CN106240794B - A kind of multi-rotor unmanned aerial vehicle horn folding device - Google Patents
A kind of multi-rotor unmanned aerial vehicle horn folding device Download PDFInfo
- Publication number
- CN106240794B CN106240794B CN201610718383.5A CN201610718383A CN106240794B CN 106240794 B CN106240794 B CN 106240794B CN 201610718383 A CN201610718383 A CN 201610718383A CN 106240794 B CN106240794 B CN 106240794B
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- horn
- fastener
- connecting plate
- connector
- support element
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/30—Parts of fuselage relatively movable to reduce overall dimensions of aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/061—Frames
- B64C1/063—Folding or collapsing to reduce overall dimensions, e.g. foldable tail booms
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Remote Sensing (AREA)
- Pivots And Pivotal Connections (AREA)
- Aerials With Secondary Devices (AREA)
Abstract
The present invention relates to support element and fastener 5, the lower hinges of support element between the lower end of 1 front of horn connector and two carbon plates between a kind of multi-rotor unmanned aerial vehicle horn folding device, including 1, two carbon plate of horn connector to offer eccentric orfice in the front end of fastener 5；The top of support element is fixed with baffle 4 between two carbon plates, blind recess 9 is offered in the centre of baffle 4, it is fixed with connecting plate 10 in the upper end of 1 front of horn connector, the connecting plate notch 11 for allowing bayonet lock 7 to pass through is offered on connecting plate 10, axis pin 6 is matched with the eccentric circular hole of fastener 5；Bayonet lock 7 is half tooth bolt, passes through the connecting plate notch 11 on horn connector 1 to be connect with the internal thread hole on axis pin 6, and be in free state relative to horn connector 1.The present invention can enhance the reliability and multi-rotor unmanned aerial vehicle overall stability of folding device part.
Description
Technical field
The present invention relates to a kind of collapsible unmanned plane horn locking devices, belong to unmanned plane field of structural design.
Background technology
In recent years, more rotor plant protection drones are increasingly used in crops and fly anti-field, compared to more rotors
Take photo by plane machine, more rotor plant protection drones because load is larger, take off needed for the pulling force that provides can increase therewith, it is therefore desirable to bigger
Propeller provides pulling force, thus caused by unmanned plane overall dimensions increase can come not to the conveyer belt of more rotor plant protection drones
Just, therefore, the fold mechanism design of more rotor plant protection drone horns is just particularly important.
More rotor horn folding devices are usually made of three parts, respectively：Carbon plate fixed part, horn coupling part,
Horn position portion.Carbon plate fixed part is bolted between upper and lower carbon plate (or integrated circuit board)；Horn interconnecting piece
Divide and be used for connecting, fix horn, the other end is hinged by axis pin and carbon plate fixed part；Horn position portion is used for realizing horn
Stretching, extension and folding.The solution of carbon plate fixed part and horn coupling part is similar, only in horn position portion
Solution is had nothing in common with each other.
Currently, there are mainly three types of horn positioning methods in：
1. direct mistake wears bolt.The positioning method is to have location hole in carbon plate fixed part and horn coupling part, when
When horn lifts each via axle center coincidence, it is inserted into stay bolt and is simultaneously tightened with nut in the other end.This kind of positioning method is simple in structure,
But dismounting is time-consuming longer, needs one by one to pass through bolt and be tightened again with nut, or bolt is removed one by one and folds horn, is easy
Bolt is caused to be lost, if bolt is stayed in carbon plate fixed part or horn coupling part, the workload for wearing bolt is double.And
Bolt easily generates deformation due to by shearing force during use, to influence the body force effect of multi-rotor unmanned aerial vehicle.
2. button-shaped unlatching closed manners.The positioning method is, using any as center of circle fixed sectors knob on carbon plate,
One section of globoidal structure (or the cambered surface is structure as a whole with horn coupling part) of horn coupling part installation same radius, utilizes
The principle that the isocentric circular arc track of same radius overlaps, under the premise of ensuring knob certain with cambered surface concentricity, turn knob,
It is fastened with globoidal structure, realizes horn positioning.This kind of positioning method, it is high to the positioning requirements precision of foldable structure, and using
In the process since the abrasion of part can make the positioning of horn generate loosening, diastema is formed, the reliability of positioning is influenced.
3. spring positioning method.The positioning method is to slot in carbon plate fixed part, to sliding part, (spring is lived
Moved end) installation；In carbon plate fixed part trepanning, to the fixation of spring fixed end part.Using the recovery characteristic of spring, lead to
Crossing promotion sliding part makes spring-compressed, and horn is unfolded, then so that the sliding part is resetted under the return action of spring, with reality
The expansion positioning of existing horn.The structure is in use since motor speed is frequently widely varied so that sliding part
Carbon plate fixed part Yu horn coupling part junction by shearing force, and because sliding part is in carbon plate fixed part and machine
The junction cross section mutation of arm coupling part leads at the variation of cross section that there are local stresses, should under the active force cut
Sliding part easily fatigue deformation or fatigue break leads to horn positioning failure.
Invention content
In view of the above-mentioned problems, the purpose of the present invention is overcoming the shortcomings of existing folding device solution, in conjunction with heavy－duty
The characteristics of multi-rotor unmanned aerial vehicle, provides one kind quick for installation, accurate positioning, the reliable folding device solution of structure.This hair
The bright reliability that can enhance folding device part and multi-rotor unmanned aerial vehicle overall stability, are effectively ensured the safety of flight.
Technical scheme is as follows：
A kind of multi-rotor unmanned aerial vehicle horn folding device, including horn connector 1, be used for and carbon plate on unmanned plane and lower carbon
Support element and fastener 5 between two carbon plates that plate is fixedly connected, which is characterized in that the lower end of 1 front of horn connector and two
The lower hinge of support element between carbon plate offers eccentric orfice in the front end of fastener 5；The top of support element is solid between two carbon plates
Surely there is baffle 4, blind recess 9 offered in the centre of baffle 4, connecting plate 10 is fixed in the upper end of 1 front of horn connector,
The connecting plate notch 11 for allowing bayonet lock 7 to pass through, the eccentric circular hole phase of axis pin 6 and fastener 5 are offered on connecting plate 10
Cooperation；Bayonet lock 7 is half tooth bolt, and the connecting plate notch 11 on horn connector 1 is passed through to connect with the internal thread hole on axis pin 6
It connects, and free state is in relative to horn connector 1；When fastening, support element between horn 1 to two carbon plate of connector is rotated
Fitting, falls into blind recess 9, and the rear end of fastener 5 is rotated to the position parallel with horn connector 1 by bayonet lock 7 so that
Bayonet lock 7 is closely connect under the barrier effect of baffle 4 with horn connector 1, fastener 5.
Preferably, the section of the fastener 5 is comma shape, and front end is cylindric, connecting plate 10
The surface being in contact with 5 front end of fastener is the cambered surface being matched therewith, comma " fastener can be in the cambered surface of connecting plate 10
It is rotated between 0 °~90 ° in a manner of inscribe.
The present invention has for the larger feature of existing more rotor plant protection drone take-off weights compared with existing solution
It has the advantage that：
(1) horn is quick for installation.When horn is unfolded, bayonet lock is caught in the groove of baffle, bayonet lock is slightly pushed down, avoids and blocks
It sells the axis pin being connected to rotate relative to " comma " fastener, " comma " fastener is rotated from 90 ° of positions to 0 ° of position
It sets.Realize horn positioning.
(2) in present design, a kind of bayonet lock actually nonstandard half tooth bolt is connect, bayonet lock with the internal thread hole on axis pin
Being screwed into the depth of axis pin can be adjusted, and may insure that diastema may be not present in the installation fastening of horn in this way；Due to this design organization
Middle bayonet lock and baffle connected to it can bear the pulling force from horn or pressure generation mechanical wear, and this abrasion can also pass through
The depth that adjusting bayonet lock is screwed into axis pin compensates, and improves the service life of main stress part to a certain extent.
(3) present design because of mechanical shock or occurs accident and generates fuselage side in the operation of more rotor plant protection drones
When turning over, since plant protection drone self inertia is larger and motor side first lands, fold mechanism axis pin is more tensioned by pulling force, to
It increases and pin is drawn to make bayonet lock be not easy to slip with the frictional force of casing member contact surface；And for toughness material (aluminium alloy 6061 or not
Become rusty steel), the tensile strength of material is greater than shearing strength, and main stress part bayonet lock is drawn by being changed by shearing force
Power also reduces the damage probability of folding device vital part.
(4) cooperation of " comma " fastener and axis pin is designed using eccentric, and after bayonet lock is caught in blind recess, " comma " is tight
Firmware can be rotated in a manner of inscribe between 0 °~90 ° in horn connector cambered surface, (" comma " fastener and horn direction
Be 90 ° when vertical, be 0 ° when consistent with horn direction) " comma " fastener it is vertical with horn direction when axis pin axle center to horn company
The distance of fitting cambered surface is minimum, and the distance of bayonet lock end surface to horn connector cambered surface is maximum, and horn is in relaxation shape at this time
State；It is maximum at a distance from axis pin axle center to horn connector cambered surface when " comma " fastener is vertical with horn direction, and bayonet lock head end
The distance of face to horn connector cambered surface is minimum, and horn is in tensioning state at this time, and horn is fixed.This patent is tied using eccentric
The characteristic of structure, simplifies structural design scheme, improves the reliability of folding device.
Description of the drawings
Fig. 1 is more rotor plant protection drone people's fold mechanism overall structure figures (impaction state) of the present invention.
Fig. 2 is more rotor plant protection drone people's fold mechanism overall structure figures (free state) of the present invention.
Fig. 3 is more rotor plant protection drone people fold mechanism overall structure front views of the present invention.
Figure label explanation：
Support element 4-baffles of L between support element 3-carbon plates of R between 1-horn 2-carbon plate of connector
5-" comma " fastener 6-axis pin, 7-bayonet lock, 8-link bolts
9- blind recess 10- connecting plate 11- connecting plate notches
Specific implementation mode
The present invention will be described with reference to the accompanying drawings and examples.
Referring to Fig. 1 and Fig. 2, more rotor plant protection drone horn folding devices provided by the invention specifically include between carbon plate
Support element L3 between support element R2 and carbon plate, is bolted on upper and lower carbon plate, support element between horn connector 1 and carbon plate
Support element L3 is connected with link bolt 8 between R2 and carbon plate, then with nut check, and horn connector 1 can be revolved around link bolt 8
Turn, until horn connector 1 with support element L3 is bonded that (when fitting, horn is relative to level between support element R2 and carbon plate between carbon plate
Direction is in 3 ° of angles, as 3 ° of upper counterangles upwards).Carbon pipe horn is inserted into the open pore of horn connector 1, with two lag bolts
Open slot is fastened, realization is circumferentially positioned, with a stay bolt through horn connector 1 and carbon pipe horn, realizes axially position.Pin
Axis 6 and the eccentric circular hole of " comma " fastener 5 coordinate, and bayonet lock 7 passes through connecting plate notch 11 and axis pin 6 on horn connector 1
On threaded hole connection, and be in free state relative to horn connector 1.Rotation horn connector 1 is supported between carbon plate
Support element L3 is bonded between part R2 and carbon plate, while the head for making " comma " fastener 5 and the connecting plate 10 on horn connector 1
Curved end is in tangent state, and bayonet lock 7 is pressed into blind recess 4 and rotates " comma " fastener 5 to parallel with carbon pipe horn
Position, make horn connector 1 and " comma " fastener 5, baffle 4 and bayonet lock 7 be closely joined together to realize horn
It is accurately positioned.
Referring to Fig. 3, " comma " fastener 5 is rotated clockwise, while bayonet lock 7 is pressed downward into blind recess 4, utilize bias
The eccentric nature of wheel realizes the self-locking property of the design folding device.
Claims (2)
1. a kind of multi-rotor unmanned aerial vehicle horn folding device, including horn connector (1), it is used for and carbon plate on unmanned plane and lower carbon
Support element and fastener (5) between two carbon plates that plate is fixedly connected, which is characterized in that the lower end of horn connector (1) front with
The lower hinge of support element between two carbon plates offers eccentric orfice in the front end of fastener (5)；The support element between two carbon plates
Top is fixed with baffle (4), offers blind recess (9) in the centre of baffle (4), the upper end in horn connector (1) front
It is fixed with connecting plate (10), the connecting plate notch (11) for allowing bayonet lock (7) to pass through, axis pin are offered on connecting plate (10)
(6) it is matched with the eccentric circular hole of fastener (5)；Bayonet lock (7) is half tooth bolt, passes through the connection on horn connector (1)
Board slot mouth (11) is connect with the internal thread hole on axis pin (6), and is in free state relative to horn connector (1)；When fastening,
Rotation horn connector (1) between two carbon plates support element be bonded, bayonet lock (7) is fallen into blind recess (9), and by fastener
(5) rear end rotates to the position parallel with horn connector (1) so that bayonet lock (7) under the barrier effect of baffle (4) with machine
Arm connector (1), fastener (5) closely connect, and the surface that connecting plate (10) is in contact with fastener (5) front end is to match with it
The cambered surface of conjunction, fastener (5) can be rotated in a manner of inscribe between 0 °~90 ° in the cambered surface of connecting plate (10).
2. multi-rotor unmanned aerial vehicle horn folding device according to claim 1, which is characterized in that the fastener (5)
Section be comma shape, front end be it is cylindric.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610718383.5A CN106240794B (en) | 2016-08-24 | 2016-08-24 | A kind of multi-rotor unmanned aerial vehicle horn folding device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610718383.5A CN106240794B (en) | 2016-08-24 | 2016-08-24 | A kind of multi-rotor unmanned aerial vehicle horn folding device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106240794A CN106240794A (en) | 2016-12-21 |
| CN106240794B true CN106240794B (en) | 2018-07-27 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610718383.5A Active CN106240794B (en) | 2016-08-24 | 2016-08-24 | A kind of multi-rotor unmanned aerial vehicle horn folding device |
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| Country | Link |
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| CN (1) | CN106240794B (en) |
Families Citing this family (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108248818A (en) * | 2016-12-28 | 2018-07-06 | 北京卓翼智能科技有限公司 | For folding the rotation table device and its method for folding that are tethered at unmanned plane horn |
| CN106828870B (en) * | 2017-03-29 | 2023-12-12 | 河北全疆科技有限公司 | Multi-rotor unmanned aerial vehicle |
| CN107097931A (en) * | 2017-05-11 | 2017-08-29 | 珠海天晴航空航天科技有限公司 | A kind of unmanned plane horn folding device |
| CN107933876B (en) * | 2017-11-30 | 2020-01-24 | 深圳市华业航空科技有限公司 | Unmanned aerial vehicle arm folding structure with movable ejector pin and folding method thereof |
| CN108791806A (en) * | 2018-06-22 | 2018-11-13 | 北京中飞东方航空科技有限公司 | A kind of unmanned plane folding horn connector |
| CN109383741A (en) * | 2018-11-15 | 2019-02-26 | 航天神舟飞行器有限公司 | A kind of multi-rotor unmanned aerial vehicle cantilever fast folding retaining mechanism |
| CN109703733B (en) * | 2018-12-04 | 2023-12-29 | 深圳市科卫泰实业发展有限公司 | Quick folding device of horn of spacing in area |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4914783A (en) * | 1988-12-05 | 1990-04-10 | The Hartwell Corporation | Sliding hinge with locking |
| CN204323682U (en) * | 2014-12-03 | 2015-05-13 | 黄彰标 | A kind of collapsible multiaxis plant protection aircraft |
| CN205150239U (en) * | 2015-10-16 | 2016-04-13 | 零度智控（北京）智能科技有限公司 | Horn folding device and aircraft |
| CN205221093U (en) * | 2015-12-08 | 2016-05-11 | 国网山东省电力公司莱芜供电公司 | Many rotors horn folding mechanism |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH04123588A (en) * | 1990-09-14 | 1992-04-23 | Fujitsu Ltd | Structure of arm with single degree of freedom |
-
2016
- 2016-08-24 CN CN201610718383.5A patent/CN106240794B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4914783A (en) * | 1988-12-05 | 1990-04-10 | The Hartwell Corporation | Sliding hinge with locking |
| CN204323682U (en) * | 2014-12-03 | 2015-05-13 | 黄彰标 | A kind of collapsible multiaxis plant protection aircraft |
| CN205150239U (en) * | 2015-10-16 | 2016-04-13 | 零度智控（北京）智能科技有限公司 | Horn folding device and aircraft |
| CN205221093U (en) * | 2015-12-08 | 2016-05-11 | 国网山东省电力公司莱芜供电公司 | Many rotors horn folding mechanism |
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| Publication number | Publication date |
|---|---|
| CN106240794A (en) | 2016-12-21 |
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Effective date of registration: 20220622 Address after: 053200 yard, No. 2669, Jixin West Road, Jizhou District, Hengshui City, Hebei Province Patentee after: Hebei Quanjiang Technology Co.,Ltd. Address before: No.2669, Jixin West Road, Jizhou District, Hengshui City, Hebei Province 053200 Patentee before: TAIHUA WEIYE TECHNOLOGY Co.,Ltd. |