CN109229350A - A kind of multi-rotor unmanned aerial vehicle horn quick-disassembly structure - Google Patents
A kind of multi-rotor unmanned aerial vehicle horn quick-disassembly structure Download PDFInfo
- Publication number
- CN109229350A CN109229350A CN201710562228.3A CN201710562228A CN109229350A CN 109229350 A CN109229350 A CN 109229350A CN 201710562228 A CN201710562228 A CN 201710562228A CN 109229350 A CN109229350 A CN 109229350A
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- horn
- fulcrum
- aerial vehicle
- unmanned aerial
- arm
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- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims abstract description 4
- 229910052799 carbon Inorganic materials 0.000 claims abstract description 4
- 239000011324 bead Substances 0.000 claims description 7
- 230000014759 maintenance of location Effects 0.000 claims description 7
- 229910000838 Al alloy Inorganic materials 0.000 claims description 3
- 239000000956 alloy Substances 0.000 claims description 2
- 238000009434 installation Methods 0.000 abstract description 8
- 238000012423 maintenance Methods 0.000 abstract 1
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 2
- 230000005611 electricity Effects 0.000 description 2
- 235000008331 Pinus X rigitaeda Nutrition 0.000 description 1
- 235000011613 Pinus brutia Nutrition 0.000 description 1
- 241000018646 Pinus brutia Species 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000002146 bilateral effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005194 fractionation Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000003032 molecular docking Methods 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
- 230000004584 weight gain Effects 0.000 description 1
- 235000019786 weight gain Nutrition 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
-
- 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
- B64C1/068—Fuselage sections
- B64C1/069—Joining arrangements therefor
-
- 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)
- Toys (AREA)
Abstract
本发明公开了一种多旋翼无人机用机臂快拆结构，包括锁扣、锁扣导轨、支点A、机身插座板、支点B、机臂内衬、机臂插座板、机臂、机臂限位，套筒；所述锁扣、锁扣导轨、支点A、机身插座板、支点B安装在机身中心板上，机身中心板设有安装支点A、支点B的螺丝孔位；所述机臂内衬、机臂插座板、机臂限位、套筒安装在机臂上；所述机臂为25mm直径碳管，与机臂内衬固定连接；所述机臂上套有机臂限位，机臂限位与支点B通过套筒连接。该机臂快拆结构具有整体式快拆能力，极大地缩小了多旋翼无人机所需的收纳容积，方便携带运输，同时保证展开速度，不需要使用工具协助安装，结构简单，维护方便。
The invention discloses a quick-release structure for an arm of a multi-rotor unmanned aerial vehicle, comprising a lock, a lock guide, a fulcrum A, a fuselage socket plate, a fulcrum B, an arm lining, an arm socket plate, an arm, Arm limit, sleeve; the lock, lock guide, fulcrum A, fuselage socket board, fulcrum B are installed on the center plate of the fuselage, and the center plate of the fuselage is provided with screw holes for mounting fulcrum A and fulcrum B the arm lining, the arm socket plate, the arm limit, and the sleeve are installed on the arm; the arm is a 25mm diameter carbon tube, which is fixedly connected to the arm lining; The machine arm limit is set, and the machine arm limit is connected with the fulcrum B through the sleeve. The quick-release structure of the arm has an integral quick-release capability, which greatly reduces the storage volume required by the multi-rotor UAV, which is convenient for carrying and transportation, and at the same time ensures the deployment speed. It does not require the use of tools to assist in installation, and has a simple structure and convenient maintenance.
Description
Technical field
The present invention relates to multi-rotor unmanned aerial vehicle field more particularly to a kind of multi-rotor unmanned aerial vehicle horn quick-disassembly structures.
Background technique
Common flight device is divided into fixed-wing, helicopter and more rotors (quadrotor mainstream the most), in recent years in, because excellent
Handling, more rotors rapidly become the nova taken photo by plane with model plane Sports Field.Currently, more rotors have become microminiature without
Man-machine or model plane mainstreams.Since unmanned plane transition needs compact car to transport, for convenience of transporting, miniature nothing of the wheelbase in 1m or so
The man-machine main trend as current industry.In existing miniature multi-rotor unmanned aerial vehicle, when its wheelbase reaches 1m or so, for convenience
Receiving, collapsible horn is often the first choice of this kind of type, and there is also parts to consider directly to consolidate horn and rack for protection
It is fixed, it is non-dismountable, and the containing box of these types is larger, is unable to store in the lesser compact car of part boot.
For existing miniature multi-rotor unmanned aerial vehicle, the whole flight control system component of the work flight control of source blade is provided
Size is little, even if the size including power battery will not still occupy too many volume, and its lift space is then entire more rotations
The component most to take up space on wing unmanned plane, for wheelbase is in the multi-rotor unmanned aerial vehicle of 1m or so, horn is fixed on nothing in rack
A large amount of storage spaces will be occupied by doubting, and to avoid influence of the horn vertical vibration to fold mechanism, collapsible horn is often using vertical
To the form of folding, and this folding mode is due to horn length, and foot prop height will have to increase, this makes fuselage
Certain space is wasted in height；It needs to reduce as far as possible not photograph foot prop when guaranteeing camera shooting for aerial survey field
Height of the camera in unmanned plane, to guarantee that camera is sufficiently low after the increasing of foot prop, the mounting rack of fixed camera also needs to lengthen,
This will cause unnecessary weight gain.Therefore, it is necessary to a kind of structure, guarantee that horn is not take up storage space in all directions, together
When, this structure cannot influence the convenience that unmanned plane uses.
Summary of the invention
In view of this, present invention design completes a kind of multi-rotor unmanned aerial vehicle horn quick-disassembly structure.
The present invention is solved the above problems by following technological means:
A kind of multi-rotor unmanned aerial vehicle horn quick-disassembly structure, including support plate, fulcrum, fuselage socket, fulcrum B, horn,
Horn limit, sleeve；The A, fulcrum B are connect by screw with support plate；The horn sequentially passes through fulcrum disposed in parallel
A, the circular hole of fulcrum B, and the inner surface of fuselage socket is withstood on, fuselage socket is connect by screw with fulcrum A；The horn
On be cased with horn limit, with fulcrum B by sleeve connection, fulcrum B is connect with bush whorl for horn limit.
Further, the sleeve is equipped with locking buckle, and locking buckle is equipped with oblique angle, and adjacent oblique angle forms card slot；Branch
One end of fagging connecting fulcrum B is equipped with lock guide rail, and lock guide rail is flexibly connected with lock, and the hook that lock is equipped with is stuck in card
In slot.
Further, the horn limit is equipped with retention bead, and fulcrum B is recessed equipped with being cooperatively connected with retention bead
Slot.
Further, the horn is 25mm diameter carbon pipe, and horn is fixedly connected with horn liner.
Further, for the lock with lock guide rail by 4mm compressed spring interval, fulcrum A, fulcrum B are aluminium alloy material
Material, is connect by M2.5 screw with fuselage central plate.
Further, the fuselage socket is connect by M2 screw with fulcrum A, the 4mm diametric hole peace of fuselage socket
XT60 plug is filled, 1mm diametric hole installs XH2.54 socket.
Further, the horn liner is connect by M2 screw with horn socket, the 4mm diametric hole of horn socket
XT60 plug is installed, 1mm diametric hole installs XH2.54 socket.
A kind of multi-rotor unmanned aerial vehicle of the invention has the advantages that the quick-disassembly structure has with horn quick-disassembly structure
Monoblock type Quick Release ability, storage volume needed for greatly reducing multi-rotor unmanned aerial vehicle, is convenient for carrying transport, while guaranteeing to be unfolded
Speed does not need to assist to install using tool, and structure is simple, easy to maintain.
Detailed description of the invention
In order to illustrate more clearly of technical solution of the present invention, attached drawing needed in embodiment will be made below
Simply introduce, it should be apparent that, the accompanying drawings in the following description is only some embodiments of the present invention, general for this field
For logical technical staff, without creative efforts, it is also possible to obtain other drawings based on these drawings.
Fig. 1 is a kind of multi-rotor unmanned aerial vehicle horn quick-disassembly structure overall structure diagram of the present invention；
Fig. 2 is a kind of multi-rotor unmanned aerial vehicle horn quick-disassembly structure fractionation structural representation；
Fig. 3 is a kind of multi-rotor unmanned aerial vehicle horn quick-disassembly structure fulcrum A main view of the present invention；
Fig. 4 is a kind of multi-rotor unmanned aerial vehicle horn quick-disassembly structure fuselage socket top view of the present invention；
Fig. 5 is a kind of multi-rotor unmanned aerial vehicle horn quick-disassembly structure fulcrum B main view of the present invention；
Fig. 6 is a kind of multi-rotor unmanned aerial vehicle horn quick-disassembly structure lock guide rail top view of the present invention；
Fig. 7 is a kind of multi-rotor unmanned aerial vehicle horn quick-disassembly structure lock main view of the present invention；
Fig. 8 is a kind of multi-rotor unmanned aerial vehicle horn quick-disassembly structure horn liner main view of the present invention；
Fig. 9 is a kind of multi-rotor unmanned aerial vehicle horn quick-disassembly structure horn socket top view of the present invention；
Figure 10 is a kind of multi-rotor unmanned aerial vehicle horn quick-disassembly structure horn limit main view of the present invention；
Figure 11 is a kind of multi-rotor unmanned aerial vehicle horn quick-disassembly structure sleeve main view of the present invention；
In figure: 1. locks；11. hook；2. support plate；21. latching guide rail；3. fulcrum A；4. fuselage socket；5. fulcrum
B；51. groove；6. horn liner；7. horn socket；8. horn；9. spacing collar；91. retention bead；10. sleeve；101. anti-
Pine buckle；102. oblique angle.
Specific embodiment
The present invention is described in detail below with reference to the accompanying drawings and embodiments.
Embodiment
As depicted in figs. 1 and 2, a kind of multi-rotor unmanned aerial vehicle is divided into two parts with horn quick-disassembly structure, wherein lock 1, branch
Fagging 2, lock guide rail 21, fulcrum A3, fuselage socket 4, fulcrum B5 are mounted on fuselage central plate, and fuselage central plate needs basis
The installation hole location design corresponding position of fulcrum A3, fulcrum B5, fulcrum A3, fulcrum B5 are successively arranged the coaxial circular hole of center line, and
Pass through screw connection with support plate 2；Horn liner 6, horn socket 7, horn limit 9, sleeve 10 are mounted on horn 8, machine
Arm 8 need to use 25mm diameter carbon pipe, need to be according to the installation hole location reserved location of horn liner 6, and fix and connect with horn liner 6
It connects, horn limit 9 is cased on horn 8, horn limits 9 and fulcrum B5 and connects by sleeve 10；The fulcrum A3, fulcrum B5, machine
Arm liner 6, horn 8, horn limit 9,10 center line of sleeve are coaxial；The horn 8 sequentially passes through fulcrum A3 disposed in parallel, branch
The circular hole of point B5, and the inner surface of fuselage socket 4 is withstood on, fuselage socket 4 is connect by screw with fulcrum A3；The horn
Limit 9 is equipped with retention bead 91, and fulcrum B5 is equipped with the groove 51 being cooperatively connected with retention bead 91.
As shown in Figure 3 and Figure 5, fulcrum A3, fulcrum B5 are set there are four screw hole location, using M2.5 screw and fuselage central plate
It is connected；As shown in Figure 6 and Figure 7,1 top of lock is equipped with spanner, and 4mm is installed while installing fulcrum A3, fulcrum B5 and compresses bullet
Spring then uses 4mm compressed spring interval between lock 1 and lock guide rail 21, is flexibly connected；Fulcrum B5 passes through screw thread and sleeve 10
Connection, sleeve 10 are equipped with locking buckle 101, and locking buckle 101 is equipped with oblique angle 102, and adjacent oblique angle 102 forms card slot, lock
Button hook 11 is stuck in card slot.
As shown in figure 4, symmetrical four diameters in four angles of fuselage socket 4 be 2.1mm hole, with M2 screw by its
It is connect with fulcrum A3, two 4mm diametric holes of fuselage socket 4 are distributed in symmetry axis two sides up and down, install XT60 plug, left and right
The symmetrical 6 1mm diametric holes of 6mm are spaced, XH2.54 socket is installed.
As shown in figure 9,7 central axes of horn socket bilateral symmetry is distributed the hole that two diameters are 2.1mm, it will with M2 screw
It connect with horn liner 6, and two 4mm diametric holes of horn socket 7 are distributed in symmetry axis two sides up and down, and installation XT60 is inserted
Head installs XH2.54 socket every the symmetrical 6 1mm diametric holes of 6mm between left and right.
As shown in figs, 8 end of horn is equipped with symmetrical two counter sinks in front and back, by M3 countersunk head screw through pre-
Position box out for horn liner 6 and the limit fixation of horn 9, before fixing, as shown in figure 11, sleeve 10 need to first cover
On horn 8, horn 8 is inserted into fulcrum B5 when use, machine after the guide rail in horn limit 9 is aligned with slot reserved on fulcrum B5
Arm 8 can continue into, and horn 8 reaches limit simultaneously, and plug is completed at the same time connection, and sleeve 10 and fulcrum B5 are connected by screw thread
It connects, while sleeve 10 is tightened, lock 1 is automatic locking since spring acts on；When disassembly, push lock 1 away from limit, set
Cylinder 10 can rotate, and complete disassembly,
The present invention claims multi-rotor unmanned aerial vehicle frame structures to be at least bilayer, and motor, blade, electricity are adjusted, horn 8 is whole as one
Body dismounts together；Corresponding aluminium alloy aperture part is made, fulcrum A3, fulcrum B5 undertake while installing fulcrum as horn 8
Rack bulk strength and rigidity requirement to mitigate self weight, while ensuring 8 rigidity of horn, and fulcrum A3, fulcrum B5 are two o'clock form,
Guarantee a certain distance between two parts；Installation fuselage socket 4 is added on the part of frame central, is that one kind has
The positioning plate of Quick Release plug guarantees horn 8 while installation, and the electricity on horn 8 is adjusted complete with the relevant device in the rack of center
At docking；Limit part on horn 8 is horn limit 9, and is equipped with groove 91, guarantees that horn 8 accurately slides into installation site, machine
Body socket 4 can also be docked accurately, and horn 8 is threadedly coupled with rack using sleeve 10, and sleeve 10 can directly pass through artificial hand
The dynamic mode screwed is installed in place, while design has locking card 101 on sleeve 10, and horn sleeve is directly avoided to shake due to horn 8
Dynamic to lead to thread looseness, the subsidiary oblique angle 102 of locking buckle 101 guarantees only to need turnbarrel 10 when installation, be installed
Afterwards, lock 1 will be locked automatically, be stuck in the slot that adjacent oblique angle 102 is formed, and when disassembly, pushes latch 1 manually, while screwing set
Disassembly can be completed in cylinder 10.
Compared with existing power suit, the beneficial effects of the present invention are: the present invention provides one kind not to need additional means
Responsible horn quick-disassembly structure form, can be rapidly completed the expansion and storage of related multi-rotor unmanned aerial vehicle, reduce and mutually shut down
The storage space of type, meanwhile, structure and use are simple, easy to maintain.
Finally, it should be noted that the above embodiments are merely illustrative of the technical solutions of the present invention, rather than its limitations；Although
Present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that: it still may be used
To modify the technical solutions described in the foregoing embodiments or equivalent replacement of some of the technical features；
And these are modified or replaceed, technical solution of various embodiments of the present invention that it does not separate the essence of the corresponding technical solution spirit and
Range.
Claims (7)
1. a kind of multi-rotor unmanned aerial vehicle horn quick-disassembly structure, it is characterised in that: inserted including support plate (2), fulcrum A (3), fuselage
Seat board (4), fulcrum B (5), horn (8), horn limit (9), sleeve (10)；The A (3), fulcrum B (5) pass through screw and support
Plate (2) connection；The horn (8) sequentially passes through the circular hole of fulcrum A (3) disposed in parallel, fulcrum B (5), and withstands on fuselage socket
The inner surface of plate (4), fuselage socket (4) are connect by screw with fulcrum A (3)；Horn limit is cased on the horn (8)
(9), horn limit (9) is connect with fulcrum B (5) by sleeve (10), and fulcrum B (5) is threadedly coupled with sleeve (10).
2. a kind of multi-rotor unmanned aerial vehicle horn quick-disassembly structure according to claim 1, which is characterized in that the sleeve
(10) it is equipped with locking buckle (101), locking buckle (101) is equipped with oblique angle (102), and adjacent oblique angle (102) forms card slot；Support
One end of plate (2) connecting fulcrum B (5) is equipped with lock guide rail (21), and lock guide rail (21) is flexibly connected with lock (1), latches (1)
The hook (11) being equipped with is stuck in card slot.
3. a kind of multi-rotor unmanned aerial vehicle horn quick-disassembly structure according to claim 1, which is characterized in that the horn limit
Position (9) is equipped with retention bead (91), and fulcrum B (5) is equipped with the groove (51) being cooperatively connected with retention bead (91).
4. a kind of multi-rotor unmanned aerial vehicle horn quick-disassembly structure according to claim 1, which is characterized in that the horn
It (8) is 25mm diameter carbon pipe, horn (8) is fixedly connected with horn liner (6).
5. a kind of multi-rotor unmanned aerial vehicle horn quick-disassembly structure according to claim 1, which is characterized in that the lock
(1) with lock guide rail (21) by 4mm compressed spring interval, fulcrum A (3), fulcrum B (5) are aluminum alloy materials, pass through M2.5 spiral shell
Silk is connect with fuselage central plate.
6. a kind of multi-rotor unmanned aerial vehicle horn quick-disassembly structure according to claim 1, which is characterized in that the fuselage is inserted
Seat board (4) is connect by M2 screw with fulcrum A (3), and the 4mm diametric hole of fuselage socket (4) installs XT60 plug, 1mm diameter
Hole is installed by XH2.54 socket.
7. a kind of multi-rotor unmanned aerial vehicle horn quick-disassembly structure according to claim 4, which is characterized in that in the horn
Lining (6) is connect by M2 screw with horn socket (7), and the 4mm diametric hole of horn socket (7) installs XT60 plug, and 1mm is straight
Diameter hole is installed by XH2.54 socket.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710562228.3A CN109229350A (en) | 2017-07-11 | 2017-07-11 | A kind of multi-rotor unmanned aerial vehicle horn quick-disassembly structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710562228.3A CN109229350A (en) | 2017-07-11 | 2017-07-11 | A kind of multi-rotor unmanned aerial vehicle horn quick-disassembly structure |
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| Publication Number | Publication Date |
|---|---|
| CN109229350A true CN109229350A (en) | 2019-01-18 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710562228.3A Pending CN109229350A (en) | 2017-07-11 | 2017-07-11 | A kind of multi-rotor unmanned aerial vehicle horn quick-disassembly structure |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109606668A (en) * | 2019-01-28 | 2019-04-12 | 北京云影飞扬科技有限公司 | It is a kind of to dismount efficiently multi-rotor unmanned aerial vehicle horn structure |
| CN111038678A (en) * | 2019-12-31 | 2020-04-21 | 湖南优加特装智能科技有限公司 | Quick-release type connecting structure for connecting unmanned aerial vehicle arm and body |
| CN112027075A (en) * | 2020-09-15 | 2020-12-04 | 惠州众合航空科技有限公司 | Vertical lifting wing for unmanned aerial vehicle |
| CN112520011A (en) * | 2020-12-14 | 2021-03-19 | 中宇航通(北京)航空集团有限公司 | Quick-release quick-lock structure and method and unmanned aerial vehicle |
| CN115071950A (en) * | 2022-06-30 | 2022-09-20 | 新疆生产建设兵团第七师农业科学研究所 | A quick dismantling structure and using method of an arm of a plant protection drone |
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| CN207141380U (en) * | 2017-07-11 | 2018-03-27 | 上海伯镭智能科技有限公司 | A kind of multi-rotor unmanned aerial vehicle horn quick-disassembly structure |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109606668A (en) * | 2019-01-28 | 2019-04-12 | 北京云影飞扬科技有限公司 | It is a kind of to dismount efficiently multi-rotor unmanned aerial vehicle horn structure |
| CN111038678A (en) * | 2019-12-31 | 2020-04-21 | 湖南优加特装智能科技有限公司 | Quick-release type connecting structure for connecting unmanned aerial vehicle arm and body |
| CN112027075A (en) * | 2020-09-15 | 2020-12-04 | 惠州众合航空科技有限公司 | Vertical lifting wing for unmanned aerial vehicle |
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| CN112520011A (en) * | 2020-12-14 | 2021-03-19 | 中宇航通(北京)航空集团有限公司 | Quick-release quick-lock structure and method and unmanned aerial vehicle |
| CN115071950A (en) * | 2022-06-30 | 2022-09-20 | 新疆生产建设兵团第七师农业科学研究所 | A quick dismantling structure and using method of an arm of a plant protection drone |
| CN115071950B (en) * | 2022-06-30 | 2024-12-20 | 新疆生产建设兵团第七师农业科学研究所 | A quick-detachable arm structure and use method of a plant protection UAV |
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Application publication date: 20190118 |
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