CN206243467U - A kind of four duct rotor wing unmanned aerial vehicles - Google Patents
A kind of four duct rotor wing unmanned aerial vehicles Download PDFInfo
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- CN206243467U CN206243467U CN201621252912.9U CN201621252912U CN206243467U CN 206243467 U CN206243467 U CN 206243467U CN 201621252912 U CN201621252912 U CN 201621252912U CN 206243467 U CN206243467 U CN 206243467U
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Abstract
The utility model is related to unmanned vehicle design field, more particularly to a kind of four ducts rotor wing unmanned aerial vehicle.Four duct rotor wing unmanned aerial vehicles include：Body；Fuel engines, is fixedly installed on the internal body；Four duct rotor assemblies, are uniformly distributed along same circumferencial direction and are fixed on the body outside, and be located in the same horizontal plane；Gear-box, including first gear, second gear, four two gears pass sequentially through spur gear and are meshed, and one of second gear is meshed with second gear by bevel gear structure；First Timing Belt, is arranged between the output shaft of fuel engines and the input shaft of first gear；Second Timing Belt, is arranged between the rotor output shaft of second gear and a propeller rotating shaft.Four ducts rotor wing unmanned aerial vehicle of the present utility model, drives four high-efficient duct fans to drive unmanned planes to complete the aerial missions such as VTOL by fuel engines, during with heavy－duty, boat long, high safety, using scope it is wide the features such as.
Description
Technical field
The utility model is related to unmanned vehicle design field, more particularly to a kind of four ducts rotor wing unmanned aerial vehicle.
Background technology
The culvert vertical take-off and landing unmanned machine system of petrol power four (hereinafter referred to as four ducts) is to rely on related mature technology, with
National strategy background and the multifunctional small-size UAS that Development of UAV background is demand research and development.Current many rotors are vertical
Short, load-carrying is small, the not high defect of security when there is boat landing unmanned plane more.Particularly in high-end civilian and Jun Mao fields city
, researched and developed using the unmanned plane in field for security, anti-terrorism, border patrol and arms operation etc. and need to be expanded.
The content of the invention
The purpose of this utility model there is provided a kind of four ducts rotor wing unmanned aerial vehicle, be deposited with solving existing multi-rotor unmanned aerial vehicle
At least one problem.
The technical solution of the utility model is：
A kind of four duct rotor wing unmanned aerial vehicles, including：
Body；
Fuel engines, is fixedly installed on the internal body；
Four duct rotor assemblies, are uniformly distributed along same circumferencial direction and are fixed on the body outside, and positioned at same
In horizontal plane；
Gear-box, including a first gear and arranged and four second gears engaging successively along same plane, institute
First gear one end end is stated for bevel gear structure, the other end has input shaft；One end end of four second gears is equal
Spur gear arrangement is provided with, spur gear is passed sequentially through and is meshed, the other end of four second gears is provided with rotor output
Axle；One end end with spur gear arrangement of one of them second gear is additionally provided with and is meshed with the second gear
Bevel gear structure；
First Timing Belt, is arranged between the input shaft of the output shaft of the fuel engines and the first gear；
Second Timing Belt, is arranged on the rotor output shaft and duct rotor assembly of second gear
Between propeller rotating shaft.
Preferably, one is provided with the portion position of the body upper middle and installs cabin concentratedly, the fuel engines and
Gear-box is fixedly installed on described installing concentratedly inside cabin.
Preferably, the duct rotor assembly includes duct and the propeller being arranged in the duct.
Preferably, the fuel engines is four cylinder four-stroke engine.
Preferably, the fuel engines is internally provided with supercharging device.
Preferably, the bottom of the body is fixedly installed Sledge type undercarriage.
Preferably, four described duct rotor wing unmanned aerial vehicles also include：
Fuel tank, is arranged on the organism bottom, is connected with the fuel engines, for being carried for the fuel engines
For fuel oil.
Preferably, the bottom of the body is fixedly installed setting hanger bracket.
Preferably, four described duct rotor wing unmanned aerial vehicles also include vehicle management computer, are arranged in the body
Portion, for controlling the flight of four duct rotor wing unmanned aerial vehicles.
The utility model has the advantage of：
Four ducts rotor wing unmanned aerial vehicle of the present utility model, using fuel engines as power source, is efficiently contained by four
Road fan drives unmanned plane to complete the aerial missions such as VTOL, during with heavy－duty, boat long, high safety, wide etc. using scope
Feature；Also, worked by four duct rotor assemblies of single driven by engine so that handling, wind resistance is substantially improved.
Brief description of the drawings
Fig. 1 is the structural representation of the duct rotor wing unmanned aerial vehicle of the utility model four；
Fig. 2 is the structure diagram of the duct rotor wing unmanned aerial vehicle of the utility model four；
Fig. 3 is the structure diagram of the duct rotor wing unmanned aerial vehicle gear-box of the utility model four.
Specific embodiment
For the purpose, technical scheme and advantage for implementing the utility model are clearer, below in conjunction with the utility model
Accompanying drawing in embodiment, is further described in more detail to the technical scheme in the utility model embodiment.In the accompanying drawings, ad initio
Same or similar element or element with same or like function are represented to same or similar label eventually.Described reality
It is a part of embodiment of the utility model to apply example, rather than whole embodiments.Below with reference to the embodiment of Description of Drawings
It is exemplary, it is intended to for explaining the utility model, and it is not intended that to limitation of the present utility model.It is new based on this practicality
Embodiment in type, the every other implementation that those of ordinary skill in the art are obtained under the premise of creative work is not made
Example, belongs to the scope of the utility model protection.Embodiment of the present utility model is described in detail below in conjunction with the accompanying drawings.
In description of the present utility model, it is to be understood that term " " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or position relationship of the instruction such as "left", "right", " vertical ", " level ", " top ", " bottom ", " interior ", " outward " are based on accompanying drawing institute
The orientation or position relationship for showing, are for only for ease of description the utility model and simplify description, signified rather than indicating or implying
Device or element must have specific orientation, with specific azimuth configuration and operation, therefore it is not intended that to this practicality
The limitation of novel protected scope.
1- Fig. 3 is described in further details to the duct rotor wing unmanned aerial vehicle of the utility model four below in conjunction with the accompanying drawings.
The utility model provide a kind of four ducts rotor wing unmanned aerial vehicle, can include body 1, dynamical system, task system,
Vehicle Management System, data catenary system etc., by Design of Aerodynamic Configuration, general layout completes the total arrangement of unmanned plane, and
Control to aircraft is completed by each mobile system.
Body 1：
Full machine has four duct rotor assemblies 3, one is provided with upper middle portion position and installs cabin 11 concentratedly, concentrates
Installing in cabin 11 can arrange engine, inertial navigation, task engine, battery, block terminal, gear-box 4, electro-optical system etc..In addition,
Install the upper flap of cabin 11 concentratedly to be connected by removably, to maintain easily.Body middle lower portion is provided with fuel tank 13, hangs
Hanger 14 and Sledge type undercarriage 12；Wherein, the quantity of hanger bracket 14 can as needed carry out suitable setting, and can use
Part when selecting various, in the present embodiment, hanger bracket 14 is two, can be used for hanging weapon.
Can include duct rotor assembly 3, engine system, fuel system, transmission device, displacement machine again in dynamical system
Structure and power supply.
Duct rotor assembly 3 can include duct 31 and the propeller 32 being arranged in duct 31.Wherein, duct 31 has
There is protection propeller 32, propeller efficiency improved, while duct lip can produce lift, duct lip Ying Yuji
Body collaborative design, to reduce aerodynamic interference.Propeller 32 is variable-distance propeller, and rotating speed is fixed, can be by changing propeller
Always away from change lift and torque；In addition, propeller 32 has propeller rotating shaft again.
Engine system is including fuel engines 2 and startup control box etc.；Fuel engines 2 preferably uses four cylinders four
Stroke Engine, in order to meet use requirement, fuel engines 2 carries out electrically activating repacking, and increases EFI and supercharging device, with
Improve the altitude acclimatization ability of aircraft.Also, fuel engines 2 is also equipped with starting control box, engine speed harvester etc.,
Start control box and configure contactor again.
Fuel system can provide reliable fuel feeding for fuel engines 2, mainly by fuel tank 13, filling conduit, outside confession
Oil pipe line, plus/fuel supply flow rate sensor and weight oil supply component constitute, the connected mode between each part can be using known
Connected mode, no longer specifically repeats.
Transmission device tentatively uses gear belt transmission, including gear-box 4, Timing Belt etc..
Four second gears that gear-box 4 includes a first gear 41 and arranged along same plane and engaged successively
42, one end end of first gear 41 is bevel gear structure, and the other end has input shaft；One end end of four second gears 42 is equal
Spur gear arrangement is provided with, spur gear is passed sequentially through and is meshed, the other end of four second gears 42 is provided with rotor output shaft；
One end end with spur gear arrangement of one of second gear 42 is additionally provided with the umbrella tooth being meshed with second gear 42
Wheel construction.
Timing Belt includes first Timing Belt 21 and four second Timing Belts 43.First Timing Belt 21 is arranged on fuel oil hair
Between the output shaft of motivation 2 and the input shaft of first gear 41；Second Timing Belt 43 is arranged on a rotor for second gear 42
Between output shaft and a propeller rotating shaft for duct rotor assembly 3, i.e., each second gear 42 is contained with one of respective side
Piece second Timing Belt 43 is set between road rotor assembly 3.
The output shaft of fuel engines 2 is connected to the input shaft of the first gear 41 of gear-box 4 by the first Timing Belt 21
On, the purpose of transmission power and adjustment revolution is reached, the inside of gear-box 4 passes through the bevel gear structure (first gear 41 for matching
Bevel gear structure and second gear 42 bevel gear structure) rotation direction is changed to vertically by level, while by four
The spur gear arrangement intermeshing of individual second gear 42, it is ensured that rotation direction (relative two-by-two) simultaneously realizes four power outputs, leads to
Cross four second Timing Belts 43 and rotating speed and power are passed into propeller rotating shaft, drive propeller 32 to rotate.
Pitch-changing mechanism：
This year utility model variable-distance propeller can use known various suitable displacement modes, in the present embodiment,
It is preferred that using center pull rod displacement mode.
Power supply can include being arranged on the main generator and reserve battery installed concentratedly inside cabin 11；Aircraft system power master
Main generator and reserve battery are derived from, main generator provides AC power output, is transformed to 28V by block terminal once electric
Source, powers to fly guard system, chain-circuit system and task system, and block terminal exports steering wheel power supply simultaneously.Block terminal realizes engine
CDI is powered and engine speed acquisition function, and information exchange is carried out with vehicle management computer by RS422 buses, is realized
The monitoring of power supply, power supply timing and cutting-in control.
Task system：
Mainly include mission computer, hanger bracket 14 etc. in task system, hanger bracket 14 can be according to different utilization demands
The different utensil of suspension；Mission computer can be used for corresponding part on control hanger bracket 14.
Vehicle Management System：
Vehicle Management System includes that vehicle management computer, executing agency, sensing system and chain-circuit system are constituted,
It is controlled for the flight to four duct rotor wing unmanned aerial vehicles.
Data catenary system：
Data catenary system selects ripe commercialization link, synchronous to develop multiple access link, and (2 small at least while to control 4 machines with realization
Group) demand.
Short, load-carrying is small, the stability of a system is poor, security when more than current domestic many rotor VUAVs in the presence of boat
Not high defect.General within 30 minutes during the boat of electronic unmanned plane, how not fully up to expectations load-carrying ability is also, generally 20kg
Within.
Four ducts rotor wing unmanned aerial vehicle of the present utility model, using fuel engines 2 as power source, is efficiently contained by four
Road fan drives unmanned plane to complete the aerial missions such as VTOL, during with heavy－duty, boat long, high safety, wide etc. using scope
Feature.Also, worked by four duct rotor assemblies 3 of single driven by engine so that handling, wind resistance is significantly carried
Rise.In addition, four ducts rotor wing unmanned aerial vehicle cruising time of the present utility model was up to more than 1 hour, efficient duct design is equipped with
High-power engine, makes its load-carrying ability up to 70kg.Further, four shrouded propellers 32 are wrapped in maximum limit within duct
Injury probability of the reduction of degree to personnel.Pressure charging system is installed additional by engine, it will greatly improve the altitude acclimatization of aircraft
Ability.
The above, specific embodiment only of the present utility model, but protection domain of the present utility model do not limit to
In this, any one skilled in the art in the technical scope that the utility model is disclosed, the change that can be readily occurred in
Change or replace, should all cover within protection domain of the present utility model.Therefore, protection domain of the present utility model should be with described
Scope of the claims is defined.
Claims (9)
1. a kind of four ducts rotor wing unmanned aerial vehicle, it is characterised in that including：
Body (1)；
Fuel engines (2), is fixedly installed on the body (1) internal；
Four duct rotors assembly (3), are uniformly distributed along same circumferencial direction and are fixed on the body (1) outside, and positioned at same
In one horizontal plane；
Gear-box (4), including a first gear (41) and arranged and four second gears engaging successively along same plane
(42), first gear (41) one end end is bevel gear structure, and the other end has input shaft；Four second gears
(42) one end end is provided with spur gear arrangement, passes sequentially through spur gear and is meshed, four second gears (42)
The other end is provided with rotor output shaft；One end end with spur gear arrangement of one of them second gear (42) also sets
It is equipped with the bevel gear structure being meshed with the second gear (42)；
First Timing Belt (21), is arranged on the output shaft of the fuel engines (2) and the input shaft of the first gear (41)
Between；
Second Timing Belt (43), is arranged on a rotor output shaft for the second gear (42) total with a duct rotor
Into between the propeller rotating shaft of (3).
2. four ducts rotor wing unmanned aerial vehicle according to claim 1, it is characterised in that body (1) the upper middle position
The place of putting is provided with one and installs cabin (11) concentratedly, and the fuel engines (2) and gear-box (4) are fixedly installed on described concentration pacifies
Stowage (11) is internal.
3. four ducts rotor wing unmanned aerial vehicle according to claim 1, it is characterised in that the duct rotor assembly (3) includes
Duct (31) and the propeller (32) being arranged in the duct.
4. four ducts rotor wing unmanned aerial vehicle according to claim 1, it is characterised in that the fuel engines (2) is four cylinders
Four-stroke engine.
5. four duct rotor wing unmanned aerial vehicles according to claim 1 or 4, it is characterised in that the fuel engines (2) is internal
It is provided with supercharging device.
6. four ducts rotor wing unmanned aerial vehicle according to claim 1, it is characterised in that the bottom of the body (1) is fixed and set
It is equipped with Sledge type undercarriage (12).
7. four ducts rotor wing unmanned aerial vehicle according to claim 1, it is characterised in that also include：
Fuel tank (13), is arranged on the body (1) bottom, is connected with the fuel engines (2), for being sent out for the fuel oil
Motivation (2) provides fuel oil.
8. four ducts rotor wing unmanned aerial vehicle according to claim 1, it is characterised in that the bottom of the body (1) is fixed and set
It is equipped with setting hanger bracket (14).
9. four ducts rotor wing unmanned aerial vehicle according to claim 1, it is characterised in that also including vehicle management computer,
The body (1) is arranged on internal, for controlling the flight of four duct rotor wing unmanned aerial vehicles.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621252912.9U CN206243467U (en) | 2016-11-18 | 2016-11-18 | A kind of four duct rotor wing unmanned aerial vehicles |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621252912.9U CN206243467U (en) | 2016-11-18 | 2016-11-18 | A kind of four duct rotor wing unmanned aerial vehicles |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206243467U true CN206243467U (en) | 2017-06-13 |
Family
ID=59001729
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201621252912.9U Active CN206243467U (en) | 2016-11-18 | 2016-11-18 | A kind of four duct rotor wing unmanned aerial vehicles |
Country Status (1)
| Country | Link |
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| CN (1) | CN206243467U (en) |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107298165A (en) * | 2017-08-02 | 2017-10-27 | 浙江大年科技有限公司 | A kind of fire-fighting duct depopulated helicopter |
| CN107416196A (en) * | 2017-07-05 | 2017-12-01 | 南宁学院 | A kind of aileron short distance logistics unmanned plane of a main wing four |
| CN107719657A (en) * | 2017-10-09 | 2018-02-23 | 武汉卓尔无人机制造有限公司 | A kind of rotor wing unmanned aerial vehicle of ducted fan four |
| CN107757883A (en) * | 2017-11-08 | 2018-03-06 | 沈阳旋飞航空技术有限公司 | A kind of dynamic unmanned plane undercarriage of oil |
| CN107826242A (en) * | 2017-11-30 | 2018-03-23 | 肖华清 | Culvert type multi-rotor unmanned aerial vehicle |
| CN108454839A (en) * | 2018-04-09 | 2018-08-28 | 重庆国飞通用航空设备制造有限公司 | A kind of efficient emergency broken window multi-rotor unmanned aerial vehicle system |
| CN109050899A (en) * | 2018-09-14 | 2018-12-21 | 汉中天行智能飞行器有限责任公司 | A kind of more helicopters |
| WO2019047429A1 (en) * | 2017-09-05 | 2019-03-14 | 北京工业大学 | Multi-rotor unmanned aerial vehicle-based duct propulsion system |
| JP2020100241A (en) * | 2018-12-21 | 2020-07-02 | 株式会社プロドローン | Unmanned aircraft |
| CN112340032A (en) * | 2020-11-18 | 2021-02-09 | 武汉纺织大学 | Hybrid four-duct manned aircraft |
-
2016
- 2016-11-18 CN CN201621252912.9U patent/CN206243467U/en active Active
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107416196A (en) * | 2017-07-05 | 2017-12-01 | 南宁学院 | A kind of aileron short distance logistics unmanned plane of a main wing four |
| CN107298165A (en) * | 2017-08-02 | 2017-10-27 | 浙江大年科技有限公司 | A kind of fire-fighting duct depopulated helicopter |
| WO2019047429A1 (en) * | 2017-09-05 | 2019-03-14 | 北京工业大学 | Multi-rotor unmanned aerial vehicle-based duct propulsion system |
| CN107719657A (en) * | 2017-10-09 | 2018-02-23 | 武汉卓尔无人机制造有限公司 | A kind of rotor wing unmanned aerial vehicle of ducted fan four |
| CN107757883A (en) * | 2017-11-08 | 2018-03-06 | 沈阳旋飞航空技术有限公司 | A kind of dynamic unmanned plane undercarriage of oil |
| CN107826242A (en) * | 2017-11-30 | 2018-03-23 | 肖华清 | Culvert type multi-rotor unmanned aerial vehicle |
| CN108454839A (en) * | 2018-04-09 | 2018-08-28 | 重庆国飞通用航空设备制造有限公司 | A kind of efficient emergency broken window multi-rotor unmanned aerial vehicle system |
| CN109050899A (en) * | 2018-09-14 | 2018-12-21 | 汉中天行智能飞行器有限责任公司 | A kind of more helicopters |
| JP2020100241A (en) * | 2018-12-21 | 2020-07-02 | 株式会社プロドローン | Unmanned aircraft |
| CN112340032A (en) * | 2020-11-18 | 2021-02-09 | 武汉纺织大学 | Hybrid four-duct manned aircraft |
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