CN206813315U - A kind of four rotor wing unmanned aerial vehicle aircraft - Google Patents
A kind of four rotor wing unmanned aerial vehicle aircraft Download PDFInfo
- Publication number
- CN206813315U CN206813315U CN201720660199.XU CN201720660199U CN206813315U CN 206813315 U CN206813315 U CN 206813315U CN 201720660199 U CN201720660199 U CN 201720660199U CN 206813315 U CN206813315 U CN 206813315U
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- support arm
- rotor
- nacelle
- unmanned aerial
- wing unmanned
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Abstract
The utility model provides a kind of four rotor wing unmanned aerial vehicle aircraft, including mainframe, control box, rotor driver and nacelle radome fairing, control box is fixedly mounted on the top of mainframe, mainframe includes main backstop, support arm, load seat and undercarriage, main backstop is circular double-layer structure up and down, it is separated by 90 ° in circumference between upper and lower two layers and is provided with a support arm, totally 4 support arms, main backstop bottom is provided with load seat, main backstop periphery under each support arm is provided with a undercarriage, the outer end of each support arm is respectively connected with a rotor driver, rotor driver bottom is connected with nacelle radome fairing, the utility model is designed reasonably, it is easy to use, it is compact-sized, dismounting is simple, flight stability, reliability is high, easy care, there is application well just.
Description
Technical field
It the utility model is related to unmanned plane field, and in particular to a kind of four rotor wing unmanned aerial vehicle aircraft.
Background technology
At present payload is commonly for the relatively conventional achievement in research of traditional rotor wing unmanned aerial vehicle of electric screw paddle four
5kg is confined to, cruising time is 20min-30min or so.The research of international middle-size and small-size unmanned vehicle is not also big
This two broad aspect of load, long endurance obtains considerable progress.The more rotors of propeller type can be achieved to fly by changing motor speed
Row device aerial statue and Heading control, but this improves and electrical motor gearshift performance and motor speed is accurately controlled to a certain extent
The requirement of technology；Furthermore the pitch of propeller is usually changeless, compared to variablepiston control rotor system, its
Pneumatic efficiency shows slightly deficiency.Under the equal power output of engine, the take-off weight to increase aircraft is more for propeller type
Rotor wing unmanned aerial vehicle most straightforward approach is increase propeller size with changing pitch.Increase the load of propeller type multi-rotor unmanned aerial vehicle
Another feasible scheme of Beijing South Maxpower Technology Co. Ltd's power be increase propeller quantity, increase to 8,18 it is even more more, but this mode can greatly
Reduce reliability, maintainability and the cruise-ability of aircraft.Therefore, propeller is not suitable for the multi-rotor aerocraft of big load.
Four rotor wing unmanned aerial vehicles be one kind can electricity oil two it is dynamic, be capable of the multi-rotor unmanned aerial vehicle of VTOL.It passes through balance four
Lift caused by secondary rotor and torque realize sustained turn and accurate flying.And automatic control technology, computer technology, communication
The fast development of technology, composite technology is with constantly bringing forth new ideas so that the development space of four rotor wing unmanned aerial vehicles is broader.It
Total arrangement belongs to non co axial formula symmetrical flight device in form, and compared with conventional rotary aircraft, its structure is more compact, energy
It is enough to produce bigger lift, there is its unique advantage compared with other aircraft.
Utility model content
The purpose of this utility model is to solve above-mentioned deficiency, there is provided a kind of four rotor wing unmanned aerial vehicle aircraft.
The purpose of this utility model is achieved through the following technical solutions：
A kind of four rotor wing unmanned aerial vehicle aircraft, including mainframe, control box, rotor driver and nacelle radome fairing, control box
The top of mainframe is fixedly mounted on, mainframe includes main backstop, support arm, load seat and undercarriage, and main backstop is circle
Shape double-layer structure up and down, it is separated by 90 ° in the circumference between upper and lower two layers and is provided with a support arm, totally 4 support arms, main support
Frame bottom is provided with load seat, and the main backstop periphery under each support arm is provided with a undercarriage, each support
The outer end of arm is respectively connected with a rotor driver, and rotor driver bottom is connected with nacelle radome fairing.
Connected between support arm and nacelle radome fairing by nacelle fixed seat.
Rotor driver includes propeller hub, blade, oar folder and distance-variable rocker arm, and the periphery of propeller hub is evenly arranged with 3 oar folders, each
The outer end of individual oar folder is respectively connected with a blade, propeller hub bottom connection distance-variable rocker arm.
Nacelle radome fairing is internally provided with motor.
The utility model has following beneficial effect：
The utility model is designed reasonably, easy to use, simply, flight stability, reliability is high, Yi Wei for compact-sized, dismounting
Shield, there is application well just.
Brief description of the drawings
Fig. 1 is overall structure diagram of the present utility model；
Fig. 2 is rotor driver structure chart of the present utility model.
Embodiment
The utility model is further described below in conjunction with the accompanying drawings：
As shown in figure 1, a kind of four rotor wing unmanned aerial vehicle aircraft, including mainframe, control box 1, rotor driver 2 and nacelle are whole
Stream cover 8, control box 1 are fixedly mounted on the top of mainframe, and mainframe includes main backstop 3, support arm 4, load seat 5 and risen and fallen
Frame 6, main backstop 3 are circular double-layer structure up and down, and being separated by 90 ° in the circumference between upper and lower two layers is provided with a support arm 4,
Totally 4 support arms 4, the bottom of main backstop 3 are provided with load seat 5, and the periphery of main backstop 3 under each support arm 4 is respectively provided with
There is a undercarriage 6, the outer end of each support arm 4 is respectively connected with a rotor driver 2, and the bottom of rotor driver 2 is connected with short
Cabin radome fairing 8.
Connected between support arm 4 and nacelle radome fairing 8 by nacelle fixed seat 7.
Rotor driver 2 includes propeller hub 9, blade 10, oar folder 11 and distance-variable rocker arm 12, the periphery of propeller hub 9 and is evenly arranged with 3
Oar folder 11, the outer end of each oar folder 11 are respectively connected with a blade 10, the bottom of propeller hub 9 connection distance-variable rocker arm 12.
Nacelle radome fairing 8 is internally provided with motor.
Four nacelles provide support platform for fourth officer rotor, and four tops of frame are arranged in cruciform symmetry type.To the greatest extent may be used
It can reduce to close between rotor and ensure that the coordination of complete machine structure is compact on the basis of aerodynamic interference.Nacelle and mainframe are using only respectively
Meter is erected, is combined and is fastenedly connected with corresponding combining mechanism eventually through four primary load bearing bars.
Motor is individually fixed on main rotor side by motor cabinet, that is, realizes that driving in turn ensure that good radiating effect.
Motor regulates and controls rotating speed processed by electricity, and the little gear by connecting motor shaft drives and the affixed nylon gear wheel of rotor shaft, final to pass
It is handed to propeller hub and realizes gear.
Claims (4)
1. a kind of four rotor wing unmanned aerial vehicle aircraft, including mainframe, control box, rotor driver and nacelle radome fairing, its feature exist
In：Control box is fixedly mounted on the top of mainframe, and mainframe includes main backstop, support arm, load seat and undercarriage, main branch
Support is circular double-layer structure up and down, and being separated by 90 ° in the circumference between upper and lower two layers is provided with a support arm, totally 4 supports
Arm, main backstop bottom are provided with load seat, and the main backstop periphery under each support arm is provided with a undercarriage, often
The outer end of one support arm is respectively connected with a rotor driver, and rotor driver bottom is connected with nacelle radome fairing.
A kind of 2. four rotor wing unmanned aerial vehicles aircraft according to claim 1, it is characterised in that：Described support arm and nacelle
Connected between radome fairing by nacelle fixed seat.
A kind of 3. four rotor wing unmanned aerial vehicles aircraft according to claim 1, it is characterised in that：Described rotor driver includes
Propeller hub, blade, oar folder and distance-variable rocker arm, the periphery of propeller hub are evenly arranged with 3 oar folders, and the outer end of each oar folder is respectively connected with
One blade, propeller hub bottom connection distance-variable rocker arm.
A kind of 4. four rotor wing unmanned aerial vehicles aircraft according to claim 1, it is characterised in that：In described nacelle radome fairing
Portion is provided with motor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720660199.XU CN206813315U (en) | 2017-06-08 | 2017-06-08 | A kind of four rotor wing unmanned aerial vehicle aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720660199.XU CN206813315U (en) | 2017-06-08 | 2017-06-08 | A kind of four rotor wing unmanned aerial vehicle aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206813315U true CN206813315U (en) | 2017-12-29 |
Family
ID=60759305
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720660199.XU Expired - Fee Related CN206813315U (en) | 2017-06-08 | 2017-06-08 | A kind of four rotor wing unmanned aerial vehicle aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206813315U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114514172A (en) * | 2020-12-31 | 2022-05-17 | 深圳市大疆创新科技有限公司 | Unmanned plane |
-
2017
- 2017-06-08 CN CN201720660199.XU patent/CN206813315U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114514172A (en) * | 2020-12-31 | 2022-05-17 | 深圳市大疆创新科技有限公司 | Unmanned plane |
| WO2022141572A1 (en) * | 2020-12-31 | 2022-07-07 | 深圳市大疆创新科技有限公司 | Unmanned aerial vehicle |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20171229 Termination date: 20200608 |