CN108248840A - A kind of detachable rotor wing unmanned aerial vehicle - Google Patents
A kind of detachable rotor wing unmanned aerial vehicle Download PDFInfo
- Publication number
- CN108248840A CN108248840A CN201711424384.XA CN201711424384A CN108248840A CN 108248840 A CN108248840 A CN 108248840A CN 201711424384 A CN201711424384 A CN 201711424384A CN 108248840 A CN108248840 A CN 108248840A
- Authority
- CN
- China
- Prior art keywords
- cable connector
- rotor
- pin
- plugs
- fuselage
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
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
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01R—ELECTRICALLY-CONDUCTIVE CONNECTIONS; STRUCTURAL ASSOCIATIONS OF A PLURALITY OF MUTUALLY-INSULATED ELECTRICAL CONNECTING ELEMENTS; COUPLING DEVICES; CURRENT COLLECTORS
- H01R13/00—Details of coupling devices of the kinds covered by groups H01R12/70 or H01R24/00 - H01R33/00
- H01R13/62—Means for facilitating engagement or disengagement of coupling parts or for holding them in engagement
- H01R13/629—Additional means for facilitating engagement or disengagement of coupling parts, e.g. aligning or guiding means, levers, gas pressure electrical locking indicators, manufacturing tolerances
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01R—ELECTRICALLY-CONDUCTIVE CONNECTIONS; STRUCTURAL ASSOCIATIONS OF A PLURALITY OF MUTUALLY-INSULATED ELECTRICAL CONNECTING ELEMENTS; COUPLING DEVICES; CURRENT COLLECTORS
- H01R13/00—Details of coupling devices of the kinds covered by groups H01R12/70 or H01R24/00 - H01R33/00
- H01R13/64—Means for preventing incorrect coupling
- H01R13/642—Means for preventing incorrect coupling by position or shape of contact members
Abstract
The present invention provides a kind of detachable rotor wing unmanned aerial vehicle, including fuselage, rotor and rotor connecting rod, rotor connecting rod two end is equipped with cable connector, pin plugs are equipped in cable connector, the pin plugs at both ends are mounted on cable connector seat by the connection in rotor connecting rod on fuselage and rotor, be equipped in cable connector seat and the matched pin receptacles of pin plugs, the cable connector of rotor connecting rod one end is spirally connected with fuselage, and the cable connector of the rotor connecting rod other end is spirally connected with rotor.The present invention at rotor both ends by installing cable connector, pin plugs are equipped in cable connector, and pin receptacles are installed on fuselage and rotor, rotor connecting rod and fuselage, rotor convenient disassembly, and can whole wiring directly can be completed by pin plugs and pin receptacles grafting in circuit, and wiring is simply easy.
Description
Technical field
The present invention relates to unmanned air vehicle technique field more particularly to a kind of detachable rotor wing unmanned aerial vehicles.
Background technology
In small-sized depopulated helicopter civil field, unmanned plane is a kind of most commonly seen airborne application, the prior art
In unmanned plane it is big in appearance and size, but the effective volume occupied is small, and big quantity space is occupied when packed and transported,
Cause unnecessary waste, and during by unmanned plane disassembled for transport, since unmanned plane internal wiring is more, layman can not be complete
Into wiring, if wiring error is also easy to cause unmanned plane circuit burnout.
Invention content
The technical issues of in the presence of the present invention mainly solution prior art, so as to provide a kind of convenient disassembly, it is conducive to
Transport, and wiring is easy, will not cause can not wiring or wiring error detachable rotor wing unmanned aerial vehicle.
The above-mentioned technical problem of the present invention is mainly what is be addressed by following technical proposals：
A kind of detachable rotor wing unmanned aerial vehicle provided by the invention, including fuselage, rotor and rotor connecting rod, in the fuselage
Control device is installed and for electric installation, sensor and motor is installed in the rotor, the rotor connecting rod two end is set respectively
There are the first cable connector and the second cable connector, the first pin plugs, second cable are equipped in first cable connector
Pass through the connection in rotor connecting rod, institute equipped with the second pin plugs, the first pin plugs and the second pin plugs in connector
It states and the first cable connector seat and the second cable connector seat is separately installed on fuselage and rotor, set in the first cable connector seat
Have with matched first pin receptacles of first pin plugs, be equipped in the second cable connector seat and second needle
Matched second pin receptacles of n pin package n, first pin receptacles are electric respectively with the control device in fuselage and for electric installation
Connection, second pin receptacles are electrically connected with the sensor in rotor and motor, first cable connector and fuselage
It is spirally connected, second cable connector is spirally connected with rotor.
Further, the rotor connecting rod further includes metal tube, and the first cable connector and the second cable connector are mounted on gold
Belong to the both ends of pipe, and the first cable connector and the second cable connector are also connected by cable, the cable is threaded through the metal
Inside pipe.
Further, it is arranged on first cable connector and the second cable connector there are one withholding nut, described the
One pin receptacles and the second pin receptacles outer ring are threaded, described to withhold nut and thread fitting.
Further, first pin receptacles and the second pin receptacles outer ring top offer notch, first needle
N pin package n and the second pin plugs top are equipped with the protrusion with the notches fit.
Further, the locating plate parallel with stitch, institute are additionally provided in first pin plugs and the second pin plugs
It states and is offered in the first pin receptacles and the second pin receptacles and the matched locating slot of the locating plate.
The beneficial effects of the present invention are：By installing first, second cable connector at rotor both ends, set in cable connector
There are pin plugs, and first, second pin receptacles are installed respectively on fuselage and rotor, rotor connecting rod and fuselage, rotor dismounting
It is convenient, and can whole wiring directly can be completed by pin plugs and pin receptacles grafting in circuit, and wiring is simply easy.
Description of the drawings
In order to illustrate more clearly about the embodiment of the present invention or technical scheme of the prior art, to embodiment or will show below
There is attached drawing needed in technology description to be briefly described, it should be apparent that, the accompanying drawings in the following description is only this
Some embodiments of invention, for those of ordinary skill in the art, without creative efforts, can be with
Other attached drawings are obtained according to these attached drawings.
Fig. 1 is the structure diagram of the detachable rotor wing unmanned aerial vehicle of the present invention；
Fig. 2 is the partial enlarged view at I in Fig. 1；
Fig. 3 is the partial enlarged view at II in Fig. 1；
Fig. 4 is the structure diagram of the first pin receptacles in embodiment one；
Fig. 5 is the structure diagram of the first pin plugs in embodiment one；
Fig. 6 is the structure diagram of the first pin receptacles in embodiment two；
Fig. 7 is the structure diagram of the first pin plugs in embodiment two.
Specific embodiment
The preferred embodiment of the present invention is described in detail below in conjunction with the accompanying drawings, so that advantages and features of the invention energy
It is easier to be readily appreciated by one skilled in the art, so as to make a clearer definition of the protection scope of the present invention.
Embodiment one
Refering to shown in Fig. 1 to Fig. 3, a kind of detachable rotor wing unmanned aerial vehicle of the invention, including fuselage 1, rotor 2 and rotor
Connecting rod 3 is equipped with control device in fuselage 1 and for electric installation, and sensor and motor, 3 both ends of rotor connecting rod are equipped in rotor 2
The first cable connector 31 and the second cable connector 32 are respectively equipped with, the first pin plugs 33 are equipped in the first cable connector 31, the
The second pin plugs 34 are equipped in two cable connectors 32, the first pin plugs 33 and the second pin plugs 34 pass through rotor connecting rod 3
In connection, be separately installed with the first cable connector seat 11 and the second cable connector seat 12 on fuselage 1 and rotor 2, first
Be equipped in cable connector seat 11 with 33 matched first pin receptacles 13 of the first pin plugs, set in the second cable connector seat 12
Have with 34 matched second pin receptacles 14 of the second pin plugs, the first pin receptacles 13 and the control device in fuselage 1 and
It is electrically connected for electric installation, the second pin receptacles 14 are electrically connected with the sensor in rotor 1 and motor, and the first cable connects
First 31 are spirally connected with fuselage 1, and the second cable connector 32 is spirally connected with rotor 2.In the present embodiment, the first cable connector 31 and the second line
32 structure of cable joint is identical, and the first pin plugs 33 are identical with 34 structure of the second pin plugs, the first cable connector seat 11 and
Two cable connector seats, 12 structure is identical, and the first pin receptacles 13 are identical with 14 structure of the second pin receptacles.
By installing cable connector at 2 both ends of rotor, pin plugs are equipped with, and on fuselage 1 and rotor 2 in cable connector
Pin receptacles, rotor connecting rod 3 and fuselage 1,2 convenient disassembly of rotor are installed respectively, and circuit can directly pass through pin plugs
Whole wiring can be completed with pin receptacles grafting, wiring is simply easy.
In the present embodiment, rotor connecting rod 3 further includes metal tube 35, and the first cable connector 31 and the second cable connector 32 are pacified
Mounted in the both ends of metal tube 35, and the first cable connector 31 and the second cable connector 32 are also connected by cable 3, and cable 3 is worn
Inside metal tube 35.Metal tube 35 can use aluminium-alloy pipe, and light-weight, intensity is big.Cable 36 is located in metal tube, effectively
The safety for protecting cable.
Preferably, nut 37 is withheld there are one being arranged on each first cable connector, 31 and second cable connector 32, the
One pin receptacles 13 and 14 outer ring of the second pin receptacles are threaded 15, withhold nut 37 and coordinate with screw thread 15.By withholding
Nut 37 coordinates with screw thread 15, on the one hand compresses pin plugs 32 and pin receptacles 12, on the other hand connects fuselage 1,2 and of rotor
Rotor connecting rod 3.
Refering to shown in Fig. 4, Fig. 5, connector mistake, and for positioning in order to prevent, the first pin receptacles 13 and the second needle
14 outer ring top of foot socket offers notch 131, and the first pin plugs 33 and 34 top of the second pin plugs are equipped with and notch 131
The protrusion 331 of cooperation.
Embodiment two
Refering to shown in Fig. 6, Fig. 7, the difference between this embodiment and the first embodiment lies in, the first pin plugs 33 and the second stitch
The locating plate 333 parallel with stitch 332 is additionally provided in plug 34, is opened up in the first pin receptacles 13 and the second pin receptacles 14
Have and 333 matched locating slot 132 of locating plate.
More than, specific embodiment only of the invention, but protection scope of the present invention is not limited thereto, it is any without
The change or replacement that creative work is expected are crossed, should be covered by the protection scope of the present invention.Therefore, protection of the invention
Range should be determined by the scope of protection defined in the claims.
Claims (5)
1. a kind of detachable rotor wing unmanned aerial vehicle including fuselage (1), rotor (2) and rotor connecting rod (3), is pacified in the fuselage (1)
Equipped with control device and for electric installation, sensor and motor are installed in the rotor (2), it is characterised in that：The rotor connects
Bar (3) both ends are respectively equipped with the first cable connector (31) and the second cable connector (32), are set in first cable connector (31)
There are the first pin plugs (33), the second pin plugs (34), the first pin plugs are equipped in second cable connector (32)
(33) and the second pin plugs (34) are by the connection in rotor connecting rod (3), on the fuselage (1) and rotor (2) respectively
First cable connector seat (11) and the second cable connector seat (12) are installed, are equipped with and institute in the first cable connector seat (11)
State matched first pin receptacles (13) of the first pin plugs (33), be equipped in the second cable connector seat (12) with it is described
Matched second pin receptacles (14) of second pin plugs (34), first pin receptacles (13) and the control in fuselage (1)
Device processed and confession electric installation are electrically connected, and second pin receptacles (14) connect respectively with the sensor in rotor and motor electricity
It connects, first cable connector (31) is spirally connected with fuselage (1), and second cable connector (32) is spirally connected with rotor (2).
2. detachable rotor wing unmanned aerial vehicle as described in claim 1, it is characterised in that：The rotor connecting rod (3) further includes gold
Belong to pipe (35), the first cable connector (31) and the second cable connector (32) are mounted on the both ends of metal tube (35), and the first cable
Connector (31) and the second cable connector (32) are also connected by cable (36), and the cable (36) is threaded through the metal tube (35)
It is internal.
3. detachable rotor wing unmanned aerial vehicle as claimed in claim 2, it is characterised in that：First cable connector (31) and
Nut (37), first pin receptacles (13) and the second pin receptacles are withheld there are one being arranged on two cable connectors (32)
(14) outer ring is threaded (15), and the nut (37) of withholding coordinates with screw thread (15).
4. detachable rotor wing unmanned aerial vehicle as claimed in claim 3, it is characterised in that：First pin receptacles (13) and
Two pin receptacles (14) outer ring top offers notch (131), first pin plugs (33) and the second pin plugs (34)
Top is equipped with the protrusion (331) coordinated with the notch (131).
5. detachable rotor wing unmanned aerial vehicle as claimed in claim 3, it is characterised in that：First pin plugs (33) and
The locating plate (333) parallel with stitch (332), first pin receptacles (13) and second are additionally provided in two pin plugs (34)
It is offered and the locating plate (333) matched locating slot (132) in pin receptacles (14).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711424384.XA CN108248840A (en) | 2017-12-25 | 2017-12-25 | A kind of detachable rotor wing unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711424384.XA CN108248840A (en) | 2017-12-25 | 2017-12-25 | A kind of detachable rotor wing unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108248840A true CN108248840A (en) | 2018-07-06 |
Family
ID=62722886
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711424384.XA Pending CN108248840A (en) | 2017-12-25 | 2017-12-25 | A kind of detachable rotor wing unmanned aerial vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108248840A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111086635A (en) * | 2019-12-30 | 2020-05-01 | 厦门致睿智控地信科技有限公司 | Multi-rotor unmanned aerial vehicle is with quick-witted arm can be dismantled to high stable form |
-
2017
- 2017-12-25 CN CN201711424384.XA patent/CN108248840A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111086635A (en) * | 2019-12-30 | 2020-05-01 | 厦门致睿智控地信科技有限公司 | Multi-rotor unmanned aerial vehicle is with quick-witted arm can be dismantled to high stable form |
| CN111086635B (en) * | 2019-12-30 | 2021-05-14 | 厦门致睿智控地信科技有限公司 | Multi-rotor unmanned aerial vehicle is with quick-witted arm can be dismantled to high stable form |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN104218405B (en) | A kind of spaceborne integrated miniaturization composite connector | |
| CN204998764U (en) | Detachable rotor unmanned aerial vehicle | |
| CN106477039A (en) | A kind of rotor wing unmanned aerial vehicle | |
| CN108248840A (en) | A kind of detachable rotor wing unmanned aerial vehicle | |
| CN204802078U (en) | Agricultural unmanned aerial vehicle | |
| AU2019200224B2 (en) | A cable head for a ring main unit and a ring main unit | |
| CN206480888U (en) | Power data connecting line for unmanned plane | |
| CN102762064B (en) | Electronic control unit for electric riding vehicle | |
| CN206943790U (en) | The pump nozzle attachment structure of aircraft structure | |
| CN208027885U (en) | Transformer wire clamp with set tube positioning structure | |
| CN206059808U (en) | A kind of storehouse power supply electrical connector plug structure | |
| CN206340747U (en) | A kind of mounting structure of 1394 type electric power connector | |
| CN207485778U (en) | A kind of Split type electric pressure difference signal device structure | |
| CN207338709U (en) | A kind of power input socket | |
| CN202940343U (en) | Circuit three-connection wiring fitting with grounding ring | |
| CN205543189U (en) | Direction adjustable directional aerial | |
| CN205082105U (en) | Detachable FTU rack of aviation cable socket tray | |
| CN205159642U (en) | Novel plug -in components are pulled out in pine aviation of preventing turning over | |
| CN209313135U (en) | A kind of multicore anti-explosion plug | |
| CN103985490A (en) | Socket type arrester | |
| CN208522106U (en) | A kind of anti-disconnection cable connecting arrangement | |
| CN208570968U (en) | Roadbed type ground terminal system | |
| CN108306092A (en) | Unmanned plane GNSS aviation miniature antenna mounting devices | |
| CN206494110U (en) | A kind of new fixed-wing unmanned plane | |
| CN102983423B (en) | Circuit three-connecting wire hardware fitting with ground ring |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20180706 |