CN106152123A - It is applied to the flame device of unmanned plane - Google Patents
It is applied to the flame device of unmanned plane Download PDFInfo
- Publication number
- CN106152123A CN106152123A CN201610727329.7A CN201610727329A CN106152123A CN 106152123 A CN106152123 A CN 106152123A CN 201610727329 A CN201610727329 A CN 201610727329A CN 106152123 A CN106152123 A CN 106152123A
- Authority
- CN
- China
- Prior art keywords
- fixed
- unmanned plane
- flame
- injection
- combustion gas
- 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.)
- Granted
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/02—Aircraft not otherwise provided for characterised by special use
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
- F23D11/36—Details, e.g. burner cooling means, noise reduction means
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
- F23D14/46—Details, e.g. noise reduction means
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U2101/00—UAVs specially adapted for particular uses or applications
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Feeding And Controlling Fuel (AREA)
Abstract
The invention provides a kind of flame device being applied to unmanned plane, belong to unmanned air vehicle technique field, including: body, is fixed on the fuselage of unmanned plane；Firing device, is fixed on body；Injection equipment, is fixed on body, and is connected with firing device；Wherein, in injection equipment, it is provided with a memory space, is used for storing inflammable substance；And injection equipment is connected with memory space be additionally provided with a combustion zone, make during firing device action, to burst out spark directive combustion zone, with light by memory space flow into combustion zone inflammable substance.The present invention is by being fixed on flame device on the fuselage of unmanned plane so that the position being transported to need flame to remove foreign body in the air by flame device by the flight of unmanned plane carries out flame operation, has convenient and swift and that security performance is high feature.
Description
Technical field
The invention belongs to unmanned air vehicle technique field, particularly to a kind of flame device being applied to unmanned plane.
Background technology
In recent years, the hanging wire foreign body on transmission line wire has become the great threat of electric power netting safe running, at present, runs
Department's warp is frequently with being purged processing under power down mode, but the method is limited by foreign body position, circuit surrounding geographical environment
Relatively big, and power failure processes and also can affect transmission reliability.Peace it is faced with again as used operating personnel to enter electric field equipotential live line work
The unfavorable situation that full blast danger is big, working performance is low.
From on-the-spot hanging wire foreign body statistical number it has been found that most foreign body is that plastic sheeting, kite, ad banner etc. are flammable
Property foreign body, therefore by burning remove foreign body become a kind of convenient, practical method.But, power transmission line is the highest,
When using combustion method to remove foreign body, flame projector distance operator the most farther out, remove to foreign body and make troubles.
Summary of the invention
The technical problem to be solved in the present invention is, removing high-altitude the most faster, effective foreign body.
For solving above-mentioned technical problem, the invention provides a kind of flame device being applied to unmanned plane, described flame fills
Putting and include: body, described body is fixed on the fuselage of described unmanned plane；Firing device, described firing device is fixed on described
On body；Injection equipment, described injection equipment is fixed on described body, and is connected with described firing device；Wherein, described spray
It is provided with a memory space in penetrating mechanism, is used for storing inflammable substance；And in described injection equipment with described memory space phase
Connect is additionally provided with a combustion zone, makes to burst out during described firing device action combustion zone described in spark directive, to light by institute
State memory space and flow into the described inflammable substance of described combustion zone.
Optionally, described firing device includes: ignition system, and described ignition system is fixed on described body, for point
Fire action injection spark；First tank body, described first tank body is fixed on described body, is used for storing combustion gas；Combustion gas bar, described
Combustion gas bar is fixed on described body, and communicates with described first tank body, is used for transmitting described combustion gas；Wherein, described combustion gas bar
Fuel gas injection end corresponding with the spark ejection end position of described ignition system, with by described spark ejection end in described combustion
Gas jet end carries out spark injection.
Optionally, described ignition system includes: ignition switch, and described ignition switch is arranged on the inside of described body；Electricity
Sub-conductor, described electronic wire includes electric connecting terminal and described spark ejection end, and described electric connecting terminal and described ignition switch
Connect.
Optionally, described injection equipment includes: injection system, described injection system be fixed on described internal；Second tank
Body, described second tank body is fixed on described body, is used for storing oil；Spray bar, described spray bar includes fixing end and oil spout
Hold, and described spray bar is fixed on described body by described fixing end；Described spray bar passes through described injection system and institute
State the second tank body to connect, to transmit described oil in described spray bar by described injection system described second tank body of control.
Optionally, described oil spout end is corresponding with the position of described fuel gas injection end.
Optionally, described spray bar, described electronic wire and described combustion gas bar three column distribution, and the injection of described spark
The linking corresponding with described oil spout end three of end, described fuel gas injection end.
Optionally, described injection system includes: power supply source, described power supply source be fixed on described internal；Controller, described
Controller be fixed on described internal；Manostat, described manostat be fixed on described internal, and described power supply source is by described
Manostat is connected with described controller and described firing device respectively, to power described controller and described firing device；Pipe
Way switch, described pipeline switch be fixed on described internal, and described pipeline switch is connected with described controller, and respectively with institute
The described fixing end pipeline stating the second tank body and described spray bar communicates.
Optionally, described fuel gas injection end is provided with several air inlets.
Optionally, also including: keeper, described keeper is fixed on described spark ejection end, and by described keeper
Described electronic wire is flexibly connected with described spray bar.
Optionally, described body is the casing of square structure；And described casing includes: the first side, the second side, the 3rd
Side and the 4th side；Described first side and two opposites that described second side is described casing, described 3rd side
With two opposites that described 4th side is described casing, described first side respectively with described 3rd side and the described 4th
Side adjacent distributions；Wherein, described power supply source, described controller, described manostat, described pipeline switch and described ignition switch
It is placed in described casing；Described fuselage is fixed on described first side, and described first tank body is fixed on described second side
On, described second tank body is fixed on described 3rd side, and described spray bar is fixed on described 4th side by described fixing end
On.
Beneficial effect:
A kind of flame device being applied to unmanned plane that the present invention provides, is fixed on the fuselage of unmanned plane by a body
On so that the position being transported to need flame to remove foreign body in the air by described flame device by the flight of unmanned plane carries out flame work
Industry, has convenient and swift and that security performance is high feature, solves in prior art when being hung with on power transmission line contour empty body
During foreign body, owing to suspension height is higher, when using combustion method to remove foreign body, flame projector distance operator are farther out, to foreign body
Removing brings unhandy technological deficiency.
Accompanying drawing explanation
In order to be illustrated more clearly that the embodiment of the present invention or technical scheme of the prior art, below will be to institute in embodiment
The accompanying drawing used is needed to be briefly described, it should be apparent that, the accompanying drawing in describing below is only some enforcements of the present invention
Example, for those of ordinary skill in the art, on the premise of not paying creative work, it is also possible to obtains according to these accompanying drawings
Obtain other accompanying drawing.
The unmanned plane overall structure schematic diagram being provided with flame device that Fig. 1 provides for the embodiment of the present invention；
The overall structure schematic diagram of the flame device that Fig. 2 provides for the embodiment of the present invention；
Fig. 3 is the overall structure side view of the flame device shown in Fig. 2；
Fig. 4 be in the flame device shown in Fig. 2 injection system and ignition system at intrinsic connection block diagram；
Fig. 5 props up the structural representation of rotary part in support component for what the embodiment of the present invention provided；
Fig. 6 props up the structural representation of positioning element in support component for what the embodiment of the present invention provided；
Fig. 7 is the overall structure schematic diagram of the fast removable member shown in Fig. 1；
Fig. 8 is the overall structure front view of fast removable member in Fig. 7；
Fig. 9 is that in the fast removable member shown in Fig. 1, the first location plunger is in the sectional view under contraction state；
Figure 10 is the overall structure schematic diagram that in the fast removable member shown in Fig. 1, the first location plunger is under contraction state；
Figure 11 is that in the fast removable member shown in Fig. 1, the first location plunger is in the sectional view under raised position；
Figure 12 is the overall structure schematic diagram that in the fast removable member shown in Fig. 1, the first location plunger is under raised position.
Detailed description of the invention
Embodiments provide a kind of flame device being applied to unmanned plane, be fixed on unmanned plane by a body
On fuselage so that the position being transported to need flame to remove foreign body in the air by described flame device by the flight of unmanned plane is sprayed
Fire operation, has convenient and swift and that security performance is high feature, solves in prior art when outstanding on power transmission line contour empty body
When hanging with foreign body, owing to suspension height is higher, when using combustion method to remove foreign body, flame projector distance operator farther out, give
Foreign body is removed and is brought unhandy technological deficiency.
Below in conjunction with the accompanying drawing in the embodiment of the present invention, the technical scheme in the embodiment of the present invention is carried out clear, complete
Describe, it is clear that described embodiment is only a part of embodiment of the present invention rather than whole embodiments wholely.Based on
Embodiment in the present invention, the every other embodiment that those of ordinary skill in the art are obtained, broadly fall into present invention protection
Scope；Wherein involved in this enforcement "and/or" key word, represent and or two kinds of situations, in other words, the present invention implements
A and/or B mentioned by example, illustrates A and B, two kinds of situations of A or B, describes three kinds of states existing for A Yu B, such as A and/or
B, represents: only include A and do not include B；Only include B and do not include A；Including A and B.
Meanwhile, in the embodiment of the present invention, when assembly is referred to as " being fixed on " another assembly, and it can be directly at another
On assembly or assembly placed in the middle can also be there is.When an assembly is considered as " connection " another assembly, and it can be direct
It is connected to another assembly or may be simultaneously present assembly placed in the middle.When an assembly is considered as " being arranged at " another group
Part, it can be to be set directly on another assembly or may be simultaneously present assembly placed in the middle.The embodiment of the present invention is made
Term " vertical ", " level ", "left", "right" and similar statement be merely for purposes of illustration, be not intended to
Limit the present invention.
Flame device in order to provide invention elaborates, to support the technical problem to be solved, under
Face, in the embodiment that the present invention provides, first elaborates to the overall structure of the unmanned plane being provided with flame device, then
During narration unmanned plane, draw the flame device that the present invention provides the most targetedly, to reach complete, clear
Chu, clear purpose.
Refer to Fig. 1, the unmanned plane that the embodiment of the present invention provides, at least include: fuselage 1, fast removable member 5 and institute of the present invention
The flame device 2 stated.
Wherein, described flame device 2 for flame, and by described fast removable member 5 detachable be fixed on described machine
On body 1, as it is shown in figure 1, flame device 2 is securable to the bottom of described fuselage 1, and it is positioned at the position, underface of described fuselage 1
Place, with this make flame device 2 and the undercarriage of unmanned plane or bracing frame at the bottom reasonable layout of fuselage 1, to maximize
The bottom space of Appropriate application fuselage 1.Certainly, as shown in Figure 1, unmanned flight's equipment choosing in the embodiment of the present invention
It is eight rotor wing unmanned aerial vehicles, but not represents that the flame device 2 that the embodiment of the present invention is provided is only used for eight rotor wing unmanned aerial vehicles.Change sentence
Talk about, flame device 2 that the embodiment of the present invention is provided it can also be used to four rotor wing unmanned aerial vehicles, six rotor wing unmanned aerial vehicles, fixed-wing without
Man-machine, depopulated helicopter etc., as long as can enter by the position that flame device 2 is transported to need flame to remove foreign body in the air by flight
The flight equipment of row flame operation, is all applicable to the present invention.
For flame device 2,
Referring to Fig. 2-4, described flame device 2 at least includes: body 21, firing device and injection equipment.Wherein, described
Body 21 is fixed on described fuselage 1 by described Quick-dismantle component 5.Described firing device is fixed on described body 21.Described
Injection equipment is fixed on described body 21, and is connected with described firing device.And it is provided with a storage in described injection equipment
Space, is used for storing inflammable substance.Be connected with described memory space in described injection equipment is additionally provided with a combustion zone,
Make to burst out during described firing device action combustion zone described in spark directive, flowed into described combustion zone to light by described memory space
Described inflammable substance；Described inflammable substance includes the one in following substances: imflammable gas is (such as hydrogen, helium
Deng), flammable liquid (such as gasoline) or flammable gas-liquid mixture (such as liquefied gas).
Specifically, described body 21 can be the casing of the structure that is square, and is mainly in embodiments of the present invention
The installation of fast removable member 5, firing device and injection equipment provides fixing base, and the inside of this casing is hollow-core construction.Described
Casing includes side, 6, top to bottom, left and right, front and rear, and surface therein is: the first side, the second side, the 3rd side and
Four sides.First side and described second side described in these four sides are two opposites up and down of described casing, described
3rd side and two, the left and right opposite that described 4th side is described casing, and described first side is respectively with the described 3rd
Side and described 4th side adjacent distributions.Wherein, described fast removable member 5 is fixed on described first side.Described ignitor
Structure and described injection equipment are fixed on other three sides of described casing.
Further, described firing device includes: ignition system the 221, first tank body 222 and combustion gas bar 223.Wherein, institute
State ignition system 221 to be fixed on described body 21, spray spark for firing action.Described first tank body 222 is fixed on institute
State on the second side of body 21, be used for storing combustion gas.The 4th side on described body 21 is fixed in one end of described combustion gas bar
Face, and communicate with described first tank body, it is used for transmitting described combustion gas.And the other end of described combustion gas bar 223 is as fuel gas injection
End 2231 is corresponding with the spark ejection end 2212a position of described ignition system 221, i.e. makes fuel gas injection end 2231 be sprayed
Combustion gas out, reaches exactly at spark ejection end 2212a of described ignition system 221, with by described spark ejection end
2212 sparks sprayed light the combustion gas that described fuel gas injection end 2231 is ejected.
Wherein, described ignition system 221 may include that ignition switch 2211 and electronic wire 2212.Described ignition switch
2211 inside being arranged on described body 21.Described electronic wire 2212 includes electric connecting terminal and above-mentioned spark ejection end 2212a,
Namely electric connecting terminal and spark ejection end 2212a are as the two ends of electronic wire 2212, and electricity described in described electronic wire 2212
Connect end to be connected with described ignition switch 2211.Herein ignition switch 2211, spark ejection end 2212a of electronic wire 2212 and
Ignition principle between the fuel gas injection end 2231 of combustion gas bar 223 is it can be understood as lighter or the igniting of household gas cooker
Principle, its operation principle thinks prior art, and here is omitted.But it is applied in the embodiment of the present invention, logical to realize
Cross unmanned flight's equipment and aloft the position needing flame to remove foreign body is carried out the innovation place that flame operation is the present invention, herein
First offer some clarification.
The described injection equipment provided for the embodiment of the present invention, at least may include that injection system the 231, second tank
Body 232 and spray bar 233.Wherein, in described injection system 231 is fixed on described body 21.Described second tank body 231 can be managed
Solve as being the memory space described in above-mentioned flame device 2, be fixed on the 3rd side of described body 21, be used for storing oil.Institute
State spray bar 233 and include fixing end 2331 and oil spout end 2332, and described spray bar 233 is fixed on by described fixing end 2331
On described body 21；Described spray bar 233 is connected with described second tank body 232 by described injection system 231, with by described
Injection system 231 controls described second tank body 232 and transmits described oil in described spray bar 233.And the spray of described spray bar 233
Oil end 2332 is corresponding with the position of the fuel gas injection end 2231 of described combustion gas bar 223.That is, make oil spout end 2332 be sprayed
Oil out, reaches exactly at the fuel gas injection end 2231 that described spark ejection end 2212a is lighted, with the combustion by lighting
Gas jet end 2231 lights the oil that described oil spout end 2332 is ejected further.It should be noted that institute in the process
State spray bar 233, described electronic wire 2212 and described combustion gas bar 223 three column distribution, to reach described spark ejection end
The technique effect of 2212a, described fuel gas injection end 2231 and the described corresponding linking of oil spout end 2332 three.
Certainly, during actual job, so that the imflammable gas that fuel gas injection end 2231 is ejected (as
Hydrogen, helium etc.) effectively can be combined with air and then burn, as preferably, the embodiment of the present invention is at described fuel gas injection
Hold and at 2231, be additionally provided with several air inlets 2231a.So make when the imflammable gas in described fuel gas injection end 2231
After ejection, due to the temporary reduction of its air pressure inside, the air (having carrier of oxygen) around fuel gas injection end 2231 is outside then
Entered in fuel gas injection end 2231 by air inlet 2231a under the effect of boundary's atmospheric pressure, be sufficiently mixed with imflammable gas and then quilt
Ejection is lighted.
In order to effectively, easily by injection system 231 control the second tank body 232 in described spray bar 233
Input described oil, and then realize arriving, by spray bar 233, the gas injection that the oil of described oil spout end 2332 can be ignited
Penetrate end 2231 to be ignited.As preferably, described injection system 231 at least includes: power supply source 2311, controller 2312, manostat
2313, pipeline switch 2314.Wherein, in described power supply source 2311 is fixed on the casing of described body 21.Described controller 2313
It is fixed in the casing of described body 21.Described manostat 2313 is fixed in the casing of described body 21, and described power supply source
2311 are connected with described controller 2312 and described firing device (ignition switch 2211) respectively by described manostat 2313, with
Each parts in described controller 2312 and described firing device are powered in real time.Meanwhile, described pipeline switch 2314 is solid
In the casing of described body 21, and described pipeline switch 2314 is connected with described controller 2312, and respectively with described
Described fixing end 2332 pipeline of two tank bodies 232 and described spray bar 233 communicates.Thus so that work as and need by second
When tank body 232 transmits oil in spray bar 233, control described pipeline switch 2314 for opening shape now by controller 2312
State, and then form the channel status between described second tank body 232 and described spray bar 233, it is achieved oil transmission.And when needing
During oil spout to be stopped, the most only needing controller 2312 to control described pipeline switch 2314 for closed mode, cut off described the with this
Channel status between two tank bodies 232 and described spray bar 233.
Certainly, for the controller 2312 described in the embodiment of the present invention, it is also possible to control with the flight within unmanned plane
System connects, and by the information communication between flight control system and earth station, it is achieved ground handling operator is to controller
The long-range control of 2312, transmits for the instruction between the flight control system within unmanned plane and earth station and controls to be existing
Technology, the most just repeats no more.It is emphasized that the embodiment of the present invention also can be at ignition system 221, with injection system 231
Identical, it is possible to set up one group for can only the device of Based Intelligent Control ignition switch igniting, can include a control single chip computer and
One valve, described control single chip computer is connected with described ignition switch 2211 and described controller 2312 respectively, and described valve is arranged
Between described combustion gas bar 223 and described first tank body 222, and it is connected with described control single chip computer.Same, the behaviour of earth station
Make personnel to transmit by carrying out instruction with the flight control system within unmanned plane, and then remotely control described controller 2312,
And send control instruction by described controller to described control single chip computer, light a fire operation controlling described ignition switch 2211,
And described valve be switched on or off state.It is finally reached the technique effect of long-distance intelligent control.Specifically, needs are worked as
When transmitting combustion gas by the first tank body 222 in combustion gas bar 223, control described valve for opening shape now by control single chip computer
State, and then form the channel status between described first tank body 222 and described combustion gas bar 223, it is achieved the transmission of combustion gas.And when combustion
After the oil drop combustion that described spray bar 233 is sprayed by the flame of gas jet end 2231 ejection, now can pass through described controller
2312 send the instruction of closedown valve to described control single chip computer, and then control described valve pass by described control single chip computer
Close, to cut off the transmission line between described first tank body 222 and described combustion gas bar 223, stop fuel gas injection.
It is noted that control system for controller, control single chip computer, ignition switch, pipeline switch, valve with flight
Signal transmission between system, instruction control to be prior art, i.e. send a control by earth station to described flight control system
System instruction, and by described flight control system by control instruction transmission extremely described controller, with by described controller to institute
The control instruction received makes corresponding response, then control single chip computer, pipeline switch, ignition switch, valve etc. is made operation
Control, think prior art, but its control principle is applied to the flame device 2 described in the embodiment of the present invention, further will spray
Fire device is applied to unmanned flight's equipment, to realize aloft being entered the position needing flame to remove foreign body by unmanned flight's equipment
Row flame operation is the innovation place of the present invention, the most first offers some clarification.
Further, for electronic wire 2212 involved in the ignition system 221 in the embodiment of the present invention, due to
Itself light weight, is easily blown by extraneous wind-force in the flight course of unmanned plane and is swung, then caused electronic wire
Spark ejection end 2212a of 2212 cannot corresponding be connected with the locus of the fuel gas injection end 2231 of combustion gas bar 223, Jin Erying
Ring ignition results.To this, the embodiment of the present invention also has additional positioning piece 3, and described keeper 3 is fixed on described spark ejection end
2212a, and by described keeper 3, described electronic wire 2212 is flexibly connected with described combustion gas bar 223.Activity herein is even
Connect the detachable connection that can be understood as therebetween.Keeper 3 can be diversified, as can be with screw or spiral shell
The collocation of bolt and nut uses, it is also possible to be bearing pin, being applied in combination described spark ejection end 2212a in described combustion of steady pin
Position on gas bar 223, it is also possible to spark ejection end 2212a is wound on combustion gas bar 223 by direct thin wire.Change
Sentence is talked about, as long as stable for spark ejection end 2212a of the electronic wire of lighter weight can be fixed on combustion gas bar 223,
And make the keeper 3 of fuel gas injection end 2231 linking corresponding with the position of spark ejection end 2212a of combustion gas bar 223, then
All within protection scope of the present invention.
You need to add is that, for spray bar 233, in order to avoid spray bar 233 is made owing to quality is relatively light
Become the applied defect as above-mentioned electronic wire 2212, i.e. easily blown by extraneous wind-force in the flight course of unmanned plane
And swing, then cause the oil spout end 2332 of the fuel gas injection end 2231 of combustion gas bar 223 and spray bar 233 on locus not
Can accurately corresponding be connected.Therefore, at the oil spout end 2332 of spray bar 233, it is also possible to be fixed on an above-mentioned keeper, i.e.
By described keeper 3, described electronic wire 2212 is flexibly connected with described spray bar 233.Flexible connection herein can be managed
Solve as being detachable connection therebetween.Keeper 3 is equally diversified, as can with screw or bolt with
The collocation of nut uses, it is also possible to be bearing pin, being applied in combination described oil spout end 2332 on described combustion gas bar 223 of steady pin
Position, it is also possible to oil spout end 2332 is wound on combustion gas bar 223 by direct thin wire.In other words, if energy
Enough by stable being fixed on combustion gas bar 223 of oil spout end 2332 of the spray bar 233 of lighter weight, and make combustion gas bar 223
The keeper 3 of fuel gas injection end 2231 linking corresponding with the position of oil spout end 2332, the most all protection scope of the present invention it
In.
And then, due to combustion gas bar 223 as above-mentioned electronic wire 2212 and/or the load-carrying support bar of spray bar 233,
In order to avoid combustion gas bar 223 occurs bending or even coming off because load-carrying is excessive.As preferably, the embodiment of the present invention also has additional
One support component 4, described support component 4 can include a movable end and a support end, and described support component 4 is by described work
Moved end is rotationally connected with the 4th side of described body 21, and described support component 4 is by described support end and described combustion gas bar 223
Middle part fixing near one end of fuel gas injection end 2231 connect.
Specifically, referring to Fig. 5 and Fig. 6, described support component 4 at least includes: support bar 41, rotary part 42 and fixed
Position parts 43.Wherein, one end of described support bar 41 is rotated by the 4th side of described rotary part 42 with described body 21
Connect.The other end of described support bar is connected by described positioning element 43 is fixing with described combustion gas bar 223.It is to be understood that
What one end of described rotary part 42 and described support bar 41 was constituted is the movable end of an above-mentioned support component 4, described location division
What the other end of part 43 and described support bar 41 was constituted is the support end of an above-mentioned support component 4.
Wherein, described rotary part 42 at least may include that T-shaped sleeve 421 and supports base 422.Described T-shaped sleeve
421 include T-shaped end 4211 and transverse end 4212.Described support base 422 is fixed on the 4th side of described body 21, and institute
State T-shaped sleeve 421 to be rotationally fixed on described support base 422 by described transverse end 4212, so that described T-shaped sleeve
421 is rotatable relative to described support base 422.One end of described support bar 41 is set on described T-shaped end 4211, with by institute
State support bar 41 and the fixing connection of described T-shaped sleeve 421.
Described support base 422 may include that the first pedestal 4221 and the second pedestal 4222.Wherein, described first pedestal
On 4221 the 4th sides being fixed on described body 21, and offer the first circular groove on described first pedestal 4221.Described second
Pedestal 4222 is fixed on the 4th side of described body 21, and offers the second circular groove on described second pedestal 4222.Wherein,
The transverse end 4212 of described T-shaped sleeve 421 can be understood as a hollow cylindrical structure, and the external world of this hollow cylinder with
The internal diameter of described first circular groove and described second circular groove is suitable, thus makes the two ends correspondence respectively of described transverse end 4212
Through described first circular groove and described second circular groove, so that described transverse end 4212 is rotationally fixed to described first pedestal
Between 4221 and described second pedestal 4222.
For the first circular groove and the second circular groove, can be exactly that two independent circular grooves are whole in embodiments of the present invention
Body, i.e. in installation process, directly penetrates one end of transverse end 4212 in described first circular groove, by transverse end 4212 after penetrating
The other end penetrate in described second circular groove, realize transverse end 4212 with this and be rotationally fixed to the first pedestal 4221 and second
On body 4222.Certainly, so that be rotationally connected spirit between transverse end 4212 and the first pedestal 4221 and the second pedestal 4222
Live, detachably.If for the first pedestal 4221 and the second pedestal 4222 moreover, it is also possible to be dismountable dry part assemble and
Become.
Specifically, described first pedestal 4221 at least may include that first semifixed piece of 4221a, second semifixed piece
4221b, and several first fix screw 4221c.Wherein, described first semifixed piece of 4221a is fixed on described body 21
On 4th side, and offer the first half slot on described first semifixed piece of 4221a.On described second semifixed piece of 4221b
Offer the second half slot.And described first semifixed piece of 4221a and described second semifixed piece of 4221b is interlocked, make with this
Obtain described first half slot and described second half slot is connected to constitute described first circular groove；Several described first fix screw
4221c passes described second semifixed piece of 4221b, threadeds with described first semifixed piece of 4221a.
Same, described second pedestal 4222 at least may include that the three semifixed pieces 4222a, the 4th semifixed piece
4222b, and several second fix screw 4222c.Wherein, described the three semifixed pieces 4222a are fixed on described body 21
On 4th side, and offer the 3rd half slot on described the three semifixed pieces 4222a.On described the four semifixed pieces 4222b
Offer the 4th half slot.And described three semifixed pieces of 4222a and described the four semifixed pieces 4222b are interlocked, make with this
Obtain described 3rd half slot and described 4th half slot is connected to constitute described second circular groove；Several described second fix screw
4222c passes described the four semifixed pieces 4222b, threadeds with described the three semifixed pieces 4222a.
Thus so that, install T-shaped sleeve 421 time, first the two ends of transverse end 4212 are put with being corresponding in turn to
Put first half slot of first semifixed piece of 4221a, three semifixed pieces of 4222a the 3rd half slot on, after having placed,
Directly second semifixed piece of 4221b and the four semifixed pieces 4222b is fastened on first semifixed piece of 4221a and the 3rd accordingly
On semifixed piece of 4222a, with this, the first semicircle is wiped and the second half slot forms described first circular groove, the 3rd half slot and the
Four half slots form described second circular groove.The final screw 4221c and second that directly fixes first fixes screw 4222c correspondence and inserts
Enter to lock.Thus achieve T-shaped sleeve 421 and the detachable installation supported between base 422 so that when T-shaped set
Cylinder 421 occurs when abrasion need to substitute, and directly dismounting first is fixed screw 4221c and second and fixed screw 4222c and can complete more
For dismounting.As preferably, second fix screw 4221c and second to fix the quantity of screw 4222c to be respectively 2.
Need exist for it is emphasized that the most why make described T-shaped sleeve by T-shaped sleeve 421
421 and support between base 422 rotatable, it is to realize the angle between support bar 41 and the 4th side of described body 21
Angle adjustable.Because during actual job, need according to job requirements and the sagging angle of combustion gas bar 223, regulate
Support bar 41, relative to the angle of body 21 the 4th side, completes its suspension strut to combustion gas bar 223, to reach to grasp flexibly
The purpose made, has the advantages that simple in construction, applicable performance are wide.
Further, described positioning element 43 at least may include that a location snap ring, and one end of described location snap ring is arranged
The first locating ring, the other end of described location snap ring is had to be provided with the second locating ring；And the other end of described support bar 41 passes
Described first locating ring is fixing with described location snap ring to be connected, and described combustion gas bar 223 is fixed with described through described second locating ring
Position snap ring is fixing to be connected.Described support bar 41 and described combustion gas bar 223 is realized by the first locating ring and the second locating ring with this
Between suspension be located by connecting.
For the first locating ring and the second locating ring, can be exactly in embodiments of the present invention two independent ring-type
Structure, i.e. in installation process, directly penetrates one end of support bar 41 in described first locating ring, and combustion gas bar 223 is directly worn
Enter in the second locating ring, and fix annexation owing to having one between the first locating ring and the second locating ring, then allow for
There is also a suspension fixed relationship between described support bar 41 and described combustion gas bar 223, the suspension finally realizing combustion gas bar 223 is fixed
Position.Certainly, so that between support bar 41 with the first locating ring, combustion gas bar 223 and the second locating ring fixing connection
Flexibly, detachably.For the snap ring of location, it is also possible to if being that dismountable dry part assembles.
Specifically, described location snap ring at least may include that the first half location snap rings 431, the second half location snap rings 432
Screw 433 is fixed with the 3rd.Wherein, one end of described the first half location snap rings 431 is provided with the first half circle groove, and described the first half
The other end of location snap ring 431 is provided with the second half circle groove.One end of described the second half location snap rings 432 is provided with the 3rd semi-ring
Groove, the other end of the described second fixed half location snap ring 432 is provided with the 4th half circle groove.Wherein, described first half circle groove and described
3rd half circle groove correspondence linking constitutes described first locating ring, described second half circle groove linking corresponding with described 4th half circle groove structure
Become described second locating ring；And the described 3rd fix screw through described the first half location snap rings 431 (or described second semidefinite
Position snap ring 432), threaded with described the second half location snap rings 432 (or described the first half location snap ring 431).
Here it is worth noting that constituted described first by the linking corresponding with described 3rd half circle groove of described first half circle groove
The internal diameter of locating ring is less than the external diameter of described support bar 41；The linking corresponding with described 4th half circle groove of described second half circle groove is constituted
The internal diameter of described second locating ring is less than the external diameter of described combustion gas bar 223.This is because during actual installation, the first semidefinite
Position snap ring 431 and the second half location snap rings 432 are disassembly status in advance, now by support bar 41 and/or combustion gas bar 223 correspondence
It is placed on the first half circle groove and the second half circle groove position of the first half location snap rings 431, then fastens the second half location snap rings
432, make described first half circle groove and described 3rd half circle groove be constituted described first locating ring with this, described second half circle groove and
Described 4th half circle groove constitutes described second locating ring.Just because of described first half circle groove rank corresponding with described 3rd half circle groove
Connect the internal diameter constituting described first locating ring less than the external diameter of described support bar 41；Described second half circle groove and described 4th semi-ring
The linking of groove correspondence constitutes the internal diameter of described second locating ring less than the external diameter of described combustion gas bar 223, thus makes by tightening the
Three fix screw 433, can the vertical dimension between the first half location snap rings 431 and the second half location snap rings 432 constantly be reduced,
With this, the two is fixed.Finally realize carrying out support bar 41 and combustion gas bar 223 hanging fixing purpose.
For fast removable member 5,
Referring to Fig. 7-12, wherein, described fast removable member 5 at least includes: fixed plate 51 and positioning element 52.
Wherein, described fixed plate 51 is fixed on described fuselage 1, and is slidably connected with described body 21, so that described
Body 21 slides relative to described fixed plate 51, and owing to fixed plate 51 is fixed relative to fuselage 1, and then realize body 21 phase
Fuselage 1 is slided.Certainly, the fixing connected mode between fixed plate 51 and described fuselage 1 can be diversified,
As being bolt connection, can be screw connection, can be welding, it is also possible to be one-body molded, in this embodiment of the present invention
Do not limit, as long as being capable of fixed plate 51 to be fixed on described fuselage 1.Described positioning element 52 is fixed on described fixing
On plate 51, to position described body 21 relative to the position of described fixed plate 51, and then it is relative to realize described body 21
Install or dismounting in described fuselage.
Here, positioning element 52 is equivalent to screens parts, when body 21 is installed on fuselage 1 by needs, this
A certain position is slid into relative to fixed plate 51, then by positioning element 52 to this position between Shi Benti 21 and fixed plate 51
Body 21 position, to prevent body 21 from sliding relative to fixed plate 51.And when body 21 pulled down by needs, the most only need
Manual toggle positioning element 52, it is allowed to body 21 skids off relative to fixed plate 51, can realize body 21 quick, tear open flexibly
Unload.During this, the installation and removal of body 21 are without by any extraneous utensil such as spanner etc., easy to operate, have quickly,
Feature easily.
In embodiments of the present invention, as preferably, please continue to refer to Fig. 7-8, described fixed plate 42 can be that cross section is U-shaped
Shape, the described fixed plate 42 under this shape at least may include that the first side plate 511；Second side plate 512 and transverse slat 513.
Wherein, described first side plate 511 and described second side plate 512 are parallel；And described first side plate 511 and described
Two side plates 512 are perpendicular with described transverse slat 513, and described transverse slat 513 respectively with described first side plate 511 and described second side plate
512 are slidably connected, and described body 21 is fixing with described transverse slat 513 to be connected, and then makes described body 21 by described transverse slat 513
Slide relative to described first side plate 511 and described second side plate 512.Meanwhile, described positioning element 41 is individually fixed in
On described first side plate 511 and described second side plate 512, with to described transverse slat 513 relative to described first side plate 511 and described
The position of the second side plate 512 positions.Certainly, described first side plate 511, between described second side plate 512 and described fuselage 1
Fixing connected mode can be diversified, as can be bolt connect, can be screw connect, can be welding, also
Can be one-body molded, not limit in this embodiment of the present invention, if be capable of described first side plate 511, described second
Side plate 512 is fixed on described fuselage 1.
Same principle, the fixing connected mode between described body 21 and described transverse slat 513 can also be varied
, as being bolt connection, can be screw connection, can be welding, it is also possible to be one-body molded, implement in this present invention
Example does not limits, and is relatively fixed with described transverse slat 513 as long as being capable of described body 21, all protection scope of the present invention it
In.
Further, for ease of being fixed with the transverse slat 513 of body 21, it is possible to and the spirit of first side plate the 511, second side plate 512
Live, quickly slide, in order to body 21 flexibly, is quickly installed or dismounting.A kind of enforcement as the embodiment of the present invention
It is respectively arranged with a chute, to be arranged on by described transverse slat 513 on mode, described first side plate 511 and described second side plate 512
In described chute so that described transverse slat 513 passes through described chute relative to described first side plate 511 and described second side plate 512
Slide.
Meanwhile, one end of described positioning element 52 corresponding through described first side plate 511, described second side plate 512, and
In described chute internal projection or contraction so that one end of described positioning element 52 relative to described chute at described chute convex
When rising, one end of described positioning element 52 stops that described transverse slat 513 slides in described chute, described positioning element 52
One end is relative to described chute when described chute contract, and one end of described positioning element 52 is separated with described transverse slat 513,
So that described transverse slat 513 slides in described chute.
Needing exist for explanation, in embodiments of the present invention, described " protruding " is it can be understood as be parts
Slipping in some parts, " contraction " can be understood as parts and skid off some parts.Such as, described above described
One end of positioning element 52 when described chute internal projection, i.e. refers to that one end of described positioning element 52 is slipped into relative to described chute
In described chute, one end of positioning element 52 described above when described chute contract, i.e. refers to described relative to described chute
One end of positioning element 52 skids off described chute.The body 21 dismounting relative to fuselage 1 is realized by positioning element 52 with this
Or install.
For described positioning element 52, in embodiments of the present invention, as a kind of implementation of the present embodiment, institute
State positioning element 52 can at least include: the first location plunger and described second location plunger.And described first location plunger bag
Include the first positioning end；Described second location plunger includes the second positioning end.
Wherein, described first positioning end corresponding through described first side plate, and the chute in described first side plate 511
Internal projection or contraction, so that described first positioning end is when relative to chute internal projection in described first side plate 511, described
First positioning end stops that described transverse slat 513 slides in chute, and described first positioning end is relative to described first side plate
During chute contract in 511, described first positioning end is separated, so that described transverse slat 513 is in chute with described transverse slat 513
Slide.Wherein, described second positioning end corresponding through described second side plate 512, and in described second side plate 512
Chute internal projection or contraction, so that described second positioning end is when relative to chute internal projection in described second side plate 512,
Described second positioning end stops that described transverse slat 513 slides in chute, and described second positioning end is relative to described second
During chute contract in side plate 512, described second positioning end is separated with described transverse slat, so that described transverse slat 513 is at chute
Inside slide.
Here, can be it can be understood as the first side plate 511 and the second side plate 512 symmetry as shown in Fig. 7 or Fig. 8
It is distributed in the both sides of described transverse slat 513, while thus making the both sides correspondence of described transverse slat 513, inserts described first side plate
511 and the chute offered of described second side plate 512 in, realize being fixed with the transverse slat 513 of body 21 relative to first with this
Side plate 511 and the second side plate 512 slide.Meanwhile, in order to preferably the transverse slat 513 in sliding process be positioned.This
Inventive embodiments is by the first location plunger and the second location plunger, the both sides at transverse slat 513 of symmetrical setting, namely first
Location plunger and the first side plate 511 are corresponding, and the second location plunger and the second side plate 512 are corresponding.It should be noted that at this
In inventive embodiments, the first side plate 511 and the structure of the second side plate 512 can identical can also be different, the first locating dowel
Plug and second location plunger can identical can also difference.And in embodiments of the present invention, for convenience of description, selected
First side plate 511 is identical with the second side plate 512 structure, the first location plunger and the complete phase of structure of the second location plunger
With.
Certainly, it will be understood by those skilled in the art that the first side plate 511 and the second side plate 512, first position plunger and the
Two location plungers can also be mutually different various structures, if the first side plate 511 can be square structure, and the second side plate
512 can be rectangle structure, or the first side plate 511 can be trapezium structure, the second side plate 512 can be square or
The polygonized structure such as rectangle or rhombus.In other words, as long as be capable of the first side plate 511 and the second side plate 512 with
Fuselage 1 is relatively fixed, and transverse slat 513 can first side plate 511 that slide relative with the first side plate 511 and the second side plate 512 and
Second side plate 512 structure, all within protection scope of the present invention.Same, the first location plunger and the second location plunger are also
Can be multiple different structure, if disclosure satisfy that the first location plunger can be corresponding through the first side plate 511, second is fixed
Position plunger can be corresponding through carrying out projection or flexible, with to horizontal stroke in the second side plate 512, and the chute of each its correspondence of leisure
Plate 513 carries out spacing to the greatest extent may be used.The planform being placed in the first location plunger and the second location plunger is the most identical, the present invention
Embodiment does not do restriction further.
Please continue to refer to Fig. 9-12, as stated above, as a kind of embodiment of the embodiment of the present invention, it is assumed that at this
The first location plunger selected in inventive embodiments and the second location plunger are completely identical in structure, shown in Fig. 9-12
As a example by first location plunger 521, the internal structure of location plunger is described in further detail.
Such as Fig. 9-12, described first location plunger 521 includes: first bolt the 5211, first positioning thread insert 5212, the
One location spring 5213.
Wherein, described first bolt 5211 is provided with described first positioning end 5211a；Described first positioning thread insert
5212 are set on described first bolt 5211, and described first positioning thread insert 5212 and described first bolt 5211
Between be provided with one first compression stroke 5214.Can be understood as the most described first positioning thread insert 5212
Internal diameter, more than the external diameter of described first bolt 5211, thus makes the first positioning thread insert 5212 be set in described first fixed
Time on the bolt 5211 of position, there is therebetween neutral region, this neutral region is above-mentioned first compression stroke 5214.Described
First location spring is arranged in described first compression stroke 5214；Wherein, described first positioning end 5211a sequentially passes through described
First location spring 5213, described first compression stroke 5214 and described first side plate 511, with in described first side plate 511
Chute internal projection or contraction.
It is noted that shown in Fig. 9-10 be first positioning end 5211a chute in described first side plate 511 in
Schematic diagram during contraction state.Shown in Figure 11-12 be first positioning end 5211a chute in described first side plate 511 in
Schematic diagram during raised position.And in order to preferably by the first location spring 5213 the most now at the first compression stroke
In 5214, on the described first positioning end 5211a of the first bolt 5211 described in the embodiment of the present invention, it is provided with one first
Card convex 5215, to be fully defined in described first compression stroke 5214 by described first location spring 5213, and makes described
First positioning end 5211a, when relative to chute contract in described first side plate 511, is pressed by described first card convex 5215
Contract described first location spring 5213.
Specifically, the embodiment of the present invention is during actual job, and the first location spring 5213 is at the first compression stroke
In 5214, whole process is in compression or its pre-compressed state, thus makes in its natural state, and the first location spring 5213 is the
Described first positioning end 5211a is promoted to be entered institute by the first side plate 511 by the elasticity tension of self in one compression stroke 5214
State in the chute of the first side plate 511, and then the transverse slat 513 in being in chute is positioned.And when needing transverse slat 513 from cunning
When groove skids off, namely when needing to dismantle body 21 from fuselage 1, now have only to manual toggle the first bolt
5211 so that the first positioning end 5211a compresses the first location spring 5213 by the first card convex 5215, then makes the first location
End 5211a skids off in the chute of the first side plate 511, and then realizes skidding off relative to the first side plate 511 of transverse slat 513.And work as
Without External Force Acting after the first bolt 5211, under the elasticity tension effect of the first location spring 5213, continue to press on the
One positioning end 5211a carries out return, namely the duty of the first location plunger 521 shown in Figure 11 or Figure 11.Effectively
Achieve the installation and removal of body 21 without by any extraneous utensil such as spanner etc., easy to operate, have quickly, easily
Feature.
In embodiments of the present invention, described second location plunger includes: the second bolt, described second bolt sets
It is equipped with described second positioning end；Second positioning thread insert, described second positioning thread insert is set on described second bolt, and institute
State and between the second positioning thread insert and described second bolt, be provided with one second compression stroke；Second location spring, described the
Two location springs are arranged in described second compression stroke；Wherein, described second positioning end sequentially passes through described second location bullet
Spring, described second compression stroke and described second side plate, with the chute internal projection in described second side plate or contraction.Described
On described second positioning end of the second bolt, it is provided with one second card convex, so that described second location spring is limited to institute
State in the second compression stroke, and make described second positioning end when relative to chute contract in described second side plate, logical
Cross the described second location spring of described second card convex compression.
As it has been described above, the second location plunger in the embodiment of the present invention and the first location plunger 521 shown in Fig. 9-12
Structure is identical, the most no longer repeats the internal structure of the second location plunger, for the inside of the second location plunger
The non-detailed portion of structure, see the detailed portion of the first location plunger 521 in the embodiment of the present invention.
In sum, a kind of flame device being applied to unmanned plane that the present invention provides, flown at nobody by fast removable member
On the row equipment such as fuselage of unmanned plane, detachable fixes a flame device so that during actual job, pass through unmanned plane
Flight position that flame device is transported to need in the air flame remove foreign body carry out flame operation, there is convenient and swift and peace
The feature that full performance is high, solves in prior art when being hung with foreign body on power transmission line contour empty body, due to suspension height
Higher, when using combustion method to remove foreign body, flame projector distance operator are farther out, bring unhandy to foreign body removing
Technological deficiency.
Although preferred embodiments of the present invention have been described, but those skilled in the art once know basic creation
Property concept, then can make other change and amendment to these embodiments.So, claims are intended to be construed to include excellent
Select embodiment and fall into all changes and the amendment of the scope of the invention.
Obviously, those skilled in the art can carry out various change and the modification essence without deviating from the present invention to the present invention
God and scope.So, if these amendments of the present invention and modification belong to the scope of the claims in the present invention and equivalent technologies thereof
Within, then the present invention is also intended to comprise these change and modification.
Claims (10)
1. the flame device being applied to unmanned plane, it is characterised in that described flame device includes:
Body, described body is fixed on the fuselage of described unmanned plane；
Firing device, described firing device is fixed on described body；
Injection equipment, described injection equipment is fixed on described body, and is connected with described firing device；
Wherein, in described injection equipment, it is provided with a memory space, is used for storing inflammable substance；And in described injection equipment with
What described memory space was connected is additionally provided with a combustion zone, makes to burst out during described firing device action and burns described in spark directive
District, to light the described inflammable substance being flowed into described combustion zone by described memory space.
It is applied to the flame device of unmanned plane the most as claimed in claim 1, it is characterised in that described firing device includes:
Ignition system, described ignition system is fixed on described body, sprays spark for firing action；
First tank body, described first tank body is fixed on described body, is used for storing combustion gas；
Combustion gas bar, described combustion gas bar is fixed on described body, and communicates with described first tank body, is used for transmitting described combustion gas；
Wherein, the fuel gas injection end of described combustion gas bar is corresponding, to pass through with the spark ejection end position of described ignition system
State spark ejection end and carry out spark injection at described fuel gas injection end.
It is applied to the flame device of unmanned plane the most as claimed in claim 2, it is characterised in that described ignition system includes:
Ignition switch, described ignition switch is arranged on the inside of described body；
Electronic wire, described electronic wire includes electric connecting terminal and described spark ejection end, and described electric connecting terminal and described point
Fire switch connects.
It is applied to the flame device of unmanned plane the most as claimed in claim 3, it is characterised in that described injection equipment includes:
Injection system, described injection system be fixed on described internal；
Second tank body, described second tank body is fixed on described body, is used for storing oil；
Spray bar, described spray bar includes fixing end and oil spout end, and described spray bar is fixed on described by described fixing end
On body；Described spray bar is connected with described second tank body by described injection system, to control institute by described injection system
State the second tank body in described spray bar, transmit described oil.
It is applied to the flame device of unmanned plane the most as claimed in claim 4, it is characterised in that:
Described oil spout end is corresponding with the position of described fuel gas injection end.
6. the flame device being applied to unmanned plane as described in claim 4 or 5, it is characterised in that:
Described spray bar, described electronic wire and described combustion gas bar three column distribution, and described spark ejection end, described combustion gas
Ejection end linking corresponding with described oil spout end three.
It is applied to the flame device of unmanned plane the most as claimed in claim 4, it is characterised in that described injection system includes:
Power supply source, described power supply source be fixed on described internal；
Controller, described controller be fixed on described internal；
Manostat, described manostat be fixed on described internal, and described power supply source by described manostat respectively with described control
Device processed and described firing device connect, to power described controller and described firing device；
Pipeline switch, described pipeline switch be fixed on described internal, and described pipeline switch is connected with described controller, and point
Do not communicate with the described fixing end pipeline of described second tank body and described spray bar.
It is applied to the flame device of unmanned plane the most as claimed in claim 2, it is characterised in that
Described fuel gas injection end is provided with several air inlets.
9. the flame device being applied to unmanned plane as described in claim 4 or 5, it is characterised in that also include:
Keeper, described keeper is fixed on described spark ejection end, and by described keeper by described electronic wire and institute
State spray bar to be flexibly connected.
It is applied to the flame device of unmanned plane the most as claimed in claim 7, it is characterised in that described body is square structure
Casing；And
Described casing includes: the first side, the second side, the 3rd side and the 4th side；Described first side and described second
Side is two opposites of described casing, described 3rd side and two opposites that described 4th side is described casing,
Described first side respectively with described 3rd side and described 4th side adjacent distributions；
Wherein, described power supply source, described controller, described manostat, described pipeline switch and described ignition switch are placed in institute
State in casing；Described fuselage is fixed on described first side, and described first tank body is fixed on described second side, and described
Two tank bodies are fixed on described 3rd side, and described spray bar is fixed on described 4th side by described fixing end.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610727329.7A CN106152123B (en) | 2016-08-25 | 2016-08-25 | Flame device applied to unmanned plane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610727329.7A CN106152123B (en) | 2016-08-25 | 2016-08-25 | Flame device applied to unmanned plane |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106152123A true CN106152123A (en) | 2016-11-23 |
| CN106152123B CN106152123B (en) | 2018-12-18 |
Family
ID=57342044
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610727329.7A Expired - Fee Related CN106152123B (en) | 2016-08-25 | 2016-08-25 | Flame device applied to unmanned plane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106152123B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108488798A (en) * | 2018-04-25 | 2018-09-04 | 厦门南羽科技有限公司 | Flaming system and unmanned plane |
| CN115739848A (en) * | 2022-11-28 | 2023-03-07 | 国网黑龙江省电力有限公司超高压公司 | Unmanned aerial vehicle-mounted high-voltage transmission line obstacle clearing device and obstacle clearing method |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20150246727A1 (en) * | 2014-02-28 | 2015-09-03 | Siemens Industry, Inc. | Apparatus for servicing a detector of a fire safety system |
| CN105314111A (en) * | 2014-06-27 | 2016-02-10 | 周彦辉 | Large-size high-speed invisible flying saucer |
| CN205489261U (en) * | 2016-01-13 | 2016-08-17 | 昆山市工业技术研究院有限责任公司 | High altitude flame projecting robot that removes obstacles |
| CN206001457U (en) * | 2016-08-25 | 2017-03-08 | 易瓦特科技股份公司 | It is applied to the flame device of unmanned plane |
| CN206250675U (en) * | 2016-12-20 | 2017-06-13 | 北方天途无人机科技成都有限公司 | Flame is removed obstacles unmanned plane |
-
2016
- 2016-08-25 CN CN201610727329.7A patent/CN106152123B/en not_active Expired - Fee Related
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20150246727A1 (en) * | 2014-02-28 | 2015-09-03 | Siemens Industry, Inc. | Apparatus for servicing a detector of a fire safety system |
| CN105314111A (en) * | 2014-06-27 | 2016-02-10 | 周彦辉 | Large-size high-speed invisible flying saucer |
| CN205489261U (en) * | 2016-01-13 | 2016-08-17 | 昆山市工业技术研究院有限责任公司 | High altitude flame projecting robot that removes obstacles |
| CN206001457U (en) * | 2016-08-25 | 2017-03-08 | 易瓦特科技股份公司 | It is applied to the flame device of unmanned plane |
| CN206250675U (en) * | 2016-12-20 | 2017-06-13 | 北方天途无人机科技成都有限公司 | Flame is removed obstacles unmanned plane |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108488798A (en) * | 2018-04-25 | 2018-09-04 | 厦门南羽科技有限公司 | Flaming system and unmanned plane |
| CN115739848A (en) * | 2022-11-28 | 2023-03-07 | 国网黑龙江省电力有限公司超高压公司 | Unmanned aerial vehicle-mounted high-voltage transmission line obstacle clearing device and obstacle clearing method |
| CN115739848B (en) * | 2022-11-28 | 2024-01-12 | 国网黑龙江省电力有限公司超高压公司 | Unmanned aerial vehicle-mounted high-voltage transmission line obstacle remover and obstacle removing method |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106152123B (en) | 2018-12-18 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106253135A (en) | Flame type unmanned flight's equipment | |
| CN205998135U (en) | It is applied to the injection equipment of flame device | |
| CN102901098B (en) | Ground flare multi-head high-efficiency premixed type combustion system | |
| CN106152123A (en) | It is applied to the flame device of unmanned plane | |
| CN106196046A (en) | There is the flame equipment of a support component | |
| CN206001457U (en) | It is applied to the flame device of unmanned plane | |
| CN206001458U (en) | Flame equipment with support component | |
| CN206004217U (en) | Flame type unmanned flight's equipment | |
| CN108151062B (en) | A kind of engine supersonic speed combustion chamber based on embedded central plasma torch | |
| CN109167296A (en) | High-voltage line based on unmanned plane, which floats, hangs object intelligence obstacle eliminating system and method for removing obstacles | |
| CN206001459U (en) | It is applied to the rotary part of support component | |
| CN206001487U (en) | It is applied to the firing device of flame device | |
| CN206001208U (en) | It is applied to the positioning element of support component | |
| CN206001981U (en) | It is applied to the support component of flame device | |
| CN109654535B (en) | Two-way oil supply structure of stabilizer for sub-combustion stamping engine | |
| CN205821912U (en) | Glued joint clamping plate sulfuration demountor | |
| US20150345783A1 (en) | Vertically Arranged Well Test Burner System | |
| CN206488274U (en) | Double wind matching type torch ignitors | |
| CN202792102U (en) | Ignition electric control device of well mouth of oil and gas field and ignition system with the same | |
| RU2554684C1 (en) | Universal flare facility | |
| CN205139104U (en) | Long -range automatic ignition system of oil bath fire combustion experiment | |
| CN208091322U (en) | The fire in a stove before fuel is added assembles device | |
| CN208332325U (en) | Igniter for the website that recovers the oil | |
| CN207450285U (en) | For the fixed-wing unmanned aerial vehicle ejecting system of flight controlled training | |
| CN208036616U (en) | A kind of UAV system flame device |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| 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: 20181218 Termination date: 20210825 |