guaranteed and the anti-twist function of the arms is improved. The unmanned aerial vehicle has the advantages of simple structure, and has the advantages of quickness for dismounting and convenience for connecting and mounting; especially, the firmness and rigidity of connection are guaranteed, and the flight reliability and stability of the unmanned aerial vehicle are greatly improved.
Description
Technical field
The present invention relates to many rotor unmanned aircrafts, what be specifically related to is a kind ofly have the high reliability of fast assembling-disassembling and many rotor unmanned aircrafts of high stationarity.
Background technology
There is vertical takeoff and landing, the many rotor unmanned aircrafts of microminiature of steadily hovering, boundless application prospect is had in civilian and military field, common microminiature unmanned vehicle, though can vertical takeoff and landing and hovering, but adopt common grafting because the horn of this type of unmanned vehicle is fixedly connected with spider or is simply threaded, under rotor High Rotation Speed flight progress, especially after long-time use or flight, can exist spider be connected with horn loosen or horn twist the problem of inclination, unmanned plane is caused to be subject to force unbalance to produce vibration, the phenomenon of rocking.Cause and automatically control difficulty increase, and occur the situation that flight balance is deteriorated, serious conditions there will be air crash.If do not carry out hardness design to horn connection structure, consume additional power must be needed to adjust the balance of aircraft, increase the design difficulty of flying-controlled box, affect flying power and the stability of aircraft.
Summary of the invention
For this reason, the object of the present invention is to provide and a kind of there are the high reliability of fast assembling-disassembling and many rotor unmanned aircrafts of high stationarity, be connected with spider insecure to solve traditional unmanned vehicle horn, easily loosen, cause unmanned vehicle reliability and the low problem of balance.
The object of the invention is to be achieved through the following technical solutions.
A kind of have the high reliability of fast assembling-disassembling and the unmanned vehicle of high stationarity, comprise spider, multiple connecting arm is evenly distributed with outside described spider, described each connecting arm is all connected with a horn, one horn internals are all installed in each horn described, the end face that described horn internals expose to horn is provided with the first spacing tongue;
One spider internals are all installed in each connecting arm described, the end face that described spider internals expose to connecting arm is provided with the second spacing tongue;
Wherein, the first spacing tongue is corresponding with the second spacing tongue engages formation one circular slab, and described first spacing tongue is the quadrant that central angle is greater than 180 °, the horn internals boss medial surface of described first spacing tongue and horizontal plane; Second spacing tongue is the quadrant that central angle is less than 180 °, the spider internals boss medial surface of described second spacing tongue and horizontal plane.
Described first spacing tongue is provided with two location card columns and is connected column piece with a line, the front end face that described spider internals expose to connecting arm is provided with the hole clipping corresponding with locating card column, and the jack corresponding with line joint pin.
On described first spacing tongue, inner peripheral is provided with chamfering, arranges that the inside chamfering of negative thread is relative fits with described thread complete set inwall.
Described spider internals and horn internals junction are also equipped with a thread complete set.
Described thread complete set inwall is provided with negative thread, and spider internals lateral wall is provided with the outside thread corresponding with negative thread.
Described connecting arm is by decile even outside spider.
The present invention compared with prior art, beneficial effect is: provided by the invention have the high reliability of fast assembling-disassembling and many rotor unmanned aircrafts of high stationarity, it is greater than the quadrant of 180 ° as spacing tongue by horn internals end face being arranged central angle in horn, boss medial surface and horizontal plane, spider internals front end face is arranged central angle in connecting arm and be less than the quadrant of 180 ° as spacing tongue, boss medial surface and horizontal plane, utilize two position-limited troughs to be fastened togather formation circular slab error-proof structure; Horn internals and spider internals are located card column by two and are located, and prevent twisting.And by thread complete set, horn internals and spider internals are connected to one outside the error-proof structure formed.The present invention has that structure is simple, fast assembling-disassembling, connection advantage easily, especially which ensure that the firm of junction, effectively prevent the twisting of horn, cause horn to loosen, rock, thus substantially increase the reliability of many rotor unmanned aircrafts flight and high stationarity.
Accompanying drawing explanation
Fig. 1 is the whole structure schematic diagram of unmanned vehicle of the present invention;
Fig. 2 is spider and the horn released state schematic diagram of unmanned vehicle of the present invention;
Fig. 3 is the spider of unmanned vehicle of the present invention and the joint connection diagram one of horn;
Fig. 4 is the spider of unmanned vehicle of the present invention and the joint connection diagram two of horn.
Identifier declaration in figure: spider 100, horn 200, connecting arm 300, motor 400, the spacing tongue 501 of horn internals 500, first, location card column 502, line connect chamfering 702, rotor 800 inside column piece 503, horn internals chamfering 504, horn internals boss medial surface 505, the spacing tongue 601 of spider internals 600, second, outside thread 602, spider internals boss medial surface 603, thread complete set 700, negative thread 701, thread complete set.
Detailed description of the invention
In order to make object of the present invention, technical scheme and advantage clearly understand, below in conjunction with drawings and Examples, the present invention is further elaborated.Should be appreciated that specific embodiment described herein only in order to explain the present invention, be not intended to limit the present invention.
Refer to shown in Fig. 1, Fig. 1 is the whole structure schematic diagram of the fast assembling-disassembling of the many rotor unmanned aircrafts of the present invention.Unmanned vehicle described in the present embodiment comprises spider 100 and is arranged on multiple horns 200 of spider 100 outer circumference, and in the present embodiment, horn 200 is six, and the outer circumference of whole spider 100 is divided into six parts.
As shown in Figure 2, Fig. 2 is spider and the horn released state schematic diagram of the present invention's many rotor unmanned aircrafts fast assembling-disassembling.The outside circle correspondence of described spider 100 is provided with six connecting arms 300 in the present embodiment, is provided with spider internals 600, for the connection lead in spider 100 is connected to horn 200 in each connecting arm 300.
Be connected by connecting arm 300 between horn 200 with spider 100, and the one end be connected with connecting arm 300 in horn 200 is provided with horn internals 500; The other end of horn 200 is then provided with motor 400, and the rotor 800 be connected with motor 400.
Be fixedly connected with by thread complete set 700 with connecting arm 300 junction at horn 200, to ensure the fixation connected therebetween.
As shown in Figure 3, Fig. 3 is the spider of unmanned vehicle of the present invention and the joint connection diagram one of horn.This schematic diagram is the schematic diagram seen to connecting arm 300 direction along horn 200, the end face that horn internals 500 expose to horn 200 is provided with the first spacing tongue 501, and the first spacing tongue 501 is greater than the quadrant (in the present embodiment, the central angle of the first spacing tongue 501 is 300 °) of 180 ° for central angle, first spacing tongue 501 is provided with two location card columns 502 and is connected column piece 503 with a line, line connects the home position that column piece 503 is positioned at the first spacing tongue 501, its inside is provided with connection lead, two location card columns 502 lay respectively at line and connect column piece 503 both sides, and it is symmetrical.Inside the first spacing tongue 501 upper periphery chamfering 504 and thread complete set, chamfering 702 is close to conjunction.
As shown in Figure 4, Fig. 4 is the spider of unmanned vehicle of the present invention and the joint connection diagram two of horn.This schematic diagram is the schematic diagram seen to horn 200 direction along connecting arm 300, the end face that spider internals 600 expose to connecting arm 300 is provided with the second spacing tongue 601, second spacing tongue 601 is less than the quadrant (in the present embodiment, the central angle of the second spacing tongue 601 is 60 °) of 180 ° for central angle, the end face exposing to connecting arm 300 in spider internals 600 is provided with the hole clipping corresponding with above-mentioned location card column 502, and connects jack corresponding to column piece 503 with line.
Due to the existence of the first spacing tongue 501 and the second spacing tongue 601, when connecting horn 200 to connecting arm 300, if contraposition is forbidden, then location card column 502 cannot be connected column piece 503 with line is inserted in spider internals 600, only have and engage formation one circular slab when the first spacing tongue 501 is corresponding with the second spacing tongue 601, namely, when the central angle of the first spacing tongue 501 and the central angle of the second spacing tongue 601 are combined to form 360 °, the connection of spider internals 600 and horn internals 500 could be realized.
In addition, a thread complete set 700 is equipped with in spider internals 600 and the junction of horn internals 500, the inwall of thread complete set 700 is provided with negative thread 701, the lateral wall of spider internals 600 is provided with the outside thread 602 corresponding with negative thread 701, spider internals boss medial surface 603 and horn internals boss medial surface 505 are close to conjunction, after spider internals 600 are connected with horn internals 500, the coupling end of the two can be fixed by thread complete set 700.
The present invention is fastened togather the error-proof structure of formation by two position-limited troughs, ensure that horn is connected with spider quick and accurate, and this type of error-proof structure is when producing vibrations, offset by the application force of less locating part with larger locating part joint face, effectively prevent because thread complete set loosens and occur the unstable problem in junction, simultaneously horn internals and spider internals are passed through two and are located card column and locate, and can effectively prevent because FLIGHT VEHICLE VIBRATION causes the twisting of horn.Thus ensure that the balance of aircraft in flight course and stability.
The foregoing is only preferred embodiment of the present invention, not in order to limit the present invention, all any amendments done within the spirit and principles in the present invention, equivalent replacement and improvement etc., all should be included within protection scope of the present invention.
Claims (6)
1. one kind has the high reliability of fast assembling-disassembling and many rotor unmanned aircrafts of high stationarity, comprise spider (100), described spider (100) outside is evenly distributed with multiple connecting arm (300), described each connecting arm (300) is all connected with a horn (200), it is characterized in that
One horn internals (500) are all installed in described each horn (200), the front end face that described horn internals (500) expose to horn (200) is provided with the first spacing tongue (501);
One spider internals (600) are all installed in described each connecting arm (300), the front end face that described spider internals (600) expose to connecting arm (300) is provided with the second spacing tongue (601);
Wherein, first spacing tongue (501) is corresponding with the second spacing tongue (601) engages formation one circular slab, and the quadrant that described first spacing tongue (501) is greater than 180 ° for central angle, horn internals boss medial surface (505) of described first spacing tongue (501) and horizontal plane; The quadrant that second spacing tongue (601) is less than 180 ° for central angle, spider internals boss medial surface (603) of described second spacing tongue (601) and horizontal plane.
2. there are the high reliability of fast assembling-disassembling and many rotor unmanned aircrafts of high stationarity as claimed in claim 1, it is characterized in that, described first spacing tongue (501) is provided with two location card column (502) and is connected column piece (503) with a wiring, exposing on spider internals (600) front end face of described connecting arm (300) is provided with the hole clipping corresponding with locating card column (502), and connects jack corresponding to column piece (503) with wiring.
3. there are the high reliability of fast assembling-disassembling and many rotor unmanned aircrafts of high stationarity as claimed in claim 1, it is characterized in that, described spider internals (600) and horn internals (500) junction are also equipped with a thread complete set (700).
4. there are the high reliability of fast assembling-disassembling and many rotor unmanned aircrafts of high stationarity as claimed in claim 3, it is characterized in that, the upper inner peripheral of described first spacing tongue (501) is provided with horn internals chamfering (504), and inside the thread complete set arranging negative thread with described thread complete set (700) inwall, chamfering (702) is relative fits.
5. there are the high reliability of fast assembling-disassembling and many rotor unmanned aircrafts of high stationarity as claimed in claim 4, it is characterized in that, described thread complete set (700) inwall is provided with negative thread (701), and spider internals (600) lateral wall is provided with the outside thread (602) corresponding with negative thread (701).
6. have the high reliability of fast assembling-disassembling and many rotor unmanned aircrafts of high stationarity as claimed in claim 1, it is characterized in that, described connecting arm (300) is by spider (100) outside evenly decile.
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| CN201410548586.5A CN104260879B (en) | 2014-10-16 | 2014-10-16 | High-reliability high-stability multi-rotor-wing unmanned aerial vehicle with quick-dismounting function |
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| CN201410548586.5A CN104260879B (en) | 2014-10-16 | 2014-10-16 | High-reliability high-stability multi-rotor-wing unmanned aerial vehicle with quick-dismounting function |
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| CN104260879A true CN104260879A (en) | 2015-01-07 |
| CN104260879B CN104260879B (en) | 2017-05-03 |
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Cited By (12)
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| CN105151286A (en) * | 2015-08-27 | 2015-12-16 | 蔡强 | Module combined type manufacturing method for four-axis aircraft and four-axis aircraft |
| CN105270612A (en) * | 2015-10-23 | 2016-01-27 | 精功（绍兴）复合材料技术研发有限公司 | Unmanned aerial vehicle body |
| CN105416577A (en) * | 2015-12-09 | 2016-03-23 | 施恒锦 | Multi-rotor unmanned aerial vehicle |
| CN106005364A (en) * | 2016-07-12 | 2016-10-12 | 无锡觅睿恪科技有限公司 | Wing insertion connecting structure |
| CN106081059A (en) * | 2016-06-23 | 2016-11-09 | 湖北大秀天域科技发展有限公司 | A kind of many rotor wing unmanned aerial vehicles |
| WO2017197602A1 (en) * | 2016-05-18 | 2017-11-23 | 深圳市创客工场科技有限公司 | Multi-rotor aircraft |
| CN107867389A (en) * | 2017-11-08 | 2018-04-03 | 安徽梦之翼无人机科技有限公司 | A kind of plant protection unmanned plane horn structure |
| WO2018113481A1 (en) * | 2016-12-21 | 2018-06-28 | 深圳市道通智能航空技术有限公司 | Detachable arm assembly and aircraft |
| CN109774948A (en) * | 2019-02-13 | 2019-05-21 | 山东蜂巢航空科技有限公司 | It is a kind of can a variety of load of carry oil electricity mixing multi-rotor unmanned aerial vehicle |
| CN110891858A (en) * | 2018-11-21 | 2020-03-17 | 深圳市大疆创新科技有限公司 | Rotor subassembly and unmanned vehicles |
| CN112722239A (en) * | 2015-06-01 | 2021-04-30 | 深圳市大疆创新科技有限公司 | Unmanned aerial vehicle |
| CN114312177A (en) * | 2021-11-30 | 2022-04-12 | 浙江致优汽车科技有限公司 | Trailer coupling |
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| CN112722239B (en) * | 2015-06-01 | 2023-02-28 | 深圳市大疆创新科技有限公司 | Unmanned aerial vehicle |
| CN112722239A (en) * | 2015-06-01 | 2021-04-30 | 深圳市大疆创新科技有限公司 | Unmanned aerial vehicle |
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| CN106005364A (en) * | 2016-07-12 | 2016-10-12 | 无锡觅睿恪科技有限公司 | Wing insertion connecting structure |
| WO2018113481A1 (en) * | 2016-12-21 | 2018-06-28 | 深圳市道通智能航空技术有限公司 | Detachable arm assembly and aircraft |
| CN107867389A (en) * | 2017-11-08 | 2018-04-03 | 安徽梦之翼无人机科技有限公司 | A kind of plant protection unmanned plane horn structure |
| CN110891858A (en) * | 2018-11-21 | 2020-03-17 | 深圳市大疆创新科技有限公司 | Rotor subassembly and unmanned vehicles |
| CN110891858B (en) * | 2018-11-21 | 2023-11-10 | 深圳市大疆创新科技有限公司 | Rotor assembly and unmanned vehicles |
| CN109774948A (en) * | 2019-02-13 | 2019-05-21 | 山东蜂巢航空科技有限公司 | It is a kind of can a variety of load of carry oil electricity mixing multi-rotor unmanned aerial vehicle |
| CN114312177A (en) * | 2021-11-30 | 2022-04-12 | 浙江致优汽车科技有限公司 | Trailer coupling |
| CN114312177B (en) * | 2021-11-30 | 2024-04-16 | 浙江致优汽车科技有限公司 | Trailer coupling |
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Denomination of invention: Multi rotor unmanned aerial vehicle with high reliability and high stability Effective date of registration: 20211202 Granted publication date: 20170503 Pledgee: CITIC Bank Limited by Share Ltd. Shenzhen branch Pledgor: SHENZHEN KEWEITAI ENTERPRISE DEVELOPMENT Co.,Ltd. Registration number: Y2021440020137 |