CN106275461A - The battery box structure of unmanned plane and unmanned plane - Google Patents
The battery box structure of unmanned plane and unmanned plane Download PDFInfo
- Publication number
- CN106275461A CN106275461A CN201610741737.8A CN201610741737A CN106275461A CN 106275461 A CN106275461 A CN 106275461A CN 201610741737 A CN201610741737 A CN 201610741737A CN 106275461 A CN106275461 A CN 106275461A
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- China
- Prior art keywords
- unmanned plane
- lock core
- fuselage
- locking
- battery compartment
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- 230000015572 biosynthetic process Effects 0.000 claims description 3
- 238000009434 installation Methods 0.000 description 11
- 238000005183 dynamical system Methods 0.000 description 8
- 230000013011 mating Effects 0.000 description 7
- 238000010276 construction Methods 0.000 description 4
- 230000032258 transport Effects 0.000 description 4
- 230000000007 visual effect Effects 0.000 description 4
- 238000010586 diagram Methods 0.000 description 3
- 238000006243 chemical reaction Methods 0.000 description 2
- 230000006835 compression Effects 0.000 description 2
- 238000007906 compression Methods 0.000 description 2
- 230000005611 electricity Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 239000007787 solid Substances 0.000 description 2
- 230000006978 adaptation Effects 0.000 description 1
- 230000003044 adaptive effect Effects 0.000 description 1
- 238000010009 beating Methods 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 210000002421 cell wall Anatomy 0.000 description 1
- 230000002860 competitive effect Effects 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 238000000151 deposition Methods 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000011835 investigation Methods 0.000 description 1
- 208000020442 loss of weight Diseases 0.000 description 1
- 239000007937 lozenge Substances 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 238000000465 moulding Methods 0.000 description 1
- 238000006396 nitration reaction Methods 0.000 description 1
- 238000010422 painting Methods 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 230000009466 transformation Effects 0.000 description 1
- 238000004804 winding Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/40—Arrangements for mounting power plants in aircraft
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
- H01M50/00—Constructional details or processes of manufacture of the non-active parts of electrochemical cells other than fuel cells, e.g. hybrid cells
- H01M50/20—Mountings; Secondary casings or frames; Racks, modules or packs; Suspension devices; Shock absorbers; Transport or carrying devices; Holders
-
- 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
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E60/00—Enabling technologies; Technologies with a potential or indirect contribution to GHG emissions mitigation
- Y02E60/10—Energy storage using batteries
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- Chemical & Material Sciences (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Electrochemistry (AREA)
- General Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Toys (AREA)
Abstract
The present invention discloses battery box structure and the unmanned plane of a kind of unmanned plane, wherein, the battery box structure of this unmanned plane includes battery compartment and latch components, described battery compartment is installed in the fuselage of described unmanned plane, described latch components is installed on the side of described battery compartment, and described battery compartment is fixed in fuselage by described latch components；Described latch components includes locking part and lock core, described locking part is fixedly installed in described battery compartment, described lock core is partially housed in described locking part, and at least partly expose described locking part, described lock core moves back and forth in described locking part and has locking state and disassembly status, when described lock core is in locking state, one end of this lock core is spacing fixing with the fuselage of described unmanned plane.Technical solution of the present invention can realize fast assembling-disassembling battery compartment.
Description
Technical field
The present invention relates to unmanned vehicle technical field, particularly to battery box structure and the unmanned plane of a kind of unmanned plane.
Background technology
At present, unmanned plane is widely used in civilian, commercial and military field, as taken photo by plane, fire-fighting, police investigation, and territory is surveyed
Painting, to ocean, high-tension line, the condition of a disaster, meteorology etc. monitors.At civil area, increasing extreme sport fan makes
Shoot with video-corder with unmanned plane.In commercial kitchen area, in addition to carrying picture pick-up device and being tracked taking photo by plane to every competitive sports, nobody
Machine also has been enter into logistic industry, and goods can be sent to the remote districts that manpower dispensing is more difficult, slower.Therefore, unmanned plane has
It is widely applied scope and wide market prospect.
For unmanned plane, the power supply of unmanned plane be have impact on the flying power of unmanned plane.Existing battery box structure
General all passing through is fixed in the fuselage being bolted to unmanned plane, it is impossible to accomplishing quick-replaceable, service efficiency is relatively low.
Summary of the invention
The main object of the present invention is to provide the battery box structure of a kind of unmanned plane, it is intended to quick-replaceable battery compartment.
For achieving the above object, the battery box structure of the unmanned plane that the present invention proposes, the battery box structure bag of this unmanned plane
Including battery compartment and latch components, described battery compartment is installed in the fuselage of described unmanned plane, and described latch components is installed on described
The side of battery compartment, described battery compartment is fixed in fuselage by described latch components；
Described latch components includes that locking part and lock core, described locking part are fixedly installed in described battery compartment, described lock core
Being partially housed in described locking part, and at least partly expose described locking part, described lock core moves back and forth in described locking part
And there is locking state and disassembly status, and when described lock core is in locking state, when described lock core is in locking state, this lock core
The fuselage of one end and described unmanned plane spacing fixing.
Alternatively, described latch components also includes that spring, described spring are contained in described locking part, and two ends are supported respectively
Connect described locking part and described lock core；
Described lock core includes main part and is convexly equipped in the handle portion of described main part side, and this locking part is provided with for main part
First stepping down mouth and for reciprocating first elongated hole of described handle portion of passing of one end, this main part is through described
The first formation Plug Division, one end stepping down mouth；
When described lock core is in locking state, step down mouth through described first in this Plug Division, with the fuselage of described unmanned plane
Spacing fixing.
Alternatively, described locking part is locking cylinder, and described spring is contained in described locking cylinder, and described lock core is in locking
During state, at least partly expose described locking cylinder.
Alternatively, described lock core includes the first end and the second end being relatively located at described main part two ends, this first end and
Second end is cylindrical, and described first end diameter is less than or equal to the internal diameter of described locking cylinder, described first end and the second end
Intersection forms flanged structure, and described both ends of the spring abuts and described flanged structure and the bottom of described locking cylinder respectively.
Alternatively, the lower end wall of described locking cylinder is provided with lower outlet, and the second end of described lock core is stretched in described lower outlet
Contracting motion.
Alternatively, this latch components is arranged in battery compartment, described battery compartment to be provided with mouth of stepping down with described first corresponding
Second step down mouth second elongated hole corresponding with described first elongated hole.
Alternatively, described locking part is provided with locking board, described battery compartment to be provided with described second the step down sidewall of mouth recessed
Having mounting groove, described locking board to be fixedly installed in described mounting groove, the described second mouth of stepping down is positioned at the diapire of described mounting groove.
The present invention also provides for a kind of unmanned plane, including the battery box structure of unmanned plane, the battery box structure bag of this unmanned plane
Including battery compartment and latch components, described battery compartment is installed in the fuselage of described unmanned plane, and described latch components is installed on described
The side of battery compartment, described battery compartment is fixed in fuselage by described latch components；
Described latch components includes that locking part and lock core, described locking part are fixedly installed in described battery compartment, described lock core
Being partially housed in described locking part, and at least partly expose described locking part, described lock core moves back and forth in described locking part
And there is locking state and disassembly status, and when described lock core is in locking state, when described lock core is in locking state, this lock core
The fuselage of one end and described unmanned plane spacing fixing.
Alternatively, this unmanned plane includes fuselage, is provided with median septum in described fuselage, and septum plate is by described fuselage point
Being divided into the first containing cavity and the second containing cavity, the master control borad of described unmanned plane, power panel are arranged in the first containing cavity, described nothing
Man-machine battery compartment is arranged in the second containing cavity, and septum plate is provided with fixing hole, when described lock core is in locking state, and should
One end of lock core and wherein lightening hole grafting described in, with spacing fixing with the fuselage of described unmanned plane.
Alternatively, it is provided with between described master control borad with described power panel and is connected socket.
Technical solution of the present invention, by using the battery box structure of unmanned plane, when unmanned plane uses, makes one end of lock core
Motion manifests locking part, and makes this lock core be in locking state, one end of this lock core and the abutting of fuselage, and by this snap close group
Part is spacing fixing with the fuselage of unmanned plane so that this battery compartment is fixed in the fuselage of unmanned plane.When needs dismounting battery compartment,
Only need to will be at disassembly status in this lock core retraction to locking part, and depart from the fuselage of unmanned plane, then battery compartment is taken out
Go out.So, the installation and removal of battery compartment are the most more convenient.
Accompanying drawing explanation
In order to be illustrated more clearly that the embodiment of the present invention or technical scheme of the prior art, below will be to embodiment or existing
In having technology to describe, the required accompanying drawing used is briefly described, it should be apparent that, the accompanying drawing in describing below is only this
Some embodiments of invention, for those of ordinary skill in the art, on the premise of not paying creative work, it is also possible to
Other accompanying drawing is obtained according to the structure shown in these accompanying drawings.
Fig. 1 is the structural representation of unmanned plane one embodiment of the present invention；
Fig. 2 is the structural representation at another visual angle of unmanned plane in Fig. 1；
Fig. 3 is the part-structure schematic diagram of unmanned plane in Fig. 1；
Fig. 4 is the sectional view in Fig. 3 along line A-A；
Fig. 5 is the enlarged drawing in Fig. 4 at A；
Fig. 6 is the structural representation of battery box structure one embodiment of unmanned plane of the present invention；
Fig. 7 is the structural representation of battery compartment in Fig. 6；
Fig. 8 is the structural representation of latch components in Fig. 6；
Fig. 9 is the sectional view at another visual angle of latch components in Fig. 8；
Figure 10 is the part-structure schematic diagram of paddle arm structure one embodiment of unmanned plane of the present invention；
Figure 11 is the structural representation of paddle arm linkage section in Figure 10；
Figure 12 is the top view of paddle arm linkage section in Figure 10；
Figure 13 is the part-structure schematic diagram of hanger one embodiment of unmanned plane of the present invention；
Figure 14 is the cross-sectional schematic at a visual angle of the hanger of unmanned plane in Figure 13；
Figure 15 is the middle hanger of the hanger of unmanned plane in Figure 13 and position limiting structure structural representation；
Figure 16 is the cross-sectional schematic at the visual angle with position limiting structure of the middle hanger in Figure 15；
Figure 17 is the structural representation of the lower hanger of the hanger of unmanned plane in Figure 13；
Figure 18 is the structural representation of the position limiting structure of the hanger of unmanned plane in Figure 13.
Drawing reference numeral illustrates:
The realization of the object of the invention, functional characteristics and advantage will in conjunction with the embodiments, are described further referring to the drawings.
Detailed description of the invention
Below in conjunction with the accompanying drawing in the embodiment of the present invention, the technical scheme in the embodiment of the present invention is carried out clear, complete
Describe, it is clear that described embodiment is only a part of embodiment of the present invention rather than whole embodiments wholely.Base
Embodiment in the present invention, those of ordinary skill in the art obtained under not making creative work premise all its
His embodiment, broadly falls into the scope of protection of the invention.
It is to be appreciated that directional instruction in the embodiment of the present invention (such as up, down, left, right, before and after ...) is only used
In explaining relative position relation between each parts, motion conditions etc. under a certain particular pose (as shown in drawings), if should
When particular pose changes, then directionality instruction changes the most therewith.
It addition, the description relating to " first ", " second " etc. in the present invention is only used for describing purpose, and it is not intended that refer to
Show or imply its relative importance or the implicit quantity indicating indicated technical characteristic.Thus, define " first ", "
Two " feature can express or implicitly include at least one this feature.It addition, the technical scheme between each embodiment can
To be combined with each other, but must be based on those of ordinary skill in the art are capable of, when the combination of technical scheme occurs
Conflicting will be understood that the combination of this technical scheme does not exists, the most not at the protection model of application claims when maybe cannot realize
Within enclosing.
The present invention proposes a kind of unmanned plane 100.
Referring to figs. 1 through Fig. 3, this unmanned plane 100 includes fuselage 10, at least one horn of being arranged on fuselage 10 and setting
Being placed in dynamical system and the propeller of horn one end, described dynamical system is generally motor, and propeller is connected to the rotating shaft of motor,
Motor drives propeller rotational, thus provides the lift taken off for unmanned plane.Described horn is the structure of hollow, sets inside horn
There is wire, power for dynamical system.In order to prevent being interfered of dynamical system, it is further provided with paddle arm structure 20, this oar
Arm configuration 20 includes the first paragraph paddle arm 21 that is connected with the fuselage 10 of described unmanned plane 100 and the machine away from described unmanned plane 100
The second segment paddle arm 22 of body 10.This first paragraph paddle arm 21 is general and fuselage 10 integrated molding is arranged, by fuselage 10 main part
Extend and formed.Second segment paddle arm 22 and first paragraph paddle arm 21 removably connect facilitate installation and carry unmanned plane 100.Transport and
When depositing, take apart to save space by first paragraph paddle arm 21 and second segment paddle arm 22.During use, by first paragraph paddle arm 21 and second
Section paddle arm 22 is fixing to be connected.It is provided with the master control borad 11 with described unmanned plane 100 in described first paragraph paddle arm 21 to be electrically connected with
The first wire (not shown), be provided with the second wire being connected with described first wire in described second segment paddle arm 22 and (do not scheme
Show), realize the power supply to dynamical system by the first wire and the second wire.
The junction of described first wire and described second wire is provided with electromagnetic shield 27.
So, by electromagnetic shield 27, the junction of the first wire and the second wire can be formed electromagnetic shielding, prevent
Electromagnetic interference and affect dynamical system.
Concrete, this paddle arm structure 20 also includes paddle arm linkage section 26, described first wire and the junction of the second wire
Being positioned at this paddle arm linkage section 26, described paddle arm linkage section 26 has the first end 261 and the second end 262 being oppositely arranged, and this is years old
One end 261 is connected to first paragraph paddle arm 21, and this second end 262 is connected to second segment paddle arm 22.Described first end paddle arm 21 cross section
Generally triangle, described second end 262 be close to horn inwall arrange, therefore, described second end 262 is the most also triangle
Structure.Certainly, this paddle arm linkage section 26 can be one-body molded with the first end paddle arm 21.
With reference to Figure 11, the second end 262 of paddle arm linkage section 26 is provided with receiving chamber 211, the described fixing peace of electromagnetic shield 27
It is loaded in described receiving chamber 211.
Concrete, the second end 262 of paddle arm linkage section 26 generally " ten " word structure, it is provided with in described receiving chamber 211
Junction block 23, described junction block 23 is for connecting the first wire and the second wire, and described junction block 23 stretches near the first end 261
Side be additionally provided with described electromagnetic shield 27.The wire being somebody's turn to do i.e. fuselage interior is connected to junction block 23, then by junction block 23
It is connected to the wire of dynamical system.
General, it is provided with dividing plate 211a between described first end 261 and the second end 262, described receiving chamber 211 is separated
Form two parts, in the middle of described dividing plate 211a, be provided with square perforation (sign), for installing described junction block 23.For this
Junction block 23, in the present embodiment, shape and the set-up mode of employing are: with reference to Figure 11, described junction block 23 includes main board 231
With the connecting cylinder 232 being located on main board 231, main board 231 is fixedly installed in described receiving chamber 211, described first wire and
The junction of the second wire is placed in this connecting cylinder 232.
General, electromagnetic shield 27 is shielding button, and this shielding button 27 is the most square, and the square of described dividing plate leads to
Hole interference fit.
The quantity of this connecting cylinder 232 is typically based on the quantity set connecting plug, as used 4 connecting cylinders in the present embodiment
232.The shape of this main board 231 is general with the shape adaptation of containing cavity 411, the most also setting in cross.
This junction block 23, can be with bolts, as described main board 231 is secured by bolts in dividing plate 211a.Also may be used
Employing snaps connection, the most within the scope of the present invention.
Mount and dismount described first paragraph paddle arm 21 and described second segment paddle arm 22 for convenience, with reference to Figure 10, described the
The junction of one section of paddle arm 21 and described second segment paddle arm 22 is provided with one of them of buckle 24 or button bit 25, described second segment oar
The junction of arm 22 and described first paragraph paddle arm 21 be provided with buckle 24 or button bit 25 wherein another, described buckle 24 and described button
Position 25 fastens, and is connected described first paragraph paddle arm 21 to be detachably fixed with described second segment paddle arm 22.
Concretely, described buckle 24 one end is hinged with first paragraph paddle arm 21, and the other end is provided with the first grab 241, institute
State the first grab 241 to extend from buckle 24 and to the second end paddle arm 22 direction bending extension so that the first grab 241 is in circular arc
Shape, described first grab 241 stretches in button bit 25, and the connection completing first paragraph paddle arm 21 and second segment paddle arm 22 is fixed.So,
The installation and removal being made first paragraph paddle arm 21 and second segment paddle arm 22 by the cooperation of buckle 24 and button bit 25 are more convenient.
It is understood that the setting of buckle 24 and button bit 25 is one to one, its quantity arranged is also dependent on reality
Depending on the situation of border, along as described in first paragraph paddle arm 21 or as described in second segment paddle arm 22 be provided at circumferentially spaced 3 buckles 24 or button
Position 25.
In order to prevent first paragraph paddle arm 21 and second segment paddle arm 22 from rotating against, the cross section of first paragraph paddle arm 21 generally three
Dihedral, the cross section of second segment paddle arm 22 is the most also triangular structure.
Further, with reference to Figure 10 and Figure 11, what the sidewall in described receiving chamber 211 surrounded be shaped as cross, described the
Construction section in two-stage nitration paddle arm 22 is also arranged in cross, and the sidewall of described mounting groove 411 is inserted into described construction section (does not schemes
Show) in.
That is, described second end 262 is substantially in cross, including the first cross end, the second cross end, the 3rd cross end and
4th cross end, described first cross end and described 3rd cross end be oppositely arranged, described second cross end and the described 40th
Word end is oppositely arranged, and in order to coordinate the structure of described horn, the cross section of described second cross end and the 4th cross end is substantially in ladder
Shape structure.
Further, the outside wall surface of the cavity wall in described receiving chamber 211 is provided with locating slot 212, and described locating slot 212 is from described
Second end 262 of paddle arm linkage section 26 extends to the first end 261, and described second segment paddle arm 22 is to being provided with calmly by locating slot 212
Position block (not shown), described locating piece grafting is placed in this locating slot 212.So, location and installation first paragraph paddle arm 21 He
During second segment paddle arm 22, described locating slot 212 can play initial alignment effect, can play guiding the most when mounted and make
With.
The present invention arranges paddle arm structure 20, connects first paragraph paddle arm 21 and second segment paddle arm 22 by paddle arm linkage section 26,
Make unmanned plane 100 easy dissembling and-assembling.Meanwhile, this paddle arm linkage section 26 arranges junction block 23 and electromagnetic shield 27
(shielding button), reduces the interference to dynamical system power line, decreases flight safety hidden danger, is the most also beneficial to shielding button 27
Amendment and adjustment, additionally, fixing by buckle the 24, first grab 241 and button bit 25, the cross structure of the second end 262 is solid
Fixed, and triple fixing between locating slot 212 and locating piece so that first paragraph paddle arm 21 and the second end paddle arm 22 firmly connect
Connect.
With reference to Fig. 1, Figure 13 and Figure 14, the lower end of this fuselage 10 is provided with hanger 30, and this hanger 30, for suspended item, makes
Unmanned plane 100 can suspended item.
The hanger 30 of this unmanned plane 100 includes that the fuselage 10 with unmanned plane 100 fixes upper hanger 31, the mounting article being connected
Lower hanger 35, and connect described upper hanger 31 and the middle hanger 33 of described lower hanger 35；
Upper hanger 31 is typically provided with stud, is fixed by the fuselage of bolt with unmanned plane, certainly can also pass through buckle
Or other connected modes are attached.
Described lower hanger 35 is provided with spacing hole 351, and in this, hanger 33 is provided with in this spacing hole 351 up and down motion
Position limiting structure 37, when this position limiting structure 37 part is placed in this spacing hole 351, in this, hanger 33 and lower hanger 35 are in horizontal direction
The most spacing；
Described middle hanger 33 downwardly extends and is provided with shackle member 331, and described lower hanger 35 is provided with slip draw-in groove 353, and this is sliding
Being provided with mounting position 353c in dynamic draw-in groove 353, this shackle member 331 is slided to depart from described slip draw-in groove 353 or is mounted on
Mounting position 353c.
When preparing to use unmanned plane 100 to transport article, first article to be transported are connected (this thing to be transported with lower hanger 35
Product can be some devices that unmanned plane 100 has itself, such as delivery device, or other airborne device, naturally it is also possible to it is to treat
Parcel of transport etc.), then play the mounting position 353c that the shackle member 331 of hanger 35 is mounted in slip draw-in groove 353, so that in
Hanger 33 and lower hanger 35 are spacing fixing at above-below direction.Meanwhile, position limiting structure 37 part is contained in spacing hole 351, with this
The hole wall of spacing hole 351 abuts spacing so that in this, hanger 33 and lower hanger 35 are fixed in horizontal direction upper limit.So, make
Obtain article to be transported and be fixed on unmanned plane 100.When unmanned plane 100 transports article to destination, first position limiting structure 37 is departed from
Go out spacing hole 351, then promote lower hanger 35, make shackle member 331 slide in slip draw-in groove 353, thus depart from mounting position
353c, hanger 33 during lower hanger 35 is departed from, and then article are taken off.The hanger 30 being arranged such, facilitates unmanned plane 100 quick
Mounting and dismounting article, Lifting Convey efficiency, Lifting Convey efficiency.
General, incorporated by reference to Figure 15, in order to alleviate the weight of hanger 30, upper hanger 31, middle hanger 33 and lower hanger 35 are equal
It is provided with lightening hole (sign) so that upper hanger 31, middle hanger 33 and lower hanger 35 are in grid-like setting.Middle hanger 33 is downward
Projection the second grab 331 is to form shackle member 331.This second grab 331 is positioned at the downside of the grille strip of middle hanger 33, typically sets
Being equipped with four the second grabs 331, hanger is substantially square setting.Four the second grabs 331 are positioned at four of middle hanger 33
End angle.The second general L-shaped setting of grab 331.
Incorporated by reference to Figure 17, the slip draw-in groove 353 that lower hanger 35 is arranged includes lead segment 353a and connects with this lead segment 353a
Clamping section 353b connect, described mounting position 353c is positioned at described clamping section 353b.Shackle member 331 slides in lead segment 353a
Clamping section 353b clamping.Being provided with card adapter plate 353c in this slip draw-in groove 353, this card adapter plate 353c is positioned at clamping section 353b and shape
Becoming mounting position 353c, the second grab 331 is connected in this card adapter plate 353c.This slip draw-in groove 353 generally bottle shape, its large aperture
Section forms lead segment 353a, and small-bore section forms clamping section 353b, and card adapter plate 353c is located at this small-bore section, is generally located on cunning
The cell wall upper end of dynamic draw-in groove 353.
In the present embodiment, in conjunction with Figure 15 to Figure 18, this position limiting structure 37 includes mounting box 371, typically this mounting box 371
Fastened by upper cover plate and lower cover and form.
This mounting box 371 is provided with impeller 373 and ejection piece 375, and impeller 373 is partially housed in this mounting box 371
In, and move back and forth in this mounting box 371, described ejection piece 375 is installed in described mounting box 371, this mounting box 371
Base plate is provided with the resigning hole 371a, this resigning hole 371a passed for described ejection piece 375 and just arranges spacing hole 351；Promote
Part 373 abuts with ejection piece 375, with promote described ejection piece 375 through resigning hole 371a in described spacing hole 351 up and down
Motion.
When ejection piece 375 is positioned in spacing hole 351, ejection piece 375 engages with the hole wall of spacing hole 351 so that lower extension
Frame 35 and middle hanger 33 are the most spacing in horizontal direction.When impeller 373 promotes ejection piece 375, ejection piece 375 is retracted into
In mounting box 371, the most spacing in horizontal direction between lower hanger 35 and middle hanger 33, now, only need in the horizontal direction
Hanger 35 under upper promotion, makes the second grab 331 of lower hanger 35 depart from card adapter plate 353c in slip draw-in groove 353, i.e. can be taken off
Lower hanger 35 so that the dismounting of lower hanger 35 is more convenient.
With reference to Figure 18, this impeller 373 includes catch bar 3731 and is located at the pushing block of described catch bar 3731 one end
3732, this wedge shaped setting of pushing block 3732, described ejection piece 375 has the mating holes 3751 coordinated in this pushing block 3732,
The lozenges of pushing block 3732 supports the hole wall of mating holes 3751, and this pushing block 3732, in horizontal motion, ejects to promote
Part 375 moves up and down.The height of pushing block 3732 near catch bar 3731 one end to away from catch bar 3731 one end by
Gradually reducing, ejection piece 375 is positioned at one end away from catch bar 3731 of pushing block 3732, and the lower end of ejection piece 375 stretches to limit
In hole 351, position.Therefore, when catch bar 3731 is towards promotion in mounting box 371, the height of wedge 3732 gradually rises, wedge
The upper hole wall of mating holes 3751 is supported in shape face so that ejection piece 375 moves upward and makes its lower end depart from spacing hole 351, thus
Make position limiting structure 37 the most spacing middle hanger 33 and lower hanger 35 in horizontal direction.By the setting of wedge 3732, make
Obtain catch bar 3731 and the relatively simple convenience of cooperation of ejection piece 375.This ejection piece 375 be typically square tabular arrange, eject
Mating holes 3751 in part 375 is also square setting.
This catch bar 3731 is additionally provided with the first clamp 3733, and the height that this first clamp 3733 is positioned at pushing block 3732 is higher
One end, and ejection piece 375 clamping, in case the higher one end of thrust motion block 3732 is slipped in mating holes 3751.
General, the medial recess of this pushing block 3732 forms chute 3732a, and the hole wall of this mating holes 3751 upper end is downward
Extending and be provided with the second clamp 3752, this second clamp 3752 slides in this chute 3732a, and with the end wall of this chute 3732a
Abut spacing.It is arranged such, is slipped in mating holes 3751 also for preventing the one end that pushing block 3732 is higher.
One end being provided with pushing block 3732 of this catch bar 3731 is additionally provided with the first elastic component 376, this first elastic component 376
Two ends abut with the sidewall of mounting box 371 and the end elasticity of pushing block 3732, with promote catch bar 3731 complete in hang
After frame 33 and lower hanger 35 separate, it is achieved the elastic reset of catch bar 3731.The upper end of this ejection piece 375 is provided with the second elastic component
377, the two ends of this second elastic component 377 abut with the roof of mounting box 371 and the upper end elasticity of ejection piece 375, to promote
After catch bar 3731 completes middle hanger 33 and the separation of lower hanger 35, it is achieved the elastic reset of ejection piece 375.This first elastic component
376 and second elastic component 377 all can use spring, it is, of course, also possible to use other elastic constructions such as jump ring etc..
With reference to Figure 18, in order to make the elastic compression of the first elastic component 376 and the second elastic component 377 and reply the most firm,
The end of this catch bar 3731 is additionally provided with the first locating dowel 376a, and this first elastic component 376 is sheathed on this first locating dowel 376a.
Accordingly, the upper end of this ejection piece 375 is additionally provided with the second locating dowel (sign), this second elastic component 377 be sheathed on this second
Locating dowel.
The upper end of ejection piece 375 is arranged with slot to make way, and this second locating dowel is installed in this slot to make way, so that this top
Go out the simple in construction of part 375, and installation and operation is the most firm.
The base plate of this mounting box 371 is also convexly equipped with two slide units 378, and described in two, slide unit 378 is positioned at the both sides of resigning hole 371a,
Wherein the both sides of slide unit 378 described in are convexly equipped with baffle plate 378a, form slideway between two baffle plate 378a, and impeller 373 is sliding in this
Slide in road.Make it slide more steady, coordinate the most firm.
Master control borad 11, power panel 12 and battery box structure 40 and various function element it is provided with in this fuselage 10.Described machine
Being provided with median septum 13 in body 10, septum plate 13 is divided into the first containing cavity and the second containing cavity, institute by described fuselage 10
State the master control borad 11 of unmanned plane 100, power panel 12 is arranged in the first containing cavity, certainly, is additionally provided with other in the first containing cavity
Components and parts.The battery box structure 40 of described unmanned plane 100 is arranged in the second containing cavity.First containing cavity is normally at fuselage 10
Top, the second containing cavity is positioned at the bottom of fuselage 10.Setting by median septum 13 so that the installation of fuselage 10 inner part is relatively
For orderly and convenient.
Further, with reference to Fig. 4, it is provided with between described master control borad 11 with described power panel 12 and is connected socket 14.So, logical
Cross this connection socket 14, the inside winding displacement of unmanned plane 100 can be reduced, facilitate the cabling layout in fuselage 10.
With reference to Fig. 2, unmanned plane 100 is generally provided with radio antenna 50 and high definition antenna 60, radio antenna 50 and high definition
Antenna 60 is typically located at the lower end of the fuselage 10 of unmanned plane 100 to facilitate reception and transmission signal and data.
The mounting means of this radio antenna 50 is: with reference to Fig. 2, and described unmanned plane 100 includes radio antenna 50, described unmanned
The fuselage 10 of machine 100 is provided with antenna mounting post 51, and one end deviating from described fuselage 10 of described antenna mounting post 51 is provided with installation
Hole (does not indicates), is provided with rubber stop collar 52 in this installing hole, and the grafting of described radio antenna 50 is limited in described rubber stop collar
In 52.So, radio antenna 50 can be prevented to be retracted into the fuselage of unmanned plane 100 during installing by rubber stop collar 52
In 10 so that the signal reception of radio antenna 50 is unaffected.
The mounting means of this high definition antenna 60 is: with reference to Fig. 2, and described unmanned plane 100 includes high definition antenna 60, described unmanned
The fuselage 10 of machine 100 is provided with the installing port 61 that the cable for this high definition antenna 60 passes, the cable of described high definition antenna 60
Through this installing port 61, described high definition antenna 60 is provided with installing plate 62, and this installing plate 62 is fixedly installed in described unmanned plane 100
Fuselage 10.General, use screw to be fixedly connected this installing plate 62.By arranging installing plate 62 so that this high definition electric wire
Fix with the fuselage 10 of unmanned plane 100 and be connected.The installing port 61 preventing repeatedly dismantling high definition antenna 60 and cause becomes big problem.
For unmanned plane 100, the power supply of unmanned plane 100 be have impact on the flying power of unmanned plane 100, nothing is being set
During the man-machine battery box structure 40 of 100, the fast assembling-disassembling of battery compartment 41 to be considered, do not have with the battery at unmanned plane 100
Service efficiency can be improved with quick-replaceable during electricity.Therefore, the present invention provides the battery box structure of a kind of novel unmanned plane 100
40, with reference to Fig. 4 to Fig. 9, including battery compartment 41 and latch components 42, described battery compartment 41 is installed on the machine of described unmanned plane 100
In body 10, described latch components 42 is installed on the side of described battery compartment 41, and described battery compartment is fixed by described latch components 42
In fuselage；
Described latch components 42 includes that locking part 421 and lock core 422, described locking part 421 are fixedly installed in described battery
Storehouse 41, described lock core 422 is partially housed in described locking part 421, and at least partly exposes described locking part 421, described lock core
422 move back and forth in described locking part 421 and make described lock core 422 have locking state and disassembly status, described lock core 422
When being in locking state, one end of this lock core 422 is spacing fixing with the fuselage 10 of described unmanned plane 100.
Technical solution of the present invention, by using the battery box structure 40 of unmanned plane 100, when unmanned plane 100 uses, makes lock
One end motion of core 422 manifests locking part 421, and makes this lock core 422 be in locking state, one end of this lock core 422 and machine
The abutting of body 10, and by spacing fixing with the fuselage 10 of unmanned plane 100 for this latch components 42 so that this battery compartment 40 is fixed on nothing
In the fuselage 10 of man-machine 100.When needs dismounting battery compartment 41, only this lock core 422 retraction need to be made at it to locking part 421
In disassembly status, and depart from the fuselage 10 of unmanned plane 100, then battery compartment 42 is extracted out.So, the installation of battery compartment 42
The most more convenient with dismounting.
When may be appreciated, this lock core 422 moves back and forth in locking part 421, can use various ways, e.g., locking
Part 421 is internal arranges slide rail, and this slide rail has tooth bar, and the side of lock core 422 also has the tooth bar engaged in this tooth bar, passes through
The mode of rack gear makes lock core 422 move back and forth in locking part 421.It is, of course, also possible to use the mode of spring 423,
Concrete:
Described latch components 42 also includes that spring 423, described spring 423 are contained in described locking part 421, and two ends are divided
Do not abut described locking part 421 and described lock core 422.
Described lock core 422 includes main part 4221 and is convexly equipped in the handle portion 4222 of described main part 4221 side, this lock
What firmware 421 was provided with that the one end for main part 4221 passes first steps down mouthful 4211a and back and forth transporting for described handle portion 4222
The first dynamic elongated hole 4212a.This main part 4221 is stepped down through described first formation Plug Division, one end 4221a of mouthful 4211a.
Described main part 4221 moves back and forth in described locking part 421 and makes described lock core 422 have locking state and disassembly status,
When described lock core 422 is in locking state, this Plug Division 4221a steps down a mouthful 4211a through described first, with described unmanned plane
The fuselage 10 of 100 is spacing fixing.
Specifically, described locking part 421 is locking cylinder, described spring is contained in described locking cylinder 421, described lock core
422 are partially housed in described locking cylinder 421, and at least partly expose described locking cylinder 421.General, described locking cylinder 421 is
The hollow cylindrical of one end open.
Specifically, described lock core 422 includes the first end 422a and the second end being relatively located at described main part 4221 two ends
422b, is substantially cylindric, described first end 422a diameter equal to or slightly less than the internal diameter of described locking cylinder 421, described the
The intersection of one end 422a and the second end 422b forms flanged structure 422c, and described spring 423 two ends abut convex with described respectively
Edge structure and the bottom of described locking cylinder 421.
The length of the second end 422b of this lock core 422 can be arranged according to practical situation, as in the present embodiment, and described locking
The lower end wall of cylinder 421 is provided with lower outlet (sign), and the second end 422b of described lock core 422 is flexible fortune in described lower outlet
Dynamic.
General, this second end 422b diameter, equal to or slightly less than the diameter of described lower outlet, can be applied at lock core 422
External force used under in described lower outlet stretching motion.
Certainly, in another embodiment, it is not provided with lower outlet, and the height of the second end 422b is shortened, it is also possible to complete
The locking state of lock core 422 and the conversion of disassembly status.
General, the Plug Division 4221a that this first end 422a is formed is plugged in the median septum 13 of fuselage 10.This battery compartment 41
For rectangle box body, the second containing cavity is to the shape of battery compartment 41 should making adaptive adjustment and arrange.This second containing cavity
The most typically arranging slide rail (sign), battery compartment 41 coordinates the motion of plug type in this second containing cavity with this slide rail.?
When unmanned plane 100 uses, this lock core 422 is in locking state, is fixed with the spacing of fuselage 10 by Plug Division 4221a so that
This battery compartment 41 is fixed in this second containing cavity.It is appreciated that the corresponding described Plug Division 4221a of septum plate 13 is provided with solid
Determining hole, concrete it may be that septum plate 13 is provided with some lightening holes, described Plug Division 4221a passes through one of loss of weight
Hole, when described Plug Division 4221a is plugged in one of them lightening hole, described latch components 42 is in locking state, when needing
Dismantle, only need to press handle portion 4222, when described handle portion 4222 is applied the power along locking cylinder 421 axis direction, described
Lock core 422 moves under the drive of described handle portion 4222, so that the second end 422b of lock core 422 skids off lower outlet.Make
This handle portion 4222 moves downward in the first elongated hole 4212a, drives the second end 422a compression spring of main part 4221
423 so that Plug Division 4221a departs from fuselage 10, then battery compartment 41 is extracted out.
For the installation settings of latch components 42, this latch components 42 can be provided separately within the side of this battery compartment 41
Wall, as being arranged on the lateral wall of one end of its length direction, in the present invention, for easy for installation and saving installing space, should
Latch components 42 is integrally disposed in battery compartment 41.
Concrete, with reference to Fig. 6 to Fig. 9, described battery compartment 41 be provided with corresponding for mouthful 4211a second of stepping down with described first
Step down mouthful 41a and described first the second corresponding for elongated hole 4212a elongated hole 41b.So, latch components 42 is arranged on electricity
In storehouse, pond 41, handle portion 4222 sequentially passes through the first elongated hole 4212a and the second elongated hole 41b and manages for user.Grafting
Portion 4221a sequentially passes through the first mouthful 4211a and second that steps down and steps down a mouthful 41a, and spacing fixing with the fuselage 10 of unmanned plane 100.
Further, in order to make being more firmly mounted and stable of latch components 42, reference Fig. 7 to 9, described locking part
421 are provided with locking board 424, and described second sidewall stepping down mouthful 41a that is provided with of described battery compartment 41 is arranged with mounting groove 411, institute
Stating locking board 424 to be fixedly installed in described mounting groove 411, the described second mouthful 41a that steps down is positioned at the end of described mounting groove 411
Wall.
General, described locking board 424 is located at above described battery compartment 41, for example, it may be, described battery compartment 41 top
Concave downward is formed with the mounting groove 411 accommodating described locking board 424, the shape of described mounting groove 411 and described locking board 424
Shape adapt.Optionally, described locking board 424 is fixed on described battery compartment 41 top, now, described locking by screw
Being provided with some through holes on plate 424, described battery compartment 41 is provided with screwed hole, and some screws are fixed on screwed hole through some through holes
In, to be fixed by described locking board 424, after locking board 424 is fixing, described locking cylinder 421 i.e. extend in battery compartment 41, optional
, described locking board 424 can also be fixed on battery compartment 41 top, such as buckle, bonding etc. by other means.Such as, institute
The surface stating locking board 424 is provided with buckle (not shown), and the diapire of described mounting groove 411 is provided with button bit (not shown), described
Buckle is fastened on described button bit.
Described locking board 424 is provided with one and crosses mouth, and described locking cylinder 421 can be to downwardly extend shape along the described hoop crossing mouth
The hollow columnar structures of the one end open become.
With reference to Fig. 8 and Fig. 9, in order to preferably manipulate latch components 42, further:
The side of described main part 4221 is arranged with screw (sign), and one end of described handle portion 4222 is provided with thread segment
4222a, described thread segment 4222a are spirally connected with described screw, so that described handle portion 4222 is fixed on described main part 4221.
That is, when installing lock core 422, first main part 4221 is arranged in locking part 421, by handle portion 4222 after allowing
It is spirally connected and screw.The main part 4221 arranged by split and the lock core 422 of handle portion 4222 composition, when installation and removal relatively
For convenience.
Certainly, in another embodiment of the invention, it is also possible to by described main part 4221 and described handle portion 4,222 1
Body chemical conversion type.So, the processing of lock core 422 is facilitated.
With reference to Fig. 8, the outer surface of described handle portion 4222 is provided with friction protrusion 4222b.Setting by friction protrusion 4222b
Put, the coefficient of friction of handle portion 4222 can be increased.Operator is made can preferably to manage handle portion 4222, it is to avoid to occur beating
Sliding situation.
Further, with reference to Fig. 8, in order to make latch components 42 with spacing fixing the most firm, described Plug Division
The wedge shaped setting of 4221a.
The foregoing is only the preferred embodiments of the present invention, not thereby limit the scope of the claims of the present invention, every at this
Under the inventive concept of invention, utilize the equivalent structure transformation that description of the invention and accompanying drawing content are made, or directly/indirectly use
The technical field relevant at other is included in the scope of patent protection of the present invention.
Claims (10)
1. the battery box structure of a unmanned plane, it is characterised in that include that battery compartment and latch components, described battery compartment are installed on
In the fuselage of described unmanned plane, described latch components is installed on the side of described battery compartment, and described latch components is by described battery
Storehouse is fixed in fuselage；
Described latch components includes that locking part and lock core, described locking part are fixedly installed in described battery compartment, described lock core part
Being contained in described locking part, and at least partly expose described locking part, described lock core moves back and forth in described locking part and has
Having locking state and disassembly status, when described lock core is in locking state, one end of this lock core limits with the fuselage of described unmanned plane
Position is fixing.
2. the battery box structure of unmanned plane as claimed in claim 1, it is characterised in that described latch components also includes spring,
Described spring is contained in described locking part, and two ends abut described locking part and described lock core respectively；
Described lock core includes main part and is convexly equipped in the handle portion of described main part side, and this locking part is provided with for main part
Hold through first step down mouth and for reciprocating first elongated hole of described handle portion, this main part passes described first
Step down the formation Plug Division, one end of mouth；
When described lock core is in locking state, step down mouth through described first in this Plug Division, spacing with the fuselage of described unmanned plane
Fixing.
3. the battery box structure of unmanned plane as claimed in claim 2, it is characterised in that
Described locking part is locking cylinder, and described spring is contained in described locking cylinder, when described lock core is in locking state, at least
Part exposes described locking cylinder.
4. the battery box structure of unmanned plane as claimed in claim 2, it is characterised in that described lock core includes relatively being located at described
First end at main part two ends and the second end, this first end and the second end are cylindrical, and described first end diameter is less than or equal to
The internal diameter of described locking cylinder, the intersection of described first end and the second end forms flanged structure, and described both ends of the spring abuts respectively
With described flanged structure and the bottom of described locking cylinder.
5. the battery box structure of unmanned plane as claimed in claim 4, it is characterised in that the lower end wall of described locking cylinder is provided with down
Outlet, the second end of described lock core is stretching motion in described lower outlet.
6. the battery box structure of unmanned plane as claimed in claim 2, it is characterised in that this latch components is arranged on battery compartment
In, described battery compartment be provided with mouth of stepping down with described first corresponding second step down mouth corresponding with described first elongated hole the
Two elongated holes.
7. the battery box structure of unmanned plane as claimed in claim 6, it is characterised in that described locking part is provided with locking board, institute
Described second sidewall stepping down mouth that is provided with stating battery compartment is arranged with mounting groove, and described locking board is fixedly installed in described mounting groove
In, the described second mouth of stepping down is positioned at the diapire of described mounting groove.
8. a unmanned plane, it is characterised in that include the battery box structure of unmanned plane as described in arbitrary in claim 1 to 7.
9. unmanned plane as claimed in claim 8, it is characterised in that include fuselage, is provided with median septum in described fuselage, described in
Dividing plate will be divided into the first containing cavity and the second containing cavity in described fuselage, the master control borad of described unmanned plane, power panel are arranged on
In described first containing cavity, the battery compartment of described unmanned plane is arranged in described second containing cavity, and septum plate is provided with fixing
Hole, when described lock core is in locking state, one end of this lock core and described fixing hole grafting, limit with the fuselage with described unmanned plane
Position is fixing.
10. unmanned plane as claimed in claim 9, it is characterised in that be provided with between described master control borad with described power panel and be connected
Socket.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610741737.8A CN106275461A (en) | 2016-08-26 | 2016-08-26 | The battery box structure of unmanned plane and unmanned plane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610741737.8A CN106275461A (en) | 2016-08-26 | 2016-08-26 | The battery box structure of unmanned plane and unmanned plane |
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| Publication Number | Publication Date |
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| CN106275461A true CN106275461A (en) | 2017-01-04 |
Family
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610741737.8A Pending CN106275461A (en) | 2016-08-26 | 2016-08-26 | The battery box structure of unmanned plane and unmanned plane |
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| CN107380446A (en) * | 2017-09-20 | 2017-11-24 | 杭州迅蚁网络科技有限公司 | A kind of multifunctional logistics unmanned plane |
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| CN109606662A (en) * | 2018-12-11 | 2019-04-12 | 泉州齐美电子科技有限公司 | A kind of quadrotor drone rolled over |
| CN110217399A (en) * | 2019-05-31 | 2019-09-10 | 沈阳无距科技有限公司 | Unmanned plane |
| WO2021217545A1 (en) * | 2020-04-30 | 2021-11-04 | 深圳市大疆创新科技有限公司 | Unmanned aerial vehicle |
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