CN206813323U - A kind of fire-fighting unmanned plane with hydraulic shock-absorption gun tube - Google Patents
A kind of fire-fighting unmanned plane with hydraulic shock-absorption gun tube Download PDFInfo
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- CN206813323U CN206813323U CN201720296945.1U CN201720296945U CN206813323U CN 206813323 U CN206813323 U CN 206813323U CN 201720296945 U CN201720296945 U CN 201720296945U CN 206813323 U CN206813323 U CN 206813323U
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Abstract
It the utility model is related to a kind of fire-fighting unmanned plane with hydraulic shock-absorption gun tube, including aviation mechanism and control cabinet, control cabinet is arranged on aviation mechanism, and aviation mechanism parallel beneath is provided with multiple fire monitors, and fire monitor is fixed on below aviation mechanism by monitor body fixture；Fire monitor includes gun barrel and gun tube, and gun barrel is set in outside gun tube；Internal diameter is more than both ends internal diameter in the middle part of gun barrel, and the first spring and second spring are provided with the middle part of gun barrel；A lug boss is provided with the middle part of gun tube outer surface, lug boss is arranged between the first spring and second spring；Gun barrel bottom is provided with a piston, and piston is fixedly connected with the connecting rod of gun tube underrun one, and at least one through hole is provided with piston；Piston is provided with a dividing plate between gun tube, and connecting rod passes through the dividing plate, and dividing plate forms a confined space with gun barrel bottom；Liquid is injected with confined space；The utility model reduces fire monitor recoil by hydraulic shock-absorption, coordinates spring, can be further ensured that unmanned plane smooth flight.
Description
Technical field
The utility model belongs to unmanned plane fire-fighting domain, and in particular to a kind of fire-fighting with hydraulic shock-absorption gun tube nobody
Machine.
Background technology
Now in society, as urbanization promotes, high building construction speed is accelerated, but tackles the equipment development phase of tall-building fire fighting
To hysteresis, meanwhile, with developing rapidly for chemical industry, all kinds of easily blasts are not suitable for the mankind and are in close to the fire-fighting event of processing
Ascendant trend.This year, firefighterses cause to hinder because closely handling explosive case during tall-building fire fighting equipment hysteresis, fire-fighting
The number of dying is on the increase, and the problem in this fire-fighting is not resolved always.Current means of fire, it is to use aerial ladder fire-fighting mostly
Car solves the problems, such as tall-building fire fighting, and the effective operation of common hook and ladder is highly 30-50 rice, then high reachable 60-70
Rice.But fire fighting truck is generally spent limitation by street, it is difficult to passed through in narrow street, usually because volume is larger in responding fire-fighting
Scene of fire can not be rushed in the very first time, cause fire further to deteriorate.
Fire once occurs for skyscraper, has one to be significantly characterized in " stack effect ", i.e.,：In the fire that bottom occurs
The hot-air of formation, because density is told somebody what one's real intentions are, flowed on the net through lift trough or stair passage, just as in a huge chimney
Air-flow, make hot gas constantly passage obtain top gather, result be make the intensity of a fire through this air convection current in mansion
Top layer manufactures another scene of a fire.And as the discharge of hot-air, fresh air constantly suck from bottom flow, the intensity of a fire is caused to be entered
One step is aggravated.This fire is mostly can not be as handling common buildings fire along lift trough or the sprawling of corridor passage, fire fighter
Put out a fire like that from outside, air respiratorresuscitator can only be worn and enter the scene of a fire, big fire of putting out a fire to save life and property is stormed by inside.But at this
A little narrow zones, fire-extinguishing apparatus can not effective operation, once fire spread can not carry fire-extinguishing apparatus to high-rise floor, fireman
Puted out a fire to save life and property, very big difficulty is brought to rescue work.
With the development of science and technology, unmanned air vehicle technique reaches its maturity, unmanned plane is wide with the characteristics of its speed is fast, operation is flexible
General application, and it is introduced in fire-fighting fire extinguishing field.Fire monitor carrying unmanned plane is usually flown to the scene of fire of skyscraper,
And launch firefighting cartridge to put out a fire, still, during fire monitor transmitting firefighting cartridge, can have certain recoil, and unmanned aerial vehicle body compared with
Gently, recoil too conference causes the direct disequilibrium of unmanned plane, or even air crash, and recoil is small, causes firefighting cartridge range region to subtract
It is small, therefore, cause the use of fire-fighting unmanned plane to be restricted.
Utility model content
In order to solve that unmanned plane air crash may be caused because of recoil caused by transmitting firefighting cartridge present in prior art
Technical problem, the utility model provides following technical scheme：
A kind of fire-fighting unmanned plane with hydraulic shock-absorption gun tube, including aviation mechanism and control cabinet, the control cabinet are set
In on the aviation mechanism, the aviation mechanism parallel beneath is provided with multiple fire monitors, and the fire monitor is fixed by monitor body
Part is fixed on below the aviation mechanism, and the monitor body fixture is set on the multiple fire monitor be arrangeding in parallel；
The fire monitor includes gun barrel and gun tube, and the gun barrel is set in outside the gun tube；
Internal diameter is more than both ends internal diameter in the middle part of the gun barrel, and the first spring and second spring are provided with the middle part of the gun barrel；
A lug boss is provided with the middle part of the gun tube outer surface, the lug boss is arranged at first spring and the second bullet
Between spring；
The gun barrel bottom is provided with a piston, and the piston is fixedly connected in the connecting rod of gun tube underrun one, institute
State and at least one through hole is provided with piston；
A dividing plate is provided between the piston and gun tube, the connecting rod passes through the dividing plate, the dividing plate and the big gun
Cylinder bottom forms a confined space；
Liquid is injected with the confined space.
As further explanation of the present utility model, damping is provided between the monitor body fixture and the aviation mechanism
Device；
The damping device includes being arranged at least one set of slide rail below the aviation mechanism, and the slide rail both ends are fixed
Fixed plate is connected with, the fixed plate top is fixed on below the aviation mechanism；
Two sliding blocks are provided with the upward chute of the slide rail upper shed；
The slide rail both ends are arranged with left spring and right spring respectively, and the left spring and right spring one end are fixed on described
In fixed plate, the other end is fixed on the sliding block；
The first connecting plate is fixedly connected with the sliding block, the slide rail both sides are provided with two piece of second connecting plate, described
The upper end of first connecting plate and the second connecting plate is fixedly connected；
The second connecting plate lower end is fixedly connected with the monitor body fixture upper surface.
As further explanation of the present utility model, the monitor body fixture lower surface is fixedly installed supporting leg.
As further explanation of the present utility model, the supporting leg includes sleeve, the 3rd spring and expansion link, and described
Three springs are arranged in the sleeve, and the gun tube fixture lower surface is fixed on the expansion link top, and bottom is stretched into described
In sleeve.
As further explanation of the present utility model, the aviation mechanism includes rotor platform, rotor arm, rotor and flight
Motor, the rotor arm are uniformly fixed on the rotor platform edges, and the rotor is installed on the rotor arm end and by institute
State the driving rotation of flight motor.
As further explanation of the present utility model, the control cabinet is arranged on the rotor platform, the control cabinet
Inside it is provided with battery and camera.
Compared with prior art, what the utility model obtained has the beneficial effect that：
Fire-fighting unmanned plane of the present utility model, liquid is injected with the confined space of gun barrel bottom, in transmitting fire control shell
When, the liquid can play the effect of hydraulic shock-absorption, reduce the recoil of gun tube, the first spring and second being arranged on the outside of gun tube
Spring, a restoring force can be formed to gun tube, gun tube is resetted rapidly；The left spring and right spring pair set at slide rail both ends
Fire monitor forms secondary shock-absorbing, can ensure unmanned plane smooth flight.
The utility model is described in further details below with reference to drawings and Examples.
Brief description of the drawings
Fig. 1 is fire-fighting unmanned plane structural representation of the present utility model.
Fig. 2 is fire-fighting unmanned plane A-A diagrammatic cross-sections of the present utility model.
Fig. 3 is fire-fighting unmanned plane fire monitor structural representation of the present utility model.
In figure：1st, fire monitor；2nd, monitor body fixture；3rd, gun barrel；4th, gun tube；5th, the first spring；6th, second spring；7th, it is raised
Portion；8th, piston；9th, connecting rod；10th, through hole；11st, dividing plate；12nd, confined space；13rd, control cabinet；14th, slide rail；15th, fixed plate；16、
Sliding block；17th, left spring；18th, right spring；19th, the first connecting plate；20th, the second connecting plate；21st, the 3rd spring；22nd, expansion link；
23rd, sleeve；24th, rotor platform；25th, rotor arm；26th, rotor；27th, flight motor.
Embodiment
For the technological means and effect that the utility model is reached predetermined purpose and taken is expanded on further, below in conjunction with accompanying drawing
And embodiment describes in detail as follows to specific embodiment of the present utility model, architectural feature and its effect.
As shown in Figure 1 and Figure 2, a kind of fire-fighting unmanned plane structural representation with hydraulic shock-absorption gun tube of the present utility model
It is arranged at A-A diagrammatic cross-sections, including aviation mechanism and control cabinet 13, control cabinet 13 on aviation mechanism, below aviation mechanism
It is arranged with multiple fire monitors 1 in parallel, fire monitor 1 is fixed on below aviation mechanism by monitor body fixture 2,2 sets of monitor body fixture
It is located on multiple fire monitors 1 be arrangeding in parallel.
As shown in figure 3, fire monitor structural representation, fire monitor 1 includes gun barrel 3 and gun tube 4, and gun barrel 3 is set in the big gun
Outside pipe 4；The middle part internal diameter of gun barrel 3 is more than both ends internal diameter, and the middle part of gun barrel 3 is provided with the first spring 5 and second spring 6；The appearance of gun tube 4
Middle face is provided with a lug boss 7, and lug boss 7 is arranged between the first spring 5 and second spring 6；The bottom of gun barrel 3 is provided with one
Piston 8, piston 8 are fixedly connected in the connecting rod 9 of 4 underrun of gun tube one, and at least one through hole 10 is provided with piston 8；Piston 8 with
A dividing plate 11 is provided between gun tube 4, connecting rod 9 passes through the dividing plate 11, and dividing plate 11 forms a confined space with the bottom of gun barrel 3
12；Liquid is injected with confined space 12.
When launching firefighting cartridge, gun tube 4 can be moved round about, and now, second spring 6 is compressed, and gun tube 4 is formed
Opposite direction（The firefighting cartridge direction of the launch）Active force, piston 8 also moves to the bottom of gun barrel 3, now, the liquid in confined space 12
Pass through the left side space of through hole 10 injection the right space on piston 8（Left and right is defined in Fig. 3）, due to being set at least on piston 8
One through hole 10, and the diameter very little of through hole 10（It is preferred that 3-5mm）, so liquid flowing is slow, now moved to reducing piston 8
Speed, that is, the recoil of gun tube 4 is reduced, when the recoil of gun tube 4 is kept to zero, because the elastic force of second spring 6 acts on, make big gun
Pipe 4 moves to the firefighting cartridge direction of the launch, now, to avoid lug boss 7 from bumping against with gun barrel 3, and so the first spring 5 is provided with, when
Gun tube 4 because second spring 6 active force to the firefighting cartridge direction of the launch move when, then compress the first spring 5, meanwhile, piston 8 also to
The firefighting cartridge direction of the launch is moved, and the liquid of confined space 12 injects left side space by the through hole 10 on piston 8 by the right space,
Because liquid flowing is slow, so reducing the movement velocity of piston 8, that is, the active force of gun tube 4 is reduced, because being flowed when liquid is compressed
Dynamic slow, so being moved in gun tube 4, when piston 8 compresses the liquid in confined space 12, liquid can preferably prevent piston 8 from moving
It is dynamic, reach damping effect, coordinating the first spring 5 and second spring 6, spacing, guarantee gun tube 4 and gun barrel 3 are formed to lug boss 7
Will not hard hit, ensure unmanned plane transmitting firefighting cartridge when, also being capable of smooth flight.
Although the first spring 5, second spring 6 and liquid and piston 8 in confined space 12 that the inside of fire monitor 1 is set
It can realize and reduce the recoil of gun tube 4 and gun tube 4 is set back rapidly, still, when launching fire monitor 1, fire monitor 1 is overall
Also there can be certain recoil, fire monitor 1 is overall also to move relative to unmanned plane during flying mechanism to the opposite direction of firefighting cartridge,
Now, if recoil is excessive, unmanned plane disequilibrium, or even air crash are also resulted in.
Preferably, it is provided with damping device between monitor body fixture 2 and aviation mechanism；The damping device is winged including being arranged at
At least one set of slide rail 14 below row mechanism, the both ends of slide rail 14 are fixedly connected with fixed plate 15, and the top of fixed plate 15 is fixed on winged
Below row mechanism；Two sliding blocks 16 are provided with the upward chute of the upper shed of slide rail 14；The both ends of slide rail 14 are arranged with left bullet respectively
Spring 17 and right spring 18, left spring 17 and the one end of right spring 18 are fixed in fixed plate 15, and the other end is fixed on sliding block 16；It is sliding
The first connecting plate 19 is fixedly connected with block 16, the both sides of slide rail 14 are provided with two piece of second connecting plate 20, the He of the first connecting plate 19
The upper end of second connecting plate 20 is fixedly connected；The lower end of second connecting plate 20 is fixedly connected with the upper surface of monitor body fixture 2.
When launching firefighting cartridge, due to the effect of recoil, the entirety of fire monitor 1 is launched anti-with movable slider 16 to firefighting cartridge
Direction is moved, and now compresses left spring 17, and left spring 17 applies an opposite direction to sliding block 16（The firefighting cartridge direction of the launch）Bullet
Power, so as to reduce recoil, when the recoil of fire monitor 1 disappears, now due to the elastic force of left spring 17, make fire monitor 1 to
The firefighting cartridge direction of the launch is moved, and now compresses right spring 18, and recoil during transmitting firefighting cartridge is much smaller than due to elastic force now,
So under the elastic force effect of right spring 18, fire monitor 1 moves to the opposite direction of transmitting firefighting cartridge again, is so acted in elastic force
Under, rocked although unmanned plane can be caused to produce, due to energy loss, each elastic force is all sequentially reduced, and this, which is rocked, to lead
Unmanned plane disequilibrium is caused, will not more cause unmanned plane that air crash occurs, the left spring 17 and right spring 18 form secondary shock-absorbing, entered
One step ensures unmanned plane smooth flight.
Preferably, the lower surface of monitor body fixture 2 is fixedly installed supporting leg.Supporting leg includes sleeve 23, the 3rd spring 21
With expansion link 22, the 3rd spring 21 is arranged in sleeve 23, and the fixture lower surface of gun tube 4, bottom are fixed in the top of expansion link 22
Stretch into sleeve 23.3rd spring 21 plays cushioning effect in unmanned plane takeoff and landing, makes unmanned plane takeoff and landing
Also can steadily carry out.
Aviation mechanism includes rotor platform 24, rotor arm 25, rotor 26 and flight motor 27, and rotor arm 25 is uniformly fixed on
The edge of rotor platform 24, rotor 26 are installed on the end of rotor arm 25 and drive rotation by flight motor 27.Control cabinet 13 is arranged at
On rotor platform 24, battery and camera are provided with control cabinet 13.
The fire-fighting unmanned plane, by storage battery power supply, the spiraling of rotor 26 is driven by flight motor 27, control centre passes through
Camera determines unmanned plane during flying route and target, and to objective emission firefighting cartridge, on the unmanned plane, monitor body fixture 2
On multiple fire monitors 1 can be installed, particular number can determine according to the loading capacity of unmanned plane, fire extinguishing when, can be larger to the intensity of a fire
More pieces of firefighting cartridges of field emission, can so avoid because come and go shoot and lose time, miss the best opportunity of fire extinguishing.
Above content is to combine specific preferred embodiment further detailed description of the utility model, it is impossible to
Assert that specific implementation of the present utility model is confined to these explanations.For the ordinary skill of the utility model art
For personnel, without departing from the concept of the premise utility, some simple deduction or replace can also be made, should all be regarded
To belong to the scope of protection of the utility model.
Claims (6)
1. a kind of fire-fighting unmanned plane with hydraulic shock-absorption gun tube, including aviation mechanism and control cabinet（13）, the control cabinet
（13）It is arranged on the aviation mechanism, it is characterised in that：The aviation mechanism parallel beneath is provided with multiple fire monitors（1）,
The fire monitor（1）Pass through monitor body fixture（2）It is fixed on below the aviation mechanism, the monitor body fixture（2）It is set in
The multiple fire monitor be arrangeding in parallel（1）On；
The fire monitor（1）Including gun barrel（3）And gun tube（4）, the gun barrel（3）It is set in the gun tube（4）Outside；
The gun barrel（3）Middle part internal diameter is more than both ends internal diameter, the gun barrel（3）Middle part is provided with the first spring（5）With the second bullet
Spring（6）；
The gun tube（4）A lug boss is provided with the middle part of outer surface（7）, the lug boss（7）It is arranged at first spring（5）
And second spring（6）Between；
The gun barrel（3）Bottom is provided with a piston（8）, the piston（8）In the gun tube（4）The connecting rod of underrun one（9）
It is fixedly connected, the piston（8）On be provided with least one through hole（10）；
The piston（8）With gun tube（4）Between be provided with a dividing plate（11）, the connecting rod（9）Through the dividing plate（11）, it is described
Dividing plate（11）With the gun barrel（3）Bottom forms a confined space（12）；
The confined space（12）Inside it is injected with liquid.
2. fire-fighting unmanned plane according to claim 1, it is characterised in that：The monitor body fixture（2）With the flying machine
Damping device is provided between structure；
The damping device includes being arranged at least one set of slide rail below the aviation mechanism（14）, the slide rail（14）Both ends
It is fixedly connected with fixed plate（15）, the fixed plate（15）Top is fixed on below the aviation mechanism；
The slide rail（14）Two sliding blocks are provided with the upward chute of upper shed（16）；
The slide rail（14）Both ends are arranged with left spring respectively（17）With right spring（18）, the left spring（17）With right spring
（18）One end is fixed on the fixed plate（15）On, the other end is fixed on the sliding block（16）On；
The sliding block（16）On be fixedly connected with the first connecting plate（19）, the slide rail（14）Both sides are provided with two piece of second connection
Plate（20）, first connecting plate（19）With the second connecting plate（20）Upper end be fixedly connected；
Second connecting plate（20）Lower end and the monitor body fixture（2）Upper surface is fixedly connected.
3. fire-fighting unmanned plane according to claim 2, it is characterised in that：The monitor body fixture（2）Lower surface is fixed and set
It is equipped with supporting leg.
4. fire-fighting unmanned plane according to claim 3, it is characterised in that：The supporting leg includes sleeve（23）, the 3rd bullet
Spring（21）And expansion link（22）, the 3rd spring（21）It is arranged at the sleeve（23）It is interior, the expansion link（22）Top is consolidated
Due to the gun tube（4）The sleeve is stretched into fixture lower surface, bottom（23）It is interior.
5. according to the fire-fighting unmanned plane described in claim any one of 1-4, it is characterised in that：The aviation mechanism is put down including rotor
Platform（24）, rotor arm（25）, rotor（26）With flight motor（27）, the rotor arm（25）Uniformly it is fixed on the rotor platform
（24）Edge, the rotor（26）It is installed on the rotor arm（25）End and by the flight motor（27）Driving rotation.
6. fire-fighting unmanned plane according to claim 5, it is characterised in that：The control cabinet（13）The rotor is arranged to put down
Platform（24）On, the control cabinet（13）Inside it is provided with battery and camera.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720296945.1U CN206813323U (en) | 2017-03-24 | 2017-03-24 | A kind of fire-fighting unmanned plane with hydraulic shock-absorption gun tube |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720296945.1U CN206813323U (en) | 2017-03-24 | 2017-03-24 | A kind of fire-fighting unmanned plane with hydraulic shock-absorption gun tube |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206813323U true CN206813323U (en) | 2017-12-29 |
Family
ID=60752330
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720296945.1U Expired - Fee Related CN206813323U (en) | 2017-03-24 | 2017-03-24 | A kind of fire-fighting unmanned plane with hydraulic shock-absorption gun tube |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206813323U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110193153A (en) * | 2019-06-03 | 2019-09-03 | 河南大域航空科技有限公司 | A kind of outdoor fire disaster rescue auxiliary device based on unmanned plane |
-
2017
- 2017-03-24 CN CN201720296945.1U patent/CN206813323U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110193153A (en) * | 2019-06-03 | 2019-09-03 | 河南大域航空科技有限公司 | A kind of outdoor fire disaster rescue auxiliary device based on unmanned plane |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20171229 Termination date: 20180324 |