CN205801517U - A kind of unmanned plane battery lock structure - Google Patents
A kind of unmanned plane battery lock structure Download PDFInfo
- Publication number
- CN205801517U CN205801517U CN201620633319.2U CN201620633319U CN205801517U CN 205801517 U CN205801517 U CN 205801517U CN 201620633319 U CN201620633319 U CN 201620633319U CN 205801517 U CN205801517 U CN 205801517U
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- unmanned plane
- main body
- connection member
- drive division
- dead bolt
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Abstract
The utility model discloses a kind of unmanned plane battery lock structure, including battery main body with for carrying the unmanned plane main body of this battery main body, battery main body is extended with latch hook, unmanned plane main body has the fore shaft for receiving latch hook, the dead bolt for locking latch hook it is provided with in fore shaft, dead bolt is separated with unmanned plane main body, is connected by the dismantled and assembled elasticity of elastic connecting element between dead bolt with unmanned plane main body.The unmanned plane main body that this utility model need not more renew after dead bolt damages, the dead bolt that only need to more renew just can complete the repair to dead bolt, be continuing with unmanned plane, it is possible to decrease the expense of unmanned plane maintenance, the beneficially popularization and application of unmanned plane.
Description
Technical field
This utility model relates to a kind of unmanned plane latch-up structure, particularly relates to a kind of unmanned plane battery lock structure.
Background technology
As depicted in figs. 1 and 2, unmanned plane battery lock structure of the prior art, including battery main body 1 ' be used for holding
Carrying the unmanned plane main body 2 ' of this battery main body 1 ', described battery main body 1 ' is extended with latch hook 1 '-1 ', described unmanned plane main body 2 ' has
For receiving described latch hook 1 '-1 ' fore shaft 2 '-1 ', described fore shaft 2 '-1 ' in be provided with for locking described latch hook 1 '-1 '
Dead bolt 2 '-2 ', described dead bolt 2 '-2 ' synthesize integral piece, described latch hook 1 '-1 with the injection of described unmanned plane main body 2 ' ' with described
Battery main body 1 ' injection synthesizes integral piece.Such unmanned plane battery lock structure, in the process relatively frequently changing battery
In, dead bolt 2 '-2 ' be easy to rupture and split away off from unmanned plane main body 2 ', the dead bolt 2 '-2 after coming off because intensity is relatively low '
Cannot be fixed on again in unmanned plane main body 2 ', it is impossible to realizing stably locking battery main body 1 ', unmanned plane is in the state of scrapping.
In order to be continuing with unmanned plane, only way is exactly to change a new unmanned plane main body 2 '.Even, latch hook sometimes
1 '-1 ' also can rupture and split away off from battery main body 1 ', the most also the battery main body that more renews.So, greatly increase
Add the expense of unmanned plane maintenance, be unfavorable for the popularization and application of unmanned plane.Meanwhile, be by battery main body 1 ' from unmanned owner
Disassemble harder on body 2 '.
Utility model content
The technical problems to be solved in the utility model is to provide a kind of unmanned plane battery lock structure, this unmanned plane battery lock
The unmanned plane main body that fixed structure need not more renew after dead bolt damages just can complete the repair to dead bolt, is continuing with unmanned
Machine, it is possible to decrease the expense of unmanned plane maintenance, the beneficially popularization and application of unmanned plane.
In order to solve above-mentioned technical problem, this utility model provides a kind of unmanned plane battery lock structure, including battery
Main body and for carrying the unmanned plane main body of this battery main body, described battery main body is extended with latch hook, and described unmanned plane main body has
For receiving the fore shaft of described latch hook, being provided with the dead bolt for locking described latch hook in described fore shaft, described dead bolt is with described
Unmanned plane main body is separated, and is connected by the dismantled and assembled elasticity of elastic connecting element between described dead bolt with described unmanned plane main body.
Described elastic connecting element includes that lever connection member and elastomeric element, the middle part of described lever connection member are hinges
Meeting portion, described lever connection member is hinged with described unmanned plane main body by articulated section and hinge, after described lever connection member
The top in portion have the space for accommodating described latch hook, the rear end of described lever connection member be upturned formation described dead bolt,
The front portion of described lever connection member is elastomeric element seat, and described elastomeric element seat is by described elastomeric element and described unmanned plane
Body elastic connects.
The articulated section of described lever connection member has fraising, described lever connection member to be overlapped rotationally by described fraising
On described hinge.
The perimembranous of described elastomeric element seat upwardly extends formation annular anti-delinking part, and/or, the central authorities of described elastomeric element seat
Upwardly extend formation cylindricality anti-delinking part.
Described elastomeric element is spring.
Described elastic connecting element also includes rotating toggle, and described rotation toggle passes through to be sequentially distributed and pulls
, axle root, pin-and-hole, at least one press drive division, described unmanned plane main body wall is provided with big axis hole, described pressing drive division
Inserting in described big axis hole, described pressing drive division presses with the end sides of described dead bolt and coordinates, described axle root with described greatly
Axis hole is rotatably assorted, and is inserted with alignment pin in described pin-and-hole.
Described pressing drive division has two, and the first pressing drive division and the second pressing drive division are connected as a single entity by connecting rod
Part, described connecting rod is positioned at the space of described lever connection member, described first pressing drive division and the second pressing drive division
Between formed for accommodating the space of described latch hook with the top of described connecting rod, the outer end of described second pressing drive division is arranged
There are spindle nose, the axis of described spindle nose to coincide with the axis of described axle root, are positioned at described big axis hole in described unmanned plane main body
Being provided with toggle support, described toggle support is provided with little axis hole, the axis phase of the axis of described little axis hole and described big axis hole
Overlapping, described spindle nose is rotatably assorted with described little axis hole, and the rear portion of described lever connection member is positioned at described toggle support.
Two end sides of described dead bolt are respectively provided with jagged or recess and form driven holding section, the first driven engaging
Press between portion with described first pressing drive division and coordinate, press between the second driven holding section and described second pressing drive division
Coordinate.
The limit notch in described unmanned plane main body it is positioned at inside the handle of described rotation toggle, described rotation toggle
It is positioned at outside handle outside the limit notch in described unmanned plane main body.
Described latch hook is separated with described battery main body, can by connection member between described latch hook and described battery main body
Dismounting connects.
Unmanned plane battery lock structure of the present utility model compared with prior art has the advantages that.
1, the technical program is separated with described unmanned plane main body owing to have employed described dead bolt, described dead bolt and described nothing
By the dismantled and assembled elastic technological means connected of elastic connecting element between man-machine main body, so, need not be more after dead bolt damages
The unmanned plane main body renewed, the dead bolt that only need to more renew just can complete the repair to dead bolt, be continuing with unmanned plane, can drop
The expense of low unmanned plane maintenance, the beneficially popularization and application of unmanned plane.
2, the technical program includes lever connection member and elastomeric element owing to have employed described elastic connecting element, described
The middle part of lever connection member is articulated section, and described lever connection member is cut with scissors with described unmanned plane main body by articulated section and hinge
Connecing, there are the space for accommodating described latch hook, the rear end of described lever connection member in the top at described lever connection member rear portion
Be upturned the described dead bolt of formation, and the front portion of described lever connection member is elastomeric element seat, and described elastomeric element seat passes through institute
State the technological means that elastomeric element is connected with described unmanned plane body elastic, so, be conducive to increasing intensity and the elasticity of dead bolt.
3, the technical program has fraising, described lever connection member due to the articulated section that have employed described lever connection member
The technological means on described hinge it is enclosed within rotationally by described fraising, so, the steady of lever connection member swing can be improved
Qualitative.
4, the technical program due to the perimembranous that have employed described elastomeric element seat upwardly extend formation annular anti-delinking part, and/
Or, the central authorities of described elastomeric element seat upwardly extend the technological means forming cylindricality anti-delinking part, so, elasticity can be effectively prevented
Parts come off in the horizontal direction.
5, the technical program is owing to have employed the technological means that described elastomeric element is spring, so, it can be ensured that dead bolt has
There is enough elasticity.
6, the technical program also includes rotating toggle owing to have employed described elastic connecting element, and described rotation toggle is from one
End to the other end be sequentially distributed handle, axle root, pin-and-hole, at least one press drive division, the setting of described unmanned plane main body wall
Having big axis hole, described pressing drive division inserts in described big axis hole, described pressing drive division and the end sides pressure of described dead bolt
Dynamic cooperation, described axle root is rotatably assorted with described big axis hole, is inserted with the technological means of alignment pin in described pin-and-hole, so, can
Latching operation is conciliate in the convenient locking to battery main body.
7, the technical program has two owing to have employed described pressing drive division, and the first pressing drive division and the second pressing are driven
Dynamic portion is connected as a single entity part by connecting rod, and described connecting rod is positioned at the space of described lever connection member, and described first presses
Formed for accommodating the space of described latch hook with the top of described connecting rod between drive division and the second pressing drive division, described the
The outer end of two pressing drive divisions is provided with spindle nose, and the axis of described spindle nose coincides with the axis of described axle root, described unmanned plane
Being positioned in main body at described big axis hole and be provided with toggle support, described toggle support is provided with little axis hole, the axle of described little axis hole
Line coincides with the axis of described big axis hole, and described spindle nose is rotatably assorted with described little axis hole, after described lever connection member
Portion is positioned at the technological means of described toggle support, so, it is not only advantageous to increase the strength and stiffness rotating toggle, and,
It may also be ensured that rotate the axiality that toggle rotates, meanwhile, pressing drive division is more uniform to the active force of dead bolt.
8, the technical program is jagged owing to two end sides that have employed described dead bolt are respectively provided with or recess is formed
Driven holding section, presses between the first driven holding section with described first pressing drive division and coordinates, the second driven holding section and institute
State the technological means pressing cooperation between the second pressing drive division, so, steady to the effect of dead bolt of pressing drive division can be improved
Qualitative and reliability.
9, the technical program is positioned at the limit in described unmanned plane main body owing to have employed inside the handle of described rotation toggle
In the recess of position, outside the handle of described rotation toggle, it is positioned at the technological means outside the limit notch in described unmanned plane main body, institute
With, not only can prevent rotating toggle and rotate excessive, and, be conducive to rotating rotation toggle.
10, the technical program is separated with described battery main body owing to have employed described latch hook, described latch hook and described electricity
By the technological means of the dismantled and assembled connection of connection member between tank main body, so, the battery that need not more renew after latch hook damages
Main body, the latch hook that only need to more renew just can complete the repair to latch hook, be continuing with unmanned plane, can reduce nothing further
The further popularization and application of the expense of man-machine maintenance, beneficially unmanned plane.
Accompanying drawing explanation
With detailed description of the invention, unmanned plane battery lock structure of the present utility model is made further below in conjunction with the accompanying drawings
Describe in detail.
Fig. 1 is the battery main body of unmanned plane left front lower perspective structural representation in prior art.
Fig. 2 is the unmanned plane left back upper perspective structural representation (after battery main body unlocks) of prior art.
Fig. 3 is this utility model unmanned plane left front lower perspective structural representation (after battery main body unlocks).
Fig. 4 is this utility model unmanned plane left back upper perspective structural representation (after battery main body unlocks).
Fig. 5 is this utility model unmanned plane left back upper perspective structural representation (after battery main body locking).
Fig. 6 is this utility model unmanned plane battery lock structure right back upper place perspective structure schematic diagram (after decomposition).
Fig. 7 is this utility model unmanned plane battery lock structure right back upper place perspective structure schematic diagram (after combination).
Fig. 8 is this utility model unmanned plane main body left part right back lower place perspective structure schematic diagram (not installing dead bolt).
Fig. 9 is this utility model unmanned plane main body left part right back upper place perspective structure schematic diagram (having installed dead bolt).
Figure 10 is this utility model unmanned plane main body left part right front lower place perspective structure schematic diagram (having installed dead bolt).
Description of symbols in accompanying drawing is as follows.
1'～battery main body
1'-1'～latch hook
2'～unmanned plane main body
2'-1'～fore shaft
2'-2'～dead bolt
1～battery main body
1-1～latch hook
2～unmanned plane main body
2-1～fore shaft
2-3～big axis hole
2-4～toggle support
2-5～little axis hole
2-6～hinge
2-7～limit notch
3～elastic connecting element
3-1～lever connection member
3-1-1～dead bolt
3-1-2～the first driven holding section
3-1-3～the second driven holding section
3-1-4～space
3-1-5～articulated section
3-1-6～reinforcement
3-1-7～elastomeric element seat
3-1-8～anti-delinking part
3-1-9～injection hole
3-2～elastomeric element
3-3～rotation toggle
3-3-1～handle
3-3-2～axle root
3-3-3～pin-and-hole
3-3-4～first pressing drive division
3-3-5～connecting rod
3-3-6～space
3-3-7～second pressing drive division
3-3-8～spindle nose
3-4～alignment pin
3-4-1～shoulder
3-4-2～projection
3-4-3～profile groove
3-4-4～handling hole
Detailed description of the invention
As shown in figs. 3 and 10, present embodiments provide for a kind of unmanned plane battery lock structure, including battery main body 1
With the unmanned plane main body 2 for carrying this battery main body 1, described battery main body 1 is extended with latch hook 1-1, described unmanned plane main body 2
There is the fore shaft 2-1 for receiving described latch hook 1-1, in described fore shaft 2-1, be provided with the dead bolt 3-for locking described latch hook 1-1
1-1, described dead bolt 3-1-1 are separated with described unmanned plane main body 2, logical between described dead bolt 3-1-1 and described unmanned plane main body 2
Cross the dismantled and assembled elastic connection of elastic connecting element 3.It can be seen that latch hook 1-1 is positioned at the front lower of battery main body 1 from Fig. 3 to Fig. 5
Side to the left, portion also downwardly extends, and the upper back of unmanned plane main body 2 forms right-angle notch, and battery main body 1 is positioned at this right-angle notch.
Fore shaft 2-1 is arranged on the right angle side to the left of unmanned plane main body 2.
Present embodiment is separated with described unmanned plane main body owing to have employed described dead bolt, and described dead bolt is unmanned with described
By the dismantled and assembled elastic technological means connected of elastic connecting element between owner's body, so, need not change after dead bolt damages
New unmanned plane main body, the dead bolt that only need to more renew just can complete the repair to dead bolt, be continuing with unmanned plane, it is possible to decrease
The expense of unmanned plane maintenance, the beneficially popularization and application of unmanned plane.
The first step as present embodiment is improved, and as shown in Fig. 6 to Figure 10, described elastic connecting element 3 includes lever
Connection member 3-1 and elastomeric element 3-2, the middle part of described lever connection member 3-1 is articulated section 3-1-5, and described lever connects
Parts 3-1 is hinged with described unmanned plane main body 2 by articulated section 3-1-5 and hinge 2-6, described lever connection member 3-1 rear portion
Top have the space 3-1-4 for accommodating described latch hook 1-1, the rear end of described lever connection member 3-1 is upturned formation
Described dead bolt 3-1-1, the front portion of described lever connection member 3-1 is elastomeric element seat 3-1-7, described elastomeric element seat 3-1-7
It is connected with described unmanned plane main body 2 elasticity by described elastomeric element 3-2.It is of course also possible to be, dead bolt passes through spring leaf and spiral shell
Nail or nut elasticity dismantled and assembled with unmanned plane main body 2 are connected.
Present embodiment includes lever connection member and elastomeric element, described thick stick owing to have employed described elastic connecting element
The middle part of bar connection member is articulated section, and described lever connection member is cut with scissors with described unmanned plane main body by articulated section and hinge
Connecing, there are the space for accommodating described latch hook, the rear end of described lever connection member in the top at described lever connection member rear portion
Be upturned the described dead bolt of formation, and the front portion of described lever connection member is elastomeric element seat, and described elastomeric element seat passes through institute
State the technological means that elastomeric element is connected with described unmanned plane body elastic, so, be conducive to increasing intensity and the elasticity of dead bolt.
Second step as present embodiment improves, and as shown in Figure 6, the shape of described lever connection member 3-1 is in by long
The bending shape that stripe board is alongst formed after bending repeatedly, the articulated section 3-of described lever connection member 3-1
1-5 has concave groove, described lever connection member 3-1 to ride on described hinge 2-6, the front portion of described lever connection member 3-1
Fovea superior equal with rear portion.
Present embodiment is owing to have employed the shape of described lever connection member in by elongated plates alongst warp
The bending shape formed after crossing bending repeatedly, there are concave groove, described lever connecting portion in the articulated section of described lever connection member
Part rides on described hinge, the technological means of the equal fovea superior of front and rear of described lever connection member, so, beneficially lever
The installation and removal of connection member.
The 3rd step as present embodiment is improved, and as shown in Fig. 6 to Figure 10, is provided with two and adds in described concave groove
Fraising, described lever connection member 3-1 is formed between top and the articulated section 3-1-5 of strong muscle 3-1-6, described reinforcement 3-1-6
It is enclosed within described hinge 2-6.It is of course also possible to be, in described concave groove, it is provided with one or more reinforcement 3-1-6.
Present embodiment owing to have employed in described concave groove at least provided with a reinforcement, described reinforcement upper
Forming fraising between side and articulated section, described lever connection member is enclosed within the technological means on described hinge, so, not only can increase
The strength and stiffness of big lever connection member, and, the stability that lever connection member swings can be improved.
The 4th step as present embodiment is improved, as shown in Fig. 6 to Figure 10, and the perimembranous of described elastomeric element seat 3-1-7
Upwardly extend formation annular anti-delinking part 3-1-8.It is of course also possible to be, the central authorities of described elastomeric element seat 3-1-7 upwardly extend shape
Become cylindricality anti-delinking part.
Present embodiment upwardly extends formation annular anti-delinking part due to the perimembranous that have employed described elastomeric element seat, and/or,
The central authorities of described elastomeric element seat upwardly extend the technological means forming cylindricality anti-delinking part, so, elastic can be effectively prevented
Part comes off in the horizontal direction.
The 5th step as present embodiment is improved, and as shown in Fig. 6 to Figure 10, described annular anti-delinking part 3-1-8 is by multiple
The arc convex surrounding annular spaced apart is constituted.It is of course also possible to be, the shape of described annular anti-delinking part 3-1-8 is in continuously
Annular.
Present embodiment is owing to have employed described annular anti-delinking part by multiple arc convex structures surrounding annular spaced apart
Become, or, the shape of described annular anti-delinking part is the technological means of continuous print annular, so, can produce according to practical situation
Multiple unmanned plane battery lock structure.
The 6th step as present embodiment is improved, as shown in Fig. 6 to Figure 10, and the top of described annular anti-delinking part 3-1-8
Having a radially inwardly extending formation mousing-hook at two, in like manner, the top of described cylindricality anti-delinking part has at two and extends radially outward
Form mousing-hook.It is of course also possible to be, the top of described annular anti-delinking part 3-1-8 has at one or many places are radially inwardly extending
Forming mousing-hook, the top of described cylindricality anti-delinking part has at one or many places extend radially outward formation mousing-hook.
Present embodiment is owing to have employed the top at least radially inwardly extending formation at one of described annular anti-delinking part
Mousing-hook, the top of described cylindricality anti-delinking part at least extends radially outward the technological means forming mousing-hook at one, so,
Elastomeric element can be effectively prevented vertically come off.
The 7th step as present embodiment is improved, and as shown in Fig. 6 to Figure 10, the top of described articulated section 3-1-5 has
Injection hole 3-1-9.
Present embodiment has the technological means of injection hole due to the top that have employed described articulated section, so, not only have
It is beneficial to injection molded, moreover, it is also possible to save the raw material of lever connection member.
The 8th step as present embodiment is improved, and as shown in Fig. 6 to Figure 10, described elastomeric element 3-2 is spring.When
So, it is also possible to be, described elastomeric element 3-2 is rubber column.
Present embodiment owing to have employed the technological means that described elastomeric element is rubber column or spring, so, can basis
The demand of different clients produces multiple unmanned plane battery lock structure.
The 9th step as present embodiment is improved, and as shown in Fig. 6 to Figure 10, described spring is tower spring.
Present embodiment owing to have employed the technological means that described spring is tower spring, so, it is possible to increase lever connection member
Swing traverse, be conducive to the locking of battery main body and unblock.
The tenth step as present embodiment is improved, and as shown in Fig. 6 to Figure 10, described elastic connecting element 3 also includes rotation
The transfer button 3-3, described rotation toggle 3-3 pass through and have been sequentially distributed handle 3-3-1, axle root 3-3-2, pin-and-hole 3-3-
3, pressing drive division, described unmanned plane main body 2 is housing, and described unmanned plane main body 2 sidewall is provided with big axis hole 2-3, described presses
Pressure drive division inserts in described big axis hole 2-3, and described pressing drive division presses with the end sides of described dead bolt 3-1-1 and coordinates,
Described axle root 3-3-2 is rotatably assorted with described big axis hole 2-3, is inserted with alignment pin 3-4 in described pin-and-hole 3-3-3.
Present embodiment also includes rotating toggle owing to have employed described elastic connecting element, and described rotation toggle is from one end
To the other end be sequentially distributed handle, axle root, pin-and-hole, at least one press drive division, described unmanned plane main body is housing, described
Unmanned plane main body wall is provided with big axis hole, and described pressing drive division inserts in described big axis hole, described pressing drive division and institute
The end sides stating dead bolt presses cooperation, and described axle root is rotatably assorted with described big axis hole, is inserted with alignment pin in described pin-and-hole
Technological means, so, latching operation is conciliate in the convenient locking to battery main body.
The 11st step as present embodiment is improved, and as shown in Fig. 6 to Figure 10, described pressing drive division has two, the
One pressing drive division 3-3-4 and the second pressing drive division 3-3-7 is connected as a single entity part by connecting rod 3-3-5, described connecting rod 3-
3-5 is positioned at the space 3-1-4 of described lever connection member 3-1, and described first pressing drive division 3-3-4 and the second pressing drive
Form the space for accommodating described latch hook 1-1, described second pressing with the top of described connecting rod 3-3-5 between portion 3-3-7
The outer end of drive division 3-3-7 is provided with spindle nose 3-3-8, and the axis of described spindle nose 3-3-8 is mutually overlapping with the axis of described axle root 3-3-2
Closing, be positioned at described big axis hole 2-3 and be provided with toggle support 2-4 in described unmanned plane main body 2, described toggle support 2-4 is arranged
Little axis hole 2-5, the axis of described little axis hole 2-5 is had to coincide with the axis of described big axis hole 2-3, described spindle nose 3-3-8 and institute
Stating little axis hole 2-5 to be rotatably assorted, the rear portion of described lever connection member 3-1 is positioned at described toggle support 2-4.
Present embodiment has two owing to have employed described pressing drive division, and the first pressing drive division and the second pressing drive
Portion is connected as a single entity part by connecting rod, and described connecting rod is positioned at the space of described lever connection member, and described first pressing is driven
With the formation of the top of described connecting rod for accommodating the space of described latch hook between dynamic portion and the second pressing drive division, described second
The outer end of pressing drive division is provided with spindle nose, and the axis of described spindle nose coincides with the axis of described axle root, described unmanned owner
Internal being positioned at described big axis hole is provided with toggle support, and described toggle support is provided with little axis hole, the axis of described little axis hole
Coinciding with the axis of described big axis hole, described spindle nose is rotatably assorted with described little axis hole, the rear portion of described lever connection member
It is positioned at the technological means of described toggle support, so, it is not only advantageous to increase the strength and stiffness rotating toggle, and, also
May insure that and rotate the axiality that toggle rotates, meanwhile, pressing drive division is more uniform to the active force of dead bolt.
The 12nd step as present embodiment is improved, as shown in Fig. 6 to Figure 10, and described first pressing drive division 3-3-4
End surface shape and second pressing drive division 3-3-7 end surface shape semicircular in shape.
Present embodiment is owing to have employed end surface shape and the end of the second pressing drive division of described first pressing drive division
The technological means of face shape semicircular in shape, so, can greatly increase the strength and stiffness of pressing drive division.
The 13rd step as present embodiment is improved, as shown in Fig. 6 to Figure 10, and two ends of described dead bolt 3-1-1
Side is respectively provided with jagged or recess and forms driven holding section, and the first driven holding section 3-1-2 drives with described first pressing
Press cooperation between portion 3-3-4, press between the second driven holding section 3-1-3 with described second pressing drive division 3-3-7 and coordinate.
Present embodiment is jagged owing to two end sides that have employed described dead bolt are respectively provided with or recess formed from
Dynamic holding section, presses between the first driven holding section with described first pressing drive division and coordinates, and the second driven holding section is with described
The technological means of cooperation is pressed between second pressing drive division, so, pressing drive division stablizing the effect of dead bolt can be improved
Property and reliability.
The 14th step as present embodiment is improved, and as shown in Fig. 6 to Figure 10, described pin-and-hole 3-3-3 lays respectively at two
In the individual plane being parallel to each other, the axis of described pin-and-hole 3-3-3 is perpendicular to this two planes being parallel to each other.
Present embodiment lays respectively in two planes being parallel to each other owing to have employed described pin-and-hole, the axle of described pin-and-hole
Line is perpendicular to the technological means of these two planes being parallel to each other, so, be conducive to inserting alignment pin.
The 15th step as present embodiment is improved, and as shown in Fig. 6 to Figure 10, described rotation toggle 3-3 is by aluminium alloy
Material is made.
Present embodiment owing to have employed the technological means that described rotation toggle is made by aluminum alloy materials, so,
The strength and stiffness rotating toggle can be substantially increased, be greatly improved the service life rotating toggle.
The 16th step as present embodiment is improved, and as shown in Fig. 6 to Figure 10, described alignment pin 3-4 is near one end
Side is provided with shoulder 3-4-1, and one end of described alignment pin 3-4 is provided with handling hole 3-4-4, described alignment pin 3-4 near another
The side of one end is provided with projection 3-4-2, and the termination of the described alignment pin 3-4 other end is provided with profile groove 3-4-3, described profile groove 3-
The bottom of trench of 4-3 is through the plane at described projection 3-4-2 place.
Present embodiment is elongated due to the shape that have employed described alignment pin, and described alignment pin is near the side of one end
Being provided with shoulder, one end of described alignment pin is provided with handling hole, and described alignment pin is provided with projection near the side of the other end,
The termination of the described alignment pin other end is provided with profile groove, and the bottom of trench of described profile groove is through the technology hands of the plane at described projection place
Section, so, it is not only advantageous to the installation of alignment pin, and, it is also beneficial to the dismounting of alignment pin.
The 17th step as present embodiment is improved, and as shown in Fig. 6 to Figure 10, described alignment pin 3-4 is by plastic production
Form.
Present embodiment owing to have employed described alignment pin by the technological means of plastic production, so, not only manufacture
Easily, furthermore, it is possible to reduce the manufacturing cost of unmanned plane battery lock structure.
The 18th step as present embodiment is improved, as it is shown in figure 5, inside the handle 3-3-1 of described rotation toggle 3-3
It is positioned at limit notch 2-7 in described unmanned plane main body 2, outside the handle 3-3-1 of described rotation toggle 3-3, is positioned at described nothing
Outside limit notch 2-7 in man-machine main body 2.
Present embodiment is owing to have employed be positioned at inside the handle of described rotation toggle in described unmanned plane main body spacing
In recess, outside the handle of described rotation toggle, it is positioned at the technological means outside the limit notch in described unmanned plane main body, so,
Not only can prevent rotating toggle and rotate excessive, and, be conducive to rotating rotation toggle.
The 19th step as present embodiment is improved, as it is shown on figure 3, described latch hook 1-1 divides with described battery main body 1 phase
From, it is connected by connection member (not drawing in figure) is dismantled and assembled between described latch hook 1-1 with described battery main body 1.
Present embodiment is separated with described battery main body owing to have employed described latch hook, described latch hook and described battery master
By the technological means of the dismantled and assembled connection of connection member between body, so, the battery main body that need not more renew after latch hook damages,
The latch hook that only need to more renew just can complete the repair to latch hook, is continuing with unmanned plane, can reduce unmanned plane further
The expense of maintenance, the beneficially further popularization and application of unmanned plane.
Claims (10)
1. a unmanned plane battery lock structure, including battery main body (1) be used for carrying the unmanned owner of this battery main body (1)
Body (2), it is characterised in that: described battery main body (1) is extended with latch hook (1-1), and described unmanned plane main body (2) has for receiving
State the fore shaft (2-1) of latch hook (1-1), in described fore shaft (2-1), be provided with the dead bolt (3-1-for locking described latch hook (1-1)
1), described dead bolt (3-1-1) is separated with described unmanned plane main body (2), described dead bolt (3-1-1) and described unmanned plane main body
(2) by the dismantled and assembled elastic connection of elastic connecting element (3) between.
Unmanned plane battery lock structure the most according to claim 1, it is characterised in that: described elastic connecting element (3) wraps
Including lever connection member (3-1) and elastomeric element (3-2), the middle part of described lever connection member (3-1) is articulated section (3-1-
5), described lever connection member (3-1) is hinged with described unmanned plane main body (2) by articulated section (3-1-5) and hinge (2-6),
There are the space (3-1-4) for accommodating described latch hook (1-1), described lever in the top at described lever connection member (3-1) rear portion
The rear end of connection member (3-1) is upturned and forms described dead bolt (3-1-1), and the front portion of described lever connection member (3-1) is
Elastomeric element seat (3-1-7), described elastomeric element seat (3-1-7) is by described elastomeric element (3-2) and described unmanned plane main body
(2) elastic connection.
Unmanned plane battery lock structure the most according to claim 2, it is characterised in that: described lever connection member (3-1)
Articulated section (3-1-5) have fraising, described lever connection member (3-1) to be enclosed within described hinge rotationally by described fraising
(2-6) on.
Unmanned plane battery lock structure the most according to claim 2, it is characterised in that: described elastomeric element seat (3-1-7)
Perimembranous upwardly extend formation annular anti-delinking part (3-1-8), and/or, the central authorities of described elastomeric element seat (3-1-7) upwardly extend
Form cylindricality anti-delinking part.
Unmanned plane battery lock structure the most according to claim 2, it is characterised in that: described elastomeric element (3-2) is bullet
Spring.
Unmanned plane battery lock structure the most according to claim 2, it is characterised in that: described elastic connecting element (3) is also
Including rotating toggle (3-3), described rotation toggle (3-3) passes through and has been sequentially distributed handle (3-3-1), axle root
(3-3-2), pin-and-hole (3-3-3), at least one press drive division, described unmanned plane main body (2) sidewall is provided with big axis hole (2-
3), described pressing drive division inserts in described big axis hole (2-3), described pressing drive division and the end of described dead bolt (3-1-1)
Side presses cooperation, and described axle root (3-3-2) is rotatably assorted with described big axis hole (2-3), is inserted with in described pin-and-hole (3-3-3)
Alignment pin (3-4).
Unmanned plane battery lock structure the most according to claim 6, it is characterised in that: described pressing drive division has two,
First pressing drive division (3-3-4) and the second pressing drive division (3-3-7) are passed through connecting rod (3-3-5) and are connected as a single entity part, described
Connecting rod (3-3-5) is positioned at the space (3-1-4) of described lever connection member (3-1), described first pressing drive division (3-3-
4) formed with the top of described connecting rod (3-3-5) between and the second pressing drive division (3-3-7) and be used for accommodating described latch hook (1-
1) space, the outer end of described second pressing drive division (3-3-7) is provided with spindle nose (3-3-8), the axle of described spindle nose (3-3-8)
Line coincides with the axis of described axle root (3-3-2), is positioned at described big axis hole (2-3) place and arranges in described unmanned plane main body (2)
Toggle support (2-4), described toggle support (2-4) is had to be provided with little axis hole (2-5), the axis of described little axis hole (2-5) and institute
The axis stating big axis hole (2-3) coincides, and described spindle nose (3-3-8) is rotatably assorted with described little axis hole (2-5), and described lever is even
The rear portion of relay part (3-1) is positioned at described toggle support (2-4).
Unmanned plane battery lock structure the most according to claim 7, it is characterised in that: two of described dead bolt (3-1-1)
End sides is respectively provided with jagged or recess and forms driven holding section, and the first driven holding section (3-1-2) is pressed with described first
Cooperation is pressed, the second driven holding section (3-1-3) and described second pressing drive division (3-3-7) between pressure drive division (3-3-4)
Between press cooperation.
Unmanned plane battery lock structure the most according to claim 6, it is characterised in that: described rotation toggle (3-3) pulls
(3-3-1) inner side is positioned at the limit notch (2-7) on described unmanned plane main body (2), the handle of described rotation toggle (3-3)
(3-3-1) outside is positioned at the limit notch (2-7) on described unmanned plane main body (2) outward.
Unmanned plane battery lock structure the most according to claim 1, it is characterised in that: described latch hook (1-1) and described electricity
Tank main body (1) is separated, and is connected by connection member is dismantled and assembled between described latch hook (1-1) with described battery main body (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620633319.2U CN205801517U (en) | 2016-06-24 | 2016-06-24 | A kind of unmanned plane battery lock structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620633319.2U CN205801517U (en) | 2016-06-24 | 2016-06-24 | A kind of unmanned plane battery lock structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205801517U true CN205801517U (en) | 2016-12-14 |
Family
ID=57505473
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620633319.2U Expired - Fee Related CN205801517U (en) | 2016-06-24 | 2016-06-24 | A kind of unmanned plane battery lock structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205801517U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107684412A (en) * | 2017-09-30 | 2018-02-13 | 常州凯南迪克医疗科技有限公司 | One kind miniaturization upper digestive tract dynamic ph Impedance monitoring device |
| CN110444707A (en) * | 2018-11-08 | 2019-11-12 | 苏州乐轩科技有限公司 | Battery assembly, battery assembly and disassembly system and method |
-
2016
- 2016-06-24 CN CN201620633319.2U patent/CN205801517U/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107684412A (en) * | 2017-09-30 | 2018-02-13 | 常州凯南迪克医疗科技有限公司 | One kind miniaturization upper digestive tract dynamic ph Impedance monitoring device |
| CN107684412B (en) * | 2017-09-30 | 2023-10-31 | 常州凯南迪克医疗科技有限公司 | Miniaturized upper gastrointestinal dynamic pH impedance monitoring device |
| CN110444707A (en) * | 2018-11-08 | 2019-11-12 | 苏州乐轩科技有限公司 | Battery assembly, battery assembly and disassembly system and method |
| CN110444707B (en) * | 2018-11-08 | 2022-01-21 | 苏州乐轩科技有限公司 | Battery assembly, battery assembly and disassembly system and method |
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|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20161214 Termination date: 20200624 |