CN109747833A - A kind of removable duct spray appliance - Google Patents
A kind of removable duct spray appliance Download PDFInfo
- Publication number
- CN109747833A CN109747833A CN201711068738.1A CN201711068738A CN109747833A CN 109747833 A CN109747833 A CN 109747833A CN 201711068738 A CN201711068738 A CN 201711068738A CN 109747833 A CN109747833 A CN 109747833A
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- duct
- main body
- fuselage main
- engine
- steering engine
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Abstract
The present invention relates to a kind of removable duct spray appliances, including unmanned plane, the unmanned plane includes fuselage main body, first duct, second duct, third duct, 4th duct, nose-gear and rear undercarriage, first duct, second duct, the inside of third duct and the 4th duct is provided with blower device and spray head, first duct, second duct, the exit of third duct and the 4th duct is respectively connected with rectifying cavity, the import of the rectifying cavity and the outlet of duct are smoothly connected, multiple spray heads are provided in the duct, the axial cross section of the rectification cavity wall is made of two sections curve, curve with duct wall connecting portion is upper section curve, exit site is lower section curve.The present invention keeps the flight of the duct spray appliance more flexible, and the operation of user is more convenient, has reached better spray effect, has saved a large amount of labour and time, ensure that the pharmacological property of normal pesticide.
Description
Technical field
The present invention relates to air vehicle technique field more particularly to a kind of removable duct spray appliances.
Background technique
With rapid development of economy, scientific and technological is showing improvement or progress day by day, and unmanned plane has been widely used in agricultural field of irrigating, and
And play an important role, but traditional unmanned plane, in flying spray operation, spraying operation uses insufflation showerhead to carry out work
Make, in sprinkler design, for sprinkling uniformly and from the aspect of medical fluid makes full use of, what the liquid-drop diameter of ejection often designed
The smaller the better, such spray head is in ground machine operation in use, since spray head is close with plant and ground distance, after medical fluid ejection very
Site of action can be reached fastly, and influence of the evaporative effect to medical fluid almost can be ignored, but applies when it and spray in flight
Field, since there is certain altitude on plane distance ground, the drop of ejection needs to arrive by one section of quite long sedimentation time
Up to ground, drop evaporation capacity at this time will be far longer than evaporation capacity in ground spray, cause a large amount of wastes of medicament.
Summary of the invention
The purpose of the invention is to overcome the deficiencies of the prior art and provide a kind of removable duct spray appliance.
The present invention is achieved through the following technical solutions:
A kind of removable duct spray appliance, including unmanned plane, the unmanned plane include fuselage main body, the first duct,
The first of two ducts, third duct, the 4th duct, nose-gear and rear undercarriage, first duct and the fuselage main body
Side connection, second duct connect with second side of the fuselage main body, and the of the third duct and the fuselage main body
The connection of three sides, the 4th duct are connect with the 4th side of the fuselage main body, first duct and the third duct phase
The fuselage main body is symmetrical arranged, second duct and the 4th duct are symmetrically set relative to the fuselage main body
It sets, the lower head of the fuselage main body is arranged in the nose-gear, and the fuselage main body is arranged in the rear undercarriage
Below tail portion, first duct, the second duct, third duct and the 4th duct inside be provided with blower device and spray
Head, the spray head are set at the lower wind direction of blower device, first duct, the second duct, third duct and the 4th duct
Exit be respectively connected with rectifying cavity, the rectifying cavity expand outwardly it is in the shape of a trumpet, the import of the rectifying cavity and duct
Outlet is smoothly connected, and multiple spray heads are provided in the duct, and the multiple spray head is described along the radially uniform distribution of duct inner wall
The axial cross section of rectification cavity wall is made of two sections curve, and the curve with duct wall connecting portion is upper section curve, outlet
Position is lower section curve, and upper section curve is the camber line that outward dissipates tangent with duct wall, and lower section curve is flat with upper section curve
Slip and to the convergent curve of duct axial direction.
Further, first duct is turned by the first side of the first duct direction controlling steering engine and the fuselage main body
Dynamic connection, second duct are rotatablely connected by second side of the second duct direction controlling steering engine and the fuselage main body, institute
It states third duct to be rotatablely connected by the third side of third duct direction controlling steering engine and the fuselage main body, the 4th duct
It is rotatablely connected by the 4th side of the 4th duct direction controlling steering engine and the fuselage main body.
Further, the first duct direction controlling steering engine is turned by the first side of the first steering wheel and the fuselage main body
Dynamic connection, the second duct direction controlling steering engine are rotatablely connected by second side of the second steering wheel and the fuselage main body, institute
It states third duct direction controlling steering engine to be rotatablely connected by the third side of third steering wheel and the fuselage main body, the 4th duct
Direction controlling steering engine is rotatablely connected by the 4th side of the 4th steering wheel and the fuselage main body.
Further, first duct, the second duct, third duct and the 4th duct be identical and duct internal diameter with
The ratio of duct width within the scope of 1.4-1.6, blower device at duct entrance one third, duct outlet diameter with
Duct internal diameter ratio is within the scope of 1.1-1.2.
Further, first duct, the second duct, third duct and the 4th duct be identical and duct internal diameter with
The ratio of duct width is 1.5, and the duct outlet diameter and duct internal diameter ratio are 1.15.
It further, further include controller, the first duct direction controlling steering engine of the controller and first duct
And the second duct direction controlling steering engine and the second engine, the third duct of first engine, second duct
Third duct direction controlling steering engine and third engine, the 4th duct direction controlling steering engine of the 4th duct and
Four engines, the undercarriage steering-engine are electrically connected, and the controller is started by control first engine, second
Machine, the revolving speed of third engine and the 4th engine and first duct, the second duct, third duct and the 4th duct
Direction controls the flight of unmanned plane.
Compared with prior art, the beneficial effects of the present invention are: the duct spray appliance in the present invention includes four positions
In the duct that the unmanned plane is not ipsilateral, by described four be located at the not ipsilateral duct of the unmanned plane be the unmanned plane provide power with
The adjustment for carrying out direction avoids screw blade injury caused by people of peripheral hardware, while spray head being arranged in duct,
It is provided with blower device in duct, gives drop one initial downward sinking speed by blower device, accelerates the sedimentation of drop
Speed greatly reduces infall process Chinese medicine volatile quantity, but also the flight of the unmanned plane spray appliance is more flexible, user
Operation it is more convenient.
Detailed description of the invention
Fig. 1 is the structural diagram of the present invention；
Fig. 2 is the structural schematic diagram of duct in the present invention；
Fig. 3 is the sectional view and air-flow schematic diagram of Fig. 2.
In figure: 1, the first duct；2, the second duct；3, third duct；4, the 4th duct；5, the first duct direction controlling rudder
Machine；6, the second duct direction controlling steering engine；7, third duct direction controlling steering engine；8, the 4th duct direction controlling steering engine；9, machine
Body main body；10, blower device；11, spray head；12, rectifying cavity；13, upper curve；14, lower curve.
Specific embodiment
In order to make the objectives, technical solutions, and advantages of the present invention clearer, with reference to the accompanying drawings and embodiments, right
The present invention is further elaborated.It should be appreciated that the specific embodiments described herein are merely illustrative of the present invention, and
It is not used in the restriction present invention.
Please refer to Fig. 1, Fig. 2 and a kind of removable duct spray appliance shown in Fig. 3, including unmanned plane, the unmanned plane
It is described including fuselage main body 9, the first duct 1, the second duct 2, third duct 3, the 4th duct 4, nose-gear and rear undercarriage
First duct 1 is connect with the first side of the fuselage main body 9, and second duct 2 and second side of the fuselage main body 9 connect
It connecing, the third duct 3 is connect with the third side of the fuselage main body 9, and the of the 4th duct 4 and the fuselage main body 9
The connection of four sides, first duct 1 and the third duct 3 are symmetrical arranged relative to the fuselage main body 9, second duct
2 and the 4th duct 4 relative to the fuselage main body 9 be symmetrical arranged, the fuselage main body 9 is arranged in the nose-gear
Lower head, it is described after undercarriage be arranged in below the tail portion of the fuselage main body 9, first duct 1, the second duct 2, the
The inside of three ducts 3 and the 4th duct 4 is provided with blower device 10 and spray head 11, and the spray head 11 is set to blower device 10
Lower wind direction at, first duct 1, the second duct 2, third duct 3 and the 4th duct 4 exit be respectively connected with rectifying cavity
12, the rectifying cavity 12 expands outwardly in the shape of a trumpet, and the import of the rectifying cavity 12 and the outlet of duct are smoothly connected, described
Be provided with multiple spray heads 11 in duct, the multiple spray head 11 along the radially uniform distribution of duct inner wall, 12 wall of rectifying cavity
Axial cross section is made of two sections curve, and the curve with duct wall connecting portion is upper section curve 13, under exit site is
Section curve 14, upper section curve 13 are the camber line that outward dissipates tangent with duct wall, and lower section curve 14 is and upper section curve smoothing
Connection and to the convergent curve of duct axial direction.
In the present embodiment, first duct 1 pass through the first duct direction controlling steering engine 5 and the fuselage main body 9 the
Side rotation connection, second duct 2 are turned by the second duct direction controlling steering engine 6 and second side of the fuselage main body 9
Dynamic connection, the third duct 3 are rotatablely connected by the third side of third duct direction controlling steering engine 7 and the fuselage main body 9,
4th duct 4 is rotatablely connected by the 4th duct direction controlling steering engine 8 and the 4th side of the fuselage main body 9, and described the
One duct direction controlling steering engine 5 is rotatablely connected by the first side of the first steering wheel and the fuselage main body 9, the second duct side
It is rotatablely connected to control steering engine 6 by second side of the second steering wheel and the fuselage main body 9, the third duct direction controlling rudder
Machine 7 is rotatablely connected by the third side of third steering wheel and the fuselage main body 9, and the 4th duct direction controlling steering engine 8 passes through
4th side of the 4th steering wheel and the fuselage main body 9 is rotatablely connected.
In the present embodiment, first duct 1, the second duct 2, third duct 3 and the 4th duct 4 are identical and duct
The ratio of internal diameter and duct width is 1.5, and the duct outlet diameter and duct internal diameter ratio are 1.15.
It further include controller in the present embodiment, the first duct direction controlling rudder of the controller and first duct 1
The the second duct direction controlling steering engine 6 and the second engine, the third of machine 5 and the first engine, second duct 2
The third duct direction controlling steering engine 7 of duct 3 and the 4th duct direction controlling rudder of third engine, the 4th duct 4
Machine 8 and the 4th engine, the undercarriage steering-engine are electrically connected, and the controller is started by control described first
Revolving speed and first duct 1, the second duct 2, the third culvert of machine, the second engine, third engine and the 4th engine
The direction of road 3 and the 4th duct 4 controls the flight of unmanned plane.
Duct spray appliance in the present invention includes four and is located at the not ipsilateral duct of the unmanned plane, is located at by described four
The not ipsilateral duct of the unmanned plane provides power for the unmanned plane and carries out the adjustment in direction, and the screw blade for avoiding peripheral hardware can
It can be injured caused by people, while spray head being arranged in duct, due to being arranged spray head in duct, air blast is set in duct
Device, blower device give drop one initial downward sinking speed, accelerate the sinking speed of drop, while to avoid droplets from
It collides with each other in narrow duct and is combined into biggish drop, in the duct rear design rectifying cavity of bulging, when air-flow rushes
After duct enters rectifying cavity out, due to the adherent and Coanda effect of high-speed flow, air-flow will be distributed along the inner wall part of rectifying cavity, patch
Wall goes out rectifying cavity, is thusly-formed the biggish sprinkling air-flow in a cross section, it is ensured that normal spray effect, simultaneously because
Drop is applied with a biggish downward initial velocity by blower device, will be more a small number of than the natural subsidence used time times, substantially reduces
Medicament volatile quantity in infall process, but also the flight of the unmanned plane spray appliance is more flexible, the operation of user is more
It is convenient, reach better spray effect, saved a large amount of labour and time, ensure that the pharmacological property of normal pesticide.
The foregoing is merely illustrative of the preferred embodiments of the present invention, is not intended to limit the invention, all in essence of the invention
Made any modifications, equivalent replacements, and improvements etc., should all be included in the protection scope of the present invention within mind and principle.
Claims (6)
1. a kind of removable duct spray appliance, it is characterised in that: including unmanned plane, the unmanned plane include fuselage main body (9),
First duct (1), the second duct (2), third duct (3), the 4th duct (4), nose-gear and rear undercarriage, described first contains
Road (1) is connect with the first side of the fuselage main body (9), and second side of second duct (2) and the fuselage main body (9) connects
It connects, the third duct (3) connect with the third side of the fuselage main body (9), the 4th duct (4) and the fuselage main body
(9) the 4th side connection, first duct (1) and the third duct (3) are symmetrically set relative to the fuselage main body (9)
It sets, second duct (2) and the 4th duct (4) are symmetrical arranged relative to the fuselage main body (9), the nose-gear
Lower head in the fuselage main body (9) is set, the rear undercarriage is arranged below the tail portion of the fuselage main body (9),
First duct (1), the second duct (2), third duct (3) and the 4th duct (4) inside be provided with blower device
(10) and spray head (11), the spray head (11) are set at the lower wind direction of blower device (10), first duct (1), second
The exit of duct (2), third duct (3) and the 4th duct (4) is respectively connected with rectifying cavity (12), and the rectifying cavity (12) is outside
Expand in the shape of a trumpet, the import of the rectifying cavity (12) and the outlet of duct are smoothly connected, and are provided in the duct multiple
Spray head (11), the multiple spray head (11) is along the radially uniform distribution of duct inner wall, and the axial cross section of the rectification cavity wall is by upper
Lower two sections of curves composition, the curve with duct wall connecting portion are upper section curve (13), and exit site is lower section curve (14), on
Section curve (13) be the camber line that outward dissipates tangent with duct wall, lower section curve (14 for connect with upper section curve smoothing and to
The convergent curve of duct axial direction.
2. a kind of removable duct spray appliance according to claim 1, it is characterised in that: first duct (1) is logical
The first side for crossing the first duct direction controlling steering engine (5) and the fuselage main body (9) is rotatablely connected, and second duct (2) is logical
The second side for crossing the second duct direction controlling steering engine (6) and the fuselage main body (9) is rotatablely connected, and the third duct (3) is logical
The third side for crossing third duct direction controlling steering engine (7) and the fuselage main body (9) is rotatablely connected, and the 4th duct (4) is logical
The 4th side for crossing the 4th duct direction controlling steering engine (8) and the fuselage main body (9) is rotatablely connected.
3. a kind of removable duct spray appliance according to claim 1 or 2, it is characterised in that: the first duct side
It is rotatablely connected to control steering engine (5) by the first side of the first steering wheel and the fuselage main body (9), the control of second duct direction
Steering engine (6) processed is rotatablely connected by second side of the second steering wheel and the fuselage main body (9), the third duct direction controlling rudder
Machine (7) is rotatablely connected by the third side of third steering wheel and the fuselage main body (9), the 4th duct direction controlling steering engine
(8) it is rotatablely connected by the 4th side of the 4th steering wheel and the fuselage main body (9).
4. a kind of removable duct spray appliance according to claim 3, it is characterised in that: first duct (1),
Two ducts (2), third duct (3) and the 4th duct (4) are identical and the ratio of duct internal diameter and duct width is in 1.4-1.6
In range, blower device (10) is at duct entrance one third, and duct outlet diameter and duct internal diameter ratio are in 1.1-1.2
In range.
5. a kind of removable duct spray appliance according to claim 4, it is characterised in that: first duct (1),
Two ducts (2), third duct (3) and the 4th duct (4) are identical and the ratio of duct internal diameter and duct width is 1.5, institute
Stating duct outlet diameter and duct internal diameter ratio is 1.15.
6. a kind of removable duct spray appliance according to claim 1 or 2 or 4, it is characterised in that: further include control
Device, the first duct direction controlling steering engine (5) and the first engine of the controller and first duct (1), described the
Second duct direction controlling steering engine (6) of two ducts (2) and the third duct side of the second engine, the third duct (3)
To control steering engine (7) and the 4th duct direction controlling steering engine (8) and the 4th of third engine, the 4th duct (4)
Engine, the undercarriage steering-engine are electrically connected, and the controller is started by control first engine, second
Machine, the revolving speed of third engine and the 4th engine and first duct (1), the second duct (2), third duct (3) and
The direction of 4th duct (4) controls the flight of unmanned plane.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711068738.1A CN109747833A (en) | 2017-11-03 | 2017-11-03 | A kind of removable duct spray appliance |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711068738.1A CN109747833A (en) | 2017-11-03 | 2017-11-03 | A kind of removable duct spray appliance |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109747833A true CN109747833A (en) | 2019-05-14 |
Family
ID=66398052
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711068738.1A Pending CN109747833A (en) | 2017-11-03 | 2017-11-03 | A kind of removable duct spray appliance |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109747833A (en) |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106347648A (en) * | 2016-11-11 | 2017-01-25 | 北京航空航天大学 | Multi-rotor plant protection unmanned aerial vehicle |
| CN205952321U (en) * | 2016-08-04 | 2017-02-15 | 安阳全丰航空植保科技股份有限公司 | Duct formula sprinkler |
| CN106672230A (en) * | 2016-12-07 | 2017-05-17 | 深圳市元征科技股份有限公司 | Ducted unmanned aerial vehicle |
| CN106927023A (en) * | 2017-03-27 | 2017-07-07 | 上海珞鹏航空科技有限公司成都研发分公司 | A kind of agricultural plant protection controls culvert type unmanned plane with rudder face |
-
2017
- 2017-11-03 CN CN201711068738.1A patent/CN109747833A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN205952321U (en) * | 2016-08-04 | 2017-02-15 | 安阳全丰航空植保科技股份有限公司 | Duct formula sprinkler |
| CN106347648A (en) * | 2016-11-11 | 2017-01-25 | 北京航空航天大学 | Multi-rotor plant protection unmanned aerial vehicle |
| CN106672230A (en) * | 2016-12-07 | 2017-05-17 | 深圳市元征科技股份有限公司 | Ducted unmanned aerial vehicle |
| CN106927023A (en) * | 2017-03-27 | 2017-07-07 | 上海珞鹏航空科技有限公司成都研发分公司 | A kind of agricultural plant protection controls culvert type unmanned plane with rudder face |
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| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20190514 |