CN206624006U - Battery quick fixation structure and aircraft - Google Patents
Battery quick fixation structure and aircraft Download PDFInfo
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- CN206624006U CN206624006U CN201720352024.2U CN201720352024U CN206624006U CN 206624006 U CN206624006 U CN 206624006U CN 201720352024 U CN201720352024 U CN 201720352024U CN 206624006 U CN206624006 U CN 206624006U
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- fixation structure
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- 238000003825 pressing Methods 0.000 claims description 3
- 238000010276 construction Methods 0.000 abstract description 3
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- 230000005611 electricity Effects 0.000 description 6
- 230000005484 gravity Effects 0.000 description 4
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
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Abstract
The utility model is applied to battery fastening structure technical field, there is provided a kind of battery quick fixation structure and aircraft.For battery quick fixation structure suitable for aircraft, aircraft includes fuselage, and battery quick fixation structure is used to battery-disassembled being installed in the mounting groove of fuselage；The horizontal fastening structure that battery quick fixation structure includes being used to limit battery transverse shifting, the electric connection structure for making battery and fuselage electric connection and the longitudinal fastening structure for being arranged on electric connection structure and being vertically moved for limiting battery；Horizontal fastening structure guides battery container so that battery main body is inserted in mounting groove in the lump together with battery container.The battery quick fixation structure is used to be installed in the mounting groove of fuselage by battery-disassembled, when battery is installed on fuselage, one end of battery is inserted in mounting groove from top to bottom, and battery is fixed on fuselage using horizontal fastening structure and longitudinal fastening structure, can rapidly dismounting cell, simple in construction and convenient disassembly.
Description
Technical field
The utility model belongs to battery fastening structure technical field, more particularly to a kind of battery quick fixation structure and with should
The aircraft of battery quick fixation structure.
Background technology
For for agro-farming management, the agriculture unmanned vehicle sprayed insecticide, typically all can on the fuselage of aircraft
It is provided for depositing the medicine-chest of decoction and the battery of electric energy is provided.In order to ensure the endurance of unmanned plane, the capacity of battery
Need to reach certain numerical requirements, in addition, in order to ensure sustainable operation, it is necessary to change reserve battery.
However, in existing unmanned vehicle, battery is moved horizontally with reality toward generally use when installing on fuselage
The mode now installed, need to overcome gravity to install because battery weight is heavier, during installation, very big inconvenience is caused to installation.
Utility model content
The purpose of this utility model is to provide a kind of battery quick fixation structure, it is intended to solves battery in the prior art and installed
Cheng Zhongxu overcomes battery gravity and the technical problem of very big inconvenience is brought to installation.
The utility model is achieved in that a kind of battery quick fixation structure, and suitable for aircraft, the aircraft includes
Fuselage, the battery quick fixation structure are used to be installed on battery-disassembled in the mounting groove of the fuselage, and the battery includes electricity
Tank main body and the battery container being coated on outside the battery main body；The battery quick fixation structure includes being used to limit the battery
The horizontal fastening structure of transverse shifting, for making the electric connection structure and be arranged at that the battery is electrically connected with the fuselage
On the electric connection structure and for limiting longitudinal fastening structure that the battery vertically moves；The horizontal fastening structure is set
In on the battery container and the mounting groove inwall, and guide the battery container with by the battery main body together with the electricity
Pond housing is inserted in the mounting groove in the lump；The electric connection structure is arranged at the battery container and the mounting groove inwall
On.
Further, the horizontal fastening structure is including for guiding the guide frame of the battery disassembly and assembly and for inciting somebody to action
The buckle structure that the battery container snaps connection with the guide frame.
Further, the guide frame include along the mounting groove inwall and in above-below direction extension guide pad with
And be arranged on the battery container and end has the guide groove of introducing port, the guide pad is when dismounting the battery along institute
Guide groove is stated to slide up and down.
Further, the width of the introducing port along end to the guide groove in be gradually reduced, the guide pad is provided with
The guide ramp coordinated with the introducing port, the guide ramp are located at the upper end of the guide pad.
Further, the guide frame includes being used for the damping that damping action is formed to the battery in disassembly process
Part, the damping piece are located on the guide pad and interacted with the groove bottom of the guide groove.
Further, the damping piece is to be rotatablely installed to be provided with the damping wheel on the guide pad, the guide pad
It is pivotally connected and the link slot of damping wheel described in partial receipt, the groove bottom of the guide groove is held in the damping wheel and relative to institute
Guide pad is stated to move up and down.
Further, the buckle structure includes being arranged at the buckle slot of the guide pad upper end and is convexly equipped in described
On battery container and the jut that is fastened in the buckle slot, upper wall surface of the jut along the guide groove is described in
Introducing port side protrudes extension.
Further, the electric connection structure includes being fixed on the battery container and with the battery main body electrically connecting
The battery electrical connection section connect and the fuselage for being fixed on the mounting groove inwall and being electrically connected with the battery electrical connection section
Electrical connection section, the battery electrical connection section pass through the mutually electrical grafting of pin with the fuselage electrical connection section.
Further, the electric connection structure also includes relative to being arranged at the pin front and rear sides with to the battery
Electrical connection section and the fuselage electrical connection section are mutually inserted the outer barricade for playing positioning action and interior catch.
Further, longitudinal fastening structure includes in the battery electrical connection section and the fuselage electrical connection section one
Upper set clamping roller bearing and the clinching set by another, the clinching are connected on the clamping roller bearing.
Further, the clamping roller bearing is articulated on the outer barricade, and the clinching is arranged at the battery connection part
Go up and the cover plate including being movably connected on the battery electrical connection section, along the cover plate inner bulge and be fastened on the clamping
Buckle projection and the press section upwardly extended along the cover panel end on roller bearing, the buckle is raised to be connected with the press section
Connect, the buckle projection is opened when pressing the press section from the clamping roller bearing.
Further, the battery container includes being oppositely arranged and being mutually permanently connected so that the battery main body to be coated on
Lower house and upper shell therein, the battery electrical connection section are fixed on the one side of the upper shell.
Further, the battery also includes being installed on the upper shell top surface and the handle extended in left-right direction, institute
State the centre position that handle is arranged at the upper shell top surface width.
The utility model additionally provides a kind of aircraft, including fuselage, the battery for providing electric energy, multiple around described
The circumferentially spaced wing components of fuselage and the battery for the battery-disassembled to be installed on the fuselage are fast
Assembling structure, the battery quick fixation structure are above-mentioned battery quick fixation structure.
Further, the fuselage includes fuselage body and the support frame being fixed on the fuselage body, the branch
Support encloses the mounting groove to form a side opening, and the mounting groove is located at the rear portion of the fuselage body.
Further, the left side wall of support frame as described above and at least one of right side wall are provided with a laterally fastening
Structure, the electric connection structure is on the rear side wall of support frame as described above.
The utility model has the technical effect that relative to prior art：The battery quick fixation structure is used for the battery is removable
It is installed on unloading in the mounting groove of the fuselage, specifically, using being arranged on the battery container and the mounting groove inwall
The horizontal fastening structure limit the transverse shifting of the battery, meanwhile, utilize the institute being arranged on the electric connection structure
Longitudinal fastening structure limitation battery is stated to vertically move, so, when the battery is installed on the fuselage, the electricity
The one end in pond is inserted in the mounting groove from top to bottom, and utilizes the horizontal fastening structure and longitudinal fastening structure by institute
Battery is stated to be fixed on the fuselage；When the battery is unloaded from the fuselage, the horizontal fastening structure and institute are opened
Longitudinal fastening structure is stated, limitation is limited and vertically move with the transverse shifting released to the battery, so as to rapidly will
The battery takes out from the fuselage.Therefore, the battery, simple in construction and convenient disassembly can rapidly be dismounted.
Brief description of the drawings
In order to illustrate more clearly of the technical scheme of the utility model embodiment, below will to the utility model embodiment or
The required accompanying drawing used is briefly described in description of the prior art, it should be apparent that, drawings described below is only
Some embodiments of the utility model, for those of ordinary skill in the art, on the premise of not paying creative work,
Other accompanying drawings can also be obtained according to these accompanying drawings.
Fig. 1 is the installation diagram that the battery is installed on fuselage by the battery quick fixation structure that the utility model embodiment provides；
Fig. 2 is the exploded view for the battery quick fixation structure that the utility model embodiment provides；
Fig. 3 is the side view diagram for the battery quick fixation structure that the utility model embodiment provides, and has intercepted part fuselage；
Fig. 4 is sectional view of the battery quick fixation structure along a direction in Fig. 3；
Fig. 5 is another view for the battery quick fixation structure that the utility model embodiment provides, and has intercepted part fuselage；
Fig. 6 is sectional view of the battery quick fixation structure along a direction in Fig. 5；
Fig. 7 is the structural representation for the aircraft that the utility model embodiment provides；
Fig. 8 is the partial enlarged drawing of VIII in Fig. 7；
Fig. 9 is the partial enlarged drawing of IX in Fig. 7.
Description of reference numerals：
Embodiment
Embodiment of the present utility model is described below in detail, the example of the embodiment is shown in the drawings, wherein from beginning
Same or similar element is represented to same or similar label eventually or there is the element of same or like function.Below by ginseng
The embodiment for examining accompanying drawing description is exemplary, it is intended to for explaining the utility model, and it is not intended that to the utility model
Limitation.
In description of the present utility model, it is to be understood that term " length ", " width ", " on ", " under ", " preceding ",
The orientation or position relationship of the instruction such as " rear ", "left", "right", " vertical ", " level ", " top ", " bottom " " interior ", " outer " are based on attached
Orientation or position relationship shown in figure, it is for only for ease of and describes the utility model and simplify to describe, rather than instruction or hint
Signified device or element must have specific orientation, with specific azimuth configuration and operation, therefore it is not intended that to this
The limitation of utility model.
In addition, term " first ", " second " are only used for describing purpose, and it is not intended that instruction or hint relative importance
Or the implicit quantity for indicating indicated technical characteristic.Thus, define " first ", the feature of " second " can be expressed or
Implicitly include one or more this feature.In description of the present utility model, " multiple " are meant that two or two
More than, unless otherwise specifically defined.
In the utility model, unless otherwise clearly defined and limited, term " installation ", " connected ", " connection ", " Gu
It is fixed " etc. term should be interpreted broadly, for example, it may be fixedly connected or be detachably connected, or integrally；Can be
Mechanically connect or electrically connect；Can be joined directly together, can also be indirectly connected by intermediary, can be two
The connection of element internal or the interaction relationship of two elements.For the ordinary skill in the art, can basis
Concrete condition understands concrete meaning of the above-mentioned term in the utility model.
In order that the purpose of this utility model, technical scheme and advantage are more clearly understood, below in conjunction with accompanying drawing and implementation
Example, the utility model is further elaborated.
Fig. 1 to Fig. 7 is refer to, the battery quick fixation structure that the utility model embodiment provides is described suitable for aircraft
Aircraft includes fuselage 20, and the battery quick fixation structure is used for the mounting groove 22 that battery 30 is removably mounted to the fuselage 20
Interior, the battery 30 includes battery main body 36 and the battery container 32 being coated on outside the battery main body 36；The battery is fast
Assembling structure include be used for limit the transverse shifting of battery 30 horizontal fastening structure (not indicating), for make the battery 30 with
The electric connection structure (not indicating) and be arranged on the electric connection structure and be used to limit institute that the fuselage 20 is electrically connected with
State longitudinal fastening structure (not indicating) that battery 30 vertically moves；The horizontal fastening structure is arranged at the He of battery container 32
On the inwall of mounting groove 22, and guide the battery container 32 with by the battery main body 36 together with the battery container 32 1
And it is inserted in the mounting groove 22；The electric connection structure is arranged at battery container 32 and the mounting groove 22 inwall
On.
The battery quick fixation structure that the utility model embodiment provides is described for the battery 30 to be removably installed in
In the mounting groove 22 of fuselage 20, specifically, described in being arranged on battery container 32 and the mounting groove 22 inwall
Horizontal fastening structure limits the transverse shifting of the battery 30, meanwhile, it is described vertical on the electric connection structure using being arranged at
The battery 30 is limited to fastening structure to vertically move, it is so, described when the battery 30 is installed on the fuselage 20
One end of battery 30 is inserted in the mounting groove 22 from top to bottom, and fastens knot using the horizontal fastening structure and the longitudinal direction
The battery 30 is fixed on the fuselage 20 by structure；When the battery 30 is unloaded from the fuselage 20, the horizontal stroke is opened
To fastening structure and longitudinal fastening structure, limitation is limited and vertically moves with the transverse shifting released to the battery 30,
So as to which rapidly the battery 30 is taken out from the fuselage 20.Therefore, the battery 30 can be rapidly dismounted, is tied
Structure is simple and convenient disassembly.
In this embodiment, the above-below direction along figure of battery 30 is dismounted.
In this embodiment, the electric connection structure is used to be electrically connected with the battery 30 and the fuselage 20, so that institute
Battery 30 is stated to be powered for each part on the fuselage 20.
In this embodiment, the horizontal fastening structure is arranged on battery container 32 and the mounting groove 22 inwall
On, the battery container 32 and the inwall of the mounting groove 22 are detachably combined, in order to dismount.
Fig. 1 to Fig. 6 is refer to, further, the horizontal fastening structure includes being used to guide what the battery 30 dismounted
Guide frame 10 and the buckle structure (not indicating) for the battery container 32 and the guide frame 10 to be snapped connection.
The battery quick fixation structure is installed on institute by setting the guide frame 10 to guide the battery 30 to dismount, to the battery 30
State and positioning and guide effect are played in mounting groove 22, make the installation of the battery 30 more quick and accurate, improve installation effectiveness.
The battery quick fixation structure realizes the dismounting to the battery 30 and the guide frame 10 by setting the buckle structure,
That is, when needing to disassemble on the battery 30, the buckle structure is opened, is led with releasing the battery container 32 with described
Combination to structure 10, and the battery 30 is taken out from the mounting groove 22 along the guide frame 10；When need by institute
When stating battery 30 and being installed in the mounting groove 22, the battery 30 is inserted in the mounting groove 22 and by institute along the vertical direction
The installation site that guide frame 10 directs it to the mounting groove 22 is stated, using the buckle structure by the battery container 32
It is fastened on the guide frame 10, the battery 30 is fixedly connected with the fuselage 20.
Refer to Fig. 1, Fig. 3 and Fig. 8, further, the guide frame 10 include along the inwall of mounting groove 22 and
In above-below direction extension guide pad 12 and be arranged on the battery container 32 and end has the guide groove of introducing port 322
320, the guide pad 12 slides up and down when dismounting the battery 30 along the guide groove 320.The battery quick fixation structure passes through
The guide pad 12 coordinates with the guide groove 320 to play positioning and guiding function to the installation process of battery 30, described
When battery 30 is inserted in the mounting groove 22, the top of the guide pad 12 enters the guide groove through the introducing port 322
In 320, so that the battery 30 moves up and down relative to the guide pad 12, so, front and back also are played to the battery 30
To with left and right directions restriction effect, avoid the battery 30 double swerve in the mounting groove 22.
In this embodiment, the guide pad 12 is fixed on the inwall of mounting groove 22, can adopt the side of being screwed
The mode such as formula or welding realizes fixation, not limited to this.The guide pad 12 is in strip, and along the inwall of mounting groove 22
Above-below direction extends, and is convexly equipped on the inwall of mounting groove 22, and its bearing of trend inserts the mounting groove with the battery 30
22 direction is consistent, to play guide effect to the battery 30.
In this embodiment, the width of the guide pad 12 is slightly not more than the width of the mounting groove 22, with described in guarantee
In sliding process, the guide pad 12 can smoothly slide battery 30 along the mounting groove 22.
Fig. 1, Fig. 2 and Fig. 8 are refer to, further, the width of the introducing port 322 is along end to the guide groove 320
Inside it is gradually reduced, the guide pad 12 is provided with the guide ramp 120 coordinated with the introducing port 322, the guide ramp 120
In the upper end of the guide pad 12.The introducing port 322 is in horn-like, when the battery 30 inserts the mounting groove 22,
The guide pad 12 can be slipped into smoothly in the guide groove 320, ensure the accuracy and rapidity of positioning.The guide pad 12
Upper end the guide ramp 120 is set so that the guide pad 12 is slides quickly into the guide groove 320, ensure that positioning
Accuracy and high efficiency.
In this embodiment, the guide ramp 120 is tilted down by the upper end of the inwall of mounting groove 22.
Fig. 1, Fig. 2 and Fig. 8 are refer to, further, the guide frame 10 includes being used for described in disassembly process
Battery 30 formed damping action damping piece 14, the damping piece 14 be located on the guide pad 12 and with the guide groove 320
Groove bottom interaction.The battery quick fixation structure is by setting the damping piece 14 with during the battery 30 is dismounted
Damping action is produced to the battery 30, plays certain cushioning effect.During the battery 30 is dismounted, the guiding
The groove bottom of groove 320 interacts with the damping piece 14, so generation damping force can be played to the battery 30, to the electricity
Pond 30 produces damping, plays a part of the protection battery 30.
Fig. 2 and Fig. 8 are refer to, further, the damping piece 14 is to be rotatablely installed in the damping on the guide pad 12
Wheel, the guide pad 12 are provided with the link slot 122 of pivot joint and damping wheel described in partial receipt, the bottom land of the guide groove 320
Face is held in the damping wheel and moved up and down relative to the guide pad 12.It is to be appreciated that the wheel face of the damping wheel is dashed forward
For the outer surface of the guide pad 12, to be acted on the groove bottom of the guide groove 320, the damping wheel is rotationally connected with institute
State in link slot 122, during the battery 30 is dismounted, the battery 30 slides relative to the guide pad 12, and institute
State damping wheel to rotate relative to the guide pad 12, so, produced between the groove bottom of the guide groove 320 and the damping wheel
Damping force, the moving direction of the damping force and the battery 30 are effectively protected on the contrary, can slow down the decrease speed of the battery 30
Protect battery 30.
In this embodiment, the width axially along the guide pad 12 of the damping wheel is set, so that the resistance
Buddhist nun's wheel is to damping force direction caused by battery 30 with the moving direction of battery 30 on the contrary, so as to play damping action.
In this embodiment, the quantity of the damping wheel is at least one.When the quantity of the damping wheel is 2 or 2
During the individual above, each damping wheel is along the spaced and parallel setting of the moving direction of battery 30, it is preferable that each damping wheel is equidistantly set
Put.
Fig. 2 to Fig. 4 and Fig. 8 is refer to, further, the buckle structure includes being arranged at the upper end of guide pad 12
The buckle slot 16 in portion and the jut 324 for being convexly equipped on the battery container 32 and being fastened in the buckle slot 16, it is described
Upper wall surface of the jut 324 along the guide groove 320 protrudes towards the side of introducing port 322 to be extended.The battery quick fixation structure
By setting the buckle slot 16 in the upper end of the guide pad 12 and setting the projection on the battery container 32
Portion 324, coordinated using the jut 324 and the buckle slot 16, during so that the battery 30 being moved to precalculated position, to institute
State battery container 32 and play the effect of laterally limiting.
In this embodiment, the jut 324 is arranged on the upper wall surface of the guide groove 320, the buckle slot 16
The upper end of the guide pad 12 is arranged on, and recessed is fastened on the card in the guide ramp 120, the jut 324
When in catching groove 16, limited with the fore-and-aft direction to the battery 30.
Fig. 1 to Fig. 6 and Fig. 9 is refer to, further, the electric connection structure includes being fixed on the battery container 32
The upper and battery electrical connection section 40 that is electrically connected with the battery main body 36 and be fixed on the inwall of mounting groove 22 and with
The fuselage electrical connection section 50 that the battery electrical connection section 40 is electrically connected with, the battery electrical connection section 40 electrically connect with the fuselage
Portion 50 passes through the mutually electrical grafting of pin 52.In the disassembly process of battery 30, the battery electrical connection section 40 and the machine
Body electrical connection section 50 is mutually inserted or departed from grafting, to realize power supply and power-off to the fuselage 20.It is to be appreciated that institute
State battery electrical connection section 40 to be mutually inserted by the pin 52 with the fuselage electrical connection section 50, on the one hand can make the electricity
Pond 30 electrically conducts with the fuselage 20, simple in construction, on the other hand can play certain positioning and restriction effect.
In this embodiment, the pin 52 is arranged on the fuselage electrical connection section 50, and is set in a row；Accordingly,
Electrical contacts that are corresponding with the pin 52 and electrically conducting also are provided with the battery electrical connection section 40.
Fig. 1, Fig. 2 and Fig. 9 are refer to, further, the electric connection structure also includes relative to being arranged at the pin
The outer of positioning action is played to be mutually inserted to the battery electrical connection section 40 and the fuselage electrical connection section 50 in 52 front and rear sides
Barricade 54 and interior catch 56.The battery quick fixation structure by setting the outer barricade 54 respectively in the front and rear sides of the pin 52
With the interior catch 56, so, between the outer barricade 54 and the interior catch 56 formed and supply the He of battery electrical connection section 40
The locating slot that the fuselage electrical connection section 50 is mutually inserted, avoid grafting inaccurate, to ensure quick grafting, and can play certain
Foolproof function.
Preferably, the both ends of the outer barricade 54 are arcuation and centre is straight panel shape, and the interior catch 56 is relative to institute
State outer barricade 54 to set, and be straight panel shape, be less than the width of the outer barricade 54 along the width of the arragement direction of pin 52, from
And foolproof function is played in the grafting to the battery electrical connection section 40 and the fuselage electrical connection section 50.
Fig. 2, Fig. 6 and Fig. 9 are refer to, further, longitudinal fastening structure includes the He of battery electrical connection section 40
A upper set clamping roller bearing 58 and the clinching 42 set by another, the clinching 42 block in the fuselage electrical connection section 50
It is connected on the clamping roller bearing 58.The battery quick fixation structure is coordinated using the clinching 42 with the clamping roller bearing 58, with to peace
The battery 30 for being attached to position plays locking effect, the battery 30 is fixedly mounted in the mounting groove 22, and
The battery 30 is effectively prevented to be shifted over along longitudinal direction.
In this embodiment, longitudinal fastening structure can also be the fastening structure of male-female engagement, not limited to this, with energy
It is enough that the battery 30 locking is advisable.
It is to be appreciated that the clamping roller bearing 58 can be arranged on the battery electrical connection section 40 and the clinching 42
It is arranged on the fuselage electrical connection section 50；Or the clamping roller bearing 58 can be arranged on the fuselage electrical connection section 50
And the clinching 42 is arranged on the battery electrical connection section 40.
Fig. 2, Fig. 6 and Fig. 9 are refer to, further, the clamping roller bearing 58 is articulated on the outer barricade 54, the pressure
Button 42 be arranged on the battery electrical connection section 40 and the cover plate 420 including being movably connected on the battery electrical connection section 40,
Along the inner bulge of cover plate 420 and the buckle projection 422 being fastened on the clamping roller bearing 58 and along the end of the cover plate 420
Hold the press section 424 that upwardly extends, the buckle projection 422 is connected with the press section 424, the buckle projection 422 by
Opened when pressing the press section 424 from the clamping roller bearing 58.It is to be appreciated that the cover plate 420, the buckle are raised
422 and the press section 424 be made by being integrally formed.The cover plate 420 can rotate around the battery electrical connection section 40, institute
State cover plate 420 to be articulated on the battery electrical connection section 40, such as the mode of drive-connecting shaft is set, it is preferable that the buckle is raised
422 and the press section 424 be located at the both sides of the drive-connecting shaft respectively, the cover plate 420 is similar to lever.When the buckle
When projection 422 is fastened on the clamping roller bearing 58, the press section 424 is pressed, the cover plate 420 turns around the drive-connecting shaft
It is dynamic, to drive the buckle projection 422 to depart from the cooperation of the clamping roller bearing 58.
Fig. 1 to Fig. 6 is refer to, further, the battery container 32 includes being oppositely arranged and being mutually permanently connected to incite somebody to action
The battery main body 36 is coated on lower house 326 and upper shell 328 therein, and the battery electrical connection section 40 is fixed on described
On the one side of housing 328.It is to be appreciated that the upper shell 328 and the lower house 326 are screwed and are connected to one
Rise, and the battery main body 36 is played a protective role.
In this embodiment, the guide groove 320 is arranged at least on one side of the lower house 326.Preferably, institute
The two relative side that guide groove 320 is arranged at the lower house 326 is stated, such as in the left and right sides of the lower house 326, institute
Battery electrical connection section 40 is stated to be arranged on the preceding surface of the upper shell 328, with the battery 30 is carried out it is multi-direction limitation and
Positioning.
In this embodiment, still there are the crossbeam being across in the mounting groove 22, the crossbeam and institute on the fuselage 20
State fuselage electrical connection section 50 to be oppositely arranged, the mounting groove 22 is restricted to the size of battery 30, the battery 30 is risen
To limitation and positioning action.
Referring to Fig.1 and 2, further, the battery 30 also includes being installed on the top surface of upper shell 328 and along a left side
The handle 34 of right direction extension, the handle 34 are arranged at the centre position of the top surface width of upper shell 328.The battery
Quick fixation structure carries the battery 30 by setting the handle 34, can realize that one hand is grabbed, and the battery 30 is heavy along its
Force direction is placed and lifted downwards.
During installation, one hand, which is grabbed, carries the handle 34, the battery 30 is placed downwards along its gravity direction, the battery 30
On the guide groove 320 moved down along the guide pad 12, the damping wheel be close to the guide groove 320 groove bottom rolling
It is dynamic, play the purpose for slowing down the decrease speed of battery 30.When the battery 30, which declines, to be moved into place, the buckle is raised
422 are fastened in the buckle slot 16, to limit the movement of the fore-and-aft direction of battery 30；Meanwhile press the press section
424, so as to be that cover plate 420 rotates around the drive-connecting shaft so that the buckle projection 422 is opened and is articulated in the clamping rolling
On axle 58, the battery 30 is fixed on the fuselage 20, now, the battery electrical connection section 40 is electrically connected with the fuselage
Socket part 50 realizes grafting, electrically connects more firm.In the operating process, the gravity of itself of battery 30 is effectively utilized,
So that battery 30 is easier for installation and firm, rapid operation.
Fig. 7 is refer to, the aircraft that the utility model embodiment provides includes fuselage 20, the battery for providing electric energy
30th, it is multiple around the circumferentially spaced wing components 70 of the fuselage 20 and for the battery 30 removably to be installed
Battery quick fixation structure on the fuselage 20, the battery quick fixation structure are above-mentioned battery quick fixation structure.In the present embodiment
The battery quick fixation structure has identical structure with battery quick fixation structure in the various embodiments described above, and role is also identical,
Do not repeat herein.
In this embodiment, the aircraft is by setting the wing components 70 to provide lifting drive.
Fig. 7 is refer to, further, the fuselage 20 includes fuselage body 24 and is fixed on the fuselage body 24
Support frame 26, support frame as described above 26 encloses the mounting groove 22 to form a side opening, and the mounting groove 22 is located at the machine
The rear portion of body body 24.It is to be appreciated that support frame as described above 26 is fixedly connected with the fuselage body 24, and support frame as described above 26
Enclose and set to form the mounting groove 22, the open upper end of the mounting groove 22, described in the battery 30 is from top to bottom inserted
In mounting groove 22.The fuselage electrical connection section 50 is arranged on support frame as described above 26, and is arranged at the rear portion of support frame as described above 26,
A part for the battery 30 is supported on support frame as described above 26 and the battery electrical connection section 40 and the fuselage electrical connection section
50 are electrically connected with.
Fig. 1, Fig. 2 and Fig. 7 are refer to, further, the left side wall of support frame as described above 26 and at least the one of right side wall
Individual to be provided with a horizontal fastening structure, the electric connection structure is on the rear side wall of support frame as described above 26.It can manage
Xie Di, the horizontal fastening structure can be 1 or 2, in the case of two, by the horizontal fastening structure
It is arranged on the left side wall and right side wall of support frame as described above 26, so that there is corresponding guiding the two sides of the battery 30
Locked with fastening so that the battery 30 is more smoothly in moving process and fastens locating effect more preferably.By fuselage electricity
Connecting portion 50 is arranged on the rear side wall of support frame as described above 26, and the battery 30 is lock onto on the fuselage 20.
Fig. 7 is refer to, further, the aircraft also includes being installed on each wing components 70 and for spraying
The shower nozzle 60 of decoction.The aircraft connects the liquid container installed on fuselage 20 by the shower nozzle 60, so that decoction is from described
Shower nozzle 60 is sprayed to the region of required sprinkling, to meet medicine liquid spray requirement.
In this embodiment, the aircraft can be used in agro-farming industry carrying out pesticide spraying or moisture to agricultural product
The activities such as sprinkling irrigation.Certainly, the aircraft can be used for sprinkling of extinguishing fluid etc. in forest fire.
In this embodiment, the power of the shower nozzle 60 can be provided by the wing components 70, can also be separately configured
Motor drives.
Fig. 7 is refer to, further, each wing components 70 include horn 72, the peace being installed on the fuselage 20
Rotor 74 and drive device 76 loaded on the end of horn 72, the drive device 76 drives the rotor 74 to rotate, described
Shower nozzle 60 is arranged at the underface of the drive device 76.It is to be appreciated that the end of each horn 72 is equipped with the He of rotor 74
The drive device 76 for driving rotor 74 to rotate, such as motor, rotor 74 can with the motor axis connection of motor, to make rotor 74
Rotate so as to drive aircraft to be flown.Preferably, the quantity of the wing components 70 is group, i.e., the aircraft is four rotors
74 aircraft, certainly, the quantity of the wing components 70 can also be other quantity, such as aircraft of six rotor 74 etc..
Fig. 7 is refer to, further, the aircraft is also fixedly installed on the fuselage 20 including a pair and to incite somebody to action
The fuselage 20 is suspended on the support foot rest 80 on ground.The aircraft is by setting the support foot rest 80, so that the flight
When ground is parked in device landing, the fuselage 20 is not directly contacted with ground, the damage to the fuselage 20 is prevented, using this to described
Support foot rest 80 plays support and protective effect.
Preferred embodiment of the present utility model is the foregoing is only, it is all at this not to limit the utility model
All any modification, equivalent and improvement made within the spirit and principle of utility model etc., should be included in the utility model
Protection domain within.
Claims (16)
1. a kind of battery quick fixation structure, suitable for aircraft, the aircraft includes fuselage, it is characterised in that the battery
Quick fixation structure is used to be installed on battery-disassembled in the mounting groove of the fuselage；The battery quick fixation structure includes being used to limit
The horizontal fastening structure of the battery transverse shifting, for make the electric connection structure that the battery and the fuselage are electrically connected with
And it is arranged on the electric connection structure and is used to limit longitudinal fastening structure that the battery vertically moves；The battery includes
Battery main body and the battery container being coated on outside the battery main body, the horizontal fastening structure are arranged at the battery container
On the mounting groove inwall, and the battery container is guided so that the battery main body to be plugged in the lump together with the battery container
In in the mounting groove；The electric connection structure is arranged on the battery container and the mounting groove inwall.
2. battery quick fixation structure as claimed in claim 1, it is characterised in that the horizontal fastening structure includes being used to guide institute
State the guide frame of battery disassembly and assembly and the buckle structure for the battery container and the guide frame to be snapped connection.
3. battery quick fixation structure as claimed in claim 2, it is characterised in that the guide frame is included along the mounting groove
On wall and in above-below direction extension guide pad and be arranged on the battery container and end has the guide groove of introducing port,
The guide pad slides up and down when dismounting the battery along the guide groove.
4. battery quick fixation structure as claimed in claim 3, it is characterised in that the width of the introducing port is led along end to described
It is gradually reduced into groove, the guide pad is provided with the guide ramp coordinated with the introducing port, and the guide ramp is positioned at described
The upper end of guide pad.
5. battery quick fixation structure as claimed in claim 3, it is characterised in that the guide frame includes being used for disassembly process
In the battery formed damping action damping piece, the damping piece be located on the guide pad and with the groove of the guide groove
Bottom surface interacts.
6. battery quick fixation structure as claimed in claim 5, it is characterised in that the damping piece is to be rotatablely installed in the guiding
Damping wheel on block, the guide pad are provided with the link slot of pivot joint and damping wheel described in partial receipt, the groove of the guide groove
Bottom surface is held in the damping wheel and moved up and down relative to the guide pad.
7. battery quick fixation structure as claimed in claim 3, it is characterised in that the buckle structure includes being arranged at the guiding
The buckle slot of block upper end and the jut for being convexly equipped on the battery container and being fastened in the buckle slot, the projection
Upper wall surface of the portion along the guide groove protrudes towards the introducing port side to be extended.
8. the battery quick fixation structure as described in claim 1 to 7 any one, it is characterised in that the electric connection structure includes
The battery electrical connection section that is fixed on the battery container and is electrically connected with the battery main body and it is fixed on the installation
The fuselage electrical connection section being electrically connected with groove inwall and with the battery electrical connection section, the battery electrical connection section and the fuselage
Electrical connection section passes through the mutually electrical grafting of pin.
9. battery quick fixation structure as claimed in claim 8, it is characterised in that the electric connection structure also includes relative to setting
In the pin front and rear sides to be mutually inserted to the battery electrical connection section and the fuselage electrical connection section and play positioning action
Outer barricade and interior catch.
10. battery quick fixation structure as claimed in claim 8, it is characterised in that longitudinal fastening structure includes the battery
A upper set clamping roller bearing and the clinching set by another, the clinching in electrical connection section and the fuselage electrical connection section
It is connected on the clamping roller bearing.
11. battery quick fixation structure as claimed in claim 10, it is characterised in that the clamping roller bearing is articulated in the outer barricade
On, the clinching is arranged in the battery connection part and the cover plate including being movably connected on the battery electrical connection section, edge
The cover plate inner bulge and buckle that is fastened on the clamping roller bearing is raised and upwardly extended along the cover panel end
Press section, the buckle is raised to be connected with the press section, and the buckle projection is when pressing the press section from the clamping
Opened on roller bearing.
12. battery quick fixation structure as claimed in claim 8, it is characterised in that the battery container includes being oppositely arranged and phase
Mutually it is fixedly connected so that the battery main body is coated on into lower house and upper shell therein, the battery electrical connection section is fixed on institute
State on the one side of upper shell.
13. battery quick fixation structure as claimed in claim 12, it is characterised in that the battery also includes being installed on the upper casing
Body top surface and the handle extended in left-right direction, the handle are arranged at the centre position of the upper shell top surface width.
14. a kind of aircraft, it is characterised in that battery including fuselage, for providing electric energy, multiple circumferential around the fuselage
Spaced wing components and the battery quick fixation structure for being installed on the battery-disassembled on the fuselage, institute
Battery quick fixation structure is stated as the battery quick fixation structure as described in claim 1 to 13 any one.
15. aircraft as claimed in claim 14, it is characterised in that the fuselage includes fuselage body and is fixed on described
Support frame on fuselage body, support frame as described above enclose the mounting groove to form a side opening, and the mounting groove is positioned at described
The rear portion of fuselage body.
16. aircraft as claimed in claim 15, it is characterised in that the left side wall and right side wall of support frame as described above are extremely
Few one is provided with a horizontal fastening structure, and the electric connection structure is on the rear side wall of support frame as described above.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720352024.2U CN206624006U (en) | 2017-04-05 | 2017-04-05 | Battery quick fixation structure and aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720352024.2U CN206624006U (en) | 2017-04-05 | 2017-04-05 | Battery quick fixation structure and aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206624006U true CN206624006U (en) | 2017-11-10 |
Family
ID=60207211
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720352024.2U Active CN206624006U (en) | 2017-04-05 | 2017-04-05 | Battery quick fixation structure and aircraft |
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| Country | Link |
|---|---|
| CN (1) | CN206624006U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108622397A (en) * | 2018-06-04 | 2018-10-09 | 广州市华科尔科技股份有限公司 | A kind of foldable multi-rotor unmanned aerial vehicle |
| CN109878731A (en) * | 2019-03-31 | 2019-06-14 | 拓攻（南京）机器人有限公司 | A kind of plant protection drone |
-
2017
- 2017-04-05 CN CN201720352024.2U patent/CN206624006U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108622397A (en) * | 2018-06-04 | 2018-10-09 | 广州市华科尔科技股份有限公司 | A kind of foldable multi-rotor unmanned aerial vehicle |
| CN108622397B (en) * | 2018-06-04 | 2024-04-30 | 广州市华科尔科技股份有限公司 | Foldable multi-rotor unmanned aerial vehicle |
| CN109878731A (en) * | 2019-03-31 | 2019-06-14 | 拓攻（南京）机器人有限公司 | A kind of plant protection drone |
| CN109878731B (en) * | 2019-03-31 | 2024-04-30 | 拓攻（南京）机器人有限公司 | Plant protection unmanned aerial vehicle |
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Address after: 510000 Block C, 115 Gaopu Road, Tianhe District, Guangzhou City, Guangdong Province Patentee after: XAG Co., Ltd. Address before: 510000 3A01, No. 1, Cheng Cheng Road, Guangzhou, Guangdong, Tianhe District Patentee before: Guangzhou Xaircraft Technology Co.,Ltd. |
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