CN103640700A - Anti-drifting nozzle device for spraying of fixed wing aircraft - Google Patents
Anti-drifting nozzle device for spraying of fixed wing aircraft Download PDFInfo
- Publication number
- CN103640700A CN103640700A CN201310676406.7A CN201310676406A CN103640700A CN 103640700 A CN103640700 A CN 103640700A CN 201310676406 A CN201310676406 A CN 201310676406A CN 103640700 A CN103640700 A CN 103640700A
- Authority
- CN
- China
- Prior art keywords
- spray boom
- housing
- drift
- fixed wing
- wing aircraft
- 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
Images
Abstract
The invention discloses an anti-drifting nozzle device for spraying of a fixed wing aircraft, and belongs to the technical field of agricultural aviation plant protection equipment. The anti-drifting nozzle device comprises an L-shaped spray rod, a cover, a nozzle part, an inner guide vane, a primary diffusion section, a secondary diffusion section and an overflowing hole. The device is mounted on the horizontal spray rod below an aircraft wing and symmetrically arranged on two sides of the aircraft wing. In a spraying operation process of the fixed wing aircraft, a high-speed incoming flow passes through the overflowing hole to form a deflection air flow, fog drops are guided to deposit to plants in a target area, the anti-drifting performance of the device is realized, and the influences caused by factors such as flowing around of the aircraft wing and the like on fog drop deposition are reduced; and at the same time, a buffering effect between the flowing around the aircraft wing and the fog drops by rough air produced in an outer wall boundary layer of the device is realized, and the anti-drifting effect of the device is enhanced further.
Description
Technical field
Patent of the present invention relates to a kind of fixed wing aircraft spraying with anti-drift ejecting device, belongs to efficient plant protection spray technique field, specifically, is a kind of anti-drift device of fixed wing aircraft fog system for the spraying operation of large area farmland that is specifically designed to.
Background technology
Agricultural aviation spray technique is a kind of efficient, advanced modern agriculture plant protection technology, and it has the advantages that operating efficiency is high, safety good, applicability is wide and cost is low, and the Qi U.S., Japan and the large agricultural country such as Brazilian have now obtained widespread use.In aviation spraying operation process, owing to being subject to the impact of the factors such as environment wind-force, flying speed, attitude and manual control, part pesticide droplet can float to non-target region and produce deposition thereupon along with air-flow, form so-called spray drift phenomenon, this phenomenon has had a strong impact on operation quality and the efficiency of aviation spraying, and farmland surrounding environment and crowd etc. are produced to very large harm, spray drift is an agricultural aviation spraying field important problem urgently to be resolved hurrily.At present, in agricultural aviation technical field, about the spray research of anti-drift technology of aviation, comprise initiatively anti-drift technology, passive anti-drift technology, the aspects such as anti-drift nozzle technology and spray model technology, considering on the gentle stream distribution characteristics of fixed wing aircraft fog system operation basis, patent of the present invention guides and boundary 1ayer control technology by air-flow, design a kind of nothing power consumption that has, the active anti-drift device of the lightweight and strong feature of applicability, this device utilizes the air high speed incoming flow of wing front end in flight course, by housing top flowing hole, form deflection air-flow at a high speed, the droplet that shower nozzle produces is drifted about towards ground plant direction, the rough air simultaneously being produced by device outside wall surface boundary layer flow just and between shower nozzle mist torch has been set up cushion space under the wings of an airplane, avoid the droplet of shower nozzle outlet towards the tail space drift of wing below, reduce the impact of moving on spraying droplet of streaming of aerofoil surface.At present, at home and abroad about agricultural aviation, spray in the research of anti-drift technology, yet there are no similar patent of invention report.
Summary of the invention
Technical matters solved by the invention: in agricultural fixed wing aircraft spraying operation process, be subject to the impact of the factors such as ambient windstream, wing winding flow disturbance and temperature traverse, be easy to produce serious spray drift phenomenon, the efficiency that has reduced aviation spraying has a negative impact to surrounding environment simultaneously.In order to improve anti-drift performance and the accuracy of fixed wing aircraft spraying.Consider the high speed inlet flow conditions producing at fixed wing aircraft in operation process, the invention provides a kind of so anti-drift ejecting device, by the flowing hole of housing, change the direction of high speed incoming flow, the deflection air-flow that formation is mobile towards ground, by the two-phase shear flow between deflection air-flow and spraying droplet, deflection air-flow can increase spraying droplet towards the deposition velocity of ground plant direction, meanwhile, by the boundary layer perturbation air-flow of housing and diffuser outer wall, between wing winding flow flow field and spraying droplet, set up the cushion space with certain flowing law, reduce the impact of wing winding flow on spray drift, thereby improve operation quality and the efficiency of fixed wing aircraft fog system.
The technical solution adopted for the present invention to solve the technical problems is: anti-drift ejecting device comprises housing 1, interior stator 2, nozzle component 3, chopped-off head diffuser 4, secondary diffuser 5, flowing hole 6 and L-type spray boom 7.Nozzle component 3 is fixedly mounted on L-type spray boom 7 ends, and housing 1 inwall and L-type spray boom 7 are fixedly connected.Housing 1, chopped-off head diffuser 4 and secondary diffuser 5 connect successively along spray boom axis direction, and form air-flow and pass through space.Housing 1 outer wall is the tapering type rotational symmetry thin-wall construction of arc along spray boom axis direction, outer wall section start camber line and spray boom axis direction angle are α 1, interior stator 2 is thin-walled muscle rib structure radially in housing 1, it is uniformly distributed circumferentially in housing, in housing 1 upper design, there is some well-distributeds flowing hole, housing 1 bottom wall does not have flowing hole, housing 1 tip designs has chopped-off head diffuser 4 and 5 two diffusion structures of secondary diffuser, it is rotational symmetry thin-wall construction, and its wall and spray boom axis direction angle are respectively α 2 and α 3.α 1 is between 35 ° to 45 °.α 2 is between 35 ° to 45 °.α 3 is between 40 ° to 55 °.
Liquid flows through L-type spray boom 7 and nozzle component 3, and the droplet group that nozzle component 3 sprays and deflection air-flow form gas-liquid two-phase droplet at housing 1 back space and flow.
During use, along the arranged beneath of fixed wing aircraft wing, parallel with it horizontal spray boom is installed, anti-drift ejecting device is arranged on the horizontal spray boom of wing below by L-type spray boom 7, and this device is symmetrical arrangement in wing both sides.By flowing hole 6, high speed incoming flow is guided in housing 1,2 pairs of deflection air-flows of interior stator have certain even rectification effect, with this, increase stability and the degree of uniformity of deflection air-flow, the outer wall boundary layer of housing 1, chopped-off head diffuser 4 and secondary diffuser 5 can produce the rough air with certain pooling feature, to alleviate the impact of wing winding flow on spraying droplet, generally speaking, the inside and outside air-flow producing in high speed incoming flow by this anti-drift ejecting device, can effectively improve the anti-drift performance of aviation spraying operation.
Beneficial effect of the present invention: anti-drift ejecting device provided by the present invention has feature simple in structure, that nothing consumes energy, reliable and applicability is strong, solved the droplet group drifting problem in fixed wing aircraft spray process, applicable to the aviation fog system with large area farmland spraying job requirements.
Accompanying drawing explanation
Fig. 1 is anti-drift ejecting device constructional drawing for fixed wing aircraft is sprayed.
Fig. 2 is the scheme of installation of anti-drift ejecting device for fixed wing aircraft spraying.
In figure: 1-housing, 2-interior stator, 3-nozzle component, 4-chopped-off head diffuser, 5-secondary diffuser, 6-flowing hole, 7-L-type spray boom, 8-anti-drift ejecting device, 9-horizontal spray boom, 10-wing, 11-fixed wing aircraft body, 12-screw propeller.
The specific embodiment
Fixed wing aircraft spraying comprises housing 1, interior stator 2, nozzle component 3, chopped-off head diffuser 4, secondary diffuser 5, flowing hole 6, L-type spray boom 7 with anti-drift ejecting device.Housing 1, chopped-off head diffuser 4 and secondary diffuser 5 connect successively along spray boom axis direction, and form air-flow and pass through space, interior stator 2 is radially thin-walled muscle rib structure in housing 1, between housing 1 inwall and L-type spray boom 7 outer walls, be fixedly connected, nozzle component 3 is fixedly mounted on the end of L-type spray boom 7, liquid flows through L-type spray boom 7 and nozzle component 3, and the droplet group that nozzle component 3 sprays and deflection air-flow form gas-liquid two-phase droplet at housing 1 back space and flow.
When using this device, anti-drift ejecting device 8 is arranged on by L-type spray boom 7 on the horizontal spray boom 9 of wing 10 belows, and this device is symmetrical arrangement in wing 10 both sides.Arranged beneath along fixed wing aircraft wing is installed parallel with it horizontal spray boom 9.The air high speed incoming flow that in flight course, wing front end produces forms deflection air-flow by housing top flowing hole at a high speed, the droplet that shower nozzle produces is drifted about towards ground plant direction, the rough air simultaneously being produced by device outside wall surface boundary layer flow just and between shower nozzle mist torch has been set up cushion space under the wings of an airplane, avoid the droplet of shower nozzle outlet towards the tail space drift of wing below, reduce the impact of moving on spraying droplet of streaming of aerofoil surface.
Claims (5)
1. a fixed wing aircraft anti-drift ejecting device for spraying, comprise housing (1), interior stator (2), nozzle component (3), chopped-off head diffuser (4), secondary diffuser (5), flowing hole (6) and L-type spray boom (7), it is characterized in that: anti-drift ejecting device is arranged on the horizontal spray boom of wing below by L-type spray boom (7), nozzle component (3) is fixedly mounted on L-type spray boom end, and housing (1) inwall and L-type spray boom (7) are fixedly connected; Housing (1), chopped-off head diffuser (4) and secondary diffuser (5) connect successively along spray boom axis direction, and form air-flow and pass through space; Housing (1) outer wall is the tapering type rotational symmetry thin-wall construction of arc along spray boom axis direction, outer wall section start camber line and spray boom axis direction angle are α 1, interior stator (2) is thin-walled muscle rib structure radially in housing, it is uniformly distributed circumferentially in housing, on housing (1) top, there is flowing hole (6), housing (1) bottom wall does not have flowing hole, housing (1) end has chopped-off head diffuser (4) and (5) two diffusion structures of secondary diffuser, it is rotational symmetry thin-wall construction, and its wall and spray boom axis direction angle are respectively α 2 and α 3.
2. fixed wing aircraft spraying according to claim 1, with anti-drift ejecting device, is characterized in that: flowing hole (6) is for being uniformly distributed.
3. fixed wing aircraft spraying according to claim 1, with anti-drift ejecting device, is characterized in that, housing (1) outer wall section start camber line and spray boom axis direction angle α 1 are between 35 ° to 45 °.
4. fixed wing aircraft spraying according to claim 1, with anti-drift ejecting device, is characterized in that, chopped-off head diffuser (4) wall and spray boom axis direction angle α 2 are between 35 ° to 45 °.
5. fixed wing aircraft spraying according to claim 1, with anti-drift ejecting device, is characterized in that, secondary diffuser (5) wall and spray boom axis direction angle α 3 are between 40 ° to 55 °.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310676406.7A CN103640700A (en) | 2013-12-13 | 2013-12-13 | Anti-drifting nozzle device for spraying of fixed wing aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310676406.7A CN103640700A (en) | 2013-12-13 | 2013-12-13 | Anti-drifting nozzle device for spraying of fixed wing aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN103640700A true CN103640700A (en) | 2014-03-19 |
Family
ID=50246040
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310676406.7A Pending CN103640700A (en) | 2013-12-13 | 2013-12-13 | Anti-drifting nozzle device for spraying of fixed wing aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN103640700A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106482929A (en) * | 2016-11-30 | 2017-03-08 | 南京航空航天大学 | A kind of cover type thin-slab structure streaming tail for cutting down probe pole |
| CN106672231A (en) * | 2016-10-19 | 2017-05-17 | 吴瑞霞 | Unmanned aerial vehicle |
| JP2020059001A (en) * | 2018-10-12 | 2020-04-16 | 株式会社プロドローン | Unmanned aircraft |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5025988A (en) * | 1988-10-17 | 1991-06-25 | Maynard Lund | Airborne liquid spraying system for crop spraying |
| JP2005297790A (en) * | 2004-04-13 | 2005-10-27 | New Delta Ind Co | Chemical spraying device mounted to radio control helicopter |
| CN201395248Y (en) * | 2009-05-18 | 2010-02-03 | 张�杰 | Ultralow-volume spraying system of remote control helicopter for aviation plant protection |
| CN102000646A (en) * | 2010-12-09 | 2011-04-06 | 大连东芳果菜专业合作社 | Drift-proof pesticide precise spray cap |
-
2013
- 2013-12-13 CN CN201310676406.7A patent/CN103640700A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5025988A (en) * | 1988-10-17 | 1991-06-25 | Maynard Lund | Airborne liquid spraying system for crop spraying |
| JP2005297790A (en) * | 2004-04-13 | 2005-10-27 | New Delta Ind Co | Chemical spraying device mounted to radio control helicopter |
| CN201395248Y (en) * | 2009-05-18 | 2010-02-03 | 张�杰 | Ultralow-volume spraying system of remote control helicopter for aviation plant protection |
| CN102000646A (en) * | 2010-12-09 | 2011-04-06 | 大连东芳果菜专业合作社 | Drift-proof pesticide precise spray cap |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106672231A (en) * | 2016-10-19 | 2017-05-17 | 吴瑞霞 | Unmanned aerial vehicle |
| CN106482929A (en) * | 2016-11-30 | 2017-03-08 | 南京航空航天大学 | A kind of cover type thin-slab structure streaming tail for cutting down probe pole |
| CN106482929B (en) * | 2016-11-30 | 2018-08-28 | 南京航空航天大学 | It is a kind of to be used to cut down the cover type thin-slab structure that probe strut streams tail |
| JP2020059001A (en) * | 2018-10-12 | 2020-04-16 | 株式会社プロドローン | Unmanned aircraft |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103661946A (en) | Flow diversion anti-drifting devices for rotary-wing unmanned plane mist spraying | |
| CN106394906B (en) | A kind of the nozzle configuration mode and its sprinkling system of the agricultural unmanned plane of more rotors | |
| CN108271759A (en) | A kind of multi-rotor unmanned aerial vehicle sprinkling system | |
| CN105134383B (en) | Hypersonic interior rotatable air intake duct lip cover method for designing based on streamline deviation | |
| CN103640700A (en) | Anti-drifting nozzle device for spraying of fixed wing aircraft | |
| CN103723274A (en) | Spraying device for rotorcraft and application thereof | |
| CN107021235B (en) | A kind of low-to-medium altitude aircraft driving device, driving method and low-to-medium altitude aircraft | |
| CN203329386U (en) | Hot air distributor for spray tower | |
| CN205186508U (en) | Novel many rotor unmanned aerial vehicle wing | |
| CN109850128A (en) | Multistage air blowing circular rector high lift device and aircraft | |
| CN105289863A (en) | Tangential centrifugal agricultural sprayer nozzle with two spraying hole sheets | |
| CN204979220U (en) | But agricultural many rotor unmanned aerial vehicle of automatic adjustment flight height | |
| CN205392785U (en) | Meticulous atomizing helix sprinkler head | |
| CN102288380B (en) | Blowing type gust generator | |
| CN203601567U (en) | Compound sprinkling system of helicopter | |
| CN111674534A (en) | Closed-loop active flow control device of underwater glider based on constant-temperature blowing and sucking flow | |
| CN203946277U (en) | A kind of unmanned plane for spraying insecticide | |
| CN202819401U (en) | Sprayer and pneumatic conveying spraying device thereof | |
| CN113619772B (en) | Jet-type second grade spout circulation control wing section in coordination | |
| CN108583899A (en) | A kind of novel spray structure on unmanned plane propeller | |
| CN204735092U (en) | Rotatory atomizing waste gas spray set | |
| CN209238214U (en) | A kind of energy-saving atomized spray head of agricultural unmanned plane | |
| CN204433072U (en) | A kind of canard with vector spout and a kind of aircraft | |
| CN105818970A (en) | Upper air unmanned paint sprayer | |
| CN203780795U (en) | Aft body blowing type rectifying device of airplane with double engines and single vertical fin |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20140319 |