CN108945458A - Docking damping device for unmanned plane - Google Patents
Docking damping device for unmanned plane Download PDFInfo
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- CN108945458A CN108945458A CN201810595789.8A CN201810595789A CN108945458A CN 108945458 A CN108945458 A CN 108945458A CN 201810595789 A CN201810595789 A CN 201810595789A CN 108945458 A CN108945458 A CN 108945458A
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- Prior art keywords
- unmanned plane
- gag lever
- lever post
- interface
- spring
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D1/00—Dropping, ejecting, releasing, or receiving articles, liquids, or the like, in flight
- B64D1/02—Dropping, ejecting, or releasing articles
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D47/00—Equipment not otherwise provided for
-
- 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
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
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Abstract
The invention discloses a kind of docking damping devices for unmanned plane, belong to air vehicle technique field, including joint unit and damping part.Joint unit includes the first interface, ontology and the second interface.First interface and fuselage are detachably connected, and ontology and the first interface are fixedly connected, and the second interface is fixedly connected with ontology, and the first clamping seat and the second clamping seat are provided on the second interface.Damping part includes the first gag lever post, the second gag lever post, the first elastic parts and the second elastic parts.First gag lever post is provided with the first fastening end and the second fastening end；Second gag lever post is provided with third fastening end and the 4th fastening end；First elastic parts is set in the outside of the first gag lever post；Second elastic parts is set in the outside of the second gag lever post.The present invention reaches the maintenance cost for reducing unmanned plane shooting component；Be conducive to eliminate recoil to the adverse effect of unmanned plane, unmanned plane is enabled to help the technical effect of indicator of trapped personnel escape in time.
Description
Technical field
The invention belongs to air vehicle technique field, in particular to a kind of docking damping device for unmanned plane.
Background technique
Unmanned unmanned plane referred to as " unmanned plane ", is grasped using radio robot and the presetting apparatus provided for oneself
Vertical not manned unmanned plane.Without cockpit on machine, but automatic pilot, presetting apparatus, information collecting device are installed etc.
Equipment.On ground, naval vessels or machine tool remote control station personnel are by the equipment such as radar, it is tracked, is positioned, is remotely controlled, telemetering and
Digital Transmission.It can take off as common unmanned plane under wireless remotecontrol or be launched with booster rocket, it can also be by machine tool
Aerial launch is taken to fly.
For unmanned plane, unmanned aerial vehicle body in the prior art is formed using integrally formed structure fabrication.Nobody
If owner is by fuselage, wing and positioned at the propeller of head, and is mounted in the video camera on unmanned plane to constitute.Usually
From received professional training operator and with take off in the case where parasite power, the lift of flight be by wing and
It is provided positioned at the propeller of head.When high-rise fire occurs, each building is observed by the video camera being mounted on unmanned plane
The fire condition of layer, then indicator of trapped personnel is saved by aerial ladder.Since the shooting component and unmanned aerial vehicle body of unmanned plane are fixed
It is integrally formed structures, if when shooting parts damages entire unmanned plane will be needed replacing, this will increase maintenance cost.Meanwhile
If being shot at by unmanned plane to glass, powerful recoil will damage unmanned aerial vehicle body, and the stabilization of unmanned plane is interfered to fly
Row.This makes the glass of high residential building be difficult to smash, and rescue worker is caused to cannot be introduced into interior, and indoor indicator of trapped personnel can not yet
It escapes from, escapes in time to be unfavorable for indicator of trapped personnel.
In conclusion the maintenance cost that unmanned plane shoots component is high in existing unmanned air vehicle technique；Shooting can not be eliminated
When the recoil that generates to the adverse effect of unmanned plane, prevent unmanned plane from helping indicator of trapped personnel to escape in time, it is difficult to succour
Indicator of trapped personnel in high residential building.
Summary of the invention
The technical problem to be solved by the present invention is to the maintenance cost of unmanned plane shooting component is high；Production when can not eliminate shooting
Raw recoil is to the adverse effect of unmanned plane, prevent unmanned plane from helping indicator of trapped personnel to escape in time, it is difficult to which rescue is high-rise
Indicator of trapped personnel in house.
In order to solve the above technical problems, the present invention provides a kind of docking damping device for unmanned plane, it is described nobody
Machine includes fuselage, and the docking damping device for unmanned plane includes: joint unit, and the joint unit includes: the first rank
Junction, first interface and the fuselage are detachably connected；Ontology, the ontology and first interface are fixed to be connected
It connects；Second interface, second interface are fixedly connected with the ontology, are provided with the first clamping on second interface
Seat and the second clamping seat；Wherein, the ontology is between first interface and second interface；First card
The centrosymmetric distribution of joint chair and the second clamping seat relative to second interface；First interface and described
Second interface is symmetrical relative to the ontology；Damping part, the damping part include: the first gag lever post, and described
One gag lever post is provided with the first fastening end and the second fastening end, and first fastening end is fixedly connected with the first pedestal, and described
Second fastening end is fixedly connected with the second pedestal, and first gag lever post passes through the first mounting hole；Second gag lever post, described second
Gag lever post is provided with third fastening end and the 4th fastening end, and the third fastening end is fixedly connected with third pedestal, and described
Four fastening ends are fixedly connected with the 4th pedestal, and second gag lever post passes through the second mounting hole；First elastic parts, described first
Elastic parts is set in the outside of first gag lever post, and first elastic parts is located at first fastening end and described
Between two fastening ends；Second elastic parts, second elastic parts are set in the outside of second gag lever post, and described second
Elastic parts is between the third fastening end and the 4th fastening end；Wherein, first fastening end and described second
Fastening end is the both ends of the first gag lever post opposition, and the third fastening end and the 4th fastening end are second limits
The both ends of bar opposition.
Further, it includes the first bullet that the docking damping device for unmanned plane, which includes: first elastic parts,
Spring and second spring, first spring are set in the outside of first gag lever post, and the second spring be set in it is described
The outside of first gag lever post.
Further, the docking damping device for unmanned plane includes: that first spring is located at described first tightly
Between fixed end and first mounting hole.
Further, the docking damping device for unmanned plane includes: that the second spring is located at described second tightly
Between fixed end and first mounting hole.
Further, it includes third bullet that the docking damping device for unmanned plane, which includes: second elastic parts,
Spring and the 4th spring, the third spring are set in the outside of second gag lever post, and the 4th spring be set in it is described
The outside of second gag lever post.
Further, the docking damping device for unmanned plane includes: that be located at the third tight for the third spring
Between fixed end and second mounting hole.
Further, the docking damping device for unmanned plane includes: that the 4th spring is located at the described 4th tightly
Between fixed end and second mounting hole.
Further, it is engraved structure that the docking damping device for unmanned plane, which includes: first interface,.
Further, it is engraved structure that the docking damping device for unmanned plane, which includes: second interface,.
Further, it is engraved structure that the docking damping device for unmanned plane, which includes: the ontology,.
The utility model has the advantages that
The present invention provides a kind of docking damping device for unmanned plane, by the way that the ontology of joint unit and first to be connected
Face is fixedly connected, and the second interface of joint unit is fixedly connected with ontology, on the second interface be arranged first clamping seat and
Second clamping seat, makes ontology between the first interface and second interface, the first clamping seat and the second clamping seat phase
Centrosymmetric distribution for the second interface, the first interface and the second interface are symmetrical relative to ontology.Due to
The first interface and fuselage of joint unit are detachably connected, if emission element and/or joint unit damage, do not need to replace
Unmanned plane, it is only necessary to replace emission element and/or joint unit, object of the unmanned plane in time to target area can be enable
(such as glass) is shot at.Meanwhile by the way that the first fastening end in the first gag lever post is fixedly connected with the first pedestal, the first limit
The second fastening end is fixedly connected with the second pedestal in bar, and the first gag lever post is made to pass through the first mounting hole.By in the second gag lever post
Three fastening ends are fixedly connected with third pedestal, and the 4th fastening end is fixedly connected with the 4th pedestal in the second gag lever post, make the second limit
Position bar passes through the second mounting hole.And the first elastic parts is set in the outside of the first gag lever post, makes the first elastic parts position
Between the first fastening end and second fastening end；Second elastic parts is set in the outside of the second gag lever post, makes second
Elastic parts is between third fastening end and the 4th fastening end.In actual operation, emitting object to be penetrated to target area (such as
Window) be shot at during, generated recoil will force the first elastic parts and the second elastic parts to emit elastic shape
Become, the ability that recoil is generated is converted into the elastic potential energy of the first elastic parts and the second elastic parts, after then weakening
Adverse effect of the recoil to unmanned plane.To reach the maintenance cost for reducing unmanned plane shooting component；When being conducive to eliminate shooting
The recoil of generation enables unmanned plane to help indicator of trapped personnel to escape in time the adverse effect of unmanned plane, and rescue high level is lived
The technical effect of indicator of trapped personnel in residence.
Detailed description of the invention
It in order to more clearly explain the embodiment of the invention or the technical proposal in the existing technology, below will be to institute in embodiment
Attached drawing to be used is needed to be briefly described, it should be apparent that, the accompanying drawings in the following description is only some implementations of the invention
Example, for those of ordinary skill in the art, without creative efforts, can also obtain according to these attached drawings
Obtain other attached drawings.
Fig. 1 is a kind of overall structure diagram of the grenade instrumentation for unmanned plane provided in an embodiment of the present invention；
Fig. 2 provides a kind of top view illustration of grenade instrumentation for unmanned plane for the embodiment of the present invention；
Fig. 3 provides a kind of left view schematic diagram of grenade instrumentation for unmanned plane for the embodiment of the present invention；
Fig. 4 provides a kind of right view schematic diagram of grenade instrumentation for unmanned plane for the embodiment of the present invention；
Fig. 5 provides a kind of front view schematic diagram of grenade instrumentation for unmanned plane for the embodiment of the present invention；
Fig. 6 provides a kind of rearview schematic diagram of grenade instrumentation for unmanned plane for the embodiment of the present invention；
Detailed description of the invention:
100-emission elements, 110-ejecting ends, 120-tube bodies, 121-first sides, 122-second sides, 123-
Hollow portion, the 124-the first pedestal, the 125-the second pedestal, 126-third pedestals, the 127-the four pedestal, 130-handling ends,
131-enter bullet mouth, 132-control switches, 140-objects to be penetrated, the 150-the first positioning area, the 160-the second positioning area, and 170-the
Three positioning areas, 180-baffles, the 181-the first trajectory, the 182-the second trajectory；
200-joint units, the 210-the first interface, 220-ontologies, the 230-the second interface, the 231-the first clamping
Seat, the 232-the second clamping seat；
300-load-supporting parts, the 310-the first support arm, 311-first ends, 312-second ends, the 313-the first installation
Hole, the 320-the second support arm, 321-third ends, the 322-the four end, the 323-the second mounting hole；
400-damping parts, the 410-the first gag lever post, the 411-the first fastening end, the 412-the second fastening end, 420-the
Two gag lever posts, 421-third fastening ends, the 422-the four fastening end, the 430-the first elastic parts, the 440-the second elastic parts.
Specific embodiment
The present invention provides a kind of docking damping device for unmanned plane, by the way that the ontology of joint unit and first to be connected
Face is fixedly connected, and the second interface of joint unit is fixedly connected with ontology, on the second interface be arranged first clamping seat and
Second clamping seat, makes ontology between the first interface and second interface, the first clamping seat and the second clamping seat phase
Centrosymmetric distribution for the second interface, the first interface and the second interface are symmetrical relative to ontology.Due to
The first interface and fuselage of joint unit are detachably connected, if emission element and/or joint unit damage, do not need to replace
Unmanned plane, it is only necessary to replace emission element and/or joint unit, object of the unmanned plane in time to target area can be enable
(such as glass) is shot at.Meanwhile by the way that the first fastening end in the first gag lever post is fixedly connected with the first pedestal, the first limit
The second fastening end is fixedly connected with the second pedestal in bar, and the first gag lever post is made to pass through the first mounting hole.By in the second gag lever post
Three fastening ends are fixedly connected with third pedestal, and the 4th fastening end is fixedly connected with the 4th pedestal in the second gag lever post, make the second limit
Position bar passes through the second mounting hole.And the first elastic parts is set in the outside of the first gag lever post, makes the first elastic parts position
Between the first fastening end and second fastening end；Second elastic parts is set in the outside of the second gag lever post, makes second
Elastic parts is between third fastening end and the 4th fastening end.In actual operation, emitting object to be penetrated to target area (such as
Window) be shot at during, generated recoil will force the first elastic parts and the second elastic parts to emit elastic shape
Become, the ability that recoil is generated is converted into the elastic potential energy of the first elastic parts and the second elastic parts, after then weakening
Adverse effect of the recoil to unmanned plane.To reach the maintenance cost for reducing unmanned plane shooting component；When being conducive to eliminate shooting
The recoil of generation enables unmanned plane to help indicator of trapped personnel to escape in time the adverse effect of unmanned plane, and rescue high level is lived
The technical effect of indicator of trapped personnel in residence.
In order to elaborate to a kind of docking damping device for unmanned plane provided by the invention, to support invention institute
Technical problems to be solved, in the following, being done in detail to a kind of grenade instrumentation for unmanned plane first in embodiment provided by the invention
Describe in detail it is bright, then during describing a kind of grenade instrumentation for unmanned plane, further targetedly draw the present invention
A kind of docking damping device for unmanned plane of offer, it is complete, clear, clear to achieve the purpose that.
Following will be combined with the drawings in the embodiments of the present invention, and technical solution in the embodiment of the present invention carries out clear, complete
Site preparation description, it is clear that described embodiments are only a part of the embodiments of the present invention, instead of all the embodiments.It is based on
Embodiment in the present invention, those of ordinary skill in the art's every other embodiment obtained belong to what the present invention protected
Range；Wherein "and/or" keyword involved in this implementation, indicate and or two kinds of situations, in other words, the present invention implement
A and/or B mentioned by example, illustrate two kinds of A and B, A or B situations, describe three kinds of states present in A and B, such as A and/or
B, indicate: only including A does not include B；Only including B does not include A；Including A and B.
Meanwhile in the embodiment of the present invention, when component is referred to as " being fixed on " another component, it can be directly at another
On component or there may also be components placed in the middle.When a component is considered as " connection " another component, it be can be directly
It is connected to another component or may be simultaneously present component placed in the middle.When a component is considered as " being set to " another group
Part, it, which can be, is set up directly on another component or may be simultaneously present component placed in the middle.Made in the embodiment of the present invention
Term "vertical", "horizontal", "left" and "right" and similar statement are merely for purposes of illustration, and are not intended to
The limitation present invention.
It is right first in order to which a kind of grenade instrumentation for unmanned plane provided in an embodiment of the present invention is described in detail
Technical term involved in the embodiment of the present invention does description below explanation:
Detachable connection, which may is that, to be bolted or is bonded；
It is fixedly connected and may is that welding or integrated molding；
Ground may is that ground when unmanned plane is parked；
It takes off the process that may is that unmanned plane reaches aerial rising from ground；
Landing may is that process of the unmanned plane from airborne to ground；
Object 140 to be penetrated can be the article for referring to shattered glass, such as glass marbles, metal hoodle, metal nail etc..
Referring to Figure 1, Fig. 1 is that a kind of overall structure of grenade instrumentation for unmanned plane provided in an embodiment of the present invention is shown
It is intended to.A kind of grenade instrumentation for unmanned plane provided in an embodiment of the present invention, a kind of grenade instrumentation for unmanned plane include
Emission element 100, joint unit 200, load-supporting part 300 and damping part 400.Now to emission element 100, joint unit 200,
Load-supporting part 300 and damping part 400 carry out following detailed description respectively:
For emission element 100:
Emission element 100 may include ejecting end 110, tube body 120, handling end 130 and object to be penetrated 140.
Tube body 120 is provided with first side 121, second side 122 and hollow portion 123, can be set in first side 121
There are the first pedestal 124 and the second pedestal 125；Third pedestal 126 and the 4th pedestal 127 can be set in second side 122；Dress
Unloading end 130 can be set into bullet mouth 131 and control switch 132, and object 140 to be penetrated is connected with control switch 132, and wait penetrate
Object 140 is located in bullet mouth 131.Wherein, tube body 120 can be located at handling end 130 and enter between bullet mouth 131, and hollow portion 123 can
To pass through into bullet mouth 131 and ejecting end 110；
Ejecting end 110 can also include the first positioning area 150, the second positioning area 160 and third positioning area 170, and first is fixed
Position is fixedly installed with first laser transmitter in area 150, and second laser transmitter is fixedly installed on the second positioning area 160, the
Image pick-up device is fixedly installed on three positioning areas 170.Wherein, the first positioning area 150 and the second positioning area 160 can be relative to thirds
Positioning area 170 is symmetrical；Hollow portion 123 can be 30 ° -60 ° relative to the angular range of second interface 230.
Go out baffle 180 can be installed entering bullet mouth 131, baffle 180 and entering is hinged at bullet mouth 131.And baffle
180 can be connected with control switch 132, and baffle 180 can be located between bullet mouth 131 and control switch 132.
Hollow portion 123 may include the first trajectory 181 and the second trajectory 182.First trajectory 181 and the second trajectory 182 can
To be parallel to each other distribution relative to first side 121.Wherein, the first trajectory 181 can be passed through into bullet mouth 131 and ejecting end 110,
And the second trajectory 182 can be passed through into bullet mouth 131 and ejecting end 110.
Referring to Figure 1 and Fig. 2, Fig. 1 be a kind of grenade instrumentation for unmanned plane provided in an embodiment of the present invention entirety
Structural schematic diagram, Fig. 2 provide a kind of top view illustration of grenade instrumentation for unmanned plane for the embodiment of the present invention.Tube body
120, which can be metal material, is made, and tube body 120 is rendered as hollow structure, which penetrates object for accommodating hoodle waiting
140.Tube body 120 has first side 121 and second side 122, and it is position that first side 121 and second side 122, which can be distributed,
In the face of 120 left and right sides of tube body.The both ends of tube body 120 are that handling and enter bullet mouth 131 at end 130 respectively, and entering at bullet mouth 131 can be with
Be provided with baffle 180, baffle 180 and entering is hinged at bullet mouth 131, i.e., baffle 180 can be opened relative to bullet mouth 131 is entered or
Person's closure.Baffle 180 is located between bullet mouth 131 and control switch 132, and the inside for entering bullet mouth 131 have accommodate to
Penetrate the space of object 140.Object 140 to be penetrated can be connected with control switch 132, excite position by the on-off of control switch 132
In entering the object to be penetrated 140 in bullet mouth 131, make object 140 to be penetrated from enter bullet mouth 131 along hollow portion 123 reach ejecting end 110, from
110 homed on its target region of ejecting end (such as glass edge of high residential building window).
First laser transmitter, the second positioning area 160 can be fixedly installed on first positioning area 150 of ejecting end 110
On can be fixedly installed with second laser transmitter, image pick-up device can be fixedly installed on third positioning area 170.First laser hair
Emitter and second laser transmitter are symmetrical relative to image pick-up device.First laser transmitter and second laser transmitter can be
Laser aiming utensil, such as beam of laser is emitted by first laser transmitter, the hot spot which generates in target area can
To be the aiming point for indicating object 140 to be penetrated and coming to target.It can be improved by first laser transmitter and second laser transmitter
Accuracy after penetrating object 140 and projecting.Image pick-up device can be camera, which can feed back in the region passed through to ground
On the display of face operator, ground handling operator passes through the video image and first laser transmitter and second laser
Aiming point caused by transmitter, precisely to be shot to target area.
Entering baffle 180 can be installed at bullet mouth 131, make baffle 180 and enter to be hinged at bullet mouth 131.And it keeps off
Plate 180 can be connected with control switch 132, and baffle 180 can be located between bullet mouth 131 and control switch 132.In pipeline
Can there are the first trajectory 181 and the second trajectory 182, the first trajectory 181 and the second trajectory 182 can be relative to first sides 121
Be parallel to each other distribution.Wherein, the first trajectory 181 can be passed through into bullet mouth 131 and ejecting end 110, and the second trajectory 182 can be with
It passes through into bullet mouth 131 and ejecting end 110.In actual use, object 140 to be penetrated can be pre-loaded with the first trajectory 181 and second
In trajectory 182, object 140 to be penetrated is blocked by baffle 180, such as two hoodles are respectively charged into the first trajectory 181 and the second bullet
In road 182, then by the closure of baffle 180 it is separately fixed at two hoodles in the first trajectory 181 and the second trajectory 182.Baffle
The control switch 132 of 180 sides can be connected with two hoodles respectively, when control switch 132 is closed, can excite positioned at the
Object to be penetrated 140 in one trajectory 181 and the second trajectory 182 makes the first trajectory of hoodle approach 181 being located in the first trajectory 181,
It is projected at a high speed from ejecting end 110, makes the second trajectory of hoodle approach 182 being located in the second trajectory 182, it is also high from ejecting end 110
Rapid fire goes out.Since there are two trajectories for tool, then entering to be packed into two objects 140 to be penetrated in bullet mouth 131, if which overcome only one
It is a to be somebody's turn to do after penetrating object 140 when penetrating object 140 when projecting, when the shock strength wait penetrate object 140 is not enough to shattered glass, unmanned plane
It is only drop to ground, object 140 to be penetrated of reloading takes off again to original position, is shot at, when this is both expended
Between, also it is unfavorable for the technological deficiency succoured in time to indoor indicator of trapped personnel.When in pipeline have the first trajectory 181 and second
When trajectory 182, if the shock strength wait penetrate object 140 for being located at the first trajectory 181 when being not enough to shattered glass, can make to be located at the
The object to be penetrated 140 of two trajectories 182 emits simultaneously, bigger impact force is generated, then timely shattered glass, convenient for the people of indoor and outdoor
Member's disengaging.To reach the glass that can quickly smash target area, the technical effect of indoor indicator of trapped personnel is succoured in time.
Referring to Figure 1, Fig. 1 is that a kind of overall structure of grenade instrumentation for unmanned plane provided in an embodiment of the present invention is shown
It is intended to.Angular range of the hollow portion 123 relative to the second interface 230 (the second interface 230 can be parallel to each other with ground)
Can be 30 ° -60 °, i.e., the angular range of route when penetrating object 140 and projecting and the second interface 230 can be 30 ° -
60°.Assuming that hollow portion 123 is A relative to the angle of the second interface 230, then 30 °≤A≤60 °.When 30 ° of A <, if transmitting
Object 140 to be penetrated, then object 140 to be penetrated will generate recoil, the direction of the recoil and ejecting end 110 it is contrary, at this point, by force
Big recoil mutually seriously affects the balance of unmanned plane itself, or even destroys the state of flight of unmanned plane, and unmanned plane is caused to stop
It runs well, to be unfavorable for the normal work of unmanned plane, influences the stability of ejecting end 110, reduce the accuracy of shooting.When
At 60 ° of A >, if emitting object 140 to be penetrated, make ejecting end 110 and wall close to horizontal state, it at this time can not be to target area
The glass in domain is aimed at, but also powerful recoil caused by object to be penetrated 140 seriously affects the balance of unmanned plane itself, very
To the state of flight for destroying unmanned plane, unmanned plane is caused to stop running well, to be unfavorable for the normal work of unmanned plane, influenced
The stability of ejecting end 110 reduces the accuracy of shooting.
For joint unit 200:
The joint unit 200 may include the first interface 210, ontology 220 and the second interface 230.
First interface 210 can be detachably connected with fuselage；Ontology 220 can be fixedly connected with the first interface 210；
Second interface 230 can be fixedly connected with ontology 220, and the first clamping seat 231 and the second card are provided on the second interface 230
Joint chair 232；Wherein, ontology 220 can be between the first interface 210 and the second interface 230；First clamping 231 He of seat
Second clamping seat 232 can be rendered as symmetrically being distributed relative to the center of the second interface 230；First interface 210 and
Two interfaces 230 can be rendered as symmetrical relative to ontology 220.First interface 210 can be rendered as engraved structure,
And/or second interface 230 can be rendered as engraved structure, and/or, ontology 220 can be rendered as engraved structure.
Referring to Figure 1 and Fig. 3, Fig. 1 be a kind of grenade instrumentation for unmanned plane provided in an embodiment of the present invention entirety
Structural schematic diagram, Fig. 3 are that the embodiment of the present invention provides a kind of left view schematic diagram of grenade instrumentation for unmanned plane.At nobody
The clamping portion to match with the first interface 210 can be set in the fuselage bottom of machine, which can be with clamping portion
Dismountable connection.Ontology 220 can be fixedly connected with the first interface 210, and the second interface 230 can be solid with ontology 220
Fixed connection, allows to constitute joint unit 200 by the first interface 210, ontology 220 and the second interface 230.Second
The first clamping seat 231 and the second clamping seat 232 can be set on interface 230.First clamping seat 231 can be with the first support
The first end 311 of arm 310 is mutually permanently connected, and the second clamping seat 232 can be mutual with the third end 321 of the second support arm 320
It is fixedly connected.The center of second interface 230 can be the geometric center of the second interface 230, such as the second interface 230 is in
When being now square, the center of second interface 230 can be the geometric center of square.Ontology 220 can be positioned at
Part between one interface 210 and the second interface 230, can be by the first interface 210, ontology 220 and the second interface
230 constitute joint unit 200.
First interface 210 can be rendered as engraved structure, and/or, the second interface 230 can be rendered as hollow out knot
Structure, and/or, ontology 220 can be rendered as engraved structure.That is the first interface 210 and the second interface 230 can be rendered as
Engraved structure or the first interface 210 and third interface can be rendered as engraved structure etc..Due to the first interface
210 can be rendered as engraved structure, and/or, the second interface 230 can be rendered as engraved structure, and/or, ontology 220 can be with
It is rendered as engraved structure；When then the engraved structure can reduce the first interface 210 of production, ontology 220 and the second interface 230
Material, then reduce the weight of the first interface 210, ontology 220 and the second interface 230, when taking off to reduce unmanned plane
The weight of entrained load is conducive to the flying height for promoting unmanned plane, increases the cruise duration of unmanned plane.
In order to the first interface 210 can and fuselage be detachably connected and be explained in detail, now said in detailed below
Bright: unmanned plane can be multi-rotor unmanned aerial vehicle, and the fuselage of unmanned plane is segmented into including at least three sections, i.e. head, fuselage and machine
Tail, and can be attached by the connection type of detachable connection between three sections, being constituted an internal structure with this can
The fixed-wing unmanned plane of disassembly, so that when local damage occurs in the fuselage of unmanned plane, corresponding can remove and damage
Bad position repairs, and has simple, convenient technical effect.And when the part of fuselage can not due to damaging
When reparation, can also the position that can not repair of corresponding dismounting, i.e., the position that can not be repaired is substituted, to overcome
In the prior art because fuselage is using integrated whole design, when so that there is fuselage local damage and can not repair, it has to more
The technological deficiency for changing the entire fuselage of unmanned plane, reaches and significantly reduces the technical effect of maintenance cost.Also, in unmanned plane
Head, and/or, fuselage, and/or, the attachment base to match with the first interface 210 can be set on tail, so that
One interface 210 can be detachably connected with the fuselage.It then, must not when local damage, which occurs, in grenade instrumentation to be repaired
It is changed without the technological deficiency of the entire fuselage of unmanned plane, reaches and significantly reduces the technical effect of maintenance cost.
For load-supporting part 300:
Load-supporting part 300 may include the first support arm 310 and the second support arm 320.
First end 311 and second end 312, first end 311 and the first clamping seat 231 has can be set in first support arm 310
It is fixedly connected, the first mounting hole 313 can be set in second end 312；
Third end 321 and the 4th end 322, third end 321 and the second clamping seat has can be set in second support arm 320
232 are fixedly connected；The second mounting hole 323 can be set on the 4th end 322；Wherein, first end 311 and second end
312 can be the both ends of the first support arm 310 opposition respectively, and third end 321 and the 4th end 322 can be the second support arm respectively
The both ends of 320 opposition.First support arm 310 and/or the second support arm 320 can be and be rendered as engraved structure, to reduce nobody
The weight of entrained load when machine takes off is conducive to the flying height for promoting unmanned plane, increases the cruise duration of unmanned plane.
First mounting hole 313 may include first through hole and the second through-hole, and first through hole and the second through-hole are relative to second
The center at end 312 can be rendered as symmetrical.Wherein, the first gag lever post 410 passes through first through hole and the second through-hole；First is logical
The diameter in hole can be greater than the diameter of the first gag lever post 410, and the diameter of the second through-hole can be greater than the first gag lever post 410
Diameter.Second mounting hole 323 may include third through-hole and fourth hole, and third through-hole and fourth hole are relative to the 4th
The center at end 322 can be rendered as symmetrical.Wherein, the second gag lever post 420 can pass through third through-hole and fourth hole；The
The diameter of three through-holes can be greater than the diameter of the second gag lever post 420, and the diameter of fourth hole can be greater than the second gag lever post
420 diameter.
Referring to Figure 1 and Fig. 4, Fig. 1 be a kind of grenade instrumentation for unmanned plane provided in an embodiment of the present invention entirety
Structural schematic diagram, Fig. 4 are that the embodiment of the present invention provides a kind of right view schematic diagram of grenade instrumentation for unmanned plane.First end
311 and second end 312 can be respectively the first support arm 310 both ends, first end 311 can be fixed with the first clamping seat 231
Connection, makes the first support arm 310 and joint unit 200 link together, and when relay part is moved with unmanned plane, drives first
Brace 310 moves together.The first mounting hole 313 can be set in second end 312, the first mounting hole 313 may include
One through-hole and the second through-hole.
In order to which the first gag lever post 410 is explained in detail across first through hole and the second through-hole, following two is now provided
Embodiment is described in detail:
The first embodiment.It the aperture direction of first through hole can be with second end 312 close to the plane phase of first through hole
It is mutually parallel.First through hole can be formed along the direction of the column body section by installing a column in first end 311,
So that the aperture direction of first through hole is parallel to each other relative to ducted body.The diameter of first through hole can be greater than the first gag lever post
410 diameter, it is assumed that the diameter of the first gag lever post 410 is B, and the diameter of first through hole is C1, then C1 > B.Due to first through hole
Diameter be greater than the first gag lever post 410 diameter, then the first gag lever post 410 can slide in first through hole, this to be arranged
The first support arm 310 outside the first gag lever post 410 can be moved along the first gag lever post 410.When object 140 to be penetrated from
After ejecting end 110 projects, it is mobile relative to the first support arm 310 that generated back pressure can push emission element 100, then leads to
It crosses and first spring is set between the first fastening end 411 and the first mounting hole 313, in the second fastening end 412 and the first mounting hole
Second spring is set between 313, by the deformation of the first spring and/or second spring, to absorb energy caused by object 140 to be penetrated
Amount.To overcome the back pressure damage unmanned plane and load-supporting part 300 that generate when penetrating object 140 and projecting, reaches and be conducive to nothing
The technical effect that man-machine normal flight and 300 joint unit 200 of load-supporting part work normally.
Second of embodiment.It the aperture direction of second through-hole can be with second end 312 close to the plane phase of first through hole
It is mutually parallel.The second through-hole can be formed along the direction of the column body section by installing a column in second end 312,
So that the aperture direction of the second through-hole is parallel to each other relative to ducted body.The diameter of second through-hole can be greater than the first gag lever post
410 diameter, it is assumed that the diameter of the first gag lever post 410 is B, and the diameter of the second through-hole is C2, then C2 > B.Due to the second through-hole
Diameter be greater than the first gag lever post 410 diameter, then the first gag lever post 410 can slide in the second through-hole, this to be arranged
The first support arm 310 outside the first gag lever post 410 can be moved along the first gag lever post 410.When object 140 to be penetrated from
After ejecting end 110 projects, it is mobile relative to the first support arm 310 that generated back pressure can push emission element 100, then leads to
It crosses and first spring is set between the first fastening end 411 and the first mounting hole 313, in the second fastening end 412 and the first mounting hole
Second spring is set between 313, by the deformation of the first spring and/or second spring, to absorb energy caused by object 140 to be penetrated
Amount.To overcome the back pressure damage unmanned plane and load-supporting part 300 that generate when penetrating object 140 and projecting, reaches and be conducive to nothing
The technical effect that man-machine normal flight and 300 joint unit 200 of load-supporting part work normally.
It should be noted that first through hole and the second through-hole can be different relative to the distance of the first interface 210, such as
First through hole is more farther than the distance of second the first interface of through-hole distance 210, then makes between first through hole and the second through-hole
With difference in height, after the first gag lever post 410 being made to pass through first through hole and the second through-hole by the difference in height, relative to
Ground is heeling condition.First gag lever post 410 can be 30 ° -60 ° relative to the tilt angle on ground.If the first limit
Bar 410 is W1 relative to the tilt angle on ground, then 30 °≤W1≤60 °, can make so among the above sky portion 123 relative to
The angular range of second interface 230 can be 30 ° -60 °.
After the first gag lever post 410 passes through first through hole and the second through-hole, it is assumed that extended line by first through hole and
P1 point is intersected at by the extended line of the second through-hole, is connected by P1 point, first through hole and the second through-hole and forms a right angle trigonometry
Shape, the first gag lever post 410 across first through hole and the second throughhole portions are the bevel edge of the right angled triangle.First through hole and
The right-angle side that P1 point is formed is Y1, and the right-angle side that the second through-hole and P1 point are formed is Y2, then Y2:Y1=Z1, then the range of Z1 can
To be (1/2)≤Z1≤(√ 3)/2.Due to (1/2)≤Z1≤(√ 3)/2, when the first gag lever post 410 passes through first through hole and the
After two through-holes, the first gag lever post 410 is heeling condition relative to ground, and hollow portion 123 can be made relative to the first linking
The angular range in face 210 can be 30 ° -60 °, then ejecting end 110 can then make than handling end 130 closer to ground at this time
Obtaining the object to be penetrated 140 projected from ejecting end 110 can be relative to the first shooting downwards of interface 210, and it is right in the sky to not only improve
Glass at door and window is aimed at, and the recoil for being conducive to generate object 140 to be penetrated tilts upward, and it is downward to overcome recoil
When, it will push the technological deficiency that unmanned plane decline bumps against ground or metope.Make unmanned plane safety, smooth flight to reach,
And the technical effect that object 140 to be penetrated steadily projects.
Continuing with being a kind of grenade instrumentation for unmanned plane provided in an embodiment of the present invention referring to Fig. 1 and Fig. 4, Fig. 1
Overall structure diagram, Fig. 4 are that the embodiment of the present invention provides a kind of right view schematic diagram of grenade instrumentation for unmanned plane.For
Third through-hole is passed through to second gag lever post 420 and fourth hole is explained in detail, now provide following two embodiment into
Row is described in detail:
The first embodiment.It the aperture direction of third through-hole can be with the 4th end 322 close to the plane phase of third through-hole
It is mutually parallel.Third through-hole can be formed along the direction of the column body section by installing a column on the 4th end 322,
So that the aperture direction of third through-hole is parallel to each other relative to ducted body.The diameter of third through-hole can be greater than the second gag lever post
420 diameter, it is assumed that the diameter of the second gag lever post 420 is B, and the diameter of third through-hole is C3, then C3 > B.Due to third through-hole
Diameter be greater than the second gag lever post 420 diameter, then the second gag lever post 420 can slide in third through-hole, this to be arranged
The second support arm 320 outside the second gag lever post 420 can be moved along the second gag lever post 420.When object 140 to be penetrated from
After ejecting end 110 projects, it is mobile relative to the second support arm 320 that generated back pressure can push emission element 100, then leads to
The setting third spring between third fastening end 421 and the second mounting hole 323 is crossed, in the 4th fastening end 422 and the second mounting hole
4th spring is set between 323, by the deformation of third spring and/or the 4th spring, to absorb energy caused by object 140 to be penetrated
Amount.To overcome the back pressure damage unmanned plane and load-supporting part 300 that generate when penetrating object 140 and projecting, reaches and be conducive to nothing
The technical effect that man-machine normal flight and 300 joint unit 200 of load-supporting part work normally.
Second of embodiment.It the aperture direction of fourth hole can be with the 4th end 322 close to the plane phase of fourth hole
It is mutually parallel.Fourth hole can be formed along the direction of the column body section by installing a column on the 4th end 322,
So that the aperture direction of fourth hole is parallel to each other relative to ducted body.The diameter of fourth hole can be greater than the second gag lever post
420 diameter, it is assumed that the diameter of the second gag lever post 420 is B, and the diameter of third through-hole is C4, then C4 > B.Due to fourth hole
Diameter be greater than the second gag lever post 420 diameter, then the second gag lever post 420 can slide in fourth hole, this to be arranged
The second support arm 320 outside the second gag lever post 420 can be moved along the second gag lever post 420.When object 140 to be penetrated from
After ejecting end 110 projects, it is mobile relative to the second support arm 320 that generated back pressure can push emission element 100, then leads to
The setting third spring between third fastening end 421 and the second mounting hole 323 is crossed, in the 4th fastening end 422 and the second mounting hole
4th spring is set between 323, by the deformation of third spring and/or the 4th spring, to absorb energy caused by object 140 to be penetrated
Amount.To overcome the back pressure damage unmanned plane and load-supporting part 300 that generate when penetrating object 140 and projecting, reaches and be conducive to nothing
The technical effect that man-machine normal flight and 300 joint unit 200 of load-supporting part work normally.
Continuing with being a kind of grenade instrumentation for unmanned plane provided in an embodiment of the present invention referring to Fig. 1 and Fig. 5, Fig. 1
Overall structure diagram, Fig. 5 are that the embodiment of the present invention provides a kind of front view schematic diagram of grenade instrumentation for unmanned plane.The
Three through-holes and fourth hole can be different relative to the distance of the first interface 210, such as third through-hole is than fourth hole distance
The distance of first interface 210 is farther, then makes have difference in height between third through-hole and fourth hole, passes through the difference in height
It is heeling condition relative to ground after the second gag lever post 420 can be made to pass through third through-hole and fourth hole.Second limit
Position bar 420 can be 30 ° -60 ° relative to the tilt angle on ground.If inclination of i.e. the first gag lever post 410 relative to ground
Angle is W2, then 30 °≤W2≤60 °, can make angle model of the sky portion 123 relative to the second interface 230 among the above in this way
It encloses and can be 30 ° -60 °.
After the second gag lever post 420 passes through third through-hole and fourth hole, it is assumed that by third through-hole extended line and
P2 point is intersected at by the extended line of fourth hole, is connected by P2 point, third through-hole with fourth hole and forms a right angle trigonometry
Shape, the second gag lever post 420 across third through-hole and fourth hole part are the bevel edge of the right angled triangle.Third through-hole and
The right-angle side that P2 point is formed is Y3, and the right-angle side that fourth hole and P1 point are formed is Y4, then Y4:Y3=Z2, then the range of Z2 can
To be (1/2)≤Z2≤(√ 3)/2.Due to (1/2)≤Z2≤(√ 3)/2, when the second gag lever post 420 passes through third through-hole and the
After four through-holes, the second gag lever post 420 is heeling condition relative to ground, and hollow portion 123 can be made relative to the first linking
The angular range in face 210 can be 30 ° -60 °, then ejecting end 110 can then make than handling end 130 closer to ground at this time
Obtaining the object to be penetrated 140 projected from ejecting end 110 can be relative to the first shooting downwards of interface 210, and it is right in the sky to not only improve
Glass at door and window is aimed at, and the recoil for being conducive to generate object 140 to be penetrated tilts upward, and it is downward to overcome recoil
When, it will push the technological deficiency that unmanned plane decline bumps against ground or metope.Make unmanned plane safety, smooth flight to reach,
And the technical effect that object 140 to be penetrated steadily projects.
For damping part 400:
The damping part 400 may include the first gag lever post 410, the second gag lever post 420,430 and of the first elastic parts
Second elastic parts 440.
First gag lever post 410 can be set the first fastening end 411 and the second fastening end 412, and the first fastening end 411 can be with
It is fixedly connected with the first pedestal 124, and the second fastening end 412 can be fixedly connected with the second pedestal 125, the first gag lever post
410 can pass through the first mounting hole 313；Third fastening end 421 and the 4th fastening end 422 has can be set in second gag lever post 420,
Third fastening end 421 can be fixedly connected with third pedestal 126, and the 4th fastening end 422 can be with the 4th pedestal 127
It is fixedly connected, the second gag lever post 420 can pass through second mounting hole 323.
First elastic parts 430 can be set in the outside of first gag lever post 410, and the first elastic parts 430 can be with
Between the first fastening end 411 and the second fastening end 412；Second elastic parts 440 can be set in the second gag lever post 420
Outside, the second elastic parts 440 can be between third fastening end 421 and the 4th fastening ends 422.Wherein, first is tight
Fixed end 411 and the second fastening end 412 can be the both ends of the first gag lever post 410 opposition, third fastening end 421 and the 4th fastening end
422 can be the both ends of the second gag lever post 420 opposition.
First elastic parts 430 may include the first spring and second spring, and the first spring can be set in described first
The outside of gag lever post 410, and second spring can be set in the outside of the first gag lever post 410；Wherein, the first spring can position
Between the first fastening end 411 and the first mounting hole 313, and second spring can be located at the second fastening end 412 and the first peace
It fills between hole 313.Second elastic parts 440 may include third spring and the 4th spring, and third spring can be set in second
The outside of gag lever post 420, and the 4th spring can be set in the outside of the second gag lever post 420；Wherein, third spring can position
Between third fastening end 421 and the second mounting hole 323, and the 4th spring can be located at the 4th fastening end 422 and the second peace
It fills between hole 323.
Referring to Figure 1 and Fig. 6, Fig. 1 be a kind of grenade instrumentation for unmanned plane provided in an embodiment of the present invention entirety
Structural schematic diagram, Fig. 6 are that the embodiment of the present invention provides a kind of rearview schematic diagram of grenade instrumentation for unmanned plane.First limit
Position bar 410 and/or the second gag lever post 420, which can be, is rendered as cylindrical metal, rod-shaped stick.First fastening end 411 and second is tight
Fixed end 412 can be the both ends of the first gag lever post 410 respectively, and third fastening end 421 and the 4th fastening end 422 can be respectively
The both ends of two gag lever posts 420.
First fastening end 411 of the first gag lever post 410 can be fixedly connected with the first pedestal 124, the first gag lever post 410
The second fastening end 412 be fixedly connected with the second pedestal 125, to make the tube body in the first gag lever post 410 and emission element 100
120 are fixed to each other.The third fastening end 421 of second gag lever post 420 is fixedly connected with the 4th pedestal 127, the second gag lever post 420
The 4th fastening end 422 be fixedly connected with the 4th pedestal 127, to make the tube body in the second gag lever post 420 and emission element 100
120 are fixed to each other.Then the first gag lever post 410 and the second gag lever post 420 is made to be separately fixed at the two sides of tube body 120, by tube body
120 are fixed between the first gag lever post 410 and the second gag lever post 420.
In order to be set in outside and the first elastic parts 430 packet of the first gag lever post 410 to the first elastic parts 430
It includes the first spring and second spring is explained in detail, following two embodiment is now provided and is described in detail respectively:
The first embodiment.It can be arranged with the first spring in the outside of the first gag lever post 410, the first spring can position
Between the first fastening end 411 and the first mounting hole 313.One end of first spring can be clamped with the first fastening end 411, i.e., by
One end of the first spring is kept out in first fastening end 411, is fixed on one end of the first spring at the first fastening end 411.First
The other end of spring can be clamped with the second end 312 for being provided with the first mounting hole 313, i.e., keep out first by second end 312
The other end of spring is fixed on the other end of the first spring at second end 312.Make the both ends of the first spring respectively in this way and
First fastening end 411, second end 312 are fixedly connected, when tube body 120 drives the first gag lever post 410 to move along the first mounting hole 313
When dynamic, also drive the first spring that elastic deformation occurs, it is mobile to absorb tube body 120 due to the elastic deformation that the first spring occurs
The kinetic energy of generation reduces the generated mechanical energy pair when penetrating object 140 and projecting to reach the operating position of stable tube body 120
The damage of load-supporting part 300, joint unit 200, or influence the normal operating conditions of load-supporting part 300, joint unit 200；Together
When, adverse effect when also reducing to unmanned plane stabilized flight or hovering.
Second of embodiment.It can be arranged with second spring in the outside of the first gag lever post 410, second spring can position
Between the second fastening end 412 and the first mounting hole 313.One end of second spring can be clamped with the second fastening end 412, i.e., by
One end of second spring is kept out in second fastening end 412, is fixed on one end of second spring at the second fastening end 412.Second
The other end of spring can be clamped with the second end 312 for being provided with the first mounting hole 313, i.e., keep out second by second end 312
The other end of spring is fixed on the other end of second spring at second end 312.Make the both ends of second spring respectively in this way and
Second fastening end 412, second end 312 are fixedly connected, when tube body 120 drives the first gag lever post 410 to move along the first mounting hole 313
When dynamic, also drive second spring that elastic deformation occurs, it is mobile to absorb tube body 120 due to the elastic deformation that second spring occurs
The kinetic energy of generation reduces the generated mechanical energy pair when penetrating object 140 and projecting to reach the operating position of stable tube body 120
The damage of load-supporting part 300, joint unit 200, or influence the normal operating conditions of load-supporting part 300, joint unit 200；Together
When, adverse effect when also reducing to unmanned plane stabilized flight or hovering.
Continuing with being a kind of grenade instrumentation for unmanned plane provided in an embodiment of the present invention referring to Fig. 1 and Fig. 6, Fig. 1
Overall structure diagram, Fig. 6 are that the embodiment of the present invention provides a kind of rearview schematic diagram of grenade instrumentation for unmanned plane.For
The outside of second gag lever post 420 is set in the second elastic parts 440 and second elastic parts 440 includes third spring
It is explained in detail with the 4th spring, following two embodiment is now provided and is described in detail respectively:
The first embodiment.It can be arranged with third spring in the outside of the second gag lever post 420, third spring can position
Between third fastening end 421 and the second mounting hole 323.One end of third spring can be clamped with third fastening end 421, i.e., by
One end of third spring is kept out in third fastening end 421, is fixed on one end of third spring at third fastening end 421.Third
The other end of spring can be clamped with the 4th end 322 for being provided with the second mounting hole 323, i.e., keep out third by the 4th end 322
The other end of spring is fixed on the other end of third spring at the 4th end 322.Make the both ends of third spring respectively in this way and
Third fastening end 421, the 4th end 322 are fixedly connected, when tube body 120 drives the second gag lever post 420 to move along the second mounting hole 323
When dynamic, also drive third spring that elastic deformation occurs, it is mobile to absorb tube body 120 due to the elastic deformation that third spring occurs
The kinetic energy of generation reduces the generated mechanical energy pair when penetrating object 140 and projecting to reach the operating position of stable tube body 120
The damage of load-supporting part 300, joint unit 200, or influence the normal operating conditions of load-supporting part 300, joint unit 200；Together
When, adverse effect when also reducing to unmanned plane stabilized flight or hovering.
Second of embodiment.It can be arranged with the 4th spring in the outside of the second gag lever post 420, the 4th spring can position
Between the 4th fastening end 422 and the second mounting hole 323.One end of 4th spring can be clamped with the 4th fastening end 422, i.e., by
One end of the 4th spring is kept out in 4th fastening end 422, is fixed on one end of the 4th spring at the 4th fastening end 422.4th
The other end of spring can be clamped with the 4th end 322 for being provided with the second mounting hole 323, i.e., keep out the 4th by the 4th end 322
The other end of spring is fixed on the other end of the 4th spring at the 4th end 322.Make the both ends of the 4th spring respectively in this way and
4th fastening end 422, the 4th end 322 are fixedly connected, when tube body 120 drives the second gag lever post 420 to move along the second mounting hole 323
When dynamic, also drive the 4th spring that elastic deformation occurs, it is mobile to absorb tube body 120 due to the elastic deformation that the 4th spring occurs
The kinetic energy of generation reduces the generated mechanical energy pair when penetrating object 140 and projecting to reach the operating position of stable tube body 120
The damage of load-supporting part 300, joint unit 200, or influence the normal operating conditions of load-supporting part 300, joint unit 200；Together
When, adverse effect when also reducing to unmanned plane stabilized flight or hovering.
First spring and second spring can all be rendered as cylinder, and the diameter of the first spring can be the straight of second spring
Twice of diameter assumes that the diameter of the first spring is P1, the diameter of second spring is P2, then P1=2*P2.Due to the first spring
Diameter be twice of diameter of second spring, when recoil pushes the first spring and elastic deformation occurs for second spring, the
One spring can be more with respect to second spring absorption recoil energy, then reduce tube body 120 relative to the first mounting hole
313 mobile distances and speed are conducive to the flight for stablizing unmanned plane so that reaching reduces recoil to the impact force of unmanned plane
State improves the technical effect of shooting accuracy.
Third spring and the 4th spring can all be rendered as cylinder, and the diameter of third spring can be the straight of the 4th spring
The diameter of twice of diameter, i.e. hypothesis third spring is P3, and the diameter of the 4th spring is P4, then P3=2*P4.Due to third spring
Diameter be twice of diameter of the 4th spring, when recoil pushes third spring and elastic deformation occurs for the 4th spring, the
Three springs can be more with respect to the 4th spring absorption recoil energy, then reduce tube body 120 relative to the second mounting hole
323 mobile distances and speed are conducive to the flight for stablizing unmanned plane so that reaching reduces recoil to the impact force of unmanned plane
State improves the technical effect of shooting accuracy.
In practical applications, when fire occurs for high residential building, object 140 to be penetrated can be packed into ejecting end 110 in advance, it will
First interface 210 is fixedly connected with the bottom of unmanned aerial vehicle body in joint unit 200.Flight system is passed through by ground handling operator
It unites to issue to unmanned plane and instruct, unmanned plane is made to take off to the story height that fire occurs.Then by being arranged in ejecting end 110
The floor external circumstances of fire occur to watch for image pick-up device on three positioning areas 170, when finding the external windows of fiery residence floor,
Unmanned plane can be hovered to window.Emitted again by being located at the first laser in ejecting end 110 on first positioning area 150
Device, second laser transmitter on the second positioning area 160 aim at the glass of window, can choose the edge to glass
Place is aimed at, such as is aimed at positioned at the junction of glass and wall, lesser shock strength can be used in this way to hit
Cullet.If by the spatial position of mobile unmanned plane, so that first laser transmitter and second laser transmitter are targeted to window
The glass of mouth then can issue shooting instruction to unmanned plane by ground handling operator.At this point, being located at outside baffle 180
Control switch 132 is closed, since control switch 132 and object to be penetrated 140 connect, then the closure of control switch 132 can excite to
It penetrates object 140 and reaches ejecting end 110 along the first trajectory 181 and/or the second trajectory 182 from entering bullet mouth 131, it is high from ejecting end 110
Rapid fire goes out.The glass at window can be smashed by the powerful kinetic energy of object 140 to be penetrated, has then got through and has been located in fire floor room
The window that indicator of trapped personnel is connected to the external world, allows indoor indicator of trapped personnel to escape from window；It is also possible that being located at room
Outer fire fighter is entered the room from window by equipment such as aerial ladders and is succoured.To reach by unmanned plane with transmitting
Component 100, joint unit 200, load-supporting part 300 and damping part 400.Now to emission element 100, joint unit 200, load-bearing
Component 300 and the flight of damping part 400 make object to be penetrated at the high residential building door and window that fire occurs, then through control switch 132
140 shattered glass door and windows carry out the technical effect for helping the indicator of trapped personnel in high residential building to escape in time.
The present invention provides a kind of docking damping device for unmanned plane, by the way that the ontology of joint unit and first to be connected
Face is fixedly connected, and the second interface of joint unit is fixedly connected with ontology, on the second interface be arranged first clamping seat and
Second clamping seat, makes ontology between the first interface and second interface, the first clamping seat and the second clamping seat phase
Centrosymmetric distribution for the second interface, the first interface and the second interface are symmetrical relative to ontology.Due to
The first interface and fuselage of joint unit are detachably connected, if emission element and/or joint unit damage, do not need to replace
Unmanned plane, it is only necessary to replace emission element and/or joint unit, object of the unmanned plane in time to target area can be enable
(such as glass) is shot at.Meanwhile by the way that the first fastening end in the first gag lever post is fixedly connected with the first pedestal, the first limit
The second fastening end is fixedly connected with the second pedestal in bar, and the first gag lever post is made to pass through the first mounting hole.By in the second gag lever post
Three fastening ends are fixedly connected with third pedestal, and the 4th fastening end is fixedly connected with the 4th pedestal in the second gag lever post, make the second limit
Position bar passes through the second mounting hole.And the first elastic parts is set in the outside of the first gag lever post, makes the first elastic parts position
Between the first fastening end and second fastening end；Second elastic parts is set in the outside of the second gag lever post, makes second
Elastic parts is between third fastening end and the 4th fastening end.In actual operation, emitting object to be penetrated to target area (such as
Window) be shot at during, generated recoil will force the first elastic parts and the second elastic parts to emit elastic shape
Become, the ability that recoil is generated is converted into the elastic potential energy of the first elastic parts and the second elastic parts, after then weakening
Adverse effect of the recoil to unmanned plane.To reach the maintenance cost for reducing unmanned plane shooting component；When being conducive to eliminate shooting
The recoil of generation enables unmanned plane to help indicator of trapped personnel to escape in time the adverse effect of unmanned plane, and rescue high level is lived
The technical effect of indicator of trapped personnel in residence.
It should be noted last that the above specific embodiment is only used to illustrate the technical scheme of the present invention and not to limit it,
Although being described the invention in detail referring to example, those skilled in the art should understand that, it can be to the present invention
Technical solution be modified or replaced equivalently, without departing from the spirit and scope of the technical solution of the present invention, should all cover
In the scope of the claims of the present invention.
Claims (10)
1. a kind of docking damping device for unmanned plane, the unmanned plane includes fuselage, which is characterized in that described to be used for nobody
The docking damping device of machine includes:
Joint unit, the joint unit include:
First interface, first interface and the fuselage are detachably connected；
Ontology, the ontology are fixedly connected with first interface；
Second interface, second interface are fixedly connected with the ontology, are provided with the first card on second interface
Joint chair and the second clamping seat；
Wherein, the ontology is between first interface and second interface；The first clamping seat and described
Centrosymmetric distribution of the second clamping seat relative to second interface；First interface and second interface
It is symmetrical relative to the ontology；
Damping part, the damping part include:
First gag lever post, first gag lever post are provided with the first fastening end and the second fastening end, first fastening end and
One pedestal is fixedly connected, and second fastening end is fixedly connected with the second pedestal, and first gag lever post passes through the first installation
Hole；
Second gag lever post, second gag lever post are provided with third fastening end and the 4th fastening end, the third fastening end and
Three pedestals are fixedly connected, and the 4th fastening end is fixedly connected with the 4th pedestal, and second gag lever post passes through the second installation
Hole；
First elastic parts, first elastic parts are set in the outside of first gag lever post, first elastic parts
Between first fastening end and second fastening end；
Second elastic parts, second elastic parts are set in the outside of second gag lever post, second elastic parts
Between the third fastening end and the 4th fastening end；
Wherein, first fastening end and second fastening end are the both ends of the first gag lever post opposition, and the third is tight
Fixed end and the 4th fastening end are the both ends of the second gag lever post opposition.
2. being used for the docking damping device of unmanned plane as described in claim 1, which is characterized in that pair for unmanned plane
Connecing damping device includes:
First elastic parts includes the first spring and second spring, and first spring is set in first gag lever post
Outside, and the second spring is set in the outside of first gag lever post.
3. being used for the docking damping device of unmanned plane as claimed in claim 2, which is characterized in that pair for unmanned plane
Connecing damping device includes:
First spring is between first fastening end and first mounting hole.
4. being used for the docking damping device of unmanned plane as claimed in claim 3, which is characterized in that pair for unmanned plane
Connecing damping device includes:
The second spring is between second fastening end and first mounting hole.
5. being used for the docking damping device of unmanned plane as described in claim 1, which is characterized in that pair for unmanned plane
Connecing damping device includes:
Second elastic parts includes third spring and the 4th spring, and the third spring is set in second gag lever post
Outside, and the 4th spring is set in the outside of second gag lever post.
6. being used for the docking damping device of unmanned plane as claimed in claim 5, which is characterized in that pair for unmanned plane
Connecing damping device includes:
The third spring is between the third fastening end and second mounting hole.
7. being used for the docking damping device of unmanned plane as claimed in claim 6, which is characterized in that pair for unmanned plane
Connecing damping device includes:
4th spring is between the 4th fastening end and second mounting hole.
8. being used for the docking damping device of unmanned plane as described in claim 1, which is characterized in that pair for unmanned plane
Connecing damping device includes:
First interface is engraved structure.
9. being used for the docking damping device of unmanned plane as claimed in claim 8, which is characterized in that pair for unmanned plane
Connecing damping device includes:
Second interface is engraved structure.
10. be used for the docking damping device of unmanned plane as claimed in claim 9, which is characterized in that described for unmanned plane
Docking damping device includes:
The ontology is engraved structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810595789.8A CN108945458A (en) | 2018-06-11 | 2018-06-11 | Docking damping device for unmanned plane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810595789.8A CN108945458A (en) | 2018-06-11 | 2018-06-11 | Docking damping device for unmanned plane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108945458A true CN108945458A (en) | 2018-12-07 |
Family
ID=64488418
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810595789.8A Pending CN108945458A (en) | 2018-06-11 | 2018-06-11 | Docking damping device for unmanned plane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108945458A (en) |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH08280834A (en) * | 1995-04-12 | 1996-10-29 | Kawasaki Heavy Ind Ltd | Method for guiding fire-extinguishing shell |
| CN204161623U (en) * | 2014-09-05 | 2015-02-18 | 徐伟佳 | A kind of unmanned plane air attack bullet dispenser |
| CN106945836A (en) * | 2017-03-24 | 2017-07-14 | 西安旋飞电子科技有限公司 | A kind of fire-fighting unmanned plane |
-
2018
- 2018-06-11 CN CN201810595789.8A patent/CN108945458A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH08280834A (en) * | 1995-04-12 | 1996-10-29 | Kawasaki Heavy Ind Ltd | Method for guiding fire-extinguishing shell |
| CN204161623U (en) * | 2014-09-05 | 2015-02-18 | 徐伟佳 | A kind of unmanned plane air attack bullet dispenser |
| CN106945836A (en) * | 2017-03-24 | 2017-07-14 | 西安旋飞电子科技有限公司 | A kind of fire-fighting unmanned plane |
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Application publication date: 20181207 |
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